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Carrier-based aircraft automatic landing control method based on robust preview control

A predictive control and automatic landing technology, applied in the direction of adaptive control, general control system, control/adjustment system, etc., can solve the problems of low landing success rate and difficulty in tracking glideslope trajectory for carrier-based aircraft

Inactive Publication Date: 2015-09-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the actual glide tracking stage, it is difficult for the traditional PID controller to make the carrier aircraft quickly track the glideslope trajectory; in the actual deck compensation stage, it is difficult for the traditional PID controller to make the carrier aircraft completely track the deck movement in the final landing stage. resulting in a low landing success rate

Method used

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  • Carrier-based aircraft automatic landing control method based on robust preview control
  • Carrier-based aircraft automatic landing control method based on robust preview control
  • Carrier-based aircraft automatic landing control method based on robust preview control

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Experimental program
Comparison scheme
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Embodiment Construction

[0054] The present invention will be further explained below in conjunction with the accompanying drawings.

[0055] In order to facilitate the public's understanding of the technical solution of the present invention, the physical quantities and parameters involved in the present invention are described with the following table 1:

[0056] Table 1

[0057] variable

the meaning

T s

sampling time

ω

Dynamic noise of deck motion system

υ

observation noise

w k-1

System Dynamic Noise

H k

Observation coefficient matrix

v k

observation noise

N

Foresight steps

△x blon

Longitudinal State Variable Matrix

△V

Difference between speed feedback amount and trim value

△α

The difference between the angle of attack feedback and the trim value

△q

Difference between pitch rate feedback and trim value

△q

Difference between pitch angle feedback and trim va...

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Abstract

The invention discloses a carrier-based aircraft automatic landing control method based on robust preview control. Future information and current information on a glide slope track and longitudinal deck movement are used for preview control of a carrier-based aircraft, so as to achieve the tracking of the height of a glide slope and the compensation of the longitudinal deck movement, and meanwhile lateral offset can be effectively suppressed and eliminated to enable the carrier-based aircraft to main lateral stability. The future information is used for feedforward control, the current information is used for feedback control, average operation can be performed in advance for the control surface and a throttle of the carrier-based aircraft to achieve the purposes of tracking and compensation, the instantaneous energy can be reduced, the response speed is accelerated, and the carrier-based aircraft can be ensured to safely land on an aircraft carrier.

Description

technical field [0001] The invention relates to an automatic landing control method for a carrier aircraft, in particular to an automatic landing control method for a carrier aircraft based on robust predictive control. Background technique [0002] The basic principle of the carrier-based aircraft automatic landing control system is that the tracking radar on the aircraft carrier measures the actual position of the carrier-based aircraft, and at the same time, the deck motion sensor measures the movement of the flight deck of the aircraft carrier, and calculates the position of the carrier-based aircraft through the estimation method. Ideal position, the ideal position and actual position of the carrier-based aircraft are input into the command computer, and the error signal is obtained by comparison. According to the error signal, the control command of the carrier-based aircraft is calculated through the guidance control law, and then sent to the carrier-based aircraft by ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D1/10
Inventor 甄子洋邵敏敏龚华军江驹
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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