CN221173156U - Folding wing for aircraft and aircraft - Google Patents

Abstract

The utility model provides a folding wing for an aircraft and the aircraft, which relate to the technical field of the aircraft and comprise the following components: the device comprises a support body, wherein one side of the support body is rotationally connected with a wing plate, a first elastic driving part is arranged between the support body and the wing plate, and the other side of the support body is used for being connected with an aircraft; the limiting body is in sliding connection with the supporting body, a first limiting part is arranged on the outer side of the limiting body, the first limiting part is matched with a first limiting groove on the wing plate and used for limiting the wing plate to rotate relative to the supporting body, and a second elastic driving part is arranged between the limiting body and the supporting body; the triggering part is connected with the limiting body and the supporting body before triggering and used for limiting the limiting body to move relative to the supporting body, and limiting the limiting body can be released after triggering; the folding wing device solves the problems that in the prior art, when a controllable power source is adopted by a folding wing on an aircraft, the structure is complex, the weight is large, the cost is high, when the controllable power source is not adopted, the unfolding moment of the wing plate cannot be controlled, and the use scene is limited.

Description

Folding wing for aircraft and aircraft

Technical Field

The utility model belongs to the technical field of aircrafts, and particularly relates to a folding wing for an aircraft and the aircraft.

Background

At present, the technology of folding wings of aircrafts at home and abroad is very mature, from a small unmanned aerial vehicle to a special aircraft, various folding wings are applied and developed to different degrees, and the folding wings have the advantages of higher reliability, practicability, economy and the like. However, there is still room for improvement in the existing folding wing of the hundred rod head. First, folding wings with controllable power source, such as: the folding wings taking the electric cylinder and the motor gear rack as power occupy larger space, have larger weight and higher cost, and bring corresponding defects to the overall design; secondly, the barrel type launching folding wing aircraft is represented, the folding wing aircraft is simple and reliable in structure and convenient to use, but the wing panels of the aircraft are unfolded immediately after being launched, the unfolding time of the wing panels cannot be controlled, and the use scene is limited to a certain extent.

Disclosure of utility model

The utility model aims to overcome the defects in the prior art, provides a folding wing for an aircraft and the aircraft, and solves the problems that the folding wing on the aircraft in the prior art is complex in structure, heavy in weight and high in cost when a controllable power source is adopted, the unfolding moment of a wing plate cannot be controlled when the controllable power source is not adopted, and the use scene is limited.

In order to achieve the above object, the present utility model provides a folding wing for an aircraft, comprising:

The device comprises a support body, wherein one side of the support body is rotatably connected with a wing plate, a first elastic driving part is arranged between the support body and the wing plate, the first elastic driving part can apply a first elastic force for expanding the wing plate, and the other side of the support body is used for being connected with an aircraft;

The limiting body is in sliding connection with the supporting body, a first limiting part is arranged on the outer side of the limiting body, the first limiting part is matched with a first limiting groove on the wing plate and used for limiting the wing plate to rotate relative to the supporting body, a second elastic driving part is arranged between the limiting body and the supporting body, and the second elastic driving part can apply a second elastic force to the limiting body to enable the limiting body to move relative to the wing plate so as to enable the first limiting part to deviate from the first limiting groove;

The triggering part is connected with the limiting body and the supporting body before triggering and is used for limiting the limiting body to move relative to the supporting body, and the limiting of the limiting body can be relieved after triggering of the triggering part.

Optionally, the triggering part is an explosion bolt, a first bolt hole and a second bolt hole are respectively arranged on the supporting body and the limiting body, and the explosion bolt is connected with the first bolt hole and the second bolt hole.

Optionally, the support body includes a plurality of backup pads, and a plurality of the backup pad is connected gradually and is formed annular structure, annular structure can overlap establish on the periphery of aircraft, and with the aircraft is connected.

