NASA SBIR 2014 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 14-2 Z20.01-8807
PHASE 1 CONTRACT NUMBER: NNX14CC99P
SUBTOPIC TITLE: Deep Space Cubesat Technology
PROPOSAL TITLE: LunarCube for Deep Space Missions

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Busek Company, Inc.
11 Tech Circle
Natick, MA 01760 - 1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael Tsay
mtsay@busek.com
11 Tech Circle
Natick, MA 01760 - 1023
(508) 655-5565

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Judy Budny
judy@busek.com
11 Tech Circle
Natick, MA 01760 - 1023
(508) 655-5565

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

Technology Available (TAV) Subtopics
Deep Space Cubesat Technology is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Busek, in partnership with Morehead State University (MSU), proposes to develop a versatile 6U CubeSat capable of reaching a lunar orbit from GEO. The primary objective of the Phase II effort is to demonstrate a complete, mini ion propulsion system that provides ~3000sec Isp heretofore unavailable to CubeSats, with a solid-storable iodine propellant. This type of propulsion technology would be a huge mission enabler and ideal for volume-limited satellites such as CubeSats. The 6U bus, combined with ion propulsion, has already shown being highly attractive to science payload developers targeting the upcoming SLS/EM-1 lunar mission.

During Phase I Busek successfully demonstrated the world's first iodine-fueled gridded ion thruster "BIT-3". Key performance characteristics of BIT-3 include a compact design envelope (<2U volume), nominal 60W consumption, highly-throttleable thrust of ~1.4mN, and Isp up to 3200sec (nearly identical as with xenon). BIT-3 has a unique advantage of being iodine-compatible due to its plasma generation mechanism and construction material. The ability to use iodine as propellant is a true game-changer for CubeSat propulsion, because iodine can be stored as a dense solid (at 4.9g/cc) and its sub-Torr storage pressure enables very lightweight, even plastic tanks. With a mere 300cc iodine tank onboard, the BIT-3 thruster is capable of providing >2.8km/s delta-V to a 6U/12kg CubeSat.

The ultimate goal of the LunarCube program is to undertake a mission to the Moon from GEO or a translunar trajectory (such as the EM-1 drop-off) that would demonstrate the propulsion system, and carry out a lunar science program as a capability demonstration of the platform. During this mission, a related goal is to demonstrate that much of the spacecraft's miniature electronics, primarily C&DH, communications, and the propulsion system's PPU can be based on low cost components and survive the harsh deep-space environment.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The high-Isp ion propulsion, in addition to the low-cost radiation tolerant electronics needed for the lunar mission, is crucial for future deep space missions. Exploring our solar system with low-cost robotic/scout vehicles as precursors for human missions or science missions will benefit from these technologies. Busek's revolutionary iodine RF ion thruster enables small satellites to fly beyond earth orbit and can be used in close proximity operations. Potential NASA applications include missions to the moon (such as the upcoming EM-1 mission), inner planets and asteroids. Additionally, this mini ion propulsion system is ideal for drag make-up applications for earth observation (EO) missions from low flying platforms, down to altitudes of ~200km. Altitude reduction is essential for high resolution EO from small, low-cost satellites that are by definition unsuitable for large optical or RF apertures and thus lower altitude is the only option for higher image resolution.

Potential post applications of MSU's multi-band communications systems include productization and marketing to the small satellite community for a variety of applications in LEO and beyond. The capabilities and flexibility of this system (software controlled frequency agility and controllable, variable power output combined with a variety of modulation schemes) combined with an extremely low price point will make the system attractive to small satellite developers supported by NASA.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The market size for the LunarCube's iodine ion propulsion system is very large. Potential non-NASA customers include commercial human exploration and presence in space, commercial asteroid missions, DoD and commercial EO missions. Busek has already received significant interest from science and commercial missions including lunar exploration, asteroid prospecting, etc. NRO has also indicated interest in this propulsion technology for stationkeeping LEO spacecraft.

MSU's LunarCube C&DH system will also be ultimately produced for both the small satellite and UAV markets. The small size, low power consumption and significant processing capabilities combined with low cost and expandability, will make this C&DH system competitive in these markets.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Fuels/Propellants
Navigation & Guidance
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Spacecraft Main Engine

Form Generated on 11-25-15 23:55