Triplex redundancy-based realization method for fly-by-light fight control system

A technology of a flight control system and an implementation method, which is applied in the field of digital control technology and flight control, can solve problems such as poor mission reliability, and achieve the effects of less supporting hardware, strong flexibility, and reduced discreteness

Inactive Publication Date: 2012-10-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0007] (3) The reliability of the task is mainly determined by the degree of redundancy. Generally speaking,

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  • Triplex redundancy-based realization method for fly-by-light fight control system
  • Triplex redundancy-based realization method for fly-by-light fight control system
  • Triplex redundancy-based realization method for fly-by-light fight control system

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[0041] The technical scheme of the invention will be described in detail below in conjunction with the drawings:

[0042] The structure configuration scheme of the three-redundancy realization method of the optical flight control system is as follows figure 1 As shown, in the flight margin control system, due to the large number of sensors, if figure 1 (1) In the direct cross-connection method, the required input channels are doubled, and too many interfaces and connections also increase the source of faults, thereby reducing reliability. Therefore, such as figure 1 (2) The scheme shown uses a serial cross-channel data link between computers for data transmission, and data voting and monitoring are performed in the computer.

[0043] System voting / monitoring plane such as figure 2 As shown, the voting / monitoring module of computer input is used to monitor the faults of sensors and other components; the voting / monitoring module of computer output data is used to monitor the correctne...

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Abstract

The invention, which belongs to the digital control technology and flight control field, relates to a triplex redundancy-based realization method for a fly-by-light fight control system. According to the invention, three-level voting/monitoring modules are arranged, wherein the three-level voting/monitoring modules includes monitors and voters; optical signals of the sensors are converted into electrical signals that then enter voting/monitoring modules at the input terminals of computers; after flight control law calculation, the processed signals pass through the voting/monitoring modules at output terminals of the computers and then enter servers; and when the electrical signals pass through the voting/monitoring modules, the monitors remove fault channels and the voters select output from residual signals. Beneficial effects of the realization method are as follows: monitoring and fault positioning can be carried out conveniently, faults can be shielded effectively, and a dispersion degree of an inputted signal can be reduced; besides, the realization method with strong flexibility and less hardware enables the computers to work synchronously.

Description

technical field [0001] The invention relates to a realization method of an optical transmission flight control system based on triple redundancy, and belongs to the field of digital control technology and flight control. Background technique [0002] With the improvement of aircraft performance requirements, digital control technology has been widely used in flight control systems. At the same time, the digital control system has many advantages, such as small size, light weight, high fault detection coverage with less hardware, can eliminate tolerance accumulation, provide perfect signal selection and performance monitoring, and the design has a strong Flexibility, easy modification, etc. However, the failure rate of the digital control system is high, and the general single-channel digital control loop cannot meet the reliability requirements of the aircraft. In order to realize the safety and reliability of the aircraft control system, in addition to trying to reduce th...

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Application Information

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IPC IPC(8): G05D1/10
Inventor 王新华甄子洋龚华军江驹杨一栋
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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