Implementation method for reconfigurable aircraft control system

An implementation method and technology of a control system, which are applied in the field of reconfigurable control system implementation of multi-propeller and multi-rudder surface combined aircraft, can solve the problem of difficulty in realizing the design of a general reconfigurable controller for aircraft, and achieve enhanced fault-tolerant flight capability, Achieve simple, low-computation effects

Active Publication Date: 2015-07-08
上海交大重庆临近空间创新研发中心
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Problems solved by technology

However, this technology is aimed at the decoupled control system, and it is di

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  • Implementation method for reconfigurable aircraft control system
  • Implementation method for reconfigurable aircraft control system
  • Implementation method for reconfigurable aircraft control system

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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] 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

[0025] Such as figure 2 As shown, the angle δ of the three rudder surfaces of the aircraft in this example 0 ,δ 1 and δ 2 It can be decomposed as follows to realize the aileron δ a , elevator ...

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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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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
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