Optionally, each of the two ends of the supporting plate are respectively provided with a connecting lug, a rotating shaft is arranged between the connecting lugs adjacent to each other of the supporting plates, and the wing plates are rotatably sleeved on the outer sides of the rotating shafts.

Optionally, a limiting block is arranged between the connecting lugs adjacent to the supporting plates and close to each other, and the limiting block is used for limiting the rotation of the wing plate after being unfolded so as to enable the wing plate to be kept in an unfolded state.

Optionally, a sliding groove is formed in the other side of the supporting body, the limiting body is embedded in the sliding groove in a sliding mode, and the first limiting portion is arranged on one side, close to the wing plate, of the limiting body.

Optionally, the outside of the spacing body is provided with second spacing portion, second spacing portion with first spacing portion is in respectively the both sides of pterygoid lamina, the both sides of pterygoid lamina are provided with respectively first spacing recess and second spacing recess, second spacing portion with the cooperation of second spacing recess, when first spacing portion embedding first spacing recess time second spacing portion with form first clearance between the pterygoid lamina, when trigger part releases to the restriction of the spacing body under the driving action of second elastic drive part, spacing relative the supporter removes for second spacing portion moves to being close to the direction of second spacing recess until embedding second spacing recess.

Optionally, the first spacing portion includes first connecting portion and first fixture block portion, first connecting portion with first fixture block portion connects and forms first L shape structure, the second spacing portion includes second connecting portion and second fixture block portion, the second connecting portion with second fixture block portion connects and forms second L shape structure, first fixture block portion with the second fixture block portion is the big outer end of inner little wedge, first spacing recess with the shape of second spacing recess respectively with first fixture block portion with the shape of second fixture block portion cooperatees.

Optionally, the first elastic driving component and the second elastic driving component are respectively a first torsion spring and a second torsion spring, two ends of the first torsion spring are respectively connected with the supporting body and the wing plate, and when the wing plate is in a folded state, the first torsion spring is in an energy storage state, two ends of the second torsion spring are respectively connected with the supporting body and the limiting body, and before the triggering component triggers, the second torsion spring is in an energy storage state.

The utility model also provides an aircraft comprising:

An aircraft body;

The folding wing for the aircraft is connected with the outer wall of the aircraft through the supporting body.

The utility model provides a folding wing for an aircraft and the aircraft, which have the beneficial effects that: the folding wing for the aircraft is provided with a supporting body, a limiting body and a triggering part, wherein the wing plate is in rotary connection with the outer side of the aircraft through the supporting body, the wing plate keeps unfolding trend under the action of a first elastic driving part, the first limiting part on the limiting body is matched with a first limiting groove on the wing plate, the first elastic driving part is kept in an energy storage state by the limiting body, the wing plate is kept in a folding state, the limiting body keeps moving relative to the supporting body under the action of a second elastic driving part so that the first limiting part is separated from the first limiting groove, the limiting body is controlled by the triggering part, the triggering part is connected with the limiting body and the supporting body, the limiting body keeps the limitation of the rotation of the wing plate by the limiting body, and when the wing plate is required to be unfolded, the triggering part releases the limitation of the limiting body relative to the supporting body, so that the limiting body moves relative to the supporting body under the driving of a second elastic driving part, the first limiting part is separated from the first limiting groove, and the limitation of the rotation of the wing plate is released, and the wing plate is unfolded relative to the supporting body under the driving of the first elastic driving part; the folding wing for the aircraft does not adopt controllable power sources like an electric cylinder, a motor gear rack and the like, has simple structure, light weight and low cost, can realize the control of the unfolding time of the wing plate through the triggering part, and has wide application scene; in addition, the folding wing for the aircraft can be conveniently installed on the outer side of the aircraft through the supporting body to form a modularized design, so that the folding wing does not occupy the space in the aircraft, and is convenient to assemble and disassemble.

Additional features and advantages of the utility model will be set forth in the detailed description which follows.

Drawings

The foregoing and other objects, features and advantages of the utility model will be apparent from the following more particular descriptions of exemplary embodiments of the utility model as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the utility model.

