NASA Scientific and Technical Aerospace Reports - The University ...

cross sectional shapes that receives and holds thermally cured thermal protection (TP) blocks that have corresponding cross
sectional shapes. Material composition for TP blocks in different locations can be varied to account for different atmospheric
heating characteristics at the different locations. TP block side walls may be attached to all, or to less than all, the
corresponding honeycomb structure side walls.
Official Gazette of the U.S. Patent and Trademark Office
Honeycomb Structures; Heat Shielding; Thermal Protection; Atmospheric Entry; Temperature Effects
20100017675 NASA Marshall Space Flight Center, Huntsville, AL, USA
Thermal Control System for a Small, Extended Duration Lunar Surface Science Platform
Bugby, D.; Farmer, J.; OConnor, B.; Wirzburger, M.; Abel, E.; Stouffer, C.; 9-11 Mar. 2010; 18 pp.; In English; Spacecraft
Thermal COntrol Workshop, 9-11 Mar. 2010, El Segundo, CA, USA; Original contains color illustrations
Report No.(s): M10-0336; Copyright; Avail.: CASI: A03, Hardcopy
ONLINE: http://hdl.handle.net/2060/20100017675
The presentation slides include: Introduction: lunar mission definition, Problem: requirements/methodology, Concept:
thermal switching options, Analysis: system evaluation, Plans: dual-radiator LHP (loop heat pipe) test bed, and Conclusions:
from this study.
Derived from text
Lunar Surface; Heat Pipes; Temperature Control; Test Stands; Thermal Environments
20100017677 NASA Marshall Space Flight Center, Huntsville, AL, USA
Robotic Lunar Lander Development Project Status
Hammond, Monica; Bassler, Julie; Morse, Brian; March 2010; 9 pp.; In English; 41st Lunar and Planetary Science
Conference (LPSC), 1-5 Mar. 2010, The Woodlands, TX, USA; Original contains color illustrations
Report No.(s): M10-0395; Copyright; Avail.: CASI: A02, Hardcopy
ONLINE: http://hdl.handle.net/2060/20100017677
This slide presentation reviews the status of the development of a robotic lunar lander. The goal of the project is to
perform engineering tests and risk reduction activities to support the development of a small lunar lander for lunar surface
science. This includes: (1) risk reduction for the flight of the robotic lander, (i.e., testing and analyzing various phase of the
project); (2) the incremental development for the design of the robotic lander, which is to demonstrate autonomous, controlled
descent and landing on airless bodies, and design of thruster configuration for 1/6th of the gravity of earth; (3) cold gas test
article in flight demonstration testing; (4) warm gas testing of the robotic lander design; (5) develop and test landing
algorithms; (6) validate the algorithms through analysis and test; and (7) tests of the flight propulsion system.
CASI
Flight Tests; Lunar Surface; Risk; Robotics; Lunar Exploration
20100017708 Texas Univ., Austin, TX, USA
Theoretical Foundation of Copernicus: A Unified System for Trajectory Design and Optimization
Ocampo, Cesar; Senent, Juan S.; Williams, Jacob; May 3, 2010; 8 pp.; In English; 4th International Conference on
Astrodynamics Tools and Techniques, 3-6 May 2010, Madrid, Spain
Report No.(s): JSC-CN-20552; Copyright; Avail.: CASI: A02, Hardcopy
ONLINE: http://hdl.handle.net/2060/20100017708
The fundamental methods are described for the general spacecraft trajectory design and optimization software system
called Copernicus. The methods rely on a unified framework that is used to model, design, and optimize spacecraft trajectories
that may operate in complex gravitational force fields, use multiple propulsion systems, and involve multiple spacecraft. The
trajectory model, with its associated equations of motion and maneuver models, are discussed.
Author
Design Optimization; Mathematical Models; Spacecraft Trajectories; Spacecraft Maneuvers
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