Hostname: page-component-cd9895bd7-gbm5v Total loading time: 0 Render date: 2024-12-26T22:46:44.506Z Has data issue: false hasContentIssue false
  • English
  • Français

Rotorcraft control response using linearised and non-linear flight dynamic models with different inflow models

Published online by Cambridge University Press:  23 February 2017

T. Sakthivel  and
C. Venkatesan
T. Sakthivel*
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, India
C. Venkatesan
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, India
*
sakvel@iitk.ac.in
Get access Rights & Permissions [Opens in a new window]

Abstract

The aim of the present study is to develop a relatively simple flight dynamic model which should have the ability to analyse trim, stability and response characteristics of a rotorcraft under various manoeuvring conditions. This study further addresses the influence of numerical aspects of perturbation step size in linearised model identification and integration timestep on non-linear model response. In addition, the effects of inflow models on the non-linear response are analysed. A new updated Drees inflow model is proposed in this study and the applicability of this model in rotorcraft flight dynamics is studied. It is noted that the updated Drees inflow model predicts the control response characteristics fairly close to control response characteristics obtained using dynamic inflow for a wide range of flight conditions such as hover, forward flight and recovery from steady level turn. A comparison is shown between flight test data, the control response obtained from the simple flight dynamic model, and the response obtained using a more detailed aeroelastic and flight dynamic model.

Keywords

Helicopter flight dynamicsinflow modelupdated Drees inflow
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1238 , April 2017 , pp. 553 - 575
Copyright
Copyright © Royal Aeronautical Society 2017 

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

REFERENCES

1. Anon . Helicopter flying and ground handling qualities, general requirements for, MIL-H-8501A, September 1961, Department of Defense, USA.Google Scholar
2. Anon . Aeronautical design standard, handling qualities requirements for military rotorcraft, ADS-33E, March 2000, US Army, St. Louis, Missouri, US.Google Scholar
3. Cooper, G.E. and Harper, R.P. The use of pilot rating and evaluation of aircraft handling qualities, AGARD Report - 567, April 1969, Neuilly sur seine, France.Google Scholar
4. Kalketka, J. BO 105 identification results, AGARD Lecture Series 178, Germany, 1991, 9, pp 1–50.Google Scholar
5. Pallett, T.J. and Ahmad, S. Real time flight control: Modelling and control by linearization and neural network, August 1991, Real Time Robot Control Laboratory, School of Electrical Engineering, Purdue University, West lafayette, USA.Google Scholar
6. Kim, S.K. and Tilbury, D.M. Mathematical modeling and experimental identification of an unmanned helicopter robot with flybar dynamics, J Robotic Systems, February 2004, 21, (3), pp 95-116.Google Scholar
7. Cunha, R. and Silvestrey, C. Dynamic modelling and stability analysis of model scale helicopters with Bell-Hiller stabilizer bar, 2003, Institute of Superior Tecnico, Institute for Systems and Robotics, Lisbon, Portugal.Google Scholar
8. Sakthivel, T. Influence of Stabilizer Bar on Stability and Control Response of Mini Helicopter, M. Tech Thesis, June 2014, Dept. Aerospace engineering, IIT Kanpur, India.Google Scholar
9. Chen, R.T.N. A survey of nonuniform inflow models for rotorcraft flight dynamics and control applications, NASA Technical Memorandum - 102219, November 1989, NASA, Ames research center, Moffett field, California, USA.Google Scholar
10. Min, Y.B. and Sankar, L.N. Hybrid Navier-Stokes/Free-Wake method for modeling blade vortex interactions, J Aircraft, May 2010, 47, (3), pp 975–982.CrossRefGoogle Scholar
11. Rohin Kumar, M. and Venkatesan, C. Rotorcraft aeroelastic analysis using dynamic wake/dynamic stall models and its validation, J Aeroelasticity and Structural Dynamics, 2014, 3, (1), pp 65–87.Google Scholar
12. Rohin Kumar, M. and Venkatesan, C. Effects of blade configuration parameters on helicopter rotor structural dynamics and whirl tower loads, Aeronautical J, February 2016, 120, (1224), pp 271–290.Google Scholar
13. Laxman, V. and Venkatesan, C. Influence of dynamic stall and dynamic wake effects on helicopter trim and rotor loads, J American Helicopter Society, July 2009, 54, (3), pp (032001-1)–(032001-18).Google Scholar
14. Pitt, D.M. and Peters, D.A. Rotor dynamic inflow derivatives and time constants from various inflow models, 9th European Rotorcraft Forum, September 1983, Stresa, Italy.Google Scholar
15. Padfield, G. D. Helicopter Flight Dynamics, 2nd ed, 2011, Blackwell Publishing. Wiley India edition, New Delhi, India.Google Scholar
16. Singh, G.D. and Venkatesan, C.. In-house code for analysis of helicopter flight dynamics, National Seminar on Indigenous Technology Base for Growth of Aerospace Ecosystem, 2015, HAL Bengaluru, India.Google Scholar