受限计算制导与控制方法及其在高超声速再入中的应用
Method for Constrained Computational Guidance and Control with Application to Hypersonic Entry
浏览论文内容
中文总结 AI 辅助
本文提出一种通过周期性重解受限最优控制问题并引入惩罚项增大约束裕度的计算制导与控制方法，并在最大横程RLV再入问题中验证了其可行性。
中文摘要 AI 辅助
本文描述了一种受限计算制导与控制方法。该方法通过周期性重新求解受限最优控制问题来实现制导更新。通过防止扰动系统中的约束违反，提高了最优控制问题的可行性。为防止约束违反，在最优控制问题中增加了一个惩罚项，该惩罚项旨在当扰动系统接近约束极限时增大约束与其极限之间的裕度。附加的惩罚项采用平滑最大值近似来增大约束与其极限之间的裕度。本文所开发的方法在最大横程可重复使用运载器（RLV）再入问题中得到了验证，该问题的参考解包含一段长时间的受限弧段。结果表明，本文所开发的方法对于路径受限的最优制导与控制是可行的。
英文摘要
A method for constrained computation guidance and control is described. The method employs guidance updates by periodically re-solving a constrained optimal control problem. Feasibility of the optimal control problem is improved by preventing constraint violations in the perturbed system. Constraint violation is prevented by augmenting the optimal control problem with a penalty term intended to increase the margin between a constraint and its limit when the perturbed system is within certain proximity of the constraint limit. The additional penalty term employs a smooth maximum approximation to increase the margin between the constraint and its limit. The method developed in this paper is demonstrated on the maximum cross-range reusable launch vehicle (RLV) entry problem, for which the reference solution contains a long-duration constrained arc. The results demonstrate that the method developed in this paper is viable for path-constrained optimal guidance and control.
发表机构
- University of Florida（佛罗里达大学）
机构由 AI 辅助整理，请以论文原文为准。
