Parachute and unmanned aerial vehicle

Abstract

The utility model provides a parachute and an unmanned aerial vehicle, relates to the technical field of aircrafts, and solves the technical problem that the parachute is difficult to adapt to unmanned aerial vehicles with different appearance structures. The parachute is used for landing of the unmanned aerial vehicle and comprises a parachute bin and a fixing assembly used for attaching the parachute bin to the top of the unmanned aerial vehicle, the fixing assembly comprises a plurality of flexible belts distributed in the circumferential direction of the parachute bin, one end of each flexible belt is connected to the parachute bin, and the other end of each flexible belt is detachably connected to the position, close to the bottom, of the unmanned aerial vehicle. According to the parachute, the parachute bin is attached and fixed to the top of the unmanned aerial vehicle through the multiple flexible belts, and the parachute can adapt to unmanned aerial vehicles of different appearance structures on the basis of being easy to disassemble and assemble and is light in weight.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a parachute and a drone. Background Art

[0002] As drones are increasingly used, the risks they bring are also increasing, especially for drones flying over cities, where falling from high altitudes is fatal. Installing a parachute on a drone can solve this problem, but in related technologies, the method of fixing with screws is not convenient for removal from the drone, and the direct buckle connection is prone to fall off due to impact after opening the parachute, which is unstable. At the same time, the above connection method has poor adaptability to drones with different shapes and structures. Utility Model Content

[0003] The utility model aims to provide a parachute and a UAV, so as to solve the technical problem that the parachute is difficult to adapt to UAVs with different shapes and structures.

[0004] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0005] In a first aspect, the utility model provides a parachute for landing of an unmanned aerial vehicle, the parachute comprising a parachute compartment and a fixing assembly for attaching the parachute compartment to the top of the unmanned aerial vehicle, the fixing assembly comprising at least two flexible belts distributed along the circumference of the parachute compartment, one end of each of the flexible belts being connected to the parachute compartment, and the other end being used for detachable connection to a position near the bottom of the unmanned aerial vehicle.

[0006] According to at least one embodiment of the present utility model, the parachute also includes at least two arms connected to the parachute compartment, and the arms extend obliquely toward the outside of the parachute compartment in the direction toward the drone, and one end of each flexible belt is connected to the end of the corresponding arm away from the parachute compartment.

[0007] According to at least one embodiment of the present utility model, the end of the support arm close to the umbrella compartment has a preset width.

[0008] According to at least one embodiment of the utility model, the support arm has a connecting section, a middle section and an inclined section distributed away from the umbrella compartment, the connecting section is connected to the side of the umbrella compartment, and the connecting section and the inclined section are respectively located on two opposite sides of the middle section;

[0009] At least one first reinforcing rib is provided on the inclined section, and the first reinforcing rib extends along the extending direction of the inclined section;

[0010] The connecting section and the middle section are also connected via at least one second reinforcing rib, and the second reinforcing rib extends in the same direction as the first reinforcing rib.

[0011] According to at least one embodiment of the present utility model, the side of the connecting section facing the umbrella compartment further has at least one protrusion, and the at least one protrusion is used to connect with the umbrella compartment in a vertical direction.

[0012] According to at least one embodiment of the present utility model, the umbrella silo includes an umbrella silo body and a control cabin connected to the bottom of the umbrella silo body, and an umbrella opening device is provided in the umbrella silo body;

[0013] A posture sensing unit is provided in the control cabin, and the posture sensing unit is used to obtain the flight posture of the UAV, and the posture sensing unit is communicatively connected with the parachute opening device.

[0014] According to at least one embodiment of the present utility model, each of the supporting arms is connected to the control cabin, and the top of the control cabin also has at least one recessed portion, and each of the recessed portions is used to accommodate a corresponding protrusion on the connecting section of the supporting arm.

[0015] According to at least one embodiment of the present utility model, the preset width is 30% to 60% of the maximum width of the control cabin.

[0016] According to at least one embodiment of the utility model, the parachute further comprises a waterproof ring located at the bottom of the control cabin, the waterproof ring being used for waterproofing between the control cabin and the drone.

[0017] According to at least one embodiment of the present utility model, the fixing assembly further includes at least two adjusting buckles, each of which is used to adjust the length of the corresponding flexible belt.

[0018] In a second aspect, the utility model provides a drone, comprising the parachute described in the first aspect.

