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Full-mode flight control method for composite rotor aircraft

A technology for rotorcraft and flight control, which is applied in the fields of flight mechanics and flight simulation, and can solve problems such as difficulties in control system design.

Active Publication Date: 2019-04-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
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Problems solved by technology

This creates great difficulties in the design of the control system.

Method used

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  • Full-mode flight control method for composite rotor aircraft
  • Full-mode flight control method for composite rotor aircraft
  • Full-mode flight control method for composite rotor aircraft

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Embodiment Construction

[0080] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the accompanying drawings.

[0081] like figure 1 The block diagram of the full-mode flight control structure of the compound rotorcraft includes the following steps:

[0082] Step 1. Select the compound rotorcraft dynamics model as the research object, and obtain the flight system's expected velocity tracking command according to the compound rotorcraft's flight mission. The expected velocity tracking command includes: expected forward flight speed u c , expected lift velocity v c and the desired yaw velocity w c , and take the desired speed tracking command as the input of the controller;

[0083]Step 2. Design the control structures of the velocity loop and the attitude loop respectively. The velocity loop is used as the outer loop to provide the desired attitude control command for the attitude loop. The desired control c...

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Abstract

The invention discloses a full-mode flight control method for a composite rotor aircraft. Firstly, a nonlinear system model linearization theory is used to rapidly and effectively solve a dynamic inverse model controller under a plurality of mode reference flight states. Then, a neural network is used to compensate the errors of a multi-mode dynamic inverse model. Finally, an adaptive terminal sliding mode is used to ensure the stability, rapidity and robustness of a full-mode flight control system. According to full-mode flight control method for the composite rotor aircraft, a dynamic inverse adaptive terminal sliding mode control method is designed in an attitude loop and a speed loop, so that the composite rotor aircraft can complete the system instruction tracking in a set finite time, the convergence is good, and the flight system has good robustness, and the full envelope and full mode flight of the aircraft can be realized, and the switching of controllers is not needed in theflight process, the complexity of the flight system is reduced, and the safety of the aircraft mode switching is improved.

Description

technical field [0001] The invention belongs to the technical field of flight mechanics and flight simulation, and in particular relates to a composite rotorcraft full-mode flight control technology. Background technique [0002] The composite rotorcraft has a thrust device, a fixed wing and a rotor at the same time. It can not only realize the vertical take-off and landing and hovering flight of the helicopter flight mode, but also has the high-speed and long-range cruising flight capabilities of the fixed-wing aircraft. It has been researched by helicopters all over the world. institutions and researchers. At present, the research on the compound rotorcraft carrier-based UAV is still in its infancy at home and abroad. Due to technical confidentiality and other reasons, there are few domestic and foreign issues related to the multi-mode flight control of high-speed helicopters. [0003] The compound rotorcraft flight control system is the key and guarantee for the safe and...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 郑峰婴刘龙武程月华董敏陈之润陈志明华冰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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