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Spacecraft non-centroid relative movement modeling method

A technology of relative motion and modeling methods, applied in the direction of instruments, adaptive control, control/regulation systems, etc., can solve problems such as reducing the efficiency of task completion

Inactive Publication Date: 2017-10-24
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0004] In the existing modeling methods, the rigid body or the center of mass of the spacecraft is used as the motion reference point for the description of motion. However, in the process of operation tasks such as on-orbit maintenance, on-orbit assembly, and recovery of abandoned maintenance, it is often necessary to consider the The relative motion between the devices on the surface (non-centroid) of the device, the centroid model requires additional motion planning for the operating points on the surface during the task operation, which reduces the efficiency of task completion

Method used

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  • Spacecraft non-centroid relative movement modeling method

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Embodiment

[0088] The simulation background is designed as the close rendezvous stage of the spacecraft on orbit. Here, it is assumed that the target spacecraft is flying in orbit without maneuvering, and in order to facilitate the calculation of the projection of its velocity screw in its own system, the main axis of the body coordinate system of the target spacecraft is consistent with the main axis of the orbit coordinate system during operation, and its The parameter setting of the motion track is shown in Table 1:

[0089] Table 1. Orbital parameters of the target spacecraft

[0090] Number of six tracks

[0091] Both mass and moment of inertia are real values ​​and remain constant. Using the non-centroid relative motion attitude-orbit coupling model established by the present invention, the attitude-orbit coupling control in the rendezvous process is carried out, and the simulation results are as follows Figure 3-Figure 8 As shown in the figure, it can be seen from the f...

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Abstract

The invention discloses a spacecraft non-centroid relative movement modeling method. By introducing the appropriate conversion operator, the relative speed screw between the non-centroid docking points is established, and then based on the basic mechanics principle and screw theory, the derivation is carried out to obtain a non-centroid point relative movement attitude and trajectory coupled model. The modeling method has the characteristics of concise and convenient operation, and is compact in formula expression and easy to analyze and understand.

Description

technical field [0001] The invention relates to the technical field of relative motion of spacecraft, and relates to a modeling method for non-centroid relative motion of a spacecraft. Background technique [0002] Modeling and control of relative motion of spacecraft is the basis for space approach, rendezvous and docking, module replacement, and capture operations. Existing modeling methods mainly focus on relative motion modeling with the center of mass as the reference point, including vector algebra-based The modeling method of description and the modeling method based on spiral pair description of even numbers. [0003] The modeling of spatial relative motion based on the vector algebra method is generally to combine the orbital dynamics model described by the position vector and the attitude dynamics model described by the direction cosine (or quaternion or Rodrigues parameter), the essence of which is Separate modeling of rotation and translation is not conducive to...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 朱战霞刘红庆樊瑞山袁建平
Owner NORTHWESTERN POLYTECHNICAL UNIV
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