The Application of Hybrid Computer Techniques to Determine a Minimum Fuel Trajectory of the Second Stage of a Three Stage Missile.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The feasibility of using the hybrid computer to solve complex optimal control problems is demonstrated by determining a minimum fuel trajectory for the second stage of a three stage booster. The booster model includes pitch dynamics and realistic constraints on gimbal angle, pitch rage and angle of attack. Two solutions are obtained using a digital computer and a hybrid computer, and the solutions compare favorably to three significant figures. A generalized procedure for programming optimal control problems involving aerospace vehicles on the hybrid computer is derived. The procedure is based on the magnitude and frequency components of the state variable equations, and leads to minimization of roundofftruncation error and problem solution time. Author
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