by National Aeronautics and Space Administration, Ames Research Center, National Technical Information Service, distributor in Moffett Field, Calif, [Springfield, Va .
Written in English
|Statement||Lawson H. Robinson and Peretz P. Friedmann.|
|Series||NASA contractor report -- 4623., NASA contractor report -- NASA CR-4623.|
|Contributions||Friedmann, Peretz., Ames Research Center.|
|The Physical Object|
Higher-Harmonic-Control Algorithm for Helicopter Vibration Reduction Revisited. Time-domain adaptive harmonic control for rejection of sinusoidal disturbances acting on an unknown discrete-time system. The AVINOR Aeroelastic Simulation Code and Its Application to Reduced Vibration Composite Rotor Blade by: A combined Multiple Time Scales and Harmonic Balance approach for the transient and steady-state response of nonlinear aeroelastic systems Journal of Fluids and Structures, Vol. 80 Parametric Flutter Margin Method for Aeroservoelastic Stability AnalysisCited by: In this chapter harmonics modelling and simulation has been performed at power distribution voltage level. For this purpose the chapter is sub-divided into two main parts. The first part deals with harmonics modelling and simulation at High Voltage (HV) distribution level which is 11 kV in most of the countries including by: 1. Application of higher harmonic control to hingeless rotor systems [microform] / Khanh Nguyen and Inderji Aeroelastic simulation of higher harmonic control [microform] / Lawson H. Robinson and Peretz P. Friedmann; Comprehensive analysis of helicopters with bearingless rotors [microform]: status report / by V.R. Murthy.
Designed as both a textbook for advanced engineering students and a reference book for practicing engineers, this highly regarded work deals not only with the practical aspects of aeroelasticity, but the aerodynamic and structural tools upon which these rest. Accordingly, the book divides roughly into two halves: the first deals with the tools and the second with applications of the tools to 4/5(2). A linear quadratic Gaussian (LQG) controller for active vibratory loads reduction in helicopters is proposed based on a revisited higher harmonic control (HHC) input by active tra. aeroelasticity and flight dynamics of very flexible aircraft. With the focus on a reduced number of states to represent the complex nonlinear problem, the framework, named the University of Michigan’s Nonlinear Aeroelastic Simulation Toolbox (UM/NAST), provides a suitable plant representation for control design. Several aeroelastic. Introduces the latest developments and technologies in the area of nonlinear aeroelasticity Nonlinear aeroelasticity has become an increasingly popular research area in recent years. There have been many driving forces behind this development, increasingly flexible structures, nonlinear control laws, materials with nonlinear characteristics, etc. Introduction to Nonlinear Aeroelasticity covers.
Analytic simulation of higher harmonic control using a new aeroelastic model. By P. P. Friedmann and L. H. Robinson. Abstract. This paper describes a higher harmonic control (HHC) study of a four bladed hingeless rotor using a coupled flap-lag-torsional aeroelastic stability and response analysis which incorporates finite-state, time-domain. This paper describes a higher harmonic control (HHC) study of a four-bladed helicopter rotor using a coupled flap-lag-torsional aeroelastic stability and response analysis which incorporates finite-state, time-domain aerodyamics. The rotor trim condition is determined using a simplified flap-lag-torsional aeroelastic analysis. Firstly, aeroelastic responses at Mach of the panel are studied under a wide range of dynamic pressure. Panel response across the dynamic pressure is illustrated in Fig. comparison, this figure contains data obtained from Gordnier & Visbal  and Alder  for the same panel deflection and maximum amplitude of the LCO at x/a = are shown for a range of λ. of vibration control has been treated in a recent survey26 ocontrol-coupled vibration probl~ms in presence of higher harmonic or other active load control and response alleviation devices, have been treated in detail in a recent review27 2. Formulation of Rotary Wing Aeroelastic Problems for the Isolated Blade Case General.