Landing device for inspection unmanned aerial vehicle

Abstract

The utility model relates to the technical field of auxiliary parts of unmanned aerial vehicles, in particular to a landing device of an inspection unmanned aerial vehicle, which solves the technical problem that a small unmanned aerial vehicle body in the prior art is easy to damage power parts of the body under the impact of an existing elastic device, and comprises an unmanned aerial vehicle shell, a landing cabin assembly and a landing cabin, the landing bin assembly is provided with a release end, and the release end is connected with a release cover. The ejection mechanism is arranged on the landing bin assembly, and a parachute is arranged between the ejection mechanism and the release cover; the driving mechanism can drive the ejection mechanism to apply elastic force to the parachute to break through the release cover to eject the parachute; according to the technical scheme, released elastic force is more concentrated, the parachute can be effectively and directly released, and power components of the unmanned aerial vehicle are prevented from being damaged by counter-acting force.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle auxiliary components, in particular to a landing device for an inspection unmanned aerial vehicle. Background Art

[0002] In the current method, the UAV landing device uses a parachute and an ejection device to complete an emergency landing. The main problem in the prior art is that the landing device is configured on a large and heavy UAV, and the ejection landing can play a good role; but for small UAVs, specifically UAVs with a fuselage and wings less than 20 cm in length, the ejection landing will impact the fuselage and cause damage to the key power components of the fuselage; and UAVs of this size are common types of UAVs in the prior art, and they will also carry some shooting data. If the parachute cannot be deployed in time to avoid danger, the data at work will be lost; therefore, the prior art lacks a UAV landing device to adapt to the release of the landing device of a smaller UAV to reduce the impact on the fuselage. Utility Model Content

[0003] The utility model aims to solve the technical problem in the prior art that the fuselage of a small UAV is easily damaged by the impact of an existing elastic device, and provides a landing device for an inspection UAV.

[0004] In order to solve the above technical problems, the technical solution of the utility model is as follows:

[0005] A landing device for an inspection drone, comprising:

[0006] A drone casing, with a landing chamber assembly connected to the top;

[0007] The landing chamber assembly has a release end, and the release end is connected to a release cover;

[0008] An ejection mechanism, which is arranged on the landing chamber assembly, and a parachute is arranged between the ejection mechanism and the release cover;

[0009] The driving mechanism can drive the ejection mechanism to apply elastic force to the parachute to break through the release cover and eject the parachute.

[0010] Specifically, the landing chamber assembly includes:

[0011] Landing capsule shell;

[0012] A first slideway groove and a second slideway groove are constructed in the landing chamber shell;

[0013] The plane formed by the first slide groove is parallel to the plane formed by the second slide groove;

[0014] The first slideway groove is internally connected to a first frame;

[0015] The second slideway groove has a second frame connected to the inner rail;

[0016] The first frame and the second frame are connected by a compression spring.

[0017] Specifically, the compression spring has a compressed state;

[0018] In the compressed state, a connecting portion is rotatably connected to one side of the first frame and one side of the second frame, and is inclined.

[0019] Specifically, in the compressed state, the first end of the first frame is fixedly connected to the first connection plate;

[0020] A second connection plate is fixedly connected to the first end of the second frame;

[0021] Two ends of the compression spring are fixedly connected to the first connection plate and the second connection plate respectively.

[0022] Specifically, in the compressed state, an umbrella space is provided between the first connection disk and the release cover.

[0023] Specifically, a positioning hole is provided on the connecting portion, a positioning shaft is passed through the positioning hole, and the positioning shaft is connected to the landing chamber shell.

[0024] Specifically, both ends of the connecting portion can be rotatably connected to a rotating shaft seat respectively;

[0025] A group of the rotating shaft seats is respectively arranged on the far side of the first frame relative to the compression spring and on the far side of the second frame relative to the compression spring.

[0026] Specifically, a cylinder connection plate is provided at the second end of the second frame;

[0027] The cylinder connecting plate is connected to an output end of a driving cylinder;

[0028] The driving cylinder is fixedly connected in the casing of the drone.

[0029] Specifically, in the compressed state, the second frame is limited by a limit stop block, and the limit stop block is arranged on the second slide groove.

[0030] Specifically, the release cover is connected to the first end of the landing chamber shell through a plurality of connection traces;

[0031] The parachute comprises a parachute rope, a parachute body and a parachute end arranged on the parachute body;

[0032] The parachute rope connects the parachute body and the first connecting plate;

[0033] The umbrella body is squeezed and placed in the umbrella arrangement space.

