Aircraft Drive System Torque Envelope Control
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Solution Overview
Problem
Current drive systems for aircraft, particularly those with electric or hybrid drives, are complex and burdensome for pilots to operate, lacking simplicity and efficiency in mode selection and energy management.
Innovation Solution
A drive system that includes a propeller, an electric motor, a transmission system, and an energy management system, allowing automatic selection between propulsion and recovery modes based on predefined torque envelopes and rotational speed, simplifying pilot input through a percentage-based interface and enhancing energy flow control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If automatic mode selection and energy management are implemented, then pilot workload is reduced and ease of operation is improved, but device complexity increases due to additional control units and sensors
Solution Approach 1:
The drive system automatically monitors its own operational parameters (torque, rotational speed) and self-regulates mode selection between propulsion and recovery modes without requiring continuous pilot intervention. The control unit autonomously manages energy flow based on detected conditions, enabling the system to serve itself and reduce pilot workload.
Solution Approach 2:
The system incorporates sensors that continuously detect operational parameters such as torque and rotational speed, feeding this information back to the control unit. Based on this feedback, the control unit automatically adjusts the active mode and energy management strategies, creating a closed-loop control system that adapts to changing flight conditions.
2Use of energy by moving object
If torque envelope control is implemented to optimize energy recovery, then energy efficiency is improved, but control complexity increases
Solution Approach 1:
The system dynamically adjusts the torque envelope parameters (maximum positive torque and minimum negative torque) based on the detected rotational speed and operational mode. By changing these parameters adaptively rather than using fixed values, the system optimizes energy recovery efficiency across different flight conditions while managing control complexity through parameter-based regulation.
3Measurement precision
If multiple sensors and control units are added for automatic mode selection, then measurement precision and control accuracy are improved, but device complexity and manufacturing cost increase
Solution Approach 1:
The control unit is designed to perform multiple functions: detecting rotational speed, determining operational mode, managing energy flow, and controlling torque output. By making the control unit multi-functional rather than having separate dedicated units for each function, the system achieves high measurement and control precision while reducing overall manufacturing complexity and cost.
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 significantly reduces pilot workload by simplifying operations and optimizing energy use, allowing for efficient torque management and automatic mode selection based on flight conditions, thereby enhancing aircraft performance and safety.
Implementation Method 1
an electric motor E; a first unit (105) to control a torque T acting on the electric motor E
Implementation Method 2
to transmit a negative torque T− from the propeller P in a windmill braking state on the electric motor E; wherein the electric motor E generates electrical recovery energy Erecup in the recovery mode RM
Data Source
AI summary
Drive system for an aircraft, including: a propeller; electric motor; transmission system for transmitting positive torque from the motor to drive the propeller and negative torque from the propeller in windmill braking state to drive the motor; interface for inputting an input; first unit for controlling torque acting on the motor; second unit for detecting rotational speed of the motor; selection unit to select an active mode from propulsion mode and recovery mode, wherein the motor generates recovery energy in the recovery mode; and management system to control energy flow in an electrical system of the aircraft, the electrical system including the motor, is controlled according to the active mode; wherein the selection unit is configured to select the active mode according to the input, rotational speed, and predefined envelope, wherein the envelope indicates a maximum positive torque and minimum negative torque that depends on the rotational speed.