Swiveling Tail Aircraft for VTOL-to-Forward Flight Transition
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Solution Overview
Problem
Existing aircraft technologies face challenges in transitioning between different types of flight modes, such as vertical take-off and landing, hover, and forward flight, in a simple and reliable manner.
Innovation Solution
The aircraft design incorporates a swiveling tail with a horizontal stabilizer and an impeller integrated into the tailplane, allowing the rear fuselage section to pivot relative to the front fuselage section about a transverse axis, enabling different flight configurations by adjusting the orientation of the tail and drive devices to generate lift and propulsion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a conventional fixed-wing aircraft design is used, then forward flight is efficient, but vertical take-off and landing capability is lost
Solution Approach 1:
The patent applies dynamics by making the horizontal stabilizer pivotable relative to the fuselage, allowing it to change orientation between parallel and perpendicular positions. This dynamic configuration enables the aircraft to transition between different flight modes (vertical take-off/landing and forward flight) by adjusting the stabilizer's angle, thereby achieving flight mode versatility without requiring a completely reconfigurable airframe.
Solution Approach 2:
The horizontal stabilizer is designed to serve multiple functions: it provides horizontal stabilization during forward flight when parallel to the fuselage, and generates vertical lift during vertical take-off and landing when perpendicular to the fuselage. This multi-functionality allows a single component to enable diverse flight capabilities, resolving the contradiction between versatility and complexity.
2Adaptability or versatility
If the horizontal stabilizer is made pivotable to enable different flight modes, then flight mode transitions are enabled, but structural complexity increases
Solution Approach 1:
The horizontal stabilizer is designed with a pivot mechanism that allows it to dynamically change its orientation relative to the fuselage. This dynamic capability enables the stabilizer to assume different positions (parallel or perpendicular to the fuselage) depending on the desired flight mode, thereby enabling flight mode transitions without requiring multiple separate components or complex reconfiguration systems.
3Ease of operation
If dual propulsion devices are integrated into the horizontal stabilizer and fuselage, then lift and propulsion control is improved, but device complexity increases
Solution Approach 1:
The first propulsion device in the fuselage and the second propulsion device in the horizontal stabilizer work together as an integrated propulsion system. The fuselage-mounted propulsion provides primary thrust, while the stabilizer-mounted propulsion assists with lift generation and attitude control. This multi-functional propulsion arrangement improves ease of operation by providing redundant and complementary thrust sources that can be independently controlled for various flight phases.
Solution Approach 2:
The patent merges two propulsion systems into a unified configuration where the first propulsion device in the fuselage and the second propulsion device in the horizontal stabilizer operate in coordination. This combination allows the aircraft to achieve both forward thrust and vertical lift through a integrated system, improving propulsion control efficiency while sharing common control mechanisms.
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 allows for seamless transitions between flight modes, enabling the aircraft to take off and land vertically, hover, and fly forward efficiently, with the swiveling tail and dual drive systems ensuring reliable lift and propulsion control.
Implementation Method 1
at least one first propulsion device provided in the region of the forward fuselage section and/or on the wing, which is configured to generate thrust
Implementation Method 2
at least one second propulsion device provided on the horizontal stabilizer and/or on the rear fuselage section, which is configured to generate lift
Implementation Method 3
at least one wing provided in the region of the forward fuselage section
Implementation Method 4
at least one horizontal stabilizer, which is configured to rotate and/or stabilize the aircraft about a transverse axis of the aircraft during flight
Data Source
Figure 1
Figure 2a~2c
Figure 3a~3c
AI summary
The invention relates to an aircraft and a method for operating an aircraft comprising at least one fuselage (7) which has a front fuselage section (7a) and a rear fuselage section (7b), at least one wing (1) provided in the region of the front fuselage section (7a), at least one first drive unit (2) provided in the region of the front fuselage section (7a) and/or on the wing (1) and which is designed to generate propulsion and/or lift, and at least one horizontal stabiliser (3) which is designed to rotate the aircraft about a transverse axis of the aircraft and/or stabilise the aircraft during flight, wherein the horizontal stabiliser (3) is attached to the fuselage (7) and the rear fuselage section (7b) can be pivoted relative to the front fuselage section (7a) about a pivot axis (S2) which is substantially parallel to the transverse axis of the aircraft and/or the horizontal stabiliser (3) is attached to at least one support element (6) which is mounted on the fuselage (7) and/or on the wing (1) and which can be pivoted relative to the fuselage (7) or the wing (1) about a pivot axis (S1) which is substantially parallel to the transverse axis of the aircraft.