As part of a NIAC funded Titan sample return mission, NASA GRC’s Compass Team has investigated a two-stage, in-situ propellant, launch vehicle design. This paper presents a proposed trajectory for the vehicle and mission of interest. This trajectory is optimally solved to balance drag losses in the denser atmosphere along with gravity losses accumulated during vehicle ascent to select an optimal path from Titan’s surface to a parking orbit. The resulting trajectory is characterized by a slow, vertical climb to an altitude above the densest part of the atmosphere followed by a vehicle pitch-over and climb to orbital insertion. The resulting ∆V is 3.96 km/s.
An Optimized Trajectory for a Two-Stage, Surface to Orbit Titan Launch Vehicle
2022 AAS/AIAA Astrodynamics Specialist Conference ; 2022 ; Charlotte, NC, US
Aufsatz (Konferenz)
Keine Angabe
Englisch
Two-Stage Launch Vehicle Trajectory Modeling for Low Earth Orbit Applications
BASE | 2016
|Trajectory optimization method in two-stage-to-orbit RBCC-RKT launch vehicle
Online Contents | 2014
|Tema Archiv | 1989
|SAE Technical Papers | 1989
|