The effects of orthogonality error in aircraft flight simulation

2001 ◽  
Author(s):  
W. Phillips ◽  
C. Hailey ◽  
G. Gebert
Keyword(s):  
Flight Simulation ◽  
Aircraft Flight

Fundamental and Practical Aspects of Crack Growth under Corrosion Fatigue Conditions

1977 ◽  
Vol 191 (1) ◽  
pp. 107-114 ◽  
Author(s):  
J. Schijve
Keyword(s):  
Crack Growth ◽  
Aluminium Alloys ◽  
Relevant Information ◽  
Flight Simulation ◽  
Shear Mode ◽  
Load Spectrum ◽  
Aircraft Flight ◽  
Cracking Modes ◽  
Crack Growth Mechanism ◽  
High Level

The crack growth mechanism is dependent on environment, frequency and temperature as shown by some examples. Two cracking modes are observed in aluminium alloys: the tensile mode and the shear mode. Examples show that inert environments promote the shear mode whereas aggressive environments promote the tensile mode. Information from constant-amplitude tests need not be applicable to service loading conditions as illustrated by an example. Significant environmental effects on crack growths are observed in aircraft flight-simulation tests. Growth delays induced by severe flights occur in all environments. As a consequence the truncation of the load spectrum at the high level end is a difficult question. The problem of producing relevant information in the laboratory is discussed.

Roll performance assessment of a light aircraft: flight tests and flight simulation

2015 ◽  
Author(s):  
Fabrizio Nicolosi ◽  
Agostino De Marco ◽  
Vito Sabetta ◽  
Pierluigi Della Vecchia
Keyword(s):  
Performance Assessment ◽  
Flight Simulation ◽  
Flight Tests ◽  
Aircraft Flight

scholarly journals Mathematical Models for Human Pilot Maneuvers in Aircraft Flight Simulation

2009 ◽  
Author(s):  
Yan Zhang ◽  
Seamus McGovern
Keyword(s):  
Mathematical Models ◽  
Automatic Control ◽  
Pid Controller ◽  
Flight Simulation ◽  
High Fidelity ◽  
Proportional Integral Derivative ◽  
Vertical Control ◽  
Aircraft Flight ◽  
Pilot Model ◽  
Simulation Input

Mathematical models are presented in this paper to describe human maneuvers for aircraft flight simulation. Input parameters for the human pilot model (HPM), such as the course deviation indicator (CDI) and the heading change, are defined for the model, and are related mathematically to those in the proportional-integral-derivative (PID) controller for automatic control. Similarities are discussed between the parameters in HPM and those in the automatic control for better understanding of the significance of human factors and their effect on aircraft behavior. Examples for the HPM include aircraft instrument landing system (ILS) lateral and vertical control, heading change, and homing. The model is tested by using the high-fidelity flight simulation simulator JSBSim [1].

Hardware-in-the-loop flight motion simulation of flexible variable sweep aircraft

2018 ◽  
Vol 90 (9) ◽  
pp. 1428-1437 ◽  
Author(s):  
Irum Inayat ◽  
Rooh ul Amin ◽  
Malik Mazhar Ali
Keyword(s):  
Cost Effective ◽  
Flight Simulation ◽  
Hardware In The Loop ◽  
Motion Simulation ◽  
Computationally Efficient ◽  
Motion Platform ◽  
Flexible Aircraft ◽  
Content Type ◽  
Aircraft Flight ◽  
Washout Filter

Purpose This paper aims to propose an improved and computationally efficient motion simulation of a flexible variable sweep aircraft. Design/methodology/approach The motion simulation is performed on hardware-in-the-loop simulation setup using 6 degree-of-freedom motion platform. The dynamic model of a flexible variable sweep aircraft, Rockwell B-1 Lancer is presented using equations of motions for combined rigid and flexible motions. The peak filter is introduced as a new method to separate flexible motion from aircraft motion data. Standard adaptive washout filter is modified and redesigned for an accurate flexible aircraft flight simulation. The flight data are generated using FlightGear software. Another motion profile with significant oscillations is also tested. The peak filter and the modified adaptive washout filter both are used to process the data according to the motion envelop of motion platform. Findings The performance of the modified adaptive washout filter is evaluated using hardware-in-the-loop simulation setup and results are compared with the standard adaptive washout filter. Results exhibit that the proposed method is computationally cost-effective and improves the motion simulation of flexible aircraft with close to realistic motion cues. Originality/value The proposed work presents motion simulation of a flexible aircraft by introducing a peak filter to extract flexible motion in contrast to the traditional motion separation methods. Also, a modified adaptive washout filter is designed and implemented in place of the traditional washout filters for improved flexible aircraft flight motion simulation.

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