Drone Pivot Half-Wings for Energy Efficiency
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Solution Overview
Problem
Current drones with three lift and propulsion rotors have limited autonomy and endurance due to high electrical energy consumption, especially during hovering and cruising flights, which restricts their ability to perform missions over long distances without damaging their wings when used as landing gear.
Innovation Solution
The drone features pivot-type connected half-wings that can alternately serve as landing gear or fixed wings to reduce rotor energy consumption, with axes of rotation perpendicular to the longitudinal direction, allowing for vertical thrust and independent rotation around two axes to control pitch and roll, and includes additional propulsion rotors for increased speed and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the drone uses at least three lift and propulsion rotors for hovering and cruising flight, then it can achieve vertical take-off and landing capability, but the electrical energy consumption increases significantly, reducing autonomy and endurance
Solution Approach 1:
The patent applies the dynamics principle by making the half-wings movable rather than fixed. The half-wings can pivot between a folded position (for vertical take-off and landing) and a deployed position (for efficient cruising flight). This dynamic configuration allows the drone to adapt its structure based on flight phase, reducing energy consumption during cruising by utilizing aerodynamic lift from the deployed wings while maintaining vertical operation capability when wings are folded.
Solution Approach 2:
The half-wings serve multiple functions: they act as landing gear when folded and as aerodynamic surfaces for lift generation when deployed. This multi-functionality resolves the contradiction by allowing the same structural element to support both vertical operation and energy-efficient cruising, eliminating the need for separate dedicated components.
2Volume of moving object
If the half-wings are folded against the supporting structure to form landing gear, then the drone can achieve compact configuration for vertical landing, but the trailing edge of the aerodynamic profile comes into contact with the ground, causing damage and degrading flight performance
Solution Approach 1:
The patent inverts the conventional folding approach by orienting the rotation axis of the half-wings perpendicular to the longitudinal direction of the drone. Instead of the trailing edge contacting the ground during folding, the leading edge or intermediate portion contacts the ground, while the trailing edge remains elevated and protected. This inverted configuration preserves wing integrity while achieving compact landing gear formation.
Solution Approach 2:
The patent applies local quality by differentiating the functional characteristics of different parts of the half-wing. The rotation axis is specifically positioned and oriented to ensure that only certain portions of the wing (not the critical trailing edge) contact the ground during folding. This localized protection strategy maintains the aerodynamic integrity of the trailing edge while still achieving compact configuration.
3Reliability
If the axis of rotation of the half-wings is oriented perpendicular to the longitudinal direction of the drone, then the wings can fold without the trailing edge contacting the ground, but the drone loses the ability to rest on its tail with an optimal angle
Solution Approach 1:
The patent segments the support functions by separating the wing-folding mechanism from the tail-resting function. The perpendicular rotation axis orientation specifically protects the wings during folding, while the tail section independently provides the necessary support angle for vertical landing. This segmentation allows each component to optimize its specific function without compromising the other.
4Use of energy by moving object
If the drone uses fixed wings to reduce rotor energy consumption during cruising flight, then autonomy and endurance increase, but the wings cannot be compactly stored for vertical take-off and landing operations
Solution Approach 1:
The patent applies dynamics by making the wings movable rather than fixed. The half-wings pivot on axes perpendicular to the longitudinal direction, allowing them to transition between a folded configuration (for vertical take-off and landing) and a deployed configuration (for energy-efficient cruising). This dynamic adaptability resolves the contradiction by enabling the drone to have fixed-wing capabilities when needed while maintaining configuration flexibility for vertical operations.
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 design enhances the drone's autonomy and endurance by reducing energy consumption during flight, preventing wing damage, and enabling longer-distance missions while maintaining efficient flight performance and control.
Implementation Method 1
at least three lift and propulsion rotors driven in rotation by at least three independent electric motors
Implementation Method 2
to achieve their propulsion and their lift, such drones have a lift assembly formed by these at least three rotors
Implementation Method 3
The mobile portions of the two half-wings of the drone are arranged according to a pivot-type connection with respect to the support structure
Data Source
Figure 1~3
Figure 4~6
Figure 7~9
AI summary
The present invention relates to a Drone (1) comprising a supporting structure (2), at least three rotors (3-6) for lift and propulsion and a control system (7) for delivering at least one electrical power supply to at least three electric motors (8) driving in rotation respectively said at least three rotors (3-6), said at least three rotors (3-6) being spaced longitudinally and transversely side by side, characterized in that said drone (1) comprises: • a wing (9) comprising two half-wings (10), symmetrical with respect to an anteroposterior plane of symmetry P of said drone (1), intended at least to increase the lift of said drone (1),each of said two half-wings (10) comprising at least one movable portion (11) capable of moving relative to said supporting structure (2) of said drone (1) along at least one first degree of freedom in rotation about a first axis of rotation parallel to a longitudinal direction X of said drone (1), • two first electric actuators allowing each to move said movable portion (11) of one of said two half-wings (10).