Accession Number:

ADP011124

Title:

Active/Adaptive Rotor Blade Control for Disturbance Rejecton and Performance Enhancement

Descriptive Note:

Corporate Author:

DAIMLER CHRYSLER AEROSPACE AG MUENCHEN (GERMANY) MILITARY AIRCRAFT DIV

Personal Author(s):

Report Date:

2001-06-01

Pagination or Media Count:

12.0

Abstract:

As part of a program for development of activeadaptive rotor systems light tests were performed with a helicopter featuring a powerful blade root acutuation system and a comprehensive sensor instrumentation. The test results gave a deep insight in the mechanisms involved in the reduction of BVI noise emissions and fuselage vibrations through 2rev blade root control inputs and allowed the derivation of an algorithm for online estimation of the BVI noise emissions experienced on ground. In combination with a closed loop control law it yields a system which allows an automation reduction of the rotor disturbances on the basis of local blade surface pressure measurements. The closed loop system can also be applied to a trailing edge flap which has been realized and investigated in the Transonic Wind Tunnel Goettingen TWG in the second part of the activeadaptive rotor development program. The test results demonstrated the ability of a servo flap to twist the blade to a degree which is required for rejection of the rotor disturbances and enhancement of the rotor performance.

Subject Categories:

  • Aerodynamics
  • Helicopters
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE