Reconfigurable Propulsion Mechanisms for UAV Flight Duration
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Solution Overview
Problem
Multi-propeller aerial vehicles face a trade-off between weight and flight duration, as increased weight to support components reduces flight time, and existing configurations lack efficient power management for maneuverability and efficiency.
Innovation Solution
The implementation of reconfigurable pivot assemblies that adjust propulsion mechanisms between a maneuverability configuration for vertical takeoff and landing, and an efficiency configuration for horizontal flight, using ducted propellers to reduce power consumption and enhance lift, allowing for extended flight duration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If the aerial vehicle uses a fixed configuration for vertical takeoff and landing, then maneuverability is maintained, but power consumption increases and flight duration decreases
Solution Approach 1:
The patent applies the Dynamics principle by making the propulsion mechanisms movable rather than fixed. The pivot assemblies enable the propulsion mechanisms to dynamically change their orientation between vertical (for takeoff/landing) and horizontal (for cruise flight) configurations. This dynamic reconfiguration allows the vehicle to optimize power consumption by using horizontal propulsion during efficient cruise flight while maintaining vertical propulsion capability for maneuvering, thereby extending flight duration without sacrificing maneuverability
2Reliability
If the aerial vehicle supports more components for stability and control, then reliability improves, but weight increases and flight duration decreases
Solution Approach 1:
The patent applies the Universality principle by designing the pivot assemblies and propulsion mechanisms to serve multiple functions. The same propulsion mechanisms that provide thrust also contribute to stability and control through their reconfigurable positioning. During cruise flight, the horizontal configuration provides stable forward motion, while during maneuvering, the vertical configuration enables precise control. This multi-functionality eliminates the need for separate dedicated stability components, reducing overall weight while maintaining reliability and extending flight duration
3Use of energy by moving object
If the aerial vehicle uses ducted propellers in horizontal flight configuration, then efficiency increases and power consumption decreases, but maneuverability is reduced
Solution Approach 1:
The patent resolves this contradiction through dynamic reconfiguration. The propulsion mechanisms are designed to operate in ducted configuration during horizontal cruise flight to maximize efficiency and minimize power consumption. When maneuvering is required, the pivot assemblies rotate the propulsion mechanisms to vertical configuration, restoring full maneuverability. This dynamic switching between configurations allows the vehicle to achieve both low power consumption during cruise and high maneuverability during maneuvering phases
4Adaptability or versatility
If the aerial vehicle maintains a fixed propulsion configuration, then device complexity is reduced, but adaptability to different flight phases decreases
Solution Approach 1:
The patent applies the Segmentation principle by dividing the propulsion system into modular units, each with its own pivot assembly. This segmentation allows independent control and reconfiguration of each propulsion mechanism, providing high adaptability for different flight phases. The modular design actually reduces overall system complexity by enabling standardized, interchangeable components and simplified control architecture compared to a monolithic fixed configuration system
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 enables aerial vehicles to efficiently manage power consumption and extend flight duration by optimizing propulsion mechanisms' orientation and configuration, balancing maneuverability and efficiency.
Implementation Method 1
the airflow over the airfoil shaped ducts generates lift to maintain the aerial vehicle's altitude
Implementation Method 2
the propulsion mechanisms are oriented to generate a vertical thrust or lifting force
Data Source
AI summary
Described are apparatus and processes for reconfiguring aerial vehicles, such as unmanned aerial vehicles (UAV) during navigation of the aerial vehicle between a maneuverability configuration and an efficiency configuration. When an aerial vehicle needs to be able to quickly maneuver in any direction (vertical, horizontal, pitch, roll, yaw) it is operating in a maneuverability configuration. When configured to operate in the maneuverability configuration, the primary function of the aerial vehicle configuration is to increase maneuverability of the aerial vehicle. When the aerial vehicle is navigating in a direction that is substantially horizontal, for example when navigating between locations, it may be configured to operate in an efficiency configuration. When configured to operate in the efficiency configuration, the primary function of the aerial vehicle configuration is to increase efficiency of the aerial vehicle and reduce power consumption.