Synthesis of Ramjet Missile Integrated Flight Control/Fuel Control.
Final technical rept. 20 Oct 72-19 Oct 73,
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CONN
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An analytical study and computer simulation were conducted to investigate integrated flight controlfuel control systems for controlling the longitudinal-plane flight path and dynamics of a ramjet missile. The hypotherical mission and control objectives chosen for the missile were assumed to be representative of fleet air defense tasks. It was assumed that the missile would be launched from an aircraft at supersonic speeds and would be commanded to accelerate and climb to intercept altitude. The flight envelope encompassed altitudes from 20,000 to 80,000 ft and Mach numbers from 2.0 to 4.0. Modified author abstract
- Guided Missile Trajectories, Accuracy and Ballistics
- Air- and Space-Launched Guided Missiles