Redundancy switching circuit used for ground test launch and control system of carrier rocket

Abstract

The invention relates to a redundancy switching circuit used for a ground test launch and control system of a carrier rocket, which mainly comprises an FPGA module, a singlechip, a switching relay and a manual transfer switch, wherein the FPGA module realizes an automatic switching function and an Ethernet switching function, and the switching priority level of the Ethernet is high; the singlechip receives the interface signal of the Ethernet, transmits the signal to the FPGA module, meanwhile receives the master-slave machine working condition from the FPGA module and carries out real-time display; an amplifying circuit receives the output signal of the FPGA module and carries out power amplification; the relay receives the drive signal of the amplifying circuit and executes action; and the manual transfer switch is used for the manual switching involved by people under an emergency state, and the priority level of manual switching is the highest. The invention ensures that the test launch and control system is not disturbed when in outputting, thereby ensuring the reliability and the safety of the whole test launch and control system. The invention solves the problem that a rocket is unattended before being launched because of low reliability of general test launch and control equipment, thereby meeting the demands of high reliability and safety of the carrier rocket on the ground test launch and control system.

Description

technical field [0001] The invention relates to a general dual-redundant hot-backup switching circuit of a rocket ground test launch control system, which realizes "automatic" and "manual" long-distance non-disturbance switching of the double-redundant hot-backup measurement and control system. Background technique [0002] In the design of the launch control system for launch vehicle ground testing, general-purpose measurement and control equipment is widely used, such as PXI, CPCI, PXI, etc. However, these general-purpose measurement and control equipment do not support dual redundant hot backup functions. , It is necessary to ensure that the equipment has high reliability. Therefore, dual redundant hot backup design measures must be adopted to ensure that the test launch control system can run continuously and reliably for a long time, and ensure that the equipment is in normal working condition when no one is on duty before shooting. [0003] Existing measurement and con...

AI Technical Summary

Problems solved by technology

It solves the problem of low reliability of general measurement and control equipment, and it is difficult to ensure that the rocket is unat

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