Download or read book Control Law Synthesis for Lockheed Martin s Innovative Control Effectors Aircraft Concept written by Cameron James Segard and published by . This book was released on 2019 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis documents a conventional and modern flight control system design process carried out on a tailless aircraft Simulink model with innovative control effectors provided by Lockheed Martin. To set scope and design requirements a performance analysis was carried out to categorize the aircraft. Evaluation of open-loop dynamics reveled modal instabilities as well as state and control coupling. Flight condition dependent pole migration mapping reveled large changes in the aircraft’s static stability. Leading to the development of a four channel proportional-integral- derivative (PID) stability and control augmentation system (SCAS) controlling pitch-rate, roll-rate, side-slip angle, and airspeed states. PID gains are scheduled via iterative constrained optimization throughout the linearized flight envelope generating a full flight envelope flight control system. The linear quadratic (LQ) servo design method provides optimal control allocation at every linearized flight condition, controlling angle of attack, roll angle, side-slip angle, and airspeed states. LQ controlled states were modified to be equivalent to the PID control system for real time handling qualities (HQ) evaluation. Both control systems required gain scaling to prevent state resonance and control saturation during nonlinear 6-degree-of-freedom (6DOF) real-time simulation. Either method achieved stable augmented control of the innovative control effectors (ICE) aircraft throughout the flight envelope. The HQ’s for the control methods are satisfactory for conventional aerobatics but became dissimilar for sustained super-maneuverability flight conditions.
Download or read book Modular Control Law Design for the Innovative Control Effectors ICE Tailless Fighter Aircraft Configuration 101 3 written by James F. Buffington and published by . This book was released on 1999-06-01 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modular flight control system is developed for a tailless fighter aircraft with innovative control effectors. Dynamic inversion control synthesis is used to develop a full envelope flight control law. Minor dynamic inversion command variable revisions are required due to the tailless nature of the configuration studied to achieve nominal stability and performance. Structured singular value and simulation analysis shows that robust stability is achieved and robust performance is slightly deficient due to modeling errors. A multi- branch linear programming based method is developed and used for allocation of redundant limited control effectors.
Download or read book Model Predictive Control Synthesis for the Innovative Control Effector Tailless Fighter Aircraft written by Christopher Charles Proctor and published by . This book was released on 2019 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: A nonlinear model predictive control law was developed for the Lockheed Martin Innovative Control Effector tailless fighter aircraft to track way points. In general, aircraft are described by nonlinear dynamics that are dependent on the regime of flight. Additionally strict requirements on state and actuator constraints are common to all aircraft. Tailless aircraft are usually overdetermined systems, meaning solutions to control problems are not unique, and the system is non-affine. The proposed nonlinear control law considers those constraints during run-time, and solves the nonlinear control problem for a range of points within different flight regimes. The control law was developed using a computer simulation of the tailless fighter aircraft, and further simulation was used to validate the control law when applied to the aircraft. It was found that the controller was able to track reference step commands in altitude anywhere from sea level to 50,000 ft and remain stable. It is also shown that the single nonlinear controller is able to handle lateral translations at the same time as altitude commands, demonstrating its authority over the entire 6 degree of freedom system. The controller is not real time applicable but research indicates that it is possible to apply such a technique in real time. It was concluded that nonlinear model predictive control is a viable control synthesis technique for tailless fighter aircraft if real-time algorithms can be developed.
Download or read book Modular Control Design for the Innovative Control Effectors ICE Tailless Fighter Aircraft Configuration 101 3 written by James Buffington and published by . This book was released on 1999-06-01 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modular flight control system is developed for a tailless fighter aircraft with innovative control effectors. Dynamic inversion control synthesis is used to develop a full envelope flight control law, Minor dynamic inversion command variable revisions are required due to the tailless nature of the configuration studied to achieve nominal stability and performance. Structured singular value and simulation analysis shows that robust stability is achieved and robust performance is slightly deficient due to modeling errors. A multi- branch linear programming-based method is developed and used for allocation of redundant limited control effectors.
