Model-following control for an oblique-wing aircraft

Cover of: Model-following control for an oblique-wing aircraft |

Published by National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, For sale by the National Technical Information Service] in Edwards, Calif, [Springfield, Va .

Written in English

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Subjects:

  • Airplanes -- Control systems.

Edition Notes

Book details

Other titlesModel following control for an oblique wing aircraft.
StatementGurbux S. Alag ... [et al.].
SeriesNASA technical memorandum -- 88269.
ContributionsAlag, Gurbux S., Dryden Flight Research Facility.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL18048829M

Download Model-following control for an oblique-wing aircraft

Model-Following Control for an Oblique-Wing Aircraft Gurbux S. Alag, Robert W. Kempel, Joseph W. Pahle, John J. Bresina, and Febo Bartoli r (NASfl-TM) HODEX-FOLLGHJNG CONTBOL FOE NS AW fT (NASfl), 13 p CSCL 01C Unclas G3/08 August NASA National Aeronautics and Space Administration.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Model-Following Control for and Oblique-Wing Aircraft Author: Gurbux S. Alag, Robert W. Kempel, Joseph W. Pahle, John J. Bresina, and Febo Bartoli Subject: NASA TM Keywords: Asymmetric aircraft control, Flight control systems, Model-following con trol system, Multi-variable control system Created Date: 9/18/ PM.

Nonlinear Optimal Model Following Control of Flexible Aircraft: Modelling, Simulation and Control of Flexible Aircraft [André Luís da Silva] on *FREE* shipping on qualifying offers. Every aircraft is a flexible body and its motion should be evaluated by the continuum mechanics.

However. COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle coronavirus.

Output Model-Following Control Synthesis for an Oblique-Wing Aircraft Author: Joseph W. Pahle Subject: H Keywords: Automatic control, Control law synthesis, Model-following, Oblique wing Created Date: 1/22/ AM. Model following has been shown to be an effective method for dccoupling and stabilization of an initial OWRA configuration in previous work by Alag and others ().

Implicit and explicit model-following (EMF) techniques were used successfully in a variety of controller structures to decouple the aircraft dynamics, but control surface. Model-following control for an oblique-wing aircraft. By F. Bartoli, R. Kempel, J. Bresina, G. Alag and J. Pahle.

Abstract. A variable-skew oblique wing offers a substantial aerodynamic performance advantage for aircraft missions that require both high efficiency in subsonic flight and supersonic dash or cruise. The most obvious. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: 7.

Model-following control for an oblique-wing aircraft. A variable-skew oblique wing offers a substantial aerodynamic performance advantage for aircraft missions that require both high efficiency in subsonic flight and supersonic dash or cruise.

The most obvious characteristic of the oblique-wing concept is the asymmetry associated with wing. In this chapter the model following control problem has been formulated as an eigenstructure assignment problem. For the special case where the plant and model have the same number of states, both EMF and IMF control schemes can be adopted.

The equivalence between the two schemes has been established. For this special case, the constraints on the plant and model stability matrices for Cited by: Get this from a library. Output model-following control synthesis for an oblique-wing aircraft.

[Joseph W Pahle; Dryden Flight Research Facility.]. The movement characteristics and control response of oblique wing aircraft (OWA) are highly coupled between the longitudinal and lateral-directional axes and present obvious nonlinearity.

The effectiveness of the control laws developed in achieving the desired decoupling is illustrated by application to linearized equations of motion of an oblique-wing aircraft for a given flight.

The application of the Model Following Control (MFC) technique to the RCAM autopilot design problem is presented. The overall controller structure and the design cycle are discussed.

A Cited by: 3. Introduction. Oblique wing aircraft (OWA) can vary wing sweep for optimal configuration at various flight speeds and extension of their flight envelope.1, 2 Compared to conventional fixed-wing aircraft, an OWA maintains excellent low-speed, takeoff and landing performance at no sweep while being capable of large lift to drag ratio via high skew angle in supersonic by: 5.

Introduction. Oblique Wing Aircraft (OWA) can rotate the wing at different flight velocities to form various wing sweep configurations. Representing a simplified minimum drag solution in supersonic flow, the oblique elliptic wing can achieve efficient flight under subsonic cruise/loiter conditions while providing excellent supersonic dash/cruise capability.1, 2 Therefore, OWA can adapt to Author: Ting Yue, Zijian Xu, Lixin Wang, Tong Wang.

An oblique wing (also called a slewed wing) is a variable geometry wing concept. On an aircraft so equipped, the wing is designed to rotate on center pivot, so that one tip is swept forward while the opposite tip is swept aft.

By changing its sweep angle in this way, drag can be reduced at high speed (with the wing swept) without sacrificing. Aircraft control commands for the flare control design in Matlab-Simulink environment are sent to the aircraft model in X-Plane flight simulator via User Datagram Protocol (UDP) and then the measured aircraft output variables are received : Ender Cetin, Ali Turker Kutay.

Aircraft Control Allocation addresses the problem of allocating supposed redundant flight controls. It provides introductory material on flight dynamics and control to provide the context, and then describes in detail the geometry of the problem.

Includes examples based on actual aircraft. The book is a vital reference for researchers and. This happens in the swing wing aircraft and the control system is complicated. Engine and payload In case of swing wing aircraft, the engines can be mounted in the fuselage (like F) or in the (fixed part of) wing itself (like B-1).

In case of the oblique wing aircraft, locating the engines anywhere except the fuselage is effectively ruled out. Interest in oblique-wing aircraft has surfaced periodically since the 's.

