Пространственная имитационная модель системы управления автоматическим маневренным летательным аппаратом

FIELD: armament; rocket equipment. SUBSTANCE: invention can be used in development of short-range complexes and systems with aircraft maneuvering on target. Invention is intended for analysis of aircraft guidance on different types of targets, including intensive maneuvering, with the possibility of correction of parameters of elements of aircraft control system for determination of technical capabilities of increase of control accuracy in specific tactical situations without carrying out natural experiments. Model is based on use of transfer functions of short-range aircraft control loop. Essence of the model consists in the fact that AC control commands are generated in two mutually independent channels (azimuth and elevation angle), and as initial information on input of model is supplied mixture of angular coordinates of target and angular noise generated by separate radar model of target. EFFECT: thus obtained homing path parameters enable to analyze homing characteristics of various types of aerial targets in various tactical situations with sufficient accuracy and reliability. 1 cl, 16 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 735 418 C2 (51) МПК F41G 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F41G 9/00 (2020.08) (21)(22) Заявка: 2019105223, 25.02.2019 (24) Дата начала отсчета срока действия патента: Дата регистрации: 02.11.2020 (43) Дата публикации заявки: 25.08.2020 Бюл. № 24 (45) Опубликовано: 02.11.2020 Бюл. № 31 2 7 3 5 4 1 8 R U (56) Список документов, цитированных в отчете о поиске: RU 2570115 C2, 10.12.2015. RU 144759 U1, 27.08.2014. RU 2632546 C1, 05.10.2017. RU 2310909 C1, 20.11.2007. US 8563908 B1, 22.10.2013. (54) Пространственная имитационная модель системы управления автоматическим маневренным летательным аппаратом (57) Реферат: Изобретение относится к области вооружения, функций контура управления ЛА малой а именно к ракетной технике, и может быть дальности. Сущность ...

Способ наведения инерционного летательного аппарата с учетом несоответствия динамических свойств цели и перехватчика

FIELD: control systems. SUBSTANCE: invention relates to control systems, in particular, to complex systems including jointly operating subsystems with different dynamic properties. Proposed guidance method allows compensating mismatch between the dynamic properties of the interceptor and the target in the guidance process without solving the complex two-point boundary problem. Control signal is generated according to law: where j i is required transverse acceleration of interceptor; – optimum estimates of courses and angular velocities of interceptor and target; and are estimates of range to target and its first derivative; T – time constant of the interceptor, which characterizes its inertia; b is control signal amplification factor; q 21 is the penalty rate for accuracy of guidance of the system by angle; q 22 is the penalty rate for accuracy of guidance of the system from angular velocity; g 22 is the interaction factor of the guidance and target maneuver error interaction; k is coefficient of penalties per value of control signal. In contrast to the prototype, the proposed method has a third nonstationary term which takes into account discrepancy between dynamic properties of the target and the interceptor. EFFECT: use of the invention will make it possible to provide interception of fast-moving targets in a wide range of their speeds and courses; saving energy consumption for control at initial guidance areas and improving its accuracy at the final section. 1 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 727 777 C1 (51) МПК F41G 9/00 (2006.01) F41G 7/22 (2006.01) G05D 1/00 (2006.01) B64C 13/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F41G 9/00 (2020.02); F41G 7/00 (2020.02); B64C 13/00 (2020.02); G05D 1/00 (2020.02) (21)(22) Заявка: 2019124761, 05.08.2019 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): Акционерное общество "Концерн радиостроения ...

Пространственная имитационная модель системы управления автоматическим маневренным летательным аппаратом

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2019 105 223 A (51) МПК F41G 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2019105223, 25.02.2019 Приоритет(ы): (22) Дата подачи заявки: 25.02.2019 (43) Дата публикации заявки: 25.08.2020 Бюл. № 24 R U (57) Формула изобретения Пространственная имитационная модель системы управления автоматическим маневренным летательным аппаратом, включающая в себя канал выработки команд управления в вертикальной плоскости наведения, на вход которого поступает координата угла места цели, которая проходя через сумматор преобразуется в угловое отклонение траектории полета ЛА от кинематической, преобразуемое путем умножения на программную функцию дальности до ЛА в линейное отклонение ЛА, далее поступает на вход устройств, предназначенных для вывода ЛА на кинематическую траекторию, откуда после срабатывания схемы переключения режимов «вывод - наведение» на вход устройств режима «наведения» и далее после сложения с командой компенсации динамической ошибки наведения через устройство ограничения максимальных команд управления на вход системы «автопилот - ЛА» и через кинематическое звено на сумматор, замыкая обратную связь, отличающаяся от известной тем, что выработка команд управления ЛА происходит также и в горизонтальной плоскости наведения, а на вход каналов управления поступает аддитивная смесь текущих угловых координат цели и углового шума, вырабатываемого моделью углового шума цели раздельно для плоскостей наведения, команды компенсации динамических ошибок наведения вырабатываются в двух каналах управления, а совместный пересчет команд управления с учетом скручивания производится в преобразователе исполнительной системы координат. Стр.: 1 A 2 0 1 9 1 0 5 2 2 3 A (54) Пространственная имитационная модель системы управления автоматическим маневренным летательным аппаратом 2 0 1 9 1 0 5 2 2 3 (72) Автор(ы): Жарков Сергей Валентинович (RU), Болычевский Сергей Константинович (RU), ...

WEAPON CONTROL SYSTEMS

... 1409701 Weapon control system WILLIAM WAHL CORP 25 Jan 1974 03500/74 Heading F3C A weapon control system for changing the state of one or more of a group of multistate weapon actuating devices comprises at least one remote station, the or each station including actuator means 12 for effecting a change of state of one of the devices, state sensor means 14 for sensing the states of the devices and transmitting status words each including a representation of the sensed state of the corresponding device. A command station including sensor command means 16 is provided for generating test words for transmission to the state sensor means 14 and means to actuate the sensor means 14 and cause transmission of the status words. A command status memory 18 receives and stores the status words transmitted from the state sensor means 14. Means 20 for selecting a word having a predetermined state from the command status memory is provided and reads out the selected word as an actuator word. The actuator ...

Target tracking missile guidance method

A network of intercommunicating battlefield devices

A plurality of battlefield devices that communicate with a battle management system using a communications network to form a network of intercommunicating battlefield devices that may be deployed in a battlefield environment. Each battlefield device comprising one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the battlefield device. The processor configured to cause the data to be sent to another location and to process other data received from other locations over said communications network.

Guided munition systems for detecting off-axis targets

Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.

RATE INTEGRATING GYROSCOPIC AIMING METHOD AND DEVICE THEREFOR

A NETWORK OF INTERCOMMUNICATING BATTLEFIELD DEVICES

A plurality of battlefield devices that communicate with a battle management system using a communications network to form a network of intercommunicating battlefield devices that may be deployed in a battlefield environment. Each battlefield device comprising one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the battlefield device. The processor configured to cause the data to be sent to another location and to process other data received from other locations over said communications network.

SUBMUNITION-MINE.

Target tracking system - firing or triggering signal is function of parameters of moving object

APPARATUS FOR PROVIDING ULTRAHIGH FREQUENCY-BASED SEEKING FUNCTION OF GUIDED WEAPON AND METHOD THEREOF

본 발명에 의한 유도 무기의 초고주파 기반 탐색 기능을 제공하기 위한 장치 및 그 방법이 개시된다. 본 발명의 일 실시예에 따른 유도 무기의 초고주파 기반 탐색 기능을 제공하기 위한 장치는 미리 설정된 탐색 영역 내 표적으로부터 반사된 적외선 신호를 수신하는 안테나; 상기 안테나를 지지하고, 조종사의 조작에 따라 선택된 탐색 모드에 따라 미리 설정된 탐색 패턴에 따라 구동되어 상기 안테나의 지향 방향을 조절하는 김발 조립체; 상기 안테나를 초고주파 신호를 송신하는 송신기나 상기 초고주파 신호를 수신하는 수신기로 전환시키는 서큘레이터; 상기 수신된 신호를 이용하여 상기 탐색 영역 내에서 상기 표적을 탐지하고, 상기 탐지된 표적을 추적하여 그 추적한 결과로 추적 정보를 생성하는 신호 처리기; 및 상기 생성된 추적 정보를 이용하여 상기 김발 조립체를 구동하는 김발 제어기를 포함한다. An apparatus and method for providing a very high frequency based search function of an induced weapon according to the present invention is disclosed. An apparatus for providing a very high frequency based search function of guided weapon according to an embodiment of the present invention includes an antenna for receiving an infrared signal reflected from a target in a predetermined search area; A gimbal assembly that supports the antenna and is driven according to a search pattern set according to a search mode selected according to a pilot's operation to adjust a direction of the antenna; A circulator for converting the antenna into a transmitter for transmitting a very high frequency signal and a receiver for receiving the very high frequency signal; A signal processor for detecting the target in the search area using the received signal, tracking the detected target and generating tracking information as a result of the tracking; And a gimbal controller for driving the gimbal assembly using the generated tracking information.

APPARATUS TO EMULATE CHARGING INFORMATION DATA IN GUIDED WEAPON SYSTEM AND METHOD THEREOF

The present invention relates to an apparatus to emulate charging information data in a guided weapon system, to generate a plurality pieces of charging information data transmitted to a plurality of guided weapons, and a method thereof. According to the present invention, the apparatus to emulate charging information data in a guided weapon system comprises: a charging information data generation unit embedded in a guided weapon system to generate a plurality pieces of charging information data transmitted to the guided weapons; a transmission beamforming unit to perform transmission beamforming with respect to the guided weapons; a first beam scanning unit to beam-scan a space of the arranged guided weapons after transmission beamforming; a first signal to noise ratio (SNR) measurement unit to measure a maximum SNR from a signal received from the guided weapons during beam scanning; and a charging information data transmission unit using a beam steering angle calculated based on the measured ...

미사일 마스킹 영역 산출방법 및 이를 이용한 공대공 미사일 운용방법

... 본 발명은 전투기의 기체 형상의 모델을 로딩하는 단계, 기체에 적용되는 무장의 추적기(seeker) 위치를 추출하여 기준위치로 설정하는 단계, 기준위치에서 기체에 의한 시야 차단영역인 마스킹(Masking) 영역을 산출하는 단계, 마스킹 영역의 정보를 저장하는 단계를 포함하는 미사일 마스킹 영역 산출방법에 관한 것이다. 본 발명에 따른 미사일 마스킹 영역 산출방법은 실제 무장 운용단계에서 발생할 수 있는 미사일 추적기의 시야 차단에 의한 문제점을 비 실시간 시뮬레이션 모델링을 이용하여 마스킹 영역을 산출함으로써 미리 판단하고 이에 해당하는 경우 다른 미사일을 선택할 수 있는 데이터를 제공할 수 있다. 따라서 촌각을 다투는 공대공 전투시 우위를 점할 수 있는 효과를 발휘할 수 있게 된다.

APPARATUS AND METHOD FOR CONTROLLING PERFORMANCE INSPECTION OF SEARCHER

The present invention relates to an apparatus and a method for controlling performance inspection of a searcher while the searcher is mounted in an aircraft. According to the present invention, the apparatus comprises: a searcher operation determination portion for determining whether or not the searcher mounted on the aircraft normally operates; a scenario selection portion for selecting a scenario related to a current location of the aircraft among scenarios related to performance inspection of the searcher if the searcher is determined to be normally operated; and a searcher performance inspection portion for inspecting performance of the searcher based on the scenario related to the current location of the aircraft. COPYRIGHT KIPO 2017 (111) Pod connector (120) Searching device (130) Data storage device (140) Power supply device (150) Operation control device (151) Inertial navigation system (160) Flight (AA) Location information ...

연속적 시변 편향을 이용한 충돌각 제어 방법

... 본 발명에 따르면, 목표 충돌각 제어부가 상기 유도 발사체 발사 전 상기 표적 요격 시까지의 목표 충돌각을 제어하는 단계, 편향 계산부가 유도 발사체 발사 후 연속적으로 변화하는 편향 순시치를 계산하는 단계 및 가속도 명령 생성부가 상기 편향 계산부로부터 계산된 편향을 고려하여 상기 유도 발사체의 가속도 명령을 생성하는 단계를 포함하여 가속도 제한을 고려하여 충돌각을 제어할 수 있는 연속적 시변 편향을 이용한 충돌각 제어 방법이 개시된다.

Communication delay compensation for local defense

METHOD AND DEVICE FOR PROGRAMMING A PROJECTILE

The invention relates to inductively or capacitively programming a projectile (5). According to the invention, a waveguide (2, 11) is used for the programming, the electromagnetic field being concentrated in the waveguide. The used programming unit (1) consists of at least one waveguide (2, 11) which is preferably located and/or integrated in the region of the muzzle, for example in front of the muzzle brake (6). A transmission coupler (3) for the transmission is fed by a signal generator (4). Said information relating to the projectile (5) is modulated to the carrier frequency (f1) in the modulator (18). A reception coupler (8) integrated on/in the projectile (5),is electrically interconnected to a store or processor (19) in the projectile (5). Said reception coupler receives the modulated signal and transmits it to the processor (19) which is where the eventual programming takes place.

Fused sensor situation display

A method for providing an observer with an intuitive awareness of a tactical environment is disclosed. In an illustrative embodiment, the method displays a 360° panoramic view of the environment surrounding a warship, wherein the view is augmented by radar data, infrared imagery, visible imagery, and tactical information about targets within the field-of-view.

INTERCEPTION MISSLE AND WARHEAD THEREFOR

A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

ИМИТАЦИОННАЯ МОДЕЛЬ СИСТЕМЫ УПРАВЛЕНИЯ ВОЗДУШНОЙ МИШЕНЬЮ НА ОСНОВЕ БЕСПИЛОТНОГО ЛЕТАТЕЛЬНОГО АППАРАТА ИЗ СОСТАВА МИШЕННОГО КОМПЛЕКСА

Имитационная модель системы управления воздушной мишенью на основе беспилотного летательного аппарата из состава мишенного комплекса содержит контуры автопилота для управления боковым и продольным движениями воздушной мишени на основе БПЛА. Контур управления боковым движением автопилота содержит подконтур управления курсовым углом воздушной мишени с последовательным замыканием с подконтуром управления креном воздушной мишени и имеет коэффициент усиления дифференциального регулятора демпфирования скорости крена для внутреннего контура. Контур управления продольным движением содержит подконтуры обратной связи: подконтур выдерживания высоты полета воздушной мишени на основе БПЛА с помощью управляющих сигналов по тангажу с последовательным замыканием с подконтуром автопилота стабилизации по углу тангажа, используемого в качестве внутреннего подконтура, подконтур выдерживания скорости воздушной мишени на основе БПЛА с помощью регулирования тангажа, подконтур стабилизации скорости воздушной мишени ...

СПОСОБ НАВЕДЕНИЯ САМОНАВОДЯЩЕГОСЯ БОЕПРИПАСА В УСЛОВИЯХ ЛАЗЕРНОГО ВОЗДЕЙСТВИЯ

Изобретение относится к системам огневого поражения объектов управляемыми боеприпасами. Способ наведения самонаводящегося боеприпаса (СНБП) в условиях лазерного воздействия, дополнительно к известному способу, включает использование двух матричных фотоприемников (МФП) поражающего лазерного излучения (ПЛИ), включающих по одной линейке координатно-привязанных фоточувствительных элементов (ФЧЭ), размещенных перпендикулярно друг другу в плоскости, перпендикулярной оптической оси оптико-электронного координатора (ОЭК), на максимальном расстоянии от оптической оси ОЭК и на минимальном удалении от фокусной плоскости ОЭК, поля зрения ориентируются на оптическую ось ОЭК. Принимают МФП рассеянного вбок газовой средой ОЭК излучения источника ПЛИ и определяют координаты ФЧЭ МФП, сигнал на выходе которых превысил пороговое значение и параметры углового рассогласования направления полета СНБП и направления на источник ПЛИ. В случае неработоспособности фотоприемника осуществляют корректировку траектории ...

