论文部分内容阅读
为提高大升阻比高超声速滑翔飞行器机动突防能力,提出了一种侧向摆动式机动弹道的设计方法。基于动态逆的思想,建立了侧向摆动式机动弹道的弹道形式和所需倾侧角间的关系模型;在平衡滑翔假设下,将包括动压、过载和热流在内的飞行约束转化为迎角约束,从而确定了迎角-速度飞行走廊;在此基础上,设计了平衡滑翔情况下满足侧向摆动式机动及飞行约束所需的迎角变化规律。根据所设计的迎角和倾侧角,即可实现平衡滑翔情况下预定机动模式的侧向机动。以HTV(Hypersonic Technology Vehicle)为例进行仿真分析,结果表明该方法能够快速设计出预定机动幅度和机动频率的侧向摆动式机动突防弹道。
In order to improve the ability of large lift-resistance hypersonic gliding aircraft to defend against maneuver, a design method of lateral swinging maneuvering trajectory is proposed. Based on the idea of dynamic inverse, a model of the relationship between the trajectory of the lateral swinging maneuvering trajectory and the required roll angle is established. Under the condition of balanced gliding, flight constraints including dynamic pressure, overload and heat flux are transformed into the angle of attack Then the AOA-speed flight corridor is determined. On the basis of this, the change rules of the angle-of-attack required to meet the lateral swing maneuvering and flight constraints under the condition of balanced gliding are designed. According to the design of the angle of attack and roll angle, you can achieve the case of balanced gliding lateral maneuvers scheduled maneuver mode. Taking HTV (Hypersonic Technology Vehicle) as an example, the simulation results show that this method can rapidly design a lateral swinging PDS with a predetermined maneuvering amplitude and maneuvering frequency.