Carrier rocket hot commissioning control system

Abstract

The invention relates to a carrier rocket hot commissioning control system which is composed of a back-end test device, a front-end test device, and a rocket-borne system device. The back-end test device and the front-end test device carry out data communication via the Ethernet. The front-end test device and the rocket-borne system device carry out data communication mainly via a 1553B bus. The back-end test device issues a control instruction to the front-end test device according to the test process. The front-end test device receives and executes the control instruction or forwards the control instruction to the rocket-borne system device for execution. The front-end test device collects a feedback signal thereof and a feedback signal of the rocket-borne system device at the same time, and sends the feedback signals to the back-end test device for display. The carrier rocket hot commissioning control system of the invention has the characteristics of being digital, intelligent, integrated and universal.

Description

technical field [0001] The invention relates to the field of launch vehicle control systems, in particular to a launch vehicle thermal test run control system. Background technique [0002] The launch vehicle is the basis of space activities. In order to ensure the correctness and coordination of the power system design scheme, a hot test run test is required in the model development stage. The hot test run test is the test of the power system closest to the flight state. Generally, the sub-level hot test run test In order to complete the control of ignition and shutdown of the power system, the control system needs to participate in it. [0003] Different from the flight test control system, the function of the hot test run test control system is mainly to realize the timing control and servo control, unguided navigation and attitude control requirements, so if the control system of the flight test is directly used to participate in the hot test run test, there are mainly...

AI Technical Summary

Problems solved by technology

[0004] 1) The system composition is complex and the level of integration is low

[0005] The composition of the flight test control system is relatively complex. There are centralized control units on the arrow and on the ground. During the test launch process, the control authority needs to be switched. The ground equipment is relatively large, the ground network structure is complex, and the level of integration needs to be improved. The control system of the flight test will significantly increase the complexity of the hot test run test, which is not conducive to the development progress of the hot test run test;

[0006] 2) The testing process is complicated

[0008] 3) Poor economy

[0009] Since the general flight test products and sub-level thermal test runs are carried out in parallel during the development process, and at the same time, the sub-level thermal test runs will also be carried out in parallel, which requires multiple sets of control system equipment. If all flight test products are used, the development Long cycle and expensive, poor economy

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