Aircraft Sensor Probe With Side-Mounted Connector
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Solution Overview
Problem
Smaller aircraft and electrically-powered vertical takeoff and landing (eVTOL) aircraft face challenges due to limited space for sensors, difficulty in placing sensors, and unsuitable size, weight, and power characteristics of existing sensors, which hinder effective flight information collection.
Innovation Solution
A sensor design featuring a probe portion that extends outward from the aircraft with an interior portion within the aircraft, including a housing and airdata computer, and an electrical connector on either side, allowing for reduced size and efficient routing of wiring to accommodate the limited space and power requirements of eVTOL aircraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If existing sensors are used in smaller aircraft and eVTOL, then flight information collection is achieved, but the sensor depth requirement of 7.0 inches or more exceeds the limited space available inside the aircraft skin
Solution Approach 1:
The sensor is divided into separate functional components: the probe portion that extends outside the aircraft skin and the interior portion containing the airdata computer that fits within the limited internal space. This segmentation allows each component to be optimized for its specific spatial requirements.
Solution Approach 2:
The electrical connector is positioned on the side of the interior portion rather than requiring deep insertion, changing the connection geometry from a deep axial arrangement to a side-mounted configuration that accommodates limited internal depth while maintaining electrical connectivity.
2Productivity
If existing sensors are installed in smaller aircraft, then flight information is collected, but the wiring routing becomes difficult due to limited space and unconventional sensor placement locations
Solution Approach 1:
The electrical connector is pre-positioned on the side of the interior portion at optimal locations for wiring access, allowing cables to be routed externally along the aircraft skin surface rather than requiring complex internal routing through limited space.
Solution Approach 2:
The side-mounted electrical connector acts as an intermediary interface between the internal airdata computer and external wiring, enabling simplified cable routing along the aircraft exterior while maintaining secure internal connections.
3Measurement precision
If existing sensors are used in eVTOL aircraft, then flight parameters are measured, but the size, weight, and power characteristics are not suited for electrically-powered vertical takeoff and landing aircraft
Solution Approach 1:
The airdata computer and associated electronics are extracted into a separate interior portion with its own housing, separating the measurement function (probe) from the processing function (airdata computer). This allows the overall sensor system to be distributed across available spaces rather than requiring a single heavy unit.
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
Enables effective collection of flight information such as airspeed, altitude, and temperature in eVTOL aircraft by optimizing sensor placement and reducing the space and power requirements, enhancing the operational capabilities of these vehicles.
Implementation Method 1
One exemplary type of aircraft sensor is a Pitot probe, which functions as a speedometer, measuring air speed based on airflow across the sensor.
Implementation Method 2
Other sensors measure altitude (e.g., via static pressure), temperature outside of the aircraft, angle of attack, and other conditions.
Implementation Method 3
Other sensors measure altitude (e.g., via static pressure), temperature outside of the aircraft, angle of attack, and other conditions.
Data Source
AI summary
A sensor configured for use with a vertical takeoff and landing capable aircraft (VTOL aircraft) includes a probe portion configured to extend outward of an outer surface of the VTOL aircraft. The probe portion includes a distal end formed by a probe on a first side of the sensor. The sensor has an interior portion configured to extend within the outer surface of the VTOL aircraft, the interior portion including a proximal end having an electrical connector on a second side of the sensor, the second side being opposite the first side.