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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

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Мониторинг СМИ

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

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 10. Отображено 10.
01-04-2015 дата публикации

Cable hooking preventing structure for low-altitude flying aircraft

Номер: CN104477397A
Автор: DENG CHENGYANG, JI XIANWU, LIANG HAO, XU HUANYU, LI XIAOBAO, ZHANG GAIHUA, LU WEIFU, WU GENLIN, FU JIEBIN, CHEN LIGEN, HU DINGHONG, LI WEIDONG, XIONG YI, WANG BIN, ZHANG WEI, YIN XIAOXIA, CHEN LONGHUI, WANG ZHIZHU, ZUO XIAOJUAN, PENG RUI
Принадлежит:

The invention relates to a cable hooking preventing structure for a low-altitude flying aircraft, and belongs to the structural design of aircrafts. The cable hooking preventing structure is that a steel cable is arranged between a cockpit and a fixed fin of an empennage and is fixed on a bracket through a steel sleeve ring I, wherein the bracket is fixed on the fixed fin; a lead cutter structure is additionally arranged on an aircraft body; the upper part of the lead cutter structure is fixed on the cockpit through an upper bracket of a lead cutter, and while the lower part of the lead cutter structure is fixed on the aircraft body through a lower bracket of the lead cutter; the steel cable is integrally connected with a steel sleeve ring II and then is fixed to the upper part of the lead cutter through an elastic screw barrel. The cable hooking preventing structure is suitable for the low-altitude flying aircraft and has the advantages of being simple in structure, high in safety and ...

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Номер записи: 1
19-03-2014 дата публикации

All-moving control surface installation structure of airplane

Номер: CN103640689A
Автор: FU JIEBIN, ZHANG YUECHAO, LIANG HAO, WANG JIANHUA, ZHANG HUA, LI XIAOBAO, ZHANG GAIHUA, ZHANG YUHUA, TAO LIANG, WANG BIN, HUANG XUN, LI WEIDONG, XU HUANYU, XIA YANPENG
Принадлежит:

The invention relates to the installation field of airplane control surfaces, and in particular relates to an all-moving control surface installation structure of an airplane. The all-moving control surface installation structure comprises a rotating shaft, a first bearing, a second bearing, a control surface rocker arm, an end socket bolt, a lock washer, a gasket, a check ring, a cone-shaped clamp, a clamp nut, four hollow cone-shaped bushings, two screw rods and two nuts, wherein the inner diameter of the first bearing is cone-shaped, one end of the cone-shaped clamp is provided with outer threads, the rotating shaft is sequentially provided with the check ring, the first bearing, the cone-shaped clamp, the clamp nut and the control surface rocker arm, the end of the rotating shaft is sequentially sleeved with the second bearing, the gasket and the lock washer, the end of the rotating shaft is provided with a screw hole for installing the end socket bolt, the rotating shaft and the control ...

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Номер записи: 2
11-03-2015 дата публикации

Novel engine fixing structure

Номер: CN104401496A
Автор: DENG CHENGYANG, JI XIANWU, LIANG HAO, XU HUANYU, LI XIAOBAO, ZHANG GAIHUA, LU WEIFU, WU GENLIN, FU JIEBIN, CHEN LIGEN, HU DINGHONG, LI WEIDONG, XIONG YI, WANG BIN, ZHANG WEI, YIN XIAOXIA, CHEN LONGHUI, WANG ZHIZHU, ZUO XIAOJUAN, PENG RUI
Принадлежит:

The invention relates to a novel engine fixing structure, and belongs to the technical field of plane structure design. The novel engine fixing structure is characterized in that a plane body framework is connected with a mounting ring on an engine through three structures, namely, a top left supporting rod, a medium supporting rod and a bottom left supporting rod, wherein the top left supporting rod and the medium supporting rod are both connected with an top girder; the bottom left supporting rod is fixed to a lower girder; an oil tank bracket I and an oil tank bracket II are fixed to a lug plate I on the plane body framework through screws I, and the two brackets are fixed to an oil tank support on the engine through screws II. According to the novel engine fixing structure, the supporting rods and other structures are added to enable the plane body framework to be stably connected with the engine; meanwhile, the center of gravity of the engine can be further fixed by reinforcing the ...

