Satellite co-location analysis and modeling method and system based on hybrid orbit control technology
A technology of hybrid power and modeling method, which is applied in general control systems, control/regulation systems, simulators, etc., can solve the uncertainty of co-location management risks, and the design simulation difficulties of hybrid satellite co-location schemes and orbit control schemes. and other problems, to achieve the effect of minimizing operation tasks and coordination workload, ensuring coverage accuracy requirements, and small control window
Active Publication Date: 2021-11-16
中国卫通集团股份有限公司
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Problems solved by technology
[0003] The technical problem solved by the present invention is to overcome the deficiencies of the prior art, provide a satellite co-location analysis modeling method and system based on hybrid orbit control technology, and solve the design of hybrid satellite co-location scheme and orbit control scheme Difficult simulation, uncertain risks of co-location management, so as to meet Samsung's long-term co-location operation needs
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[0034] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0035] figure 1 It is a flow chart of the satellite co-location analysis and modeling method based on the hybrid orbit control technology provided by the embodiment of the present invention. Such as figure 1 As shown, the method includes the following steps:
[0036] Step 1: For A star, co-orbit 01 star and co-orbit 02 star, adopt the co-location strategy of joint isolation of eccentricity vector difference and inclination vector difference, the analysis is as follows;
[0037] The electric thruster is used as the actuator of the control subsystem for A star; the thrust of the electric thruster is low, and the position maintenance maneuver is frequent; the electric thruster is used on a civilian satellite for the first time, and there is no in-orbit operation data for the performance index; the payload ground coverage accuracy requires high , high orbit...
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The invention discloses a method and system for satellite co-location analysis and modeling based on hybrid orbit control technology, wherein the method includes: using eccentricity vector difference and inclination vector for A star, common orbit 01 satellite and common orbit 02 satellite The co-location strategy of differential joint isolation; obtain the orbit control strategy of A star, the orbit control strategy of co-orbit 01 star and the orbit control strategy of co-orbit 02 star; according to the orbit control strategy and quality of A star, light pressure coefficient, satellite effective Modeling and simulation of illuminated area, electric thruster configuration and chemical thruster configuration; modeling and simulation based on the orbit control strategy and quality, light pressure coefficient, effective illuminated area of the satellite and chemical thruster configuration of the common orbit 01 satellite; The orbit control strategy and quality of the 02 star, the light pressure coefficient, the effective illuminated area of the satellite and the configuration of the chemical thruster are modeled and simulated. The invention solves the problems of difficulty in designing and simulating a co-location scheme and an orbit control scheme based on a hybrid power satellite, and uncertain risks of co-location management.
Description
technical field [0001] The invention belongs to the field of on-orbit management of space vehicles, and in particular relates to a satellite co-location analysis modeling method and system based on hybrid orbit control technology. Background technique [0002] A certain satellite (hereinafter denoted by A star) is a technical test and communication satellite based on Dongfanghong-3 B platform, with two hybrid powers of chemical propulsion and electric propulsion onboard, and it has been in the environment of three-star co-location mission for a long time. The Dongfanghong-3 B platform is a newly developed platform. It is the first time in China to use hybrid power for position control. The traditional chemical propulsion orbit control strategy is not suitable for electric propulsion orbit control. Electric propulsion has high specific impulse but small thrust, and frequent maneuvers lead to complex orbit control strategy design scenarios, many constraints, huge amount of ana...
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IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor杨学猛赵悦许珩张东旭朱新昱李玉群
Owner中国卫通集团股份有限公司