Design, Modelling and Simulation of Maritime UAV-VTOL Flight Dynamics

2012 ◽  
Vol 152-154 ◽  
pp. 1533-1538
Author(s):  
Jun Cao ◽  
Amir M. Anvar
Keyword(s):  
Structural Design ◽  
Water Surface ◽  
Unmanned Aircraft ◽  
The Other ◽  
Underwater Robot ◽  
Unmanned Air Vehicle ◽  
Vtol Uav ◽  
Air Vehicle ◽  
Remotely Piloted Aircraft ◽  
Aerial Vehicle

An Unmanned Aerial Vehicle (UAV) is referred to as a remotely piloted aircraft or an unmanned aircraft which can be navigated with human operator in the loop. This paper discusses the design of a UAV with Vertical Take-Off and Landing (VTOL) capability for Maritime applications. The design provides a means for surveillance and communication in Maritime applications. The VTOL-UAV utilises a five-rotor propulsion system that can be launched from confined platforms such as ship-decks. The intended applications of this M-UAV drove the development of an innovative landing system which in the case of emergencies can allow the M-UAV’s soft and potential landing on the water surface. The other functionalities of this UAV are its capabilities to deploy communication Micro-sonobuoys which allows for communication with underwater Robot(s) via Operator in the loop. In this paper we also discuss the process of structural design modelling and evaluation of the development of the Maritime Unmanned Air Vehicle.

Aerodynamic and structural design for the development of a MALE UAV

2018 ◽  
Vol 90 (7) ◽  
pp. 1077-1087 ◽  
Author(s):  
Pericles Panagiotou ◽  
Efstratios Giannakis ◽  
Georgios Savaidis ◽  
Kyros Yakinthos
Keyword(s):  
Structural Design ◽  
Design Procedure ◽  
Unmanned Aircraft ◽  
Content Type ◽  
Parameterized Design ◽  
Detail Design ◽  
Aerial Vehicle ◽  
Structural Parts ◽  
Long Endurance ◽  
Structural Aspects

Purpose The purpose of this paper is to present the preliminary design of a medium altitude long endurance (MALE) unmanned aerial vehicle (UAV), focusing on the interaction between the aerodynamic and the structural design studies. Design/methodology/approach The classic layout theory was used, adjusted for the needs of unmanned aircraft, including aerodynamic calculations, presizing methods and CFD, to estimate key aerodynamic and stability coefficients. Considering the structural aspects, a combination of layout, finite element methods and custom parameterized design tools were used, allowing automatic reshapes of the skin and the internal structural parts, which are mainly made of composite materials. Interaction loops were defined between the aforementioned studies to optimize the performance of the aerial vehicle, maximize the aerodynamic efficiency and reduce the structural weight. Findings The complete design procedure of a UAV is shown, starting from the final stages of conceptual design, up to the point where the detail design and mechanical drawings initiated. Practical implications This paper presents a complete view of a design study of a MALE UAV, which was successfully constructed and flight-tested. Originality/value This study presents a complete, synergetic approach between the configuration layout, aerodynamic and structural aspects of a MALE UAV.

scholarly journals Design and Fabrication of Small Vertical-Take-Off-Landing Unmanned Aerial Vehicle

2018 ◽  
Vol 152 ◽  
pp. 02023 ◽  
Author(s):  
Yasir Ashraf Abd Rahman ◽  
Mohammad Taghi Hajibeigy ◽  
Abdulkareem Shafiq Mahdi Al-Obaidi ◽  
Kean How Cheah
Keyword(s):  
Design Methodology ◽  
The Other ◽  
Long Distance ◽  
Open Spaces ◽  
Flight Tests ◽  
Flight Range ◽  
Horizontal Flight ◽  
Vtol Uav ◽  
Aerial Vehicle ◽  
Horizontal Thrust

Modern UAVs available in the market have well-developed to cater to the countless field of application. UAVs have their own limitations in terms of flight range and manoeuvrability. The traditional fixed-wing UAVs can fly for long distance but require runways or wide-open spaces for take-off and landing. On the other hand, the more trending multirotor UAVs are extremely manoeuvrable but cannot be used for long-distance flights because of their slower speeds and relatively higher consumption of energy. This study proposed the implementation of hybrid VTOL UAV which has the manoeuvring advantage of a multirotor UAV while having the ability to travel fast to reach a further distance. The design methodology and fabrication method are discussed extensively which would be followed by a number of flight tests to prove the concept. The proposed UAV would be equipped with quadcopter motors and a horizontal thrust motor for vertical and horizontal flight modes respectively.

