Temat: flight - Prolib Integro

Skocz do pozycji: 1.

Tytuł:: Identification of the aircraft control basing on the linear and angular accelerations recorder
Autorzy:: Pyrz, J.
Maryniak, J.
Tematy:: flight dynamics
flight control
flight simulation; Pokaż więcej
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Powiązania:: https://bibliotekanauki.pl/articles/279813.pdf Link otwiera się w nowym oknie
Opis:: A method for identification of the aircraft control based on the recorded linear and angular accelerations is presented in the paper. The aircraft accelerations have been calculated by means of numerical simulation of a flight for specified deflections of the control surfaces. these values have been also applied to reconstruction of the manual control. The computations were made for the I-22 IRYDA M93 aircraft.
Wyznaczanie sterowania samolotu na podstawie zarejestrowanych przyspieszeń liniowych i kątowych. W pracy przedstawiono metodę wyznaczania kątów wychyleń powierzchni sterowych oraz sterowania zespołem napędowym na podstawie zarejestrowanych przyspieszeń liniowych i kątowych samolotu. Przyspieszenia działające na samolot zostały wyznaczone w drodze symulacji numerycznej lotu samolotu przy z góry zadanym sterowaniu powierzchniami sterowymi oraz obrotami silnika. Nastepnie, wykorzystując tą samą metodę, przeprowadzono próbę odtworzenia tych sterowań. Obliczenia zostały wykonane na przykładzie samolotu I-22 Iryda M93 jako obiekcie testowym.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Numerical simulation of the aircraft flight after encountering a microburst windshear
Autorzy:: Deptuła, R.
Maryniak, J.
Tematy:: flight dynamics
flight simulation; Pokaż więcej
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Powiązania:: https://bibliotekanauki.pl/articles/280555.pdf Link otwiera się w nowym oknie
Opis:: A physical and mathematical modelling of the microburst effect on aircraft behaviour is presented in the paper. Dynamics equations of the aircraft motion are derived in a plane-fixed co-ordinate system using the Boltzmann-Hamel formalism for material systems with holonomic constraints. The aircraft is treated as a six-degree-of-freedom rigid body. For calculating of aerodynamic forces and moments the rules of quasi-stationary aerodynamics were employed. The windshear velocity field is described by the 3D mathematical Bray' model which was applied basing on the meteorogical data resulting from the Joint Airport Weather Studies Project. The influence of local parameters of the microburst was introduced into the equations of flying object motion in terms of three instananeous linear components of wind velocity and the three angular ones. Computations were made taking the PZL I-22 "Iryda" as a test aircraft.
Symulacja numeryczna lotu samolotu po przejściu przez podmuch typu "microburst". W pracy przedstawiono fizyczne i matematyczne modelowanie wpływu podmuchu microburst na dynamikę samolotu. Dynamiczne równania ruchu obiektu wyprowadzono w układzie sztywno związanym z samolotem, stosując zapis Boltzmanna-Hamela dla układów mechanicznych o więzach holonomicznych. Samolot potraktowano jako bryłę sztywną o sześciu stopniach swobody. Symulację wykonano dla fazy lotu poziomego z trzymanymi sterami. Obliczenia zmian sił aerodynamicznych i momentów sił aerodynamicznych wykonano w oparciu o aerodynamike quasistacjonarną. Pole prędkości podmuchu microburst opisano w pełni trójwymiarowym modelem matematycznym Braya, opracowanym na bazie danych meteorologicznych z projektu badawczego Joint Airport Weather Studies z 1982 roku w USA. Wpływ parametrów lokalnych pola wiatru w równaniach ruchu obiektu latającego uwzględniono przez trzy chwilowe liniowe składowe wektora prędkości podmuchu i trzy chwilowe kątowe składowe tegoż wektora. W pracy przeanalizowano zachowanie się samolotu po przelocie mimośrodowym przez obszar podmuchu dla różnych parametrów charakteryzujących uskok wiatru. Wykazano, że składowa pionowa prędkości wiatru nie musi być wielka, aby zagrozić bezpieczeństwu lotu. Jako samolot testowy wybrano PZL-I 22 "Iryda".
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Flight simulators – from electromechanical analogue computers to modern laboratory of flying
Autorzy:: Zazula, A
Myszor, D.
Antemijczuk, O.
Cyran, K., A.
Tematy:: flight simulator
history of flight simulators
virtual flight laboratory; Pokaż więcej
Wydawca:: Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Powiązania:: https://bibliotekanauki.pl/articles/102023.pdf Link otwiera się w nowym oknie
Opis:: This article presents discussion about flight simulators starting from training simulators, applied in military and civil training tasks, up to the domestic simulators. Article describes history of development of flight simulation equipment. At the end of this paper new unit of Silesian University of Technology – Virtual Flight Laboratory – is presented.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Initial flight screening of military pilots in Poland
Autorzy:: Bogusz, Dariusz
Wydawca:: Warsaw Management University
Opis:: Ministerstwo Nauki i Szkolnictwa Wyższego
Doskonała Nauka II
The selection of military pilot candidates is very important due to the cost of flight training and the high demands placed on military pilots. Proper selection saves time and money. Modern recruitment and selection is a complex, well-organised system for admitting selected candidates to service in military aviation. The flight school recruitment and selection process includes medical and psychological examinations, as well as practical tests to assess military pilot candidates’ mental and physical aptitude. The aviation selection process requires initial flight screening. Initial flight screening is the first stage of flight training and the basis for accepting candidates who meet the recruitment criteria for military aviation. A candidate for a military pilot, and then a pilot, is subject to continuous verification during his service. Initial flight screening aims to check the candidate’s behaviour in the air. After leaving the ground, the functioning of most people’s bodies deteriorates and their thought processes slow down. This type of training is intended to check the candidate’s functioning in the air and whether the specific work environment does not disturb his perception and thought processes, that is, it does not impair his operational efficiency.
Dostawca treści:: Repozytorium Centrum Otwartej Nauki

