Download or read book Gain Scheduling Controller for Aircraft with Mass and Inertia Variation written by Eunyoung Kim (Ph.D.) and published by . This book was released on 2019 with total page 135 pages. Available in PDF, EPUB and Kindle. Book excerpt: Robustness is one of the main control design requirements for aircraft control. Robustness is sought in the stability and performance of closed loop system against various factors such as disturbance, measurement error, modeling error or un-modeled dynamics. In aircraft control design, it is common to assume that the mass and inertia properties of aircraft are constant. Further, aircraft is assumed to have symmetry in its mass distribution relative to its mid-vertical plane. There are, however, cases where the aircraft mass changes rapidly, most notably in aerial refueling operation. The mass change also results in changes in the inertia matrix. An aircraft may also lose its mass symmetry in the case of, for example, asymmetric fuel loading or internal fuel transfer between fuel tanks. If a control design is carried out based on a specific mass and inertia configuration, the stability and performance of the closed loop system may degrade when the aircraft flies with a different configuration. This research effort focuses on addressing this issue in aerial refueling and formation flight by employing gain scheduling based on the aircraft mass and inertia configuration. The fuel mass in each fuel tank is considered as gain scheduling variables in addition to the ones associated with aircraft dynamics such as airspeed and turn rate. The first step of this research is to determine the number of nominal flight conditions to be included in the gain scheduling control design. Eigenvalue and Bode plot analyses are carried out based on the linearized equations of motion for various flight conditions, and symmetric and asymmetric fuel mass configurations. To reduce the number of cases included in the gain scheduling, "similar" cases are combined. An LQR-based MIMO (Multi Input Multi Output) integral control is designed for each nominal flight and mass configuration. An interpolation scheme based on the "mass distance" is developed to combine this linear controllers into the gain scheduling controller. The "mass distance" is defined as the norm of the differences between the current fuel tank amounts and those of each nominal mass configuration. This gain scheduling controller is implemented in aerial refueling simulation for a tailless delta wing aircraft with thrust vectoring capability. The simulation environment includes the 6-DOF models of both tanker and receiver, mass and inertial variation of the receiver aircraft in terms of the fuel mass in each fuel tank, aerodynamic coupling due to the tanker wake induced non uniform wind. The controller of the tanker aircraft is to y the aircraft at commanded altitude, speed, and turn rate. The gain scheduling controller of the receiver aircraft is to track the commanded position relative to the body frame of the tanker aircraft. The receiver controller was tuned in three control allocation cases: (1) no thrust vectoring; only aerodynamic control effects in use, (2)both aerodynamic effectors and thrust vectoring in use, and (3) no elevator or rudder used; only thrust vectoring and aileron in use. The performance of the gain scheduling controller is evaluated through the aerial refueling maneuver when the receiver moves between the observation position, point on the side and behind the tanker, and the refueling position, a point right behind and slightly below the tanker. The simulation results first of all demonstrates that a linear controller designed based on a nominal flight condition and mass configuration cannot safely complete the refueling maneuver when the aircraft has a different mass configuration. The simulation results further shows that the gain scheduling controller employing mass configuration as additional scheduling variables can successfully carry out the refueling maneuver with various symmetric and asymmetric fuel tank configuration.

