Aeronautics and astronautics – Missile stabilization or trajectory control – Remote control
Patent
1980-08-25
1983-06-14
Bentley, Stephen C.
Aeronautics and astronautics
Missile stabilization or trajectory control
Remote control
60234, F42B 1328
Patent
active
043878652
ABSTRACT:
A method for steering solid propellant ballistic vehicles during powered flight which eliminates the requirement for cutoff control by allowing simultaneous fuel depletion and velocity-to-be-gained, V.sub.G, nulling. The vehicle booster is steered along a velocity trajectory of length equal to the remaining velocity capability, V.sub.CAP, which results in a fuel-inefficient trajectory. The trajectory is divided basically into three phases--an exit phase, a fuel-depletion guidance (FDG) phase and a short phase of constant attitude thrusting just prior to final stage burnout. For the exit phase the launch azimuth and the pitch-over magnitude can be varied from their usual fuel-efficient values. During fuel-depletion guidance the additional degree of freedom is the angle, .theta., between V.sub.G and the desired thrust direction, U.sub.S, where: ##EQU1## a.sub.T being the sensed acceleration vector.
REFERENCES:
patent: 2515051 (1950-07-01), Lloyd
F. W. Sears, Mechanics, Heat and Sound, "6-3 Body Projected at an Angle", 50, pp. 100-103.
Boelitz Martin V.
De Swarte Thomas W.
Howard Peter B.
Bentley Stephen C.
Curry Charles D. B.
Gray Francis I.
Sciascia R. S.
The United States of America as represented by the Secretary of
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