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

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...

AI Technical Summary

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 rotor will be limited due to the stall of the rotor's backward blade and the shock wave generated by the forward blade, which will cause the negative force generated by the rotor, wing and other lifting surfaces to be unable to support the entire aircraft. aircraft weight

Therefore, in the transition section, there are both minimum and maximum flight speed constraints

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