Tail Sitter Wing Configuration for Aerodynamic Efficiency
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Solution Overview
Problem
Tail sitters face geometrical and operational constraints due to their vertical take-off and landing position, which limits their aerodynamic efficiency and performance, leading to complexity and inefficiency in cruising conditions, ultimately preventing their effective deployment.
Innovation Solution
A tail sitter design featuring a closed front section wing with cantilever half-wings and engines positioned to maximize aerodynamic efficiency, eliminating the need for complex support structures and tail fins, allowing for simple construction and reduced weight by using a wing configuration that generates lift through airflow deflection without additional wing surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the tail sitter uses traditional half-wing configuration with vertical take-off and landing position, then the aircraft can achieve vertical take-off and landing capability, but the aerodynamic efficiency in cruising conditions is penalized and the configuration becomes complex
Solution Approach 1:
The patent applies dynamics by making the half-wings movable relative to the fuselage. The half-wings can rotate about their longitudinal axes to change their orientation angle. During vertical take-off and landing, the half-wings are positioned at a first angle to minimize wind exposure and sensitivity to gusts. During horizontal cruising flight, the half-wings rotate to a second angle that optimizes aerodynamic efficiency and lift generation. This dynamic adjustment allows the aircraft to adapt its wing configuration to different flight phases, resolving the contradiction between construction simplicity and aerodynamic efficiency.
2Object-affected harmful factors
If the tail sitter minimizes the surface of the half-wing exposed to the wind during take-off and landing, then sensitivity to gusts is reduced, but the performance in cruising position is penalized
Solution Approach 1:
The patent applies dynamics by making the half-wings movable relative to the fuselage. The half-wings can rotate about their longitudinal axes to change their orientation angle. During vertical take-off and landing, the half-wings are positioned at a first angle to minimize wind exposure and sensitivity to gusts. During horizontal cruising flight, the half-wings rotate to a second angle that optimizes aerodynamic efficiency and lift generation. This dynamic adjustment allows the aircraft to adapt its wing configuration to different flight phases, resolving the contradiction between construction simplicity and aerodynamic efficiency.
3Reliability
If the tail sitter uses complex support structures and additional wing surfaces to improve aerodynamic efficiency, then cruising performance increases, but the device complexity and weight increase
Solution Approach 1:
The patent applies dynamics by making the half-wings movable relative to the fuselage. The half-wings can rotate about their longitudinal axes to change their orientation angle. During vertical take-off and landing, the half-wings are positioned at a first angle to minimize wind exposure and sensitivity to gusts. During horizontal cruising flight, the half-wings rotate to a second angle that optimizes aerodynamic efficiency and lift generation. This dynamic adjustment allows the aircraft to adapt its wing configuration to different flight phases, resolving the contradiction between construction simplicity and aerodynamic efficiency.
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
The design enhances aerodynamic efficiency in cruising conditions while simplifying the configuration, reducing complexity and weight, enabling high-performance flight without the need for additional stability surfaces, making the tail sitter more practical for use.
Implementation Method 1
a wing (4) with a closed front section (C), comprising a pair of half-wings (5) projecting in a cantilever fashion from mutually opposite sides of the fuselage (2)... a plurality of engines (15a, 15b, 15c, 15d) carried by the wing (4)... the axes (A) of the hubs (16) of the engines (15a, 15b, 15c, 15d) being arranged on the front section (C) of the wing (4)
Data Source
AI summary
A tail sitter aircraft is described that comprises: a fuselage arranged vertically in a take-off/landing position and transversely to a vertical direction in a cruising position of the aircraft; a single wing; at least two first engines configured to exert respective first thrusts directed along respective first axes on the tail sitter; and at least two second engines rotating about respective second axes arranged above said first axes of the first engines, with reference to the cruising position; the at least two second engines being configured to exert respective second thrusts directed along respective second axes on the tail sitter; the first and second engines being carried by the single wing; the single wing comprises a first portion and a second portion mutually staggered from one another; the second portion being arranged above said first portion, with reference to said cruising position; said first portion comprises two half-wings, extending from opposite lateral sides of the fuselage; the wing further comprises a third portion arranged below said first portion with reference to said cruising position of said aircraft.