Aircraft Wing Harness Layout for Rotor Burst Fault Isolation
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Solution Overview
Problem
The existing design of electric multirotor aircraft does not adequately consider the arrangement of components to prevent damage from scattered engine fragments in case of a rotor burst, leading to potential failures and reduced safety.
Innovation Solution
The aircraft is designed with a generator and electric motors arranged such that the engine overlaps the wing in the front-rear direction, and the power harnesses are separated within the wing to minimize the risk of simultaneous failure of rotors and power transmission systems in the event of a rotor burst.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the engine is arranged to overlap the wing in the front-rear direction, then the space utilization is improved, but the risk of rotor failure due to fragment scattering increases
Solution Approach 1:
The wing is divided into multiple sections with separate harnesses routed through different segments (front wing section and rear wing section). This segmentation ensures that if the engine bursts and scatters fragments, the damage is localized to one segment while other segments remain functional, preventing simultaneous failure of all rotors.
Solution Approach 2:
The wing structure acts as an intermediary barrier between the engine and the rotors. By routing harnesses through the wing's internal structure at different locations, the wing provides physical separation and protection, reducing the direct impact of engine fragments on critical electrical components.
2Strength
If the harnesses are routed inside the wing, then the wiring protection is improved, but the complexity of harness arrangement increases
Solution Approach 1:
Multiple harnesses are merged into a single bundled arrangement within the wing structure. Instead of routing each harness separately through complex paths, they are combined into a unified harness assembly that follows a standardized route through the wing, simplifying the overall arrangement while maintaining protection.
Solution Approach 2:
The harnesses are nested within the wing's internal structure, utilizing the existing structural cavities and channels. This nesting approach provides natural protection while avoiding the need for additional external routing, reducing overall system complexity.
3Reliability
If the engine is positioned to overlap the rotation trajectory region, then the fragment scattering impact is reduced, but the available space for component arrangement decreases
Solution Approach 1:
The engine positioning strategy moves from a two-dimensional planar arrangement to a three-dimensional spatial arrangement. By utilizing the vertical dimension and positioning the engine to overlap the rotation trajectory region in the front-rear direction, the design achieves better fragment protection while maintaining adequate space through vertical separation.
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 design reduces the likelihood of rotor failures and power system disruptions during a rotor burst, allowing for continued flight and minimizing damage to components, thereby enhancing safety and reliability.
Implementation Method 1
a generator (46) configured to generate electric power; an engine (44) configured to drive the generator
Implementation Method 2
a first electric motor (20V5_1) configured to drive the first rotor; a second electric motor (20V7_2) configured to drive the second rotor
Implementation Method 3
a first rotor (18V5) configured to generate thrust in a vertical direction; a second rotor (18V7) configured to generate thrust in the vertical direction
Implementation Method 4
a wing (14b) attached to a fuselage (12) and configured to generate lift
Data Source
AI summary
An aircraft includes: a gas turbine for driving a generator; a first electric motor for driving a first rotor; and a second electric motor for driving a second rotor. The gas turbine is arranged in a manner so that the gas turbine overlaps a rear wing in the front-rear direction of a fuselage, and a first high-voltage harness for transmitting electric power to the first electric motor and a second high-voltage harness for transmitting electric power to the second electric motor are arranged inside the rear wing so as to be separated from each other in the front-rear direction of the fuselage.