[0019] Among the one or more technical solutions provided in the exemplary embodiments of the present utility model, at least one of the following beneficial effects can be achieved.

[0020] The parachute of the exemplary embodiment of the utility model is achieved by fitting the parachute compartment to the top of the drone and connecting it to the part near the bottom of the drone through a plurality of flexible belts distributed around the parachute compartment, so that the parachute compartment does not need to be directly fixed to the top of the drone, thus avoiding the problem of inconvenient assembly and disassembly with screws. At the same time, compared with rigid connections, the flexible belt can be matched according to the shape of the drone, so it can be adapted to drones with different shapes and structures, and has high versatility. The flexible belt is detachably connected to the part near the bottom of the drone, so the flexible belt can be easily removed together with the parachute compartment, so that the parachute compartment can be quickly replaced. Furthermore, compared with the method of directly fixing the parachute compartment on the top of the drone with screws, the flexible belt is lighter in weight, which can further reduce the overall weight of the parachute. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings illustrate exemplary embodiments of the present invention and are used to explain the principles of the present invention together with the description thereof, wherein these drawings are included to provide a further understanding of the present invention, and the accompanying drawings are included in and constitute a part of this specification;

[0022] Figure 1 It is a schematic diagram of the axonometric structure of a parachute according to an embodiment of the utility model;

[0023] Figure 2 It is a schematic diagram of a three-dimensional exploded structure of a parachute according to an embodiment of the utility model;

[0024] Figure 3 It is a schematic diagram of the axonometric structure of the support arm according to the embodiment of the utility model;

[0025] Figure 4 It is a schematic diagram of the isometric structure of the support arm according to another angle of the embodiment of the utility model;

[0026] Figure 5 It is a schematic diagram of the structure of a drone (fixed with a parachute) according to an embodiment of the utility model;

[0027] Figure 6 is a schematic structural diagram of a drone (detached from a parachute) according to an embodiment of the utility model;

[0028] Figure 7 It is a schematic diagram of the three-dimensional exploded structure of the lock body according to the embodiment of the utility model;

[0029] Figure 8 It is a structural schematic diagram of a lock tongue according to an embodiment of the utility model;

[0030] Fig. 9 It is a schematic diagram of the quick-release structure (lock tongue half-inserted state) according to an embodiment of the utility model;

[0031] Fig.10 yes Fig. 9 A longitudinal cross-sectional view of

[0032] Fig.11 It is a structural schematic diagram of the quick-release structure (locked state) according to an embodiment of the utility model;

[0033] Fig.12 yes Fig.11 Longitudinal section view of .

[0034] 1. Lock body; 11. Shell; 12. Reset element; 13. Locking part; 131. Second abutting surface; 132. Third abutting surface; 14. Force-applying part; 15. Pin; 16. Limiting element; 17. Lock hole; 20. Lock tongue; 21. Top surface; 22. Sliding surface; 23. First abutting surface; 24. Groove; 30. Flexible belt; 31. Adjustment buckle; 40. Support arm; 41. Connecting section; 411. Protruding part; 42. Middle section; 43. Inclined section; 431. First reinforcing rib; 432. Second reinforcing rib; 51. Parachute compartment body; 52. Control cabin; 521. Posture sensing part; 522. Adapter plate; 523. Body quick-release line; 60. Body; 61. Battery; 62. Camera. DETAILED DESCRIPTION

[0035] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0036] In the related art, the drone and the parachute are fixed by bolt connection or snap connection. Since the parachute needs maintenance after a period of time, the bolt connection method is not convenient for disassembly and maintenance, and it also increases the weight of the drone. As for the snap connection method, the parachute is easy to fall off after being opened and subjected to instant impact, and the stability is not high, which does not play a safety role. When the drone is flying over the city, once it loses control or fails, the drone falling from a high altitude is fatal to the ground personnel. At the same time, due to the different structures and sizes of drones, there are different adaptation requirements when adding parachutes. The above connection method cannot have the characteristics of strong versatility on the basis of the rapid replacement of parachutes.

[0037] In view of the above problems, the parachute provided by the exemplary embodiment of the utility model is connected with multiple flexible belts around the parachute compartment, and the other end of the flexible belt is detachably connected to the position near the bottom of the drone, so that the parachute compartment is stably fixed to the top of the drone; the flexible belt can play a buffering role at the moment of opening the parachute, and the connection is stable while being detachable. Moreover, the flexible belt can adapt to drones with different shapes and structures, and has strong versatility.

