Computer Operations

Three types of test control systems are employed to meet specific test requirements.  Three HP9000 are networked with HP VXI-based data acquisition and test control hardware to meet current DOD test system requirements for on-the-fly data display.  Six Hewlett-Packard HP1000 A-series computer systems with HP 2250 Measurement and Control Units are available for use on both full-scale static and durability tests, and smaller component and subsystem tests.  These systems are networked with the Vought Aircraft LAN providing the capability for data transmittal to customer computer systems in a variety of formats.  Twelve Hewlett-Packard HP9000 computer systems with HP3852 Data Acquisition/Control Units are available for test support on smaller tests.  These modular systems are easily configured to support tests at the various facilities within Test Operations.

Highly skilled engineers design and implement product-specific software for computerized data acquisition and testing.  Application software to support the test control systems is routinely designed to meet specific testing needs.  Software for test control, data acquisition, and processing has been developed and proven by many hours of daily operation leading to the successful completion of test programs including:

• B-1 Wing Outer Panel, Pivot Joint, Wing Center Section Durability Test Program
• TA-3B Douglas Skywarrior Full-Scale Wing-Fuselage Fatigue Test Program
• EA-6B Full-Scale Wing-Fuselage Fatigue Test Program
• EKA-3B Douglas Skywarrior Full-Scale Wing-Fuselage Fatigue Test Program
• F-14 Full-Scale Wing Outer Panel/Pivot Joint Fatigue/SLEP Test Programs
• C-17 Horizontal Stabilizer Full-Scale Static and Durability Tests
• C-17 Nacelle Static Test
• C-17 Composite Horizontal Stabilizer Full-Scale Static Test
• F/A-18E/F Wing Panel Fatigue/Damage Tolerance/Residual Strength Tests
• Thermomechanical Randomized Fatigue Testing for Advanced Technology Structures

Test data is monitored for indications of strain variations during testing which might indicate structural failure and load path change.   Acquired data is compared to baseline data and will inform test personnel should deviations occur.

For more information please contact:

John Vaught
e-mail: john_vaught@voughtaircraft.com