SBIR-STTR Award

Problem: Provide lightweight on board capability installed in heavy aircraft to generate 1000KVA electricity and 800lbsm/min of pressurized air at 50psia. Fuel cell technology is insufficiently mature for this purpose. System options: 1). Single turbo shaft engine/generator(s) combined with load compressor(s) sized to requirements. 2). Multiple turbo shaft engines (2 or more) driving synchronized generators and load compressors sized to requirements. 3). Multiple light weight (2 or more) turbo shaft engines with supplemented airflow at altitude (supercharged) driving synchronized generators and load compressors sized to requirements. 4). Integrated single shaft engine generator(s) as represented by SAE Paper 981281coupled with single or multiple load compressor(s). Each option includes: 1). Analysis and selection of optimum generators matched to available shaft power. 2). Develop methodologies for mating generator(s) and load compressor(s) to selected engines. 3). System integration and packaging i.e. enclosures, ducting, control system, fire suppression etc. and provision for delivering electrical power and pressurized air to the aircraft systems. 4). Weight reduction by modifying aircraft system components. Best value candidate(s) will be identified during first month. Research activity at SDII is underway. Best value candidate(s) concepts refined and developed during balance of Phase I. Anticipated

Benefits:
The technologies developed will provide an independent dedicated source of electric power and pressurized air for aircraft systems whether the aircraft itself is on the ground or airborne. The components of the system to be developed for continuous operation can be optimized for maximum efficiency. A separate system for electric power and pressurized air adds to overall aircraft system redundancy-enhancing safety. Aircraft performance increases, if only minimally, when main engines are utilized only for flight propulsion. No power drain for electricity and pressurized air. Certain military aircraft have requirements for electricity and pressurized air, which cannot be reasonably met by adding generators to main engines or allocating engine power to "bleed air". The proliferation of equipment and appliances added to aircraft require dedicated sources of electricity and pressurized air for safety and reliability, particularly in twin-engine airplanes.

Potential Commercial Applications:
Certain military aircraft with extraordinary requirements for electricity and pressurized air will use this technology. Commercial and military aircraft in development with their increasing needs for electric power and pressurized air to operate installed, on board, equipment can effectively utilize dedicated source for electricity and pressurized air independent of main engines. The equipment being developed by this program can be scaled up or down to provide an efficient supply of electric power and pressurized air to fit a variety of aircraft. As discussed elsewhere herein, SDII views the commercial requirements for this technology to be an emerging market, which SDII, with its past history, is particularly well equipped to exploit.

SDII continually seeks, identifies, and examines available market sources to refine its own technologies for innovative solutions for large platform aircraft systems growing power and cooling needs. SDII Engineering is in the process of developing Supplemental Power System, spirally configured, which adapts a single turbo shaft engine/generator(s) combined with load compressor(s) driving single/dual large or multiple smaller synchronized generators and load compressors, to produce large amounts of electrical power, 1mGW or larger, and compressed air, 800lbm/min @50psia, for cooling and aircraft engine starting. Preliminary design options include: 1) Analysis and selection of optimum generator(s) matched to available shaft power, 2) Methodologies for mating generator(s) and load compressor(s) to selected power plant, 3) System integration and packaging i.e. enclosures, ducting, control system, fire detection and suppression, and provision for delivering electrical power and pressurized air to Mission package and, 4) Weight reduction without compromising redundancy by eliminating or modifying system components. Designs will conform to established best value system configuration and will apply to military or civilian large platform aircraft requiring additional power and air to supplement or replace the platform systems without compromising weight, volume and acoustic considerations.

Keywords:
Apu - Auxiliary Power Unit, Sps - Supplemental Power System, Seps - Supp Electric Power System, Electric Power, Generator, Bleed Air, Cooling Ai