Modular UAV with Removable VTOL Rotor Modules
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Solution Overview
Problem
There is a need for an unmanned aerial vehicle (UAV) that can be launched and recovered without a dedicated runway, eliminating the need for specialized ground support equipment like portable catapult launchers and recovery systems, while maintaining the capabilities of a fixed-wing aircraft in terms of endurance, range, payload, speed, and service ceiling.
Innovation Solution
The UAV is designed to be field-configurable for vertical takeoff and landing (VTOL) capability by using removable vertical lift rotor modules and gyrocopter modules, allowing it to be assembled and disassembled into lightweight components for easy transportation and deployment, and can switch between fixed-wing and VTOL configurations using field joints and fastening mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed-wing UAV is launched using a portable catapult launcher and recovered using a portable recovery system, then the UAV can operate without a dedicated runway, but the cost and complexity of operating the UAV increases
Solution Approach 1:
The UAV is equipped with integrated vertical lift rotors that enable it to perform its own takeoff and landing operations without requiring external catapult launchers or recovery systems. The aircraft generates its own vertical thrust through the rotors, making the ground support equipment unnecessary and eliminating the associated complexity and costs.
Solution Approach 2:
The vertical lift rotors serve multiple functions: they provide vertical thrust for takeoff, enable hover capability, and facilitate vertical landing. This multi-functional design replaces the need for separate specialized ground support equipment, reducing overall system complexity while maintaining runway independence.
2Adaptability or versatility
If vertical lift rotor modules are added to enable VTOL capability, then the UAV can operate without a dedicated runway, but the weight of the aircraft increases
Solution Approach 1:
The vertical lift system is divided into separate, removable rotor modules that can be attached to or detached from the aircraft. Each module contains a rotor and motor assembly that can be independently managed. This segmentation allows the aircraft to carry only the necessary vertical lift capacity for its mission requirements, reducing unnecessary weight while maintaining VTOL capability when needed.
Solution Approach 2:
The aircraft configuration is made dynamic through the ability to reconfigure the vertical lift rotor modules. The modules can be attached when VTOL capability is required and removed when fixed-wing operation is sufficient, allowing the aircraft weight to adapt to the operational requirements rather than always carrying the full VTOL system weight.
3Ease of operation
If the UAV is designed as a modular aircraft with removable components, then the UAV can be easily transported and assembled in the field, but the device complexity increases
Solution Approach 1:
The aircraft is divided into major modular components including the fuselage, wings, empennage, and vertical lift rotor modules. Each module is designed with standardized attachment interfaces that simplify field assembly. The segmentation allows components to be transported separately and quickly reconfigured in the field without requiring complex tools or procedures.
Solution Approach 2:
The modular components are designed with universal attachment mechanisms that can accommodate different configurations. The same basic interfaces and fastening systems are used across different modules, reducing the number of specialized parts needed and simplifying the overall assembly process despite the modular design.
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
This configuration enables the UAV to operate without a dedicated runway, providing improved operational flexibility and reducing costs and complexity, while maintaining the performance of a fixed-wing aircraft.
Implementation Method 1
Four fixed, open and horizontal, vertical takeoff and landing (VTOL) thrust rotors are mounted to the airframe in a quadrotor pattern for providing vertical lift to the aircraft
Implementation Method 2
a vertical, forward thrust rotor is mounted to the trailing extremity of the fuselage between the trailing extremity of the fuselage and the empennage for providing forward thrust to the aircraft
Implementation Method 3
a fixed wing airframe having opposed left and right wings extending from left and right sides, respectively, of a fuselage
Data Source
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AI summary
An aircraft includes a fuselage module (104) and at least two vertical lift rotor modules (300) supporting at least four rotor assemblies (302). Each rotor assembly (302) is supported by a rotor boom (308) having at least one boom free end and a boom mounting portion. Each rotor assembly (300) has at least one vertical lift rotor (304) mounted on the boom free end. Each boom mounting portion is removably couplable to the fuselage module (104). The vertical lift rotor modules (304) are configured such that when coupled to the fuselage module (104), a pair of the rotor assemblies (300) are located on each of laterally opposite sides of the fuselage module (104), and the rotor assemblies (300) of each pair are respectively located forward of and aft of a wing center portion (208). A pair of wings (200) are configured to be removably couplable to the wing center portion (208). The aircraft includes a forward thrust module (122) removably couplable to the fuselage body (104).