Настройки

Укажите год
-

Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

Подробнее
-

Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

Подробнее

Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 46. Отображено 46.
09-06-2023 дата публикации

Semi-physical simulation system and simulation test method thereof

Номер: CN116243622A
Автор: ZHANG CHI, BU XIANGWEI, XU GUOGUANG, WEI KAI, PENG HAOMIN, YAO SONG, SHI SHENGQING, XU LIJIE, ZHAO YENI, ZU YUNYU, WANG CHENXI, WU KAO, LIU CHANG
Принадлежит:

The invention provides a semi-physical simulation system and a simulation test method thereof. The system comprises a personal computer, a device to be tested and a general simulation access device matched with the device to be tested. The general simulation access equipment comprises an optical fiber reflection memory interface and various peripheral interfaces, and the types of the peripheral interfaces are matched with the interface requirements of the equipment to be tested; the personal computer comprises a real-time simulation engine and simulation model software, and the real-time simulation engine software is used for operating the simulation model software and performing real-time closed-loop integration on the simulation model software and input and output data of the equipment to be tested, so that a semi-physical simulation test is realized; the personal computer and the general simulation access equipment carry out data communication based on the optical fiber reflection memory ...

Подробнее
Номер записи: 1
22-08-2023 дата публикации

Sighting device for offshore rocket and parameter determination method

Номер: CN116625165A
Автор: WANG YANAN, BU XIANGWEI, WEI KAI, PENG HAOMIN, YAO SONG, WANG YONGGANG
Принадлежит:

The invention provides an aiming device for an offshore rocket and a parameter determination method, and relates to the field of rocket light aiming equipment. The sighting device for the offshore rocket comprises an erecting arm, a launching pad and a sighting device, wherein the end part of the first end of the erecting arm is rotationally connected with the launching pad; the light aiming equipment is arranged at the second end of the erecting arm and is used for calibrating the rocket; the hydraulic rod is used for controlling the erecting arm to rotate, the first end of the hydraulic rod is fixedly connected with the erecting arm, and the second end of the hydraulic rod is fixedly connected with the launching platform; when the light aiming equipment processes the working state, the erecting arm is erected through the hydraulic rod, and when a rocket launching instruction is received, the erecting arm withdraws from the rocket through the hydraulic rod. According to the scheme, real-time ...

Подробнее
Номер записи: 2
23-05-2023 дата публикации

Temperature control system of rocket-borne flight control combination and preparation method of flexible heating device

Номер: CN116149396A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, YU JICHAO, GUO WENZHENG
Принадлежит:

The invention provides a temperature control system of a rocket-borne flight control combination and a preparation method of a flexible heating device, and relates to the technical field of temperature control of the rocket-borne flight control combination. The temperature control system of the rocket-borne flight control combination comprises a temperature acquisition module used for detecting the temperature of the rocket-borne flight control combination in real time; the flexible heating device is arranged on the rocket-borne flight control combination and used for heating the rocket-borne flight control combination; the main control module is electrically connected with the temperature acquisition module and the flexible heating device, and is used for acquiring the real-time temperature data acquired by the temperature acquisition module, comparing the real-time temperature data with preset temperature data to obtain a comparison result, and sending the comparison result to the flexible ...

Подробнее
Номер записи: 3
28-07-2023 дата публикации

Method and device for determining minimum gap of offshore dynamic thermal emission

Номер: CN116502465A
Автор: WANG YANAN, BU XIANGWEI, WEI KAI, PENG HAOMIN, YAO SONG, WANG YONGGANG
Принадлежит:

The invention relates to the technical field of offshore dynamic thermal emission, in particular to a method and a device for determining a minimum gap of offshore dynamic thermal emission. The method comprises the steps that land drift distance parameters, take-off height fitting data, launching ship motion data, supporting point initial coordinates and rocket nozzle point initial coordinates are collected; according to the land drift distance parameter, the takeoff height fitting data, the launching ship motion data, the initial coordinates of the supporting point and the initial coordinates of the rocket nozzle point, obtaining a time change function of the supporting point and a time change function of the rocket nozzle point; according to the time change function of the supporting point, the time change function of the rocket nozzle point and the motion data of the launching ship, a supporting point motion function and a rocket nozzle point motion function are established; and according ...

Подробнее
Номер записи: 4
09-05-2023 дата публикации

Energy testing system of gas pushing and punching device

Номер: CN116086678A
Автор: XING CHUNLEI, PENG HAOMIN, BU XIANGWEI, PENG WEIBIN, SONG WENFENG, WEI KAI
Принадлежит:

The invention, which belongs to the technical field of rocket thrust device testing, discloses an energy testing system for a gas thrust device, comprising a gas thrust device, a turntable, a weight, an unlocking device and a shooting cylinder with a linear shooting channel inside. The heavy object is loaded on the shooting channel; the turntable is rotationally connected with the shooting barrel; the turntable is configured to lock the heavy object on the shooting channel; the unlocking device is configured to drive the rotating disc to rotate, and the weight is adjusted to be in an unlocking state; the pushing and punching end of the air pushing and punching device abuts against the heavy object, and the air pushing and punching device is configured to push the heavy object in the unlocking state to be shot away from the shooting barrel along the shooting channel. According to the invention, instant unlocking of the heavy object can be realized, and accurate data of the pushing amount ...

Подробнее
Номер записи: 5
30-06-2023 дата публикации

Cylinder separation system design method and device, computer device and storage medium

Номер: CN116361908A
Автор: XING CHUNLEI, PENG HAOMIN, BU XIANGWEI, PENG WEIBIN, SONG WENFENG, WEI KAI
Принадлежит:

The invention discloses a cylinder separation system design method and device, a computer device and a storage medium, and belongs to the field of spaceflight equipment.The method comprises the steps that the mass center of a pushed object is determined; establishing a three-dimensional coordinate system by taking the mass center of the pushed object as a coordinate origin; setting coordinate points of a plurality of separation cylinders in a three-dimensional coordinate system; calculating the sum of the thrust of each separation cylinder in the actual separation direction; calculating the sum of the moments of the separated cylinders relative to the mass center; and determining design parameters of the cylinder separation system according to design requirements, and designing the cylinder separation system. Optimized design of the air cylinder separation system can be achieved, the stability of the air cylinder separation system is improved, and the production cost is reduced.

