Add to ORKGThe use of high strength and modulus of advanced filamentary composites to reduce the structural weight of aerospace vehicles was investigated. Application of the technology to space shuttle components was the primary consideration. The mechanical properties for the boron/epoxy, graphite/epoxy, and polyimide data are presented. Structural testing of two compression panel components was conducted in a simulated space shuttle thermal environment. Results of the tests are analyzed
Two manufacturing demonstration panels (1/16th-arc-segments of 10 m diameter cylinder) were fabricat...
Based on estimated graphite and boron fiber properties, allowable stresses and strains were establis...
A cylindrical shell structure 3.66 m (144 in.) high by 4.57 m (180 in.) diameter was designed using ...
The development of metal structures reinforced with filamentary composites as a weight saving featur...
The autoclave based THERM-X(sub R) process was evaluated by cocuring complex curved panels with fram...
A summary is given of the in-house and contract work accomplished under the CASTS Project. In July 1...
Design studies involving weight and cost were carried out for several structural concepts applicable...
Analytical and experimental investigations, performed to establish the feasibility of reinforcing me...
An advanced composite shear web design concept was developed for the Space Shuttle orbiter main engi...
Refurbishable composite thermostructural heat shield panels for manned lifting entry vehicle
Information on materials and structures for use in space is given in viewgraph form. Information is ...
The weight savings potential, of graphite-epoxy composites for secondary and medium primary aircraft...
The use of filamentary composite materials in the design and construction of primary aircraft struct...
The results of an evaluation of candidate metal-matrix composite materials for shuttle space radiato...
Composite materials tests for expandable manned space structures including flammability, micrometeor...
Two manufacturing demonstration panels (1/16th-arc-segments of 10 m diameter cylinder) were fabricat...
Based on estimated graphite and boron fiber properties, allowable stresses and strains were establis...
A cylindrical shell structure 3.66 m (144 in.) high by 4.57 m (180 in.) diameter was designed using ...
The development of metal structures reinforced with filamentary composites as a weight saving featur...
The autoclave based THERM-X(sub R) process was evaluated by cocuring complex curved panels with fram...
A summary is given of the in-house and contract work accomplished under the CASTS Project. In July 1...
Design studies involving weight and cost were carried out for several structural concepts applicable...
Analytical and experimental investigations, performed to establish the feasibility of reinforcing me...
An advanced composite shear web design concept was developed for the Space Shuttle orbiter main engi...
Refurbishable composite thermostructural heat shield panels for manned lifting entry vehicle
Information on materials and structures for use in space is given in viewgraph form. Information is ...
The weight savings potential, of graphite-epoxy composites for secondary and medium primary aircraft...
The use of filamentary composite materials in the design and construction of primary aircraft struct...
The results of an evaluation of candidate metal-matrix composite materials for shuttle space radiato...
Composite materials tests for expandable manned space structures including flammability, micrometeor...
Two manufacturing demonstration panels (1/16th-arc-segments of 10 m diameter cylinder) were fabricat...
Based on estimated graphite and boron fiber properties, allowable stresses and strains were establis...
A cylindrical shell structure 3.66 m (144 in.) high by 4.57 m (180 in.) diameter was designed using ...