scholarly journals 1/20 scale model pump test program: preliminary test plan

1977 ◽  
Author(s):  
P. W. Runstadler, Jr.
Keyword(s):  
Preliminary Test ◽  
Scale Model ◽  
Test Plan ◽  
Test Program ◽  
Pump Test

Overview of the Ares I scale model test program

2011 ◽  
Vol 130 (4) ◽  
pp. 2542-2542
Author(s):  
Douglas D. Counter ◽  
Janice Houstion
Keyword(s):  
Model Test ◽  
Scale Model ◽  
Test Program ◽  
Ares I

STOVL Hot Gas Ingestion Control Technology

1989 ◽  
Author(s):  
K. C. Amuedo ◽  
B. R. Williams ◽  
J. D. Flood ◽  
A. L. Johns
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Scale Model ◽  
Nasa Lewis Research ◽  
Control Technology ◽  
Test Program ◽  
Hot Gas ◽  
Vertical Landing ◽  
Low Speed Wind Tunnel ◽  
Face Temperature

A comprehensive wind tunnel test program was conducted to evaluate control of Hot Gas Ingestion (HGI) on a 9.2% scale model of the McDonnell Aircraft Company model 279-3C advanced Short Takeoff and Vertical Landing (STOVL) configuration. The test was conducted in the NASA-Lewis Research Center 9 foot by 15 foot Low Speed Wind Tunnel during the summer of 1987. Initial tests defined baseline HGI levels as determined by engine face temperature rise and temperature distortion. Subsequent testing was conducted to parametrically evaluate HGI control using: Lift Improvement Devices (LIDs), forward nozzle splay angle, combination of LIDs and forward nozzle splay angle, and main inlet blocking. The results from this test program demonstrate that HGI can be effectively controlled and that HGI is not a barrier to STOVL aircraft development.

Reactor Coolant Pump Flywheel Overspeed Evaluation

1974 ◽  
Vol 96 (4) ◽  
pp. 279-285 ◽  
Author(s):  
P. C. Riccardella ◽  
W. H. Bamford
Keyword(s):  
Fracture Mechanics ◽  
Ductile Failure ◽  
Light Water Reactor ◽  
Scale Model ◽  
Intensity Factors ◽  
Test Program ◽  
Primary Coolant ◽  
Coolant Pump ◽  
Reactor Primary Coolant ◽  
Experimental Effort

The overspeed capability of the large steel flywheels used on light water reactor primary coolant pumps has been evaluated through a combined analytical and experimental effort. Limiting speeds of the prototype flywheel design were calculated for the ductile failure mode using the principles of Section III of the ASME Boiler and Pressure Vessel Code, and for the brittle fracture mode using a fracture mechanics approach in which stress intensity factors were determined from finite element computer analysis. The accuracy of the analytical approach was verified by a scale model test program which demonstrates excellent agreement between experiment and analysis. The results of the evaluation are presented in this paper, and they illustrate the kinds of things which can be accomplished through application of modern fracture mechanics technology, including plasticity considerations, to the solution of hardware problems of real engineering interest.

scholarly journals Artificial Neural Networks as Applied to Aircraft Flight Test Planning / Wykorzystanie Sztucznych Sieci Neuronowych W Planowaniu Badań W Locie

2012 ◽  
Vol 21 (1) ◽  
pp. 149-162
Author(s):  
Mirosław Zieja ◽  
Joanna Wójcik
Keyword(s):  
Neural Network ◽  
Artificial Neural Network ◽  
Flight Test ◽  
Test Plan ◽  
Military Aircraft ◽  
Test Program ◽  
Aircraft Flight ◽  
Artificial Neural ◽  
Artificial Neural Network Ann ◽  
The Military

Abstract Any flight test programme is essentially based on a flight test plan, i.e. a document agreed upon and accepted by all the parties interested in the tests, and authorised by the superior body/authorities responsible for the execution of the tests. The flight test plan determines the number of flights and flight hours indispensable to verify whether a given aircraft satisfies specified requirements. Many and various external factors may have significant and adverse effect on the execution of the flight test program according to the earlier agreed schedule. The study also covers the structure of a model of a management system for aircraft prototype testing, and the structure of artificial neural network (ANN) developed on the basis of experimentally gained data from the military aircraft testing. A mathematical model based on the artificial neural network and its potential for the managing of aircraft prototypes testing has been formulated as well.

Unit Cell Sparger Test Program and Preliminary Test Results for APR1400

2002 ◽  
Author(s):  
Choon-Kyung Park ◽  
Seok Cho ◽  
Chul-Hwa Song ◽  
Se-Young Chun
Keyword(s):  
Preliminary Test ◽  
Test Results ◽  
Test Program ◽  
Flow Area ◽  
Water Level Variation ◽  
Air Bubble ◽  
Discharge Line ◽  
Test Parameters ◽  
Hydraulic Load ◽  
Valve Opening

KAERI has performed a series of blowdown tests to assess the performance of prototypic steam sparger which will be used in a APR1400 reactor. The test program consists of 22 blowdown tests and each test simulates air clearing phase during an opening of depressurization valves. The major test parameters include air mass in the discharge line, air temperature, flow area, valve opening time, IRWST water temperature, and submergence of a sparger. The CPT-3 test was conducted for typical PWR condition. Following valve actuation, the pressure within the discharge line underwent pressure transient and the discharged high pressure air formed air bubbles, which expanded and compressed periodically in the simulated IRWST. Loop behavior as well as hydraulic load caused by air bubble oscillation during the air clearing phase were described. In addition, water level variation in the sparger during operation of a vacuum breaker was also discussed.

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