Подробнее
Номер записи: 6
30-05-2023 дата публикации

Method, device and equipment for encrypted storage of rocket-borne data

Номер: CN116186742A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, YU JICHAO, GUO WENZHENG
Принадлежит:

The invention provides a rocket-borne data encryption storage method, device and equipment, and relates to the technical field of information security. The method comprises the following steps: acquiring rocket-borne data; decoding and modulating the rocket-borne data to obtain plaintext rocket-borne data to be encrypted; obtaining an initial key and N levels of sub-keys for encrypting the plaintext rocket-borne data; performing encryption processing on the plaintext rocket-borne data by using the initial key to obtain a 0-level encryption result; encrypting an (N-1) th level encryption result according to an Nth level sub-key in the N levels of sub-keys to obtain an Nth level encryption result, the N levels of sub-keys being obtained according to the initial key; n is a positive integer greater than or equal to 1; storing the Nth-level encryption result into a preset storage module according to a preset storage speed and a preset storage bandwidth; the scheme of the invention can be used ...

Подробнее
Номер записи: 7
23-05-2023 дата публикации

Spring compression tool for rocket installation and parameter determination method thereof

Номер: CN116141266A
Автор: WANG YANAN, BU XIANGWEI, WEI KAI, PENG HAOMIN, YAO SONG, WANG YONGGANG
Принадлежит:

The invention provides a spring compression tool for rocket installation and a parameter determination method of the spring compression tool. The tool comprises a spring installation barrel, a spring compression assembly and a spring compression assembly, the spring mounting column and the pressing rod are arranged in the spring mounting cylinder, and one end of the pressing rod is fixedly connected with the spring mounting column; the limiting ring is fixedly connected with one end of the spring mounting barrel; the handle rotating device is arranged on the limiting ring and the pressing rod in a sleeving mode, a thrust bearing is arranged in the handle rotating device, and the thrust bearing comprises a thrust shaft sleeve, a thrust shaft seat and a ball arranged between the thrust shaft sleeve and the thrust shaft seat; one side of the thrust shaft sleeve is fixedly connected with the limiting ring, and a first preset distance is formed between the other side and the inner wall of the ...

Подробнее
Номер записи: 8
18-08-2023 дата публикации

Rocket sub-level life evaluation method, computer equipment and readable storage medium

Номер: CN116611351A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, MA XIANGMING, LI LINGYUN
Принадлежит:

The invention discloses a rocket sub-level life evaluation method, computer equipment and a readable storage medium, and belongs to the technical field of rocket recycling, and the rocket sub-level life evaluation method comprises the steps that when a launching task is executed, key data is stored in a block of an alliance chain; establishing an intelligent contract containing a rocket recovery sub-level life evaluation algorithm model; and submitting the key data to an intelligent contract of the alliance chain, performing evaluation and early warning on the residual life of the rocket recovery sub-level by using a rocket recovery sub-level life evaluation algorithm, and storing the corresponding data to a block of the alliance chain. According to the method, the rocket subgrade life can be rapidly evaluated, whether the rocket subgrade life is suitable for reuse or not can be judged, the dependence on physical inspection and testing is reduced, the cost and time consumption are reduced ...

Подробнее
Номер записи: 9
22-08-2023 дата публикации

Operation control method, device and equipment for carrier rocket

Номер: CN116627157A
Автор: ZHOU LIANG, BU XIANGWEI, PENG HAOMIN, ZHAO YENI, YIN CHAOLIANG, LI YU, WANG WEILONG, GAO GANG
Принадлежит:

The invention provides a carrier rocket operation control method, device and equipment. The carrier rocket operation control method comprises the steps of obtaining flight data generated when a simulation system simulates carrier rocket operation; according to a preset pulling deviation object, a flight environment model of rocket operation is constructed; resolving the flight data according to the flight environment model, a preset three-dimensional carrier rocket model and a preset rocket flight control system to obtain first trajectory information; performing optimization processing on the first track information according to a preset optimization model to obtain target track information; the preset optimization model is obtained by training historical flight data based on a preset convolutional neural network; and controlling the carrier rocket to operate according to the target trajectory information. According to the scheme provided by the invention, the trajectory information of ...

Подробнее
Номер записи: 10
15-08-2023 дата публикации

Intelligent processing method, device and equipment for spaceflight data

Номер: CN116595339A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, MA XIANGMING, LI LINGYUN
Принадлежит:

The invention provides an intelligent processing method, device and equipment for spaceflight data, and relates to the field of artificial intelligence. The intelligent processing method for the aerospace data is applied to a spacecraft, and comprises the following steps: acquiring to-be-processed data of the spacecraft; performing data preprocessing on the to-be-processed data to obtain text data of the to-be-processed data; inputting the text data into an intelligent processing model for data analysis processing to obtain a processing result of the to-be-processed data, and outputting the processing result; wherein the intelligent processing model is obtained by training a first preset processing model according to a historical processing data set of to-be-processed data of a spacecraft, and the first preset processing model is constructed according to the to-be-processed data. According to the scheme, rapid response of the spacecraft problem in the spacecraft development process is achieved ...

