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Bennett, F. O.

Publications and source records attributed to Bennett, F. O..

5 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1990

COLD-SAT orbital experiment configured for Altas launch

A study was done of the feasibility of conducting liquid hydrogen orbital storage, acquisition, and transfer experiments aboard a spacecraft launched by a commercial Atlas launch vehicle. Three hydrogen tanks are mated to a spacecraft bus that is similar to that used for three-axis-controlled satellites. The bus provides power, communications, and attitude control along with acceleration levels ranging from 10 exp -6 to 10 exp -4 g. At launch, all the liquid hydrogen is contained in the largest tank, which has an insulation system designed for both space operation and the short-term launch pad and ascent environment. This tank is much lighter and lower in cost than a vacuum-jacketed design, and is made possible by the experiment tanking options available due to the hydrogen-fueled Centaur upper stage of the Atlas I.

Schuster, J. R.↗
NASA NTRS1989

COLD-SAT orbital experiment configured for Atlas launch

The design and requirements for the proposed cryogenic on-orbit liquid depot storage, acquisition, and transfer (COLD-SAT) satellite experiment, which is to be launched by Atlas I, are examined. The COLD-SAT experiments are categorized as class I and II; class I involves technology related to space transportation missions and class II represents alternative fluid management operations and data. The hardware for the COLD-SAT experiments consists of three hydrogen tanks contained in the experimental module; the experimental module is connected to a three-axis-controlled spacecraft bus, and thrusters are positioned on the forward and aft ends of the spacecraft and on the cylindrical portion of the experimental module. The components and systems of the experiment module and the types of experiments that can be conducted in each tank are described. Diagrams of the spacecraft configuration are provided.

Shuster, J. R.↗
NASA NTRS1986

Evaluation of on-orbit cryogenic propellant depot options for the orbital transfer vehicle

An orbital cryogenic propellant storage facility will be required for a space-based Orbital Transfer Vehicle. The facility tanks will have features to permit fluid acquisition and transfer in low gravity and to limit cryogen boiloff caused by environmental heating. Boiloff management features will include thick multilayer insulation, vapor-cooled shields, low conductance structural supports and penetrations, and possibly refrigeration systems.

Schuster, J. R.↗