Solid micro thruster array and magnetic moment device joint control method

A technology of micro propulsion and magnetic torque device, which is applied in the direction of aircraft, aerospace vehicles, and guidance devices of aerospace vehicles, etc. It can solve the problems of unguaranteed attitude control accuracy, difficulty in power consumption, volume, and large thruster scale.

Active Publication Date: 2018-11-27
NORTHWESTERN POLYTECHNICAL UNIV
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  • Application Information

AI Technical Summary

Problems solved by technology

When the thrust of a single thruster is large, the accuracy of attitude control cannot be guaranteed; while when the thrust of the thruster is small, the scale of the thrusters required to complete large-angle maneuvers or multiple maneuvers is difficult to achieve in terms of power consumption

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  • Solid micro thruster array and magnetic moment device joint control method
  • Solid micro thruster array and magnetic moment device joint control method
  • Solid micro thruster array and magnetic moment device joint control method

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Embodiment Construction

[0053] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0054] The invention discloses a joint control method of a solid micro-propeller array and a magnetic torque device, which specifically includes the following steps:

[0055] Step 1. Design MSPT (solid micro propulsion array) optimal ignition model.

[0056] For the derotation or three-axis stable control of the Pina satellite, the combined ignition algorithm of the direct force attitude control system composed of the solid pulse thruster array to generate the specified torque at a given position is studied. This problem can finally be transformed into an optimal combination selection problem with the number of propellers to be ignited as the target and satisfying the torque constraints of the response. A very suitable method for solving this combinatorial selection problem is the 0-1 programming problem.

[0057] The MSPT array ignition al...

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Abstract

The invention discloses a solid micro thruster array and magnetic moment device joint control method. A solid micro thruster array optimization ignition model is designed, a solid micro thruster arrayis controlled by the optimization ignition model for performing large-angle speed damping control on a satellite till the angular speed of the satellite meets the equation shown in the description, small-angle damping joint control is performed on the satellite through a magnetic moment device and a solid micro thruster array till the angular speed of the satellite meets the equation shown in thespecification, and joint gesture capture control is performed on the satellite through the magnetic moment device and the solid micro thruster array; by designing the MSPT ignition model, ignition ofthe solid micro thruster can be optimized, the best ignition combination is given, according to the task requirement, joint control is performed by combining the solid micro thruster array and the magnetic moment device, the effectiveness of an algorithm is testified through theoretical deduction and simulation experiments, the gesture control period of the satellite can be lowered, the control precision can be improved, and the control energy consumption can be lowered.

Description

【Technical field】 [0001] The invention belongs to the technical field of micro-satellite attitude control, and in particular relates to a combined control method of a solid micro-propeller array and a magnetic torquer. 【Background technique】 [0002] In units and enterprises, micro-satellites are used in emergency communication, space networking and other fields due to their low cost of implementation and quick response capabilities such as short design time periods. In college education, its low-cost and high-integration features enable Pina Satellite to be well integrated into innovation and learning, which is very helpful for the development of students, so it is valued by many universities. At present, many universities have successfully launched small satellites. Attitude Determination and Control System (ADCS for short) of Pina satellite provides attitude control capability for small satellites, which is composed of attitude sensor, attitude control actuator and attit...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 侯晓磊周康博刘勇潘泉
Owner NORTHWESTERN POLYTECHNICAL UNIV
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