A Redundant Sequence Control System for Launch Vehicle

Abstract

The invention relates to a launcher hot-run control system. The system is composed of rear-end test equipment, front-end test equipment and rocket-borne system equipment. The rear-end test equipment and the front-end test equipment carry out data communication by an Ethernet network; and the front-end test equipment and the rocket-borne system equipment carry out data communication by a 1553B bus. The rear-end test equipment sends a control instruction to the front-end test equipment according to a testing process; the front-end test equipment receives and executes the instruction or forwards the instruction to the rocket-borne system equipment for execution; and the front-end test equipment collects feedback signals from the front-end test equipment and the rocket-borne system equipment simultaneously and sends the signals to the rear-end test equipment to carry out displaying. According to the invention, the provided system has high digitization, intelligence, integration and generalization levels.

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 t...

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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