Способ прицеливания при сбросе грузов в точку земной поверхности с маневрирующего летательного аппарата

Изобретение относится к области авиационных средств прицеливания при сбросе грузов с летательного аппарата. Сущность изобретения заключается в том, что измеряют текущие значения фазовых координат летательного аппарата и цели, решают задачу прогнозирования фазовых координат движения маневрирующего летательного аппарата, формируют сигнал координат траектории выведения летательного аппарата. Формируют директорные сигналы текущих перегрузки и крена и заданных перегрузки и крена, необходимых для полета по траектории выведения. Формируют временной интервал до сброса. По достижении директорными сигналами заданных перегрузки, крена или времени, оставшегося до сброса, управляют наведением летательного аппарата, совмещая директорные сигналы заданной и текущей перегрузки и заданного и текущего крена. Для текущих значений скорости и угла наклона траектории определяют минимальную безопасную высоту точки сбрасывания, для которой решают задачу баллистики сбрасываемого груза, и формируют сигнал координат окружности точек сбрасывания, обеспечивающих попадание в цель, формируют сигнал координат поверхности цилиндра, пересекающей окружность точек сбрасывания и содержащей точку текущего положения и прогнозируемую траекторию движения маневрирующего летательного аппарата. Выделяют сигнал рассогласования между текущим положением и прогнозируемой траекторией движения маневрирующего летательного аппарата, корректируют сигналы заданной перегрузки и заданного крена сигналом рассогласования для выхода на траекторию выведения. Технический результат – повышение точности доставки грузов с криволинейных траекторий. 3 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 695 591 C1 (51) МПК F41G 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F41G 9/00 (2019.05) (21)(22) Заявка: 2018141047, 21.11.2018 (24) Дата начала отсчета срока действия патента: Дата регистрации: 24.07.2019 Приоритет(ы): (22) Дата подачи заявки: 21.11.2018 (56) Список ...

Устройство для наведения ракетного вооружения зенитных самоходных установок

Полезная модель относится к военной технике и может быть использована в конструкциях пусковых установок, устанавливаемых на башнях зенитных самоходных установок ближнего действия и служащих для проведения одиночного, последовательного или залпового пусков самонаводящимися ракетами. Устройство содержит две пусковые установки, каждая из которых состоит из универсального пускового модуля, платформы наведения, блока управления платформой наведения. Платформы наведения жестко закреплены на кронштейнах, которые смонтированы на корме башни симметрично относительно ее продольной оси. Платформа наведения выполнена в виде электромеханического привода наведения вооружения и понижающего редуктора. Выходной вал редуктора жестко связан с поворотной платформой и через кинематическую пару связан с датчиком измерения угла положения поворотной платформы по углу места, а через сектор кинематической пары кинематически связан с выходным валом электромеханического привода. Электромеханический привод содержит ...

Способ коррекции навесной траектории артиллерийского снаряда

FIELD: weapons and ammunition.SUBSTANCE: invention relates to barrel artillery ammunition and can be used in detonators of artillery projectiles to correct trajectory of their movement. Method of correcting trajectory of artillery projectile comprises the fact that prior to firing in computing device of head detonating fuse an algorithm is introduced to determine design value of switching on time of braking device of projectile t. A series of initial data relating to parameters of the gun, shell parameters and gun guidance parameters is entered, namely: design distance L, when projectile achieves this distance formation of control pulse, length of rifling pitch in barrel of artillery weapon l, angle of gun height during firing α, dimensionless aerodynamic drag coefficient C(M), projectile weight P. A shot is fired. Projectile flight time t is continuously recorded. By means of the pressure sensor installed in the detonating fuse the atmosphere pressure in the projectile flight zone is continuously recorded. Information from the pressure sensor is introduced into the fuse computing device as a function of time t. Using a fuse computer, two time values tand t(t<<t) are chosen, at which values of registered pressures coincide. Using the relation T=(t+t)/2 define time corresponding to maximum flight height of projectile T. By means of technical devices installed in fuse projectile in upper point of trajectory of projectile flight (at time T), projectile speed around its axis Nis measured. Based on the data entered into the projectile computing device before the shot and the measured values according to the predetermined algorithm using the fuse computing device, calculating the value tusing the following ratio: t=T+({L-[Vsin2α/2g(kVsinα+1)]}/Vcosα e), where V=Nl, k– coefficient, which is calculated by fuse computer using ratio k≅(-2P/VρQcosαC(M)+{[(2P/VρQcosαC(M)]+8Psinα/ρQsinαC(M)})/4Psinα/ρQcosαC(M).EFFECT: high accuracy of determining actuation time.1 cl, 1 dwg ...

AUTOMATISCHE BEURTEILUNG DER BEDROHUNG UND WISSENSBASIERTE ZUORDNUNG VON WAFFEN

Verfahren und Zieleinrichtung zur Ermittlung einer Wahrscheinlichkeit eines Treffers eines Zielobjekts

Die Erfindung betrifft ein Verfahren zur Ermittlung einer Wahrscheinlichkeit eines Treffers eines Zielobjekts sowie eine Zieleinrichtung, bei dem das Verfahren eingesetzt wird. Bei der Erfindung wird die ermittelte Wahrscheinlichkeit in einer Zieleinrichtung angezeigt, wobei das Zielobjekt mit einer Waffe beschossen wird. Bei dem Verfahren ist es vorgesehen, dass das Zielobjekt mit einer Zieleinrichtung anvisiert wird, dass beim Anvisieren des Zielobjekts eine Trefferfläche des Zielobjekts bestimmt wird, wobei die Trefferfläche durch ein Geschoss getroffen werden soll. Ferner umfasst das Verfahren die folgenden Schritte: Bestimmen mindestens eines ersten Faktors, welcher eine Flugbahn des Geschosses in Richtung des Zielobjekts beeinflusst, Berechnen einer ersten Trefferwahrscheinlichkeit, inwieweit das Geschoss unter Berücksichtigung des ersten Faktors die Trefferfläche des Zielobjekts trifft, Bestimmen einer ersten graphischen Darstellung der ersten Trefferwahrscheinlichkeit in Form einer ...

Waffensystem und Verfahren zum Lenken eines Wirkelements durch einen Schützen

Die Erfindung geht aus von einem Verfahren zum Lenken eines Wirkelements (10) durch einen Schützen in ein Ziel (16) mit einem Waffensystem (4), das eine Abfeuervorrichtung (8) zum Abfeuern des Wirkelements (10) aufweist. Um dem Schützen eine Unterstützung zur Ausrichtung der Abfeuervorrichtung (8) oder zur Lenkung des fliegenden Wirkelements (10) zu geben, wird vorgeschlagen, dass ein Lageparameter eines Gebiets (18) ermittelt wird, innerhalb derer das Waffensystem (4) in seinem momentanen Zustand eine vorbestimmte Einsatzeigenschaft erreicht.

Advanced air countermeasure and dispenser system

A countermeasure cartridge (squib) 22 comprises a controller 23 disposed within said cartridge, which is interrogated, in use, by a system external to said cartridge; wherein said controller communicates the configuration of said cartridge to said system. Data communication takes place over the same electrical connections that are used to fire the squib. Keywords: countermeasure squib, cocktails, dispenser, bridgewire.

No title

Mission planning for weapons systems

Improvements relating to target direction indication and accoustic pulse analysis

Data processing

Storing, at a first memory location, a first copy 46 of a set of data; storing, at a second memory location, a second copy 48 of a set of data; comparing 42 the first copy to the second copy so as to identify, within the first copy, a pointer 54, the pointer being located at a first data element of the first copy, the pointer specifying a second data element of the first copy; determining an offset 62 for the identified pointer, the offset specifying a number of data elements between the first data element and the second data element; and modifying the first copy such that the pointer within the first copy specifies the second data element using only the first data element and the offset. The invention is preferably applied to determination of the feasibility of a weapon carried on an aircraft successfully engaging a target or the target successfully engaging the aircraft.

DISPLAYING TARGETS

A network of intercommunicating battlefield devices

A NETWORK OF INTERCOMMUNICATING BATTLEFIELD DEVICES A plurality of battlefield devices that communicate with a battle management system using a communications network to form a network of intercommunicating battlefield devices that may be deployed in a battlefield environment. Each battlefield device comprising one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the battlefield device. The processor configured to cause the data to be sent to another location and to process other data received from other locations over said communications network.

RATE INTEGRATING GYROSCOPIC AIMING METHOD AND DEVICE THEREFOR

A gyroscopic azimuth aiming concept adapted to aim a drone or missile at the launch site but also to aim other military and non-military equipment. This concept is characterized by its use of a conventional rate integrating gyroscope to both measure the aiming error, which results from an approximate initial aiming done with a magnetic compass, and to effect the correction of the aiming error without the use of surveying or optical sighting instrument. This invention defines the method of measuring the aiming error including toppling the gyroscope to displace the input axis thereof from horizontal to vertical, in order to provide a measure of the required angular correction. This invention also defines a device wherein a conventional rate integrating gyroscope is pivotally mounted to allow rotation of 180.degree. in azimuth between a first and a second measurements of the rotation of the input axis direction and to allow toppling of the input axis as above mentioned.

A NETWORKED BATTLE SYSTEM WITH HEADS UP DISPLAY

A networked battle system includes a communication network, a first rifle and a sensor pack attached to the rifle that includes a sensor for determining a bearing of the first rifle, a sensor for an accelerometer and a rate gyroscope. The system also includes a communication element coupled to the rifle allowing the sensor pack to provide sensor information to the communication network, a battle management system in communication with the first rifle through the communication network that receives the sensor information from the sensor pack updates a battle plan based on the sensor information to form an updated battle plan and a heads up display unit at least in operative communication with the communication network and the communication element and that displays the updated battle plan to a user.

A NETWORKED BATTLE SYSTEM OR FIREARM

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

INTEGRATED COMBAT RESOURCE MANAGEMENT SYSTEM

An integrated combat resource management device is in the form of a smartphone with a display screen and user input device. The smartphone has a set of integrated applications stored therein which when executed provide an interactive display offering dynamic real-time situational awareness information to the user. Configuration files contain user-specific profiles. A launcher application offers access control and the management of several user profiles on the same smartphone such that upon successful login the appropriate user-specific profile is applied.

METHOD AND DEVICE FOR PROGRAMMING A PROJECTILE

Apparatus to direct the grenadage of the submarines

A METHOD FOR DETERMINING THE ACTUAL VALUE OF THE PARAMETERS CONDITIONING THE BALLISTIC TRAJECTORY FOLLOWED BY A PROJECTILE

REAL-TIME SMALL TARGET DETECTION METHOD USING LOCAL CONTRAST DIFFERENCE MEASURE

The present invention relates to a real-time small target detection method using local contrast difference measure comprises the following steps: detecting a small target candidate region; selecting label regions and obtaining a size (k) and a center coordinate of each label region; obtaining a local contrast map; classifying the region into a region having a high possibility of a small target and a region having a small possibility of a small target; and detecting a small target by performing adaptive binarization according to a pixel brightness value of the target. The real-time small target detection method using local contrast difference measure of the present invention can overcome the scale-dependent problem of a structure element-based target detection method by dynamically calculating the scale of the target by predicting target candidate pixel regions through the morphological difference operation and labeling predicted candidate pixels.

FLIGHT VEHICLE HAVING SHAPED CHARGE ASSEMBLY

The present invention provides a shaped charge assembly and a flight vehicle having the same, which can control a direction of a shaped charge in real time. According to the present invention, the flight vehicle in which a shaped charge assembly is mounted comprises: a target position detection unit placed at one side of the flight vehicle, and detecting position information of a target; a flight vehicle inducement control unit placed at the other side of the flight vehicle, and inducing and controlling the flight vehicle to a point in which the target is placed; and a shaped charge assembly placed between the target position detection unit and the flight vehicle inducement control unit, and controlling a direction of a shaped charge to strike the target in real time. COPYRIGHT KIPO 2017 ...

Area denial communication latency compensation

An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.

Methods and systems for estimating weapon effectiveness

Methods and systems for providing an estimate of effectiveness of a selected weapon against a selected target prior to release of the weapon are described. One described method comprises receiving a position uncertainty for a weapon platform, receiving a position uncertainty for a selected target, and determining an ability of the selected weapon to navigate to the selected target. An estimated effectiveness of the selected weapon is determined utilizing one or more of the weapon platform position uncertainty, the target position uncertainty, the navigation capability of the selected weapon, and a kill radius for the selected weapon.

GUIDANCE METHOD AND APPARATUS

СПОСОБ И УСТРОЙСТВО ДЛЯ ПРОГРАММИРОВАНИЯ СНАРЯДА

Изобретение относится к области программирования снаряда во время прохождения им ствола или дульного тормоза. Предложено выполнение программирования снаряда (5) индуктивными и/или емкостными датчиками. Предложено использовать волновод (2, 11) для программирования, так как электромагнитное поле сконцентрировано в волноводе. Используемое при этом программное устройство (1) состоит, по меньшей мере, из одного волновода (2, 11), который предпочтительно находится или установлен в зоне ствола, например, перед дульным тормозом (6). Соединитель (3) для передачи питается от генератора (4) сигналов. В модуляторе (18) на несущую частоту (f) модулируется информация, предусмотренная для снаряда (5). На/в снаряде (5) установлен приёмный соединитель (8), который электрически подключен к накопителю или процессору (19) в снаряде (5). Он принимает модулированный сигнал и передает его дальше в процессор (19), где далее происходит сам процесс программирования. Изобретение позволяет создать систему, которая ...

УСТРОЙСТВО МЕТАНИЯ СЕТИ НАПРАВЛЕННОГО ДЕЙСТВИЯ ДЛЯ БЕСПИЛОТНЫХ ЛЕТАТЕЛЬНЫХ АППАРАТОВ (БПЛА)

Полезная модель относится к устройствам борьбы с беспилотными летательными аппаратами (БПЛА), а именно к устройствам для перехвата БПЛА. Технический результат достигается тем, что устройство метания сети направленного действия для беспилотных летательных аппаратов (БПЛА), выполненное в виде корпуса, с верхней стороны которого смонтирован соединительный элемент, выполненный с возможностью фиксации к БПЛА, содержащий застёжку и фоторезистор, с нижней стороны корпуса выполнено углубление, в центральной части которого смонтировано контактное гнездо, в которое смонтирован электрический пиропатрон при помощи разъёмного соединения, отличающееся тем, что корпус содержит информационную панель управления, выполненную с возможностью регулирования подачи электрического тока к электрическому пиропатрону, фоторезистор выполнен с возможностью реагирования на LED-подсветку БПЛА, с нижней стороны корпуса на разъёмное соединение смонтирован газораспределительный элемент, содержащий ёмкость и основание, к ...

Способ работы транспортной системы специализированный автопоезд - лёгкий штурмовик - беспилотный летательный аппарат (БЛА) и устройство транспортной системы

СПОСОБ КОМБИНИРОВАННОГО НАВЕДЕНИЯ ЛЕТАТЕЛЬНОГО АППАРАТА

Способ комбинированного наведения летательного аппарата, включающий комбинацию радиокомандного на начальном участке полета летательного аппарата (в ближней зоне) и радиолокационного или оптического самонаведения на конечном участке (в дальней зоне), отличающийся тем, что величина команды управления на выходе устройства выработки команд на этапе радиокомандного наведения рассчитывается в соответствии с зависимостьюгде ωимеет смысл полосы пропускания контура наведения, q - показатель степени, определяющий вид нелинейности, h - линейная ошибка наведения,- оценка скорости изменения линейной ошибки наведения;а на этапе самонаведения - в соответствии с выражениемгде- оценка относительной дальности «летательный аппарат - воздушный объект»,- оценка скорости сближения летательного аппарата с воздушным объектом,Tv - аэродинамическая постоянная, К- назначаемый коэффициент,- оценка угловой скорости линии визирования «летательный аппарат - воздушный объект», q - показатель степени, определяющий вид ...

Interactive reticle for a tactical battle management system user interface

An interactive reticle to be displayed on a user interface displayed on a touchscreen device is disclosed. The interactive reticle comprises a center portion comprising a zone for displaying data and a plurality of icons displayed around the center portion, each of the plurality of icons for executing a corresponding application upon detection of a corresponding finger gesture on a corresponding icon.

Missile guidance system and method

A guidance system and method for a missile, in which the missile 1 is guided to the target by a concealed spotter via a relay station 3 with line of sight to the target 4. Relay station transmits an image of the target to the spotter using a TV camera (6, Fig 2) and/or a thermal imager, locates the missile by means of a missile locator (5) axially coordinated with the camera, and communicates guidance signals to the missile only after the launch of missile 1. Locator (5) and relay station 3 receive modulated radiation from a pulsed light source 10 that is present in the missile tail. Locator (5) opens a reception window in time synchronization with the pulsed light 10. Both device 6 and locator 5 may be installed and stabilised on a drone. Element 2 identifies obstructions experienced during operation.

INFORMATION TRANSMITTING SYSTEM

Advanced air countermeasure and dispenser system

A countermeasure cartridge (squib) 22 comprises a controller 23 disposed within the cartridge, which is interrogated, in use, by a system external to the cartridge. The controller 23 communicates the configuration of the cartridge to said system. The configuration may include information about the type of cartridge and the manufacturer. The cartridge is automatically selected and fired if its configuration corresponds to that of a misfiring cartridge. Data communication takes place over the same electrical connections that are used to fire the squib. Keywords: countermeasure squib, cocktails, dispenser, bridgewire ...

