CN218703844U

CN218703844U - Unmanned aerial vehicle

Info

Publication number: CN218703844U
Application number: CN202222279879.0U
Authority: CN
Inventors: 贺军; 房佳琦; 周雷海; 邓登宝
Original assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Current assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Priority date: 2022-08-26
Filing date: 2022-08-26
Publication date: 2023-03-24
Anticipated expiration: 2032-08-26

Abstract

The utility model provides an unmanned aerial vehicle comprises a fuselage and a wing which are connected with each other, the unmanned aerial vehicle also comprises a locking mechanism, the locking mechanism comprises a base, a rotating seat, an elastic part, a first locking part and a second locking part, the base is assembled on the fuselage, the rotating seat is connected with the base, the first end of the elastic part is connected with the base, the second end of the elastic part is connected with the rotating seat, the first locking part is assembled on the rotating seat, and the second locking part is assembled on the wing; when the wing is in the folded position, the first locking piece and the second locking piece are connected with each other; when the wings are in the unfolding position, the first locking piece and the second locking piece are separated from each other, and the elastic piece drives the rotating seat to rotate into the airplane body. When the unmanned aerial vehicle needs to make the wings be in the unfolding position, the first locking piece and the second locking piece are separated from each other, and the elastic piece drives the rotating seat to rotate into the fuselage, so that the locking mechanism is prevented from damaging the aerodynamic appearance of the fuselage of the unmanned aerial vehicle due to the fact that the locking mechanism is exposed out of the fuselage.

Description

Unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to unmanned aerial vehicle.

Background

At present, along with the development of unmanned aerial vehicles, unmanned aerial vehicles are more and more widely used in military and civil fields. And in order to reach the purpose that reduces the loading space, more and more unmanned aerial vehicles adopt folding fin structure. However, no matter which folding method is adopted, a reliable locking mechanism is needed to lock the folded tail wings. If the tail wing cannot be reliably locked after being folded, the tail wing can be uncontrollably unfolded or loosened under the interference of external factors such as overload, vibration, airflow and the like, and collides with a machine body, a transport box and a carrier, so that the task cannot be continued.

Present unmanned aerial vehicle fin folding locking mechanical system all needs control locking such as electric putter, electromagnetic drive, piezoelectric actuator, and current locking mechanical system weight is heavy, the space that occupies is big, and the structure exposes outside the organism to need additionally increase the shape preserving swell on the organism, consequently, destroyed unmanned aerial vehicle's the pneumatic appearance of fuselage.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an avoid destroying unmanned aerial vehicle of the pneumatic appearance of unmanned aerial vehicle's fuselage.

In order to achieve the above object, the utility model provides an unmanned aerial vehicle includes fuselage and wing that interconnect, and unmanned aerial vehicle still includes locking mechanical system, and locking mechanical system includes base, rotation seat, elastic component, first locking piece and second locking piece, and the base assembles in the fuselage, rotates the seat and connects in the base, and the first end of elastic component is connected in the base, and the second end of elastic component is connected in the rotation seat, and first locking piece assembles in the rotation seat, and the second locking piece assembles in the wing; when the wing is in the folded position, the first locking element and the second locking element are connected with each other; when the wings are in the unfolding position, the first locking piece and the second locking piece are separated from each other, and the elastic piece drives the rotating seat to rotate into the airplane body.

By the above scheme, when the unmanned aerial vehicle needs to make the wings be in the unfolding position, the first locking piece and the second locking piece are separated from each other, and the elastic piece drives the rotating seat to rotate into the fuselage, so that the locking mechanism is prevented from damaging the aerodynamic appearance of the fuselage of the unmanned aerial vehicle due to the fact that the locking mechanism is exposed out of the fuselage.

In some embodiments, the first locking member is an explosive bolt.

In some embodiments, the second lock is an explosive bolt release pin.

In some embodiments, the locking mechanism further comprises a rotating shaft, and the rotating shaft passes through the base and the rotating seat.