Download or read book Innovative Control Effectors ICE written by E. L. Roetman and published by . This book was released on 1996 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a joint U.S. Air Force. U.S. Navy sponsored investigation of innovative aerodynamic control concepts for fighter aircraft without vertical tails. Land-based and carrier-based configurations were analyzed to determine the flying qualities, performance, and aircraft-level integration impacts of the innovative controls. Six control concepts were evaluated for their potential to provide sufficient lateral-directional control power to a highly maneuverable tailless fighter. They were: (1) split ailerons; (2) movable chine strakes; (3) seamless leading and trailing edge flaps; (4) pneumatic forebody devices; (5) wing leading edge blowing; (6) wing mounted yaw vanes. After a preliminary screening, only the first two and a new concept, variable dihedral horizontal tails were chosen for further investigation. Detailed evaluations of the three selected controllers against baseline fighter configurations with vertical tails included low-speed, high-speed, and high AOA flying qualities performance, structural weight and subsystem integration impacts, signature performance, and carrier suitability impacts. The variable dihedral horizontal tail was evaluated as the best all-round control effector of those investigated. The split aileron and movable chine strake were ranked 2nd and 3rd, respectively.
Download or read book A Generic Inner Loop Control Law Structure for Six Degree Of Freedom Conceptual Aircraft Design written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-27 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A generic control system framework for both real-time and batch six-degree-of-freedom simulations is presented. This framework uses a simplified dynamic inversion technique to allow for stabilization and control of any type of aircraft at the pilot interface level. The simulation, designed primarily for the real-time simulation environment, also can be run in a batch mode through a simple guidance interface. Direct vehicle-state acceleration feedback is required with the simplified dynamic inversion technique. The estimation of surface effectiveness within real-time simulation timing constraints also is required. The generic framework provides easily modifiable control variables, allowing flexibility in the variables that the pilot commands. A direct control allocation scheme is used to command aircraft effectors. Primary uses for this system include conceptual and preliminary design of aircraft, when vehicle models are rapidly changing and knowledge of vehicle six-degree-of-freedom performance is required. A simulated airbreathing hypersonic vehicle and simulated high-performance fighter aircraft are used to demonstrate the flexibility and utility of the control system.Cox, Timothy H. and Cotting, M. ChristopherArmstrong Flight Research CenterAIRCRAFT DESIGN; DEGREES OF FREEDOM; CONTROL SYSTEMS DESIGN; ALGORITHMS; AIRCRAFT PERFORMANCE; COMPUTERIZED SIMULATION; HYPERSONIC VEHICLES; STABILITY; CONTROL SURFACES; REAL TIME OPERATION; CONTROLLABILITY...
Download or read book Flight Control Law Synthesis Using Neural Network Theory written by and published by . This book was released on 1990 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: A commonly used technique for advanced fighter aircraft control law development involves a lengthy process of linearizing the aircraft model and calculating many control system gains via conventional linear methods. This process must be repeated for a number of trim points within the flight envelope to achieve the aircraft stability and flying qualities mandated by various military specifications. Neural networks have been used extensively in many applications such as pattern recognition and optimization because of their ability to create nonlinear mappings of continuous valued inputs through supervised learning. This report outlines a concept which incorporates emerging neural network technology with present-day control theory to produce a system by which optimal controller gains can be automatically generated. The research completed to date and the results contained in this report are intended to provide a proof of concept by applying the neural network synthesis technique to some simplified linear and nonlinear examples.
Download or read book Innovative Control Effectors ICE Phase III written by Kenneth M. Dorsett and published by . This book was released on 1997 with total page 420 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the Phase 2 portion of a joint U.S. Air Force U.S. Navy sponsored investigation of innovative aerodynamic control concepts for fighter aircraft without vertical tails. The Phase 1 work consisted of effector performance prediction, vehicle integration assessment, and transition studies for numerous control effector concepts. The Phase 2 effort is an extension of the Phase 1 work and consists mainly of three wind tunnel tests to acquire more information about the aerodynamic performance of all moving wing tips (AMTs) and spoiler slot deflectors (SSDs). These tests clearly showed both the AMT and SSD can produce significant yaw control power and are strong control effector candidates for tailless fighters. Predicted vehicle dynamics from Phase 1 are compared with predictions developed utilizing the new aerodynamic data acquired in Phase 2.
