Rocket ground test control system based on redundant structure

A ground test and control system technology, applied in the direction of weapon accessories, offensive equipment, etc., can solve the problem that the command of the ground control system cannot reach the arrow, so as to reduce the possibility, improve the reliability, and achieve the effect of redundancy

Active Publication Date: 2014-05-28
SHANGHAI AEROSPACE COMP TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When a single network path or actuator fails, the commands of the ground c

Method used

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  • Rocket ground test control system based on redundant structure
  • Rocket ground test control system based on redundant structure
  • Rocket ground test control system based on redundant structure

Examples

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Embodiment 1

[0025] Such as figure 1 As shown, a rocket ground test control system based on a redundant architecture includes a front-end transmission control PLC unit 1, an optical transceiver unit 2, a back-end switch unit 3, and a main control microcomputer 4 connected in sequence.

[0026] Among them, the main control microcomputer 4 is used to send a control instruction, which is input to the front-end transmission control PLC unit 1 via the back-end switch unit 3 and the optical transceiver unit 2 in turn; the front-end transmission control PLC unit 1 is used to output the control instruction to the carrier The rocket receives the feedback signal from the launch vehicle, and then sends the feedback signal to the main control microcomputer 4 via the optical transceiver unit 2 and the back-end switch unit 3 in turn.

[0027] In order to realize the redundant configuration of control command transmission, such as figure 2 As shown, the front-end PLC unit 1 includes two redundantly configured...

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PUM

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Abstract

The invention discloses a rocket ground test control system based on a redundant structure. The rocket ground test control system based on the redundant structure comprises a front-end sending controlling PLC unit, an optical terminal machine unit, a rear-end interchanger unit and a main control computer. The front-end sending controlling PLC unit comprises two redundantly configured front-end PLC sub-systems and at least two bus stations, wherein the two front-end PLC sub-systems are connected with the bus stations respectively, the bus stations are sequentially connected with other bus stations, the two front-end PLC sub-systems are respectively provided with a CPU module and at least one input module, the two CPU modules are mutually connected, all the input modules simultaneously receive the same way of input signals, and each bus station is respectively provided with at least one output module. The rocket ground test control system based on the redundant structure has the advantages of achieving redundancy, improving the reliability of a test process and reducing the possibility that a single-point failure mode occurs.

Description

Technical field [0001] The invention relates to a launch vehicle ground measurement and launch control system, in particular to a redundant control system for a launch vehicle ground test process. Background technique [0002] In the prior art, in the launch vehicle, the power supply and distribution and status control of each single product of the rocket control system, external security system, strapdown system, telemetry system, etc. Redundant control PLC or VXI control matrix for control. The control command can only reach the front-end control equipment from the back end through a single network path, and the actuator of the front-end control equipment is also a single non-redundant configuration. When a single network access or actuator fails, the ground control system's instructions cannot reach the arrow, which will cause serious consequences. Summary of the invention [0003] In order to overcome the shortcomings in the prior art, a rocket ground test control system bas...

Claims

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Application Information

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IPC IPC(8): F41G9/00
Inventor 赵阳朱奕蔡珂吕振彬
Owner SHANGHAI AEROSPACE COMP TECH INST
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