Convertible Monocopter Aircraft with Pivoting Wing and Propulsion
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Solution Overview
Problem
Existing unmanned flying devices, such as drones, face limitations in flight time due to inefficient power usage and are restricted by conventional flight techniques, which hinder their application in various commercial and non-toy uses.
Innovation Solution
The development of an unmanned flying device with a main body, pivotally coupled wing, propulsion unit, and a control system that allows for multiple flight modes, including autorotation, hovering, and fixed-wing flight, enabled by a latching mechanism for aggregation and disaggregation of flying devices, optimizing thrust and energy usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If conventional flight techniques are used in existing drones, then the device can operate in standard flight modes, but flight time is limited due to inefficient power usage
Solution Approach 1:
The patent implements dynamic flight mode transitions allowing the unmanned aircraft to switch between autorotation, hovering, and fixed-wing flight modes. The wing and propulsion unit can pivot between different configurations, enabling the system to optimize power usage based on operational requirements. This dynamic adaptability resolves the contradiction by allowing extended flight time through efficient fixed-wing cruise while maintaining the ability to perform vertical takeoff and hovering when needed.
2Adaptability or versatility
If existing drone designs are used, then the structure is simple, but the device is restricted to conventional flight techniques and cannot achieve versatile operation
Solution Approach 1:
The patent designs the unmanned aircraft with multi-functional capabilities, where the same wing and propulsion unit structure serves multiple purposes across different flight modes. The pivotal coupling mechanism allows these components to perform functions in autorotation mode, hovering mode, and fixed-wing flight mode, eliminating the need for separate systems for each mode and managing complexity through universal component design.
Solution Approach 2:
The aircraft employs dynamic reconfiguration of its wing and propulsion unit through pivotal couplings, allowing the structure to adapt its configuration based on the desired flight mode. This dynamic capability enables versatile operation without requiring multiple static structures, as the same components transform to meet different operational requirements.
3Adaptability or versatility
If multiple flight modes are implemented, then operational versatility is improved, but control system complexity increases
Solution Approach 1:
The control system incorporates feedback mechanisms to monitor the aircraft's state and automatically adjust control inputs for smooth transitions between flight modes. This feedback control manages the complexity by providing automated stabilization and mode transition management, reducing the burden on the operator while enabling versatile multi-mode operation.
Solution Approach 2:
The control system is designed with universal control logic that manages multiple flight modes through a unified architecture. Rather than requiring separate control systems for each mode, the universal controller handles autorotation, hovering, and fixed-wing flight through integrated control algorithms, managing complexity through consolidation.
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 solution enhances flight efficiency, extends flight time, and allows for versatile operation in various modes, including vertical takeoff and landing, rotational, and fixed-wing flight, improving the reliability and applicability of unmanned flying systems.
Implementation Method 1
thrust generated by the propulsion unit can rotate the unmanned flying device in a manner that causes the wing to generate lift
Implementation Method 2
the wing in a first configuration and the propulsion unit in a first configuration, thrust generated by the propulsion unit can rotate the unmanned flying device in a manner that causes the wing to generate lift
Data Source
AI summary
Systems, methods and devices for rotary and fixed wing convertible aircraft with monocopters. A monocopter flying device may include a main body and a wing pivotally coupled to the main body. A wing actuator operably coupled to the wing may be configured to pivot the wing about its longitudinal axis. The flying device may include a propulsion unit pivotally coupled to the main body that includes a motor and a propeller having a hub and radially extending blades. A propulsion unit actuator may be configured to pivot the propulsion unit about an axis non-parallel to the axis of rotation of the propellor. The flying device may include a control system including one or more processors configured to control operation of the devices. The flying devices may connect together to form a flying system having multiple flight modes with varying orientations. The flying system may disaggregate the flying devices in flight.