Inflatable Mylar parachutes for high altitudes.
Inflatable parachute system developed for deceleration of ionospheric probe instrumentation descending after expulsion from rocket
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Inflatable parachute system developed for deceleration of ionospheric probe instrumentation descending after expulsion from rocket
Cryogenic temperature resistant plastics in space program, discussing insulation, adhesives, seals, gaskets and expulsion of cryogenic propellant in zero gravity environment
Patch-type tests of ethylene-propylene rubber expulsion bladder material for thermal sterilization compatibility studies
Engineering and performance of warm gas mass expulsion system for attitude control on long space voyages
Design of dielectrophoretic liquid orientation and expulsion systems for zero gravity environments with maximum electromechanical effects of imposed electric field
Design changes in expulsion diaphragm and screen trap during sterilizable liquid propulsion system development
Technique development and test methods for improvement of polytetrafluoroethylene films for bladder expulsion
Physical parameter effect on pressurant gas requirements during expulsion of liquid hydrogen from spherical tanks
Solid para hydrogen coated graphite particles expulsion into interstellar medium from star formation regions, considering mantles stability and particles extinction efficiency, albedo and phase function
Mass expulsion and momentum systems for orbiting space station attitude control optimized, considering reaction jet and control moment gyro systems
Permeation of high density gases and propellant vapors through laminated Teflon expulsion bladders
Expulsion and measuring device for determining quantity of liquid in tank under conditions of weightlessness
Spacecraft propellant expulsion systems, comparing capillary with conventional techniques
Waste hydrogen utilization in microthrustors for spacecraft attitude control involving mass expulsion of cold gas
Comet Alcock flareup on 27-29 May 1969, noting visible rays in coma, dust grains expulsion from nucleus, tail structure, etc
Computer program calculates actual and useable remaining propellant quantities as required in positive expulsion rocket engine propellant feed system. Program establishes relationship between helium system pressures and temperatures and propellant weight remaining in tanks. Program is written in FORTRAN 4 for IBM-360 computer.
Helium gas requirements for liquid hydrogen expulsion from spherical tank
Development and characteristics of elastomeric materials for positive expulsion bladders