In some embodiments, the base includes a positioning portion and a connecting portion, the positioning portion being assembled to the body, the connecting portion protruding from an inner end surface of the positioning portion toward an inner side of the body; the quantity of connecting portion is two, and two connecting portion are mutual symmetrical arrangement, and each connecting portion are equipped with first through-hole, and the pivot is inserted and is located connecting portion.

In some embodiments, the base includes a first abutting portion protruding from the inner end surface of the positioning portion to the inner side of the body, and the first end of the elastic member is inserted into the first abutting portion.

In some embodiments, the rotating seat comprises a main portion and an engaging portion which are connected with each other, the rotating shaft is inserted into the main portion, and the first locking member is fixedly connected to the engaging portion.

In some embodiments, the primary section comprises an end piece and a check arm connected to each other, the end piece and the interface being located outside the fuselage when the wing is in the folded position;

when the wing is in the unfolding position, the elastic piece drives the end block and the joint part to rotate into the fuselage, and the limiting arm abuts against the inner end face of the positioning part.

In some embodiments, the locking mechanism includes a third lock, the third lock passing through the airfoil, the third lock coupled to the second lock; the elastic part is a torsion spring.

Drawings

The invention is further described with the aid of the accompanying drawings, in which, however, the embodiments do not constitute any limitation to the invention, and for those skilled in the art, other drawings may be obtained without inventive effort from the following drawings.

Figure 1 is the utility model relates to a local structure chart when the wing of unmanned aerial vehicle embodiment is in folding position.

Figure 2 is a partial structure view of a locking mechanism when the wings of an unmanned aerial vehicle embodiment are in a folded position.

Figure 3 is a partial structure view of a locking mechanism of an unmanned aerial vehicle embodiment when the wings are in the deployed position.

Figure 4 is a structure diagram of a rotating seat of an unmanned aerial vehicle embodiment.

Figure 5 is a partial structure view of a locking mechanism when the wing of an unmanned aerial vehicle embodiment is in the deployed position.

Figure 6 is a partial structure view of a wing of an unmanned aerial vehicle embodiment of the present invention in an extended position.

The reference numbers illustrate: a base 1; a rotating seat 2; an elastic member 3; a first locking member 4; a second locking member 5; a rotating shaft 6; a wing 7; a body 8; a third locking piece 9; a folding assembly 10; a positioning portion 11; a connecting portion 12; a first abutting portion 13; a main section 14; a joint portion 15; an end block 16; a stopper arm 17; a first side 18.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.

Referring to fig. 1 to 3, the unmanned aerial vehicle that this embodiment provided includes locking mechanical system, locking mechanical system includes base 1, rotate seat 2, elastic component 3, first locking piece 4 and second locking piece 5, unmanned aerial vehicle still includes interconnect's fuselage 8 and wing 7, base 1 assembles in fuselage 8, it connects in base 1 to rotate seat 2, the first end of elastic component 3 is connected in base 1, the second end of elastic component 3 is connected in rotating seat 2, first locking piece 4 assembles in rotating seat 2, second locking piece 5 assembles in wing 7.

In this embodiment, the base 1 and the rotating base 2 are respectively an integrally formed component, the elastic member 3 is a torsion spring, the first locking member 4 is an explosive bolt, and the second locking member 5 is an explosive bolt separation pin.

The locking mechanism further comprises a rotating shaft 6, and the rotating shaft 6 penetrates through the base 1 and the rotating seat 2.

The base 1 includes a positioning portion 11 and a connecting portion 12, the positioning portion 11 is detachably fixed to the body 8 by screwing, and the connecting portion 12 protrudes from an inner end surface of the positioning portion 11 toward the inner side of the body 8.

The number of connecting portion 12 is two, and two connecting portions 12 are mutual symmetrical arrangement, and each connecting portion 12 is equipped with first through-hole, and pivot 6 inserts the first through-hole of locating connecting portion 12.

The base 1 includes a first abutting portion 13, the first abutting portion 13 protrudes from the inner end surface of the positioning portion 11 to the inner side of the body 8, and the first end of the elastic member 3 is inserted into the first abutting portion 13.

