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Examination of indirect responses of helicopters using a refined inflow model

Shahmiri, F ; Sharif University of Technology | 2009

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  1. Type of Document: Article
  2. DOI: 10.1108/00022660910926881
  3. Publisher: 2009
  4. Abstract:
  5. Purpose - The purpose of this paper is to examine the cross-coupled responses of a coupled rotor-fuselage flight dynamic simulation model, including a finite-state inflow aerodynamics and a coupled flap-lag and torsion flexible blade structure. Design/methodology/approach - The methodology is laid out based on model development for an articulated main rotor, using the theories of aeroelastisity, finite element and finite-state inflow formulation. The finite-state inflow formulation is based on a 3D unsteady Euler-based concepts presented in the time domain. The most advantages of the model are the capability of modeling dynamic wake effects, tip losses and skewed wake aerodynamics. This is, in fact, a special type of the inflow model relating inflow states, to circulatory blade loadings through a set of first-order differential equations. A non-iterative solution of the differential equations has practically altered the model into a simple and direct formulation appending properly to the rest of the helicopter mathematical model. A non-linear distribution of the induced velocity over the rotor disc is finally obtained by the use of both Legendre polynomials and higher-harmonic functions. Ultimately, validations of the theoretical results show that the on-axis response, direct reaction to the pilot input, has a good accuracy both quantitatively and qualitatively against flight test data, and the off-axis response, cross-coupled or indirect reaction to the pilot input are improved by this approach of modeling. Findings - Improvements in dynamic prediction of both trim control settings and dynamic cross-coupled responses of helicopter to pilot inputs are observed. Research limitations/implications - Further work is required for investigation of the augmented finite state inflow model, including the wake rotation correction factors to describe helicopter maneuvering flight characteristics. Practical implications - The results of this work support the future researches on design and development of advanced flight control system, incorporating a high bandwidth with low-phase delay to control inputs and also high levels of dynamic stability within minimal controls cross coupling. Originality/value - This paper provides detailed characteristics on the mathematical integration problems associated with the advanced helicopter flight dynamics research. © Emerald Group Publishing Limited
  6. Keywords:
  7. Flight dynamics ; Flow ; Helicopters ; Simulation ; Aerodynamics ; Air ; Control systems ; Distribution functions ; Dynamic models ; Dynamics ; Equations of state ; Flow simulation ; Fourier series ; Functions ; Gas dynamics ; Harmonic analysis ; Phase stability ; Programming theory ; Three dimensional ; Wakes ; Blade loadings ; Control inputs ; Correction factors ; Coupled rotors ; Cross couplings ; Cross-coupled ; Design and Development ; Design/methodology/approach ; Direct formulations ; Direct reactions ; Dynamic predictions ; Dynamic simulation models ; Dynamic stabilities ; Finite elements ; Finite state ; First-order differential equations ; Flight controls ; Flight-test datum ; Harmonic functions ; Helicopter flight dynamics ; High bandwidths ; Indirect reactions ; Induced velocities ; Integration problems ; Legendre polynomials ; Maneuvering flights ; Model development ; Non-iterative ; Non-linear distributions ; Off-axis ; Phase delays ; Rotor discs ; Simulation ; Theoretical results ; Time domains ; Tip loss ; Trim controls ; Wake effects ; Wake rotations ; Work supports ; Flight control systems
  8. Source: Aircraft Engineering and Aerospace Technology ; Volume 81, Issue 1 , 2009 , Pages 25-37 ; 00022667 (ISSN)
  9. URL: https://www.emerald.com/insight/content/doi/10.1108/00022660910926881/full/html