摘要：为了研究助推滑翔导弹针对地面固定目标的快速打击方法,通过受力分析,提出一种新的弹道下压段俯冲弹道模型.采用翻身下压的飞行方式,使导弹主升力面朝下,弹道下压过程中以正攻角下压为主,延后并缩短了负攻角的使用时间,获得了更快的弹道下压速率.以美国CAV-H为研究对象,利用高斯伪谱法进行弹道仿真计算,并与传统弹道下压方式进行对比.结果表明,与传统弹道下压方式相比,翻身下压具有更高的弹道下压效率及在高速飞行的高热流区保持正攻角飞行的特点.对于采用腹部防热设计的助推滑翔导弹,在实现弹道快速下压的前提下,有效杜绝了热流向背部蔓延,提高了俯冲攻击过程中导弹的安全性.%To study the method of boost-glide missile striking ground fixed target rapidly,a new trajectory model for diving phase was proposed by analyzing the force. Adopting the rollover pushing flight,the main lifting surface of missile was faced down,and the angle of attack was almost positive through the flight. The appearance of negative attack angle was delayed,and the duration was shorten. The fast ballistic diving rate was obtained. Taking the CAV-H as the research object,the proposed method was compared with the normal diving method by using Gauss pseudospectral method. The results show that the proposed method is more efficient than the normal one,and the angle of attack is maintained positive in the high heat flow zone in the high-speed flight phase. For the boost-glide missile with abdomen thermal design, the heat flow can be prevented spreading to the back of missile,and the security of diving attack improves.
