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Helikopter Ana Rotor Parametrelerinin Gerekli Güçteki Etkisinin Teorik İncelenmesi

Year 2022, Volume: 4 Issue: 3, 143 - 158, 31.12.2022

Semanur Altıntaş Mehmet Bakırcı

https://doi.org/10.46740/alku.1208515

Abstract

Ana rotor, helikopter performansını ve yakıt tüketimini etkileyen temel faktördür. Ana rotor tasarımını da etkileyen birçok temel geometrik parametre bulunmaktadır. Yarıçap ve veter bu temel geometrik parametreler arasındadır. Bu çalışmada, farklı uçuş şartlarında yarıçap ve veter değerlerinin değişimlerinin gerekli güçteki etkilerinin incelenmesi amaçlandı. Hafif sınıf helikopter grubundan B0105 ve S-76 helikopterlerinin tasarım değerleri baz alındı. Yalnızca yarıçapın ve yalnızca genişliğin %+8 ile %-8 arasında değiştiği ve her iki parametrenin de %+8 ile %-8 arasında değiştiği durumlarda gerekli güç hesaplamaları yapıldı. Bu hesaplamalar, hover, 50 knots, 90 knots, 130 knots ileri uçuşlarda ve deniz seviyesi, 5000 ft, 10000 ft irtifalar için tekrarlandı. Yarıçap ve veter uzunluğunun değişimi ile gerekli güçteki maksimum azalma ve artışların olduğu durumlar ortaya konuldu. Genişliğin artırılması, tüm uçuş koşullarında gerekli güçte artışa neden olurken, genişliğin azaltılması gerekli güçte azalmaya neden olduğu saptandı. Ancak sadece yarıçap değişiminin gerekli güçteki etkisi, irtifalara ve ileri uçuş hızlarına göre farklılık göstermektedir. Yarıçap ve genişliğin değiştirilmesi ile elde edilen kombinasyonların da gerekli güçteki maksimum azalma ve artış miktarları, irtifalara, askı durumu ve ileri uçuş hızlarına göre farklılık göstermektedir.

Keywords

helikopter ana rotor gerekli güç askı ileri uçuş hızı pal yarıçap ve veter uzunluğu

References

  • [1] Kim, C. K. (1985), ‘The Effects Of Parameter Variation On Helicopter Performance’, Naval Postgraduate School.
  • [2] Rohin K. M., Berend G. v. d. W., Christoph G. Balzarek (2021), ‘Linearly variable chord-extension morphing for helicopter rotor blades’, CEAS Aeronautical Journal, 55.
  • [3] Johnson, W. (1994), ‘Helicopter Theory’, Dover Publications Inc New York, p:278-310.
  • [4] Mihir M., Farhan G. (2014), Helicopter Performance Improvement with Variable Rotor Radius and RPM, Journal of The American Helicopter Society, 59, 042010.
  • [5] Stanisław K., Robert R., Jakub K. (2021), ‘Review of Modern Helicopter Constructions and an Outline of Rotorcraft Design Parameters’, Problems Of Mechatronics Armament, Aviation, Safety Engineering, 12, 3 (45), 27-52.
  • [6] Afthon M. F., Moelyadi M. A. (2020), ‘A Study in Aerodynamic Optimization of UAV Helicopter Rotor- Blades Planform in Vertical Motion’, International Journal of Aviation Science and Engineering, Volume 2, Issue 1, June, 1-8
  • [7] Joanne L. W., Gene J. B., Michael F. R. (1987), ‘Optimization Methods Applied to the Aerodynamic Design of Helicopter Rotor Blades’, Journal of The American Helicopter Society, 34-44.
  • [8] Even A. F. (1978), ‘Aerodynamic Design of the Sikorsky S‐76 SPIRIT™ Helicopter’, Journal of The Helicopter Society, 15-17.
  • [9] Hasan I. (2007), ‘Helikopter Ön Tasarım Otomasyonu’, İstanbul Technical University.
  • [10] https://en.wikipedia.org/wiki/MBB_Bo_105
  • [11] Constantin R., Michael T. (2017), ‘Helicopter Flight Physics’, DOI: http://dx.doi.org/10.5772/intechopen.71516
  • [12] Mustafa Cavcar (1992), ‘Helikopter Taşımacılığında Yakıt Sarfiyatı Minimizasyonu Açısından Tasarım ve Performans Analizi’, İstanbul Technical University
  • [13] Layton, Donald M. (1984), ‘Helicopter Design Manual’, Naval Postgraduate School, Monterey, California.
  • [14] Stephen Glenn Kee (1983), ‘Guide for Conceptual Helicopter Design’, Naval Postgraduate School Monterey, California.
  • [15] Mehmet Ş., Nilay S. U., Dilek F. K. (2016), ‘Model Helikopter Döner Kanat Sistemi İçin Yer Etkisi Durumunda Performans ve Akış Araştırması’, VI. Ulusal Havacılık ve Uzay Konferansı.
  • [16] Seddon, J. (1990), ‘Basic helicopter aerodynamics’, BSP Professional Books, Oxford.
  • [17] Johnson W. (1994), ‘Helicopter Theory’, New York: Dover Publications, Inc., Pp. 299–300.

Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power

Year 2022, Volume: 4 Issue: 3, 143 - 158, 31.12.2022

Semanur Altıntaş Mehmet Bakırcı

https://doi.org/10.46740/alku.1208515

Abstract

The main rotor is the principal factor effecting helicopter performance and fuel consumption. There are many basic geometric parameters that constitutive the main rotor design. Radius and chord are among these basic geometric parameters. In this study, it is aimed to examine the effects of variation in radius and chord on required power at different flight conditions. Based on the design values of B0105 and S-76 from utility helicopter the group, the power calculations were made for the main rotor only when the radius and only the chord changed between +8% and -8%, and both parameters changed between +8% and 8%. These calculations were repeated for hover, 50 knots, 90 knots, 130 knots forward flights, and for sea level, 5000 ft, 10000 ft altitudes. With the variation of radius and chord, the cases that the maximum reductions and increases in required power were revealed. Results shows İncreasing the chord alone resulted in an increase in required power in all flight conditions. It has been observed that the combinations obtained by variation the radius and chord of maximum decrease and increase amount in the required power are different from according to the altitude, suspension condition and forward flight velocity.

Keywords

helicopter main rotor required power hover forwrd flight velocity blade radius and chord length

References

  • [1] Kim, C. K. (1985), ‘The Effects Of Parameter Variation On Helicopter Performance’, Naval Postgraduate School.
  • [2] Rohin K. M., Berend G. v. d. W., Christoph G. Balzarek (2021), ‘Linearly variable chord-extension morphing for helicopter rotor blades’, CEAS Aeronautical Journal, 55.
  • [3] Johnson, W. (1994), ‘Helicopter Theory’, Dover Publications Inc New York, p:278-310.
  • [4] Mihir M., Farhan G. (2014), Helicopter Performance Improvement with Variable Rotor Radius and RPM, Journal of The American Helicopter Society, 59, 042010.
  • [5] Stanisław K., Robert R., Jakub K. (2021), ‘Review of Modern Helicopter Constructions and an Outline of Rotorcraft Design Parameters’, Problems Of Mechatronics Armament, Aviation, Safety Engineering, 12, 3 (45), 27-52.
  • [6] Afthon M. F., Moelyadi M. A. (2020), ‘A Study in Aerodynamic Optimization of UAV Helicopter Rotor- Blades Planform in Vertical Motion’, International Journal of Aviation Science and Engineering, Volume 2, Issue 1, June, 1-8
  • [7] Joanne L. W., Gene J. B., Michael F. R. (1987), ‘Optimization Methods Applied to the Aerodynamic Design of Helicopter Rotor Blades’, Journal of The American Helicopter Society, 34-44.
  • [8] Even A. F. (1978), ‘Aerodynamic Design of the Sikorsky S‐76 SPIRIT™ Helicopter’, Journal of The Helicopter Society, 15-17.
  • [9] Hasan I. (2007), ‘Helikopter Ön Tasarım Otomasyonu’, İstanbul Technical University.
