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Integrated Flight Propulsion Control With Variable Rotor Speed Command For Rotorcraft
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Book Synopsis Integrated Flight/propulsion Control with Variable Rotor Speed Command for Rotorcraft by : Stanford University. Department of Aeronautics and Astronautics
Download or read book Integrated Flight/propulsion Control with Variable Rotor Speed Command for Rotorcraft written by Stanford University. Department of Aeronautics and Astronautics and published by . This book was released on 1996 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Rotorcraft Flight-propulsion Control Integration by : James R. Mihaloew
Download or read book Rotorcraft Flight-propulsion Control Integration written by James R. Mihaloew and published by . This book was released on 1988 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Control Design for Rotorcraft with Variable Rotor Speed by : Wei Guo
Download or read book Flight Control Design for Rotorcraft with Variable Rotor Speed written by Wei Guo and published by . This book was released on 2009 with total page 121 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight control design issues for rotorcraft with variable rotor speed are investigated, and new design methodologies are developed to deal with the challenges of variable rotor speed. The benefits of using variable rotor speed for rotorcraft are explored with a rotor speed optimization study using a modified GENHEL model of UH-60A Blackhawk. The optimization results recommend to use the optimal rotor speed in each flight condition to improve the helicopter performance. The efforts are made to accommodate the optimal rotor speed schedule into the flight control system design and also address the stability issues due to the rotor speed variation. The rotor speed optimization results show significant performance improvements can be achieved with moderate reductions in rotor speed. The objective of the control design is to accommodate these rotor speed variations, while achieving desired flying qualities and maneuver performance. A gain scheduled model following/model inversion controller is used to control the roll, pitch, yaw, heave, and rotor speed degrees of freedom. Rotor speed is treated as a redundant control effector for the heave axis, and different control allocation schemes are investigated. The controllers are evaluated based on step responses and the ADS-33E height response requirement. Results show that dynamic variation in rotor speed can improve maximum climb rate and flying qualities for moderate to large commands in vertical speed, but that non-linear effects present significant challenges when integrating control of the aircraft and the engine. The effects of reduced rotor speeds on stability margins, torque required, and stability issues are also studied. A power command system in the vertical axis is designed to incorporate variable rotor speed while handling torque limits and other constraints. The vertical axis controller uses a fixed nonlinear mapping to find the combination of collective pitch and rotor speed to optimize performance in level flight, climbing/descending flight, and steady turns. In this scheme, the controller is open-loop, making it an inexpensive and reliable solution. The mapping is designed to produce a desired power level for a given pilot input. Thus the mapping can take into account the performance limits associated with the vertical axis such as power limits, torque limits, and maximum rate of descent. A model following controller is implemented for the pitch, roll, and yaw axes. The piloted simulation was performed to evaluate the controller. The impact of variable rotor speed on closed loop stability of rotorcraft is discussed. The model following controller can provide high bandwidth control and improve performance using variable rotor speed. However, reduction of rotor speed can result in rotor body coupling and even instability. A rotor state feedback control law can be designed independently and easily integrated into the baseline model following control architecture. Simulations were performed to verify the effectiveness of RSF control to stabilize the rotorcraft dynamics or improve the command tracking performance in the presence of reduced rotor RPM.
Book Synopsis Rotorcraft Flight-propulsion Control Integration by : James R. Mihaloew
Download or read book Rotorcraft Flight-propulsion Control Integration written by James R. Mihaloew and published by . This book was released on 1988 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Propulsion System Performance Resulting from an Integrated Flight/propulsion Control Design by : Duane Loren Mattern
Download or read book Propulsion System Performance Resulting from an Integrated Flight/propulsion Control Design written by Duane Loren Mattern and published by . This book was released on 1992 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 control design for a 'short takeoff and vertical landing' (STOVL) aircraft in transition flight. The IMPAC method is briefly discussed and the propulsion system specifications for the integrated control design are examined. The structure of a linear engine controller that results from partitioning a linear centralized controller is discussed. The details of a nonlinear propulsion control system are presented, including a scheme to protect the engine operational limits: the fan surge margin and the acceleration/deceleration schedule that limits the fuel flow. Also, a simple but effective multivariable integrator windup protection scheme is examined. Nonlinear closed-loop simulation results are presented for two typical pilot commands for transition flight: acceleration while maintaining flightpath angle and a change in flightpath angle while maintaining airspeed. The simulation nonlinearities include the airframe/engine coupling, the actuator and sensor dynamics and limits, the protection scheme for the engine operational limits, and the integrator windup protection. Satisfactory performance of the total airframe plus engine system for transition flight, as defined by the specifications, was maintained during the limit operation of the closed-loop engine subsystem.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722748029 Total Pages :30 pages Book Rating :4.7/5 (48 download)
Book Synopsis Rotorcraft Flight-Propulsion Control Integration by : National Aeronautics and Space Administration (NASA)
Download or read book Rotorcraft Flight-Propulsion Control Integration written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Ames and Lewis Research Centers, in conjunction with the Army Research and Technology Laboratories have initiated and completed, in part, a joint research program focused on improving the performance, maneuverability, and operating characteristics of rotorcraft by integrating the flight and propulsion controls. The background of the program, its supporting programs, its goals and objectives, and an approach to accomplish them are discussed. Results of the modern control governor design of the T700 and the Rotorcraft Integrated Flight-Propulsion Control Study, which were key elements of the program, are also presented. Mihaloew, James R. and Ballin, Mark G. and Ruttledge, D. G. C. Ames Research Center; Glenn Research Center ...
