Range maximization method for ramjet powered missiles with flight path constraints
Abstract
Mission performance of ramjet powered missiles is strongly infuenced by the trajectory flown. The trajectory optimization problem considered is to obtain the control time histories (i.e., propellant flow rate and angle of attack) which maximize the range of ramjet powered supersonic missiles with preset initial and terminal fight conditions and operational constraints. The approach chosen employs a parametric control model to represent the infinitedimensional controls by a finite set of parameters. The resulting suboptimal parameter optimization problem is solved by means of nonlinear programming methods. Operational constraints on the state variables are treated by the method of penalty functions. The presented method and numerical results refer to a fixed geometry solid fuel integral rocket ramjet missile for airtosurface or surfacetosurface missions. The numerical results demonstrate that continuous throttle capabilities increase range performance by about 5 to 11 percent when compared to more conventional throttle control.
 Publication:

In AGARD Ramjets and Ramrockets for Mil. Appl. 19 p (SEE N8232256 2299
 Pub Date:
 March 1982
 Bibcode:
 1982rrma.agar.....S
 Keywords:

 Angle Of Attack;
 Distance;
 Flight Paths;
 Flow Velocity;
 Fuel Flow;
 Missile Trajectories;
 Ramjet Missiles;
 Nonlinear Programming;
 Optimization;
 Parameterization;
 Solid Propellant Rocket Engines;
 Supersonic Combustion Ramjet Engines;
 Variable Thrust;
 Launch Vehicles and Space Vehicles