Fig. 1 shows a schematic overall structure of a folding wing for an aircraft according to an embodiment of the utility model.

Fig. 2 shows a schematic view of an explosive structure of a folding wing for an aircraft according to an embodiment of the utility model.

Fig. 3 shows a schematic illustration of a limiting body structure for a folding wing of an aircraft according to an embodiment of the utility model.

Fig. 4 shows a schematic view of an explosive structure of a support body and a wing panel for a folding wing of an aircraft according to an embodiment of the utility model.

Fig. 5 shows a schematic view of an assembly structure of a wing panel for a folding wing of an aircraft according to an embodiment of the utility model.

Fig. 6 shows a schematic structural view of a limiter-to-wing plate limiter for a folding wing of an aircraft according to one embodiment of the utility model.

Fig. 7 shows a schematic structural view of a limiter for a folding wing of an aircraft releasing the limit of the wing panel according to an embodiment of the utility model.

Fig. 8 shows a schematic structural view of a deployment procedure for a wing panel of a folding wing of an aircraft according to an embodiment of the utility model.

Fig. 9 shows a schematic structural view of one side of a wing panel for a folding wing of an aircraft according to one embodiment of the utility model.

Fig. 10 shows a schematic structural view of the other side of a wing panel for a folding wing of an aircraft according to one embodiment of the utility model.

Fig. 11 shows a schematic view of a partially enlarged construction of a limiter for a folding wing of an aircraft according to one embodiment of the utility model.

Fig. 12 shows a schematic structural view of a limiter-to-wing panel limiter for a folded wing of an aircraft after deployment according to an embodiment of the utility model.

Fig. 13 shows a schematic structural view of a folded state of a wing panel of an aircraft according to an embodiment of the utility model.

Fig. 14 shows a structural schematic view of a wing panel deployment state of an aircraft according to an embodiment of the utility model.

Reference numerals illustrate:

1. A missile; 2. folding the wings; 3. a limiting body; 4. a second torsion spring; 5. a connecting lug; 6. a wing plate; 7. an explosive bolt; 8. a first torsion spring;

3-1, a connector; 3-2, a first limiting part; 3-3, a second limiting part; 3-4, a second bolt hole; 3-5, a fourth clamping groove;

5-1, fixing holes; 5-2, a first accommodating groove; 5-3, rotating shaft; 5-4, a first limit plane; 5-5, sliding grooves; 5-6, a second accommodating groove; 5-7, a first bolt hole;

6-1, a second limiting plane; 6-2, a second clamping groove; 6-3, a first limit groove; 6-4, a second limiting groove; 6-5, shaft holes.

Detailed Description

Preferred embodiments of the present utility model will be described in more detail below. While the preferred embodiments of the present utility model are described below, it should be understood that the present utility model may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the utility model to those skilled in the art.

As shown in fig. 1 and 2, the present utility model provides a folding wing for an aircraft, comprising:

The device comprises a support body, wherein one side of the support body is rotatably connected with a wing plate 6, a first elastic driving part is arranged between the support body and the wing plate 6, the first elastic driving part can apply a first elastic force for expanding the wing plate 6, and the other side of the support body is used for being connected with an aircraft;

The limiting body 3 is in sliding connection with the supporting body, a first limiting part 3-2 is arranged on the outer side of the limiting body 3, the first limiting part 3-2 is matched with a first limiting groove 6-3 on the wing plate 6 and used for limiting the wing plate 6 to rotate relative to the supporting body, a second elastic driving part is arranged between the limiting body 3 and the supporting body, and the second elastic driving part can apply a second elastic force to the limiting body 3 to enable the limiting body 3 to move relative to the wing plate 6 so as to enable the first limiting part 3-2 to deviate from the first limiting groove 6-3;

The triggering part is connected with the limiting body 3 and the supporting body before triggering and is used for limiting the limiting body 3 to move relative to the supporting body, and the limiting of the limiting body 3 can be relieved after triggering of the triggering part.