Emergency vehicle traffic signal preemption system

A networked battle system with heads up display

A networked battle system includes a communication network, a first rifle and a sensor pack attached to the rifle that includes a sensor for determining a bearing of the first rifle, a sensor for an accelerometer and a rate gyroscope. The system also includes a communication element coupled to the rifle allowing the sensor pack to provide sensor information to the communication network, a battle management system in communication with the first rifle through the communication network that receives the sensor information from the sensor pack updates a battle plan based on the sensor information to form an updated battle plan and a heads up display unit at least in operative communication with the communication network and the communication element and that displays the updated battle plan to a user.

A NETWORKED BATTLE SYSTEM OR FIREARM

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

INTERACTIVE RETICLE FOR A TACTICAL BATTLE MANAGEMENT SYSTEM USER INTERFACE

An interactive reticle to be displayed on a user interface displayed on a touchscreen device is disclosed. The interactive reticle comprises a center portion comprising a zone for displaying data and a plurality of icons displayed around the center portion, each of the plurality of icons for executing a corresponding application upon detection of a corresponding finger gesture on a corresponding icon.

COOLING SYSTEM FOR COMBINED COOLING TYPE SEARCH WINDOW

The present invention relates to a cooling system for a combined cooling type search window, comprising: a combined cooling type search window provided in a dome of a guided missile; a film cooling gas supply portion for supplying gas to spread on a surface of the combined cooling type search window; and an accumulator for supplying cooling liquid into the combined cooling type search window. According to the present invention, the outside and the inside of the search window can be simultaneously cooled to efficiently block heating of the search window, and a temperature gradient according to the location of the search window can be reduced. COPYRIGHT KIPO 2018 ...

Device with a scope coupled to a network to enable simultaneous tracking of targets at a plurality of devices

DEVICE FOR SIMULATING FLIGHT VEHICLE

The present invention provides a method for simulating a flight vehicle, and a device therefor based on a virtual model after extracting parameters related to a flight vehicle to generate the virtual model of the flight vehicle. According to the present invention, the device comprises: a parameter obtaining unit obtaining the parameters related to the flight vehicle; a virtual model generating unit generating the virtual model with respect to the flight vehicle based on the parameters; and a flight vehicle simulation unit simulating the flight vehicle based on the virtual model. COPYRIGHT KIPO 2017 (110) Launch control equipment (120) Flight vehicle (140) Interworking data DB (150) Parameter extraction DB (160) Flight simulator (161) Flight model production (162) Flight vehicle data regeneration (163) Flight simulation ...

연속적 시변 편향을 이용한 충돌각 제어 장치

... 본 발명에 따르면, 유도 발사체 발사 전 상기 표적 요격 시까지의 목표 충돌각 제어를 위한 목표 충돌각 제어부 및 상기 유도 발사체 발사 후 연속적으로 변화하는 편향 순시치를 계산하는 편향 계산부를 포함하여 가속도 제한을 고려하여 충돌각을 제어할 수 있는 연속적 시변 편향을 이용한 충돌각 제어 장치가 개시된다.

SEMI-ACTIVE GUIDED AERIAL VEHICLE FOR INTERCEPTING FLIGHT VEHICLE

비행체 요격용 반능동 유도 비행체를 공개한다. 본 발명은 표적을 탐지하기 위해 발사 통제 레이더에서 방사된 방사 신호가 표적에 반사된 신호를 각각 전방 신호로서 수신하는 복수개의 전면 안테나와 발사 통제 레이더에서 방사된 방사 신호를 직접 후방 신호로서 수신하는 적어도 하나의 후면 안테나를 구비하고, 복수개의 전방 신호 각각과 후방 신호를 합성하여 주파수 하향 변환하고, 주파수 하향 변환된 복수개의 전방 신호를 분석하여 표적의 위치를 판별하는 탐색기, 유도 비행체의 추진력을 제공하고, 핀을 구동하여 유도 비행체의 비행 방향을 조절하는 구동 및 추진부, 및 발사 통제 레이더와 통신을 수행하여 표적 위치 정보를 인가받고, 표적 위치 정보에 따라 표적을 추적하기 위해 구동 및 추진부를 제어하며, 탐색기가 표적의 위치를 판별하면, 탐색기가 판별한 표적의 위치에 따라 표적이 유도 비행체의 조준선에 위치하도록 구동 및 추진부를 제어하는 유도 조종부를 포함한다. Disclose semi-active guidance vehicle for flight intercept. The present invention includes a plurality of front antennas, each of which receives a radar signal radiated from a launch control radar as a front signal, and a radar signal radiated from the radar, A searcher that has a single rear antenna and synthesizes a plurality of forward signals and a backward signal to perform frequency downconversion and analyzes a plurality of downwardly converted forward signals to determine a position of a target, A drive and propulsion unit that drives the pin to control the flight direction of the guided vehicle, and a launch control radar to receive the target position information and control the drive and propulsion unit to track the target in accordance with the target position information If the searcher determines the position of the target, And an induction control unit for controlling the driving and propulsion unit so as to be positioned at the line of sight of the guidance vehicle.

비행경로각 예측을 이용한 유도 비행체 제어 방법

... 본 발명은 대공 유도 비행체 제어 방법에 대한 것으로서, 표적의 비행경로각 의 변화를 예측하여 유도 비행체를 제어하는 방법에 대한 것이다. 본 발명의 일 실시예에 따르면, 활성화된 상태에서 표적을 탐색하는 탐색기 및 탐색 결과를 분석하여 표적의 관측각을 분석하고, 관측각을 이용하여 미리 설정된 방법에 따라 표적의 비행경로를 예측하며, 비행경로를 이용하여 제어신호를 생성하는 콘트롤러를 포함하는 유도 비행체가 개시된다. 본 발명에 따르면, 표적의 비행경로각을 예측하고, 그 예측 결과를 바탕으로 유도 비행체의 기동을 제어하므로, 회피 기동을 수행하는 표적과의 충돌 가능성을 높일 수 있다.

Bestämning av rollvinkel

Devices with network-connected scopes for allowing a target to be simultaneously tracked by multiple devices

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope.

Collision targeting for an unoccupied flying vehicle (UFV)

Disclosed herein are example embodiments for collision targeting for an unoccupied flying vehicle (UFV). For certain example embodiments, at least one machine, such as a UFV, may: (i) ascertain at least one target for at least one collision to include a UFV; or (ii) execute at least one maneuver to divert a UFV at least toward at least one target to induce at least one collision to include the UFV and the at least one target. However, claimed subject matter is not limited to any particular described embodiments, implementations, examples, or so forth.

Способ подготовки пуска управляемых ракет и управляющая система комплекса ракетного вооружения

FIELD: rocket equipment.SUBSTANCE: group of inventions relates to the field of guided missile weapon application and can be used in multichannel complexes having means of detecting, tracking targets and direction finding of missiles. Method involves detecting, capturing and tracking several targets, assigning each target to each missile by specifying a channel interval. After each missile is tied to its target and a command is received to launch the missile, the on-board missile equipment is ready to record repeating code parcels. In each premise, a set of parameters of the corresponding channel interval target, which are used in the control system when transmitting commands to the missile and receiving response signals from it, as well as the target type are generated. Recording is performed until its confirmation from on-board equipment of missile. Then, the recorded set of parameters is read out and compared with the transmitted set. In case of their match, write-reading of parameters is terminated and rocket is launched with further controlled flight. In case of discrepancy of set of parameters recorded in on-board equipment, transmitted write-reading procedure is repeated for preset time. If the set of parameters does not match, the missile is launched without flight control with subsequent self-liquidation.EFFECT: shorter time for checking readiness of missile before launch.2 cl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 689 008 C1 (51) МПК F42B 15/01 (2006.01) F41G 7/30 (2006.01) F41G 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F42B 15/01 (2019.02); F41G 7/30 (2019.02); F41G 9/00 (2019.02) (21)(22) Заявка: 2018119846, 29.05.2018 (24) Дата начала отсчета срока действия патента: Дата регистрации: 23.05.2019 (45) Опубликовано: 23.05.2019 Бюл. № 15 2 6 8 9 0 0 8 R U (56) Список документов, цитированных в отчете о поиске: RU 2321818 C1, 10.04.2008. RU 2131577 С1, 10.06.1999. RU 2258900 С1, ...

МОРСКАЯ СТОРОЖЕВАЯ МИНА

FIELD: blasting operations. SUBSTANCE: invention relates to marine watchmines. Proposed mine comprises hull of elongated drop-like shape, consisting of three parts, nose part of which has the shape of a hemisphere, middle part forms a cylinder and aft part has a shape of truncated cone with stabilizers on sides. Wherein aft part is made fired off. Flare containers are placed between middle and aft parts and these flares are activated after aft part firing off. There are harpoon guns symmetrically placed outside middle part of the hull. Middle cylindrical part of the hull contains working unit consisting infrasound generator generating infrasound of certain frequency, hydroacoustic signal generator and power supply system including batteries and generator with drive consisting of step-up reduction gear and radial impeller. EFFECT: technical result consists in improvement of enemy neutralization efficiency, while ensuring the safety of his vessel. 1 cl, 15 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 599 152 C1 (51) МПК F42B 22/04 (2006.01) F42B 12/34 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2015134627/03, 17.08.2015 (24) Дата начала отсчета срока действия патента: 17.08.2015 (72) Автор(ы): Гаршин Олег Николаевич (RU) (73) Патентообладатель(и): Гаршин Олег Николаевич (RU) R U Приоритет(ы): (22) Дата подачи заявки: 17.08.2015 (45) Опубликовано: 10.10.2016 Бюл. № 28 2 5 9 9 1 5 2 (56) Список документов, цитированных в отчете о поиске: RU 2413156 C1, 27.02.2011. RU 2032139 C1, 27.03.1995. RU 2493535 C1, 20.09.2013. UA 31308 U, 10.04.2008. US 4215630 A, 05.08.1980. 2 5 9 9 1 5 2 R U (54) МОРСКАЯ СТОРОЖЕВАЯ МИНА (57) Реферат: Изобретение относится к морским сторожевым минам. Мина содержит корпус удлиненной каплеобразной формы, состоящий из трех частей, из которых носовая часть имеет форму полусферы, средняя в форме цилиндра и кормовая в форме усеченного конуса со стабилизаторами по бокам. Причем ...

СПОСОБ И УСТРОЙСТВО ДЛЯ ПРОГРАММИРОВАНИЯ СНАРЯДА

1. Способ программирования снаряда (5) во время его прохождения сквозь ствол (7), дульный тормоз (6) или подобное посредством программного устройства (1),отличающийся тем, что- при прохождении снаряду (5) сообщают создаваемую для программирования генератором (4) сигналов частоту (f), причем несущей частоте (f) модулируется информация для программирования, и- программирование в течение прохождения осуществляют посредством волновода (2), который эксплуатируется ниже граничной частоты соответствующего режима волновода (ТЕ, ТМ).2. Способ по п.1, отличающийся тем, чтов волноводе (2, 11) можно осуществлять измерение начальной скорости Vснаряда (5) посредством сгенерированной для измерения частоты (f), которая однако по времени проходит перед программированием.3. Способ по п.2, отличающийся тем, чтовозбуждают соответствующее электромагнитное поле в волноводе (2, 11), так что частота (f) в снаряде (5) может отражаться и обрабатываться.4. Способ по любому из пп.1-3, отличающийся тем, чтов волноводе (2, 11) можно осуществлять передачу энергии на снаряд (5) посредством сгенерированной для передачи энергии частоты (f).5. Способ по любому из пп.1-3, отличающийся тем, что частоты (f) больше 0 Гц.6. Способ по п.4, отличающийся тем, что частоты (f) больше 0 Гц.7. Устройство для программирования снаряда (5) во время прохождения его сквозь ствол (2), дульный тормоз (6) или подобное посредством программного устройства (1), содержащего, по меньшей мере, один волновод (2), который может являться стволом (7), дульным тормозом (6) или дополнительным элементом между концом ствола (7) и началом дульного тормоза (6) или дополнительно устанавливаться на конце дульного тормоза (6), с, по меньше РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (51) МПК F42C 17/04 (11) (13) 2012 137 289 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2012137289/03, 28.01.2011 (71) Заявитель(и): РЕЙНМЕТАЛЛ ЭЙР ДИФЕНС АГ (CH) Приоритет(ы): (30) Конвенционный приоритет: (72) ...

Verfahren und Vorrichtung zur Programmierung eines Projektils

Verfahren zur Programmierung eines Projektils (5) während des Durchlaufs durch ein Waffenrohr (7), Mündungsbremse (6) oder dergleichen mittels einer Programmiereinheit (1), dadurch gekennzeichnet, dass dem Projektil (5) eine von einem Signalerzeuger (4) für die Programmierung erzeugte Frequenz (f1) beim Durchlauf aufgeprägt wird, wobei der Trägerfrequenz (f1) die für die Programmierung Information aufmoduliert wurde, und das Programmieren innerhalb des Durchlaufs durch einen Hohlleiter (2) erfolgt, der unter der Grenzfrequenz des betreffenden Hohlleiter-Modes (TE, TM) betrieben wird, wobei die für die integrierte Elektronik des Projektils (5) notwendige Energie mit einer Energieübertragungseinheit (21) vor der Programmierung übertragen wird.

System integration

Disclosed is a system and method for generating, in an aircraft (1, fig.1a) in flight, a display indicative of the feasibility of a weapon carried on the aircraft successfully engaging a target (5, fig.1) and/or the feasibility of a weapon carried on the target successfully engaging the aircraft. The method comprises: using a performance envelope of the weapon and performance envelope(s) for one or more different types of aircraft, determining a further performance envelope specifying the performance of the weapon when carried by any of the different aircraft types; determining coefficients 21 for a generic polynomial that fit the generic polynomial to the further performance envelope; uploading, to the aircraft, the generated coefficients; and, on the aircraft, reconstructing 25 the further performance envelope and generating the feasibility display. The target may be a further aircraft and the display may indicate a Launch Acceptability Region (LAR) or a Launch Success Zone (LSZ). The ...

A mine

Advanced air countermeasure and dispenser system

FIREARM ELECTRONIC SYSTEM

Man portable weapons include integrated electronics that calculate orientation and movement in addition to providing that data to a user's heads-up displays (HUD) as well as to group and area networks. By passing data to a HUD, the user is able to see, virtually, the flight path, point of impact and other ballistic data as well as data representing the condition and performance of the weapon for any rounds fired. The HUD also displays the relative position of other members of the team, last known enemy area of operation and other useful parameters from the man portable weapons of the other team members through the network. The electronics may be integrated within the main components of any suitable man portable weapon in a non intrusive way as to have no effect on the firing mechanism of the small arm when it is fully assembled. Fig 3. WO 2017/184230 PCT/US2017/016565 4-0 3/8 Thermii~~ehage (V[J F3 2C ro -oo Xceiver 1 L~rreIH1rmotof ~~)oL5orrco 56t~e Crtoe 2 C2 4farp- Ham LuIJ ---- ---- ...

A network of intercommunicating battlefield devices

A NETWORK OF INTERCOMMUNICATING BATTLEFIELD DEVICES A plurality of battlefield devices that communicate with a battle management system using a communications network to form a network of intercommunicating battlefield devices that may be deployed in a battlefield environment. Each battlefield device comprising one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the battlefield device. The processor configured to cause the data to be sent to another location and to process other data received from other locations over said communications network.

A networked battle system or firearm

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

A networked battle system or firearm

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

Firearm electronic system

Man portable weapons include integrated electronics that calculate orientation and movement in addition to providing that data to a user's heads-up displays (HUD) as well as to group and area networks. By passing data to a HUD, the user is able to see, virtually, the flight path, point of impact and other ballistic data as well as data representing the condition and performance of the weapon for any rounds fired. The HUD also displays the relative position of other members of the team, last known enemy area of operation and other useful parameters from the man portable weapons of the other team members through the network. The electronics may be integrated within the main components of any suitable man portable weapon in a non-intrusive way as to have no effect on the firing mechanism of the small arm when it is fully assembled.

FIREARM ELECTRONIC SYSTEM

Man portable weapons include integrated electronics that calculate orientation and movement in addition to providing that data to a user's heads-up displays (HUD) as well as to group and area networks. By passing data to a HUD, the user is able to see, virtually, the flight path, point of impact and other ballistic data as well as data representing the condition and performance of the weapon for any rounds fired. The HUD also displays the relative position of other members of the team, last known enemy area of operation and other useful parameters from the man portable weapons of the other team members through the network. The electronics may be integrated within the main components of any suitable man portable weapon in a non-intrusive way as to have no effect on the firing mechanism of the small arm when it is fully assembled.

DEVICES WITH NETWORK-CONNECTED SCOPES FOR ALLOWING A TARGET TO BE SIMULTANEOUSLY TRACKED BY MULTIPLE DEVICES

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope.

