Coaxial Rotor System with Asymmetric Rotor Arrangement and Method Thereof

Non-Confidential description of the invention

The present invention relates to aircraft rotor systems, and more particularly relates to a helicopter rotor system having asymmetric rotor arrangement in a coaxial configuration to achieve high efficiency by minimizing the interference losses, maximizing thrust generation and enabling significant power saving in hovering flight. A co-axial rotor assembly comprising a main rotor system, having a plurality of rotor blades coupled to a central rotor shaft and extending radially outwards, an antitorque rotor system having a plurality of rotor blades coupled to another rotor shaft and extending outwards. The rotor blades of the main rotor assembly and anti torque rotor assembly are coupled to an engine via the rotor shaft and spin in opposite direction to each other when in operation. The main rotor and the anti-torque rotor assemblies are asymmetrical and coupled to the rotor shaft one above the other. The rotor blades of the main rotor assembly have small root cut-out and large span and the rotor blades of the anti-torque rotor assembly have small span and root cut-out equal to or larger than the radius of the main rotor blades to eliminate interference losses.

Inventors

Dr. Abhishek (AE), Mr. Rahul R(PhD Student,AE)

IPA

201711013049

Date of Filing

11/04/2017

Status

Date Of Grant

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