Aircraft recovery device and aircraft

Abstract

The utility model discloses an aircraft recovery device and an aircraft, and relates to the technical field of aircrafts. The recycling bin is installed on the foundation, the end, away from the ground, of the recycling bin is of an opening structure, and a plurality of through holes are formed in the side wall of the recycling bin in the circumferential direction; the fixing mechanisms are arranged on the outer side of the recycling bin in the circumferential direction; the multiple locking mechanisms are rotationally connected to the multiple fixing mechanisms corresponding to the locking mechanisms, at least part of the locking mechanisms penetrate through the through holes and are located in the recycling barrel, and when the aircraft is recycled, the part of the locking mechanisms located in the recycling barrel abut against the bottom of the aircraft. And the locking mechanism located outside the recycling bin penetrates through the through hole and abuts against the outer wall of the aircraft so as to lock the aircraft. Therefore, according to the aircraft recovery device, the aircraft is prevented from carrying an undercarriage, the energy consumption of the aircraft is reduced, the flight performance of the aircraft is improved, and meanwhile, the recovery safety of the unmanned aerial vehicle is improved.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft recovery device and an aircraft. Background Art

[0002] A drone is an aircraft that is controlled by radio remote control or onboard computer program control equipment. After being launched, the aircraft must be recovered by a specific device to complete the next aircraft launch operation.

[0003] At present, aircraft are usually recovered by using arresting nets or built-in landing gear. Arresting nets can intercept and recover aircraft, which may cause damage to the aircraft during the recovery process. Aircraft with built-in landing gear rely on landing gear to take off or land, but the take-off weight of the aircraft is increased, thereby increasing the energy consumption of the aircraft. Utility Model Content

[0004] The embodiments of the present application provide an aircraft recovery device and an aircraft, thereby solving the technical problems in the prior art that an arresting net may cause damage to the aircraft during the recovery process, and an aircraft with its own landing gear will increase the take-off weight of the aircraft and increase the energy consumption of the aircraft.

[0005] In a first aspect, an embodiment of the present application provides an aircraft recovery device, comprising: a recovery bucket installed on a foundation, an end of which is away from the ground is an open structure, and a plurality of through holes are circumferentially arranged on its side wall; a plurality of fixing mechanisms are arranged on the circumferential outer side of the recovery bucket; a plurality of locking mechanisms are rotatably connected to a plurality of the fixing mechanisms corresponding thereto, and at least part of the locking mechanisms pass through the through holes and are located in the recovery bucket, and are configured such that when the aircraft is recovered, the locking mechanisms partially located in the recovery bucket abut against the bottom of the aircraft, so that the locking mechanisms located outside the recovery bucket pass through the through holes and abut against the outer wall of the aircraft to lock the aircraft.

[0006] In combination with the first aspect, in a possible implementation, the fixing mechanism includes a first connecting plate, a second connecting plate, a third connecting plate and a rotating shaft; the first connecting plate is installed on the base and is arranged on the circumferential outer side of the recycling bin; the second connecting plate and the third connecting plate are both connected to the first connecting plate and are spaced apart along the length direction of the first connecting plate; the two ends of the rotating shaft are respectively connected to the second connecting plate and the third connecting plate; the locking mechanism is sleeved on the outer wall of the rotating shaft and is rotatably connected to the rotating shaft.

[0007] In combination with the first aspect, in a possible implementation, the fixing mechanism also includes a limit plate; the two ends of the limit plate are respectively connected to the second connecting plate and the third connecting plate, and are located on the side of the locking mechanism away from the recovery barrel, and are configured to prevent the locking mechanism from rotating in the opposite direction.

