meetings - Space Flight Mechanics Committee

Feb 14, 2013
Puna Room C&D
SESSION 28: MISSION/MANEUVER DESIGN
Chair: Dr. Rodney Anderson, Jet Propulsion Laboratory
8:00 AAS Modeling and Simulation of the MICROSCOPE mission
13-447 Meike List, ZARM (Center of Applied Space Technology and Microgravity),
University of Bremen
The French MICROSCOPE mission is designed to test the weak Equivalence Principle with
an accuracy of 1E-15. The experiment will be carried out on board of a small satellite,
developed and produced within the CNES Myriad series. The desired accuracy of the
measurement will be provided with the help of two high-precision capacitive diff erential
accelerometers. The ZARM is involved in the mission data evaluation process. In this
context a comprehensive simulation of the real system is being set up. The simulation tool
HPS as well as an overview about different modelling aspects will be presented.
8:20 AAS Orbital Transfer Techniques for Round-Trip Mars Missions
13-449 Damon Landau, NASA / Caltech JPL
The human exploration of Phobos and Deimos presents a highly constrained orbital transfer
problem, as the equatorial plane is generally not accessible from the arrival/departure
interplanetary trajectories with energetically optimal maneuvers. The proposed strategy
shifts the arrival/departure maneuvers away from periapsis so that the apsides of the parking
orbit lie in the plane of the target orbit, permitting efficient plane change maneuvers at
apoapsis of an elliptical parking orbit. This technique is approximately five times as
efficient as shifting the apsides in orbit, providing significant propellant savings to transfer
between the arrival, target, and departure orbits at Mars.
8:40 AAS Optimal Mixed Impulsive/Continuous Thrust Trajectories to the Interior
13-451 Earth-Moon L1 Lagrange Point
Daero Lee, New Mexico State University; Eric Butcher, New Mexico State
University; Amit Sanyal, New Mexico State University
Optimal transfer trajectories are designed for a spacecraft using mixed impulsive and
continuous thrust propulsion to depart low-Earth orbit and enter a specified planar
Lyapunov orbit at the interior Earth-Moon L1 Lagrange point in the framework of the
planar Circular Restricted Three Body Problem. The flight time and impulsive/continuous
thrust weighting factor are specified in advance. The continuous dynamic optimization
problem is reformulated as a discrete optimization through direct transcription and
collocation, which then is solved using nonlinear programming software. The design results
of various types of transfer trajectories are analyzed through the parametric study.
9:00 AAS The Plans for Getting OCO-2 into Orbit
13-452 Mark Vincent, Raytheon; Mark Garcia, NASA / Caltech JPL
Page 100
23 rd AAS / AIAA Space Flight Mechanics Meeting