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

A technology of tilt-rotor and switching process, which is applied in the field of geometric optimal controller design of the transition-state switching process of tilt-rotor aircraft, can solve the problems of no given or designed aircraft, etc., to ensure uniqueness and avoid singularity sexual effect

Active Publication Date: 2018-05-18
DALIAN UNIV OF TECH
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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 b

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

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[0042] The specific implementation manners of the present invention will be further described below in conjunction with the accompanying drawings and technical solutions.

[0043] Based on the rigid body continuous geometric dynamic switching model established on the (SE(3)) group, the continuity equation is transformed into a discrete geometric dynamic switching equation according to the discrete Hamiltonian principle method. Specifically, the state and control variables of the optimal control problem are discretized on Legendre-Gauss points, and Lagrangian interpolation polynomials or spline functions are constructed with discrete points as nodes to approximate the state variables and control variables. The derivative of the state variable with respect to time is approximated by taking the derivative of an interpolating polynomial, thereby converting differential equation constraints into algebraic constraints. The Lie group variational integrator is used to calculate under ...

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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...

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 张硕孙涛孙希明崔文越周文雅
Owner DALIAN UNIV OF TECH
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