An aerodynamic configuration optimization method for reducing lateral aerodynamic nonlinearity of reentry vehicle

CHEN Gong; TANG Zhigong; DENG Chen; WANG Wenzheng

doi:10.7638/kqdlxxb-2020.0131

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An aerodynamic configuration optimization method for reducing lateral aerodynamic nonlinearity of reentry vehicle

更新时间：2026-05-28

- An aerodynamic configuration optimization method for reducing lateral aerodynamic nonlinearity of reentry vehicle
- Vol. 39, Issue 2, Pages: 33-38(2021)
- 作者机构：
  
  1. 国防科技大学空天科学学院,长沙,410073
  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-2020.0131
  CLC： V211.3;TP18
- Published：2021
- 稿件说明：
移动端阅览
陈功, 唐志共, 邓晨, 等. 一种减小再入飞行器侧向气动非线性的布局优化方法[J]. 空气动力学学报, 2021, 39(2): 33−38.

CHEN Gong, TANG Zhigong, DENG Chen, et al. An aerodynamic configuration optimization method for reducing lateral aerodynamic nonlinearity of reentry vehicle[J]. 2021, 39(2): 33-38.
陈功, 唐志共, 邓晨, 等. 一种减小再入飞行器侧向气动非线性的布局优化方法[J]. 空气动力学学报, 2021, 39(2): 33−38. DOI： 10.7638/kqdlxxb-2020.0131

CHEN Gong, TANG Zhigong, DENG Chen, et al. An aerodynamic configuration optimization method for reducing lateral aerodynamic nonlinearity of reentry vehicle[J]. 2021, 39(2): 33-38. DOI： 10.7638/kqdlxxb-2020.0131.

摘要

为改善升力式再入飞行器在跨声速段出现的侧向气动特性非线性问题，发展了一种基于Kriging代理模型的自适应迭代气动布局优化方法。设计了一种常规升力式再入飞行器布局，计算了该布局在跨声速段的侧向气动力，分析了可能影响侧向气动特性的机翼布局参数。根据气动布局优化流程，计算了气动布局样本气动特性，建立了布局参数到侧向力矩系数导数的代理模型，完成了以减小飞行器侧向非线性为目标的布局优化设计。优化布局的气动特性计算结果表明，所发展的方法是可行和有效的。该项研究为再入飞行器减小侧向气动非线性提供了新的布局设计途径，有利于降低控制系统设计难度，保障飞行安全。

Abstract

In order to reduce the lateral nonlinear aerodynamic characteristics of lifting reentry vehicles in the transonic regime

a new adaptive optimization method for the aerodynamic configuration has been developed in the present study based on the Kriging meta-model. To test this method

a standard lifting reentry vehicle is designed

which lateral aerodynamic force in the transonic regime is calculated using the computational fluid dynamics (CFD) tool

and those parameters for the wing configuration which may affect the lateral aerodynamic characteristic are analyzed. Based on the optimization process for the aerodynamic configuration

the lateral aerodynamic characteristics for the samples are first evaluated

then a meta-model is established to map the configuration parameters to the derivatives of the lateral moment

so that the optimization of the aerodynamic configuration with the objective of minimizing the nonlinearity of the lateral moment is achieved. Aerodynamic data of the optimized vehicle configuration suggests that the new design method is useful and effective. This work introduces a new way of designing aerodynamic configuration

which can reduce the difficulty in control system design as well as ensure flight safety for reentry vehicles.

关键词

Keywords

references

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