Method for determining transient process switching corridor of tilt rotor unmanned aircraft

A tilt-rotor, transition process technology, applied in aircraft parts, ground installations, transportation and packaging, etc., can solve problems such as the inability to support the weight of the aircraft, the limitation of rotor thrust, and the inability of the aircraft to support the weight of the entire aircraft.

Inactive Publication Date: 2013-06-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0003] However, when transitioning between the helicopter mode and the fixed-wing aircraft mode, the tilt-rotor UAV will suffer from a sudden decrease in the lift caused by the stall of the wing on the one hand, so that the lift force received by the aircraft cannot support the weight of the entire aircraft. On the other hand, the thrust generated by the rot...

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  • Method for determining transient process switching corridor of tilt rotor unmanned aircraft
  • Method for determining transient process switching corridor of tilt rotor unmanned aircraft
  • Method for determining transient process switching corridor of tilt rotor unmanned aircraft

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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the accompanying drawings.

[0027] Such as figure 1 , figure 2 As shown, at first the dynamic models of the rotor, wing, nacelle, fuselage, horizontal tail and vertical tail of the tilt-rotor UAV are established respectively, and the nonlinear model of the tilt-rotor UAV is obtained; the nonlinear model It includes an input module, an aircraft component model module, a motion module and an output module. The input module has rotor collective pitch, rotor lateral periodic pitch, rotor longitudinal periodic pitch, aileron deflection angle, elevator deflection angle, and rudder deflection angle6 The aircraft component model module includes the left rotor model, the right rotor model, the wing model, the horizontal tail model, the vertical tail model and the fuselage model; after obtaining the aerodynamic force and moment of each part of the aircraft, it is used as the motion module. Input, the o...

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Abstract

The invention discloses a method for determining a transient process switching corridor of a tilt rotor unmanned aircraft, comprising the steps that a kinetic model of the tilt rotor unmanned aircraft is built, a nonlinear model of the tilt rotor unmanned aircraft is obtained, the feature of the helicopter mode and the feature of the fixed wing aircraft of the tilt rotor unmanned aircraft are respectively subjected to linear analysis, a linear model of the tilt rotor unmanned aircraft is obtained, the linear model is subjected to handling characteristic analysis, the maximum speed and the minimum speed in the range of trim angle of pitch are figured out, and the step of determining the borderline of the transient process switching corridor of the tilt rotor unmanned aircraft is finally carried out. According to the method, an optimal transient path is given by taking the minimum pitch trim attitude angle of the aircraft in the switching process as the index.

Description

technical field [0001] The invention belongs to the field of unmanned aerial vehicle control, and relates to a method for determining the transition corridor of a tilt-rotor unmanned aerial vehicle Background technique [0002] As a new type of aircraft that combines the characteristics of fixed-wing aircraft and helicopters, tilt-rotor UAV is also a hot research topic at home and abroad in recent years. Engine nacelles are installed at both ends of the wings of the aircraft, and takeoff and landing can be realized like a dual-rotor helicopter; when flying forward, the nacelle tilts forward, and the rotor generates forward thrust, similar to a propeller aircraft. Tilt-rotor UAVs not only have the vertical take-off and landing and hovering capabilities of conventional helicopters, but also have the advantages of fast flight speed of fixed-wing aircraft, so they have very high application value. [0003] However, when transitioning between the helicopter mode and the fixed-wi...

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Application Information

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IPC IPC(8): B64F5/00
Inventor 曹云峰庄丽葵王彪徐砚峰朱国鸣谢也申珊颖胡亮
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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