Low-altitude attitude control method for ejection seat

Abstract

The invention provides a low-altitude attitude control method for an ejection seat, and belongs to the field of aviation life-saving safety protection. The low-altitude attitude control method is mainly used for solving the problems of optimality and timeliness of control strategy of an aircraft during low-altitude flight. According to the low-altitude attitude control method, a mode of combininga genetic algorithm (GA) and a BP neural network algorithm is adopted to obtain a neural network structure between flight state parameters and control parameters, when a pilot needs ejection life-saving during low-altitude flight, the working states of a main rocket, a roll rocket and a pitching rocket are judged according to an established neural network, the optimal working time of each rocket and the optimal time for shooting a parachute are obtained, finally through a timing controller, optimal or near-optimal attitude control of a human-seat system during low-altitude life-saving is achieved, and the life-saving success rate can be effectively increased. Compared with a traditional mode control method, the low-altitude attitude control method has the advantages that timeliness is high, the control effect is close to the optimal effect, and fault tolerance is high.

Description

technical field [0001] The invention relates to the field of aviation safety and lifesaving protection, in particular to a low-altitude attitude control method of an ejection seat. Background technique [0002] The attitude control strategy of the ejection seat is one of the core technologies of the fourth-generation seat, and it is also the first problem that must be solved to solve the problem of seat adaptive control. At present, the ejection seat mainly adopts the method of mode division to realize attitude control, but this method has great limitations. With the increase of state parameters, the mode division in multi-dimensional space becomes extremely complicated, and the critical value of each parameter is also difficult to determine. In addition, each working mode adopts a single control parameter, which makes it difficult to ensure the optimality of the control law, which leads to unnecessary loss of life-saving altitude, especially when the aircraft is flying at ...

AI Technical Summary

Problems solved by technology

At present, the ejection seat mainly adopts the method of mode division to realize attitude control, but this method has great limitations

With the increase of state parameters, the mode division in multi-dimensional space becomes extremely complicated, and the critical value of each parameter is also difficult to determine

In addition, each working mode adopts a single control parameter, which makes it difficult to ensure the optimality of the control law, resulting in unnecessary loss of life-saving height, especially when the aircraft is flying at low altitude

[0003] In order to obtain the optimal control law of low-altitude attitude, an effective way is to adopt the method of group selection of control parameters according to the state parameters of specific flight to obtain the optimal control strategy, but when there are many state parameters and control parameters, the The approach is time-consuming and impractical, and also not time-sensitive

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