【作者】 杨峰；

【导师】 崔乃刚；

【作者基本信息】 哈尔滨工业大学 ， 飞行器设计， 2011， 硕士

【摘要】 随着军事科技的创新和武器系统的换代,大量的旧式弹道导弹面临着退役,如何处理这些弹道导弹并节约国家资源是一个需要解决的重要问题。借鉴助推-滑翔导弹的思想,对即将退役的弹道导弹进行一定的改造,将其作为滑翔导弹的助推器,是对上述问题的一个解决方案,而这种方案的可行性需要一定的理论分析和仿真验证。另外伴随着导弹防御系统的发展和伪装技术的进步,当滑翔导弹的攻击目标丢失(伪装隐匿或防御严密难以有效打击)后,如何选择新的目标,并规划出最优弹道并跟踪飞行也需要进行深入研究。第一个问题的难点集中在弹道导弹的弹道相对固定,滑翔弹头会以较大的弹道倾角再入大气层,造成了滑翔导弹再入后需要调整弹道倾角以进入稳定滑翔段,这对滑翔导弹制导控制系统和防热技术等提出了挑战。本文按照弹道优化设计的思想对该问题进行了研究和分析。首先在发射坐标系中建立了滑翔导弹的简化三自由度动力学与运动模型,建立了其气动模型,并给出了最终使用的优化模型。然后利用直接打靶法和序列二次规划算法,完成了对该种导弹无动力段弹道(即再入弹道)的最大纵程、最大横程仿真分析,从理论上验证了这种组合方式的导弹具备可行性。最后还对过固定路径点的弹道进行了仿真分析,为滑翔导弹的突防和在线目标重瞄提供了参考数据。第二个问题的难点集中在滑翔导弹的在线规划和标准弹道的跟踪制导上,归结起来是一个滑翔制导技术的应用问题。本文建立了以能量为自变量的滑翔导弹的运动学与动力学模型,参考阻力加速度再入制导技术提出了基于阻力加速度的滑翔制导算法,并利用该算法对滑翔导弹的在线目标重瞄制定了两种方案,进行了仿真分析。仿真结果显示该算法能够实现滑翔导弹的在线目标重瞄。本文顺利完成了对上述两个问题的研究和分析工作,但是也存在着一定的不足。首先,针对过固定路径点的弹道优化问题,还需要在理论上有所创新,能够在优化中对约束实现细化,从而使仿真弹道具有更大的参考价值。其次,对于在线目标重瞄技术,还需要进一步的研究和仿真验证,解决大弹道倾角、大攻角再入时滑翔导弹对标称轨道跟踪误差较大的问题。更多还原

【Abstract】 With the innovation of military technology and the upgrading of weapons systems, there are a lot of old ballistic missiles that will be decommissioned. How to deal with these ballistic missiles and to save the country’s resources is an important issue need to address. Refer to the conception of Boost-Glide Missile, those ballistic missiles can be used as a booster for the glide missile with a certain transformations, which is a solution to the issue. But the feasibility of such a solution requires a certain theoretical Analysis and simulation. Also associated with the development of missile defense systems and camouflage technology, when the glider lost its target (camouflage or hard to strike), how to select a new target, plan the optimal trajectory and tracking it are also need to address.Difficulties in the first issue focused on that glide warhead reentry with a large trajectory angle as the ballistic missile trajectory is relatively fixed. As a result, the glide must adjust its trajectory angle to fly stably, which bring on a challenge to the guidance & control systems and the thermal protection systems of the glide missile. However, the paper will use the trajectory optimization theory to analyze the feasibility of the solution. Firstly, the paper established a simplified three degrees of freedom dynamics model and motion model in the launching coordinate. Secondly, the paper use the direct shooting method and sequential quadratic programming algorithm to optimize the reentry trajectory that include the maximum longitudinal range trajectory and the maximum transverse range trajectory, which verified the feasibility of missile combination in theory. Finally, the paper simulated the trajectory over fixed path points, which will benefit for target penetration and online re-aiming to the glide missile.Difficulties in the Second issue focused on the trajectory online program and the standard trajectory tracking, totally speaking, this is a application problem of the glide-guided algorithms. The paper established the dynamics and motion models of the glide missile using energy as the independent variable. Then, proposed the glide guidance algorithms that improved on the drag acceleration reentry guidance. At last, the paper designed tow kinds of programs for online re-aiming using the glide guidance algorithms and completed the simulation analysis. The results of the simulation show that the algorithm can achieve online re-aiming of the glide missile.In summary, the paper successfully completed the research and analytical work of the two issues, but there are still some shortcomings. Firstly, the innovative theory is needed for the optimal problem of trajectory over fixed path points, so that the constraints could be refined in the optimization and the results of the optimization have more values. Secondly, further research and simulation are needed for the technology of online re-aiming, so that the errors in tracking standard trajectory in the early time of reentry with big trajectory angle and attack angle.更多还原