Laser Air-Motion Sensor Aircraft Instrument Calibration
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Solution Overview
Problem
Current methods for calibrating aircraft pressure and temperature instruments are unreliable and lack precision, especially for continuous and high-precision airspeed measurements, and do not provide independent temperature measurements, leading to potential flight hazards and measurement uncertainties.
Innovation Solution
A method and apparatus using a laser air-motion sensor (LAMS) to receive airspeed measurements, calculate corrected ambient pressure, and subsequently determine calculated temperature, incorporating total pressure measurements to improve the accuracy of airspeed and pressure readings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a trailing-cone system is used to calibrate pressure measurements, then measurement precision is improved, but device complexity and installation difficulty increase
Solution Approach 1:
The patent extracts the pressure sensing function from the complex trailing-cone system and implements it using a simpler probe assembly that can be integrated into the aircraft structure. The probe contains pressure sensors that directly measure ambient, total, and differential pressures without requiring the elaborate trailing-cone configuration.
Solution Approach 2:
The patent replaces the mechanical trailing-cone system with an electronic sensing system using pressure sensors and signal processing. The measurement function is transferred from a mechanical aerodynamic structure to electronic sensors that can be processed computationally, reducing mechanical complexity.
2Ease of manufacture
If traditional pressure sensing systems are used, then installation is simplified, but measurement reliability deteriorates due to airflow distortions
Solution Approach 1:
The patent positions pressure sensors in specific locations on the aircraft where airflow distortion is minimized. The probe assembly is designed with sensors placed at optimal positions relative to the aircraft structure, allowing accurate measurements while maintaining ease of installation compared to trailing-cone systems.
Solution Approach 2:
The patent introduces a probe assembly as an intermediary structure that interfaces between the aircraft and the pressure sensing system. This probe serves as a mediator that protects the sensors from direct exposure to distorted airflow while maintaining measurement accuracy, and it can be integrated into the aircraft structure relatively easily.
3Quantity of substance
If multiple interlinked measurements are taken simultaneously, then comprehensive data is obtained, but measurement uncertainty increases due to interconnected errors
Solution Approach 1:
The patent segments the measurement system into independent pressure sensing channels (ambient pressure, total pressure, differential pressure) that can be measured simultaneously without interfering with each other. Each sensor measures its parameter independently, avoiding the error propagation that occurs when measurements are interlinked and dependent on each other.
Solution Approach 2:
The patent uses the independently measured pressure values to provide feedback for calculating airspeed and temperature. The system cross-validates measurements by using multiple independent pressure readings to derive the same physical quantities, allowing error detection and correction while maintaining comprehensive measurement capability.
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 solution provides reliable, continuous, and precise airspeed and pressure measurements, reducing uncertainty and enabling accurate temperature calculations, even in cloudy conditions, thus enhancing flight safety and measurement reliability.
Implementation Method 1
receiving an airspeed measurement from a laser sensor
Data Source
AI summary
A method for correcting an ambient pressure measurement, a method for calculating a temperature, and an apparatus for affecting the same for an aircraft measuring system are provided. The methods include the steps of receiving an airspeed measurement from a laser sensor, receiving a total pressure measurement, and calculating an ambient pressure correction. A corrected ambient pressure or a calculated temperature may be calculated. The apparatus includes a laser sensor configured to provide an airspeed measurement, an aircraft instrument configured to provide a total pressure measurement, and a processing system.