类HyTRV升力体阻尼/交叉动导数特性分析

闫浩; 陈琦; 王新光; 安效民; 乔晨亮

doi:10.7638/kqdlxxb-2025.0012

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类HyTRV升力体阻尼/交叉动导数特性分析

研究论文 | 更新时间：2026-05-28

- 类HyTRV升力体阻尼/交叉动导数特性分析
- Analysis of damping and cross dynamic derivative characteristics for a quasi-HyTRV lifting body
- 空气动力学学报 2026年44卷第4期页码：88-99
- 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：
  
  闫浩（1999—），男，新疆博乐人，博士研究生，研究方向：动导数计算辨识与稳定性分析. E-mail：yanhao528@mail.nwpu.edu.cn
  王新光*，高级工程师，研究方向：空气动力学. E-mail：xinguangwang2014@126.com
- 基金信息：
  
  国家自然科学基金（12572198）;四川省科技计划杰出青年科技人才项目（2024NSFJQ0062）
- DOI：10.7638/kqdlxxb-2025.0012
  中图分类号： V212
- 纸质出版：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

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