Manned Planetary Flight - Where are We Today
Known and unknown information on manned planetary flight
Manned space flight↗
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Results for “INTERPLANETARY SPACE”
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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Nonconventional communication devices for the mars mission/ques/
Application of millimeter wavelengths for mars mission communication offers a small advantage over conventional microwave systems
MILLIMETER WAVE↗
Radiation doses in interplanetary flight.
Radiation doses due to van allen belts, galactic cosmic rays and solar cosmic rays for interplanetary flight
RADIATION DOSE↗
Manned mars trips using venus swingby modes.
Venus swingby used to decelerate manned spacecraft returning from Mars
PLANETARY GRAVITATION↗
Comparative studies of conceptual design and qualification procedures for a Mars probe/lander. Volume II - Probe/Lander, entry from the approach trajectory. Book 2 - Mission and system specifications Final report
Mission and system specifications for Mars probe based on capsule entry from interplanetary approach trajectory
MARS PROBE↗
Cosmic dust detectors.
Mariner IV Cosmic Dust Detector measurement of momentum, mass distribution, flux densities and time histories of dust particles near Earth and in space
COSMIC DUST↗
Data automation system.
Data automation system /DAS/ on Mariner IV MARS probe involving real and nonreal time for experiments during cruise and encounter flights
REAL TIME↗
Manned Mars trips using Venus flyby modes.
Venus swingby used to decelerate manned spacecraft returning from Mars
EARTH-MARS RENDEZVOUS TRAJECTORY↗
Analysis and Interpretation of Magnetic Field Measurements Between Earth and Mars Received from Mariner IV Semiannual Progress Report, Dec. 1, 1965 - Aug. 31, 1966
Analysis and interpretation of Mariner IV MAGNETIC field measurements between Earth and Mars
MARINER IV SPACE PROBE↗
Venus Swingbys for Manned Mars Missions During the 1978-1986 Period
Venus swingby trajectory for manned Mars mission as possibility in 1978-1986
MISSION PLANNING↗
Implications of the meteoroid environment on the design of spacecraft.
Meteoroid protection system designs for optimum orbital space laboratories and manned interplanetary spacecraft
METEOROID PROTECTION↗
Analysis of multipurpose entry vehicle requirements for unmanned landings on bodies having tenuous atmospheres.
Multipurpose entry vehicle requirements for unmanned landings on bodies in solar system having tenuous atmospheres
ATMOSPHERIC ENTRY↗
Applications of combined electric, high-thrust propulsion systems.
Combined electric constant low thrust and chemical or nuclear high thrust space propulsion systems for interplanetary missions
Dugan, D. W.↗
Techniques for achieving magnetic cleanliness on deep-space missions
Techniques for obtaining magnetic cleanliness on deep space missions to allow interplanetary magnetic field mapping
West, W. S.↗
The Pioneer 9 electric field experiment. II - Observations between 0.75 and 1.0 AU
Pioneer 9 interplanetary observations, presenting deep space data for solar rotations and radial gradient in VLF electric field behavior
Scarf, F. L.↗
Modular thrust subsystem approaches to solar electric propulsion module design
Three approaches are presented for packaging the elements of a 30 cm ion thruster subsystem into a modular thrust subsystem. The individual modules, when integrated into a conceptual solar electric propulsion module are applicable to a multimission set of interplanetary flights with the space shuttle interim upper stage as the launch vehicle. The emphasis is on the structural and thermal integration of the components into the modular thrust subsystems. Thermal control for the power processing units is either by direct radiation through louvers in combination with heat pipes or an all heat pipe system. The propellant storage and feed system and thruster gimbal system concepts are presented. The three approaches are compared on the basis of mass, cost, testing, interfaces, simplicity, reliability, and maintainability.
Cake, J. E.↗
Modular thrust subsystem approaches to solar electric propulsion module design
Three approaches are presented for packaging the elements of a 30 cm ion thrustor subsystem into a modular thrust subsystem. The individual modules, when integrated into a conceptual solar electric propulsion module are applicable to a multimission set of interplanetary flights with the Space Shuttle/Interim Upper Stage as the launch vehicle. The emphasis is on the structural and thermal integration of the components into the modular thrust subsystems. Thermal control for the power processing units is either by direct radiation through louvers in combination with heat pipes of an all heat pipe system. The propellant storage and feed system and thrustor gimbal system concepts are presented. The three approaches are compared on the basis of mass, cost, testing, interfaces, simplicity, reliability, and maintainability.
Cake, J. E.↗