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Three-axis decoupling attitude control method for thruster multiplexing

A technology of attitude control and decoupling control, which is applied in the direction of attitude control, non-electric variable control, control/regulation system, etc. It can solve problems such as large amount of calculation and difficulty in modeling solar pressure, and achieve improved accuracy and robustness , Improve dynamic characteristics and steady-state accuracy, and reduce the effect of disturbance torque

Active Publication Date: 2022-02-08
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0003] The technical problem solved by the present invention is: Aiming at problems such as the difficulty in modeling solar light pressure and the large amount of calculation in real-time estimation on orbit, a three-axis decoupling attitude control method oriented to thruster reuse is proposed, relying on data-driven to obtain the fitting The parameter sequence converts the time series according to the fixed-point position and the starting time of the light pressure fitting, and provides a solar light pressure on-orbit fitting and processing method with a small amount of calculation for practical applications such as on-orbit disturbance moment estimation and at the same time meeting the accuracy requirements

Method used

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  • Three-axis decoupling attitude control method for thruster multiplexing
  • Three-axis decoupling attitude control method for thruster multiplexing
  • Three-axis decoupling attitude control method for thruster multiplexing

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Embodiment

[0075] The calculation example is set as follows: allow jet time-sharing decoupling control, thruster single-branch control, the initial value of the control command torque Thr and the initial value of the disturbance feed-forward compensation Tfd are both [0,0,0]Nm, that is, there is no initial control output. As in Table 2:

[0076] Table 2 Example setting parameters

[0077]

[0078] In the first step of the control cycle, the on-board controller automatically completes the following calculations according to the present invention: first, the control algorithm generates the control instruction torque Thr as [0.31, 0.24, 0.16] Nm, which is input as the algorithm; then, according to the time-sharing decoupling logic, This cycle only outputs the X-axis control torque, so ThrOut is [0.31,0.0,0.0]Nm, select the thruster combination 1A+2A output according to the attitude control thrust distribution logic table; next, compare the output torque with the control command torque, ...

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Abstract

The invention relates to a three-axis decoupling attitude control method for thruster multiplexing, and belongs to the field of spacecraft attitude orbit control. The method comprises the following steps: (1) recording an initial value of a control period count k as 1, and if air injection time-sharing decoupling control is allowed, circularly carrying out steps (2) to (6); (2) calculating an air injection output shaft; (3) distributing attitude control thrusters; (4) calculating a time-sharing decoupling disturbance torque; (5) calculating an interference feedforward compensation amount; (6) if the air injection time-sharing decoupling control is forbidden, quitting the calculation process; otherwise, returning to the step (2), and adding 1 to k. According to the thruster torque output time-sharing modulation method, aiming at the thruster output coupling problem, a time-sharing modulation mode is adopted, three-axis air injection output torque decoupling is achieved, and the disturbance torque of an unexpected output shaft is reduced.

Description

technical field [0001] The invention relates to a three-axis decoupling attitude control method oriented to thruster multiplexing, and belongs to the field of spacecraft attitude orbit control. Background technique [0002] A platform adopts compartmentalized structural design for the first time in China, and the propulsion service compartment of the platform is used as a common part, and the design of the load compartment module is designed flexibly according to different load types. This brings a new layout of thrusters, which brings new difficulties to attitude control, that is, the reuse of attitude control thrusters is serious. In the case of single-branch thrusters performing attitude control, the non-decoupled output seriously affects the control effect. . Contents of the invention [0003] The technical problem solved by the present invention is: Aiming at problems such as the difficulty in modeling solar light pressure and the large amount of calculation in real-...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 刘潇翔石恒王淑一何刚林波于强王佐伟李建平
Owner BEIJING INST OF CONTROL ENG
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