Book Synopsis Integrated Flight and Propulsion Controls for Advanced Aircraft Configurations by : Walter C. Merrill
Download or read book Integrated Flight and Propulsion Controls for Advanced Aircraft Configurations written by Walter C. Merrill and published by . This book was released on 1995 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight-determined Benefits of Integrated Flight-propulsion Control Systems by : James F. Stewart
Download or read book Flight-determined Benefits of Integrated Flight-propulsion Control Systems written by James F. Stewart and published by . This book was released on 1992 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight-determined Benefits of Integrated Flight-propulsion Control Systems by : James F. Stewart
Download or read book Flight-determined Benefits of Integrated Flight-propulsion Control Systems written by James F. Stewart and published by . This book was released on 1992 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Continuously Variable Rotorcraft Propulsion System by : Naveen Kumar Vallabhaneni
Download or read book Continuously Variable Rotorcraft Propulsion System written by Naveen Kumar Vallabhaneni and published by LAP Lambert Academic Publishing. This book was released on 2012-03 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: Explore the variable speed operation and shift response of a prototype of a continuously variable rotorcraft propulsion system and development of a Comprehensive Variable Speed Rotorcraft Propulsion system Modeling (CVSRPM) tool.Simulate the drive system dynamics in steady forward speed condition in an attempt to build upon previous variable speed rotorcraft propulsion studies by including, fully nonlinear first principles based transient gas-turbine engine model with shaft flexibility and incorporating a basic flight dynamics model to account for interactions with the flight control system. Explore the interactions between the various subsystems and obtain insight into the continuing development of variable speed rotorcraft propulsion systems and a study of various variable ratio transmissions that have already been explored.
Book Synopsis Integrated Flight Propulsion Control Research Results Using the NASA F-15 HIDEC Flight Research Facility by : James F. Stewart
Download or read book Integrated Flight Propulsion Control Research Results Using the NASA F-15 HIDEC Flight Research Facility written by James F. Stewart and published by . This book was released on 1992 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comprehensive modeling and analysis of rotorcraft variable speed propulsion system with coupled engine/transmission/rotor dynamics by : Hans A. DeSmidt
Download or read book Comprehensive modeling and analysis of rotorcraft variable speed propulsion system with coupled engine/transmission/rotor dynamics written by Hans A. DeSmidt and published by . This book was released on 2013 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1988 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Application of an Integrated Methodology for Propulsion and Airframe Control Design to a STOVL Aircraft by :
Download or read book Application of an Integrated Methodology for Propulsion and Airframe Control Design to a STOVL Aircraft written by and published by . This book was released on 1994 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Integrated Flight-propulsion Control Concepts for Supersonic Transport Airplanes by :
Download or read book Integrated Flight-propulsion Control Concepts for Supersonic Transport Airplanes written by and published by . This book was released on 1990 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Criteria for Design of Integrated Flight/propulsion Control Systems for STOVL Fighter Aircraft by : James A. Franklin
Download or read book Criteria for Design of Integrated Flight/propulsion Control Systems for STOVL Fighter Aircraft written by James A. Franklin and published by . This book was released on 1993 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722979188 Total Pages :144 pages Book Rating :4.9/5 (791 download)
Book Synopsis Cooperative Control Theory and Integrated Flight and Propulsion Control by : National Aeronautics and Space Administration (NASA)
Download or read book Cooperative Control Theory and Integrated Flight and Propulsion Control 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 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: The major contribution of this research was the exposition of the fact that airframe and engine interactions could be present, and their effects could include loss of stability and performance of the control systems. Also, the significance of two directional, as opposed to one-directional, coupling was identified and explained. A multivariable stability and performance analysis methodology was developed, and applied to several candidate aircraft configurations. In these example evaluations, the significance of these interactions was underscored. Also exposed was the fact that with interactions present along with some integrated control approaches, the engine command/limiting logic (which represents an important nonlinear component of the engine control system) can impact closed-loop airframe/engine system stability. Finally, a brief investigation of control-law synthesis techniques appropriate for the class of systems was pursued, and it was determined that multivariable techniques, including model-following formulations of LQG and/or H infinity methods, showed promise. However, for practical reasons, decentralized control architectures are preferred, which is an architecture incompatible with these synthesis methods. The major contributions of the second phase of the grant was the development of conditions under which no decentralized controller could achieve closed loop system requirements on stability and/or performance. Sought were conditions that depended only on properties of the plant and the requirement, and independent of any particular control law or synthesis approach. Therefore, they could be applied a priori, before synthesis of a candidate control law. Under this grant, such conditions were found regarding stability, and encouraging initial results were obtained regarding performance. Schmidt, David K. and Schierman, John D. Unspecified Center AIRCRAFT STABILITY; AIRFRAMES; CONTROL THEORY; CONTROLLABILITY; ENGINE AIRFRAME INTEGRATION; ENGINE CONTROL; F...
