Preliminary sizing method for near-space high supersonic unmanned aerial vehicles

被引：0
作者：
You L. [1 ]
Yu X. [1 ]
机构：
[1] Key Laboratory of Fundamental Science for National Defense Advanced Design, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Yu, Xiongqing (yxq@nuaa.edu.cn) | 1600年 / Chinese Society of Astronautics卷 / 38期
关键词：
Conceptual design; Constraint analysis; High supersonic speed; Mission analysis; Near space; Unmanned aerial vehicle;
D O I：
10.7527/S1000-6893.2016.0255
中图分类号：
学科分类号：
摘要：
An improved method is proposed for preliminary sizing in conceptual design of a near-space high supersonic unmanned aerial vehicle (HSUAV). This improved method is aimed to enhance reliability of the preliminary sizing. An iterative sizing process is developed, in which the aerodynamic and propulsion models with higher applicability and accuracy are integrated into traditional methods of constraint analysis and mission analysis. The aerodynamic model is established using the parametric method. The aerothermodynamic model of the propulsion system is achieved by treating each stream as the one-dimensional flow of a perfect gas. With the method proposed, the preliminary sizing process in the conceptual design of the near-space high supersonic unmanned aerial vehicles is accomplished. The results show that sizing parameters are converged after several iterations, and there exist significant differences between the result obtained from the traditional method and that from the improved method. The preliminary sizing results obtained from the method proposed in the paper are more reliable due to higher fidelity of the aerodynamic and propulsion models. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.
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