Angled Multicopter Rotor Layout for Debris Deflection and Yaw Control
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Solution Overview
Problem
Multicopter aircraft with horizontally oriented rotors pose a risk to occupants and equipment due to debris thrown by spinning rotors, and existing flight control systems lack efficient methods to control yaw and manage actuator power effectively.
Innovation Solution
A multicopter aircraft design featuring angled rotors, where each rotor is mounted at a non-zero angle to avoid intersecting with the fuselage or occupied areas, and a flight control system that optimizes actuator usage to generate lateral forces and moments for yaw control, while minimizing power consumption and ensuring safety by preventing debris from hitting critical structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If rotors are mounted horizontally to provide lift, then lift generation is effective, but debris from spinning rotors poses a risk to occupants and equipment
Solution Approach 1:
The patent applies asymmetry by mounting rotors at angled orientations rather than horizontally. Specifically, rotors are positioned at angles (e.g., 45 degrees) relative to the horizontal plane, creating an asymmetric configuration that redirects debris away from the fuselage and occupied areas while maintaining lift generation capability
Solution Approach 2:
The patent transitions from horizontal rotor mounting (2D plane) to angled rotor mounting involving the vertical dimension. By tilting rotors at specific angles relative to the horizontal plane, the system adds a third dimensional aspect to rotor orientation, redirecting debris trajectories away from critical areas
2Adaptability or versatility
If more actuators are used to control six degrees of freedom, then control authority is improved, but power consumption and system complexity increase
Solution Approach 1:
The patent applies multi-functionality by configuring angled rotors to perform multiple functions simultaneously. Each angled rotor contributes to both lift generation and yaw control, allowing the system to achieve six-degree-of-freedom control with fewer actuators than traditional horizontal configurations, thereby reducing power consumption while maintaining control authority
Solution Approach 2:
The patent merges lift and yaw control functions into a single actuator system. By angling the rotors, the system combines what would traditionally require separate actuators (lift fans and yaw control) into an integrated configuration where each rotor contributes to both vertical lift and rotational moment generation
3Reliability
If angled rotors are used to reduce debris risk, then safety is improved, but control precision and power optimization become more challenging
Solution Approach 1:
The patent employs feedback mechanisms through the flight control system that continuously monitors aircraft attitude, rotor positions, and performance parameters. This feedback enables real-time adjustment of rotor speeds and angles to maintain precise control despite the angled configuration, managing the increased control complexity while preserving safety benefits
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 angled rotor design reduces the risk of debris hitting critical areas and enhances yaw control capabilities, while the flight control system optimizes actuator usage for efficient power management and seamless operation even with rotor failures.
Implementation Method 1
A plurality of lift fans or other rotors may be disposed in a configuration around a fuselage... each rotor mounted at a corresponding non-zero angle... to provide lift, stability, and control
Data Source
AI summary
A multicopter with angled rotors includes a fuselage and a plurality of rotors. At least some of the rotors are disposed on opposite sides of the fuselage and each is oriented at a corresponding angle to a substantially horizontal plane of the aircraft, the angle being of a magnitude such that a plane of rotation of the rotor does not intersect at least a critical portion of the fuselage.