Geometrical optimal controller design method in tilt-rotor aircraft transition state switching process

Abstract

The invention provides a geometrical optimal controller design method in the tilt-rotor aircraft transition state switching process. The geometrical optimal controller design method aims at the problems of singularity, locality and the like of attitude control of a tilt-rotor aircraft in a Euclidean space, a Li group algebra in a Riemannian space is introduced, and through the combination of a Lagrangian function of a system and variation of an SO (3) tangent bundle, a Hamilton least principle is utilized to obtain global geometrical description of the tilt-rotor aircraft based on the SO (3) group. Through a built geometric switching dynamic model, the model problem of the tilt-rotor aircraft in a continuous space is converted into a nonlinear geometric optimal switching control problem. The algorithm can be applied to full-automatic unmanned driving and fuel economy of the tilt-rotor aircraft excessive switching process.

Description

technical field [0001] The present invention relates to an optimal controller design method for fuel optimization and switching time optimization of a tilt rotor aircraft in the state switching process, specifically through a special orthogonal matrix group (SO(3) in the Riemannian geometric manifold ) and R 3 Modeling on the configuration space (SE(3)) group formed by the semidirect product of , and designing an optimal controller design method for fuel consumption, switching time, etc. Background technique [0002] Tilting rotor aircraft is a new type of aircraft that integrates fixed-wing aircraft and helicopters. It not only has the vertical take-off and landing and air hovering capabilities of conventional helicopters, but also has the high-speed cruise flight capabilities of turboprop aircraft. The unique power plant and unique structural layout of the rotary wing aircraft are one of the key development directions of future aircraft, both in the field of civil transpo...

AI Technical Summary

Problems solved by technology

However, this article does not give the optimization controller method for the attitude performance parameters of the tilt-rotor aircraft (rigid body) in a given transition time, such as fuel, tracking, etc., and does not design the aircraft (rigid body) in the process of attitude switching. The optimal fuel, the optimal switching time, the optimal attitude tracking, and the shortest time controller design methods for constraint conditions, as well as the corresponding solution algorithms, etc.

Images