高速飞行器气动推进一体化性能参数化分析

陈镜帆; 范晓樯; 熊冰

doi:10.7638/kqdlxxb-2025.0029

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高速飞行器气动推进一体化性能参数化分析

研究论文 | 更新时间：2026-07-11

- 高速飞行器气动推进一体化性能参数化分析
- Parametric analysis of aerodynamic-propulsion integratedperformance for hypersonic vehicles
- 空气动力学学报 2026年44卷第6期页码：34-44
- 作者机构：
  
  国防科技大学高超声速技术实验室,长沙,410073
- 作者简介：
  
  陈镜帆，研究方向：内外流一体化设计. E-mail：chenjingfan97@foxmail.com
  范晓樯*，研究方向：内外流一体化设计. E-mail：xqfan@nudt.edu.cn
- 基金信息：
  
  国家自然科学基金面上项目（12102470）;国家自然科学基金青年科学基金项目（12372298）
- DOI：10.7638/kqdlxxb-2025.0029
  中图分类号： V211.73
- 纸质出版：2026
- 稿件说明：
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陈镜帆, 范晓樯, 熊冰. 高速飞行器气动推进一体化性能参数化分析[J]. 空气动力学学报, 2026, 44(6): 34−44.

Chen Jingfan, Fan Xiaoqiang, Xiong Bing. Parametric analysis of aerodynamic-propulsion integratedperformance for hypersonic vehicles[J]. 2026, 44(6): 34-44.
陈镜帆, 范晓樯, 熊冰. 高速飞行器气动推进一体化性能参数化分析[J]. 空气动力学学报, 2026, 44(6): 34−44. DOI： 10.7638/kqdlxxb-2025.0029

Chen Jingfan, Fan Xiaoqiang, Xiong Bing. Parametric analysis of aerodynamic-propulsion integratedperformance for hypersonic vehicles[J]. 2026, 44(6): 34-44. DOI： 10.7638/kqdlxxb-2025.0029.

摘要

为了参数化评估吸气式高速飞行器的气动推进一体化性能，进一步揭示飞行器总体参数对其性能的影响规律，本文构建了一种基于推阻平衡并充分考量升阻特性与发动机特性间耦合关系的一体化性能参数化计算方法。在该方法框架下，针对飞行器在恒定高度与速度下的巡航工况，深入探究了发动机性能以及气动性能等参数对飞行器一体化性能的影响。结果表明：对于典型飞行器构型，最优升阻比对应的攻角为8.1°，最大巡航比冲对应的攻角为6.7°；当飞行器的气动性能维持不变时，在一定范围内，安装具有更高基准比冲且比冲随当量比增大而减小的发动机，能够使飞行器展现出更优异的一体化性能；在发动机推力特性恒定的情况下，通过对气动外形进行优化调整，降低飞行器的零攻角升力系数、升力线斜率、零升阻力系数以及升致阻力系数，同时提高零攻角基准流量系数与流量系数变化率，亦可有效提升飞行器的一体化性能。本文研究有望为吸气式高速飞行器总体参数设计优化提供指导。

Abstract

To parametrically assess the aerodynamic-propulsion integrated performance of air-breathing hypersonic vehicles and comprehensively elucidate the influence rules of overall vehicle parameters on their performance

this paper proposes a parametric calculation method for integrated performance grounded in thrust-drag equilibrium. This method comprehensively considers the coupling between lift-drag characteristics and engine features

thereby providing a solid basis for subsequent research. Under this research framework

with a focus on the vehicle's cruising conditions at a constant altitude and speed

an in-depth exploration is made into the effects of overall parameters such as cruising angle of attack

engine performance

and aerodynamic performance on the vehicle's integrated performance. Research results reveal that

for typical vehicle configurations

the angle of attack corresponding to the optimal lift-drag ratio of 8.1° differs from that of 6.7° corresponding to the maximum cruising specific impulse. When the vehicle's aerodynamic performance remains constant

within a certain range

installing an engine with a higher baseline specific impulse and a specific impulse that decreases as the equivalence ratio increases can endow the vehicle with more excellent integrated performance. When the engine's thrust characteristics are invariant

through optimizing the aerodynamic shape to reduce the vehicle's zero-angle-of-attack lift coefficient

lift-curve slope

zero-lift drag coefficient

and lift-induced drag coefficient

while concurrently increasing the zero-angle-of-attack baseline flow coefficient and the flow-coefficient change rate

the vehicle's integrated performance can be effectively enhanced.Through the research presented in this paper

it is expected to provide guidance for the overall parameter design of air-breathing hypersonic vehicles.

关键词

Keywords

references

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