固体助推火箭助推段能量管理分析

Energy Management Analysis of Ascent Phase for Solid Rocket Booster

高超声速滑翔飞行器是未来超远程打击的重要手段之一,为了实现快速响应,高超声速滑翔飞行器采用小型固体助推火箭发射。由于小型固体助推火箭采用耗尽关机方式,为了适应大小不同射程,主动段需要进行能量管理。文章基于高斯伪谱法实现了固体助推火箭助推段的弹道优化设计,并针对影响能量管理能力的因素进行了分析。分析结果表明,能量管理飞行中,采用小推力有助于提高能量管理能力,增大攻角及其角速率约束也可显著提高能量管理能力。最后,给出了主动段能量管理的俯仰角模型,为固体助推火箭助推段能量管理和制导方法设计提供了依据。

Hypersonic Glide Vehicles （HGVs） will be an important means for long-range striking. Small solid rocket booster is developed to launch the HGV to implement fast response. It is necessary to manage the final ener- gy in order to meet diverse range demands. This paper conducts the ascent trajectory optimization with Gauss Pseu- do-spectral Method （GPM）, and then analyzes the factors which decide energy management capability. The analy- sis results show preliminarily that： （1） low thrust in energy management phase leads to a higher capability of final energy management; （2） large value of angle of attack （AoA） constraint and angle velocity of AoA constraint in- creases the capability of final energy management evidently. Finally, this paper presents a pitch angle model for en- ergy management ; provides, we believe, the principles for the ascent guidance of solid rocket with energy manage- ment considered.