Maneuver Load Analysis of Overdetermined Trim Systems

A new method for computational fluid dynamics-based maneuver trim optimization is presented, in which the aircraft is trimmed by using the angle-of-attack, tail deflection, and wing control surfaces. The method belongs to the category of closely coupled aeroelastic analyses, in which the flow analysis, elastic deformations, and trim optimization computations are embedded within the computational fluid dynamics code, and performed within a single run. The method is tested on a maneuvering fighterlike aircraft model in a 1-g level flight, at Mach 0.5, sea level, and a 5-g pull-up maneuver, at Mach 0.8, sea level. The trim algorithm is found to be robust, and the closely coupled approach is computationally efficient. The newly proposed methodology provides a tool for computing loads on a maneuvering realistic aircraft in both traditional maneuver trim, and when wing control surfaces are used. It can be used to compute nonlinear maneuver loads, in the transonic flight regime, for structural design, and to gain insight on control laws that can be applied to reduce maneuver loads on existing aircrafts.

[1]  M. Karpel,et al.  Modal-Based Structural Optimization with Static Aeroelastic and Stress Constraints , 1997 .

[2]  R. N. Desmarais,et al.  Interpolation using surface splines. , 1972 .

[3]  J. Volk,et al.  Integration of a generic flight control system into ASTROS , 1996 .

[4]  Vincent J. Harrand,et al.  Development of a Multi-Disciplinary Computing Environment (MDICE) , 1998 .

[5]  S. Obayashi,et al.  Convergence acceleration of a Navier-Stokes solver for efficient static aeroelastic computations , 1995 .

[6]  Guru P. Guruswamy,et al.  Coupled finite-difference/finite-element approach for wing-body aeroelasticity , 1992 .

[7]  Asme,et al.  A collection of technical papers : 38th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit and AIAA/ASME/AHS Adaptive Structures Forum, April 7-10, 1997, Kissimmee, FL , 1997 .

[8]  Dimitri N. Mavris,et al.  Maneuver Trim Optimization Techniques for Active Aeroelastic Wings , 2000 .

[9]  Regine Ahrem,et al.  Aeroelastic Computation Using the AMANDA Simulation Environment , 2001 .

[10]  David M. Schuster,et al.  Static aeroelastic analysis of fighter aircraft using a three-dimensional Navier-Stokes algorithm , 1990 .

[11]  Daniella E. Raveh,et al.  Structural Optimization of Flight Vehicles with Computational-Fluid-Dynamics-Based Maneuver Loads , 1999 .

[12]  David M. Schuster,et al.  Application of Navier-Stokes aeroelastic methods to improve fighter wing maneuver performance , 1995 .

[13]  Daniella E. Raveh,et al.  Computational-fluid-dynamics-based aeroelastic analysis and structural design optimization—a researcher’s perspective , 2005 .

[14]  David M. Schuster,et al.  Application of a Navier-Stokes aeroelastic method to improve fighter wing performance at maneuver flight conditions , 1993 .

[15]  David M. Schuster,et al.  Comparison of two Navier-Stokes aeroelastic methods using BACT benchmark experimental data , 1999 .

[16]  Dimitri N. Mavris,et al.  Robust Structural Design of an Active Aeroelastic Wing with Maneuver Load Uncertainty , 2002 .

[17]  M. Stettner,et al.  COUPLED STATIC AND DYNAMIC AEROELASTIC SIMULATIONS IN TRANSONIC AND SUPERSONIC FLOW , 2000 .

[18]  Asme,et al.  A collection of technical papers : 37th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, April 15-17, 1996, Salt Lake City, UT , 1996 .

[19]  Daniella E. Raveh,et al.  Nonlinear Design Loads for Maneuvering Elastic Aircraft , 2000 .

[20]  J. Ausman,et al.  Integration of control surface load limiting into ASTROS , 1997 .

[21]  Eric Charlton.  COMPUTATIONAL AEROELASTICITY IN HIGH PERFORMANCE AIRCRAFT FLIGHT LOADS , 2000 .

[22]  Yuval Levy,et al.  Numerical Simulation of Dynamically Deforming Aircraft Configurations Using Overset Grids , 2001 .

[23]  G. Miller.  An active flexible wing multi-disciplinary design optimization method , 1994 .