meetings - Space Flight Mechanics Committee

Feb 11, 2013 Kauai Salon 3
SESSION 3: TRAJECTORY OPTIMIZATION -- I
Chair: Dr. Thomas Eller, Astro USA, LLC
8:00 AAS Loads Alleviation on European Launchers Using Wind Biased Trajectory
13-220 Optimization
Benjamin Carpentier, CNES; Pierre-Emmanuel Haensler, ALTEN; Benoit
Mazellier, CNES; Amaya Espinosa, CNES
In this paper is studied the use of wind-biased optimization for atmospheric phase trajectory
of European launchers. Such methodology has been extensively used in US programs but
was not on European launcher up to now. A benchmark is considered to evidence and
quantify the interest of such an approach in terms of loads alleviation, and TVC deflection
budget reduction. Two different approaches are discussed: the first one using a mean
seasonally wind profile, the second one using a day-of-launch sounded wind profile. Pros
and cons of each approach are discussed, as second one obviously implies operationnal
constraints.
8:20 AAS Time-Optimal Trajectory Design for a Dual-Satellite Sailcraft Interstellar
13-221 Mission with Probe Release
Xiangyuan Zeng, Tsinghua University; Kyle T. Alfriend, Texas A&M University;
Srinivas R. Vadali, Texas A&M University; Hexi Baoyin, Tsinghua University; Ying
Zhan, Beijing Branch of PCTEL(Tianjin) Wireless Telecommunications Products
Co., Ltd; Shengping Gong, Tsinghua University
A time-optimal trajectory design for a novel dual-satellite sailcraft is presented to
accomplish interstellar missions by releasing a probe at the perihelion point. Consequently,
the lightness number of the sail undergoes a positive jump at probe release, reaching a value
significantly greater than one, thus allowing the sailcraft to reach a very high terminal speed
at a sail-jettison distance of 5 AU. Such a discontinuous, time-optimal control problem is
solved with an indirect method, involving the solution to a multi-point boundary value
problem. A number of mission scenarios are investigated by varying relevant parameters.
8:40 AAS Preliminary Development of an Optimized Lambert Problem Solver for
13-222 Targets in Elliptical Orbits
David Spencer, The Pennsylvania State University; Brian Shank, The Pennsylvania
State University
This paper investigates the solution of Lambert’s Problem for targets in elliptical orbits.
Preliminary efforts are made in developing a mission design software tool to determine the
optimal interplanetary trajectory and final capture orbit based on mission constraints and
requirements between a departure and arrival body. Integration of the Applied Research
Laboratory Trade Space Visualizer software will permit a mission designer to visually
inspect the multi-dimensional trade space and investigate regions of ideal trajectories.
23 rd AAS / AIAA Space Flight Mechanics Meeting Page 23