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Results for “THRUST PROGRAMMING”

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 127 records · Page 7
All sourcesNASA NTRSDOE OSTI
NASA NTRS1980

Experimental evaluation of exhaust mixers for an Energy Efficient Engine

Static scale model tests were conducted to evaluate exhaust system mixers for a high bypass ratio engine as part of the NASA sponsored Energy Efficient program. Gross thrust coefficients were measured for a series of mixer configurations which included variations in the number of mixer lobes, tailpipe length, mixer penetration, and length. All of these parameters have a significant impact on exhaust system performance. In addition, flow visualization pictures and pressure/temperature traverses were obtained for selected configurations. Parametric performance trends are discussed and the results considered relative to the Energy Efficient Engine program goals.

Kozlowski, H.↗
NASA NTRS1978

Pointing and control system enabling technology for future automated space missions

Future automated space missions present challenging opportunities in the pointing-and-control technology disciplines. The enabling pointing-and-control system technologies for missions from 1985 to the year 2000 were identified and assessed. A generic mission set including Earth orbiter, planetary, and other missions which predominantly drive the pointing-and-control requirements was selected for detailed evaluation. Technology candidates identified were prioritized as planning options for future NASA-OAST advanced development programs. The primary technology thrusts in each candidate program were cited, and advanced development programs in pointing-and-control were recommended for the FY 80 to FY 87 period, based on these technology thrusts.

Dahlgren, J. B.↗
NASA NTRS1977

Future thrusts in the U.S. planetary program

The aim of the U.S. deep space program concept is to complete the reconnaissance of the solar system and to transfer to the era of space utilization. Such spacecraft as the Voyager Jupiter-Saturn and the Pioneer Venus will be used to visit all the planets and smaller bodies of the solar system by the year 2000. In the present paper, some missions, still in the early planning stage and requiring Congressional approval are discussed, and the enormous capabilities of Solar Electric Propulsion (SEP) and Solar Sailing are pointed out. The advantages of such low-thrust propulsion systems in performance, mission design, and operations flexibility are noted.

Friedman, L. D.↗
NASA NTRS1966

How many impulses/ques/

Minimum fuel transfer solution of Lawden problem involving finite number of impulse thrusts separated by coasting arcs

OPTIMUM THRUST PROGRAMMING↗
NASA NTRS1971

Performance of an electrically raised, synchronous satellite when subjected to radiation degradation effects

The use of solar electric propulsion to raise a high-power communication satellite from a low altitude, inclined circular orbit of the geosynchronous orbit is evaluated. Since the satellite ascends through the high intensity radiation belts, the power available from the solar array and therefore to the ion thrusters degrades. The performance of the solar electric stage in combination with the thrust augmented Thor/Delta launch vehicle is evaluated for two thrust steering programs. The transfer times and solar array requirements are presented for total geosynchronous payloads from 450 to 1100 kg.

Cake, J. E.↗