Specifically, in order to solve the problems of complex structure, heavy weight and high cost when a controllable power source is adopted by a folding wing on an aircraft in the prior art, the unfolding moment of a wing plate 6 cannot be controlled when the controllable power source is not adopted, and the use scene is limited; the folding wing for the aircraft provided by the utility model is provided with the supporting body, the limiting body 3 and the triggering part, the wing plate 6 is in rotary connection with the outer side of the aircraft through the supporting body, under the action of the first elastic driving part, the wing plate 6 keeps unfolding trend, through the cooperation of the first limiting part 3-2 on the limiting body 3 and the first limiting groove 6-3 on the wing plate 6, the limitation of the limiting body 3 on the energy storage state of the first elastic driving part is realized, the wing plate 6 is kept in a folding state, under the action of the second elastic driving part, the limiting body 3 keeps moving relative to the supporting body to enable the first limiting part 3-2 to deviate from the trend of the first limiting groove 6-3, the limiting body 3 is controlled by the triggering part, the triggering part is connected with the limiting body 3 and the supporting body, the limiting body 3 keeps the limitation of the rotation of the wing plate 6 relative to the supporting body, and when the wing plate 6 is required to be unfolded, the triggering part releases the limitation of the limiting body 3 relative to the supporting body 3, the limiting body 3 moves relative to the supporting body under the driving of the second elastic driving part, and the limitation of the wing plate 6 is released when the wing plate 6 is required to be unfolded, and the limitation of the wing plate 3 is realized; the folding wing for the aircraft does not adopt controllable power sources like an electric cylinder, a motor gear rack and the like, has simple structure, light weight and low cost, can realize the control of the unfolding time of the wing plate 6 through the triggering part, and has wide application scene; in addition, the folding wing for the aircraft can be conveniently installed on the outer side of the aircraft through the supporting body to form a modularized design, so that the folding wing does not occupy the space in the aircraft, and is convenient to assemble and disassemble.

Optionally, the triggering component is an explosion bolt 7, the supporting body and the limiting body 3 are respectively provided with a first bolt hole 5-7 and a second bolt hole 3-4, and the explosion bolt 7 is connected with the first bolt hole 5-7 and the second bolt hole 3-4.

Specifically, the explosion bolt 7 is used as a triggering part and is arranged on the supporting body and the limiting body 3, one end of the explosion bolt 7 is exposed out of the outer end of the first bolt hole 5-7, the triggering time can be controlled according to the requirement, and the unfolding time of the wing plate 6 can be controlled.

In the embodiment, the aircraft is the missile 1, and for the application scene that the folded wings are unfolded after a certain safety distance is required to be pulled away from the carrier after the missile 1 is launched, the advantage is obvious; meanwhile, the explosion bolt 7 is small in size and free to fall off after triggering, so that the influence on the posture of the missile 1 is small.

Optionally, the support body includes a plurality of backup pads, and a plurality of the backup pad is connected gradually and is formed annular structure, annular structure can overlap establish on the periphery of aircraft, and with the aircraft is connected.

Specifically, a plurality of backup pads can be connected into annular structure, can conveniently overlap through annular structure and establish on the periphery of aircraft, only adopt several screw and aircraft to be connected fixedly can, the dismouting is very convenient.

In this embodiment, each support plate is an arc-shaped plate, and a plurality of support plates can form a circular ring structure after being sequentially connected, and can be directly sleeved on the outer surface of the missile 1; each supporting plate is provided with a fixing hole 5-1 for penetrating a screw to realize the fixed connection with the missile 1.

Optionally, two ends of each supporting plate are respectively provided with a connecting lug 5, a rotating shaft 5-3 is arranged between the connecting lugs 5 adjacent to each other of the supporting plates, and the wing plates 6 are rotatably sleeved on the outer sides of the rotating shafts 5-3.

