CN217260638U

CN217260638U - But unmanned aerial vehicle's quick detach formula folding wing and unmanned aerial vehicle

Info

Publication number: CN217260638U
Application number: CN202122476866.8U
Authority: CN
Inventors: 顾勇涛; 王友聪; 王一飞; 江峰; 邓富强; 刘文辉
Original assignee: Jiangsu Hengrui Aviation Industry Co ltd
Current assignee: Jiangsu Hengrui Aviation Industry Co ltd
Priority date: 2021-10-14
Filing date: 2021-10-14
Publication date: 2022-08-23
Anticipated expiration: 2031-10-14

Abstract

The utility model discloses a quick-release type foldable wing of an unmanned aerial vehicle, which comprises a middle wing skin (1), a central wing reinforcing rib (7), a folding wing (2), a folding wing reinforcing rib (3), a first carbon fiber tube (5) and a second carbon fiber tube (6) which are longitudinally and symmetrically arranged along the middle wing skin (1), wherein the first carbon fiber tube (5) and the second carbon fiber tube (6) are detachably fixed on the central wing reinforcing rib (7) through segmented splicing; the folding wing (2) is connected with the first carbon fiber tube (5) and the second carbon fiber tube (6) through a web plate of the folding wing reinforcing rib (3), and a turning hinge (4) is arranged at the connection position; the folding wing reinforcing rib (3) is fixed at one end of the folding wing (2) close to the middle wing skin (1).

Description

But unmanned aerial vehicle's quick detach formula folding wing and unmanned aerial vehicle

Technical Field

The utility model belongs to unmanned aerial vehicle makes the field, concretely relates to collapsible wing of unmanned aerial vehicle's quick detach formula.

Background

The structural design of the unmanned aerial vehicle composite material meets the performance requirements, the specified load condition, the environmental conditions, the structural geometric shape and the size limit of the structure according to the use target and various indexes of an airplane; typically including pneumatic requirements, quality requirements, manufacturability requirements, maintenance requirements, etc.; these requirements are often conflicting and interrelated. The unmanned aerial vehicle compound material structural design key points need consider following several: the design in the aspects of static strength, rigidity and stability of the structure is met; fatigue/durability, damage tolerance and kinetic design; maintainability, manufacturability and use environment requirements. Composite materials differ significantly from metallic materials in terms of performance, failure mode, durability and damage tolerance mechanisms, manufacturing processes, quality control, etc., and therefore require expertise, experience, and careful trade-offs.

Because the fuselage and the span of the medium-large unmanned aerial vehicle are very long, the transportation space of a common truck cannot be met. Therefore, based on transportation needs, it is often necessary to make folding or quick release designs that are quickly assembled after reaching the destination, or prior to flight. And traditional aircraft structural design scheme can't satisfy wing folding, quick detach requirement simultaneously, guarantees to pass power and continuous and structural strength.

Disclosure of Invention

In order to overcome the deficiencies in the prior art, the utility model provides a, concrete technical scheme is as follows: a quick-release type foldable wing of an unmanned aerial vehicle comprises a middle wing skin 1, a central wing reinforcing rib 7, a folding wing 2, a folding wing reinforcing rib 3, a first carbon fiber tube (5) and a second carbon fiber tube (6) which are longitudinally and symmetrically arranged along the middle wing skin 1, wherein the first carbon fiber tube (5) and the second carbon fiber tube (6) are detachably fixed on the central wing reinforcing rib 7 through segmented splicing; the folding wing 2 is connected with a first carbon fiber tube (5) and a second carbon fiber tube (6) through a web plate of the folding wing reinforcing rib 3, and a turning hinge 4 is arranged at the connection position; the folding wing reinforcing rib 3 is fixed at one end of the folding wing 2 close to the middle wing skin 1. Further, the first carbon fiber tube (5) is thicker than the second carbon fiber tube (6).

The length ratio of the middle wing skin 1 to the folding wings 2 is 0.45-0.5.

The folding wings 2 are hollow shells and integrally formed skin shells. Furthermore, the tail edge of the folding wing 2 is provided with an aileron 8 for adjusting the lifting force.

The thickness of the main body of the middle wing skin 1 is 1 mm.

The thickness of the joint of the middle wing skin 1 and the central wing reinforcing rib (7), namely the root reinforcing area, is 1.5 mm.

The middle wing skin (1) is connected with the central wing reinforcing rib (7) through a connecting fastener (9), and the connecting fastener (9) is formed by supporting plate nuts and matched bolts.

The detachable folding wings are symmetrically arranged on two sides of the unmanned aerial vehicle body, and the number of the wings is even.

The outer wing load mainly comprises bending and torsion generated by aerodynamic lift, the concentrated lift of the propeller can be borne on a wing-hung propeller unmanned aerial vehicle under the vertical lifting working condition, the root of the wing is connected to the central wing of the vehicle body, and the whole wing is equivalent to a cantilever beam. The internal force generated by the torsional deformation is born by the closed section box section separated by the wing rib, which is a traditional design mode, and the utility model is not changed; whereas bending deformation is mainly borne by the massive spar in conventional designs: the web mainly bears bending shearing force, and the edge strip mainly bears bending axial force. And medium-sized unmanned aerial vehicle sets up traditional spar to resist the efficiency of bending not high because the wing section height is low. Unmanned aerial vehicle has strict requirement to structural weight, can not set up complicated redundant power transmission mechanism, need design the power transmission route ingeniously, has both satisfied the requirement of quick dismantlement, also can distribute the aircraft main load.

