Compact VTOL Wing Layout With Rotor Overlap for Reduced Width
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Solution Overview
Problem
Existing unmanned aircraft designs, particularly VTOL-type and those with horizontal wings, suffer from large lateral width, making storage and transportation cumbersome.
Innovation Solution
An unmanned aircraft design featuring a wing body positioned above the aircraft body, overlapping partially with rotor blade regions, and supported by rods, with a shape that minimizes overlap and reduces lateral width, allowing for compact storage and transportation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a horizontal wing is added to generate aerodynamic lift, then rotor output requirements are reduced, but the lateral width of the aircraft becomes extremely large
Solution Approach 1:
The patent repositions the wing from a lateral extension to a vertical position above the fuselage, changing the spatial dimension from horizontal to vertical. This allows the wing to generate aerodynamic lift without increasing the aircraft's lateral width, resolving the contradiction between reduced rotor power needs and compact lateral dimensions.
Solution Approach 2:
The wing is positioned within the rotational region of the rotors, nesting the wing structure inside the existing rotor sweep area. This allows the wing to coexist with the rotors in the same vertical space without requiring additional lateral clearance, thereby reducing overall aircraft width while maintaining lift-generating capability.
2Force
If the wing is positioned to overlap rotor rotational regions, then lift generation is improved, but the structural complexity increases
Solution Approach 1:
The patent merges the wing structure with the fuselage by directly mounting the wing on top of the fuselage rather than using separate support structures. This integration reduces structural complexity while maintaining the wing's lift-generating function and its positional overlap with the rotor rotational regions.
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 design achieves a compact aircraft with reduced rotor output requirements during high-speed flight by generating lift with the wing body, minimizing width, and stabilizing airflow, thus reducing the need for excessive rotor power.
Implementation Method 1
lift force can be generated using aerodynamics
Data Source
AI summary
An unmanned aircraft including a horizontal wing and compact as a whole is provided.An unmanned aircraft 100 includes an unmanned aircraft body 101, a plurality of rotors 104A, 104B, and 104C that have rotational axes extending in an up-down direction and are configured to enable the unmanned aircraft 100 to perform horizontal flight by controlling rotation of the plurality of rotors 104A, 104B, and 104C, and a wing body 106 provided above the unmanned aircraft body 101 and disposed to overlap at least part of rotational regions 104R of the plurality of rotors 104A, 104B, and 104C in a plan view.