Roskam, Jan :

Dr. Jan Roskam holds the Dean E. Ackers Distinguished Professorship in Aerospace Engineering at The University of Kansas in Lawrence, Kansas, where he teaches airplane design, stability and control. He is the author of a two-volume text called: Airplane Flight Dynamics and Automatic Flight Controls and an eight volume text called: Airplane Design. He has co-authored (with Dr. C. Edward Lan) a text called: Airplane Aerodynamics and Performance. These texts are currently used by educators and industry practitioners across the globe as both a textbook and a key reference. In addition he has authored or co-authored over 160 papers, articles and technical reports. Dr. Roskam has actively participated in more than 25 major airplane programs and is president of DARcorporation.
Dr. C. Edward Lan has authored two books on airplane aerodynamics and airplane performance. He is the author of more than 100 papers on these topics and the co-author of Airplane Aerodynamics and Performance. He is the Warren S. Bellows Distinguished Professor of Aerospace Engineering at The University of Kansas, where he teaches airplane aerodynamics and performance, computational fluid dynamics, helicopter aerodynamics, aero elasticity and advanced aerodynamics courses.

The design methodology used in the development of the Advanced Aircraft Analysis (AAA) software program is based on Airplane Design, Parts I - VIII, Airplane Flight Dynamics & Automatic Flight Controls, Parts I & II, and Airplane Aerodynamics and Performance. AAA incorporates and coordinates the methods, statistical databases, formulas, and relevant illustrations and drawings from these references.

In Part I of this 2-part series, exhaustive coverage is provided of the methods for analysis and synthesis of the steady state and perturbed state (open loop) stability and control of fixed wing aircraft. This widely used book has been updated with modern flying quality criteria and aerodynamic data. Throughout this text, the practical (design) applications of the theory are stressed with many examples and illustrations. Aircraft stability and control characteristics are all heavily regulated by civil as well as by military airworthiness authorities for safety reasons. The role of the these safety regulations in the application of the theory is therefore stressed throughout. This text is an essential reference for all aeronautical engineers working in the area of stability and control, regardless of experience levels. The book minimizes reader confusion through a systematic progression of fundamentals:

• General steady and perturbed state equations of motion for a rigid airplane
• Concepts and use of stability & control derivatives
• Physical and mathematical explanations of stability & control derivatives
• Solutions and applications of the steady state equations of motion from a viewpoint of airplane analysis and emphasis on airplane trim, take-off rotation and engine-out control
• Open loop transfer functions
• Analysis of fundamental dynamic modes: phugoid, short period, roll, spiral and dutch roll
• Equivalent stability derivatives and the relation to automatic control of unstable airplanes
• Flying qualities and the Cooper-Harper scale: civil and military regulations
• Extensive numerical data on stability, control and hingemoment derivatives

SYMBOLS AND ACRONYMS
INTRODUCTION
1. EQUATIONS OF MOTION AND AXIS SYSTEMS
1.1 COORDINATE SYSTEMS AND EXTERNAL FORCES
1.2 DERIVATION OF THE EQUATIONS OF MOTION
1.3 EFFECT OF SPINNING ROTORS
