Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body

Yan Hao; Chen Qi; Wang Xinguang; An Xiaomin; Qiao Chenliang

doi:10.7638/kqdlxxb-2025.0012

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body

更新时间：2026-05-28

- Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body
- Vol. 44, Issue 4, Pages: 88-99(2026)
- 作者机构：
  
  1. 西北工业大学航天学院,西安,710072
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0012
  CLC： V212
- Published：2026
- 稿件说明：
移动端阅览
闫浩, 陈琦, 王新光, 等. 类HyTRV升力体阻尼/交叉动导数特性分析[J]. 空气动力学学报, 2026, 44(4): 88−99.

Yan Hao, Chen Qi, Wang Xinguang, et al. Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body[J]. 2026, 44(4): 88-99.
闫浩, 陈琦, 王新光, 等. 类HyTRV升力体阻尼/交叉动导数特性分析[J]. 空气动力学学报, 2026, 44(4): 88−99. DOI： 10.7638/kqdlxxb-2025.0012

Yan Hao, Chen Qi, Wang Xinguang, et al. Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body[J]. 2026, 44(4): 88-99. DOI： 10.7638/kqdlxxb-2025.0012.

摘要

动导数是构建气动力模型的基本参数，也是评估飞行器动态特性品质的重要指标。受气动布局和非定常气动特性等因素的影响，超高速升力体飞行器各通道耦合效应突出，表征横航向之间耦合效应的交叉动导数显著增大。本文基于国家数值风洞高速模拟软件NNW-HyFLOW，采用强迫振荡法开展了动导数的计算和辨识。首先，针对OV-102航天飞机标模进行了方法验证；然后，针对高速转捩研究飞行器（high-speed transition research vehicle

HyTRV）的相似模型开展阻尼/交叉动导数的辨识，分析了攻角和马赫数等参数对动导数的影响规律。结果表明，类HyTRV升力体的横向和航向之间耦合效应突出，在攻角大于2°、马赫数小于5时，偏航-滚转力矩交叉导数甚至会超过滚转力矩阻尼导数。随着攻角的增大，俯仰静稳定性逐渐减弱，动稳定性先小幅降低，在平衡攻角处最弱，而后显著增强；偏航静、动稳定性均减弱，而滚转静、动稳定性均增强。随着马赫数的增大，俯仰、偏航和滚转方向的静稳定性增强，而阻尼、交叉动导数均逐渐减小，动稳定性减弱。本文研究可为面对称高速飞行器的动态稳定性评估与气动建模提供理论依据与数据支撑。

Abstract

Dynamic derivatives are fundamental parameters for aerodynamic modeling and crucial for assessing vehicle dynamic characteristics. For hypersonic lifting-body vehicles

aerodynamic coupling among pitch

yaw

and roll directions is significant due to aerodynamic layout and unsteady aerodynamic effects

leading to marked increases in cross dynamic derivatives that characterize yaw-roll coupling. In this paper

the forced oscillation method was employed to calculate and identify the dynamic derivatives based on the National Numerical Windtunnel hypersonic software

named NNW-HyFLOW. First

the method is validated using the OV-102 space shuttle standard model. Then

the effects of parameters (e.g.

angle of attack and Mach number) on dynamic derivatives were analyzed. Results indicate significant yaw-roll aerodynamic coupling in the quasi-HyTRV (high-speed transition research vehicle) lifting body. The results show that the aerodynamic coupling effect between the yaw and roll directions of the quasi-HyTRV lifting-body is significant. The rolling-moment derivative due to yaw rate exceeds the roll damping derivative when the angle of attack is greater than 2° or the Mach number is less than 5. As the angle of attack increases

the pitching static stability decreases

while the dynamic stability first slightly drops to a minimum at the equilibrium angle of attack then increases significantly. The yaw static and dynamic stability both decrease

while the roll static and dynamic stability enhance simultaneously. With increasing Mach number

the static stability in the pitch

yaw

and roll directions improves

while the damping and cross-dynamic derivatives gradually decrease

and the dynamic stability declines. This study can provide a theoretical basis and data support for the dynamic stability assessment and aerodynamic modeling of lateral-symmetric hypersonic vehicles.

关键词

Keywords

references

Li Yixiang. Research on the development history of US hypersonic aircrafts[D]. Harbin: Harbin Institute of Technology, 2016(in Chinese).

LI Qian, ZHAO Zhongliang, WANG Xiaobing, et al. Rolling stability research of a near space hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(03): 6−13(in Chinese). doi: 10.1080/08929882.2015.1088734

Liu Xu, Liu Wei, Chai Zhenxia, et al. Research progress of numerical method of dynamic stability derivatives of aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8): 2348−2369(in Chinese). doi: 10.7527/S1000-6893.2016.0098

Mi B G, Zhan H. Review of numerical simulations on aircraft dynamic stability derivatives[J]. Archives of Computational Methods in Engineering, 2020, 27(5): 1515−1544. doi: 10.1007/s11831-019-09370-8

Xu Min, An Xiaomin. Analysis and calculation method of aerodynamic characteristics of aircraft[M]. Xi'an: Northwestern Polytechnical University Press, 2012: 180-183(in Chinese).

Yuan Xianxu, Chen Qi, Xie Yufei, et al. Problems in numerical prediction of dynamic stability derivatives[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8): 2385−2394(in Chinese). doi: 10.7527/S1000-6893.2016.0180

An Fuxing, Li Lei, Su Wei, et al. Key issues in hypersonic vehicle aerodynamic design[J]. Scientia Sinica Physica, Mechanica Astronomica, 2021, 51(10): 2−21(in Chinese). doi: 10.1360/SSPMA-2021-0135

Li Qian, Zhao Zhongliang, Wang Xiaobing, et al. Rolling stability research of a near space hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(3): 1−8(in Chinese). doi: 10.7527/S1000-6893.2017.xxxx

He Zhidai. Sensitivity of aircraft stability to cross-coupling derivatives and angular accelaration derivatives at high angles of attack[J]. Acta Aerodynamica Sinica, 1987, 5(4): 334−344(in Chinese).

