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A multi-stage rocket engine ignition safety system and detection method thereof

A detection method and engine technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of poor testability of cable network resources during flight and occupation of detection methods, etc.

Active Publication Date: 2021-05-14
北京中科宇航技术有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of this application is to provide a multi-stage rocket engine ignition safety system and its detection method to solve the problem that the detection method occupies too much cable network resources and the testability of the flight process is poor

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  • A multi-stage rocket engine ignition safety system and detection method thereof
  • A multi-stage rocket engine ignition safety system and detection method thereof
  • A multi-stage rocket engine ignition safety system and detection method thereof

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Embodiment Construction

[0025] The technical solutions in the embodiments of the present application are clearly and completely described below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without making creative efforts belong to the scope of protection of this application.

[0026] The application relates to an ignition safety system of a multistage rocket engine and a detection method thereof. According to the present application, the problem that the detection method occupies too much cable network resources and the testability of the flight process is poor is solved.

[0027] See figure 2 , is a schematic diagram of the multi-stage rocket engine ignition safety system provided in the embodiment of the present application, including: ground measurem...

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Abstract

This application discloses an ignition safety system of a multi-stage rocket engine and a detection method thereof. The ignition safety mechanism of a multi-stage rocket engine includes: a ground measurement and launch control system, an N-level ignition safety mechanism, an N-level intelligent detection combination; an N-level intelligent The detection combination is used to detect and record the working status of the corresponding ignition safety mechanisms at all levels, and send it to the ground measurement and launch control system; the ground measurement and launch control system is used to detect the insurance status and working status of the ignition safety mechanism, and receive Record the working state of the ignition safety mechanism detected by the N-level intelligent detection combination, and detect the safety state of the ignition safety mechanism according to the insurance state and / or working state of the ignition safety mechanism. The ignition safety mechanisms at all levels of the application are connected in series, which simplifies the design complexity of the cable network and reduces the weight of the cable network.

Description

technical field [0001] The present application relates to the field of rockets, in particular to an ignition safety system of a multi-stage rocket engine and a detection method thereof. Background technique [0002] Multi-stage rocket engines generally ensure the safety of use by controlling the ignition safety mechanism, prevent accidental detonation of the engine, and ensure the safety of personnel, launch equipment, site facilities and aerospace vehicles. In order to improve the operation and control safety of the ignition safety mechanism, the relay logic mutual exclusion interlocking control principle is generally adopted, and the state of the ignition safety mechanism is divided into an insurance state and a working state, and the two states are logically mutually exclusive. The current detection methods for multi-stage rocket engines are as follows: figure 1 shown. The ground measurement and control system connects the safety status (K1bx, K2bx...KNbx) and working s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/38F02K9/96
CPCF02K9/38F02K9/96
Inventor 郭文正辛哲奎朱永泉杨毅强
Owner 北京中科宇航技术有限公司
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