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Dual-pulse solid rocket motor electric connector fixation structure

A technology of solid motors and electrical connectors, which is applied to the installation of connecting parts, etc., can solve the problems of unrealized application of ignition signals in the aircraft control cabin, and achieve the effects of simplifying the electrical control process, improving environmental adaptability, and reliable electrical connection

Active Publication Date: 2017-02-22
SHANGHAI XINLI POWER EQUIP RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Existing design scheme: the double pulse does not adopt the cable structure through the compartment, and the ignition signal is not uniformly applied by the aircraft control cabin; the first pulse ignition signal is applied from the tail nozzle by the ground, and the first pulse ignition device does not need an electrical connector; The pulse ignition signal is applied by the aircraft control cabin, and there is no electrical connector; therefore, in order to ensure the reliability of the ignition circuit of the first and second pulse engines and improve the convenience of installation, the industry needs a fixed structure for the electrical connector of the double pulse solid engine

Method used

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  • Dual-pulse solid rocket motor electric connector fixation structure
  • Dual-pulse solid rocket motor electric connector fixation structure
  • Dual-pulse solid rocket motor electric connector fixation structure

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Embodiment Construction

[0026] The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0027] The design method and principle of a double-pulse solid motor electrical connector fixing structure of the present invention are now described in detail

[0028] see Figure 1~3 , a pulse ignition electrical connector fixing frame 1 of the embodiment of the present invention is "L" type, and there are 2 threaded holes on its vertical plane, used for connecting with a pulse ignition device; There are 3 kinds of square grooves on the horizontal surface, used Fixed to electrical connectors and cable outlets. The two-...

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Abstract

The invention discloses a dual-pulse solid rocket motor electric connector fixation structure, which comprises a first pulse ignition electric connector fixation frame and a second pulse ignition electric connector fixation frame. The first pulse ignition electric connector fixation frame is in an L-shaped structure, and is connected with a pulse ignition device through a screw; and the second pulse ignition electric connector fixation frame is formed by a bunch clamp and a cover plate, and is connected with a motor bay through a screw. The electric connector fixation structure not only can fix the electric connector reliably, but also can fasten wires reliably, thereby preventing the welding place of the wire and an electric connector from being broken due to vibration fatigue, improving working reliability of an engine ignition circuit, improving motor performance and improving structural integrity and assembly convenience.

Description

technical field [0001] The invention relates to double-pulse solid rocket motor technology, in particular to an electrical connector fixing structure for a double-pulse solid rocket motor piercing ignition circuit. Background technique [0002] The dual-pulse solid rocket motor is a power device that provides dual thrust for the aircraft. By controlling the ignition time of the two-stage solid motor, the thrust law of the outer trajectory of the aircraft can be changed. [0003] The double-pulse engine is located between the aircraft control cabin and the steering gear cabin, and the two-stage pulse engine is isolated by a compartment device. The ignition signal of the aircraft is provided by the control cabin, and is transmitted to the ignition device of the first pulse engine through the two-pulse engine and the compartment device. When the first-pulse engine is working, the compartment device plays the role of bearing the first-pulse working pressure and isolating the fi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01R13/73
CPCH01R13/73
Inventor 刁吉阳刘喆孙福合杨明李建罗思璇
Owner SHANGHAI XINLI POWER EQUIP RES INST
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