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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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Форма поиска

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 14. Отображено 14.
11-02-2015 дата публикации

Locking device

Номер: CN104345768A
Автор: TONG QIANG, LI LIMING, YU GUOQING, XUE WEISONG, ZHANG JUNMING, HE DONGXU, KONG FANLIANG, SHEN TIEJUN, LI YANZE, SUN YUFENG
Принадлежит:

The invention belongs to the technical field of locking device design, and particularly relates to a great-load locking device. The great-load locking device comprises a locking module and an unlocking module. The automatic locking is realized through the tension force of a tension spring and a mechanical structure of a lock body per se. The locking device has the advantages that the structure is simple, the locking force is great, and the locking is reliable. The locking and unlocking processes are smooth and reliable. The tension spring is adopted, so that the unexpected unlocking of a lock in the electric control process when accidents such as power failure occur can be avoided, the unlocking is realized through a hydraulic or pneumatic actuator cylinder, and in addition, a hydraulic or pneumatic valve can be controlled through external connection of external triggering signals to realize the automatic control.

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Номер записи: 1
30-07-2014 дата публикации

Hydraulic adjusting module for undercarriage lowering and hoisting test

Номер: CN103953599A
Автор: ZHENG MU, LIU DAYONG, WANG JIANFENG, KONG FANLIANG, XUE WEISONG, DONG WEI, CAI XIAOXU
Принадлежит:

The invention belongs to the technical field of hydraulic pressure, and relates to a hydraulic adjusting module for undercarriage lowering and hoisting test. The hydraulic adjusting module comprises a hydraulic source oil return quick-change connector, a hydraulic source oil supply quick-change connector, a valve block, a high pressure ball valve, an emergency system oil supply quick-change connector, a normal system oil supply quick-change connector, an emergency system oil return quick-change connector, a normal system oil return quick-change connector, a multi-way meter switch, a speed control valve and a pressure meter. The hydraulic adjusting module adopts a single-way to double-way hydraulic adjusting module conversion structure, realizes that one set of hydraulic oil source is converted into a double-way adjustable pressure and flow oil source, successfully realizes that different pressures and flows of two sets of oil source oil supply systems on an airplane are simulated through ...

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Номер записи: 2
28-05-2014 дата публикации

Wireless dynamic balance test bench hinge torque measurement method

Номер: CN103822741A
Автор: LIU ZAIXING, YANG SHITAO, XUE WEISONG, ZHANG JUNMING, LI HUIBIN, XIA XIAODONG, SHI YUE
Принадлежит:

The invention belongs to the technical field of helicopter test, and particularly relates to a blade dynamic balance test bench hinge torque measurement method. According to the method, data measured by a force sensor is transmitted by a transmitting device in a wireless signal mode, and then a receiving device receives the data measured by the force sensor and transfers the data to data acquisition equipment for recording and storing. Namely, when a rotor head drives helicopter blades to rotate on a dynamic balance test bench, the force sensor generates a signal, and the signal is transmitted by the transmitting device above the rotor head in a wireless signal mode, received by the receiving device and transferred to signal acquisition equipment so as to complete data acquisition and recording.

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Номер записи: 3
15-06-2011 дата публикации

Load control method for aircraft flap experiment

Номер: CN0102095577A
Автор: WEISONG XUE, MU ZHENG, CHUNLAN ZHAO, JIANFENG WANG, PEIJUN XIAO, ZHANGHUA ZHANG, LIYA LIANG, XUE WEISONG, ZHENG MU, ZHAO CHUNLAN, WANG JIANFENG, XIAO PEIJUN, ZHANG ZHANGHUA, LIANG LIYA
Принадлежит:

The invention relates to a load control method for an aircraft experiment, in particular to a load control method for an aircraft flap experiment. In the method, a mode that a flap movement angle and the turning pulse signal of a driving mechanism output shaft correspond is adopted, and the pulse signal serves as the reference to carry out follow-up load. The method mainly comprises three-aspect contents, i.e. a segmented linear simulation non-linear control mode, an in-segment speed-regulation compensation mode and an in-segment pulse counting point-by-point load mode. With the method, a passive and precise follow-up non-linear load is realized, the operation response speed and the control precision of a loading system are improved, system stability is enhanced, and the load control method can be used for aircraft flap experiments for driving mechanism output shafts with a pulse output signal.

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Номер записи: 4
18-07-2023 дата публикации

Colorectal cancer organoid drug sensitivity evaluation and prognosis prediction system, method and equipment

Номер: CN116445574A
Автор: TANG YUTING, YAN JUN, XUE WEISONG, WANG TING, ZHANG BIAO, CHEN ZHENBANG, WANG SHIJIE, DONG SHUMIN
Принадлежит:

The invention belongs to the technical field of drug sensitivity detection, and discloses a colorectal cancer organoid drug sensitivity evaluation and prognosis prediction system, method and equipment, the colorectal cancer organoid drug sensitivity evaluation system comprises: a standard establishment module, which is used for establishing an organoid drug sensitivity evaluation standard, the chemosensitivity and the non-sensitivity are distinguished based on drug sensitivity evaluation criteria; and the standard verification module is used for verifying the established organoid drug sensitivity evaluation standard. The colorectal cancer organoid drug sensitivity evaluation method comprises the following steps: establishing an organoid drug sensitivity evaluation standard, and distinguishing chemosensitivity and non-sensitivity based on the drug sensitivity evaluation standard; and verifying the established organoid drug sensitivity evaluation standard. The method can quantitatively, directly ...

