Unmanned aerial vehicle undercarriage

Abstract

The utility model discloses an undercarriage of an unmanned aerial vehicle. The undercarriage comprises an undercarriage assembly, an oil tank assembly and a load mounting assembly, the undercarriage assembly comprises undercarriage inclined supporting rods, undercarriage skid rods and an undercarriage skid connecting rod, any undercarriage skid rod is fixedly connected with any two undercarriage inclined supporting rods, and the two ends of the undercarriage skid connecting rod are connected with the undercarriage skid rods; the oil tank assembly comprises an oil tank supporting rod and an oil tank shell, the oil tank supporting rod is connected with the undercarriage inclined supporting rod, and the oil tank shell is fixed to the oil tank supporting rod; the load mounting assembly comprises a load connecting rod and a load mounting plate, the load connecting rod is connected with the undercarriage diagonal bar, and the load mounting plate is fixed on the load connecting rod. According to the undercarriage of the hybrid multi-rotor unmanned aerial vehicle, the weight of the hybrid multi-rotor unmanned aerial vehicle is reduced, the space flexibility and expansibility of equipment arrangement are improved, and the production and manufacturing cost of the unmanned aerial vehicle is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to an undercarriage of an unmanned aerial vehicle. Background Art

[0002] Most multi-rotor unmanned aerial vehicles adopt a modular unit design, and each system device of the unmanned aerial vehicle is independently assembled and used. In addition to the components of a general electric multi-rotor unmanned aerial vehicle, a hybrid multi-rotor unmanned aerial vehicle also includes a set of fuel-powered power generation system. Among them, the fuel tank for storing fuel has a large size and a heavy weight after being fully loaded with fuel, which is an important consideration in the layout design of the hybrid multi-rotor unmanned aerial vehicle. In order to ensure that the center of gravity of the multi-rotor unmanned aerial vehicle does not change due to fuel consumption during flight, the fuel tank is generally designed above the central plate of the unmanned aerial vehicle fuselage or mounted in the undercarriage below the central plate of the fuselage. To meet the requirements of the fuel tank for tightness, rigidity, mounting adaptability to the airframe, and attachment installation, most of the hybrid multi-rotor fuel tanks on the market currently use hard PE plastic material. The modular hard fuel tank of the hybrid multi-rotor unmanned aerial vehicle needs to be manufactured by rotational molding. Its installation steps are complex and its attachment hanging capacity is low. Therefore, it has no advantages in terms of cost, weight, and installation space flexibility. Content of the Utility Model

[0003] The purpose of the utility model is to provide an undercarriage of an unmanned aerial vehicle for the above problems existing in the prior art.

[0004] To achieve the above object, the utility model adopts the following technical solutions:

[0005] An undercarriage of an unmanned aerial vehicle includes an undercarriage assembly, a fuel tank assembly, and a load mounting assembly; the undercarriage assembly includes undercarriage diagonal struts, undercarriage skid bars, and undercarriage skid linkages; any one of the undercarriage skid bars is fixedly connected to any two of the undercarriage diagonal struts respectively, and both ends of the undercarriage skid linkage are connected to the undercarriage skid bars; the fuel tank assembly includes a fuel tank support rod and a fuel tank housing, the fuel tank support rod is connected to the undercarriage diagonal strut, and the fuel tank housing is fixed on the fuel tank support rod; the load mounting assembly includes a load linkage and a load mounting plate, the load linkage is connected to the undercarriage diagonal strut, and the load mounting plate is fixed on the load linkage.

[0006] Preferably, one end of the undercarriage diagonal strut is provided with a first kit, and the undercarriage diagonal strut and the undercarriage skid bar are fixedly connected through the first kit; both ends of the undercarriage skid linkage are provided with second kits, and the undercarriage skid linkage and the undercarriage skid bar are fixedly connected through the second kits.

[0007] Preferably, third kits are provided at both ends of the fuel tank support rod. The fuel tank support rod and the landing gear diagonal strut are fixedly connected through the third kits, and the load link rod is arranged in parallel with the landing gear skid link rod or the landing gear skid rod.

[0008] Preferably, the fuel tank housing includes a fuel tank bottom plate, fuel tank side plates and a fuel tank top plate. The fuel tank bottom plate, fuel tank side plates and fuel tank top plate are spliced with nuts to form the main body of the fuel tank housing. The fuel tank bottom plate and the fuel tank support rod are connected by a hoop to fix the fuel tank housing on the fuel tank support rod.

[0009] Preferably, the fuel tank bottom plate, fuel tank side plates and fuel tank top plate are made of carbon fiber plates, and a plurality of weight reduction holes are provided on the fuel tank bottom plate, fuel tank side plates and fuel tank top plate; the fuel tank link rod is made of a carbon fiber tube; the fuel tank link rod is made of a carbon fiber tube.

