Aerodynamic characteristics modeling of post-stall re-orientation maneuver

KONG Yinan; WU Bin; WANG Qing; CHEN Gong; YU Jing

doi:10.7638/kqdlxxb-2023.0049

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Aerodynamic characteristics modeling of post-stall re-orientation maneuver

更新时间：2026-05-28

- Aerodynamic characteristics modeling of post-stall re-orientation maneuver
- Vol. 42, Issue 5, Pages: 72-80(2024)
- 作者机构：
  
  1. 中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
  2. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621000
  3. 南京航空航天大学航空学院,南京,210016
  4. 上海机电工程研究所,上海,201100
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0049
  CLC： TJ013
- Published：2024
- 稿件说明：
移动端阅览
孔轶男, 伍彬, 汪清, 等. 过失速重新定向机动过程气动特性建模[J]. 空气动力学学报, 2024, 42(5): 72−80.

KONG Yinan, WU Bin, WANG Qing, et al. Aerodynamic characteristics modeling of post-stall re-orientation maneuver[J]. 2024, 42(5): 72-80.
孔轶男, 伍彬, 汪清, 等. 过失速重新定向机动过程气动特性建模[J]. 空气动力学学报, 2024, 42(5): 72−80. DOI： 10.7638/kqdlxxb-2023.0049

KONG Yinan, WU Bin, WANG Qing, et al. Aerodynamic characteristics modeling of post-stall re-orientation maneuver[J]. 2024, 42(5): 72-80. DOI： 10.7638/kqdlxxb-2023.0049.

摘要

以过失速重新定向技术为基础的自翻转越肩飞行器与传统越肩发射飞行器相比，具有响应时间短、机动性能高、射程远等优势。本文针对飞行器过失速重新定向机动过程，基于CFD动态计算数据分析了该过程中的飞行器气动特性，通过改进微分方程模型成功描述了机动过程中的迟滞环效应，同时验证了最小二乘支持向量机方法在此建模问题中的适用性。本文的建模方法可以准确捕捉飞行器过失速重新定向机动过程中的非线性非定常气动特性，为飞行器过失速重新定向机动控制律设计提供模型基础。

Abstract

Compared to traditional over-shoulder-launched aircrafts

aircrafts based on the post-stall re-orientation technique have operational advantages

such as short response time

high manoeuvrability

and long range. Therefore

it is an advantageous option for the new generation of air-launched aircrafts to achieve omnidirectional attack. Focusing on the manoeuvre course of the post-stall re-orientation slender body

CFD simulations were performed to analyze the aerodynamic characteristics in this study. By improving the differential equation method

the hysteresis characteristics that exist in the post-stall re-orientation process can be successfully predicted. At the same time

the applicability of the least square support vector machine(LS-SVM) method in modeling such a problem has been verified. The present method can capture the non-linear unsteady aerodynamic characteristics in the re-orientation process

which provides a foundation in the control law design for post-stall re-orientation slender body.

关键词

Keywords

references

WISE K A, ROY D J B . Agile missile dynamics and control[J ] . Journal of Guidance, Control, and Dynamics, 1998 , 21 ( 3 ): 441 − 449 .

YAN L, MA K M, DONG J P, et al . Design of over-the-shoulder launch control for air-to-air missiles with lateral jets[J ] . Aero Weaponry, 2013 , 20 ( 6 ): 3 − 8 (in Chinese) .

WANG P, CHEN W C, YIN X L . Large angle attitude reaction jet control for an air-to-air missile[J ] . Acta Aeronautica et Astronautica Sinica , 2005 , 26 ( 3 ): 263 − 267 (in Chinese) .

ZHANG Y, LIU C F . Unsteady aerodynamics characteristics on self-turning of missile at extra-wide angle-of-attack[J ] . Journal of Projectiles, Rockets, Missiles and Guidance, 2015 , 35 ( 5 ): 112 − 118 (in Chinese) .

HESSMAN F. High angle of attack aerodynamic characteristics for a finless TVC missile configuration[C]// 9th Atmospheric Flight Mechanics Conference, San Diego, CA. Reston, Virginia: AIAA, 1982: 1337.

SMITH E H, HEBBAR S K, PLATZER M F . Aerodynamic characteristics of a canard-controlled missile at high angles of attack[J ] . Journal of Spacecraft and Rockets, 1994 , 31 ( 5 ): 766 − 772 .

LI X P, LIN J . Experimental investigation on pressure distribution characteristics of wings of ×× missile at supersonic speeds and high angles of attack[J ] . Journal of Experiments in Fluid Mechanics, 2001 , 15 ( 3 ): 43 − 47 (in Chinese) .

GENG X. Experimental study on rolling characteristics of high maneuvering missile at high angle of attack[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016(in Chinese).

KINSEY D, STRANG W. Aerodynamic analysis of finned missiles at supersonic speeds and high angles of attack[C]//18th Applied Aerodynamics Conference, Denver, CO. Reston, Virginia: AIAA, 2000: 4213.

MCGOWAN G, KURZEN M, NANCE R, et al. Computational investigation of pitch damping on missile geometries at high angles of attack[C]//30th AIAA Applied Aerodynamics Conference, New Orleans, Louisiana. Reston, Virginia: AIAA, 2012: 2903.

