Modular VTOL Aircraft with Variable Pitch Propellers
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Solution Overview
Problem
Current vertical takeoff and landing (VTOL) vehicles face inefficiencies due to redundant propulsion systems, limited payload flexibility, lengthy recharging times, and large ground footprints, which affect controllability, efficiency, and storage capabilities.
Innovation Solution
An autonomous, modular, and portable VTOL aircraft with distributed electric propulsion, variable pitch propellers, and collective pitch control, along with removable mission pods for flexible payload handling and energy storage, enabling efficient hover and forward flight, reduced downtime, and compact storage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If separate propulsors are used for vertical and forward motion with blades optimized for unique airspeed and thrust requirements, then vehicle control is simplified, but parasitic weight increases due to redundant systems
Solution Approach 1:
The patent implements a single propulsor system that performs both vertical takeoff/landing and forward flight functions. The propeller blades are designed with variable pitch capability, allowing them to adapt to different flight regimes (hover, transition, forward flight) without requiring separate optimized propulsors for each mode, thereby eliminating redundant weight while maintaining control simplicity
2Ease of operation
If variable pitch propellers are used, then controllability is improved with faster response to speed changes, but device complexity increases
Solution Approach 1:
The patent employs variable pitch propellers where the blade pitch angle can be dynamically adjusted during flight. This dynamic adjustment allows the propeller to optimize performance across different flight phases (vertical hover, transition, forward flight) and provides faster response to control inputs compared to fixed pitch systems, while the complexity is managed through integrated control systems
3Device complexity
If fixed pitch propulsors are used for both vertical and forward flight, then device complexity is reduced, but propulsive efficiency decreases significantly
Solution Approach 1:
The patent uses variable pitch propellers that can dynamically adjust blade angle to optimize propulsive efficiency across different flight regimes. During vertical flight, the pitch is set for maximum hover efficiency; during forward flight, the pitch transitions to optimize high-speed propulsion, thereby maintaining high efficiency throughout all flight phases unlike fixed pitch systems
4Ease of operation
If payload is carried within an open bay in the fuselage, then loading and unloading can be performed, but the vehicle must sit out of use during these operations and sensitivity to center of gravity increases
Solution Approach 1:
The patent divides the payload system into separable modules: the airframe and the payload pod are distinct, detachable components. The payload pod can be quickly attached or detached from the airframe at the pylon interface, allowing payload changes without requiring the entire vehicle to be stationary for extended periods, thereby reducing downtime while maintaining payload handling capability
Solution Approach 2:
The patent incorporates a payload pod positioning system with motors that can adjust the pod's location along the pylon before flight. This preliminary positioning capability allows the center of gravity to be pre-adjusted to optimal values for different payload configurations, reducing sensitivity to weight variations and eliminating the need for time-consuming manual balancing during loading operations
5Quantity of substance
If conventional aircraft design is used, then payload can be carried, but the footprint on the ground is large making storage and transport challenging and expensive
Solution Approach 1:
The patent separates the payload carrying function into a detachable pod that attaches to the airframe at a pylon location. This segmentation allows the payload pod to be optimized for compact storage when not in use, while the airframe maintains minimal footprint. The pod can be vertically or horizontally oriented and designed to fit in compact spaces, eliminating the need for large conventional fuselages required for internal payload bays
Solution Approach 2:
The patent utilizes vertical space for payload storage by positioning the payload pod beneath the airframe at the pylon, extending downward rather than requiring lateral expansion. This vertical dimensionality allows compact ground footprint while maintaining payload capacity, as the pod hangs below the aircraft rather than requiring the aircraft to be wider or longer
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
The solution enhances controllability and efficiency by eliminating redundant systems, minimizing downtime, and allowing for flexible payload handling and compact storage, while reducing drag and operational complexity.
Implementation Method 1
distributed electric propulsion
Implementation Method 2
Variable pitch actuation may allow the propeller system to change the thrust and torque of a propeller with less delay
Implementation Method 3
Large-diameter rotors may have high moments of inertia and thus may be slower when changing speed in response to motor torque
Data Source
AI summary
According to at least one exemplary embodiment, a method, system and apparatus for an aircraft may be shown and described. An exemplary embodiment may be an autonomous aircraft which can vertically takeoff and land (VTOL). The VTOL aircraft may have a modular pod which carries a removable payload. The entire VTOL aircraft may be portable. An exemplary embodiment may fit into a standard sized freight container. A propulsion system may be based on distributed electric propulsion. An exemplary embodiment may implement variable pitch propellers and collective pitch variation.