Experimental Thermal Response and Demisability Investigations on five Aerospace Structure Materials under Simulated Destructive Re-Entry Conditions

Pagan, Adam S.; Massuti-Ballester, Bartomeu; Herdrich, Georg

doi:10.2514/6.2016-4154

Cited by 5 publications

(2 citation statements)

References 6 publications

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“…A further field of research which is conducted using the PWK1 facility is the investigation of space debris and demisable materials [43,44]. An advantage here is the ability to simulate the upper Earth atmosphere where the destructive re-entry processes start.…”

Section: Pwk1mentioning

confidence: 99%

Assessment of high enthalpy flow conditions for re-entry aerothermodynamics in the plasma wind tunnel facilities at IRS

Loehle¹,

Zander

Eberhart³

et al. 2021

CEAS Space J

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This article presents the full operational experimental capabilities of the plasma wind tunnel facilities at the Institute of Space Systems at the University of Stuttgart. The simulation of the aerothermodynamic environment experienced by vehicles entering the atmosphere of Earth is attempted using three different facilities. Utilizing the three different facilities, the recent improvements enable a unique range of flow conditions in relation to other known facilities. Recent performance optimisations are highlighted in this article. Based on the experimental conditions demonstrated a corresponding flight scenario is derived using a ground-to-flight extrapolation approach based on local mass-specific enthalpy, total pressure and boundary layer edge velocity gradient. This shows that the three facilities cover the challenging parts of the aerothermodynamics along the entry trajectory from Low Earth Orbit. Furthermore, the more challenging conditions arising during interplanetary return at altitudes above 70 km are as well covered.

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Section: Pwk1mentioning

confidence: 99%

Assessment of high enthalpy flow conditions for re-entry aerothermodynamics in the plasma wind tunnel facilities at IRS

Loehle¹,

Zander

Eberhart³

et al. 2021

CEAS Space J

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“…У роботах [1,2] ці проблеми розглядаються з позиції необхідності спалювання елементів космічного сміття в атмосфері Землі внаслідок аеродинамічного нагрівання і різного роду конструкційних рішень [3]. Термічна деградація різних конструкційних матеріалів внаслідок аеродинамічного нагрівання розглядається в роботах [4,5].…”

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Моделювання Процесів Аеродинамічного Нагріву І Плавлення Космічних Об’єктів В Атмосфері Землі

Дреус¹,

Дронь²,

Губін³

et al. 2022

sdaatc

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The results of modeling the processes of thermal destruction of large-sized space debris objects due to aerodynamic heating and melting in the upper atmosphere are presented in order to determine the feasibility of using a combined method for their de-orbiting. The cylindrical and spherical models of space debris elements were considered to estimation of the parameters of thermal destruction. The guess, that melt layer which is formed on an object surface, is carried away by a running atmospheric flow, was assumed. The value of heat flux depends on the location on the body surface, thus, two cases were considered: stagnation point, where the heat flux is maximum, and the point on a flat surface. It is shown that the efficiency of destruction of cylindrical bodies (first stages of launch vehicles) depends on the angle of attack during object movement in the atmosphere. The most advantageous, to provide the maximum thermal load, are the angles of attack not less than 40°. At small angles of attack, the thermal load on the side surface is insignificant, which can lead to incomplete destruction of the object. Calculations also showed effective combustion of objects spherical shape (fuel tanks of upper stages in the atmosphere. The presented trajectories of deorbiting of space debris objects confirm the effectiveness of thermal destruction for reentry angles: 0°; 0,5°; 1,0°; 1,5°. At the same time, the melting rate increases when reentry angle is increasing. Complete thermal destruction (melting) of the discharge objects is possible for the structural material from aluminum alloys, in particular АМг6. This case takes place in aerospace design practice. Thus, the use of a combined method of deorbiting the large-sized space debris into the dense layers of the Earth's atmosphere is quite appropriate, because it provides the productive aerodynamic heating and thermal destruction in the atmosphere some objects like as used first stages of launch vehicles or fuel tanks, which are the most typical components of space debris

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The Plasma Wind Tunnels at the Institute of Space Systems: Current Status and Challenges

Löhle

Fasoulas

Herdrich

et al. 2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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Experimental Thermal Response and Demisability Investigations on five Aerospace Structure Materials under Simulated Destructive Re-Entry Conditions

Cited by 5 publications

References 6 publications

Assessment of high enthalpy flow conditions for re-entry aerothermodynamics in the plasma wind tunnel facilities at IRS

Assessment of high enthalpy flow conditions for re-entry aerothermodynamics in the plasma wind tunnel facilities at IRS

Моделювання Процесів Аеродинамічного Нагріву І Плавлення Космічних Об’єктів В Атмосфері Землі

The Plasma Wind Tunnels at the Institute of Space Systems: Current Status and Challenges

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