Automatic ignition control system of carrier rocket

A launch vehicle, automatic ignition technology, applied in rocket engine devices, combustion engines, machines/engines, etc., can solve the problem of low launch accuracy, achieve good anti-interference, improve orbit accuracy, and avoid failure problems.

Pending Publication Date: 2022-05-20
中国航天系统科学与工程研究院
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is: aiming at the shortcomings of the traditional manual ignition and launch accuracy of the traditional launch vehicle in the current prior art, an automatic ignition control system for the launch vehicle is proposed, which uses the B code timing signal as the time for ignition and launch The benchmark provides precise ignition signals for the control system, adopts fully automatic ignition control, improves the orbital accuracy of the launch vehicle, and creates conditions for zero-window launch

Method used

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  • Automatic ignition control system of carrier rocket
  • Automatic ignition control system of carrier rocket
  • Automatic ignition control system of carrier rocket

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Embodiment Construction

[0035] An automatic ignition control system for carrier rockets, which is suitable for fully automatic ignition and launch of carrier rockets. It uses the B-code timing signal as the time reference for ignition and launch, and provides precise ignition signals for the control system. It changes the traditional manual ignition and launch. The automatic ignition control improves the accuracy of the launch vehicle's entry into orbit. The specific components of the system are as follows:

[0036] The automatic ignition control device system includes a host subsystem and a display control subsystem. The host subsystem is set in an external standard cabinet or workbench, and the display control subsystem is set on an external workbench. The display control subsystem provides information on the ignition status of the launch vehicle. The state monitoring information of the launch vehicle controls the ignition state of the launch vehicle through the host subsystem. The host subsystem ad...

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Abstract

An automatic ignition control system of a carrier rocket comprises a host subsystem and a display control subsystem, the host subsystem comprises a B code unit module, a two-out-of-three judgment module, a standard single board CPU module, a redundant hot backup power source and a host box, and the control system uses a B code timing system signal as a time reference of ignition emission and provides an accurate ignition signal for the control system. Traditional manual ignition launching is changed, full-automatic ignition control is adopted, the injection precision of the carrier rocket is improved, conditions are created for zero-window launching, and therefore the requirements of a manned spacecraft for the injection precision and the launching window of the carrier rocket are met.

Description

technical field [0001] The invention relates to an automatic ignition control system for a launch vehicle, which belongs to the technical field of automatic ignition and launch of a launch vehicle. Background technique [0002] The ignition control of traditional launch vehicles in our country adopts manual ignition control, the time accuracy is low and cannot be used in occasions that have high requirements for the accuracy of orbiting, and it can no longer meet the needs of manned, lunar exploration, space stations, etc. Therefore, a new structure of launch vehicle automatic ignition control equipment is needed to solve the deficiencies and problems existing in the existing ignition control. Contents of the invention [0003] The technical problem solved by the present invention is: aiming at the shortcomings of the traditional manual ignition and launch accuracy of the traditional launch vehicle in the current prior art, an automatic ignition control system for the laun...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/95
CPCF02K9/95Y02T10/40
Inventor 尹燕飞张研钟安彪任志国李洪李昱燃李宗华高星明王宝良王丹丽李超
Owner 中国航天系统科学与工程研究院
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