Undercarriage and unmanned aerial vehicle
By using magnetic components between the landing gear and fuselage of the drone, the problems of increased weight and reduced endurance caused by carrying the landing gear during flight are solved, and more efficient flight performance and convenient operation are achieved.
Patent Information
- Application Number
- CN202422011916.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-19
- Publication Date
- 2025-05-13
- Estimated Expiration
- 2034-08-19
AI Technical Summary
Existing drones need to carry landing gear during flight, resulting in increased weight, reduced endurance and mileage, and the disassembly of landing gear is cumbersome and inconvenient.
A landing gear driven by magnetic elements is designed. By providing magnetic elements on the first bottom surface of the landing gear and the abdomen of the fuselage of the drone, the landing gear and the fuselage can be quickly disassembled and connected, and separate flight of the landing gear can be achieved.
It realizes that the drone does not need to carry a landing gear during flight, thereby reducing weight, improving endurance and flight stability. At the same time, it simplifies the disassembly and installation process of the landing gear, making the operation simple and convenient.
Smart Images
Figure CN222859753U_ABST
Abstract
Description
[Technical field]
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a landing gear and a unmanned aerial vehicle. [Background technology]
[0002] With the development of science and technology and the low-altitude economy, drones are being used more widely in all walks of life. Drones have begun to be gradually applied from traditional limited scenarios such as test aircraft and reconnaissance aircraft to various industries such as logistics, transportation, and warfare.
[0003] Compared with traditional aircraft, for example, most civil aircraft have airport runways for takeoff and landing. However, for drones, as the application scenarios gradually diversify, it is not realistic to open separate airport runways for them. Therefore, most existing drones have their own landing gear. The existing drones have the landing gear set under the drone, and the two are an integrated structure to facilitate the need for the drone to land anytime and anywhere. As a result, the drone also needs to fly with the lower landing gear during the flight, but during the flight, the drone's landing gear does not play a role, and increases the overall weight of the drone, thereby reducing the drone's endurance and flight mileage.
[0004] Based on this, there is an urgent need to develop a landing gear and a corresponding UAV so that the UAV can be separated from the landing gear during flight, and the separation method needs to be as simple and convenient as possible to meet the diversified and complex application scenarios of UAVs. [Contents of the utility model]
[0005] In view of the above technical problems in the prior art, the utility model provides a landing gear, comprising:
[0006] Support device;
[0007] The landing platform, the supporting device is arranged below the landing platform, and the landing platform comprises:
[0008] first side;
[0009] Second side;
[0010] A first bottom surface, wherein the first bottom surface, the first side surface and the second side surface together form a landing groove;
[0011] The supporting device is respectively connected to the first side surface and the second side surface;
[0012] The first bottom surface is provided with a first magnetic element.
[0013] It should be noted that the first bottom surface is provided with a first magnetic element, so that the landing gear and the fuselage can be quickly disassembled. The traditional disassembly process also requires manpower to tighten or loosen the parts, which takes a long time and is inconvenient to operate. However, the utility model operates through magnetic elements, does not require additional manpower for manual tightening or loosening operations, and only needs to control the change in the size of the magnetism, and relies on the size of the magnetism to immediately achieve the separation and bonding of the landing gear and the fuselage.
[0014] Specifically, the first bottom surface includes a plurality of reinforcing edges distributed in a circumferential direction, and the plurality of reinforcing edges are connected to form the first bottom surface together, and the first bottom surface is a hollow structure in the middle.
[0015] It should be noted that the first bottom surface is designed as a hollow structure in the middle. On the one hand, this is to save materials and reduce costs. On the other hand, this is because the first bottom surface is located at the belly of the fuselage. During the use of the drone, the belly of the fuselage may involve hanging items or installing other electronic components.
[0016] Specifically, a receiving cavity is provided on the surface of the reinforcing edge for receiving the first magnetic element.
[0017] Specifically, the first side surface includes a plurality of reinforcing ribs spaced apart longitudinally, and the plurality of reinforcing ribs surround the first side surface;
[0018] The second side surface includes a plurality of reinforcing ribs spaced apart longitudinally, and the plurality of reinforcing ribs surround the second side surface;
[0019] A plurality of the reinforcing ribs and a plurality of the reinforcing edges are fixedly connected to form the landing groove.