Książka

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Skocz do pozycji: 5.

Tytuł:: Development of a flight simulator for conceptual aircraft design and sizing
Autorzy:: Hon, Kai San
Karpuk, Stanislav
Yang, Daqing
Elham, Ali
Tematy:: flight dynamics
flight simulation
aircraft design; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/36455876.pdf Link otwiera się w nowym oknie
Opis:: This article describes the development of a flight simulator module within the ADEMAO aircraft design framework to investigate the effects of novel airframe and propulsion technologies on new generations of aircraft. Methods used to develop and integrate the fight simulator into the overall design framework are described. The simulator is validated based on existing data from the Convair CV-880M and is then used to analyze an example case of a conceptual medium-range aircraft with advanced airframe technologies designed in the Sustainable and Energy-Efficient Aviation research cluster at the Institute of Aircraft Design and Lightweight Structures at the Technische Universität Braunschweig. Results show the deficiencies of the medium-range aircraft in short-period pitch and Dutch roll performance, and recommendations for modifications to the conceptual medium-range aircraft are drafted.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Flight path management of an aircraft in emergency situation
Autorzy:: Majka, A.
Tematy:: general aviation
flight path optimization
flight safety; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/248107.pdf Link otwiera się w nowym oknie
Opis:: A distress event i.e. loss of engine power, structural damage etc., creates a major emergency situation in General Aviation (GA) aircraft. It requires location of a safe-to-land runway within reach, and immediately planning and executing an effective flight path towards it. Currently, technological development in avionics allows creating a flight deck decision support tool for trajectory planning of GA aircraft in emergency situation. Principal part of the system constitutes flight path optimization module. The automated path-planning algorithm generates within seconds an optimized trajectory to be followed by the pilot to safe landing. The trajectory planning is formulated as an optimal control problem, with the aircraft kinematics and dynamics expressed by the state equations, and objective functional that may capture the time, length, energy loss, etc. Obstacles and restricted or prohibited zones are represented as constraints on the positional state variables. The purpose of the paper is to present the method of flight path optimization of an aircraft in emergency, after a distress event, which makes impossible continuation of the original flight. The methods allow determining optimal escape flight path from special protection areas (e.g. cities etc.) or danger zones, as well. The simplified realization of the Ritz-Galerkin method was used in this work, which uses an approximate solution to boundary value problems for determining the optimal flight trajectory. The method allows determining the optimal trajectory of the flight satisfying the initial/final conditions and control functions and path constrains for an aircraft.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Computational simulation of fully trimmed flight of a helicopter in hover
Autorzy:: Stalewski, Wieńczysław
Zalewski, Wiesław
Surmacz, Katarzyna
Pulfer, Maximilian
Hirsch, Frieder
Tematy:: helicopter flight simulation
hover
trimmed flight
URANS; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/241633.pdf Link otwiera się w nowym oknie
Opis:: In trimmed flight of a helicopter, all the forces and moments, aerodynamic, inertial, and gravitational, are in balance. Keeping the helicopter in trimmed state, needs a precise adjustment of flight controls. The methodology of simulation of a fully trimmed flight of rotorcraft has been developed and applied to simulate hover of a helicopter. The presented approach is based on a solution of Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations. In contrast to typical solutions of such problem, in the newly developed methodology, the flight controls corresponding to the trimmed-flight conditions are also determined based on the solution of URANS equations. The methodology is based on coupling of several computational models of Computational Fluid Dynamics and Flight Dynamic. The URANS equations are solved in a three-dimensional region surrounding the flying helicopter, using the ANSYS FLUENT code. The approach is truly three-dimensional, with truly modelled geometry and kinematics of main and tail rotor blades. This applies to modelling of blade flapping and lead-lag motion, too. The trimming procedure uses six independent parameters (i.e. collective and cyclic pitch of main rotor blades, collective pitch of tail rotor blades, pitch, and bank angles of a helicopter) that should be adjusted so as to balance all forces and moments acting on the helicopter. The detailed description of the developed methodology as well as the results of simulation of trimmed hover of the helicopter was presented.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Flight tests of upgraded helicopters
