Redundancy time sequence control system for carrier rocket

Abstract

The invention relates to a redundancy time sequence control system for a carrier rocket, and the system comprises a rocket-borne computer, an integrated controller, a resistor box, ground time sequence test equipment, a display terminal and ground launch control equipment. The integrated controller receives a time reference instruction from the rocket-borne computer and a time reference instruction from the ground launch control equipment, and controls a corresponding loop to output a signal, which is transmitted to an external time sequence control load through the resistor box, according to pre-bound flight time sequence data. The resistor box provides a time series test signal, a solenoid valve waveform sampling signal, an electric explosion circuit monitoring signal and a loop resistance signal interface for the ground time sequence test equipment. The ground time sequence test equipment carries out sampling, and then displays the signals for a user through the display terminal, so as to achieve the monitoring and interpretation. The system provided by the invention gives full consideration to the universality for different types, can flexibly control the number of integrated controllers and the number of resistor boxes according to different launch vehicle configurations, is high in reliability and intelligentization and is quick in testing.

Description

technical field [0001] The invention relates to the field of launch vehicle control systems, in particular to a launch vehicle redundant timing control system. Background technique [0002] The launch vehicle is the foundation of space activities. The timing control system is an important part of the launch vehicle. It is used to complete key action controls such as engine ignition, shutdown, inter-stage separation, and star-rocket separation at all levels. The reliability of the timing control system has a great impact on the launch vehicle. is crucial. [0003] The traditional launch vehicle timing control system sends address codes to the electronic program distributor through the rocket-borne computer, and the electronic program distributor performs address code decoding to control the corresponding timing channel output. The rocket-borne computer and the electronic program distributor are connected by analog cables. The following disadvantages: [0004] 1) The reliabi...

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Problems solved by technology

[0004] 1) The reliability is not high, and there is a single point of failure

[0005] Electronic program distributors use power field effect transistor discrete devices as timing control execution devices. Due to the large load current of timing control, the required power field effect transistor discrete devices are large and occupy a lot of space, resulting in the limitation of single machine volume. It is difficult to realize the redundant design of a single machine under the premise of the single-point failure mode, which makes it difficult to improve the reliability level

[0006] 2) The degree of intelligence is not enough

[0007] The electronic program distributor has no autonomous control function, and all timing control information is stored in the arrow-borne computer. The electronic program distributor decodes the address code of the arrow-borne computer and then outputs the corresponding timing channel. The electronic program distributor has a low degree of intelligence. Increase the workload of the rocket-borne computer

[0008] 3) The timing test is complex

[0009] Due to the importance of timing control and the particularity of the corresponding pyrotechnic load, the test coverage of timing control is becoming more and more important. The traditional test equipment is relatively large and difficult to move and carry. State switching is required during the test, and related tests are more complicated. It is not conducive to the integration test of the system

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