Dual Vertical Tail Airframe for Stable UAV Transition Flight
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Solution Overview
Problem
Existing unmanned aerial vehicles face instability during transition from vertical to horizontal flight due to turbulence and disturbance generated by the propeller, lacking an airframe structure that combines the benefits of both fixed-wing and multi-rotor-wing vehicles.
Innovation Solution
An airframe structure with symmetric main wings, upper and lower vertical tail wings, and horizontal tail wings arranged at specific angles and distances to stabilize the aircraft, utilizing NACA airfoils for stability and incorporating a bob-weight assembly for balanced weight distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the unmanned aerial vehicle uses a fixed-wing configuration for horizontal flight, then energy consumption is reduced and flight endurance is increased, but the site requirements are higher and a flat runway is needed
Solution Approach 1:
The aircraft is divided into distinct functional modules: a multi-rotor system for vertical takeoff and landing, and a fixed-wing system for horizontal flight. This segmentation allows the vehicle to operate in different flight modes independently, combining the advantages of both configurations without requiring compromise on either energy efficiency or site adaptability.
Solution Approach 2:
The aircraft transitions dynamically between vertical and horizontal flight modes. The multi-rotor wings can rotate and adjust their orientation, allowing the vehicle to switch from vertical takeoff to horizontal flight configuration. This dynamic adaptability enables the aircraft to overcome the site requirements limitation of fixed-wing vehicles while maintaining their energy efficiency advantage.
2Duration of action of moving object
If the unmanned aerial vehicle transitions from vertical to horizontal flight state, then flight endurance and speed are improved, but turbulence and disturbance from the propeller affect flight stability
Solution Approach 1:
A tail wing is introduced as an intermediary element between the propeller and the rear fuselage. This tail wing acts as a mediator that counteracts the turbulence and disturbance generated by the propeller during transition phases. The tail wing provides stabilizing aerodynamic forces that maintain flight stability while the vehicle transitions from vertical to horizontal flight, enabling the vehicle to achieve long endurance and high speed without sacrificing stability.
3Ease of operation
If the unmanned aerial vehicle uses a multi-rotor-wing configuration for vertical takeoff, then site requirements are reduced and direct vertical takeoff is enabled, but energy consumption is high and flight endurance is short
Solution Approach 1:
The aircraft is divided into distinct functional modules: a multi-rotor system for vertical takeoff and landing, and a fixed-wing system for horizontal flight. This segmentation allows the vehicle to operate in different flight modes independently, combining the advantages of both configurations without requiring compromise on either energy efficiency or site adaptability.
Solution Approach 2:
The aircraft transitions dynamically between vertical and horizontal flight modes. The multi-rotor wings can rotate and adjust their orientation, allowing the vehicle to switch from vertical takeoff to horizontal flight configuration. This dynamic adaptability enables the aircraft to overcome the site requirements limitation of fixed-wing vehicles while maintaining their energy efficiency advantage.
4Adaptability or versatility
If the unmanned aerial vehicle combines both fixed-wing and multi-rotor characteristics, then versatility is improved, but device complexity increases
Solution Approach 1:
The patent merges the multi-rotor and fixed-wing configurations into a single integrated airframe. The aircraft features both rotating multi-rotor wings for vertical flight and a fixed wing structure for horizontal flight, combining these two previously separate vehicle types into one versatile platform. This merging approach achieves flight mode versatility while managing structural complexity through unified design elements.
Solution Approach 2:
The aircraft is designed with universal components that serve multiple functions. The multi-rotor wings can function both as lift-generating rotors during vertical flight and as stabilizing surfaces during horizontal flight. The tail wing serves both aerodynamic stabilization and structural support functions. This multi-functionality reduces overall system complexity while achieving versatile flight capabilities.
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 airframe structure enhances stability during transition by blocking turbulence and maintaining balanced weight, allowing for efficient energy use and extended flight range.
Implementation Method 1
a lot of turbulence and disturbance is generated in the tip of the main wing 102 and at the position of the propeller
Implementation Method 2
The main wing and the horizontal tail wing are NACA airfoils
Data Source
AI summary
An airframe structure and an unmanned aerial vehicle thereof is disclosed, which belongs to the technical field of the unmanned aerial vehicle. The airframe structure includes: a main airframe; at least two main wings, which are symmetrically provided on the two sides of the main airframe, and which are provided with a propeller and a motor to provide power to the propeller; an upper vertical tail wing, which is provided at the upper end of the main airframe; and a lower vertical tail wing, which is provided at the lower end of the main airframe. The characteristics of a fixed-wing unmanned aerial vehicle and a multi-rotor-wing unmanned aerial vehicle are considered.