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本专利披露了按模块式设计的一个改进的前段和一个装有主动式控制系统的改进的后段,可以把这两段稍加修改,用于现有的球—锥几何外形的再入体(RB),并且它们可以改进再入体的气动性能和再入体的释放精度,而与导弹的诸误差l源及再入体投放程序无关。后段装有控制电子设备,推进系统和控制喷嘴,它们可以使再入体在整个飞行剖面图中主动地修正姿态和速度散布。
This patent discloses an improved anterior segment that is modular in design and an improved posterior segment that incorporates an active control system that can be slightly modified for reentrance of an existing ball-cone geometry (RBs), and they can improve both the aerodynamic performance of the reentry body and the release accuracy of the reentry body, regardless of the source of the missiles and the reentry delivery procedure. The rear section contains control electronics, propulsion systems and control nozzles that allow the reentry proactively correct attitude and velocity spread throughout the flight profile.