GUIDANCE METHOD AND APPARATUS

A method of guiding a pursuer to a target is provided, and is of particular use when the possible target location is described by non-Gaussian statistics. Importantly, the method takes into account the fact that different potential target tracks in the future have significantly different times to go. That can give rise to emergent behaviour, in which the guidance method covers several possible outcomes at the same time in an optimal way. An example embodiment of the method combines Particle Filter ideas with Swarm Optimization techniques to form a method for generating guidance commands for systems with non- Gaussian statistics. That example method is then applied to a dynamic mission planning example, to guide an airborne pursuer to a ground target travelling on a network of roads where the pursuer has no-go areas, to avoid collateral damage.

Process for the ordering and the propulsion of an air body, in particular of a formation of air bodies, and device and air body for the implementation of this process

SIGHTING MEANS FOR MISSILES

METHOD FOR CREATING REFERENCE ROUTE FOR REAL-TIME INSPECTION OF INTEGRATED ELECTRONIC APPARATUS

The present invention relates to a reference route creation technique in a navigation system, and more particularly, to a method of creating a reference route (a reference value of guided missile state information according to flight time) required for automatizing a real-time inspection of an integrated electronic apparatus, a method for setting an error range of the reference route to automatize determination of inspection result, and a method for implementing the same in a test set. According to the present invention, proceduralization and/or automation of reference route creation and error range setting process necessary for automatizing real-time inspection can be possible.

킬비클용 궤도수정 및 자세 제어장치 및 이의 동작 방법

... 본 발명은 킬비클용 궤도수정 및 자세 제어장치 및 이의 동작 방법에 관한 것이다. 이를 위한 본 발명의 일측에 시커부가 형성된 요격 미사일의 킬비클(kill-vihicle)에 탑재되고, 요격 미사일의 자세 제어를 수행하는 킬비클용 궤도수정 및 자세 제어장치는 킬비클의 중심을 기준으로 킬비클의 일측에 배치되고, 내부에 무게 조절용 유체를 보관하는 제 1 유체 저장부; 제 1 유체 저장부에 이격되어 배치되는 제 2 유체 저장부; 일측이 제 1 유체 저장부에 연결되고, 타측이 제 2 유체 저장부에 연결된 배관; 및 배관을 통한 무게 조절용 유체의 이동 속도를 제어함으로써, 요격 미사일의 궤도수정 및 자세를 제어하는 자세 제어부를 포함하는 것을 특징으로 한다.

Method and apparatus for determining location using nominal trajectory

METHOD AND SYSTEM FOR ESTIMATING TRUST LEVEL IN ACCORDANCE WITH ACCURACY RATE OF GUIDED WEAPON

According to an aspect of the present invention, provided is a method for estimating a trust level in accordance with an accuracy rate of a guided weapon, including: a step of inputting a total amount of guided weapons (N), a guaranteed accuracy rate (w), the allowable defective number (c), and a guided weapon test-launching quantity (n); a step of calculating a probability (P) of the number of guided weapon test launches being all normal, through a hyper-geometric distribution based on a non-accuracy rate (P) in accordance with the number of defective products within a total number of guided weapons; and a step of calculating a confidence level (cl) in accordance with a Bayesian rule based on a ratio of the sum of the probabilities (P) of satisfying the guaranteed accuracy rate (w) or more with respect to the sum of the calculated probabilities (P). Accordingly, the present invention is able to minimize a quantity of tests with respect to a guided weapon launching test which is a high-priced ...

복합 냉각식 탐색창 냉각 시스템

... 본 발명은 유도탄의 돔에 마련되는 복합 냉각식 탐색창, 상기 복합 냉각식 탐색창의 표면으로 분사하기 위한 기체를 공급하는 막냉각 기체 공급부 및 상기 복합 냉각식 탐색창의 내부로 냉각 액체를 공급하기 위한 축압기를 포함하는 복합 냉각식 탐색창 냉각 시스템으로서, 본 발명에 의하면, 탐색창의 외부 및 내부를 동시에 냉각이 가능하여 탐색창의 히팅을 효율적으로 차단시키고, 탐색창의 위치에 따른 온도 구배를 감소시킬 수 있다.

APPARATUS FOR DEPLOYING CANARD OF GUN LAUNCHED GUIDED MISSILE AND DEPLOYMENT METHOD THEREOF

The present invention relates to an apparatus for deploying a canard of a gun launched guided missile. More specifically, the present invention is housed in an initial shell through an apparatus for deploying a canard of a gun launched guided missile, and then deploys the canard to the outside of the shell more promptly after being fired. The apparatus for deploying a canard of a gun launched guided missile of the present invention comprises: a deployment bracket located at the top of a center; a fixing bracket connected to the development bracket around the development bracket; the canard which is restrained by the fixing bracket or released from the restraint; and a deployment spring for applying elastic force in the deploying direction so that the canard can deployed. Further, in the present invention, as the deployment bracket is raised, the canard is deployed. COPYRIGHT KIPO 2018 ...

ROLL AND PITCH CANARD DRIVE DEVICE FOR PRECISION GUIDANCE KIT

The present invention relates to canard driving for a precision guidance kit. More particularly, the present invention relates to a roll and pitch canard drive device for a precision guidance kit in which a roll canard drive unit and a pitch canard drive unit are efficiently designed and arranged. The roll canard drive unit rotates two roll canards in opposite directions by operating one motor through a link mechanism. The pitch canard drive unit rotates two pitch canards in the same direction by operating one motor. The roll and pitch canard drive device according to the present invention includes a roll canard drive unit rotating first and second roll canards in opposite directions about a roll canard rotary shaft by first motor operation; and a pitch canard drive unit rotating first and second pitch canards in the same directions about a pitch canard rotary shaft by second motor operation. The roll canard drive unit and the pitch canard drive unit are independently operated. COPYRIGHT ...

HILS SYSTEM FOR DUAL-SENSOR IMAGING SEEKER'S TEST AND EVALUATION

EMERGENCY VEHICLE TRAFFIC SIGNAL PREEMPTION SYSTEM

An emergency vehicle traffic light preemption system (100) for preemption of traffic lights at an intersection to allow safe passage of emergency vehicles. The system (100) includes a real-time status monitor (42) of an intersection which is relayed to a control module (10) for transmission to emergency vehicles as well as to a central dispatch office. The system (100) also provides for audio warning at an intersection to protect pedestrians who may not be in a position to see visual warnings or for various reasons cannot hear the approach of emergency vehicles. A transponder (200) mounted on an emergency vehicle provides autonomous control so the vehicle operatorcan attend to getting to an emergency and not be concerned with the operation of the system. Activation of a priority-code (i.e. Code-3) situation provides communications with each intersection being approached by an emergency vehicle and indicates whether the intersection is preempted or if there is any conflict with other approaching ...

GUIDANCE METHOD AND APPARATUS

A method of guiding a pursuer to a target is provided, and is of particular use when the possible target location is described by non-Gaussian statistics. Importantly, the method takes into account the fact that different potential target tracks in the future have significantly different times to go. That can give rise to emergent behaviour, in which the guidance method covers several possible outcomes at the same time in an optimal way. An example embodiment of the method combines Particle Filter ideas with Swarm Optimization techniques to form a method for generating guidance commands for systems with non- Gaussian statistics. That example method is then applied to a dynamic mission planning example, to guide an airborne pursuer to a ground target travelling on a network of roads where the pursuer has no-go areas, to avoid collateral damage.

Verfahren und Vorrichtung zur Programmierung eines Projektils

Vorgeschlagen wird die Programmierung eines Projektils (5) induktiv und/oder kapazitiv vorzunehmen. Vorgeschlagen wird, einen Hohlleiter (2, 11) für die Programmierung zu nutzen, da das elektromagnetische Feld in einem Hohlleiter konzentriert ist. Die hierbei verwendete Programmiereinheit (1) besteht dabei zumindest aus einem Hohlleiter (2, 11), der sich bevorzugt im Bereich der Mündung, beispielsweise vor einer Mündungsbremse (6), befindet bzw. eingebunden ist. Ein Sende-Koppler (3) für die Übertragung wird dabei von einem Signalerzeuger (4) gespeist. Diesem wird in einem Modulator (18) auf die Trägerfrequenz (f1) die für das Projektil (5) vorgesehenen Informationen aufmoduliert. Am/im Projektil (5) eingebundenen ist ein Empfangs-Koppler (8), der mit einem Speicher oder Prozessor (19) im Projektil (5) elektrisch verschaltet ist. Dieser nimmt das modulierte Signal auf und leitet es an den Prozessor (19) weiter. Dort erfolgt dann die eigentliche Programmierung.

Methods and apparatus for controlling deployment of systems

Methods and apparatus for controlling deployment of systems according to various aspects of the present invention operate in conjunction with at least one deployable asset, a scoring system, and an optimization system. The scoring and optimization systems provide an optimized solution to mission planning, asset positioning, and control of multiple entities within a geographic region. The system combines a scoring method with an optimization method to quickly select a globally optimal solution from a larger set of potential solutions.

GUIDANCE METHOD AND APPARATUS

A method of guiding a pursuer to a target is provided, and is of particular use when the possible target location is described by non-Gaussian statistics. Importantly, the method takes into account the fact that different potential target tracks in the future have significantly different times to go. That can give rise to emergent behaviour, in which the guidance method covers several possible outcomes at the same time in an optimal way. An example embodiment of the method combines Particle Filter ideas with Swarm Optimization techniques to form a method for generating guidance commands for systems with non-Gaussian statistics. That example method is then applied to a dynamic mission planning example, to guide an airborne pursuer to aground target travelling on a network of roads where the pursuer has no-go areas, to avoid collateral damage. 1. A method of guiding a pursuer to a target , the method comprising:(a) providing a plurality of possible target trajectories, weighted to represent a probability distribution of the target trajectories;(b) providing a plurality of candidate guidance controls, parameterised by a candidate guidance parameter; a. determining a projected pursuer trajectory resulting from the candidate guidance control corresponding to the candidate guidance parameter value;', 'b. using the projected pursuer trajectory so far developed, determining the next occurrence of a termination condition for the pursuer trajectory relative to any of the target trajectories for which a termination condition has not yet occurred;', 'c. adjusting the projected pursuer trajectory, subsequent to that termination-condition occurrence, to account for that target trajectory;', 'd. repeating steps b and c until the termination conditions corresponding to all of the plurality of possible target trajectories have been accounted for; and', 'e. recording a cost for the candidate guidance control based on the projected pursuer trajectory and the miss distances at the ...

Extra-sensory perception sharing force capability and unknown terrain identification system

An occlusion or unknown space volume confidence determination, and planning system using databases, position, and shared real time data to determine unknown regions allowing planning and coordination of pathways through space to minimize risk. Data such as from cameras, or other sensor devices can be shared and routed between units of the system. Hidden surface determination, also known as hidden surface removal (HSR), occlusion culling (OC) or visible surface determination (VSD), can be achieved by identifying obstructions from multiple sensor measurements and incorporating relative position with depth between sensors to identify occlusion structures. Weapons ranges, and orientations are sensed, calculated, shared, and can be displayed in real time. Data confidence levels can be highlighted from time, and frequency of data. The real time data can be displayed stereographically for and highlighted on a display.

Reflexive response system for popup threat survival

Methods and apparatus for assessing threats to a vehicle to facilitate a reflexive response. Threat timeline parameters for a detected threat to the vehicle including a threat mode and a time progression of the threat in the threat mode is determined based, at least in part, on a plurality of information sources. One or more candidate solutions for facilitating the reflexive response to the threat are determined based, at least in part, on the threat mode and the time progression and one or more of the candidate solutions are presented to an operator of the vehicle to enable the operator to mediate the threat.

Method and device for programming a projectile

An inductive or capacitative programming of a projectile is disclosed. A waveguide is used for the programming, the electromagnetic field being concentrated in the waveguide. The used programming unit includes at least one waveguide which is preferable located and/or integrated in the region of the muzzle, for example in front of the muzzle brake. A transmission coupler for the transmission is fed by a signal generator. The information relating to the projectile is modulated to the carrier frequency in the modulator. A reception coupler integrated on/in the projectile is electrically interconnected to a store or processor in the projectile. The reception coupler receives the modulated signal and transmits it to the processor which is where the eventual programming takes place.

Devices with network-connected scopes for allowing a target to be simultaneously tracked by multiple devices

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope.

Internal display for an optical device

A system can include an optical device and an accessory device. The optical device can include a housing, an objective lens at a first end of the housing and supported by the housing, an ocular lens at a second end of the housing and supported by the housing, and an optical path defined from the objective lens through the housing to the ocular lens, and a display device supported by the housing proximate the second end of the housing. The display device can include a display, hardware logic circuitry to process display data and to display the display data on the display, an input port, and a display holder to position the display in the optical path in the presence of a signal from the accessory device and to position the display out of the optical path in the absence of a signal from the accessory device.

Virtual Roll Gyro for Spin-Stabilized Projectiles

A method is described for determining roll rate for a spin-stabilized projectile. A yaw signal and a pitch signal are measured for the projectile, wherein: (i) for a trajectory path being travelled by the projectile over the Earth's surface, projectile stability is created by spinning of the projectile about a longitudinal spin axis oriented tangent to the projectile trajectory, (ii) the yaw signal represents yaw motion of the projectile about a yaw axis oriented along a line through the Earth's center and orthogonal to the spin axis, and (iii) the pitch signal represents pitch motion of the projectile about a pitch axis orthogonal to the spin axis and the yaw axis, and wherein the yaw signal and the pitch signal are modulated by spin rate of the projectile spinning about the spin axis. A roll rate signal is extracted from one of the yaw signal and the pitch signal. 1. A computer-implemented method employing at least one hardware implemented computer processor for determining roll rate for a spin-stabilized projectile , the method comprising: ["(i) for a trajectory path being travelled by the projectile over the Earth's surface, projectile stability is created by spinning of the projectile about a longitudinal spin axis oriented tangent to the projectile trajectory,", "(ii) the yaw signal represents yaw motion of the projectile about a yaw axis oriented along a line through the Earth's center and orthogonal to the spin axis,", 'wherein the yaw signal and the pitch signal are modulated by spin rate of the projectile spinning about the spin axis;', '(iii) the pitch signal represents pitch motion of the projectile about a pitch axis orthogonal to the spin axis and the yaw axis, and'}], 'operating the at least one hardware processor to execute program instructions to: measure a yaw signal and a pitch signal for the projectile, whereinextract a roll rate signal from one of the yaw signal and the pitch signal; andprovide the yaw signal, the pitch signal, and the roll rate ...

WIDE AREA NEUTRALIZER

A weapon system includes a number of WAN components, each WAN component includes a warhead, a launch mechanism for launching the warhead, an aiming mechanism for aiming the launch mechanism to launch the warhead in a desired direction, and a controller that, upon receipt of a command to aim and launch the warhead, operates the aiming mechanism to aim the warhead in the desired direction and then operates the launch mechanism to launch the warhead. The weapon system also includes a WAN component deployment mechanism for deploying the plurality of WAN components in a defended area; and a command center for instructing the controller of one or more of the WAN components to aim and launch the warhead of the each WAN component at a target that has been detected in the defended area. 1. A weapon system comprising: (i) a warhead,', '(ii) a launch mechanism for launching the warhead,', '(iii) an aiming mechanism for aiming said launch mechanism to launch said warhead in a desired direction, and', '(iv) a controller that, upon receipt of a command to aim and launch said warhead, operates said aiming mechanism to aim said warhead in said desired direction and then operates said launch mechanism to launch said warhead;, '(a) a plurality of WAN components, each said WAN component including(b) a WAN component deployment mechanism for deploying said plurality of WAN components in a defended area; and(c) a command center for instructing said controller of each of at least one of said WAN components to aim and launch said warhead of said each WAN component at a target that has been detected in said defended area.2. The weapon system of claim 1 , wherein said WAN component deployment mechanism includes at least one precision guided munition claim 1 , at least a portion of said plurality of WAN components being housed within each said at least one precision guided munition prior to said deployment and being released from said precision guided munition during said deployment.3. The ...

VISUAL GUIDANCE SYSTEM FOR BARREL-FIRED PROJECTILES

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel. 1. A winged guidance external frame or vehicle placed near the muzzle that is coupled to a projectile while exiting the barrel which is carried by the projectile's kinetic energy , and which is capable of maneuvering the projectile accurately using its wings and onboard electronics , wherein:the winged external frame tightly encompasses the periphery of the projectile and is carried by the projectile while the electronics onboard the winged frame guide the projectile accurately to target;the external frame has a coupling rod and the projectile has a receiver;the external frame has a receiver and the projectile has a coupling rod;the external frame has a pole to hit the ground and parachute to land the frame smoothly; andthe external frame may have an autopilot.2. The winged vehicle as claimed in claim 1 , wherein:said coupling rod is attached to said external frame; andsaid projectile comprises:a fuse or sensor attached to the nose,input port to receive commands from the computers onboard the external frame,segmented insulated command input contact points to receive command pulses from the input port and pass the external commands to the receiver,a detonator, andclaws or inflating object to grip on the receiver from the inside on penetration.3. The winged vehicle as claimed in claim 1 , wherein: said receiver may have claws to grip the coupling rod released mechanically on impact', 'said receiver may have a rolling shutter to capture the coupling rod on penetration', 'said the receiver has contact points to receive the external commands pulses ...

