Hostname: page-component-cd9895bd7-gbm5v Total loading time: 0 Render date: 2024-12-28T20:38:51.418Z Has data issue: false hasContentIssue false
  • English
  • Français

A non-iterative design for aileron to rudder interconnect gain

Published online by Cambridge University Press:  09 December 2020

J. Myala Open the ORCID record for J. Myala [Opens in a new window] ,
V.V. Patel  and
G.K. Singh
J. Myala*
Affiliation:
Scientist, Integrated Flight Control Systems, ADA Bangalore, India Student of Academy of Scientific and Innovative Research (AcSIR), CSIR-NAL, Bangalore, India
V.V. Patel
Affiliation:
Scientist, Integrated Flight Control Systems, ADA, Bangalore, India
G.K. Singh
Affiliation:
Scientist, Flight Mechanics Control Division, NAL, Bangalore, India Faculty of Academy of Scientific and Innovative Research (AcSIR), CSIR-NAL, Bangalore, India
*
jayalakshmim@nal.res.in
Get access Rights & Permissions [Opens in a new window]

Abstract

Aileron to Rudder Interconnect (ARI) gain is implemented on most fighter aircraft, primarily to reduce the side slip produced due to adverse yaw from pilot lateral control stick input and to improve the turn rate response. A systematic and non-iterative design procedure for ARI gain is proposed herein based on the evaluation of a transfer function magnitude at the aircraft roll mode frequency. The simplicity of the proposed method makes it useful for real-time flight control law reconfiguration in situations where the aileron control authority is diminished due to damage. This is demonstrated by a simulation example considering an aileron surface damage scenario.

Keywords

aileron to rudder interconnect gaincontrol lawARIaircraftflightreconfiguration
Type
Research Article
Information
The Aeronautical Journal , Volume 125 , Issue 1286 , April 2021 , pp. 763 - 774
Copyright
© The Author(s), 2020. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Jafarov, E.M. and Tasaltin, R. Robust sliding mode control for the uncertain MIMO aircraft model F-18, IEEE Trans Aerosp Electron Syst, 2000, 36, (4), pp 1127–1141. doi: 10.1109/7.892663.Google Scholar
Balas, G.J., Packard, A.K., Renfrow, J., Mullaney, C. and M'closkey, R.T. Control of F-14 Aircraft Lateral-directional axis during powered approach, J Guid Control Dyn, 1998, 21, (6), pp 899–908. doi: 10.2514/2.4323CrossRefGoogle Scholar
Fialho, I., Balas, G.J., Packard, A.K., Renfrow, J. and Mullaney, C. Gain-scheduled lateral control of the F-14 aircraft during powered approach landing, J Guid Control Dyn, 2000, 28, (3), pp 450–458. doi: 10.2514/2.4550CrossRefGoogle Scholar
McLean, D. Automatic Flight Control Systems, Prentice-Hall, 1990, New York, Chaps.7 and 9.Google Scholar
Stevens, B.L. and Lewis, F.L. Aircraft Control and Simulation, 2nd edition, John Wiley and Sons, 1992, New York, Chaps. 3,4.Google Scholar
Blakelock, J.H. Automatic Control of Aircraft and Missiles, 2nd edition, John Wiley and Sons, Inc., 1991 New York, Chaps. 1 to 5, 9,10.Google Scholar
Roskam, J. Airplane Flight Dynamics and Automatic Flight Controls-Part II, DAR corporation, 2003, US, pp 685–789.Google Scholar
Ellis, D. Aileron-Rudder Interconnects and Flying Qualities, SAE Technical Paper 720317, 1972, doi: 10.4271/720317CrossRefGoogle Scholar
Barnes, C.S. and Nicholas, O.P. Preliminary Flight Assessment of the Low-Speed Handling of the BAC 221 Ogee-Wing Research Aircraft, Royal Aeronautical Establishment, Aerodynamics department., Bedford, ARC-CP-1102, November 1967.Google Scholar
Kelley, W.W. and Enevoldson, V.E.K. Limited Evaluation of an F-14A Airplane Utilizing an Aileron-Rudder Interconnect Control System in Landing Configuration, NASA Technical Memorandum, Issues 81958-81979, Report No. 81972, December 1981.Google Scholar
Department of Defense, OO-ALCIYPVT, 6080 Gum Ln., Hill AFB, UT 84056-5825, Flight Manual- USAF/EPAF series aircraft –F-16A/B- BLOCKS 10 and 15, Lockheed Martin Corporation, T.O.1F-16A-l, Section iv, 14th August 1995.Google Scholar
Chetty, S. and Deodhare, G. Design and development of flight control laws for LCA, J Aeronaut Soc India, 54, 2002, pp 142–144.Google Scholar
Srinathkumar, S. Eigen Structure Control Algorithms: Application to Aircraft/Rotorcraft Handling Qualities Design, IET-Control Engineering, 2011, UK, Chap. 9.CrossRefGoogle Scholar
Military specification flight control systems—design, installation and test of piloted aircraft, Tech. Rep. MIL-F-9490D, Dept. of Defense, Washington DC, 5th October 1992.Google Scholar
Military specification flying qualities of piloted airplanes. Tech. Rep. MIL-F-8785C, Dept. of Defense, 5th November 1980.Google Scholar
Jee, G., Sharma, K.K., Rao, K.K., Zachariah, S.K., Brinda, V., Lalithambika, V.R., Dhekane, M.V., Deodhare, G.S. and Chetty, S. Evolution of attitude control law of an Indian re-entry launch vehicle, Int J Adv Eng Sci Appl Math, July–December 2014, 6, (3–4), pp 148–157, doi: 10.1007/12572-015-0118-1.CrossRefGoogle Scholar
Myala, J., Patel, V.V. and Singh, G.K. Reliable Fault Identification for Aircraft Control Surface Damage, 2019 Sixth Indian Control Conference (ICC), Hyderabad, India, 2019, pp 490–495, doi: 10.1109/ICC47138.2019.9123243.CrossRefGoogle Scholar