  • [10] https://en.wikipedia.org/wiki/MBB_Bo_105
  • [11] Constantin R., Michael T. (2017), ‘Helicopter Flight Physics’, DOI: http://dx.doi.org/10.5772/intechopen.71516
  • [12] Mustafa Cavcar (1992), ‘Helikopter Taşımacılığında Yakıt Sarfiyatı Minimizasyonu Açısından Tasarım ve Performans Analizi’, İstanbul Technical University
  • [13] Layton, Donald M. (1984), ‘Helicopter Design Manual’, Naval Postgraduate School, Monterey, California.
  • [14] Stephen Glenn Kee (1983), ‘Guide for Conceptual Helicopter Design’, Naval Postgraduate School Monterey, California.
  • [15] Mehmet Ş., Nilay S. U., Dilek F. K. (2016), ‘Model Helikopter Döner Kanat Sistemi İçin Yer Etkisi Durumunda Performans ve Akış Araştırması’, VI. Ulusal Havacılık ve Uzay Konferansı.
  • [16] Seddon, J. (1990), ‘Basic helicopter aerodynamics’, BSP Professional Books, Oxford.
  • [17] Johnson W. (1994), ‘Helicopter Theory’, New York: Dover Publications, Inc., Pp. 299–300.
There are 17 citations in total.

Details

Primary Language English
Subjects Engineering
Journal Section Makaleler
Authors

Semanur Altıntaş 0000-0002-6058-0030

Mehmet Bakırcı 0000-0002-1061-698X

Publication Date December 31, 2022
Submission Date November 23, 2022
Acceptance Date December 26, 2022
Published in Issue Year 2022 Volume: 4 Issue: 3

Cite

APA Altıntaş, S., & Bakırcı, M. (2022). Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power. ALKÜ Fen Bilimleri Dergisi, 4(3), 143-158. https://doi.org/10.46740/alku.1208515
AMA Altıntaş S, Bakırcı M. Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power. ALKÜ Fen Bilimleri Dergisi. December 2022;4(3):143-158. doi:10.46740/alku.1208515
Chicago Altıntaş, Semanur, and Mehmet Bakırcı. “Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power”. ALKÜ Fen Bilimleri Dergisi 4, no. 3 (December 2022): 143-58. https://doi.org/10.46740/alku.1208515.
EndNote Altıntaş S, Bakırcı M (December 1, 2022) Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power. ALKÜ Fen Bilimleri Dergisi 4 3 143–158.
IEEE S. Altıntaş and M. Bakırcı, “Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power”, ALKÜ Fen Bilimleri Dergisi, vol. 4, no. 3, pp. 143–158, 2022, doi: 10.46740/alku.1208515.
ISNAD Altıntaş, Semanur - Bakırcı, Mehmet. “Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power”. ALKÜ Fen Bilimleri Dergisi 4/3 (December 2022), 143-158. https://doi.org/10.46740/alku.1208515.
JAMA Altıntaş S, Bakırcı M. Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power. ALKÜ Fen Bilimleri Dergisi. 2022;4:143–158.
MLA Altıntaş, Semanur and Mehmet Bakırcı. “Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power”. ALKÜ Fen Bilimleri Dergisi, vol. 4, no. 3, 2022, pp. 143-58, doi:10.46740/alku.1208515.
Vancouver Altıntaş S, Bakırcı M. Theoretical Investigation on Effect of Helicopter Main Rotor Parameters in Required Power. ALKÜ Fen Bilimleri Dergisi. 2022;4(3):143-58.
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