VTOL UAV Payload Bay and Inclined Tail Rotor for Lower Drag
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Solution Overview
Problem
Existing hybrid VTOL UAVs face inefficiencies in payload integration, modularity, and increased aerodynamic drag, limiting operational flexibility and flight performance.
Innovation Solution
A vertical take-off and landing (VTOL) aerial vehicle design featuring a hollow fuselage with a vertical cavity, perpendicularly configured fixed wing, and detachable payload system, enabling direct electrical connection between a power source and avionics, and an inclined tail rotor for reduced drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If hybrid fixed-wing VTOL UAV is designed with both rotor-blade arms and fixed wings, then vertical take-off and landing capability is achieved, but aerodynamic drag increases during horizontal flight
Solution Approach 1:
The vehicle is divided into distinct functional modules: a fuselage module containing the power source and a fixed-wing module containing the avionics systems. This segmentation allows the rotor-blade arms to be positioned only when needed for vertical operations, reducing drag during horizontal flight while maintaining VTOL capability.
Solution Approach 2:
The rotor-blade arms are designed to be dynamically positioned - deployed during vertical take-off and landing operations, and retracted or positioned to minimize drag during horizontal flight. This dynamic configuration resolves the contradiction between needing rotor capability and minimizing aerodynamic drag.
2Strength
If payload is integrated into the fuselage structure, then structural strength is improved, but payload handling flexibility and modularity decrease
Solution Approach 1:
The payload system is segmented into a detachable payload module that can be independently attached and detached from the fuselage. This allows the main fuselage structure to maintain its strength while enabling flexible payload handling and mission-specific configurations.
Solution Approach 2:
The payload attachment system uses dynamic coupling mechanisms that allow the payload to be securely fixed during flight operations and easily detached when needed. This dynamic attachment maintains structural integrity during operation while providing flexibility for payload changes.
3Reliability
If electrical connection between power source and avionics is achieved through existing hybrid VTOL design, then system integration is complete, but payload handling efficiency decreases due to complex routing
Solution Approach 1:
The electrical connection system is segmented into modular connectors located at the interface between the fuselage module and fixed-wing module. This segmentation allows electrical connections to be made through the modular interface, simplifying payload integration while maintaining reliable power and data transmission.
Data Source
AI summary
A vertical take-off and landing vehicle (100) includes a hollow fuselage (102) accommodating a power source (112-1,112-2); a fixed wing (106) is perpendicularly configured on the hollow fuselage (102) which accommodates avionics; a payload (110) detachably fixed to a mounting holder (108) of the fixed wing (106) through a vertical cavity (104) of the hollow fuselage (102). The fixed-wing (106) configured on the hollow fuselage (102) enables electrical communication from the power source (112-1,112-2) to the avionics for lifting and vertical landing of the payload (110) by the vehicle (100). An unmanned aerial vehicle (UAV) (200) includes a fuselage (202) having a tail rotor (204) inclinedly positioned where a rotational axis of the tail rotor (204) is positioned at a first predefined angle (X) relative to a horizontal axis of the fuselage (202) for providing axial thrust to facilitate horizontal movement of the UAV (200) and aerodynamics with reduced drag.