NASA Scientific and Technical Aerospace Reports

Science missions with the ability to operate in vacuum or in an atmosphere such as on Mars. High efficiency is obtained
through the use of free-piston Stirling power conversion. Power output will be greater than 100 watts at the beginning of life
with the decline in power largely due to the decay of the plutonium heat source. In support of the DOE SRG project, the NASA
Glenn Research Center (GRC) has established a technology effort to provide data to ensure a successful transition to flight
for what will be the first dynamic power system in space. Initially, a limited number of areas were selected for the effort,
however this is now being expanded to more thoroughly cover key technical issues. There is also an advanced technology
effort that is complementary to the near-term technology effort. Many of the tests use the 55-We Technology Demonstration
Convertor (TDC). There have been multiple controller tests to support the LMA flight controller design effort. Preparation is
continuing for a thermal/vacuum system demonstration. A pair of flight prototype TDC s have been placed on continuous
operation. Heater head life assessment continues, with the material data being refined and the analysis moving toward the
system perspective. Magnet aging tests continue to characterize any possible aging in the strength or demagnetization
resistance of the magnets in the linear alternator. A reliability effort has been initiated to help guide the development activities
with focus on the key components and subsystems. This paper will provide an overview of some of the GRC technical efforts,
including the status, and a description of future efforts.
Author
Radioisotope Batteries; Generators; Heat Sources; Stirling Cycle; Transition Flight
20040073693 Air Force Research Lab., Edwards AFB, CA
Ph.D. Research
Beasley, Joe; Holmes, Mike; Apr. 28, 2004; 41 pp.; In English; Original contains color illustrations
Contract(s)/Grant(s): Proj-1011
Report No.(s): AD-A422593; No Copyright; Avail: CASI; A03, Hardcopy
A major requirement for using a solar propulsion system is the proper placement of the focal spot on the thruster absorber
plane. Without proper placement of the focal spot, solar energy is not transferred to the propellant gas or at worst case, a
significantly smaller proportion of the incident energy is transferred to the gas.
DTIC
Solar Energy
20040073774 Maryland Univ., College Park, MD
Small-Scale Propulsion for Jump Augmentation
Lewis, Mark J.; Beksinski, David; White, Peter; Dec. 31, 2001; 20 pp.; In English; Original contains color illustrations
Contract(s)/Grant(s): DAAD19-00-01-0129
Report No.(s): AD-A422725; ARO-41275.1-CH; No Copyright; Avail: CASI; A03, Hardcopy
This program was an examination of the feasibility of providing small-scale propulsion systems to provide power and
propulsion assistance for soldiers, especially to offer a capability for extended vertical leap with heavy combat weights. The
concept under development was the use of multiple small-scale (though not micro) gas turbine engines, capable of providing
thrust levels in the 50-lb range, with engine weights of 5 lbs. The concept was to use these engines to help a soldier jump over
an obstacle, or possibly to produce electrical power with the efficiency of a gas turbine engine. Work on this project proceeded
along two tracks. First, the analysis, testing, and design of a benchmark propulsion pack was performed, culminating in the
development of prototype hardware with gas turbine engines mounted, powered, and coordinated. Various issues related to
their starting and operational characteristics of these engines were explored, as well as practical operational issues associated
with their use in a backpack configuration, including acoustic signature, heating, etc, In the final phase, since the last interim
report, practical issues of engine mounting, starting of multiple engines, and body mounting of the engines were explored.
DTIC
Augmentation; Propulsion; Propulsion System Configurations; Propulsion System Performance
20040074214 NASA Stennis Space Center, Bay Saint Louis, MS, USA
Implementation of Wireless and Intelligent Sensor Technologies in the Propulsion Test Environment
Solano, Wanda M.; Junell, Justin C.; Shumard, Kenneth; July 1, 2003; 5 pp.; In English; SiCon/04 Sensors for Industry
Conference, 27-29 Jan. 2004, New Orleans, LA, USA
Report No.(s): SE-2003-07-00049-SSC; No Copyright; Avail: CASI; A01, Hardcopy
From the first Saturn V rocket booster (S-II-T) testing in 1966 and the routine Space Shuttle Main Engine (SSME) testing
beginning in 1975, to more recent test programs such as the X-33 Aerospike Engine, the Integrated Powerhead Development
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