Canted Co-Axial Rotors for Low-Power Yaw Control
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Solution Overview
Problem
Multi-rotor rotorcrafts face limitations in maneuverability and payload capacity due to increased power requirements as they scale, especially in yaw control, and are constrained by power sources like batteries which can lead to reduced range and payload capacity.
Innovation Solution
The implementation of a rotorcraft design with canted rotors, where each rotor's axis of rotation is non-parallel and non-perpendicular to the yaw axis, allowing for increased yaw control through differential rotational speeds of opposing pairs of rotors, reducing power consumption and enhancing payload capacity and range.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If traditional multi-rotor rotorcrafts use vertical rotors for yaw control, then the control mechanism is simple, but the power consumption increases and payload capacity decreases
Solution Approach 1:
The patent applies asymmetry by canting the rotors at angles relative to the vertical axis, creating an asymmetric rotor configuration where rotors are positioned at specific angles (e.g., 30 degrees) from the vertical. This asymmetric arrangement allows the rotors to generate both vertical lift and horizontal thrust components, enabling yaw control without requiring differential power to opposing rotors, thereby reducing overall power consumption while maintaining control efficiency
Solution Approach 2:
The patent transitions from a traditional vertical rotor arrangement to a canted rotor configuration that utilizes three-dimensional spatial orientation. By tilting the rotors at angles to the vertical axis, the system exploits the third dimension (angular orientation) to generate thrust components in multiple directions simultaneously, allowing yaw control through the horizontal thrust component of canted rotors rather than relying solely on differential vertical thrust
2Quantity of substance
If rotorcraft scale to larger sizes, then payload capacity increases, but maneuverability decreases due to increased moment of inertia
Solution Approach 1:
The canted rotor configuration creates asymmetric thrust vectors that can be independently controlled to produce rotational moments. This asymmetric arrangement allows larger rotorcraft to achieve yaw control through the horizontal components of canted rotor thrust, reducing the power required compared to traditional vertical rotor differential control, thereby improving maneuverability while maintaining larger payload capacity
Solution Approach 2:
The patent changes the geometric parameter of rotor orientation from vertical to canted angles, fundamentally altering how thrust is generated and distributed. This parameter change ( rotor cant angle) transforms the thrust vector orientation, allowing the same rotor system to provide both lift and yaw control functions, improving maneuverability characteristics of larger rotorcraft without increasing power consumption
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 design enhances yaw control and reduces power consumption, enabling rotorcrafts to maintain maneuverability and increase payload capacity and range by utilizing thrust components oriented non-parallel to the yaw axis, thus overcoming the limitations of traditional multi-rotor designs.
Implementation Method 1
Each of the at least four rotors may produce a thrust component oriented perpendicular to a ray extending from a yaw axis
Data Source
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AI summary
A rotorcraft has a frame and a plurality of rotors connected to the frame. The frame has a roll axis and a pitch axis. Each of the rotors includes a rotor shaft. The rotor shaft of each of the rotors is canted with respect to at least one of the roll axis and the pitch axis. The rotor shaft of each of the rotors may be canted between 3 and 15 degrees. Each of the rotors may be a co-axial co-rotating rotor. The rotors may be oriented in opposing pairs across the frame. Both rotors in each opposing pair rotate in the same direction. The rotorcraft may include at least two additional rotors, each having a forward cant. Each of the additional rotors may be a co-axial contra-rotating rotor.