INVESTIGATION OF THE CHARACTERISTICS OF THE SENSOR UNIT OF THE PA-2 HORIZONTAL STABILISATION SYSTEM

Aviation ◽  
2012 ◽  
Vol 16 (1) ◽  
pp. 10-15 ◽  
Author(s):  
Aleksandr Zbrutsky ◽  
Viktor Kanchenko ◽  
Roman Karnaushenko ◽  
Aleksandr Marinoshenko ◽  
Nikolay Chepur
Keyword(s):  
Environmental Monitoring ◽  
Unmanned Aircraft ◽  
Stabilization System ◽  
Sensor Unit ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Flight Level ◽  
Output Characteristics ◽  
Horizontal Stabilization

For tasks such as radiation and environmental monitoring using an unmanned air vehicle, it is necessary to maintain stable flight level. The authors used a PA-2 horizontal stabilization system, manufactured by Futaba Inc., to maintain the orientation of an unmanned aircraft during flight. This work represents the investigation of the characteristics of a PA-2 sensor unit in the laboratory. The authors obtained the optical and output characteristics of the sensor unit, operating angles, and dependence of output characteristics on UAV orientation.

L1 Controller Design for a Flying Wing Unmmaned Aerial Vehicle

2013 ◽  
Vol 436 ◽  
pp. 18-24
Author(s):  
Adrian Mihail Stoica
Keyword(s):  
Controller Design ◽  
Design Method ◽  
Output Feedback Control ◽  
Controller Synthesis ◽  
Control Law ◽  
Design Algorithm ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Aerial Vehicle

The paper presents a design method for the control system of a flying wing unmanned air vehicle (UAV). A modified loop-shaping type configuration is adopted for the controller synthesis such that maneuverability, robustness with respect to modeling uncertainty and sensitivity reduction performances are accomplished. A stabilizing output feedback control law minimizing the $L_1$ norm of the resulting system is determined. The proposed design algorithm is illustrated by a case study.

Design, analysis and experimental validation of a morphing UAV wing

2011 ◽  
Vol 115 (1174) ◽  
pp. 761-765 ◽  
Author(s):  
M. Bolinches ◽  
A. J. Keane ◽  
A. I. J. Forrester ◽  
J. P. Scanlan ◽  
K. Takeda
Keyword(s):  
Structural Design ◽  
Experimental Validation ◽  
3D Printer ◽  
Hot Wire ◽  
Polystyrene Foam ◽  
Element Analysis ◽  
Roll Control ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
The University

Abstract The design of wings with morphing capabilities is known to give aerodynamic benefits. These aero-dynamic benefits come from both the use of hinge-less surfaces and the greater adaptability to flight conditions. This paper describes the structural design of a twisting wing to be used for an unmanned air vehicle (UAV) and presents finite element analysis and experiment results. This is part of a research project carried out at the University of Southampton in which one of the goals is to compare different novel wing designs and technologies to determine which one of them gives the best performance. The twisting capability provides roll control without hinged surfaces hence providing aerodynamic improvement. The wing is manufactured using polystyrene foam and is cut out of block of this material using a hot wire machine. In order to link this foam structure to a main spar, ABS plastic inserts were manufactured using a 3D printer. The mechanisms used to actuate the wing are also made from this material. A full scale UAV wing has been manufactured and tested in order to compare with FEA results.

A stability-guaranteed smooth-scheduled MIMO robust emergency autopilot for a lateral surface jammed UAV

2017 ◽  
Vol 232 (12) ◽  
pp. 2286-2299
Author(s):  
İsmail Hakkı Şahin ◽  
Coşku Kasnakoğlu
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Autonomous Navigation ◽  
Control Laws ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
The Disabled ◽  
Aerial Vehicle ◽  
And Performance ◽  
Control Surfaces

This paper investigates a methodology for autopilot design for an unmanned air vehicle where one of the lateral control surfaces, i.e. the aileron or rudder, becomes jammed and unusable. The autopilot handles the automatic recovery, autonomous guidance and landing of the disabled unmanned aerial vehicle. An accurate nonlinear aircraft model is used to build local flight control laws using loop-shaping to decouple longitudinal and lateral channels. The design is carried out in a way to allow smooth scheduling over the local controllers without losing stability and performance, culminating in a robust emergency autopilot over the full flight envelope. The autopilot is tested on an example distress scenario involving aileron surface jam. It is confirmed through simulations that the autopilot design is capable of resuming safe flight and autonomous navigation under the fault scenario and is able to safely land the unmanned aerial vehicle to a target runway.

