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Extraterrestrial celestial body surface soft landing closed-loop follow-up control test method

A test method and closed-loop technology, applied in the field of spacecraft, can solve the problems of affecting the adequacy of the test, limiting the number of ignition tests, increasing the difficulty of implementation and safety requirements, and achieving the effect of saving test costs and improving reliability

Active Publication Date: 2021-06-18
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

These factors increase the difficulty of implementation and safety requirements, and also limit the number of ignition tests, affecting the adequacy of the test

Method used

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Embodiment Construction

[0047] In order to make the object, technical solution and advantages of the present invention clearer, the embodiments disclosed in the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0048] Such as figure 1 , in this embodiment, the soft landing closed-loop follow-up control test method on the surface of an extraterrestrial celestial body includes:

[0049] Step 1, install the verifier in the closed-loop follow-up control test system through the sling, and determine the initial position f of the verifier in the closed-loop follow-up control test system 0 (x,y,z) and initial pose ρ 0 (α,β,γ); then start the experiment.

[0050] In this embodiment, before step 1 is executed, it also includes:

[0051] (1) Establish a closed-loop servo control test system.

[0052] In this example, if figure 2 , the closed-loop follow-up control test system includes: test tower, X-direction servo motor, Y-direction servo motor, ...

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Abstract

The invention discloses an extraterrestrial celestial body surface soft landing closed-loop follow-up control test method, which adopts a closed-loop follow-up control test system to replace a real engine to realize the function of an execution mechanism, and equivalently verifies the soft landing process of a spacecraft on an extraterrestrial celestial body without real ignition of the engine. The method comprises the following steps: connecting a closed-loop follow-up control test system with a verifier; hoisting the verifier to an initial position and finishing alignment of the initial position; determining the displacement of the lifting rope according to the pose parameters, sent by the verifier in real time, of the next control period, and driving the verifier to move to the target position; and according to the real-time navigation of the verifier and the external measurement result of the test field, evaluating the follow-up control result of the verifier every time, and moving the verifier to a final target landing point to complete the test verification. According to the method, the problem of open-loop control of a traditional extraterrestrial celestial body soft landing task ground verification platform is solved, and the problem of insufficient verification of autonomous navigation, guidance and control strategies of a spacecraft is avoided.

Description

technical field [0001] The invention belongs to the technical field of spacecraft, in particular to a closed-loop follow-up control test method for soft landing on the surface of an extraterrestrial celestial body. Background technique [0002] The orbit change control of the spacecraft during its in-orbit flight is all completed by the ground, that is, the orbit of the spacecraft is obtained by the ground measurement and control system, and the speed increment required for orbit change is calculated according to the parameters of the spacecraft mass, engine specific impulse, and target orbit. , the ground generates the orbit change attitude and engine ignition time and uploads them to the spacecraft. Finally, the orbit adjustment is completed through multiple cooperations between the spacecraft and the ground. During this process, the spacecraft is in an open-loop control mode. However, for spacecraft that perform soft landing on the surface of extraterrestrial celestial bo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0243G05B2219/24065
Inventor 赵洋任德鹏邢卓异李青白崇延
Owner BEIJING INST OF SPACECRAFT SYST ENG
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