[0008] In combination with the first aspect, in a possible implementation, the locking mechanism includes a first locking tongue, a second locking tongue and two elastic members; one end of the first locking tongue is a free end, and the other end of the first locking tongue is connected to one end of the second locking tongue, and the other end of the second locking tongue is a free end; the second locking tongue is sleeved on the outer wall of the rotating shaft and is rotatably connected to the rotating shaft; the length of the first locking tongue is less than the length of the second locking tongue; the two elastic members are both sleeved on the outer wall of the rotating shaft and are located on both sides of the second locking tongue; when the aircraft is not recovered, the second locking tongue is located in the recovery bucket, and the first locking tongue abuts against the limit plate under the pre-tightening force of the elastic member; when the aircraft is recovered, the second locking tongue abuts against the bottom of the aircraft, and the second locking tongue rotates, driving the first locking tongue to rotate, so that the first locking tongue passes through the through hole and abuts against the outer wall of the aircraft to lock the aircraft.

[0009] In combination with the first aspect, in a possible implementation manner, the recovery barrel is a bell-mouth structure.

[0010] In combination with the first aspect, in a possible implementation, three of the fixing mechanism and three of the locking mechanism are provided, and the three fixing mechanisms are evenly arranged on the circumferential outer side of the recovery barrel.

[0011] In combination with the first aspect, in a possible implementation, the foundation includes a bottom plate; and an upper surface of the bottom plate is connected to the bottom of the recycling barrel.

[0012] In combination with the first aspect, in a possible implementation manner, a plurality of locking holes are arranged around the bottom plate.

[0013] In combination with the first aspect, in a possible implementation, the aircraft recovery device further includes a plurality of lifting ears; the plurality of lifting ears are all arranged in the circumference of a side of the base plate away from the ground.

[0014] In a second aspect, an embodiment of the present application provides an aircraft, wherein the aircraft comprises the aircraft recovery device described in the first aspect or any possible implementation of the first aspect.

[0015] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0016] The present application provides an aircraft recovery device including a recovery bucket, a fixing mechanism and a locking mechanism. The recovery bucket of the embodiment of the present application plays a positioning role for the aircraft. When recovering the aircraft, the aircraft enters the recovery bucket, and the bottom of the aircraft first abuts against the locking mechanism located in the recovery bucket. The aircraft is acted upon by gravity so that its weight acts on the locking mechanism, and the locking mechanism rotates along the fixing mechanism so that the locking mechanism located outside the recovery bucket passes through the through hole and clamps to the outer wall of the aircraft to lock the aircraft. Therefore, the aircraft recovery device of the embodiment of the present application avoids the aircraft carrying landing gear, reduces the energy consumption of the aircraft, improves the flight performance of the aircraft, and at the same time improves the safety of drone recovery. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments of the present application will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 A schematic diagram of the structure of an aircraft recovery device provided in an embodiment of the present application;

[0019] Figure 2 A front view of an aircraft recovery device provided in an embodiment of the present application;

[0020] Figure 3 A top view of an aircraft recovery device provided in an embodiment of the present application;

[0021] Figure 4 A schematic diagram of the structure of the fixing mechanism and the locking mechanism provided in the embodiment of the present application;

[0022] Figure 5 A schematic diagram of the structure of the locking mechanism provided in an embodiment of the present application when locking an aircraft;

[0023] Figure 6 This is a schematic diagram of the structure of the locking mechanism provided in an embodiment of the present application when the aircraft is not locked.

