Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Discrete Proportional Plus Integral Pi Multivariable Control Laws For The Control Reconfigurable Combat Aircraft Crca
Download Discrete Proportional Plus Integral Pi Multivariable Control Laws For The Control Reconfigurable Combat Aircraft Crca full books in PDF, epub, and Kindle. Read online Discrete Proportional Plus Integral Pi Multivariable Control Laws For The Control Reconfigurable Combat Aircraft Crca ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Discrete Proportional Plus Integral (PI) Multivariable Control Laws for the Control Reconfigurable Combat Aircraft (CRCA). by : Jamie L. Foelker (CAPT, USAF.)
Download or read book Discrete Proportional Plus Integral (PI) Multivariable Control Laws for the Control Reconfigurable Combat Aircraft (CRCA). written by Jamie L. Foelker (CAPT, USAF.) and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Discrete Proportional Plus Integral (PI) Multivariable Control Laws for the Control Reconfigurable Combat Aircraft (CRCA). by :
Download or read book Discrete Proportional Plus Integral (PI) Multivariable Control Laws for the Control Reconfigurable Combat Aircraft (CRCA). written by and published by . This book was released on 1989 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: Multivariable control laws developed by Dr. Brian Porter of the University of Salford, England are used to successfully perform maneuvering tracking tasks with the NASA/Grumman Control Reconfigurable Combat Aircraft (CRCA). Porter's method is used to design discrete Proportional plus Integral (PI) control laws. Output and selected state rate feedback are used. The results in three no failure flight conditions show robust tracking control of the CRCA for five selected maneuvers. Single failures are introduced to test the ability of the fixed-gain designs to successfully control the aircraft and perform the maneuvers. The time responses show that discrete PI control law can make the CRCA successfully perform all five maneuvers for two of the three control surface failures investigated in two of the three point designs. The step response PI control law results in stable control for only one of three failure situations. Keywords: Control theory; Flight control systems; Multivariable control; Adaptive control systems. (jes).
Book Synopsis Multivariable Control Law Design for the Control Reconfigurable Combat Aircraft (CRCA). by : Daryl Hammond
Download or read book Multivariable Control Law Design for the Control Reconfigurable Combat Aircraft (CRCA). written by Daryl Hammond and published by . This book was released on 1988 with total page 422 pages. Available in PDF, EPUB and Kindle. Book excerpt: Typically, control law analysis and design for an aircraft include separating the longitudinal and lateral equations of motion and designing control laws for each separate motion. The simplifying assumptions are often valid and do not adversely affect the analysis and design when aerodynamic cross-coupling is minimal. The Control Reconfigurable Combat Aircraft (CRCA) design includes an all-flying canard with 30 degrees of dihedral angle which prevents the normal separation of lateral and longitudinal equations because of high aerodynamic cross-coupling. The multivariable control law design used in this thesis incorporates the high gain error actuated Proportional plus Integral (PI) controller developed by Professor Brian Porter of the University of Salford, England. Control law development and simulation are preformed using the computer aided design program called mat. Two successful fixed gain controller design methods and an adaptive controller design are demonstrated. The three control surfaces on each wing are operated together, so they are treated in this thesis as one control effector. Thus, the five CRCA control inputs for this design consist of two canards, left trailing edge flaperon, right trailing edge flaperon, and rudder. An adaptive controller design, using a recursive least squares (RLS) parameter estimation algorithm, is developed for a self-tuning control system. Theses. (SDW).
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1990 with total page 482 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Multivariable Control Law Design for the Control Reconfigurable Combat Aircraft (CRCA). by : Daryl Hammond (CAPT, USAF.)
Download or read book Multivariable Control Law Design for the Control Reconfigurable Combat Aircraft (CRCA). written by Daryl Hammond (CAPT, USAF.) and published by . This book was released on 1988 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Proceedings of the IEEE 1990 National Aerospace and Electronics Conference, NAECON 1990 by :
Download or read book Proceedings of the IEEE 1990 National Aerospace and Electronics Conference, NAECON 1990 written by and published by . This book was released on 1990 with total page 464 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1990 with total page 1652 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1990 with total page 1102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Proceedings of the IEEE 1989 National Aerospace and Electronics Conference, NAECON 1989 by :
Download or read book Proceedings of the IEEE 1989 National Aerospace and Electronics Conference, NAECON 1989 written by and published by . This book was released on 1989 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. AIR FORCE INSTITUTE OF TECHNOLOGY, WRIGHT-PATTERSON AFB, Multivariable control design for the control reconfigurable combat aircraft (CRCA). by : D. Hammond
Download or read book U.S. AIR FORCE INSTITUTE OF TECHNOLOGY, WRIGHT-PATTERSON AFB, Multivariable control design for the control reconfigurable combat aircraft (CRCA). written by D. Hammond and published by . This book was released on with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Reconfigurable Multivariable Control Law for Commercial Airplane Using a Direct Digital Output Feedback Design by :
Download or read book Reconfigurable Multivariable Control Law for Commercial Airplane Using a Direct Digital Output Feedback Design written by and published by . This book was released on 1984 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Multivariable Control Law Design for the AFTI/F-16 with a Failed Control Surface Using a Parameter-Adaptive Controller by : Julio E. Velez
Download or read book Multivariable Control Law Design for the AFTI/F-16 with a Failed Control Surface Using a Parameter-Adaptive Controller written by Julio E. Velez and published by . This book was released on 1987 with total page 183 pages. Available in PDF, EPUB and Kindle. Book excerpt: Multivariable control laws are designed for the Advanced Fighter Technology Integration F-16 (AFTI/F-16). Both fixed gain and adaptive Proportional plus Integral (PI) controllers are designed for a plant were the number of outputs are not equal to the number of inputs (rectangular plant). Simulations are conducted for a healthy and a failed aircraft model. The failure consists of reducing the left elevator by 50%. When the fixed gain controller is used for the flight control system, the simulation reveals the fact that the aircraft failure causes the output responses to diverge. If provided with a persistently exciting input the adaptive controller prevents the aircraft failure simulation from diverging and going unstable. However, additional testing and/or tuning of the adaptive controller is required to determine and enhance the stability of the adaptive controller.
Book Synopsis Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 274) by :
Download or read book Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 274) written by and published by . This book was released on 1992 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 261) by :
Download or read book Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 261) written by and published by . This book was released on 1991 with total page 566 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Direct Digital Design Method for Reconfigurable Multivariable Control Laws for the A-7D Digitac II Aircraft by :
Download or read book Direct Digital Design Method for Reconfigurable Multivariable Control Laws for the A-7D Digitac II Aircraft written by and published by . This book was released on 1980 with total page 145 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis investigates control of an aircraft when there is a primary control surface failure. The object of this study is to reconfigure the remaining control surfaces to compensate for the additional forces and moments generated by the inoperative control surface. To study this flight control problem, a comprehensive aircraft model is required which considers each control surface operating individually. A six degree-of-freedom aircraft model is developed, including all the individual control surfaces. A control surface input can produce both a lateral and/or a longitudinal response. Thus, the equations of motion cannot be decoupled for the design of the control laws. The coupling between the axes requires the derivation of several new non-dimensional control derivatives. Using the geometrical properties of the aircraft and the Digital Datcom computer program, the needed control derivatives are derived. The entire eigenstructure assignment method is used to assign both the eigenvalues and the eigenvectors to the closed-loop plant matrix. This method is used for the direct digital design of a multivariable discrete regulator and tracker control law. The effect of increasing the number of control inputs on the relative degree of controllability of the states was determined by singular value decomposition.
