Method and system for tiltrotor flight control for high and low undulating terrain environment

Abstract

The present invention provides a tilt rotor aircraft flight control method and system for high and low undulating terrain environments. Firstly, the pitching moment produced by the rotor to the body in each state is calculated; The generated pitching moments and the flat tail sum the pitching moments generated by the body to obtain the pitching moments of the body in different states; then input the pitching moments of the body in different states into the tiltrotor dynamics model to obtain the pitching angles of the body in different states Increase rate; finally, select the state with the fastest increase rate of the pitch angle as the best control state at the current flight speed, switch to the control mode corresponding to the best control state, and realize the best flight of the tiltrotor in the environment of high and low undulating terrain. The present invention uses the rate of increase of the pitch angle of the body with the speed of the change of the control amount as the basis for the pitch maneuver characteristics, so as to improve the control efficiency of the tilt rotor aircraft by at least 40% in high and low undulating terrain.

Description

technical field [0001] The invention relates to the technical field of tilt rotor aircraft flight control, in particular to a tilt rotor aircraft flight control method and system for high and low undulating terrain environments. Background technique [0002] Tilting rotor aircraft combines the advantages of fixed-wing aircraft and helicopters. It can hover, take off and land, fly sideways, and fly upside down like a helicopter. It has the high-speed cruise capability of a fixed-wing aircraft. It is a key research model at home and abroad. Because it takes into account both the helicopter flight mode and the fixed-wing aircraft flight mode, the tilt rotor aircraft can perform flight tasks in various terrains and scenarios. [0003] The conversion and manipulation between different flight modes of the tiltrotor will cause great changes in the flight performance of the tiltrotor, and also affect the efficiency and success of the aircraft's flight mission. Therefore, it is a bi...

AI Technical Summary

Problems solved by technology

This patent uses a special orthogonal matrix group in the Riemannian geometric manifold with R 3 Modeled on the configuration space group formed by the semidirect product and designed an optimal controller design method for fuel consumption, switching time, etc. This method mainly studies the relationship between fuel consumption and flight state switching, and does not consider the actual flight process. Pitch Maneuvering Characteristics of Tilting Rotorcraft

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