Dual-State Propulsion System for VTOL Aircraft
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Solution Overview
Problem
Current propeller-driven VTOL aircraft face challenges in efficiently transitioning between vertical and horizontal flight modes due to the complexity, weight, and cost of separate propulsion systems, which often require tilting mechanisms and actuators for propeller orientation and pitch control.
Innovation Solution
A dual-state propulsion system that integrates a motor, nacelle tilt actuation, and propeller blade pitch control into a single unit, allowing for efficient vertical and horizontal flight by rotating the nacelle and adjusting propeller pitch through a motor shaft with a deviation angle, enabling seamless mode transitions without additional actuators or heavy structural reinforcement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate dedicated propulsion systems are used for vertical lift and forward thrust, then reliability and practicality are improved, but device complexity and weight increase
Solution Approach 1:
The patent implements a universal propulsion system where a single integrated engine and propeller assembly performs both vertical lift and forward thrust functions. The propeller blade pitch mechanism enables the same propulsion unit to efficiently operate in both flight modes by adjusting blade angle, eliminating the need for separate dedicated propulsion systems while maintaining reliability and reducing complexity
2Adaptability or versatility
If tilting mechanisms and actuators are added for propeller orientation, then adaptability for different flight modes is improved, but device complexity and weight increase
Solution Approach 1:
The patent merges the propeller pitch control function with the nacelle structure by integrating the pitch mechanism directly into the nacelle assembly. This combination allows the propeller blade pitch to be adjusted through the integrated mechanism without requiring separate tilting mechanisms or additional actuators, achieving flight mode adaptability while simplifying the overall system
3Device complexity
If integrated dual-state propulsion system is used, then device complexity and weight are reduced, but manufacturing precision requirements increase
Solution Approach 1:
The patent employs parameter changes in the motor shaft design, specifically configuring the motor shaft axis at a deviation angle (5-85 degrees) relative to the nacelle pivot axis. This angular parameter adjustment enables the integrated propulsion system to achieve proper orientation and functionality while accommodating manufacturing tolerances, reducing the stringency of precision requirements compared to traditional aligned configurations
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 simplifies the propulsion system, reducing weight and complexity while maintaining efficient thrust in both flight modes, allowing for reliable and safe operation with minimal moving parts and optimized propulsion redundancy.
Implementation Method 1
a motor, which can be rigidly connected to the rotatable nacelle, wherein the motor comprises a rotatable motor shaft
Implementation Method 2
a thruster, which can be connected to an outer end of the rotatable motor shaft... a first propeller torque of the thruster
Data Source
AI summary
A dual-state propulsion aircraft includes an aircraft fuselage; and at least one dual-state propulsion system, including a fixed nacelle, a rotatable nacelle optionally including a front curved section and rear straight section, mechanical nacelle rotation stops, mechanical shaft rotation stops, a motor, and a thruster with pivotable blades; such that the at least one dual-state propulsion system is rotatable to a first system position configured for horizontal flight and to a second system position configured for vertical flight.