CN217893206U - Wing folding, automatic unfolding and locking device of fixed-wing unmanned aerial vehicle - Google Patents
Wing folding, automatic unfolding and locking device of fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN217893206U CN217893206U CN202220376340.4U CN202220376340U CN217893206U CN 217893206 U CN217893206 U CN 217893206U CN 202220376340 U CN202220376340 U CN 202220376340U CN 217893206 U CN217893206 U CN 217893206U
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Abstract
The utility model discloses a fixed wing unmanned aerial vehicle wing is folding, expand automatically and locking device belongs to unmanned aerial vehicle design and manufacturing field. The folding mechanism comprises a rotary locking mechanism, a folding driving mechanism, a return-preventing limiting mechanism and a return mechanism, wherein the rotary locking mechanism, the folding driving mechanism and the return mechanism are coaxially arranged; the folding driving mechanism provides driving force for folding or automatically unfolding between the wing fixing part and the folded part; the rotary locking mechanism is used for controlling the folding or unfolding angle of the folding driving mechanism; the anti-return limiting mechanism is used for limiting the operation of the rotary locking mechanism; the return mechanism is used for controlling the rotary locking mechanism to return. The wing is folded, so that the space and ground occupancy rate are greatly reduced, high-density cluster launching can be further met, and the launching efficiency is improved.
Description
Technical Field
The utility model relates to a controlling means of aircraft wing specifically says that a fixed wing unmanned aerial vehicle wing is folding, automatic expandes and locking device, belongs to unmanned aerial vehicle design and manufacturing field.
Background
At present, the take-off state wings of the fixed-wing unmanned aerial vehicle mainly comprise a full-span state and a folded state. The full span state is widely used, the structure is simple and reliable, the technical state is mature, but obvious defects such as large space volume occupancy rate exist. The folding wings can effectively reduce the space requirement of the unmanned aerial vehicle, more unmanned aerial vehicle clusters can be arranged in a smaller space, and the unmanned aerial vehicle clusters can be launched quickly. However, compared with a full-span long wing, the folding wing has the obvious defects of complex structure, low reliability, high technical difficulty and the like.
The driving for folding and unfolding the wings generally comprises motor driving, hydraulic driving, elastic component driving and the like, the motor and the hydraulic driving are often used for large-load wings such as carrier-based aircrafts and fighters, the unfolding time is long, and the structure is relatively complex. The small unmanned aerial vehicle can rapidly take off, and comprises a target drone, various projectiles and the like, the wing surfaces of the small unmanned aerial vehicle are often required to be rapidly unfolded in place in a short time by using an elastic element, and the small unmanned aerial vehicle can be reliably locked. In recent years, the demand of the market for cluster launching of unmanned aerial vehicles, especially target plane products is gradually increased, the old-fashioned launching mode also uses a full-wing structure, the preparation time is long, the space and ground occupancy rate is high, the unmanned aerial vehicle cannot be competent for high-density cluster launching, the efficiency is low, and the current market demand cannot be met.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that overcome prior art defect, provide a space and ground occupancy are low, can realize that the fixed wing unmanned aerial vehicle wing of high density cluster transmission is folding, automatic expansion and locking device.
In order to solve the technical problem, the wing folding, automatic unfolding and locking device for the fixed-wing unmanned aerial vehicle comprises a rotary locking mechanism, a folding driving mechanism, a return-preventing limiting mechanism and a return mechanism, wherein the rotary locking mechanism, the folding driving mechanism and the return mechanism are coaxially arranged;
the folding driving mechanism provides driving force for folding or automatic unfolding between the wing fixing part and the folded part;
the rotary locking mechanism is used for controlling the folding or unfolding angle of the folding driving mechanism;
the anti-return limiting mechanism is used for limiting the operation of the rotary locking mechanism;
and the return mechanism is used for controlling the rotary locking mechanism to return.
The utility model discloses in, rotatory locking mechanism includes a pair of face of each other cooperation and can follow the locking piece of pivot axial float.