Подробнее
Номер записи: 11
23-06-2023 дата публикации

Automatic docking device for rocket air conditioner winch

Номер: CN116294841A
Автор: LIU RUIZHE, BU XIANGWEI, PENG HAOMIN, WANG YONGGANG, WANG YANAN
Принадлежит:

The invention discloses an automatic docking device for a rocket air conditioner winch, and belongs to the technical field of rocket launching. Comprising a rocket fairing flange, an air conditioner hard through pipe, a supporting frame, a butt joint driving mechanism used for driving the air conditioner hard through pipe and the rocket fairing flange to be pulled and inserted, and a direction adjusting mechanism used for adjusting the angle of a pipe opening of the air conditioner hard through pipe. The support frame comprises a bottom support frame and a movable frame; the movable frame is connected with the bottom support frame in a sliding manner; the direction adjusting mechanism comprises a direction adjusting support, a connecting disc and a winch, the winch is connected with the direction adjusting support through a cable, and the angle of the direction adjusting support is controlled by controlling the length of the cable. The automatic butt joint process of the air conditioner ...

Подробнее
Номер записи: 12
22-08-2023 дата публикации

Rocket simulation launching parameter interpretation method, computing device and storage medium

Номер: CN116629143A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, MA XIANGMING, LI LINGYUN
Принадлежит:

The invention discloses a rocket simulation launching parameter interpretation method, computing equipment and a storage medium, and belongs to the technical field of data processing, and the method comprises the steps: collecting interpretation parameter data of a rocket simulation launching test, and carrying out the preprocessing and feature extraction of the collected interpretation parameter data of the rocket simulation launching test; using the data after preprocessing and feature extraction to construct an interpretation model; performing interpretation model training by using the training data set, and evaluating and verifying the trained interpretation model by using the test data set; and integrating the trained interpretation model with a real-time data acquisition system and a sensor to realize rapid interpretation and analysis of real-time rocket simulated launching data. According to the invention, automatic interpretation of simulated launch test data of the carrier rocket ...

Подробнее
Номер записи: 13
16-05-2023 дата публикации

Carrier rocket image acquisition system, method and device and storage medium

Номер: CN116132602A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, YU JICHAO, GUO WENZHENG
Принадлежит:

The invention provides a carrier rocket image acquisition system, method and device and a storage medium wherein a rocket control terminal responds to an image acquisition request input by a user and sends an image acquisition instruction to a rocket launching platform end; the rocket launching platform end responds to the image acquisition instruction and performs image acquisition on each key point location in the at least one key point location of the target rocket to obtain at least one initial key point image; the rocket launching platform end is used for carrying out image compression on each initial key point image in the at least one initial key point image to obtain candidate key point images; the rocket launching platform end encrypts each candidate key point image by using a Hash encryption algorithm to obtain a target key point image; and the rocket launching platform end target key point image is sent to the rocket control terminal. By adopting the system, the time consumed ...

Подробнее
Номер записи: 14
15-08-2023 дата публикации

Inspection method and device for rocket system

Номер: CN116595811A
Автор: CHEN LE, BU XIANGWEI, PENG HAOMIN, ZHAO YENI, WEN TIANLE
Принадлежит:

The invention relates to the technical field of spaceflight, in particular to an inspection method and device for a rocket system. The method comprises the following steps: acquiring position parameters of to-be-inspected parts in each system of a rocket, to-be-inspected data and rocket model data; binding the to-be-checked data with the rocket model data according to the position parameters to obtain a to-be-checked rocket model; inputting the received inspection data into the rocket model to be inspected to obtain a state inspection result; and outputting check feedback information according to the state check result. According to the scheme, the to-be-inspected data and the rocket model data are bound to obtain the to-be-inspected rocket model, the actual inspection data are input into the to-be-inspected rocket model to inspect the state of each system of the rocket, and the purposes of simply, conveniently and visually testing and controlling the rocket system are achieved; the method ...

Подробнее
Номер записи: 15
11-04-2023 дата публикации

Automatic docking device for rocket air conditioner

Номер: CN115950312A
Автор: LIU RUIZHE, BU XIANGWEI, PENG HAOMIN, WANG YONGGANG, WANG YANAN
Принадлежит:

The invention discloses an automatic docking device for a rocket air conditioner, which belongs to the technical field of rocket launching and comprises a rocket fairing flange, an air conditioner hard through pipe, a support frame, a direction adjusting bracket, a docking driving mechanism and a direction adjusting mechanism for adjusting the angle of a hard through pipe interface, the air conditioner hard through pipe comprises a hard through pipe connector which is matched with the rocket fairing flange and can be inserted into the rocket fairing flange to be connected with the rocket fairing flange in a sealed mode. The support frame comprises a main support frame and a bottom support frame with a sliding rail; the direction adjusting mechanism comprises a horizontal direction adjusting mechanism and a vertical direction adjusting mechanism. The automatic butt joint process of the air conditioner pipelines can be achieved, and the butt joint efficiency and the butt joint effect of the ...

Подробнее
Номер записи: 16
09-05-2023 дата публикации

Space-based infrared target recognition system and target recognition method thereof

Номер: CN116087974A
Автор: CHENG RUI, PENG HAOMIN, BU XIANGWEI, YU JICHAO, GUO WENZHENG, TANG KAIYI, WANG JIAN
Принадлежит:

The invention provides a space-based infrared target identification system and a target identification method thereof. The system comprises an observation satellite which operates at a descending node and is in a low sun-synchronous orbit near noon; a target observation assembly, an on-satellite computer and satellite orbit measurement equipment are arranged on the observation satellite, the target observation assembly comprises an infrared remote sensing camera and a laser range finder which are arranged on a two-dimensional tracking rotary table or a whole-satellite three-axis stabilizing device, and the infrared remote sensing camera and the laser range finder are the same in axial direction and are arranged adjacently. The infrared remote sensing camera is used for collecting an infrared image corresponding to a flying target, the laser range finder is used for sending a laser beam to the flying target and receiving a corresponding echo signal, and the satellite orbit measurement equipment ...

