Hostname: page-component-8448b6f56d-qsmjn Total loading time: 0 Render date: 2024-04-25T05:29:32.676Z Has data issue: false hasContentIssue false
  • English
  • Français

Investigation of Chinook helicopter operations with an external slung load after cable failure

Published online by Cambridge University Press:  03 February 2016

M. D. Pavel
M. D. Pavel*
Affiliation:
m.d.pavel@tudelft.nl, Delft University of Technology, Delft, The Netherlands
Get access Rights & Permissions [Opens in a new window]

Abstract

The Royal Netherlands Air Force (RNLAF) conducts frequent operations of Chinook helicopters with external slung loads. The normal RNLAF practice is for large external loads to be underslung by means of a two-strop suspension system backed up by a third point of suspension, the so-called ‘redundant HUSLE (Helicopter Underslung Load Equipment)’ comprising a redundant set of slings which come into action if one of the normal strops fails. The redundant HUSLE is relatively expensive in terms of time and operating costs. The present work has investigated the behaviour of a Chinook helicopter with an underslung load following failure of a front or rear strop, to determine whether the three-point suspension system can be safely replaced by a two-point suspension, eliminating the redundant HUSLE. The paper will demonstrate that although in general the redundant HUSLE results in a less violent helicopter reaction to a cable failure, it does not necessarily guarantee safety. It is concluded that flying with loads up to around two tonnes could be done safely with a two-point suspension system. A novel feature of this analysis of helicopter operations with slung loads is the integrated approach used for simulating pilot-in-the-loop load failures using a full non-linear model.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1156 , June 2010 , pp. 345 - 365
Copyright
Copyright © Royal Aeronautical Society 2010 

