3 edition of Initial piloted simulation study of geared flap control for tilt-wing V/STOL aircraft found in the catalog.
Initial piloted simulation study of geared flap control for tilt-wing V/STOL aircraft
by National Aeronautics and Space Administration, Ames Research Center, For sale by the National Technical Information Service in Moffett Field, Calif, [Springfield, Va
Written in English
|Statement||Lourdes M. Guerrero and Lloyd D. Corliss.|
|Series||NASA technical memorandum -- 103872., NASA technical memorandum -- 103872.|
|Contributions||Corliss, Lloyd D., Ames Research Center.|
|The Physical Object|
The Electronic Flap Actuator (/) is an electronic module designed to automatically control an electrical flap actuator and provide visual readout of 3 or 4 flap positions. The device can be used with any electrical actuator providing the operating current is less than 8 amps at 12 volts. Simulated Lyapunov-based backstepping control in hover with initial vehicles. In general, two types of UAVs are produced, remote piloted and self-piloted. Remote piloted UAVs allow an operator to control the vehicle to perform a mission aircraft with the combined STOL and VTOL capabilities. The vehicle can take-o.
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The Stroukoff YC-1 34A was the first large STOL research aircraft flown at NASA’s Ames Research Center. NASA. historian Edwin Hartman wrote in , "BLC was the first practical step toward achieving a V/STOL airplane.” This research had demonstrated the benefits of boundary layer flap-blowing, which eventually was applied to operational high-performance aircraft.. Description. Flaps are a high lift device consisting of a hinged panel or panels mounted on the trailing edge of the wing. When extended, they increase the camber and, in most cases, the chord and surface area of the wing resulting in an increase of both lift and drag and a reduction of the stall factors result in an improvement in takeoff and landing performance.
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A simulation study of a representative tilt-wing V/STOL (VerticaVShort Takeoff and Landing) aircraft was conducted in on the Ames Vertical Motion Simulator Thls simulation was con- ducted because of renewed interest in tilt-wing aircraft for use in several applications including the.
Get this from a library. Initial piloted simulation study of geared flap control for tilt-wing V/STOL aircraft.
[Lourdes M Guerrero; Lloyd D Corliss; Ames Research Center.]. A simulation study of a representative tilt wing transport aircraft was conducted in on the Ames Vertical Motion Simulator. This simulation is in response to renewed interest in the tilt wing concept for use in future military and civil : Lloyd D.
Corliss and Lourdes M. Guerrero. PILOTED SIMULATION STUDY OF TWO TILT-WING CONTROL CONCEPTS LOURDES G. BIRCKELBAW AND LLOYD D. CORLISS Ames Research Center Moffett Field, California Summary A two-phase piloted simulation study was conducted to investigate alternative wing and flap controls for tilt-wing aircraft.
A two phase piloted simulation study has been conducted in the Ames Vertical Motion Simulator to investigate alternative wing and flap controls for tilt-wing aircraft.
This report documents the flying qualities results and. Stingray's List of Rotorcraft-> Stingray's Rotorcraft Forum-> Technical Research-> Initial Piloted Simulation Study of Geared Flap Control for Tilt-Wing V/STOL Aircraft Start A New Topic Reply Subscribe Printer Friendly.
Initial piloted simulation study of geared flap control for tilt-wing V/STOL aircraft For past tilt wing concepts, pitch control in hover and low-speed flight has required a tail rotor or.
The geared flap is a subject of this current study. This report describes the geared flap concept, the tilt wing aircraft, the simulation model, the simulation facility and experiment setup, the. An exploratory simulation study of a novel approach to pitch control for a tilt wing aircraft was conducted in on the NASA-Ames Vertical Motion Simulator.
The first step to growing as a safe and competent pilot is to fully understand how an aircraft works. This includes understanding every part of an airplane, especially its control surfaces and how they affect performance.
Fully comprehending the ways in which various sections of the airplane affect aerodynamics, as well as how the laws of aerodynamics work on the aircraft, is the best way to.
A simulation study was initiated to investigate alternative wing and flap controls for tilt-wing aircraft. The initial phase of the study compared the flying qualities of both a conventional. control for a tilt wing aircraft was conducted in on the NASA-Ames Vertical Motion Simulator.
The purpose of the study was to evaluate and compare the handling qualities of both a conventional and a geared flap tilt wing control configuration. The geared flap is an innovative control concept which has the potential for reducing or eliminating the.
An exploratory simulation study of a novel approach to pitch control for a tilt wing aircraft was conducted in on the NASA-Ames Vertical Motion Simulator. The purpose of the study was to evaluate and compare the handling qualities of both a conventional and. Unconventional aircraft / Peter M.
Bowers Multi-engine piston / David Robson Initial piloted simulation study of geared flap control for tilt-wing V/STOL aircraft [microform] / Lour. A piloted simulation study was initiated at NASA Ames Research Center in response to renewed interest in tilt-wing aircraft for use in several applications including the U.
Special Operations Command aircraft, the U. Air Force. This paper describes a mathematical model of a tilt-wing aircraft that was used in a piloted, six-degree-of-freedom flight simulation application. Two types of control systems developed for the math model are discussed a conventional, programmed-flap wing-tilt control system and a.
The initial data for the airfoil NACA are taken from NACA database , and slotted flap coordinates take into account .
In this study, the simulation of the unsteady flow field around wing with slotted flap configuration has been realized using FLUENT solver. Grid Generation The applied methodology for the execution of the. This paper describes a complete six-degree-of-freedom nonlinear mathematical model of a tilt rotor unmanned aerial vehicle (UAV).
The model is specifically tailored for the design of a hover to forward flight and forward flight to hover transition control system. In that respect, the model includes the aerodynamic effect of propeller-induced airstream which is a function of cruise speed, tilt.
Tilt-wing aircraft offer the best combination of hover capability and cruise efficiency. Tilt-wing aircraft have been successfully tested for many decades. For example, the Canadair CL received positive reviews from over 40 pilots during its intensive test programme in the ’60s and ’70s, including carrier operations in gale storm conditions.
A piloted simulation was performed on the Vertical Motion Simulator at NASA Ames Research Center to evaluate flying qualities of a tilt-wing Short Take-Off and Landing (STOL) transport aircraft during final approach and landing.
V/STOL RESEARCH. As was mentioned in the Introduction, Ames became the center for V/STOL research when the NACA was absorbed into NASA.
This decision was a consequence of Ames' experience with low-speed aircraft flying qualities and of the availability of the by foot wind tunnel for low-speed, full-scale aircraft testing. • Designing a flight control system with automatic gain generation to stabilize the vehicle and meet requirements • Performing simulations to verify the design and visualize the simulation in a realistic 3D environment.
The primary focus is for engineers whose workflow involves modeling, simulation, and control of aircraft.The results of a two-propeller tilt wing aircraft static stability and performance simulation utilizing a NASA Ames computer code, Tilt Wing Application General (TWANG), are presented with comparisons to actua test flight data.
The Canadair CL tilt wing aircraft was used as a model for the geometric data utilized by the computer simulation.