[0010] Preferably, the fuel tank housing further includes top aluminum columns, which are arranged on the top surface of the fuel tank top plate and are used for connecting with the fuselage bottom plate of the unmanned aerial vehicle.

[0011] Preferably, the load link rod is located below the fuel tank support rod and is arranged perpendicular to the fuel tank support rod. The load link rod includes fourth kits provided at both ends. The load link rod and the landing gear diagonal strut are fixedly connected through the fourth kits, and the load link rod is arranged in parallel with the landing gear skid link rod.

[0012] Preferably, the load mounting plate includes an upper load mounting plate and a lower load mounting plate. The upper load mounting plate and the lower load mounting plate are fixedly connected with the load link rod by a hoop.

[0013] Preferably, the upper load mounting plate and the lower load mounting plate are made of carbon fiber plates, and a plurality of weight reduction holes are provided on the upper load mounting plate and the lower load mounting plate; the load link rod is made of a carbon fiber tube.

[0014] Preferably, the load mounting assembly further includes load support aluminum columns, which are arranged on the top surface of the upper load mounting plate and are connected with the fuel tank bottom plate.

[0015] The beneficial effects of the present utility model are as follows: The landing gear of the unmanned aerial vehicle of the present utility model is arranged around the fuel tank of the hybrid multi-rotor unmanned aerial vehicle, while considering the connection strength of the landing gear and providing installation positions for other airborne devices. The landing gear of the unmanned aerial vehicle of the present utility model adopts a multi-functional integrated design, with functions such as load mounting, fuel loading and equipment installation, reducing the weight of the hybrid multi-rotor unmanned aerial vehicle, improving the spatial flexibility and expandability of equipment layout, and reducing the production and manufacturing cost of the unmanned aerial vehicle. Description of the Drawings

[0016] Figure 1 It is a three-dimensional schematic diagram of the landing gear of the present utility model unmanned aerial vehicle.

[0017] Figure 2 It is a front view of the landing gear of the present utility model unmanned aerial vehicle.

[0018] Figure 3 It is a left view of the landing gear of the present utility model unmanned aerial vehicle.

[0019] The meanings of the reference numerals in the figure:

[0020] 11 - Landing gear diagonal brace; 12 - Landing gear skid bar; 13 - Landing gear skid link; 14 - First kit; 15 - Second kit; 21 - Fuel tank support bar; 22 - Fuel tank bottom plate; 23 - Fuel tank side plate; 24 - Fuel tank top plate; 25 - Third kit; 26 - Top aluminum column; 31 - Load link; 32 - Upper load mounting plate; 33 - Lower load mounting plate; 34 - Load support aluminum column; 35 - Fourth kit. Specific embodiments

[0021] The following specifically introduces the present utility model in combination with the accompanying drawings and specific embodiments.

[0022] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0023] Such as Figures 1 to 3An unmanned aerial vehicle landing gear shown in the figure includes a landing gear assembly, a fuel tank assembly and a payload mounting assembly. The landing gear assembly includes landing gear diagonal braces 11, landing gear skid bars 12 and landing gear skid linkages 13. Any one of the landing gear skid bars 12 is fixedly connected to any two of the landing gear diagonal braces 11 respectively, and both ends of the landing gear skid linkage 13 are connected to the landing gear skid bars 12 respectively; the fuel tank assembly includes fuel tank support bars 21 and a fuel tank housing, the fuel tank support bars 21 are connected to the landing gear diagonal braces 11, and the fuel tank housing is fixed on the fuel tank support bars 21; the payload mounting assembly includes payload linkages 31 and a payload mounting plate, the payload linkages 31 are connected to the landing gear diagonal braces 11, and the payload mounting plate is fixed on the payload linkages 31. The landing gear of the unmanned aerial vehicle of the present utility model adopts a multi-functional integrated design, has functions such as payload mounting, fuel loading and equipment installation, etc., reduces the weight of the hybrid multi-rotor unmanned aerial vehicle, improves the spatial flexibility and expandability of equipment layout, and reduces the production and manufacturing cost of the unmanned aerial vehicle.

[0024] In a preferred embodiment, a first kit 14 is provided at one end of the landing gear diagonal brace 11, and the landing gear diagonal brace 11 and the landing gear skid bar 12 are fixedly connected through the first kit 14; second kits 15 are provided at both ends of the landing gear skid linkage 13, and the landing gear skid linkage 13 and the landing gear skid bar 12 are fixedly connected through the second kits 15. Specifically, one end of the first kit 14 is sleeved on the landing gear skid bar 12, and the other end is sleeved on the main body of the landing gear diagonal brace 11. Similarly, one end of the second kit 14 is sleeved on the landing gear skid bar 12, and the other end is sleeved on the main body of the landing gear skid linkage 13. Such a connection method is firm, easy to implement and easy to disassemble.

