Filament Wound Kevlar 49/Epoxy Rocket Motor Cases

1979 ◽  
Vol 1 (3) ◽  
pp. 7
Author(s):  
TT Chiao ◽  
PL Lien ◽  
RJ Morgan ◽  
KL Reifsnider ◽  
RR Heitkamp ◽  
...  
Keyword(s):  
Rocket Motor ◽  
Filament Wound

Infrared Nondestructive Testing of Glass Filament-Wound Rocket Motor Cases

2009 ◽  
pp. 105-105-10
Author(s):  
Frederick E. Alzofon ◽  
Lester E. Florant ◽  
Richard K. Ronald ◽  
Marvin J. Vann ◽  
Julian E. FItzgerald
Keyword(s):  
Nondestructive Testing ◽  
Rocket Motor ◽  
Filament Wound ◽  
Glass Filament

Using potential of filament-wound carbon/glass polymeric composites as rocket motor thermal insulation

2021 ◽  
Vol 29 (9_suppl) ◽  
pp. S1541-S1554
Author(s):  
Jelena Rusmirović ◽  
Jela Galović ◽  
Marija Kluz ◽  
Srdja Perković ◽  
Saša Brzić ◽  
...  
Keyword(s):  
Thermal Insulation ◽  
Glass Fibers ◽  
Polymeric Composites ◽  
Peak Height ◽  
Mechanical Analysis ◽  
Rocket Motor ◽  
Filament Winding ◽  
Woven Fabric ◽  
Filament Wound ◽  
Interlaminar Shear

The study aim is to develop hybrid filament-wound polymeric composites based on flame retardant polyester resin (UPe) and multi-layer structured glass or combined carbon and glass fibers for use as ablative thermal insulation of rocket motor by wet filament winding technique. The composites have a multi-layered structure consisting of two layers of carbon (CF) or glass woven fabric (GF) and one layer of carbon or glass direct roving (CR or GR, respectively), repeated in three cycles. Structural analysis, performed using FTIR spectroscopy and dynamical-mechanical analysis, confirm highly polymerized network. Lower values of the tanδ peak height indicate improved interfacial adhesion between carbon/glass fibers and UPe. The improvements of thermal insulation index of 37% and erosion rate of 38.6% at 180°C are achieved for combined carbon/glass fiber–based composite compared to the neat UPe. Tensile and interlaminar shear properties are investigated according to the fiber orientation and the highest values of tensile and interlaminar shear strengths are obtained for composites with longitudinal orientation, 417.48 MPa and 22.30 MPa, respectively. Compared to the neat UPe, which degrades after 50 s at 3000°C, the composites are stable up to 192 s.

Design and Validation of a Filament Wound Composite Rocket Motor Case

2018 ◽  
Author(s):  
Emre Özaslan ◽  
Bülent Acar ◽  
Ali Yetgin
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Composite Structures ◽  
Rocket Motor ◽  
Fiber Direction ◽  
Element Analysis ◽  
Filament Wound ◽  
Filament Wound Composite ◽  
Winding Angle ◽  
Wound Composite

Filament wound composite structures are widely used in aerospace applications such as motor case of rockets owing to their high stiffness/weight ratio and high strength. However, design and analysis of a filament wound structure is so complex due to the anisotropic nature of the composite material. Variation of the winding angle through the rocket motor case axis and through the thickness, which is also a function of winding angle are the main challenges to the realistic modeling of a filament wound composite rocket motor case. In this study, finite element analysis of a filament wound rocket motor case with unequal dome openings was performed. The finite element model was compared with manufactured motor case in terms of winding angle and thickness to ensure the exact modeling. The finite element analysis was compared with burst tests in terms of fiber direction strain distribution through the outer surface of the motor case to verify analysis. The weak regions of the motor case were determined with finite element analysis to be transition region from cylinder to dome which is subjected to significant bending because of the stiffness difference between these regions. Then, some design improvements were proposed to increase the mechanic performance of motor case. Significant improvement was succeeded in terms of mechanic performance. Important aspects of designing and analyzing a filament wound composite rocket motor case were addressed for designers.

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