[0034] The utility model has the following beneficial effects:

[0035] The present application relies on a compression spring to transmit elastic force in a directional direction to achieve the purpose of releasing the parachute body. There is no specific requirement for the force applied by the driving cylinder, so that the force direction of the entire elastic release process is more concentrated, and the reaction force has a driving cylinder, which is equivalent to a buffer for the reaction force, avoiding direct impact on the power components in the drone and preventing damage.

[0036] Therefore, the elastic force released in this technical solution is more concentrated, which can effectively release the parachute directly and avoid the reaction force from damaging the power components of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The utility model is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0038] Figure 1 It is a schematic diagram of the structure of the utility model;

[0039] Figure 2 It is a schematic diagram of the first slideway groove and the second slideway groove of the utility model;

[0040] Figure 3 A three-dimensional schematic diagram of one side of the utility model;

[0041] Figure 4 It is a cross-sectional schematic diagram of the utility model;

[0042] Figure 5 It is a three-dimensional schematic diagram of the other side of the utility model.

[0043] The reference numerals in the figures indicate:

[0044] UAV housing 10, landing chamber assembly 20, ejection mechanism 30, release cover 201, drive mechanism 40;

[0045] A first slideway groove 211, a second slideway groove 212, a first frame 221, and a second frame 222;

[0046] Compression spring 223, first connection plate 251, second connection plate 252, connection portion 240;

[0047] Umbrella space 1001, rotating shaft seat 241, positioning hole 214;

[0048] Driving cylinder 41 , limiting blocking block 270 , connection trace portion 281 , umbrella end 293 , umbrella rope 291 , and umbrella body 292 . DETAILED DESCRIPTION

[0049] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model; it should be noted that in this application, for the convenience of description, the "left side" in the current view is the "first end", the "right side" is the "second end", the "upper side" is the "first end", and the "lower side" is the "second end". The purpose of such description is to clearly express the technical solution, and it should not be understood as an improper limitation on the technical solution of this application.

[0050] The utility model aims to solve the technical problem in the prior art that the fuselage of a small UAV is easily damaged due to the impact of an existing elastic device, and provides a landing device for the inspection UAV, the main structure of which includes: a UAV casing 10, the top of which is connected to a landing chamber assembly 20; the landing chamber assembly 20 has a release end, and the release end is connected to a release cover 201; an ejection mechanism 30, which is arranged on the landing chamber assembly 20, and a parachute 202 is arranged between the ejection mechanism 30 and the release cover 201; a driving mechanism 40, which can drive the ejection mechanism 30 to apply an elastic force to the parachute 202 to break through the release cover 201 and eject the parachute 202.

[0051] The specific working principle is: the driving mechanism 40 is a driving cylinder 41, and when the cylinder rod is output, the compression spring enters a compressed state, and the umbrella is deployed at this time; when the cylinder rod of the driving cylinder 41 is retracted, the relative separation of the first frame 221 and the second frame 222 is completed by the rotation of the connecting part 240, and at this time the compression spring releases the elastic force to directly impact the release cover 201, and after the connection trace part 281 is damaged, the umbrella body 292 is unfolded.

[0052] It should be noted that the attached Figure 3 FIG. 2 shows an extreme state in which the connecting portion 240 is rotated and the compression spring is released. Figure 3 The situation of the middle wing 292 is not shown in the attached Figure 3 Shown in.

[0053] In a specific embodiment, please refer to the attached Figure 3 , 4As shown in Figures 5 and 6, the landing bin assembly 20 includes: a landing bin shell 210; a first slide groove 211 and a second slide groove 212, which are constructed in the landing bin shell 210; a plane formed by the first slide groove 211 and a plane formed by the second slide groove 212 are parallel; a first frame 221 is connected to the inner rail of the first slide groove 211; a second frame 222 is connected to the inner rail of the second slide groove 212; the first frame 221 and the second frame 222 are connected by a compression spring 223.

[0054] In a specific embodiment, the attached Figure 3 As shown, the compression spring 223 has a compressed state; in the compressed state, a connecting portion 240 is rotationally connected to one side of the first frame 221 and one side of the second frame 222, respectively, and is inclined.

[0055] In a specific embodiment, in the compressed state, the first end of the first frame 221 is fixedly connected to the first connection disk 251; the first end of the second frame 222 is fixedly connected to the second connection disk 252;

[0056] Two ends of the compression spring are fixedly connected to the first connection plate 251 and the second connection plate 252 respectively.

[0057] In a specific embodiment, in the compressed state, an umbrella space 1001 is provided between the first connection disk 251 and the release cover 201 .

[0058] In a specific embodiment, a positioning hole 214 is provided on the connecting portion 240 , a positioning shaft 242 is passed through the positioning hole 214 , and the positioning shaft 242 is connected to the landing chamber shell 210 .

