Modeling of aerodynamic heat flux and thermoelastic behavior of nose caps of hypersonic vehicles

Persova, Marina G.; Soloveichik, Yuri G.; Belov, V. K.; Kiselev, Dmitry S.; Vagin, Denis V.; Domnikov, Petr A.; Patrushev, Ilya I.; Kurskiy, Denis N.

doi:10.1016/j.actaastro.2017.02.021

Cited by 41 publications

(8 citation statements)

References 20 publications

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“…The wind tunnel testing technology is the most effective and reliable way of obtaining the aerodynamic characteristics of aircrafts [28,29], spacecrafts [30], missiles, parachutes and so on. During the experiments, the total pressure and the temperature were kept at 110KPa and 287K, respectively.…”

Section: Resultsmentioning

confidence: 99%

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Dong¹,

Yang²,

Yu³

et al. 2018

dtcse

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An experimental study is conducted to characterize the aerodynamic performances of two parachutes in the Mars probe decelerator system and the experiments are carried out in the 2.4 m×2.4 m transonic wind tunnel. The lift, drag and pitch moment coefficients versus the angle of attack from 0 to 25 degrees at Mach 0.4 and 0.8 are accurately measured and carefully analyzed. A novel mathematical model is proposed to express the aerodynamic characteristics of the parachutes. The obtained results show that the drag coefficient of the parachutes varies in a small range of 0.525~0.575 at Mach 0.4 and 0.8 as the angle of attack increases from 0 to 25 degrees. The simulated results of the propose model have a well agreement with the wind tunnel experimental data. The investigations in the present paper have a good significant to the engineering development of the parachutes in Mars probe decelerator system.

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Section: Resultsmentioning

confidence: 99%

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Dong¹,

Yang²,

Yu³

et al. 2018

dtcse

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“…Many efforts have been made to improve the understanding of the multiphysical coupling of a hypersonic vehicle. In References [7,8], the coupling model of the nose cap and hypersonic flow was established, and the effect of an attack angle on the nose cap response was analyzed. The ablation was predicted by using the moving mesh algorithm.…”

Section: Introductionmentioning

confidence: 99%

Thermo-Structural Behaviour Prediction of the Nose Cap of a Hypersonic Vehicle Based on Multifield Coupling

Sun

Yang

2020

International Journal of Aerospace Engineering

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The analysis of thermo-structural behaviour is crucial to the nose cap of a hypersonic vehicle under aerothermodynamic loads. Considering chemical nonequilibrium of the flow field, heat transfer, and deformation of the structure, a fluid-thermal-structural coupling model of the typical nose cap was established. The coupling relation between the flow field and nose cap was analyzed. The results show that the fluid-thermal-structural model can effectively predict the response of the nose cap under a hypersonic environment. The highest temperature and the peak of maximum principal stress appear at the front of the nose cap at an initial stage. As time goes on, the highest temperature increases gradually and the peak of maximum principal stress decreases after reaching a certain value. The position of the peak of maximum principal stress gradually moves to the inside of the nose cap and eventually stabilizes. With the increase in the Mach number, the highest temperature and the peak of maximum principal stress of the nose cap increase. The fluid-thermal-structural coupling model can provide guidance for the optimal design of the nose cap of a hypersonic vehicle.

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“…Unfortunately, researchers have mainly focused on the transient aerodynamic heating of vehicle in some specific flight states [27][28][29]. However, aeroheating characteristics on the surface of vehicles are not only determined by the current flight state but also related closely to the heat transfer environment during the flight, which is a progressive, lasting, and dynamic process [30]. Therefore, the results of the transient thermal analysis were inevitably deviated from a practical situation, which cannot be used for real-time tracking and monitoring of the IR detecting system [31].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Aerothermal Analysis of a Cone-Cylinder Flight Body

Zhang

Jia

Mkumbuzi

et al. 2020

International Journal of Aerospace Engineering

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Exploring the aerothermal characteristic of a flight body has great military applications in tracking, locating, thermal protection, and infrared stealth technologies. Available studies are mostly focused on the transient aerothermal characteristics of vehicles in some specific flight datum, which are not able to satisfy the requirements in real-time tracking for an infrared system. This paper probes into a method of dynamic thermal analysis of a cone-cylinder flight body with a high spinning speed. Firstly, a theoretical model for analyzing the dynamic aerothermal characteristics is established using the thermal node-network method. Then, trajectory datum and the convective heat-transfer coefficients are solved simultaneously. Besides, the trajectory datum in supersonic, transonic, and subsonic regimes is separately defined as the boundary conditions, and fluid-thermal analysis methods are implemented by a combination of sliding mesh and multicoordinate approaches. Finally, the flow characteristics are analyzed and compared with disregarding the rotational speed. The results demonstrate that there are significant differences between the two cases, especially at the high-speed regimes. This study further confirms that it is essential to conduct the aerothermal analysis from a dynamic point of view, and taking the impacts of coupling motion into account is also of vital importance.

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Modeling of aerodynamic heat flux and thermoelastic behavior of nose caps of hypersonic vehicles

Cited by 41 publications

References 20 publications

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Thermo-Structural Behaviour Prediction of the Nose Cap of a Hypersonic Vehicle Based on Multifield Coupling

Dynamic Aerothermal Analysis of a Cone-Cylinder Flight Body

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