On-orbit separation ground test device and detection method of binary star assembly spacecraft

A technology of ground test and detection method, which is applied to the simulation device, transportation and packaging of space navigation conditions, space navigation equipment, etc. It can solve the problems of unsuccessful instructions and reports, and achieve economical and effective gravity unloading and system stability. Good performance, to achieve the effect of gravity unloading

Active Publication Date: 2020-07-14
SHANGHAI INST OF SATELLITE EQUIP
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Problems solved by technology

[0004] Descriptions and reports of success with such techniques have not yet been received

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  • On-orbit separation ground test device and detection method of binary star assembly spacecraft
  • On-orbit separation ground test device and detection method of binary star assembly spacecraft
  • On-orbit separation ground test device and detection method of binary star assembly spacecraft

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Embodiment Construction

[0049] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0050] Such as figure 1 As shown, the present invention provides a kind of ground test device (hereinafter referred to as test device) that two independent stars A and B are separated on the ground by unlocking and separating devices for binary star assembly spacecraft separation, including simulated star A11, simulated Star body B8, gantry 1, pulley assembly 2, limit assembly, counterweight 3, dynamometer 5, gas separation equipment 9, and laser tracker 10; wherein, the pulley assembly 2 is installed o...

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Abstract

The invention provides a test device which simulates a satellite in-orbit state and separates two independent stars A and B through unlocking and separating devices on the ground and a detecting method. According to the scheme, a simulated star A is suspended by a structure mainly, and is unloaded gravitationally so as to simulate a test environment during separation of the star A and the star B;an unlocking bolt is unlocked by gas separation equipment, and the simulated star A acquires an upward thrust through a separating spring; by a pulley block and a balance weight mode, the gravity of the simulated star A is balanced; and by T-Prob of a laser tracker, position postures (x, y, z, alpha, beta, gamma) of the simulated star A in a whole upward movement process are acquired in real time.The test principle is simple, and the test device is easy to operate; an in-orbit state can be simulated, and gravitational balanced unloading to a spacecraft is realized effectively; a separation route is not lower than 80 mm; a balance force in the route is stable, and deviation is not greater than 0.1%; and a separation route is finished, the gradient of a system is smaller than 1 degree, andthe stability of the system is good.

Description

technical field [0001] The invention relates to a spacecraft test device, in particular to a ground test device and a detection method for the on-orbit separation of a binary-satellite assembly spacecraft. In particular, it is an on-orbit separation ground test device for a double-star assembly spacecraft that separates two independent stars A and B on the ground through an unlocking separation device. Background technique [0002] The common spacecraft separation test is to assess the separation between satellites and rockets. The object of the assessment is the pyrotechnic cutter and whether it can correctly ensure the normal separation between the satellites and rockets, and the content of the assessment does not include the separation distance. Therefore, in In the conventional separation test, it is not required to have a spatial displacement after the separation of the star and rocket. However, with the development of aerospace technology, the designer proposed a desi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 李金柱倪骏赵红张蓉姜祎君周国辉
Owner SHANGHAI INST OF SATELLITE EQUIP
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