Single-Motor Rotorcraft Thrust Vectoring for Stable Maneuvering
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Solution Overview
Problem
Existing rotorcraft drones are often expensive and complex, making them unsuitable for certain applications due to their multi-rotor designs and operational requirements.
Innovation Solution
A single-motor unmanned rotorcraft with a reorientable propulsion unit and collapsible blades, allowing for efficient directional maneuvering and flight path maintenance using a solenoid-type actuator to pivot the propulsion unit and adjust the thrust vector.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple rotors are used to enable hovering and forward flight, then flight capability is improved, but device complexity and cost increase
Solution Approach 1:
The patent combines multiple rotor functions into a single rotor system. The single rotor performs both hovering and forward flight functions by varying its pitch angle, eliminating the need for multiple separate rotor assemblies and their associated motors, thereby reducing device complexity while maintaining flight capability
Solution Approach 2:
The single rotor is designed to perform multiple functions: it can generate lift for hovering by rotating vertically, and generate thrust for forward flight by tilting forward. This multi-functional design allows one component to replace what would traditionally require multiple specialized components
2Reliability
If multiple rotors with separate motors are used, then flight control is improved, but cost increases
Solution Approach 1:
The patent merges multiple motor functions into a single motor that drives one rotor. By combining the propulsion functions that would traditionally require separate motors into one motor- rotor assembly, the system reduces component count and cost while maintaining flight control capability through electronic pitch adjustment
3Device complexity
If a single rotor is used for VTOL, then device complexity is reduced, but maneuverability and stability control become difficult
Solution Approach 1:
The patent implements dynamic control of the rotor pitch angle to enable maneuvering. The rotor can dynamically adjust its pitch between vertical (for hovering) and tilted (for forward flight), allowing the single-rotor system to achieve the maneuverability traditionally associated with multi-rotor configurations
Solution Approach 2:
The system changes the operational parameters of the single rotor by adjusting the pitch angle. This parameter change allows the same rotor to produce different thrust vectors, enabling both vertical and horizontal flight control without adding mechanical complexity
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 solution enables cost-effective, simplified operation and maneuverability, making it suitable for various roles such as surveillance, communication, and precise aerial delivery, while maintaining stability and control during flight.
Implementation Method 1
using a solenoid-type actuator to pivot the propulsion unit and adjust the thrust vector
Implementation Method 2
micro aircraft able to perform 'Vertical Take-off and Landing (VTOL)' and maintaining altitude when the aircraft is moving or when the horizontal velocity of a vehicle is at 0 by getting lift only from a single rotor's rotation
Implementation Method 3
fixed-wings that are placed in certain angle and space around the outside of the aircraft body in order to reduce a reaction torque, which affects the body to turn the opposite direction of the rotor, from the rotor's movement
Data Source
Figure 1
Figure 2A~2B
Figure 2C~2D
AI summary
An unmanned rotorcraft 101 includes an airframe 103, rotor blades 105 that are coupled to the airframe 103 for rotation therewith, a propulsion unit 107 having a propeller 109, and an actuator 137 that is coupled to the airframe 103 and adapted to temporarily reorient the propulsion unit 107 such that an axis 123 of the propeller 109 moves out of alignment with an axis 117 of the rotor blades 105. Rotation of the propeller 109 causes counter-rotation of the airframe 103 and rotor blades 105. The rotor blades 105 and blades 111 of the propeller 109 are adapted to deploy from collapsed positions when flight of the rotorcraft 101 is initiated. A method of operation by the rotorcraft 101 includes, when it is determined that a current heading does not correspond to a determined flight path, causing the actuator 137 to temporarily reorient the propulsion unit 107 in accordance with an angular orientation of the actuator 137 relative to the current heading.