Flying Object Vibration Reduction via Shaft Intermediary
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Solution Overview
Problem
Conventional helicopters face issues with vibration transmission, flight stability, and the risk of crashes due to single rotor blade units, which can lead to instability and accidents if damaged.
Innovation Solution
A flying object design featuring a longer shaft member and multiple rotor blade units with a protection mechanism, including a telescopic shaft and tilting/rotation means, to reduce vibration, enhance stability, and prevent crashes by providing redundancy and external protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If the rotation shaft length is increased to reduce vibration transmission, then the boarding feeling is improved, but the device complexity increases
Solution Approach 1:
A shaft member is introduced as an intermediary component between the rotor blade unit and the fuselage. This shaft member has a specific length that is greater than the rotation diameter of the rotor blade unit, serving as a vibration-isolating intermediary that reduces the transmission of vibration to the fuselage while maintaining structural connectivity.
2Device complexity
If the fuselage is positioned close to the rotor blades to reduce structural complexity, then the device complexity is reduced, but the flight stability deteriorates when rotor blades encounter external resistance
Solution Approach 1:
The shaft member acts as a spatial intermediary that positions the rotor blade unit at a distance from the fuselage. The length of the shaft member is specifically designed to be greater than the rotation diameter of the rotor blade unit, creating a buffer zone that prevents direct coupling between fuselage movements and rotor blade responses, thereby improving flight stability.
3Device complexity
If only one rotor blade unit is provided to reduce device complexity, then the device complexity is reduced, but the reliability decreases when the rotor blade unit is damaged
Solution Approach 1:
The rotor blade system is segmented into multiple independent rotor blade units (first rotor blade unit and second rotor blade unit). Each unit can operate independently, and the system is designed such that even if one unit is damaged or stops rotating, the other units can continue to provide lift and propulsion, ensuring flight safety and reliability.
4Reliability
If multiple rotor blade units are provided to improve reliability, then the reliability is improved, but the device complexity increases
Solution Approach 1:
The system is divided into multiple independent rotor blade units that can be configured in different arrangements (e.g., side-by-side or stacked). This segmentation allows for improved reliability through redundancy while managing complexity through modular design, where each unit follows the same structural blueprint.
Solution Approach 2:
Multiple rotor blade units are combined in a coordinated manner around the fuselage, with each unit having its own rotation shaft but sharing common control and power distribution systems. This merging approach achieves reliability through redundancy while avoiding proportional increases in overall system complexity.
Data Source
AI summary
A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio.