ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Preliminary sizing method for near-space high supersonic unmanned aerial vehicles
Received date: 2016-06-11
Revised date: 2016-09-09
Online 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
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.
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 . DOI: 10.7527/S1000-6893.2016.0255
[1] CURRAN E T, MURTHY S N B. Scramjet propulsion[M]. Reston:AIAA Inc., 2000:449.
[2] RICH B R. F-12 series aircraft aerodynamic and thermodynamic design in retrospect[J]. Journal of Aircraft, 1974, 11(7):401-406.
[3] SCHVTTE G, STAUDACHER S. Probabilistic aspects of scramjet design[J]. Journal of Propulsion and Power, 2009, 25(2):281-288.
[4] Marshall Space Flight Center. Study on the modifications required to re-engine the Lockheed D-21 Drone:NASA 1999-0110312[R]. Washington, D.C.:NASA, 1999.
[5] HOWE D. Aircraft conceptual design synthesis[M]. Hoboken, NJ:John Wiley & Sons, Ltd., 2000:1-22.
[6] RAYMER D. Aircraft design:A conceptual approach[M]. 5th ed. Reston:AIAA Inc., 2012:27-702.
[7] MATTINGLY J D, HEISER W H, PRATT D T. Aircraft engine design[M]. 2nd ed. Reston:AIAA Inc., 2002:3-229.
[8] GUDMUNDSSON S. General aviation aircraft design:Applied methods and procedures[M]. Amsterdam:Elsevier Inc., 2014:925-934.
[9] HEISER W H, PRATT D T, DALEY D H, et al. Hypersonic airbreathing propulsion[M]. Reston:AIAA Inc., 1994:456-463.
[10] SAUNDERS J D, KEITH T G. Results from computational analysis of a mixed compression supersonic inlet:NASA TM 104475[R]. Washington, D.C.:NASA, 1991.
[11] FRY R S. A century of ramjet propulsion technology evolution[J]. Journal of Propulsion and Power, 2004, 20(1):27-58.
[12] PATERSON J. Overview of low observable technology and its effects on combat aircraft survivability[J]. Journal of Aircraft, 1999, 36(2):380-388.
[13] ROSKAM J. Airplane design Part I:Preliminary sizing of airplanes[M]. Lawrence, KS:Design, Analysis and Research Corporation, 1985:1-202.
[14] IQBAL L U, SULLIVAN J P. Multidisciplinary design and optimization (MDO) methodology for the aircraft conceptual design[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston:AIAA, 2009.
[15] 余雄庆, 丁运亮. 多学科设计优化算法及其在飞行器设计中应用[J]. 航空学报, 2000, 21(1):1-6. YU X Q, DING Y L. Multidisciplinary design optimization a survey of its algorithms and applications to aircraft design[J]. Acta Aeronautica et Astronautica Sinica, 2000, 21(1):1-6 (in Chinese).
[16] NICOLAI L M, CARICHNER G E. Fundamentals of aircraft and airship design Volume I-Aircraft design[M]. Reston:AIAA Inc., 2010:323-779.
[17] BOWCUTT K G, ANDERSON J D, CAPRIOTTI D. Viscous optimized hypersonic waveriders:AIAA-1987-0272[R]. Reston:AIAA, 1987.
[18] MURTHY S N B, CURRAN E T. Developments in high-speed vehicle propulsion systems[M]. Reston:AIAA Inc., 1996:188-202.
[19] JACOB D, SACHS G, WAGNER S. Basic research and technologies for two-stage-to-orbit vehicles[M]. Weinheim:WILEY-VCH Verlag GmbH & Co. KGaA, 2005:9-267.
[20] 有连兴, 余雄庆, 欧阳星. 高马赫数无人机概念设计的外形参数化建模[J]. 南京航空航天大学学报, 2014, 46(3):425-432. YOU L X, YU X Q, OUYANG X. Parametric geometry modeling for conceptual design of high supersonic unmanned aerial vehicles[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2014, 46(3):425-432 (in Chinese).
[21] 余雄庆, 欧阳星, 邢宇, 等. 机翼结构重量预测的多学科分析优化方法[J]. 航空学报, 2016, 37(1):235-243. YU X Q, OUYANG X, XING Y, et al. Weight prediction method of wing structure using multidisciplinary analysis and optimization[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1):235-243 (in Chinese).
/
| 〈 |
|
〉 |
CJA