Partially Fixed-Wing VTOL Aircraft With Corotating Tiltwings
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Solution Overview
Problem
Conventional tiltrotor aircrafts require high speed transitions between helicopter and fixed-wing modes, are slow in tilting, and have difficulty adapting to complex environments.
Innovation Solution
A wing-engine corotating vertical takeoff and landing aircraft with partially fixed wings, utilizing engines for vertical suspension in hovering and wings for horizontal flight, with propellers tilting along tiltwings and a four-engine layout for combined hovering and horizontal flight mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional tiltrotor aircraft use two tilt rotors to switch between helicopter and fixed-wing modes, then vertical takeoff and landing capability is achieved, but the tilting process is slow and requires high horizontal flight speed transitions
Solution Approach 1:
The aircraft divides the lifting function into multiple independent engines (four engines total) distributed across the wing structure, allowing individual or collective tilting of engine-propeller assemblies. This segmentation enables faster, more flexible mode transitions compared to conventional two-tiltrotor designs, as each engine unit can be independently controlled during the transition process.
Solution Approach 2:
The engine mounting structure incorporates dynamic tilting mechanisms that allow the engines and propellers to rotate relative to the wing. This dynamic configuration enables the propeller disc plane to transition from a horizontal orientation (helicopter mode) to various angles up to 90 degrees or more (fixed-wing mode), achieving rapid mode switching without the speed restrictions of conventional designs.
2Adaptability or versatility
If conventional tiltrotor aircraft require high horizontal flight speed for mode transitions, then fixed-wing flight capability is achieved, but acceleration and deceleration times are prolonged
Solution Approach 1:
The aircraft performs preliminary tilting of the engines and propellers during approach and departure phases, preparing the configuration for mode transition before full speed is achieved. This preliminary action reduces the time required for complete mode switching, as the mechanical reconfiguration begins earlier in the flight sequence rather than waiting for high-speed conditions.
Solution Approach 2:
The aircraft utilizes variable parameters including tilt angle, propeller pitch, and engine thrust distribution to optimize the transition process. By dynamically adjusting these parameters, the aircraft can transition between modes at lower speeds and reduce acceleration/deceleration requirements, breaking the conventional trade-off between adaptability and time loss.
3Stability of the object's composition
If conventional tiltrotor aircraft use symmetrical tilt rotors, then balance is achieved, but the structure is complex and requires high flight environment requirements
Solution Approach 1:
The aircraft employs an asymmetrical configuration with four engines distributed across the wing structure rather than two symmetrical tilt rotors. This asymmetrical layout, with engines positioned at different locations and orientations, provides inherent stability through distributed thrust while simplifying the overall structure by eliminating the need for complex symmetrical tilting mechanisms. The configuration allows flexible weight and balance management through differential engine control.
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 efficient vertical takeoff and landing, high-speed horizontal flight, and smooth transitions between modes without engine shutdown or restart, with enhanced stability and maneuverability.
Implementation Method 1
the propeller disc surface of the tilt rotor is parallel to the ground, and the rotor rotates to provide the lift
Implementation Method 2
the angle change of the tilt rotor is achieved through the nacelle tilting, so that the propeller disc surface forms an included angle of 70° to 90° with the ground
Implementation Method 3
In a horizontal flight state, the aircraft flies completely rely on the lift by the wings at a sufficiently high speed
Data Source
AI summary
A wing-engine corotating vertical takeoff and landing aircraft with partially fixed wings is provided. The aircraft includes an aircraft fuselage, and front wings and rear wings arranged on the aircraft fuselage. Each of the front wings and the rear wings includes a fixed wing connected with the aircraft fuselage, and a tiltwing is hinged with an end, away from the aircraft fuselage, of the fixed wing. A rotational axis of the tiltwing extends horizontally inward and is perpendicular to an axis of the aircraft fuselage. Each tiltwing is provided with a propeller tilting along with the tiltwing. Geometrically, one end of a rotating shaft of the propeller is arranged on the tiltwing, and the other end of the rotating shaft of the propeller extends along the advancing or ascending direction of the aircraft fuselage, and the rotating shaft forms a negative angle with the plane where the tiltwing is located.