Gyroscope Vibration Control Assembly for Aircraft
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Solution Overview
Problem
Existing active vibration control techniques for aircraft, such as helicopters, are inefficient due to the heavy weight added by linear vibratory force actuators, which limit payload capacity and are not effectively counteracting undesirable vibratory hub moments.
Innovation Solution
A vibration control assembly that includes a housing with a rotatable cage and gyroscope wheel, where the gyroscope wheel is angularly displaced to produce a controllable moment, using a planetary gear arrangement and a braking mechanism to efficiently counteract vibratory moments, reducing the need for heavy linear actuators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If linear vibratory force actuators are used to counteract vibratory moments, then vibration control is achieved, but the assembly weight increases significantly
Solution Approach 1:
The patent replaces traditional linear vibratory force actuators with a gyroscope-based system that uses rotational mechanics and precession to generate counter-moments. The gyroscope wheel rotates at high speed within a cage, and by tilting the cage, gyroscopic precession produces the required counter-vibratory moments without needing heavy linear actuators, thus resolving the contradiction between vibration control effectiveness and assembly weight
Solution Approach 2:
The invention changes the operating parameters from linear oscillation to rotational motion at high speeds. The gyroscope wheel rotates at high rotational speed, and the cage tilts at controlled angles to generate precession moments. This parameter change from linear to rotational dynamics enables more efficient moment generation with reduced mass, addressing the weight versus effectiveness contradiction
2Object-affected harmful factors
If linear actuators are used to generate counter-moments, then vibration control is provided, but the payload capability is reduced
Solution Approach 1:
By substituting heavy linear actuators with a lightweight gyroscope system, the overall weight of the vibration control assembly is reduced. This weight reduction directly increases the available payload capacity of the aircraft while maintaining the ability to counteract vibratory hub moments through gyroscopic precession mechanisms
Solution Approach 2:
The gyroscope system generates counter-moments that balance the vibratory hub moments produced by helicopter rotors. By using the gyroscopic effect rather than heavy counterbalancing masses, the system achieves vibration control with minimal weight penalty, thereby preserving payload capability
3Object-affected harmful factors
If heavy designs are used to produce counter-moment effects, then vibration control is achieved, but the efficiency relative to weight is poor
Solution Approach 1:
The system changes from static or low-speed linear actuation to high-speed rotation with controlled precession. The gyroscope wheel spins at high rotational speed, and the cage tilts at optimized angles to maximize gyroscopic moment generation. This parameter optimization enables high moment production efficiency relative to the lightweight assembly, resolving the contradiction between vibration control effectiveness and weight efficiency
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 effectively reduces aircraft vibrations with minimal weight addition, allowing for efficient counteraction of pitching and rolling moments, thereby enhancing payload capacity while minimizing the assembly's weight.
Implementation Method 1
a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle
Implementation Method 2
a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis
Data Source
AI summary
A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track.