In-flight Reconfigurable Hybrid UAV Wing Pivot Mechanism
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Solution Overview
Problem
Current unmanned aerial vehicles (UAVs) lack the ability to efficiently transition between vertical and horizontal flight configurations, limiting their operational flexibility and efficiency in terms of energy conservation and maneuverability.
Innovation Solution
The UAV features a reconfigurable wing structure with rotatably coupled wing segments and adjustable propulsion units, allowing it to pivot the wing segments around the center of mass, enabling seamless transitions between vertical and horizontal flight modes, and incorporating a tail that can fold to facilitate landing in both configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed wing aircraft uses a fixed orientation propulsion system, then the structure is simple, but the aircraft cannot transition between vertical and horizontal flight modes
Solution Approach 1:
The propulsion system is designed with rotatable propulsion units that can change orientation from vertical to horizontal. The propulsion units are mounted on a rotation mechanism that allows them to pivot between approximately perpendicular orientations, enabling the aircraft to switch between vertical takeoff/landing mode and horizontal flight mode.
Solution Approach 2:
The propulsion system serves multiple functions by being capable of providing thrust in both vertical and horizontal directions. The same propulsion units can operate in different orientations to support different flight modes, eliminating the need for separate propulsion systems for different flight configurations.
2Adaptability or versatility
If a helicopter uses a fixed orientation rotor propulsion system, then the structure is simple, but the aircraft cannot transition to horizontal flight mode efficiently
Solution Approach 1:
The rotorcraft-style propulsion units are mounted to rotate relative to the fuselage, allowing transition from a vertical thrust orientation to a horizontal thrust orientation. This rotational capability enables the vehicle to switch between vertical flight and horizontal flight modes using the same propulsion units.
Solution Approach 2:
The propulsion system is divided into separate rotatable propulsion units that can independently change orientation. Each propulsion unit can be rotated to the appropriate angle for the desired flight mode, allowing flexible transition between vertical and horizontal flight configurations.
3Adaptability or versatility
If the UAV uses a reconfigurable wing structure, then the aircraft can transition between flight modes, but the structural complexity increases
Solution Approach 1:
The wing structure is divided into multiple segments that can be independently positioned. The wing includes a first wing segment and a second wing segment that can be rotated relative to each other about a pivot point, allowing the wing to be configured for different flight modes such as vertical takeoff, horizontal flight, and intermediate transitions.
Solution Approach 2:
The wing structure incorporates rotatable segments that can dynamically change position during flight. The segments are connected by pivots that allow rotation, enabling the wing to adapt its configuration based on the desired flight mode while maintaining structural integrity during transition.
4Ease of operation
If the UAV operates in vertical flight configuration, then the aircraft can perform maneuvering, but the energy consumption increases
Solution Approach 1:
The aircraft can dynamically switch between vertical and horizontal flight configurations based on operational needs. When horizontal flight is required for long-distance travel, the aircraft transitions to this mode to reduce energy consumption. When maneuverability is needed, the aircraft can transition to vertical flight configuration.
Solution Approach 2:
The aircraft changes its operational parameters by transitioning between different flight modes. The propulsion unit orientation, wing segment positions, and flight characteristics are adjusted as parameters that can be changed between vertical and horizontal configurations to optimize energy efficiency for the given mission requirements.
Data Source
AI summary
This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.