Подробнее
Номер записи: 17
15-08-2023 дата публикации

Rocket launching pad

Номер: CN116592707A
Автор: WANG YONGGANG, WEI KAI, BU XIANGWEI, PENG HAOMIN, YAO SONG, LIU DAHUI, SUN ZHONGYU, HAN ZONGZHEN, TENG YAO
Принадлежит:

The invention provides a rocket launching pad. The rocket launching pad comprises a pad body; the cabin is arranged in the platform body; the lifting platform is arranged on the platform body and located in the center of the platform body, a core first-stage rocket is hoisted on the lifting platform, and the rocket is in a vertical state by adjusting the lifting platform; the plurality of upper supporting legs are fixed on the platform body and arranged around the lifting platform, the end parts of the plurality of upper supporting legs are all provided with supporting discs, and rocket boosters are hoisted on the supporting discs, so that the rocket boosters are fixed with a core first-stage rocket; the umbilical tower is arranged on the side surface of the platform body and is fixedly connected with the platform body; the lower supporting legs are arranged on the platform body and located on the opposite side of the lifting platform. According to the scheme, a rocket can be supported ...

Подробнее
Номер записи: 18
11-07-2023 дата публикации

Data communication method and equipment

Номер: CN116418656A
Автор: ZHANG JIANZHONG, BU XIANGWEI, WU JIE, PENG HAOMIN
Принадлежит:

Provided are a data communication method and device, relating to the technical field of data communication, applied to a receiver, the method comprising: receiving a subframe sequence sent by a transmitter, the subframe sequence comprising at least one subframe arranged in sequence, the subframe comprises a first synchronization sequence, bearing data, a second synchronization sequence, a third synchronization sequence and an idle time slice; performing channel estimation operation on the third synchronization sequence and a preset synchronization sequence to obtain a channel estimation value; performing frequency domain equalization on the bearing data and the second synchronization sequence by using the channel estimation value to obtain an equalization result; and processing the equalization result to obtain communication data, and performing frequency point switching in the idle time slice of the subframe. According to the invention, frequency domain equalization and frequency hopping ...

Подробнее
Номер записи: 19
13-06-2023 дата публикации

Method and device for determining rocket simulation model

Номер: CN116257942A
Автор: XU LIJIE, ZHANG CHI, BU XIANGWEI, WEI KAI, YAO SONG, PENG HAOMIN, WANG CHENXI, WU KAO, ZU YUNYU, HOU SHIYUAN
Принадлежит:

The invention provides a rocket simulation model determination method and device, and relates to the field of vertical recovery rocket modeling simulation. The rocket simulation model determination method comprises the steps of obtaining at least one basic model library component in a preset language model library; constructing at least one special model library in the rocket simulation model according to the at least one basic model library component; constructing at least one subsystem model of the rocket simulation model according to the at least one special model library; and according to the preset language, performing simulation processing on the at least one subsystem model to obtain a target rocket simulation model. According to the scheme, all subsystem models of the rocket simulation model are constructed through the preset language, the simulation efficiency of the rocket simulation model and the reliability and accuracy of the simulation result are improved, and meanwhile the ...

Подробнее
Номер записи: 20
30-05-2023 дата публикации

Carrier rocket telemetry system PCM/FM code stream transmission method

Номер: CN116192341A
Автор: YIN CHAOLIANG, PENG HAOMIN, BU XIANGWEI, ZHAO YENI, HE HAO, WEI KAI, YAO SONG
Принадлежит:

The invention provides a carrier rocket telemetry system PCM/FM code stream transmission method, which comprises the following steps that: a ground detection system fills code stream data blocks into a to-be-sent cache region, sends data blocks in the to-be-sent cache region to a data analysis system, fills the data blocks in the to-be-sent cache region into a sent cache region, and sends the data blocks to the data analysis system; the data analysis system receives the data block sent by the ground detection system, fills the data block into the receiving cache region, and modifies the mark of the position corresponding to the currently received data block in the mark cache region as occupation; after a preset number of data blocks are received, packet loss serial numbers are determined based on marks of all positions in the mark cache region, retransmission commands containing the packet loss serial numbers are sent to the ground detection system, and after the ground detection system ...

Подробнее
Номер записи: 21
07-07-2023 дата публикации

Carrier rocket load shedding control method, computing device and storage medium

Номер: CN116400723A
Автор: WU KAO, BU XIANGWEI, PENG HAOMIN, XU GUOGUANG, WEI KAI, ZHANG CHI, WANG CHENXI, ZHANG JIE, ZU YUNYU, FAN SHAOBING, LIU CHANG, XU LIJIE
Принадлежит:

The invention discloses a carrier rocket load shedding control method, a computing device and a storage medium, and belongs to the technical field of aerospace craft control, and the method comprises the steps: adding an expansion section state observer in a control system, obtaining the swing angle of a servo mechanism or a control surface through the calculation of a control network according to a signal measured by an inertia measurement device, and obtaining the load shedding control of a carrier rocket. Therefore, the flight attitude of the rocket is changed, and the purpose of load shedding is achieved. According to the carrier rocket load shedding control method, the flight attack angle in a strong wind area can be compensated, active load shedding is carried out, and the carrying capacity is improved.

Подробнее
Номер записи: 22
15-08-2023 дата публикации

Rocket sublevel vertical recovery control method, computing device and storage medium

Номер: CN116594309A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, MA XIANGMING, LI LINGYUN
Принадлежит:

The invention discloses a rocket sub-level vertical recovery control method, computing equipment and a storage medium, and belongs to the technical field of rocket recoverability, the rocket sub-level vertical recovery control method comprises the following steps: establishing a physical dynamics model, and defining physical parameters and control parameters in the physical dynamics model; initializing a population; performing population local search and optimization through a simulated annealing algorithm, and optimizing a rocket sub-level recovery trajectory; path selection and population local search of the rocket sublevel are carried out through an ant colony algorithm, and attitude and speed control parameters of the rocket sublevel are optimized; and the optimal landing point coordinate and control parameter combination of the rocket sub-stage is found by applying a genetic algorithm, so that the rocket sub-stage reaches the expected landing point position in the recovery process.

