NUST Institutions Library Catalogue

Includes bibliographical references (pages 409-412) and index.

Part 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 -- Part 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 model ; 2.7. 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-gimbaled SMGs. 2.14.1. Math model of a SGCMS array ; 2.14.2. Steering logic for a spacecraft with SGCMGs -- Part 3. Linear perturbation equations used in control analysis. 3.1. Force and acceleration equations ; 3.2. 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 gyros ; 3.11.4. 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 and LVLH orbit ; 3.14. Linearized equations of an orbiting spacecraft with RWA and momentum bias ; 3.15. Linearized equations of spacecraft with SGCMG -- Part 4. Actuators for engine nozzles and aerosurfers 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 example -- Part 5. Effector combination logic. 5.1. Dedication 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 ; 5.3. Space shuttle ascent analysis example. 5.3.1. Pitch axis analysis ; 5.3.2. Lateral axes flight control system ; 5.3.3. Closed-loop simulation analysis -- Part 6. Trimming the vehicle effectors. 6.1. Classical aircraft trimming ; 6.2. Trimming along a trajectory. 6.2.1. Aerodynamic moments and forces ; 6.2.2. Moments and forces from an engine gimbaling in pitch and yaw ; 6.2.3. Numerical solution for calculating the effector trim deflections and throttles ; 6.2.4. Adjusting the trim profile along the trajectory -- Part 7. Static performance analysis along a flight trajectory. 7.1. Transforming the aeromoment coefficients ; 7.2. Control demands partial matric C(T). 7.2.1. Vehicle moments and forces generated from a double-gimbaling engine ; 7.2.2. Vehicle moments and forces generated by an engine gimballing in single direction ; 7.2.3. Moment and force variations generated by a throttling engine ; 7.2.4. Vehicle moments and forces generated by control surfaces ; 7.2.5. Total vehicle moments and forces due to all effectors combined ; 7.3. Performance parameters. 7.3.1. Aerodynamic center ; 7.3.2. Static margin ; 7.3.3. Center of pressure ; 7.3.4. Pitch static stability/time to double amplitude parameter (T2) ; 7.3.5. Derivation of time to double amplitude ; 7.3.6. Directional stability (Cnb-dynamic) ; 7.3.7. Lateral static stability/time to double amplitude ; 7.3.8. Authority of the control effectors ; 7.3.9. Biased effectors ; 7.3.10. Control to disturbance moments ratio (MaIMg) ; 7.3.11. Pitch control authority against an angle of attach amax dispersion ; 7.3.12. Lateral control authority against an angle of sideslip Bmax disturbance ; 7.3.13. Normal and lateral loads ; 7.3.14. Bank angle and side force during a steady sideslip ; 7.3.15. Engine-out of Ycg offset situations ; 7.3.16. Lateral control departure parameter ; 7.3.17. Examples showing the effects of LCDP sign reversal on stability ; 7.3.18. Effector capability to provide rotational accelerations ; 7.3.19. Effector capability to provide translational accelerations ; 7.3.20. Steady pull-up maneuverability ; 7.3.21. Pitch inertial coupling due to stability roll ; 7.3.22. Yaw inertial coupling due to loaded roll ; 7.3.23. Moments at the hinges of the control surfaces ; 7.4. Notes on spin departure / Aditya A. Paranjape. 7.4.1. Stability-based criteria ; 7.4.2. Solution-based criteria ; 7.5. Appendix -- Part 8. Graphical performance analysis. 8.1. Contour plots of performance parameters versus (mach and alpha) ; 8.2. Vector diagram analysis. 8.2.1. Maximum moment and force vector diagrams ; 8.2.2. Maximum acceleration vector diagrams ; 8.2.3. Moment and force partials vector diagrams ; 8.2.4. Vector diagram partials of acceleration per acceleration demand ; 8.3. Converting the aero uncertainties from individual surfaces to vehicle axes. 8.3.1. Uncertainties in the control partials ; 8.3.2. Uncertainties due to peak control demands ; 8.3.3. Acceleration uncertainties -- Part 9. Flight control design. 9.1. LQR state-feedback control ; 9.2. H-infinity state-feedback ; 9.3. H-infinity control using full-order output feedback ; 9.4. Control design examples ; 9.5. Control design for a reentry vehicle. 9.5.1. Early reentry phase ; 9.5.2. Midphase ; 9.5.3. Approach and landing phase ; 9.6. Rocket plane with a throttling engine. 9.6.1. Design model ; 9.6.2. LQR control design ; 9.6.3. Simulation of the longitudinal control system ; 9.6.4. Stability analysis ; 9.7. Shuttle ascent control system redesign using H-infinity. 9.7.1. Pitch axis H-infinity ; 9.7.2. Lateral axes H-infinity design ; 9.7.3. Sensitivity comparison using simulations ; 9.8. Creating uncertainty models ; 9.8.1. The internal feedback loop structure ; 9.8.2. Implementation of the IFL model -- Part 10. Vehicle design examples. 10.1. Lifting-body space-plane reentry design example. 10.1.1. Control modes and trajectory description ; 10.1.2. Early hypersonic phase using alpha control ; 10.1.3. Normal acceleration control mode ; 10.1.4. Flight-path angle control mode ; 10.1.5. Approach and landing phase ; 10.1.6. Six-DOF nonlinear simulation ; 10.2. Launch vehicle with wings. 10.2.1. Trajectory analysis ; 10.2.2. Trimming along the trajectory ; 10.2.3. Trimming with an engine thrust failure ; 10.2.4. Analysis of static perforce along the trajectory ; 10.2.5. Controllability analysis using vector diagrams ; 10.2.6. Creating an ascent dynamic model and an effector mixing logic ; 10.2.7. Ascent control system design, analysis and simulation ; 10.3. Space station design example. 10.3.1. Control design ; 10.3.2. Simulation and analysis.