Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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SPACECRAFT PROPULSION AND POWER
Includes main propulsion systems and components, e.g., rocket engines; and spacecraft auxiliary power sources. For related information,
see also 07 Aircraft Propulsion and Power; 28 Propellants and Fuels; 15 Launch Vehicles and Launch Operations; and 44 Energy
Production and Conversion.
20000063506 NASA Glenn Research Center, Cleveland, OH USA
The Electric Power System of the International Space Station: A Platform for Power Technology Development
Gietl, Eric B., Boeing Co., USA; Gholdston, Edward W., Boeing Co., USA; Manners, Bruce A., NASA Glenn Research Center,
USA; Delventhal, Rex A., NASA Glenn Research Center, USA; June 2000; 12p; In English; Aerospace, 18-25 Mar. 2000, Big
Sky, MT, USA; Sponsored by Institute of Electrical and Electronics Engineers, USA
Contract(s)/Grant(s): RTOP 478-29-10
Report No.(s): NASA/TM-2000-210209; E-12329; NAS 1.15:210209; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche
The electrical power system developed for the International Space Station represents the largest space-based power system
ever designed and, consequently, has driven some key technology aspects and operational challenges. The full U.S.-built system
consists of a 160-Volt dc primary network, and a more tightly regulated 120-Volt dc secondary network. Additionally, the U.S.
system interfaces with the 28-Volt system in the Russian segment. The international nature of the Station has resulted in modular
converters, switchgear, outlet panels, and other components being built by different countries, with the associated interface challenges.
This paper provides details of the architecture and unique hardware developed for the Space Station, and examines the
opportunities it provides for further long-term space power technology development, such as concentrating solar arrays and flywheel
energy storage systems.
Author
Electric Power Supplies; Energy Storage; Space Platforms; Fabrication
20000064686 NASA Marshall Space Flight Center, Huntsville, AL USA
Fastrac Nozzle Design, Performance and Development
Peters, Warren, NASA Marshall Space Flight Center, USA; Rogers, Pat, NASA Marshall Space Flight Center, USA; Lawrence,
Tim, NASA Marshall Space Flight Center, USA; Davis, Darrell, NASA Marshall Space Flight Center, USA; DAgostino, Mark,
NASA Marshall Space Flight Center, USA; Brown, Andy, NASA Marshall Space Flight Center, USA; [2000]; 11p; In English;
36th; Joint Propulsion, 17-19 Jul. 2000, Huntsville, AL, USA; Sponsored by American Inst. of Aeronautics and Astronautics,
USA
Report No.(s): AIAA Paper 2000-3397; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche
With the goal of lowering the cost of payload to orbit, NASA/MSFC (Marshall Space Flight Center) researched ways to
decrease the complexity and cost of an engine system and its components for a small two-stage booster vehicle. The composite
nozzle for this Fastrac Engine was designed, built and tested by MSFC with fabrication support and engineering from Thiokol-
SEHO (Science and Engineering Huntsville Operation). The Fastrac nozzle uses materials, fabrication processes and design features
that are inexpensive, simple and easily manufactured. As the low cost nozzle (and injector) design matured through the
subscale tests and into full scale hot fire testing, X-34 chose the Fastrac engine for the propulsion plant for the X-34. Modifications
were made to nozzle design in order to meet the new flight requirements. The nozzle design has evolved through subscale testing
and manufacturing demonstrations to full CFD (Computational Fluid Dynamics), thermal, thermomechanical and dynamic analysis
and the required component and engine system tests to validate the design. The Fastrac nozzle is now in final development
hot fire testing and has successfully accumulated 66 hot fire tests and 1804 seconds on 18 different nozzles.
Author
Nozzle Design; Injectors; Design Analysis; Engine Design
20000064699 Thiokol Propulsion, Brigham City, UT USA
Internal Flow Analysis of Large L/D Solid Rocket Motors
Laubacher, Brian A., Thiokol Propulsion, USA; [2000]; 12p; In English; 36th; 36th Joint Propulsion Conference, 16-19 Jul. 2000,
Huntsville, AL, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA
Contract(s)/Grant(s): NAS8-38100
Report No.(s): AIAA Paper 2000-3803; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche
Traditionally, Solid Rocket Motor (SRM) internal ballistic performance has been analyzed and predicted with either zero-dimensional
(volume filling) codes or one-dimensional ballistics codes. One dimensional simulation of SRM performance is only