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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >BALLISTIC MISSILE TRAJECTORY DESIGN CONSIDERING IMPACT ANGLE CONSTRAINT
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BALLISTIC MISSILE TRAJECTORY DESIGN CONSIDERING IMPACT ANGLE CONSTRAINT

机译：考虑冲击角约束的弹道导弹弹道设计

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The current paper investigates the problem of guiding ballistic re-entry vehicles to the terminal point under the additional terminal constraint of final flight path angle. In this regard, the classical Lambert's Problem is reformulated to include the final flight path angle constraint. The proposed solution of the modified Lambert's problem consists of a minimum of two different trajectories starting from the same initial location and intersecting each other at a location, which is determined by applying the desired time of flight and terminal flight path angle constraints. The modified Lambert strategy strategy is shown to satisfy terminal flight path angle constraint along with the time of fliglit, initial and final location constraints. This scheme requires the ballistic vehicle to perform an additional stage burn during descent in-order to switch from an initial trajectory, using Lambert strategy, to a final trajectory which satisfies the final flight path angle constraint. An additional stage burn is provided such that the position and velocity of the vehicle traveling in the initial trajectory is matched with that required for it to be on the final trajectory. It is also found that the amount of propellant required for the trajectory transfer, is dependent on the total time of flight and the altitude at which the additional stage burn occurs. The optimal values of these two parameters are found using interior-point optimization technique.
机译：本文研究了在最终飞行路径角的附加终端约束下将弹道再入飞行器引导到终端的问题。在这方面，经典兰伯特问题被重新表述为包括最终飞行路径角度约束。修改后的兰伯特问题的拟议解决方案包括从相同的初始位置开始并在一个位置彼此相交的至少两个不同的轨迹，这是通过应用所需的飞行时间和终端飞行路径角度约束来确定的。改进的Lambert策略策略显示满足终端飞行路径角度约束以及跳动，初始和最终位置约束的时间。该方案要求弹道飞行器在下降期间执行额外的阶段燃烧，以便使用兰伯特策略从初始轨迹切换到满足最终飞行路径角度约束的最终轨迹。提供附加的阶段燃烧，使得在初始轨迹上行驶的车辆的位置和速度与其在最终轨迹上所需的位置和速度相匹配。还发现，轨迹转移所需的推进剂的量取决于飞行的总时间和发生额外阶段燃烧的高度。使用内点优化技术找到这两个参数的最佳值。

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    Karthikeyan Kalirajan; Ashok Joshi;

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    Department of Aerospace Engineering, Indian Institute of Technology Bombay, Powai, Mumbai-400 076, India;

    Department of Aerospace Engineering, Indian Institute of Technology Bombay, Powai, Mumbai-400 076, India;

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