Closed form low-thrust trajectories for Mars missions
Conference
·
OSTI ID:7069691
Several closed form trajectory solutions have been developed for low-thrust interplanetary flight and used with patched conics for analysis of combined propulsion systems. The solutions provide insight into alternative types of Mars missions, and show considerable mass savings for fast crewed missions with outbound trip times on the order of 90--100 days. 7 refs.
- Research Organization:
- Sandia National Labs., Albuquerque, NM (United States)
- Sponsoring Organization:
- DOE; USDOE, Washington, DC (United States)
- DOE Contract Number:
- AC04-76DP00789
- OSTI ID:
- 7069691
- Report Number(s):
- SAND-92-1598C; CONF-920747--6; ON: DE92017431
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
42 ENGINEERING
420200* -- Engineering-- Facilities
Equipment
& Techniques
ANALYTICAL SOLUTION
DIFFERENTIAL EQUATIONS
EFFICIENCY
ENERGY EFFICIENCY
EQUATIONS
EQUATIONS OF MOTION
EXPLORATION
INTERPLANETARY SPACE
MARS PLANET
PARTIAL DIFFERENTIAL EQUATIONS
PLANETS
PROPULSION
PROPULSION SYSTEMS
SPACE
SPACE VEHICLES
TRAJECTORIES
VEHICLES
420200* -- Engineering-- Facilities
Equipment
& Techniques
ANALYTICAL SOLUTION
DIFFERENTIAL EQUATIONS
EFFICIENCY
ENERGY EFFICIENCY
EQUATIONS
EQUATIONS OF MOTION
EXPLORATION
INTERPLANETARY SPACE
MARS PLANET
PARTIAL DIFFERENTIAL EQUATIONS
PLANETS
PROPULSION
PROPULSION SYSTEMS
SPACE
SPACE VEHICLES
TRAJECTORIES
VEHICLES