Download or read book Performance Analysis Dynamic Simulation and Control of Mass actuated Airplane written by Sukru Akif Erturk and published by . This book was released on 2016 with total page 219 pages. Available in PDF, EPUB and Kindle. Book excerpt: The control of space, aerial and underwater vehicles requires moment generation mechanisms to change their orientation. In addition to or in place of conventional moment generation actuators, internally moving-mass actuation has been proposed and/or used for such vehicles. The primary principle for mass-actuation is to reposition gravitational force to change the associated moment while the secondary effect may come from the inertial force due to the motion of the masses. Recent development/miniaturization in flight control sensor, computing and actuation, and electric motors and expansion of applications for small UAV (Unmanned Aerial Vehicle) offer a potential for implementation of internal mass-actuation in small UAV. The massactuation offers various advantages over the conventional mechanisms in airplane flight such as reduced drag and lift loss due to aerodynamic control surface deflections, simplified wing and tail design, improved lift-generation performance of wing, smaller radar signature for stealth aircraft. This dissertation research investigates the feasibility and benefit of mass-actuation of a small UAV in various flight phases and full missions consisting of all these flight phases and transitions between them. Three different configurations of the same airplane are considered: (1) aero-actuated, conventional airplane with three standard aerodynamic control surfaces, aileron, elevator and rudder, (2) mass-actuated, a mass moving along the fuselage to mainly generate pitching moment, and another mass moving along the wing to generate rolling moment, and (3) mass-rudder actuated, mass-actuation as in case-2 augmented with a rudder. The airplane is an electric powered and has a single propeller at the nose. A full 6-DOF (Degrees of Freedom) nonlinear equations of motion are derived, including the terms modeling inertia forces induced by the motion of the internal masses, and the effect of this internal mass motion on the variation of the center of mass and inertia matrix. The dynamics of the electric motor of the propeller and the servos of the actuators are also modeled. The effect of the propeller on the dynamics of the aircraft is also included. Modeling also includes electric power consumption by the electric motor driving the propeller, and servos of the aerodynamic and mass actuators. An integrated simulation environment is developed that includes all these factors and can be switched between the different configurations defined above. Trim analyses of all three configurations of the airplane are carried out in all four flight conditions (steady climb, cruise, steady turn, steady descent). Trim analyses consider all the constraints of the control and state variables such as limits on the deflections of the aerodynamic surfaces, position of the mass actuators, battery provided voltage, and angle of attack. These analyses demonstrate the feasibility of flying the airplane with mass-actuation only within varying speed ranges depending on the actuation mechanism. The results also show the benefit of mass-actuation over the conventional aero-actuation in terms of range and endurance especially in cruise flight, as compared to the other two configurations. In the second phase of the research, controllability of the airplane with each actuation mechanisms is determined and compared over the feasible speed range of each trim condition. A new relative controllability metrics is defined and calculated for this purpose. This analysis, based on the linearized model of the aircraft in each trim flight condition, show that the mass-actuation provides full controllability with various degree over the speed ranges. Once the controllability is verified, an LQR-based gain scheduling controller is designed for each aircraft configuration to track commanded climb/descent rate, altitude, airspeed, and turn rate. These controllers are implemented in the integrated simulation environment to simulate various flight profiles including full missions that start with a hand-launch of the airplane, climb to a specified altitude, and cruise at that altitude with various commanded speed, and loiter with commanded left and right turn rates, and descend to land with varying approach speed. These simulations also demonstrate the feasibility potential benefits, and/or limitations of mass actuation.

Download or read book Flight Mechanics Modeling and Analysis written by Jitendra R. Raol and published by CRC Press. This book was released on 2023-03-31 with total page 567 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight Mechanics Modeling and Analysis comprehensively covers flight mechanics and flight dynamics using a systems approach. This book focuses on applied mathematics and control theory in its discussion of flight mechanics to build a strong foundation for solving design and control problems in the areas of flight simulation and flight data analysis. The second edition has been expanded to include two new chapters and coverage of aeroservoelastic topics and engineering mechanics, presenting more concepts of flight control and aircraft parameter estimation. This book is intended for senior undergraduate aerospace students taking Aircraft Mechanics, Flight Dynamics & Controls, and Flight Mechanics courses. It will also be of interest to research students and R&D project-scientists of the same disciplines. Including end-of-chapter exercises and illustrative examples with a MATLAB®-based approach, this book also includes a Solutions Manual and Figure Slides for adopting instructors. Features: • Covers flight mechanics, flight simulation, flight testing, flight control, and aeroservoelasticity. • Features artificial neural network- and fuzzy logic-based aspects in modeling and analysis of flight mechanics systems: aircraft parameter estimation and reconfiguration of control. • Focuses on a systems-based approach. • Includes two new chapters, numerical simulation examples with MATLAB®-based implementations, and end-of-chapter exercises. • Includes a Solutions Manual and Figure Slides for adopting instructors.

Download or read book Aerial Manipulation written by Matko Orsag and published by Springer. This book was released on 2017-09-19 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt: This text is a thorough treatment of the rapidly growing area of aerial manipulation. It details all the design steps required for the modeling and control of unmanned aerial vehicles (UAV) equipped with robotic manipulators. Starting with the physical basics of rigid-body kinematics, the book gives an in-depth presentation of local and global coordinates, together with the representation of orientation and motion in fixed- and moving-coordinate systems. Coverage of the kinematics and dynamics of unmanned aerial vehicles is developed in a succession of popular UAV configurations for multirotor systems. Such an arrangement, supported by frequent examples and end-of-chapter exercises, leads the reader from simple to more complex UAV configurations. Propulsion-system aerodynamics, essential in UAV design, is analyzed through blade-element and momentum theories, analysis which is followed by a description of drag and ground-aerodynamic effects. The central part of the book is dedicated to aerial-manipulator kinematics, dynamics, and control. Based on foundations laid in the opening chapters, this portion of the book is a structured presentation of Newton–Euler dynamic modeling that results in forward and backward equations in both fixed- and moving-coordinate systems. The Lagrange–Euler approach is applied to expand the model further, providing formalisms to model the variable moment of inertia later used to analyze the dynamics of aerial manipulators in contact with the environment. Using knowledge from sensor data, insights are presented into the ways in which linear, robust, and adaptive control techniques can be applied in aerial manipulation so as to tackle the real-world problems faced by scholars and engineers in the design and implementation of aerial robotics systems. The book is completed by path and trajectory planning with vision-based examples for tracking and manipulation.

