Rotatable Wing Flight Module for VTOL Lift and Drag Control
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Solution Overview
Problem
Existing vertical take-off and landing aircraft designs face issues with protruding air guidance devices that disrupt take-off and landing, mechanical load imbalances, inefficient propulsion power adjustment, and unfavorable aerodynamics due to fixed airfoils and propeller configurations.
Innovation Solution
Integrate rotatable wings with airfoil shapes into the supporting structure beams, allowing adjustable angles to optimize lift and propulsion based on flight phases, and use turbine propellers for improved aerodynamics and reduced mechanical load.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If air guidance devices are mounted on the outer circumference of the supporting structure, then air control capability is improved, but the flight module becomes very protruding which disrupts take-off and landing operations
Solution Approach 1:
The air guidance devices are mounted on pivoting supports that allow them to rotate between a operational position (extending from the supporting structure) and a stowed position (folded against the supporting structure). This dynamic positioning enables the devices to be deployed during cruise flight for air control while being retracted during take-off and landing to minimize protrusion and avoid disruption.
2Device complexity
If air guidance devices are mounted on one side of the supporting structure, then device complexity is reduced, but considerable bending load is created on the air guidance devices and supporting structure
Solution Approach 1:
The patent employs asymmetric mounting of air guidance devices on pivoting supports along the supporting structure beams. This asymmetric configuration allows the devices to be positioned optimally for aerodynamic control while the pivoting mechanism distributes mechanical loads more evenly along the supporting structure, reducing concentrated bending stresses compared to fixed symmetric mounting.
3Device complexity
If the number of propellers is fixed, then structural simplicity is maintained, but propulsion power cannot be adjusted to match requirements in different flight phases
Solution Approach 1:
The propulsion system incorporates a variable number of operational propellers that can be dynamically adjusted based on flight phase requirements. During cruise flight, fewer propellers operate to reduce drag and improve efficiency, while during take-off and landing phases, additional propellers are activated to provide maximum thrust. This dynamic configuration allows the system to adapt propulsion power to match the aerodynamic requirements of different flight conditions.
4Use of energy by moving object
If propellers are switched off during inclined flight position, then energy consumption is reduced, but rotor blades create unfavorable air resistance due to lateral flow
Solution Approach 1:
The patent incorporates adjustable inclination angles for the propeller rotor blades that can be dynamically modified during flight. When propellers are switched off during inclined cruise flight, the rotor blades can be adjusted to a lower inclination angle to minimize their cross-sectional area and reduce parasitic drag from lateral flow. This dynamic adjustment ensures that even non-operational propeller blades present minimal resistance to the airflow, improving overall aerodynamic efficiency.
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
Enhances flight efficiency, stability, and aerodynamics by optimizing lift and propulsion power distribution, reducing size and mass, and improving maneuverability under varying flight conditions.
Implementation Method 1
The wing has on its upper side a curved inflow surface in relation to the inflow surface of its underside, which deflects and accelerates the air flow over the upper side of the wing in order to generate dynamic lift when the wing is subjected to airflow, thus causing a negative pressure on the upper side of the wing and an overpressure on the underside of the wing.
Implementation Method 2
a certain number of supporting structure beams each have at least one wing with a wing shape, which is arranged or designed to be rotatable in a longitudinal section (wing section) of the supporting structure beam
Data Source
Figure 1a
Figure 1b
Figure 1c
AI summary
The invention relates to a flight module for a vertical take-off and landing aircraft with a plurality of drive units arranged on a support structure, wherein the support structure comprises elongate support beams joined to one another at nodes. According to the invention, a specified number of the support beams each comprise at least one wing with aerofoil form, which is mounted or designed for rotation in a length section of the support beam extending between two nodes.