Collapsible Ducted Fan UAV for Compact Transport
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Solution Overview
Problem
Ducted fan UAVs are limited in their ability to be transported in large numbers due to their bulky size, requiring launch in flight configuration, which restricts their deployment in small-diameter launch tubes and hinders space-efficient multi-UAV carriage on platforms like aircraft or ships.
Innovation Solution
A collapsible ducted fan UAV design that can be stowed and deployed by inflating the duct, with rotor blades, struts, and control vanes folded into a compact configuration and unfolded into flight-ready positions using hinges and a pressurization system, allowing for deployment after launch or at the mission location.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the ducted fan is provided in a flight configuration, then thrust generation efficiency is improved, but the volume and bulkiness increase, limiting transport capability
Solution Approach 1:
The duct is designed to be dynamically changeable between inflated and deflated states. The duct includes an inflatable structure that can be pressurized to expand from a compact deflated state during transport to a fully inflated flight configuration when deployed, allowing the UAV to achieve optimal thrust generation efficiency while minimizing transport volume.
Solution Approach 2:
The physical state of the duct is changed from deflated to inflated by introducing pressurized gas. This parameter change allows the duct to transition between a compact state for transport (reducing volume) and an expanded state for flight (improving thrust generation efficiency).
2Ease of operation
If the ducted fan UAV is launched in flight configuration, then operational readiness is improved, but the ability to launch from small-diameter tubes and platforms is reduced
Solution Approach 1:
The UAV system incorporates a dynamic duct structure that can be deflated to a compact configuration for launch through small-diameter tubes and then inflated to full operational size after launch. This allows the UAV to be launched in a space-efficient state while maintaining full operational capability after deployment.
Solution Approach 2:
The duct is pre-configured in a deflated state before launch to enable passage through small-diameter launch tubes. After launch, the duct is inflated to its operational configuration, ensuring that the preliminary action of deflation enables the subsequent action of full operational deployment.
3Adaptability or versatility
If multiple UAVs are carried on a single platform, then mission versatility is improved, but the space required for each UAV increases
Solution Approach 1:
Each UAV is equipped with a dynamically collapsible duct that can be deflated to minimize volume during transport and storage on the platform. This allows multiple UAVs to be carried on a single platform with reduced space requirements, while each UAV maintains full operational capability when deployed and inflated.
Solution Approach 2:
The deflated duct structure allows the UAV to be compacted to a smaller size, enabling multiple UAVs to be nested or stored more efficiently on a single platform. The compact deflated state of each UAV allows for better space utilization when carrying multiple units.
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 efficient space utilization and flexible deployment of multiple UAVs by collapsing the ducted fan system for transport and launching in a compact state, then rapidly expanding for flight, enhancing operational flexibility and versatility.
Implementation Method 1
a pressurization system providing a pressurant to a chamber within the duct so as to inflate the duct and cause the struts, the rotor blades and the control vanes to move from the stowed configuration to the deployed configuration
Data Source
AI summary
A ducted fan UAV that can be collapsed into a stowed configuration and then deployed for flight by, for example, inflating the duct to a deployed configuration. The UAV includes a plurality of rotor blades, a plurality of struts and a plurality of control vanes each being pivotally mounted to a center body by a hinge so that the rotor blades, the struts and the control vanes can be folded into the stowed configuration to be substantially parallel to the center body and be unfolded into the deployed configuration to be substantially perpendicular to the center body. The UAV also includes a pressurization system providing a pressurant to a chamber within the duct so as to inflate the duct and cause the struts, the rotor blades and the control vanes to move from the stowed configuration to the deployed configuration.