Referring to fig. 4, the rotating base 2 includes a main portion 14 and a joint portion 15 that are connected to each other, the rotating shaft 6 is inserted in the main portion 14, the first locking member 4 is fixedly connected to the joint portion 15, the joint portion 15 is a semi-waist-shaped arrangement, the joint portion 15 is provided with a positioning through hole, the first locking member 4 and the positioning through hole are in interference fit to realize that the first locking member 4 is fixedly connected to the joint portion 15, and the positioning through hole is a circular hole.

The main section 14 comprises an end piece 16 and a retaining arm 17 connected to each other, the end piece 16 and the joint 15 being located outside the fuselage 8 when the wing 7 is in the folded position; when the wing 7 is in the unfolding position, the elastic piece 3 drives the end block 16 and the joint part 15 to rotate into the fuselage 8, and the limiting arm 17 abuts against the inner end surface of the positioning part 11.

The number of the limiting arms 17 is two, the two limiting arms 17 are symmetrically arranged, each limiting arm 17 is provided with a second through hole, the rotating shaft 6 is inserted into the second through hole of the limiting arm 17, the first through hole and the second through hole are coaxially arranged, and the first through hole and the second through hole are respectively round holes.

The second end of the elastic member 3 is inserted into one of the stopper arms 17, or the second end of the elastic member 3 is inserted into the engaging portion 15.

The main part 14 comprises a first side 18 and a second side, the first side 18 comprising at least the rear side of the end piece 16 and the second side comprising at least a part of the rear side of the retainer arm 17, the first side 18 and the second side being parallel to each other. In this embodiment the first side 18 comprises the rear side of the end block 16 and a part of the rear side of the retainer arm 17, and the second side comprises another part of the rear side of the retainer arm 17.

The locking mechanism comprises a third locking element 9, the third locking element 9 passing through the wing 7, the third locking element 9 being connected to the second locking element 5. In this embodiment, the third locking member 9 is a bolt, and the third locking member 9 is screwed into a threaded hole of the wing 7.

The folding assembly 10 can also realize the mutual rotating connection between the fuselage 8 and the wings 7, the folding assembly 10 can use a known pivot hinge structure, when the first locking piece 4 and the second locking piece 5 are separated from each other, the wings 7 are unfolded under the action of the folding assembly 10, and the wings 7 are the empennage of the unmanned aerial vehicle.

Referring to fig. 1 and 2, when the wing 7 needs to be folded, the rotating base 2 is rotated to enable the first side surface 18 to abut against the base 1, the base 1 can limit the rotating base 2, then the wing 7 is rotated, the folding assembly 10 can enable the wing 7 to rotate relative to the fuselage 8, the wing 7 is provided with a groove for adapting to the second locking piece 5, after the wing 7 rotates until the second locking piece 5 abuts against the groove, the third locking piece 9 penetrates through the wing 7 and is in threaded connection with a threaded hole of the second locking piece 5, at the moment, the wing 7 is in a folding position, the locking mechanism locks the folding state of the wing 7, and the first locking piece 4 is connected with the second locking piece 5.

Referring to fig. 3 to 6, a known control system is used to energize a first locking member 4, because the first locking member 4 is an explosive bolt, the first locking member 4 can be separated from a second locking member 5 after being energized, an elastic member 3 drives a rotating base 2 to rotate, the rotating base 2 drives the first locking member 4 to rotate into a fuselage 8, a second side surface abuts against an inner end surface of a positioning portion 11, the rotating base 2 does not rotate any more, the first side surface 18 follows the fuselage 8, a wing 7 rotates and expands under the action of an explosive and folding assembly 10, the second locking member 5 and a third locking member 9 move synchronously with the wing 7, the locking mechanism provided in this embodiment unlocks the locking of the folded state of the wing, at this time, the wing 7 is in an expanded position, the first locking member 4 is separated from the second locking member 5, and the elastic member 3 drives the rotating base 2 to rotate into the fuselage 8.

Therefore, when the unmanned aerial vehicle needs to enable the wings 7 to be located at the unfolding position, the first locking piece 4 and the second locking piece 5 are separated from each other, and the elastic piece 3 drives the rotating seat 2 to rotate into the fuselage 8, so that damage to the aerodynamic shape of the fuselage 8 of the unmanned aerial vehicle due to the fact that the locking mechanism is exposed out of the fuselage 8 is avoided.