[0038] It should be noted that the parachute of the utility model can be used for drones, and can also be applied to light and ultralight aircraft, light helicopters, gliders, delta wings, powered delta wings, paragliders, powered paragliders, hot air balloons, airships, aviation models, and aerospace models, etc.

[0039] Figure 1 It is a schematic diagram of the axonometric structure of a parachute according to an embodiment of the utility model; Figure 2 1 is a schematic diagram of a three-dimensional exploded structure of a parachute according to an embodiment of the present utility model. Figure 1 and Figure 2 As shown, the parachute provided by the exemplary embodiment of the utility model includes a parachute compartment and a fixing assembly for attaching the parachute compartment to the top of the drone, the fixing assembly includes a plurality of flexible belts 30 distributed along the circumference of the parachute compartment, one end of each flexible belt 30 is connected to the parachute compartment, and the other end is used for detachable connection to a position near the bottom of the drone.

[0040] In actual use, refer to Figure 5 , Figure 5 : is a schematic diagram of the structure of a drone (fixed with a parachute) according to an embodiment of the utility model. The parachute compartment is attached to the top of the drone body 60, and the flexible belt 30 symmetrically arranged on the side of the compartment is connected to the compartment at one end, and the other end is connected to the drone body 60 near the bottom by a detachable connection. For example, it is detachably connected to the load-bearing position of the drone landing gear, that is, the length of the entire flexible belt 30 is roughly equivalent to the height of the body 60. By distributing a plurality of flexible belts 30 in the circumferential direction and connecting to the position near the bottom of the body 60, the parachute compartment can be stably attached to the top of the drone body 60 without using screws to fix the parachute compartment to the top of the body 60. The flexible belt 30 is lighter than the screws, so the weight of the entire parachute will be lighter. Furthermore, since the flexible belt 30 can be adapted to the shape of the body 60, it is applicable to drones of various shapes. At the same time, the flexible belt 30 can play a certain buffering role, which can effectively reduce the impact on the drone when the parachute is opened, and it is not easy to damage the body 60 of the drone, and it also avoids the problem of easy falling off caused by the snap connection method in the prior art.

[0041] Figure 6Schematic diagram of the structure of the drone (without parachute) according to the embodiment of the utility model. Figure 6 As shown, when the drone is flying without a parachute in some cases, or when the parachute chamber needs maintenance after long-term use, the parachute chamber and the flexible belt 30 are removed from the drone together. Exemplarily, the flexible belt 30 is connected to the body 60 through a quick-release structure, wherein the lock body 10 is arranged at the end of the flexible belt 30, and the lock tongue 20 is fixedly arranged at a position near the bottom of the body 60 of the drone, such as the load-bearing position of the landing gear; the lock tongue 20 can also be arranged at the end of the flexible belt 30, and the lock body 10 is fixedly arranged at a position near the bottom of the body 60 of the drone, such as the load-bearing position of the landing gear, and the selection is made according to the actual situation. Specifically, by pressing the two force-applying parts on the lock body 10 with fingers, the lock tongue 20 can be unlocked and disengaged from the lock body 10 to complete the disassembly. Based on this, the overall disassembly and assembly of the parachute from the drone can be completed only by locking and unlocking the lock tongue 20 and the lock body 10 in the quick-release structure, which can be quickly replaced, and at the same time, it is light in weight and has better adaptability and stability.

[0042] Exemplarily, the flexible belt 30 may be a Kevlar strap, or a rope made of other high-strength materials, such as high-strength polyethylene, etc., which can ensure a certain strength while maintaining flexibility.

[0043] Since the flexible belt 30 has the characteristic of following the shape, it may be deviated due to wind resistance and acceleration during the flight of the UAV, thereby affecting the normal operation of the functional components on the UAV. The parachute provided by the exemplary embodiment of the utility model also includes at least two arms 40 connected to the parachute compartment, and the arms 40 extend obliquely toward the outside of the parachute compartment in the direction toward the UAV, and one end of each flexible belt 30 is connected to the end of the corresponding arm 40 away from the parachute compartment.

