Method and system for on-orbit correction of orbit control strategy based on thruster bias estimation
A thruster and orbit control technology, which is applied in aircraft, transportation and packaging, space navigation equipment, etc., can solve the problems of affecting attitude control accuracy, large interference of orbit control thrusters, affecting orbit control accuracy, etc., so as to improve control accuracy. and efficiency, minimization of orbital disturbances, and reduced propellant consumption
A thruster and orbit control technology, which is applied in aircraft, transportation and packaging, space navigation equipment, etc., can solve the problems of affecting attitude control accuracy, large interference of orbit control thrusters, affecting orbit control accuracy, etc., so as to improve control accuracy. and efficiency, minimization of orbital disturbances, and reduced propellant consumption
CN109649692BActive Publication Date: 2021-10-01SHANGHAI AEROSPACE CONTROL TECH INST
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[0039] In order to make the object, technical solution and advantages of the present invention clearer, the embodiments disclosed in the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0040] Such as figure 1 , in this embodiment, the on-orbit correction method of the orbit control strategy based on thruster bias estimation includes:
[0041] Step 101, obtain the position information of the center of mass of the entire star, the first orbital thruster and the second orbital thruster relative to the layout system; and obtain the thrust vector directions of the first orbital thruster and the second orbital thruster.
[0042] In this embodiment, the ground measurement results can be obtained first; then, the position information of the center of mass of the entire star, the first orbital control thruster and the second orbital control thruster relative to the layout system can be obtained through screening from the grou...
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The invention discloses an orbit control strategy on-orbit correction method and system based on thruster deviation estimation. The method includes: separately obtaining the positions of the center of mass of the entire satellite, the first orbital thruster and the second orbital thruster relative to the layout system information; and, obtain the thrust vector directions of the first orbital control thruster and the second orbital control thruster; perform on-orbit identification, and determine the generation of the first orbital control thruster and the second orbital control thruster according to the on-orbit identification results The torque; construct the disturbance torque evaluation function; solve the disturbance torque evaluation function, determine the minimum value of the disturbance torque evaluation function, and calculate the jet pulse width; perform orbit control according to the calculated jet pulse width. The invention adopts the energy optimal principle to update the orbit control thrust distribution strategy on the orbit, and realizes the minimization of the orbit control interference.
Description
technical field [0001] The invention belongs to the technical field of orbit control, and in particular relates to an orbit control strategy on-orbit correction method and system based on thruster deviation estimation. Background technique [0002] Generally speaking, the design of satellite platforms is based on the load requirements. Most of the loads have certain requirements on the orbital accuracy of the satellite, and the initial low launch of the satellite, the impact of orbital perturbation during the orbit operation, etc. will make the actual orbit There is a certain deviation from the nominal orbit, so the satellite platform is required to have orbit control capabilities. [0003] Ideally, the orbit control thruster should only generate thrust in the required direction, without generating additional force and moment on the satellite. Therefore, it is necessary to comprehensively consider the mass characteristics of the satellite and the installation layout of the t...
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Patent Timeline
01 Oct 2021
Publication
CN109649692B
- IPC
- B64G1/24; B64G1/26
- CPC
- B64G1/242; B64G1/26
- Inventors
- ćć·; ççż