Method and system for controlling coordinated turn of rotorcraft

A technology for coordinating turning and control methods, applied in the field of aircraft control, can solve problems such as no research on turning and flight control of rotorcraft, and achieve the effects of reducing potential safety hazards, accurately controlling heading, and improving stability and speed.

Inactive Publication Date: 2019-02-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] At present, the research on the turning flight of aircraft is mostly concentrated on the research on the turning

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  • Method and system for controlling coordinated turn of rotorcraft
  • Method and system for controlling coordinated turn of rotorcraft
  • Method and system for controlling coordinated turn of rotorcraft

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Embodiment Construction

[0055] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0056] In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0057] Rotorcraft fixed-altitude hovering flight control includes two aspects of plane flight control and altitude flight control, but these two aspects are not separated, but interrelated as a whole, so all contro...

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Abstract

The invention discloses a method and a system for controlling a coordinated turn of a rotorcraft. The method comprises the steps of: obtaining an actual flight parameter value and a corresponding reference parameter value of the rotorcraft when turning; using an actual height value and a reference height value as inputs of a height controller; using the PID algorithm to obtain a speed correction value; using an actual speed value, a reference speed value and the speed correction value as inputs of a speed controller; using the PID algorithm to obtain an attitude angle correction value and an engine thrust; using an actual attitude angle value, an actual angular speed value, a reference attitude angle value and the attitude angle correction value as inputs of an inner loop attitude controller; using a robust control method to obtain a control torque; and using the control torque and the engine thrust as inputs of a ground-air vehicle flight dynamics model to control flight states of therotorcraft during turn. By adopting the method or the system, the stability and the speed of the rotorcraft during turn can be improved, the flight direction can be accurately controlled, and the hidden danger can be reduced.

Description

technical field [0001] The invention relates to the technical field of aircraft control, in particular to a rotorcraft coordinated turning control method and system. Background technique [0002] Turning flight refers to a flight mode in which the target position is not in the current heading and the flight direction needs to be adjusted, especially when circling reconnaissance of ground targets, it is even more necessary. During the turning flight of the aircraft, the fuselage produces a rolling tilt, which makes the adjustment of the heading also affect the longitudinal attitude; The flight is stable, so the aircraft generally adopts the coordinated turning flight mode during the turning flight. [0003] At present, most of the researches on the turning flight of the aircraft are concentrated on the research on the turning flight control of the helicopter, and there is almost no special research on the turning flight control of the rotorcraft. With the wide application o...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 马越项昌乐林露黄楠阮书敏
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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