Download or read book Gain Scheduled Aircraft Control Using Linear Parameter Varying Feedback written by Martin R. Breton and published by . This book was released on 1996-06-01 with total page 218 pages. Available in PDF, EPUB and Kindle. Book excerpt: Systems which vary significantly over an operating envelope, such as fighter aircraft, generally cannot be controlled by a single linear time- invariant controller. As a result, gain-scheduling methods are employed to design control laws which can provide the desired performance. This thesis examines a relatively new approach to gain-scheduling, in which the varying controller is designed from the outset to guarantee robust performance, thereby avoiding the disadvantages of point designs. Specifically, the parameter-varying (LPV) aircraft model is linearized using linear fractional transformations (LFT's), and the resulting control problem is characterized as the solution to a set of four linear matrix inequalities (LMI's). The supporting theory is reviewed and two pitch-rate controllers are designed; one for the full longitudinal aircraft model, and another for the short period model. It is found that, even though the varying controllers are quite conservative, they can guarantee better robust performance over a large portion of an operating envelope when compared to time-invariant u-synthesis controllers.

Download or read book Gain Scheduling of Aircraft Pitch Attitude and Control of Discrete Affine Linear Parametrically Varying Systems written by Zhe Lin and published by . This book was released on 2002 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt: This research is motivated by gain scheduling, a technique which has been successfully applied to many nonlinear control problems. In flight controls, the wide variations in the characteristics of the aircraft dynamics throughout the flight envelope make gain scheduling a particularly suitable design strategy. This research consists of two parts: (1) aircraft pitch attitude scheduling scheme designs, and (2) control of a class of linear parametrically varying (LPV) systems. In the first part, the classical gain scheduling technique and the single quadratic Lyapunov function (SQLF) based LPV technique are investigated. In the classical gain scheduling design, the H[subscript Infinity] mixed sensitivity GS/T method is chosen for local linear time invariant (LTI) designs to provide robustness to unmodeled dynamics and parametric uncertainties. Following a model reduction procedure that exploits the optimal controller structure, LTI controllers designed at the selected equilibrium points are reduced to second order controllers and realized in a feedback path configuration. Such controllers are shown to retain the superior robust performance at each flight condition, while having a low order that is amenable to scheduling. A gain-scheduling law is developed and simulation results verify that the closed-loop performance specifications are met. In the LPV design, the mixed sensitivity S/KS/T design setup is used. An approximation to the original LPV controller using the linear fractional transformation (LFT) representation is constructed. Our design exhibits potential applications of the LPV technique to commercial aircraft gain scheduling designs. In the second part, we consider a class of discrete, affine, linear parametrically varying (DALPV) systems. For this type of systems, the parameters are assumed to vary in a polytope and the state space matrices are assumed to depend affinely on the varying parameters. A sufficient condition is derived to analyze the stability and the l[subscript Infinity] to l[subscript Infinity] performance of a DALPV system. For an open-loop DALPV system, a procedure is proposed to design a gain-scheduled controller such that the close-loop system is asymptotically stable and achieves a certain level of l[subscript Infinity] to l[subscript Infinity] performance.

Download or read book New Achievements in Unmanned Systems written by T. Hikmet Karakoc and published by Springer Nature. This book was released on 2023-06-27 with total page 291 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unmanned systems are one of the fastest-growing and widely developing technologies in the world, offering many possibilities for a variety of research fields. This book comprises the proceedings of the 2021 International Symposium on Unmanned Systems and the Defense Industry (ISUDEF), a multi-disciplinary conference on a broad range of current research and issues in areas such as autonomous technology, unmanned aircraft technologies, avionics, radar systems, air defense, aerospace robotics and mechatronics, and aircraft technology design. ISUDEF allows researchers, scientists, engineers, practitioners, policymakers, and students to exchange information, present new technologies and developments, and discuss future direction, strategies, and priorities in the field of autonomous vehicles and unmanned aircraft technologies. Covers a range of emerging topics; Addresses current issues on autonomous vehicles and unmanned aircraft; Full proceedings of ISUDEF 2021 held at Howard University.

