Helicopter Cross-Flow Fan for Anti-Torque and Lift
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Solution Overview
Problem
Conventional helicopters rely on fixed vertical and horizontal stabilizing surfaces that do not provide additional propulsive force and are prone to damage from foreign objects, with tail rotors posing safety risks, and require significant redesign for diameter changes.
Innovation Solution
Integration of a cross-flow fan with a pivotable housing and radially oriented airfoil blades, providing anti-torque and lift without a tail rotor or horizontal stabilizers, with adjustable thrust vectoring and additional thrust through the Coanda effect and diffuser outlet.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a tail rotor is used as an anti-torque device, then anti-torque is provided, but safety risks arise due to potential danger to humans and damage from foreign objects
Solution Approach 1:
The patent removes the traditional tail rotor component entirely and replaces it with a cross-flow fan system. This extraction eliminates the rotating blades that pose safety risks to humans and vulnerability to foreign object damage, while maintaining the anti-torque function through a different mechanical approach.
Solution Approach 2:
The cross-flow fan uses a ducted design with fixed or slowly moving vanes instead of high-speed rotating blades. This design is more tolerant of foreign object ingestion and less dangerous to personnel, effectively treating the anti-torque system as a more robust, damage-tolerant component.
2Device complexity
If fixed vertical and horizontal stabilizing surfaces are used, then structural simplicity is maintained, but no additional propulsive force is provided
Solution Approach 1:
The cross-flow fan system performs multiple functions: it provides anti-torque, generates propulsive thrust, and can contribute to lift. This multi-functionality replaces the need for separate horizontal stabilizers and tail rotors, achieving both structural simplification and enhanced productivity.
Solution Approach 2:
The patent combines the functions of the tail rotor (anti-torque) and horizontal stabilizer (pitch control and thrust) into a single integrated cross-flow fan system. This merging eliminates redundant structures while providing combined anti-torque and propulsive capabilities.
3Adaptability or versatility
If the diameter of rotating devices is changed, then performance adjustment is achieved, but major changes and re-designs of the entire helicopter are required
Solution Approach 1:
The cross-flow fan system incorporates adjustable vanes and configurable housing that can be modified to change the diameter and thrust characteristics without requiring complete redesign of the helicopter. This dynamic adjustability allows performance optimization while maintaining the core structure.
Solution Approach 2:
The anti-torque and propulsion system is divided into modular components including the cross-flow fan, housing, and vane assembly. These segmented components can be independently adjusted or replaced, allowing diameter and performance changes without affecting the entire helicopter design.
4Stability of the object's composition
If conventional stabilizers are used, then pitch stability is maintained, but minimum drag fuselage attitude cannot be fully achieved
Solution Approach 1:
The cross-flow fan system provides dynamic control of the airflow direction and thrust magnitude, enabling active adjustment of the fuselage attitude to achieve minimum drag configurations. This dynamic capability surpasses fixed stabilizers while maintaining pitch stability through controlled thrust vectoring.
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
Enables efficient anti-torque and lift generation, improved flight performance, and reduced risk of damage from foreign objects, with the ability to adjust thrust components and eliminate the need for traditional stabilizers and tail rotors.
Implementation Method 1
Cross-Flow Fans with blades arranged to a torus-like configuration are known from the heating, ventilating and air conditioning field, providing an airflow passing the blades crosswise.
Implementation Method 2
at least one housing of a cross flow fan is mounted to said fuselage, said at least one housing extending longitudinally essentially in direction of said roll axis with an offset relative to said yaw axis. Said at least one housing is at least partly pivotable about its longitudinal axis.
Implementation Method 3
with the ability to adjust thrust components and eliminate the need for traditional stabilizers and tail rotors
Data Source
AI summary
A helicopter with a fuselage (4), at least one engine, a roll axis, at least one main rotor, and at least one housing (2) mounted to said fuselage (4). An air inlet (8) and an air outlet (7) are provided along at least a part of a circumference of the at least one housing (2), said air inlet (8) and said air outlet (7) being formed by angularly offset and separate gaps between an inside segment (33) and an outside segment (34) essentially extending respectively longitudinally in direction of said roll axis. At least one rotatable compressor (1) with a plurality of airfoil blades (6) is provided radial inside said at least one housing (2) between said air inlet (8) and said air outlet (7), said at least one rotatable compressor (1) being drivable by said at least one engine about a fan axis (5) and each chord of said airfoil blades (6) is essentially radial oriented with regard to said fan axis (5).