The synthesis of an optimal trajectory envelope for a missile capable of controllable post-stall maneuvering is considered. The model is representative of a generic high performance system with control capability enhanced by reaction jet thrust. Trajectory synthesis is carried out first by using classical nonlinear costrained optimization methods on a point mass model with relaxed constraints on angles of attack and sideslip. A second approach includes maneuverability and agility considerations in the optimization process, with a kinematic model and constraints obtained from dynamic limits. Results are presented for both methods, with reference to a minimum time heading reversal maneuver. (Author)
AbstractThe synthesis of an optimal trajectory envelope for a missile capable of controllable post-stall maneuvering is considered.The model is representative of a generic high performance system with control capability enhanced by reaction jet thrust. Trajectory synthesis is carried out first by using classical nonlinear costrained optimization methods on a point mass model with relaxed constraints on angles of attack and sideslip. A second approach, includes maneuverability and agility considerations in the optimization process, with a kinematic model and constraints obtained from dynamic limits. Results are presented for both methods, with reference to a minimum time heading reversal maneuver.
Notation
T = main thrustF w = -pV 2 S(C D ;Cy;C L } aerodynamic force £ m = mass of vehicle p= air density a = speed of sound g = gravity acceleration F= speed (m Y> %) = Euler angles of the wind axis frame (a, P) = aerodynamic angles T mg 2mg (adimensional time) (Thrust/Weight ratio) (Reference area) (Mach number) fPhD Student Associate Professor, Associate Fellow AIAA "