Tilt-rotor UAV Ele-wings and Rotating Propellers for Flight Mode Transition
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Solution Overview
Problem
Current unmanned air vehicles face challenges in transitioning smoothly between vertical and linear flight modes due to limitations in wing design and propulsion systems, which affect their ability to efficiently perform tasks such as cargo delivery and surveillance.
Innovation Solution
The design incorporates 'ele-wings' that function as both elevators and ailerons, capable of adjusting wing angle of attack, and a system of rotating propellers that can change orientation from vertical to linear flight, supported by a robust frame and landing gear for versatile operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional separate elevator and aileron surfaces are used, then control functions are distinct and simple, but the wing design complexity increases and smooth transition between flight modes becomes difficult
Solution Approach 1:
The patent combines the elevator and aileron control surfaces into a single integrated ele-wing structure. This ele-wing can perform both pitch control (elevator function) and roll control (aileron function) through different movement modes, reducing the number of separate control surfaces while maintaining full control capability across vertical and linear flight modes
Solution Approach 2:
The ele-wing is designed with dynamic adjustability, allowing it to change its functional mode during flight. The ele-wing can rotate about the longitudinal axis for roll control, pivot about the lateral axis for pitch control, and adjust its angle of attack, enabling smooth transition between vertical and linear flight modes through continuous motion rather than discrete position changes
2Speed
If fixed wing angle of attack is used, then structural design is simpler, but stall speed remains high and smooth flight mode transition is hindered
Solution Approach 1:
The ele-wing incorporates dynamic angle of attack adjustment capability through rotation about the longitudinal axis and pivoting motions. This allows the wing to optimize its angle of attack during transition between vertical and linear flight modes, reducing stall speed by maintaining favorable airflow attachment while adapting to changing flight conditions
Solution Approach 2:
The patent changes the operational parameters of the wing by allowing continuous adjustment of the angle of attack and control surface deflections. During flight mode transition, the ele-wing dynamically modifies these parameters to maintain aerodynamic efficiency and reduce stall speed, rather than operating at a fixed angle
3Adaptability or versatility
If propellers are fixed in orientation, then propulsion system is simpler, but the vehicle cannot efficiently perform both vertical and linear flight modes
Solution Approach 1:
The propulsion system employs dynamically adjustable propeller orientation, where each propeller can rotate to different angles depending on the flight mode. During vertical flight, propellers are positioned for optimal upward thrust; during linear flight, they rotate to provide forward propulsion, enabling efficient operation across multiple flight modes through continuous repositioning
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 enables seamless transitions between flight modes, reducing stall speed and enhancing the vehicle's ability to perform various tasks like take-off, cruising, descending, and landing, while also supporting cargo and power systems for extended functionality.
Implementation Method 1
A plurality of spaced apart propellers, each having propeller drive motors, is attached to the center frame. The propellers are configured to propel the aircraft in a vertical flying mode and rotate 90 degrees or more to propel the air vehicle in a linear flying mode.
Implementation Method 2
The ele-wings shall provide traditional elevator and aileron functions while having the ability to rotate the wing surface angle of attack in order to lower the wing stall speed which facilitates a smooth transition from vertical to linear flight.
Data Source
AI summary
An unmanned air vehicle is provided. The unmanned air vehicle includes a frame having a center portion connecting two substantially parallel transversely spaced apart ele-wings. The ele-wings may store batteries and rotate along a forward axis to provide lift during a transition from vertical flight to linear flight. The landing gear may be connected to the ele-wings and configured to change pitch of the ele-wing to ensure stable flight during flight mode transition. A plurality of propellers, each having propeller drive motors, are attached to the frame and able to rotate from parallel position, relative to the center portion, for vertical flight to a perpendicular position, relative to the center portion, for linear flight. The propeller drives rotate on its axis and may be configured to propel the vehicle in a ground and flight mode.