Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

20000062846 Defence Science and Technology Organisation, Airframes and Engines Div., Melbourne Australia
Development of a Stress Transfer Function for an Idealised Helicopter Structure
Polanco, Frank G.; Mar. 2000; 74p; In English
Report No.(s): AD-A377442; DSTO-RR-0171; DODA-AR-011-237; No Copyright; Avail: CASI; A04, Hardcopy; A01, Microfiche
This report presents an investigation of the effects that may have an influence on the development of a linear stress transfer
function (STF) relating the stress in dynamic components to the stress in static components. Effects such as buckling, non-uniqueness,
vibration, and solution procedure are considered. Two procedures for determining the STF are compared, one termed the
vector procedure and the other the matrix procedure. A simple two dimensional truss, which models an idealised helicopter structure,
is constructed to numerically simulate the development of a STF. Using random inputs the resulting stresses are evaluated
exactly. Noise is then added to both the input loads and output stresses to develop a noisy data set. Using this noisy data set, STFs
are developed using both the vector and matrix techniques. The vector procedure is shown to be sensitive to collinearity in the
input, while the matrix technique is found to be more stable under the same ill-conditioning.
DTIC
Stress Analysis; Stress Functions; Fracturing; Euler Buckling; Helicopters
20000064011 NASA Dryden Flight Research Center, Edwards, CA USA
The SR-71 Test Bed Aircraft: A Facility for High-Speed Flight Research
Corda, Stephen, NASA Dryden Flight Research Center, USA; Moes, Timothy R., NASA Dryden Flight Research Center, USA;
Mizukami, Masashi, NASA Dryden Flight Research Center, USA; Hass, Neal E., NASA Dryden Flight Research Center, USA;
Jones, Daniel, NASA Dryden Flight Research Center, USA; Monaghan, Richard C., NASA Dryden Flight Research Center, USA;
Ray, Ronald J., NASA Dryden Flight Research Center, USA; Jarvis, Michele L., NASA Dryden Flight Research Center, USA;
Palumbo, Nathan, NASA Dryden Flight Research Center, USA; June 2000; 38p; In English
Contract(s)/Grant(s): RTOP 529-70-14
Report No.(s): NASA/TP-2000-209023; NAS 1.60:209023; H-2405; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche
The SR-71 test bed aircraft is shown to be a unique platform to flight-test large experiments to supersonic Mach numbers.
The test bed hardware mounted on the SR-71 upper fuselage is described. This test bed hardware is composed of a fairing structure
called the ”canoe” and a large ”reflection plane” flat plate for mounting experiments. Total experiment weights, including the
canoe and reflection plane, as heavy as 14,500 lb can be mounted on the aircraft and flight-tested to speeds as fast as Mach 3.2
and altitudes as high as 80,000 ft. A brief description of the SR-71 aircraft is given, including details of the structural modifications
to the fuselage, modifications to the J58 engines to provide increased thrust, and the addition of a research instrumentation system.
Information is presented based on flight data that describes the SR-71 test bed aerodynamics, stability and control, structural and
thermal loads, the canoe internal environment, and reflection plane flow quality. Guidelines for designing SR-71 test bed experiments
are also provided.
Author
SR-71 Aircraft; Flight Tests; Aerodynamic Stability; Test Stands; Fuselages; Structural Design
20000064050 Department of Defense, Office of the Inspector General, Arlington, VA USA
Quick-Reaction Report on the Acquisition of the F-15 Downsized Tester
Jun. 30, 1993; 66p; In English
Report No.(s): AD-A376228; IG/DOD-93-138; No Copyright; Avail: CASI; A01, Microfiche; A04, Hardcopy
The Air Force is procuring an F-15 Downsized Tester (the Tester) to replace existing automatic test equipment for the F-15
aircraft. The Tester will be a portable automatic test equipment system for testing a portion of the electronic equipment on the F-15
aircraft at the intermediate maintenance level. The Tester will initially replace the F-15 Avionics Intermediate Shop test equipment
that has been in operation since 1974. Later the Tester will replace the F-15E Mobile Electronic Test Set used on the F-13E model
aircraft since 1986. The audit was requested by the Director, Weapon Support Improvement Group, Office of the Assistant Secretary
of Defense (Production and Logistics). The Air Force plans to award a contract for 167 million for 55 units of automatic test
equipment over the 6-year Future Years Defense Program (FY 1992 through FY 1997).
DTIC
Electronic Equipment; Portable Equipment; Automatic Test Equipment
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