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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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At least 1,135 records · Page 63
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Space shuttle baseline accommodations for payloads

The space shuttle system as it relates to payloads is described. This study provides potential users of the space shuttle with a uniform base of information on the accommodations between the payload and the shuttle. By utilizing this information, preliminary payload planning and design studies can be evaluated and compared against a common set of shuttle/payload accommodations. This information also minimizes the necessity for each payload study to develop information on the shuttle configuration.

Source record↗
NASA NTRS1973

Worldwide variations in atmospheric transmission. I - Baseline results from Smithsonian observations.

The spectrobolometer used in the studies is discussed, giving attention to instrument design, the method of recording, and the spectral resolution. The atmospheric transmission for each wavelength was determined by making observations over a range of air masses. The precipitable water vapor values were found from the spectrobolograms by measurement of the depths of water vapor bands at 0.935, 1.13, and 1.47 microns. The results of the studies are discussed together with seasonal variations, long term trends, and the nature of the aerosols.

Roosen, R. G.↗
NASA NTRS1969

Apollo 14 (mission H-3) Baseline Mission Profile

Preliminary Apollo 14 (Mission H-3) trajectory data for the July 1970 launch window are presented in this document. A general mission profile is presented, and approximate variations of selected mission parameters are indicated. Note that the information in this document is preliminary and will be updated in the Apollo 14 (Mission H-3) operational trajectory documents.

Source record↗
NASA NTRS1972

Very Long Baseline Interferometry (VLBI) earth physics

The characteristics of the Michelson/Pease stellar interferometer are discussed. An analog of the interferometer using radio waves is described. The use of a conventional hard-wired interferometer with very long base line interferometry (VLBI) is analyzed. Mathematical models are developed to analyze the VLBI techniques. A summary of VLBI geodetic experiments is tabulated. The concept and application of the astronomical radio interferometric earth surveys (ARIES) are reported. A schematic diagram of ARIES implementation is provided.

Macdoran, P. F.↗
NASA NTRS1974

Triple balance test of the PRR baseline space shuttle configuration on a .004 scale model of the MCR 0074 orbiter configuration in the MSFC 14 x 14 inch Trisonic Wind Tunnel (TWT 570) IA31F(B), volume 1

A wind tunnel force and moment test of the space shuttle launch vehicle was conducted. The wind tunnel model utilized a triple balance such that component aerodynamics of the orbiter, external tank, and solid rocket booster was obtained. The test was conducted at an angle of attack range from -10 deg to 10 deg, and angle of sideslip range from -10 deg to 10 deg, and a Mach number range from 0.6 to 4.96. Simulation parameters to be used in future launch vehicle wind tunnel tests were investigated. The following were included: (1) effect of orbiter -ET attach hardware; (2) model attachment (spacer) effects; (3) effects of grit on model leading surfaces; and (4) model misalignment effects. The effects of external tank nose shape was studied by investigating five different nose configurations. Plotted and tabulated data is reported.

Ramsey, P. E.↗
NASA NTRS1975

An investigation in the NASA MSFC 14-inch trisonic wind tunnel to determine the pressure distribution over the components of a 0.004 scale version of the Rockwell MCR 0074 baseline shuttle ascent configuration (IA32F), volume 1

Data were obtained for Mach numbers from 0.6 to 3.48, angles of attack from -10 to 10 degrees, and angles of sideslip from -10 to 10 degrees at zero angle of attack. Also, -4 and 4 degrees sideslip were run for an angle of attack of -5 and 5 degrees. Aerodynamic configurations of the solid rocket motors, external tank, and orbiter are shown. Graphs of plotted pressure data (pressure coefficients) for the external tank and solid rocket motors are given. A description of the test facility is included.

Ramsey, P. E.↗