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20030025272 NASA Goddard Space Flight Center, Greenbelt, MD, USA
A NASA Perspective and Validation and Testing of Design Hardening for the Natural Space Radiation Environment
(GOMAC Tech 03)
Day, John H., Technical Monitor; LaBel, Kenneth A.; Howard, James W.; Carts, Martin A.; Seidleck, Christine; [2003]; 5 pp.;
In English; Government Microcircuit Applications and Critical Technology Conference, 31 Mar. - 3 Apr. 2003, Tampa, FL,
USA; Copyright; Avail: CASI; A01, Hardcopy
With the dearth of dedicated radiation hardened foundries, new and novel techniques are being developed for hardening
designs using non-dedicated foundry services. In this paper, we will discuss the implications of validating these methods for
the natural space radiation environment issues: total ionizing dose (TID) and single event effects (SEE). Topics of discussion
include: Types of tests that are required, Design coverage (i.e., design libraries: do they need validating for each application?)
A new task within NASA to compare existing design. This latter task is a new effort in FY03 utilizing a 8051 microcontroller
core from multiple design hardening developers as a test vehicle to evaluate each mitigative technique.
Author
Aerospace Environments; Extraterrestrial Radiation; Foundries; Design
20030032189 NASA Goddard Space Flight Center, Greenbelt, MD, USA
NASA GSFC Mechanical Engineering Latest Inputs for Verification Standards (GEVS) Updates
Kaufman, Daniel; [2003]; 10 pp.; In English; International Workshop on Test Philosophies, Standards and Methods, 18-19
Mar. 2003, Tourin, Italy; No Copyright; Avail: CASI; A02, Hardcopy
This viewgraph presentation provides information on quality control standards in mechanical engineering. The
presentation addresses safety, structural loads, nonmetallic composite structural elements, bonded structural joints, externally
induced shock, random vibration, acoustic tests, and mechanical function.
CASI
Quality Control; Standards; Mechanical Engineering
20030032198 NASA Glenn Research Center, Cleveland, OH, USA
Advanced Control Surface Seal Development at NASA GRC for 3rd Generation RLV
Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; DeMange, Jeffrey J.; Breen, Daniel P.; November 12, 2002; 20 pp.; In English;
RLV/SOV Airframe Technology Review, 19-22 Nov. 2002, Hampton, VA, USA; Original contains black and white
illustrations; Copyright; Avail: CASI; A03, Hardcopy
NASA’s Glenn Research Center (GRC) is developing advanced control surface seal technologies for the 3rd Generation
RLV program. GRC has designed several new test rigs to simulate the temperatures, pressures, and scrubbing conditions that
seals would have to endure during service. A hot compression test rig and hot scrub test rig are being developed to perform
tests at temperatures up to 3000 F. Another new test rig allows simultaneous seal flow and scrub tests at room temperature
to evaluate changes in seal performance with scrubbing. High temperature ceramic preloading devices are being developed
and evaluated as ways to improve seal resiliency.
Author
Reusable Launch Vehicles; Control Surfaces; Design Analysis; Temperature; Simulation; Pressure; Seals (Stoppers)
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STRUCTURAL MECHANICS
Includes structural element design, analysis and testing; dynamic responses of structures; weight analysis; fatigue and other structural
properties; and mechanical and thermal stresses in structures. For applications see 05 Aircraft Design, Testing and Performance; and
18 Spacecraft Design, Testing and Performance.
20030022740 NASA Glenn Research Center, Cleveland, OH, USA
Plastic Coupling and Stress Relaxation During Nonproportional Axial-Shear Strain-Controlled Loading
Lissenden, Cliff J.; Arnold, Steven M.; Saleeb, Atef F.; Journal of Pressure Vessel Technology; February 08, 2001; 123,
pp. 81-87; In English; Pressure Vessels and Piping Conference, 23-27 Jul. 2000, Seattle, WA, USA
Contract(s)/Grant(s): NCC3-597; Copyright; Avail: Other Sources
A nonproportional strain-controlled load path consisting of two segments was applied to the cobalt-based alloy Haynes
188 at 650 C. The first segment was purely axial; the aria1 strain was then held constant while the shear strain was increased
during the second segment. The alloy exhibited about a 95-percent reduction in axial stress (298 to 15 MPa during shear
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