Helicopter Wing Augmented Lift Anti-Torque Fans
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Solution Overview
Problem
Conventional rotorcraft designs require tail rotor systems or counter-rotating blades to counteract fuselage rotation, which increase size and drag, limiting top speeds.
Innovation Solution
The design eliminates the tail rotor system and uses coaxial fans to counteract fuselage rotation, with the fans providing antitorque and thrust during hover and forward flight, and wings augmenting lift to enhance speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a tail rotor system is provided to counteract fuselage rotation, then rotational stability is improved, but the overall size envelope and drag increase
Solution Approach 1:
The patent removes the conventional tail rotor system from the helicopter design. Instead of using a separate tail rotor mounted on a tail boom, the invention integrates anti-torque functionality into the main rotor blades themselves through variable pitch control, eliminating the need for a dedicated tail rotor component and its associated drag.
Solution Approach 2:
The main rotor blades are designed to perform multiple functions: they provide lift during hover and forward flight, and simultaneously generate anti-torque forces through variable pitch control. This eliminates the need for a separate tail rotor system, reducing overall drag while maintaining rotational stability.
2Stability of the object's composition
If a tail rotor system is provided to counteract fuselage rotation, then rotational stability is improved, but the overall size envelope increases
Solution Approach 1:
The patent removes the conventional tail rotor system from the helicopter design. Instead of using a separate tail rotor mounted on a tail boom, the invention integrates anti-torque functionality into the main rotor blades themselves through variable pitch control, eliminating the need for a dedicated tail rotor component and its associated drag.
Solution Approach 2:
The invention merges the anti-torque function with the main rotor blade system. By using variable pitch control on the main rotor blades, the design combines lift generation and anti-torque production into a single integrated system, eliminating the need for a separate tail rotor and reducing the overall size envelope.
3Speed
If wings are added to augment lift in forward flight, then top speed is improved, but device complexity increases
Solution Approach 1:
The wings are designed with variable geometry capabilities, allowing their configuration to change dynamically based on flight conditions. During forward flight, the wings can be adjusted to optimize lift generation for higher speeds, while during hover or low-speed flight, they can be reconfigured to minimize drag and complexity.
Solution Approach 2:
The wings are designed to perform multiple functions across different flight regimes: they provide lift augmentation during forward flight for higher top speeds, and can be adjusted or reconfigured during hover or low-speed operations to minimize their impact on device complexity and drag.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration reduces overall drag, allowing for higher top speeds without the need for a tail rotor, while maintaining rotational stability and control through fan operation and wing lift.
Implementation Method 1
a main rotor system comprising main rotor blades
Implementation Method 2
a first fan carried by the left wing and a second fan carried by the right wing, each comprising a hub, a leading edge, a trailing edge, a first fan blade and a second fan blade
Implementation Method 3
wings to augment lift in forward flight which can allow a higher top speed in forward flight
Data Source
AI summary
A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.