Analysis of Near Rectilinear Halo Orbit Insertion with a 40-kW Solar Electric Propulsion System
Analysis of Near Rectilinear Halo Orbit Insertion with a 40-kW Solar Electric Propulsion System
- Neue Suche nach: S. L. Mccarty
- Neue Suche nach: W. K. Sjauw
- Neue Suche nach: L. M. Burke
- Neue Suche nach: M. L. McGuire
- Neue Suche nach: S. L. Mccarty
- Neue Suche nach: W. K. Sjauw
- Neue Suche nach: L. M. Burke
- Neue Suche nach: M. L. McGuire
This paper examines low thrust trajectories for delivery of a 40-kW solar electric propulsion spacecraft and potential additional payload to a desired NRHO. One option considered is a trans-lunar injection launch as a co-manifested payload on the Space Launch System. For this option, a reference trajectory is designed and a scan of launch dates is completed to understand the propellant mass sensitivity. A 15-day period cyclical variation in required propellant is observed that is attributed to solar gravity effects. A second option considered is to launch on a smaller commercial launch vehicle to a less energetic elliptical orbit and use SEP to spiral out to NRHO. For this option, analysis is completed to understand the trades between delivered mass to NRHO, total propellant required, time of flight, and solar array degradation. Results show that, while launching to lower altitudes can deliver greater payload mass to NRHO, significant solar array degradation can be observed.
Dokumentinformationen
Analysis of Near Rectilinear Halo Orbit Insertion with a 40-kW Solar Electric Propulsion System
2018
31 pages
Report
Keine Angabe
Englisch
Astronautics , Spacecraft Trajectories & Flight Mechanics , Aerodynamic characteristics , Cislunar space , Degradation , Halo orbit space station , Low thrust , Payloads , Solar arrays , Solar electric propulsion , Altitude , Electric potential , Injection , Lunar launch , Propellant sensitivity , Space commercialization