The utility model discloses in, be two step contacts that are parallel to each other between the fitting surface of two lock pieces.
The utility model discloses in, be two gradually the alternating expression contact between the fitting surface of two locking pieces.
The utility model discloses in, rotatory locking mechanical system is two, is located folding actuating mechanism's front and back both sides respectively.
The utility model discloses in, folding actuating mechanism takes place the component for the moment of torsion, and wing fixed part is connected to moment of torsion emergence component one end, and the wing is connected by the folding part to the other end.
The utility model discloses in, return mechanism is the spring.
The utility model discloses in, prevent returning stop gear includes non return round pin and pressure spring, and the non return round pin supports the pressure spring.
The utility model discloses in, rotatory locking mechanism, folding actuating mechanism and return mechanism install in the pivot.
In the utility model, sleeves are arranged between the folding driving mechanism and the rotating shaft as well as between the return mechanism and the rotating shaft; and a bearing is arranged between the rotary locking mechanism and the rotating shaft.
The beneficial effects of the utility model reside in that: (1) The wing can be directly additionally arranged on a given wing section, namely the folding, automatic unfolding and locking functions of the wing can be realized, the application range is wide, and a large number of fixed wings with different structures can be compatible; the wing folding greatly reduces the space and has high ground occupancy rate, thereby meeting the requirement of high-density cluster emission and improving the emission efficiency; (2) The wing aerodynamic lift force can be utilized to accelerate the unfolding of the wing, the aerodynamic resistance in flight is also beneficial to the locking of the device, and the secondary locking can be effectively realized under the action of the lift force and the resistance, so that the wing rebound is prevented; (3) The device has simple structure, convenient assembly and low cost, and can effectively utilize the aerodynamic lift force and the resistance of the wings to provide external force for unfolding and locking the wings, thereby further improving the reliability of the device; (4) The structure is convenient to disassemble, and the rotary locking structure or the torque element can be replaced to achieve the functions of improving the locking efficiency and adjusting the unfolding time; (5) The matching surfaces of the two locking pieces are in two gradually staggered contact, so that the stability of folding or automatic unfolding when the axial stroke between the wing fixing part and the folded part is too large can be ensured.
Drawings
FIG. 1 is a schematic structural view of a wing folding, automatic unfolding and locking device of a fixed-wing UAV;
FIG. 2 is a schematic view of a partial structural assembly of a wing folding, automatic unfolding and locking device of a fixed wing drone;
FIG. 3 is a top view of a wing folding device;
FIG. 4 is a schematic view of the rotational locking arrangement of FIG. 1;
FIG. 5 is a schematic view of a rotational locking arrangement of FIG. 2;
FIG. 6 is a schematic view of a wing unlocking and folding process;
FIG. 7 is a schematic diagram of an automatic wing deployment and locking process.
In the figure, 1-outer wing connecting reinforcing rib, 2-inner wing connecting reinforcing rib, 3-rotating shaft, 4-fastening pin, 5-compression spring, 6-check pin cover plate, 7-check pin, 8-check pin compression spring, 9-torsion spring cover plate, 10-rotation locking structure, 11-torsion spring, 12-compression spring sleeve, 13-torsion spring sleeve, 14-bearing, 15-wing fixing part and 16-wing folded part.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 to 3, the wing folding, automatic unfolding and locking device of the fixed-wing unmanned aerial vehicle in the embodiment includes an outer wing connecting reinforcing rib 1, an inner wing connecting reinforcing rib 2, a rotating shaft 3, a pressure spring 5, a rotation locking structure 10 and a torsion spring 11.
The outer wing connecting and reinforcing rib 1 is used for being connected with a folded part 16 of the wing, and the form is determined by the wing section and the wing framework together. The inner wing connecting and reinforcing rib 2 is used for being connected with the wing fixing part 15, and the form is determined by the wing section and the wing framework together.
