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Implementation method of aircraft reconfigurable control system

An implementation method and control system technology, applied in the field of reconfigurable control system realization of multi-propeller and multi-rudder combined aircraft, can solve problems such as difficult to realize general reconfigurable controller design of aircraft, achieve enhanced fault-tolerant flight capability, The effect of reducing the amount of calculation and the amount of calculation is small

Active Publication Date: 2017-04-19
上海交大重庆临近空间创新研发中心
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this technology is aimed at the decoupled control system, and it is difficult to realize the general reconfigurable controller design of the aircraft

Method used

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  • Implementation method of aircraft reconfigurable control system
  • Implementation method of aircraft reconfigurable control system
  • Implementation method of aircraft reconfigurable control system

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] Such as figure 1 As shown, this embodiment is aimed at multi-vector thrust and multi-rudder surface combination aircraft, and its multi-rudder surface means that the rudder surface of the aircraft can realize basic pitch, yaw and roll functions, specifically with six propellers and For the aircraft with aerodynamic rudder surfaces, 1 to 6 and their positions respectively represent the layout of the aircraft propeller and the layout of the Y-shaped aerodynamic rudder surface at the tail.

[0024] The installation position of the propeller in this implementation example is shown in the table below, where: the origin is the volume center of the aircraft

[0025] x(m) y(m) z(m) propeller 1 27.0834 ‐12.01 5.329 propeller 2 ‐4.9166 ‐13.095 5.964 propeller 3 ‐20.9166 ‐12.01 5.329 propeller 4 27.0834 12.01 5.329 propeller 5 ‐4.9166 13.095 5.964 propeller 6 ‐20.9166 12.01 5.329

[0026] Such as figure 2 As sh...

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Abstract

The invention provides an implementation method for a reconfigurable aircraft control system. The system comprises a controller module, a torque control and distribution module, a rudder face reconfiguration distributor, a vector thrust reconfiguration controller, two fault recognition units and a state measurement unit. The reconfigurable control system is designed through a weighted generalized inverse method; when an execution mechanism fails, the rapid configurability of the control system can be achieved by only changing the weighted value of a control efficiency weighting matrix without changing the control law; by introducing an indirect control amount, the reversing of the control matrix is not related to the state of the execution mechanism, offline calculation can be achieved, and the calculation amount of a controller is reduced.

Description

technical field [0001] The invention relates to a technology in the field of aircraft control, in particular to a method for realizing a reconfigurable control system of an aircraft with multiple propellers and multiple rudder surfaces. Background technique [0002] There are two ways to reconfigure the aircraft control system in the prior art: one is realized by using hardware (multi-sensor and multi-actuator backup), this method has been applied in the current aircraft control system, but this method brings to increase weight and cost; the other is achieved through a certain fault-tolerant algorithm, which is to make full use of fault information to model the system under fault, and use the redundancy of aircraft aerodynamics and structure to control the method or control according to a certain algorithm. This method is easy to implement and does not increase the cost of hardware, so it is widely used. [0003] After searching the prior art, the Chinese document patent nu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B19/048
CPCG05B19/048
Inventor 陈丽温余彬刘芬周华段登平
Owner 上海交大重庆临近空间创新研发中心