Flight control principles for control configured vehicles /
Edmund G. Rynaski, Norman C. Weingarten.

Description

Main Author

Rynaski, Edmund G.

Related Names

Weingarten, Norman C., author.
United States. Air Force.
Air Force Flight Dynamics Laboratory (U.S.)
Cornell Aeronautical Laboratory

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972.

Subjects

Mathematical models.
Flight control.
Drag (Aerodynamics)
Airplanes > Airplanes / Control systems.
Airplanes > Airplanes / Control surfaces.
Mathematical models.
Drag (Aerodynamics)
Airplanes > Airplanes / Control surfaces.
Flight control.
Airplanes > Airplanes / Control systems.

Summary

The compatibility between maneuver load control, relaxed static stability, and flying qualities requirements is investigated in the report. Three steps were involved in the investigation: an analysis was made of control surface combinations and their effectiveness for maneuver load control when used with an airplane having shortened tail length and reduced tail surface area, control system configurations were synthesized that minimize a weighted measure of change in drag, wing root bending moment, control surface activity and response error between a Level 1 flying qualities model and the actual T-33 airplane; and a direct optimization of the tail length, tail area and control surface deflections required to obtain a compatible compromise of the CCV objectives was performed.

Note

AD0749479 (from http://www.dtic.mil).
"January 1972."

Physical Description

x, 87 pages : illustrations, tables ; 28 cm.

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