Area denial communication latency compensation

An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.

Aircraft control device, aircraft, and method for computing aircraft trajectory

An aircraft control device calculates trajectories of multiple aircraft that is member of a flight by use of a method such as Direct Collocation with Nonlinear Programming (DCNLP), in which an optimal solution is obtained by discretizing continuous variables. Nodes indicating the trajectory are calculated and set by substituting a discretized control variable of the aircraft into an aircraft equation of motion, or by use of other methods. Instead of calculating the trajectory of the aircraft as a continuous problem, discretisation reduces the calculation amount and time required for the trajectory calculation. The aircraft control device then determines, from among trajectories satisfying constraints corresponding to the role of the aircraft, an optimal trajectory based on an evaluation value obtained by an objective function corresponding to the role. Accordingly, the aircraft control device can calculate a more optimal trajectory corresponding to the role of the aircraft in a shorter time.

Unmanned aerial vehicle

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.

Mobile ballistics processing and targeting display system

A mobile ballistics processing and targeting display system for receiving data associated with one or more ballistics variables, for processing such variables, and for displaying an intuitive targeting solution. One or more ballistics variables are inputted into a mobile computing device or are otherwise acquired by such device. Projected in-flight projectile characteristics are calculated by the computing device based upon ballistics variables. A mobile computer processing device having an image collection sensor and display mounted to an optical sight provides a user with the ability to easily view targeting solutions with reference to the sight picture viewable through the sight. The targeting solution displayed to the user is capable of continuous updating to account for changing environmental conditions affecting the calculation of a ballistics solution.

DETERMINATION OF GUIDED-MUNITION ROLL ORIENTATION

Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change. 1. A method for determination of a guided munition roll orientation , the method comprising:calculating, by a processor-based system, a ratio of a lateral acceleration vector measurement of the guided munition to a velocity of the guided munition, to generate an estimated lateral turn rate vector of the guided munition;integrating, by the processor-based system, the estimated lateral turn rate vector, over a period of time associated with flight of the guided munition, to generate a first type of predicted attitude change;obtaining, by the processor-based system, a lateral turn rate vector measurement of the guided munition;integrating, by the processor-based system, the measured lateral turn rate vector, over the period of time associated with flight of the guided munition, to generate a second type of predicted attitude change; andcalculating, by the processor-based system, a gravity direction vector based on a difference between the first type ...

Visual guidance system for barrel-fired projectiles

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

System integration

A method and apparatus for generating, in an aircraft in flight, a feasibility display indicative of the feasibility of a weapon, the method comprising: providing a performance envelope for the weapon; determining, using the performance envelope, configuration data for configuring a generic algorithm; uploading the configuration data to the aircraft; generating feasibility data N indicative of the feasibility of a weapon carried on the aircraft successfully engaging a target and/or the feasibility of a weapon carried on the target successfully engaging the aircraft; determining, on board the aircraft, using the same generic algorithm and the uploaded configuration data, one or more test criteria; performing, on board the aircraft, an assessment process including determining whether or not the feasibility data satisfies the one or more test criteria; and, based the assessment, using the feasibility data, generating the feasibility display.

Inertial navigation system

An inertial measurement system for a spinning projectile comprising: a first, roll gyro to be oriented substantially parallel to the spin axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system; a controller, arranged to: compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; calculate a roll angle error based on the difference between the computed pitch and yaw angles and expected pitch and yaw angles; provide the roll angle error as an input to a Kalman filter that outputs a roll angle correction and a roll rate scale factor correction; and apply the calculated roll angle correction and roll rate scale factor correction to the output of the roll gyro; wherein the Kalman filter models roll angle error as a function of roll rate and one or more wind variables. The system provides improved calibration of the roll axis rate gyro scale factor, e.g. of an IMU fitted to a rolling projectile. A separate process (an Euler angle filter) is used to calculate an estimate of the roll angle error without the use of the Kalman filter and is then provided as an input to the Kalman filter which can then operate in a stable manner. The filter can be configured to estimate and correct for crosswind effects which would otherwise significantly degrade performance.

SWARM NAVIGATION USING FOLLOW THE FORWARD APPROACH

The system and method of swarm navigation using a follow the forward approach. Using on-board sensors and communications links between members of a swarm, numerous targets can be engaged more quickly and precisely. In some cases, a designator is used to help a forward of the swarm navigate to a target using image-based navigation up until terminal guidance is used. A cascade of messages are projected back to a following round so that, each member of a swarm can determine a best target/round match and provide real-time, up-to-date information regarding targets' locations and each round's location, range to target, target selection, and the like. 1. A system for swarm navigation using a follow the forward approach , comprising [ provide angular bearing of a designator spot location within a target area;', 'provide angular bearings for any forward rounds; and', 'provide an optical communications link via a receiver;, 'a seeker per round configured to provide at least one of, locate and identify a plurality of targets in the target area; or', 'provide image-based navigation when correlated with the designator spot location; and, 'an imager configured to;'}, decode optical messaging from the communications link;', 'correlate the designator laser spot with imagery captured by the imager;', 'generate a target data set;', 'select a target from any currently un-selected targets within the target data set;', 'plot a trajectory for navigation to the selected target using any forward rounds as an airborne constellation; and', 'broadcast, via the optical communications link, the target data set, one or more data sets from forward rounds, and a self-data set in order to sustain a cascade., 'an on-board processor per round configured to;'}], 'a plurality of rounds, wherein the plurality of rounds comprise2. The system for swarm navigation using a follow the forward approach according to claim 1 , wherein the imagers can be visible (VIS) claim 1 , near infrared (NIR) claim 1 , ...

UNMANNED AERIAL SYSTEM TARGETING

An unmanned aerial system (UAS) includes a body and a lift and propulsion system coupled to the body. The UAS includes a weapon coupled to the body. The weapon has an aiming axis oriented in a fixed direction relative to the body. The UAS includes a control system operatively coupled to the lift and propulsion system and the weapon. The control system is configured to determine a roll angle and a flight path such that the aiming axis is directed at a target when the UAS moves according to at least a portion of the flight path at the roll angle. The control system is further configured to control the lift and propulsion system such that the UAS moves according to the at least the portion of the flight path at the roll angle. 1. An unmanned aerial system (UAS) comprising:a body;a lift and propulsion system coupled to the body;a weapon coupled to the body and having an aiming axis oriented in a fixed direction relative to the body; and determine a roll angle and a flight path such that the aiming axis is directed at a target when the UAS moves according to at least a portion of the flight path at the roll angle; and', 'control the lift and propulsion system such that the UAS moves according to the at least the portion of the flight path at the roll angle., 'a control system operatively coupled to the lift and propulsion system and the weapon, the control system configured to2. The UAS of claim 1 , wherein the control system is configured to:receive one or more indicators of one or more flight parameter guidelines;determine, based at least in part on the one or more flight parameter guidelines, parameters that the UAS is to maintain relative to the target while the UAS moves according to the at least the portion of the flight path; anddetermine the at least the portion of the flight path at least in part based on the determined parameters.3. The UAS of claim 2 , wherein the one or more flight parameter guidelines include a minimum altitude parameter guideline indicative ...

ENERGY BEAM INTERCEPTOR

Disclosed is an energy beam interceptor that includes an interceptor vehicle of either a missile or a lighter than air vehicle that carries an energy beam generator with a minimum power output of approximately 500 W, a high density power supply that power the energy beam generator, an energy beam targeting apparatus that directs emissions from the energy beam generator and an energy beam targeting controller that targets emissions from the energy beam generator with the energy beam targeting apparatus. 1. An energy beam interceptor comprising:a missile;an energy beam generator with a minimum power output of approximately 500 W, wherein the energy beam generator is mounted on the missile;a high density power supply constructed and arranged to power the energy beam generator, wherein the high density power supply is mounted on the missile;an energy beam targeting apparatus constructed and arranged to direct emissions from the energy beam generator, wherein the energy beam targeting apparatus is mounted on the missile; andan energy beam targeting controller constructed and arranged to target emissions from the energy beam generator with the energy beam targeting apparatus.2. The energy beam interceptor of claim 1 , wherein the missile has a payload capacity exceeding 300 lbs with a flight ceiling exceeding 250 claim 1 ,000 feet.3. The energy beam interceptor of claim 1 , wherein the energy beam generator has a minimum power output of approximately 3 kW.4. The energy beam interceptor of claim 1 , further comprising a sensor configured to detect external electromagnetic signals.5. The energy beam interceptor of claim 4 , wherein the sensor is selected from the group comprising: visible light sensor claim 4 , radar receiver claim 4 , laser receiver and heat sensor.6. The energy beam interceptor of claim 4 , further comprising a targeting emitter.7. The energy beam interceptor of claim 6 , wherein the targeting emitter is a radar emitter.8. The energy beam interceptor of ...

LAR DISPLAY SYSTEM AND METHOD

A Launch Acceptability Region [LAR] display system and method for a payload-releasing platform, the system being configured to be communicably coupled to a LAR computing module () configured to compute LAR data representative of a Launch Acceptability Region in respect of said platform based on a set of input parameters and predefined payload performance parameters, the system comprising: —an input module () configured to obtain or receive a first input parameter value in respect of a first of said input parameters, generate a set of second input parameter values in respect of said first of said input parameters, said second input parameter values being different to and at respective intervals from, said first input parameter value, and input said first input parameter value and said second input parameter values to said LAR computing module so as to cause said LAR computing module to compute, based on each of said first and second input parameter values, a respective LAR and output a set of LAR data, each data item of said set of LAR data being representative of a respective LAR and the input parameter value on which it is based; —an image data generation module () configured to receive said set of LAR data and generate therefrom a set of LAR image data, each data item of said set of LAR image data being representative of a respective data item of said set of LAR data; and—a display module () configured to receive said set of LAR image data and display, simultaneously, a visual representation of each LAR, wherein the relative positions in said display of said visual representations is based on their respective associated input parameter value. 1: A Launch Acceptability Region [LAR] display system for a payload-releasing platform , the system being configured to be communicably coupled to a LAR computing module configured to compute LAR data representative of a Launch Acceptability Region in respect of said platform based on a set of input parameters and predefined ...

SYSTEM FOR TRACKING A PRESUMED TARGET USING NETWORK-CONNECTED LEAD AND FOLLOWER SCOPES, AND SCOPE FOR CONFIGURED FOR USE IN THE SYSTEM

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope. 1. (canceled)2. A system for tracking a presumed target using scopes that are remotely located from each other , the presumed target having a target position , the system comprising: (i) a first plurality of measurement devices, and', (A) identify current target position data regarding a presumed target that is located by the first scope, the current target position data being identified using the plurality of measurement devices in the first scope, and', '(B) electronically communicate the current target position data regarding the presumed target identified by the first scope to a computer via an electronic network; and, '(ii) a first processor configured to], '(a) a first scope including (i) a second plurality of measurement devices, and', ["(A) identify current target position data of the second scope's current target position using the second plurality of measurement devices in the second scope;", '(B) communicate with the computer via the electronic network to receive the current target position data regarding the presumed target identified by the first scope;', '(C) calculate, using its current target position data and the current target position data received from the first scope, position movements that are required to move the second scope from its current target position to the target position of the ...

Weapon on-board velocity and range tracking

The system and method of weapon on-board range and velocity tracking using a synchronized clock and a pulse beacon on a fire control system, or the like, coupled with an on-board rear-facing detector and processor. A round or a UAS may use this system to accurately estimate range with respect to the fire control system, over time, and the round's or UAS's velocity at various times along its flight path. The system provides for smaller miss distances, and the like.

MULTIMODE UNMANNED AERIAL VEHICLE

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change. 1. An unmanned aerial vehicle (UAV) comprising:a processing unit which transitions the UAV from a first trajectory to impact a target to a second trajectory to avoid impact of the target by the UAV, wherein the transition is responsive to an indicator generated by onboard processing of the processing unit as an autonomous determination of scene change.2. The UAV of wherein the processing unit maintains a divert trajectory outside of a closed maneuver limit cone while in the first trajectory.3. The UAV of wherein the UAV transfers power from a battery of the UAV to a flight energy of the UAV in the divert trajectory claim 2 , wherein the divert trajectory transitions the UAV from the first trajectory to the second trajectory claim 2 , and wherein the UAV can achieve at least an altitude in the second trajectory as the altitude at a start of the first trajectory.4. The UAV of wherein the processing unit stores at least one of: a pre-terminal commit point and a return waypoint claim 2 , wherein the processing unit transitions the UAV to at least one of: the pre-terminal commit point and the return waypoint in response to an external command to transition the UAV from the first trajectory to the second trajectory.5. The UAV of wherein the external command causes the processing unit to transition from the first trajectory to the second trajectory claim 4 , and wherein the external command is received via an uplink receiver.6. The UAV of further comprising:one or more sensors, wherein the one or more sensors detect at least one of: a UAV position, a UAV linear velocity, a UAV rotational velocity, a UAV linear acceleration, and a UAV attitude.7. The UAV of wherein the processing unit transitions the UAV from the first trajectory to the second trajectory via the ...

HARMONIC SHUTTERED SEEKER

A dual-mode, semi-active, laser-based and passive image-based seeker for projectiles, missiles, and other ordnance that persecute targets by detecting and tracking energy scattered from targets. The disclosed embodiments use a single digital imager having a single focal plane array sensor to sense data in both the image-based and laser-based modes of operation. A shuttering technique allows the relatively low frame-rate of the digital imager to detect, decode and localize in the imager's field-of-view a known pulse repetition frequency (PRF) from a known designator in the presence of ambient light and other confusing target designators, each having a different PRF. 1. A method of detecting and decoding locking pulses having a predetermined PRF , the steps comprising:dividing a pulse interval of the predetermined PRF into a plurality of repeating subintervals;shuttering alternating ones of said plurality of repeating subintervals with an exposure;determining whether two or more received pulses are received in one of said subintervals by said shuttering step; andidentifying said one of said subintervals of said pulse interval, thereby detecting and decoding said received pulses of said one of said subintervals as having the predetermined PRF.2. The method of further comprising the step of:adjusting said shuttering step to shutter on said one of said subintervals, thereby locking on to a PRF pattern of said received pulses of said one of said subintervals as having the predetermined PRF.3. The method of further comprising the step of capturing said received pulses of said one of said subintervals.4. The method of further comprising the step of using said received pulses of said one of said subintervals to derive control information to steer an ordinance to a target.5. The method of further comprising the step of evaluating others of said subintervals to determine if a lack of pulses is present in said others of said subintervals.6. The method of further comprising the ...

DATA PROCESSING

A data processing method and apparatus, the method comprising: storing, at a first memory location in a memory, a first copy of a set of data; storing, at a second memory location in a memory, a second copy of a set of data; comparing the first copy to the second copy so as to identify, within the first copy, a pointer, the pointer being located at a first data element of the first copy, the pointer specifying a second data element of the first copy; determining an offset for the identified pointer, the offset specifying a number of data elements between the first data element and the second data element; and modifying the first copy such that the pointer within the first copy specifies the second data element using only the first data element and the offset. 1. A data processing method comprising:storing, at a first memory location in a memory, a first copy of a set of data;storing, at a second memory location in a memory, a second copy of a set of data;comparing the first copy to the second copy so as to identify, within the first copy, a pointer, the pointer being located at a first data element of the first copy, the pointer specifying a second data element of the first copy;determining an offset for the identified pointer, the offset specifying a number of data elements between the first data element and the second data element; andmodifying the first copy such that the pointer within the first copy specifies the second data element using only the first data element and the offset.2. The method according to claim 1 , the method further comprising:determining the set of data using a generic algorithm, the set of data being configuration data for the generic algorithm;uploading the modified first copy of the data set to an aircraft;determining, on board the aircraft, using the same generic algorithm and the uploaded modified first copy of the data set, a specific algorithm; andperforming, on board the aircraft, the specific algorithm.3. The method according to ...

