Tilt-Rotor and Stacked Rotor Layout for Low-Interference VTOL Flight
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Solution Overview
Problem
Existing aircraft with distributed electric propulsion systems face challenges in configuring the airframe and propulsion system architecture to achieve efficient VTOL flight and high-speed cruise while maintaining system redundancy and minimizing noise and drag.
Innovation Solution
A flying vehicle design featuring a first rotor assembly with a tilt-rotor and a second rotor assembly with a stacked plurality of vertical thrust rotors, positioned longitudinally and vertically aligned, with the stacked rotors on one side of a pylon to minimize wash interference and enhance efficiency, noise performance, and dynamic benefits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If the first rotor assembly and second rotor assembly are positioned close together to share components and reduce weight, then weight is reduced, but one rotor experiences wash interference from the other increasing drag and reducing efficiency
Solution Approach 1:
The patent positions the first and second rotor assemblies in the longitudinal direction (front-to-back) rather than laterally adjacent, utilizing the longitudinal dimension to separate rotors while maintaining compact lateral footprint. This dimensional reorganization allows component sharing for weight reduction while minimizing wash interference by placing downstream rotors out of the direct wash zone of upstream rotors
2Loss of energy
If the stacked rotors are positioned on one side of the pylon to minimize wash interference, then efficiency and noise performance improve, but the structure becomes more complex
Solution Approach 1:
The patent employs asymmetric positioning of the stacked rotor assembly relative to the pylon, placing all stacked rotors on one side rather than distributing them symmetrically. This asymmetric arrangement minimizes wash interference and improves noise performance while the pylon structure itself is designed to accommodate this asymmetric configuration efficiently
3Use of energy by moving object
If the tilt-rotor is used to improve cruise efficiency, then conventional flight efficiency improves, but the structure becomes heavier compared to fixed vertical thrust rotors
Solution Approach 1:
The tilt-rotor assembly is designed to perform multiple functions: it provides conventional forward thrust for efficient cruise flight, can tilt to provide vertical thrust for takeoff and landing, and can operate in intermediate configurations for transition flight. This multi-functionality eliminates the need for separate dedicated cruise and vertical flight rotor systems, optimizing the weight-efficiency tradeoff
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 design improves efficiency and reduces noise by allowing the rotors to function as a single lifting aerofoil, minimizes drag through close proximity and alignment, and facilitates weight reduction by sharing components, while maintaining redundancy and flexibility in flight configurations.
Implementation Method 1
a tilt-rotor arranged to tilt between delivery of substantially vertical flight thrust and substantially conventional flight thrust
Implementation Method 2
a second rotor assembly comprising a stacked plurality of substantially vertical thrust rotors
Data Source
AI summary
Disclosed is a flying vehicle comprising a first rotor assembly, a second rotor assembly and a second rotor assembly pylon arranged to mount the second rotor assembly to the remainder of the flying vehicle. The first rotor assembly and the second rotor assembly are located so that they are spaced in a longitudinal direction of the flying vehicle and so they are substantially on a vertical plane that is parallel to a vertical plane aligned with a longitudinal axis of the flying vehicle. The first rotor assembly comprises a tilt-rotor arranged to tilt between delivery of substantially vertical flight thrust and substantially conventional flight thrust. The second rotor assembly comprises a stacked plurality of substantially vertical thrust rotors mounted to the pylon so as to be substantially to the same side of the pylon.