scholarly journals Using Presagis simulation software to model UAV aircraft in a humanitarian mission configuration

2021 ◽  
Author(s):  
Aaron Sotto
Keyword(s):  
Calculated Data ◽  
Flight Test ◽  
Simulation Software ◽  
Dynamic Responses ◽  
Humanitarian Mission ◽  
Stability Derivatives ◽  
Short Period ◽  
The Stability ◽  
And Control ◽  
Flight Model

Aircraft simulation software was used together to simulate a humanitarian variant of the MQ-9 Reaper drone as well as its longitudinal stability response upon dropping an aid payload. This project derives stability derivatives from the MQ-9 dimensions using the mass moments of inertia and approximate air- foil shape using Athena Vortex Lattice (AVL) code. The stability derivatives, aircraft properties, weights and control systems were modelled with Presagis FlightSim 14 to approximate the MQ-9 flight model. A graphics model was also built using Presagis Creator and the flight model and graphics model were unified into a virtual environment. Its longitudinal short period and phugoid responses as well as the lateral Dutch mode after dropping a 200 kg payload was recorded and analysed. The older Ryan Navion was also modelled using the same method which was used to model the MQ-9. The same dynamic responses were compared to real Navion flight test and calculated data in order to validate the aforementioned modelling method.

scholarly journals Using Presagis simulation software to model UAV aircraft in a humanitarian mission configuration

2021 ◽  
Author(s):  
Aaron Sotto
Keyword(s):  
Calculated Data ◽  
Flight Test ◽  
Simulation Software ◽  
Dynamic Responses ◽  
Humanitarian Mission ◽  
Stability Derivatives ◽  
Short Period ◽  
The Stability ◽  
And Control ◽  
Flight Model

Aircraft simulation software was used together to simulate a humanitarian variant of the MQ-9 Reaper drone as well as its longitudinal stability response upon dropping an aid payload. This project derives stability derivatives from the MQ-9 dimensions using the mass moments of inertia and approximate air- foil shape using Athena Vortex Lattice (AVL) code. The stability derivatives, aircraft properties, weights and control systems were modelled with Presagis FlightSim 14 to approximate the MQ-9 flight model. A graphics model was also built using Presagis Creator and the flight model and graphics model were unified into a virtual environment. Its longitudinal short period and phugoid responses as well as the lateral Dutch mode after dropping a 200 kg payload was recorded and analysed. The older Ryan Navion was also modelled using the same method which was used to model the MQ-9. The same dynamic responses were compared to real Navion flight test and calculated data in order to validate the aforementioned modelling method.

scholarly journals Stability of Fractional Order Systems

2013 ◽  
Vol 2013 ◽  
pp. 1-14 ◽  
Author(s):  
Margarita Rivero ◽  
Sergei V. Rogosin ◽  
José A. Tenreiro Machado ◽  
Juan J. Trujillo
Keyword(s):  
Fractional Calculus ◽  
Fractional Order ◽  
State Of The Art ◽  
Point Of View ◽  
Fractional Order Systems ◽  
Short Period ◽  
Systems And Control ◽  
Different Types ◽  
The Stability ◽  
And Control

The theory and applications of fractional calculus (FC) had a considerable progress during the last years. Dynamical systems and control are one of the most active areas, and several authors focused on the stability of fractional order systems. Nevertheless, due to the multitude of efforts in a short period of time, contributions are scattered along the literature, and it becomes difficult for researchers to have a complete and systematic picture of the present day knowledge. This paper is an attempt to overcome this situation by reviewing the state of the art and putting this topic in a systematic form. While the problem is formulated with rigour, from the mathematical point of view, the exposition intends to be easy to read by the applied researchers. Different types of systems are considered, namely, linear/nonlinear, positive, with delay, distributed, and continuous/discrete. Several possible routes of future progress that emerge are also tackled.

scholarly journals Towards Bio-Inspiration, Development, and Manufacturing of a Flapping-Wing Micro Air Vehicle

