SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS

A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 25 - DECEMBER 16, 2005

07 AIRCRAFT PROPULSION AND POWER
Includes primary propulsion systems and related systems and components, e.g., gas turbine engines, compressors, and fuel systems; and onboard auxiliary power plants for aircraft.

For related information see also 20 Spacecraft Propulsion and Power28 Propellants and Fuels; and 44 Energy Production and Conversion.

20050241829 Air Force Research Lab., Edwards AFB, CA USA

The Case for Small Spacecraft: An Integrated Perspective on Electric Propulsion

Barnhart, D.; Wojnar, R.; Tilley, D.; Spores, R.; Jan. 1, 1995; 13 pp.; In English Contract(s)/Grant(s): Proj-2308 Report No.(s): AD-A438994; IEPC-95-148; No Copyright; Avail.: CASI: A03, Hardcopy

As economies of scale were reduced in commercial and military endeavors, and with the international climate trending toward cooperation and stabilization, the aerospace industry today has taken a decided turn toward decreasing expenditures. This reduction in funding has challenged project managers and engineers to reduce the overall size of spacecraft while still accomplishing the same or similar tasks as larger spacecraft. Solutions to reconnaissance, environmental monitoring, and ground imaging are flow currently being demonstrated by small satellites. Physical reductions in the sire of overall spacecraft have been accompanied by reductions in subsystems and components. All manor of subsystems including propulsion, command and data handling, telemetry and electrical power must respond to the sire challenge of smaller mass and volumetric requirements. This applies equally to electric propulsion. Overall power requirements for a small satellite can be considered between 100-300 Watts for LEO/GEO/ missions, and between 300-650 Watts for long duration missions. This paper will discuss the small satellite paradigm shift, unique approaches to electric propulsion integration into small satellite architectures, and develop a sample mission that focuses on enabling one of the emerging markets' for small satellites using electric propulsion as the performance-merit enhancer. DTIC

Electric Propulsion; Aerospace Industry; Economy; Imaging Techniques

20050243001 Naval Postgraduate School, Monterey, CA USA

Improved Aerothermodynamic Measurements of the T63-A-700 Gas Turbine Engine

Garrott, Kristine B.; Sep. 1, 2005; 77 pp.; In English; Original contains color illustrations Report No.(s): AD-A439420; No Copyright; Avail.: CASI: A05, Hardcopy

This thesis contains an analysis of the failure of the instrumentation ring for measuring the combustor exit temperature and total pressure in the T63-A-700 gas turbine engine. An improved ring design has been constructed and installed. Extensions to the exhaust stacks have been installed to keep the cell temperature reasonable. A water-cooled heat exchanger was installed in place of an air-cooled heat exchanger that was not adequately cooling the oil temperature while running the engine. In the program GASTURB, a compressor map with data from the manufacturer was created and an operating line from three separate speeds was plotted. DTIC

Aerothermodynamics; Gas Turbine Engines; Gas Turbines

Source: NASA.