Powered Trajectory Studies for Low Thrust Space Vehicles
Powered trajectory calculations have been carried out for missions from Earth to Venus, Mars, Jupiter and return. The procedure used was based upon an optimization that minimizes total energy requirements and maximizes payload. Data are presented which relate payload fraction, total mission time, and minimum specific power requirements. It is shown that propulsion plant weight-to-exhaust power ratios of 122 lb/kw and 22 lb/kw are adequate for missions ranging in difficulty from one-way trips to Mars with 10% payload fraction to round trips to Mars with 30% payload, respectively. In both cases the transfer is assumed to be between low altitade satellite orbits about the planets in question.
- Research Organization:
- Univ. of California, Livermore
- Sponsoring Organization:
- USDOE
- NSA Number:
- NSA-15-009634
- OSTI ID:
- 4087884
- Journal Information:
- ARS Journal, Journal Name: ARS Journal Journal Issue: 1 Vol. 31; ISSN 1936-9972
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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