Drones ◽  
2020 ◽  
Vol 4 (3) ◽  
pp. 39
Author(s):  
P. Lane ◽  
G. Throneberry ◽  
I. Fernandez ◽  
M. Hassanalian ◽  
R. Vasconcellos ◽  
...  
Keyword(s):  
Aerodynamic Force ◽  
Force Production ◽  
Flight Test ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Successful Design ◽  
The Stability ◽  
And Control ◽  
The Impact

Throughout the last decade, there has been an increased demand for intricate flapping-wing drones with different capabilities than larger drones. The design of flapping-wing drones is focused on endurance and stability, as these are two of the main challenges of these systems. Researchers have recently been turning towards bioinspiration as a way to enhance aerodynamic performance. In this work, the propulsion system of a flapping-wing micro air vehicle is investigated to identify the limitations and drawbacks of specific designs. Each system has a tandem wing configuration inspired by a dragonfly, with wing shapes inspired by a bumblebee. For the design of this flapping-wing, a sizing process is carried out. A number of actuation mechanisms are considered, and two different mechanisms are designed and integrated into a flapping-wing system and compared to one another. The second system is tested using a thrust stand to investigate the impact of wing configurations on aerodynamic force production and the trend of force production from varying flapping frequency. Results present the optimal wing configuration of those tested and that an angle of attack of two degrees yields the greatest force production. A tethered flight test is conducted to examine the stability and aerodynamic capabilities of the drone, and challenges of flapping-wing systems and solutions that can lead to successful flight are presented. Key challenges to the successful design of these systems are weight management, force production, and stability and control.

The Influences on Turnout Dynamic Responses due to its Irregularities

2011 ◽  
Vol 105-107 ◽  
pp. 1181-1186 ◽  
Author(s):  
Yang Cao ◽  
Wang Ping ◽  
Wei Hua Zhao ◽  
Cai You Zhao
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Dynamic Response ◽  
Structure Design ◽  
Simulation Software ◽  
Dynamic Responses ◽  
Dynamics Simulation ◽  
Combined Effects ◽  
Vehicle Model ◽  
The Stability

A vehicle model and a movable-point simple turnout model were established, and the influences on dynamic responses caused by turnout irregularities when train passes through No.18 turnout was analyzed by using the turnout dynamics simulation software based on finite element method. It shows that turnout dynamic responses are influenced by the combined effects of various types of irregularities, which produce bigger dynamic response than single irregularity. In the turnout devise and use, the distance between slide plate and switch rail or nose rail should be as close as possible, the position arrangements of traction points should be optimized and the insufficient displacement should be eliminated as much as possible; No.18 turnout structure design is reasonable, which can ensure the safety and the stability when train passes over turnout.

scholarly journals Aplikasi Filter KALMAN Pada Gerak Matra Longitudinal Pesawat Udara Boeing-747

2019 ◽  
Vol 23 (4) ◽  
pp. 362
Author(s):  
Sayuti Syamsuar
Keyword(s):  
Kalman Filter ◽  
Control System ◽  
Closed Loop ◽  
Flight Test ◽  
Loop Control ◽  
Output Response ◽  
Closed Loop Control System ◽  
Loop Control System ◽  
The Stability ◽  
And Control

Many of aircraft perfonnance became from the stability and control of flight test data analysis. This paper introduces the Kalman Filter analysis on the Boeing 747 data aircraft to knawn the output response if disturbance (as turbulence or noise) absence on the closed loop control system. We found the output response of the plant on algorithm Kalman Filter tend to the unstable conditions, but we don't knaw the response of the whole of closed loop diagram block control system of Boeing 747 aircraft.Keywords : aircraft control system, turbulence, Kalman Filter

scholarly journals Pierre Young, 12 June 1926 - 4 August 1985

1988 ◽  
Vol 34 ◽  
pp. 983-1001
Keyword(s):  
World War Ii ◽  
National Physical Laboratory ◽  
French Language ◽  
World War ◽  
Stability And Control ◽  
Physical Laboratory ◽  
Short Period ◽  
The Stability ◽  
And Control ◽  
Coded Messages

