A Spacecraft Attitude Follow-up System Applicable to Dynamic Variation of Center of Mass

Abstract

A spacecraft attitude follow-up system suitable for dynamic changes in the center of mass of the present invention includes a follow-up support frame, a spacecraft center-of-mass following clamping module, and a control module. The follow-up support frame can ensure that the spacecraft does not suffer from gravity under low friction Adjust its pitch and yaw angles under the influence of the environment; the center of mass of the spacecraft follows the clamping module to follow the rolling motion of the spacecraft, and when the center of mass of the spacecraft changes, the existing attitude of the spacecraft remains unchanged Follow its center of mass to ensure that the suspension force and the center of mass of the spacecraft are always on the same straight line; the data acquisition control module is responsible for system signal transmission and coordinated control, so that each module of the system works according to the system design, and completes the tracking and tracking of the attitude of the spacecraft. The center of mass of the spacecraft automatically follows when the center of mass changes, and has the advantages of simple and compact structure, small size, and high precision.

Description

Technical field [0001] The invention belongs to the technical field of spacecraft space task ground verification, and in particular relates to a spacecraft attitude follow-up system suitable for dynamic changes of the center of mass. Background technique [0002] There is a major difference between the space environment and the ground laboratory environment. In order to ensure the successful completion of the space mission of the spacecraft, the space environment must be partially or fully simulated when verifying various performances of the spacecraft on the ground. [0003] When the spacecraft moves in space, it is in an unconstrained microgravity environment from free to free, and the ground laboratory is a gravity environment. In order to verify the completion of the space mission of the spacecraft on the ground, it is necessary to ensure that the gravity of the spacecraft during the verification is basic to its motion. There is no effect and the spacecraft is in a float...

AI Technical Summary

Problems solved by technology

The common methods of weightlessness are parabolic flight and free fall. The disadvantages of this method are short time, large space occupation, limited space and high cost; liquid flotation method has large damping, high maintenance cost and is only suitable for low-speed motion; The levitation distance of the magnetic levitation method is limited, that is, the movement of the spacecraft part is limited, and electromagnetic interference will be generated; while the system structure of the air flotation method and the suspension method is relatively simple, and it is easy to establish an unconstrained microgravity environment in the laboratory, but the air flotation method Generally, only five degrees of freedom can be provided.

In addition, considering that space missions such as space rendezvous and docking require the spacecraft to extend out of the docking mechanism, its structure changes, causing the overall center of mass of the spacecraft to shift. The existing technology is basically realized by multi-point suspension, but the system structure Complicated, increasing the difficulty of control

[0004] In order to overcome the situation that the existing spacecraft ground test method is not suitable for the change of the spacecraft center of mass, the present invention proposes a compact attitude follow-up system suitable for the change of the spacecraft structure center of mass, which improves the ground verification navigation, guidance and control. system reliability

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