KINETIC PROPERTY OF A PRESSURE VESSEL MADE FROM CFRP FABRICATED A FILAMENT WINDING METHOD
DOI:
https://doi.org/10.29121/granthaalayah.v6.i3.2018.1507Keywords:
Micro Satellite, Filament Winding, CFRP, Fuel TankAbstract [English]
Since the specific strength and the specific elasticity of carbon fiber reinforced plastics (CFRPs) are the greatest in practical materials, they are used abundantly in transport structures. This CFRP can also be used for a pressure vessel which stores liquid hydrazine, the required burst pressure is approximately 22MPa. Many researchers have been studying pressure vessels made from a CFRP fabricated by a filament winding (FW) method.
In order to acquire the fundamental mechanical properties of a CFRP container, the small cylinder made from CFRP fabricated by the spiral winding type FW method is designed and manufactured. The winding angle of a carbon fiber of this cylinder is ±45 degrees. The plastic deformation of this cylinder generates from the strain range of 0.7%. So as to confirm by the analytical method that a small tank made from CFRP fabricated by the FW method can be utilized as a tank for liquid hydrazine, an analysis model is created. Since the pressure to which the strain of this CFRP tank reaches to 0.7% is approximately 35MPa, this small tank can be used as a fuel tank for micro satellites.
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Paul S. Griffin, Ian A. Ballinger, Donald E. Jaekle Jr. and Arthur C. Jackson III, DESIGN AND MANUFACTURE OF A LIGHTWEIGHT FUEL TANK ASSEMBLY, AIAA-2003-4606, 39th AIAA PROPULSION CONFERENCE, 21 July 2003, Alabama (USA). DOI: https://doi.org/10.2514/6.2003-4606
Walter Tam, Mike Hersh, and Ian Ballinger, HYBRID PROPELLANT TANKS FOR SPACECRAFT AND LAUNCH VEHICLES, AIAA-2003-4607, 39th AIAA PROPULSION CONFERENCE, 21 July 2003, Alabama (USA).
N Walter H. Tam, Michael J. Debreceni, Michael S. Hersh and Charles D. Nye, LOW COST DERIVATIVE TANKS FOR SPACECRAFT AND LAUNCH VEHICLES, 35th AIAA/ASME/SAE/ASEE JOINT PROPULSION CONFERENCE, 20-24 July 1999, California (USA).
M S. Okamoto1, M. Yamamoto, K. Hosokawa, M. Nakano and K. Hanaoka, MECHANICAL PROPERTIES OF CFRP PRESSURE VESSELS AND IDENTIFICATION OF EQUIVALENT ELASTIC MODULI OF CFRPS, WIT Transactions on The Built Environment, Vol 97 (2008), pp. 471-480.
M. Uemura, K. Yamawaki, S. Abe and H. Iyama, ABOUT THE RIGIDITY OF A FILAMENT WINDING MATERIAL, BULLETIN OF THE INSTITUTE OF SPACE AND AERONAUTICAL SCIENCE, University of Tokyo, Vol.4, No.3(B)(1968), pp. 448-463 (in Japanese).
Stephen W Tsai, STRUCTURAL BEHAVIOR OF COMPOSITE MATERIALS, National Aeronautics and Space Administration contractor report NASA CR-71 (1964), Washington (USA).
Zvi Hashin and B. Walter Rosen, THE ELASTIC MODULI OF FIBER-REINFORCED MATERIALS, Journal of Applied Mechanics, Vol. 31, Issue 2 (1964), pp. 223-232.
Jae-Sung Park, Cheol-Ung Kim, Hyun-Kyu Kang, Chang-Sun Hong and Chun-Gon Kim, STRUCTURAL ANALYSIS AND STRAIN MONITORING OF THE FILAMENT WOUND MOTOR CASE, Journal of Composite Materials, Vol. 36, No. 20 (2002), pp. 2373-2388.
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