Electric Propulsion Airspeed Sensing for Rapid Airflow Vector Control
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Solution Overview
Problem
Existing aircraft systems face challenges in accurately detecting airspeed and airflow direction without increasing cost and weight, particularly in vertical take-off and landing aircraft, which are prone to safety risks due to horizontal or vertical winds, and require rapid adjustments in propulsion system operations.
Innovation Solution
An electric propulsion system control device with multiple airspeed measurement units, including first and second airspeed measurement units, calculates airspeed and airflow direction based on propulsion system parameters, reducing reliance on pitot tubes and enabling rapid detection and control of aircraft attitudes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a pitot tube and pressure gauge are used to detect airspeed, then airspeed can be measured, but the system becomes heavier and more complex
Solution Approach 1:
The patent replaces the mechanical pitot tube system with an electric propulsion system-based measurement method. By using the electric motor's current consumption characteristics and propeller rotation parameters, the system calculates airspeed through electrical and rotational measurements rather than mechanical pressure detection, thereby eliminating the need for heavy pitot tube piping.
Solution Approach 2:
The electric propulsion system serves dual purposes: it provides thrust while simultaneously enabling airspeed measurement through its own operational parameters. The motor current and propeller rotation data, which are already required for propulsion control, are utilized for airspeed calculation, eliminating the need for separate dedicated measurement hardware.
2Measurement precision
If conventional airspeed detection methods are used, then airspeed can be measured, but the system cannot rapidly respond to changes in airspeed vector
Solution Approach 1:
The system continuously monitors motor current and propeller rotation parameters in real-time, providing immediate feedback on airspeed changes. This continuous feedback loop enables the control system to rapidly detect and respond to changes in airspeed vector, allowing for dynamic adjustment of propulsion parameters to maintain optimal flight conditions.
Solution Approach 2:
The patent implements a dynamic measurement approach where airspeed is continuously calculated based on real-time motor current and rotation data. This dynamic calculation method allows the system to rapidly track changes in airspeed vector without the delays inherent in mechanical pressure measurement systems, enabling proactive control adjustments.
3Measurement precision
If multiple detection means are mounted to detect airspeed and airflow direction, then measurement accuracy improves, but cost and weight increase
Solution Approach 1:
The electric propulsion system's motor and propeller serve multiple functions: they provide thrust while simultaneously enabling airspeed measurement, airflow direction detection, and propulsion control. By utilizing the existing motor current and rotation parameters for multiple measurement purposes, the system achieves multi-functionality without adding separate detection hardware.
Solution Approach 2:
The patent merges the airspeed measurement function with the electric propulsion system. Instead of having separate detection devices, the system combines motor current sensing, propeller rotation detection, and airflow measurement into a unified measurement approach, thereby reducing overall system complexity while maintaining measurement accuracy.
Data Source
AI summary
[Object] To detect airspeed and an airflow direction with respect to an airframe of a motorized aircraft with high accuracy without increasing the cost and weight and rapidly control attitudes of an electric propulsion system and the airframe in accordance with fluctuations of the airspeed and airflow direction.[Solving Means] An electric propulsion system control device includes: a first airspeed measurement unit that is mounted on an airframe of an aircraft and includes a first propulsion system parameter detector that detects a propulsion system parameter, the propulsion system parameter being a parameter of an electric propulsion system, the electric propulsion system being driven by an electric motor and rotating about a rotation axis as a center, and a first airspeed calculator that calculates first airspeed on a basis of the propulsion system parameter, the first airspeed being airspeed with respect to a first direction that is a direction of the rotation axis; a second airspeed measurement unit that is mounted on the airframe and measures second airspeed, the second airspeed being airspeed with respect to a second direction different from the first direction; and an airflow calculator that calculates airspeed and airflow direction with respect to the airframe on a basis of the first direction and the first airspeed and the second direction and the second airspeed.