Control Bodies Hinge Moments Computing

Aeronautical and Space-Rocket Engineering


Аuthors

Sashin A. P.1*, Erokhin A. P.2**

1. Company «Tupolev», 17, nab. Akademika Tupoleva, Moscow, 105005, Russia
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: switteramm@gmail.com
**e-mail: a-erokhin@yandex.ru

Abstract

Non-traditional aircraft layout schemes, which require employing new types of control surfaces, are finding nowadays more and more application. Often, these rudders are poorly studied in the field of aerodynamics (as applied to our article, the hinge moments computing is being considered). Numerical methods are especially up-to-date for non-traditional deflectable surfaces, for which experimental data is missing.
The presented work considers hinge moments computation of the controls. As a rule, the hinge moments of controls are obtained by the experiments in wind tunnels. This requires large material costs (design, construction and maintenance of wind tunnels; production of individual blow-through models of different scales; construction of rigging for conducting the experiment) and time. The presented technique is intended to reduce the above described time and financial costs due to the fact that the results computed by it will allow estimating the magnitude of hinge moments, establishing requirements for the control system and determining the required drive power in the first approximation at the early stages of design. Thus, the subject of this work is relevant.
The main objective of the work consists in computing the values the hinge moments of a swept wing split aileron by the new proposed technique.
In view of the above said, the following tasks were set:
● to evaluate the effect of the computational grid nodes number on the aerodynamic characteristics of the wing section; to compare computational results employing both various turbulence models and the results, obtained from the open sources. This stage is necessary for further comparison of the results and of the reliability verification of the obtained coefficients. As long as the values closest to the experimental data are the computational results for the Spalart-Almaras turbulence model, this turbulence model was used for computations in the following sections;
● to compare the obtained results when computing with the presented technique and numerical modeling of the hinge moments of a medium-range passenger aircraft ailerons with the results obtained earlier experimentally;
● by computations with the new technique, to obtain the split aileron hinge moment coefficients values in various flight modes and compare them with the numerical modeling data.
The results of the hinge moments of the aircraft wing with deflected controls obtained by the proposed technique demonstrate good convergence with the data obtained from the results of the experiment in the wind tunnel. In in this respect a conclusion was made on the advisability of applying this technique for the data clarifying.
The authors are planning hereinafter to extrapolate the employed approach on the other aircraft controls, such as the rudder, all-moving vertical stabilizer, and elevator. Besides, the additional section of the technique for the hinge moments computing, dealing with the hinge moments computing of the deflected surfaces at the critical angles of attack is under development.

Keywords:

splitting aileron, hinge moment computing method, Spalart-Almaras turbulence model, profile curvature, profile thickness

References

  1.  Gulimovskii IA, Greben’kov SA. Applying a modified surface mesh wrapping method for numerical simulation of icing processes. Aerospace MAI Journal. 2020;27(2):29-36. (In Russ.). DOI: 10.34759/vst-2020-2-29-36
  2. Eger SM, Matveenko AM, Shatalov IA. Osnovy aviatsionnoi tekhniki (Fundamentals of aviation technology). 3rd ed. Moscow: Mashinostroenie; 2003. 720 p. (In Russ.).
  3. Eger SM, Mishin VF, Liseitsev NK. et al. Proektirovanie samoletov (Aircraft design). 3rd ed. Moscow: Mashinostroenie; 1983. 616 p. (In Russ.).
  4. Hammerand DC, Gariffo JM, Roughen KM. Efficient Creation of Aeroservoelastic Models Using Interpolated Aerodynamics Models. 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference (April 04-07, 2011; Denver, Colorado). AIAA 2011-1770. DOI: 10.2514/6.2011-1770
  5. Advisory Material Joint. AC/AMJ 25.671 Control Systems General. Draft. USA: U.S. Department of Transportation, Federal Aviation Administration; 2001. 44 p.
  6. Moorhouse DJ, de Boer W, Fielding C. et al. Flight Control Design – Best Practices. RTO Technical Report 29. France: NATO; 2000. 214 p.
  7. Bulat PV, Prodan NV, Vokin LO. Comparison of Turbulence Modelsin the Numerical Simulation of the Model Ducted Propeller. Izvestiya vysshikh uchebnykh zavedenii. Aviatsionnaya tekhnika. 2022(4):74-80. (In Russ.).
  8. Erokhin PV, Kudashkina EA, Goncharov MM. Numerical modeling of coefficients of hinge moments of control bodies. In: Novye tekhnologii, materialy i oborudovanie rossiiskoi aviakosmicheskoi otrasli. Sbornik trudov Vserossiiskoi nauchno-prakticheskoi konferentsii s mezhdunarodnym uchastiem (August 08–10, 2018; Kazan). Kazan: KGTU im. A.N. Tupoleva; 2018. p. 34-39. (In Russ.).
  9. Moir I, Seabridge A. Aircraft Systems: Mechanical, electrical, and avionics subsystems integration. 3rd ed. England: John Wiley & Sons, Ltd.; 2008. 560 p.
  10. Airfoil Tools, http://airfoiltools.com/airfoil
  11. Rukovodstvo dlya konstruktorov po proektirovaniyu samoletov (A guide for designers on the design of aircraft). Moscow: TsAGI, 1993. (In Russ.).
  12. Mezhgosudarstvennyi aviatsionnyi komitet. Aviatsionnye Pravila. Chast' 25. Normy letnoi godnosti samoletov transportnoi kategorii. St. Petersburg: SZ RTsAI; 2022. 372 p. (In Russ.).
  13. Tu-204 aircraft, https://www.tupolev.ru/planes/tu-204/
  14. Brutyan MA, Vyshinskii VV, Lyapunov SV. Osnovy dozvukovoi aerodinamiki (Fundamentals of subsonic aerodynamics). Moscow: Nauka; 2021. 269 p. (In Russ.).
  15. Mikeladze VG, Titov VM. Osnovnye geometricheskie i aerodinamicheskie kharakteristiki samoletov i raket: Spravochnik (Basic geometric and aerodynamic characteristics of aircraft and missiles: Handbook). Moscow: Mashinostroenie; 1982. 149 p. (In Russ.).
  16. Ramakrishna N, Kumar VP. Aerodynamic Effect Caused by Ice Aircraft Wing. International Journal of Advanced Technology and Innovative Research. 2017;9(4):547-553.
  17. Stanford BK. Aeroservoelastic Optimization under Stochastic Gust Constraints. Applied Aerodynamics Conference, AIAA AVIATION Forum (June 25-29, 2018; Hyatt Regency, Atlanta, Georgia). AIAA 2018-2837. DOI: 10.2514/6.2018-2837
  18. Golubev AG, Epikhin AS, Kalugin  VT. et al. Aerodinamika (Aerodynamics). 2nd ed. Moscow: BMGTU; 2017. 607 p. (In Russ.).
  19. Biryuk VV, Blagin EV, Lysenko YuD. et al. Aerodinamika i samoletostroenie (Aerodynamics and aircraft engineering). Samara: Samarskii universitet; 2018. 180 p. (In Russ.).
  20. Ermakov SA, Karev VI, Konstantinov SV. et al. Fly-by-wire control systems and servo actuators design and development. Aerospace MAI Journal. 2013;20(2):161-171. (In Russ.). URL: https://vestnikmai.ru/eng/publications.php?ID=42842

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