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Side wind resistance landing flight track tracking control method based on side direction guide

A control method and track tracking technology, which is applied in the field of flight control, can solve the problems that the wind speed changes greatly and cannot meet the requirements of aircraft precision track tracking and ideal landing, and achieve the effect of convenient system design

Active Publication Date: 2010-06-30
INST OF AUTOMATION CHINESE ACAD OF SCI
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AI Technical Summary

Problems solved by technology

[0011] In fact, the wind speed may vary greatly during the landing process. This semi-closed-loop control method cannot meet the requirements of precise track tracking and ideal landing of the aircraft.

Method used

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  • Side wind resistance landing flight track tracking control method based on side direction guide
  • Side wind resistance landing flight track tracking control method based on side direction guide
  • Side wind resistance landing flight track tracking control method based on side direction guide

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Embodiment Construction

[0044] The present invention will be described in detail below in conjunction with accompanying drawing, specific embodiment is as follows: figure 2 It is a structural block diagram of the lateral track tracking control method in the present invention, including: lateral guidance law 1, inner ring attitude control 2, route switching logic 3 and aircraft lateral and lateral motion model 4.

[0045] The inner loop attitude control command is calculated by the track tracking lateral deviation through the lateral guidance law 1, the inner loop attitude controller 2 generates steering gear control commands to control the attitude of the aircraft, and the route switching logic 3 is calculated according to the current state of the aircraft The current lateral deviation is obtained for the calculation of the lateral guidance law. Aircraft lateral motion model 4 is used to simulate the dynamics and kinematics model of the aircraft.

[0046] The specific design is as follows:

[0047] ...

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Abstract

The invention provides a side wind resistance landing flight track tracking control method based on side direction guide, which belongs to the flight track tracking control technology of airplanes landed under the side wind condition. The flight track tracking control method based on side direction guide is adopted, and comprises the following steps: calculating the inner ring posture control commands through a side direction guide law by the flight track tracking side direction deviation; generating steering engine control commands by an inner ring posture controller for controlling the airplane posture; and calculating the current side direction deviation by the flight line switching logics according to the current state of the airplane for the side direction guide law calculation. A transverse side direction movement model of the airplane is used for simulating the dynamic and kinematic model of the airplane. When being adopted, the side direction flight track control system based on the ground speed guide has better inhabitation effect on the side wind phenomena such as side direction gust wind, air turbulence, side direction wind shear and the like when the airplane is landed. At the same time, the side direction flight line switching logics can also meet the requirement of approach flight of the airplane under the side wind condition.

Description

technical field [0001] The invention belongs to the technical field of flight control, and relates to track tracking control technology under crosswind conditions, in particular to the side track tracking automatic driving under the conditions of side gust, side turbulent flow and side split shear in the landing process Control Technology. Background technique [0002] Autonomous landing technology is currently one of the weakest technical links in aircraft autopilot, and many flight accidents occur during the landing phase. Severe weather is an important cause of landing flight accidents, in which the crosswind has a great impact on the landing of the aircraft, and even when the crosswind is too strong, the aircraft cannot land. When encountering a crosswind when approaching and landing, if no correction is made, the flight path of the aircraft will deviate from the plane of symmetry of the aircraft, resulting in a bias current, which will cause the aircraft to move sidewa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/00G01C21/20
Inventor 范国梁易建强常红星
Owner INST OF AUTOMATION CHINESE ACAD OF SCI
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