Foldable Multirotor Wing Layout for Stable Hover and Forward Flight
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Solution Overview
Problem
Multirotor aircraft face instability and energy inefficiency due to wind interference with fixed wings during horizontal flight, hovering, and landing, especially when winds are present, leading to loss of control and reduced flight time.
Innovation Solution
A foldable wing mechanism that deploys during forward flight to provide lift and reduces surface area during hovering and landing to minimize wind interference, with the wing's center of gravity and aerodynamic center aligned with the aircraft's, using actuators and aerodynamic forces for deployment and folding.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional fixed-wing or fixed-rotor UAV designs are used, then structural simplicity is maintained, but adaptability to different flight conditions (hovering, high-speed forward flight, rough terrain) deteriorates
Solution Approach 1:
The patent applies dynamics by making the wing configuration changeable during flight. The wings can transition between folded and unfolded states, and the rotor system can transition between single-rotor and dual-rotor configurations. This dynamic adaptability allows the UAV to optimize its performance for different flight conditions (hovering, forward flight, rough terrain) without requiring multiple specialized vehicles, thereby improving versatility while managing structural complexity through a single integrated platform.
Solution Approach 2:
The patent applies segmentation by dividing the wing structure into foldable segments that can be independently positioned. The wings are divided into multiple sections connected by hinges, allowing selective folding and unfolding of different wing portions. This segmentation enables the UAV to adjust its wing span and configuration based on flight requirements, improving adaptability while maintaining a compact form factor when folded.
2Speed
If rotor size is increased to improve hovering capability, then hovering performance is improved, but forward speed and compactness deteriorate
Solution Approach 1:
The patent applies dynamics by enabling the rotor system to dynamically reconfigure between single-rotor and dual-rotor modes. During forward flight, the system operates in single-rotor mode for high speed. During hovering operations, additional rotors are deployed to provide the necessary lift and control authority. This dynamic reconfiguration allows the UAV to achieve both high forward speed and excellent hovering capability without compromising either performance metric.
Solution Approach 2:
The patent applies nesting by incorporating foldable wings that can be stored within or alongside the fuselage when not in use. The wings are designed to fold into a compact configuration that nests within the overall vehicle envelope, reducing the aircraft's stowed size and improving compactness while maintaining full wingspan when deployed for forward flight operations.
3Adaptability or versatility
If wing span is increased to improve lift, then hovering capability is improved, but compactness and storage efficiency deteriorate
Solution Approach 1:
The patent applies nesting by designing wings that can be folded into a compact configuration for storage. The wings are divided into sections that can be folded back along the fuselage or stored in dedicated compartments, significantly reducing the stowed volume. When hovering capability is required, the wings are deployed to their full span to provide the necessary lift surface area.
Solution Approach 2:
The patent applies dimensionality change by transitioning the wing configuration from a two-dimensional spread-out structure during flight to a three-dimensional compact folded structure for storage. The wings utilize multi-axis folding mechanisms that collapse the wing span in multiple directions, efficiently packing the large wing area into a small storage volume within the fuselage.
4Reliability
If dual-rotor configuration is used to improve hovering control, then hovering precision is improved, but device complexity and forward speed deteriorate
Solution Approach 1:
The patent applies dynamics by making the rotor configuration changeable based on flight phase. The system dynamically transitions between single-rotor mode for forward flight and dual-rotor mode for hovering operations. This dynamic reconfiguration provides precise hovering control when needed while maintaining simplicity and high speed during forward flight, thereby improving reliability without permanently increasing device complexity.
Data Source
Figure 1A~1B
Figure 2A~2B
Figure 3A~3C
AI summary
A multirotor aircraft that includes a chassis, vertical rotors, foldable wings, and a means for deploying and folding the foldable wing. The foldable wing is attached to the chassis and the means for deploying and folding the foldable wing is designed to deploy and open the foldable wing from a folded and closed state to a deployed and opened state, and vice versa. The gravity center of the folded wing in a folded and closed state is near and close to the gravity center of the multirotor aircraft, and by that enabling to fold and close the foldable wing when hovering, landing and during takeoff and to deploy and open it when flying forward.