ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT Nazlıcan KARACA Department of Aerospace Engineering Thesis Advisor: Yrd. Doç. Dr. Melike NİKBAY May 2018 1
ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT Nazlıcan KARACA 110120309 Department of Aerospace Engineering Thesis Advisor: Yrd. Doç. Dr. Melike NİKBAY JUNE 2018
Nazlıcan KARACA, student of ITU Faculty of Aeronautics and Astronautics student ID 110120309, successfully defended the graduation entitled MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY, which he prepared after fulfilling the requirements specified in the associated legislations, before the jury whose signatures are below. Thesis Advisor : Yrd. Doç. Dr. Melike NİKBAY... Istanbul Technical University Jury Members : Prof.Dr. A. Rüstem ASLAN... Istanbul Technical University Dr.Öğr.Üye. K. Bülent YÜCEİL... Istanbul Technical University Date of Submission : 28 May 2018 Date of Defense : 12 June 2018
FOREWORD With the exponential improvements on technology, every part of the spacecrafts and rockets are aim to be re-used, for both financial reasons and convenience. This aim makes the analysis of re-entry vehicles highly important and crucial for the future of the space industry. On this paper, I am investigating and re-simulating the project, SMAAC (Sounding Rocket Experiment of Membrane Aeroshell for Atmospheric- Entry Capsule). June 2018 Nazlıcan KARACA
TABLE OF CONTENTS Page FOREWORD... 7 TABLE OF CONTENTS... 8 SYMBOLS... 11 LIST OF FIGURES... 12 SUMMARY... 13 1 INTRODUCTION... 14 1.1 Purpose of thesis... 14
ABBREVIATIONS ATM B CONV SOLAR T : Atmosphere : Background : Convection : Solar : Turbulent : Freestream
SYMBOLS
LIST OF FIGURES Page Figure 1.1. Photographs of the SMAAC[1]... Hata! Yer işareti tanımlanmamış. Figure 1.2. MAAC configuration and mounting positions of thermocouples (all dimensions are in millimeters). [1]... 2
MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY SUMMARY A SMAAC (Sounding Rocket Experiment of Membrane Aeroshell for Atmospheric-Entry Capsule) project is investigated and re-simulated in this paper. Simulation and real trial values have been compared. The tested values have been obtained from the Takahashi,2015 paper [1]. Test values have obtained by a demonstartion flight of an advanced reentry vehicle which was carried out by a Japan Aerospace Exploration Agency S-310-41 sounding rocket. The reason for researches of inflatable and flexible aeroshell is its low ballistic coefficient which results on the reduction in aerodynamic heating and deceleration at high altitude. Measurements of temperatures were taken both from the backside of the flexible aeroshell and inside of the capsule by thermocouples at a good many of times during its flight back into atmosphere. The results from those measurements investigated and a thermal history has been constituted. Also a numerical prediction in which a flow field simulation which consisted of both laminar and turbulent flow and deformation of the flexible aeroshell considered, of the heating was conducted and the results from these have been combined. With the knowledge from these steps a thermal module composed.
1 INTRODUCTION 1.1 Purpose of thesis Inflatable aeroshels have a high importance among the space industry. National Aeronautics and Space Administration (NASA), the European Space Agency (ESA), and the Japan Aerospace Exploration Agency (JAXA) are working to improve this project. Figure 1 Photographs of the SMAAC Figure 1 shows a photograph of the SMAAC before the flight experiment. In the demonstration flight, the reentry vehicle (a capsule with an inflatable aeroshell) was separated from the rocket at an altitude of 111 km and started to re-enter from an altitude of about 150 km. The vehicle achieved a maximum velocity of 1320 m s,mach number of 4.5, and dynamic pressure of 500 Pa according to [2].
Figure 2 MAAC configuration and mounting positions of thermocouples (all dimensions are in millimeters).
2 CONCLUSION
REFERENCES [1] Takahashi,2015, Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight [2] Yamada,K.,Nagata,Y., Abe,T.,Suzuki,K.,Imamura,O.,andAkita,D., Suborbital Reentry Demonstration of Inflatable Flare-Type Thin- Membrane Aeroshell Using a Sounding Rocket, Journal of Spacecraftand Rockets,Vol. 52, No. 1, 2015, pp. 275 284.doi:10.2514/1.A32807