Template For The Preparation Of Papers For On-Line Publishing In ODE

Military aircraft are proximity to terrain, controlled collision int various methodologie computing optimal traj terrain 3D map to av issues are addressed various optimal flight t subject to different following, minimum ti collision. These simul possible to generate fl terrain to avoid colli instruments are not question is how sensiti trajectory to input err understand as terrain c To assess this, the optim flown again with a sm conditions. Optimal considered as a mi problem, which is solv very general framew problems, we are able smooth cost function nonlinear programmi formulation, we are al terrain avoidance m smooth derivatives approximate it us implementation and nu different constraints, position/velocity and follow the optimal traje OPTIMUM FLIGHT TRAJECTORIES ENSITIVITY ANALYSIS FOR TERRAIN OLLISION AVOIDANCE SYSTEMS T Sharma*, C Bil*, A Eberhard** Wackett Centre for Aerospace Design Technology, Royal Melbourne Technology, GPO Box 2476V, Melbourne Victoria, 3001, Australia Mathematics and Geospatial Sciences, Royal Melbourne Institute of ology, GPO Box 2476V, Melbourne, Victoria, 3001, Australia often flown in close which can result in o terrain. In this paper, s are presented for ectories within a digital oid collision. Two main in this paper. Firstly, rajectories are computed objectives, eg terrain me, etc. while avoiding ations show that it is yable trajectories within sion. In practice, flight fully accurate and the ve is the optimum flight ors. This is essential to learances can be small. al flight trajectories are all change in the initial terrain following is nimax optimal control ed using direct Within a ork for solving such to transform the noninto a constrained ng problem. In the so able to solve optimal anoeuvres. To ensure of the terrain, we ing B-Splines. The merical case studies for and initial aircraft the errors in trying to ctory are discussed. Nomenclature x& State vector in x direction y& State vector in y direction z& State vector in altitude V Velocity γ Climb angle φ Bank angle x W& Wind factor in x direction y W& Wind factor in y direction z W& Wind factor = z direction ρ Air density S Span L C Lift coefficient D C Drag coefficient T Thrust ε Thrust angle with respect to fixed body α Angle of attack D Aerodynamic Drag L Aerodynamic Lift