Toroidal Ducted UAV Control Surfaces for Pocket VTOL Flight
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Solution Overview
Problem
Existing unmanned aerial vehicles (UAVs) are bulky and heavy due to components like fuel tanks and exposed deflection assemblies, making them difficult to store and handle, and they lack efficient control systems for vertical take-off and landing.
Innovation Solution
A compact, lightweight UAV with a toroidal body and a duct system that uses a fan for thrust generation, along with independently controllable flight control surfaces and actuators, allowing for vertical take-off and landing, and enabling remote operation and autonomous flight with AI and machine learning for various applications.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If fuel tanks and exposed deflection assemblies are used in UAVs, then thrust generation and flight control are achieved, but the overall mass and size of the UAV increase
Solution Approach 1:
The invention extracts and eliminates the fuel tank component by using an electric motor and battery system instead, thereby removing unnecessary mass while maintaining the thrust generation function through electrically-powered fans
Solution Approach 2:
The flight control surfaces are integrated directly into the duct structure, merging the control surface function with the existing structural component, which reduces overall device complexity and eliminates the need for separate exposed deflection assemblies
2Speed
If a single duct with multiple vanes and spoilers is used for flight control, then flight path control is achieved, but air flow through the duct is reduced and lift capabilities are diminished
Solution Approach 1:
The flight control surfaces are designed to be movable and adjustable during flight, allowing dynamic optimization of air flow paths while maintaining effective flight control, rather than being fixed structural elements that continuously obstruct the duct
Solution Approach 2:
The control surfaces are positioned strategically within the duct to affect only specific portions of the air flow needed for control, rather than obstructing the entire air flow path, thereby maintaining high lift capabilities while achieving effective flight path control
3Ease of operation
If dual counter-rotating blades with collective and cyclic pitch control are used, then flight path control is achieved, but the device complexity and mass increase
Solution Approach 1:
The complex mechanical pitch control systems are replaced with simpler electrically-controlled flight control surfaces that achieve the same flight path control functionality through electronic actuation rather than mechanical linkages
Solution Approach 2:
The flight control surfaces serve multiple functions simultaneously, including pitch, roll, and yaw control, as well as potentially serving as structural components of the duct, thereby reducing the need for separate specialized control mechanisms
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
The UAV is small enough to be stored in a pocket, offers efficient vertical take-off and landing, and can perform complex flight maneuvers and tasks such as surveillance and inspection with real-time image capture and data analysis, enhancing its usability in security and maintenance applications.
Implementation Method 1
at least one fan for directing a flow of air into a first end of the duct and out a second end that is opposite the first end. The directed air flow creates a reactionary thrust-force for substantially vertical take-off and landing of the UAV
Implementation Method 2
at least two flight control surfaces that can independently, or together, change the direction, pressure and rate of the directed air as it flows through the duct
Data Source
AI summary
A lightweight, pocket-sized unmanned aerial vehicle (UAV) that can be held in an outstretched hand by a user for take-off and landing of the UAV. The UAV comprises a semi-toroidal or a substantially toroidal hollow body that defines a duct. The UAV further comprises a motor for rotating a fan that directs air into and out of the duct enabling UAV to take flight. The UAV comprises a flight-control system that comprises at least two flight control surfaces that can alter the directed air as it flows through the duct for controlling the roll and pitch and optionally the yaw of the UAV during flight. The flight control system may be controlled by a microprocessor controller. The UAV further comprises a payload, with at least a wireless transmitter and receiver unit.