VTOL Aircraft Forward Rotor Segmentation for Transition Stability
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Solution Overview
Problem
Winged VTOL aircraft face challenges in efficiently transitioning between hovering and cruising modes due to high tilting forces and aerodynamic instability, often requiring substantial energy and being prone to single-point non-performance events.
Innovation Solution
The design features independently tiltable forward rotors, which generate thrust during both hovering and cruising, while fixed rear rotors provide vertical thrust, reducing the need for tilting all rotors and enhancing stability and redundancy in the propulsion system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If all rotors are tilted simultaneously to transition between hovering and cruising, then the aircraft can change flight modes, but the aircraft becomes aerodynamically unstable and requires substantial force
Solution Approach 1:
The rotor system is segmented into forward rotors and rearward rotors with independent tilt control. The forward rotors can be tilted independently from the rearward rotors, allowing differential adjustment to maintain aerodynamic stability during mode transitions while still achieving the necessary thrust vector changes.
Solution Approach 2:
Different tilt mechanisms are provided for different rotor groups based on their specific functional requirements. The forward rotors have independent tilt control optimized for cruise transition, while rearward rotors maintain fixed or different tilt for vertical thrust, allowing each component to optimize its local function during the transition.
2Device complexity
If a single tilting mechanism is used to tilt multiple rotors, then the structure is simplified, but the aircraft is vulnerable to single-point non-performance events
Solution Approach 1:
The single tilting mechanism is segmented into multiple independent tilt mechanisms, one for each rotor or rotor group. This segmentation maintains structural simplicity while distributing the risk of failure across independent components, ensuring that a malfunction in one mechanism does not compromise the entire rotor system.
Solution Approach 2:
Redundant tilt mechanisms are provided for each rotor group, preparing the system in advance to withstand potential failures. If one tilt mechanism fails, the redundant mechanism can compensate, cushioning against the harmful effects of single-point non-performance events.
3Adaptability or versatility
If two separate sets of fixed-position rotors are used (one for vertical flight, another for horizontal flight), then the aircraft can perform both flight modes, but the aircraft becomes heavier and less energy efficient
Solution Approach 1:
Each rotor is designed as a universal component capable of performing both vertical and horizontal flight functions through independent tilt control. This eliminates the need for separate dedicated rotor sets, reducing weight while maintaining dual flight mode capability through the multi-functionality of the rotor system.
Solution Approach 2:
The rotors transition from static fixed-position designs to dynamic tiltable configurations. By enabling rotors to change their orientation dynamically between vertical and horizontal positions, the system achieves flight mode versatility without requiring separate static rotor sets, thereby reducing weight.
4Adaptability or versatility
If tilting mechanisms are added to enable mode transitions, then the aircraft can switch between hover and cruise, but the energy consumption increases during transition
Solution Approach 1:
The tilt mechanisms are segmented and applied only to the forward rotors rather than all rotors. This selective segmentation reduces the total mass of tilting components, thereby reducing the energy required to accelerate and decelerate them during mode transitions while still achieving the necessary flight mode switching capability.
Solution Approach 2:
Instead of tilting all rotors completely to switch modes, the system uses partial tilting of only the forward rotors. This partial action is sufficient to achieve the necessary thrust vector changes for mode transition while minimizing the energy consumption associated with moving all rotor masses.
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 approach allows for smoother, more efficient transitions between hovering and cruising, reducing energy consumption and increasing safety and reliability by distributing thrust generation and eliminating the risk of single-point failures.
Implementation Method 1
The propulsion system (6) comprises rotors (8), and more specifically, comprises one or more tilt-adjustable rotors (10) positioned forward of the forward set of wings (20)
Data Source
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AI summary
Winged tilt-rotor vertical take-off and landing (VTOL) aircraft and related methods are disclosed. Aircraft comprise an airframe comprising one or more wings; one or more tilt-adjustable rotors positioned forward of the one or more wings; and one or more fixed-tilt rotors positioned behind at least one of the one or more wings. Methods comprise tilting only one or more forward rotors positioned in front of one or more wings of the aircraft, and not tilting one or more rearward rotors positioned behind at least one of the one or more wings.