超声速飞机低声爆布局混合优化方法研究
收稿日期: 2012-09-20
修回日期: 2012-12-31
网络出版日期: 2013-02-26
基金资助
西北工业大学博士论文创新基金(CX-201232)
Hybrid Optimization Approach Research for Low Sonic Boom Supersonic Aircraft Configuration
Received date: 2012-09-20
Revised date: 2012-12-31
Online published: 2013-02-26
Supported by
Doctorate Foundation of Northwestern Polytechnical University (CX-201232)
声爆精确预测及低声爆设计方法已成为新一代军民用超声速飞机研制过程中必须解决的关键难题之一。将改进后的SGD(Seebass-George-Darden)反设计方法、声爆预测算法与遗传算法相结合,形成低声爆布局混合优化方法,利用遗传算法对SGD参数进行优化,得到具有较低声爆超压值和较大有效容积的等效截面积分布,进而得到低声爆布局方案。构建了低声爆混合优化设计环境,可以对方案的声爆水平、感觉噪声级、机体有效容积以及等效截面积分布等进行计算分析,在总体设计阶段具有较高的工程实用价值。优化后的方案采用连翼布局,钝形机头设计,优化后方案的声爆超压值降低了14.51%,机体有效容积增加了15.08%。由于尾部激波强度的不同,地面声爆感觉噪声级随滚转角的变化呈现先变小、后变大、再变小的趋势,对于尾部声爆波形还需进一步优化研究,以降低感觉噪声级。
冯晓强 , 宋笔锋 , 李占科 , 桑建华 . 超声速飞机低声爆布局混合优化方法研究[J]. 航空学报, 2013 , 34(8) : 1768 -1777 . DOI: 10.7527/S1000-6893.2013.0057
High fidelity sonic boom prediction and low sonic boom design methods are key technologies of next generation supersonic aircraft. By coupling a modified SGD (Seebass-George-Darden) method, a high fidelity sonic boom prediction method and a Pareto genetic algorithm, a hybrid optimizing approach is developed. The parameters of the SGD method are optimized and an equivalent area distribution with a lower sonic boom overpressure and large available volume can be obtained. By using the optimized equivalent area distribution, a low boom layout can be designed. A low sonic boom configuration mixed optimizing environment is developed, which integrates sonic boom analysis, perceived loudness analysis, available volume calculation and equivalent area distribution generation. The low sonic boom configuration mixed optimizing environment can be used in the conceptual design phase. The optimized layout is a joint wing configuration with a blunt nose. The sonic boom overpressure decreases by 14.51% and the available volume increases nearly 15.08%. Due to the different strengths of the after shock wave, the relationship between the PLdB and roll angle is complex. The after shock of the sonic boom should be optimized in future work for mitigating PLdB.
[1] Menexiadis G. Long-range propagation of sonic boom form the concorde airliner: analyses and simulations. Journal of Aircraft, 2008, 45(5): 1612-1618.
[2] Seebass A R. Sonic boom theory. Journal of Aircraft, 1969, 6(13): 177-184.
[3] Kusunose K. A fundamental study for the development of boomless supersonic transport aircraft. AIAA-2006- 654, 2006.
[4] Li W, Shields E, Le D. Interactive inverse design optimization of fuselage shape for low-boom supersonic concepts. Journal of Aircraft, 2008, 45(4): 1381-1398.
[5] Howe D C. Development of the Gulfstream quiet spike for sonic boom minimization. AIAA-2008-124, 2008.
[6] Knight M. Quiet spike prototype morphing performance during flight test. AIAA-2008-127, 2008.
[7] Zi Z H, Lv Y L. Study of passive acoustic locating of supersonic multi-target. Computer Engineering and Applications, 2010, 46(10): 202-205. (in Chinese) 字正华, 吕永林.多超声速目标被动声定位技术研究.计算机工程与应用, 2010, 46(10): 202-205.
[8] Chen P, Li X D. Frequency domain method for predicting sonic boom propagation based on Khokhlov-Zabolotskaya-Kuznetsov equation. Journal of Aerospace Power, 2010, 25(2): 359-365.(in Chinese) 陈鹏,李晓东.基于Khokhlov-Zabolotskaya-Kuznetsov方程的声爆频域预测. 航空动力学报, 2010, 25(2): 359-365.
[9] Dan D. Supersonic business design based on request of sonic boom and takeoff/approaching acoustics. Chengdu: Chengdu Aircraft Research and Design Institute, 2010.(in Chinese) 但聃. 基于声爆和起降噪声要求的超音速公务机设计. 成都: 成都飞机设计研究所, 2010.
[10] Feng X Q, Li Z K, Song B F. Preliminary analysis on the sonic boom of supersonic aircraft. Flight Dynamics, 2010, 28(6): 21-27.(in Chinese) 冯晓强, 李占科, 宋笔锋. 超音速客机音爆问题初步研究. 飞行力学, 2010, 28(6): 21-27.
[11] Feng X Q, Li Z K, Song B F. A research on inverse design method of a lower sonic boom supersonic aircraft configuration. Acta Aeronautica et Astronautica Sinica, 2011, 32(11): 1980-1986.(in Chinese) 冯晓强, 李占科, 宋笔锋.超声速客机低音爆布局反设计技术研究. 航空学报, 2011, 32(11): 1980-1986.
[12] Feng X Q. The research of sonic boom prediction method and application in supersonic aircraft design. Xi'an: School of Aeronautics, Northwestern Polytechnical University, 2012.(in Chinese) 冯晓强. 声爆计算方法研究及在超声速客机设计的应用. 西安: 西北工业大学航空学院, 2012.
[13] Rallabhandi S. Sonic boom minimization through vehicle shape optimization and probabilistic acoustic propagation.Georgia Institute of Technology, 2005.
[14] Liang Y, Cheng X Q, Li Z N. Multi-object aerodynamic configuration parameter design using kriging approximation. Acta Aeronautica et Astronautica Sinica, 2010, 31(6): 1141-1148.(in Chinese) 梁煜, 程小全, 郦正能. 基于代理模型的气动外形平面参数多目标匹配设计.航空学报, 2010, 31(6): 1141-1148.
[15] Kalyanmoy D, Pratap A. A fast and elitist multi-objective genetic algorithm: NSGA-Ⅱ. IEEE Transactions on Evolutionary Computation, 2002, 6(2): 182-197.
[16] Plotkin K J. State of the art of sonic boom modeling. Journal of Acoustical Society of America, 2002, 111(1): 530-536.
[17] Siclari M, Darden C. A euler code prediction of near to mid-field sonic boom pressure signature. AIAA-1990-4000, 1990.
[18] Thomas C L. Extrapolation of sonic boom pressure signatures by the waveform parameter method. NASA TND-6832, 1972.
[19] Page J A. An efficient method for incorporating computational fluid dynamics into sonic boom prediction.AIAA-1991-53882, 1991.as C L. Extrapolation of sonic boom pressure signatures by the waveform parameter method[R]. NASA TND-6832, 1972.
[18] J.A.Page. An efficient method for incorporating computational fluid dynamics into sonic boom prediction[R].AIAA-1991-53882,1991.
[19] Stevens.S.S. Perceived level of noise by Mark VII and decibels. The Journal of the Acoustical Society of America,1972;51(2):575-601.
/
| 〈 |
|
〉 |
CJA