High Altitude UAV Engine Project, boundary layer turbine, pyro-catalytic chamber, hydrazine, nitromethane, direct combustion, low cost, high altitude UAVs, PNGinc

April 10, 2003

High Altitude UAV Engine Project

From the very beginning of aviation history, man has attempted to fly higher and break altitude records. Along the way he has discovered that atmospheric conditions at altitudes over 10,000 feet are dramatically different than at sea level. In fact, achieving an altitude of 70,000 - 100,000 feet is a monumental task, considering the state of present day engine technology.

In the recent past, aircraft engineers have used a number of technologies to reach these higher altitudes such as modified turbojets, ramjets, and triple-stage turbocharged piston engines. While these costly engines enable operations in these higher altitudes, unmodified turbo/fan jets are limited to a ceiling of around 65,000 feet. In other words, lower-cost, fuel-efficient engines are unable to deliver power at the higher altitude regions.

PNGinc has a couple of low-cost solutions to enable operations in the medium and high altitude regions.

In the medium region (20,000 - 65,000 ft) our designs call for low-cost superchargers on piston engines or direct combustion boundary layer turbines.

For higher altitudes (above 65,000 ft) our concept is to use hydrazine, nitromethane, hydrogen peroxide, etc. in a pyro-catalytic chamber to produce steam in a closed or open loop boundary layer turbine system.

Contact: Ken Rieli

PNGinc Documents

High Altitude UAV Engine Project