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Spacecraft controlling force layout optimizing method for improving failure reconfigurability

A layout optimization and spacecraft technology, applied in the field of aerospace control, can solve problems such as poor reconfigurability and failure to fully utilize resources

Active Publication Date: 2015-05-27
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0004] Redundancy is considered in the current satellite thruster system design, but the three-axis independent design is still adopted in the configuration design, which fails to achieve full utilization of resources and has poor reconfigurability

Method used

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  • Spacecraft controlling force layout optimizing method for improving failure reconfigurability
  • Spacecraft controlling force layout optimizing method for improving failure reconfigurability
  • Spacecraft controlling force layout optimizing method for improving failure reconfigurability

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Embodiment Construction

[0026] Such as figure 1 Shown is the flowchart of the method of the present invention.

[0027] Here, it is assumed that there are m thrusters in the spacecraft thruster system, and the number of thrusters to be optimized is p, where p≤m, and both m and p are positive integers. Such as figure 2 As shown, each thruster has two design variables (α i ,β i ), α i and beta i are two mounting angles, i=1,2,3...p. The present invention transforms the reconfigurable design problem into an optimization problem, and the main steps are as follows:

[0028] Step (1): Determine the independent variables and initial values ​​of the optimization problem.

[0029] In the present invention, the independent variable is all (p installation angle pairs to be designed, totally 2p variables) installation angles to be designed, θ=[…α i ,β i …], give the initial value of the simulation. Since the present invention will use the genetic algorithm to iterate later, the initial value can be gi...

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Abstract

The invention discloses a spacecraft controlling force layout optimizing method for improving failure reconfigurability. The optimizing method comprises the following steps: adopting the smallest eigenvalue of the controllable Gramian matrix and the minimal radius of the attainable set as the performance index; adding into an optimized objective function after a spacecraft control system breaks down, so that the optimized result fully takes the performance into account after the spacecraft control system breaks down. Besides, an attainable set based unconstrained feasibility judgment method is designed, and is used for carrying out the feasibility judgment of the thruster configuration in the optimization process, so as to guarantee that the spacecraft control system can still have better service performance after the failure.

Description

technical field [0001] The invention belongs to the field of aerospace control and relates to a method for layout of control forces of spacecraft. Background technique [0002] In recent years, serious events of complete failure of spacecraft have occurred many times at home and abroad, indicating that improving the fault handling capability of spacecraft control systems has become a key issue for spacecraft to achieve high reliability and long life. As for how to improve the spacecraft’s fault handling capability, current research mainly focuses on fault detection and fault-tolerant control, but these are remedial measures after a fault, and fail to fundamentally improve the reconfigurability of the spacecraft. [0003] Reconfigurability refers to the ability to restore performance after a system failure. A good redundant configuration design can ensure that after a system failure, the remaining system still has good performance, which can fundamentally improve the reconfi...

Claims

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Application Information

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IPC IPC(8): G05B13/04
Inventor 王大轶段文杰刘成瑞邢琰何英姿
Owner BEIJING INST OF CONTROL ENG
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