Drone interceptor system, and methods and computer program products useful in conjunction therewith

A system operative to down a target drone having propellers deployed along a perimeter p, comprising a processor-controlled interceptor drone bearing a processor-controlled flexible elongate intercepting agent cannon and an onboard camera; and an onboard processor to receive sensed wind conditions and to a firing distance d, between interceptor and target drones, given a firing angle A, and wherein the processor is configured to track the target drone using imagery generated by the onboard camera including at least once, when said wind conditions exist, guiding the interceptor drone to a firing position whose distance from the target drone is d, and commanding the cannon to fire at firing angle A, once said firing position is achieved, thereby to use the flexible elongate intercepting agent to down target drones.

Machine to Machine Targeting Maintaining Positive Identification

A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate for a second aircraft in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.

Interactive reticle for a tactical battle management system user interface

An interactive reticle to be displayed on a user interface displayed on a touchscreen device is disclosed. The interactive reticle comprises a center portion comprising a zone for displaying data and a plurality of icons displayed around the center portion, each of the plurality of icons for executing a corresponding application upon detection of a corresponding finger gesture on a corresponding icon.

COMBAT IDENTIFICATION SERVER CORRELATION REPORT

The system and method of improving the analysis of and implementation of a combat identification (CID) server system including providing correlation reports. There are at least two forms of correlation report, namely incident report and a summation report. The summation report has two types of totals, a summary total of all interrogations, and a breakdown of totals based on the Source JU. In one example, a correlated incident would be the combination of a Lock On or Mark Point with a Weapon Release, Disengage, or Attack. 1. A method for analyzing target area information in a system comprising:at least one processor configured to receive information of at least one classification level;a database in communication with the at least one processor, the database including information about a region of interest; receiving, via the at least one processor, an interrogation from a requesting entity about the region of interest;', 'receiving, via the at least one processor, information from the database regarding situational awareness for the region of interest of the interrogation;', 'processing, via the at least one processor, the information from the database, including tagging the information, said tagging comprising an age of the information and the geographical location of one or more tracks;', 'filtering, via the at least one processor, the information based on results from the processing step to form filtered information, including whether or not a one or more track is friendly;', 'sending the filtered information to the requesting entity for use in determining a subsequent action by the requesting entity;', 'performing, via the requester, the subsequent action;', 'correlating, via the at least one processor, data regarding the filtered information and the subsequent action taken by the requesting entity to create a plurality of correlated incidents; and', 'generating, via the at least one processor, a report for use in analyzing the target area information in a ...

DEVICES WITH NETWORK-CONNECTED SCOPES FOR ALLOWING A TARGET TO BE SIMULTANEOUSLY TRACKED BY MULTIPLE DEVICES

A network of scopes, including one or more lead scopes and one or more follower scopes, is provided to allow scope operators of the respective scopes to track the same presumed target. A lead scope locates a target and communicates target position data of the presumed target to the follower scope. The follower scope uses the target position data and its own position data to electronically generate indicators for use to prompt the operator of the follower scope to make position movements so as to re-position the follower scope from its current target position to move towards the target position defined by the target position data received from the lead scope. 1. (canceled)2. A scope configured to be a lead scope or a follower scope , the scope comprising:(a) a plurality of measurement devices configured to collect data that is necessary to identify current target position data for a presumed target that is located by an operator of the scope; (i) electronically communicate current target position data of the presumed target identified by the operator of the scope to an electronic network for sending via the electronic network to a follower scope when the scope is configured to act as a lead scope, and', '(ii) receive via the electronic network current target position data of a presumed target that was previously identified by a lead scope and communicated to the electronic network when the scope is configured to act as a follower scope; and, '(b) a network interface configured to (i) calculate the current target position data of the scope from the data collected by the plurality of measurement devices,', '(ii) calculate, using the current target position data of the scope and the current target position data received from the lead scope, position movements that are required to move the scope from its current target position to the target position of the presumed target identified by the lead scope, and', '(iii) output electronically generated indicators for use by ...

System And Method For Identifying And Mitigating A Threat In A Facility

A system for mitigating a threat in a facility according to the present disclosure includes a threat identification module and at least one group of drones. The threat identification module is configured to generate a threat identification signal indicating that the threat has been identified in the facility and transmit the threat identification signal to a central command center. The at least one group of drones is configured to move toward the threat in response to at least one of the threat identification signal and a command from the central command center. 1. A system for mitigating a threat in a facility , the system comprising: generate a threat identification signal indicating that the threat has been identified in the facility; and', 'transmit the threat identification signal to a central command center; and, 'a threat identification module configured toat least one group of drones positioned within the facility and configured to move toward the threat in response to at least one of the threat identification signal and a command from the central command center.2. The system of further comprising a gunshot detection module configured to detect a gunshot in the facility claim 1 , wherein the threat identification module is configured to generate the threat identification signal when the gunshot is detected.3. The system of claim 1 , further comprising a silent alarm operable to output a signal indicative of a trespasser claim 1 , wherein the threat identification module is configured to generate the threat identification signal when in receipt of the signal from the silent alarm.4. The system of wherein the threat identification module is configured to generate the threat identification signal when in receipt of a signal that an emergency call is made from the facility.5. The system of further comprising a microphone located in the facility claim 1 , wherein the threat identification module is configured to generate the threat identification signal when the ...

SYSTEM AND METHOD FOR INTERCEPTION AND COUNTERING UNMANNED AERIAL VEHICLES (UAVS)

Systems, devices, and methods for identifying a target aerial vehicle, deploying an interceptor aerial vehicle comprising at least one effector, maneuvering the interceptor aerial vehicle to a position to engage a target aerial vehicle, deploying the at least one effector to intercept the target aerial vehicle, and confirming that the target aerial vehicle has been intercepted. 1. A method comprising:deploying an interceptor aerial vehicle comprising at least one effector;maneuvering the interceptor aerial vehicle to a position to engage a target aerial vehicle; anddeploying the at least one effector to intercept the target aerial vehicle.2. The method of further comprising:identifying the target aerial vehicle.3. The method of further comprising:confirming that the target aerial vehicle has been intercepted.4. The method of wherein confirming that the target aerial vehicle has been intercepted further comprises:determining a capture of the target aerial vehicle in the effector based on a change in position of the interceptor aerial vehicle, wherein the effector is connected to the interceptor aerial vehicle via a tether; andproviding, via a ground control system (GCS) in communication with the interceptor aerial vehicle, at least one of: a visual indication, an audible indication, and a haptic feedback.5. The method of further comprising:selecting, via a ground control system (GCS) in communication with the interceptor aerial vehicle, the target aerial vehicle; andtracking the selected target aerial vehicle.6. The method of wherein selecting the target aerial vehicle further comprises:receiving, at the GCS, a video feed from a camera of the interceptor aerial vehicle;displaying, via a display of the GCS, the video feed containing the target aerial vehicle; andselecting, via a user interface of the GCS, the target aerial vehicle in the video feed.7. The method of wherein tracking the selected target aerial vehicle further comprises:maneuvering, via the GCS, the ...

PAYLOAD DELIVERY

Disclosed is a method for delivering a load on-board an aircraft to a target. The method comprises: acquiring a position of the target; acquiring parameter values relating to aircraft manoeuvrability; acquiring load properties; acquiring parameter values relating to environmental conditions; using the acquired information, determining a position and a velocity value; performing, by the aircraft, the procedure; and, at a point in the procedure that the aircraft has the determined position and its travelling at a velocity equal to the determined velocity value, releasing the load. The determined position and velocity value are such that, were the aircraft to release the load whilst having the determined position and velocity, the load would travel to be within a predetermined distance of the target. The procedure is such that the aircraft would have the determined position and velocity at some time-step. 1. A method for delivering a load to a target , the load being releasably attached to an unmanned aircraft , the method comprising:{'b': '8', 'acquiring, by one or more processors, a position of the target on the ground ();'}acquiring, by the one or more processors, parameter values relating to manoeuvrability of the aircraft;acquiring, by the one or more processors, one or more properties of the load;acquiring, by the one or more processors, parameter values relating to environmental conditions in which the aircraft is flying;using the acquired target position, the acquired load properties, and the acquired parameter values relating to the environmental conditions, determining, by the one or more processors, a position for the aircraft and a value of a velocity for the aircraft;using the determined position and velocity value, determining, by the one or more processors, a procedure for the aircraft;performing, by the aircraft, the determined procedure; andat a point in the procedure that the aircraft has the determined position and a velocity equal to the determined ...

Projectiles Specialized for DNA and Other Trace Evidence Collection

New projectiles specialized for creating and recovering trace evidence at a crime scene are provided. A wide variety of embodiments are provided, covering several use scenarios—including, but not limited to, home security devices, which may be built into an entryway or other building structure, and law enforcement guns. In some embodiments, a projectile within a projectile is provided, which fires in the direction of a primary impact. A sampler device is provided within some projectiles, which may comprise tracing barbs, containers for analytes and even a hypodermic extraction apparatus. In some embodiments, projectiles have rebounding devices, which may overlap with aspects of the sampler device, for developing distance from a criminal suspect. Other aspects, such as GPS, fasteners and defense mechanisms, are also disclosed, which encourage recovery by the authorized user and deter interception.

AREA DENIAL COMMUNICATION LATENCY COMPENSATION

An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition. 1. A method for communication latency compensation in an area denial system , the area denial system including a plurality of munitions defining an obstacle field , one or more sensor devices , and a command and control unit , networked together , via one or more gateway devices , in an area denial network having a command and control latency for communication between the command and control unit and a remainder of the area denial system , the method comprising:notifying one or more human operators, via the command control unit, of one or more recommended munitions for engaging a target based on a first target position detected by the one or more sensor devices, the notification subject to a data latency between the command control unit and the one or more gateway devices;receiving, from at least one of the one or more human operators via the command and control unit, authorization to fire one or more munitions of the plurality of munitions, the authorization received subject to the data latency between the command and control unit and the one or more gateway devices,determining a second target ...

Networked battle system or firearm

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

AUGMENTED REALITY VISUALIZATION SYSTEM

An augmented reality (AR) system comprising a head mounted display (HMD) configured to display one or more AR visualizations within an operator's field of view (FOV), a control system including a processor and a storage system configured to store machine readable instructions, sensors configured to determine at least location and/or orientation of said sensors including a head mounted and device mounted sensor, and a communication system configured to communicate data between elements of the AR system. The software including various subroutines or machine readable instructions including an orientation/location instructions for determining orientation and/or position of the sensors, a visualizations generation instructions section configured to generate a visualization showing an aim point of a device coupled to said device mounted sensor, a path of travel of a projectile launched from said device, or an impact point of said projectile. Embodiments can include one or more photogrammetry processing sections. 1a head mounted display (HMD) comprising a visual display system and a head mounting structure adapted to fix the HMD with respect to a human operator's field of view (FOV), and a camera system oriented towards said FOV configured to capture a plurality of video images of entities or objects within the FOV;a plurality of sensors comprising a head mounted position sensor and a first position sensor receiver positioned on a first device, said plurality of sensors comprising one or more internal navigation units (INU) or an internal measuring unit (IMU), said INU comprising a plurality of accelerometers, said IMU comprising an INU and a global position system (GPS) configured to determine a location of the GPS system, wherein said INU and IMU are configured to determine an orientation of at least a first device each said sensor is coupled with and output of said location as an orientation data;a control system comprising a storage medium comprising a plurality of ...

Firearm Electronic System

Man portable weapons include integrated electronics that calculate orientation and movement in addition to providing that data to a user's heads-up displays (HUD) as well as to group and area networks. By passing data to a HUD, the user is able to see, virtually, the flight path, point of impact and other ballistic data as well as data representing the condition and performance of the weapon for any rounds fired. The HUD also displays the relative position of other members of the team, last known enemy area of operation and other useful parameters from the man portable weapons of the other team members through the network. The electronics may be integrated within the main components of any suitable man portable weapon in a non-intrusive way as to have no effect on the firing mechanism of the small arm when it is fully assembled.

AREA DENIAL COMMUNICATION LATENCY COMPENSATION

An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition. 1. A method for communication latency compensation in an area denial system , the area denial system including a plurality of munitions and a command and control unit networked together in an area denial network having a command and control latency for communication between the command and control unit and the remainder of the area denial system , the method comprising:receiving, from at least one or more human operators, authorization to fire one or more munitions of the plurality of munitions, the authorization transmitted from the command and control unit via the area denial network;determining, subsequent to transmission of the authorization to fire one or more munitions, a target position relative to the obstacle field; anddetermining that the target position is outside of a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.2. The method of claim 1 , further comprising:determining one or more recommended munitions of a plurality of munitions and notifying, using the command and control ...

Method and device for security in public places

Security system for public places controlled remotely, manually and by a computer program, using cameras and various weapons. Using amongst other methods of crisis identification; facial recognition, behavior recognition and sound recognition. Methods to neutralize the danger of suspect attackers. Useable in public buildings, at public gatherings, on public transport and the like.

대방사 유도무기용 탐색기

대방사 유도무기용 탐색기를 공개한다. 본 발명은 대방사 유도무기의 관형의 동체 측면 둘레에 배치되는 복수개의 측면 안테나 및 복수개의 측면 안테나에서 감지한 전파신호를 인가받아, 전파신호와 복수개의 측면 안테나 중 전파신호를 수신한 측면 안테나가 배치된 방향을 분석하여 표적의 위치를 판별하는 수신기를 포함한다.

Vehicle intercept system and method using w-band

W 대역 신호를 이용한 차량 요격 시스템 및 방법을 공개한다. 본 발명은 유도 명령에 응답하여 기지정된 기준 고도로 비행하면서 지상 방향으로 기지정된 기준 각도로 W 대역의 FMCW 형태의 신호를 방사 신호로 푸쉬브룸 스캔 방식으로 방사하고, 방사 신호가 반사되어 수신된 수신 신호를 분석하여, 표적인 차량을 탐색하며, 표적이 탐지되면 유도 명령과 무관하게 기설정된 펄스 폭과 반복 주기를 갖는 펄스 반복 주파수 신호를 방사 신호로 방사하는 모노펄스 탐지 추적 방식으로 표적을 추적하여 요격하는 유도 무기 및 유도 무기를 발사하고, 발사된 유도 무기가 표적이 위치하는 방향으로 이동 하도록 유도 명령을 전송하는 발사체를 포함한다. Discloses a vehicle intercept system and method using a W-band signal. In accordance with the present invention, the FMCW-shaped signal of the W band is radiated in the pushbroom scan mode as a radiated signal at a predetermined reference angle in the ground direction while flying at a predetermined reference altitude in response to an inductive command, A monopulse detection tracking method that detects a target vehicle and radiates a pulse repetition frequency signal having a predetermined pulse width and repetition period as a radiation signal irrespective of an induction command when a target is detected, And a launch vehicle that transmits an instruction to cause the guided weapon to be fired to move in the direction in which the target is located.

Guidance system and method for guided weapon using inertial navigation

유도 무기 유도 시스템 및 방법을 공개한다. 본 발명은 이동하는 자신의 위치를 관성 항법을 이용하여 판별하고, 표적을 탐색하여 표적의 상대 위치를 획득하며, 판별된 자기 위치와 표적의 상대 위치를 이용하여 표적 위치 정보를 생성하며, 생성된 표적 위치 정보를 송신하는 이동 발사체 및 이동 발사체에 장착되어 발사되며, 직접 표적을 탐지할 때까지, 이동 발사체에서 전송되는 표적 위치 정보와 이동 발사체의 자기 위치를 기초로 관성 항법을 이용하여 판별되는 현재 위치에 따라 표적을 추적하는 적어도 하나의 유도 무기를 포함한다. Discloses an induction weapon induction system and method. The present invention distinguishes a moving position of the user using inertial navigation, acquires a relative position of a target by searching for a target, generates target position information using the determined relative position of the target and the target, The present invention relates to a method and apparatus for detecting a target, which is mounted on a mobile launch vehicle for transmitting target position information and a mobile launch vehicle, And at least one guided weapon that tracks the target according to its location.

Method for determining of firing window throgh firing range simulation

A method for determining a firing range of a marksman through a firing range simulation is disclosed. According to one embodiment of the present invention, the method for determining a firing range comprises: a step of setting a target position for each range with respect to a guided weapon and generating a temporary target in a temporary target generating range of the set target position; a step of calculating an angle of fire where the guided weapon can reach the generated temporary target; a step of applying the calculated angle of fire to be guided to the target and collecting a guidance success angle group where guidance is succeed; and a step of determining a firing range for each range based on the collected guidance success angle group.

Deployment control system

Deployment control system comprises a weapon usage monitoring system for obtaining data of weapon usage, an aggregation system for aggregating usage of individual weapons to a predetermined level, and a presentation system for presentation of said weapon usage individually or at the predetermined level.