This concept offers some substantial aerodynamic performance advantages but also has significant aerodynamic and inertial cross-coupling between the aircraft longitudinal and lateral-directional axes.

This paper presents a technique for synthesizing a decoupling controller while providing the desired stability Cited by: 8. The NASA AD-1 was both an aircraft and an associated flight test program conducted between and at the NASA Dryden Flight Research Center, Edwards California, which successfully demonstrated an aircraft wing that could be pivoted obliquely from zero to 60 degrees during flight.

The unique oblique wing was demonstrated on a small, subsonic jet-powered research aircraft called the AD-1 Unit cost: USD $, The chapter illustrates the significance of volume as a comparative measure of the performance of different methods of allocating the control effectors.

The data used to create the figure are representative of a real tactical fighter aircraft, and the pseudo‐inverse, or something like it, was for many years the default method of allocating. Includes examples based on actual aircraft. The book is a vital reference for researchers and practitioners working in aircraft control, as well as graduate students in aerospace engineering.

Author Information. Wayne Durham had a full career as a U.S. Navy fighter pilot and test pilot. He is a member of the Society of Experimental Test Pilots.

Macintosh HD:Final book Chapter 19 Case Study: Case Study of Aircraft Wing Manufacture1 ÒYeah. If that alignment is off, engineering comes down and designs us a shim.

We have to wait 24 hours while they do the calculations. When the line is supposed to move every three days, thatÕs a disaster.Ó A File Size: 1MB. Books shelved as model-airplanes: Kites: How to Make and Fly Them by Marion Downer, Kites by Wyatt Brummitt, How to Design & Build Flying Models by Keith.

The paper is focused on the computation of all possible robustly stabilizing Proportional-Integral-Derivative (PID) controllers for plants with interval uncertainty. The main idea of the proposed method is based on Tan’s (et al.) technique for calculation of (nominally) stabilizing PI and PID controllers or robustly stabilizing PI controllers by means of plotting the stability boundary locus Cited by: Oblique wing: | | ||| | Oblique wing on a |NASA AD-1| | | World Heritage Encyclopedia, the aggregation of the largest online encyclopedias available, and the most.

The diagram covers the books devoted to a single research program, summarizing the information provided in the list above (*) complemented with some basic technical data about each aircraft (The book about the mishaps covers so many different aircraft along the decades that I deemed it better to eventually prepare a separated chart for it).Then, the figure provides a visual cue of the.

An authoritative work on aircraft control allocation by its pioneers Aircraft Control Allocation addresses the problem of allocating supposed redundant flight controls. It provides introductory material on flight dynamics and control to provide the context, and then describes in detail the geometry of the by: 5.

In this part, all robustly stabilizing PID controllers are going to be found for the same oblique wing aircraft model. Initially, the derivative constant is chosen and fixed as k D = 1.

The first of the segment plants (18) is constructed using:Cited by:   The oblique or slew-wing concept was first proposed by Richard Vogt (of whom more later) in and was revived by Robert T Jones at NASA, a pioneer of delta wing technology.

Jones proposed that a large oblique-wing aircraft, flying at speeds up to Machwould have considerably better aerodynamic performance than a conventional aircraft. Control laws. For oblique-wing aircraft, the intuitive feeling is that the main problems are more likely to do with ensuring adequate control rather than drag reduction.

METHODS USED On 'unusual' and asymmetric configurations, the experience suggests that the complexities are too much for an automatic "hands-off" design. The experimental Oblique Wing Aircraft (OWA) has a wing that pivots, as shown in Figure P The wing is in the normal unskewed position for low speeds and can move to a skewed position for improved supersonic flight [11].

The aircraftcontrol system loop transfer function is (a) Sketch the Bode diagram%(3). Wayne Durham had a full career as a U.S. Navy fighter pilot and test pilot. He is a member of the Society of Experimental Test Pilots. After retiring from the Navy he earned a Ph.D.

in Aerospace Engineering at Virginia Tech, researching model-following control under the. In this paper, the adaptive neural attitude control is developed for near-space vehicles with the oblique wing (NSVOW) via using the sliding mode disturbance observer technique.

The radial basis function neural network (RBFNN) is employed to approximate the unknown system by: 1. A generic skew-wing aircraft model was developed for 45 deg wing skew at a flight condition of Mach and m altitude.

At this flight condition the aircraft has a wing flutter mode. An active implementable control law was developed using the linear quadratic Gaussian design technique.

Aircraft wing configurations An overview This is a Wikipedia book, a collection of Wikipedia articles that can be easily saved, imported by an external electronic rendering service, and ordered as a printed book.

The NASA AD-1 was both an aircraft and an associated flight test program conducted between and at the NASA Dryden Flight Research Center, Edwards California, which successfully demonstrated an aircraft wing that could be pivoted obliquely from zero to 60 degrees during flight.

The unique oblique wing was demonstrated on a small, subsonic jet-powered research aircraft called the AD. NASA Technical Reports Server (NTRS) An integrated study of structures, aerodynamics and controls on the forward swept wing XA and the oblique wing research aircraft .A variable-sweep wing, colloquially known as a "swing wing", is an airplane wing, or set of wings, that may be swept back and then returned to its original straight position during allows the aircraft's shape to be modified in flight, and is therefore an example of a variable-geometry aircraft.

A straight wing is most efficient for low-speed flight, but for an aircraft designed for.A swept wing just looks like it has less drag. Explaining why is more difficult - and the answer may surprise you. Sweeping the wings makes the wing feel like it's flying slower.

That, in turn, delays the onset of supersonic airflow over the wing - which delays wave drag. But it's not all benefit - there's a hefty price which shows up at slow.

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