Multi-Element Wing VTOL Aircraft with Integrated Ducted Fans
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Solution Overview
Problem
Existing aerial vehicles struggle with efficient vertical take-off and landing (VTOL) capabilities while maintaining effective forward flight configurations, often requiring complex control systems and additional control elements.
Innovation Solution
A multi-element lifting system with integrated propulsion, featuring upper and lower wing elements, internal ducted fans, and a controllable control wing element that articulates for VTOL configurations, allowing for efficient airflow management and thrust direction control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If complex control systems and additional control elements are used to achieve efficient VTOL capabilities, then vertical take-off and landing performance is improved, but device complexity increases
Solution Approach 1:
The control wing element serves multiple functions: it acts as a lifting surface during forward flight and as a thrust vectoring surface during VTOL operations. By articulating to different positions, the same element provides both cruise lift and vertical thrust direction control, eliminating the need for separate control elements for each flight regime.
Solution Approach 2:
The patent combines the control surface and thrust vectoring functions into a single integrated control wing element. This merging of functions reduces the number of separate control elements needed, simplifying the overall control system while maintaining full control authority across all flight modes including VTOL and forward flight.
2Adaptability or versatility
If additional control elements are added to maintain full control of all angular axes during VTOL transitions, then control authority is preserved, but device complexity increases
Solution Approach 1:
The control wing element is designed to perform multiple control functions across different flight regimes. By articulating to appropriate positions, it provides pitch control during forward flight and thrust vectoring control during VTOL, maintaining full angular axis control authority without requiring additional dedicated control elements for each function.
Solution Approach 2:
The control wing element's articulation mechanism allows it to dynamically change its function and orientation based on flight mode. This dynamic reconfiguration enables the same physical element to provide different control authorities as needed, preserving adaptability while reducing the static number of control elements required.
3Device complexity
If conventional propulsion systems are used, then simplicity is maintained, but debris ingestion risks increase during VTOL operations
Solution Approach 1:
The fan is nested within a duct structure that is integrated with the wing element. This nested configuration allows the duct to serve as a protective shroud around the fan, preventing debris from reaching the rotating blades while the entire assembly remains part of the wing structure, reducing overall complexity compared to separate protective systems.
Solution Approach 2:
The duct acts as an intermediary structure between the external environment and the fan. It provides a protective barrier that filters or blocks debris before it can reach the fan blades, reducing ingestion risks while maintaining a relatively simple propulsion system architecture through this intermediate protective element.
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
Enables seamless transitions between VTOL and forward flight modes, providing full control of all angular axes without additional control elements, while reducing debris ingestion risks and simplifying control element deployment mechanisms.
Implementation Method 1
The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system
Implementation Method 2
The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing
Data Source
AI summary
A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.