Stability and Control of Conventional and Unconventional Aerospace Vehicle Configurations: A Generic Approach from Subsonic to Hypersonic Speeds

By Bernd Chudoba

This book introduces a stability and control methodology named AeroMech, capable of sizing the primary control effectors of fixed wing subsonic to hypersonic designs of conventional and unconventional configuration layout. Control power demands are harmonized with static-, dynamic-, and maneuver stability requirements, while taking the six-degree-of-freedom trim state into account. The stability and control analysis solves the static- and dynamic equations of motion combined with non-linear vortex lattice aerodynamics for analysis. 

The true complexity of addressing subsonic to hypersonic vehicle stability and control during the conceptual design phase is hidden in the objective to develop a generic (vehicle configuration independent) methodology concept. The inclusion of geometrically asymmetric aircraft layouts, in addition to the reasonably well-known symmetric aircraft types, contributes significantly to the overall technical complexity and level of abstraction. The first three chapters describe the preparatory work invested along with the research strategy devised, thereby placing strong emphasis on systematic and thorough knowledge utilization. The engineering-scientific method itself is derived throughout the second half of the book. 

This book offers a unique aerospace vehicle configuration independent (generic) methodology and mathematical algorithm. The approach satisfies the initial technical quest: How to develop a ‘configuration stability & control’ methodology module for an advanced multi-disciplinary aerospace vehicle design synthesis environment that permits consistent aerospace vehicle design evaluations?

• Language: English
• Publisher: Springer
• Release date: Jul 23, 2019
• ISBN: 9783030168568

Book preview

Springer Aerospace Technology

The Springer Aerospace Technology series is devoted to the technology of aircraft and spacecraft including design, construction, control and the science. The books present the fundamentals and applications in all fields related to aerospace engineering. The topics include aircraft, missiles, space vehicles, aircraft engines, propulsion units and related subjects.

More information about this series at http://​www.​springer.​com/​series/​8613

Bernd Chudoba

Stability and Control of Conventional and Unconventional Aerospace Vehicle ConfigurationsA Generic Approach from Subsonic to Hypersonic Speeds

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Bernd Chudoba

Department of Mechanical and Aerospace Engineering, The University of Texas at Arlington, Arlington, TX, USA

ISSN 1869-1730e-ISSN 1869-1749

Springer Aerospace Technology

ISBN 978-3-030-16855-1e-ISBN 978-3-030-16856-8

https://doi.org/10.1007/978-3-030-16856-8

© Springer Nature Switzerland AG 2019

This work is subject to copyright. All rights are reserved by the Publisher, whether the whole or part of the material is concerned, specifically the rights of translation, reprinting, reuse of illustrations, recitation, broadcasting, reproduction on microfilms or in any other physical way, and transmission or information storage and retrieval, electronic adaptation, computer software, or by similar or dissimilar methodology now known or hereafter developed.

The use of general descriptive names, registered names, trademarks, service marks, etc. in this publication does not imply, even in the absence of a specific statement, that such names are exempt from the relevant protective laws and regulations and therefore free for general use.

The publisher, the authors and the editors are safe to assume that the advice and information in this book are believed to be true and accurate at the date of publication. Neither the publisher nor the authors or the editors give a warranty, expressed or implied, with respect to the material contained herein or for any errors or omissions that may have been made. The publisher remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.

This Springer imprint is published by the registered company Springer Nature Switzerland AG

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Don’t let your preoccupation with reality stifle your imagination.

Robert A. Cassanova and Sharon M. Garrison

Acknowledgements

A number of people cooperated in making this work possible, and I would like to acknowledge their contributions.

The presented methodology concept was developed from 1995 to 1999 at Cranfield University, England, as part of a research contract with DaimlerChrysler Aerospace Airbus GmbH under contract number EZ Future Projects 80995517. The research contract was formally funded by the European Supersonic Commercial Transport (ESCT) project with Dr. Josef Mertens serving as technical monitor for the first two years. The European trilateral technical cooperation had been established by the ESCT project managers Detlef Reimers (DaimlerChrysler Aerospace Airbus), Phil Green (British Aerospace Airbus) and Michèle Pacull (Aérospatiale). In retrospect, the following lists some of the specialists involved: Ulf Graeber, Burkhard Kiekebusch, Dirk von Reith and Dr. Alexander Van der Velden (Synaps Inc.) from DaimlerChrysler Aerospace Airbus; Les Hyde, Dr. Clyde Warsop and Alan Perry from British Aerospace Airbus; Elie Khaski and Joseph Irvoas from Aérospatiale Aéronautique Airbus, just to mention some.

The views and conclusions contained in this book, however, are those of the author and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of DaimlerChrysler Aerospace Airbus or any other company.

I am especially grateful for the joint effort of Mike Cook and Dr. Howard Smith at Cranfield University. They knew when to applaud my progress and when to demand more. Mike Cook’s intimate understanding of flight mechanics, his devoted ability of being a teacher for academic and technical issues are clearly an everlasting experience. Howard Smith’s knowledge of aerospace vehicle design, in particular the computational side, proved to be invaluable during the method planning phase. I am thankful for their unbiased technical, academic and personal support throughout the entire research period.

The author gratefully acknowledges the dedicated skill and expertise from the following individuals, who endured without any hesitation in intensifying the author’s fascination for aerospace science. I have been fortunate to receive their attention, which enhanced disciplinary and multidisciplinary understanding of technical and non-technical issues: Georg Poschmann (Airbus Industrie), Dr. Jean Roeder (Airbus Industrie), Alan Perry (British Aerospace Airbus), Dr. Clyde Warsop (BAe Sowerby Research Center), Juergen Hammer (Airbus Industrie), Joseph Irvoas (Aérospatiale), Robert G. Hoey (USAF), Gerald C. Blausey (Lockheed Martin), Irving Ashkenas (Northrop, STI), Fred Krafka (Airbus Industrie), Clyde Warsop (BAe Sowerby Research Center), Professor Mason (Virginia Tech), Professor Fielding, Professor Howe, Professor Stollery and Pete Thomasson from Cranfield University.

I wish to acknowledge with deep gratitude the support of my wife, Andrea, and our children, Elena Sophia and Luca Samuel, for putting up with my very erratic hours of working. They all encouraged me through the years of my trying periods of my research life. Andrea helped me through the research period exciting and as well difficult times. It is to her, my best and beautiful critic, that this book is dedicated.

Arlington, USA

June 2019

Bernd Chudoba

Notations

Abbreviations

a.c.