[0020] It should be noted that the structure of the landing groove is that the reinforcing ribs and the reinforcing edges enclose a space, and the space is named as the landing groove here.
[0021] Specifically, the support device includes: a support column; a base column fixedly connected to the support column; the support column and the base column form a support surface, and the support surface is trapezoidal.
[0022] It should be noted that the support surface can also be made into a hollow structure and surrounded by only four frames. The beneficial effect of using a trapezoidal shape here is to enhance the stability of the support surface.
[0023] The utility model also provides a drone comprising:
[0024] said landing gear;
[0025] A fuselage is detachably connected to the landing gear.
[0026] Specifically, the fuselage includes:
[0027] The belly of the fuselage has a shape that matches the shape of the landing slot, so that the belly of the fuselage can be accommodated in the landing slot;
[0028] A second magnetic element is disposed on the outer surface of the belly of the fuselage, and the second magnetic element is opposite to the first magnetic element;
[0029] There is an attractive force between the first magnetic element and the second magnetic element.
[0030] Specifically, the belly of the fuselage includes:
[0031] The convex ridge is arranged on one side of the second magnetic element, and the positions of the convex ridge and the reinforcing ridge correspond to each other, and the two are engaged with each other.
[0032] Specifically, the fuselage includes a fuselage side portion, and the shape of the fuselage side portion is adapted to the shape of the landing slot, so that the fuselage side portion can be accommodated in the landing slot;
[0033] The fuselage side portion and the fuselage belly form a landing outer surface of the fuselage, and the landing outer surface can be accommodated in the landing slot.
[0034] Specifically, the magnetic magnitude of the first magnetic element may vary.
[0035] The utility model provides a landing gear, and a drone using the landing gear, wherein the landing gear includes: a supporting device; a landing platform, the supporting device is arranged below the landing platform, and the landing platform includes: a first side surface; a second side surface; a first bottom surface, the first bottom surface, the first side surface and the second side surface together form a landing groove; the supporting device is respectively connected to the first side surface and the second side surface; the first bottom surface is provided with a first magnetic element. By providing the magnetic element, the disassembly process between the landing gear and the fuselage of the drone can be completed very simply and conveniently, so that the drone does not need to carry the landing gear additionally during flight, thereby improving the endurance of the drone. Secondly, the magnetic connection method requires fewer connecting parts, is simple and convenient to connect, has a low probability of failure, and is simple and efficient to operate.
Brief Description of the Drawings
[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative work, among which:
[0037] Figure 1 It is a schematic diagram of the structure of a UAV revealed;
[0038] Figure 2 It is a structural schematic diagram of a landing gear disclosed;
[0039] Figure 3 It is revealing Figure 1 Schematic diagram of the structure of the belly of the drone. [Specific implementation method]
[0040] 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 of 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.
[0041] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back...) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.
[0042] In addition, in the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.
[0043] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" 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 an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0044] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.
[0045] See also Figure 1 , Figure 1 1 is a schematic diagram of the structure of a drone disclosed in the utility model; the drone 100 comprises a landing gear 1, a fuselage 3 and a propeller 5, wherein the landing gear 1 is mounted below the fuselage 3 and the two are detachably connected. The propeller 5 is mounted above the fuselage 3 and the two are detachably connected.
[0046] In a preferred embodiment, the blades 5 are also installed at the rear of the fuselage 3 .
[0047] The beneficial effect of the above technical solution is that the fuselage 3 and the landing gear 1 are connected in a detachable manner, so that the landing gear 1 and the fuselage 3 are separated during the flight of the UAV 100, thereby reducing the weight of the fuselage 3 and improving the endurance and flight stability of the UAV 100.