[0025] In a preferred embodiment, third kits 25 are provided at both ends of the fuel tank support bar 21, the fuel tank support bar 21 and the landing gear diagonal brace 11 are fixedly connected through the third kits 25, and the fuel tank support bar 21 is arranged in parallel with the landing gear skid bar 12. The fuel tank housing includes a fuel tank bottom plate 22, fuel tank side plates 23 and a fuel tank top plate 24. The fuel tank bottom plate 22, fuel tank side plates 23 and fuel tank top plate 24 are spliced with nuts to form the main body of the fuel tank housing, and the fuel tank bottom plate 22 and the fuel tank support bar 21 are connected by a hoop to fix the fuel tank housing on the fuel tank support bar 21. The fuel tank housing spliced with nuts ensures the rigidity of the fuel tank. A flexible fuel tank is placed inside the fuel tank housing. The combination form of the flexible and rigid fuel tanks makes the fuel tank capacity and shape design have high flexibility.

[0026] In a preferred embodiment, the fuel tank bottom plate 22, the fuel tank side plates 23 and the fuel tank top plate 24 are made of carbon fiber plates, and a plurality of weight reduction holes are provided on the fuel tank bottom plate 22, the fuel tank side plates 23 and the fuel tank top plate 24; the fuel tank connecting rod 21 is made of a carbon fiber tube. The use of carbon fiber material and the design of weight reduction holes further reduce the overall weight of the device.

[0027] In a preferred embodiment, the fuel tank housing further includes a top aluminum column 26, and the top aluminum column 26 is arranged on the top surface of the fuel tank top plate 24 for connecting with the fuselage bottom plate of the unmanned aerial vehicle. The height space reserved by the top aluminum column 26 can be used to load airborne equipment on the fuel tank top plate 24, and has high expandability for equipment installation.

[0028] In a preferred embodiment, the load connecting rod 31 is located below the fuel tank support rod 21 and is perpendicularly arranged to the fuel tank support rod 21. The load connecting rod 31 includes fourth kits 35 provided at both ends. The load connecting rod 31 is fixedly connected to the landing gear diagonal strut 11 through the fourth kits 35, and the load connecting rod 31 is parallel to the landing gear skid link 13. The fuel tank support rod 21 and the load connecting rod 31 are respectively parallel to the landing gear skid rod 12 and the landing gear skid link 13, so that the fuel tank support rod 21 and the load connecting rod 31 form a 90-degree installation angle on the horizontal plane, constituting a "square" shaped reinforcing frame, which provides a reinforcing support for the overall landing gear.

[0029] In a preferred embodiment, the load mounting plate includes an upper load mounting plate 32 and a lower load mounting plate 33, and the upper load mounting plate 32 and the lower load mounting plate 33 are fixedly connected to the load connecting rod 31 by a hoop.

[0030] In a preferred embodiment, the upper load mounting plate and the lower load mounting plate are made of carbon fiber plates, and a plurality of weight reduction holes are provided on the upper load mounting plate and the lower load mounting plate; the load connecting rod is made of a carbon fiber tube. The use of carbon fiber material and the design of weight reduction holes further reduce the overall weight of the device.

[0031] In a preferred embodiment, the load mounting assembly further includes a load support aluminum column 34, and the load support aluminum column 34 is arranged on the top surface of the upper load mounting plate 32 and is connected to the fuel tank bottom plate 22. The connection structure of the load support aluminum column 34 enables the fuel tank assembly, the load mounting assembly and the landing gear assembly to jointly form an integral force-bearing framework.

[0032] In summary, the disclosed unmanned aerial vehicle landing gear of the present utility model has the installation function requirements of multiple hybrid multi-rotor unmanned aerial vehicle devices, and avoids the strength and weight redundancy caused by independently designing the installation support structures for each component.

[0033] (1) Reduced the structural weight of the drone: For a 120 kg hybrid multi-rotor drone of the same level, the total weight of the landing gear, fuel tank, and accessory installation structure is 6.75 kg. After using the landing gear technical solution of the present utility model, the total weight of the landing gear, fuel tank, and accessory installation structure of the drone is 5.96 kg, and the installation structure space of the equipment is increased. The following improvements are achieved compared with the existing landing gear:

[0034] (2) Reduced costs: For a 120 kg hybrid multi-rotor drone of the same level, the unit cost of making the fuel tank by die-casting is about 8,000 yuan per piece. After using the landing gear technical solution of the present utility model, the production cost of the fuel tank is about 2,000 yuan per piece.

