Details

Autor(en) / Beteiligte

• Qu, Zhengyu
• Yang, Yanchu
• Yan, Feng

Titel

Optimization Study of High Altitude Micro Gliding Air Vehicle Re-Entry Path Characteristics

Ist Teil von

• Xibei Gongye Daxue Xuebao, 2019-10, Vol.37 (5), p.983-991

Ort / Verlag

EDP Sciences

Erscheinungsjahr

2019

Link zum Volltext

Quelle

EZB Electronic Journals Library

Beschreibungen/Notizen

• Based on the characteristics of the configuration and flight of the micro gliding air vehicle (MGAV), an analysis and optimization for general gliding path of different mission demands is carried out. Firstly, an overall design method and parameters are summarized. Secondly, the equilibrium glide launching parameters are determined based on the general aircraft re-entry equation. The real launching parameter are also developed by considering the real launching facility. Furthermore, the un-controlled maximum-range-towards path characteristics for the real and equilibrium glide are compared and analyzed. The range in equilibrium glide is 5 km larger than real glide. Then, two potential flight demand are explained and the Gauss pseudo-spectral method is adopted to solve the maximum endurance and the maximum endurance and range with the process constraint and final constraint. The first target is 8 minutes longer than the original glide path but the range is 20 km less compared to the maximum range. The second target could keep the maximum range and at the meantime, the endurance could be increased 2 minutes. Finally, the control variables are substituted into the dynamic equations to validate the results. The result shows that the Gauss pseudo-spectral method is an effective and feasible way to solve the optimum gliding path. 基于滑翔式微型飞行器（micro gliding air vehicle，MGAV）的布局、投射及飞行特点，分析并优化其在不同任务需求下的一般轨迹特性。首先，概述了此种MGAV的设计过程及总体参数；接着，基于一般意义的飞行器平面运动模型，推导出平衡滑翔初始投射条件，并结合实际投射装置参数推导真实初始投射条件。进一步分别比较了在这两种投射条件下的无约束最远射程轨迹特性，真实滑翔比平衡滑翔在射程上减少约5 km。然后，分析了此种飞行器可能存在的任务需求，采用高斯伪谱法得到在过程约束及终端约束下最长滑翔时间及保证滑翔时间及滑翔距离同时最长2种目标函数下的最优滑翔轨迹。第一种目标下，优化后航时和无控滑翔相比可提高约8 min，但是和理论最远射程136 km相比缩短20 km。第二种目标下，在最远射程维持不变的同时可使航时提高约2 min。最后，将优化轨迹的控制变量带入到动力学方程积分进行可行性验证。研究结果表明，基于高斯伪谱法的轨迹分析是一种高效可行的轨迹优化策略。