Autorzy:: Nowakowski, M.
Tematy:: transport
helicopter flight
flight tests
flying qualities
performances; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/247172.pdf Link otwiera się w nowym oknie
Opis:: In-flight tests and measurements are usually performed for newly built or modernised aircraft utilised by the Polish Armed Forces. In the course of the in-flight tests the airborne equipment is investigated also. The main goal of the performed tests is to verify the tactical performance and to identify the technical parameters of the investigated aircraft or equipment. New aeronautical designs are subjected to flight test prior to being introduced into production and service. It is why ITWL was involved in both functional tests of equipment /systems installed on-board of helicopters as well as tests intended to determine flying qualities and performance thereof. Numerous test flights have been carried out in conformance to the newly developed methodology that takes account of the Joint Airworthiness Requirements - JAR 29 - Large Rotorcraft. Helicopter flight data and control parameters have been recorded in the course of experimental test flights by means of the measuring and recording equipment. The post-flight analyses of the recorded data made it possible to assess longitudinal static stability and directional stability, manoeuvrability and agility as well as performances of the upgraded helicopter Mi-17-IV.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Efficient Positioning of Two Long-Range Passenger Aircraft in Formation Flight
Autorzy:: Antczak, Adam
Lasek, Maciej
Sibilski, Krzysztof
Tematy:: formation flight
optimisation
strip theory
dynamics of flight; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Powiązania:: https://bibliotekanauki.pl/articles/36782619.pdf Link otwiera się w nowym oknie
Opis:: In today’s world, each airline is forced to look for new savings opportunities. One of the methods may be the use of formation flights in daily flight operations, which may allow a reduction in fuel consumption by several percentages. The paper presents the genesis of how the consideration of such flights and the possibility of their implementation in an airline had started. The leader’s plane generates vortices, which, with the proper alignment of the planes to one another, can reduce the drag on the wingman. However, the wrong position may not only have no positive effect but also may be a threat to stable wingman flight. The article presents a method of using these vortices in such a way as to have a positive impact on the aerodynamics of the wingman. A favourable position in the vertical and horizontal axes will be determined in relation to the vortex generated by the leader’s plane in order to obtain the greatest benefit in reducing fuel consumption. The paper presents an operational analysis of the possibility of maintaining such a distance to obtain profit on fuel but also to ensure the highest level of safety of the flight.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Mathematical and graphical modelling of aerobatic flight trajectories
Autorzy:: Linka, A.
Wroblewska, A.
Tematy:: mathematical models
flight trajectory
aerobatics
flight safety
glider aerobatics; Pokaż więcej
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Powiązania:: https://bibliotekanauki.pl/articles/245876.pdf Link otwiera się w nowym oknie
Opis:: The article presents the current state of knowledge related to mathematical and graphical modelling of aircraft trajectories, particularly those of aerobatic flights. The first part of the article is an introduction to the subject of training and aerobatic flight. In the second chapter of this work, the authors describe the basic definitions related to mathematical modelling, rules for glider aerobatics (rules for the pilots and for the judges) and specification of navigation software, which is using during competitions. In the further part of the article the authors present example possibilities of application of the mathematical modelling tools in General Aviation and describe the possibilities of implementing the obtained models in selected navigation and tracking systems. In the same part of the article there is a description of the AeroSafetyShow Demonstrator PL – an intelligent system of flights supervision and safety (ASSD+PL), which will be using to compare the real flights trajectory and the models build trough the mathematical software. ASSD+PL in also only tracking system using by the judges at glider aerobatic World Championships. The aim of this article is to validate the applicability of the system comparing to the actual aircraft trajectory with the models referred to as ‘ideal’ for aerobatic purposes.
Dostawca treści:: Biblioteka Nauki

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