Spacecraft Attitude Fault-Tolerant Control Method for Single Frame Control Moment Gyroscope Group

A technology for controlling moment gyroscopes and fault-tolerant control, which is applied in attitude control, non-electric variable control, control/regulation systems, etc., and can solve problems that are difficult to apply and have no engineering application methods

Active Publication Date: 2017-12-05
BEIHANG UNIV
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0005] The existence of the above problems makes it difficult to apply the current research results in actual engineering, especially in the field of spacecraft attitude fault-tolerant control with CMG as the actuator. At present, there is basically no good engineering application method to achieve

Method used

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  • Spacecraft Attitude Fault-Tolerant Control Method for Single Frame Control Moment Gyroscope Group
  • Spacecraft Attitude Fault-Tolerant Control Method for Single Frame Control Moment Gyroscope Group
  • Spacecraft Attitude Fault-Tolerant Control Method for Single Frame Control Moment Gyroscope Group

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Embodiment Construction

[0112] Attached below Figure 1-7 As shown, taking a certain type of spacecraft as an example, the implementation process of the present invention will be described in detail. The parameters of the spacecraft are as follows:

[0113] The moment of inertia matrix of the spacecraft is:

[0114]

[0115] SGCMGs with a pyramid configuration are selected, in which the nominal angular momentum of the gyro is 200Nms; the initial attitude angle is: θ(0)=1.5°, ψ(0)=1.5°; ω b The initial value of ω b (0)=[0 0 0] T ; The flight orbit of the spacecraft is a circular orbit, and the radius of the flight orbit is 26600km. The environmental disturbance moment comprehensively considers the earth's gravitational perturbation, solar light pressure moment, solar radiation pressure disturbance, etc., and adopts the following external disturbance form, as

[0116]

[0117] where A 0 is the disturbance torque amplitude, take A 0 =1.5×10 -5 N·m.

[0118] Assume that multiplicative and...

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Abstract

A spacecraft posture fault tolerance control method of single gimbal control moment gyroscope groups includes the following steps that firstly, a kinetic equation and a kinematical equation are established when partial failures exist in the single gimbal control moment gyroscope groups (SGCMGs), wherein a coordinate system is defined, and a control system state equation is established; secondly, on the basis of in-orbit operation characteristics of a spacecraft, the spacecraft posture fault tolerance control method of the single gimbal control moment gyroscope groups is adopted; thirdly, the sliding mode control law is designed, wherein a sliding mode face is designed, the control law is primarily designed and the control law is improved. The method has the advantages that the designed control law is also applicable to fault tolerance control of aircrafts with flywheels as execution mechanisms; people do not need to learn about prior information of faults, real-time estimation of fault information and interference information is achieved through self-adaptation control, and fault time varying is allowed; the method is applicable to SGCMGs of any structure or partial failure modes of flywheels; the method is used in aircrafts of the SGCMGs, the rotation speed of a gyroscope frame serves as direct control amount, and the method conforms to engineering practice.

Description

【Technical field】 [0001] The present invention uses Single Gimbal Control Moment Gyros (SGCMGs) as the three-axis stable spacecraft as the actuator, and the attitude fault-tolerant control method (Fault-Tolerant Control, FTC) when the actuator fails partially, In order to realize that the spacecraft has strong robustness to faults, it belongs to the field of spacecraft attitude control. 【Background technique】 [0002] With the development of aerospace technology, space missions are becoming more and more complex, which puts forward higher requirements for the safety, stability and control precision of spacecraft. It can be seen from the development history of aerospace technology that many accidents are caused by only a small fault. For example, in 1997, the Lewis satellite launched by NASA failed, causing all thrusters to fail, and finally the satellite fell into the atmosphere, causing huge losses. How to avoid risks and make spacecraft fault-tolerant has become a focus o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 张福桢金磊
Owner BEIHANG UNIV
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