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Matlab_3dof_animation
- 采用比例导引法,把三维追击轨道分解到两个二维平面上分别导引,并充分考虑到目标的 机动性对弹道的影响,用MATLAB软件编写程序模拟出导弹实际追击的三维变轨弹道,绘制出分运动和合运动中各参数的 变化曲线。最后比较了不同的追击速度和不同的导引系数k对弹道特性的影响,考虑到导弹实际飞行时受需用法向过载的 制约,导出了导引系数k应满足的普遍公式,提出了对实战具有一定参考价值的建议。 -Using proportional navigation law, in pursuit of the
ResearchontheProcessofShiptoairMissile
- 舰空导弹协同制导流程研究,通过对舰空导弹常见制导方法过程的分析,结合网络中心战以及协同作战能力的概念,提出多平台协同制导对 导弹制导模式的要求,对未来舰空导弹协同制导时的制导过程进行初步探讨,并指出实现协同制导需要解决的关键技术。-Ship-to-air guided missile synergistic flow study, through the ship-to-air guided missile common method of analysis of the process,
Missile_Guidance_Control_Systems
- The book presents a historical background of past and present guided missile systems and the evolution of modern weapons,discusses the generalized missile equations of motion, aerodynamic forces and coefficients, the important subject of the various
duocengcifa
- 为了使导弹优化的弹道更有效地杀伤目标,采用多层次法来设计防空导弹中制导段弹道.-In order to optimize the ballistic missile more effective anti-target, multi-level method to design air-defense missiles Guidance Trajectory.
missile-guidance-for-beginners
- 关于导弹制导的一些文献 适合初学者对制导率原理的认识和设计-Some of the literature on missile guidance guidance for beginners to understand and design principles of the rate
Missile
- 导弹内部控制系统的设计。包括导弹制导，导弹飞行，导弹控制，通信传输等等部分。-Missile internal control system design. Including missile guidance, missile flight, missile control, communications, transport and so on parts.
MISSILE
- 针对三点法三维运动学弹道仿真问题，建立了两种仿真模型 第一种模型采用数值积分算法求解 三点法运动学方程组，求解过程较为复杂 第二种模型利用三维空间相关几何知识，将求解三点法三维运动学 弹道的图解法转化为求解一元二次方程的问题，使求解过程简单直观 最后，对两种模型进行了仿真，并将其 应用到地空导弹制导控制系统的仿真研究中，将理想弹道与控制弹道进行了对比 结果表明，两个模型均解决了一般情形下三点法三维运动学弹道求解的问题，为三点法三维制导律以及弹道特性研究提供了一种方法-Three-po
Considering-the-model-uncertainty
- 导弹制导的协同控制方法:针对导弹制导系统中存在的模型不确定性和外部扰动，研究了末制导规律的设计与实现问题。-Considering the model uncertainty and external disturbance in guidance system，the de— sign and implementation method of terminal guidance law for a missile is investigated
pgmissile
- Project : Missile Target Simulation using Proportional Navigation Proportional navigation is the guidance law used by most missiles in operational use today. This method of guidance, generates missile acceleration commands in proportion to the
coorsinat
- The success of a guided missile is dependent on certain factors. The most significant error sources affecting the success of a guided missile are the initial heading error of the missile and the target maneuvers. Apart from these, the dynamic
Trajectory-Shape-Varying-Missile-Guidance-for-Int
- Trajectory-Shape-Varying Missile Guidance for Interception of Ballistic Missiles during the Boost Phase