Advanced UAV Aerodynamics, Flight Stability and Control

Novel Concepts, Theory and Applications

Pascual Marqués, Andrea Da Ronch, Pascual Marqués, Andrea Da Ronch, Peter Belobaba, Jonathan Cooper, Allan Seabridge

• Publisher: Wiley
• Year: 2017
• Print ISBN:
  9781118928684
• eBook ISBN:
  9781118928707
• Edition: 1
• Topic: Tecnologia e ingegneria
• Subtopic: Ingegneria meccanica

Comprehensively covers emerging aerospace technologies 

Advanced UAV aerodynamics, flight stability and control: Novel concepts, theory and applications presents emerging aerospace technologies in the rapidly growing field of unmanned aircraft engineering. Leading scientists, researchers and inventors describe the findings and innovations accomplished in current research programs and industry applications throughout the world. Topics included cover a wide range of new aerodynamics concepts and their applications for real world fixed-wing (airplanes), rotary wing (helicopter) and quad-rotor aircraft.

The book begins with two introductory chapters that address fundamental principles of aerodynamics and flight stability and form a knowledge base for the student of Aerospace Engineering. The book then covers aerodynamics of fixed wing, rotary wing and hybrid unmanned aircraft, before introducing aspects of aircraft flight stability and control.

Key features:

• Sound technical level and inclusion of high-quality experimental and numerical data.
• Direct application of the aerodynamic technologies and flight stability and control principles described in the book in the development of real-world novel unmanned aircraft concepts.
• Written by world-class academics, engineers, researchers and inventors from prestigious institutions and industry.

The book provides up-to-date information in the field of Aerospace Engineering for university students and lecturers, aerodynamics researchers, aerospace engineers, aircraft designers and manufacturers.

1
Advanced UAV Aerodynamics, Flight Stability and Control: An Introduction

Pascual Marqués

Marques Aviation Ltd, Southport, UK

‘For some years I have been afflicted with the belief that flight is possible to man.’

Wilbur Wright, 13 May 1900.

This introductory chapter is divided into two main sections: Section 1.1 on unmanned aircraft aerodynamics and Section 1.2 on flight stability, and control. The chapter addresses fundamental principles of aerodynamics, flight stability and control and forms a knowledge base for the student of aerospace engineering before proceeding to more advanced chapters in this book. The chapter includes classroom problems.

1.1 Unmanned Aircraft Aerodynamics

1.1.1 Introduction: UAV Categories and Configurations

Unmanned aerial vehicle (UAV) size categories range from nano air vehicles (NAV) with a wing span of only 4 cm to high‐altitude long‐endurance (HALE) aircraft with a wing span of 35 m or more. In between, UAV categories include micro (MAV), mini, close‐range, medium‐range or tactical and medium‐altitude long‐endurance (Figure 1.1). The fluid medium in which an NAV operates is highly viscous, whereas the fluid flow around large (normally manned) aircraft is dominated by inertial effects. Consequently, aerodynamic characteristics vary considerably according to the size of the vehicle.

Figure 1.1 General Atomics RQ‐1A Predator.

(Photo: USAF Museum).

The aeronautical configuration of a UAV is closely related to its operational mission requirements and dictated by airspeed, endurance and operational range. Whether the vehicle is fixed‐wing or rotary‐wing is determined by the speed requirements. HALE surveillance aircraft necessitate a high aspect ratio (AR) wing for flight at high altitude. In contrast, Unmanned Combat Air Vehicles (UCAVs) operate at high airspeed and perform rapid manoeuvers and therefore have low AR wings. Civilian or military applications that involve operation from off‐board a ship benefit from vertical take‐off and landing capability of the aircraft. Fixed‐wing configurations include tailplane aft, tailplane forward or canard, and tailless types.

The conventional tailplane aft designs usually have the horizontal stabiliser positioned aft on the fuselage or connected to the wings by booms. The aircraft’s centre of gravity (CG) is often forward of the aerodynamic centre (AC), which creates a nose‐down pitching moment. To this negative moment must be added the nose‐down moment characteristic of cambered wings. The net nose‐down moment is balanced by a down‐load on the tailplane.

In a canard configuration, both the foreplane and the CG are located forward of the wing. Equilibrium in pitch is achieved by the positive lift generated by the foreplane. The canard design is aerodynamically more efficient than the tailplane aft design, as both the horizontal stabiliser and the wing produce positive lift.

Tailless types include the flying wing and delta configurations. Tailless types have sweptback wings and an effective tail. The airfoils at the wingtips are set at a lower incidence than the airfoils of the inner wing, in a washout configuration to provide stability in pitch. The absence of a horizontal stabiliser reduces profile drag. However, wing sweepback in the flying wing leads to poor lift distribution, high induced drag and negative lift at high airspeeds. Delta wings have a low AR, poor lift distribution and higher induced drag caused by high span loading.

In the majority of UAVs, the powerplant is mounted at the rear of the fuselage. This arrangement makes the front of the aircraft available for the installation of a payload and allows an unobstructed view forward. There are also aerodynamic advantages when using a rear‐mounted p...

Table of contents

• Cover
• Title Page
• Table of Contents
• List of Contributors
• Series Preface
• Preface
• Companion Website
• 1 Advanced UAV Aerodynamics, Flight Stability and Control
• 2 Aerodynamics of UAV Configurations
• Part I: Novel Concepts in Unmanned Aircraft Aerodynamics
• 1.2 Rotary‐wing (helicopter)
• 1.3 Hybrid Aircraft
• Part II: Novel Concepts in Unmanned Aircraft Flight Stability and Control
• 2.2 Quad‐rotor Aircraft
• Index
• End User License Agreement