1.4 ORIENTATION OF THE AIRPLANE RELATIVE TO THE EARTH FIXED COORDINATE SYSTEM X'Y'Z'
1.5 THE AIRPLANE FLIGHT PATH RELATIVE TO THE EARTH
1.6 THE COMPONENTS OF THE GRAVITATIONAL FORCE
1.7 REVIEW OF THE EQUATIONS OF MOTION
1.8 STEADY STATE EQUATIONS OF MOTION
1.8.1 CASE 1: Equations of motion for steady state rectilinear flight
1.8.2 CASE 2: Equations of motion for steady state turning flight
1.8.3 CASE 3: Equations of motion for steady symmetrical pull-up
1.9 PERTURBED STATE EQUATIONS OF MOTION
1.10 SUMMARY FOR CHAPTER 1
1.11 PROBLEMS FOR CHAPTER 1
1.12 REFERENCES FOR CHAPTER 1
2. REVIEW OF AERODYNAMIC FUNDAMENTALS
2.1 DEFINITION OF AIRFOIL PARAMETERS
2.2 AIRFOIL AERODYNAMIC CHARACTERISTICS
2.2.1 Airfoil aerodynamic center
2.2.2 Airfoil lift curve slope
2.3 PLANFORM PARAMETERS
2.4 COEFFICIENTS AND REFERENCE GEOMETRIES
2.5 AERODYNAMIC CHARACTERISTICS OF PLANFORMS AND FUSELAGE
2.5.1 Lift-curve slope
2.5.2 Aerodynamic center
2.5.3 Zero-lift angle of attack
2.5.4 Moment coefficient about the aerodynamic center
2.5.5 Down-wash, up-wash and dynamic pressure ratio
2.5.6 Effect of the fuselage on wing aerodynamic center
2.6 EFFECTIVENESS OF CONTROL SURFACES
2.7 MODERN AIRFOILS COMPARED TO NACA AIRFOILS
2.8 SUMMARY FOR CHAPTER 2
2.9 PROBLEMS FOR CHAPTER 2
2.10 REFERENCES FOR CHAPTER 2
3. AERODYNAMIC AND THRUST FORCES AND MOMENTS
3.1 STEADY STATE FORCES AND MOMENTS
3.1.1 Longitudinal aerodynamic forces and moments
3.1.2 Airplane drag
3.1.3 Airplane lift
3.1.4 Airplane aerodynamic pitching moment
3.1.5 Longitudinal thrust forces and moments
3.1.6 Assembling the steady state longitudinal forces and moments
3.1.7 Lateral-directional aerodynamic forces and moments
3.1.8 Airplane aerodynamic rolling moment
3.1.9 Airplane aerodynamic side force
3.1.10 Airplane aerodynamic yawing moment
3.1.11 Lateral-directional thrust forces and moments
3.1.12 Assembling the steady state lateral-directional forces and moments
3.2 PERTURBED STATE FORCES AND MOMENTS
3.2.1 Perturbed state, longitudinal aerodynamic forces and moments
3.2.2 Aerodynamic force and moment derivatives with respect to forward speed
3.2.3 Aerodynamic force and moment derivatives with respect to angle of attack
3.2.4 Aerodynamic force and moment derivatives with respect to angle of attack rate
3.2.5 Aerodynamic force and moment derivatives with respect to pitch rate
3.2.6 Aerodynamic force and moment derivatives with respect to longitudinal control surface and flap deflections
3.2.7 Assembling the perturbed, longitudinal aerodynamic forces and moments
3.2.8 Perturbed state, lateral-directional aerodynamic forces and moments
3.2.9 Aerodynamic force and moment derivatives with respect to sideslip
3.2.10 Aerodynamic force and moment derivatives with respect to sideslip rate
3.2.11 Aerodynamic force and moment derivatives with respect to roll rate
3.2.12 Aerodynamic force and moment derivatives with respect to yaw rate
3.2.13 Aerodynamic force and moment derivatives with respect to lateral-directional control surface deflections
3.2.14 Assembling the perturbed, lateral-directional aerodynamic forces and moments
3.2.15 Perturbed state longitudinal and lateral-directional thrust forces and moments
3.2.16 Thrust force and moment derivatives with respect to forward speed
3.2.17 Thrust force and moment derivatives with respect to angle of attack
3.2.18 Thrust force and moment derivatives with respect to angle of sideslip
3.2.19 Assembling the perturbed state longitudinal and lateral-directional thrust forces and moments
3.3 OVERVIEW OF USUAL SIGNS FOR AERODYNAMIC COEFFICIENTS
