Development of a Deployable Nonmetallic Boom for Reconfigurable Systems of Small Spacecraft

Abstract Submission - AIAA Structures 2007Development of a Deployable Nonmetallic Boomfor Reconfigurable Systems of Small Modular SpacecraftCorresponding Author: Fredrik RehnmarkLockheed Martin Advanced Technology Center3251 Hanover St., Palo Alto, CA 94304phone: 650-354-5545fredrik.rehnmark@hnco.comAbstractLaunch vehicle payload capacity and the launch environment represent two of themost operationally limiting constraints on space system mass, volume, and configuration.Large-scale space science and power platforms as well as transit vehicles have beenproposed that greatly exceed single-launch capabilities. Reconflgurable systemslaunched as multiple small modular spacecraft with the ability to rendezvous, approach,mate, and conduct coordinated operations have the potential to make these designsfeasible. A key characteristic of these proposed systems is their ability to assemble intodesired geometric (spatial) configurations.While flexible and sparse formations may be realized by groups of spacecraft flyingin close proximity, flyers physically connected by active structural elements couldcontinuously exchange power, fluids, and heat (via fluids). Configurations of smallmodular spacecraft temporarily linked together could be sustained as long as needed withminimal propellant use and reconflgured as often as needed over extended missions withchanging requirements. For example, these vehicles could operate in extremely compactconfigurations during boost phases of a mission and then redeploy to generate power orcommunicate while coasting and upon reaching orbit.In 2005, NASA funded Phase 1 of a program called Modular Reconflgurable High-Energy Technology Demonstrator Assembly Testbed (MRHE) to investigatereconfigurable systems of small spacecraft. The MRHE team was led by NASA'sMarshall Space Flight Center and included Lockheed Martin's Advanced TechnologyCenter (ATC) in Palo Alto and its subcontractor, ATK. One of the goals of Phase 1 wasto develop an MRHE concept demonstration in a relevant 1-g environment to highlight anumber of requisite technologies.In Phase 1 of the MRHE program, Lockheed Martin devised and conducted anautomated space system assembly demonstration featuring multipurpose free-floatingrobots rei_reseiiting Spacecraft in the neMy built Controls and Automation Laboratory(CAL) at the ATC. The CAL lab features a 12' x 24' granite air-bearing table and anoverhead simulated starfleld. Among the technologies needed for the concept demo weremating interfaces allowing the spacecraft to dock and deployable structures allowing foradjustable separation between spacecraft after a rigid connection had been established.The decision to use a nonmetallic deployable boom for this purposewas driven by theMRHE concept demo requirements reproduced in Table 1.