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Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft

A technology of successive approximation and Euler axis, which is applied in the direction of the guidance device of the aerospace vehicle, can solve the problems of the complex configuration of the jet control system, the difficulty in reducing the volume and weight of the satellite, and the short service life of the satellite, so as to improve the utilization rate, Lightweight, low cost effect

Inactive Publication Date: 2011-01-12
HARBIN INST OF TECH
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Problems solved by technology

[0003] In order to solve the problems of high fuel consumption, short service life of the satellite, complex configuration of the control system of the air jet, and difficulty in reducing the volume and weight of the satellite, the present invention proposes a flywheel-based Satellite successive approach attitude maneuver control device and control method around instantaneous Euler axis

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  • Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft
  • Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft

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specific Embodiment approach 1

[0040] Specific implementation mode one: combine figure 1 Describe this embodiment, this embodiment comprises star angular velocity sensor 1, star angular position sensor 2 and reaction flywheel 3; It also comprises on-board control assembly 5, and described on-board control assembly 5 includes instantaneous Euler axis algorithm module 5-1 , successive approximation algorithm module 5-2, target attitude position module 5-3, proportional term Kp multiplier module 5-4, error angular velocity estimation algorithm module 5-5, damping term Kd multiplier module 5-6 and subtractor 5- 7;

[0041] The star angular velocity sensor 1 is used to detect the angular velocity of the star, and the detected angular velocity data is sent to the error angular velocity estimation algorithm module 5-5 in the onboard control assembly 5;

[0042] The star angular position sensor 2 is used to detect the angular position of the star, and simultaneously sends the detected angular position data to the ...

specific Embodiment approach 2

[0052] Specific implementation mode two: combination figure 1 Describe this embodiment, the difference between this embodiment and the specific embodiment is that it also increases the control vector limiter module 5-8; the control vector limiter module 5-8 is used to receive the subtractor 5-7 to send flywheel control data command, and perform vector clipping, and send the flywheel control data command after vector clipping. Other compositions and connection methods are the same as those in Embodiment 1.

specific Embodiment approach 3

[0053] Specific embodiment three: adopt the control method that the satellite based on flywheel described in specific embodiment one or two approaches the attitude maneuvering control device successively around the instantaneous Euler axis, it is realized by the following algorithm:

[0054] First, set the parameters of the control device according to the system requirements of the control device. The parameters to be designed are: Kd, Kp, Limit60,

[0055] where Kd=diag([Kdx Kdy Kdz] T ), parameter Kd is satellite controller differential coefficient matrix: Kp=diag ([KpxKpy Kpz] T ): The parameter Kp is the proportional coefficient matrix of the satellite controller, and the design principle is:

[0056] Kp=Ib*Wc 2 , formula one

[0057] Kd=2Ib*keci*Wc, Formula 2

[0058] The parameter Limit60 is the upper limit coefficient for limiting the maneuvering angular velocity during the satellite capture phase; the design value of Limit60 is:

[0059] Limit60=2keci*WLimit / Wc, F...

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Abstract

The invention discloses flywheel based attitude maneuvering control device and method for successive approaching of a satellite rounding an instantaneous Euler shaft and relates to control device and method for satellite attitude adjustment. The invention is provided for solving the problems of great fuel consumption, short service life of a satellite, complex configuration of an air injecting control system and difficult reduction of size and weight of the satellite existing in the realization of satellite wide-angle attitude maneuvering by adopting air injecting control. The method comprises the following steps of: setting a parameter of the control device according to the system requirement of the control device and obtaining attitude deviation angular velocity according to a motion equation; and expressing a relationship of the instantaneous Euler shaft and a deviation angle of the current attitude and a target attitude of the satellite by an attitude error quaternion to obtain a control signal, calculating to obtain a flywheel control input moment vector calculated by a satellite controller, to be used as a data control command as a basis for generating moment by a back action flywheel. The invention does not consume other resources on the satellite or consume fuel, prolongs the service life of the satellite and can be widely suitable for various satellites needing attitude maneuvering.

Description

technical field [0001] The invention relates to a control device for satellite attitude adjustment and a control method thereof. Background technique [0002] Large-angle attitude maneuvering has gradually become an essential function of modern small satellites. The existing large-angle attitude maneuvers of satellites are generally realized by jet control, but due to frequent large-angle attitude maneuvers, it is bound to cause a large amount of satellite fuel consumption and restrict the service life of the satellite, and the configuration of the jet control system is also relatively complicated. It is difficult to reduce the volume and weight of the satellite. Contents of the invention [0003] In order to solve the problems of high fuel consumption, short service life of the satellite, complex configuration of the control system of the jet, and difficulty in reducing the volume and weight of the satellite, the present invention proposes a flywheel-based The satellite...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
Inventor 耿云海陈雪芹曹喜滨孙兆伟李东柏李化义
Owner HARBIN INST OF TECH
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