Rotor Blade Pitch Detection with Hall Sensors for VTOL Flight
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Solution Overview
Problem
Existing aircraft, such as helicopters and gyroplanes, face limitations in operating efficiency, vertical takeoff and landing capabilities, and flight mode transitions, with helicopters being inefficient and gyroplanes lacking variable pitch rotors for vertical takeoff.
Innovation Solution
An aircraft design incorporating a rotor assembly with a lower and upper rotor hub assembly, blade pitch detection apparatus, and sensors like hall effect sensors to monitor rotor blade pitch and rotational speed, enabling efficient vertical takeoff, horizontal flight, and seamless flight mode transitions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a helicopter uses a fixed vertical shaft with swash plates and links to the rotor head, then the pilot can modify the pitch of the rotor blades generating lift, but the operating energy efficiency is poor compared to fixed-wing aircraft
Solution Approach 1:
The patent implements a dynamic blade pitch adjustment system where the rotor blades can automatically adjust their pitch angle based on flight conditions. The blade pitch adjustment linkage connects the rotor blades to the rotor hub, allowing real-time modification of blade pitch without requiring complex swash plate mechanisms, thereby improving energy efficiency while maintaining operational flexibility
Solution Approach 2:
The system changes the pitch parameter of the rotor blades dynamically during flight. By adjusting the blade pitch angle according to operational requirements (vertical takeoff, horizontal flight, hovering), the aircraft optimizes its energy consumption for each flight phase while maintaining the ability to modify pitch when needed
2Productivity
If a gyrocopter uses an unpowered rotor in autorotation to develop lift, then forward thrust is provided by an engine-driven propeller, but the aircraft cannot take off and land vertically
Solution Approach 1:
The patent creates a multi-functional rotor system that can operate in multiple flight modes: vertical takeoff and landing, horizontal flight, and hovering. The rotor assembly with adjustable pitch blades can function as both a gyrocopter rotor for forward flight and a helicopter rotor for vertical maneuvers, eliminating the need for separate systems and providing versatile flight capabilities
Solution Approach 2:
The system dynamically switches between different flight modes by adjusting the rotor blade pitch and the tilt of the rotor hub. The blade pitch adjustment linkage and rotor hub tilt mechanism enable the aircraft to transition from gyrocopter mode (horizontal flight) to helicopter mode (vertical flight) and back, providing adaptability for different operational requirements
3Ease of operation
If a gyrocopter has a fixed pitch rotor with zero pitch, then the rotor can rotate freely in autorotation, but the aircraft lacks the ability to achieve vertical takeoff
Solution Approach 1:
The patent introduces dynamic pitch adjustment capability to the rotor blades through the blade pitch adjustment linkage. This allows the rotor to transition from fixed zero pitch (suitable for autorotation) to variable pitch (required for vertical takeoff), maintaining operational flexibility while enabling previously impossible flight modes
Solution Approach 2:
The blade pitch adjustment mechanism is designed to automatically adjust blade pitch based on rotor speed and flight conditions. The system uses the rotor's own rotational characteristics to trigger pitch changes, eliminating the need for external control inputs and maintaining ease of operation while enabling vertical takeoff capability
4Reliability
If a helicopter uses a propeller mounted vertically at the end of a boom to create thrust, then torque generated by the motor driving the rotor head is counteracted, but the device complexity increases
Solution Approach 1:
The patent extracts the torque counteraction function from the complex vertical propeller mounting structure. Instead of using a vertical propeller on a boom, the system uses the rotor hub tilt mechanism and blade pitch adjustment to generate counter-torque, simplifying the overall structure while maintaining the ability to counteract motor torque during vertical flight
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 aircraft achieves efficient forward flight, hovering, and vertical takeoff/landing with precise monitoring of rotor blade pitch and speed, allowing for extended data gathering without runways and reduced complexity.
Implementation Method 1
a sensor coupled to a component of the lower rotor hub assembly and configured to generate a signal in the presence of the magnet
Data Source
AI summary
A blade pitch detection apparatus for an aircraft having a lower rotor hub assembly and an upper rotor hub assembly, the upper rotor hub assembly including a blade pitch adjustment linkage configured to maintain the rotor blades at a first blade pitch while a rotational velocity of the upper rotor hub assembly is below a threshold and to maintain the rotor blades at a second blade pitch while the rotational velocity is above a threshold. The pitch detection apparatus includes a magnet coupled to a component of the blade pitch adjustment linkage and a sensor coupled to a component of the lower rotor hub assembly and configured to generate a signal in the presence of the magnet. Processing circuitry in communication with the sensor can determine whether the plurality of rotor blades are at the first blade pitch or the second blade pitch based on the signals.