Attitude cooperative tracking control method for distributed spacecraft

A tracking control and spacecraft technology, which is applied in the field of multi-spacecraft formation flight, can solve the problems of unknown change degree of spacecraft rotational inertia, spacecraft attitude control system control input saturation, etc.

Active Publication Date: 2020-10-09
YANCHENG INST OF TECH
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Problems solved by technology

In addition, the spacecraft will be subject to unknown disturbance moments caused by gravity gradient, solar light pressure, solar radiation, etc., and due to the influence of fuel consumption, liquid sloshing and solar panel rotation, the moment of inertia of the spacecraft will change from time to

Method used

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  • Attitude cooperative tracking control method for distributed spacecraft
  • Attitude cooperative tracking control method for distributed spacecraft
  • Attitude cooperative tracking control method for distributed spacecraft

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[0082] Example

[0083] Using a formation system consisting of 4 following spacecraft and 1 leader as the research object, figure 2 A directional communication topology is given, including 4 follower spacecraft (marked as nodes 1, 2, 3, 4) and 1 navigator (marked as node 0). It can be seen that there is only the first spacecraft The device can obtain the information of the leader.

[0084] Leader trajectory: ω 0 =[0.1sin(0.2t),0.1cos(0.2t),0.1cos(0.5t)] T , with It can be obtained by kinematic equation (1).

[0085] The specific parameters of the four following spacecraft are as follows:

[0086] Table 1. Spacecraft inertia matrix and initial attitude

[0087]

[0088] Input saturation value τ 1max =[3,1,2] T Nm,τ 2max =[4,2,2] T Nm,τ 3max =[2,3,2] T Nm,τ 4max =[4,2,2] T Nm. External interference i =(0.5+||ω i || 2 )[0.02sin(t),0.05cos(t),0.03cos(t)] T , I=1,2,3,4. The initial value of the observer state and adaptive parameter is σ i (0)=[0,0,0] T , Ρ i (0)=[0,0,0] T , The ...

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Abstract

The invention discloses an attitude cooperative tracking control method for a distributed spacecraft, and relates to the technical field of spacecraft formation flight. A communication topological structure which has few communication paths and only enables a part of followers to obtain pilot information is adopted among spacecraft formation members, and in order to obtain the pilot information, adistributed finite time state observer is designed to observe the pilot information; a rapid nonsingular terminal sliding mode control algorithm is adopted to enable the attitude of a formation spacecraft to be rapidly coordinated and tracked, a saturation function is input to limit the amplitude of a control moment, and a self-adaptive algorithm is adopted to perform self-adaptive compensation on inertia change and external disturbance. A distributed spacecraft formation adaptive finite time attitude cooperative tracking control method is designed. According to the method, the considerationof communication resources, input saturation, rapid convergence, external interference and inertia uncertainty is more perfect, the formation spacecraft attitude cooperative tracking error system canbe rapidly converged, and the robustness and practicability of the system are improved.

Description

technical field [0001] The invention relates to the technical field of multi-spacecraft formation flight, in particular to an attitude cooperative tracking control method of distributed spacecraft. Background technique [0002] With the diversification of space missions, the traditional working mode in which a single spacecraft completes tasks alone has been difficult to meet the needs of practical space missions such as synthetic aperture imaging, space exploration, satellite capture, space-based interferometry, and long-distance communication. In this context, the research on multi-spacecraft formation flight has developed rapidly, and attitude coordination, as the basic technology of spacecraft formation flight, has become one of the research hotspots in recent years. [0003] The attitude cooperative control is carried out through information transmission between individual spacecraft in the formation, so as to achieve specific space missions. The formation of multiple ...

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/104
Inventor 高直朱志浩
Owner YANCHENG INST OF TECH
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