Download or read book Nonlinear Analysis and Synthesis Techniques for Aircraft Control written by Declan Bates and published by Springer. This book was released on 2007-10-04 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the first book to focus on the use of nonlinear analysis and synthesis techniques for aircraft control. It is also the first book to address in detail closed-loop control problems for aircraft "on-ground" – i.e. speed and directional control of aircraft before take-off and after touch down. The book will be of interest to engineers, researchers, and students in control engineering, and especially aircraft control.
Download or read book A Generic Inner Loop Control Law Structure for Six Degree Of Freedom Conceptual Aircraft Design written by Timothy H. Cox and published by BiblioGov. This book was released on 2013-07 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: A generic control system framework for both real-time and batch six-degree-of-freedom simulations is presented. This framework uses a simplified dynamic inversion technique to allow for stabilization and control of any type of aircraft at the pilot interface level. The simulation, designed primarily for the real-time simulation environment, also can be run in a batch mode through a simple guidance interface. Direct vehicle-state acceleration feedback is required with the simplified dynamic inversion technique. The estimation of surface effectiveness within real-time simulation timing constraints also is required. The generic framework provides easily modifiable control variables, allowing flexibility in the variables that the pilot commands. A direct control allocation scheme is used to command aircraft effectors. Primary uses for this system include conceptual and preliminary design of aircraft, when vehicle models are rapidly changing and knowledge of vehicle six-degree-of-freedom performance is required. A simulated airbreathing hypersonic vehicle and simulated high-performance fighter aircraft are used to demonstrate the flexibility and utility of the control system.
Download or read book Integrated Flight Control Law Synthesis for an Aeroelastic Forward swept Wing Aircraft written by Kapseong Ro and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Acsynt Inner Loop Flight Control Design Study written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Ames Research Center developed the Aircraft Synthesis (ACSYNT) computer program to synthesize conceptual future aircraft designs and to evaluate critical performance metrics early in the design process before significant resources are committed and cost decisions made. ACSYNT uses steady-state performance metrics, such as aircraft range, payload, and fuel consumption, and static performance metrics, such as the control authority required for the takeoff rotation and for landing with an engine out, to evaluate conceptual aircraft designs. It can also optimize designs with respect to selected criteria and constraints. Many modern aircraft have stability provided by the flight control system rather than by the airframe. This may allow the aircraft designer to increase combat agility, or decrease trim drag, for increased range and payload. This strategy requires concurrent design of the airframe and the flight control system, making trade-offs of performance and dynamics during the earliest stages of design. ACSYNT presently lacks means to implement flight control system designs but research is being done to add methods for predicting rotational degrees of freedom and control effector performance. A software module to compute and analyze the dynamics of the aircraft and to compute feedback gains and analyze closed loop dynamics is required. The data gained from these analyses can then be fed back to the aircraft design process so that the effects of the flight control system and the airframe on aircraft performance can be included as design metrics. This report presents results of a feasibility study and the initial design work to add an inner loop flight control system (ILFCS) design capability to the stability and control module in ACSYNT. The overall objective is to provide a capability for concurrent design of the aircraft and its flight control system, and enable concept designers to improve performance by exploiting the interrelationships between aircraft...
