Aircraft Cyclogyro Eccentric Bearing Axis Offset Adjustment
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Solution Overview
Problem
Cyclogyro rotors face significant loads on the eccentric bearing axis due to centrifugal forces and inertia, leading to instability and increased energy consumption, which complicates design and operation, especially at high speeds.
Innovation Solution
A propulsion device with a blade mounted for pivoting about a blade bearing axis parallel to the axis of rotation, featuring an offset device that defines an eccentric bearing axis at an adjustable offset distance, allowing for a pendular movement that influences pitch movement, thereby reducing higher harmonic values and loads on the eccentric bearing axis.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the offset distance of the eccentric bearing axis is increased to adjust for changing thrust, then the thrust adjustment capability is improved, but the load on the eccentric bearing axis increases and stability deteriorates
Solution Approach 1:
The patent implements a dynamic offset distance adjustment mechanism that allows the eccentric bearing axis offset distance to be changed during operation. This enables the pitch mechanism to adapt to varying thrust requirements while maintaining optimal load characteristics at each operating point, resolving the contradiction between adaptability and stability.
Solution Approach 2:
The patent changes the geometric parameter of the offset distance to optimize performance. By adjusting the offset distance between the eccentric bearing axis and the rotation axis, the system can modify the pitch angle characteristics to reduce higher harmonic values and minimize loads on the eccentric bearing axis, thereby maintaining stability while achieving thrust adjustment.
2Productivity
If the rotational speed of the cyclogyro rotor is increased to improve productivity, then the thrust generation capability is improved, but the loads on the eccentric bearing axis increase significantly
Solution Approach 1:
The patent optimizes the offset distance parameter as a function of rotational speed. By adjusting the offset distance to decrease as rotational speed increases, the pitch angle characteristics are modified to reduce higher harmonic values, thereby minimizing the load on the eccentric bearing axis while maintaining high thrust generation capability at elevated speeds.
3Power
If the pitch angle of the blade is increased to improve thrust generation, then the thrust capability is improved, but the load on the eccentric bearing axis increases
Solution Approach 1:
The patent modifies the offset distance parameter to optimize the pitch angle characteristics. By carefully selecting the offset distance, the system achieves the desired pitch angle range for effective thrust generation while minimizing the higher harmonic values that cause excessive loads on the eccentric bearing axis, thus resolving the contradiction between power and force.
4Reliability
If the eccentric bearing axis is designed to be more stable to reduce instability, then the rotor stability is improved, but the installation space increases and lightweight construction is compromised
Solution Approach 1:
The patent optimizes the offset distance parameter to minimize loads on the eccentric bearing axis rather than designing for high stability margins. By reducing the higher harmonic values through parameter optimization, the system achieves adequate stability with a more compact and lightweight design, avoiding the need for oversized structural elements.
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 configuration minimizes loads on the eccentric bearing axis, enhances stability, and reduces energy consumption by optimizing the pitch movement and thrust generation, allowing for more efficient operation of the cyclogyro rotor.
Implementation Method 1
the blade is coupled by the coupling device in such a way that the rotation of the blade about the axis of rotation of the propulsion device along a circular path effects a pitch movement of the blade when the offset distance is set to a nonzero value
Implementation Method 2
The offset device defines an eccentric bearing axis which is mounted at an adjustable offset distance parallel to the axis of rotation of the propulsion device
Data Source
AI summary
The invention relates to a propulsion device for an aircraft, comprising a blade (2) which can be rotated about an axis of rotation (51) of the propulsion device along a circular path (52) and is mounted for pivoting about a blade bearing axis parallel to the axis of rotation; a pitch mechanism having a coupling device (31) and a bearing device (33); and an offset device (4) to which the blade is coupled, the offset device defining an eccentric bearing axis (41) which is mounted at an adjustable offset distance. The coupling device is coupled to the blade at a coupling point (32) which is positioned in such a way that the plane that comprises the blade bearing axis and the coupling point and the tangential plane to the circular path through the blade bearing axis include a certain, non-vanishing angle (wα) when the offset distance is set to zero. According to a second aspect the blade bearing axis is shifted toward the axis of rotation by a certain distance relative to the plane that extends through the center of mass of the blade and that extends parallel to the axis of rotation and to the chord of the blade.