Investigation of aircraft maneuverability by modelling

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F60162694%3AG43__%2F13%3A00496154" target="_blank" >RIV/60162694:G43__/13:00496154 - isvavai.cz</a>

Výsledek na webu

<a href="http://vavtest.unob.cz/registr" target="_blank" >http://vavtest.unob.cz/registr</a>

DOI - Digital Object Identifier

—

Jazyk výsledku

angličtina

Název v původním jazyce

Investigation of aircraft maneuverability by modelling

Popis výsledku v původním jazyce

The paper deals with determining of aircraft performance characteristics by flight path modeling. Calculation is realized by numerical integration of equations of motion, non-linear differential equations of first order. A numerical calculation is aimedto determine a flight trajectory of general unstable maneuver by universal model describing flight parameters in phase space. A mathematical model is controlled by parameters of control. Control laws are determined to simulate maneuver as close to real maneuver as is possible. An aircraft is described in model by its weight, aerodynamic and powerplant characteristics. A specification of flight parameters and flight path for given maneuver is possible by reduction of phase coordinates and by determiningof control laws. Results of two different tasks are included to clarify modeling method. The International Standard Atmosphere is respected. An aircraft is replaced with a mass point, what simplifies numerical model by ensuring relevant r

Název v anglickém jazyce

Investigation of aircraft maneuverability by modelling

Popis výsledku anglicky

The paper deals with determining of aircraft performance characteristics by flight path modeling. Calculation is realized by numerical integration of equations of motion, non-linear differential equations of first order. A numerical calculation is aimedto determine a flight trajectory of general unstable maneuver by universal model describing flight parameters in phase space. A mathematical model is controlled by parameters of control. Control laws are determined to simulate maneuver as close to real maneuver as is possible. An aircraft is described in model by its weight, aerodynamic and powerplant characteristics. A specification of flight parameters and flight path for given maneuver is possible by reduction of phase coordinates and by determiningof control laws. Results of two different tasks are included to clarify modeling method. The International Standard Atmosphere is respected. An aircraft is replaced with a mass point, what simplifies numerical model by ensuring relevant r

Druh

D - Stať ve sborníku

CEP obor

KA - Vojenství

OECD FORD obor

—

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2013

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

Investigation of aircraft maneuverability by modelling

ISBN

978-80-553-1416-7

ISSN

—

e-ISSN

—

Počet stran výsledku

6

Strana od-do

130-135

Název nakladatele

Technicka univerzita v Kosiciach Letecka fakulta

Místo vydání

Technicka univerzita v Košiciach Letecka fakulta

Místo konání akce

Herlany 25.-26.4.2013

Datum konání akce

1. 1. 2010

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

—