Cyclorotor Thrust Vectoring via Linear Actuator Pitch Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Cyclorotors require a mechanism to oscillate blades in sync with rotation and vary motion for thrust direction and magnitude control, while also needing a geared drivetrain for high torque, which must be integrated with a support structure to transmit aerodynamic forces to the host vehicle.
Innovation Solution
The system uses linear actuators to pseudo-sinusoidally modify cyclorotor blade pitch kinematics in phase and amplitude, integrated with a transmission system including a pinion gear and main gear to provide high torque power, allowing rapid thrust vectoring without changing rotational speed or orientation, and is supported on a frame that translates aerodynamic forces to a flying or marine vehicle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If linear actuators are used to modify blade pitch kinematics pseudo-sinusoidally, then rapid thrust vectoring is achieved, but device complexity increases
Solution Approach 1:
The blade pitch kinematics are made dynamically adjustable through linear actuators that modify the pitch motion pseudo-sinusoidally. This dynamic control enables rapid thrust vectoring by varying blade pitch in real-time according to the pseudo-sinusoidal pattern, allowing the cyclorotor to achieve fast thrust direction changes without sacrificing structural integrity.
Solution Approach 2:
The linear actuators modify blade pitch following a pseudo-sinusoidal pattern, which is a periodic motion pattern. This periodic action is synchronized with the cyclorotor rotation to achieve rapid thrust vectoring while maintaining smooth, continuous control. The periodic nature of the pitch modification enables predictable and controllable thrust direction changes.
2Power
If a geared drivetrain is integrated to provide high torque, then power transmission capability is improved, but device complexity increases
Solution Approach 1:
The geared drivetrain is integrated within the cyclorotor structure itself, merging the power transmission function with the rotational support structure. The pinion gear on the motor shaft meshes with the main gear on the cyclorotor shaft, combining torque multiplication and rotational support into a unified integrated assembly, reducing the need for separate mounting structures.
Solution Approach 2:
The transmission system is nested within the cyclorotor assembly, with the pinion gear and main gear integrated into the rotational structure. This nesting arrangement allows the drivetrain components to be housed within the existing structural envelope of the cyclorotor, minimizing additional space requirements and reducing overall system complexity.
3Ease of operation
If blade pitch is oscillated once per revolution, then thrust direction control is achieved, but manufacturing precision requirements increase
Solution Approach 1:
The blade pitch oscillation is synchronized to occur once per cyclorotor revolution, creating a periodic control pattern. This periodic action is coordinated with the rotational position of the cyclorotor, ensuring that pitch changes occur at the correct phases of rotation to achieve effective thrust direction control while maintaining manufacturable tolerances.
Solution Approach 2:
The control system incorporates feedback mechanisms to monitor and adjust blade pitch oscillation timing and amplitude. This feedback ensures that the pitch oscillation remains synchronized with cyclorotor rotation, maintaining precise thrust direction control while compensating for manufacturing variations and operational conditions.
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
Enables efficient and precise control of cyclorotor thrust direction and magnitude in the plane perpendicular to rotation, providing high torque power and low aerodynamic noise, suitable for various fluid propulsion and control applications.
Implementation Method 1
Linear actuators are used to modify cyclorotor blade pitch kinematics pseudo-sinusoidally in phase and amplitude
Implementation Method 2
A transmission including a pinion gear on a motor and a main gear on a cyclorotor shaft is integrated within this system to provide high torque power to the cyclorotor
Implementation Method 3
These transmission and blade pitch control systems are integrated on a frame which translates cyclorotor aerodynamic forces to a flying or marine vehicle
Implementation Method 4
As the cyclorotor rotates these blades are oscillated once per revolution so that the individual blade aerodynamic lift produces a net thrust in a unified direction
Data Source
AI summary
A device for controlling the orientation and magnitude of cyclorotor thrust and for providing mechanical power to that cyclorotor including a system of linear actuators to position a cam or eccentric around a geared shaft. The invention includes a frame which supports the main cyclorotor shaft, provides mounting for the linear actuators, and contains the mechanical gearing system.