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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 343 records · Page 19
All sourcesNASA NTRSDOE OSTI
NASA NTRS1970

Balloon-borne radio altimeter

Pulse radar altimeter design for balloon sounding, discussing flight tests, superregenerative stage, etc

Levanon, N.↗
NASA NTRS1971

Altimeter and radiometer for a Venus orbiter mission

The concept, constraints, and capabilities of a radar altimeter type contour mapper for a Venus orbiter mission are presented. The system was developed for the proposed planetary explorer universal bus concept. A system with a height precision of 30meters over a surface area of 7200 square kilometers is achieved. Using this system and the orbit proposed in the orbiting bus concept, the northern hemisphere of Venus is mapped in one Venus day. The radar receiver system, is used in a radiometer mode to obtain a map of the diurnal and logitudinal variations of the Venus surface temperature with a resolution of 3.0 degrees Kelvin.

Bryan, J. W.↗
NASA NTRS1971

A radar altimeter-driftmeter for small planetary probes

A light weight radar altimeter-driftmeter applicable to landing planetary probes is described. The system utilizes a small light weight phased array antenna to generate three independent radio frequency beams. The range and Doppler along each of these beams is measured. The six measured quantitites are then combined with a resulting range (altitude) accuracy of 75 meters and a horizontal drift velocity accuracy of 6 cm/sec. The entire system weighs less than 3.7 kilograms and requires less than 9 watts of dc power.

Bryan, J. W.↗
NASA NTRS1972

Apollo 15 laser altimeter, part D

The laser altimeter, consisting of a Q switched ruby laser, transmitting optics, counting timer, receiving optics, and a photomultiplier is described. Harmonic analysis of the mission data is also presented.

Robertson, F. L.↗
NASA NTRS1972

Determination of the geoid from satellite altimeter data

The characteristics of the geoid surface are quantitatively described. A procedure for calculating the satellite altitude is developed. Error sources are described quantitatively, mathematically modeled, and evaluated in computer simulation. Procedures for maximum likelihood processing of altimeter data for recovery of orbit and geopotential information are presented for several geopotential models.

Brown, R. D.↗
NASA NTRS1970

Single arc tracking errors associated with altimeter measurements

This study investigated the accuracies of orbit determinations in the radial coordinate utilizing currently available tracking systems. The results pinpoint certain areas which are critical for the efficient utilization of altimeter measurements.

Mcgoogan, J. T.↗
NASA NTRS1972

The Skylab radar altimeter

A summary of the significant hardware characteristics of the S-193 altimeter experiment portion of the 1973 Skylab Mission is presented. A detailed discussion of the altimetry, oceanographic, and instrumentation technology objectives are presented along with a discussion of the major experiments associated with these objectives.

Stanley, H. R.↗
NASA NTRS1972

GEOS-C radar altimeter characteristics

The purpose of the GEOS-C mission and the operating characteristics of its special K-band altimeter are outlined. Special attention was given to the possible use of height measurements and other supporting GEOS-C data to evaluate the feasibility and value of altimetry on a global basis.

Oakes, J. B.↗
NASA NTRS1972

Satellite altimeters after Skylab and GEOS-C - should they utilize a single transmitter or an array of pulsed amplifiers?

An attempt was made to determine if future satellite altimeters, operating at K-band, should use a single transmitter or an array of pulsed amplifiers. The two systems were compared as a function of reliability, power, service life, system requirements, and weight. Preliminary results indicate the modular system to be superior in service life and reliability although it requires more power and is substantially heavier than the single system. No concrete conclusions were reached as to which system should be used.

Greene, A. H.↗