Dynamic Aircraft Model with Active Winglet, Effects of Flight Mechanics and Loads Analysis

2015 ◽  
pp. 293-318
Author(s):  
Toni Kanakis ◽  
Bimo Prananta ◽  
Hans van Tongeren ◽  
Rob Huls
Keyword(s):  
Flight Mechanics ◽  
Aircraft Model ◽  
Loads Analysis

Application of the weight function method on a high incidence research aircraft model

2013 ◽  
Vol 117 (1195) ◽  
pp. 897-912 ◽  
Author(s):  
N. Anton ◽  
R. M. Botez ◽  
D. Popescu
Keyword(s):  
Weight Function ◽  
Flight Mechanics ◽  
System Stability ◽  
Weight Functions ◽  
System Modelling ◽  
Stable Model ◽  
Aircraft Model ◽  
High Incidence ◽  
Research Aircraft ◽  
Defence Research

Abstract This paper assesses the application of a new method for system stability analysis, the weight functions method, to the longitudinal and lateral motions of a High Incidence Research Aircraft Model. The method consists of finding the number of weight functions that is equal to the number of differential equations required for system modelling. The aircraft’s stability is determined from the sign of the total weight function; which should be negative for a stable model. The Aero-Data Model In Research Environment (ADMIRE) simulation, developed by the Swedish Defence Research Agency, was used for the aerodynamic aircraft modelling, with the following configurations: Mach number = 0·25, altitude = 500m, angle-of-attack [–10 to 30]°, elevon deflection angle [–30 to 30]°, canard deflection [0° and 25°] and rudder deflection angles [–30° and 30°]. These flight configurations were selected because they are among the flight conditions for Cat. II Pilot Induced Oscillation (PIO) criteria validation, performed on the FOI aircraft model presented in the PIO Handbook by the Group for Aeronautical Research and Technology in Europe, Flight Mechanics/Action Group 12. This aircraft model has a known instability for longitudinal and lateral motions and so a control law was introduced to stabilise its flight.

NUMERICAL AND EXPERIMENTAL INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF THE HYPERSONIC AIRCRAFT MODEL OF INTEGRATED CONFIGURATION

2013 ◽  
Vol 44 (1) ◽  
pp. 111-127
Author(s):  
Sergey Mikhailovich Zadonsky ◽  
Alexander Petrovich Kosykh ◽  
Garry Grantovich Nersesov ◽  
Iraida Fedorovna Chelysheva ◽  
Sergey Valer'evich Chernov ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Aerodynamic Characteristics ◽  
Aircraft Model ◽  
Hypersonic Aircraft

ESTIMATION OF AERODYNAMIC FORCES AND MOMENTS DERIVATIVES WITH RESPECT TO THE ANGULAR VELOCITY COMPONENTS OF THE AIRCRAFT MODEL IN A WIDE RANGE OF ANGLES OF ATTACK

2018 ◽  
Vol 49 (1) ◽  
pp. 43-64
Author(s):  
Mikhail Alekseyevich Golovkin ◽  
Andrey Aleksandrovich Efremov ◽  
Miroslav Sergeevich Makhnev
Keyword(s):  
Angular Velocity ◽  
Aerodynamic Forces ◽  
Aircraft Model ◽  
Wide Range
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