[0048] See also Figure 2 and Figure 3 , Figure 2 It is a structural schematic diagram of a landing gear disclosed by the utility model. Figure 3 It is revealing Figure 1 The structural diagram of the belly of the fuselage of the UAV in FIG. The landing gear 1 includes: a supporting device 11; a landing platform 13; the supporting device 11 is arranged below the landing platform 13, and the landing platform 13 includes a first side surface 131; a second side surface 133; a first bottom surface 135; the first bottom surface 135, the first side surface 131 and the second side surface 133 together form a landing slot 137. The supporting device 11 is connected to the first side surface 131 and the second side surface 133 respectively. The first bottom surface 135 is provided with a first magnetic element 139.
[0049] It should be noted that the first magnetic element 139 can be a magnet or a magnetizable magnetic metal.
[0050] In one embodiment of the utility model, the first bottom surface 135, the first side surface 131 and the second side surface 133 of the landing platform 13 are respectively solid panel structures, and the first bottom surface 135, the first side surface 131 and the second side surface 133 form a "U"-shaped landing groove 137.
[0051] It should be noted that the shape of the landing slot 137 may vary according to the actual model of the UAV.
[0052] In another embodiment of the utility model, the first bottom surface 135, the first side surface 131 and the second side surface 133 of the landing platform 13 are respectively hollow panel structures. It should be noted that the first bottom surface 135 includes a plurality of reinforcing ribs 1351 distributed circumferentially, and the plurality of reinforcing ribs 1351 are connected to form the first bottom surface 135, and the first bottom surface 135 is a hollow structure in the middle. A receiving cavity 1352 is provided on the surface of the reinforcing ribs 1351 for accommodating the first magnetic element 139. The first side surface 131 includes a plurality of reinforcing ribs 1311 distributed longitudinally at intervals, and the plurality of reinforcing ribs 1311 form the first side surface 131; the second side surface 133 includes a plurality of reinforcing ribs 1311 distributed longitudinally at intervals, and the plurality of reinforcing ribs 1311 form the second side surface 133; the plurality of reinforcing ribs 1311 and the plurality of reinforcing ribs 1351 are fixedly connected to form the landing slot 137.
[0053] It should be noted that the first magnetic element 139 can be finally fixed in the accommodating cavity 1352 by gluing, snapping, etc.
[0054] The beneficial effect of the above technical solution is that the first bottom surface 135, the first side surface 131 and the second side surface 133 are set as a hollow frame-like structure, which reduces the weight of the first bottom surface 135, the first side surface 131 and the second side surface 133, reduces the cost of consumables, and reduces the weight of the drone 100.
[0055] See also Figure 2 and Figure 3 , Figure 2 It is a structural schematic diagram of a landing gear disclosed by the utility model; Figure 3 It is revealing Figure 1 The support device 11 includes:
[0056] The support column 111 and the bottom column 113 are fixedly connected to the support column 111 ; the support column 111 and the bottom column 113 form a support surface 115 , and the support surface 115 is a hollow trapezoid.
[0057] The base column 113 mentioned here is fixedly connected to the support column 111 , and the two may be integrally connected or detachably connected.
[0058] In another embodiment, the supporting device 11 may also be directly designed as a solid trapezoidal panel structure.
[0059] The beneficial effect of adopting the trapezoidal design is that it has better force stability during the support process, which facilitates the drone 100 to have better landing effect and stability after landing and reduces the occurrence of failure rate.
[0060] If the trapezoidal structure is designed to be hollow, and only the support columns 111 and the bottom columns 113 are used to form a hollow trapezoid, the weight of the landing gear will be further reduced, thereby reducing the cost.
[0061] See also Figure 2 and Figure 3 , Figure 2 It is a structural schematic diagram of a landing gear disclosed; Figure 3 It is revealing Figure 1 Schematic diagram of the structure of the belly of the drone.
[0062] The fuselage 3 includes a fuselage belly 31, and the shape of the fuselage belly 31 is adapted to the shape of the landing slot 137, so that the fuselage belly 31 can be accommodated in the landing slot 137;
[0063] A second magnetic element 33 is disposed on the outer surface of the belly 31 of the fuselage, and the second magnetic element 33 and the first magnetic element 139 are located opposite to each other;
[0064] There is an attractive force between the first magnetic element 139 and the second magnetic element 33 .
