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

Roll performance assessment of a light aircraft: Flight simulations and flight tests

2018 ◽  
Vol 76 ◽  
pp. 471-483 ◽  
Author(s):  
Fabrizio Nicolosi ◽  
Agostino De Marco ◽  
Vito Sabetta ◽  
Pierluigi Della Vecchia
Keyword(s):  
Performance Assessment ◽  
Flight Tests ◽  
Aircraft Flight ◽  
Flight Simulations

scholarly journals IMUMETER—A Convolution Neural Network-Based Sensor for Measurement of Aircraft Ground Performance

Sensors ◽  
2021 ◽  
Vol 21 (14) ◽  
pp. 4726
Author(s):  
Jarosław Pytka ◽  
Piotr Budzyński ◽  
Paweł Tomiło ◽  
Joanna Michałowska ◽  
Ernest Gnapowski ◽  
...  
Keyword(s):  
Neural Network ◽  
Artificial Intelligence ◽  
Convolution Neural Network ◽  
Flight Tests ◽  
Motion Measurement ◽  
Aircraft Flight ◽  
Acceleration Data ◽  
Measurement Results ◽  
Measurement And Analysis ◽  
Ground Distance

The paper presents the development of the IMUMETER sensor, designed to study the dynamics of aircraft movement, in particular, to measure the ground performance of the aircraft. A motivation of this study was to develop a sensor capable of airplane motion measurement, especially for airfield performance, takeoff and landing. The IMUMETER sensor was designed on the basis of the method of artificial neural networks. The use of a neural network is justified by the fact that the automation of the measurement of the airplane’s ground distance during landing based on acceleration data is possible thanks to the recognition of the touchdown and stopping points, using artificial intelligence. The hardware is based on a single-board computer that works with the inertial navigation platform and a satellite navigation sensor. In the development of the IMUMETER device, original software solutions were developed and tested. The paper describes the development of the Convolution Neural Network, including the learning process based on the measurement results during flight tests of the PZL 104 Wilga 35A aircraft. The ground distance of the test airplane during landing on a grass runway was calculated using the developed neural network model. Additionally included are exemplary measurements of the landing distance of the test airplane during landing on a grass runway. The results obtained in this study can be useful in the development of artificial intelligence-based sensors, especially those for the measurement and analysis of aircraft flight dynamics.

High altitude aircraft flight tests

1996 ◽  
Author(s):  
Henry Helmken ◽  
Peter Emmons ◽  
David Homeyer
Keyword(s):  
High Altitude ◽  
Flight Tests ◽  
Aircraft Flight

On Aerodynamic Modelling and Simulation of the Dynamic Interface

2005 ◽  
Vol 219 (5) ◽  
pp. 393-410 ◽  
Author(s):  
S J Zan
Keyword(s):  
Flight Simulation ◽  
Modelling And Simulation ◽  
Flight Tests ◽  
Simulation Fidelity ◽  
The Past ◽  
Lighting Conditions ◽  
Dynamic Interface ◽  
Flight Envelope ◽  
Initial Work ◽  
Aerodynamic Modelling

The past decade has seen significant advancements in modelling and simulation of the dynamic interface. The goal of the initial work in this area was to reduce the costs associated with first-of-class flight trials, and to deal with the backlog of aircraft-ship combinations for which flight-clearance envelopes were minimal or non-existent. A decade ago, piloted simulation of the dynamic interface appeared to be the obvious way to overcome these deficiencies. Validated models of fixed-wing and rotorcraft were in existence, and work began to combine these models with prescribed weather/lighting conditions (wind, rain, snow, fog, night, etc.), ship visuals, and motion. It had been envisioned that through the use of high-fidelity flight simulation, a test pilot could rapidly and safely determine the flight envelope boundaries without resorting to, or at least minimizing, flight trials. During the past decade, significant advancements in simulation fidelity did transpire due to increased computational power, an improved understanding of airwakes, and enhanced simulation capabilities. The article describes some of the fundamental and applied research that contributed to the improved fidelity, much of it gained in a collaborative fashion. To date, modelling and simulation technologies have not advanced to the state where they can replace flight tests to derive flight-clearance envelopes, but they have approached the point where they can augment flight tests and serve in a training capacity. The accrual of a training benefit has recently emerged and is a significant, though unplanned, dividend from the efforts directed towards flight-envelope prediction. This article sets out to examine some of the strengths and deficiencies of the current capabilities, and provides a discussion of the way forward. Modelling and simulation of the dynamic interface are discussed in a broad context, wherein they are defined to include non-piloted, non-real-time activities. The article will provide a critical review of many of these efforts to date, focusing primarily on aerodynamic issues. The article also discusses the challenges which are present for rotary-wing operations, for both small and large ships. It compares the environment in both cases and how that impacts the simulation requirements.

