Floating Rotor Mast Control for Low-Drag Rotorcraft Maneuvering
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Solution Overview
Problem
Traditional rotorcraft maneuvering is hindered by increased drag and decreased responsiveness due to the tilting of the entire craft for lift and thrust, which affects technical performance.
Innovation Solution
Implementing rotorcraft with at least three rigid rotor system arms, each equipped with a floating mast that can be pivotally supported by single or dual pivot axes, and a flight control system that controls the rotor systems and cyclic rotor blade pitch to tilt the masts independently, allowing for improved maneuverability and responsiveness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional rotorcraft tilt the entire craft for lift and thrust, then maneuvering capability is achieved, but drag increases and responsiveness decreases
Solution Approach 1:
The rotorcraft system is segmented into multiple independent rotor systems (at least three rotor system arms), each capable of independent tilt control. This segmentation allows individual rotors to be tilted for maneuvering while the main fuselage remains level, thereby achieving maneuvering capability without increasing overall drag on the craft body.
Solution Approach 2:
The invention introduces dynamically controllable floating masts with pivot axes that enable real-time adjustment of rotor tilt angles. The flight control system continuously adjusts the tilt of individual rotor masts based on maneuvering requirements, allowing responsive control without requiring the entire craft to tilt, thus maintaining low drag configuration during maneuvers.
2Ease of operation
If traditional rotorcraft tilt the entire craft for steering, then directional control is achieved, but technical performance decreases
Solution Approach 1:
Steering control is achieved by segmenting the control function across multiple independent rotor systems. Each rotor system arm can be independently tilted to generate differential thrust, providing precise steering control without requiring the entire fuselage to tilt, thereby maintaining high technical performance and aerodynamic efficiency.
Solution Approach 2:
The floating mast with pivot axis acts as an intermediary mechanism between the flight control system and the rotor blades. It enables independent tilt adjustment of each rotor system, serving as a mediator that translates control inputs into differential thrust for steering without affecting the overall craft orientation and performance.
3Speed
If individual masts are tilted for maneuvering, then responsiveness improves, but device complexity increases
Solution Approach 1:
The floating mast design with pivot axes introduces dynamic tilt capability to each rotor system. The mast can rapidly tilt in response to control inputs, enabling fast response times for maneuvering. The dynamic nature of the pivot mechanism allows quick adjustment without requiring complex active actuators on each rotor assembly.
Solution Approach 2:
The pivot axis mechanism enables the mast to tilt and return to neutral position through aerodynamic forces and gravity alone, without requiring powered actuators or complex control mechanisms. The system uses the natural physics of the tilted mast and rotor thrust to achieve and maintain the tilted configuration, reducing mechanical complexity while maintaining responsiveness.
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 rotorcraft achieves enhanced maneuverability, faster response times, and energy efficiency by tilting individual masts rather than the entire craft, enabling smoother transitions between flight phases and reducing drag.
Implementation Method 1
a change in a floating mast's tilt position is enabled by lift forces by virtue of a change in its cyclic rotor blade pitch
Implementation Method 2
a support mechanism for pivotally supporting a floating mast about a single pivot axis or dual pivot axes
Implementation Method 3
A floating mast has controllable cyclic rotor blade pitch
Data Source
AI summary
Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.