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Tilt-rotor helicopter control decoupling design method

A technology of tilt rotor and design method, which is applied in the field of helicopters, can solve problems such as redundancy of control rudder surfaces of tilt rotor helicopters, and achieve the effect of smooth transition and reduction of control load

Active Publication Date: 2021-01-05
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

[0003] The present invention proposes a longitudinal control strategy and decoupling design method for a tilt-rotor helicopter in the process of switching between the helicopter mode and the fixed-wing mode, so as to solve the redundancy of the control surface of the tilt-rotor helicopter and the control of the rotor deflection angle, collective pitch control and Coupling Problems Between Longitudinal Manipulations

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  • Tilt-rotor helicopter control decoupling design method
  • Tilt-rotor helicopter control decoupling design method
  • Tilt-rotor helicopter control decoupling design method

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Embodiment Construction

[0028] The technical scheme adopted in the present invention is a design method for the longitudinal maneuvering strategy of a tilt-rotor helicopter, and the process is shown in the attached figure 1 , with the following steps:

[0029] The first step is to formulate the initial longitudinal control strategy of the tiltrotor, including the change of the longitudinal joystick, the tilt angle of the rotor, and the change of the total pitch of the rotor with the tilt angle of the rotor.

[0030] Obtain the initial control range of the rotorcraft, including the initial control range [a1, b1] of the longitudinal cyclic pitch change and the initial control range [a2, b2] of the elevator, then the transfer coefficient of the longitudinal cyclic pitch change C1 is (a1-b1) / N, the transfer coefficient C2 of the elevator is (a2-b2) / N; where the value of N can be the total travel of the joystick, for example, it can be 100.

[0031] Then the change of the longitudinal joystick of the ro...

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Abstract

The invention discloses a tilt-rotor helicopter control decoupling design method which comprises the following steps: making an initial longitudinal control strategy of a tilt-rotor helicopter, establishing an aerodynamic force and moment model and a gravity model of a tilt-rotor helicopter component, and obtaining a nonlinear differential equation set based on a six-degree-of-freedom motion equation; according to the nonlinear differential equation set, selecting a rotor wing deflection angle under an interval value, solving the flight trim control quantity of the maximum speed of the tilt rotor wing helicopter and the required engine power, establishing a maximum level flight speed trim result table under different rotor wing deflection angles, and determining a new longitudinal controlstrategy; determining a new level flight speed balancing result table based on the new longitudinal control strategy; selecting a rotor total propeller pitch corresponding to the same steering columnlongitudinal control quantity under different rotor deflection angles in the table, and determining a decoupling coefficient between the rotor deflection angles and the rotor total propeller pitch based on the rotor total propeller pitch; calculating the change of the total pitch along with the inclination angle of the rotor according to the decoupling coefficient so as to solve the total pitch ofthe rotor.

Description

technical field [0001] It relates to the technical field of helicopters, in particular to a control decoupling design method for tilt rotor helicopters. Background technique [0002] A tilt-rotor helicopter has the handling characteristics of a helicopter and a fixed-wing aircraft. In helicopter mode, it relies on the rotor system to generate lift and pull, and realizes longitudinal, lateral and directional control through the periodic pitch change of the main rotor. In the fixed-wing mode, rely on the wings to generate lift, rely on the rotor to generate pulling force, and realize longitudinal, lateral and directional control through the elevator, aileron and rudder. In addition, the tilt rotor helicopter has a degree of freedom to change the azimuth angle of the rotor pull relative to the helicopter. During the transition process of the tilt-rotor helicopter from the helicopter mode to the fixed-wing mode, the pilot mainly realizes the transition flight of the tilt-rotor ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20Y02T90/00
Inventor 刘毅苏小恒刘宝方孙强马成江万海明
Owner CHINA HELICOPTER RES & DEV INST
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