So the utility model discloses in, use composite material carbon fiber pipe to replace traditional spar, do not link to each other with the covering. The folding wings are designed as hollow shells, transferring the load to the carbon fiber tubes through the end ribs and the flip hinges. Therefore, the carbon fiber tube only shares the bending load of the folding wing part (outer section), hardly bears the bending axial force of the fixed wing (middle section), and only bears the bending shear force, so that the carbon fiber tube can achieve the purposes of weight reduction and easy disassembly. And the bending axial force of the middle section is mainly borne by the middle section skin, so that the thickness of the middle section skin and the connecting area of the middle section skin and the central wing reinforcing rib is properly thickened.

Simultaneously, because unmanned aerial vehicle's user demand, whole wing will be dismantled from the fuselage fast conveniently. Therefore, the middle wing skin is connected with the reinforcing rib of the central wing and the fuselage skin by a small amount of supporting plate nuts and bolts, and the middle wing skin can be conveniently detached from the outside by using a screwdriver. The carbon fiber pipe is inserted in a segmented mode and can be conveniently drawn out.

The utility model discloses under the prerequisite of guaranteeing wing biography power and structural strength, through the segmentation partial shipment weight has been alleviateed. On the premise of ensuring the force transmission and the structural strength of the wings, the design is convenient and quick to disassemble through skin overlapping and carbon fiber pipe splicing.

Drawings

Fig. 1 is a schematic view of embodiment 1 of the present invention.

Wherein: 1-a mid-wing skin; 2-folding wings; 3-folding wing reinforcing ribs; 4-turning over the hinge; 5-a first carbon fiber tube; 6-a second carbon fiber tube; 7-center wing stiffener; 8-ailerons; 9-connecting the fasteners.

Detailed Description

Example 1

As shown in fig. 1, a fast-dismantling foldable wing of an unmanned aerial vehicle comprises a middle wing skin 1, a central wing reinforcing rib 7, a folding wing 2, a folding wing reinforcing rib 3, a first carbon fiber tube 5 and a second carbon fiber tube 6, wherein the first carbon fiber tube 5 and the second carbon fiber tube 6 are longitudinally and symmetrically arranged along the middle wing skin 1, and are detachably fixed on the central wing reinforcing rib 7 through segmented insertion; the folding wing 2 is connected with a first carbon fiber tube 5 and a second carbon fiber tube 6 through a web plate of the folding wing reinforcing rib 3, and a turning hinge 4 is arranged at the connection part; the folding wing reinforcing rib 3 is fixed at one end of the folding wing 2 close to the middle wing skin 1. The length ratio of the middle wing skin 1 to the folding wing 2 is 0.45, the thickness of the main body of the middle wing skin 1 is 1mm, and the thickness of the joint of the middle wing skin 1 and the central wing reinforcing rib 7, namely the root reinforcing area, is 1.5 mm. The folding wing 2 is a hollow shell and is an integrally formed skin shell.

Example 2

Unlike embodiment 1, the length ratio of the middle wing skin 1 and the folded wing 2 is 0.5.

Claims

1. The fast-dismounting foldable wing of the unmanned aerial vehicle comprises a middle wing skin (1), a central wing reinforcing rib (7), and is characterized by further comprising folding wings (2), folding wing reinforcing ribs (3), a first carbon fiber tube (5) and a second carbon fiber tube (6) which are longitudinally and symmetrically arranged along the middle wing skin (1), wherein the first carbon fiber tube (5) and the second carbon fiber tube (6) are detachably fixed on the central wing reinforcing rib (7) through segmented splicing; the folding wing (2) is connected with the first carbon fiber tube (5) and the second carbon fiber tube (6) through a web plate of the folding wing reinforcing rib (3), and a turning hinge (4) is arranged at the connection position; the folding wing reinforcing rib (3) is fixed at one end of the folding wing (2) close to the middle wing skin (1), and the folding wing (2) is a hollow shell.

2. The fast-release foldable wing of the unmanned aerial vehicle as claimed in claim 1, wherein the length ratio of the middle wing skin (1) to the folding wing (2) is 0.45-0.5.

3. The fast-release foldable wing of an unmanned aerial vehicle according to claim 1, characterized in that the folding wing (2) is embodied as an integrally formed skin shell.

4. The fast-release foldable wing of unmanned aerial vehicle according to claim 1, characterized in that the thickness of the middle wing skin (1) body is 1 mm.

5. The fast-release foldable wing of unmanned aerial vehicle according to claim 4, characterized in that the thickness of the junction of the middle wing skin (1) and the central wing stiffener (7) is 1.5 mm.

6. The fast-release foldable wing of an unmanned aerial vehicle according to claim 1, characterized in that the middle wing skin (1) and the central wing reinforcing rib (7) are connected by a connecting fastener (9), and the connecting fastener (9) is composed of a supporting plate nut mating bolt.

7. An unmanned aerial vehicle, characterized in that, the quick-release foldable wings of the unmanned aerial vehicle as claimed in any one of claims 1-6 are symmetrically arranged on two sides of the fuselage.