Aircraft Electric Propulsion Assembly With Split Vibration-Isolated Supports
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing electric propulsion systems in aircraft face challenges with vibration propagation to sensitive components like fuel cells and hydrogen tanks, leading to increased mass and energy consumption due to vibration-damping designs.
Innovation Solution
Implementing two separate and independent supports for the electric propulsion system and electrical power source, with vibration-filtering attachments and joints to prevent vibration transmission, reducing the need for vibration-limiting designs and minimizing mass and size.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single support structure is used to hold both the electric propulsion system and the electrical energy source, then the structural complexity is reduced, but vibration propagation increases causing higher mass requirements and energy consumption
Solution Approach 1:
The support structure is divided into two distinct and dissociated supports: a first support for the electric propulsion system and a second support for the electrical energy source. This segmentation isolates vibration sources from sensitive components, eliminating the need for complex vibration-dampening designs while reducing overall mass and energy consumption.
Solution Approach 2:
The electric propulsion system is extracted from the single support structure and mounted on a separate first support. This extraction removes the primary vibration source from the support structure holding the electrical energy source, allowing for simpler, lighter support designs that do not require extensive vibration mitigation features.
2Object-affected harmful factors
If vibration-dampening designs are implemented in the support structure, then vibration propagation is limited, but the mass and bulk of the propulsion assembly increase
Solution Approach 1:
By segmenting the support structure into two separate supports, the patent eliminates the need for complex vibration-dampening features within a single structure. The first support can be optimized for the electric propulsion system while the second support is optimized for the electrical energy source, both being simpler and lighter than a unified vibration-dampening structure.
Solution Approach 2:
The attachment systems act as intermediaries between the supports and the aircraft support structure. These attachments can include damping or anti-vibration elements that filter vibrations in multiple directions, providing vibration isolation without requiring the supports themselves to be massive or complex.
3Ease of manufacture
If a single support structure is used, then manufacturing is simplified, but vibration sensitivity of fuel cells requires complex damping designs
Solution Approach 1:
The support structure is segmented into two independent supports, each with its own attachment system. This segmentation allows each support to be manufactured as a simpler, lighter component without requiring integrated vibration-dampening features, while the attachments provide the necessary vibration filtering for the sensitive fuel cells.
Solution Approach 2:
The vibration filtering function is extracted from the support structure itself and transferred to the attachment systems. This allows the supports to be manufactured as simple, lightweight structures, while the attachments incorporate damping or anti-vibration elements that protect the fuel cells without adding mass to the supports.
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 isolates the electrical power source from propulsion vibrations, reducing the overall mass and size of the propulsion system while maintaining efficient operation.
Implementation Method 1
at least one element among the first attachment and the second attachment comprises damping or anti-vibration elements for filtering vibrations in the first, second and third directions
Implementation Method 2
at least one first element among the first attachment and the second attachment, comprises at least one pivoting connection or one linear connection for filtering the vibrations according to at least one first orientation
Data Source
Figure 1~3
Figure 4~6
AI summary
The invention relates to an aircraft propulsion assembly comprising at least one first support (62) that supports an electric propulsion system (46), at least one first attachment (64) configured to connect the first support (62) and a support structure (42) of an aircraft, at least one second support (68), separate from and independent of the first support (62), supporting an electrical power source (50) configured to supply electrical power to the electric propulsion system (46), and at least one second attachment (70) configured to connect the second support (68) and the support structure (42). The invention also relates to an aircraft comprising at least one such propulsion assembly. Since the second support (68) is separate from and independent of the first support (62), the vibrations generated by the electric propulsion system (46) are not transmitted to the electrical power source (50).