[0024] Icons: 1-recycling bin; 11-through hole; 2-fixing mechanism; 21-first connecting plate; 22-second connecting plate; 23-third connecting plate; 24-rotating shaft; 25-limiting plate; 3-locking mechanism; 31-first locking tongue; 32-second locking tongue; 33-elastic member; 4-aircraft; 5-foundation; 51-bottom plate; 511-locking hole; 6-lifting ear. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0026] In the description of the embodiments of the present application, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0027] The present application embodiment provides an aircraft recovery device, such as Figures 1 to 6 As shown. The aircraft recovery device includes a recovery bucket 1, a fixing mechanism 2 and a locking mechanism 3. The recovery bucket 1 is installed on a base 5, and one end thereof away from the ground is an open structure, and a plurality of through holes 11 are circumferentially arranged on its side wall. The through hole 11 facilitates the passage of the locking mechanism 3. A plurality of fixing mechanisms 2 are arranged on the circumferential outer side of the recovery bucket 1. The plurality of locking mechanisms 3 are all rotatably connected to the plurality of fixing mechanisms 2 corresponding thereto, and at least part of the locking mechanisms 3 pass through the through holes 11 and are located in the recovery bucket 1, and are configured such that when the aircraft 4 is recovered, a part of the locking mechanism 3 located in the recovery bucket 1 abuts against the bottom of the aircraft 4, so that the locking mechanism 3 located outside the recovery bucket 1 passes through the through holes 11 and abuts against the outer wall of the aircraft 4 to lock the aircraft 4.

[0028] Furthermore, the aircraft 4 of the embodiment of the present application may be a coaxial unmanned aerial vehicle or a multi-rotor unmanned aerial vehicle.

[0029] It should be noted that the recycling barrel 1 of the embodiment of the present application can play a positioning role for the aircraft 4. When the aircraft 4 is recovered, the aircraft 4 enters the recycling barrel 1, and the bottom of the aircraft 4 first abuts against the locking mechanism 3 located in the recycling barrel 1. The aircraft 4 is subjected to the action of gravity, so that its weight acts on the locking mechanism 3, and the locking mechanism 3 rotates along the fixing mechanism 2, so that the locking mechanism 3 located outside the recycling barrel 1 passes through the through hole 11 and is clamped on the outer wall of the aircraft 4 to lock the aircraft 4. Therefore, the aircraft recovery device of the embodiment of the present application avoids the aircraft 4 from carrying the landing gear, reduces the energy consumption of the aircraft 4, improves the flight performance of the aircraft 4, and at the same time improves the safety of the drone recovery.

[0030] In the embodiment of the present application, the fixing mechanism 2 includes a first connecting plate 21, a second connecting plate 22, a third connecting plate 23 and a rotating shaft 24. The first connecting plate 21 is mounted on the base 5 and is arranged on the circumferential outer side of the recycling bin 1. The second connecting plate 22 and the third connecting plate 23 are both connected to the first connecting plate 21 and are arranged at intervals along the length direction of the first connecting plate 21. The two ends of the rotating shaft 24 are respectively connected to the second connecting plate 22 and the third connecting plate 23. The locking mechanism 3 is sleeved on the outer wall of the rotating shaft 24 and is rotatably connected to the rotating shaft 24.

[0031] It should be noted that the second connecting plate 22 and the third connecting plate 23 of the embodiment of the present application are both provided with connecting holes, and the two ends of the rotating shaft 24 pass through the two connecting holes respectively. The second connecting plate 22 and the third connecting plate 23 of the embodiment of the present application are arranged in parallel and are both vertically connected to the first connecting plate 21. The first connecting plate 21 is provided with a plurality of mounting holes, and the mounting holes are used to be fixed to the foundation 5.

[0032] In the embodiment of the present application, the fixing mechanism 2 further includes a limit plate 25. The limit plate 25 is connected to the second connecting plate 22 and the third connecting plate 23 at both ends, and is located on the side of the locking mechanism 3 away from the recycling bin 1, and is configured to prevent the locking mechanism 3 from rotating in the opposite direction.

[0033] In the present application embodiment, Figure 4As shown, the locking mechanism 3 includes a first locking tongue 31, a second locking tongue 32 and two elastic members 33. One end of the first locking tongue 31 is a free end, and the other end thereof is connected to one end of the second locking tongue 32, and the other end of the second locking tongue 32 is a free end. The second locking tongue 32 is sleeved on the outer wall of the rotating shaft 24 and is rotatably connected to the rotating shaft 24. The length of the first locking tongue 31 is less than the length of the second locking tongue 32. Both elastic members 33 are sleeved on the outer wall of the rotating shaft 24 and are located on both sides of the second locking tongue 32. When the aircraft 4 is not recovered, the second locking tongue 32 is located in the recovery barrel 1, and the first locking tongue 31 abuts against the limit plate 25 under the preload force of the elastic member 33. When the aircraft 4 is recovered, the second locking tongue 32 abuts against the bottom of the aircraft 4, and the second locking tongue 32 rotates, driving the first locking tongue 31 to rotate, so that the first locking tongue 31 passes through the through hole 11 and abuts against the outer wall of the aircraft 4 to lock the aircraft 4. The first locking tongue 31 and the second locking tongue 32 of the embodiment of the present application are both provided with protrusions, and the protrusions can contact the aircraft 4 more quickly.

[0034] Specifically, the elastic member 33 has a certain preload force. When the aircraft 4 is not recovered, the elastic members 33 on both sides of the second locking tongue 32 make the first locking tongue 31 abut against the limit plate 25 to prevent the first locking tongue 31 and the second locking tongue 32 from rotating in the opposite direction.

[0035] Furthermore, the elastic member 33 in the embodiment of the present application may be a torsion spring.

[0036] It should be noted that when the aircraft 4 falls, the bottom of the aircraft 4 first abuts against the second locking tongue 32 of the locking mechanism 3, and the second locking tongue 32 rotates around the rotating shaft 24, so that the first locking tongue 31 of the locking mechanism 3 abuts against the outer wall of the aircraft 4, and the aircraft 4 acts on the second locking tongue 32, so that the first locking tongue 31 is clamped on the outer wall of the aircraft 4. Therefore, the locking mechanism 3 of the embodiment of the present application adopts a one-way mechanical design, which has higher recovery safety performance, is easy to install, and is easy to maintain.

[0037] In the embodiment of the present application, the recovery barrel 1 is a trumpet-mouth structure, and the barrel diameter on the side away from the foundation is larger, which is convenient for the aircraft 4 to locate and land.

[0038] In the embodiment of the present application, three fixing mechanisms 2 and three locking mechanisms 3 are provided, and the three fixing mechanisms 2 are evenly arranged on the circumferential outer side of the recovery barrel 1. Specifically, the three locking mechanisms 3 are evenly stressed, so that the aircraft 4 is not easy to tilt during recovery, and the recovery method is safe and reliable and can be reused. Conversely, the aircraft recovery device can be used to launch the aircraft 4.

[0039] In the embodiment of the present application, the foundation 5 includes a bottom plate 51. The upper surface of the bottom plate 51 is connected to the bottom of the recycling barrel 1. The bottom plate 51 can increase the contact area with the ground and increase the stability of the overall structure.

[0040] Of course, the foundation 5 of the embodiment of the present application is not limited to the bottom plate 51, the foundation 5 may also be the ground, and the recycling bin 1 may be directly installed on the ground.

[0041] In the embodiment of the present application, a plurality of locking holes 511 are arranged around the bottom plate 51. The plurality of locking holes 511 are used for fixing to the ground.

[0042] In the embodiment of the present application, the aircraft recovery device further includes a plurality of lifting ears 6. The plurality of lifting ears 6 are all arranged on the circumference of the side of the bottom plate 51 away from the ground, so as to facilitate the staff to carry the aircraft recovery device. In the embodiment of the present application, two lifting ears 6 are arranged and are hinged to the bottom plate 51.

[0043] In addition, an embodiment of the present application provides an aircraft, which includes the above-mentioned aircraft recovery device.

