Inflatable honeycomb Patent
Inflatable honeycomb panel element for lightweight structures usable in space stations and other construction
Schnitzer, E.↗
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Results for “inflated”
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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Inflatable radar reflector unit Patent
Inflatable radar reflector unit - lightweight, highly reflective to electromagnetic radiation, and adaptable for erection and deployment with minimum effort and time
Radnofsky, M. I.↗
Thermal testing of inflatable solar shields for cryogenic space vehicles
Thermal testing of inflatable solar shields for cryogenic space vehicles, discussing shield misalignment effects on propellant tank temperatures
Doughty, R. O.↗
Deployment and inflation characteristics tests of a Buoyant Venus Station balloon
Buoyant Venus station balloon for deployment and inflation during parachute descent into Venus atmosphere tested with scale model balloons in wind tunnels
Holle, G. F.↗
Magnetosphere inflation during four magnetic storms in 1965
Magnetic storms development via initial asymmetric inflation of evening magnetosphere, using Explorer 26 and ground observatory data
Cahill, L. J., Jr.↗
Attached Inflatable Decelerator performance evaluation and mission-application study
Attached Inflatable Decelerator for planetary atmospheric entry, discussing mission applications and wind tunnel models performance
Bohon, H. L.↗
Structural behavior of tapered inflated fabric cylinders under various loading conditions
Method analyzes inflatable structures and considers axial loads, torsional moment, and internal pressure. Behavior depends on anistropic nature and large deflection stress-strain characteristics of fabric material. Behavior equations for pressurized cylinder loaded in torsion are developed.
Kovalevsky, L.↗
Inflation system for balloon type satellites Patent
Inflation system for balloon type satellites
Chapman, R. M.↗
Rotating mandrel for assembly of inflatable devices Patent
Rotating, multisided mandrel for fabricating gored inflatable spacecraft
Macfadden, J. A.↗
Design, fabrication, and static testing of Attached Inflatable Decelerator /AID/ models
Design, fabrication and static testing of attached inflatable decelerator models for supersonic wind tunnel evaluation
Faurote, G. L.↗
Method of making inflatable honeycomb Patent
Technique for making foldable, inflatable, plastic honeycomb core panels for use in building and bridge structures, light and radio wave reflectors, and spacecraft
Schnitzer, E.↗
Method of making an inflatable panel Patent
Forming inflatable panels erectable in space for passive communication satellite
Gillespie, W., Jr.↗
Thermal and stress analysis of an Attached Inflatable Decelerator /AID/ deployed in the Mars and Earth atmospheres
Trajectory, thermodynamic, and stress analyses of spacecraft inflatable decelerators in Mars and Earth atmospheres
Burgess, J. L.↗
Drag coefficients for partially inflated flat circular parachutes
Free-body tests of flat circular parachutes and determination of aerodynamic drag coefficients during partial inflation
Scher, S. H.↗
Design, fabrication, and static testing of first-stage Attached Inflatable Decelerator (AID) models
Design, fabrication, and static testing of wind tunnel models of first-stage Attached Inflatable Decelerator canopies for supersonic vehicles
Johnson, B. A.↗
Investigation of packaging, deployment, and leak-rate characteristics of an inflatable lunar-shelter model
Development, characteristics, and evaluation of inflatable lunar shelter model to determine leak rate in near vacuum conditions
Keffer, C. O.↗
Aerodynamic heating at Mach 8 of attached inflatable decelerator configurations
Mach 8 variable-density tunnel used for determination of aerodynamic heating of attached inflatable decelerator configurations
Creel, T. R., Jr.↗
Subsonic pressure distributions around a solid model of an inflatable decelerator attached to the base of an ogive-cylinder
A wind-tunnel investigation was conducted at free-stream Mach numbers from 0.20 to 1.00 and corresponding Reynolds numbers, based on maximum afterbody diameter, from 2.25 x one million to 6.90 x one million on a solid model of an attached inflatable decelerator (AID) connected to the base of an ogive-cylinder. Tests were conducted to obtain ram-air and surface pressure distributions about the AID. AID shapes derived for subsonic deployment are dependent on the pressure distributions used in their derivation, and the different shapes obtained are dependent on the Mach number for which the design is made. The resulting pressure distributions were used in a design program to obtain new shapes which were compared with the original pressure-distribution shape.
Sawyer, J. W.↗