Aircraft Energy State Modeling for In-Flight Performance Capability
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Solution Overview
Problem
Conventional methods for determining aircraft performance capability are limited by reliance on accurate weight and condition information, and fail to account for variations in performance due to factors like ice build-up and wind shear.
Innovation Solution
An avionics system that includes a storage device and data processors configured to monitor actual aircraft performance by determining measured flight characteristics, executing flight maneuvers, generating predicted energy changes, and adjusting an energy state model based on measured values and predicted changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If complex equations are used to determine forces acting on aircraft during flight, then prediction accuracy of aircraft performance is improved, but computational capacity requirements increase significantly
Solution Approach 1:
The patent replaces complex, computationally intensive equations with simplified energy state models that provide adequate accuracy for performance prediction without requiring excessive computational resources onboard the aircraft
Solution Approach 2:
The patent transitions from using detailed force equations to using energy state parameters (potential energy, kinetic energy, and their rates of change) to predict aircraft performance, simplifying the computational requirements while maintaining useful accuracy
2Device complexity
If conventional energy methods are used to determine aircraft performance, then computational requirements are reduced, but accuracy deteriorates due to reliance on potentially incorrect weight and condition information
Solution Approach 1:
The patent implements feedback by continuously monitoring actual aircraft performance (acceleration, climb rate, airspeed) and using these measurements to detect and correct errors in the energy state model, thereby maintaining accuracy despite uncertainties in weight and condition data
Solution Approach 2:
The system uses the aircraft's own operational data (measured acceleration, airspeed, altitude) to self-correct performance predictions, eliminating the need for externally provided accurate weight and condition information
3Ease of operation
If maximum PS value is used to determine aircraft capabilities, then determination of maximum characteristics is simplified, but adaptability to actual varying conditions deteriorates
Solution Approach 1:
The patent transitions from static maximum PS value determination to dynamic energy state modeling that continuously adapts to actual flight conditions by measuring and responding to real-time changes in acceleration, airspeed, and altitude
Solution Approach 2:
The system preliminarily establishes energy state models based on available information, then continuously refines these models during flight operations to adapt to actual conditions before making performance determinations
Data Source
AI summary
Systems and aircraft are provided. An avionics system includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: determine a first measured value of a flight characteristic of the aircraft at a first position of the aircraft; execute at least one flight maneuver between the first position and a second position of the aircraft; generate a predicted energy change between the first position and the second position based on the at least one flight maneuver and an energy state model; determine a second measured value of the flight characteristic of the aircraft at the second position; and generate an adjustment to the energy state model based on the first measured value, the second measured value, and the predicted energy change.