Multi-Wing VTOL Aircraft with Rotating Fuselage for Pitching Moment Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Rotary wing aircraft face inefficiencies due to rotor-induced turbulence, lift dissymmetry, and high aerodynamic drag, especially when lifting heavy payloads, while fixed-wing aircraft excel in fuel efficiency at high horizontal air velocities, but lack maneuverability and VTOL capabilities.
Innovation Solution
A compact, manned or unmanned aircraft with a boxed planform multi-wing assembly statically affixed to a co-planar counter-rotating quad-rotor system and a teardrop-shaped fuselage free to rotate, enabling dynamic orientation and high maneuverability, reducing drag, and enhancing fuel efficiency and VTOL capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If rotary wing aircraft use small diameter fixed pitch rotors for simplicity and low cost, then device complexity is reduced, but rotor efficiency deteriorates due to nonlinear inefficiencies during hover and horizontal flight
Solution Approach 1:
The aircraft divides the lifting function into multiple segments: the quad-rotor system provides vertical lift and hover capability, while the multi-wing assembly provides forward flight lift. This segmentation allows each component to operate in its optimal efficiency range, resolving the contradiction between simple rotor design and overall system efficiency
Solution Approach 2:
The aircraft employs dynamic reconfiguration of the lifting system. During hover, the quad-rotors provide all lift; during forward flight, the wings progressively assume more lift generation. This dynamic transition optimizes energy efficiency across different flight phases while maintaining operational simplicity
2Force
If rotary wing aircraft use large diameter rotors for heavy payload lifting, then lifting capability is improved, but aerodynamic drag increases and device complexity increases
Solution Approach 1:
The lifting function is segmented between the quad-rotor system and the multi-wing assembly. The rotors handle vertical lift and payload elevation, while the wings provide aerodynamic lift during forward flight. This segmentation eliminates the need for oversized complex rotor hubs while maintaining heavy payload capability
Solution Approach 2:
The multi-wing assembly serves multiple functions: it provides aerodynamic lift during forward flight, contributes to directional stability, and can be configured in different arrangements (boxed planform, V-formation, etc.). This multi-functionality replaces the need for complex, oversized rotor systems
3Loss of energy
If fixed-wing aircraft are used for high horizontal air velocity flight, then fuel efficiency is improved, but VTOL capability and maneuverability are lost
Solution Approach 1:
The aircraft dynamically transitions between hover mode (vertical orientation) and forward flight mode (horizontal orientation). The control system coordinates the quad-rotors and multi-wing assembly to smoothly transition between these states, enabling both VTOL capability and fuel-efficient forward flight
Solution Approach 2:
The hybrid aircraft performs multiple functions: it can hover vertically like a helicopter, transition to horizontal flight like an airplane, and perform maneuvers intermediate between the two. This multi-functionality resolves the contradiction between fixed-wing efficiency and VTOL versatility
4Ease of operation
If helicopter uses dynamic pitch control and tail rotor for attitude control, then maneuverability is improved, but device complexity and cost increase
Solution Approach 1:
The control function is segmented between the quad-rotor system (which provides individual motor control for pitch, roll, and yaw) and the multi-wing assembly (which provides aerodynamic stability and control surfaces). This segmentation achieves helicopter-level maneuverability while using simpler, more distributed control mechanisms
Solution Approach 2:
The multi-wing assembly provides natural aerodynamic stability and control authority through its configuration, reducing the need for complex active control systems. The aircraft's geometry itself contributes to attitude control, making the system more self-regulating
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 aircraft achieves high maneuverability, attitude control, and fuel-efficient flight with enhanced VTOL capabilities, allowing rapid transitions between vertical and horizontal flight orientations, while minimizing manufacturing complexity and cost.
Implementation Method 1
co-planar adjacent counter-rotating quad-rotor air propulsion system
Implementation Method 2
plurality of parallel wings forming a boxed planform multi-wing assembly
Implementation Method 3
fuselage of teardrop shape free to rotate under servo control
Implementation Method 4
counter rotating dual-rotor helicopter resolves lift dissymmetry
Data Source
AI summary
This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation.