Performance evaluation and design of flight vehicle control systems / Eric T. Falangas.
This book will help students, control engineers and flight dynamics analysts to model and conduct sophisticated and systemic analyses of early flight vehicle designs controlled with multiple types of effectors and to design and evaluate new vehicle concepts in terms of satisfying mission and perform...
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| Format: | eBook |
| Language: | English |
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Hoboken, New Jersey :
Wiley,
2016.
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Table of Contents:
- Performance Evaluation and Design of Flight Vehicle Control Systems; Contents; Preface; Acknowledgments; Introduction; 1 DESCRIPTION OF THE DYNAMIC MODELS; 1.1 AERODYNAMIC MODELS; 1.2 STRUCTURAL FLEXIBILITY; 1.3 PROPELLANT SLOSHING; 1.4 DYNAMIC COUPLING BETWEEN VEHICLE, ACTUATORS, AND CONTROL EFFECTORS; 1.5 CONTROL ISSUES; 1.6 COORDINATE AXES; NOMENCLATURE; 2 NONLINEAR RIGID-BODY EQUATIONS USED IN 6-DOF SIMULATIONS; 2.1 FORCE AND ACCELERATION EQUATIONS; 2.2 MOMENT AND ANGULAR ACCELERATION EQUATIONS; 2.3 GRAVITATIONAL FORCES; 2.4 ENGINE TVC FORCES; 2.5 AERODYNAMIC FORCES AND MOMENTS.
- 2.6 PROPELLANT SLOSHING USING THE PENDULUM MODEL2.7 EULER ANGLES; 2.8 VEHICLE ALTITUDE AND CROSS-RANGE VELOCITY CALCULATION; 2.9 RATES WITH RESPECT TO THE STABILITY AXES; 2.10 TURN COORDINATION; 2.11 ACCELERATION SENSED BY AN ACCELEROMETER; 2.12 VEHICLE CONTROLLED WITH A SYSTEM OF MOMENTUM EXCHANGE DEVICES; 2.13 SPACECRAFT CONTROLLED WITH REACTION WHEELS ARRAY; 2.14 SPACECRAFT CONTROLLED WITH AN ARRAY OF SINGLE-GIMBAL CMGs; 2.14.1 Math Model of a SGCMG Array; 2.14.2 Steering Logic for a Spacecraft with SGCMGs; 3 LINEAR PERTURBATION EQUATIONS USED IN CONTROL ANALYSIS.
- 3.1 FORCE AND ACCELERATION EQUATIONS3.2 LINEAR ACCELERATIONS; 3.3 MOMENT AND ANGULAR ACCELERATION EQUATIONS; 3.4 GRAVITATIONAL FORCES; 3.5 FORCES AND MOMENTS DUE TO AN ENGINE PIVOTING AND THROTTLING; 3.6 AERODYNAMIC FORCES AND MOMENTS; 3.7 MODELING A WIND-GUST DISTURBANCE; 3.8 PROPELLANT SLOSHING (SPRING-MASS ANALOGY); 3.9 STRUCTURAL FLEXIBILITY; 3.9.1 The Bending Equation; 3.10 LOAD TORQUES; 3.10.1 Load Torques at the Nozzle Gimbal; 3.10.2 Hinge Moments at the Control Surfaces; 3.11 OUTPUT SENSORS; 3.11.1 Vehicle Attitude, Euler Angles; 3.11.2 Altitude and Cross-Range Velocity Variations.
- 3.11.3 Gyros or Rate Gyros3.11.4 Acceleration Sensed by an Accelerometer; 3.11.5 Angle of Attack and Sideslip Sensors; 3.12 ANGLE OF ATTACK AND SIDESLIP ESTIMATORS; 3.13 LINEARIZED EQUATIONS OF A SPACECRAFT WITH CMGs IN LVLH ORBIT; 3.14 LINEARIZED EQUATIONS OF AN ORBITING SPACECRAFT WITH RWA AND MOMENTUM BIAS; 3.15 LINEARIZED EQUATIONS OF SPACECRAFT WITH SGCMG; 4 ACTUATORS FOR ENGINE NOZZLES AND AEROSURFACES CONTROL; 4.1 Actuator Models; 4.1.1 Simple Actuator Model; 4.1.2 Electrohydraulic Actuator; 4.1.3 Electromechanical Actuator; 4.2 Combining a Flexible Vehicle Model with Actuators.
- 4.3 Electromechanical Actuator Example5 EFFECTOR COMBINATION LOGIC; 5.1 DERIVATION OF AN EFFECTOR COMBINATION MATRIX; 5.1.1 Forces and Moments Generated by a Single Engine; 5.1.2 Moments and Forces Generated by a Single Engine Gimbaling in Pitch and Yaw; 5.1.3 Moments and Forces of an Engine Gimbaling in a Single Skewed Direction; 5.1.4 Moments and Forces Generated by a Throttling Engine or an RCS Jet; 5.1.5 Moment and Force Variations Generated by a Control Surface Deflection from Trim; 5.1.6 Vehicle Accelerations due to the Combined Effect from all Actuators; 5.2 MIXING-LOGIC EXAMPLE.