[0044] Figure 5 : is a schematic diagram of the structure of a drone (fixed with a parachute) according to an embodiment of the utility model. Figure 5 As shown, when the umbrella compartment is connected to the flexible belt 30 through the support arm 40, since the support arm 40 extends outwardly from the umbrella compartment to the body 60, the connection point between the flexible belt 30 and the end of the support arm 40 can be adjusted by designing the inclination angle and length of the support arm 40, thereby shifting the position of the flexible belt 30. Figure 6As shown, at the position of the binocular camera 62 near the top of the body 60, if the flexible belt 30 is arranged in front of the camera 62, during the flight of the drone, the flexible belt 30 may be offset due to its flexibility, thereby affecting the normal image acquisition of the camera 62. However, by transitioning through the rigid support arm 40 in front of the camera 62, this problem will not occur. In addition, the conformal characteristic of the flexible belt 30 is that it is possible to fit and tighten the battery 61, and the battery 61 is inevitably involved in the movement process, which may cause the battery 61 to shift under the action of external force and have poor contact. By designing and adjusting the inclination angle of the support arm 40, the flexible belt 30 can be prevented from fitting on the battery 61, thereby avoiding the possibility that the battery 61 may have poor contact under the action of the flexible belt 30. Based on this, through the design of the rigid support arm 40, the flexible belt 30 can be avoided from the relevant functional parts on the drone, so as not to affect the normal operation of the drone.

[0045] On the other hand, by designing the support arm 40 to be tilted downward, even if the parachute chamber structure is miniaturized, the flexible belt 30 can be connected to the parachute chamber structure through the support arm 40, thereby achieving a small-size parachute chamber structure that can be adapted to the drone without affecting the normal operation of related functional components on the drone.

[0046] Considering that the connection between the support arm 40 and the parachute chamber needs to have a certain strength to counteract the destructive force caused by wind resistance and acceleration during the flight of the drone. The support arm 40 in the parachute of the exemplary embodiment of the utility model has a preset width at the end close to the parachute chamber. That is, the end where the support arm 40 is connected to the parachute chamber has a preset width to form a rigid connection with a certain strength, so that the parachute chamber has strong stability even when encountering destructive forces such as wind resistance and acceleration. Exemplarily, the preset width of the end of the support arm 40 can be selected within the allowable range according to the size of the parachute chamber. For example, when the parachute chamber includes a parachute chamber body 51 and a control cabin 52, and the support arm 40 is connected to the control cabin 52, the preset width of the end of the support arm 40 is 30% to 60% of the maximum width of the control cabin 52. Within this range, the required connection strength can be guaranteed and the weight can be reduced as much as possible; optionally, the preset width of the end of the support arm 40 can be half of the maximum width of the control cabin 52.

[0047] Exemplarily, the width of the arm 40 can be constant or gradually decrease in the direction away from the parachute compartment. When the width of the arm 40 gradually decreases, the end of the arm 40 away from the parachute compartment reaches the minimum width and adapts to the width of the flexible belt 30, thereby minimizing the weight of the arm 40 itself while maintaining a certain strength.

[0048] Figure 3 It is a schematic diagram of the axonometric structure of the support arm according to the embodiment of the utility model; Figure 4FIG. 2 is a schematic diagram of the isometric structure of the support arm according to another embodiment of the present invention. Figure 3 and Figure 4 As shown, in the parachute provided by the exemplary embodiment of the utility model, the support arm 40 has a connecting section 41, an intermediate section 42 and an inclined section 43 distributed away from the parachute compartment, the connecting section 41 is connected to the side of the parachute compartment, and the connecting section 41 and the inclined section 43 are respectively located on two opposite sides of the intermediate section 42; at least one first reinforcing rib 431 is provided on the inclined section 43, and the first reinforcing rib 431 extends along the extension direction of the inclined section 43; the connecting section 41 and the intermediate section 42 are also connected by at least one second reinforcing rib 432, and the extension direction of the second reinforcing rib 432 is consistent with that of the first reinforcing rib 431.

