Transformable Wing VTOL UAV for Confined Space Deployment
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Solution Overview
Problem
Current systems face challenges in deploying and operating long-endurance, high-aspect ratio Vertical Takeoff and Landing (VTOL) Unmanned Aerial Vehicles (UAVs) from confined spaces due to efficiency penalties, complexity in transition phases, and exposure risks for ground personnel.
Innovation Solution
A system and method for a Tier 2-sized Robust Efficient Vertical Launch and Recovery (REVLAR) UAV featuring a fuselage with counter-rotating engines, a transformable wing configuration, and retractable pogo supports, allowing vertical takeoff and landing with minimal infrastructure requirements, enabling organic deployment and operation from confined areas.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a hover phase is incorporated for VTOL operation, then vertical takeoff and landing capability is achieved, but flight efficiency deteriorates
Solution Approach 1:
The wing configuration is made dynamic by allowing it to transform between vertical and horizontal positions. During takeoff, the wing is in vertical configuration to enable VTOL; during cruise, it transitions to horizontal configuration to reduce drag and improve efficiency, thus resolving the contradiction between VTOL capability and flight efficiency
2Adaptability or versatility
If transition from vertical to horizontal flight is implemented, then VTOL operation is enabled, but system complexity increases
Solution Approach 1:
The transition mechanism is merged with the wing structure itself rather than being a separate complex system. The pivotal connectors are integrated into the wing-fuselage junction, allowing the wing to pivot and transform configuration as part of its structural design, thereby reducing overall system complexity while enabling flight mode transition
3Ease of operation
If ground personnel are exposed to high-speed rotors for deployment, then organic deployment is possible, but safety deteriorates
Solution Approach 1:
The patent replaces traditional high-speed rotating rotor systems with a propeller-based propulsion system. The propellers operate at lower speeds and can be positioned to direct thrust away from the ground, significantly reducing the harmful effects on ground personnel while still enabling organic deployment from confined spaces
4Duration of action of moving object
If long endurance is achieved for flights exceeding 8 hours, then mission capability is improved, but aircraft size and weight increase
Solution Approach 1:
The patent employs high-aspect ratio wings with optimized aerodynamic parameters to reduce induced drag and improve lift efficiency. This allows the aircraft to achieve long endurance (exceeding 8 hours) with a relatively small size and weight, as the efficient aerodynamics reduce the power requirements and fuel consumption over extended flight durations
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, organic deployment and operation of long-endurance VTOL UAVs from confined spaces, reducing the need for complex ground support and minimizing exposure risks, with improved propulsion efficiency and stable transition between hover and wing-borne flight.
Implementation Method 1
two counter-rotating engines that are arranged such that one engine is mounted on the wing at each side of the fuselage
Implementation Method 2
the wing is configured to transform between a vertical configuration and a horizontal configuration using at least one pivotal connector positioned on each side of the fuselage
Implementation Method 3
The retractable pogo support is configured to deploy from the fuselage to form a tripod launch and recovery configuration with the empennage
Implementation Method 4
during a first phase of takeoff, the wing is in the vertical configuration thereby causing the nose end of the fuselage to lift off the ground while the tail end remains on the ground
Implementation Method 5
during a third phase of takeoff, the wing is in the horizontal configuration and the aircraft is capable of wingborne flight
Data Source
AI summary
A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.