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Design method of switching controller for constrained space vehicle orbital rendezvous system

An orbital rendezvous and design method technology, applied in the aerospace field, can solve problems such as the failure of the spacecraft rendezvous mission, and achieve the effect of improving the convergence speed, meeting the requirements of fast convergence performance, and reducing the amount of calculation.

Active Publication Date: 2022-01-25
HANGZHOU DIANZI UNIV
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AI Technical Summary

Problems solved by technology

At this time, the control system does not work according to the designed controller, which will lead to the failure of the spacecraft rendezvous mission

Method used

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  • Design method of switching controller for constrained space vehicle orbital rendezvous system
  • Design method of switching controller for constrained space vehicle orbital rendezvous system
  • Design method of switching controller for constrained space vehicle orbital rendezvous system

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Comparison scheme
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Embodiment Construction

[0064] A switching controller design method for constrained spacecraft orbital rendezvous, the design of the controller specifically includes the following steps:

[0065] a) The nonlinear differential equation of the spacecraft orbital rendezvous system is established, as follows:

[0066]

[0067] Among them, x, y, z, Respectively represent the relative distance and relative speed of the tracking spacecraft relative to the target spacecraft on the X, Y, and Z axes, a X , a Y and a Z Respectively represent the acceleration in the X, Y, Z axis, ω>0 ( η is the gravitational constant, R is the target orbital radius) is the orbital angular velocity of the target spacecraft. where the non-linear term

[0068] (b) Using Taylor series expansion, the nonlinear term Linearize and preserve to first-order terms, while selecting the state vector The following state space expression can be obtained

[0069]

[0070] where Sat represents an asymmetric saturation function,...

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Abstract

The invention discloses a design method of a switching controller for a constrained space vehicle orbit rendezvous. The invention adopts the mathematical modeling of the space spacecraft rendezvous system, the conversion of asymmetric saturation functions, the residence time method of the switching controller, By means of parametric Riccati equation method and other means, a switching controller based on dwell time is designed. The present invention equivalently expresses a control system with asymmetrical input saturation as a control system with multiple symmetrical input saturations. In fact, the resulting equivalent symmetric input saturated system is essentially a switched system. The designed controller only needs to solve the parameter Riccati equation off-line, which is simple and easy to operate, and the calculation amount is low. The proposed control method can effectively improve the convergence speed of the control system state and meet the requirements of the aerospace field for the fast convergence performance of the control system.

Description

technical field [0001] The invention belongs to the field of aerospace, and in particular relates to a design method of a switching controller for orbital rendezvous of space vehicles subject to limited reasoning constraints. Background technique [0002] Space spacecraft orbital rendezvous finally needs to complete the position alignment between the target spacecraft and the tracking spacecraft, that is to say, the relative distance between the target spacecraft and the tracking spacecraft is required to be zero. Space spacecraft orbital rendezvous is an important space technology in the field of spacecraft, and it is a prerequisite for completing some advanced space missions, such as interception between spacecraft, on-orbit maintenance, and space garbage disposal. [0003] Actuator saturation is unavoidable due to the physical limitations of the device. Actuator saturation will affect the performance of the control system and even cause the control system to be unstable....

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 王茜薛安克
Owner HANGZHOU DIANZI UNIV