Подробнее
Номер записи: 23
22-08-2023 дата публикации

Spacecraft supply chain management method and equipment based on block chain, and storage medium

Номер: CN116628757A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI
Принадлежит:

The invention discloses a spacecraft supply chain management method and device based on a block chain and a storage medium, and belongs to the technical field of block chains, and the spacecraft supply chain management method based on the block chain comprises the steps: in the whole process of a spacecraft development cycle, each part and related data in a spacecraft supply chain are identified; performing digital signature and verification on each identifier and related data by using an encryption technology; setting a smart contract for managing the contract, and storing the smart contract on the block chain; a block chain technology is used to record and store transactions and data in a spacecraft supply chain, and the transactions and data are broadcasted to a block chain network, so that authorized participants can check and update data within the permission range of the participants. According to the method, the transparency, traceability and safety of the spacecraft supply chain ...

Подробнее
Номер записи: 24
30-05-2023 дата публикации

Carrier rocket attitude control method and device and flight control computer

Номер: CN116185058A
Автор: WU KAO, BU XIANGWEI, PENG HAOMIN, ZHANG CHI, XU GUOGUANG, WEI KAI, YAO SONG, WANG CHENXI, ZU YUNYU, XU LIJIE, LIU CHANG, ZHANG JIE, FAN SHAOBING
Принадлежит:

The invention provides a carrier rocket attitude control method and device and a flight control computer, and relates to the technical field of rocket solid booster attitude control, and the method comprises the steps: obtaining at least one disturbance torque of a booster of a carrier rocket in a thrust descent stage; according to at least one disturbance torque and a control torque provided by a booster of the carrier rocket in a thrust descending stage, determining the ignition time of a core-level engine when the flight attitude of the carrier rocket changes; acquiring a flight attitude control scheme; and controlling the flight attitude of the carrier rocket according to the ignition time and the flight attitude control scheme. According to the invention, the attitude control of the carrier rocket in the boosting flight section is more stable.

Подробнее
Номер записи: 25
21-07-2023 дата публикации

Power distribution control system and method of aircraft and flight control computer

Номер: CN116466637A
Автор: CHENG RUI, PENG HAOMIN, BU XIANGWEI, YAO SONG, WEI KAI, YU JICHAO, GUO WENZHENG
Принадлежит:

The invention provides a power distribution control system and method for an aircraft and a flight control computer, and the system comprises the flight control computer which is internally provided with a cell pile, a power management board electrically connected with the cell pile, and a central processing unit electrically connected with the power management board; the ground control system is electrically connected with the flight control computer; wherein after a central processing unit of the flight control computer receives a power-on signal sent by a ground control system, the aircraft is in a test mode, and the central processing unit controls a power management board, so that the ground control system supplies power to electric equipment of the aircraft; when the central processing unit receives a mode switching signal sent by the ground control system, the aircraft is switched from a test mode to a flight mode, and the central processing unit controls the power management board ...

Подробнее
Номер записи: 26
09-05-2023 дата публикации

Rocket semi-physical simulation data anomaly evaluation method and decision-making device based on LSTM (Long Short Term Memory)

Номер: CN116088349A
Автор: ZHOU LIANG, BU XIANGWEI, PENG HAOMIN, ZHAO YENI, YIN CHAOLIANG
Принадлежит:

The invention discloses an LSTM-based rocket semi-physical simulation data exception assessment method and decision making device, and belongs to the technical field of rocket semi-physical simulation data exception assessment. An LSTM neural network algorithm is adopted, data output from an optical fiber in semi-physical simulation are used as input of an LSTM neural network model, a predicted value is calculated through an LSTM prediction model, and the predicted value is used as a prediction result of the rocket semi-physical simulation data exception assessment method. And taking the predicted value set as the input of an anomaly judgment model, if the anomaly judgment model judges the data as abnormal data, inputting the data into an LSTM decision model to obtain the priority of equipment power failure and stop, sending a stop instruction through an optical fiber to control a turntable to stop, and sending an SCPI instruction through the Ethernet to control a power supply to be turned ...

Подробнее
Номер записи: 27
07-04-2023 дата публикации

Operation control method, device and equipment of rocket control software

Номер: CN115933501A
Автор: WEN TIANLE, PENG HAOMIN, BU XIANGWEI, ZHAO YENI, CHEN LE
Принадлежит:

The invention provides an operation control method, device and equipment for rocket control software, and relates to the technical field of computer information processing. The method comprises the following steps: acquiring a voice control instruction input through voice input equipment; analyzing the voice control instruction to obtain a voice feature signal corresponding to the voice control instruction; if the voice feature signal is successfully matched with preset voice data, determining an operation corresponding to the voice control instruction; and performing operation control on rocket control software according to the operation. According to the scheme, remote control over the rocket control software is achieved, operation of the rocket control software is more convenient, and the use threshold of the rocket control software is lowered.

Подробнее
Номер записи: 28
28-04-2023 дата публикации

Method and system for controlling attitude of carrier rocket in boosting stage

Номер: CN116025486A
Автор: LIU CE, BU XIANGWEI, PENG HAOMIN, WEI KAI, GUO WENZHENG, YU JICHAO, WU KAO, GUO PENGFEI, CHENG RUI
Принадлежит:

The invention provides a method and a system for controlling the attitude of a carrier rocket in a boosting stage, and relates to the technical field of aircraft attitude control. The method comprises the steps that an attitude control instruction is sent to a boosting servo driver of a boosting engine; receiving a first position state signal of a first servo actuator and a second position state signal of a second servo actuator fed back by the boosting servo driver according to the attitude control instruction; the first servo actuator is located in a first quadrant of the boosting engine, and the second servo actuator is located in a fourth quadrant of the boosting engine; and according to the first position state and the second position state, the first servo actuator and the second servo actuator are controlled to adjust the posture of a spray pipe of the boosting engine. According to the scheme, the rolling posture of the boosting section of the rocket is controlled through the spray ...

