UAV Virtual Swashplate Propulsion System
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Solution Overview
Problem
The mechanical complexity and large spacing requirements of traditional UAV propulsion systems with swashplates limit their compactness and suitability for small to medium-sized vehicles.
Innovation Solution
A 'virtual swashplate' system where the propeller pitch is controlled by changing the relative position of the rotors of two motors, using a hinged connection and radial ball bearings to vary blade pitch without the need for a traditional swashplate, allowing for cyclic and collective pitch control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a traditional swashplate system is used for pitch control, then cyclic and collective pitch control can be achieved, but the device complexity and spacing requirements increase
Solution Approach 1:
The patent extracts the essential function of the swashplate (pitch control) and implements it through a simplified mechanism using a single rotor with variable pitch blades. The complex multi-rotor swashplate system is replaced by taking out only the necessary pitch variation function and implementing it through blade pitch adjustment mechanisms on a single rotor, thereby reducing device complexity while maintaining pitch control capability.
Solution Approach 2:
The patent replaces the traditional mechanical swashplate system with an alternative mechanical arrangement that uses a different principle to achieve pitch control. Instead of the complex intersecting planes and linkages of a swashplate, the invention uses a simplified linkage system that connects the rotor hub to the blade pitch mechanisms, substituting the mechanical approach while achieving the same control function with reduced complexity.
2Adaptability or versatility
If a traditional swashplate system is used for pitch control, then cyclic and collective pitch control can be achieved, but the spacing requirements between motor and propeller increase
Solution Approach 1:
The patent extracts the essential pitch control function from the swashplate system and implements it with a compact mechanism that requires minimal spacing. By taking out only the necessary pitch variation function and implementing it through direct blade pitch adjustment mechanisms mounted close to the motor, the design achieves the required adaptability while minimizing the spacing between motor and propeller.
Solution Approach 2:
The patent employs a nested arrangement where the pitch control mechanisms are integrated within or adjacent to the motor assembly. The blade pitch mechanisms are positioned in a nested configuration that allows them to occupy the same spatial envelope as the motor, thereby eliminating the need for additional spacing and achieving a compact overall design while maintaining full pitch control capability.
3Length of stationary object
If the rotor position is changed to control pitch, then the spacing requirements are reduced, but the control precision and stability become more challenging
Solution Approach 1:
The patent implements feedback mechanisms that monitor the rotor position and blade pitch angle in real-time. Sensors detect the actual position of the rotor and the pitch of the blades, and this information is fed back to the control system. The control system processes this feedback and adjusts the actuator commands to achieve the desired pitch control precision, compensating for any deviations caused by the compact rotor positioning.
Solution Approach 2:
The patent employs parameter changes in the control system to maintain precision despite the compact design. By dynamically adjusting control parameters such as actuator gain, response time, and pitch angle calculations based on the actual rotor position and flight conditions, the system compensates for the challenges introduced by reduced spacing and maintains high control precision and stability.
Data Source
AI summary
An unmanned aerial vehicle includes a propulsion system having at least one propulsion module comprised of at least one propeller and at least two motors/engines, one or more of the motors/engines providing mechanical energy to drive the propeller, wherein the difference between the angular velocities of the motors/engines provides energy input to a mechanical or magneto-mechanical linkage system to change the blade pitch angle of the propeller, in cyclic and/or collective manner.