An Electric Power Generation System for Launch Vehicles Honeywell International

Format:

Conference/Event

Author/Creator:

Koerner, Mike, author.

Conference Name:

Power Systems Conference (2006-11-07 : New Orleans, Louisiana, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2006

Summary:

Launch vehicles that use electric actuators for thrust vector or flight control require a safe, reliable and lightweight source of electrical power. Honeywell, working with NASA Glenn Research Center and Lockheed Martin Space Systems, has developed and successfully tested a turbine-driven electric power generation system which meets these needs.This Turbine Power Unit (TPU) uses hydrogen and oxygen propellants which react catalytically to drive a shaft-speed turboalternator mounted on foil bearings. A high-reactance permanent-magnet machine (HRPMM) was selected for this application. The power conditioning and control electronics can be located within the TPU housing and the hydrogen fuel can be used to pressurize the bearings and electronics and to regeneratively cool the machine.A brassboard unit incorporating many of these features was successfully tested at output power levels from 0 to 138 kilowatts (kW). The 270 Vdc system was designed to meet the electromagnetic compliance requirements of MIL-STD-461E and the power quality requirements of MIL-STD-704E. Testing included continuous operation at loads up to 80 kW, load transient tests to verify power quality during steps of up to 120 kW at 300 amps/msec, and restart tests with shutdown intervals ranging from a few milliseconds up to 8 minutes. Testing culminated with a successful flight simulation test

Notes:

Vendor supplied data

Publisher Number:

2006-01-3061

Access Restriction:

Restricted for use by site license