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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Joint permits smooth and easy movement of disabled arm and is smaller, lighter and less expensive than previous models. Device is interchangeable and may be used on either arm at the shoulder or at the elbow.
Proper installation techniques are described and reliable torque-tension values are presented on joint preload /or clamp load/ properties of structural threaded fasteners.
Thermal cycling effects on integrity of refractory stainless steel tubular coextruded joint
Design and development of flexible joint for pressure suits
Coextruded tantalum-316 stainless steel bimetallic joints and tubing
Fracture mechanics and time dependent strength of adhesive joints
Development of optimum fabrication techniques for brazed stainless steel transition joints
Design and development of module joint clamping device for application to solar array construction
Thermal shock testing of coextruded and brazed tubular joints of stainless steel and tantalum for SNAP-8 application
Universal joints for connecting two displaced shafts or members
Prediction of bolted joint heat transfer in spacecraft applications
Joint assessment and management evaluation system
Bimetallic refractory metal joints electron beam welding and aging for applications to in-pile thermionic converters
Fracture mechanics and time dependent strength of elastic or viscoelastic solids adhesively jointed by soft polymeric bonding layer
Stress distribution in plates and tubes bonded by stepped joints, assuming generalized plane stress
The contact of two rough, wavy surfaces; the contact of two rough but nominally flat plates pressed together over a concentrated area; and the contact of two rough but nominally flat plates bolted together are considered. In each case the pressure distribution is calculated as a function of the surface properties. In the case of wavy surfaces it is found that all necessary information for any combination of parameters can be reduced to one master graph. In the other two cases one such graph is needed for each geometry used. The resulting pressure distributions are used in a specific heat transfer example and the total joint resistance versus roughness is presented. A method for decreasing the resistance by increasing the roughness is shown.
This metallurgical program was specifically conducted for the establishment of material properties required for the design of the LF460 fan. The LF460 lift fan is an advanced 18:1 high thrust to weight single stage design. It has a turbine attached to the outer flowpath of the fan blade tip which minimizes the axial depth of the fan. Advanced lightweight attachment designs are employed in this concept to achieve minimum mass polar moments of inertia which are required for good aircraft flight response control. The design features which are unique to this advanced LF460 lift fan are the 0.010 inch thin Udimet 700 alloy integral tip turbine design, minimum weight braze attachment of the turbine to the fan blade, and the high strength and elevated temperature capability of the Rene'95 alloy for the fan blade. The data presented in this report show that the LF460 fan rotor design is feasible and that the design stresses and margins of safety were more than adequate. Prior to any production application, however, additional stress rupture/shear lap joints should be run in order to establish a firm 1200 F stress rupture curve for the CM50 braze metal.