Hybrid UAV Rotor Unit with Inclined Synchro Gears
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Solution Overview
Problem
Existing unmanned aerial vehicles (UAVs) face limitations in efficiency and safety due to conventional rotor systems that require a tail rotor for torque balance and control, leading to reduced performance and increased risk of failure.
Innovation Solution
The design incorporates a hybrid drive unit with two independent electric motors driving two main rotors, eliminating the need for a tail rotor and providing redundancy through a serial hybrid drive and buffer batteries, ensuring safe landing even in case of engine failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a conventional rotor system with tail rotor is used, then torque balance and control are achieved, but power efficiency is reduced due to power loss to the tail rotor
Solution Approach 1:
The invention divides the rotor system into two independent main rotors, each driven by its own electric motor. This segmentation eliminates the need for a separate tail rotor, as both rotors contribute to both lift and torque balance, thereby eliminating the power loss associated with driving a dedicated tail rotor while maintaining control functionality.
Solution Approach 2:
Both main rotors are designed to perform multiple functions: generating lift and providing torque balance. This multi-functionality eliminates the need for a dedicated tail rotor, as the second main rotor assumes the torque balance function traditionally performed by the tail rotor, thereby eliminating the power loss to the tail rotor while maintaining system reliability through redundant control capabilities.
2Object-affected harmful factors
If a tail rotor is included for torque balance, then control is maintained, but the risk of injury and damage increases
Solution Approach 1:
The control function is segmented between two main rotors positioned at the front and rear of the aircraft. Both rotors can be independently controlled to provide torque balance and directional control, eliminating the need for an exposed tail rotor that poses injury risks, while maintaining full control capability through the differential rotation of the two main rotors.
Solution Approach 2:
The dangerous tail rotor component is extracted and removed from the system. Its functionality is transferred to the two main rotors, which are positioned in a safer location and can provide the same torque balance and control functions without exposing rotating blades to the rear of the aircraft where personnel might be present.
3Object-affected harmful factors
If a tail rotor is used for control, then maneuverability is maintained, but vulnerability to external damage increases
Solution Approach 1:
The control function is distributed across two main rotors positioned at the front and rear of the aircraft. This segmentation allows both rotors to contribute to torque balance and maneuvering, eliminating the vulnerability of a single exposed tail rotor while maintaining full maneuverability through coordinated control of both rotors.
Solution Approach 2:
The functions of lift generation and torque balance are merged into the two main rotors. Both rotors work together to provide both vertical lift and horizontal control, eliminating the need for a separate, vulnerable tail rotor while maintaining complete maneuverability through the differential operation of the two rotors.
4Reliability
If conventional drive systems are used, then simplicity is maintained, but redundancy and safety are insufficient
Solution Approach 1:
The drive system is segmented into two independent motor-rotor units, each capable of independent operation. This segmentation provides redundancy, as the failure of one motor or rotor does not necessarily lead to complete system failure, while the modular nature of the segmentation keeps the overall system architecture relatively simple and manageable.
Solution Approach 2:
The system transitions from a single combustion engine to two independent electric motors, changing the operational parameters to enable independent control and redundancy. This parameter change allows for enhanced safety through redundant power sources while maintaining manageable complexity through the use of standardized electric motor components.
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 configuration enhances efficiency by eliminating power loss to the tail rotor and improves safety by providing redundant power sources, ensuring the UAV can safely land even if one motor fails, thus meeting stringent safety and reliability standards.
Implementation Method 1
a generator (12) and a first electric motor (7). The combustion engine (11) is configured to drive the generator (12) to produce electricity
Implementation Method 2
the generator (12) is coupled to the first electric motor (7) in such a way that the first electric motor (7) is feedable with electricity from the generator (12)
Data Source
AI summary
An aerial vehicle is disclosed having a hybrid drive unit and a rotor unit wherein the hybrid drive unit includes at least a combustion engine, a generator and a first electric motor and the rotor unit includes a first rotor. The combustion engine is configured to drive the generator to produce electricity, and the generator is coupled to the first electric motor in such a way that the first electric motor is feedable with electricity from the generator. The rotor unit includes a second rotor and the hybrid drive unit includes a second electric motor, wherein the generator is coupled to the second electric motor in such a way that the second electric motor is feedable with electricity from the generator. The first rotor is driven by the first electric motor and the second rotor is driven by the second electric motor.