The Electric Space Cruiser for High Energy Missions

Beale, Robert J.; Speiser, E. W.; Womack, J. R.

doi:10.2514/6.1963-7

Cited by 8 publications

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“…Figure 2 is a perspective view of a nuclear-electric spacecraft similar to that in Ref. 1. The principal difference is that the power-conditioning equipment has been moved closer to the payload to keep the length between the thrusters and the power-conditioning equipment fairly short and to make the pay load-to-reactor distance as large as possible.…”

Section: Introductionmentioning

confidence: 98%

Power conditioning for space propulsion systems using contact ion thrusters.

Eilenberg

Erway

1966

Journal of Spacecraft and Rockets

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The paper is concerned with the problems associated with matching the output of a large nuclear-electric power source to the requirements of contact ion thrusters. The factors that influence the design requirements and the technical approach to power conditioning, switching, and control (PCSC) subsystems are discussed. Thruster requirements, power source characteristics, and environmental constraints are analyzed from the standpoint of their relationships to power conditioning. In addition, the results of the development of a breadboard PCSC unit at a 30-kw power level are described. This work gives an insight into the problems and the possible solutions that will result in the realization of power conditioning equipment whose specific weight, efficiency, and reliability are compatible with requirements of large scale nuclear-electric rockets of the future. In particular, one of the most promising experimental results is a 30-kw breadboard whose components exhibit a total weight of 3.2 lb/ kw. The results of a design study for a 300-kw system show that it is feasible to build a PCSC system weighing 9.1 Ib/kw input power including radiators and shadow shielding with a power efficiency of 93%.

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Section: Introductionmentioning

confidence: 98%

Power conditioning for space propulsion systems using contact ion thrusters.

Eilenberg

Erway

1966

Journal of Spacecraft and Rockets

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The SNAP-50/SPUR Program Presented at the Third Biennial Aerospace Power Systems Conference, Philadelphia, Pa., September 1-4, 1964 (not preprinted). Note: This paper presents the status of the SNAP-50/SPUR Program at the time of the AIAA Conference in Philadelphia, September 1964. During 1965, it was decided to disband the Program Office and, instead, transfer responsibility on a basic technology level (as contrasted with a technology demonstration program) to the Livermore Laboratories of the U. S. A

Douthett¹

1966

Progress in Astronautics and Rocketry

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Electric Propulsion

Moeckel

1963

Science

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For space exploration we not necessarily bigger,For space exploration we not necessarily bigger, need rockets that are better, than those being developed.need rockets that are better, than those being developed.Propulsion is a means of producing motion, or, more accurately, changes in momentum. Propulsion is also required to maintain momentum in the presence of resistive or retarding forces. These functions of a propulsion system require the expenditure of energy. If this propulsive energy must be carried by the vehicle, as is the case with most systems, then the amount of change in momentum, or the length of the period during which a given momentum can be maintained, is determined by the form and amount of the energy carried along. Ideally, this energy should be in a form which yields the maximum useful propulsive energy per unit of weight.Other factors, however, such as development and operating problems and costs, or the adequacy of existing systems, may argue against use of systems having the highest possible energy per unit weight. In the case of aircraft, for example, the use of nuclear power would have greatly increased the energy per unit weight, but it involved many difficult and costly problems of development and operation. Its advantages, in terms of much greater range and duration of flight, were overbalanced by these disadvantages, and by the fact that kerosene-burning aircraft were already available with range, speed, and Propulsion is a means of producing motion, or, more accurately, changes in momentum. Propulsion is also required to maintain momentum in the presence of resistive or retarding forces. These functions of a propulsion system require the expenditure of energy. If this propulsive energy must be carried by the vehicle, as is the case with most systems, then the amount of change in momentum, or the length of the period during which a given momentum can be maintained, is determined by the form and amount of the energy carried along. Ideally, this energy should be in a form which yields the maximum useful propulsive energy per unit of weight.Other factors, however, such as development and operating problems and costs, or the adequacy of existing systems, may argue against use of systems having the highest possible energy per unit weight. In the case of aircraft, for example, the use of nuclear power would have greatly increased the energy per unit weight, but it involved many difficult and costly problems of development and operation. Its advantages, in terms of much greater range and duration of flight, were overbalanced by these disadvantages, and by the fact that kerosene-burning aircraft were already available with range, speed, and flight durations which were adequate for most applications of interest.For space missions, if man would be satisfied with exploring the moon, or even with settling a colony on it, there would be little incentive to develop propulsion systems with much greater energy per unit weight than the chemical rockets now in use or under development. Some economies mi...

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The Electric Space Cruiser for High Energy Missions

Cited by 8 publications

References 0 publications

Power conditioning for space propulsion systems using contact ion thrusters.

Power conditioning for space propulsion systems using contact ion thrusters.

Electric Propulsion

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