3 edition of Output model-following control synthesis for an oblique-wing aircraft found in the catalog.
Output model-following control synthesis for an oblique-wing aircraft
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
|Other titles||Output model following control synthesis for an oblique wing aircraft.|
|Statement||Joseph W. Pahle.|
|Series||NASA technical memorandum -- 100454.|
|Contributions||Dryden Flight Research Facility.|
|The Physical Object|
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Get this from a library. Output model-following control synthesis for an oblique-wing aircraft. [Joseph W Pahle; Dryden Flight Research Facility.]. Oblique Wing: Future Generation Transonic Aircraft. "Output Model-Following Control Synthesis for an. Recent interest in oblique-wing aircraft.
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. DECOUPLING CONTROL SYNTHESIS FOR AN OBLIQUE-WING AIRCRAFT, Technical Memorandum Authors: G. Alag (University of Western Michigan), R.
Kempel and J. Pahle Report Number: NASA-TM Performing Organization: NASA Dryden Flight Research Center, Edwards, CA Availability: Format(s) on-line: PDF ( KBytes) Report Date: June Design of dynamic output feedback controllers with parameter variation insensitivity.
Attitude control system synthesis for the Hoop/Column antenna using the LQG/LTR method. SUNDARARAJAN, Model-following control for an oblique-wing aircraft. ALAG. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A cumulative index to a continuing bibliography (supplement )" See other formats.
This new series of tests was designed to answer questions regarding the available aileron-control power of oblique-wing aircraft with the wing yawed at angles of 50 degrees to 60 degrees in the Mach number range of to and at a Reynolds number range from to x /m. 60 Evolving the Oblique Wing.
A Linear Quadratic Regulator synthesis technique was used to design an explicit model following control system for the Oblique Wing Research Aircraft (OWRA). The forward path model (Maneuver Command Generator) was designed to incorporate the desired flying qualities and response decoupling.
Oblique Wing Flights. NASA Image and Video Library. Flown in the mid 70's, this Oblique Wing was a large-scale R/C experimental aircraft to demonstrate the ability to pivot its wing to an oblique angle, allowing for a reduced drag penalty at transonic speeds.
Integrated Aerodynamic and Control System Design of Oblique Wing Aircraft. Ph.D. Thesis. Tokyo Tech Book Review; Help (SOFFT) flight control architecture.
Ostroff, Aaron J., Proffitt, Melissa S. National Aeronautics and Space Adminstration. 12 Technical Paper Output Model-Following Control Synthesis for an Oblique-Wing Aircraft. Pahle, Joseph W. In the latter, onboard computers "force" the aircraft to respond in a way identical to the model of the target aircraft.3 One of the most long-lived and famous of the variable-stability test aircraft was a T that had the long nose of an F attached to it in to hold the control system.4 This aircraft evolved over a year.
Full text of "NASA scientific and technical publications: A catalog of Special Publications, Reference Publications, Conference Publications, and. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.
Stability and Control of Aircraft, Marchpp. 57–70, (see N ), 72N, CASI ID: A ﬂight investigation has been made over an altitude and lift range to determine the wing loads of the Bell X-5 research airplane at a sweep angle of degrees at subsonic and transonic Mach numbers.