Ejection life-saving control method

A control method and technology for controlling objects, which can be applied to ejection/disembarkation devices and other directions, and can solve the problems of optimizing ejection time interval and incapable of safe and reliable ejection to save life.

Inactive Publication Date: 2016-06-01
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0002] At present, the command ejection system commonly used by fighter jets only controls the ejection of seats, and is separated from the control system for clearing the ejection channel. It is difficult to optimize the ejection time interval at each stage, the weight and

Method used

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  • Ejection life-saving control method

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Embodiment Construction

[0014] The present invention will be described in further detail below. refer to figure 1 , the ejection lifesaving control method controls the ejection seat in the high-pressure cockpit and the ejection channel cleaning system. For example, for a two-seat hyperbaric cabin fighter, an ejection handle can be set on the ejection seat of the front driver, and the canopy and the detonation energy cutting cable of the pressure relief port can be arranged on the top of the cockpit according to the position of the ejection seat. The aircraft is driving and sends out the "ejection command" through the ejection handle, and the two detonation points of the pressure relief port are activated at the same time, and the cutting of the pressure relief port is completed. The time backup time is set to 2s; after the depressurization is completed, activate the two detonation points of the canopy at the same time, cut and form the canopy and throw it away to complete the cleaning of the ejectio...

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Abstract

The invention belongs to control technologies of aircraft ejection life-saving systems and relates to an ejection life-saving control method. The ejection life-saving control method specifically comprises the following steps that a pilot sends an ejection command to an ejection life-saving system through an ejection handle, the ejection life-saving system excites two detonation points of a pressure relief port, and the pressure relief port is formed in the top of a high-pressure cabin through cutting; after a delay of X seconds, pressure relief of the high-pressure-difference cabin is completed, and X is determined according to the pressure and ejection height of the cabin during ejection; the delay of X seconds is backed up, and backup time is determined according to an ejection life-saving scheme; after pressure relief of the cabin is completed, two detonation points for cutting a canopy are excited, and the canopy is formed through cutting and released; and after the canopy is released, seat ejection is conducted after a delay of Y seconds, dual-redundancy design is adopted by a feedback signal of the delay of Y seconds, and Y seconds are determined according to the ejection life-saving scheme. According to the ejection life-saving control method, cleaning of an ejection channel and an ejection signal of a seat are integrally controlled, the ejection life-saving system is optimized, and the system weight is reduced.

Description

technical field [0001] The invention belongs to the field of aircraft ejection lifesaving. Background technique [0002] At present, the command ejection system commonly used by fighter jets only controls the ejection of seats, and is separated from the control system for clearing the ejection channel. It is difficult to optimize the ejection time interval at each stage, the weight and reliability of the system, etc. from the whole process of ejection rescue. . At the same time, there is no pressure relief port design in the domestic aircraft ejection life-saving system, which cannot safely and reliably perform ejection life-saving in the hyperbaric cabin. Contents of the invention [0003] The task of the present invention is to provide a kind of life-saving system control method that is used with the high-pressure cockpit fighter plane, the purpose is to optimize the ejection time interval of each stage from the perspective of the whole system, carry out the design of c...

Claims

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Application Information

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IPC IPC(8): B64D25/10B64D25/08
Inventor 关焕文杨静张絮李国栋
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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