Spacecraft separation test system and method

A technology for space vehicle and separation test, applied in the field of space vehicle separation test system, can solve the problem of inability to accurately test separation performance indicators, etc., and achieve the effects of simple operation, high precision and high efficiency

Inactive Publication Date: 2017-04-26
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology

[0003] The object of the present invention is to provide a space vehicle separation test system and method to solve the problem that the existing space vehicle separation test method cannot accurately test the performance index of separation

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  • Spacecraft separation test system and method
  • Spacecraft separation test system and method
  • Spacecraft separation test system and method

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Embodiment Construction

[0033] In order to better illustrate the present invention, the present invention will be described in detail with a preferred embodiment and with accompanying drawings, specifically as follows:

[0034] Such as figure 1 , 2 As shown, the space vehicle separation test system provided in this embodiment is used to separate the first separation test piece A from the second separation test piece B, wherein the second separation test piece B is fixedly arranged on the ground through the fixing tool 8, and the separation Before the test starts, the first separation test piece A and the second separation test piece B are connected by a separation mechanism. The separation mechanism in this embodiment includes several locking devices. The first separation test piece A and the second separation test piece B When the two bodies are not separated, a surface C to be separated is formed, and the locking device is arranged on the surface C to connect the two bodies to be separated. Speci...

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Abstract

The invention provides a spacecraft separation test system and method, and the system comprises a gravity balance device, a suspension device, a suspension point adjustment device, an inertia testing device, a photographing device, and a time signal measurement device. A second separation test piece is fixed with the ground, and a first separation body is connected with the gravity balance device through the suspension point adjustment device and the suspension device. The gravity balance device outputs a balance force, and simulates a weightless environment. After separation, an upper separation test piece can freely rotate at six freedom degrees, and the inertia testing device is used for testing the acceleration and angular speed of the separation body in a separation process. The photographing device tests the separation speed of the separation body, and the time signal measurement device separates time. After the testing of separation parameters, the gravity balance device carries out the deceleration buffering of the separation test piece. The method achieves the complete measurement of separation characteristic parameters of a spacecraft, is high in testing precision, is simple and convenient to operate, is high in efficiency, is high in adaptability, and is safe and reliable.

Description

technical field [0001] The invention relates to the technical field of space vehicle ground tests, in particular to a space vehicle separation test system and method. Background technique [0002] With the development of space vehicles, especially the development of requirements for deep space exploration missions, the aircraft is developing towards multi-combination states and multi-flight conditions, such as moon exploration, fire detection, manned spaceflight and other missions. The process involves the separation of multiple devices, and a large number of ground separation tests need to be carried out during the development process to verify the correctness and rationality of the design. At present, GJB2205 stipulates a variety of separation test methods, namely the star-arrow unlocking test method, the drop tower test method, and the pendulum test method. The star-arrow unlocking test method is only used to test the unlocking function, and cannot test the performance i...

Claims

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Application Information

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IPC IPC(8): G01M99/00B64G7/00
CPCG01M99/00B64G7/00G01M99/004
Inventor 王金童唐杰张玉花侯建文雷雨胡震宇吴昊
Owner SHANGHAI AEROSPACE SYST ENG INST
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