Download or read book Aerodynamics of Store Integration and Separation written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel. Symposium and published by . This book was released on 1996 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Advanced Flight Dynamics with Elements of Flight Control written by Nandan K. Sinha and published by CRC Press. This book was released on 2017-06-27 with total page 348 pages. Available in PDF, EPUB and Kindle. Book excerpt: Advanced Flight Dynamics aim to integrate the subjects of aircraft performance, trim and stability/control in a seamless manner. Advanced Flight Dynamics highlights three key and unique viewpoints. Firstly, it follows the revised and corrected aerodynamic modeling presented previously in recent textbook on Elementary Flight Dynamics. Secondly, it uses bifurcation and continuation theory, especially the Extended Bifurcation Analysis (EBA) procedure devised by the authors, to blend the subjects of aircraft performance, trim and stability, and flight control into a unified whole. Thirdly, rather than select one control design tool or another, it uses the generalized Nonlinear Dynamic Inversion (NDI) methodology to illustrate the fundamental principles of flight control. Advanced Flight Dynamics covers all the standard airplane maneuvers, various types of instabilities normally encountered in flight dynamics and illustrates them with real-life airplane data and examples, thus bridging the gap between the teaching of flight dynamics/ control theory in the university and its practice in airplane design bureaus. The expected reader group for this book would ideally be senior undergraduate and graduate students, practicing aerospace/flight simulation engineers/scientists from industry as well as researchers in various organizations. Key Features: Focus on unified nonlinear approach, with nonlinear analysis tools. Provides an up-to-date, corrected, and unified presentation of aircraft trim, stability and control analysis including nonlinear phenomena and closed-loop stability analysis. Contains a computational tool and real-life example carried through the chapters. Includes complementary nonlinear dynamic inversion control approach, with relevant aircraft examples. Fills the gap in the market for a text including non-linear flight dynamics and continuation methods.

Download or read book Mixed H2 Hoo Gain Scheduling Control of Aircraft written by Shyh-Pyng Shue and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Military Outlook written by Dr. Anis I. Milad and published by AuthorHouse. This book was released on 2019-05-16 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt: Military Outlook touches upon the problems in the American civilization. It also talks about the military weaknesses and strengths.

Download or read book The Aeronautical Journal written by and published by . This book was released on 2001 with total page 732 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 92 4301 to 92 4413 written by and published by . This book was released on 1992 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book IEEE Proceedings of the Southeastcon written by and published by . This book was released on 1993 with total page 718 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Feedback Systems written by Karl Johan Åström and published by Princeton University Press. This book was released on 2021-02-02 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The essential introduction to the principles and applications of feedback systems—now fully revised and expanded This textbook covers the mathematics needed to model, analyze, and design feedback systems. Now more user-friendly than ever, this revised and expanded edition of Feedback Systems is a one-volume resource for students and researchers in mathematics and engineering. It has applications across a range of disciplines that utilize feedback in physical, biological, information, and economic systems. Karl Åström and Richard Murray use techniques from physics, computer science, and operations research to introduce control-oriented modeling. They begin with state space tools for analysis and design, including stability of solutions, Lyapunov functions, reachability, state feedback observability, and estimators. The matrix exponential plays a central role in the analysis of linear control systems, allowing a concise development of many of the key concepts for this class of models. Åström and Murray then develop and explain tools in the frequency domain, including transfer functions, Nyquist analysis, PID control, frequency domain design, and robustness. Features a new chapter on design principles and tools, illustrating the types of problems that can be solved using feedback Includes a new chapter on fundamental limits and new material on the Routh-Hurwitz criterion and root locus plots Provides exercises at the end of every chapter Comes with an electronic solutions manual An ideal textbook for undergraduate and graduate students Indispensable for researchers seeking a self-contained resource on control theory

Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.

Download or read book Aircraft Control and Simulation written by Brian L. Stevens and published by John Wiley & Sons. This book was released on 2003-10-06 with total page 688 pages. Available in PDF, EPUB and Kindle. Book excerpt: This second edition covers aerodynamics, the control systems and the mathematics involved in analysing the performance of aircraft not only in the real world but also in computer-simulated flight and gaming. It includes new computer calculations in MatLab, which is commonly used in the industry.