Aerodynamics/propulsion coupled modeling and analysis of hypersonic vehicle within wide speed range

doi:10.3785/j.issn.1008-973X.2019.05.023

Journal of ZheJiang University (Engineering Science)

2019, Vol. 53

Issue (5): 1006-1018 DOI: 10.3785/j.issn.1008-973X.2019.05.023

Aerodynamics/propulsion coupled modeling and analysis of hypersonic vehicle within wide speed range

Feng CHENG1,2(

),Dong ZHANG1,2,*(

),Shuo TANG1,2

1. School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
2. Shaanxi Aerospace Flight Vehicle Design Key Laboratory, Xi’an 710072, China

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Abstract

The further investigation was required to meet the wide speed range model requirement of the airbreathing hypersonic vehicle in preliminary design phase. A wide speed range aerodynamic model for distributions of pressure and friction on the surface of vehicle, which was independent of the vehicle concept, was established based on the streamline tracing technique and the hypersonic aerodynamic theories. A wide speed range dual-mode scramjet model including boundary layer and transonic characteristics was established on the basis of quasi-one-dimensional flow theory. The errors between models and experiments less than 2% and 3% were achieved for the typical cases, respectively. The coupling/decoupling strategies of forebody/inlet and after body/nozzle forces were presented and a wide speed range aerodynamics/propulsion integrated coupling model and platform was built, based on the established models. An analysis of wide speed range aerodynamics/propulsion coupling characteristics of a typical airbreathing hypersonic vehicle was carried out, and severe nonlinear aerodynamics/propulsion coupling characteristics were observed for the integrated designed airbreathing hypersonic vehicle. The results of analysis agreed that the coupling model established could be used to evaluate the aerodynamics/propulsion coupling characteristics, qualitatively and quantitatively, under a satisfying accuracy requirement, and also helpful for the design, simulation and control research of airbreathing hypersonic vehicle.

Key words： hypersonic vehicle wide speed range aerodynamics/propulsion integration coupling model sensitivity analysis

Received: 21 May 2018 Published: 17 May 2019

CLC:	V 211
	V 236
	V 475

Corresponding Authors: Dong ZHANG E-mail: chengfengcool@mail.nwpu.edu.cn;zhangdong@nwpu.edu.cn

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Cite this article:

Feng CHENG,Dong ZHANG,Shuo TANG. Aerodynamics/propulsion coupled modeling and analysis of hypersonic vehicle within wide speed range. Journal of ZheJiang University (Engineering Science), 2019, 53(5): 1006-1018.

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http://www.zjujournals.com/eng/10.3785/j.issn.1008-973X.2019.05.023 OR http://www.zjujournals.com/eng/Y2019/V53/I5/1006

高超声速运载器宽速域气动/推进耦合建模与分析

为了满足吸气式高超声速运载器在初步设计阶段的宽速域模型需求，基于流线追踪和高超声速气动理论建立独立于构型的宽速域压力和摩擦力壁面分布气动模型；以准一维流理论为基础，建立包含边界层和跨声速特性的宽速域双模态超燃冲压发动机模型. 对于典型工况，2种模型的仿真结果与试验结果误差分别不大于2%、3%. 在所建立模型的基础上，提出前体/进气道和后体/尾喷管力系的解耦/耦合策略，建立气动和推进学科的宽速域一体化耦合模型及仿真平台.针对某吸气式高超声速运载器的分析发现一体化设计的吸气式高超声速运载器存在严重的非线性气动/推进强耦合，认为所建立的耦合模型在精度满足一定要求的条件下能够定量/定性地评估气动/推进的耦合效应，有助于吸气式高超声速运载器的构型设计、地面仿真和控制研究.

关键词： 高超声速运载器, 宽速域, 气动/推进一体化, 耦合建模, 灵敏度分析

Fig.1 Sketch of fluid along streamline

Fig.2 Sketch of boundary layer on plate

Fig.3 Framework of aerodynamic forces preliminary evaluation platform of hypersonic vehicle

Tab.1 Comparison of root mean square errors between AFPE and experimental results

Fig.4 Streamlines and contours computed by AFPE on HL-20

Fig.5 Sketch of fluid control volume

Tab.2 Experimental conditions for quasi-one-dimensional model validation

Tab.3 Comparison of root mean square errors between quasi-one-dimensional model and experimental results

Fig.6 Comparison between simulation and experimental results of quasi-one-dimensional model

Fig.7 Framework of wide range integrated coupling model of airbreathing hypersonic vehicle

Fig.8 Typical airbreathing hypersonic vehicle

Fig.9 Effects of Mach number and angle of attack on total pressure recovery coefficient and mass flow capture of inlet

Fig.10 Effects of Mach number, angle of attack and fuel equivalence ratio on propulsion of vehicle

Fig.11 Effects of Mach number, angle of attack, deflection angle of aileron and fuel equivalence ratio on lift coefficient of vehicle

Fig.12 Effects of Mach number, angle of attack, deflection angle of aileron and fuel equivalence ratio on pitch moment coefficient of vehicle


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