Подробнее
Номер записи: 29
02-05-2023 дата публикации

Carrier rocket state test method and system, computer equipment and medium

Номер: CN116045751A
Автор: GUO WENZHENG, PENG HAOMIN, BU XIANGWEI, YU JICHAO, WEI KAI, YAO SONG, SHI SHENGQING, DAI LONGPENG
Принадлежит:

The invention provides a carrier rocket state test method and system, computer equipment and a medium, a bus controller responds to a test instruction input by a user, converts the test instruction into a digital test signal and sends the digital test signal to a photoelectric converter group; the photoelectric converter group sends the digital test signal to the terminal controller; the terminal controller controls a booster of the carrier rocket to operate according to the digital test signal; after the booster runs, the terminal controller controls an attitude sensor for acquiring attitude data of the booster to acquire actual attitude data of the booster and sends the actual attitude data to the photoelectric converter group; the photoelectric converter group sends the actual attitude data to the bus controller; the bus controller judges whether the actual attitude data are the same as preset standard attitude data or not; if yes, the bus controller marks the running state of the carrier ...

Подробнее
Номер записи: 30
12-05-2023 дата публикации

Rocket sub-level recovery rocket body defect detection system and method

Номер: CN116106404A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, YU JICHAO, GUO WENZHENG
Принадлежит:

The invention provides a rocket sub-level recovery rocket body defect detection system and method, and relates to the technical field of rocket sub-level recovery. The system comprises at least one test node walking on the inner wall of the rocket sublevel recovery rocket body, and the test node comprises a permanent magnet used for magnetizing the inner wall of the tested rocket sublevel recovery rocket body and generating an electromagnetic field; the magnetic sensor group is used for acquiring magnetic field information of an electromagnetic field generated when the permanent magnet magnetizes the inner wall of the tested rocket sub-stage recovery rocket body; the position detection sensor group is used for acquiring position information of the test nodes; the electronic cabin is respectively connected with the permanent magnet, the magnetic sensor group and the position detection sensor group and is used for processing the magnetic field information and the position information of the ...

Подробнее
Номер записи: 31
07-04-2023 дата публикации

Energy testing system and testing method for gas pushing and punching device

Номер: CN115931201A
Автор: XING CHUNLEI, PENG HAOMIN, BU XIANGWEI, PENG WEIBIN, SONG WENFENG, WEI KAI
Принадлежит:

The invention discloses an energy testing system and method for a gas pushing and punching device, and belongs to the technical field of rocket pushing and punching device testing, and the system comprises a body pushing and punching device, a limiting rotation device, a weight bearing device, a gas cylinder for supplying gas to the gas pushing and punching device, and a rack with a table top. The limiting rotating device comprises a magnetic suction lifting device and a limiting rotating frame; the limiting swing frame is in a locking state or a free rotating state relative to the rack under the action of attraction or release of the magnetic attraction lifting device. The limiting swing frame in a locking state is matched with the gas pushing and punching device to lock the tested weight in the bearing sliding groove; the gas pushing and flushing device is configured to push the test weight in the bearing sliding groove away from the weight bearing device and enable the test weight to ...

Подробнее
Номер записи: 32
04-04-2023 дата публикации

Construction method and device of carrier rocket ground measurement and control network topological structure

Номер: CN115913983A
Автор: ZHAO YENI, BU XIANGWEI, PENG HAOMIN, CHEN LE, WEN TIANLE, YIN CHAOLIANG
Принадлежит:

The invention provides a carrier rocket ground measurement and control network topological structure construction method and device, and the method comprises the steps: dividing each terminal into at least one role of an action requester, an action executor, a data publisher and a data subscriber according to the business demand type of each terminal of a rocket launching system; setting a publishing and subscribing agent and an action agent, and constructing a basic topological structure based on the publishing and subscribing agent, the action agent and each terminal; according to business services of all terminals of the rocket launching system, typical services are determined, and typical service software is designed; and obtaining a final network topology structure based on the basic topology structure and the typical service software. By adopting the WebService technology and the publishing and subscribing technology, the development efficiency and the system reliability are improved ...

Подробнее
Номер записи: 33
18-08-2023 дата публикации

Rocket recovery sub-level state tracing method and device and computing equipment

Номер: CN116611821A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI
Принадлежит:

The invention provides a rocket recovery sub-level state tracing method and device and computing equipment, and relates to the technical field of rocket recovery sub-level state tracing, and the method comprises the steps: obtaining a rocket sub-level drop point, and carrying out the recovery of a rocket sub-level according to the drop point; checking and maintaining the recovered rocket sub-level; transporting the rocket sub-level after inspection and maintenance, and when the rocket sub-level is transported to a next station, carrying out transaction recording and verification through a block chain; and after verification, the rocket sub-level is repaired, and the repair process is recorded on the block chain. According to the method, the transparency and efficiency of rocket sub-level management are improved, errors of manual operation are reduced, meanwhile, due to the characteristics of the block chain, the data cannot be tampered, and the safety of the data is enhanced.

Подробнее
Номер записи: 34
14-07-2023 дата публикации

Terminal state detection system and method, computer equipment and storage medium

Номер: CN116437070A
Автор: WANG JIAN, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, YU JICHAO, GUO WENZHENG
Принадлежит:

The invention provides a terminal state detection system and method, computer equipment and a storage medium, and the system comprises an upper computer, an image tester and a to-be-detected terminal. The upper computer is used for performing PCM pulse code modulation coding on the reference image to obtain reference source code data and sending the reference source code data to the image tester; the image tester is used for performing PCM pulse code modulation decoding on the reference source code data to obtain a reference image, and sending the reference image to the to-be-detected terminal; the to-be-detected terminal is used for coding the reference image by using a pre-configured coding rule to obtain test source code data, and returning the test source code data to the upper computer; and the upper computer is used for comparing the test source code data with the reference source code data and determining the equipment state of the to-be-detected terminal according to an obtained ...

