The V-22 Fly-By-Wire Digital Flight Control System is arguably the most complex yet attempted. In addition to providing control of the aircraft in its multiple flight modes, (helicopter-conversion-airplane) the V-22 FCS is also required to provide an integrated Thrust / Power Management, aircraft maneuver limiting and navigation coupling.
The V-22 Flight Control System is also unique in its use of dedicated digital data busses as an integral part of the system architecture, and in its use of inertial reference systems as prime stability augmentation sensors. The FCS also incorporates a 5000 psi hydraulic system.
Accordingly, the testing of such a system becomes a very challenging task, especially given the schedule constraints of the V-22 program.
This paper will address the means by which the V-22 Flight Control System was tested prior to first flight, with prime focus being the software verification, hardware-software integration and system validation testing. In addition, a discussion of the regression testing required to revalidate the flight critical system as changes are made during the flight test development program will be addressed.
Citation: Ballauer, W., Leet, J., Mitchell, J., and Eck, D., "Testing of the V-22 Flight Control System," SAE Technical Paper 911107, 1991, https://doi.org/10.4271/911107. Download Citation
Author(s):
Walter L. Ballauer, John R. Leet, James Mitchell, David R. Eck
Affiliated:
Boeing Helicopters Philadelphia, PA
Pages: 16
Event:
Aerospace Atlantic Conference & Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
SAE 1991 Transactions - Aerospace-V100-1
Related Topics:
Flight control systems
Hydraulic systems
Flight tests
Fly-by-wire control systems
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