Tilt-Prop Aircraft Mechanical Pitch Actuation
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Solution Overview
Problem
Tilt-prop aircrafts require additional heavy and complex electric actuators to adjust blade pitch angles during flight mode transitions, leading to increased weight, electricity consumption, and system complexity.
Innovation Solution
A mechanical power transmission unit is used to automatically adjust the pitch angle of blades when the rotor tilt angle is varied, eliminating the need for additional electric actuators by mechanically interlocking the power transmission unit with the tilt center shaft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If electric actuators are provided for each rotor to adjust blade pitch angle and rotor tilt angle, then the flight mode switching capability is improved, but the weight of the aircraft increases
Solution Approach 1:
The patent combines the functions of blade pitch angle adjustment and rotor tilt angle adjustment into a single integrated actuator system. The actuator simultaneously controls both the pitch angles of multiple blades and the tilt angle of the entire rotor assembly, eliminating the need for separate actuators for each function and reducing overall system weight.
Solution Approach 2:
The actuator is designed as a multi-functional device that can perform multiple operations: adjusting pitch angles of blades for thrust control, tilting the rotor assembly for flight mode switching, and coordinating these movements seamlessly. This universal actuator replaces multiple specialized actuators, reducing weight while maintaining full flight mode switching capability.
2Adaptability or versatility
If electric actuators are provided for each rotor to adjust blade pitch angle and rotor tilt angle, then the flight mode switching capability is improved, but the device complexity increases
Solution Approach 1:
The patent merges the control mechanisms for blade pitch adjustment and rotor tilt adjustment into a single integrated actuator assembly. This consolidation reduces the number of independent control systems, simplifies the overall device architecture, and reduces complexity while maintaining the ability to switch between flight modes.
Solution Approach 2:
The actuator is designed as a universal control device that handles multiple functions through a unified control mechanism. By using one multi-functional actuator instead of multiple specialized actuators, the control system complexity is reduced while retaining full capability for flight mode transitions.
3Adaptability or versatility
If electric actuators are provided for each rotor to adjust blade pitch angle and rotor tilt angle, then the flight mode switching capability is improved, but the electricity consumption increases
Solution Approach 1:
The patent combines multiple actuator functions into a single integrated system, reducing the total number of motors and electrical components required. This consolidation reduces overall electricity consumption while maintaining the capability to adjust blade pitch angles and rotor tilt angles for flight mode switching.
Solution Approach 2:
The universal actuator performs multiple functions with a single electrical power source, eliminating the need for multiple independent power supplies and reducing total electricity consumption. The actuator efficiently manages power usage across pitch adjustment and tilt adjustment operations.
4Adaptability or versatility
If two control actuators are provided for each rotor in multicopter-type tilt-prop aircraft, then the flight mode switching capability is improved, but the weight of the aircraft is further increased
Solution Approach 1:
The patent applies the merging principle to multicopter configurations by integrating pitch control and tilt control into a single actuator per rotor. This reduces the number of actuators from two per rotor to one per rotor, significantly reducing the overall weight of multicopter-type aircraft while preserving flight mode switching capability.
Solution Approach 2:
The actuator is designed as a multi-functional universal controller that handles both pitch angle adjustment and rotor tilt adjustment for each rotor in the multicopter system. This universal approach eliminates redundant actuators and reduces total system weight while maintaining full adaptability for various flight modes.
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 solution reduces the weight and electricity consumption of the aircraft, simplifies the system, and improves reliability by allowing automatic pitch angle adjustments during mode transitions without additional electric actuators.
Implementation Method 1
a pitch angle of the blade is varied by a power transmission unit mechanically interlocked with the tilt center shaft
Implementation Method 2
a mechanical power transmission unit is used to automatically adjust the pitch angle of blades when the rotor tilt angle is varied, eliminating the need for additional electric actuators by mechanically interlocking the power transmission unit with the tilt center shaft
Data Source
AI summary
A tilt-prop aircraft is configured to operate in a vertical take-off and landing (VTOL) mode or a forward flight mode by adjusting a tilt angle of a rotor connected to a wing. The tilt-prop aircraft includes: a blade included in the rotor and configured to rotate to produce lift and thrust; and a tilt center shaft configured to connect the rotor and the wing to each other and adjust the tilt angle of the rotor with respect to a flight plane of the tilt-prop aircraft, wherein when the tilt angle of the rotor is adjusted, a pitch angle of the blade is varied by a power transmission unit mechanically interlocked with the tilt center shaft.