CN219806972U - Fuselage frame and unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a fuselage frame and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The fuselage frame provided by the utility model comprises two side frames and a plurality of cross beams, wherein the two side frames are arranged at intervals in the left-right direction of the unmanned aerial vehicle, and two ends of the cross beams are respectively connected with the two side frames through hoop assemblies. Two side frames spaced in the left-right direction of the unmanned aerial vehicle are connected with a beam in the middle of the two side frames through hoop components, the risk of cracking due to welding cannot exist at the joint of the beam and the side frames, and reliability is good. And connect crossbeam and two side frames through staple bolt subassembly, do not need to polish, operation such as fluting to the junction of crossbeam and side frame for the integrated into one piece of fuselage frame compares more high-efficient in welding formation, and the technology degree of difficulty of equipment is lower in welding technology moreover. The unmanned aerial vehicle provided by the utility model comprises the frame body, so that the unmanned aerial vehicle also has the corresponding beneficial effects.

Description

Fuselage frame and unmanned aerial vehicle

Technical Field

The utility model relates to the field of unmanned aerial vehicles, in particular to a fuselage frame and an unmanned aerial vehicle.

Background

The unmanned aerial vehicle's fuselage frame is used for guaranteeing unmanned aerial vehicle's fuselage intensity, also is used for installing unmanned aerial vehicle's engine, radome fairing and some electronic components simultaneously. The fuselage frame of the existing unmanned aerial vehicle is formed by welding a plurality of structural members (such as various beams and columns). However, the welded fuselage frames have a risk of cracking and are therefore less reliable.

Disclosure of Invention

The utility model aims to provide a fuselage frame and an unmanned aerial vehicle, wherein the fuselage frame has low cracking risk and high reliability.

Embodiments of the present utility model are implemented as follows:

in a first aspect, the utility model provides a fuselage frame, which is applied to an unmanned aerial vehicle and comprises two side frames and a plurality of cross beams, wherein the two side frames are arranged at intervals in the left-right direction of the unmanned aerial vehicle, and two ends of the cross beams are respectively connected with the two side frames through hoop assemblies.

In an alternative embodiment, the side frames comprise top beams and bottom beams which are arranged at intervals in the up-down direction of the unmanned aerial vehicle, and front beams and rear beams which are arranged at intervals in the front-back direction of the unmanned aerial vehicle; the back beam and the bottom beam extend in the front-back direction of the unmanned aerial vehicle, the opposite ends of the front beam are respectively connected with the front ends of the back beam and the top beam, and the opposite ends of the rear beam are respectively connected with the rear ends of the back beam and the top beam.

In an alternative embodiment, the plurality of cross beams includes at least two bottom cross beams, and each bottom cross beam is arranged at intervals in the front-back direction of the unmanned aerial vehicle, and two ends of the bottom cross beams are connected to the two bottom beams through first anchor ear assemblies respectively.

In an alternative embodiment, the first hoop assembly is a T-shaped hoop assembly.

In an alternative embodiment, the side frame further comprises a stand column, one end of the stand column is connected to the top beam, and the other end is connected to the bottom beam; the plurality of cross beams comprise middle cross beams, and two ends of the middle cross beams are respectively connected with the upright posts of the two side frames through second hoop assemblies.

In an alternative embodiment, the upright posts comprise a front upright post and a rear upright post, which are arranged at intervals in the front-rear direction of the unmanned aerial vehicle; one end of the front upright post, one end of the front beam and the front end of the bottom beam are connected through a three-way anchor ear assembly, and the other end of the front upright post is connected with the top beam through a third anchor ear assembly; one end of the rear upright post, one end of the rear beam and the rear end of the bottom beam are connected through a tee hoop assembly, and the other end of the rear upright post is connected to the top beam through a fourth hoop assembly.

In an alternative embodiment, the third and fourth hoop assemblies are T-shaped hoop assemblies.

In an alternative embodiment, the side frame further comprises a front oblique pull beam and a rear oblique pull beam, one end of the front oblique pull beam is connected with the front beam through a fifth hoop assembly, and the other end of the front oblique pull beam is detachably connected with a third hoop assembly; one end of the rear oblique pull beam is connected to the rear beam through a sixth hoop assembly, and the other end of the rear oblique pull beam is detachably connected to a fourth hoop assembly.

In an alternative embodiment, the fifth and sixth hoop assemblies are P-type hoop assemblies.

In an alternative embodiment, the front and rear diagonal beams are profiles.

In an alternative embodiment, the top beam has a length greater than the bottom beam, the angle between the front beam and the top beam is an acute angle, the angle between the front beam and the bottom beam is an obtuse angle, the angle between the rear beam and the top beam is an acute angle, and the angle between the rear beam and the bottom beam is an obtuse angle.

In an alternative embodiment, the top beams and the bottom beams of the same side frame are parallel to each other, and the length of the top beams is greater than that of the bottom beams; the top beams of the two side frames are parallel to each other and have equal length, and the bottom beams of the two side frames are parallel to each other and have equal length.

In an alternative embodiment, the top beam, the front beam, the bottom beam and the rear beam of the same side frame are sequentially connected to form an inverted isosceles trapezoid structure.

In an alternative embodiment, the spacing between the top beams of the two side frames is smaller than the spacing between the bottom beams of the two side frames.

In an alternative embodiment, the front beam is connected to the top beam by a seventh anchor assembly and the rear beam is connected to the top beam by an eighth anchor assembly.

In an alternative embodiment, the seventh and eighth hoop assemblies are V-hoop assemblies.