Fuze system for the height of burst automatically varing and control method thereof

본 발명의 일 실시예에 따르는 신관 시스템은 탄이 발사되면, 신관 내의 발사감지센서가 동작하면서 제어회로부에 발사시점 정보를 전송하는 단계와, 발사시점 정보가 수신되면 제어회로부가 비행시간을 카운트하도록 시한장치를 동작시키고, 비행고도를 측정하는 단계와, 측정된 비행고도와 비행시간으로부터 고도변화율을 구하고, 고도변화율로부터 탄의 사거리를 연산하는 단계와, 연산된 사거리에 근거하여 탄의 하강여부를 판단하고, 탄의 하강시 고도측정구간을 설정하는 단계 및 상기 고도측정구간에 탄이 도달하면 측정된 비행고도들로부터 최종 사거리를 결정하고, 상기 최종 사거리와 메모리에 저장된 사표 자료를 근거로 탄의 폭발고도를 결정하는 단계를 포함한다.

AI based precisely striking system

본 발명은 전투 또는 교전 시 타격의 효과를 극대화하기 위해 영상정보와 인공지능기술을 이용하여 표적의 인근(종말단계 등)에서 사전에 선정한 표적의 핵심 또는 취약개소를 정밀 추출하고, 미사일, 로켓, 드론 등 비행물체를 해당 위치로 유도하여 타격 또는 추적할 수 있는 기술과 그 운용방법에 관한 것이다. The present invention precisely extracts the core or vulnerable point of a target selected in advance from the vicinity of the target (end stage, etc.) using image information and artificial intelligence technology in order to maximize the effect of strike during battle or engagement, missiles, rockets, It relates to a technology that can strike or track a flying object, such as a drone, by guiding it to a specific location, and a method for operating the same.

Firing control system and operation method of the same

According to an embodiment of the present invention, a firing control system comprises: at least one ammunition each having a corresponding identifier; a shooting device for firing the at least one ammunition toward a target according to a shooting angle and a shooting direction; and a fire control device for controlling the at least one ammunition and the shooting device. After the at least one ammunition is fired, the fire control device receives the identifier from the at least one ammunition through a wireless network, and transmits target information corresponding to the identifier to the at least one ammunition through the wireless network.

Aircraft virtual image display system and method for providing a real-time perspective threat coverage display

A virtual image display system for aircraft is operative to identify threat systems that are proximal the flight path of an aircraft when the aircraft is within the threat range of such threat systems. The virtual image display system is further operative to generate three-dimensional threat envelopes of identified threat systems and to display real-time perspective video images of such three-dimensional threat envelopes for viewing by the pilot.

Method and device for programming a projectile

본 발명을 유도식으로 또는 용량식으로 발사체(5)를 프로그래밍하는 것에 관한 것이다. 본 발명에 따르면, 프로그래밍을 위해 도파관(2, 11)이 사용되며, 전자기장은 상기 도파관 내에서 집중된다. 사용되는 프로그래밍 유닛(1)은 예컨대 포구 브레이크(6) 전방에서 포구의 영역에 위치하고/위치하거나 통합되는 것이 바람직한 적어도 하나의 도파관(2, 11)으로 이루어진다. 전송을 위한 송신용 커플러(3)는 신호 발생장치(4)에 의해 입력을 받는다. 발사체(5)와 관련된 정보는 변조기(18)에서 캐리어 주파수(f1)로 변조된다. 발사체(5)에/발사체 상에 통합되는 수신용 커플러(8)는 발사체(5)에 있는 저장장치 또는 프로세서(19)에 전기적으로 상호접속된다. 상기 수신용 커플러는 변조된 신호를 수신하고 이를 프로세서(19)에 송신하는데, 이때 결과적인 프로그래밍이 이루어진다. The present invention relates to programming projectile 5 in an inductive or capacitive manner. According to the invention, waveguides 2 and 11 are used for programming and the electromagnetic field is concentrated in the waveguide. The programming unit 1 used is made up of at least one waveguide 2, 11 which is preferably positioned / integrated or integrated in the region of the port in front of the position brake 6, for example. The transmitting coupler 3 for transmission receives the input by the signal generating device 4. [ The information associated with the launch vehicle 5 is modulated at the modulator 18 to the carrier frequency f1. The receiving coupler 8 integrated on the projectile 5 / projectile is electrically interconnected to a storage device or processor 19 in the projectile 5. The receiving coupler receives the modulated signal and sends it to the processor 19, where the resulting programming takes place.

AIRCRAFT INTERCEPT SYSTEM AND METHOD USING Ka-BAND

Ka 대역 신호를 이용한 비행체 요격 시스템 및 방법을 공개한다. 본 발명은 Ka 대역의 수직 편파 신호를 송신 신호로 방사하고, 송신 신호가 반사되어 수신된 수신 신호를 수직 편파 신호와 수평 편파 신호로 구분하여 분석하여 표적의 위치를 판별하며, 판별된 표적의 위치를 표적 위치 정보로 생성하는 발사 통제 레이더, 발사 통제 레이더와 통신을 수행하여 표적 위치 정보를 인가받고, 표적 위치 정보에 따라 표적을 추적하기 위해 이동하며, 수신 신호를 직접 인가받아 수직 편파 신호와 수평 편파 신호로 구분하여 분석하여, 표적을 직접 탐색하며, 표적이 직접 탐색되면, 표적 위치 정보에 무관하게 직접 탐색된 표적의 위치를 기반으로 표적을 추적하여 요격하는 적어도 하나의 유도 무기, 및 적어도 하나의 유도 무기가 거치되고, 발사 통제 레이더의 제어에 따라 유도 무기의 발사 방향을 조절하여 발사하는 발사대를 포함한다. Discloses a flight intercept system and method using a Ka-band signal. The present invention radiates a vertically polarized signal of the Ka band as a transmission signal, discriminates the position of the target by analyzing the received signal reflected by the transmission signal and dividing the received signal into a vertical polarization signal and a horizontal polarization signal, And a launch control radar that generates the target position information, receives the target position information, moves to track the target according to the target position information, receives the received signal directly, and transmits the horizontally polarized signal and the horizontal At least one guided weapon that intercepts and tracks the target based on the location of the directly detected target regardless of the target location information when the target is directly searched, Of the guided weapons are mounted and controlled by the launch control radar, It includes.

Semi-active aircraft intercept system and method

반능동 비행체 요격 시스템 및 방법을 공개한다. 본 발명은 표적을 탐지하기 위한 방사 신호를 방사하고, 방사 신호가 표적에 반사되어 수신된 수신 신호를 분석하여 표적의 위치를 판별하며, 판별된 표적의 위치를 표적 위치 정보로 생성하는 발사 통제 레이더, 및 발사 통제 레이더와 통신을 수행하여 표적 위치 정보를 인가받고, 표적 위치 정보에 따라 표적을 추적하기 위해 이동하며, 방사 신호가 표적에 반사된 신호를 각각 전방 신호로서 수신하는 복수개의 전면 안테나와 발사 통제 레이더에서 방사된 방사 신호를 직접 후방 신호로서 수신하는 적어도 하나의 후면 안테나를 구비하고, 복수개의 전방 신호 각각과 후방 신호를 합성하여 주파수 하향 변환하고, 주파수 하향 변환된 복수개의 전방 신호를 분석하여 표적의 위치를 판별하는 유도 무기를 포함한다. Discloses an anti-active vehicle intercept system and method. The present invention relates to a radar system for radiating a radar signal for detecting a target, for analyzing a received signal reflected by the target and for receiving the radar signal, for determining a position of the target, and for generating a position of the identified target as target position information, And a plurality of front antennas for receiving the target position information by performing communication with the launch control radar, moving to track the target according to the target position information, and receiving the signals reflected from the target as front signals, And at least one rear antenna for directly receiving a radiated signal radiated from the launch control radar as a backward signal, synthesizing a plurality of front signals and a rear signal, downconverting the frequency, and analyzing a plurality of frequency downconverted front signals And a guided weapon to determine the position of the target.

Method and apparatus for removing navigational hazards in water

Guided weapon, guided weapon system, and method of identifying and tracking target

A guided weapon, a guided weapon system, and a method of identifying and tracking a target, which can more accurately and rapidly identify a target, may be disclosed. According to an embodiment of the present invention, the guided weapon system comprises: a guided weapon which acquires an image signal corresponding to an image of an object including a target in real time, and which identifies and tracks the target by applying a high-speed target identification algorithm and a target tracking algorithm to the image signal; and a launch control device which is connected to the guided weapon, which receives the image signal from the guided weapon, which applies a precision target identification algorithm to the image signal to generate precise target identification result information, and which transmits the precise target identification result information to the guided weapon. The guided weapon may derive a final target identification result based on the target identification result information and the precise target identification result information by the high-speed target identification algorithm.

Networked battle system or firearm

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

Networked battle system or firearm

A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment.

Networked battle system or firearm

A networked battle system includes a communication network, a first rifle that includes at least one accessory coupled thereto that determines a bearing of the first rifle and a communication element allowing the at least one accessory to provide bearing information to the communication network. The system also includes a battle management system in communication with the first rifle through the communication network that receives the bearing information from the accessory and updates a battle plan based on the bearing information to form an updated battle plan.

APPARATUS AND METHOD OF SOFTWARE VERIFICATION FOR GUIDANCE CONTROL UNIT USING ClOSED-LOOP SIMULATION

본 발명은 폐루프 시뮬레이션을 이용한 유도조종장치용 소프트웨어 검증 장치 및 그 방법에 관한 것으로, 본 발명의 일실시예에 따른 폐루프 시뮬레이션을 이용한 유도조종장치용 소프트웨어 검증 장치는, 소프트웨어 검증용 표적 및 탄에 대한 초기값이 입력되는 초기값 입력부; 상기 표적 및 탄에 대한 초기값과 구동장치 모델부의 현재상태를 바탕으로 상기 탄에 대한 운동을 예측하여 검증 입력 데이터를 산출하기 위한 데이터 생성부; 상기 검증 입력 데이터를 이용하여 상기 탄을 표적으로 유도하기 위한 조종 데이터를 생성하기 위한 유도조종장치 모델부; 상기 유도조종장치 모델부와 유도조종장치로부터 각각 전달된 비행시간에 따른 결과데이터를 상호 비교하기 위한 소프트웨어 검증부; 및 상기 데이터 생성부, 상기 유도조종장치 모델부, 상기 구동장치 모델부의 비행시작 시점을 지연시키는 비행 천이 제어부;를 포함하며, 상기 유도조종장치는, 상기 데이터 생성부로부터 상기 검증 입력 데이터를 전달받아 비행시간에 따른 결과데이터를 출력한다.

Guidance method of the managed ammunition

FIELD: weapons. SUBSTANCE: invention relates to weapons, in particular, to systems of fire destruction of objects with controlled ammunition. Essence of the method for directing a guided munition is to highlight the region of the underlying surface with directed optical radiation in accordance with known target coordinates, detection, capture and homing of a homing ammunition along the reflected optical radiation from the area of illumination of the underlying surface, at least two regions of the illumination of the underlying surface are selected, symmetrical with respect to the target coordinates and are in the field of view of homing ammunition, illumination of selected areas of the underlying surface is carried out with a period, smaller than the time constant for the accumulation of a homing ammunition receiver. EFFECT: technical result is a decrease in the probability of counteracting ammunition sent to the target designation. 1 cl, 2 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 660 777 C1 (51) МПК F41G 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F41G 9/002 (2006.01) (21)(22) Заявка: 2017110330, 28.03.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: 09.07.2018 (45) Опубликовано: 09.07.2018 Бюл. № 19 2 6 6 0 7 7 7 R U (56) Список документов, цитированных в отчете о поиске: RU 2256871 C1, 20.07.2005. RU 2529828 C1, 27.09.2014. RU 2293942 C2, 20.02.2007. US 4407465 A, 04.10.1983. JP 08094293 A, 12.04.1996. (54) СПОСОБ НАВЕДЕНИЯ УПРАВЛЯЕМОГО БОЕПРИПАСА (57) Реферат: Изобретение относится к вооружению, в выбирают по меньшей мере две области подсвета частности к системам огневого поражения подстилающей поверхности, симметричные объектов управляемыми боеприпасами. Сущность относительно координат цели и находящиеся в способа наведения управляемого боеприпаса поле зрения самонаводящегося боеприпаса, заключается в подсвете области подстилающей осуществляют подсвет выбранных ...

Navigation apparatus for projectiles and control method thereof

The present invention provides a navigation apparatus for a projectile and a control method thereof, the navigation apparatus installed on the projectile and generating navigation information related to a flight of the projectile. The method for controlling the navigation apparatus installed on the projectile comprises: a step of receiving global positioning system (GPS) information on the projectile from a GPS reception part, receiving angle speed information on the projectile from an angle speed sensor, and receiving acceleration information on the projectile from an acceleration sensor part; a step of generating inertia navigation data using the GPS information, the angle speed information, and the acceleration information; and a step of fusing satellite navigation data corresponding to the GPS information into the generated inertia navigation data to calculate at least one of a position, a posture, and a speed of the projectile. The step of generating the inertia navigation data includes a step of determining an initial posture of the projectile using the GPS information and the angle speed information and a step of generating the inertia navigation data based on the initial posture.

SHIP INTERCEPT SYSTEM AND METHOD USING Ka-BAND

Ka 대역 모노펄스 신호를 이용한 선박 요격 시스템 및 방법을 공개한다. 본 발명은 유도 명령을 인가받아, 유도 명령에 대응하는 이동 경로를 따라 표적인 선박 방향으로 이동하고, Ka 대역의 수직 편파 신호를 방사 신호로 방사하고, 방사 신호가 반사되어 수신된 수신 신호를 수직 편파 신호와 수평 편파 신호로 분리 및 분석하여 표적을 직접 탐색하며, 표적이 탐지되면 유도 명령과 무관하게 직접 탐지된 표적의 위치를 추적하여 요격하는 적어도 하나의 유도 무기 및 적어도 하나의 유도 무기와 별도로 표적을 탐색하고, 표적이 탐지되면, 적어도 하나의 유도 무기로 발사 명령을 인가하며, 탐지된 표적의 위치로 발사된 유도 무기가 이동하도록 유도 명령을 생성하여 전송하는 발사체를 포함한다.

Method of confirming interrogation and reply for targetidentification

A question/response checking method for recognizing a target is provided to quickly and accurately draw results from question/response recognition when a question/response checking system is interlocked with a distance measurer. A question/response checking method for recognizing a target comprises the steps for obtaining information about distance to the target from a distance measurer(110) according to commands to check question/response; producing modulated signals and question signals at a question/response checking device(120) and transmitting the question signals to the target; detecting distance about the target out of response signals about the question signals; and comparing the measured distance with the distance detected from the response signals and thereby recognizing the target. The distance measurement uses regression delay time for returning after transmitting the question signals.

Apparatus and method for controlling flight motion simulator

본 발명은 비행자세 모의기 제어 장치 및 방법에 관한 것이다. 이를 위한 본 발명의 비행자세 모의기와, 현재 탄의 상태와 입력된 관성측정장치 및 탐색기 정보를 이용하여 유도탄의 제어명령을 생성하는 유도조종장치를 이용한 모의 비행시험(HILS)에서의 비행자세 모의기 제어 장치로서, 비행자세 모의기에는 t n 시점의 각속도를 포함하는 정보를 출력하는 관성측정장치 및 표적을 탐지하여 시선각 또는 시선각 변화율을 포함하는 정보를 출력하는 탐색기가 포함되고, 비행자세 모의기 제어 장치는, 비행자세 모의기로부터 측정된 자세 정보(자세, 각속도, 각가속도)를 수집하고, 수집한 정보에 대해 분석한 결과를 이용하여 유도조종장치의 입력데이터 흐름조절과 입력된 탄의 자세와 시선각을 이용하여 자세 모의기를 제어하는 관찰/제어부; 비행자세 모의기에 탑재된 관성측정장치의 동작을 모의하는 관성측정장치 소프트웨어 모델; 비행자세 모의기에 탑재된 탐색기의 동작을 모의하는 탐색기 소프트웨어 모델; 및 관찰/제어부에서 출력된 설정 정보에 따라 관성측정장치 소프트웨어 모델 및 탐색기 소프트웨어 모델에서 출력된 모의 정보와, 비행자세 모의기에 탑재된 탐색기 및 관성측정장치에서 출력된 정보 중 하나를 유도조종장치로 전달하는 데이터 흐름 제어부를 포함하는 것을 특징으로 한다. The present invention relates to an apparatus and a method for controlling a flight attitude simulator. For this purpose, the flight attitude simulator of the present invention and the flight attitude simulator (HILS) using the induction steering system that generates the control command of the missile using the current state of the shot, the input inertial measurement device, The control device includes an inertia measuring device for outputting information including an angular velocity at time t n and a searcher for detecting a target and outputting information including a gaze angle or a gaze angle change rate, The control unit collects attitude information (posture, angular velocity, and angular acceleration) measured from the flight attitude simulator and analyzes the input data flow of the induction control apparatus using the result of analyzing the collected information, And an observation / control unit for controlling the attitude simulator using the gaze angle; Inertial measurement device software model simulating the operation of an inertial measurement device mounted on a flight attitude simulator; An explorer software model simulating the behavior of the navigator mounted on the flight attitude simulator; And one of the information output from the inertial measurement device software model and the explorer software ...