Specifically, each connecting lug 5 extends to the outside of aircraft at the both ends of backup pad, and adjacent backup pad can pass through connecting lug 5 interconnect, and pivot 5-3 sets up between two adjacent connecting lugs 5, and the one end of pterygoid lamina 6 is provided with shaft hole 6-5, and shaft hole 6-5 and pivot 5-3 normal running fit just are in between two connecting lugs 5.

Optionally, a limiting block is disposed between the adjacent connecting lugs 5 of the support plates, and the limiting block is used for limiting the rotation of the wing plates 6 after being unfolded, so that the wing plates 6 are kept in the unfolded state.

Specifically, the limiting block is located between two adjacent connecting lugs 5, mechanically interferes with the wing plate 6 located between the two connecting lugs 5, limits the wing plate 6, and when the wing plate 6 is unfolded, the wing plate 6 contacts with the limiting block, and the unfolding state of the wing plate 6 is kept by the limiting block and the first elastic driving component together.

In the embodiment, a first limiting plane 5-4 is arranged on one side, close to the wing plate 6, of the limiting block, a second limiting plane 6-1 is arranged on one side, close to the limiting block, of the wing plate 6 in the unfolded state, and the first limiting plane 5-4 and the second limiting plane 6-1 form plane contact, so that impact on the limiting block when the wing plate 6 contacts the limiting block is reduced, and stress concentration is avoided.

Optionally, a sliding groove 5-5 is arranged on the other side of the supporting body, the limiting body 3 is embedded in the sliding groove 5-5 in a sliding mode, and the first limiting portion 3-2 is arranged on one side, close to the wing plate 6, of the limiting body 3.

Specifically, the support body is slidably embedded in the sliding groove 5-5, and the first limiting part 3-2 protrudes outwards from one side, close to the wing plate 6, of the support body and can enter between two adjacent connecting lugs 5 to be clamped with the first limiting groove 6-3 on the wing plate 6.

Optionally, a second limiting portion 3-3 is disposed on the outer side of the limiting body 3, the second limiting portion 3-3 and the first limiting portion 3-2 are located on two sides of the wing plate 6, the first limiting groove 6-3 and the second limiting groove 6-4 are disposed on two sides of the wing plate 6, the second limiting portion 3-3 is matched with the second limiting groove 6-4, when the first limiting portion 3-2 is embedded into the first limiting groove 6-3, a first gap is formed between the second limiting portion 3-3 and the wing plate 6, when the triggering component releases the limitation of the limiting body 3, under the driving action of the second elastic driving component, the limiting body 3 moves relative to the supporting body, and the second limiting portion 3-3 moves in a direction close to the second limiting groove 6-4 until the second limiting groove 6-4 is embedded into the second limiting groove 6-4.

Specifically, the first limiting part 3-2 is matched with the first limiting groove 6-3 to limit the wing plate 6 in the folded state, so as to maintain the folded state of the wing plate 6 more stably after the wing plate 6 is unfolded, as shown in fig. 3, the limiting body 3 is further provided with a second limiting part 3-3, the second limiting part 3-3 and the first limiting part 3-2 are arranged at the outer side of the limiting body 3 at intervals, and the further maintenance of the unfolded state of the wing plate 6 is realized through the clamping connection of the second limiting part 3-3 and the second limiting groove 6-4 on the wing plate 6; as shown in fig. 5 to 8, when the wing plate 6 is in a folded state, the first limiting portion 3-2 is clamped into the first limiting groove 6-3, the second limiting portion 3-3 is located outside the second limiting groove 6-4, after the triggering component triggers, the second elastic driving component drives the limiting body 3 to move, the first limiting portion 3-2 is separated from the first limiting groove 6-3, the wing plate 6 starts to rotate, during the rotation and unfolding process of the wing plate 6, the first limiting portion 3-2 and the second limiting portion 3-3 are not clamped into the first limiting groove 6-3 and the second limiting groove 6-4, the second limiting portion 3-3 is in contact with the wing plate 6 and slides relatively until the wing plate 6 is completely unfolded, and as shown in fig. 12, the second limiting portion 3-3 is embedded into the second limiting groove 6-4 to keep the unfolding state of the wing plate 6.

