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A Composite Control Method for Automatic Landing of Carrier Aircraft Including Ship Tail Airflow Compensation

A compound control and automatic landing technology, applied in the field of flight control

Inactive Publication Date: 2017-01-04
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While the glideslope trajectory information of the carrier-based aircraft is predictable information during its descent, scholars at home and abroad have not used these foreseeable future information to carry out feed-forward control of the carrier-based aircraft.

Method used

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  • A Composite Control Method for Automatic Landing of Carrier Aircraft Including Ship Tail Airflow Compensation
  • A Composite Control Method for Automatic Landing of Carrier Aircraft Including Ship Tail Airflow Compensation
  • A Composite Control Method for Automatic Landing of Carrier Aircraft Including Ship Tail Airflow Compensation

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Embodiment Construction

[0066] The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0067] The invention provides a compound control method for automatic landing of a carrier-based aircraft including ship-tail airflow compensation, which realizes tracking and landing of the carrier-based aircraft along the glideslope track after the carrier-based aircraft enters the glide phase, and at the same time can effectively suppress and eliminate the lateral deviation, making the ship The carrier aircraft maintains lateral stability, and starts to suppress the ship's wake 12.5 seconds before landing to ensure the success rate and safety of the carrier aircraft's automatic landing.

[0068] In the present invention, the compound control method for automatic landing of carrier-based aircraft including ship tail airflow compensation, the principle structure is as follows figure 1 As shown, it is mainly realized through the composite co...

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Abstract

The invention relates to an automatic carrier landing composite control method of carrier airflow compensation-containing carrier-borne aircraft, and belongs to the technical field of flight control. The automatic carrier landing composite control method is implemented mainly through composite control of four modules, including an elevator channel control law module, an accelerator channel control law module, an aileron channel control law module and a rudder channel control law module. In the automatic carrier landing composite control method, feedforward control is performed by using glide path future information, feedback control is performed by using carrier-borne aircraft current information, and average operation can be performed on a control plane and an accelerator of a carrier-borne aircraft in advance so as to achieve a tracking compensating purpose, reduce instantaneous energy, increase the response speed and ensure safe carrier landing of the carrier-borne aircraft on an aircraft carrier.

Description

technical field [0001] The invention relates to a composite control method for automatic landing of a carrier-based aircraft including tail airflow compensation, and belongs to the technical field of flight control. Background technique [0002] As the main attack force of the aircraft carrier, the key technology of the carrier-based aircraft is how to ensure its safe and accurate landing in a very harsh environment. In order to reduce the meshing speed with the deck of the aircraft carrier when the carrier-based aircraft is landing, the aircraft carrier is usually required to travel against the wind at a certain speed. When the aircraft carrier is running against the wind, the airflow above the deck will change abruptly at the stern, forming a wake flow. When the carrier-based aircraft flies over this area, its flight quality will deteriorate sharply, and the most serious wake disturbance will exceed the performance boundary of the aircraft, which will make it unable to la...

Claims

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Application Information

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IPC IPC(8): B64F1/02
Inventor 甄子洋邵敏敏龚华军王新华江驹
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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