[0049] Exemplarily, the arm 40 has a connecting section 41, a middle section 42 and an inclined section 43 in sequence. The connecting section 41 is a vertical plate-like structure, which is attached to the side of the parachute compartment and fixedly connected with screws. The middle section 42 is a horizontal plate-like structure, one end of which is connected to the bottom end of the connecting section 41 and the other end is connected to the top end of the inclined section 43. The inclined section 43 is a downwardly inclined plate-like structure, and the connecting section 41 and the inclined section 43 are located on both sides of the middle section 42. A plurality of first reinforcing ribs 431 are distributed along the width direction of the arm 40 and are located on the side of the inclined section 43 facing the drone body 60. A plurality of second reinforcing ribs 432 are also distributed along the width direction of the arm 40 and are located between the connecting section 41 and the middle section 42, that is, one side of the second reinforcing rib 432 is fixed on the connecting section 41, and the other adjacent side is fixed on the middle section 42, and the side of the second reinforcing rib 432 away from the connecting section 41 and the surface of the inclined section 43 away from the drone body 60 are in the same plane. Based on this, the weight can be reduced as much as possible while ensuring that the support arm 40 has the required strength. Furthermore, in order not to affect the appearance of the drone, the screws connecting the connecting section 41 to the side of the parachute compartment are located in the space formed between the second reinforcing ribs 432, so as to hide the screws.

[0050] Since the structure of the parachute chamber needs to be as light as possible, the shells of the parachute chamber body 51 and the control cabin 52 can be made of carbon fiber shells and aviation aluminum alloys to reduce weight while ensuring structural strength. Therefore, the shells of the parachute chamber body 51 and the control cabin 52 are relatively thin. The support arm 40 can be directly connected to the shell of the parachute chamber body 51, or it can be connected to the shell of the control cabin 52. In order to ensure that the connection between the support arm 40 and the parachute chamber body 51 or the control cabin 52 has sufficient installation strength. Taking the connection between the support arm 40 and the control cabin 52 as an example, the connecting section 41 also has at least one protrusion 411 on the side facing the control cabin 52, and the protrusion direction of the protrusion 411 is toward the side of the control cabin 52, and at least one protrusion 411 is used to connect to the parachute chamber in the vertical direction. At the same time, the top of the control cabin 52 has a recessed portion matched with the raised portion 411, and corresponding threaded holes are provided on the bottom surface of the recessed portion and the raised portion 411. When the screws are assembled into the threaded holes, the bottom surface of the recessed portion and the raised portion 411 are fixedly connected in the vertical direction. Since the connecting section 41 is also connected to the side of the control cabin 52 by screws in the side direction, the connection reliability between the support arm 40 and the control cabin 52 is enhanced by the two-way screw connection.

[0051] like Figure 2 As shown, when a control cabin 52 is fixed to the bottom of the parachute chamber body 51, a parachute opening device is provided in the parachute chamber body 51; a posture sensing unit 521 is provided in the control cabin 52, and the posture sensing unit 521 is used to obtain the flight posture of the UAV, and the posture sensing unit 521 is communicatively connected with the parachute opening device.

[0052] Exemplarily, the shell of the parachute chamber body 51 contains a parachute body, a parachute rope, and a parachute opening device. For example, the parachute opening device is a gas expansion module, and the gas expansion module is used to open the shell of the parachute chamber body 51 to release the parachute body. The control cabin 52 is provided with a plug adapter plate, a body quick release line, and a posture sensing unit 521, etc., wherein the posture sensing unit 521 can be a posture board, and the body quick release line 523 is used to connect the adapter plate 522 to communicate with the drone; the posture board is used to capture and sense the flight state of the drone when the drone is powered off, and make an independent judgment whether to open the parachute, which does not rely on the controller of the drone, thereby improving safety and versatility. For example, when the attitude board detects that the flight attitude of the drone loses control and is in an abnormal attitude, it can send a signal to the gas expansion module in the parachute chamber body 51, and the gas expansion module quickly generates gas to open the shell of the parachute chamber body 51, thereby releasing the parachute body, parachute rope, etc. from the shell of the parachute chamber body 51, forming a parachute opening action, and then the drone can slowly land on the ground.

[0053] In order to seal the parachute compartment to achieve waterproof function, in the parachute provided by the exemplary embodiment of the utility model, a waterproof rubber strip is also provided at the connection position between the parachute compartment body 51 and the control cabin 52. The shell of the control cabin 52 is composed of an upper shell and a lower shell, and a waterproof rubber strip is also provided at the connection position of the upper shell and the lower shell. At the same time, at the position where the bottom of the lower shell of the control cabin 52 fits with the drone body 60, an O-type waterproof ring is also provided for waterproof connection with the drone body 60, so as to prevent water from passing through the gap of the control cabin 52 shell along the body quick release line 523 and entering the control cabin 52, thereby damaging the circuit.