Подробнее
Номер записи: 35
30-06-2023 дата публикации

System simulation model automatic generation method, device and equipment

Номер: CN116362060A
Автор: XU LIJIE, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, ZHANG CHI, LIU CHANG, WANG CHENXI
Принадлежит:

The invention provides a system simulation model automatic generation method, device and equipment, and relates to the technical field of computer information processing, and the method comprises the steps: obtaining a source code of at least one subsystem model and an extensible markup language (XML) configuration file, the XML configuration file comprises system simulation model engineering description, subsystem model calling condition description and system simulation model solving related description; according to a source code of at least one subsystem model and the XML configuration file, generating a simulation model code of each subsystem model of a system simulation model; and generating the system simulation model according to the calculation sequence of the simulation model codes of the subsystem models of the system simulation model. According to the scheme, the XML configuration file can be used for achieving automatic generation of the system simulation model code, and therefore ...

Подробнее
Номер записи: 36
18-07-2023 дата публикации

High-frequency telemetry data processing method, computing device and storage medium

Номер: CN116450994A
Автор: YIN CHAOLIANG, BU XIANGWEI, PENG HAOMIN, ZHAO YENI, HE HAO, ZHOU LIANG, CHEN LE, WEN TIANLE
Принадлежит:

The invention discloses a high-frequency telemetry data processing method, computing equipment and a storage medium, and belongs to the field of rocket telemetry data processing.The method comprises the steps that after high-frequency data of a sensor is collected, polynomial fitting is conducted on the data to obtain a nonlinear curve, a polynomial is generated, and parameters of the polynomial are sent to the ground; a polynomial is constructed on the ground through polynomial parameters, the value of the polynomial is calculated, and the extracted value is used for participating in subsequent calculation. According to the method, the proportion of high-frequency data occupying telemetry data can be reduced, key links and important positions in rocket launching can be measured more finely on the premise that the transmission capacity is not increased, and the flight condition of the rocket is evaluated more comprehensively.

Подробнее
Номер записи: 37
28-07-2023 дата публикации

Rocket swing control method and rocket

Номер: CN116495198A
Автор: HUANG SHUAI, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, SHI SHENGQING, ZHENG ZHILIN
Принадлежит:

The invention provides a rocket swing control method and a rocket. The method comprises the steps that flight state information of the rocket at the current moment is acquired; determining rocket target swing angles of the rocket in at least three axial directions according to the flight state information; according to the rocket target swing angle, the swing angle of each engine in at least five engines is determined; wherein the rocket comprises a central engine and eight engines symmetrically arranged around the central engine, and the at least five engines comprise the central engine and at least four engines in the eight engines; controlling the at least five engines to move according to the swing angle; according to the scheme, the rocket control method is effectively simplified, the complexity of control calculation is reduced, and the calculation efficiency is improved.

Подробнее
Номер записи: 38
29-08-2023 дата публикации

Rocket take-off drift distance measuring system and method

Номер: CN116659321A
Автор: WU KAO, BU XIANGWEI, PENG HAOMIN, XU GUOGUANG, WEI KAI, ZHANG CHI, ZU YUNYU, WANG CHENXI, ZHANG JIE, FAN SHAOBING, LIU CHANG, XU LIJIE
Принадлежит:

The invention discloses a rocket take-off drift distance measuring system and method, and belongs to the technical field of tracking measurement, the rocket take-off drift distance measuring system comprises a target mirror, a laser tracker, a support platform and a rocket; the target mirror comprises a target mirror A and a target mirror B; the rocket is vertically arranged on the supporting platform; the target lens A is arranged on the supporting platform; the target mirror B is arranged on the side surface of the rocket; in an initial state, the measuring head, the target mirror A and the target mirror B are arranged on the same horizontal straight line; the tracking rotating frame is configured to track a measuring target and drive the measuring head to rotate according to the target tracking condition; the supporting platform is used for supporting the rocket before launching. According to the method, the laser tracker is used for measuring the position of the target mirror to obtain ...

Подробнее
Номер записи: 39
18-08-2023 дата публикации

Initiating explosive device time sequence test system, method and equipment of rocket

Номер: CN116608741A
Автор: DAI LONGPENG, BU XIANGWEI, PENG HAOMIN, YAO SONG, WEI KAI, YU JICHAO
Принадлежит:

The invention provides an initiating explosive device time sequence test system, method and equipment of a rocket. The system comprises a first power supply module, a first rocket-borne computer module, a first initiating explosive device module, a second power supply module, a second rocket-borne computer module, a second initiating explosive device module and a time sequence collector. The first power supply module, the first rocket-borne computer module and the first initiating explosive device module are electrically connected in sequence; the second power supply module, the second rocket-borne computer module and the second initiating explosive device module are electrically connected in sequence; the time sequence collector is electrically connected with the first rocket-borne computer module and the second rocket-borne computer module, collects the first time sequence control signal and the second time sequence control signal, and determines whether the sending sequence of the first ...

Подробнее
Номер записи: 40
11-07-2023 дата публикации

Automatic gain control method, circuit and equipment

Номер: CN116419383A
Автор: ZHANG JIANZHONG, BU XIANGWEI, WU JIE, PENG HAOMIN, YAO SONG, SHI SHENGQING, WEI KAI
Принадлежит:

The invention provides an automatic gain control method, circuit and equipment, and relates to the field of wireless communication. The automatic gain control circuit comprises a radio frequency transceiver used for receiving a first signal, performing gain adjustment on the first signal to obtain a first gain signal and outputting the first gain signal; the baseband module is electrically connected with the radio frequency transceiver and is used for generating a control signal when the power of the first gain signal is not equal to preset power, and the control signal is used for controlling the radio frequency transceiver to perform gain increase or decrease adjustment on the received first signal; and sending the preset power to the radio frequency transceiver, so that a first target adjustment gain signal output by the radio frequency transceiver is equal to the preset power, and inputting the first target adjustment gain signal to a signal demodulation module of a receiver for demodulation ...

