Low-altitude attitude control method for ejection seat

An ejection seat and attitude control technology, which is applied to ejection/disembarkation devices, aircraft parts, transportation and packaging, etc., can solve the problems of difficulty in determining critical values, loss of life-saving height, and difficulty in ensuring the optimality of control laws. To achieve the effect of reducing the loss and improving the success rate

Active Publication Date: 2018-09-28
SUZHOU UNIV OF SCI & TECH
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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 unnece...

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  • Low-altitude attitude control method for ejection seat

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[0030] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0031] The invention provides a low-altitude attitude control method of an ejection seat, which ensures the optimality and timeliness of the control strategy when the aircraft is flying at low altitude. The control scheme of the invention has the advantages of high timeliness, close to optimal control effect, and high fault tolerance.

[0032] The state parameters of the present invention include roll angle and angular velocity, pitch angle and angular velocity, aircraft speed, and sinking rate of the aircraft when the seat is ejected from the aircraft; the control parameters include whether the main rocket, pitch, and roll attitude rocket work , the delay time of the main rocket, the pitch and roll attitude rocket, and the delay time of the parachute; the target parameter is the minimum safe rescue height or the height when the parachute is full...

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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 ...

Claims

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Application Information

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IPC IPC(8): B64D25/112
CPCB64D25/10Y02T90/00
Inventor 李俊谭率蒋彦龙李翠敏胡志培
Owner SUZHOU UNIV OF SCI & TECH
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