Modeling method for large complex coupling spacecraft kinetic model

Abstract

The invention relates to the field of automatic control technologies and mechanical modeling, and provides a modeling method for a large complex coupling spacecraft kinetic model, so that an established mathematical model is more suitable for an actual satellite model. The invention relates to a modeling method of a large complex coupling spacecraft kinetic model. The modeling method comprises thefollowing steps: S1, establishing a spacecraft solar panel simplified model; S2, establishing a liquid sloshing kinetic model; S3, establishing a molten steel spacecraft coupling model; S4, supplementing the established liquid sloshing model to obtain a liquid sloshing mathematical model closer to a designed sloshing rule; S5, establishing a dynamic model of the large flexible liquid-filled spacecraft by considering the vibration of the flexible accessory in S1 and the coupling influence of the liquid sloshing in S2 and S3 on the rigid body at the same time; and S6, finally, according to analysis of the rigid-flexible spacecraft model and the rigid-liquid spacecraft model, establishing a large flexible liquid-filled spacecraft model. The method is mainly applied to spacecraft kinetic model modeling.

Description

technical field [0001] The invention relates to the fields of automatic control technology and mechanical modeling. In particular, it relates to a modeling method for a dynamic model of a large complex coupled spacecraft. Background technique [0002] With the continuous development of space technology and the continuous growth of aerospace demand, spacecraft mainly develop along two major directions: one is miniaturization and clustering, and multiple micro-satellites cooperate to perform a certain task; the other is large size and structure. complex, allowing satellites to perform missions in space for extended periods of time. For large satellites, the structure is becoming more and more complex and the size is getting larger and larger. However, due to the limitation of launch cost and carrying capacity, while reducing the weight of the spacecraft, the flexibility of the structure is also increasing. When the spacecraft completes actions such as maneuvering, turning an...

AI Technical Summary

Problems solved by technology

For large satellites, the structure is becoming more and more complex and the size is getting bigger and bigger. However, due to the limitation of launch cost and carrying capacity, while reducing the weight of the spacecraft, the flexibility of the structure is also increasing.

When the spacecraft completes actions such as maneuvering, turning and docking in the air, it is easy to arouse the vibration of the flexible structure, which will increase the adjustment time of the star's attitude, affect the pointing accuracy and the normal work of the spacecraft's precision instruments

In addition, with the improvement of the spacecraft's carrying capacity, maneuverability and long life, the ratio of liquid fuel mass to the total mass of the spacecraft continues to increase, and this adverse effect also increases. It is unavoidable in the design of the spacecraft’s attitude control system. The increase in fuel mass will easily lead to strong sloshing of the liquid in the spacecraft’s liquid storage tank, which will seriously affect the accuracy and stability of the star’s attitude control.

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