[0054] In some embodiments, Figure 2 As shown, the fixing assembly also includes at least two adjustment buckles 31, each of which is used to adjust the length of the corresponding flexible belt 30. The adjustment buckle 31 is arranged on the corresponding flexible belt 30, and its specific structure is similar to the principle of the adjustment buckle on the existing shoulder strap, which will not be repeated here. By arranging the adjustment buckle 31 on each flexible belt 30, the parachute can achieve seamless switching between a large body and a small body through length adjustment, and has higher versatility.

[0055] It should be noted that there are various ways to achieve detachable connection, such as hooks and buckles, quick-release structures, etc. The quick-release structure is used as an example for explanation below.

[0056] Figure 7 It is a schematic diagram of the three-dimensional exploded structure of the lock body according to the embodiment of the utility model; Figure 8 It is a structural schematic diagram of a lock tongue according to an embodiment of the utility model; Fig. 9 It is a structural schematic diagram of the quick-release structure (lock tongue half-inserted state) according to an embodiment of the utility model; Fig.10 yes Fig. 9 A longitudinal cross-sectional view of Figure 7-10As shown, the quick-release structure provided by the exemplary embodiment of the utility model includes a lock body 10, a lock tongue 20, a limiting element 16 and at least one lock buckle assembly, the lock buckle assembly includes a reset element 12 and a lock buckle portion 13 hinged to the lock body 10 through a pin shaft 15, the lock body 10 has a lock hole 17 for the lock tongue 20 to be inserted, and the limiting element 16 is arranged at a position close to the bottom wall of the lock hole 17; the lock buckle portion 13 has a second abutment surface 131 at one end away from the pin shaft 15, and a third abutment surface 132 at the other end close to the pin shaft 15; the top end of the lock tongue 20 has a top The locking tongue 20 has a top surface 21 and a raised portion protruding from at least one side surface of the locking tongue 20, the raised portion having a first abutting surface 23 and a sliding surface 22 adjacent to the first abutting surface 23, the sliding surface 22 is used to push the locking portion 13 to rotate from the first position to the second position; the locking tongue 20 has a groove 24 formed on the top surface 21, the groove 24 stops at the limiting element 16, the locking portion 13 returns to the first position under the action of the resetting element 12, the first abutting surface 23 stops at the second abutting surface 131, and the third abutting surface 132 stops at the shell 11 of the lock body 10.

[0057] In practical applications, the lock assembly is located at one side of the lock hole 17. When the lock tongue 20 does not enter the lock hole 17, the lock portion 13 is located at the first position under the action of the reset element 12; when the lock tongue 20 enters the lock hole 17, Fig.10 As shown, the sliding surface 22 on the raised portion of the lock tongue 20 abuts against the side surface of the lock catch portion 13, and the side surface of the lock catch portion 13 can be a plane. Since the side surface of the lock catch portion 13 is inclined relative to the lock tongue 20 and is arranged at the first position, when the lock tongue 20 is inserted into the lock hole 17 under the action of external force, the sliding surface 22 slides on the side surface of the lock catch portion 13 on the one hand, and overcomes the elastic force of the reset element 12 on the other hand, and pushes the lock catch portion 13 to rotate along the pin 15 to the second position, as shown in FIG. Fig.10 As shown, the position of the locking portion 13 is the second position.

[0058] The lock tongue 20 is pushed deeper into the lock hole 17 until the groove 24 on the top surface 21 of the lock tongue 20 stops against the limiting element 16. At this time, the sliding surface 22 of the lock tongue 20 is separated from the side surface of the lock catch 13. The lock catch 13 is restored from the second position to the first position under the action of the reset element 12. Fig.11 and Fig.12 The position of the locking portion 13 shown is the first position, wherein Fig.11 is a schematic diagram of a quick-release structure (locked state) according to an embodiment of the utility model; Fig.12 yes Fig.11When the lock part 13 returns to the first position, the second abutting surface 131 of the lock part 13 abuts against the first abutting surface 23 of the lock tongue 20 to form an interference fit, and the third abutting surface 132 of the lock part 13 also abuts against the shell 11 of the lock body 10, forming an over-dead point position of the lock part 13 and the lock tongue 20. At this time, the elastic force of the reset element 12 does not affect the locking force of the lock tongue 20 and the lock part 13. The greater the external force, the tighter the lock is, thereby achieving the anti-slip function. Compared with the snap connection in the prior art, the quick-release structure of the exemplary embodiment of the utility model is safer.