In the embodiment, the limiting body 3 is in a ring shape with a notch, the first limiting part 3-2 and the second limiting part 3-3 are arranged on the periphery of the limiting body 3, and the notch can facilitate the limiting body 3 to be arranged in the chute 5-5 on the inner periphery of the support body through elastic deformation; furthermore, the limiting body 3 is formed by connecting two parts with basically the same structure, the two parts are connected through the connector 3-1, and when accessories such as a sliding block, a missile wing and the like are arranged on the aircraft, the limiting body 3 is conveniently arranged on the outer surface of the aircraft.

Optionally, the first limiting portion 3-2 includes a first connecting portion and a first clamping block portion, the first connecting portion is connected with the first clamping block portion to form a first L-shaped structure, the second limiting portion 3-3 includes a second connecting portion and a second clamping block portion, the second connecting portion is connected with the second clamping block portion to form a second L-shaped structure, the first clamping block portion and the second clamping block portion are wedge-shaped with large inner ends and small outer ends, and the shapes of the first limiting groove 6-3 and the second limiting groove 6-4 are matched with the shapes of the first clamping block portion and the second clamping block portion respectively.

Specifically, as shown in fig. 11, the first limiting portion 3-2 includes a first connecting portion connected to the outer side of the limiting body 3 and a first clamping block portion connected to the outer end of the first connecting portion, the first connecting portion and the first clamping block portion form a first L-shaped structure, the second connecting portion and the second clamping block portion form a second L-shaped structure, the first clamping block portion and the second clamping block portion are respectively disposed on one side of the first connecting portion and the second connecting portion, which are close to each other, and are respectively used for being clamped into the first limiting groove 6-3 and the second limiting groove 6-4 on the wing plate 6, the first clamping block portion and the second clamping block portion are wedge-shaped and are respectively matched with the first limiting groove 6-3 and the second limiting groove 6-4, and after the first clamping block portion is clamped into the first limiting groove 6-3, the first clamping block portion and the second clamping block portion are tightly matched, so that shaking of the wing plate 6 in a folded state is reduced, and after the second clamping block portion is clamped into the second limiting groove 6-4, the first clamping block portion and the second clamping block portion are tightly matched, so that shaking of the wing plate 6 in an unfolded state is also can be formed, and the requirement of processing error is reduced.

In this embodiment, as shown in fig. 9 and 10, the first limiting groove 6-3 and the second limiting groove 6-4 are through grooves, in order to ensure that the second clamping block portion cannot be clamped into the first limiting groove 6-3 after the first clamping block portion is separated from the first limiting groove 6-3, the outer end size of the second clamping block portion is larger than the size of an opening of the first limiting groove 6-3, which is close to one end of the second clamping block portion, and the second clamping block portion cannot be clamped into the first limiting groove 6-3, but only slides along the surface of the wing plate 6 until reaching the opening of the second limiting groove 6-4, and then is clamped into the second limiting groove 6-4.

Optionally, the first elastic driving component and the second elastic driving component are respectively a first torsion spring 8 and a second torsion spring 4, two ends of the first torsion spring 8 are respectively connected with the supporting body and the wing plate 6, and when the wing plate 6 is in a folded state, the first torsion spring 8 is in an energy storage state, two ends of the second torsion spring 4 are respectively connected with the supporting body and the limiting body 3, and before the triggering component triggers, the second torsion spring 4 is in an energy storage state.

