Vertical Takeoff Aircraft Drive Unit Configuration
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Solution Overview
Problem
Vertical take-off aircraft are hindered by their large weight due to pivoting drives, which limits flight time and distance, and requires high drive power, especially during vertical take-off, due to the need for stable connections between wings and fuselage.
Innovation Solution
The aircraft features pivoting drive units that pivot into the direction of horizontal flight, with vertically rigid drive units generating lift only during vertical flight, reducing weight and using an angle of attack to control yaw and roll, and strategically placing drive units close to the fuselage to minimize weight and bending moments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If pivoting drives are installed separately for each drive unit to enable precise control of vertical and horizontal flying positions, then flight control precision is improved, but total weight of the aircraft increases
Solution Approach 1:
The patent combines the pivoting function into a single centralized drive unit rather than installing separate pivoting drives for each drive unit. This single pivoting mechanism controls the orientation of all drive units simultaneously, reducing the total number of pivoting mechanisms and their associated weights while maintaining precise flight control capability.
Solution Approach 2:
The single pivoting drive unit performs multiple functions by controlling the orientation of multiple drive units. It enables both vertical and horizontal flying positions for all propellers simultaneously, making one mechanism serve the purpose of what would traditionally require multiple separate mechanisms.
2Stability of the object's composition
If drive units are rigidly connected to wings with stable load-bearing connections to support their weight, then structural stability is improved, but overall weight of the aircraft increases
Solution Approach 1:
The patent combines multiple drive units and their support structures into a single integrated wing assembly. The drive units are mounted on a common support structure that is rigidly connected to the wing, eliminating the need for separate heavy support structures for each drive unit while maintaining structural stability.
3Power
If large drive power is provided to overcome large total weight during vertical take-off, then vertical lift capability is improved, but remaining flight time or distance limited by battery capacity is reduced
Solution Approach 1:
The patent combines multiple drive units into a single pivoting assembly, reducing the total weight that requires vertical lift. With reduced weight, less power is needed for vertical take-off, preserving battery capacity for longer flight duration.
Solution Approach 2:
The patent changes the orientation parameter of the drive units by introducing a pivoting mechanism. This allows the drive units to be oriented vertically for lift generation during take-off and then pivoted to horizontal orientation for efficient forward flight, optimizing power usage across different flight phases.
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
This configuration results in a lighter aircraft with reduced drive power requirements, improved maneuverability, and stable flight behavior, allowing for continued flight even in case of drive unit failure, while maintaining efficiency and cost-effectiveness.
Implementation Method 1
the pivoting drive units generate an uplift necessary for a vertical flying movement of the aircraft
Implementation Method 2
the pivoting drive units generate the drive necessary for the horizontal flying movement
Data Source
AI summary
A vertical take-off aircraft (1) has two wings arranged on an aircraft fuselage (2) of the aircraft (1). Along each wing (3), in each case at least one pivoting drive unit (5) is arranged pivotably on the wings. The at least one pivoting drive unit (5) can be brought into a vertical flying position and into a horizontal flying position. In the vertical flying position, the pivoting drive units (5) generate an uplift necessary for a vertical flying movement of the aircraft (1) and, in the horizontal flying position, a propulsion necessary for a horizontal flying movement of the aircraft (1). On each wing (3), at least one vertical drive unit (6) is arranged rigidly in a vertical flying position.