Aerodynamic centre

a/c

Aircraft

ADC

Air data computer

ADS

Air data system

AEO

All engines operating

AeroMech

Aerodynamics and flight mechanics

AeroSpace

Aeronautics and space

AF

AF spring rod

AFB

Air force base

AFE

Authorised flight envelope

AIAA

American Institute of Aeronautics and Astronautics

AIC

Aerodynamic influence coefficient

AIWC

Aero-inclinsic wing concept

AoA

Angle of attack

AWC

Annular wing configuration; asymmetric wing configuration; arrow wing concept

B

Blue (hydraulic system)

BCAR

British Civil Airworthiness Requirements

BPC

Biplane configuration

BWB

Blended wing body

BWBC

Blended wing body concept

C of A

Certificate of airworthiness (CoA)

c.g.

Centre of gravity

CA

Control allocation

CAD

Computer-aided design

CAM

Computer-aided manufacture

CAP

Control anticipation parameter

CAWC

Cranked arrow wing concept

CB

Computationally based

CCV

Control configured vehicle

CE

Control effector

CEV

Centre d’Essais en Vol

CFD

Computational fluid dynamics

CIT

Comfort in turbulence

CS

Configuration setting

CWC

C-wing concept

D

Dimensional

DATCOM

Data compendium

DBS

Database system

DCFC

Design-constraining flight condition

DiCE

Directional control effector

DOC

Direct operating cost

DOF

Degree of freedom

DR

Dutch roll mode

DWC

Delta wing concept

EF

Engine ferry

EFCS

Electronic flight control system

EOM

Equations of motion

ESCT

European Supersonic Commercial Transport

ESD

Equivalent stability derivatives

ESDU

Engineering Sciences Data Unit

FAR

Federal aviation requirements

FBW

Fly-by-wire

FC

Failure condition

FCS

Flight control system

FCV

Flight condition variable

FEM

Finite element method

FSWC

Forward-swept wing concept

FWC

Flying wing configuration

FWTC

Folding wing-tip concept

G

Green (hydraulic system)

GA

Genetic algorithm

GmbH

Gesellschaft mit beschränkter Haftung

GVLM

Generalised vortex-lattice method

HCE

Horizontal control effector

HSCT

High-speed civil transport

HYD

Hydraulic system

IAO

Input, analysis, output

INS

Inertial navigation system

JAR

Joint aviation requirements

JWC

Joined wing configuration

KB

Knowledge-based

KBS

Knowledge-based system

L

Landing

LaCE

Lateral control effector

LBC

Lifting-body concept; low-boom concept

LCDP

Lateral control departure parameter

LCSP

Lateral control spin parameter

LE

Leading edge

LEX

Leading-edge extension

LFC

Lifting fuselage concept

Lg (l/g)

Landing gear

LoCE

Longitudinal control effector

LOTS

Linear optimum trim solution

m.a.c.

Mean aerodynamic chord

m.p.

Manoeuvre point

MAV

Micro-air vehicle

MBC

Multi-body concept

MDO

Multidisciplinary optimisation

MLA

Manoeuvre load alleviation

MVO

Multivariate optimisation

MWC

M-wing concept

n.p.

Neutral point

NASA

National Aeronautics and Space Administration

NASM

National Air and Space Museum

NLGS

Russian certification authority

OEI

One engine inoperative

OFW

Oblique flying wing

OFWC

Oblique flying wing configuration

OML

Outer mold line

OWC

Oblique wing configuration

P

Phugoid mode

PC

Primary controls

PCA

Propulsion-controlled aircraft

PCS

Propulsion control system; pitch compensation system

PIO

Pilot-induced oscillation

PM

Panel method

PTC

Pusher/tractor concept (power plant)

PWC

Poly-wing configuration

QN

Quetzalcoatlus Northropi

QVLM

Quasi-vortex-lattice method

R

Roll subsidence

R&D

Research and development

RCD

Rapid conceptual design

RCS

Reaction control system

ROM

Reduced-order model

RSS

Relaxed static stability

S

Spiral divergence

s&c

Stability and control

SAS

Stability augmentation system

SC

Special conditions; secondary controls

SCT

Supersonic commercial transport

SFCC

Slat and flap control computer

SLA

Stereolithography

SLC

Span-loader concept

SM

Static margin

SP

Short-period mode

SPO

Short-period oscillation

SSBJ

Supersonic business jet

SSTO

Single-stage-to-orbit

TAC

Tail-aft configuration

TBC

Twin-boom concept

TBD

To be determined

TCA

Technology concept aircraft

TCAS

Technical competition analysis system

TE

Trailing edge

TFC

Tail-first configuration

TO

Take-off

TSC

Three-surface configuration

TSS

Transport supersonique

TVC

Thrust vector control

TWC

Tandem wing configuration; telescopic wing concept

UK

United Kingdom

US

United States

USA

United States of America

VIWC

Variable-incidence wing concept

VLM

Vortex-lattice method

VORSTAB

Vortex-lattice stability and control

VSTOL

Vertical or short take-off and landing

VSWC

Variable-sweep wing concept

VTOL

Vertical take-off and landing

WAI

Wing anti-ice

Y

Yellow (hydraulic system)

Symbols

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {a}_{n}$$

Normal acceleration

A

System matrix

$$b$$

Span

B

System matrix

$$c$$

Chord

$$\bar{c}$$

Mean aerodynamic chord (m.a.c.)

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {c}$$

Control vector

$$C_{D}$$

Drag coefficient (aircraft)

$$C_{{D_{0} }}$$

Drag coefficient (aircraft) for zero angle of attack

$$C_{{D_{\alpha } }}$$

Variation of aircraft drag coefficient with angle of attack

$$C_{{D_{{\dot{\alpha }}} }}$$

Variation of aircraft drag coefficient with rate of change of angle of attack

$$C_{{D_{\beta } }}$$

Variation of aircraft drag coefficient with angle of sideslip

$$C_{{D_{{\dot{\beta }}} }}$$

Variation of aircraft drag coefficient with rate of change of angle of sideslip

$$C_{{D_{{\delta_{LoCE} }} }}$$

Variation of aircraft drag coefficient with longitudinal CE deflection angle

$$C_{{D_{{\delta_{DiCE} }} }}$$

Variation of aircraft drag coefficient with directional CE deflection angle

$$C_{{D_{{\delta_{LaCE} }} }}$$

Variation of aircraft drag coefficient with lateral CE deflection angle

$$C_{{D_{{\delta_{SC} }} }}$$

Variation of aircraft drag coefficient with secondary controls deflection angle

$$C_{{D_{{\delta_{CS} }} }}$$

Variation of aircraft drag coefficient with configuration setting deflection angle

