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1. 发明授权

US4387865A Method for steering a solid propellant ballistic vehicle 失效
标题翻译：用于转向固体推进剂弹道导弹的方法
公开(公告)号：US4387865A
公开(公告)日：1983-06-14
申请号：US181023
申请日：1980-08-25
申请人： Peter B. Howard , Martin V. Boelitz , Thomas W. De Swarte
发明人： Peter B. Howard , Martin V. Boelitz , Thomas W. De Swarte
IPC分类号： F41G7/00 , F42B13/28
CPC分类号： F41G7/00
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, 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.
摘要翻译：在动力飞行期间用于转向固体推进剂弹道车辆的方法，其通过允许同时燃料消耗和速度要求的VG，零点而消除对切断控制的要求。车辆助力器沿着长度等于剩余速度能力VCAP的速度轨迹转向，这导致燃料效率低的轨迹。轨迹基本上分为三个阶段，即退出阶段，燃料消耗指导（FDG）阶段以及在最后阶段倦怠之前持续姿态推动的短暂阶段。对于出口阶段，发射方位角和俯仰幅度可以从其通常的燃料效率值变化。在燃料消耗引导期间，额外的自由度是VG与期望的推力方向之间的角度θ，US，其中：作为感测加速度矢量的 aT。

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