Method for combination of guiding aircraft

FIELD: aviation; guidance systems. SUBSTANCE: invention is intended for interception of aerial object at large distances, including intensive maneuvering one. For this purpose, combined guidance of AC is implemented at operation of information-computer system (ICS) in three modes: target designation, radio command guidance (RCG) and homing. At that, all-sector intercept of aerial object is ensured irrespective of operating mode, and ICS operation algorithms are robust to change of modes. For this used optimal algorithms for AC control in modes of remote guidance and homing, synthesised based on use of system analysis and methods of automatic control theory, AC guidance systems theory, evaluation theory, optimum control stochastic theory, mathematical apparatus for solving differential equations, vector analysis and matrix algebra principles. EFFECT: broader functional capabilities. 1 cl, 6 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 586 399 C2 (51) МПК F41G 9/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2014144659/28, 05.11.2014 (24) Дата начала отсчета срока действия патента: 05.11.2014 (43) Дата публикации заявки: 27.05.2016 Бюл. № 15 2 5 8 6 3 9 9 Адрес для переписки: 214027, г. Смоленск, ул. Котовского, 2, ВАВПВО ВС РФ (54) СПОСОБ КОМБИНИРОВАННОГО НАВЕДЕНИЯ ЛЕТАТЕЛЬНОГО АППАРАТА (57) Реферат: Изобретение относится к системам наведения независимо от режима работы, а алгоритмы летательных аппаратов (ЛА) на воздушный функционирования ИВС робастны к смене объект и предназначено для перехвата режимов. Для этого использованы оптимальные воздушного объекта на больших дальностях, в алгоритмы траекторного управления ЛА в том числе интенсивно маневрирующего. режимах теле- и самонаведения, синтезированные Технический результат расширение на основе применения системного анализа и функциональных возможностей. Для этого методов теории автоматического управления, комбинированное наведение ЛА реализуется ...

Multimode unmanned aerial vehicle

시스템은 업링크 신호(451) 및/또는 장면 변화의 자발적인 결정에 응답하여, 터미널 호밍 모드(510)로부터 타겟 서치 모드(530)로 트랜지션되도록 구성된 무인 항공기(UAV)(100)를 포함한다.

Method for hitting rate, apparatus for hitting rate and surface vehicle

The present invention relates to a hit evaluation method, a hit evaluation apparatus, and a surface vehicle. The method for evaluating whether an armament fired at a moving target is hit comprises the following processes of: firing the armament towards a target and tracking the target; preliminarily judging whether or not the armament hits with tracking data generated by the armament while tracking the target; and re-firing the armament before a predicted hit point of the armament according to a preliminary determination result.

Appratus and method for selecting an navigator and inertial measurement unit through performance-based probability analysis

The present invention relates to an apparatus for selecting a navigator and an inertial measurement unit (IMU) through a performance-based probability analysis and a method thereof. According to the present invention, the apparatus for selecting the navigator and the IMU through the performance-based probability analysis comprises: a reference trajectory generation unit which generates a reference trajectory based on the reference navigation information of an inertial navigation system (INS) applied to guided weapon system and the reference inertia information of the IMU; an inertial measurement error generation unit which generates an inertial measurement error based on error performance indicators of the IMU; an inertial navigation error generation unit which generates an inertial navigation error based on the generated reference trajectory and the inertial measurement error; a target capture determination algorithm execution unit which performs a target capture or non-capture determination algorithm by considering the field of view (FOV) of the navigator applied to the guided weapon system based on the generated inertial navigation error; and a simulation execution unit which performs a simulation based on the results of execution of the target capture or non-capture determination algorithm. The present invention aims to provide the apparatus for selecting the navigator and the IMU through the performance-based probability analysis and the method thereof, which are able to select an IMU with high reliability and precision.

Multimode unmanned aerial vehicle

시스템은 업링크 신호(451) 및/또는 장면 변화의 자발적인 결정에 응답하여, 터미널 호밍 모드(510)로부터 타겟 서치 모드(530)로 트랜지션되도록 구성된 무인 항공기(UAV)(100)를 포함한다. The system includes an unmanned aerial vehicle (UAV) 100 configured to transition from a terminal homing mode 510 to a target search mode 530 in response to an uplink signal 451 and/or a voluntary determination of a scene change.

Systems and Methods for Interception and Countering Unmanned Aerial Vehicles (UAVs)

본 발명은 표적 항공기(104)를 식별하고(302), 적어도 하나의 이펙터(134)를 포함하는 인터셉터 항공기(102)를 전개하고(304), 인터셉터 항공기를 표적항공와 체결하기 위한로 기동하고(306), 적어도 하나의 이펙터를 전개하여 표적 항공기를 인터셉트하고(312), 표적 항공기가 인터셉트되었다는 것을 확인하는(314) 시스템, 장치, 및 방법에 관한 것이다.

Method for operating a networked military system

Die vorliegende Erfindung betrifft ein Verfahren zum Betrieb eines vernetzten militärischen Verbands mit mindestens zwei mit Sensoren (14) ausgestatteten Einsatzfahrzeugen (1, 2), wobei von mindestens einem ersten Einsatzfahrzeug (1) auf Sensordaten mindestens eines Sensors (14) eines zweiten Einsatzfahrzeugs (2) zugegriffen und der mindestens einen Sensor (14) des zweiten Einsatzfahrzeugs (2) von mindestens einem ersten Einsatzfahrzeug (1) aus fernbedient wird. The present invention relates to a method for operating a networked military unit with at least two emergency vehicles (1, 2) equipped with sensors (14) ) and the at least one sensor (14) of the second emergency vehicle (2) is remote-controlled from at least one first emergency vehicle (1).

In-flight Impact Angle Determination Apparatus for Biased Proportional Navigation Guidance, Method thereof, and Computer readable storage having the same method

The present invention relates to a flight vehicle navigation technique and, more specifically, relates to an in-flight target impact angle determination apparatus for biased proportional navigation guidance and a method thereof. According to the present invention, an in-flight target impact angle generated by relative geometry changed in launching time and hitting time.

Fixing apparatus for tail wing of guidee missile

본 발명의 유도탄용 꼬리날개 고정장치는, 화약 폭발 시 발생되는 폭발력을 이용하지 않고 화약 연소 시 발생되는 고압을 이용하여 분리뭉치(50)를 분리하면서 유도탄 꼬리날개와 연결된 와이어로프(36)를 분리할 수 있는 구조이기 때문에 폭발 충격파와 파편이 발생되지 않으므로 주변의 전자장비나 민감한 센서류를 안전하게 보호할 수 있음과 동시에 작업자 및 주변 구조물을 안전하게 보호할 수 있는 장점이 있다. The tail wing fixing device of the present invention separates the wire bundle 50 connected to the tailgate tail wing while separating the wire bundle 50 using the high pressure generated during the explosion of the powder without using the explosive force generated when the explosive explosion occurs Since explosive shock waves and debris do not occur, it is possible to safely protect surrounding electronic equipment and sensitive sensors while safely protecting workers and surrounding structures.

Operator gun fire control apparatus and method by ship posture compensation in emergency

비상시 자함 자세 보상에 의한 운용자 함포 사격 제어 장치 및 방법이 개시된다. 수동 사격 발사 장치에 추가 설치되는 조준 설정 스위치; 상기 조준 설정 스위치로부터 조준 설정 정보를 수신하는 조준 설정 정보 수신 모듈; 상기 조준 설정 정보 수신 모듈에서 수신된 조준 설정 정보가 조준 설정인 경우, 자함 자이로 센서로부터 자함 자세 정보를 수신하는 자함 자세 정보 수신 모듈; 운용자의 수동 조준에 의해 상기 수동 사격 발사 장치에 의해 설정되는 함포의 선회각 및 고각을 수신하는 표적 조준 정보 수신 모듈; 상기 표적 조준 정보 수신 모듈에서 수신된 선회각 및 고각에 상기 자함 자세 정보 수신 모듈에서 수신된 자함 자세 정보를 실시간으로 반영하고, 실시간으로 자함 자세 정보가 반영된 선회각 및 고각을 상기 함포로 제공하는 자함 자세 반영 모듈을 구성한다.

Apparatus for providing firing window at each ranges

An apparatus for providing a firing window at each range is disclosed. According to an embodiment of the present invention, the apparatus for determining a firing window at each range comprises: a setting unit setting a target position at each range with respect to a guided weapon; a generation unit generating a temporary target in a temporary target generation range of the set target position; a calculation unit calculating the angle of fire for the guided weapon to approach the generated temporary target; a collection unit applying the calculated angle of fire to perform guidance toward the target, and collecting a guidance success angle group wherein the guidance succeeds; a determination unit determining a firing window at each range based on the collected guidance success angle group; and a display unit displaying the determined firing window at each range.

Method for providing integrity bounding of weapons

A method for providing integrity bounding of a weapon for use in weapon selection and targeting is presented. The method determines an integrity bound for the weapon, the integrity bound defining a zone around the target aim-point within which engagement must occur to meet a predetermined integrity level (i.e., a probability of engagement within an allowable engagement zone). A method of assigning weapons for engaging a target is also presented. The method includes determining an aim-point of a target and determining an alert limit for the aim-point, the alert limit comprising a zone that includes the aim-point and excludes any friendly sites. Weapon selection is then performed by selecting a weapon having an integrity bound less than or equal to the alert limit.

System for Real-Time Object Detection and Interception

A system for determining a probability of interception by an interceptor of an object to be intercepted is disclosed herein. The system includes means for propagating a kinematic state of the object to be intercepted; means for determining a plurality of probabilities of intercept; means for determining whether an intercept is feasible and creating a set of probabilities of successful intercept for each probability of intercept; and means for determining the mean and variance of probability of successful intercept based on the set of probabilities of successful intercept.

Apparatus and Method for guidance control

본 발명은 표적을 탐색하는 장치 제어부를 포함한 유도 조종 장치 및 방법을 제안한다. 본 발명에 따른 장치는 무인 비행체에 탑재되는 유도 조종 장치에 있어서, 외부의 표적을 탐색하기 위한 펄스 타입의 송신 신호를 송출하고, 상기 송신된 신호의 반사에 따른 반사 신호를 수신하며, 상기 표적의 제1 위치 정보를 계산하는 표적 탐색부; 및 상기 표적의 제1 위치 정보를 이용하여 표적의 상태를 추정하며, 상기 표적의 상태를 이용하여 상기 송신 신호의 송출 방향을 지시하고, 상기 무인 비행체에 대한 유도 조종을 수행하는 유도 조종부; 를 포함한다.

Method and device for programming a projectile

建议电感和/或电容地进行射弹（5）的编程。建议将波导管（2、11）用于编程，因为电磁场集中在波导管中。在此所使用的编程单元（1）包括至少一个波导管（2、11），其优选位于或集成在出口的区域中、例如口制退器（6）前方。用于传递的发射耦合器（3）由信号发生器（4）供给。在调制器（18）中为射弹（5）设置的信息被调制到载波频率（f 1 ）上。在射弹（5）中集成接收耦合器（8），其与射弹（5）中的存储器或处理器（19）电连接。接收耦合器接收调制信号并且将其传送给处理器（19）。然后在处理器中进行原本的编程。

Method and system for correcting for curvature in determining the trajectory of a projectile

Given a trajectory and unit pointing vectors determined based on a planar or other approximation of a shock wave from a projectile, the times that sensor elements(60, 61, 62) should have detected a shock wave based on the conical geometry of the shock wave are calculated. A difference between the calculated times and the actual times measured at the sensor elements (60, 61, 62) may be minimized by perturbing the unit vector.. The minimization may be performed by perturbing the unit vectors. When the perturbation of the unit vectors results in an acceptable difference between the calculated times and the actual times measured, an accurate trajectory of the projectile is generated from the perturbed unit pointing vectors.

Apparatus for controlling guided weapons and guided weapons system and method for controlling guided weapons

본 명세서는 유도무기제어장치, 유도무기제어시스템 및 유도무기제어방법에 관한 것으로서, 보다 구체적으로는 종래기술의 한계를 해결하기 위해, 유도무기를 통제하는 명령신호가 임의의 지연 시간으로 지연되어 유도무기에 송신되도록 함으로써, 별도의 장치 및 제어방법의 추가 없이 간단하게 명령신호 간에 발생되는 간섭현상을 방지할 수 있고, 다수의 유도무기를 동시에 운용할 수 있게 되는 유도무기제어장치, 유도무기제어시스템 및 유도무기제어방법에 관한 것이다. The present invention relates to an induction control device, an induction control system, and an induction control method. More specifically, in order to overcome the limitations of the related art, a command signal for controlling a guided weapon is delayed An induction weapon control device capable of preventing an interference phenomenon generated between command signals easily without addition of a separate device and a control method and capable of simultaneously operating a plurality of guided weapons, And a guided weapon control method.

Apparatus and method for checking hit of target using sonar in combat system

An embodiment of the present invention constructs a sonar hit evaluation system capable of confirming whether a target is hit or not through a sonar sensor signal obtained by using sonar sensor and combat system information during hit evaluation on an enemy target, comprising a multifunctional console, and a sonar hit evaluation device.

Method and apparatus for conducting torpedo fire

METHOD FOR ATTACKING A TARGET USING A SURFACE PROJECTILE, AND SURFACE PROJECTILE FOR IMPLEMENTING THE METHOD

L'invention concerne un procédé pour attaquer une cible au moyen d'un projectile de survol équipé d'un détecteur de cible pour lancer sa tête offensive, caractérisé en ce que le projectile est dirigé de manière à détecter la cible à faible altitude et en ce que lorsqu'il a détecté la cible il est pivoté sur une trajectoire montante en étant orienté par son côté arrière vers la cible de manière à lancer la tête offensive à partir de l'arrière du projectile vers la cible dans le sens contraire à celui de la trajectoire montante. Le projectile destiné à la mise en oeuvre de ce procédé comprend un détecteur avant 16, un dispositif de direction de cap 21 faisant passer la trajectoire de survol à une trajectoire montante et un capteur arrière 27 alignant l'axe du projectile sur la cible 1 en vue du mancement de la tête offensive 13. The invention relates to a method for attacking a target by means of a hover projectile equipped with a target detector to launch its offensive head, characterized in that the projectile is directed so as to detect the target at low altitude and in that when it has detected the target it is rotated on an upward trajectory while being oriented by its rear side towards the target so as to launch the offensive head from the rear of the projectile towards the target in the opposite direction to that of the upward trajectory. The projectile intended for the implementation of this method comprises a front detector 16, a heading direction device 21 passing the overflight trajectory to an upward trajectory and a rear sensor 27 aligning the axis of the projectile with the target 1 in view of the attacking header 13.

Threat evaluation method for minimizing a number of defended and threat evaluation unit

본 발명은 방호목표가 최소화되는 위협평가 방법 및 위협평가 장치에 관한 것으로, 대공화기로부터 방어해야할 거리인 기준거리가 지정되는 기준거리 설정단계와, 기준거리를 근거로 방어범위를 설정하고, 방어범위 내에 존재하는 방호목표의 정보를 근거로 방호목표의 등급을 정하고 등급이 낮은 순으로부터 최종등급까지 대표방호목표를 설정하는 탐색단계와, 대표방호목표를 위협하는 위협항적의 정보를 획득하는 측정치입수단계와, 대표방호목표에 대한 위협항적의 위협치를 산출하는 위협치 산출단계를 포함하며, 실시간 연산이 필요한 전장환경에서 다수의 위협항적과 방호목표가 있는 환경에서도 처리지연이나 데이터 유실 없이 위협평가 결과를 제공할 수 있는 효과가 있는 방호목표가 최소화되는 위협평가 방법 및 위협평가 장치를 제공한다. The present invention relates to a threat evaluation method and a threat evaluation apparatus in which a protection target is minimized, and includes a reference distance setting step in which a reference distance, which is a distance to be defended, is designated from a large firearm, a step of setting a defense range based on a reference distance, A step of setting a rating of the protection target based on the information of the existing protection target and setting a representative protection target from the lowest grade to the final grade; a step of acquiring the information of the threat warnings threatening the representative protection target; , Threats to representative defense targets, threat level calculation steps to calculate threat values, and to provide threat evaluation results without delay or data loss even in environments where there are many threat wars and protective targets in battle environments requiring real-time operation Providing a threat evaluation method and a threat evaluation apparatus in which a protection target with an effective effect is minimized All.

FIRE CONTROL DEVICE