Liu Xu, Zhao Yunfei, Wang Dongfang, et al. Dynamic characteristics of hypersonic integrative vehicle with internal and external flow[J]. Journal of Ballistics, 2013, 25(3): 38−43(in Chinese). doi: 10.3969/j.issn.1004-499X.2013.03.008

Coulter S, Marquart E. Cross and cross-coupling derivative measurements on the standard dynamics model at AEDC[C]//Proc of the 12th Aerodynamic Testing Conference, Williamsburg, VA, USA. AIAA, 1982: AIAA1982-596. doi: 10.2514/6.1982-596

Mi B G. Simulation on the dynamic stability derivatives of battle-structure-damaged aircrafts[J]. Defence Technology, 2021, 17(3): 987−1001. doi: 10.1016/j.dt.2020.06.005

Langham T. Aircraft motion sensitivity to dynamic stability derivatives[C]//Proc of the 5th Atmospheric Flight Mechanics Conference for Future Space Systems, Boulder, CO, USA. AIAA, 1979: AIAA 1979-1621. doi: 10.2514/6.1979-1621

Chen Qi. Numerical study of maneuvering flight of vehicle coupling aerodynamics and control[D]. Mianyang: China Aerodynamics Research and Development Center, 2016(in Chinese).

Li Peng, Chen Jianqiang, Ding Mingsong, et al. Framework design of NNW-HyFLOW hypersonic flow simulation software[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 625718(in Chinese).

Wang X G, Yan H, He K, et al. Calculation of dynamic derivatives for high-speed vehicles based on the national numerical windtunnel software[J]. Journal of Physics: Conference Series, 2023, 2610(1): 012017. doi: 10.1088/1742-6596/2610/1/012017

Chen Q, Yuan X X, Wang X G, et al. Numerical study of saddle-node bifurcation for longitudinal flight with CFD/RBD technique[J]. Journal of Computational Science, 2018, 29: 153−162. doi: 10.1016/j.jocs.2018.10.006

Chen Q, Chen J Q, Xie Y F, et al. Study and application of virtual flight simulation for rolling control of vehicles[J]. Journal of Computational Science, 2017, 21: 77−85. doi: 10.1016/j.jocs.2017.05.009

Bykerk T, Verstraete D, Steelant J. Low speed longitudinal dynamic stability analysis of a hypersonic waverider using unsteady Reynolds averaged Navier Stokes forced oscillation simulations[J]. Aerospace Science and Technology, 2020, 103: 105883. doi: 10.1016/j.ast.2020.105883

肖中云, 周铸, 牟斌, 等. 用于飞行器动稳定性导数试验的减缩频率估算方法: CN118194774B[P]. 2024-07-23.

Mi Baigang. Calculating dynamic derivative and modeling nonlinear unsteady aerodynamics based on CFD[D]. Xi'an: Northwestern Polytechnical University, 2018(in Chinese).

Jr Freeman D C, Boyden R P, Davenport E E. Supersonic dynamic stability characteristics of a space shuttle orbiter: NASA-TN-D-8043[R]. NASA, 1976.

Granata D, Savino A, Zanotti A. Numerical evaluation of aircraft aerodynamic static and dynamic stability derivatives by a mid-fidelity approach[J]. Aerospace, 2024, 11(3): 213. doi: 10.3390/aerospace11030213

Li L, Zhang D, Zhang Z Q, et al. Quasi-steady numerical calculation method for individual dynamic derivatives of aircraft[J]. Journal of Physics: Conference Series, 2025, 2955(1): 012028. doi: 10.1088/1742-6596/2955/1/012028

Chen Jianqiang, Tu Guohua, Wan Bingbing, et al. Characteristics of flow field and boundary-layer stability of HyTRV[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 124317(in Chinese). doi: 10.7527/S1000-6893.2020.24317

Liu S S, Yuan X X, Liu Z Y, et al. Design and transition characteristics of a standard model for hypersonic boundary layer transition research[J]. Acta Mechanica Sinica, 2021, 37(11): 1637−1647. doi: 10.1007/s10409-021-01136-5

Qi H, Li X L, Yu C P, et al. Direct numerical simulation of hypersonic boundary layer transition over a lifting-body model HyTRV[J]. Advances in Aerodynamics, 2021, 3(1): 31. doi: 10.1186/s42774-021-00082-x

Yuan Xianxu, Zhang Hanxin, Xie Yufei. The pitching static/dynamic derivatives computation based on CFD methods[J]. Acta Aerodynamica Sinica, 2005, 23(4): 458−463(in Chinese). doi: 10.3969/j.issn.0258-1825.2005.04.012

Li Xinguo, Fang Qun. Flight dynamics of winged missile[M]. Xi’an: Northwestern Polytechnical University Press, 2005: 161-162(in Chinese).

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Hybrid TV-van Leer upwind scheme on unstructured grids

Study on the dynamic characteristics of MSL ballistic range test configuration

Research progress on noise reduction of centrifugal fans

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

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

Related Author

ZHANG Fan

ZHANG Lidan

LIU Jun

CHEN Biaosong

BI Lin

YUAN Xianxu

WU Bojiao

CHEN Hao

Related Institution

State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology

State Key Laboratory of Aerodynamics

Computational Aerodynamics Institute of China Aerodynamics Research and Development Center

AI问答

⁰