$$C_{{D_{u} }}$$

Variation of aircraft drag coefficient with forward speed

$$C_{{D_{{\dot{u}}} }}$$

Variation of aircraft drag coefficient with rate of change of forward speed

$$C_{{D_{p} }}$$

Variation of aircraft drag coefficient with roll rate

$$C_{{D_{{\dot{p}}} }}$$

Variation of aircraft drag coefficient with rate of change of roll rate

$$C_{{D_{q} }}$$

Variation of aircraft drag coefficient with pitch rate

$$C_{{D_{{\dot{q}}} }}$$

Variation of aircraft drag coefficient with rate of change of pitch rate

$$C_{{D_{r} }}$$

Variation of aircraft drag coefficient with yaw rate

$$C_{{D_{{\dot{r}}} }}$$

Variation of aircraft drag coefficient with rate of change of yaw rate

$$C_{l}$$

Rolling moment coefficient (aircraft)

$$C_{{l_{0} }}$$

Rolling moment coefficient (aircraft) for zero angle of attack

$$C_{{l_{\alpha } }}$$

Variation of aircraft rolling moment coefficient with angle of attack

$$C_{{l_{{\dot{\alpha }}} }}$$

Variation of aircraft rolling moment coefficient with rate of change of angle of attack

$$C_{{l_{\beta } }}$$

Variation of aircraft rolling moment coefficient with angle of sideslip

$$C_{{l_{{\dot{\beta }}} }}$$

Variation of aircraft rolling moment coefficient with rate of change of angle of sideslip

$$C_{{l_{{\delta_{LoCE} }} }}$$

Variation of aircraft rolling moment coefficient with longitudinal CE deflection angle

$$C_{{l_{{\delta_{DiCE} }} }}$$

Variation of aircraft rolling moment coefficient with directional CE deflection angle

$$C_{{l_{{\delta_{LaCE} }} }}$$

Variation of aircraft rolling moment coefficient with lateral CE deflection angle

$$C_{{l_{{\delta_{SC} }} }}$$

Variation of aircraft rolling moment coefficient with secondary controls deflection angle

$$C_{{l_{{\delta_{CS} }} }}$$

Variation of aircraft rolling moment coefficient with configuration setting deflection angle

$$C_{{l_{u} }}$$

Variation of aircraft rolling moment coefficient with forward speed

$$C_{{l_{{\dot{u}}} }}$$

Variation of aircraft rolling moment coefficient with rate of change of forward speed

$$C_{{l_{p} }}$$

Variation of aircraft rolling moment coefficient with roll rate

$$C_{{l_{{\dot{p}}} }}$$

Variation of aircraft rolling moment coefficient with rate of change of roll rate

$$C_{{l_{q} }}$$

Variation of aircraft rolling moment coefficient with pitch rate

$$C_{{l_{{\dot{q}}} }}$$

Variation of aircraft rolling moment coefficient with rate of change of pitch rate

$$C_{{l_{r} }}$$

Variation of aircraft rolling moment coefficient with yaw rate

$$C_{{l_{{\dot{r}}} }}$$

Variation of aircraft rolling moment coefficient with rate of change of yaw rate

$$C_{L}$$

Lift coefficient (aircraft)

$$C_{{L_{0} }}$$

Lift coefficient (aircraft) for zero angle of attack

$$C_{{L_{\alpha } }}$$

Variation of aircraft lift coefficient with angle of attack

$$C_{{L_{{\dot{\alpha }}} }}$$

Variation of aircraft lift coefficient with rate of change of angle of attack

$$C_{{L_{\beta } }}$$

Variation of aircraft lift coefficient with angle of sideslip

$$C_{{L_{{\dot{\beta }}} }}$$

Variation of aircraft lift coefficient with rate of change of angle of sideslip

$$C_{{L_{{\delta_{LoCE} }} }}$$

Variation of aircraft lift coefficient with longitudinal CE deflection angle

$$C_{{L_{{\delta_{DiCE} }} }}$$

Variation of aircraft lift coefficient with directional CE deflection angle

$$C_{{L_{{\delta_{LaCE} }} }}$$

Variation of aircraft lift coefficient with lateral CE deflection angle

$$C_{{L_{{\delta_{SC} }} }}$$

Variation of aircraft lift coefficient with secondary controls deflection angle

$$C_{{L_{{\delta_{CS} }} }}$$

Variation of aircraft lift coefficient with configuration setting deflection angle

$$C_{{L_{u} }}$$

Variation of aircraft lift coefficient with forward speed

$$C_{{L_{{\dot{u}}} }}$$

Variation of aircraft lift coefficient with rate of change of forward speed

$$C_{{L_{p} }}$$

Variation of aircraft lift coefficient with roll rate

$$C_{{L_{{\dot{p}}} }}$$

Variation of aircraft lift coefficient with rate of change of roll rate

$$C_{{L_{q} }}$$

Variation of aircraft lift coefficient with pitch rate

$$C_{{L_{{\dot{q}}} }}$$

Variation of aircraft lift coefficient with rate of change of pitch rate

$$C_{{L_{r} }}$$

Variation of aircraft lift coefficient with yaw rate

$$C_{{L_{{\dot{r}}} }}$$

Variation of aircraft lift coefficient with rate of change of yaw rate

$$C_{m}$$

Pitching moment coefficient (aircraft)

$$C_{{m_{0} }}$$

Pitching moment coefficient (aircraft) for zero angle of attack

$$C_{{m_{\alpha } }}$$

Variation of aircraft pitching moment coefficient with angle of attack

$$C_{{m_{{\dot{\alpha }}} }}$$

Variation of aircraft pitching moment coefficient with rate of change of angle of attack

$$C_{{m_{\beta } }}$$

Variation of aircraft pitching moment coefficient with angle of sideslip

$$C_{{m_{{\dot{\beta }}} }}$$

Variation of aircraft pitching moment coefficient with rate of change of angle of sideslip

$$C_{{m_{{\delta_{LoCE} }} }}$$

Variation of aircraft pitching moment coefficient with longitudinal CE deflection angle

$$C_{{m_{{\delta_{DiCE} }} }}$$

Variation of aircraft pitching moment coefficient with directional CE deflection angle

$$C_{{m_{{\delta_{LaCE} }} }}$$

Variation of aircraft pitching moment coefficient with lateral CE deflection angle

$$C_{{m_{{\delta_{SC} }} }}$$

Variation of aircraft pitching moment coefficient with secondary controls deflection angle

$$C_{{m_{{\delta_{CS} }} }}$$

Variation of aircraft pitching moment coefficient with configuration setting deflection angle

