Use of In-Flight Simulation to Create a Flying Qualities Database

2008 ◽  
Author(s):  
David Klyde ◽  
Ryan McMahon ◽  
Norman Weingarten ◽  
Chuck Harris
Keyword(s):  
Flight Simulation ◽  
Flying Qualities

Commercial Transport Aircraft Flight Simulator Flying Qualities Airworthiness Verification

2012 ◽  
Vol 235 ◽  
pp. 170-175 ◽  
Author(s):  
Ya Ni Zhang ◽  
Yan Li ◽  
Ya Kui Gao
Keyword(s):  
Flight Control ◽  
Flight Simulation ◽  
Flight Training ◽  
Flight Simulator ◽  
Wide Field ◽  
Motion Platform ◽  
Transport Aircraft ◽  
Flying Qualities ◽  
Six Degree Of Freedom

Flight simulation is a simulation of flight and various aspects of the flight environment. Flight simulation is used for a variety of reasons, including aircraft development and flight training. The engineering flight simulator is used for a certain commercial transport aircraft development. The aircraft adopts fly-by-wire flight control technology. The engineering flight simulator was mainly used as a platform to test flying quality of the aircraft. The simulator has actual aircraft cockpit with wide-field visual system mounted on large six degree of freedom(DOF) motion platform that feature comprehensive flight and systems models. In order to demonstrate the flying quality of the aircraft, Flying quality verification experiments were carried out on the simulator. This test provided a means by which one may evaluate flight characteristics for fly-by-wire flight control commercial transport aircraft. Experiment results were evaluated .

Helicopter Maneuver Flight Simulation and Control Law Design

2012 ◽  
Vol 232 ◽  
pp. 517-520
Author(s):  
Jing Ying Wang
Keyword(s):  
Design Methodology ◽  
Flight Simulation ◽  
Control Law ◽  
Control Performance ◽  
Flying Qualities ◽  
Attitude Error ◽  
Model Helicopter ◽  
Acceleration Method ◽  
Simulation And Control ◽  
And Control

This paper presents a solution to helicopter maneuver flight simulation according to ADS33 flying qualities requirement standard. Associated with aerodynamics and control law design methodology, the proposed scheme achieved satisfactory control performance by analyzing helicopter attitude and control parameter variation law at certain operating condition. To level flight acceleration, method based on force and moment balance is analyzed. To pirouette maneuver, a segment linear approximated trajectory is developed for attitude and velocity stability. All objective function is based on minimizing position error and attitude error. For a single rotor four bladed model helicopter in pirouette maneuver, experimental results certified its efficiency.

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