Aircraft Weight Estimation Using Dynamic Pressure and Angle of Attack
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Solution Overview
Problem
Traditional methods for estimating aircraft weight during flight are inadequate, as they rely on fuel burn measurements and do not account for dynamic changes in weight due to fuel consumption, equipment deployment, and other factors, leading to inaccuracies in flight control and airspeed estimation.
Innovation Solution
A method and system that utilize dynamic pressure, calibrated angle of attack, load factor, and wing surface area to continuously estimate aircraft weight, incorporating a proportional-integral controller and signal filtering to provide a stable weight signal, and an alternative method using historical flight data to correlate horizontal control surface position with dynamic pressure for weight determination.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional fuel burn measurement methods are used to estimate aircraft weight, then the system is simple to operate, but the measurement precision is insufficient due to not accounting for dynamic weight changes
Solution Approach 1:
The system continuously monitors multiple flight parameters (dynamic pressure, angle of attack, load factor) and uses feedback loops to continuously update and refine the weight estimation, accounting for dynamic changes during flight operations
Solution Approach 2:
The system integrates multiple existing flight instrumentation subsystems (pitot-static system, angle of attack indicator, accelerometer) to perform the additional function of weight estimation, leveraging existing sensors for multiple purposes
2Measurement precision
If continuous weight estimation using multiple parameters is implemented, then the measurement precision improves, but the device complexity increases due to multiple sensors and processing requirements
Solution Approach 1:
The system automatically processes multiple sensor inputs and performs continuous weight estimation calculations without requiring manual intervention or complex operator procedures, maintaining ease of operation through automated processing
3Reliability
If traditional weight estimation methods are used, then the device complexity is low, but the reliability is insufficient for accurate flight control and airspeed estimation
Solution Approach 1:
The continuous feedback from multiple sensors provides reliable, up-to-date weight information that accounts for dynamic changes during flight, ensuring accurate flight control and airspeed estimation throughout the flight profile
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 approach allows for accurate and continuous estimation of aircraft weight, improving flight control inputs, airspeed estimation, and serving as a logic check for fuel burn calculations, thereby enhancing flight stability and accuracy.
Implementation Method 1
providing a dynamic pressure signal from a pitot-static subsystem
Implementation Method 2
providing a load factor signal from an accelerometer
Data Source
AI summary
In an embodiment, a method for aircraft weight estimation is provided that includes determining a weight signal based on a dynamic pressure signal, a calibrated angle of attack signal, a lift coefficient signal, a load factor signal, and a wing surface area. In another embodiment, a method to estimate aircraft weight is provided that includes determining a weight based on historical flight data relating horizontal control surface position to dynamic pressure. In another embodiment, a system for continuously estimating aircraft weight during flight is provided that includes a pitot-static subsystem, an angle of attack indicator, an accelerometer, a controller configured to provide a weight signal, and a signal filter for filtering the weight signal to determine a stable aircraft weight.