XU K Z, ZHANG Y F, CHEN H X, et al . Numerical study of induced nonlinear rolling moment of finned missile at high angles of attack[J ] . Acta Aeronautica et Astronautica Sinica, 2014 , 35 ( 1 ): 97 − 104 (in Chinese) .

AGNONE A. High angle of attack aerodynamics of a cruciformed missile[C]//22nd Aerospace Sciences Meeting, Reno, NV. Reston, Virginia: AIAA, 1984: 507.

ABNEY E, MCDANIEL M. High angle of attack aerodynamic predictions using missile datcom[C]//23rd AIAA Applied Aerodynamics Conference, Toronto, Ontario, Canada. Reston, Virginia: AIAA, 2005: 5086.

LESIEUTRE D, LOVE J, DILLENIUS M. High angle of attack missile aerodynamics including rotational rates - Program M3HAX[C]//21st Atmospheric Flight Mechanics Conference, San Diego, CA. Reston, Virginia: AIAA, 1996: 3392.

GAO C H, SONG W P, HAN S Q, et al . Research on poststall re-orientation technology of air-to-air missile[J ] . Air and Space DEFENSE, 2022 , 5 ( 3 ): 17 − 26 (in Chinese).

LEI Z Y, ZHOU J . The control and simulation of over the shoulder of air-to-air missile's agile turn[J ] . Fire Control and Command Control, 2010 , 35 ( 1 ): 153 − 155 (in Chinese) .

YAN L, ZHAO Y J, ZHAO Y H, et al . Control design of lateral motion in over-the-shoulder launch of air-to-air missile[J ] . Navigation Positioning and Timing, 2015 , 2 ( 1 ): 11 − 15 (in Chinese) .

WANG Q, HE K F, QIAN W Q, et al . Aerodynamic modeling of spatial maneuveri ng aircraft at high angle of attack[J ] . Acta Aeronautica et Astronautica Sinica, 2004 , 25 ( 5 ): 447 − 450 (in Chinese) .

卢卡斯. 微分方程模型[M]. 朱煜民, 周宇虹译. 长沙: 国防科技大学出版社, 1988.

DIAS J, SULEMAN A, BROUGHTON B. Aircraft wind tunnel characterization using modern design of experiments[C]//54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Boston, Massachusetts. Reston, Virginia: AIAA, 2013: 1502.

WANG Q, QIAN W Q, DING D . A review of unsteady aerodynamic modeling of aircrafts at high angles of attack[J ] . Acta Aeronautica et Astronautica Sinica, 2016 , 37 ( 8 ): 2331 − 2347 (in Chinese) .

蔡金狮, 汪清, 王文正等. 飞行器系统辨识学[M]. 北京: 国防工业出版社, 2003.

FANG Z P, CHEN W C, ZHANG S G. Flight dynamics of aircraft[M]. Beijing: Beijing University of Aeronautics Astronautics Press, 2005(in Chinese).

SINHA N K, ANANTHKRISHNAN N. Advanced flight dynamics with elements of flight control[M]. Boca Raton: CRC Press, 2017.

WANG Q, KONG Y N, QIAN W Q, et al. Missile nonlinear unsteady aerodynamic differential equation model identification method: CN114896830B[P]. 2022-11-08(in Chinese).

WALKER J M, HELIN H E, STRICKLAND J H . An experimental investigation of an airfoil undergoing large-amplitude pitching motions[J ] . AIAA Journal, 1985 , 23 ( 8 ): 1141 − 1142 .

TUNCER I H, WU J C, WANG C M . Theoretical and numerical studies of oscillating airfoils[J ] . AIAA Journal, 1990 , 28 ( 9 ): 1615 − 1624 .

TAVARES T S, MCCUNE J E . Aerodynamics of maneuvering slender wings with leading-edge separation[J ] . AIAA Journal, 1993 , 31 ( 6 ): 977 − 986 .

VAPNIK V N. The nature of statistical learning theory[M]. New York: Springer, 1995.

SOLTANI M R, BRAGG M B, BRANDON J M . Measurements on an oscillating 70-deg delta wing in subsonic flow[J ] . Journal of Aircraft, 1990 , 27 ( 3 ): 211 − 217 .

BRAGG M B, SOLTANI M R . Measured forces and moments on a delta wing during pitch-up[J ] . Journal of Aircraft, 1990 , 27 ( 3 ): 262 − 267 .

JARRAH M A. Low speed wind tunnel investigation of the flow about delta wing, oscillating in pitch to very high angle of attack[C]// 27th Aerospace Sciences Meeting, Reno, NV, USA. Reston, Virginia: AIAA, 1989: 295.

KONG Y N, WANG Q, CHENG G, et al. Missile nonlinear unsteady aerodynamic characteristic LS-SVM modeling method: CN114611416B[P]. 2022-08-02(in Chinese) .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Multi-factor analysis and simulation of particle erosion characteristics of fan blades

Optimization of hot-air anti-icing structures based on neural networks and genetic algorithms

An Ac-criteria-based optimal input design method

Dynamic ablation morphology measurement of thermal protection materials using structured light vision

Installation effects on propeller tone noise

Related Author

No data

Related Institution

No data

AI问答

⁰