PERFORMANCE OF NUCLEAR-ELECTRIC PROPULSION SYSTEMS IN SPACE EXPLORATION
An analysis is presented of the payload capabilities of nuclear-electric spacecraft for interplanetary exploration. Results are presented in terms of vehicle terminal mass at its destination as a function of flight time for the mission. The missions which were studied include probes and orbiters to most of the planets in the solar system, plus solar probes and flights out of the plane of the ecliptic. For a given mission, flight time is chiefly determined by the initial acceleration of the spacecraft, whereas terminal mass is chiefly determined by the specific impulse of the thrust device. Some generalized curves are presented which indicate the initial accelerations requlred for several missions. The specific impulses required for various ratios of terminal mass to initial mass are shown for the same missions. Once a particular set of mission fiight time and payload requirements is established, the optimum combination of ion engine characteristics, power plant weight and power level, and launch vehicle can be specified to satisfy these requirements. (auth)
- Research Organization:
- California Inst. of Tech., Pasadena. Jet Propulsion Lab.
- DOE Contract Number:
- NASW-6
- NSA Number:
- NSA-16-009710
- OSTI ID:
- 4795037
- Report Number(s):
- JPL-TR-32-159
- Resource Relation:
- Other Information: Orig. Receipt Date: 31-DEC-62
- Country of Publication:
- United States
- Language:
- English
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