Helicopter flight simulation trim in the coordinated turn with the hybrid genetic algorithm

Helicopter trim models are multivariate nonlinear equations and it is difficult to determine these initial trim points comparable to flight conditions. To solve this question, a hybrid genetic algorithm is presented in this paper, that combines the quick convergence ability of the quasi-Newton method and the advantages of genetic algorithm, such as global convergence. The trim control vector and the constraint conditions were established in the coordinated-turn based on the helicopter flight dynamic model. The coordinated turn flight of a UH-60 A helicopter was taken as an example to simulate on the experimental platform. Comparisons were made between the trim results and flight test data and there is a good agreement among them, and the efficiency of the algorithm presented is verified. It is a general method that can be applied to trim the helicopter of different flight conditions.

[1]  S. S. Houston,et al.  Rotor-Wake Modeling for Simulation of Helicopter Flight Mechanics in Autorotation , 2003 .

[2]  Simon Newman.  Introduction to helicopter and tiltrotor flight simulation , 2007 .

[3]  George N. Barakos,et al.  A framework for CFD analysis of helicopter rotors in hover and forward flight , 2006 .

[4]  Jiyang Dai,et al.  Helicopter trim research based on hybrid genetic algorithm , 2008, 2008 7th World Congress on Intelligent Control and Automation.

[5]  Troy C. Schank,et al.  Optimal aeroelastic trim for rotorcraft with constrained, non-unique trim solutions , 2008 .

[6]  Dai Ji.  ROBUST FLIGHT CONTROLLER DESIGN FOR HELICOPTERS BASED ON GENETIC ALGORITHMS , 2001 .

[7]  Eugene L. Duke,et al.  A General Solution to the Aircraft Trim Problem , 2007 .

[8]  Ranjan Ganguli,et al.  Survey of Recent Developments in Rotorcraft Design Optimization , 2004 .

[9]  J. Miller.  Numerical Analysis , 1966, Nature.

[10]  V. Torczon,et al.  Direct search methods: then and now , 2000 .

[11]  V. M. Spathopoulos.  Validation of a rotorcraft mathematical model in autorotation by use of gyroplane flight tests , 2004 .

[12]  Mario Innocenti,et al.  Helicopter Flight Dynamics: The Theory and Application of Flying Qualities and Simulation Modeling , 1999 .

[13]  S. S. Houston.  Validation of a Rotorcraft Mathematical Model for Autogyro Simulation , 2000 .

[14]  N. Achar,et al.  Helicopter Trim Analysis by Shooting and Finite Element Methods with Optimally Damped Newton Iterations , 1993 .

[15]  Mark G. Ballin.  Validation of a real-time engineering simulation of the UH-60A helicopter , 1987 .

[16]  Zhang Lei,et al.  Trimming Aircraft on the Ground Based on the Hybrid Genetic Algorithm , 2009 .

[17]  Martin K. Sekula,et al.  Effects of Auxiliary Lift and Propulsion on Helicopter Vibration Reduction and Trim , 2004 .

[18]  Masao Fukushima,et al.  Modified Newton methods for solving a semismooth reformulation of monotone complementarity problems , 1996, Math. Program..

[19]  P. D. Talbot,et al.  A mathematical model of a single main rotor helicopter for piloted simulation , 1982 .

[20]  J. J. Howlett.  UH-60A Black Hawk engineering simulation program. Volume 1: Mathematical model , 1981 .