On-orbit autonomous management method and system for planetary probe propulsion system

Abstract

The present invention provides an on-orbit self-management method and system for a planetary probe propulsion system, comprising: the propulsion system working parameters collected by the propulsion management unit in real time, and the propulsion system failure mode is analyzed according to the set pressure or temperature threshold Judgment and identification; through the identified failure mode, complete the function of independent management of the corresponding failure mode; the failure mode of the propulsion system includes the overpressure of the orbit control pipeline, the overpressure of the attitude control pipeline, the overpressure of the pressure reducing valve, and the underpressure of the propulsion system Judgment and identification of failure modes of thruster leakage and thruster leakage; the functions of autonomous management include autonomous management of rail control pipeline pressure relief, attitude control pipeline pressure relief autonomous management, pressure relief valve overpressure autonomous management, propulsion system underpressure autonomous management and Thruster leakage autonomously managed. The invention solves the problems of five main types of failure modes of the propulsion system and long-distance deep-space exploration command time delay, and provides guarantee for the high-reliability operation of the long-distance planetary probe propulsion system.

Description

technical field [0001] The present invention relates to a method for on-orbit autonomous management, in particular to an on-orbit autonomous management method and system for a propulsion system of a planetary probe, and more specifically, to a method for propulsion of a long-distance planetary probe On-orbit autonomous management approach for the system. Background technique [0002] The deep space exploration industry is a must for international aerospace powers, and long-distance planetary exploration is one of the important development directions of future deep space exploration missions. In recent years, the United States, Russia, Europe, and Japan have launched Mars, Venus, Mercury, Jupiter, comets, asteroids and other exploration missions. Compared with traditional lunar exploration missions, long-distance planetary exploration missions have two special features. One is the long flight time in orbit (the flight time of foreign Mars exploration is 6 months to more than...

AI Technical Summary

Problems solved by technology

The overpressure of the orbit control pipeline and attitude control pipeline is mainly because after the orbit attitude control engine completes the orbit change work, the upstream self-locking valve is closed, making the downstream of the self-locking valve to the engine inlet a closed pipeline. Thermal reimmersion and temperature changes in the direction of the sun during flight will cause the pressure of the propellant in the closed pipeline to rise, causing potential danger to the propulsion subsystem

The overpressure fault of the pressure relief valve mainly refers to the static pressure climb of the pressure relief valve, that is, under the pressure of 30MPa and above in the high pressure gas circuit, the locking capacity of the pressure relief valve is limited, and it may not be able to meet the requirements of maintaining a reasonable pressure during a long flight. (Generally about 1.8~1.9MPa), the undervoltage fault of the propulsion system is mainly aimed at the self-locking valve of the upstream high-pressure gas circuit module is closed, the gas circuit is cut off, and the work is completed only by the air cushion pressure of the storage tank during the working process of falling pressure, such as The engine consumes too much propellant, which will lead to a drop in the downstream pressure of the pressure reducing valve. The above overpressure and underpressure problems will cause the propulsion system to work beyond the normal working conditions, which will adversely affect the mission.

Thruster leakage is mainly due to the leakage of the solenoid valve at the head of the thruster, which will cause the propellant in the propellant pipeline to continuously flow out through the leaking thruster. The intuitive performance is that in a vacuum environment, due to the throttling effect, the engine head There will be a significant drop in temperature (generally down to -10°C), and thruster leakage will affect the smooth execution of the propulsion system's attitude and orbit control tasks.

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