Method for steering a solid propellant ballistic vehicle

Aeronautics and astronautics – Missile stabilization or trajectory control – Remote control

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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.

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