Solving method of tilt transient process of tilt rotorcraft

A tilt-rotor, transition process technology, applied in special data processing applications, instruments, electrical digital data processing, etc. Transition efficiency, stabilize the body posture, reduce the effect of workload

Active Publication Date: 2017-05-31
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0004] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a solution method for the tilting transition process of the tilt r

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  • Solving method of tilt transient process of tilt rotorcraft
  • Solving method of tilt transient process of tilt rotorcraft
  • Solving method of tilt transient process of tilt rotorcraft

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Embodiment Construction

[0091] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and the drawings, and the content mentioned in the embodiments does not limit the present invention.

[0092] Reference figure 1 As shown, the method for solving the tilting transition process of a tilting rotor aircraft of the present invention includes the following steps:

[0093] 1) Establish a flight dynamics model suitable for calculating the tilting transition process of the tiltrotor. This model can take into account the limitation of the control system characteristics on the change speed of the control amount during the tilting transition solution process, and can also avoid the numerical solution process. There is a discontinuity in the jump;

[0094] 2) Establish appropriate boundary conditions, path constraints and performance indicators according to different flight tasks, and convert the tilting transitio...

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Abstract

The invention discloses a solving method of a tilt transient process of a tilt rotorcraft. The method comprises the steps of 1, building a flight dynamics model applicable to the calculation of the tilt transient process of the tilt rotorcraft; 2, building an appropriate boundary condition, path constraint and performance index according to different flight missions, and transforming the tilt transient process of the tilt rotorcraft into a nonlinear dynamic optimal control problem; 3, designing a numerical optimization algorithm to solve the nonlinear dynamic optimal control problem in the step 2, and obtaining the tilt transient process of the tilt rotorcraft. The solving method of the tilt transient process of the tilt rotorcraft is high in computational efficiency, fast in convergence and high in computed result reliability, and can be used for researching the optimal tilt transient process of the tilt rotorcraft.

Description

Technical field [0001] The invention belongs to the technical field of flight mechanics and flight simulation, and specifically refers to a method for solving the tilting transition process of a tilting rotor aircraft. Background technique [0002] Tilt-rotor aircraft is a new type of aircraft that combines the characteristics of helicopters and fixed-wing aircraft, and has a wide range of application prospects. The tilt-rotor aircraft has three flight modes: helicopter mode, fixed-wing aircraft mode and tilt transition mode; in order to meet the requirements of helicopter mode and fixed-wing aircraft mode, the tilt-rotor aircraft has two sets of control modes: helicopter and fixed-wing aircraft. And as the engine nacelle tilt angle changes gradually. Therefore, the tilting rotor aircraft will have the problem of maneuvering redundancy during the tilting transition process, and the pilot control will become very complicated; in addition, the entire tilting transition process mus...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 严旭飞陈仁良
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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