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Finite-time posture fault-tolerant control method for spacecraft formation

A limited-time, fault-tolerant control technology, applied in the field of multi-spacecraft formation flight, can solve problems such as unknown and momentary changes in spacecraft inertia, and achieve the effects of short coordination time, simple structure and high control precision

Inactive Publication Date: 2019-03-12
NANJING UNIV OF SCI & TECH
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  • Claims
  • Application Information

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Problems solved by technology

On the other hand, due to the influence of factors such as fuel consumption and the rotation of solar panels, the inertia of the spacecraft is constantly changing and unknown

Method used

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  • Finite-time posture fault-tolerant control method for spacecraft formation
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  • Finite-time posture fault-tolerant control method for spacecraft formation

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Embodiment

[0045] A formation system consisting of 4 follower spacecraft and 1 leader is used as the research object, and the specific parameters are as follows:

[0046] Table 1. Spacecraft inertia matrix and initial attitude

[0047]

[0048] Leader trajectory: ω 0 =[0.1sin(0.2t),0.1cos(0.2t),0.1cos(0.5t)] T ,q 0 and q 00 It can be obtained by kinematic equation (1). The total number of actuators σ=6. external disturbance τ id =(0.5+||ω i || 2 )[0.02sin(t),0.05cos(t),0.03cos(t)] T , i=1,2,3,4. The controller parameter is k 1 =diag(10,10,15,15,7,7),k 2 =diag(20,20,30,30,10,10),k 3 =diag(5,5,5,5,5,5),k 4 =diag(15,15,20,20,30,30), α=5 / 7, β=1, β 11 = β 21 = β 31 = β 41 =0.01, β 14 = β 24 = β 34 = β 44 = 0.1, β 12 =80,β 32 =50,β 22 = β 42 =100.

[0049] Select the moment distribution matrix The moment effective matrix is

[0050]

[0051]

[0052]

[0053]

[0054] First, build the spacecraft formation system model in MATLAB / Simulink, and the simu...

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Abstract

The invention relates to a finite-time posture fault-tolerant control method for a spacecraft formation and belongs to the technical field of multi-spacecraft formation flying. In order to reduce communication paths and avoid resource waste, a directional communication topological structure with small communication traffic is adopted between spacecraft formation members; in addition, in order to make a spacecraft formation posture control system achieve synergy more quickly and stably, the finite-time posture fault-tolerant control method for the spacecraft formation is provided on the basis of a finite-time algorithm with high robustness and fast convergence, a redundant fault-tolerant algorithm with better fault-tolerant performance and an self-adaptive algorithm with a good suppressioneffect on system uncertainty and interference. According to the method, a limited-capacity self-adaptive posture cooperative tracking fault-tolerant control strategy is perfected, a redundant fault-tolerant control method is achieved through reasonable torque distribution, and at the same time, a self-adaptive law is designed for reducing the influence of inertia variation and interference; moreover, fast convergence of a spacecraft cooperative tracking error system can be realized, and the robustness and practicability of the control system are further improved.

Description

technical field [0001] The invention belongs to the technical field of multi-spacecraft formation flight, in particular to a space vehicle formation limited-time attitude fault-tolerant control method. Background technique [0002] Spacecraft formation flight is a main mode of spacecraft group work, and spacecraft attitude coordination is an important basis for spacecraft formation flight. Focus distance, synthetic aperture, occlusion by special celestial bodies, or convergence of weak target signals in the deep distance can not be completed by a single spacecraft. Against this background, the research on multi-spacecraft formation flight has developed rapidly and has become one of the research hotspots in recent years. [0003] With the deepening of human research in the field of spaceflight, more and more complex space missions are put into engineering practice, and the time or coordination rate required for multi-spacecraft to complete attitude coordination has become an ...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 郭毓朱志浩王璐朱锐虞文杰吴益飞郭健陈庆伟
Owner NANJING UNIV OF SCI & TECH
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