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Номер записи: 3
11-03-2015 дата публикации

Belly large-opening engine load-bearing quick-release compartment door structure

Номер: CN104401478A
Автор: LI QIONG, LI XIAOBAO, WANG QIANG, LU WEIFU, GAO YONGQIANG, ZHU CHENGXIANG, LI SHANXUN, YI JIAN, LIU WEI, FU JIEBIN
Принадлежит:

The invention belongs to the technical field of aviation and relates to a large-opening load-bearing quick-release cap, in particular to a belly large-opening engine load-bearing quick-release compartment door structure. Girders are arranged on the left side and the right side of an airplane body, and load-bearing frames are arranged at the front end and the rear end of the airplane body; an engine compartment door adopts an all-metal thin-walled structure formed in such a way that a frame formed by a left compartment door beam, a right compartment door beam, transverse partition plates, longitudinal partition plates and profiles is riveted together with hook lock fixing seats, latch lock fixing seats, outer skin and inner connecting pieces; 2-5 latch quick-release locks are arranged at the joints of the transverse and longitudinal partition plates at the front end and the rear end of the engine compartment door and mounted in the latch lock fixing seats; three hook quick-release locks ...

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Номер записи: 4
04-03-2015 дата публикации

Rollover prevention airframe steel framework structure

Номер: CN104386239A
Автор: DENG CHENGYANG, JI XIANWU, XU HUANYU, WU GENLIN, FU JIEBIN, HU DINGHONG, YIN XIAOXIA, LI WEIDONG, CHEN LIGEN, ZHANG WEI, WANG BIN, XIONG YI, CHEN LONGHUI, WANG ZHIZHU
Принадлежит:

The invention relates to a rollover prevention airframe steel framework structure, which belongs to the technical field of aircraft structure design. The rollover prevention airframe steel framework structure comprises a steel framework fuel tank area, a steel framework work bin area and a steel framework cockpit area, wherein the two sides of a fuel tank are fixed on first steel pipes on the two sides of the airframe steel framework through standard wrapping tapes, the bottom of the fuel tank is fixed on groove type parts at the bottom part of the airframe steel framework through standard wrapping tapes, the front end of the steel framework fuel tank area forms triangular structures III with the steel framework by a second steel pipe, the rear end of the steel framework fuel tank area forms triangular structures I with the steel framework by third steel pipes, and the steel framework work bin area and the steel framework cockpit area form triangular structures II with a center wing back ...

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Номер записи: 5
26-03-2014 дата публикации

Half hidden type elevating rudder rocker arm

Номер: CN103661923A
Автор: ZHANG HUA, ZHANG YUHUA, FU JIEBIN, TAO LIANG, ZHANG YUECHAO, HUANG XUN, HUANG XIN
Принадлежит:

The invention relates to a half hidden type elevating rudder rocker arm, and belongs to the technical field of control surface structures of airplane tail wings. A rocker arm main body is positioned between a right control surface and a left control surface, the rocker arm main body is connected with an ear piece of a left joint in the left control surface through an ear piece of a right joint in the right control surface; the rocker arm main body is 'S'-shaped; the rocker arm main body is connected to a horizontal tail joint through a horizontal tail joint bolt; the rocker arm main body is connected with a control operating rod through a control connecting bolt. The structural style of the rocker arm has the advantages that aiming at the characteristic that the structure space of a light aeroplane is small, the structural style of the elevating rudder control rocker arm is improved, a traditional torque tube structure is cancelled, the conventional structure is fully used, the left control ...

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Номер записи: 6
06-06-2023 дата публикации

Unmanned aerial vehicle

Номер: CN116215837A
Автор: LI ZIQI, YANG GUANG, LIU ZHUO, YU BIN, WANG QIANG, FU JIEBIN, WANG BIN
Принадлежит:

The invention discloses an unmanned aerial vehicle which comprises a fuselage, wings, an empennage, a control surface, an undercarriage plaque spring and an air inlet channel, the fuselage and the wings can be in quick butt joint, and the empennage and the wings can be in quick butt joint; the control surfaces and the wings can be quickly disassembled and assembled; the undercarriage plaque spring is fixedly located at the abdomen of the fuselage, and the structure of the undercarriage plaque spring is optimized according to the stress condition; the air inlet channel is connected with the machine body and is integrally formed with the machine body. According to the unmanned aerial vehicle disclosed by the invention, the flight efficiency can be improved.

