中远程高超音速空舰导弹关键技术研究

【作者】 乔洋；

【导师】 赵育善；

【作者基本信息】 西北工业大学 ， 飞行器设计， 2003， 硕士

【摘要】 本文针对中远程高超音速导弹的关键技术，着重研究了导弹中段制导问题，主要内容包括：引入一种奇异摄动中制导律应用于高超音速导弹，并对此制导律加以改进，得到一种更为实用和可靠的最优中制导律；惯导／双星组合导航系统的必要性和可行性分析；提出了捷联陨导和主被动双模导引头复合制导的制导思路。解决了高超音速飞行空舰导弹中制导设计过程中的一些关键问题，本文的主要工作如下： 1、利用非线性奇异摄动系统两点约束最优问题的结论，在分析了导弹质心运动方程两时间尺度特性的基础上，本文引用了一种闭环形式的奇异摄动最优中制导律的设计方法，并将此方法应用于高超音速巡航导弹上，进行了三维弹道仿真，取得了良好的结果。 2、基于另一种时间尺度的划分方法，提出了一种计算量较小，比较简单的奇异摄动最优中制导律，并对此制导律进行进一步修正，得到一种快速爬升和快速下降的奇异摄动最优中制导律，仿真表明，改进的中制导律更加适用于高超音速巡航导弹。 3、论述了惯性／双星组合的必要性和可实现性；提出了惯性／双星组合中存在的主要问题和可能的对策。研究结果表明，惯性导航系统和双星定位系统进行组合是完全必要的，有广阔的发展空间。 4、本文提出采用捷联惯性导航与主被动双模导引头的复合制导控制技术，中制导导引方法采用“捷联惯性导航+被动寻的导引”复合制导，被动头实现对目标的角跟踪，实现导弹的侧向纠偏。导弹末制导采用“捷联惯性导航+主动寻的导引”复合制导，主动头实现对目标的角跟踪和速度跟踪。保障导弹在飞行过程全过程都有控制指令，为高超速导弹的中制导提供可行的组合方案，降低对高超速巡航导弹初始对准精度的要求。更多还原

【Abstract】 Aiming at the medium-range and long-distance high supersonic missile’s key technology, this dissertation emphasizes particularly on a high supersonic air-ship missile’s guidance and control problems, including the quotation and improvement of a singular perturbation midcourse guidance law, the analysis about the combination of inertia navigation and double star orientation and the compound guidance system of SINS/active and passive guidance head, which solve some sixty-four-dollar questions, and receive good result. The major contributions of the dissertation are as follows.1. Taking the advantage of the conclusion on the most excellent problem of two restrains in the nonlinear singular perturbed systems, through analyzing the two-time-scale behavior of point-mass equation for missiles, the paper introduce a closed loop’s design method of singular perturbed optimum midcourse guidance and control law, Finally this method is applied to a high supersonic cruise missile to imitate the three dimension trajectory, which receives a good result.2. A midcourse guidance law is presented based on the other method of dividing time-scale of point-mass equation for missiles. After the guidance law is revised, the paper puts forward a new singular perturbed optimum midcourse guidance and control law that ascents and descends more quickly. The imitation shows that the improved midcourse guidance law is more fit for high supersonic cruise missile.3. This paper discusses the indispensability and the feasibility of the combination of inertia navigation and double star orientation, then it puts forward some major problems and some possible solutions in this combinatioa The research shows that the combination system has expansive development space.4. The dissertation puts forward a compound guidance and control technology adopting SINS and guidance head, midcourse guidance method adopts compound guidance of SINS and passive guidance, passive guidance head measures angle between missile and target to rectify missile’s deviation, terminal control method is compound guidance of SINS and active guidance, active guidance head measures angle and velocity between missile and target, missiles have control instructions in the whole flight process. A feasible compound method is presented for high supersonic cruise missiles and requirement of original precision is reduced.更多还原