Stability and Control Augmentation System of "ASKA" National Aerospace Laboratory

Format:

Conference/Event

Author/Creator:

Okada, Noriaki, author.

Conference Name:

SAE International Powered Lift Conference and Exposition (1987-12-07 : Santa Clara, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1987

Summary:

"ASKA" is a STOL airplane with Upper Surface Blown type (USB) flaps used to perform research on powered lift technology developed by the National Aerospace Laboratory (NAL). ASKA has four high bypass ratio turbofan engines mounted above and forward of the wings, hydraulically actuated flight controls, and the Stability and Control Augmentation System (SCAS). The SCAS is a triple redundant system with three digital computers. In order to develop and evaluate its control laws, flight simulator tests have been conducted for 9 years during the design phase. Four flights have been devoted to evaluate functions of the SCAS and the control laws. The significant features of the control laws are to realize satisfactory flying qualities in the deep backside region at low airspeeds. As ASKA has not tested the flights in such regions up to present, this paper includes only the design features of the SCAS control laws, the results of the flight simulator tests, and interim outcomes of the flight tests on shallow USB flap configurations

Notes:

Vendor supplied data

Publisher Number:

872334

Access Restriction:

Restricted for use by site license