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V-22 Osprey Tilt-Rotor Aircraft

Description: The V-22 Osprey is a tilt-rotor aircraft, capable of vertical or short take-off and landing, with forwarding flight like a conventional fixed-wing aircraft. The MV-22 is the Marine Corps’ top aviation priority. Marine Corps leaders believe that Osprey will provide them an unprecedented capability to quickly and decisively project power from well over the horizon. The Air Force’s CV-22 version will be used for special operations. Army officials have testified that the service has no requirement … more
Date: August 23, 2006
Creator: Bolkcom, Christopher
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
captions transcript

Wings of the Future

Description: This film discusses helicopters and looks at how inventors and innovators like Igor Sikorsky, Juan de la Cierva and Arthur Young helped to make helicopter flight possible.
Date: unknown
Duration: 16 minutes 08 seconds
Item Type: Refine your search to only Video
Partner: UNT Media Library
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Evolution of the Helicopter

Description: Report presenting an investigation of problems related to helicopters. Also included are the history of the evolution of the helicopter and a series of propeller experiments.
Date: March 1923
Creator: Balaban, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Problem of the Helicopter

Description: Report discussing some of the issues regarding the design and operation of helicopters and the theoretical basis behind them. Some particular issues covered include propeller blade design, helicopters in forced descent, horizontal travel, and stability and control.
Date: May 1920
Creator: Warner, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Recent European Developments in Helicopters

Description: Descriptions are given of two captured helicopters, one driven by electric power, the other by a gasoline engine. An account is given of flight tests of the gasoline powered vehicle. After 15 successful flight tests, the gasoline powered vehicle crashed due to the insufficient thrust. Also discussed here are the applications of helicopters for military observations, for meteorological work, and for carrying radio antennas.
Date: April 1921
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Model Tests on the Economy and Effectiveness of Helicopter Propellers

Description: The average velocity of helicopter blades relative to the air is greater than that of airplane wings. The helicopter may turn out to be more economical than the airplane wing for extreme velocities of horizontal flight, the airplane then requiring a very great speed range.
Date: 1925
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Response of a helicopter rotor to oscillatory pitch and throttle movements

Description: Report presenting an analysis of the measurements of drag-angle oscillation of a helicopter rotor made with the helicopter apparatus to determine both the natural frequencies and the damping required to prevent excessive drag-angle-oscillation response to various throttle and control movements. Results regarding symmetrical oscillations, unsymmetrical oscillations, blade damping, and general discussion are provided.
Date: June 1949
Creator: Carpenter, Paul J. & Peitzer, Herbert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An introduction to the physical aspects of helicopter stability

Description: "In order to provide engineers interested in rotating-wing aircraft but with no specialized training in stability theory some understanding of the factors that influence the flying qualities of the helicopter, an explanation is made of both the static stability and the stick-fixed oscillation in hovering and forward flight in terms of fundamental physical qualities. Three significant stability factors - static stability with angle of attack, static stability with speed, and damping due to a pit… more
Date: November 1949
Creator: Gessow, Alfred & Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory of helicopter damping in pitch or roll and a comparison with flight measurements

Description: Report presenting calculations and flight-test measurements on a single-main-rotor helicopter indicate that the damping moment about the helicopter center of gravity produced during pitching or rolling by a rotor which has flapping hinges on the rotor shaft, which depends primarily on four quantities: rotor speed, blade mass factor, height of the rotor hub above the helicopter center of gravity, and the ratio of collective pitch to the thrust coefficient - solidity ratio.
Date: October 1950
Creator: Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Normal Accelerations and Operating Conditions Encountered by a Helicopter in Air-Mail Operations

Description: Note presenting an analysis of the normal accelerations and operating conditions encountered by a single-rotor helicopter engaged in air-mail operations in the vicinity of Los Angeles and its suburbs over a period of 14 months. The results indicate that, for this type of operation, maneuver loads developed in routine flight are often greater than the largest gust loads.
Date: June 1952
Creator: Crim, Almer D. & Hazen, Marlin E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of the Transition of a Helicopter From Hovering to Steady Autorotative Vertical Descent

Description: "This report is the second phase of a broad program of study of the transient motions of helicopters in autorotative flight. The first phase (reference 1) dealt with the steady-state condition of autorotative vertical descent. This report is concerned with the the transition from the steady condition of hovering to the steady autorotative descent" (p. 1).
Date: June 1949
Creator: Nikolsky, A. A. & Seckel, Edward
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Two-dimensional investigation of five related NACA airfoil sections designed for rotating-wing aircraft

Description: Report presenting testing of five NACA airfoil sections intended for use in rotor blades in the two-dimensional low-turbulence tunnel. The airfoils varied in thickness and theoretical design lit coefficients. Results regarding pitching moment, lift, drag, and helicopter performance calculations are provided.
Date: July 1949
Creator: Schaefer, Raymond F.; Loftin, Laurence K., Jr. & Horton, Elmer A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Flight-Performance Measurements on a Twisted, Plywood-Covered Helicopter Rotor in Various Flight Conditions

Description: From Introduction: "In references 1, 2, and 3, flight measurements of the performance of a conventional, single-rotor helicopter equipped with its production fabric-covered main rotor blades are presented."
Date: June 1948
Creator: Gustafson, F. B. & Gessow, Alfred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Theoretical Analysis of Elastic Vibrations of Fixed-Ended and Hinged Helicopter Blades in Hovering and Vertical Flight

Description: Note presenting a theoretical analysis of the frequency and damping characteristics of the free modes of vibrations of balanced fixed-ended and hinged elastic helicopter rotor blades in hovering and vertical flight. Torsional vibrations, bending vibrations in flapping and in lagging, and coupling between the flapping and lagging motions are considered.
Date: January 1950
Creator: Morduchow, Morris
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hovering and Low-Speed Performance and Control Characteristics of an Aerodynamic-Servocontrolled Helicopter Rotor System as Determined on the Langley Helicopter Tower

Description: Report presenting an investigation to obtain basic performance and control characteristics of an aerodynamic-servocontrolled rotor system. Results regarding the hovering performance, low-speed flight performance, control effectiveness, transient response to collective pitch, and transient response to cyclic pitch are provided.
Date: May 1950
Creator: Carpenter, Paul J. & Paulnock, Russell S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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