SBIR-STTR Award

Spacecraft power systems based upon flywheel technology have been evaluated and analyzed for many years. The potential benefits are well documented and include: Mass and cost savings, System reliability and mission life multiplier, and Electrical Power System enhancement. However, these benefits have not come to fruition due to a few technical challenges, including the extremely high momentum storage (hundreds of Nms!), uncertainty about how to launch the system (spinning or not?), difficulties of integration and test, and the problem of fault scenarios (what if a flywheel fails?) Blue Canyon Technologies has developed an innovative Counter Rotating Flywheel concept with Integrated Power and Attitude Control functionality. The main advantage of our CRFP approach is the ability to simultaneously store enough energy to power a 1kW spacecraft through GEO eclipse, yet manage the net system momentum to a very modest level. The two counter rotating flywheels spin in opposite directions and at different speeds such that the total angular velocity of both rotors stores energy and the difference in rotor angular velocities determines net momentum for attitude control authority.

Benefit:
IPACS benefits to spacecraft providers, are primarily mass and cost savings due to the elimination of batteries. Other benefits include enhanced system reliability and mission life. The market which is addressed by IPACS type systems includes GEO and LEO spacecraft of medium to large size (cubesats and microsats would be too small for the IPACS system as currently architected, although that could change once a system is proven and can be scaled down). The annual launches in this class range from 20 – 30 per year, including NASA, DoD, Classified, and commercial spacecraft. Thus the potential market for this technology is relatively large in the spaceflight market.

Keywords:
Ipacs, Spacecraft Power, Adcs

This project is developing Integrated Power and Attitude Control System (IPACS) to support 15-year Geosynchronous Earth Orbit (GEO) space missions, be capable of supplying a minimum of 1 KW of useable power, provide three-axis stabilization, and operate over a temperature range between -40 and +80 Centigrade. Additional goals include Total Dose tolerance >1 Mrad (Si), Single Event Upset immunity > 60 MeV Blue Canyon Technologies will continue the development of the prototype design from Phase I to meet the full functional requirements, including the capability to provide 1kW of power for a GEO spacecraft. We will build and test a full capability Engineering Development Unit (EDU) IPACS. This EDU will be environmentally tested to achieve TRL-6.

Benefit:
This innovative solution offers spacecraft developers the opportunity to reduce system costs, reduce spacecraft mass and greatly extend the mission life. In addition, IPACS is capable of providing extremely high pulse power, much higher than comparable size and mass batteries can provide.

Keywords:
Spacecraft, Flywheel, Battery, IPACS, Power, Attitude Control, Pulse Power, GEO ---------- The objective of this research is the development and demonstration of a small satellite bus that can operate effectively for up to 3 years in any Earth orbital regime. The satellite must package for launch in a volume that is compatible with common rideshare launch such as the EELV Secondary Payload Adapter (ESPA) and provide support for a suitable electric propulsion system and a government payload for the Space Situational Awareness (SSA) or related missions.