Slung Load Identification via Aircraft Flight Dynamics
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Solution Overview
Problem
Current systems for managing slung loads in VTOL aircraft rely on additional sensors and camera optical aids, leading to higher costs and multiple points of failure, and lack an efficient method to determine parameters associated with the load using aircraft flight system dynamics.
Innovation Solution
A method and system that utilize flight dynamics data to identify slung load parameters by determining estimated pendulum frequencies and control input commands, incorporating sensors to receive data on load rigid body modes, sling stretching, and load aerodynamics, and using an online system identification model to choose the appropriate configuration for determining longitudinal and lateral pendulum frequencies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If additional sling load sensors and camera optical aids are used to manage slung loads, then measurement precision of slung load parameters is improved, but device complexity and cost increase
Solution Approach 1:
The flight dynamics sensor system is made multi-functional by enabling it to detect both aircraft flight parameters and slung load parameters. The same sensors that monitor aircraft attitude, acceleration, and orientation are also used to infer slung load status, mass, and ground contact, eliminating the need for dedicated slung load sensors.
Solution Approach 2:
The patent merges the slung load detection function with the existing flight dynamics measurement system. By combining the analysis of aircraft flight data with slung load parameter extraction, the system achieves dual functionality without adding separate sensor hardware for load detection.
2Ease of operation
If traditional sensor-based systems are used for slung load management, then ease of operation is maintained, but loss of information regarding slung load parameters occurs
Solution Approach 1:
The system implements feedback by continuously analyzing flight dynamics data to infer slung load parameters such as mass, ground contact status, and attachment state. This feedback loop provides real-time information about the slung load without requiring separate sensors, maintaining ease of operation while preventing information loss.
Solution Approach 2:
The flight dynamics system is made universal to extract comprehensive slung load information from existing flight measurements, ensuring no loss of load parameters while maintaining simple operation through the existing control interface.
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 safe and controlled detachment of cargo by determining whether a slung load is attached, its mass, and whether it has contacted the ground, reducing costs and failure points by leveraging aircraft flight dynamics data.
Implementation Method 1
determining, with the processor, signals indicative of an estimated pendulum frequency
Data Source
AI summary
A system and method for identifying a slung load for an aircraft with one or more sensors includes receiving, with a processor via one or more sensors, sensor information related to flight dynamics data for the aircraft; determining, with the processor, control input commands for the aircraft in response to the receiving of the flight dynamics data; determining, with the processor, signals indicative of an estimated pendulum frequency; and determining, with the processor, parameters associated with the slung load in response to the determining of the estimated pendulum frequencies.