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Номер записи: 7
25-03-2015 дата публикации

Novel engine installing structure

Номер: CN104443401A
Автор: DENG CHENGYANG, JI XIANWU, LIANG HAO, XU HUANYU, WU GENLIN, FU JIEBIN, CHEN LIGEN, HU DINGHONG, LI WEIDONG, XIONG YI, WANG BIN, ZHANG WEI, YIN XIAOXIA, CHEN LONGHUI, WANG ZHIZHU, DU JINRONG
Принадлежит:

The invention relates to a novel engine installing structure and belongs to the technical field of airplane design. An engine structural-steel framework area is provided with upper supports and lower supports. The rear end of an engine is fixed to a structural-steel frame through the supports. The two sides of the engine are fixed on a steel pipe I and a fuselage frame through standard belts. Upper girders on the two sides of a fuselage are each provided with one upper support. The upper end of the engine is fixed to a fuselage frame II and a steel pipe II through standard belts. Lower girders on the two sides of the fuselage are each provided with one lower support. The lower end of the engine is fixed to a steel pipe III and a fuselage frame III through standard belts. The novel engine installing structure is applied to low-speed airplanes such as a general-purpose airplane and an agriculture and forestry airplane, and has the advantages of being simple in structure, low in manufacturing ...

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Номер записи: 8
11-03-2015 дата публикации

Novel turnover preventing structure

Номер: CN104401477A
Автор: YIN XIAOXIA, YAN LIQING, DENG CHENGYANG, JI XIANWU, LIANG HAO, WU GENLIN, XU HUANYU, FU JIEBIN, CHEN LIGEN, HU DINGHONG, LI WEIDONG, XIONG YI, WANG BIN, ZHANG WEI, CHEN LONGHUI, WANG ZHIZHU
Принадлежит:

The invention relates to a novel turnover preventing structure, and belongs to the technical field of airplane structure design. In the structure, a steel framework is divided into three parts including a fuel tank area steel framework, a workbin area steel framework and a cabin area steel framework; an inclined cross-rod steel tube is arranged at the cabin section of the cabin area steel framework to form a triangular structure I with the cabin area steel framework; the inclined cross-rod steel tube, the cabin area steel framework and a cockpit are connected to form a triangular structure II. The novel turnover preventing structure disclosed by the invention is used for general-purpose airplanes, agricultural and forestry airplanes and other low-velocity airplanes, and has the advantages of simple structure, high reliability and low cost.

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Номер записи: 9
01-04-2015 дата публикации

Novel folding wall plate structure

Номер: CN104477369A
Автор: DENG CHENGYANG, JI XIANWU, LIANG HAO, WU GENLIN, XU HUANYU, FU JIEBIN, CHEN LIGEN, HU DINGHONG, LI WEIDONG, XIONG YI, WANG BIN, ZHANG WEI, YIN XIAOXIA, CHEN LONGHUI, WANG ZHIZHU
Принадлежит:

The invention relates to a novel folding wall plate structure, belonging to the technical field of airplane designs. The wall plate is divided into an upper wall plate and a lower wall plate which are connected by virtue of a rivet and a hinge structure, wherein the section thickness of the lower wall plate is smaller than that of the upper wall plate. According to the novel folding wall plate structure disclosed by the invention, the original one large-area wall plate is replaced into two small-area wall plates which are connected by virtue of the hinge structure, so that only the small-area wall plate corresponding to a to-be-dismounted part needs to be dismounted once the wall plate needs to be opened, and thus, a good channel is provided for the maintenance of the airplane, and a problem that the large wall plate is long in dismounting period is avoided. The novel folding wall plate structure is suitable for a low altitude airplane, and has the advantages of simple structure, high reliable ...

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Номер записи: 10