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Номер записи: 5
29-10-2014 дата публикации

Helicopter main blade dynamic balancing test bed hydraulic drive system

Номер: CN104122034A
Автор: YANG SHITAO, XUE WEISONG, ZHANG JUNMING, LI HUIBIN, XIA XIAODONG, SHI YUE
Принадлежит:

The invention belongs to the technical field of rotary speed control of a helicopter main blade dynamic balancing test bed, and relates to a helicopter main blade dynamic balancing test bed hydraulic drive system. The helicopter main blade dynamic balancing test bed hydraulic drive system includes a hydraulic pump, a hydraulic pipeline, a hydraulic motor, a servo control system and a motor; the motor is connected to the hydraulic pump; the hydraulic pump is connected to the hydraulic motor via the hydraulic pipeline; the hydraulic motor is connected to a balancing test bed spindle through a gearbox; the servo control system includes a servo valve, a spindle speed measuring device, a control computer and a comparator; the servo valve is connected to the hydraulic pump; the spindle speed measuring device is connected to the control computer via a wire; the comparator is connected to the control computer via a wire; and the comparator is connected to the servo valve via a wire. The helicopter ...

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Номер записи: 6
29-10-2014 дата публикации

Hinge moment measurement system of helicopter main blade dynamic balance testing bench

Номер: CN104122017A
Автор: YANG SHITAO, XUE WEISONG, ZHANG JUNMING, LI HUIBIN, XIA XIAODONG, SHI YUE
Принадлежит:

The invention, which belongs to the technical field of dynamic balance testing bench measurement of the helicopter main blade, relates to a hinge moment measurement system of a helicopter main blade dynamic balance testing bench. The system consists of a force sensor, a signal transmitting device, a signal receiving device and a signal acquisition device. The signal transmitting device is installed at the center of the upper end of a rotor head; the force sensor is connected with the signal transmitting device by a lead and signal acquisition and modulation transmitting are carried out on electric signals from the force sensor in the signal transmitting device; and the signal receiving device connected with the signal acquisition device by a lead carries out signal demodulation on a received radio wave and inputs the demodulated signal into the signal acquisition device. According to the invention, a problem of poor contact of the slip ring system in the original system can be solved; the ...

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Номер записи: 7
29-10-2014 дата публикации

Helicopter main blade cone height measurement method

Номер: CN104121855A
Автор: YANG SHITAO, XUE WEISONG, ZHANG JUNMING, LI HUIBIN, XIA XIAODONG, SHI YUE
Принадлежит:

The invention belongs to the technical field of helicopter main blade measurement, and relates to a helicopter main blade cone height measurement method. The method comprises a first step of arranging three beams of laser having transmitting and receiving functions, wherein two beams are parallel lasers which are perpendicular to a rotation plane of a helicopter main blade and have the same distance to the rotation center of the main blade, and the other beam is an oblique laser which has two intersection points, between which the vertical distance is measured as H0, with the two parallel lasers; a second step of initiating a helicopter rotor head to rotate, with a main blade tip cutting the three beams of laser, and obtaining the time T that the main blade spends from cutting the first beam of laser to cutting the oblique laser and the time difference T0 that the main blade spends in cutting the two parallel lasers; and a third step of calculating the height H of the main blade by use ...

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Номер записи: 8
05-08-2015 дата публикации

Burner of aircraft fire protection testing apparatus

Номер: CN104819466A
Автор: ZHENG MU, YANG SHITAO, XUE WEISONG, DONG WEI, CAI XIAOXU, XUE NAIQI
Принадлежит:

The invention belongs to an aviation testing technique and relates to improvement of a burner of aircraft fire protection testing apparatus. The burner comprises a housing (1), a burning chamber (3) and a mixing base (4) and is characterized in that a mixing net module (5) is arranged in a lower port of the housing (1) and located on an air outlet of the mixing base (4), an annular cooling sleeve (7) is arranged on the outer surface of the housing (1), at least three compressed air inlet connecting nozzles (9) evenly distributed in the circumference are formed in the lower surface of the cooling sleeve (7), and a circle of cooling air inlet holes (8) evenly distributed in the circumference are formed in the outer surface of the housing (1). By means of the burner of the improved aircraft fire protection testing apparatus, the flame temperature uniformity of the burner is greatly improved, and the flame temperature of the burner meets the standard requirement.

