Tilt Driving Mechanism Torque Reduction
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Solution Overview
Problem
The existing tilt-rotor aircraft designs face challenges with high torque requirements and increased volume due to the use of connecting rods for steering gear, leading to reduced safety and stability, as well as jamming issues during flight.
Innovation Solution
A tilt driving mechanism with a housing, driving mechanism, and mounting seat, utilizing a worm and worm gear system to reduce torque and facilitate miniaturization, along with a baffle plate and retarding mechanism to enhance stability and safety, and a control method for precise tilt angle control using inertia measurement units.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a steering gear uses a connecting rod structure to control rotation of a tilt mechanism, then the tilt-rotor aircraft can achieve rotor tilting function, but the volume of the aircraft increases and safety and stability decrease
Solution Approach 1:
The patent extracts and eliminates the connecting rod from the steering gear system, replacing it with a direct drive mechanism where the steering gear is integrally connected to the tilt mechanism. This removal of the intermediate connecting rod component directly reduces the overall volume of the tilt driving mechanism while maintaining the rotor tilting function.
Solution Approach 2:
The steering gear and tilt mechanism are merged into an integrated unit, where the steering gear is directly connected to the tilt mechanism without intermediate components. This merging eliminates the need for separate connecting rods and reduces the overall volume of the system while preserving the tilting functionality.
2Adaptability or versatility
If a steering gear uses a connecting rod structure to control rotation of a tilt mechanism, then the tilt-rotor aircraft can achieve rotor tilting function, but safety and stability decrease due to jamming
Solution Approach 1:
The patent removes the connecting rod from the steering gear system, eliminating the intermediate connection that is prone to jamming. By directly connecting the steering gear to the tilt mechanism, the system eliminates potential jamming points and improves reliability during flight operations.
Solution Approach 2:
The patent converts the potential harm of complex mechanical connections (which cause jamming) into a benefit by simplifying the structure. The direct connection eliminates intermediate components that could fail, turning the complexity-induced reliability problem into a simple, reliable direct-drive system.
3Adaptability or versatility
If a steering gear uses a connecting rod structure to control rotation of a tilt mechanism, then the tilt-rotor aircraft can achieve rotor tilting function, but the steering gear requires high performance due to large torque
Solution Approach 1:
The patent extracts the connecting rod from the system, eliminating the mechanical advantage multiplication that increases torque requirements. The direct connection reduces the torque load on the steering gear by removing the intermediate lever arm, allowing for a more compact and lower-power steering gear design.
Solution Approach 2:
Instead of using a connecting rod to transmit and amplify torque from the steering gear to the tilt mechanism, the patent inverts the approach by directly connecting the steering gear output to the tilt mechanism input, eliminating the torque amplification effect and reducing the power requirements.
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
The solution significantly reduces torque, enables miniaturization, prevents jamming, and improves stability and safety, allowing for efficient and precise control of the tilt mechanism, enabling the aircraft to switch between lift and thrust modes effectively.
Implementation Method 1
The first rotation mechanism is a worm, and the second rotation mechanism is a worm gear
Data Source
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AI summary
The present invention provides an aircraft, a tilt driving mechanism and a control method thereof. The tilt driving mechanism is mounted on an aircraft to control tilting of a power unit of the aircraft. The tilt driving mechanism comprises a housing fixedly mounted on the aircraft, a driving mechanism mounted in the housing, and a mounting seat flexibly mounted on the housing. A power unit is fixedly mounted on the mounting seat, and the driving mechanism is fixedly connected to the mounting seat, so as to drive the mounting seat to rotate with respect to the housing. The tilt driving mechanism is disposed on the aircraft, and a rotation angle of the tilt driving mechanism is controlled with high precision to change a direction of the power unit, so that the power unit switches between a lift force providing position and a thrust providing position. Meanwhile, the driving mechanism is disposed in the tilt driving mechanism, thereby significantly reducing a torque of the driving mechanism, facilitating miniaturization design of the tilt driving mechanism, and improving stability and safety of the tilt driving mechanism.