[0065] The beneficial effect of the above technical solution is that, by arranging the second magnetic element 33 on the belly of the fuselage 31 and arranging the first magnetic element 139 on the landing gear 13, the fuselage 3 and the landing gear 1 can be detachably connected without adding other parts through the principle that the first magnetic element 33 and the second magnetic element 33 can attract each other. This detachable connection method has a simple structure, low cost, and is not prone to loss.
[0066] In a preferred embodiment, the magnetism of the first magnetic element 139 and / or the second magnetic element 33 can be changed, and the detachable process between the two can be achieved by adjusting the magnitude of the magnetic force between the two.
[0067] The belly portion 31 of the fuselage includes: a convex ridge 313, which is arranged on one side of the second magnetic element 33, and the positions of the convex ridge 313 and the reinforcing ridge 1351 correspond to each other, and the two are engaged with each other.
[0068] The beneficial effect of this technical solution is that the positioning effect is achieved through the position correspondence and locking relationship between the convex edge 313 and the reinforcing edge 1351, so that when the fuselage 3 and the landing gear 1 are assembled together, the first magnetic element 139 and the second magnetic element 33 are positioned correspondingly and attracted to each other.
[0069] The fuselage 3 includes a fuselage side portion 35 , and the shape of the fuselage side portion 35 is adapted to the shape of the landing slot 137 , so that the fuselage side portion 35 can be accommodated in the landing slot 137 .
[0070] The fuselage side portion 35 and the fuselage belly 31 form a landing outer surface 37 of the fuselage 3 , and the landing outer surface 37 can be accommodated in the landing slot 137 .
[0071] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.
Claims
1. A landing gear, characterized in that: include: Support device; The landing platform, the supporting device is arranged below the landing platform, and the landing platform comprises: first side; Second side; A first bottom surface, wherein the first bottom surface, the first side surface and the second side surface together form a landing groove; The supporting device is respectively connected to the first side surface and the second side surface; The first bottom surface is provided with a first magnetic element.
2. The landing gear according to claim 1, characterized in that The first bottom surface includes a plurality of reinforcing edges distributed in a circumferential direction, and the plurality of reinforcing edges are connected to form the first bottom surface together, and the first bottom surface is a hollow structure in the middle.
3. The landing gear according to claim 2, characterized in that: The surface of the reinforcing edge is provided with an accommodating cavity for accommodating the first magnetic element.
4. The landing gear according to claim 2, characterized in that: The first side surface includes a plurality of reinforcing ribs spaced apart longitudinally, and the plurality of reinforcing ribs surround the first side surface; The second side surface includes a plurality of reinforcing ribs spaced apart longitudinally, and the plurality of reinforcing ribs surround the second side surface; A plurality of the reinforcing ribs and a plurality of the reinforcing edges are fixedly connected to form the landing groove.
5. The landing gear according to claim 1, characterized in that: The supporting device comprises: Support columns; A bottom column is fixedly connected to the support column; the support column and the bottom column form a support surface, and the support surface is trapezoidal.
6. A drone, characterized in that: include: The landing gear according to any one of claims 1 to 5; A fuselage is detachably connected to the landing gear.
7. The drone according to claim 6, characterized in that: The fuselage comprises: The belly of the fuselage has a shape that matches the shape of the landing slot, so that the belly of the fuselage can be accommodated in the landing slot; A second magnetic element is disposed on the outer surface of the belly of the fuselage, and the second magnetic element is opposite to the first magnetic element; There is an attractive force between the first magnetic element and the second magnetic element.
8. The drone according to claim 7, characterized in that: The belly of the fuselage includes a convex ridge, which is arranged on one side of the second magnetic element; The first bottom surface includes a plurality of reinforcing edges distributed in the circumferential direction, and the positions of the convex edges and the reinforcing edges correspond to each other and the two are engaged with each other.
9. The drone according to claim 7, characterized in that: The fuselage comprises: A fuselage side portion, the shape of which matches the shape of the landing slot so that the fuselage side portion can be accommodated in the landing slot; The fuselage side portion and the fuselage belly form a landing outer surface of the fuselage, and the landing outer surface can be accommodated in the landing slot.
10. The drone according to claim 7, characterized in that: The magnetic magnitude of the first magnetic element can be changed.