Moreover, the unlocking time of the locking mechanism provided by the embodiment is short, the first locking member 4 serving as an explosive bolt can be unlocked by explosion, an acting force along the unfolding direction of the wing 7 is applied to the wing surface of the wing 7, and the unfolding time of the wing 7 is further shortened.

Further, the locking mechanical system that this embodiment provided's structure is simple and convenient, weight is lighter, avoids leading to the trouble probability to increase because of the structure complication, reduces unmanned aerial vehicle's flight load, extension unmanned aerial vehicle's voyage.

In addition, first side 18 is along with the fuselage 8 type, further avoids destroying unmanned aerial vehicle's the pneumatic appearance of fuselage 8, prevents to cause the influence to unmanned aerial vehicle's pneumatic performance.

Importantly, the first locking piece 4 serving as an explosion bolt is adopted to perform reliable locking in transportation, storage and other work needing to enable the wing 7 to be in a folded state, and the locking structure is stable and reliable.

As an advantage, the locking mechanical system that this embodiment provided has cancelled electromagnetic drive, prevents to produce electromagnetic interference, reduces unmanned aerial vehicle and to the interference killing feature requirement of equipment, avoids unmanned aerial vehicle to take place the accident because of electromagnetic interference, guarantees unmanned aerial vehicle's stability, safe flight.

The terms "first", "second" are used for descriptive purposes only and are not to be understood as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.

In the present invention, unless otherwise explicitly specified or limited, the terms "connected" and "positioned" are to be understood broadly, and may be, for example, fixedly connected, clamped and positioned, detachably connected, or integrated; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.

Finally, it should be emphasized that the present invention is not limited to the above-described embodiments, but only to the preferred embodiments of the invention, and the invention is not limited to the above-described embodiments, and any modifications, equivalent replacements, improvements, etc. within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle, includes interconnect's fuselage and wing, its characterized in that:

the unmanned aerial vehicle further comprises a locking mechanism, wherein the locking mechanism comprises a base, a rotating seat, an elastic part, a first locking part and a second locking part, the base is assembled on the fuselage, the rotating seat is connected to the base, the first end of the elastic part is connected to the base, the second end of the elastic part is connected to the rotating seat, the first locking part is assembled on the rotating seat, and the second locking part is assembled on the wing;

the first locking member and the second locking member are interconnected when the wing is in the folded position;

when the wing is in the unfolding position, the first locking piece and the second locking piece are separated from each other, and the elastic piece drives the rotating seat to rotate into the fuselage.

2. A drone according to claim 1, characterised in that:

the first locking member is an explosive bolt.

3. A drone according to claim 2, characterised in that:

the second locking piece is an explosive bolt release pin.

4. A drone according to claim 3, characterized in that:

the locking mechanism further comprises a rotating shaft, and the rotating shaft penetrates through the base and the rotating seat.

5. A drone according to claim 4, characterised in that:

the base comprises a positioning part and a connecting part, the positioning part is assembled on the machine body, and the connecting part protrudes from the inner end surface of the positioning part to the inner side of the machine body;

the number of the connecting portions is two, the two connecting portions are symmetrically arranged, each connecting portion is provided with a first through hole, and the rotating shaft is inserted into the connecting portions.

6. A drone according to claim 5, characterised in that:

the base comprises a first abutting portion, the first abutting portion protrudes from the inner end face of the positioning portion to the inner side of the machine body, and the first end of the elastic piece is inserted into the first abutting portion.

7. A drone according to claim 6, characterised in that:

the rotating seat comprises a main portion and a joint portion which are connected with each other, the rotating shaft is inserted into the main portion, and the first locking piece is fixedly connected to the joint portion.

8. A drone according to claim 7, characterised in that:

the main part comprises an end block and a stop arm which are connected with each other,

the end block and the interface are located outside the fuselage when the wing is in the folded position;

9. A drone according to any one of claims 1 to 8, characterised in that:

the locking mechanism includes a third lock that passes through the wing, the third lock being connected to the second lock;

the elastic piece is a torsion spring.