The rotating shaft 3 is arranged on the inner wing connecting reinforcing rib 2 through a fastening pin 4, and the rotating shaft 3 is positioned between the outer wing connecting reinforcing rib 1 and the inner wing connecting reinforcing rib 2. The rotating shaft 3 is respectively provided with a compression spring sleeve 12, a torsion spring sleeve 13 and two rotation locking structures 10.
The torsion spring sleeve 13 is sleeved with a torsion spring 11, and two sides of the torsion spring 11 are respectively connected and fixed with the outer wing connecting reinforcing rib 1 and the inner wing connecting reinforcing rib 2 through a torsion spring cover plate 9.
The two rotation locking structures 10 are located at the front and rear ends of the torsion spring 11, and can rotate around the rotating shaft 3. Bearings 14 are disposed between the rotation lock structure 10 and the rotating shaft 3 to improve sensitivity.
The compression spring 5 is sleeved on the compression spring sleeve 12 and is positioned in front of the rotation locking structure 10 at the front end of the torsion spring 11.
Be equipped with one on the inner wing connection stiffening rib 2 and hold the chamber, hold the outside that the chamber is located pressure spring 5 rear portion, hold the intracavity and set up check pin 7 and check pin pressure spring 8, check pin 7 supports check pin pressure spring 8, and 6 covers of check pin apron are holding on the chamber and fixed. The top of the check pin 7 penetrates through a groove in the accommodating cavity, and the check pin 7 can extend out of the inner wing connecting reinforcing rib 2 to block the rotary locking structure 10 from advancing under the action of the check pin pressure spring 8, so that the pressure spring 5 is limited from being compressed forwards. After the check pin 7 is retracted inward, the outer wing connecting reinforcing rib 1 can move forward and rotate relative to the inner wing connecting reinforcing rib 2 to a certain extent.
As shown in fig. 4, the rotation locking structure 10 is a pair of metal locking members that are engaged with each other in a surface-to-surface manner and can axially move along the rotating shaft 3, and the engaging surface of the metal locking member is divided into two semicircular shapes, and a step structure is formed between the two semicircular shapes. During assembly, two parallel step contacts are formed between matching surfaces of the two metal locking pieces.
In another embodiment, as shown in fig. 5, the mating surface of the metal locking member in the rotation locking structure 10 is divided into two semicircular parts, and the height of the two semicircular parts gradually rises in opposite directions. During assembly, two gradually staggered contacts are formed between the matching surfaces of the two locking pieces. Therefore, the outer wing connecting and reinforcing rib 1 can be ensured to be stably transited to the axial displacement in the rotating process relative to the inner wing connecting and reinforcing rib 2, and the structure is required to be used when the axial stroke is overlarge.
As shown in fig. 6, before the unmanned aerial vehicle takes off, the folding operation of the wings is performed manually on the ground, and the specific steps include:
(1) The check pin 7 is pulled back manually to release the axial displacement limitation between the outer wing connecting reinforcing rib 1 and the inner wing connecting reinforcing rib 2;
(2) Manually poking the outer wing connecting reinforcing rib 1 forwards to separate the matching surfaces of the locking structure 10;
(3) And external force is used for overcoming the torque of the torsion spring 11, so that the outer wing connecting and reinforcing rib 1 rotates relative to the inner wing connecting and reinforcing rib 2, and the rotation angle is determined by the folding angle of the unmanned aerial vehicle. After the wing folding is finished, the wing folding state is restrained by the unmanned aerial vehicle launching device.
As shown in fig. 7, after the unmanned aerial vehicle takes off, the target drone is separated from the launching device, the constraint of the launching device on the wings is removed, the wings are automatically unfolded and locked, and the method specifically comprises the following steps:
(1) The outer wing connecting reinforcing rib 1 is unfolded under the combined action of the torsion spring 11 and the aerodynamic lift force of the outer wing;
(2) After the wings are unfolded to be in a straight state, the outer wing connecting reinforcing rib 1 axially moves backwards relative to the inner wing connecting reinforcing rib 2 under the combined action of the pressure spring 5 and the aerodynamic resistance of the outer wing until the matching surfaces of the locking structures 10 are completely attached to each other;
(3) After the locking structure 10 is matched and reaches the limit, the check pin 7 is pushed out under the action of the check pin pressure spring 8 to fill the gap between the inner wing connecting reinforcing rib and the locking structure 10, so that the axial movement of the outer wing connecting reinforcing rib 1 is limited, and the locking is realized.
