Energy dual-redundancy system and control method thereof

Abstract

The invention provides an energy dual-redundancy system and a control method thereof. The energy dual-redundancy system comprises a controller, a main oil way and an auxiliary oil way. Each of the main oil way and the auxiliary oil way comprises a fine oil filter, an overflow valve, a servo valve, a hydraulic cylinder and a displacement sensor, and further comprises a pressure sensor, an energy selection valve, a high-pressure hose, a controller and a double-threshold logic control strategy. Automatic switching and fault isolation between the main oil way and the auxiliary oil way of an energypart are implemented, the structure is simple, the weight is light, and switching responding is fast. Because the double-threshold logic control strategy is applied, false switching between the mainoil way and the auxiliary oil way is avoided, the reliability of a servo system can be improved by one order of magnitude relative to a product in service, and the requirement for high reliability ofmanned aerospace lunar landing in China is met. The energy dual-redundancy system and the control method thereof belong to the field of electro-hydraulic servo systems.

Description

technical field [0001] The invention relates to the field of servo control systems, in particular to an energy dual redundancy system and a control method thereof. Background technique [0002] The electro-hydraulic servo system is widely used in the thrust vector control system of active launch vehicles because of its simple structure, mature technology, and fast dynamic response. The number of matching engine servo systems in each sub-stage of the launch vehicle is often an even number. The energy part of the electro-hydraulic servo system refers to The engine energy is exported to the energy regulation section of the servo valve inlet section. The energy part of the traditional launch vehicle servo system basically adopts a single-redundancy design scheme, which makes it a single point of the system. Although the reliability can meet the needs of conventional satellite launches and cargo, it cannot meet the high reliability requirements of manned moon landing. [0003] I...

AI Technical Summary

Problems solved by technology

The energy part of the traditional launch vehicle servo system basically adopts a single-redundancy design scheme, which makes it a single point of the system. Although the reliability can meet the needs of conventional satellite launches and cargo, it cannot meet the high reliability requirements of manned moon landing.

[0003] In addition, there are some researches on the redundant design of the energy section of the servo system. Some of them use high-pressure hoses to interconnect the inlet sections of the servo valves of the two sets of electro-hydraulic servo systems to form energy redundancy. If one energy source fails, the other channel cannot work normally. For others, although an energy selection valve is installed at the inlet section of the servo valve and a single pressure point is set, the auxiliary oil circuit will be switched if the pressure point is lower than this pressure point, and the auxiliary oil circuit will not be switched if the pressure point is higher than this pressure point. , but when the energy part fails, the inlet pressure may fluctuate at this pressure point, so that the energy selection valve will switch back and forth continuously, so that it cannot normally provide energy for the electro-hydraulic servo system

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