[0059] In a specific embodiment, both ends of the connection portion 240 are rotatably connected to a rotation shaft seat 241;

[0060] A group of rotating shaft seats 241 are respectively disposed on the far side of the first frame 221 relative to the compression spring 223 and the far side of the second frame 222 relative to the compression spring 223 .

[0061] In a specific embodiment, a cylinder connection plate 260 is provided at the second end of the second frame 222;

[0062] The cylinder connection plate 260 is connected to an output end of a driving cylinder 41;

[0063] The driving cylinder 41 is fixedly connected in the drone housing 10 .

[0064] In a specific embodiment, in the compressed state, the second frame 222 is limited by a limit stop block 270 , and the limit stop block 270 is disposed on the second slideway groove 212 .

[0065] In a specific embodiment, the release cover 201 is connected to the first end of the landing chamber shell 210 through a plurality of connection traces 281; the parachute 202 has a parachute rope 291, a parachute body 292 and an umbrella end 293 arranged on the parachute body 292; the parachute rope 291 connects the parachute body 292 and the first connecting plate 251; the parachute body 292 is squeezed and placed in the parachute setting space 1001, and the function of the umbrella end 293 is to facilitate the installation during the squeezing.

[0066] To sum up, the present application relies on the compression spring 223 to transmit elastic force in a directional direction to achieve the purpose of releasing the parachute body 292. There is no specific requirement for the force applied by the driving cylinder 41, so that the force direction of the entire elastic release process is more concentrated, and the reaction force has the driving cylinder 41, which is equivalent to a buffer for the reaction force, avoiding direct impact on the power components in the drone and preventing damage.

[0067] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A landing device for an inspection drone, characterized in that: include: A drone housing (10) having a landing chamber assembly (20) connected to the top thereof; The landing chamber assembly (20) has a release end, and the release end is connected to a release cover (201); An ejection mechanism (30) is arranged on the landing chamber assembly (20), and a parachute (202) is arranged between the ejection mechanism (30) and the release cover (201); A driving mechanism (40) capable of driving the ejection mechanism (30) to exert elastic force on the parachute (202) to break through the release cover (201) and eject the parachute (202); The landing chamber assembly (20) comprises: Landing chamber housing (210); A first slide groove (211) and a second slide groove (212) are constructed in the landing chamber shell (210); The plane formed by the first slide groove (211) and the plane formed by the second slide groove (212) are parallel; The inner rail of the first slideway groove (211) is connected to a first frame (221); The inner rail of the second slideway groove (212) is connected to a second frame (222); The first frame (221) and the second frame (222) are connected via a compression spring (223); The compression spring (223) has a compressed state; In the compressed state, a connecting portion (240) is rotatably connected to one side of the first frame (221) and one side of the second frame (222) respectively, and is in an inclined shape; In the compressed state, the first end of the first frame (221) is fixedly connected to the first connection plate (251); A second connection plate (252) is fixedly connected to the first end of the second frame (222); Two ends of the compression spring are respectively fixedly connected to the first connection plate (251) and the second connection plate (252); In the compressed state, an umbrella space (1001) is provided between the first connection disk (251) and the release cover (201).

2. The inspection drone landing device according to claim 1, characterized in that: The connection portion (240) is provided with a positioning hole (214), a positioning shaft (242) is passed through the positioning hole (214), and the positioning shaft (242) is connected to the landing chamber shell (210).

3. The inspection drone landing device according to claim 2, characterized in that: Both ends of the connecting portion (240) are rotatably connected to a rotating shaft seat (241); A group of rotating shaft seats (241) are respectively provided on the far side of the first frame (221) relative to the compression spring (223) and on the far side of the second frame (222) relative to the compression spring (223).

4. The inspection drone landing device according to claim 3, characterized in that: A cylinder connecting plate (260) is provided at the second end of the second frame (222); The cylinder connecting plate (260) is connected to an output end of a driving cylinder (41); The driving cylinder (41) is fixedly connected in the drone housing (10); In the compressed state, the second frame (222) is limited by a limit stop block (270), and the limit stop block (270) is arranged on the second slideway groove (212).

5. The inspection drone landing device according to claim 4, characterized in that: The release cover (201) is connected to the first end of the drop chamber shell (210) via a plurality of connection traces (281); The parachute (202) comprises a parachute rope (291), a parachute body (292), and a parachute end (293) arranged on the parachute body (292); The parachute rope (291) connects the parachute body (292) and the first connecting plate (251); The umbrella body (292) is squeezed and placed in the umbrella arrangement space (1001).

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