SBIR 95-1 SOLICITATION

PROJECT SUMMARY

Proposal Number:

09.01-0204

Project Title:

CFRC SILICON CARBIDE MONOLITHIC SENSORCRAFT FOR NEXT GENERATION MICROSPACECRAFT APPLICATION

Technical Abstract:

A low life-cycle-cost, virtual presence in space concept is enhanced by the use of lightweight, thermally stable, passively damped component materials for microspacecraft/payload elements. However, maximum mass utility is realized by a top-down system architecture which permits the integration of multiple functions into components and subsystems. The proposed innovation marries remote sensing energy collection, communications, spacecraft bus and thermal management into a <10kg package. Multiple functionality features include: the optical system performs as a 30:1 optical communica- tions beam expander/compressor and visible imager 0.3m afocal; the bus serves as a spacecraft subsystem support and a monococque structure for the optical system; and tubes embedded in the bus panels provide structural rigidity and thermal management heat pipes. Combined with silicon carbide in its bulk (optical compo- nents) and ceramic fiber reinforced composite (CFRC structure) forms, this sensorcraft innovation provides lightweight, passive athermalization and extends the benefits of material selection an additional order-of-magnitude in life cycle cost reduction. Phase I will produce a tested, 0.35m optical bench/bus assembly based on a remote body reconnaissance mission. After this feasibility demo., Phase II will produce a monolithic optical system/spacecraft bus demonstration, including embedded heat pipes. The new design para- digm as embodied in this sensorcraft will be positioned for Phase III flight qualification to enable a virtual presence in space.

Potential Commercial Applications:

The sensorcraft architecture innovation will permit an order-of- magnitude savings in mission life cycle costs based on direct and indirect mass savings. It is applicable to all spacebased pri- mary mission applications including earth monitoring (both science and commercial), communications and remote body lander or flyby/reconnaissance uses. The specific hardware concept used to demonstrate feasibility and validate the new methodology is directly applicable to the latter class of missions.

Name and Address of Offeror:

SSG, Inc.
150 Bear Hill Road
Waltham, MA 02154