[0035] (3) Simplified the assembly and maintenance processes: When using a rotomolded rigid fuel tank, it is necessary to arrange the pipeline, liquid level gauge and other accessories on the fuel tank in advance. Before assembling the fuselage and the landing gear, the fuel tank and the landing gear are assembled. When the fuel tank needs to be maintained and disassembled, the whole machine must be disassembled, including the landing gear and the fuselage, and the process is complex, involving the disassembly and assembly of the main load-bearing components. After using the landing gear technical solution of the present utility model, when the fuel tank needs to be maintained, the side carbon plate can be disassembled to complete the fuel tank replacement, without disassembling the main load-bearing structure of the drone. At the same time, the equipment installation and disassembly can be operated from the top of the flexible fuel tank, the maintenance space is increased, the assembly and maintenance processes are simplified, and the production and maintenance efficiency of the whole machine is greatly improved.

[0036] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", and "connection" 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 directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0037] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0038] The basic principle, main features and advantages of the present utility model have been shown and described above. Those skilled in the art should understand that the above embodiments do not limit the present utility model in any form. Any technical solutions obtained by using equivalent replacement or equivalent transformation fall within the protection scope of the present utility model.

Claims

1. An unmanned aerial vehicle landing gear, characterized in that, It includes a landing gear assembly, a fuel tank assembly, and a payload mounting assembly; The landing gear assembly includes landing gear diagonal braces, landing gear skid bars, and landing gear skid linkages. Any one of the landing gear skid bars is fixedly connected to any two of the landing gear diagonal braces respectively, and both ends of the landing gear skid linkage are connected to the landing gear skid bars; The fuel tank assembly includes fuel tank support bars and a fuel tank housing. The fuel tank support bars are connected to the landing gear diagonal braces, and the fuel tank housing is fixed on the fuel tank support bars; The payload mounting assembly includes payload linkages and payload mounting plates. The payload linkages are connected to the landing gear diagonal braces, and the payload mounting plates are fixed on the payload linkages.

2. The undercarriage of a drone according to claim 1, characterized in that, One end of the landing gear diagonal brace is provided with a first kit, and the landing gear diagonal brace and the landing gear skid bar are fixedly connected through the first kit; both ends of the landing gear skid linkage are provided with second kits, and the landing gear skid linkage and the landing gear skid bar are fixedly connected through the second kits.

3. The landing gear of an unmanned aerial vehicle according to claim 1, characterized in that, Both ends of the fuel tank support bar are provided with third kits, and the fuel tank support bar and the landing gear diagonal brace are fixedly connected through the third kits, and the fuel tank support bar is arranged parallel to the landing gear skid bar or the landing gear skid linkage.

4. A drone landing gear according to claim 1, characterized in that, The fuel tank housing includes a fuel tank bottom plate, fuel tank side plates, and a fuel tank top plate. The fuel tank bottom plate, fuel tank side plates, and fuel tank top plate are spliced with nuts to form the main body of the fuel tank housing, and the fuel tank bottom plate and the fuel tank support bar are connected by a hoop to fix the fuel tank housing on the fuel tank support bar.

5. The undercarriage of an unmanned aerial vehicle according to claim 4, characterized in that, The fuel tank bottom plate, fuel tank side plates, and fuel tank top plate are made of carbon fiber plates, and a plurality of weight reduction holes are provided on the fuel tank bottom plate, fuel tank side plates, and fuel tank top plate; the fuel tank linkages are made of carbon fiber tubes.

6. The landing gear of an unmanned aerial vehicle according to claim 4, characterized in that, The fuel tank housing further includes top aluminum columns arranged on the top surface of the fuel tank top plate for connecting with the fuselage bottom plate of the unmanned aerial vehicle.

7. The landing gear of a drone according to claim 1, characterized in that, The payload linkage is located below the fuel tank support bar and is arranged perpendicular to the fuel tank support bar. The payload linkage includes fourth kits provided at both ends, and the payload linkage and the landing gear diagonal brace are fixedly connected through the fourth kits, and the payload linkage is arranged parallel to the landing gear skid linkage or the landing gear skid bar.

8. The landing gear of a drone according to claim 1, characterized in that, The payload mounting plate includes an upper payload mounting plate and a lower payload mounting plate, and the upper payload mounting plate and the lower payload mounting plate are fixedly connected to the payload linkage by a hoop.

9. The undercarriage of a drone according to claim 8, characterized in that, The upper payload mounting plate and the lower payload mounting plate are made of carbon fiber plates, and a plurality of weight reduction holes are provided on the upper payload mounting plate and the lower payload mounting plate; the payload linkages are made of carbon fiber tubes.

10. A drone landing gear according to claim 8, characterized in that, The payload mounting assembly further includes payload support aluminum columns arranged on the top surface of the upper payload mounting plate and connected to the fuel tank bottom plate.

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