摘要
研究了有动力通用再入飞行器的燃料最优巡航轨迹,将问题转化为求解最优稳态巡航轨迹和最优周期巡航轨迹问题。基于稳态动力学方程求解了全局最优稳态巡航轨迹,采用直接打靶法求解了最优周期巡航轨迹,求解过程均考虑了质量变化。结果表明,与全局最优稳态巡航轨迹相比,在一个周期内,最优周期巡航轨迹在燃料消耗和吸热量两个方面都更具优势,采用超燃冲压发动机和火箭发动机分别可以节省4.75%和3.96%的燃料,吸热量分别减小10.4%和5.9%。
The fuel optimal cruise trajectory of a powered common aero vehicle was analyzed. The problem was divided into determining the optimal steady-state cruise and optimal periodic cruise problems. The global opti- mal steady-state cruise trajectory was determined based on steady-state dynamic equations. The optimal period- ic cruise trajectory was solved by the direct shooting method. The decrease of vehicle mass was considered in each case. The result shows that compared with the global optimal steady-state cruise trajectory the periodic cruise trajectory achieves better fuel consumption and heat load performances in one period. The fuel savings of 4.75 % with a scramjet engine and 3.96% with a rocket engine are achieved by the optimal periodic cruise tra- jectory over the optimal steady-state cruise trajectory. The heat loads are respectively 10.4% and 5.9% lower than those of the optimal steady-state cruise trajectory.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2009年第4期738-743,共6页
Acta Aeronautica et Astronautica Sinica
基金
国家级项目
