Closed-Front Tail Sitter Wing for Wind-Resistant VTOL Transition
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Solution Overview
Problem
Tail sitters face geometrical and operational constraints due to their vertical take-off and landing position, limiting their performance and making them less efficient compared to traditional aircraft, with previous prototypes failing to achieve effective deployment due to these issues.
Innovation Solution
A tail sitter design featuring a wing with a closed front section and engines positioned to control pitch, roll, and yaw without the need for a tail fin or canards, allowing for efficient transitions between take-off, cruising, and landing positions while minimizing wind resistance and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of moving object
If the tail sitter uses traditional half-wings exposed to wind during take-off and landing, then the wing surface area is sufficient for lift generation, but the sensitivity to gusts of wind increases and wind resistance is higher
Solution Approach 1:
The wing is divided into multiple segments including a first half-wing, a second half-wing, and a rear wing section. These segments can be independently positioned and controlled, allowing the front sections to be minimized during take-off/landing while maintaining sufficient total surface area for cruising flight.
Solution Approach 2:
The wing configuration is made dynamic through movable wing sections that can change position between take-off/landing and cruising modes. The rear wing section can be extended or repositioned to adjust the effective wing area exposed to wind, optimizing performance for different flight phases.
2Object-affected harmful factors
If the tail sitter minimizes half-wing surface area to reduce wind sensitivity, then wind resistance decreases, but the performance in cruising position is penalized
Solution Approach 1:
The wing configuration transitions dynamically between compact take-off/landing mode and extended cruising mode. During take-off and landing, the wing sections are positioned to minimize wind exposure, while during cruising flight, the sections are extended to provide sufficient lift-generating surface area for high-speed performance.
Solution Approach 2:
The wing design utilizes three-dimensional positioning of multiple wing sections rather than a single fixed plane. This allows the wing to present different effective areas to the wind by adjusting the spatial arrangement of the first half-wing, second half-wing, and rear wing section.
3Reliability
If the tail sitter uses a complex configuration with tail fins and canards for stability, then flight control is improved, but the constructional complexity increases
Solution Approach 1:
The invention eliminates traditional tail fins and canards from the configuration. Flight stability and control are achieved through the differential positioning and thrust vectoring of the multiple wing-mounted engines, rather than through separate horizontal and vertical stabilizing surfaces.
Solution Approach 2:
The wing-mounted engines serve multiple functions: they provide thrust for flight, enable pitch control through differential thrust, and contribute to roll and yaw control through their strategic positioning. This multi-functionality replaces the specialized functions of separate tail fins and canards.
4Speed
If the tail sitter positions engines for optimal thrust during cruising, then cruising speed is maximized, but the ability to control pitch during vertical take-off and landing is reduced
Solution Approach 1:
The engine mounting arrangement allows for dynamic adjustment of engine positions and thrust vectors. During vertical take-off and landing, the engines can be positioned or vectored to provide optimal pitch control, while during cruising flight, the same engines are configured for maximum thrust efficiency and speed.
Solution Approach 2:
Different regions of the wing structure provide different functions: the first and second half-wings are optimized for thrust generation during cruising, while the rear wing section and engine positioning are specifically designed to provide pitch control authority during vertical take-off and landing operations.
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 design enhances the tail sitter's performance and reduces complexity, enabling cruising speeds comparable to traditional aircraft while simplifying construction and operation, overcoming previous limitations that hindered their development and deployment.
Implementation Method 1
the thrust of the motors counters the weight of the tail sitter in take-off/landing conditions and the aerodynamic resistance of the air in flight conditions
Implementation Method 2
a tail fin equipped with movable surfaces to control the aircraft
Data Source
Figure 1~2
Figure 3~4
Figure 5~6
AI summary
A tail sitter (1, 1', 1", 1''', 1'''') comprising a wing (4) with a closed front section (C) is described.