Double-component propulsion orbital transfer method suitable for low-orbit agile satellite

Abstract

The invention discloses a double-component propulsion orbital transfer method suitable for a low-orbit agile satellite. The method aims at the characteristics of a double-component propulsion orbitaltransfer system. The traditional orbital transfer control flow is improved; satellite state setting is autonomously carried out before and after orbit control by injecting orbit control block data; orbital transfer can be completed in a short time; satellite measurement and control turns are effectively reduced; through the method in which multiple storage tanks are discharged in a balanced mannerduring rail control, and switching to a single storage tank is conducted in a long-term state after rail control, high-precision agile requirements of satellites and safety of low-orbit full-life-cycle propulsion are guaranteed, the problems that a traditional low-orbit satellite orbital transfer method is poor in autonomy, long in orbit control operation time consumption, free of backup attitudecontrol means and large in fuel consumption are solved, and meanwhile the problem of adaptability of a double-component propulsion system to application of the low-orbit agile satellites is solved.

Description

technical field [0001] The invention relates to a dual-component propulsion orbit change method suitable for low-orbit agile satellites, and belongs to the technical field of satellite control. Background technique [0002] The low-orbit agile satellite is equipped with a control moment gyro to achieve high-precision agile attitude control, and the thruster is used as a backup means of attitude control. With the increasingly diverse requirements of space missions, higher requirements are put forward for the orbital maneuverability of agile satellites. Considering the large-scale orbital maneuverability, propulsion efficiency and high demand for propellant carrying scale, single-unit propulsion The system is no longer applicable, and a supercharged dual-component propulsion system suitable for medium and low orbit satellites has been applied. [0003] The traditional low-orbit satellite orbit change method has poor autonomy. It needs to manually inject commands to set the st...

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Problems solved by technology

[0004] The technical problem solved by the present invention is: in view of the current prior art, the traditional low-orbit satellite orbit change method has poor autonomy, manual injection instructions are required before and after the orbit change, the orbit control operation takes a long time, there is no backup attitude control means, and the fuel consumption is high In addition, due to the lack of application methods for dual-component propulsion systems in low-orbit agile satellites, a dual-component propulsion orbit change method suitable for low-orbit agile satellites is proposed

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