A Study of the Thermal Effects in a Smart Structure Helicopter Rotor

Abstract

One concept being considered for active noise and vibration control of helicopter rotors is a trailing edge flap design driven by a high-displacement piezoelectric actuator device. The proposed device requires an 800-V power supply and draws a current on the order of .3 A. Thus, depending on the duty cycle and efficiency of the mechanism, some portion of the 240 W of electrical input energy will be converted to heat. This study provides an initial estimate of the temperatures that may be encountered if no provisions are made for cooling the actuator. Also included are a discussion of the heat transfer calculation, assuming conduction and radiation as the dominant modes, and a description of HEAT 8, the computer code used.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1999
Accession Number
ADA374312

Entities

People

  • Armand Martin
  • Bohdan Balko
  • Michael A. Rigdon

Organizations

  • Institute for Defense Analyses

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Actuators
  • Climate Change
  • Convection
  • Displacement
  • Energy
  • Equations
  • Fluid Mechanics
  • Geometric Forms
  • Heat Transfer
  • Helicopter Rotors
  • Helicopters
  • Materials
  • Materials Science
  • Power Supplies
  • Radiation
  • Thermal Conductivity
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Materials Science and Engineering.