3 edition of An in-flight interaction of the X-29A canard and flight control system found in the catalog.
An in-flight interaction of the X-29A canard and flight control system
M. W. Kehoe
Published
1990
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
Edition Notes
| Other titles | In flight interaction of the X-29A .... |
| Statement | Michael W. Kehoe and Lisa J. Bjarke, Edward J. Laurie. |
| Series | NASA technical memorandum -- 101718. |
| Contributions | Bjarke, Lisa J., Laurie, Edward J., Dryden Flight Research Facility. |
| The Physical Object | |
|---|---|
| Format | Microform |
| Pagination | 1 v. |
| ID Numbers | |
| Open Library | OL18035096M |
Most unconventional control systems involve some form of thrust vector control (TVC) or jet interaction (JI). We have now introduced four major categories of missile flight control systems--tail control, canard control, wing control, and unconventional control--so . Linearized aerodynamic and control law models of the XA airplane and comparison with flight data / (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, ), by John T. Bosworth and Dryden Flight Research Facility (page images at HathiTrust).
CONTENTS 1, Centering Charauteristics of Power Boosted Aircraft Control Systems' (Martin),. 2. Helicopter Powered Control System Problem8 (Slkoraky).. 3. Flight Research on Force Wheel Control (WAN) 4, An Analyeis of Fully-Powered Aircraft. Control Syatem Inuluding Some. on the role of NN technology in flight control system design have been contributed by Werbos [29] and Steinberg [30,31]. Our research has focused on the use of a direct NN based adaptive control architecture that compensates for unknown plant nonlinearities in a feedback linearizing control .
Title: Linearized Aerodynamic and Control Law Models of the XA Airplane and Comparison With Flight Data Author: John T. Bosworth Subject: NASA TM The resultant Rafale A technology demonstrator was a large-delta winged fighter, with all-moving canards, embodying fly-by-wire (FBW) flight control system. Construction of the demonstrator commenced in March , even before a contract was signed with the DGA, France's defence procurement agency. The technology demonstrator was rolled out in December in Saint-Cloud, Manufacturer: Dassault Aviation.
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Tails of an aeroservoelastic interaction experienced in flight by the XA forward-swept wing airplane. A Hz canard pitch mode response was aliased by the digital sampling rate in the canard position feed-back loop of the flight control system, resulting in a Hz signal being commanded to the longitudinal control surfaces.
An in-flight interaction of the XA canard and flight control system Author: M W Kehoe ; Lisa J Bjarke ; Edward J Laurie ; Dryden Flight Research Facility.
This paper presents the details of an aeroservoelastic interaction experienced in flight by the XA forward-swept-wing aircraft.
A Hz canard pitch-mode response was aliased by the digital sampling rate in the canard-position feed-back loop of the flight-control system, resulting in a Hz signal being commanded to the longitudinal control surfaces.
The details of an aeroservoelastic interaction experienced in flight by the XA forward-swept wing airplane. A Hz canard pitch mode response was aliased by the digital sampling rate in the canard position feedback loop of the flight control system, resulting in a Hz signal being commanded to the longitudinal control surfaces.
Buffet induced structural/flight-control system interaction of the XA aircraft. An in-flight interaction of the XA canard and flight control system.
MICHAEL KEHOE, Integrated aeroservoelastic analysis capability with XA analytical by: The XA No. 2 airplane was used primarily to examine high-AOA characteristics, but was also used to study the stability margins of the lateral–directional axes using multi-input–multi-output (MIMO) techniques at low-AOA conditions.
Description of the Flight Control System The XA airplane is controlled through a triplex fly-by-wireCited by: A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text.
The XA lateral–directional control system is a MIMO sys- tem, and the classical frequency analysis methods are inade- quate for this type of control system. The Grumman X was an American experimental aircraft that tested a forward-swept wing, canard control surfaces, and other novel aircraft technologies.
The X was developed by Grumman, and the two built were flown by NASA and the United States Air aerodynamic instability of the X's airframe required the use of computerized fly-by-wire cturer: Grumman.
The electronic flight control system uses the pitch control function of the canard foreplane to create artificial static and dynamic stability.
A benefit obtainable from a control-canard is the correction of pitch-up during a wingtip stall. An all-moving canard capable of a significant nose-down deflection can be used to counteract the pitch-up. In this study, the effects of canard–wing interference on the flight characteristics of a conceptual civilian transonic cruiser were examined.
Two different canard designs were considered, corresponding to a canard positioned closer to the nose of the aircraft and at the mid fuselage section, and to a canard closer to the wing and at a lower Cited by: 2.
Flight-testing of the self-repairing flight control system using theF highly integrated digital electronic control flight research facility JAMES STEWART and THOMAS SHUCK. This book provides a single comprehensive resource that reviews many of the current aircraft flight control programmes from the perspective of experienced practitioners directly involved in the projects.
Each chapter discusses a specific aircraft flight programme covering the control system design considerations, control law architecture, simulation and analysis, flight test optimization and Reviews: 1.
The details of an aeroservoelastic interaction experienced in flight by the X- 29A forward-swept wing airplane. A Hz canard pitch mode response was aliased by the digital sampling rate in the canard position feedback loop of the flight control system, resulting in a Hz signal being commanded to the longitudinal control surfaces.
The book meets the needs of students of ab-initio courses in aircraft maintenance and complements the ground studies of pilots on ab-initio training.
About the Author. Pallatt was formerly a Surveyor with the CAA Airworthiness Division. Shawn Coyle is a highly experience helicopter test pilot instructor/5(4). Split into two parts, the first section of the book deals with the fundamentals of flight control systems design, while the second concentrates on genuine applications based on the modern control methods used in the latest aircraft.
It is assumed that the reader will have some knowledge of classical : The Institution of Engineering and Technology. This banner text can have markup.
web; books; video; audio; software; images; Toggle navigation. Full text of "XA aircraft structural loads flight testing" See other formats NASA Technical Memorandum XA Aircraft Structural Loads Flight Testing Robert Sims NASA Ames Research Center, Dryden Flight Research Facility, Edwards, California and Paul McCrosson, Robert Ryan, and Joe Rivera Grumman Aircraft Systems, Grumman Aerospace Corporation, Edwards, California.
With high gain digital flight-control systems, this structural response may re- suit in an aeroservoelastic interaction. A structural interaction on the XA aircraft was observed during high-angle-of-attack flight testing.
The roll and yaw rate gyros sensed the aircraft's struc- tural modes at 11, 13, and 16 Size: KB. Advances in Flight Control Systems Agneta Balint (Ed) Categories: Technique flight control system longitudinal deg aileron performance marker vol stability desired conference Post a Review.
You can write a book review and share your experiences. Other readers will always be interested in your. Directional Stability and Control in Ground Rolls Vee- or Butterfly Tails Control Surface Buzz Rudder Lock and Dorsal Fins Flight Vehicle System Identification from Flight Test Early Attempts at Identification Knob Twisting Modern Identification Methods File Size: KB.You can write a book review and share your experiences.
Other readers will always be interested in your opinion of the books you've read. Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.A Historical Overview of Research in Reconfigurable Flight Control Marc Steinberg Naval Air Systems Command, Patuxent River, MD Abstract This paper presents a historical overview of research in reconfigurable flight control with a focus on work done in the United States.
For purposes of File Size: KB.
