Description: Optical communication links provide higher data transfer rates with lower mass, power, and volume than conventional radio-frequency links. For deep space applications at long operational ranges, high performance stabilization of the space terminal data link is required. To meet this need, CDI proposes a novel application of our free-floating isolation platform. Based upon a Shuttle-proven technology, this approach yields 6-DOF isolation from the disturbances of the host vehicle while providing high-bandwidth active stabilization to attenuate both payload disturbances as well as any residual disturbances transferred from the base across the power/data umbilical. The proposed approach is designed to achieve better than 0.5microradian-rms stabilization for all frequencies above 0.1Hz when operating in a space environment. Phase I develops the proposed design concept, performs architecture trade studies, and predicts performance to establish the feasibility of the approach. Using an available free-floating isolation platform and a 2-axis low-g testbed, the design concept is prototyped and demonstrated on hardware in a simulated low-g environment (TRL-5). Phase II proceeds with the development of a prototype system that will be space qualified through comprehensive ground testing (TRL-6). Technology demonstration flight tests will be proposed on sRLVs and/or ISS platforms (e.g., WORF, OPALS upgrade), achieving a TRL-7 maturity by the end of Phase II.

Benefits: The optical isolation and stabilization technology developed through this research is targeted for insertion into near-term NASA programs such as the Laser Communications Relay Demonstration Mission (LCRD) and as an upgrade for the Optical Payload for LAsercomm Science (OPALS). The capability is considered a "Push Technology" enabling new missions or enhancing missions already planned in for Deep Space Planetary Missions, the Space Communications and Navigation (SCaN) Program, and the Deep Space Optical Terminal (DOT) Project. Design geometry is readily customized to specific payload applications. As such, the design can be scaled for a 10cm telescope (e.g., Lunar Lasercom Space Terminal), a 30.5cm telescope (e.g.,Mars Laser Communications Demonstration), or larger telescopes for deep space missions. For small telescopes, the platform can be used for isolation, stabilization, and beam tracking, thus eliminating the need for the Fine Steering Mirror and its associated cost, mass, power and volume.

By providing component-level isolation and stabilization at the optical payload, this approach does not impose any unusual constraints on the host vehicle. This makes the technology broadly applicable to a wide range of vehicles including sRLVs, orbital RLVs, Earth orbiting satellites (even the simplest thruster-only designs), and deep space vehicles. The technology is targeted for high data throughput applications requiring optical links, but the core approach is applicable any space payload requiring high-performance isolation and stabilization. Applications include commercial and military communications satellites, next-generation large space telescopes, space-based interferometric telescopes, advanced geo-pointing surveillance and reconnaissance payloads, etc. NASA and the U.S. comprise less than half of the overall total satellite market, so there are significant international applications for the technology.