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Method for achieving satellite three-axis control moment decoupling based on time ratio

A technology of torque control and realization method, applied in the direction of aerospace vehicle guidance devices, etc., can solve the problems of satellite propeller layout coupling or propeller failure, failure to provide, etc., to achieve the effect of convenient optimization and reduction of fuel consumption

Active Publication Date: 2015-05-06
哈尔滨工大卫星技术有限公司
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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the satellite propeller layout is coupled or the propeller is faulty and cannot provide three-axis decoupling control torque. The present invention provides a method for realizing decoupling of satellite three-axis control torque based on time ratio

Method used

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  • Method for achieving satellite three-axis control moment decoupling based on time ratio
  • Method for achieving satellite three-axis control moment decoupling based on time ratio
  • Method for achieving satellite three-axis control moment decoupling based on time ratio

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specific Embodiment

[0044] Taking the inclined layout of the four-attitude control thrusters commonly used in satellites as an example, such as figure 2 , indicating the rationality of the designed method, the specific process is:

[0045] The installation position vector of each thruster:

[0046] R 1 = R 4 =(-0.1 0.1 0) T R 2 = R 3 =(-0.1 -0.1 0) T m

[0047]Thrust vector of each thruster:

[0048] f 1 =F 2 =(-5 0 -5) T N F 3 =F 4 =(-5 0 5) T N

[0049] The thruster control torque can be obtained as:

[0050] T 1 =(-0.5 -0.5 0.5) T T 2 =(0.5 -0.5 -0.5) T N m

[0051] T 3 =(-0.5 0.5 -0.5) T T 4 =(0.5 0.5 0.5) T N m

[0052] The positive and negative control thruster combination of each axis can be obtained by weighting the thruster combination and the time coefficient:

[0053] X-axis positive combination "2+4", X-axis negative combination "1+3";

[0054] Y-axis positive combination "3+4", Y-axis negative combination "1+2";

[0055] Z-axis positive combination "1+4",...

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Abstract

The invention belongs to the technical field of spacecraft attitude control, and discloses a method for achieving satellite three-axis control moment decoupling based on a time ratio. The method solves the problem that three-axis decoupling control moment can not be provided due to coupling existing in a layout of satellite propellers or failures of the propellers. The method for achieving satellite three-axis control moment decoupling based on the time ratio comprises the steps that the control moment of each propeller is solved according to the practical installation position of a propulsion engine; according to a time ratio method, working time factors of the control moment of the propellers are introduced, and all feasible schemes for achieving control moment three-axis decoupling are obtained through combination of the obtained control moment of the propellers and the different time factors; according to efficiencies that fuels of the determined feasible schemes are used for attitude control, priorities of the feasible schemes adopted by the three-axis positive and negative direction control moment are determined, and the priority of a feasible scheme is higher as the efficiency is higher; the working time vector quantity of each propeller is determined according to actual control signals and the determined feasible scheme with the highest priority. The method is used for carrying out attitude control on satellites by the adoption of the propellers.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control. Background technique [0002] In the field of satellite attitude control, flywheels, magnetic torque devices, and propellers are often used as the actuators for satellite attitude control. Among them, the propeller has the advantages of large control torque and fast response speed, and can be used as an actuator for stable attitude of large satellites and fast maneuvering of small satellites. Compared with the other two actuators, when the propeller is used for attitude control, the satellite attitude control accuracy is often low, and if there is coupling in the propeller layout, it is easy to cause other axis attitude changes when using the propeller to maneuver the satellite's single-axis attitude. The accuracy of satellite attitude control is further reduced. Therefore, in practical applications, propellers are often used for attitude control on large satellites, and sma...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
Inventor 耿云海易涛陈雪芹曾奎李冬柏王峰叶东
Owner 哈尔滨工大卫星技术有限公司
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