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Relative attitude and orbit coupling control method for rendezvous and docking final approaching section

A technique of rendezvous, docking, and final approach, which is applied in the direction of aerospace vehicle guidance devices, aerospace equipment, and aerospace vehicles. It can solve problems such as closed-loop system instability, reduced dynamic performance, and limited output torque, and reduce computational complexity. The effect of high degree and strong engineering practicability

Active Publication Date: 2021-11-09
BEIJING INST OF CONTROL ENG
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Problems solved by technology

In addition, due to the limitation of the physical structure of the actuator and the energy consumption of the whole star, the output torque of the actuator such as the thruster, flywheel, and control torque gyro is always limited. This control input saturation characteristic will reduce the dynamic performance of the system, and even lead to Closed-loop system is unstable

Method used

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  • Relative attitude and orbit coupling control method for rendezvous and docking final approaching section
  • Relative attitude and orbit coupling control method for rendezvous and docking final approaching section
  • Relative attitude and orbit coupling control method for rendezvous and docking final approaching section

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Embodiment Construction

[0094] A relative attitude-orbit coupling control method for the final approach segment of rendezvous and docking, such as figure 1 As shown, through the good function approximation ability of the neural network, it is used to estimate and effectively compensate the model uncertainty and control saturation nonlinearity, and based on the idea of ​​norm estimation, by estimating the norm of the weight matrix of the neural network instead of the matrix Component, taking into account the control saturation constraints of the actuator while considering the preset steady-state and transient performance, the specific steps are as follows:

[0095] (1) Considering the saturation constraint of the actuator, establish a six-degree-of-freedom rendezvous and docking model between the tracking spacecraft and the target spacecraft, in which the six-degree-of-freedom rendezvous and docking model between the tracking spacecraft and the target spacecraft includes the relative orbit between the ...

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Abstract

A relative attitude and orbit coupling control method for a rendezvous and docking final approximation section aims at particularity of a space rendezvous and docking task, inherits advantages of a preset performance control method, and utilizes approximation capability of a radial basis function neural network (RBFNN) to compensate saturation nonlinearity of an execution mechanism in an actual rendezvous and docking task. The whole controller design process does not need model priori knowledge such as saturation nonlinear structural characteristics of the execution mechanism, external interference and orbiter mass rotational inertia, the calculation complexity can be greatly reduced, meanwhile, the control saturation constraint of the execution mechanism is considered while the preset steady-state and transient-state performance is considered, and the method has high engineering practicability.

Description

technical field [0001] The invention relates to a relative attitude-orbit coupling control method in the final approach section of rendezvous and docking, belonging to the technical field of spacecraft control. Background technique [0002] In recent years, projects such as space debris removal and on-orbit service have gradually received greater attention. In the face of these complex tasks, the rendezvous and docking control between the tracking spacecraft and the target spacecraft is crucial to the successful realization of the entire mission. effect. [0003] Due to the particularity of space rendezvous and docking tasks, for tracking spacecraft, due to the influence of factors such as propeller fuel consumption and load rotation, there are often uncertainties in the system mass and mass inertia; due to the complexity of the space environment, spacecraft usually It will be disturbed by the external environment, such as atmospheric resistance, gravity gradient moment, so...

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242B64G1/244B64G1/245Y02T90/00
Inventor 汤亮陶佳伟刘磊贾永牟小刚刘昊
Owner BEIJING INST OF CONTROL ENG
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