Download or read book Aircraft Control and Simulation written by Brian L. Stevens and published by John Wiley & Sons. This book was released on 2015-10-02 with total page 768 pages. Available in PDF, EPUB and Kindle. Book excerpt: Get a complete understanding of aircraft control and simulation Aircraft Control and Simulation: Dynamics, Controls Design, and Autonomous Systems, Third Edition is a comprehensive guide to aircraft control and simulation. This updated text covers flight control systems, flight dynamics, aircraft modeling, and flight simulation from both classical design and modern perspectives, as well as two new chapters on the modeling, simulation, and adaptive control of unmanned aerial vehicles. With detailed examples, including relevant MATLAB calculations and FORTRAN codes, this approachable yet detailed reference also provides access to supplementary materials, including chapter problems and an instructor's solution manual. Aircraft control, as a subject area, combines an understanding of aerodynamics with knowledge of the physical systems of an aircraft. The ability to analyze the performance of an aircraft both in the real world and in computer-simulated flight is essential to maintaining proper control and function of the aircraft. Keeping up with the skills necessary to perform this analysis is critical for you to thrive in the aircraft control field. Explore a steadily progressing list of topics, including equations of motion and aerodynamics, classical controls, and more advanced control methods Consider detailed control design examples using computer numerical tools and simulation examples Understand control design methods as they are applied to aircraft nonlinear math models Access updated content about unmanned aircraft (UAVs) Aircraft Control and Simulation: Dynamics, Controls Design, and Autonomous Systems, Third Edition is an essential reference for engineers and designers involved in the development of aircraft and aerospace systems and computer-based flight simulations, as well as upper-level undergraduate and graduate students studying mechanical and aerospace engineering.
Download or read book Feedback Control Laws for Highly Maneuverable Aircraft written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a study of the application of H infinity and mu synthesis techniques to the design of feedback control laws for the longitudinal dynamics of the High Angle of Attack Research Vehicle (HARV) are presented. The objective of this study is to develop methods for the design of feedback control laws which cause the closed loop longitudinal dynamics of the HARV to meet handling quality specifications over the entire flight envelope. Control law designs are based on models of the HARV linearized at various flight conditions. The control laws are evaluated by both linear and nonlinear simulations of typical maneuvers. The fixed gain control laws resulting from both the H infinity and mu synthesis techniques result in excellent performance even when the aircraft performs maneuvers in which the system states vary significantly from their equilibrium design values. Both the H infinity and mu synthesis control laws result in performance which compares favorably with an existing baseline longitudinal control law. Garrard, William L. and Balas, Gary J. Unspecified Center NAG1-1380...
Download or read book Methods of Analysis and Synthesis of Piloted Aircraft Flight Control Systems Vol 1 Fundamentals of Design of Piloted Aircraft Flight Control Systems written by and published by . This book was released on 1952 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Generic Guidance and Control Structure for Six Degree Of Freedom Conceptual Aircraft Design written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-24 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A control system framework is presented for both real-time and batch six-degree-of-freedom simulation. This framework allows stabilization and control with multiple command options, from body rate control to waypoint guidance. Also, pilot commands can be used to operate the simulation in a pilot-in-the-loop environment. This control system framework is created by using direct vehicle state feedback with nonlinear dynamic inversion. A direct control allocation scheme is used to command aircraft effectors. Online B-matrix estimation is used in the control allocation algorithm for maximum algorithm flexibility. Primary uses for this framework include conceptual design and early preliminary design of aircraft, where vehicle models change rapidly and a knowledge of vehicle six-degree-of-freedom performance is required. A simulated airbreathing hypersonic vehicle and a simulated high performance fighter are controlled to demonstrate the flexibility and utility of the control system. Cotting, M. Christopher and Cox, Timothy H. Armstrong Flight Research Center NASA/TM-2005-212866, H-2596, AIAA Paper 2005-0032
Download or read book Output Model Following Control Synthesis for an Oblique Wing Aircraft written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-09 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent interest in oblique-wing aircraft has focused on the potential aerodynamic performance advantage of a variable-skew oblique wing over a conventional or symmetric sweep wing. Unfortunately, the resulting asymmetric configuration has significant aerodynamic and inertial cross-coupling between the aircraft longitudinal and lateral-directional axes. Presented here is a decoupling control law synthesis technique that integrates stability augmentation, decoupling, and the direct incorporation of desired handling qualities into an output feedback controller. The proposed design technique uses linear quadratic regulator concepts in the framework of explicit model following. The output feedback strategy used is a suboptimal projection from the state space to the output space. Dynamics are then introduced into the controller to improve steady-state performance and increase system robustness. Closed-loop performance is shown by application of the control laws to the linearized equations of motion and nonlinear simulation of an oblique-wing aircraft. Pahle, Joseph W. Armstrong Flight Research Center RTOP 533-06-01...
