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launch vehicle test launch control system

A technology for measurement, launch and control systems and launch vehicles, which is applied in the field of aerospace power, can solve the problems of poor system flexibility, low data distribution and reception efficiency, etc., and achieve the effect of improving system flexibility and data distribution and reception efficiency

Active Publication Date: 2022-01-25
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

[0004] The invention provides a launch vehicle measurement and launch control system, which is used to solve the technical problems of low data distribution and reception efficiency and poor system flexibility in the launch vehicle measurement and launch control system in the prior art

Method used

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Embodiment Construction

[0038] In order to make the purpose, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the present invention. Obviously, the described embodiments are part of the embodiments of the present invention , but not all examples. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0039] The different types of launch vehicles and the different test items that need to be completed in different development stages of the launch vehicle lead to the need for the ground measurement, launch and control system to be customized according to the rocket model or development stage. Therefore, the connection and Dependencies cannot be fully solidified, and continuous adjustment and...

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Abstract

The present invention provides a launch vehicle measurement and control system, wherein the system includes: a communication network, a first measurement and control device, a second measurement and control device, and a data proxy device; the first measurement and control device and the data proxy device are packaged through ZMQ , and connected to the communication network; the data proxy device is provided with a communication interface that matches the second measurement and control device, and is connected to the second measurement and control device based on the communication interface; the first measurement and control device Interacting with the second measurement and control device based on the communication network. The system provided by the present invention no longer needs to consider the connection relationship and dependency relationship between equipment and equipment, avoids frequent debugging of the test launch control system, can meet the needs of different development cycles of different rocket models, and improves the data of the test launch control system Distributing and receiving efficiency improves system flexibility.

Description

technical field [0001] The invention relates to the technical field of aerospace power, in particular to a launch vehicle measurement and launch control system. Background technique [0002] The launch vehicle test and control system is a test system that integrates launch vehicle testing, launch, data processing and monitoring functions. It generally includes test and launch control, front-end test and control, data processing, data storage, real-time monitoring, ground power supply, timing test, etc. equipment. The devices are connected through Ethernet or bus, and through interaction and cooperation, they can jointly complete the launch vehicle test, launch and control tasks. [0003] The existing launch vehicle test, launch and control system has complex connection relationships between various devices, and there is interdependence. Data transmission methods and communication methods are not the same. As a result, the test, launch and control system needs to be continuo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B23/02
CPCG05B23/0213H04L67/12
Inventor 不公告发明人
Owner 北京星河动力航天科技股份有限公司