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Development and Testing of a Vehicle Management System for Autonomous Spacecraft Habitat Operations
Author(s) -
Richard Levinson,
Jeremy Frank,
Michael Iatauro,
Adam Sweet,
Gordon Aaseng,
Michael Scott,
John Ossenfort,
James F. Soeder,
Tam Ngo,
Zachary Greenwood,
Jeffrey Csank,
Daniel B. Carrejo,
Andrew T. Loveless
Publication year - 2018
Publication title -
2018 aiaa space and astronautics forum and exposition
Language(s) - English
Resource type - Conference proceedings
SCImago Journal Rank - 0.103
H-Index - 1
DOI - 10.2514/6.2018-5148
Subject(s) - spacecraft , aerospace engineering , habitat , environmental science , computer science , systems engineering , automotive engineering , aeronautics , astrobiology , engineering , ecology , physics , biology
As the increased distance between Earth-based mission control and the spacecraft results in increasing communication delays, small crews cannot take on all functions performed by ground today, and so vehicles must be more automated to reduce the crew workload for such missions. In addition, both near-term and future missions will feature significant periods when crew is not present, meaning the vehicles will need to operate themselves autonomously. NASA’s Advanced Exploration Systems Program pioneers new approaches for rapidly developing prototype systems, demonstrating key capabilities, and validating operational concepts for future humanmissions beyond low-Earth orbit. Under this program, NASA has developed and demonstrated multiple technologies to enable the autonomous operation of a dormant space habitat. These technologies included a fault-tolerant avionics architecture, novel spacecraft power system and power system controller, and autonomy software to control the habitat. The demonstration involved simulation of the habitat and multiple spacecraft sub-systems (power storage and distribution, avionics, and air-side life-support) during a multi-day test at NASA’s Johnson SpaceCenter. The foundation of the demonstrationwas ‘quiescent operations’ of a habitat during a 55 minute eclipse period. For this demonstration, the spacecraft power distribution system and air-side life support system were simulated at a high level of fidelity; additional systems were managed, but with lower fidelity operational constraints and system behavior. Operational constraints for real and simulated loads were developed by analyzing on-orbit hardware and evaluating future Exploration capable technology. A total of 13 real and simulated loads were used during the test. Eight scenarios including both nominal and offnominal conditions were performed. Over the course of the test, every application performed its desired functions successfully during the simulated tests. The results will inform both future tests, as well as provide insight to NASA’s domestic and international partners, as they

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