[0059] like Fig.12 As shown, since the lock tongue 20 and the lock catch part 13 form an over-dead point, in order to achieve the rapid separation of the lock tongue 20 and the lock body 10, it is necessary to use external force to quickly separate the two. Therefore, the lock catch assembly also includes a force-applying part 14 for separating the lock catch part 13 from the lock tongue 20, and the force-applying part 14 is connected to the end of the lock catch part 13 close to the pin 15. It can be understood that at least part of the force-applying part 14 is located outside the housing 11 of the lock body 10, and most of the lock catch part 13 is located inside the housing 11. The force-applying part 14 and the lock catch part 13 can be an integrally formed structure. When the finger presses the force-applying part 14 toward the direction of the lock tongue 20, the lock catch part 13 will overcome the force of the reset element 12 and rotate in the direction of the second position, and separate from the protrusion of the lock tongue 20. At this time, if a separation force is applied to the lock body 10 and the lock tongue 20, the lock tongue 20 will be removed from the lock hole 17 to complete the quick release.

[0060] Continue to refer Fig.12 In order to make the lock tongue 20 and the lock catch 13 more stable under the mutual extrusion, when the first abutting surface 23 and the second abutting surface 131 abut, the force direction of the second abutting surface 131 is toward the pin 15. The first abutting surface 23 and the second abutting surface 131 can both be curved surfaces that match each other, wherein the force normal direction of the first abutting surface 23 of the lock tongue 20, that is, the force normal direction of the second abutting surface 131 is toward the pin 15. At this time, even if the third abutting surface 132 does not abut against the housing 11 of the lock body 10, the lock tongue 20 and the lock catch 13 will be subjected to greater force, and the greater the locking force to achieve the purpose of preventing slipping.

[0061] like Figure 7 and Fig.12As shown, in the lock tongue 20 provided by the exemplary embodiment of the utility model, the portion of the top surface 21 located on one side of the groove 24 forms a continuous curved surface with the corresponding sliding surface 22. The top surface 21 can be a plane or a curved surface. When the top surface 21 is a curved surface, a continuous curved surface can be formed between it and the sliding surface 22. Specifically, the top surface 21 extends from the groove 24 to the side and extends toward the main body of the lock tongue 20. This arrangement allows the top surface 21 to first contact the side of the lock buckle part 13 when the lock tongue 20 begins to be inserted into the lock hole 17, and then smoothly transitions to the sliding surface 22 contacting the side of the lock buckle part 13, so that the lock tongue 20 can quickly penetrate into the lock hole 17.

[0062] In some embodiments, in the quick-release structure provided by the exemplary embodiment of the present utility model, the number of the locking components is two, and the two locking components are respectively located on opposite sides of the locking tongue 20, and the limiting element 16 is located in the middle of the two locking components. Figure 9-12 As shown, two lock catch assemblies are symmetrically arranged on opposite sides of the lock tongue 20, wherein the limiting element 16 is located in the center and close to the bottom wall of the lock hole 17. When the limiting element 16 is stuck in the groove 24 of the lock tongue 20, the limiting element 16 can limit the degree of freedom of the lock tongue 20 in the distribution direction from one lock catch assembly to another lock catch assembly, so that the dead point position between the lock tongue 20 and the lock catch portion 13 is relatively stable. Further, when the quick release structure has two symmetrically arranged lock catch assemblies, even if one of the lock catch assemblies fails, it does not affect the connection performance of the quick release structure, so it is safer. When the number of lock catch assemblies is two, since the lock catch assemblies are symmetrically arranged on opposite sides of the lock tongue 20, when performing quick release, it is only necessary to use two fingers to press the two force-applying parts 14 to move toward each other, so that the lock body 10 and the lock tongue 20 are quickly separated.

[0063] It is understandable that when the two locking components are respectively located on opposite sides of the locking tongue 20, there are also two protrusions on the top of the locking tongue 20, which are respectively located on both sides of the locking tongue 20, thereby forming a portion that cooperates with the corresponding locking components to lock.