3.4 SUMMARY FOR CHAPTER 3
3.5 PROBLEMS FOR CHAPTER 3
3.6 REFERENCES FOR CHAPTER 3
4. STABILITY AND CONTROL DURING STEADY STATE FLIGHT
4.1 INTRODUCTION TO STATIC STABILITY AND ITS CRITERIA
4.1.1 Static stability criteria for velocity perturbations
4.1.2 Static stability criteria for angle of attack and sideslip perturbations
4.1.3 Static stability criteria for angular velocity perturbations
4.1.4 Discussion of pitching moment due to forward speed and rolling moment due to sideslip stability
4.2 STABILITY AND CONTROL CHARACTERISTICS FOR STEADY STATE, STRAIGHT LINE FLIGHT
4.2.1 Longitudinal stability and control characteristics for steady state, straight line flight
4.2.2 The airplane trim diagram
4.2.3 Stable and unstable pitch breaks
4.2.4 Use of windtunnel data in determining de/da
4.2.5 Effect of thrust on the trim diagram
4.2.6 Lateral-directional stability and control characteristics for steady state, straight line flight
4.3 STABILITY AND CONTROL CHARACTERISTICS FOR STEADY STATE, MANEUVERING FLIGHT
4.3.1 Stability and control characteristics for steady state, turning flight
4.3.2 Stability and control characteristics for steady state, symmetrical pull-up (push-over) flight
4.4 TRIM COMPARISONS FOR CONVENTIONAL, CANARD AND THREE-SURFACE CONFIGURATIONS
4.4.1 Trim of a conventional configuration
4.4.2 Trim of a canard configuration
4.4.3 Trim of a three-surface configuration
4.5 EFFECTS OF THE FLIGHT CONTROL SYSTEM ON STABILITY AND CONTROL IN STEADY STATE FLIGHT
4.5.1 Variation of stick-force and stick-force-speed gradient
4.5.2 Effect of control surface reversibility on static longitudinal stability
4.5.3 Another look at the stick-force-versus-speed gradient
4.5.4 Calculation of stick-force-per-'g'
4.5.5 Effect of control surface tabs, down-spring and bob-weight
4.5.5.1 Effect of trim tabs
4.5.5.2 Effect of balance or geared tabs
4.5.5.3 Effect of a blow-down tab
4.5.5.4 Effect of a down-spring
4.5.5.5 Effect of a bob-weight
4.5.6 Stick force equation in the presence of a trim tab, down-spring and bob-weight
4.6 LATERAL-DIRECTIONAL COCKPIT CONTROL FORCES
4.6.1 Rudder pedal control forces
4.6.2 Pedal-free directional stability, pedal forces in sideslip and rudder lock
4.6.3 Aileron wheel (stick) control forces
4.6.3.1 Steady state roll rate
4.6.3.2 Steady state, straight line flight
4.7 A MATRIX APPROACH TO THE GENERAL LONGITUDINAL TRIM PROBLEM
4.8 A MATRIX APPROACH TO THE GENERAL LATERAL-DIRECTIONAL TRIM PROBLEM
4.9 THE TAKEOFF ROTATION PROBLEM
4.10 INTRODUCTION TO IRREVERSIBLE FLIGHT CONTROL SYSTEMS
4.11 SUMMARY FOR CHAPTER 4
4.12 PROBLEMS FOR CHAPTER 4
4.13 REFERENCES FOR CHAPTER 4
5. STABILITY AND CONTROL DURING PERTURBED STATE FLIGHT
5.1 DYNAMIC STABILITY AND RESPONSE BEHAVIOR OF A SPRING MASS-DAMPER SYSTEM AND ITS STABILITY CRITERIA
5.2 LONGITUDINAL, DYNAMIC STABILITY AND RESPONSE
5.2.1 Longitudinal equations and transfer functions
5.2.2 Longitudinal characteristic equation roots and their connection to dynamic stability
5.2.3 Connection between dynamic and static longitudinal stability
5.2.4 Examples of longitudinal transfer functions
5.2.5 The short period approximation
5.2.6 The phugoid approximation
5.2.7 Response to an elevator step input
5.2.8 Standard format for the longitudinal transfer functions
5.2.9 The longitudinal mode shapes
5.3 LATERAL-DIRECTIONAL, DYNAMIC STABILITY AND RESPONSE
5.3.1 Lateral-directional equations and transfer functions
5.3.2 Lateral-directional characteristic equation roots and their connection to dynamic stability
5.3.3 Connection between dynamic and static lateral-directional stability
