Carrier rocket test system

A technology for launch vehicles and test systems, which is applied in test/monitoring control systems, general control systems, electrical testing/monitoring, etc. Avoid the effects of human manipulation and human interpretation

Active Publication Date: 2021-12-21
北京星河动力航天科技股份有限公司 +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The embodiment of the present application provides a launch vehicle test system, which can solve the problems that in the existing test process, a large number of human interpretations are required, human errors are easily introduced, and the existing test schemes do not have universality.

Method used

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Embodiment Construction

[0041] Embodiments of the present application are described in detail below, and examples of the embodiments are shown in the drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary only for explaining the present application, and should not be construed as limiting the present invention.

[0042] Those skilled in the art will understand that the singular forms "a", "an" and "the" used herein may also include plural forms unless otherwise stated. It should be further understood that the word "comprising" used in the description of the present application refers to the presence of features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, Steps, operations, elements, components and / or groups thereof. It will be und...

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Abstract

The embodiment of the invention provides a carrier rocket test system, and relates to the technical field of rocket test launching. The system comprises an execution module used for receiving a parsed test launch control instruction sent by a parsing module and executing the parsed test launch control instruction; the execution module comprises at least one execution device; the execution module comprises a rear-end measurement and control device, and the rear-end measurement and control device is used for receiving the analyzed test launch control instruction, determining the instruction type of the analyzed test launch control instruction, determining a target execution device for executing the analyzed test launch control instruction from at least one execution device according to the instruction type, and sending the test launch control instruction to a target execution device; and a target execution device which is used for executing the analyzed test launch control instruction and returning an execution result to the rear-end measurement and control device. According to the embodiment of the invention, automatic testing in the test launch control process of the carrier rocket is realized, and a large amount of manual operation and manual interpretation are avoided.

Description

technical field [0001] The present application relates to the technical field of rocket test launch, and in particular, the present application relates to a launch vehicle test system. Background technique [0002] The development process of the launch vehicle needs to go through unit testing, integration testing, joint testing, and rocket launch testing. Various data are tested. [0003] In the current launch vehicle test process, the test environment and the status of various test equipment are often adjusted according to the actual test needs. When the environment or test status changes, due to the test process restrictions or test requirements, it is often necessary to test repeatedly until the launch vehicle reaches the final state. In the launchable state, to perform the above repeated testing process, the usual practice is to manually repeat the execution and interpretation, and edit the basic test script for testing, resulting in the following problems: [0004] 1....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0213
Inventor 刘百奇刘志方刘建设程越巍魏鑫张伟陈亭屹帅树敏黄侃刘晓萌
Owner 北京星河动力航天科技股份有限公司
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