高马赫数临近空间无人机主要总体参数设计方法

doi:10.7527/S1000-6893.2016.0255

固体力学与飞行器总体设计

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高马赫数临近空间无人机主要总体参数设计方法

有连兴, 余雄庆

南京航空航天大学航空宇航学院飞行器先进设计技术国防重点学科实验室, 南京 210016

收稿日期:2016-06-11 修回日期:2016-09-09 出版日期:2017-04-15 发布日期:2016-10-09
通讯作者: 余雄庆 E-mail:yxq@nuaa.edu.cn
基金资助:
中央高校基本科研业务费专项资金（NZ2016101）；江苏高校优势学科建设工程资助项目

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

YOU Lianxing, YU Xiongqing

Key Laboratory of Fundamental Science for National Defense Advanced Design, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2016-06-11 Revised:2016-09-09 Online:2017-04-15 Published:2016-10-09
Supported by:
the Fundamental Research Funds for the Central Universities (NZ2016101); A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要：

针对高马赫数临近空间无人机（HSUAV）概念设计的需求，研究一种飞行器主要总体参数设计的改进方法，目的是提高主要总体参数设计的可信度。在现有的约束分析和任务分析方法基础上，通过融入适用性更广、预测精度更高的气动模型和推进系统模型，建立了一种迭代的设计计算流程。应用参数化建模方法建立了气动数值分析模型，应用发动机热力循环分析建立了推进系统模型。应用本文方法完成了高马赫数临近空间无人机主要总体参数设计计算，结果表明：经过若干次迭代设计计算，主要总体参数值收敛；由传统方法确定的主要总体参数与本文方法的结果有明显差别。由于本文方法中使用了可信度更高的气动和推进系统模型，根据本文方法确定的主要总体参数具有更高的可信度。

关键词: 无人机, 概念设计, 临近空间, 高马赫数, 约束分析, 任务分析

Abstract:

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.

Key words: unmanned aerial vehicle, conceptual design, near space, high supersonic speed, constraint analysis, mission analysis

中图分类号:

V221

有连兴, 余雄庆. 高马赫数临近空间无人机主要总体参数设计方法[J]. 航空学报, 2017, 38(4): 220514-220514.

YOU Lianxing, YU Xiongqing. Preliminary sizing method for near-space high supersonic unmanned aerial vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(4): 220514-220514.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高马赫数临近空间无人机主要总体参数设计方法

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

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