Pierre Henry John Young was born on 12 June 1926, of a French mother from Argèles in the western Pyrenees, and an Irish father, employed by Morgan’s Bank. His education started at the Lycée Condorcet in Paris, after the usual period in primary school. His father was determined that he should continue his education in England, and to this end Pierre Young was ‘crammed’ in mathematics to enter for scholarships. He gained a place as a King’s Scholar at Westminster School, although he had scarcely any knowledge of Latin and could speak little English. He moved to England in 1938 to take his place at the school, which for most of the wartime period was evacuated to Herefordshire. His parents and sisters escaped from France to England with some difficulty as hostilities developed. From Westminster School he won an Open Scholarship in Mathematics to Trinity College, Cambridge, graduating in 1946. During this time he worked for brief spells in the French Language Service of the BBC, broadcasting coded messages to the French Resistance. At the end of World War II direction of labour was still in force and Pierre Young was employed for a short period at the National Physical Laboratory, Teddington, near his home, on the stability and control of aircraft.

An investigation of the flight dynamic characteristics of gyroplanes by use of flight tests

2004 ◽  
Vol 108 (1088) ◽  
pp. 531-535
Author(s):  
V. M. Spathopoulos
Keyword(s):  
Flight Test ◽  
Accident Rate ◽  
Simulation Data ◽  
Stable Mode ◽  
Stability And Control ◽  
Centre Of Gravity ◽  
Limited Application ◽  
The Stability ◽  
And Control ◽  
Rotary Wing

AbstractAn analysis is presented both of flight test and simulation data obtained from a gyroplane aircraft. This class of rotary-wing vehicle has found limited application in areas other than recreational flying, however the accident rate has been such that it has prompted the study of the configuration’s stability and control characteristics. It is concluded that the flight dynamic response of the gyroplane examined is dominated by a fast, non-stable mode, affecting all states and thus increasing pilot workload. Simulation results indicate that the position of the centre of gravity significantly influences the stability of this mode.

New methodology and code for Hawker 800XP aircraft stability derivatives calculation from geometrical data

2010 ◽  
Vol 114 (1156) ◽  
pp. 367-376 ◽  
Author(s):  
N. Anton ◽  
R. M. Botez ◽  
D. Popescu
Keyword(s):  
Classical Method ◽  
Complex Structure ◽  
Flight Test ◽  
Stability And Control ◽  
Stability Derivatives ◽  
Subsonic Regime ◽  
Geometrical Data ◽  
And Control ◽  
Derivatives Of ◽  
New Algorithms

Abstract The new FDerivatives code was conceived and developed for calculating static and dynamic stability derivatives of an aircraft in the subsonic regime, based on its geometrical data. The code is robust and it uses geometries and flight conditions to calculate the aircraft’s stability derivatives. FDerivatives contains new algorithms and methods that have been added to DATCOM’s classical method, presented in a USAF Stability and Control DATCOM reference. The new code was written using MATLAB and has a complex structure which contains a graphical interface to facilitate the work of potential users. Results obtained with the new code were evaluated and validated with flight test data provided by CAE Inc. for the Hawker 800XP business aircraft.

Application of Optimal Input Synthesis to Aircraft Parameter Identification

1976 ◽  
Vol 98 (2) ◽  
pp. 139-145 ◽  
Author(s):  
N. K. Gupta ◽  
R. K. Mehra ◽  
W. E. Hall
Keyword(s):  
Steady State ◽  
Frequency Domain ◽  
Time Domain ◽  
Stability And Control ◽  
Input Design ◽  
Short Period ◽  
Control Derivatives ◽  
The Stability ◽  
The Time Domain ◽  
And Control

This paper considers an application of the Frequency Domain Input Synthesis procedure reference [12] for identifying the stability and control derivatives of an aircraft. In previous studies, the input design has mostly been carried out in the time-domain. However, by using a frequency-domain approach, one can handle criteria that are not easily handled by the time-domain approaches. Numerical results are presented for optimal elevator deflections to estimate the longitudinal stability and control derivatives subject to root-mean square constraints on the input. The applicability of the steady state optimal inputs to finite duration flight testing is investigated. It is shown that the steady state approximation of frequency-domain synthesis is good for data lengths greater than two time cycles for the short period mode of the aircraft longitudinal motions. For data lengths shorter than this, the phase relationships between different frequency components becomes important. The frequency domain inputs are shown to be much better than the conventional doublet inputs.

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