Multi-Mode Aircraft Wing Layout for Stable Hover Transition
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Solution Overview
Problem
Existing aircraft designs struggle to efficiently transition between forward cruise mode and vertical hover mode while maintaining stability and control, particularly in high angles of attack, due to negative interactions between wings and propeller wash.
Innovation Solution
Aircraft design incorporating a pair of wings with actuating flaps and propellers oriented horizontally to provide upward lift, coupled with tail rotors for yaw and pitch control, and an electronic controller for mode transitions, enabling seamless switching between flight modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If actuating flaps are used to transition between forward cruise mode and vertical hover mode, then the aircraft can achieve mode transitions, but negative interactions between wings and propeller wash occur at high angles of attack
Solution Approach 1:
The aircraft is divided into functionally independent components: a first pair of wings for forward flight, a second pair of wings for vertical flight, and separate propulsion systems (pusher propellers for forward flight, lift propellers for vertical flight). This segmentation allows each component to operate in its optimal performance range without negative interactions, as the wing-propeller combinations that cause interference in conventional designs are avoided.
Solution Approach 2:
The aircraft transitions between flight modes by changing the dimensional contribution of different wing-propeller combinations. In forward cruise mode, the first pair of wings and pusher propellers operate in the horizontal plane. In vertical hover mode, the second pair of wings and lift propellers operate in the vertical plane. This dimensional separation eliminates the high angle of attack interference that occurs when the same wing-propeller system must operate in both regimes.
2Adaptability or versatility
If conventional single-wing designs are used, then the structure is simpler, but the aircraft cannot efficiently transition between forward cruise mode and vertical hover mode
Solution Approach 1:
Each wing pair is designed with multi-functionality to perform different roles in different flight modes. The first pair of wings serves as the primary lifting surface in forward cruise mode, while the second pair of wings serves as the primary lifting surface in vertical hover mode. Both wing pairs are structurally integrated but functionally specialized, allowing the aircraft to achieve multi-mode capability without requiring completely separate systems for each function.
Solution Approach 2:
The aircraft employs dynamic reconfiguration of its lifting surfaces through actuating flaps on both wing pairs. These flaps can be adjusted to optimize aerodynamic performance for the current flight mode, and the transition between modes involves dynamic changes in flap positions and propeller thrust vectors. This dynamic adaptability allows efficient mode transitions while managing the complexity of the dual-wing configuration.
3Force
If propellers are oriented to provide upward lift during vertical hover mode, then vertical lift is achieved, but control authority in high angles of attack is reduced
Solution Approach 1:
Control functions are segmented between different components: the second pair of wings with their actuating flaps provides primary control authority during vertical hover mode, while the tail rotors provide dedicated yaw and pitch control. This segmentation ensures that control functions are not compromised by the high angle of attack conditions that affect conventional propeller-oriented designs, as each control surface operates in its optimal effectiveness range.
Solution Approach 2:
The tail rotors act as intermediary control elements that provide precise yaw and pitch control without being directly affected by the high angle of attack conditions at the main propellers. These tail rotors mediate the control inputs, translating pilot commands into stable aircraft attitudes during vertical hover and transition phases, thereby maintaining control authority independent of the main lift-generating propellers' operating conditions.
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
Enables stable transition between forward cruise and vertical hover modes with enhanced control authority, including yaw, pitch, and lateral movements, while minimizing negative interactions between wings and propeller wash.
Implementation Method 1
one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift
Implementation Method 2
each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode
Implementation Method 3
one or more tail rotors configured to provide at least one of: (i) yaw control or (ii) pitch control
Data Source
AI summary
An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.