Vectoring Propulsion and Modular Wings for UAV Pitch Control
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Solution Overview
Problem
Current UAV designs are limited by their power-to-weight ratios, which restrict their carrying capacity and range, and are not adaptable to varying flight conditions due to fixed wing and tail configurations, leading to inefficiencies in energy consumption and stability issues during VTOL and horizontal flight.
Innovation Solution
The design features vectoring motors and propellers that transition from vertical to horizontal flight, modular wings and tail fins for optimal configuration based on load and distance, and hybrid energy sources, along with advanced navigation and safety systems like Automated Weather Observing System (AWOS) and Traffic Collision Avoidance System (TCAS), enabling enhanced stability, efficiency, and adaptability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If more batteries are added to increase range, then the distance the UAV can travel increases, but the weight increases requiring larger and heavier motors
Solution Approach 1:
The patent implements a hybrid power system that dynamically switches between battery electric motors and combustion engines based on flight conditions. During VTOL and low-speed flight, electric motors provide quiet, efficient operation. During high-speed cruise, the combustion engine takes over, allowing batteries to be smaller and lighter while maintaining extended range capability.
2Adaptability or versatility
If fixed wing configurations are used, then the structure is simple, but the aircraft is not adaptable to varying flight conditions leading to energy inefficiency
Solution Approach 1:
The patent employs movable and adjustable wing components including variable incidence wings, adjustable tail planes, and configurable propeller angles. These dynamic adjustments allow the aircraft to optimize its aerodynamic configuration for different flight phases - achieving efficient VTOL with vertical propeller orientation, then transitioning to horizontal flight with adjusted wing and tail positions for optimal lift and drag characteristics.
Solution Approach 2:
The aircraft is divided into modular components with independent adjustment capabilities. Wings, tail planes, and propellers can be individually positioned and angled to suit specific flight conditions. This segmentation allows each component to be optimized independently for its function while maintaining overall system adaptability.
3Stability of the object's composition
If propellers are attached to wings, then the design is compact, but adverse pitch effects occur due to location along the pitch axis
Solution Approach 1:
The patent extracts the propellers from the wings and mounts them directly to the fuselage body. This separation eliminates the adverse pitch effects caused by propellers located at the wing's pitch axis. The fuselage-mounted propellers provide thrust without creating the pitching moments that would require additional stabilizing complexity.
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 configuration allows for increased carrying capacity, extended range, and improved safety by optimizing energy use and stability across different flight conditions, making the UAV suitable for diverse operational scenarios including remote and challenging environments.
Implementation Method 1
vectoring motors and propellers that transition from vertical to horizontal flight
Implementation Method 2
aerodynamic, lift generating wings
Implementation Method 3
hybrid energy sources
Data Source
Figure 1
Figure 1A
Figure 1B
AI summary
An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.