Optimum Fuel Consumption Trajectory For Single-Stage Missile.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The thesis presents the basic computer algorithm to obtain an optimal thrust profile for the launch of a one-stage rocket boosted missile. The basic equations include the effects of a round earth, the earths rotation, and the atmosphere drag. A complete derivation of the equations and an explanation of the computer algorithm are given. Appendix 8 contains a copy of the computer program. The result of applying the algorithm to a booster configuration is given as an example. Author
- Computer Programming and Software
- Rocket Engines