[0064] like Figure 5 As shown, an exemplary embodiment of the utility model also provides a drone, comprising the above-mentioned parachute.

[0065] Compared with the prior art, the advantages of the drone of the exemplary embodiment of the utility model are the same as those of the above-mentioned parachute, which will not be described in detail here.

[0066] Those skilled in the art should understand that the above embodiments are only for the purpose of clearly illustrating the present invention, and are not intended to limit the scope of the present invention. For those skilled in the art, other changes or modifications may be made based on the above disclosure, and these changes or modifications are still within the scope of the present invention.

Claims

1. A parachute, characterized in that: Used for landing of a drone, the parachute includes a parachute compartment and a fixing assembly for attaching the parachute compartment to the top of the drone, the fixing assembly includes a plurality of flexible belts distributed along the circumference of the parachute compartment, one end of each of the flexible belts is connected to the parachute compartment, and the other end is used for detachable connection to a position near the bottom of the drone.

2. The parachute according to claim 1, characterized in that The parachute also includes at least two arms connected to the parachute compartment, and the arms extend obliquely toward the outside of the parachute compartment in a direction toward the drone, and one end of each flexible belt is connected to the end of the corresponding arm away from the parachute compartment.

3. The parachute according to claim 2, characterized in that The support arm comprises a connecting section, a middle section and an inclined section which are distributed away from the parachute compartment, the connecting section is connected to the side of the parachute compartment, and the connecting section and the inclined section are respectively located on two opposite sides of the middle section; At least one first reinforcing rib is provided on the inclined section, and the first reinforcing rib extends along the extending direction of the inclined section; The connecting section and the middle section are also connected via at least one second reinforcing rib, and the second reinforcing rib extends in the same direction as the first reinforcing rib.

4. The parachute according to claim 3, characterized in that The side of the connecting section facing the umbrella compartment further has at least one protrusion, and the at least one protrusion is used to be connected to the umbrella compartment in a vertical direction.

5. The parachute according to claim 3 or 4, characterized in that: The umbrella silo includes an umbrella silo body and a control cabin connected to the bottom of the umbrella silo body, and an umbrella opening device is provided in the umbrella silo body; A posture sensing unit is provided in the control cabin, and the posture sensing unit is used to obtain the flight posture of the UAV, and the posture sensing unit is communicatively connected with the parachute opening device.

6. The parachute according to claim 5, characterized in that Each of the supporting arms is connected to the control cabin, and the top of the control cabin also has at least one recessed portion, and each of the recessed portions is used to accommodate a corresponding protruding portion on the connecting section of the supporting arm.

7. The parachute according to claim 6, characterized in that The end of the support arm close to the parachute compartment has a preset width, and the preset width is 30% to 60% of the maximum width of the control cabin; and / or, The parachute also includes a waterproof ring located at the bottom of the control cabin, and the waterproof ring is used for waterproofing between the control cabin and the drone.

8. The parachute according to claim 1, characterized in that One end of each of the flexible belts is connected to the parachute compartment, and the other end is used to be connected to a position near the bottom of the drone through a quick-release structure; The quick-release structure comprises a lock body, a lock tongue, a limiting element and at least one lock buckle assembly, wherein the lock buckle assembly comprises a reset element and a lock buckle portion hinged to the lock body through a pin shaft, the lock body has a lock hole for the lock tongue to be inserted, and the limiting element is arranged at a position of the lock hole close to the bottom wall; The top end of the locking tongue has a top surface and a protruding portion protruding from at least one side surface of the locking tongue, the protruding portion has a first abutting surface and a sliding surface adjacent to the first abutting surface, and the sliding surface is used to push the locking portion to rotate from the first position to the second position; The lock tongue has a groove formed on the top surface, the groove abuts against the limiting element, and the lock portion returns to the first position under the action of the resetting element; wherein, the lock portion has a second abutting surface at one end away from the pin shaft, and a third abutting surface at the other end close to the pin shaft; the first abutting surface abuts against the second abutting surface, and the third abutting surface abuts against the shell of the lock body.

9. The parachute according to claim 8, characterized in that The lock assembly also includes a force-applying portion for disengaging the lock portion from the lock tongue, wherein the force-applying portion is connected to an end portion of the lock portion close to the pin shaft.

10. A drone, characterized in that: A parachute comprising the parachute described in any one of claims 1 to 9.

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