3 edition of An investigation of nonlinear controller for propulsion controlled aircraft found in the catalog.
An investigation of nonlinear controller for propulsion controlled aircraft
by National Aeronautics and Space Administration, National Technical Information Service, distributor in Ames, IA : Dept. of Aerospace Engineering and Engineering Mechanics, Iowa State University, [Washington, D.C, Springfield, Va
Written in English
|Statement||prepared by Ping Lu.|
|Series||[NASA contractor report] -- NASA CR-203716.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Advanced Control of Aircraft, Spacecraft and Rockets introduces the reader to the concepts of modern control theory applied to the design and analysis of general flight control systems in a concise and mathematically rigorous style. It presents a comprehensive treatment of both atmospheric and space flight control systems including aircraft, rockets (missiles and launch vehicles), entry Cited by: Modeling and analysis for integrated airframe/propulsion control of vehicles during mode transition of over-under Turbine-Based-Combined-Cycle engines where the thrust is the interface between the aircraft control loop and the engine control loop. the previous nonlinear model with eight control inputs is now reduced into the one with Cited by: 2.
I. Programs on Integrated Flight / Propulsion Control 1. Navy Approach Power Compensation Systems 2. NASA Propulsion Controlled Aircraft – Fighter – Transport 3. Yaw stabilization of a Transport using Propulsion Control 4. Increased Power Response for Runway Incursion II. Projects for Integrated Flight / Propulsion Control | 2. Integrated Propulsion / Flight Control Example: The PCA Program • Program initiated after United Flight lost all flight control and landed at Sioux City, Iowa • Direct throttle control used, very difficult to control Phugoid and Dutch Roll Oscillations • Boeing developed a Propulsion Controlled Aircraft (PCA) flight.
This book presents a general nonlinear control design methodology for nonlinear uncertain dynamical systems. Specifically, a hierarchical nonlinear switching control framework is developed that provides a rigorous alternative to gain scheduling control for general nonlinear uncertain by: This is the first book to focus on the use of nonlinear analysis and synthesis techniques for aircraft control. The book will be of interest to engineers, researchers, and students in control engineering, and especially aircraft control.
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Cases where complete loss of control systems has occurred in multi-engine aircraft, pilots used propulsion system to regain limited control of the aircraft with various degrees of success (see ).
In order to evaluate the feasibility of using only engine thrust modulation for emergency. One objective was to determine the degree of control available with manual manipulation (open-loop) of the engine throttles. Flight tests and simulations soon showed that a closed loop controller could improve the chances of making a safe runway landing.
The major work to date has concentrated on three aircraft (F, F, and the MD).Author: Ping Lu. Get this from a library. An investigation of nonlinear controller for propulsion controlled aircraft: final report (February 1, Janu ).
[Ping Lu; United States. National Aeronautics and. Nonlinear rolling motion of a canard-controlled missile configuration at angles of attack from 0 to 30 degrees in incompressible flowCited by: Ultimately the purpose of the nonlinear flight control system developed in this work is to pave the way for an adaptive reconfigurable nonlinear controller that would make aviation a safe way of.
Primary sources of nonlinearity are the intrinsic nonlinear dynamics of the aircraft and the state and control constraints within which the aircraft must operate.
This paper examines how these nonlinearities affect the ability to control the aircraft and how they may contribute to loss of by: Nonlinear Image-Based Visual Servo Controller for the Flare Maneuver of Fixed-Wing Aircraft Using Optical Flow IEEE Transactions on Control Systems Technology, Vol.
23, No. 2 Adaptive fuzzy multi-surface sliding control of multiple-input and multiple-output autonomous flight systemsCited by: Design of a nonlinear dynamic inversion controller for trajectory following and maneuvering for fixed wing aircraft Supervising Control for Unmanned Aerial Vehicles Mathematical Problems in Engineering, Vol.
Cited by: Flight Control System Design for Propulsion-Controlled Aircraft Article in Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering (4) June.
Primary flight controls of commercial aircraft. Pitch control is exercised by four elevators located on the trailing edge of the aircraft. Each elevator section is independently powered by a dedicated flight control actuator, which in turn is powered by one of several aircraft hydraulic power systems.
In this paper, an aircraft landing autopilot is designed using the nonlinear energy-based control method (NEM). This method provides the automatic landing by energy manage-ment idea.
control mode. The nominal multivariable mode uses a controller scheduled on total corrected airflow . This paper focuses on the design of a controller for the nominal multivariable mode. The baseline controller is used during the initialization part of the simulation. The baseline control interconnection (Figure ) has an two loops.
o Fan, _ BurnerFile Size: 3MB. The design requirement is for a flight test trajectory controller (FTTC) capable of closed-loop, outer-loop control of an F aircraft performing high-quality research flight test maneuvers. First book focusing on the use of nonlinear analysis and synthesis techniques for aircraft control; Also the first book to address in detail closed-loop control problems for aircraft "on-ground" – ie speed and directional control of aircraft before take-off and after touch down.
Nonlinear dynamics and control of a laterally mass varying fighter aircraft 14 August | Proceedings of the Institution of Mechanical Engineers, Part Cited by: In this paper, the nonlinear robust control problem is dealt with for uncertain hypersonic vehicle subject to parametric uncertainties, external disturbances, nonlinear dynamics, and couplings between the flight dynamics and the propulsion systems.
A nonlinear robust controller is proposed consisting of a feedback linearization controller, a Cited by: Nonlinear Analysis and Synthesis Techniques for Aircraft Control (Lecture Notes in Control and Information Sciences) [Bates, Declan, Hagström, Martin] on *FREE* shipping on qualifying offers.
Nonlinear Analysis and Synthesis Techniques for Aircraft Control (Lecture Notes in Control and Information Sciences). This paper describes the application of two frequency domain analysis tools, the structured singular value μ and the ν-gap metric, to the problem of evaluating the robustness properties of a multivariable integrated flight and propulsion control (IFPC) system for an experimental V/STOL aircraft ions in aircraft parameters and dynamics over the V/STOL flight envelope are Cited by: Model-Based Control of a Nonlinear Aircraft Engine Simulation using an Optimal Tuner Kalman Filter Approach Joseph W.
Connolly NASA Glenn Research Center, Cleveland, OHUSA Je rey T. Csanky NASA Glenn Research Center, Cleveland, OHUSA Amy Chicatelliz Vantage Partners LLC, Brook Park, OHUSA Jacob KilverxCited by: Abstract.
An aircraft is intrinsically a nonlinear system. Therefore, if linear controllers are to be used in the aircraft flight control system, several linear controllers have to be designed and then gain-scheduled over the operating regime of the aircraft. Nonlinear Predictive Controller 66 Mach = case 66 Mach = case 75 Approximate Nonlinear Receding-Horizon Controller 81 Mach = case 81 Mach = case 87 CHAPTER 6 CONTROLLER PERFORMANCE FOR UNHEALTHY AIRCRAFT 91 Propulsion Controlled Aircraft (PCA) 91 Simulation Results Then, a Min–Max controller is designed for a two-spool turbofan engine model and the asymptotic stability of the control system is ensured using the provided methodology.
The performance of the designed controller with the linear and nonlinear turbofan engine model is compared to the Min–Max/SMC approach in fault-free and fault tolerant Cited by: 3.Propulsion-system-specific results are presented from the application of the integrated methodology for propulsion and airframe control (IMPAC) design approach to integrated flight/propulsion.