5.3.4 Examples of lateral-directional transfer functions
5.3.5 The dutch roll approximation
5.3.6 The spiral approximation
5.3.7 The roll approximation
5.3.8 Response to aileron and rudder step inputs
5.3.9 Standard format for the lateral-directional transfer functions
5.3.10 The lateral-directional mode shapes
5.4 CENTER-OF-GRAVITY AND DERIVATIVE ROOT-LOCI AND THE ROLE OF SENSITIVITY ANALYSES
5.4.1 Effect of center-of-gravity and mass distribution on longitudinal dynamic stability
5.4.2 Effect of stability derivatives on longitudinal dynamic stability
5.4.3 Effect of center-of-gravity and mass distribution on lat.-dir. dynamic stability
5.4.4 Effect of stability derivatives on lateral-directional dynamic stability
5.5 EQUIVALENT STABILITY DERIVATIVES, STABILITY AUGMENTATION AND DEPENDENCE ON CONTROL POWER
5.5.1 Equivalent pitch damping derivative
5.5.2 Equivalent yaw damping derivative
5.5.3 Equivalent longitudinal stability derivative
5.6 INERTIAL COUPLING DUE TO ROLL RATE AND PITCH RATE
5.6.1 Inertial coupling due to roll rate
5.6.2 Inertial coupling due to pitch rate
5.7 SUMMARY FOR CHAPTER 5
5.8 PROBLEMS FOR CHAPTER 5
5.9 REFERENCES FOR CHAPTER 5
6. FLYING QUALITIES AND PILOT RATINGS, REGULATIONS AND APPLICATION
6.1 FLYING QUALITIES AND PILOT RATINGS
6.2 MILITARY AND CIVILIAN FLYING QUALITY REQUIREMENTS: INTRODUCTION AND DEFINITIONS
6.2.1 Definition of airplane classes
6.2.2 Definition of mission flight phases
6.2.3 Definition of flying quality levels and allowable failure probabilities
6.3 LONGITUDINAL FLYING QUALITY REQUIREMENTS
6.3.1 Longitudinal control forces
6.3.1.1 Control forces in maneuvering flight
6.3.1.2 Control forces in steady state flight
6.3.1.3 Control forces in takeoff and landing
6.3.1.4 Control forces in dives
6.3.2 Phugoid damping
6.3.3 Flight path stability
6.3.4 Short period frequency and damping
6.3.5 Control anticipation parameter
6.4 LATERAL-DIRECTIONAL FLYING QUALITY REQUIREMENTS
6.4.1 Lateral-directional control forces
6.4.1.1 Roll control forces
6.4.1.2 Directional control forces with asymmetric loadings
6.4.1.3 Directional and roll control forces with one engine inoperative
6.4.2 Dutch roll frequency and damping
6.4.3 Spiral stability
6.4.4 Coupled roll-spiral (=lateral phugoid) stability
6.4.5 Roll mode time constant
6.4.6 Roll control effectiveness
6.4.7 Yawing moments in steady sideslips
6.4.8 Side forces in steady sideslips
6.4.9 Rolling moments in steady sideslips
6.5 CHARACTERISTICS OF THE FLIGHT CONTROL SYSTEM
6.6 RELATION BETWEEN FLYING QUALITY REQUIREMENTS AND DESIGN
6.6.1 Design for roll control effectiveness
6.6.2 Design for inherent spiral and dutch roll stability
6.6.3 Design for augmented static and dynamic stability in pitch
6.6.3.1 Effect of horizontal tail size on longitudinal stability and control derivatives
6.6.3.2 Stability augmentation by angle-of-attack and pitch-rate feedback
6.6.3.3 Effect of horizontal tail area on controllability in gust and on maneuvering
6.6.3.4 Effect of horizontal tail area on trim
6.7 SUMMARY FOR CHAPTER 6
6.8 PROBLEMS FOR CHAPTER 6
6.9 REFERENCES FOR CHAPTER 6
APPENDIX A: DESCRIPTION OF THE ADVANCED AIRCRAFT ANALYSIS (AAA) PROGRAM
A1 GENERAL CAPABILITIES OF THE AAA PROGRAM
A2 BRIEF DESCRIPTION OF AAA PROGRAM MODULES
A3 STABILITY AND CONTROL CAPABILITIES OF THE AAA PROGRAM
A4 REFERENCES FOR APPENDIX A
APPENDIX B: AIRPLANE DATA
APPENDIX C: SUMMARY OF LAPLACE TRANSFORM PROPERTIES
APPENDIX D: ON THE EFFECT OF FREE, REVERSIBLE FLIGHT CONTROLS ON AIRPLANE DYNAMIC STABILITY
INDEX TO PART I