Journal of Guidance Control and Dynamics · 1999 · 17 citations · 9 references
EngineeringAerospace EngineeringMechanical EngineeringOptimizationOrbital MechanicsPropulsionFlight Path OptimizationManeuvering FlightMissile Flight DynamicsOptimal ControlOrbital ManeuversTrajectory OptimizationLow Earth Orbit DynamicsLow Earth OrbitsMinimum Fuel TrajectoriesMinimum Time TrajectoriesOptimal Control In Trajectory DesignOptimal Control Of TrajectoriesOptimal Trajectory OptimizationOrbit Design
Optimal trajectories are found for the interception of a target in circular, low Earth orbit, by a vehicle that is initially in a higher orbit. The interceptor vehicle can use both conventional rocket propulsion and, if optimal or necessary, aerodynamic forces to change its orbit. The problem is solved using a direct method, collocation with nonlinearprogramming,inwhich the continuousoptimalcontrolproblem is converted intoa discrete problem.Both minimum-timeandminimum-fueltrajectories are found.The sensitivity of the optimal trajectories to atmospheric heating-rate constraints is determined. An interesting result is that some minimum-time trajectories enter the atmosphere and use aerodynamic forces for orbit change even when there is suf cient propellant available to accomplish the interception ballistically.
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