Flight tests and flight data analysis - teaching aerospace engineering students

2016 ◽  
Vol 6 (2) ◽  
pp. 136
Author(s):  
Grzegorz Kopecki
Keyword(s):  
Mathematical Model ◽  
Data Analysis ◽  
Engineering Students ◽  
Low Cost ◽  
Aerospace Engineering ◽  
Flight Tests ◽  
High Class ◽  
Flight Data ◽  
Aircraft Flight ◽  
The Mathematical Model

The ability to carry out in-flight tests and to analyse the flight data registered is, in the case of aerospace engineering  students, a vital aspect of education. Since aircraft flight tests are very expensive, frequently the funds allocated to them in the process of education are insufficient. The aim of this article is to present a relatively low-cost method of training students to carry out flight tests and to analyse flight data. The method relies on three consecutive steps. At first, simulation tests relying on the mathematical model of an aircraft are carried out.  During these simulations, students analyse aircraft behaviour. Next, flight data registered during previously held in-flight tests are analysed.  Finally, flight tests are performed by students.  As a result, having mastered the ability to analyse real flight data, the students trained will become high-class specialists being able to conduct flight tests and analyse flight data.

Extending FMCS Test for Flight Simulation

2011 ◽  
Vol 88-89 ◽  
pp. 72-76
Author(s):  
Zhao Hui Li ◽  
Gang Li
Keyword(s):  
Digital Simulation ◽  
Flight Simulation ◽  
Flight Tests ◽  
Large Matrix ◽  
Special Domain ◽  
Simulation Results

By means of a simulator we could expand the test research scope which could not be reached with flight tests, and recover and repeat some special domain of the test course, and make many kinds of experiments about FMCS properties, functions and with embedded failures by combining simulation tests with practical structure. The reliability and creditability of simulation results could be increased under real FMCS in conjunction with semi-entity simulation. Simulators combining a real FMCS with digital simulation have been used extensively for evaluating the large matrix of FMCS contents.

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.

Measuring and Recording Systems Used in Flight Tests of Aircraft

2011 ◽  
Vol 180 ◽  
pp. 222-231 ◽  
Author(s):  
Mirosław Nowakowski
Keyword(s):  
Flight Dynamics ◽  
Armed Forces ◽  
Design Parameters ◽  
Physical Parameters ◽  
Flight Tests ◽  
Technical Parameters ◽  
Aircraft Flight ◽  
Tests And Measurements ◽  
Measuring Devices ◽  
Experimental Apparatus

Flight tests and measurements are usually performed for newly built or modernised aircraft utilised by the Polish Armed Forces. In the course of flight tests the airborne equipment is also investigated. The main goal of the performed tests is to verify tactical performance and to identify technical parameters of aircraft and/or equipment under examination. The airborne experimental data is also applied to the aircraft flight dynamics modelling, subsequently used for the design and construction of a flight simulator. The equipment is usually arranged of the following components: ̶ sensors/measuring devices capable of converting physical parameters into optical, mechanical, or electrical signals (indicators, transmitters, sensors, transducers); ̶ conditioning systems - intermediary devices used to amplify and/or adjust any signal gained to some required value or form; ̶ recording and storing devices (data recorders, cameras, etc.); ̶ devices applied to the decoding and processing of the acquired data (decoders, computers). Some selected problems of aircraft flight tests will be discussed in the paper. A brief description of the applied experimental apparatus will be provided first. Next, the attention will be focused on the experimentally gathered data utilised in the identification of aircraft flight dynamics characteristics and on the data applied to the evaluation of selected design parameters.

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