The utility model provides a schematic structural diagram of a wing folding, automatic unfolding and locking device of a fixed-wing unmanned aerial vehicle; while there are many ways to implement the technical solution and methods, which are the preferred embodiments of the present invention, it should be noted that those skilled in the art can make various modifications and decorations without departing from the principle of the present invention, and these modifications and decorations should be regarded as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.
Claims (10)
1. The utility model provides a fixed wing unmanned aerial vehicle wing is folding, automatic expandes and locking device which characterized in that: the folding mechanism comprises a rotary locking mechanism, a folding driving mechanism, an anti-return limiting mechanism and a return mechanism, wherein the rotary locking mechanism, the folding driving mechanism and the return mechanism are coaxially arranged;
the folding driving mechanism provides driving force for folding or automatic unfolding between the wing fixing part and the folded part;
the rotary locking mechanism is used for controlling the folding or unfolding angle of the folding driving mechanism;
the anti-return limiting mechanism is used for limiting the operation of the rotary locking mechanism;
and the return mechanism is used for controlling the rotary locking mechanism to return.
2. The fixed-wing drone wing folding, automatic deployment and locking device of claim 1, characterized in that: the rotary locking mechanism comprises a pair of locking pieces which are mutually matched in surface and can axially move along the rotating shaft.
3. The fixed-wing drone wing folding, automatic deployment and locking device of claim 2, characterized in that: the matching surfaces of the two locking pieces are in stepped contact with each other in parallel.
4. The fixed-wing drone wing folding, automatic deployment and locking device of claim 2, characterized in that: the matching surfaces of the two locking pieces are in two contact in a gradually staggered manner.
5. The fixed-wing drone wing folding, automatic deployment and locking device of any one of claims 1 to 4, wherein: the two rotary locking mechanisms are respectively positioned at the front side and the rear side of the folding driving mechanism.
6. The fixed-wing drone wing folding, automatic deployment and locking device of any one of claims 1 to 4, characterized in that: the folding driving mechanism is a torque generating element, one end of the torque generating element is connected with the fixed part of the wing, and the other end of the torque generating element is connected with the folded part of the wing.
7. The fixed-wing drone wing folding, automatic deployment and locking device of any one of claims 1 to 4, characterized in that: the return mechanism is a spring.
8. The fixed-wing drone wing folding, automatic deployment and locking device of any one of claims 1 to 4, wherein: the anti-return limiting mechanism comprises a check pin and a pressure spring, and the check pin abuts against the pressure spring.
9. The fixed-wing drone wing folding, automatic deployment and locking device of any one of claims 1 to 4, characterized in that: the rotary locking mechanism, the folding driving mechanism and the return mechanism are arranged on the rotating shaft.
10. The fixed-wing drone wing folding, automatic deployment and locking device of claim 9, wherein: sleeves are arranged between the folding driving mechanism and the rotating shaft as well as between the return mechanism and the rotating shaft; and a bearing is arranged between the rotary locking mechanism and the rotating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220376340.4U CN217893206U (en) | 2022-02-23 | 2022-02-23 | Wing folding, automatic unfolding and locking device of fixed-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220376340.4U CN217893206U (en) | 2022-02-23 | 2022-02-23 | Wing folding, automatic unfolding and locking device of fixed-wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217893206U true CN217893206U (en) | 2022-11-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220376340.4U Active CN217893206U (en) | 2022-02-23 | 2022-02-23 | Wing folding, automatic unfolding and locking device of fixed-wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217893206U (en) |
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2022
- 2022-02-23 CN CN202220376340.4U patent/CN217893206U/en active Active
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