Performance Evaluation and Design of Flight Vehicle Control Systems

1. Auflage 2015
ISBN: 978-1-119-00976-4
Verlag: Wiley

Buch, Englisch, 432 Seiten, Format (B × H): 161 mm x 240 mm, Gewicht: 812 g

The purpose of this book is to assist analysts, engineers, and students toward developing dynamic models, and analyzing the control of flight vehicles with various blended features comprising aircraft, launch vehicles, reentry vehicles, missiles and aircraft.

- Graphical methods for analysing vehicle performance
- Methods for trimming deflections of a vehicle that has multiple types of effectors
- Presents a parameters used for speedily evaluating the performance, stability, and controllability of a new flight vehicle concept along a trajectory or with fixed flight conditions

Autoren/Hrsg.

Falangas, Eric T

Fachgebiete

• Technische Wissenschaften Elektronik | Nachrichtentechnik Nachrichten- und Kommunikationstechnik Regelungstechnik
• Technische Wissenschaften Verkehrstechnik | Transportgewerbe Luft- und Raumfahrttechnik, Luftverkehr

Inhaltsverzeichnis

Preface xi

Acknowledgments xiii

Introduction 1

1 Description of the Dynamic Models 7

1.1 Aerodynamic Models, 8

1.2 Structural Flexibility, 9

1.3 Propellant Sloshing, 10

1.4 Dynamic Coupling between Vehicle, Actuators, and Control Effectors, 12

1.5 Control Issues, 13

1.6 Coordinate Axes, 15

Nomenclature, 16

2 Nonlinear Rigid-Body Equations Used in 6-DOF Simulations 19

2.1 Force and Acceleration Equations, 19

2.2 Moment and Angular Acceleration Equations, 21

2.3 Gravitational Forces, 22

2.4 Engine TVC Forces, 22

2.5 Aerodynamic Forces and Moments, 24

2.6 Propellant Sloshing Using the Pendulum Model, 28

2.7 Euler Angles, 29

2.8 Vehicle Altitude and Cross-Range Velocity Calculation, 30

2.9 Rates with Respect to the Stability Axes, 30

2.10 Turn Coordination, 31

2.11 Acceleration Sensed by an Accelerometer, 31

2.12 Vehicle Controlled with a System of Momentum Exchange Devices, 32

2.13 Spacecraft Controlled with Reaction Wheels Array, 33

2.14 Spacecraft Controlled with an Array of Single-Gimbal CMGs, 37

2.14.1 Math Model of a SGCMG Array, 38

2.14.2 Steering Logic for a Spacecraft with SGCMGs, 42

3 Linear Perturbation Equations Used in Control Analysis 47

3.1 Force and Acceleration Equations, 47

3.2 Linear Accelerations, 48

3.3 Moment and Angular Acceleration Equations, 50

3.4 Gravitational Forces, 51

3.5 Forces and Moments due to an Engine Pivoting and Throttling, 52

3.6 Aerodynamic Forces and Moments, 58

3.7 Modeling a Wind-Gust Disturbance, 70

3.8 Propellant Sloshing (Spring–Mass Analogy), 73

3.9 Structural Flexibility, 80

3.9.1 The Bending Equation, 85

3.10 Load Torques, 90

3.10.1 Load Torques at the Nozzle Gimbal, 91

3.10.2 Hinge Moments at the Control Surfaces, 93

3.11 Output Sensors, 97

3.11.1 Vehicle Attitude, Euler Angles, 97

3.11.2 Altitude and Cross-Range Velocity Variations, 98

3.11.3 Gyros or Rate Gyros, 98

3.11.4 Acceleration Sensed by an Accelerometer, 100

3.11.5 Angle of Attack and Sideslip Sensors, 101

3.12 Angle of Attack and Sideslip Estimators, 102

3.13 Linearized Equations of a Spacecraft with CMGs in LVLH Orbit, 104

3.14 Linearized Equations of an Orbiting Spacecraft with RWA and Momentum Bias, 106

3.15 Linearized Equations of Spacecraft with SGCMG, 107

4 Actuators for Engine Nozzles and Aerosurfaces Control 109

4.1 Actuator Models, 111

4.1.1 Simple Actuator Model, 112

4.1.2 Electrohydraulic Actuator, 114

4.1.3 Electromechanical Actuator, 118

4.2 Combining a Flexible Vehicle Model with Actuators, 123

4.3 Electromechanical Actuator Example, 126

5 Effector Combination Logic 137

5.1 Derivation of an Effector Combination Matrix, 138

5.1.1 Forces and Moments Generated by a Single Engine, 139

5.1.2 Moments and Forces Generated by a Single Engine Gimbaling in Pitch and Yaw, 141

5.1.3 Moments and Forces of an Engine Gimbaling in a Single Skewed Direction, 142

5.1.4 Moments and Forces Generated by a Throttling Engine or an RCS Jet, 143

5.1.5 Moment and Force Variations Generated by a Control Surface Deflection from Trim, 144

5.1.6 Vehicle Accelerations due to the Combined Effect from all Actuators, 145

5.2 Mixing-Logic Example, 147

5.3 Space Shuttle Ascent Analysis Example, 152

5.3.1 Pitch Axis Analysis, 153

5.3.2 Lateral Axes Flight Control System, 163

5.3.3 Closed-Loop Simulation Analysis, 168

6 Trimming the Vehicle Effectors 171

6.1 Classical Aircraft Trimming, 171

6.2 Trimming along a Trajectory, 172

6.2.1 Aerodynamic Moments and Forces, 176

6.2.2 Moments and Forces from an Engine Gimbaling in Pitch and Yaw, 178

6.2.3 Numerical Solution for Calc

Über Autor(innen)

Eric T. Falangas was a Lead Engineer/ Specialist and Project Manager at Boeing, Rockwell International and Aerospace Corporation in the fields of flight control design, spacecraft attitude control, vibration control and active vibration isolation, and other control and dynamics related projects. He received a BS in Electrical Engineering from the University of London and a MS in Control Systems from the University of Manchester Institute of Science and Technology. Eric has published several papers in magazines and conferences and was awarded 4 patents for developing active vibration control systems using piezo-electric actuator devices, and Flixan, which is a flight vehicle modelling and performance evaluation methodology, implemented in a Windows based program.