CRYOGENIC PROPELLANT STORAGE FOR ROUND TRIPS TO MARS AND VENUS
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Knoll, R. H.↗
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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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Mars round trip mission analysis for the unfavorable 1975-1985 time period
Vehicle requirements and mission planning for manned space flight and exploration of mars during 1975-1985 time period
MANNED SPACE FLIGHT↗
Symposium synopsis- the when and what of the mars trip.
State of u.s. technology for a manned exploration of mars, including bioastronautics and communications programs, tidal history of mars and financial limitations of the space program
PLANETARY EXPLORATION↗
Instrumentation and trip report on flight no. 14.79 ue through 14.82 ue
Function and performance of instrumentation and telemeter equipment aboard Nike-Apache sounding rocket flight numbers 14.79 UE through 14.82 UE
TELEMETER↗
Manned mars trips using venus swingby modes.
Venus swingby used to decelerate manned spacecraft returning from Mars
PLANETARY GRAVITATION↗
Mars round-trip mission analysis for the 1975- 1985 time period.
Weight and energy requirements of vehicle systems for manned exploration of Mars
MARS /PLANET/↗
Minimum propellant consumption round-trip trajectories to Mars for constant-thrust, constant-specific-impulse vehicles with optimum coasting periods
Minimum propellant consumption trajectories to Mars for constant-thrust, constant-specific impulse vehicles with optimum coasting periods
INTERPLANETARY TRAJECTORY↗
Manned Mars trips using Venus flyby modes.
Venus swingby used to decelerate manned spacecraft returning from Mars
EARTH-MARS RENDEZVOUS TRAJECTORY↗
Ultek trip report
Experiences in checking production of ultrahigh vacuum systems at contractor establishment
CONTRACTOR↗
Comments on the communication and data problems associated with a Mars trip during a conjunction phase.
Communication parameters associated with Martian flyby probes and with lander and manned vehicles
FLYBY MISSION↗
Experimental evaluation of outer casing blowing or bleeding of single stage axial flow compressor. Part 2 - Performance of plain casing insert configuration with undistorted inlet flow and boundary layer trip
Outer casing blowing and bleeding and undistorted inlet flow for improved performance of high aspect ratio transonic rotor
Koch, C. C.↗
A trip to the moon begins with an Apollo/ Saturn V transporter.
Crawler transport for moving Saturn 5 mobile rocket launcher complete with umbilical tower
Buchanan, D. D.↗
Launch window analysis for round trip Mars missions.
Launch window variation using circular and elliptical parking orbits and transfer techniques, discussing Venus and Mars flyby missions
Deerwester, J. M.↗
Report on December 1969 performance and calibration trip to the Lunar Laser Ranging Station at McDonald Observatory
Detector package, Korad laser, and receiver efficiency of laser ranging station
Poultney, S. K.↗
Report on January 1970 performance and calibration trip to the Lunar Laser Ranging Station at McDonald Observatory
Start and stop line delay calibration for laser ranging station
Poultney, S. K.↗
TRIP trajectory integration program
Computer program with predictor-corrector numerical integration subroutine for fast trajectory analysis
Kaufman, B.↗
Completely modular Thermionic Reactor Ion Propulsion System (TRIPS)
The nuclear reactor powered ion propulsion system described is an advanced completely modularized system which lends itself to development of prototype and/or flight type components without the need for complete system tests until late in the development program. This modularity is achieved in all of the subsystems and components of the electric propulsion system including (1) the thermionic fuel elements, (2) the heat rejection subsystem (heat pipes), (3) the power conditioning modules, and (4) the ion thrusters. Both flashlight and external fuel type in-core thermionic reactors are considered as the power source. The thermionic fuel elements would be useful over a range of reactor power levels. Electrical heated acceptance testing in their flight configuration is possible for the external fuel case. Nuclear heated testing by sampling methods could be used for acceptance testing of flashlight fuel elements. The use of heat pipes for cooling the collectors and as a means of heat transport to the radiator allows early prototype or flight configuration testing of a small module of the heat rejection subsystem as opposed to full scale liquid metal pumps and radiators in a large vacuum chamber. The power conditioner (p/c) is arranged in modules with passive cooling.
Peelgren, M. L.↗
Use of grit-type boundary-layer-transition trips on wind-tunnel models
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Braslow, A. L.↗