SCARLET I: Mechanization solutions for deployable concentrator optics integrated with rigid array technology
The SCARLET I (Solar Concentrator Army with Refractive Linear Element Technology) solar array wing was designed and built to demonstrate, in flight, the feasibility of integrating deployable concentrator optics within the design envelope of typical rigid array technology. Innovative mechanism designs were used throughout the array, and a full series of qualification tests were successfully performed in anticipation of a flight on the Multiple Experiment Transporter to Earth Orbit and Return (METEOR) spacecraft. Even though the Conestoga launch vehicle was unable to place the spacecraft in orbit, the program effort was successful in achieving the milestones of analytical and design development functional validation, and flight qualification, thus leading to a future flight evaluation for the SCARLET technology.
- Research Organization:
- NASA Langley Research Center, Hampton, VA (United States)
- OSTI ID:
- 402041
- Report Number(s):
- N-96-27601; NASA-CP-3328; L-17569; NAS-1.55:3328; NIPS-96-49233; CONF-960595-; TRN: 9627611
- Resource Relation:
- Conference: 30. aerospace mechanisms symposium, Hampton, VA (United States), 15-17 May 1996; Other Information: PBD: May 1996; Related Information: Is Part Of 30th Aerospace Mechanisms Symposium; Bradley, O.H. Jr.; Rogers, J.F.; PB: 407 p.
- Country of Publication:
- United States
- Language:
- English
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