[0044] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0045] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. An aircraft recovery device, characterized in that: include: A recycling barrel (1) is installed on a foundation (5), the end of which is away from the ground is an open structure, and a plurality of through holes (11) are arranged in the circumferential direction of the side wall; A plurality of fixing mechanisms (2) are arranged on the circumferential outer side of the recovery barrel (1); A plurality of locking mechanisms (3) are rotatably connected to the plurality of fixing mechanisms (2) corresponding thereto, and at least a portion of the locking mechanisms (3) pass through the through hole (11) and are located in the recovery barrel (1). The locking mechanisms (3) are configured such that when the aircraft (4) is recovered, a portion of the locking mechanisms (3) located in the recovery barrel (1) abuts against the bottom of the aircraft (4), so that the locking mechanisms (3) located outside the recovery barrel (1) pass through the through hole (11) and abut against the outer wall of the aircraft (4), thereby locking the aircraft (4).

2. The aircraft recovery device according to claim 1, characterized in that: The fixing mechanism (2) comprises a first connecting plate (21), a second connecting plate (22), a third connecting plate (23) and a rotating shaft (24); The first connecting plate (21) is mounted on the base (5) and is arranged on the circumferential outer side of the recovery barrel (1); The second connecting plate (22) and the third connecting plate (23) are both connected to the first connecting plate (21), and are arranged at intervals along the length direction of the first connecting plate (21); Two ends of the rotating shaft (24) are respectively connected to the second connecting plate (22) and the third connecting plate (23); The locking mechanism (3) is sleeved on the outer wall of the rotating shaft (24) and is rotatably connected to the rotating shaft (24).

3. The aircraft recovery device according to claim 2, characterized in that: The fixing mechanism (2) further comprises a limiting plate (25); The two ends of the limit plate (25) are respectively connected to the second connecting plate (22) and the third connecting plate (23), and are located on a side of the locking mechanism (3) away from the recovery barrel (1), and are configured to prevent the locking mechanism (3) from rotating in the opposite direction.

4. The aircraft recovery device according to claim 3, characterized in that: The locking mechanism (3) comprises a first locking tongue (31), a second locking tongue (32) and two elastic members (33); One end of the first locking tongue (31) is a free end, and the other end thereof is connected to one end of the second locking tongue (32), and the other end of the second locking tongue (32) is a free end; The second locking tongue (32) is sleeved on the outer wall of the rotating shaft (24) and is rotatably connected to the rotating shaft (24); The length of the first locking tongue (31) is smaller than the length of the second locking tongue (32); The two elastic members (33) are both sleeved on the outer wall of the rotating shaft (24) and are located on both sides of the second locking tongue (32); When the aircraft (4) is not recovered, the second locking tongue (32) is located in the recovery bucket (1), and the first locking tongue (31) abuts against the limiting plate (25) under the action of the pre-tightening force of the elastic member (33); When the aircraft (4) is recovered, the second locking tongue (32) abuts against the bottom of the aircraft (4), and the second locking tongue (32) rotates, driving the first locking tongue (31) to rotate, so that the first locking tongue (31) passes through the through hole (11) and abuts against the outer wall of the aircraft (4) to lock the aircraft (4).

5. The aircraft recovery device according to claim 1, characterized in that: The recovery barrel (1) is of a bell-mouth structure.

6. The aircraft recovery device according to claim 1, characterized in that: The fixing mechanisms (2) and the locking mechanisms (3) are each provided in three numbers, and the three fixing mechanisms (2) are evenly arranged on the circumferential outer side of the recovery barrel (1).

7. The aircraft recovery device according to claim 1, characterized in that: The foundation (5) comprises a bottom plate (51); The upper surface of the bottom plate (51) is connected to the bottom of the recovery barrel (1).

8. The aircraft recovery device according to claim 7, characterized in that: A plurality of locking holes (511) are arranged in the circumferential direction of the bottom plate (51).

9. The aircraft recovery device according to claim 7, characterized in that: Also comprising a plurality of lifting ears (6); The plurality of lifting ears (6) are all arranged in the circumference of the side of the bottom plate (51) away from the ground.

10. An aircraft, characterized in that: It comprises an aircraft recovery device as described in any one of claims 1-9.

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