Helicopter Hybrid Drive Shaft Control With Torque-Speed Feedback
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Solution Overview
Problem
Existing hybrid drive systems for helicopters face safety concerns due to the division of control signals between internal combustion engines and electric motors, leading to inadequate handling of flight requirements in case of engine failure, and inefficiencies in fuel consumption and power distribution.
Innovation Solution
Incorporating torque sensors and tachometers on the drive shaft to allow the VM and EM controllers to adjust power and torque for optimal efficiency, with predefined values for speed and torque, enabling the VM to maintain a stable flight attitude and the EM to compensate for deviations quickly, ensuring safe operation and minimal fuel consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If control signals are divided between internal combustion engine and electric motor, then power distribution is optimized, but safety in case of engine failure deteriorates
Solution Approach 1:
The patent implements a feedback mechanism where the control system continuously monitors the actual power output of both the internal combustion engine and electric motor, compares it with the desired power distribution, and automatically adjusts the control signals to maintain optimal power allocation. This ensures that the divided control signal approach maintains both productivity optimization and flight safety through continuous correction.
2Stability of the object's composition
If electric motor compensates for power deviations quickly, then flight stability improves, but system complexity increases
Solution Approach 1:
The patent introduces a central control unit as an intermediary that coordinates between the pilot's control inputs, the internal combustion engine control, and the electric motor control. This intermediary processes the control signals, determines the optimal power distribution, and manages the quick compensation by the electric motor, thereby achieving flight stability while keeping the complexity manageable through centralized coordination.
3Loss of energy
If predefined optimal values are used for engine operation, then fuel efficiency improves, but adaptability to varying flight conditions deteriorates
Solution Approach 1:
The patent implements a dynamic control system that continuously adapts the predefined optimal operating values for the internal combustion engine based on real-time flight conditions. The control unit monitors parameters such as altitude, speed, and power demand, and dynamically adjusts the engine's operating point to maintain optimal fuel efficiency while adapting to varying flight conditions. This dynamic adaptation resolves the contradiction between using fixed optimal values and adapting to changing conditions.
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
The system ensures safe and efficient operation by allowing the VM to maintain a stable flight attitude and the EM to compensate for power deviations, reducing the risk of engine failure and optimizing fuel usage, while allowing for autonomous operation with minimal additional monitoring.
Implementation Method 1
an electric motor (EM), both of which act directly on the drive shaft (3)... the EM is connected to an EM control, which can operate the EM by discharging a battery
Implementation Method 2
an internal combustion engine (VM)... the VM is connected to a VM control, which can regulate the fuel supply from a fuel tank to the VM
Implementation Method 3
at least one torque sensor and one tachometer are arranged on the drive shaft, wherein both the VM control and the EM control can receive values of the current speed DZ and the current torque DM during operation
Implementation Method 4
at least one torque sensor and one tachometer are arranged on the drive shaft, wherein both the VM control and the EM control can receive values of the current speed DZ and the current torque DM during operation
Data Source
Figure 1~2
AI summary
The invention relates to a hybrid drive system (4) comprising controllers (5, 7, 11) and a drive shaft (3) of a helicopter having a main rotor (1) which is connected to a gearbox and can keep a flight attitude predefined by a pilot stable. The hybrid drive system comprises a pilot controller (5), as well as an internal combustion engine (VM) (6) and an electric motor (EM) (10) which both engage directly with the drive shaft (3). The internal combustion engine (6) is connected to an internal combustion engine controller (7), and the electric motor (10) is connected to an electric motor controller (11). According to the invention, a torque sensor (17) and a tachometer (18) are each located on the drive shaft (3), wherein both the internal combustion engine controller (7) and the electric motor controller (11) can each receive values of the current rotational speed (DZ) and of the current torque (DM) during operation. Predefined values of the rotational speed (DZ0) and of the torque (DM0), with which values the internal combustion engine (6) can increase its optimum efficiency, are stored and can be retrieved for the electric motor controller (11), and the former (DZ0) can also be retrieved for the internal combustion engine controller (7). A first directive is stored in the electric motor controller (11) to always apply a driving or braking force from the electric motor (10) to the drive shaft (3), said force being such that the internal combustion engine (6), when it has reached or is maintaining the optimum rotational speed (DZ0) at the drive shaft (3), automatically generates, at said drive shaft (3), the torque (DM0) at which it achieves the optimum motor power. The invention also relates to a corresponding method.