$$C_{{m_{u} }}$$

Variation of aircraft pitching moment coefficient with forward speed

$$C_{{m_{{\dot{u}}} }}$$

Variation of aircraft pitching moment coefficient with rate of change of forward speed

$$C_{{m_{p} }}$$

Variation of aircraft pitching moment coefficient with roll rate

$$C_{{m_{{\dot{p}}} }}$$

Variation of aircraft pitching moment coefficient with rate of change of roll rate

$$C_{{m_{q} }}$$

Variation of aircraft pitching moment coefficient with pitch rate

$$C_{{m_{{\dot{q}}} }}$$

Variation of aircraft pitching moment coefficient with rate of change of pitch rate

$$C_{{m_{r} }}$$

Variation of aircraft pitching moment coefficient with yaw rate

$$C_{{m_{{\dot{r}}} }}$$

Variation of aircraft pitching moment coefficient with rate of change of yaw rate

$$C_{n}$$

Yawing moment coefficient (aircraft)

$$C_{{n_{0} }}$$

Yawing moment coefficient (aircraft) for zero angle of attack

$$C_{{n_{\alpha } }}$$

Variation of aircraft yawing moment coefficient with angle of attack

$$C_{{n_{{\dot{\alpha }}} }}$$

Variation of aircraft yawing moment coefficient with rate of change of angle of attack

$$C_{{n_{\beta } }}$$

Variation of aircraft yawing moment coefficient with angle of sideslip

$$C_{{n_{{\dot{\beta }}} }}$$

Variation of aircraft yawing moment coefficient with rate of change of angle of sideslip

$$C_{{n_{{\beta_{dyn} }} }}$$

Dynamic directional stability parameter

$$C_{{n_{{\delta_{LoCE} }} }}$$

Variation of aircraft yawing moment coefficient with longitudinal CE deflection angle

$$C_{{n_{{\delta_{DiCE} }} }}$$

Variation of aircraft yawing moment coefficient with directional CE deflection angle

$$C_{{n_{{\delta_{LaCE} }} }}$$

Variation of aircraft yawing moment coefficient with lateral CE deflection angle

$$C_{{n_{{\delta_{SC} }} }}$$

Variation of aircraft yawing moment coefficient with secondary controls deflection angle

$$C_{{n_{{\delta_{CS} }} }}$$

Variation of aircraft yawing moment coefficient with configuration setting deflection angle

$$C_{{n_{u} }}$$

Variation of aircraft yawing moment coefficient with forward speed

$$C_{{n_{{\dot{u}}} }}$$

Variation of aircraft yawing moment coefficient with rate of change of forward speed

$$C_{{n_{p} }}$$

Variation of aircraft yawing moment coefficient with roll rate

$$C_{{n_{{\dot{p}}} }}$$

Variation of aircraft yawing moment coefficient with rate of change of roll rate

$$C_{{n_{q} }}$$

Variation of aircraft yawing moment coefficient with pitch rate

$$C_{{n_{{\dot{q}}} }}$$

Variation of aircraft yawing moment coefficient with rate of change of pitch rate

$$C_{{n_{r} }}$$

Variation of aircraft yawing moment coefficient with yaw rate

$$C_{{n_{{\dot{r}}} }}$$

Variation of aircraft yawing moment coefficient with rate of change of yaw rate

$$C_{T}$$

Thrust coefficient

$$C_{{T_{\alpha } }}$$

Variation of thrust coefficient with angle of attack

$$C_{{T_{{\dot{\alpha }}} }}$$

Variation of thrust coefficient with rate of change of angle of attack

$$C_{{T_{\beta } }}$$

Variation of aircraft thrust coefficient with angle of sideslip

$$C_{{T_{{\dot{\beta }}} }}$$

Variation of aircraft thrust coefficient with rate of change of angle of sideslip

$$C_{{T_{u} }}$$

Variation of aircraft thrust coefficient with forward speed

$$C_{{T_{{\dot{u}}} }}$$

Variation of aircraft thrust coefficient with rate of change of forward speed

$$C_{{T_{p} }}$$

Variation of aircraft thrust coefficient with roll rate

$$C_{{T_{{\dot{p}}} }}$$

Variation of aircraft thrust coefficient with rate of change of roll rate

$$C_{{T_{q} }}$$

Variation of aircraft thrust coefficient with pitch rate

$$C_{{T_{{\dot{q}}} }}$$

Variation of aircraft thrust coefficient with rate of change of pitch rate

$$C_{{T_{r} }}$$

Variation of aircraft thrust coefficient with yaw rate

$$C_{{T_{{\dot{r}}} }}$$

Variation of aircraft thrust coefficient with rate of change of yaw rate

$$C_{Y}$$

Sideforce coefficient (aircraft)

$$C_{{Y_{0} }}$$

Sideforce coefficient (aircraft) for zero angle of attack

$$C_{{Y_{\alpha } }}$$

Variation of aircraft sideforce coefficient with angle of attack

$$C_{{Y_{{\dot{\alpha }}} }}$$

Variation of aircraft sideforce coefficient with rate of change of angle of attack

$$C_{{Y_{\beta } }}$$

Variation of aircraft sideforce coefficient with angle of sideslip

$$C_{{Y_{{\dot{\beta }}} }}$$

Variation of aircraft sideforce coefficient with rate of change of angle of sideslip

$$C_{{Y_{{\delta_{LoCE} }} }}$$

Variation of aircraft sideforce coefficient with longitudinal CE deflection angle

$$C_{{Y_{{\delta_{DiCE} }} }}$$

Variation of aircraft sideforce coefficient with directional CE deflection angle

$$C_{{Y_{{\delta_{LaCE} }} }}$$

Variation of aircraft sideforce coefficient with lateral CE deflection angle

$$C_{{Y_{{\delta_{SC} }} }}$$

Variation of aircraft sideforce coefficient with secondary controls deflection angle

$$C_{{Y_{{\delta_{CS} }} }}$$

Variation of aircraft sideforce coefficient with configuration setting deflection angle

$$C_{{Y_{u} }}$$

Variation of aircraft sideforce coefficient with forward speed

$$C_{{Y_{{\dot{u}}} }}$$

Variation of aircraft sideforce coefficient with rate of change of forward speed

$$C_{{Y_{p} }}$$

Variation of aircraft sideforce coefficient with roll rate

$$C_{{Y_{{\dot{p}}} }}$$

Variation of aircraft sideforce coefficient with rate of change of roll rate

$$C_{{Y_{q} }}$$

Variation of aircraft sideforce coefficient with pitch rate

$$C_{{Y_{{\dot{q}}} }}$$

Variation of aircraft sideforce coefficient with rate of change of pitch rate

$$C_{{Y_{r} }}$$

Variation of aircraft sideforce coefficient with yaw rate

$$C_{{Y_{{\dot{r}}} }}$$

Variation of aircraft sideforce coefficient with rate of change of yaw rate

$$dm$$

Element of the aircraft

$$D$$

Drag (aircraft)

