摘要
滑翔式远程导弹的滑翔弹道选择对其航程影响极为显著。论文主要研究滑翔段轨迹特性及最大滑翔航程弹道的参数近似计算方法。提出了最大升阻比条件下的平衡滑翔弹道是航程较优的弹道的观点,并对这一观点进行了证明;进而给出了最大升阻比平衡滑翔条件下的主要参数间的解析关系式。仿真计算表明给出的滑翔段参数解析关系式精度较高,能用于最大航程弹道的参数近似计算。
The glide trajectory is very important to flying range of long range glide missile.This study analyzes the character of glide trajectory and deduces the approximate parameter formule of maximum glide range trajectory.A viewpoint that the maximal lift-drag ratio equilibrium glides are the optimum trajectory to maximum glide range was given.The viewpoint was proved by mathematic method.The formule for important parameters of maximal lift-drag ratio equilibrium glide were deduced.The simulation results show the calculation precise of these formulae is high. The parameters of the most range trajectory can be calculated by these formule in the glide aircraft concept design.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第6期2122-2126,共5页
Journal of Astronautics