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

1. Cicolani, L.S., Kanning, G. and Synnestvedt, R., Simulation of the dynamics of helicopter slung load systems, J American Helicopter Society, October 1995, 40, (4), pp 44–61.Google Scholar
2. Fusato, D., Guglieri, G. and Celi, R., Flight dynamics of an articulated rotor helicopter with an external load, J American Helicopter Society, January 2001, 46, (1), pp 3–12.Google Scholar
3. Tyson, P., et al, Simulation prediction and flight validation of UH-60A Black Hawk slung load characteristics, 55th American Helicopter Society Annual Forum, Montreal, Canada, 25-27 May, 1999.Google Scholar
4. Chen, C., Lim, K.Y. and Seah, C.S.P., Modeling and dynamic analysis of helicopter underslung system, AIAA Modeling and Simulation Technologies Conference and Exhibit, Boston, MA, USA, AIAA-98-4358, 10-12 August 1998.Google Scholar
5. Bisgarrd, M., Bendtsen, J.D. and La Cour-Habo, A., Modelling of generic sling lload system, AIAA Modeling and Simulation Technologies Conference and Exhibit, Keystone, Colorado, USA, AIAA 2006-6816, 21-24 August 2006.Google Scholar
6. Stuckey, R.A., Mathematical modelling of helicopter slung-load systems, DSTO Aeronautical and Maritime Research Laboratory, Victoria, Australia, 2002.Google Scholar
7. Kendrick, S.A. and Walker, D.J., The modelling, simulation and control of helicopters operating with external Loads, 62nd Annual Forum of the American Helicopter Society, Phoenix, AZ, USA, 9-11 May 2006.Google Scholar
8. Gabel, R. and Wilson, G.J., Test approaches to external sling load instabilities, J American Helicopter Society, July 1968, 13, (3), pp 44–54.Google Scholar
9. Nagabhushan, B.L., Low-speed stability characteristics of a helicopter with a sling load, VERTICA, 1985, 9, (4), pp 345–361.Google Scholar
10. Prabhakar, A., Stability of a helicopter carrying an underslung load, VERTICA, 1978, 2, (2), pp 121–143.Google Scholar
11. Dukes, T.A., Maneuvring heavy sling loads near hover Part I: damping the pendulous motion, J American Helicopter Society, April 1973, 18, (2), pp 2–11.Google Scholar
12. Dukes, T.A., Maneuvring heavy sling loads near hover Part II: Some elementary maneuvres, J American Helicopter Society, July 1973, 18, (3), pp 3–13.Google Scholar
13. Bisgarrd, M., Bendtsen, J.D. and La Cour-Habo, A., Input shaping for helicopter slung load swing reduction, AIAA Guidance, Navigation and Control Conference and Exhibit, Honolulu, Hawaii, USA, AIAA 2008-6964, 18-21 August 2008.Google Scholar
14. Greenwell, D.I., Modelling of static aerodynamics of helicopter underslung loads, 26th International Congress of the Aeronautical Sciences, Anchorage, Alaska, USA, 14-19 September 2008.Google Scholar
15. Buler, W., Loroch, L., Sibilski, K., Winczura, Z. and Zyluk, A., Nonlinear dynamics of helicopter with sling load analysis by continuation methods, 39th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, USA, 8-11 January 2001.Google Scholar
16. Brenner, H., Helicopter sling load pendulum damping, 35th European Rotorcraft Forum, Hamburg, Germany, 22-25 September 2009.Google Scholar
17. Brenner, H., Helicopter sling load positioning, 35th European Rotorcraft Forum, Hamburg, Germany, 22-25 September 2009.Google Scholar
18. Hoh, R. and Heffley, R., Development of handling qualities criteria for rotorcraft with externally slung loads, 58th Annual Forum of the American Helicopter Society, Montreal, Canada, 11-13 June 2002.Google Scholar
19. Hoefinger, M.T., Blacken, C.L. and Streker, G., Evaluation of ADS-33E cargo helicopter requirements using CH-53G, 62nd Annual Forum of the American Helicopter Society, Phoenix, Arizona, USA, 9-11 May 2006.Google Scholar
20. Nicoll, T.K., Mitchell, D.G. and Roark, S., Simulation investigation of cargo/sling load handling qualities, RAeS Rotorcraft Handling Qualities Conference, Liverpool, UK, 4-6 November 2008.Google Scholar
21. Lusardi, J.A., Blanken, C.L. and Braddom, S.R., UH-60 External load handling qualities evaluation, 35th European Rotorcraft Forum, Hamburg, Germany, 22-25 September 2009.Google Scholar
22. Celi, R., Huang, C. and Shih, I.C., Reconfigurable flight control systems for a tandem rotor helicopter, 52nd Annual Forum of the American Helicopter Society, Washington DC, USA, 4-6 June 1996.Google Scholar
23. Schierman, J.D., et al, On-line identification and non-linear control of rotorcraft/external load systems, AIAA Guidance Navigation and Control Conference and Exhibit, Denver, CO, USA, 14-17 August 2000.Google Scholar
24. Dzygadlo, Z. and Sibilski, K., Dynamics of longitudinal motion of an aeroplane after drop of loads, J Tech Phys, 1987, 28, (3), pp 365–373.Google Scholar
25. Bernstein, L., On the equations of motion for an aircraft with an internal moving load which is then dropped, Aeronaut J, January 1998, 102, (1011), pp 9–24.Google Scholar
26. Pavel, M.D., On the necessary degrees of freedom for helicopter and wind turbine low-frequency mode-modelling, Doc Vision BV, Delft University of Technology, The Netherlands, 2001.Google Scholar
27. Van Der Kamp, R.A., Investigation on the operations of Chinook with external tandem load after suspension failure, Delft University of Technology, The Netherlands, June 2005.Google Scholar
28. Ostroff, A.J., Downing, D.R. and Rood, W.J., A technique using a nonlinear helicopter model for determining trims and derivatives, NASA TN D-8159, Langley Research Center Hampton, Va, USA, May 1976 Google Scholar
29. Prouty, R.W., Longitudinal cyclic control for tandem-rotor helicopters, VERTIFLITE, Autumn 2001, 47, (3), p 3.Google Scholar
30. Aeronautical Design Standard-33E-PRF, Performance Specification, Handling Qualities Requirements for Military Rotorcraft, US Army AMCOM, Redstone, Alabama, USA, 21 March 2000.Google Scholar
31. Multiservice helicopter sling Load: Basic operations and equipment, US Army FM 10-450-3/MCRP 4-23E, VOL I/NWP 3-04.11/AFJMAN 11-223, VOL I/COMDTINST M13482.2A, 199.Google Scholar