Ground-Based Aircraft Flight Load Simulation System
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Solution Overview
Problem
Existing methods for measuring aircraft in-flight performance face challenges such as difficulty in measurement during flight, prolonged testing times, and operational difficulties, necessitating a method to assess aircraft performance under simulated flight-loads while on the ground.
Innovation Solution
A system comprising cradle devices and air pressure mechanisms to lift and apply simulated flight-loads to an aircraft, combined with measuring devices to track positional changes, allowing for the simulation of flight pressure distribution loads without actual flight, using data from other aircraft or computer models to determine the loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If in-flight testing methods are used to measure aircraft performance, then measurement data can be obtained under actual flight conditions, but the testing time is prolonged and operational difficulties arise
Solution Approach 1:
The patent applies preliminary action by pre-loading the aircraft structure with simulated flight loads on the ground before actual flight testing. Cradle devices are positioned against the wings and air pressure mechanisms are pre-configured to apply distributed loads that replicate in-flight pressure distributions, allowing structural measurements to be taken without requiring actual flight conditions.
Solution Approach 2:
The patent uses copying by creating a ground-based simulation that replicates in-flight pressure distribution patterns. Air pressure mechanisms generate copied flight load patterns on the aircraft structure, and measurement systems capture structural responses that mirror what would occur during actual flight, eliminating the need for prolonged in-flight testing.
2Measurement precision
If in-flight testing is conducted to measure aircraft deflections, then real flight condition data is obtained, but difficulties are experienced during flight operations
Solution Approach 1:
The patent extracts the measurement function from the flight operation context and relocates it to ground-based testing. By removing the aircraft from flight conditions and placing it on cradle devices with simulated loads, the measurement process is separated from complex flight operations, making the testing process easier to execute while maintaining measurement accuracy for wing deflections and structural responses.
Solution Approach 2:
The patent introduces intermediary elements including cradle devices that support the aircraft structure and air pressure mechanisms that mediate the application of simulated flight loads. These intermediaries create a controlled ground-based environment that replicates flight pressure distributions, allowing structural measurements to be taken without the complexity of actual flight operations.
3Loss of time
If simulated flight-loads are applied on the ground using cradle devices and air pressure mechanisms, then testing time is reduced and operational challenges are eliminated, but the device complexity increases
Solution Approach 1:
The patent applies universality by designing measurement systems that can evaluate multiple aircraft structural parameters simultaneously using the same ground-based apparatus. The cradle devices and air pressure mechanisms serve multiple functions including structural support, load application, and measurement coordination, reducing overall system complexity despite the advanced capabilities provided.
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 precise simulation of flight conditions on the ground, reducing testing time and operational challenges, allowing for accurate measurement and potential design adjustments to minimize drag, thereby reducing fuel consumption, wear, and travel time.
Implementation Method 1
an air pressure distribution is applied against the raised aircraft, while the aircraft is not in flight, to substantially simulate air pressure flight distribution loads the aircraft would experience during flight
Data Source
AI summary
A method is provided to measure an aircraft under simulated flight-loads while the aircraft is not in flight. Simulated flight-loads may be applied to the aircraft, while the aircraft is not in flight, in order to substantially simulate flight pressure distribution loads the aircraft would experience during flight. A position of one or more portions of the aircraft may be measured, while the aircraft is under the simulated flight-loads, to determine an effect of the simulated flight-loads on the aircraft.