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Switching controller design method of constrained space spacecraft orbital rendezvous system

A technology of orbital rendezvous and design method, which is applied in the aerospace field and can solve problems such as the failure of space spacecraft rendezvous missions

Active Publication Date: 2019-09-20
HANGZHOU DIANZI UNIV
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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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  • Switching controller design method of constrained space spacecraft orbital rendezvous system
  • Switching controller design method of constrained space spacecraft orbital rendezvous system
  • Switching controller design method of constrained space spacecraft orbital rendezvous system

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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 switching controller design method of constrained space spacecraft orbital rendezvous. A switching controller based on residence time is designed by means of mathematical modeling of a space spacecraft rendezvous system, conversion of an asymmetric saturation function, a residence time method of a switching controller, a parametric Riccati equation method and the like. A control system with asymmetric input saturation is equivalently expressed as the control system with a plurality of asymmetric input saturation. In fact, the obtained equivalent symmetric input saturation system is essentially a switching system. The designed controller only needs to solve the parametric Riccati equation in an offline mode, which is simple and easy to operate, and a calculation amount is low. By using the control method provided in the invention, a convergence speed of a control system state can be effectively increased and a requirement of an aerospace field to fast convergence performance of the control system can be satisfied.

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 Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 王茜薛安克
Owner HANGZHOU DIANZI UNIV
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