Aircraft Weight Estimation Using Location-Based OEW Correction
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Solution Overview
Problem
The operational empty weight (OEW) of vehicles, such as aircraft, varies with location and altitude due to differences in the Earth's gravitational field, leading to inaccuracies in load capacity calculations, which restricts payload and fuel capacity and subsequently affects revenue and utility.
Innovation Solution
A system that generates an initial weight estimate based on a reference OEW and location-specific data, including latitude and altitude, to determine an additional load capability, allowing for more accurate load calculations and increased payload or fuel storage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a reference OEW predetermined at a second location is used for weight calculations at a first location, then the weight calculation is simple, but the measurement precision deteriorates due to gravitational field variations
Solution Approach 1:
The system changes the parameter of OEW from a fixed reference value to a location-dependent variable. By adjusting the OEW based on latitude and altitude differences between the reference location and current location, the system accounts for gravitational field variations while maintaining a relatively simple calculation approach.
Solution Approach 2:
The system performs preliminary calculations to determine the gravitational field difference between locations before finalizing the weight estimate. By pre-calculating or pre-storing gravitational correction factors for different locations, the system reduces the complexity of real-time weight calculations while improving accuracy.
2Measurement precision
If the OEW is adjusted to account for location-specific gravitational field variations, then the measurement precision improves, but the device complexity increases
Solution Approach 1:
The system modifies the OEW parameter by applying correction factors derived from latitude and altitude differences. This allows accurate weight estimation without requiring complete re-weighing at each location, balancing precision improvement with manageable complexity.
Solution Approach 2:
The system uses a reference OEW measured at one location and creates adjusted versions for different locations through mathematical transformation. This copying approach with modification avoids the need for physical re-weighing while maintaining accuracy, reducing overall system complexity.
3Device complexity
If the reference OEW is used without location adjustment, then the device complexity remains low, but the productivity decreases due to restricted payload and fuel capacity
Solution Approach 1:
By dynamically adjusting the OEW parameter based on location, the system enables more accurate determination of available payload and fuel capacity. This allows operators to maximize vehicle productivity at each location without exceeding weight limits, improving operational efficiency while maintaining reasonable calculation complexity.
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 enhances the utility and revenue of vehicles by enabling them to carry more cargo or travel longer distances without exceeding weight criteria, thereby attracting more passengers and increasing operational efficiency.
Implementation Method 1
The operational empty weight (OEW) of vehicles, such as aircraft, varies with location and altitude due to differences in the Earth's gravitational field
Data Source
AI summary
In a particular implementation, a method includes generating an initial weight estimate associated with an aircraft based on a reference operational empty weight (OEW) and at least one of a latitude or an altitude of the aircraft at a first location. The reference OEW is predetermined at a second location that is distinct from the first location. The method includes determining an additional load capability of the aircraft based on a difference between the initial weight estimate and the reference OEW. The method further includes generating an output that indicates the additional load capability.