Method for Steering a Solid Propellant Ballistic Vehicle.
Patent, Filed 25 Aug 80, patented 14 Jun 83,
DEPARTMENT OF THE NAVY WASHINGTON DC
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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, nulling. The vehicle booster is steered along a velocity trajectory of length equal to the remaining velocity capability, VCAP, which results in a fuel inefficient trajectory. The trajectory is divided basically into three phases and 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 VG and the desired thrust direction.
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