Electric Helicopter Torque Arm Rotor Drive
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Solution Overview
Problem
Traditional helicopters face inefficiencies and control issues due to the need for tail rotors and complex transmission systems, which consume power and increase manufacturing difficulties, and the weight of engines at the rotor tip generates significant centrifugal forces, complicating safe autorotation landing.
Innovation Solution
A helicopter design using a torque arm assembly with an electric propeller to directly drive the main rotor, eliminating the need for a tail rotor and complex drive train, with the motor aligned coaxially with the main rotor axis to minimize centrifugal forces and enhance efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a traditional tail rotor and long tail boom system is used to balance fuselage torque, then the fuselage maintains directional stability, but the system consumes nearly 20% of power and increases manufacturing difficulties and control issues
Solution Approach 1:
The patent extracts and eliminates the tail rotor and tail boom system from the helicopter configuration. By using a different main rotor drive mechanism (torque arm with propeller at the end), the system removes the need for counteracting tail rotor torque, thereby eliminating the complex tail assembly while maintaining fuselage stability through the alternative drive system configuration
Solution Approach 2:
The torque arm assembly serves multiple functions: it transmits engine power to the main rotor, provides structural support, and eliminates the need for a separate tail rotor system. The propeller at the end of the torque arm both drives the main rotor and balances the system, combining functions that traditionally required separate components
2Stability of the object's composition
If a jet engine is mounted at the tip of the main rotor assembly to produce thrust force, then there is no torque on the fuselage and no tail rotor is needed, but the weight of the engine generates huge centrifugal force and the jet output direction constantly changes
Solution Approach 1:
The patent introduces a timing belt as an intermediary mechanism to transmit power from the engine to the propeller at the end of the torque arm. This allows the engine to remain stationary relative to the fuselage while the propeller rotates, mediating between the need for stable engine mounting and the need for rotating propulsion
Solution Approach 2:
Instead of mounting the engine at the rotor tip and rotating it with the rotor (which creates centrifugal force issues), the patent inverts the approach by mounting the engine centrally and stationary, and using a timing belt to drive a propeller at the torque arm end that provides the rotational drive in the opposite sense
3Power
If a traditional gearbox is used to decelerate engine power and increase torque for the main rotor, then the main rotor can be driven effectively, but the transmission system complexity and power loss increase
Solution Approach 1:
The patent replaces the traditional mechanical gearbox transmission system with a direct drive configuration using a torque arm and propeller mechanism. The engine connects directly to the torque arm, which leverages its length to provide the necessary torque multiplication without requiring complex gear reduction mechanisms
Solution Approach 2:
The patent transitions from a centralized horizontal drive system (engine to main rotor through gearbox) to a vertical dimension solution by using the torque arm extending downward or upward, leveraging the vertical space and gravitational alignment to simplify the power transmission path and eliminate the need for complex horizontal gear trains
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 increases driving efficiency by 35%, simplifies the mechanical structure by 40%, enables safe autorotation landing, and improves hovering and climbing capabilities, allowing for longer flight times and stable operation in various conditions.
Implementation Method 1
the thrust force (pulling or pushing the propeller) multiplying the torque arm radius of approximate one meter giving the power torque required for the main rotor
Implementation Method 2
A timing belt with a center distance of approximately 1 meter drives the tip of the propeller from inside the torque arm
Implementation Method 3
When the main rotor assembly is under rotation, the weight of the engine installed at the tip of the rotor generates huge centrifugal force
Data Source
AI summary
A battery powered helicopter uses one or more torque arms as the power source directly driving the propeller to rotate. The helicopter does not require a combustion engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor, or a fuel supply system. The output shaft of the high-energy motor is coaxial with the main rotor shaft. The centrifugal force of one or more motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arms of the plurality of torque arms includes a propeller and a driving system.