Подробнее
Номер записи: 41
04-04-2023 дата публикации

Flight target space-based monitoring and predicting method and device capable of being updated online

Номер: CN115902980A
Автор: CHENG RUI, PENG HAOMIN, BU XIANGWEI, YU JICHAO, GUO WENZHENG, JIA SONGTAO, ZHAO JINDONG
Принадлежит:

The invention provides a flying target space-based monitoring and prediction method and device capable of being updated online, and the method is applied to a low-orbit satellite, and comprises the steps: obtaining the measurement information of the low-orbit satellite at different moments in a preset time period; obtaining an initial moment model set of the low-orbit satellite in the preset time period, and predicting motion states of the flight target at different moments in the preset time period by adopting a VSIMM-3DOF-UKF real-time motion estimation algorithm; sending the measurement information and the motion states of the flight target at different moments in the preset time period to the ground, and receiving a ground correction model set returned by the ground; and updating the model set of the low-orbit satellite based on the ground correction model set. According to the invention, the real-time motion estimation algorithm is adopted to monitor and predict the flying target on ...

Подробнее
Номер записи: 42
28-07-2023 дата публикации

Data encryption storage method and device, equipment and storage medium

Номер: CN116502251A
Автор: WEN TIANLE, BU XIANGWEI, PENG HAOMIN, ZHAO YENI, CHEN LE
Принадлежит:

The invention provides a data encryption storage method and device, equipment and a storage medium, and relates to the technical field of aerospace data processing. The method comprises the following steps: acquiring to-be-processed data, wherein the to-be-processed data comprises equipment configuration data and experimental data in a rocket testing and launching terminal; performing security classification on the to-be-processed data to obtain target data of at least one security classification; processing the target data of the at least one security level by using an encryption algorithm of the at least one target security level to obtain a data processing result; the encryption algorithm of the target security level is in one-to-one correspondence with the security level of the target data; and storing the data processing result into a target storage device. According to the scheme, different types of rocket test data can be classified, encrypted and stored, the safety of data transmission ...

Подробнее
Номер записи: 43
04-07-2023 дата публикации

Carrier rocket attitude control simulation method and system

Номер: CN116382124A
Автор: ZHOU LIANG, BU XIANGWEI, PENG HAOMIN, YAO SONG, ZHAO YENI, YIN CHAOLIANG, HE HAO, ZHANG CHI
Принадлежит:

The invention provides an attitude control simulation method and system for a carrier rocket. The method comprises the following steps: receiving a pulse total amount sent by a laser strapdown inertial measurement unit; carrying out resolving processing according to the pulse total amount to obtain a target resolving result; the target calculation result comprises a navigation calculation result, a guidance calculation result and an attitude control calculation result; sending the navigation resolving result, the guidance resolving result and the attitude control resolving result to a simulation server; according to the scheme, the problems that the real environment is difficult to simulate, the verification mode is not visual enough and the safety risk is high during carrier rocket testing are solved, simulation and optimization of the carrier rocket under different working conditions on a computer are achieved, experimental verification is not needed, time and cost are saved, and the ...

Подробнее
Номер записи: 44
18-08-2023 дата публикации

Simulation analysis method and device for launching pad flow guide model and computing equipment

Номер: CN116611370A
Автор: WANG YONGGANG, WEI KAI, BU XIANGWEI, PENG HAOMIN, YAO SONG, HUANG YAJUN, LIU DAHUI, LIU JINCHENG, SUN ZHONGYU, TENG YAO, WANG SHOUJUN
Принадлежит:

The invention provides a simulation analysis method and device of a launching pad flow guide model and computing equipment, and relates to the technical field of simulation analysis of launching pad flow guide models.The method comprises the steps that a computing model of the launching pad flow guide model is established according to geometrical shape and size parameters; performing grid division on a computational domain range corresponding to the computational model, and setting boundary conditions and simulation parameters to obtain a numerical solution of a flow field structure of the diversion model; performing numerical simulation calculation according to the numerical solution of the flow field structure of the flow guide model, analyzing the flow field structure of the flow guide model, and obtaining various flow guide indexes; according to each flow guide index, carrying out optimization design on geometric shape and size parameters of the launching pad flow guide model; and verifying ...

Подробнее
Номер записи: 45
22-08-2023 дата публикации

Method and device for determining parameters of flow guide groove of petal-shaped launching pad

Номер: CN116629028A
Автор: WANG YONGGANG, WEI KAI, BU XIANGWEI, PENG HAOMIN, YAO SONG, HUANG YAJUN, LIU DAHUI, SUN ZHONGYU, LIU JINCHENG, TENG YAO, WANG SHOUJUN
Принадлежит:

The invention provides a petal-shaped launching pad diversion trench parameter determination method and device, and relates to the technical field of launching pad diversion trench analogue simulation, and the method comprises the steps: building a numerical simulation model according to the shape and size of a diversion trench, carrying out the numerical simulation of the diversion trench through the numerical simulation model, and obtaining a numerical simulation result, the numerical simulation result comprises a flow field distribution condition in the diversion trench; according to a numerical simulation result, adjusting the shape and size parameters of the diversion trench to obtain a final flow field distribution effect; verifying the final flow field distribution effect to determine the accuracy of a numerical simulation result and the effectiveness of optimization design; and determining final diversion trench parameters according to the accuracy of the numerical simulation result ...

Подробнее
Номер записи: 46