Motor Pulse-Induced Cyclic Control for Aerial Vehicle
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Solution Overview
Problem
Conventional mechanical swashplate systems used for cyclic control in large aircraft are burdensome due to weight, size, assembly complexity, and maintenance requirements, making them unsuitable for small aerial vehicles like drones.
Innovation Solution
The use of motor pulse-induced cyclic control with mono-blade rotors, which employs electromagnets or magswitches to lock rotors during cruise mode, and inverted Y-tail propellers for pitch and yaw control, reducing the need for mechanical swashplates and servomotor actuators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a mechanical swashplate system is used for cyclic control, then cyclic control functionality is achieved, but weight, size, assembly complexity, and maintenance requirements increase significantly
Solution Approach 1:
The patent replaces the mechanical swashplate system with an electrical control system using pulse-width modulation (PWM) signals to control motor actuators. This substitution eliminates complex mechanical linkages, ball joints, and swashplate assemblies in favor of electrical motors and control circuits, directly resolving the technical contradiction by maintaining cyclic control functionality while dramatically reducing mechanical complexity
Solution Approach 2:
The patent extracts and removes the mechanical swashplate components (swashplate bearing surface, ball joint linkages, ball servomotor actuators) from the system entirely. By taking out these problematic mechanical elements and replacing them with a simplified electrical actuation system, the invention resolves the contradiction between achieving cyclic control and avoiding mechanical complexity
2Reliability
If a mechanical swashplate system is used for cyclic control, then cyclic control functionality is achieved, but weight and size increase significantly
Solution Approach 1:
The patent substitutes the heavy mechanical swashplate system with lightweight electrical motor actuators and control electronics. This replacement eliminates the weight burden of mechanical linkages, bearings, and structural components while maintaining the essential cyclic control function through electrical actuation of the rotor blades
Solution Approach 2:
The patent changes the control mechanism from mechanical (physical linkages and leverage) to electrical (PWM signals and motor actuation). This parameter change in the control method enables the same cyclic control functionality to be achieved with significantly reduced weight by using electromagnetic actuation instead of mechanical force transmission
3Weight of moving object
If motor pulse-induced cyclic control is used, then weight and complexity are reduced, but control precision must be maintained
Solution Approach 1:
The patent replaces the mechanical precision transmission system with an electrical control system using PWM technology. This substitution maintains control precision through electronic signal modulation and motor control algorithms while eliminating the weight and complexity of mechanical precision linkages and bearings
Solution Approach 2:
The patent implements feedback control mechanisms to maintain precision in the motor pulse-induced cyclic control system. By using feedback from sensors and control algorithms to adjust motor actuation in real-time, the system achieves the required control precision without relying on heavy mechanical precision components
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 solution enhances on-blade cyclic control, reduces drag, and maintains vehicle reliability while enabling efficient commercial range and payload capabilities, including vertical descent and challenging takeoffs/landings, with reduced structural and battery mass.
Implementation Method 1
The electric motor control system controlling the electric motor using pulse-induced cyclic control
Implementation Method 2
employs electromagnets or magswitches to lock rotors during cruise mode
Data Source
AI summary
An aerial vehicle that uses motor pulsed-induced cyclic control is provided. In example embodiments, the aerial vehicle comprises a fuselage incorporating a battery system and a payload bay for operatively receiving and holding a payload and at least one mono-blade rotor coupled to an electric motor and an electric motor control system. The electric motor control system controls the electric motor using pulse-induced cyclic control. The aerial vehicle further includes at least one wing, at least one cruise propeller, and an avionics system. The avionic system is configured to transition the aerial vehicle between a vertical take-off and landing mode in which the at least one mono-blade rotor is primarily engaged to propel the aerial vehicle vertically and a cruising mode in which the at least one cruise propeller is primarily engaged to propel the aerial vehicle horizontally.