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {f}$$

External force acting upon the aircraft c.g.

$$F_{B}$$

Body axes: F B ( c.g., x, y, z )

$$F_{CF}$$

Centrifugal force

$$F_{E}$$

Frame of reference (inertial system) attached to the Earth: F E ( O E , x E , y E , z E )

$$F_{{T_{x} }} ,F_{{T_{y} }} ,F_{{T_{z} }}$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {T}$$

$$g$$

Acceleration due to gravity

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {G}$$

Resultant external moment vector, about the mass centre

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {h}$$

Angular momentum vector of the aircraft with respect to its mass centre

$$h_{x} ,h_{y} ,h_{z}$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {h}$$ in F B

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {h}$$ ′

Angular momentum vector of spinning rotors with respect to rotor mass centre

$$h^{\prime}_{x} ,h^{\prime}_{y} ,h^{\prime}_{z}$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {h}$$ ′ in F B

$$i$$

Aerodynamic control effector variable-incidence stabiliser angle (trimmable CE)

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {i} ,\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {j} ,\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {k}$$

Unit vectors

$$I_{B}$$

Inertia matrix

$$I_{x} ,I_{y} ,I_{z}$$

Moments of inertia

$$I_{xy} ,I_{yz} ,I_{xz}$$

Products of inertia

$${{I}^*_L}, {{I}^*_M}, {{I}^*_N}$$

Inertia coupling terms

$${{I}^{**}_L}, {{I}^{**}_M}, {{I}^{**}_N}$$

Inertia coupling terms

$${{I}^{***}_L}, {{I}^{***}_M}, {{I}^{***}_N}$$

Inertia coupling terms

$$K$$

Generalised control system gain

$$K_{v} ,K_{w}$$

Attitude feedback gains

$$K_{p} ,K_{q} ,K_{r}$$

Rate feedback gains

$$l$$

Length, moment arm

$$L$$

Lift (aircraft)

$$L,M,N$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {G}$$ in F B , thrust moments

$$L/D$$

Aerodynamic efficiency

$$L_{\beta }$$

Variation of aircraft rolling moment with angle of sideslip

$$L_{EB}$$

Matrix of the direction cosines

$$L_{p}$$

Variation of rolling moment with roll rate

$$L_{q}$$

Variation of rolling moment with pitch rate

$$L_{r}$$

Variation of rolling moment with yaw rate

$$L_{u}$$

Variation of rolling moment with axial velocity

$$L_{v}$$

Variation of rolling moment with lateral velocity

$$L_{w}$$

Variation of rolling moment with normal velocity

$$\varDelta L_{CE}$$

Sum of rolling control moments

$$L_{{\delta_{LoCE} }}$$

Rolling control moment due to LoCE deflection

$$L_{{\delta_{DiCE} }}$$

Rolling control moment due to DiCE deflection

$$L_{{\delta_{LaCE} }}$$

Rolling control moment due to LaCE deflection

$$L_{\tau }$$

Rolling control moment due to thrust controls

$$m$$

Mass

$$M$$

Mach number

$$M_{\alpha }$$

Variation of aircraft pitching moment with angle of attack

$$M_{c}$$

Design cruising Mach number

$$M_{D}$$

Design dive Mach number

$$M_{DF}$$

Demonstrated flight diving Mach number

$$M_{p}$$

Variation of pitching moment with roll rate

$$M_{q}$$

Variation of pitching moment with pitch rate

$$M_{r}$$

Variation of pitching moment with yaw rate

$$M_{u}$$

Variation of pitching moment with axial velocity

$$M_{v}$$

Variation of pitching moment with lateral velocity

$$M_{w}$$

Variation of pitching moment with normal velocity

$$M_{{\dot{w}}}$$

Variation of pitching moment with rate of change of angle of attack

$$\varDelta M_{D}$$

Pitching moment increment due to engine failure

$$\varDelta M_{CE}$$

Sum of pitching control moments

$$M_{{\delta_{LoCE} }}$$

Pitching control moment due to LoCE deflection

$$M_{{\delta_{DiCE} }}$$

Pitching control moment due to DiCE deflection

$$M_{{\delta_{LaCE} }}$$

Pitching control moment due to LaCE deflection

$$M_{\tau }$$

Pitching control moment due to thrust controls

$$n$$

Load factor

$$N_{n}$$

Net normal force

$$N_{p}$$

Variation of yawing moment with roll rate

$$N_{q}$$

Variation of yawing moment with pitch rate

$$N_{r}$$

Variation of yawing moment with yaw rate

$$N_{u}$$

Variation of yawing moment with axial velocity

$$N_{v}$$

Variation of yawing moment with lateral velocity

$$N_{w}$$

Variation of yawing moment with normal velocity

$$\varDelta N_{D}$$

Yawing moment increment due to engine failure

$$\varDelta N_{CE}$$

Sum of yawing control moments

$$N_{{\delta_{LoCE} }}$$

Yawing control moment due to LoCE deflection

$$N_{{\delta_{DiCE} }}$$

Yawing control moment due to DiCE deflection

$$N_{{\delta_{LaCE} }}$$

Yawing control moment due to LaCE deflection

$$N_{\tau }$$

Yawing control moment due to thrust controls

$$p,q,r$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {\omega }$$ in F B

$$\dot{p},\dot{q},\dot{r}$$

Scalar components of $$\dot{\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {\omega } }$$ in F B , rate of change of aircraft angular velocity components

$$P$$

Power

$$\bar{q}$$

Aircraft dynamic pressure

$$\vec{r}_{{c.g._{B} }}$$

Position vector of dm in the frame F B

$$\vec{r}_{{c.g._{E} }}$$

Position vector of dm in the frame F E

R

Turning radius

S

Area; wing reference area

t

Time

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {T}$$

Thrust vector; time constant

$$T_{x} ,T_{y} ,T_{z}$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {T}$$

$$T_{{{1 \mathord{\left/ {\vphantom {1 2}} \right. \kern-0pt} 2}}}$$

Time to half amplitude

$$T_{2}$$

Time to double amplitude

$$u,v,w$$

Scalar components of $$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {V}$$ in F B , perturbed values of U, V and W

