Battery-Mass Vibration Attenuation for Rotorcraft Airframes
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Solution Overview
Problem
Aircraft experience vibrations due to mechanical components and airflow, which existing vibration attenuation systems like tuned mass absorbers and Frahms often address inadequately due to their weight and added mass, posing challenges in maintaining structural integrity and payload capacity.
Innovation Solution
The implementation of a vibration attenuation system using multiple batteries coupled with elastic devices of varying stiffness, which oscillate to attenuate vibratory forces exerted on the airframe, thereby reducing resonance and structural stress without adding dead weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If tuned mass absorbers or Frahms are used to mitigate vibrations, then vibration attenuation is improved, but aircraft weight increases
Solution Approach 1:
The patent applies multi-functionality by using batteries that already exist in the aircraft for dual purposes: power supply and vibration attenuation. The batteries serve as tuned mass absorbers, eliminating the need for separate vibration mitigation components and thereby avoiding additional weight while still achieving vibration reduction across multiple frequencies
Solution Approach 2:
The invention merges the power supply function and vibration attenuation function into a single integrated system. The batteries are coupled to the airframe structure and configured to attenuate vibrations at their natural frequency and harmonics, combining two essential aircraft functions into one component system
2Object-affected harmful factors
If multiple batteries with different stiffness elastic devices are used to attenuate vibrations across a range of frequencies, then vibration attenuation effectiveness is improved, but device complexity increases
Solution Approach 1:
The patent applies local quality by configuring different elastic devices with varying stiffness values for different batteries based on their specific locations and vibration attenuation requirements. Each battery-elastic device combination is locally optimized for its frequency range, with stiffer devices for higher frequencies and more compliant devices for lower frequencies, achieving broad-spectrum attenuation without requiring a completely different system design
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 attenuates vibrations across a range of frequencies, maintaining aircraft payload capacity and reducing the risk of resonance-induced damage, as the batteries and elastic devices work together to absorb and dissipate vibratory energy.
Implementation Method 1
The rotor system is operable to exert a vibratory force on the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
Implementation Method 2
The elastic devices are configured attenuate the vibratory force of the airframe based on facilitating oscillation of the two or more batteries. Each of the elastic devices has a stiffness different from others of the elastic devices.
Implementation Method 3
The elastic devices are coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
Implementation Method 4
The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. The two or more batteries and elastic devices work together to absorb and dissipate vibratory energy.
Data Source
Figure 1A~1B
Figure 2A
Figure 2B
AI summary
In some examples, an aircraft (600) comprises an airframe (602), a rotor system (604a, 604b) coupled to the airframe (602), and a vibration attenuation system (610). The rotor system (604a, 604b) is operable to exert a vibratory force on the airframe (602). The vibration attenuation system (610) comprises two or more batteries (606) and elastic devices (608). The two or more batteries (606) are operable to supply power to the rotor system (604a, 604b). The elastic devices (608) coupled to the two or more batteries (606) and the airframe (602). The elastic devices (608) are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries (606). In other examples, a method comprises coupling elastic devices (608) to two or more batteries (606) and an airframe (602) of an aircraft (600). The elastic devices (608) receiving a vibratory force via the airframe (602) and attenuate the vibratory force based on facilitating oscillation of the two or more batteries (606).