Aircraft Angle of Attack Determination via Leading Edge Temperature
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft angle of attack instruments are susceptible to damage from foreign objects such as ice, birds, and volcanic ash, as they are typically positioned on the exterior of the aircraft.
Innovation Solution
A method that determines an aircraft parameter indicative of the longitudinal axis position during flight, along with a wind parameter based on temperature distribution about the leading edge of an aircraft component, to calculate an offset angle between the aircraft's longitudinal axis and the relative wind direction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If angle of attack instruments are positioned on the exterior of the aircraft, then measurement precision is improved, but reliability deteriorates due to susceptibility to damage from foreign objects
Solution Approach 1:
The patent uses temperature distribution as an intermediary parameter to indirectly determine the angle of attack. Instead of directly measuring the angle with external instruments, the system measures temperature at multiple locations on the leading edge, which serves as a mediator that reflects the angle of attack through aerodynamic heating patterns, thereby avoiding direct exposure of measurement instruments to foreign objects
Solution Approach 2:
The patent replaces mechanical angle measurement instruments with a thermal field-based measurement system. By substituting mechanical sensors with temperature sensors that detect aerodynamic heating patterns, the system achieves angle of attack determination without vulnerable mechanical components exposed to the external environment
2Reliability
If temperature sensors are disposed within the component of the aircraft, then reliability is improved by protecting sensors from foreign objects, but device complexity increases
Solution Approach 1:
The patent divides the temperature measurement function into multiple discrete sensor locations distributed along the leading edge. By segmenting the measurement task across several simple temperature sensors rather than using a single complex external instrument, the system achieves both protection from foreign objects and adequate measurement capability
Solution Approach 2:
The leading edge component serves multiple functions: it is both a structural aerodynamic surface and a sensor array platform. The same component that provides aerodynamic function also houses the temperature sensors, eliminating the need for separate protective housings or mounting structures for the sensors
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 solution allows for accurate determination of the angle of attack and sideslip angle of the aircraft, reducing the risk of damage from external factors and enhancing flight stability and safety.
Implementation Method 1
A temperature distribution about a leading edge of a component of the aircraft is determined. The wind parameter is determined based on the temperature distribution about the leading edge of the component of the aircraft.
Data Source
AI summary
A method of operation is provided during which an aircraft parameter is determined indicative of a position of a longitudinal axis of an aircraft during a flight of the aircraft. A wind parameter is determined indicative of a relative wind direction during the flight of the aircraft. The wind parameter is determined based on a temperature distribution about a leading edge of a component of the aircraft. An offset angle between the longitudinal axis of the aircraft and the relative wind is determined based on the aircraft parameter and the wind parameter.