$$U,V,W$$

Scalar velocity components of $$\vec{V}$$

$$\vec{v}_{E}$$

Inertial velocity of dm in the Earth frame F E

V

Volume; control volume coefficient

$$\vec{V}$$

Aircraft velocity vector

$$V_{{\alpha_{{\max_{1g} }} }}$$

Minimum speed at high incidence

$$V_{1}$$

Decision speed on take-off

$$V_{2}$$

Take-off safety speed

$$V_{3}$$

Steady initial climb speed with all engines operating

$$\vec{V}_{B}$$

Airspeed vector of the aircraft mass centre in the body frame

$$V_{C}$$

Design cruising speed

$$V_{D}$$

Design diving speed

$$V_{DF}$$

Demonstrated flight diving speed

$$V_{LOF}$$

Lift-off speed

$$V_{MCA}$$

Minimum control speed, take-off climb

$$V_{MCA - 2}$$

Minimum control speed, take-off climb two engines inoperative

$$V_{MCG}$$

Minimum control speed, on or near ground

$$V_{MCL}$$

Minimum control speed, approach and landing

$$V_{MCL - 1}$$

Minimum control speed, one engine inoperative

$$V_{MCL - 2}$$

Minimum control speed, two engines inoperative

$$V_{MIN}$$

Minimum speed

$$V_{MO}$$

Maximum operating limit speed

$$V_{MPC - 1}$$

Minimum power controllability speed, one engine inoperative

$$V_{MPC - 2}$$

Minimum power controllability speed, two engines inoperative

$$V_{REF}$$

Reference airspeed; landing approach speed, all engines operating

$$V_{REF - 1}$$

Reference airspeed with critical engine failed; landing approach speed with critical engine failed

$$V_{{S_{1g} }}$$

One-g stall speed

$$V_{TMD}$$

Minimum demonstrated threshold speed

$$V_{Z}$$

Climb/descent speed

W

Weight (aircraft)

$$W_{rp}$$

Load at the rotation point

$$x,y,z$$

Coordinates

$$x_{T} ,y_{T} ,z_{T}$$

Thrust line coordinates relative to the aircraft c.g.

$$\hat{x},\hat{z}$$

Coordinates of c.g. relative to rotation point (main gear axel)

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {x}$$

State vector

$$\dot{\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {x} }$$

Derivative of the state vector

$$x_{E} ,y_{E} ,z_{E}$$

Coordinates of aircraft mass centre relative to fixed axes (inertial system F E )

$$x_{c.g.}$$

Centre of gravity location as fraction of the m.a.c., measured from the LE of the m.a.c., positive aft

$$x_{m.p.}$$

Manoeuvre point location as fraction of the m.a.c., measured from the LE of the m.a.c., positive aft

$$x_{n.p.}$$

Neutral point location as fraction of the m.a.c., measured from the LE of the m.a.c., positive aft

$$X,Y,Z$$

Components of resultant force acting on the aircraft

$$X_{p}$$

Variation of axial force component with roll rate

$$X_{q}$$

Variation of axial force component with pitch rate

$$X_{r}$$

Variation of axial force component with yaw rate

$$X_{u}$$

Variation of axial force component with axial velocity

$$X_{v}$$

Variation of axial force component with lateral velocity

$$X_{w}$$

Variation of axial force component with normal velocity

$$\varDelta X_{D}$$

Axial drag increment due to engine failure

$$\varDelta X_{CE}$$

Sum of axial control forces

$$X_{{\delta_{LoCE} }}$$

Axial control force due to LoCE deflection

$$X_{{\delta_{DiCE} }}$$

Axial control force due to DiCE deflection

$$X_{{\delta_{LaCE} }}$$

Axial control force due to LaCE deflection

$$X_{\tau }$$

Axial control force due to thrust controls

$$Y_{p}$$

Variation of lateral force component with roll rate

$$Y_{q}$$

Variation of lateral force component with pitch rate

$$Y_{r}$$

Variation of lateral force component with yaw rate

$$Y_{u}$$

Variation of lateral force component with axial velocity

$$Y_{v}$$

Variation of lateral force component with lateral velocity

$$Y_{w}$$

Variation of lateral force component with normal velocity

$$\varDelta Y_{CE}$$

Sum of lateral control forces

$$Y_{{\delta_{LoCE} }}$$

Lateral control force due to LoCE deflection

$$Y_{{\delta_{DiCE} }}$$

Lateral control force due to DiCE deflection

$$Y_{{\delta_{LaCE} }}$$

Lateral control force due to LaCE deflection

$$Y_{\tau }$$

Lateral control force due to thrust controls

$$Z_{p}$$

Variation of normal force component with roll rate

$$Z_{q}$$

Variation of normal force component with pitch rate

$$Z_{r}$$

Variation of normal force component with yaw rate

$$Z_{u}$$

Variation of normal force component with axial velocity

$$Z_{v}$$

Variation of normal force component with lateral velocity

$$Z_{w}$$

Variation of normal force component with normal velocity

$$Z_{{\dot{w}}}$$

Variation of normal force component with rate of change of angle of attack

$$\varDelta Z_{CE}$$

Sum of normal control forces

$$Z_{{\delta_{LoCE} }}$$

Normal control force due to LoCE deflection

$$Z_{{\delta_{DiCE} }}$$

Normal control force due to DiCE deflection

$$Z_{{\delta_{LaCE} }}$$

Normal control force due to LaCE deflection

$$Z_{\tau }$$

Normal control force due to thrust controls

Greek Letters

$$\alpha$$

Angle of attack

$$\beta$$

Angle of sideslip

$$\gamma$$

Flight path angle

$$\delta$$

Control effector deflection angle

$$\delta_{LoCE}$$

Aerodynamic longitudinal control effector deflection angle

$$\delta_{DiCE}$$

Aerodynamic directional control effector deflection angle

$$\delta_{LaCE}$$

Aerodynamic lateral control effector deflection angle

$$\hat{\delta }$$

Pilot manoeuvre command, CE deflection

$$\varDelta$$

Increment (perturbation) of a parameter; nonzero reference value

$$\varGamma$$

Circulation, vortex strength; dihedral angle

$$\varepsilon$$

Principal x -axis vertical inclination angle

$$\zeta$$

Damping ratio

$$\varLambda$$

Sweep angle

$$\phi ,\theta ,\psi$$

Euler angles

$$\mu_{x} ,\mu_{y}$$

Tire-to-runway friction coefficient

$$\rho_{a/c}$$

Aircraft mass density

$$\sigma$$

Principal x -axis horizontal inclination angle; static margin

$$\tau$$

Time delay; thrust control

$$\hat{\tau }$$

Pilot manoeuvre command; thrust controls deflection

$$\tau_{X} ,\tau_{M} ,\tau_{N}$$

Corrections for propulsive installation

$$\phi_{T}$$

Vertical thrust line inclination angle (projection on xz -plane)