Specifically, a first accommodating groove 5-2 is formed in the connecting lug 5 of the support body and is used for accommodating the first torsion spring 8, a first clamping groove communicated with the first accommodating groove 5-2 and used for clamping one end of the first torsion spring 8 and a second clamping groove 6-2 used for clamping the other end of the first torsion spring 8 are formed in the connecting lug 5 and the wing plate 6 respectively, a second accommodating groove 5-6 is formed in the other side of the support body and is used for accommodating the second torsion spring 4, and a third clamping groove communicated with the second accommodating groove 5-6 and used for clamping one end of the second torsion spring 4 and a fourth clamping groove 3-5 used for clamping the other end of the second torsion spring 4 are formed in the other side of the support body and the limiting body 3 respectively.

The utility model also provides an aircraft comprising:

An aircraft body;

The folding wing 2 for the aircraft is connected with the outer wall of the aircraft through the supporting body.

Specifically, the folding wing 2 for the aircraft is connected to the outer surface of the aircraft body through the supporting body, the wing plate 6 is in a folding state in the initial state, the first limiting part 3-2 on the limiting body 3 limits the wing plate, and the limiting body 3 is limited by the triggering part, so that the action of the wing plate is avoided; when the wing plate 6 needs to be unfolded, the triggering part is used for triggering, the limit of the limit body 3 is released, the limit body 3 moves to release the limit of the wing plate 6, the wing plate 6 can automatically rotate to an unfolding state, and the unfolding time of the wing plate 6 is controllable.

In summary, when the aircraft provided by the utility model with the folding wing 2 for the aircraft operates, the folding wing 2 for the aircraft is provided with four wing plates 6, and is used on the missile 1 as an example: in the initial state, as shown in fig. 13, the wing plate 6 is in a folded state; as shown in fig. 6, the four wing plates 6 are respectively locked by the first limiting part 3-2 on the limiting body 3 in a limiting way, when the wing plates 6 are required to be unfolded by the missile 1, a signal is sent to trigger the explosion bolt 7, at this time, the limiting body 3 rotates around the periphery of the missile body under the action of the second torsion spring 4, as shown in fig. 7, and the first limiting part 3-2 is released; then, the wing plate 6 is unfolded under the action of the first torsion springs 8 at the two sides of the wing plate; when the limiting body 3 rotates, as shown in fig. 8, the second limiting portion 3-3 does not immediately extend into the first limiting groove 6-3 from the B surface of the wing plate 6, so that the wing plate 6 will be smoothly unfolded; during the unfolding process of the wing plate 6, the second limiting part 3-3 is always pressed on the B surface of the wing plate 6 until the wing plate 6 is unfolded in place, and the second limiting part 3-3 stretches into the second limiting groove 6-4 of the wing plate 6. The caliber of the A surface of the first limiting groove 6-3 is larger than the caliber of the B surface, and the drawing angle of the first limiting groove 6-3 is consistent with the drawing angle of the first limiting part 3-2 on the limiting body 3, so that the first limiting groove 6-3 can smoothly enter and well cooperate; similarly, the caliber of the B surface of the second limiting groove 6-4 on the wing plate 6 is larger than the caliber of the A surface, the drawing angle is consistent with the second limiting part 3-3, the matching requirement can be ensured, and the swinging of the wing plate 6 is well limited. The second limiting part 3-3 is smaller than the B surface size of the second limiting groove 6-4, and when the wing plate 6 rotates and expands to a final position, the second limiting part 3-3 reliably stretches into the second limiting groove 6-4 to form locking limit on the wing plate 6; similarly, the first limiting part 3-2 is smaller than the caliber of the A face of the first limiting groove 6-3, and the first limiting part can smoothly enter the first limiting groove during installation. After the expansion operation of the wing plate 6 is completed, as shown in fig. 14, the wing plate 6 is in the expanded state and stably maintains its expanded state.

The foregoing description of embodiments of the utility model has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.

