Helicopter Rotor-Fuselage Actuator for Vibration Control
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Solution Overview
Problem
Existing helicopter vibration control devices are inefficient in reducing vibrations across the fuselage, particularly in areas further away from the force field application, leading to non-homogeneous vibration, increased energy consumption, weight, and size requirements, and fatigue stress due to alternating force patterns.
Innovation Solution
A vibration control device with accelerometers and actuators integrated into the connection assembly between the rotor and fuselage, where actuators are strategically positioned within the rods to generate a force field that counteracts vibrations at their source, minimizing energy consumption and weight while ensuring homogeneous vibration reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If actuators are positioned away from the fuselage connection point to reduce vibration, then vibration reduction effectiveness improves, but energy consumption and actuator weight increase
Solution Approach 1:
The actuator applies counteracting force at the connection point before vibration propagates to distant fuselage areas, preventing vibration transmission rather than correcting it after propagation. This preliminary intervention reduces the energy required compared to compensating for already-transmitted vibrations.
Solution Approach 2:
The connection point between rotor and fuselage serves as an intermediary where the actuator applies force to block vibration transmission. By intervening at this critical transmission point, the system achieves effective vibration reduction with lower energy consumption than applying force at distant locations.
2Reliability
If actuators generate stronger force fields to reduce vibration in distant fuselage areas, then vibration reduction effectiveness improves, but actuator weight and size increase
Solution Approach 1:
By applying counteracting force at the connection point before vibration propagates, the actuator prevents vibration transmission to distant areas. This eliminates the need for heavy actuators that would otherwise be required to generate strong force fields at distant locations.
Solution Approach 2:
The connection point acts as a strategic intermediary where a lighter actuator can effectively block vibration transmission. Intervening at this point with minimal force prevents vibration propagation, avoiding the need for heavy actuators that would be required for direct distant area control.
3Reliability
If actuators apply force field to counteract vibration, then vibration reduction effectiveness improves, but fatigue stress on fuselage increases due to alternating force patterns
Solution Approach 1:
The actuator applies counteracting force at the connection point to prevent vibration propagation, using forces that are synchronized with and oppose the incoming vibration. This preliminary counter-action reduces the net alternating stress on fuselage structures compared to applying corrective forces at distant locations where vibration amplitude is already magnified.
4Reliability
If traditional actuators are used to reduce vibration, then vibration control function is achieved, but device size and complexity increase
Solution Approach 1:
The actuator is positioned at the connection point to apply preliminary counteracting force, preventing vibration propagation. This strategic positioning simplifies the overall system design by eliminating the need for multiple distributed actuators or complex force field distribution systems, thereby reducing device complexity and size.
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 solution effectively reduces fuselage vibrations, minimizes energy consumption and equipment size/weight, and prevents fatigue stress, allowing for uniform crew accommodation without excessive design restrictions.
Implementation Method 1
one or more actuators which act on the fuselage to generate said force field
Data Source
AI summary
A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.