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Automatic launch control method for carrier rocket low-temperature power system

A power system and automatic launch technology, which is applied in rocket launching devices, weapon accessories, ammunition tests, etc., to achieve the effects of high safety risks, avoiding safety hazards, and high disposal requirements

Active Publication Date: 2021-03-23
BEIJING INST OF ASTRONAUTICAL SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The launch preparations of cryogenic rockets are carried out crosswise and functionally belong to different subsystems. However, during the launch preparation process, many test and operation items influence each other and are tightly coupled.

Method used

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  • Automatic launch control method for carrier rocket low-temperature power system
  • Automatic launch control method for carrier rocket low-temperature power system
  • Automatic launch control method for carrier rocket low-temperature power system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0025] 1. Guided knowledge entry

[0026] According to the five-layer tree structure of "rocket model-flight launch-test type-test stage-subsystem", the knowledge is managed, and the automatic control process of the low-temperature power rocket is divided into 7 stages from -12h to ignition. Create instruction rules, fault detection criteria, and fault location criteria in a wizard-like manner, such as layer structure. Guided knowledge input process such as figure 2 As shown, the main steps are:

[0027] The first step: create a test project (instruction rules)

[0028] List the test items to be diagnosed in turn, and set the test item start flag or trigger condition.

[0029] Step 2: Establish fault detection criteria

[0030] Select the parameters to be monitored or judged, set the change rules of the parameters, and support the description forms such as upper and lower limits, standard values ​​and errors, functions, expected values, and time series.

[0031] Step 3: ...

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Abstract

The invention discloses an automatic launch control method for a carrier rocket low-temperature power system. According to the method, the whole launch process is subjected to stage planning accordingto the characteristics of different time period processes of a launch day; each stage is divided into a plurality of items of work according to the independent degree of the work content, and each item of work is controlled and executed by an independent automatic control program; and due to the fact that the interpretation data is more, the algorithm is complex, the fault detection and positioning difficulty is high, and the processing requirement is high, a data processing knowledge base for fault diagnosis is constructed while the automatic launch control is executed, the important data inthe flow is interpreted, the rapid fault positioning is realized, and the fault processing is automatically executed.

Description

technical field [0001] The invention belongs to the technical field of novel carrier rocket power systems, and is especially designed for large-scale low-temperature power carrier rockets, and realizes the automatic test function of the low-temperature power system after the low-temperature propellant is filled and before the rocket is launched. Background technique [0002] Cryogenic launch vehicles using liquid hydrogen / liquid oxygen and liquid oxygen / kerosene engines will become the main force of my country's space transportation system. The pre-launch process, especially the propellant filling process, has very high safety requirements. The United States, the former Soviet Union, Brazil and other countries have all had catastrophic accidents in which rockets exploded on towers and caused a large number of casualties, and the lessons are painful. In September 2016, the Falcon 9 rocket exploded during the static test after filling. Fortunately, due to the use of many autom...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F41F3/04F42B35/00
CPCF41F3/04F42B35/00
Inventor 韩雨桐刘巧珍赵心欣王晓林张青松姜先炜郭葳吴义田何巍卢頔李璨王淑炜王之平岳玮王耕
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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