Tilting Rotor Mount Orientation for Balanced Aircraft Control

Solution Overview

Problem

Existing aircraft designs face challenges in achieving balanced control performance, particularly in pitch, roll, and yaw, especially under varying wind conditions, which hinders stable flight and maneuverability.

Innovation Solution

The aircraft incorporates motor mounts with bent parts and second motors that rotate these mounts to switch the orientation of rotor planes between radially and circumferentially inclined positions, enhancing control performance by optimizing lift and propulsion directions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the rotor plane orientation is fixed in conventional designs, then the structure is simple, but the control performance in pitch, roll, and yaw is unbalanced especially under wind conditions

Engineering Contradiction:

Improvecontrol performanceVSAvoidmotor mount structure

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The motor mount structure is made dynamic by enabling rotation between two distinct orientations (radially inclined and circumferentially inclined) through second motors. This allows the system to adapt rotor plane orientation based on flight conditions, improving control performance in pitch, roll, and yaw while maintaining a relatively simple structural foundation.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system changes the orientation parameter of the rotor planes by switching between two specific configurations: radially inclined orientation for enhanced pitch and roll control, and circumferentially inclined orientation for enhanced yaw control. This parameter switching allows optimized control performance for different flight scenarios without requiring complete structural redesign.

Inventive Principle:

Principle #35Parameter changes

2Adaptability or versatility

If the aircraft uses fixed rotor orientation, then the device complexity is low, but the maneuverability under varying wind conditions deteriorates

Engineering Contradiction:

Improveflight condition adaptabilityVSAvoidmotor mount and control system

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The motor mount structure is made dynamic by enabling rotation between two distinct orientations (radially inclined and circumferentially inclined) through second motors. This allows the system to adapt rotor plane orientation based on flight conditions, improving control performance in pitch, roll, and yaw while maintaining a relatively simple structural foundation.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system changes the orientation parameter of the rotor planes by switching between two specific configurations: radially inclined orientation for enhanced pitch and roll control, and circumferentially inclined orientation for enhanced yaw control. This parameter switching allows optimized control performance for different flight scenarios without requiring complete structural redesign.

Inventive Principle:

Principle #35Parameter changes

3Reliability

If the aircraft maintains stable hover, then the positioning accuracy is high, but the response to wind interference and maneuvering capability are reduced

Engineering Contradiction:

Improvehover stabilityVSAvoidresponse speed

Core Design Contradiction:

ReliabilityVSSpeed

Solution Approach 1:

The motor mount structure is made dynamic by enabling rotation between two distinct orientations (radially inclined and circumferentially inclined) through second motors. This allows the system to adapt rotor plane orientation based on flight conditions, improving control performance in pitch, roll, and yaw while maintaining a relatively simple structural foundation.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system changes the orientation parameter of the rotor planes by switching between two specific configurations: radially inclined orientation for enhanced pitch and roll control, and circumferentially inclined orientation for enhanced yaw control. This parameter switching allows optimized control performance for different flight scenarios without requiring complete structural redesign.

Inventive Principle:

Principle #35Parameter changes

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 improves tracking performance in pitch-angle, roll-angle, and yaw-rate controls, allowing the aircraft to maintain stability and maneuverability under different flight conditions, including wind interference and turning maneuvers.

Implementation Method 1

rotors each of which is positioned at a distal end of a corresponding arm of the arms and generates lift by rotating

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Data Source

PatentUS12497198B2Aircraft

Publication Date: 2025.12.16 SUBARU CORP

AI summary

An aircraft includes: a main body; arms extending substantially horizontally from the main body; rotors that are located at distal ends of the arms and generate lift by rotating; first motors that are coupled to the rotors and rotate the rotors; motor mounts supporting the first motors; and second motors that rotate the motor mounts relative to the arms. The motor mounts each includes a mount proximal end, a mount distal end, and a bent part. The first motors are each fixed to the mount distal end. The mount proximal end is disposed so as to extend substantially vertically upward from the arm. The motor mounts are each coupled to the distal end. The second motors each rotates the mount proximal end with respect to the arm to switch an orientation of a plane of rotation of the rotor between a radially inclined orientation and a circumferentially inclined orientation.