Active and passive combined fixed-wing aircraft gust alleviation control method

A control method and fixed-wing technology, applied in the field of aircraft control, can solve the problems of feedback time lag, insufficient control efficiency, large general weight, etc., and achieve the effects of increasing efficiency, weakening overload and deformation, and reducing rudder deflection angle.

Active Publication Date: 2018-09-11
BEIHANG UNIV
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Problems solved by technology

However, in order to meet the redundancy requirements, this active control method generally requires a large weig

Method used

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  • Active and passive combined fixed-wing aircraft gust alleviation control method
  • Active and passive combined fixed-wing aircraft gust alleviation control method
  • Active and passive combined fixed-wing aircraft gust alleviation control method

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Embodiment Construction

[0048] The specific implementation method of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0049] A kind of active and passive combination of the control method of fixed-wing aircraft gust mitigation of the present invention, such as figure 1 As shown, the specific steps are as follows:

[0050] Step 1. For a fixed-wing aircraft, construct the two-dimensional coordinate system OZX required for dynamic modeling describing wing deformation;

[0051] Step 2, the wing of the fixed-wing aircraft is divided into an inner wing and a full-motion wingtip, and the full-motion wingtip serves as a passive gust mitigation device and is connected to the inner wing through a torsion shaft.

[0052] Such as figure 2 As shown, the wing of the fixed-wing aircraft is divided into two parts, the inner wing 3 and the full-moving wingtip 1, wherein the full-moving wingtip 1 is a passive gust mitigation device connected to the inner wing ...

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Abstract

The invention discloses an active and passive combined fixed-wing aircraft gust alleviation control method, and belongs to the technical field of aircraft control. Firstly, a two-dimensional coordinate system OZX is constructed, a wing comprises an inner side wing body and a full-moving wing tip, the wing is discretized in the OZX, and a vibration differential equation of the inner side wing bodyand the all-moving wing tip is listed; aerodynamic force acting on the inner side wing body is obtained through an aerodynamic force coefficient matrix, and discrete gust is calculated; the aerodynamic force and a model of the gust are substituted into the vibration differential equation, shear force merging is eliminated to obtain a kinetic equation in a complete machine large matrix form, and the kinetic equation is converted into an aircraft gust response dynamics equation; the acceleration and displacement of the wing mass center of a fixed-wing aircraft are selected as an objective function of the optimal control design, the deformation of the wing is worked out, and the efficiency of gust alleviation is verified. According to the method, under the same gust intensity and overload requirements, a required rudder deflection angle is reduced, the efficiency of the gust alleviation is improved, and a good weakening effect on the overload and deformation of the wing tip is achieved.

Description

technical field [0001] The invention belongs to the technical field of aircraft control, in particular to a control method for gust mitigation of fixed-wing aircraft combining active and passive. Background technique [0002] Fixed-wing aircraft are subjected to additional overload due to atmospheric disturbances and gusts during flight, among which vertical gusts are particularly serious. Gust overload will not only reduce the stability characteristics of the aircraft and destroy its flight quality, but also generate large dynamic structural loads and accelerate the fatigue damage of the structure. Therefore, gust mitigation control for fixed-wing aircraft is necessary. [0003] At present, the method of fixed-wing gust mitigation is mainly to use the control surface for active control: for general fixed-wing aircraft, the coordinated deflection of flaps or ailerons and elevators is usually used to reduce the overload caused by gusts. However, in order to meet the redunda...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64C3/36
CPCB64C3/36B64F5/00
Inventor 李道春向锦武张志飞谭溥学
Owner BEIHANG UNIV
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