$$\psi_{T}$$

Horizontal thrust line inclination angle (projection on xy -plane)

$$\varPhi$$

Perturbation velocity potential

$$\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {\omega }$$

Angular velocity vector

$$\omega_{n}$$

Undamped natural frequency

Subscripts

A

Aerodynamic

B, b

Body frame F B

CE

Control effector

DiCE

Directional control effector

DR

Dutch roll mode

E

Earth (inertial) frame F E

H

Horizontal CE

i, j, k

Variable indices

LaCE

Lateral control effector

limit

Limit value of a parameter

LoCE

Longitudinal control effector

max

Maximum

min

Minimum

P

Phugoid mode

R

Roll mode

s

Stability axes

S

Spiral mode

SAS

Stability augmentation system (augmented)

sf

Sideforce

SP

Short-period mode

T

Thrust

trim

Trim value

0

Reference values in reference condition

$$\infty$$

Free-stream quantity

Superscripts

(a), (b)

Case (a) and case (b)

E

Inertial system, frame F E

Contents

1 Introduction and Objectives 1

1.​1 Research Project Initiation and Motivation 1

1.​1.​1 Background 1

1.​1.​2 Today’s Aerospace Vehicle Design Problem 3

1.​1.​3 New Aerospace Vehicle Design Problem 9

1.​2 Research Project Aims, Scope, and Objectives 15

1.​3 Summary of Results 15

References 16

2 Generic Aerospace Vehicle Design—Knowledge Utilisation 19

2.​1 Introduction 19

2.​2 Prelude—Design Office of Nature 19

2.​2.​1 Technology Spin-off 21

2.​2.​2 Emulation of Nature’s Evolutionary Process 26

2.​3 Design Knowledge 28

2.​3.​1 Knowledge—A Definition 28

2.​3.​2 Quest for Engineering Design Knowledge 29

2.​3.​3 Novelty and Associated Knowledge Available 31

2.​4 Research Strategy Selected 32

2.​5 Design Knowledge Utilisation 35

2.5.1 Aircraft Conceptual Design Data-Base System (DBS) 39

2.5.2 Aircraft Conceptual Design Knowledge - Based System (KBS) 42

2.​6 Summary of Results 43

References 44

3 Assessment of the Aircraft Conceptual Design Process 47

3.​1 Introduction 47

3.​2 Interrelationshi​p Between Aerospace Vehicle Design and Airworthiness 47

3.​2.​1 Principles of the Certification Process 48

3.​2.​2 Some Limitations of Airworthiness Codes 49

3.​2.​3 Airworthiness Codes and Design Philosophy 51

3.2.4 AeroMech Development Requirements— Airworthiness 54

3.​3 Aircraft Conceptual Design Synthesis 55

3.​3.​1 Characteristics of the Conceptual Design Phase 56

3.​3.​2 Classification and Characterisation​ of Vehicle Synthesis Efforts 57

3.3.3 AeroMech Development Requirements— Synthesis System 67

3.​4 Methodology of Aerodynamic Project Predictions 67

3.​4.​1 Configuration Aerodynamics 69

3.​4.​2 Status of Computational Aerodynamics for Conceptual Design 70

3.​4.​3 Design Versus Analysis—Computational Aerodynamics in Vehicle Design 72

3.4.4 AeroMech Development Requirements— Configuration Aerodynamics 74

3.​5 Methodology of Stability and Control Project Predictions 74

3.​5.​1 Classification of Flight Mechanics 75

3.​5.​2 Confluence of Stability and Control Theory and Practice 77

3.​5.​3 Stability and Control at Conceptual Design Versus Detail Design 79

3.5.4 AeroMech Development Requirements— Project Stability and Control 80

3.​6 Summary of Results 81

References 82

4 Generic Characterisation​ of Aircraft—Parameter Reduction Process 91

4.​1 Introduction 91

4.​2 Geometry and Mass Characterisation​ 92

4.​2.​1 Classification of Aircraft Configuration and Concept 92

4.​2.​2 Stability and Control Design Guide Parametrics 94

4.​3 Configuration Aerodynamics Characterisation​ 113

4.​3.​1 Configuration Aerodynamics Work During Vehicle Synthesis 113

4.​3.​2 Identification of Gross Configuration Aerodynamics Parameters 120

4.​3.​3 Evaluation of Relevant Aerodynamic Prediction Codes 131

4.​4 Stability and Control Project Characterisation​ 136

4.​4.​1 Stability and Control Work During Vehicle Synthesis 136

4.​4.​2 Concepts and Technologies 145

4.​5 Flight Evaluation Characterisation​ 160

4.​5.​1 Flight Evaluation Work During Vehicle Synthesis 160

4.​5.​2 Design-Constraining Flight Conditions (DCFCs) 161

4.​6 1st-Level and 2nd-Level DCFCs 169

4.​7 Summary of Results 176

References 178

5 ‘ AeroMech ’—Conception of a Generic Stability and Control Methodology 189

5.​1 Introduction 189

5.​2 Methodology Concept 189

5.2.1 AeroMech Logic—Flowchart 190

5.​2.​2 Synopsis of Process Logic, Information Flow, and Calculation Algorithms 198

5.​3 Algorithm—Stability and Control Mathematical Modelling 200

5.​3.​1 Steady State Equations of Motion 202

5.​3.​2 Small Perturbation Equations of Motion 234

5.​4 Summary of Results 241

References 242

6 AeroMech Feasibility 245

6.​1 Introduction 245

6.​2 Demonstration of Process Logic 246

6.3 Validation and Integration of AeroMech 251

6.3.1 Data Availability to Enable Validation and Calibration of AeroMech 251

6.3.2 Integration of AeroMech into an Aerospace Vehicle Design Synthesis Environment 251

6.​4 Summary of Results 255

References 256

7 Conclusions 257

7.​1 Contributions and Conclusion Summary 258

7.​2 Recommendations for Future Work 261

Appendix 263

Author Index 373

Subject Index 379

List of Figures

Fig. 1.1 Problem description: today’s aerospace vehicle design problem5

Fig. 1.2 Problem description: new aerospace vehicle design problem11

Fig. 2.1 Configuration comparison: Manta Birostris (Phillip Colla Photography) and NASA Langley Research Center/McDonnell Douglas/Stanford University Blended-Wing-Body (BWB) small scale demonstrator21

Fig. 2.2 Wings of a Pterosaur ( a ), a bird ( b ), and a bat ( c ) as evolutionary variations in comparison with the arm of man ( d ). Langston 22

