Tiltrotor Wing Cycloidal Rotors for Vertical Lift Augmentation
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Solution Overview
Problem
Conventional tiltrotor aircraft designs face a compromise between high thrust requirements in helicopter flight mode and optimized forward flight in airplane mode, lacking efficient vertical lift and hover augmentation.
Innovation Solution
The integration of cycloidal rotors within the wing channels of a tiltrotor aircraft, which provide vertical lift and hover augmentation by generating variable thrust and thrust vectors, reducing the load on proprotor assemblies and enabling more efficient operation in both helicopter and airplane flight modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If large proprotors are used to meet high thrust requirements in helicopter flight mode, then vertical lift capability is improved, but forward flight performance and device complexity are compromised
Solution Approach 1:
The invention divides the lift generation function into two separate systems: proprotors for forward thrust and cycloidal rotors for vertical lift. This segmentation allows each component to be optimized for its specific function, with cycloidal rotors providing vertical lift augmentation without requiring oversized proprotors, thereby reducing overall system complexity while maintaining high thrust capability.
2Speed
If conventional proprotor designs are used, then forward flight capability is achieved, but vertical lift and hover performance are insufficient
Solution Approach 1:
The cycloidal rotors serve multiple functions: they provide vertical lift during hover and low-speed flight, assist in thrust during transition phases, and can be adjusted to optimize performance across different flight regimes. This multi-functionality supplements the proprotors without compromising forward flight capability, enabling both high forward airspeed and adequate vertical thrust.
3Force
If proprotors are oversized for vertical lift, then hover capability is improved, but forward flight efficiency deteriorates
Solution Approach 1:
By separating the vertical lift function (cycloidal rotors) from the forward thrust function (proprotors), the system allows proprotors to be sized appropriately for forward flight efficiency rather than being oversized for hover. The cycloidal rotors handle the hover thrust requirement, enabling proprotors to be optimized for minimal drag and maximum efficiency during forward flight.
4Force
If vertical lift augmentation is added to tiltrotor aircraft, then hover efficiency is improved, but device complexity increases
Solution Approach 1:
The cycloidal rotors are integrated within the existing wing and propulsion structure of the tiltrotor aircraft. The cycloidal rotor assemblies are positioned within the wing nacelles or attached to the proprotor assemblies, utilizing existing structural elements and minimizing additional complexity. This nested integration allows vertical lift augmentation while maintaining a compact and manageable system architecture.
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 allows for enhanced vertical takeoff and landing capabilities, improved hover efficiency, and reduced complexity in proprotor control systems, enabling tailored proprotor designs for higher inflow environments and optimized forward flight performance.
Implementation Method 1
each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations
Implementation Method 2
the blades of each cycloidal rotor may travel along a generally circular path and may have a plurality of pitch angle configurations
Implementation Method 3
Each pylon assembly includes a mast and a proprotor assembly that is operable to rotate with the mast to generate thrust
Implementation Method 4
At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies
Data Source
AI summary
A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.