Tilting Wing Rotation Mechanism for Hover Download Reduction
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Solution Overview
Problem
Rotorcrafts face challenges in balancing thrust requirements for hover and forward-flight modes, as adding wings to reduce main rotor thrust also increases rotor download, necessitating a system that can efficiently manage wing rotation and lift distribution without additional propulsion devices.
Innovation Solution
A rotorcraft design incorporating a wing rotation system with first and second drive shafts and a uniform actuator, allowing the wings to rotate 360°, tilt differentially, and adjust flaps to minimize rotor download in hover mode while providing additional lift in forward-flight mode, thereby reducing tail rotor power and optimizing lift distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If wings are added to the rotorcraft to reduce main rotor thrust, then forward-flight performance is improved, but rotor download increases requiring more thrust and power for hover and low speed forward-flight
Solution Approach 1:
The patent implements dynamic wing rotation capability where wings can tilt between horizontal and vertical positions. In forward-flight mode, wings are horizontal to provide lift and reduce rotor power requirements. In hover mode, wings rotate to vertical position to minimize rotor download. This dynamic reconfiguration allows the system to optimize performance for different flight phases, resolving the contradiction between forward-flight speed and hover power requirements.
2Power
If wings are added to reduce main rotor thrust, then rotor power is offloaded for high speed forward-flight, but rotor download increases
Solution Approach 1:
The wing rotation system dynamically adjusts wing position based on flight mode. During forward-flight, wings are positioned horizontally to generate lift and offload rotor power. During hover, wings rotate to vertical position to minimize their contribution to rotor download. This dynamic behavior allows the system to achieve power offloading during forward-flight without permanently increasing rotor download, resolving the contradiction between these two parameters.
3Device complexity
If a uniform actuator is used to actuate both wings, then device complexity is reduced, but the system must manage differential wing rotation requirements
Solution Approach 1:
The patent introduces a differential gear mechanism as an intermediary between the uniform actuator and the wings. The uniform actuator provides synchronized motion to both wings, while the differential gear mechanism allows each wing to rotate at different angles and in different directions. This intermediary component enables the system to maintain simplicity in the actuator while achieving the adaptability needed for differential wing rotation, resolving the contradiction between device complexity and adaptability.
Data Source
AI summary
According to one implementation of the present disclosure, a rotorcraft includes a fuselage, an airframe, a main rotor, first and second wings, and a wing rotation system. The wing rotation system may be coupled to the first and the second wings and includes a first drive shaft, a second drive shaft, and a uniform actuator. The first drive shaft may be coupled to the first wing for rotation around a central wing axis, the second drive shaft may be coupled to the second wing for rotation around the central wing axis, and the uniform actuator may be coupled between the first drive shaft and the airframe. Also, the wing rotation system can be configured to actuate rotation of the first and the second wings from a first direction to a second direction.