Fig. 2.3 Largest flying animal ever to inhabit the Earth is thought to have been the pterosaur Quetzalcoatlus Northropi 23

Fig. 2.4 Harmonisation of design capabilities targeted with design knowledge available32

Fig. 2.5 Concentric evolution spheres represent the research strategy selected for the development of a generic stability and control methodology concept33

Fig. 2.6 Interdependence of subject matters to be considered for development of a generic stability and control methodology for aircraft conceptual design level35

Fig. 2.7 Comparison of a sweptback and oblique wing (left) and untrimmed yawing moment coefficient at unity load factor for different wing sweep angles of the AD-1 research aircraft (right)37

Fig. 2.8 Coupling between minimum preparatory work required and synthesis work to construct a generic stability and control methodology38

Fig. 2.9 Representative case studies selected for assemblage of a conceptual design knowledge baseline38

Fig. 3.1 Classification scheme for flight mechanics with subject matters relevant for stability and control at the design stage76

Fig. 4.1 The spectrum of aircraft and their changing aerodynamic shape with speed93

Fig. 4.2 Multi-dimensional aircraft configuration and aircraft concept design parameter space94

Fig. 4.3 Categorising of aircraft mass into the concepts of the mass point, centre of gravity, and moment of inertia95

Fig. 4.4 Definition of aircraft axes and angles for the symmetric aircraft type, illustrated with operational asymmetry97

Fig. 4.5 Definition of aircraft axes and angles for the asymmetric aircraft type (OFWC), illustrated with operational asymmetry97

Fig. 4.6 Moment of inertia design interaction and design guide parametrics99

Fig. 4.7 Relative positioning of the c.g., n.p., m.p., and the m.a.c. positions for an aircraft with variable wing geometry101

Fig. 4.8 Centre of gravity design interaction and design guide parametrics102

Fig. 4.9 Lift element design interaction and design guide parametrics105

Fig. 4.10 Landing gear design interaction and design guide parametrics106

Fig. 4.11 Ground clearance envelopes qualitatively for the TAC, FWC, and OFWC107

Fig. 4.12 Propulsion element design interaction and design guide parametrics109

Fig. 4.13 Control element design interaction and design guide parametrics111

Fig. 4.14 Unification of aircraft and rocket developments114

Fig. 4.15 The governing equations of numerical fluid-simulation methods117

Fig. 4.16 Configuration aerodynamics dependency120

Fig. 4.17 Multi-dimensional dependence of aerodynamic flow phenomena121

Fig. 4.18 Dependence of aerospace vehicle design on aerodynamic data and control data124

Fig. 4.19 Dependency of control power on configuration & concept, aerodynamic effectiveness, and stability and control criteria125

Fig. 4.20 Multi-dimensional dependence of stability derivatives130

Fig. 4.21 Visualisation proposal of generic stability derivative information: ‘Stability Derivative Card’131

Fig. 4.22 Survey of potential flow computer-based aerodynamic prediction methods133

Fig. 4.23 Horseshoe vortex filament implementation of the standard vortex lattice method (VLM)135

Fig. 4.24 Aerodynamic control effector (CE) family147

Fig. 4.25 Classical LoCE sizing diagram with design criteria for the TAC-type aircraft configuration149

Fig. 4.26 Flying qualities, handling qualities, and airframe stability and control characteristics of: a the conventional aircraft, and b the FBW aircraft. Data adapted, in part, from Cook 150

Fig. 4.27 AeroMech FCS options shown qualitatively along the open-loop and closed-loop aircraft chain 152

Fig. 4.28 Control effector design regions qualitatively in the flight envelope163

Fig. 5.1 AeroMech flowchart—input file definition 191

Fig. 5.2 AeroMech flowchart—aerodynamic analysis 193

Fig. 5.3 AeroMech flowchart—stability and control analysis 194

Fig. 5.4 AeroMech flowchart—output file 198

Fig. 5.5 AeroMech flowchart—illustration of information flow and emphasizing of calculation routines 199

Fig. 5.6 Asymmetric-flight CE sizing scenarios qualitatively213

Fig. 5.7 Horizontal steady turning flight216

Fig. 5.8 Steady state pull-up and push-over flight220

Fig. 5.9 Roll performance at ϕ = 0 227

Fig. 5.10 Take-off rotation ‘snap-shot’231

Fig. 6.1 AeroMech TAC to OFWC input file definition schematic 247

Fig. 6.2 AeroMech TAC to OFWC aerodynamic analysis schematic 248

Fig. 6.3 AeroMech TAC to OFWC stability and control analysis schematic 249

Fig. 6.4 AeroMech TAC to OFWC output file definition schematic 250

Fig. 6.5 Functional integration of AeroMech into an aircraft development engineering organisation 254

Fig. A.1 File structure of the literature Data-Base System (DBS) and a screenshot of the FWC.doc flying-wing file264

Fig. A.9.1 Inertial frame and body frame309

Fig. A.11.1 Thrust force component break-down348

Fig. A.11.2 Horizontal steady state turning flight352

Fig. A.11.3 Symmetric steady pull-up and push-over flight357

Fig. A.11.4 Roll performance at ϕ = 0 364

Fig. A.11.5 Take-off rotation ‘snap-shot’368

List of Tables

Table 1.1 Designer career length versus new military designs by decade (1950–2000)4

Table 1.2 Foreseen excess design-potential of B707-type aircraft layout (1999 technology level assumed)7

Table 1.3 Design cycle periods of selected civil and military aircraft programmes8

Table 1.4 Recent future-efficient aircraft programmes13

Table 2.1 Nature’s design refinements to match power required to power available of the Pterodactyl23

Table 2.2 Quetzalcoatlus Northropi —Selected design detail 24

Table 2.3 Classification of symmetric and asymmetric aircraft configurations36

Table 2.4 Organisation-scheme of knowledge utilisation activities towards conceptual design parameter reduction39

Table 3.1 Overview of selected aerospace vehicle design codes of airworthiness49

Table 3.2 AeroMech development requirements— Airworthiness 55

Table 3.3 Aircraft and AEROSPACE vehicle Class IV synthesis systems 61

Table 3.4 AeroMech development requirements— Synthesis system 68

Table 3.5 AeroMech development requirements— Configuration aerodynamics 74

Table 3.6 Relevant and excluded subject matters of flight mechanics at the conceptual design stage77

Table 3.7 AeroMech development requirements— Project stability and control 81

Table 4.1 Moments of inertia about the principal axes of pitch, roll, and yaw97

Table 4.2 Engineering techniques for configuration aerodynamics