| 摘要 |
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, VG, 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-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 VG and the desired thrust direction, US, where: <IMAGE> aT being the sensed acceleration vector.
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