Unmanned Air Vehicle Research Simulator - Prototyping and Testing of Control and Navigation Systems

2013 ◽  
Vol 198 ◽  
pp. 266-271 ◽  
Author(s):  
Paweł Rzucidło
Keyword(s):  
Flight Control ◽  
Navigation Systems ◽  
Hardware In The Loop ◽  
Unmanned Air Vehicle ◽  
University Of Technology ◽  
Small Uav ◽  
Air Vehicle ◽  
Aerial Vehicle ◽  
Data Bus ◽  
And Control

This paper presents an experimental research simulator of an Unmanned Aerial Vehicle (UAV) and supporting systems, designed at the Department of Avionics and Control, Rzeszow University of Technology. The research simulator enables hardware-in-the-loop testing of an autopilot, actuators, the ground control station and telemetry modules. Particular hardware blocks can be integrated with real-time environment with the use of a CAN data bus, Ethernet interface and a set of popular serial interfaces. Current experiments support development and hardware-in-the-loop testing of advanced flight control and navigation systems of a small UAV (taking into account both the on-board and the ground segments).

Aerodynamic and structural design of a solar-powered micro unmanned air vehicle

2000 ◽  
Vol 214 (2) ◽  
pp. 97-106 ◽  
Author(s):  
C Wilson ◽  
J Nutbean ◽  
I Bond
Keyword(s):  
Structural Design ◽  
Solar Power ◽  
Size Range ◽  
Small Scale ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Solar Powered ◽  
Aircraft System ◽  
Technological Improvements ◽  
Aircraft Configurations

The field of micro unmanned aerial vehicles ((μUAVs) has advanced rapidly in recent years. This paper studies the design and construction of a small solar-powered aircraft near the size range of current (μUAVs. A number of aspects of their design were analysed, including structural, aerodynamic and propulsion system considerations. The effect of small-scale, low Reynolds number aerodynamics was investigated, and the performance of a range of candidate aerofoils was compared. The integration of a solar power source into the aircraft system was considered a key design issue. Consequently, a number of aircraft configurations were examined, with the intention of optimizing the application of solar power in a miniature aircraft. Investigation of improved system components suggests that a practical solar-powered aircraft in the size range below 500 mm maximum linear dimension should be viable given modest technological improvements.

Preliminary design of a box-wing VTOL UAV

2019 ◽  
Vol 92 (5) ◽  
pp. 737-743
Author(s):  
Giuseppe Palaia ◽  
Vittorio Cipolla ◽  
Vincenzo Binante ◽  
Emanuele Rizzo
Keyword(s):  
Mechanical Design ◽  
Design Procedure ◽  
General Aviation ◽  
Preliminary Design ◽  
Content Type ◽  
Unmanned Air Vehicle ◽  
Vtol Uav ◽  
Air Vehicle ◽  
Aerodynamic Performances ◽  
Vtol Aircraft

Purpose This paper aims to present a preliminary study on a disruptive vertical take-off and landing (VTOL) configuration based on the best wing system concept by L. Prandtl. Design/methodology/approach A preliminary design has been addressed from several points of views: a conceptual design has been carried out thanks to in-house optimization tool; aerodynamic performances, propulsion design and mechanical design have been addressed to make the first prototype for preliminary vertical flight tests. Findings The study shows the feasibility of box-wing configuration for VTOL aircraft. Practical implications The work shows a general design procedure for box-wing unmanned air vehicle (UAV) configuration. The study of this configuration can be easily adopted in wider range, from UAV to general aviation. In the last category, it can be a promising configuration for the future of urban air mobility. Originality/value This work lays the foundation for studying and testing box-wing configuration for unmanned VTOL aircraft. The design procedure can be scaled to manned aircraft belonging to general aviation aircraft.

scholarly journals Formation of appearance of helicopter-type unmanned airvehicle with consideration of landing on complex-moving platform

2020 ◽  
pp. 16-22 ◽  
Author(s):  
V. A. Bykov ◽  
A. E. Parnenkov
Keyword(s):  
Power Plant ◽  
Necessary Conditions ◽  
Unmanned Aircraft ◽  
Unmanned Helicopter ◽  
Structural Power ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Moving Platform

The article considers an approach to the formation of the image of an unmanned aircraft, taking into account the landing on a complex-moving platform. The main parameters characterizing the appearance of a helicopter-type unmanned air vehicle are analyzed and the task of appearance forming is formulated. Two necessary conditions for landing on a ship, such as static and dynamic compatibility are defined and formulated. The formation of the technical appearance of the ship unmanned helicopter is based on the interrelated processes of determination of the following parameters: volume-mass, structural-power, aerodynamic, power plant and take-off and landing devices. The formulation of the initial parameters of the landing pad movement on the ship is considered and the main dependencies of pitching are formulated. On the basis of the conducted researches and taking into account the accepted restrictions, the authors propose technical ways to solve the problem.

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