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Номер записи: 9
29-10-2014 дата публикации

Helicopter main blade dynamic balancing test bed servo valve system

Номер: CN104122033A
Автор: YANG SHITAO, XUE WEISONG, ZHANG JUNMING, LI HUIBIN, XIA XIAODONG, SHI YUE
Принадлежит:

The invention belongs to the technical field of rotary speed control of a helicopter main blade dynamic balancing test bed, and relates to a helicopter main blade dynamic balancing test bed servo valve system. The helicopter main blade dynamic balancing test bed servo valve system is characterized in that the servo valve system comprises an angle sensor (6), a servo valve (1) and a valve seat (2); the angle sensor (6) and the servo valve (1) are respectively installed on the valve seat (2); the valve seat (2) is connected to a hydraulic pump, and an actuator cylinder (4) is fixed in the hydraulic pump and is connected to the valve seat (2) via an oil path; and the hydraulic actuator cylinder (4) is connected to a hydraulic pump swash disc (5), and a connecting rod of the angle sensor (6) is connected to the hydraulic pump swash disc (5). According to the invention, by use of a split structure, the cost is saved significantly under the premise of ensuring experimental table rotational speed ...

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Номер записи: 10
11-02-2015 дата публикации

Tool drilling method for parts in closed space

Номер: CN104338955A
Автор: LI LIMING, YU GUOQING, TONG QIANG, XUE WEISONG, ZHANG JUNMING, HE DONGXU, KONG FANLIANG, SHEN TIEJUN, LI YANZE, SUN YUFENG
Принадлежит:

The invention belongs to the technical field of aircraft assembly and in particular relates to a tool drilling method for parts in closed space. According to the tool drilling method, basic holes are formed in the lower surface in a box body and all have space angles, so that after the box body is mounted, the basic holes are closed in the box body. By a transition die, the shape of the closed part and the holes to be drilled are completely and accurately copied to replace the box body, and the drilling operation can be finished without mounting of the box body.

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Номер записи: 11
30-07-2014 дата публикации

Fatigue test loading mechanism with tensile pressing cushion

Номер: CN103954502A
Автор: DONG WEI, ZHENG MU, XUE WEISONG
Принадлежит:

The invention belongs to the field of fatigue test loading, and relates to a fatigue test loading mechanism with a tensile pressing cushion. The tensile pressing cushion of the loading mechanism consists of an adhesive tape, a clamp, an aluminum rod and a rubber block, wherein the adhesive tape is formed by sewing flax canvas and comprises four parts including covering cloth, filling cloth, bottom cloth and reinforced cloth. According to the mechanism, the breakthrough that the bidirectional load is finished through mounting on one single side of a test piece is realized, the adhesion quantity of the adhesive tape, the machining and mounting quantity of levers, and the mounting quantity of test loading equipment can be reduced to be half in the previous test, and therefore, the test tool cost, the tool mounting amount and the maintenance cost are greatly reduced, the working efficiency is improved, and the interference problem caused by test restriction points is avoided; moreover, the ...

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Номер записи: 12
05-08-2015 дата публикации

Aircraft fire protection testing burner air supply system

Номер: CN104819467A
Автор: ZHENG MU, YANG SHITAO, XUE WEISONG, DONG WEI, CAI XIAOXU, XUE NAIQI
Принадлежит:

The invention belongs to an aviation testing technique and relates to improvement of an aircraft fire protection testing burner air supply system. The aircraft fire protection testing burner air supply system comprises a compressor (1), a pressure reducing valve (2), a first energy storage tank (3), a first throttling valve (4), a second throttling valve (5), a third throttling valve (6) and a burner (7) and is characterized in that a pressure stabilizing valve (8) and a second energy storage tank (9) are arranged between the compressor (1) and the pressure reducing valve (2). The improved aircraft fire protection testing burner air supply system greatly reduces flame temperature fluctuation of the burner and improved temperature stability and cooling air temperature adjusting effect.

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Номер записи: 13
11-02-2015 дата публикации

Anti-instability structure for composite plate part during airworthiness verification tests

Номер: CN104340376A
Автор: LI LIMING, YU GUOQING, TONG QIANG, XUE WEISONG, ZHANG JUNMING, HE DONGXU, KONG FANLIANG, SHEN TIEJUN, LI YANZE, SUN YUFENG
Принадлежит:

The invention relates to the technical field of composite structure part tests, in particular to an anti-instability structure for a composite plate part during airworthiness verification tests. The anti-instability structure comprises a base (1), side supporting seats (4) and clamping blocks (5), wherein the side supporting seats (4) are fixed to a T-shaped groove (9) of the base (1) by T-shaped groove bolts (2); the clamping blocks (5) are fixed to the long holes (8) of the side supporting seats (4) by bolts (3); the whole set of anti-instability structure is fixed with a loading device (7) through the T-shaped groove bolts (2). According to the anti-instability structure, the problem of redesign of a test tool for composite plate test parts with different specifications is solved, and the commonality of the test tool is achieved; the anti-instability structure is successfully applied to three different aircraft component or detail component tests, the conformity of the composite aircraft ...

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Номер записи: 14