Claims (10)

1. A folding wing for an aircraft, comprising:

The device comprises a support body, wherein one side of the support body is rotatably connected with a wing plate, a first elastic driving part is arranged between the support body and the wing plate, the first elastic driving part can apply a first elastic force for expanding the wing plate, the other side of the support body is used for being connected with an aircraft, and a fixing hole is formed in the support body and used for penetrating a screw so as to enable the support body to be detachably connected with the aircraft;

The limiting body is in sliding connection with the supporting body, a first limiting part is arranged on the outer side of the limiting body, the first limiting part is matched with a first limiting groove on the wing plate and used for limiting the wing plate to rotate relative to the supporting body, a second elastic driving part is arranged between the limiting body and the supporting body, and the second elastic driving part can apply a second elastic force to the limiting body to enable the limiting body to move relative to the wing plate so as to enable the first limiting part to deviate from the first limiting groove;

The triggering part is connected with the limiting body and the supporting body before triggering and is used for limiting the limiting body to move relative to the supporting body, and the limiting of the limiting body can be relieved after triggering of the triggering part.

2. The folding wing for an aircraft according to claim 1, wherein the triggering member is an explosion bolt, and the supporting body and the limiting body are respectively provided with a first bolt hole and a second bolt hole, and the explosion bolt is connected with the first bolt hole and the second bolt hole.

3. The folding wing for an aircraft according to claim 1, wherein the support body comprises a plurality of support plates, the plurality of support plates being connected in sequence to form a ring-shaped structure, the ring-shaped structure being capable of being sleeved on the periphery of the aircraft and being connected to the aircraft.

4. A folding wing for an aircraft according to claim 3, wherein each of the support plates is provided with a respective one of the two ends thereof with a respective one of the connecting lugs, a rotary shaft being provided between the connecting lugs of adjacent ones of the support plates adjacent to each other, the wing plates being rotatably fitted over the outer sides of the rotary shaft.

5. The folding wing for aircraft according to claim 4, characterized in that a stopper is provided between the mutually adjacent connection lugs of the support plates, the stopper being intended to limit the rotation of the wing after deployment so as to keep the wing in its deployed state.

6. The folding wing for an aircraft according to claim 1, wherein a chute is provided on the other side of the support body, the limiting body is slidably embedded in the chute, and the first limiting portion is provided on a side of the limiting body, which is close to the wing plate.

7. The folding wing for an aircraft according to claim 6, wherein a second limiting portion is disposed on an outer side of the limiting body, the second limiting portion and the first limiting portion are disposed on two sides of the wing plate respectively, the first limiting groove and the second limiting groove are disposed on two sides of the wing plate respectively, the second limiting portion is matched with the second limiting groove, a first gap is formed between the second limiting portion and the wing plate when the first limiting portion is embedded into the first limiting groove, and the limiting body moves relative to the supporting body under the driving action of the second elastic driving member when the triggering member releases the limitation of the limiting body, so that the second limiting portion moves in a direction approaching to the second limiting groove until being embedded into the second limiting groove.

8. The folding wing for an aircraft according to claim 7, wherein the first limiting portion includes a first connecting portion and a first clamping block portion, the first connecting portion is connected with the first clamping block portion to form a first L-shaped structure, the second limiting portion includes a second connecting portion and a second clamping block portion, the second connecting portion is connected with the second clamping block portion to form a second L-shaped structure, the first clamping block portion and the second clamping block portion are wedge-shaped with large inner ends and small outer ends, and the shapes of the first limiting groove and the second limiting groove are matched with the shapes of the first clamping block portion and the second clamping block portion respectively.

9. The folding wing for an aircraft according to claim 1, wherein the first elastic driving component and the second elastic driving component are a first torsion spring and a second torsion spring, two ends of the first torsion spring are respectively connected with the supporting body and the wing plate, when the wing plate is in a folded state, the first torsion spring is in an energy storage state, two ends of the second torsion spring are respectively connected with the supporting body and the limiting body, and before the triggering component triggers, the second torsion spring is in an energy storage state.

10. An aircraft, comprising:

An aircraft body;

Folding wing for an aircraft according to any of claims 1 to 9, which is connected to the outer wall of the aircraft by a support body.