In an alternative embodiment, the fuselage frame further comprises a front connection beam and a rear connection beam; the both ends of preceding tie-beam are connected in the front beam of two side frames respectively through ninth staple bolt subassembly, and the both ends of back tie-beam are connected in the back beam of two side frames respectively through tenth staple bolt subassembly.

In an alternative embodiment, the fuselage frame comprises two front connection beams and two rear connection beams, the two front connection beams being arranged crosswise and the two rear connection beams being arranged crosswise.

In an alternative embodiment, the ninth hoop assembly and the tenth hoop assembly are P-type hoop assemblies.

In an alternative embodiment, the fuselage frame further comprises a gear box mount, and both ends of the gear box mount are connected to the top beams of the two side frames by eleventh anchor ear assemblies, respectively.

In an alternative embodiment, the fuselage frame further comprises landing gear, which is detachably connected to the two side frames.

In a second aspect, the present utility model provides a unmanned aerial vehicle comprising the airframe of any one of the preceding embodiments.

The embodiment of the utility model has the beneficial effects that:

the fuselage frame provided by the embodiment of the utility model comprises two side frames and a plurality of cross beams, wherein the two side frames are arranged at intervals in the left-right direction of the unmanned aerial vehicle, and two ends of the cross beams are respectively connected with the two side frames through hoop assemblies. Two side frames spaced in the left-right direction of the unmanned aerial vehicle are connected with a beam in the middle of the two side frames through hoop components, the risk of cracking due to welding cannot exist at the joint of the beam and the side frames, and reliability is good. And connect crossbeam and two side frames through staple bolt subassembly, do not need to polish, operation such as fluting to the junction of crossbeam and side frame for the integrated into one piece of fuselage frame compares more high-efficient in welding formation, and the technology degree of difficulty of equipment is lower in welding technology moreover. In addition, because the fuselage frame is formed by adopting a mode of assembling two side frames and a plurality of cross beams, when one structural member (such as the side frames or the cross beams) is damaged, the structural member can be directly replaced, so that the maintenance is more convenient. The unmanned aerial vehicle provided by the embodiment of the utility model comprises the frame body, so that the unmanned aerial vehicle also has the corresponding beneficial effects.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present utility model and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of a fuselage frame in one embodiment of the utility model;

FIG. 2 is a schematic view of a landing gear according to one embodiment of the present utility model;

FIG. 3 is an enlarged view of part III of FIG. 2 (with the second connector omitted);

FIG. 4 is a schematic illustration of the connection of the bottom rail, front stud, front rail, and landing gear of one embodiment of the present utility model;

FIG. 5 is a schematic illustration of the connection of the front uprights, top beams, and front diagonal braces in an embodiment of the present utility model;

FIG. 6 is a schematic diagram illustrating the connection of a front diagonal draw beam to a front beam in accordance with one embodiment of the present utility model;

FIG. 7 is a schematic view showing the connection of the middle cross member in an embodiment of the present utility model;

FIG. 8 is a schematic illustration of the connection of the front rail, top rail and gearbox mount in one embodiment of the present utility model;

fig. 9 is a schematic diagram illustrating connection between a front connection beam and a front beam according to an embodiment of the present utility model.

010-fuselage frame; 110-top beam; 111-seventh hoop assembly; 120-bottom beams; 121-a tee hoop assembly; 130-front beam; 140-a rear beam; 150-front posts; 151-a third hoop assembly; 160-a rear pillar; 170-front diagonal draw beam; 171-a fifth hoop assembly; 180-rear oblique pull beam; 210-a bottom beam; 211-a first hoop assembly; 220-middle cross beam; 221-a second hoop assembly; 230-front connection beams; 231-ninth hoop assembly; 240-rear connection beams; 300-a gear box mounting seat; 310-eleventh hoop assembly; 400-landing gear; 410-supporting frame; 411-left bracket; 412-right rack; 413-slots; 414-a second connector; 420-skid; 421-first connector.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the present utility model, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or directions or positional relationships in which the inventive product is conventionally put in use, are merely for convenience of describing the present utility model and for simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal," "vertical," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

The fuselage frame 010 of the unmanned aerial vehicle in the related art is formed by connecting a plurality of structural members by welding. However, there is a risk of cracking when welding is used between structural members, so that the reliability of the fuselage frame 010 in the related art is poor. In addition, the welding process itself is complex, for example, the arc-shaped groove needs to be machined at the position where the pipes are connected, and then welding is performed. Therefore, the frame 010 of the related art has high process requirements and low production efficiency. Also, when any one of the structural members of the body frame 010 is damaged, replacement is difficult.

In order to improve the shortcomings of the related art, the present utility model provides a fuselage frame 010 that can be assembled by using a hoop assembly. In addition, the embodiment of the utility model also provides an unmanned aerial vehicle which comprises the airframe 010.

Fig. 1 is a schematic view of a fuselage frame 010 in an embodiment of the utility model. Referring to fig. 1, the fuselage frame 010 provided by the embodiment of the utility model can be applied to an unmanned aerial vehicle, and particularly can be applied to a tandem double-rotor unmanned helicopter. The fuselage frame 010 of this embodiment includes two side frames and a plurality of crossbeam, and two side frames set up in unmanned aerial vehicle's left and right sides orientation (arrow cd direction in the figure) interval, and the both ends of crossbeam are connected in two side frames through staple bolt subassembly respectively. Further, the side frames include top beams 110 and bottom beams 120 that are disposed at intervals in the up-down direction (arrow ef direction in the figure) of the unmanned aerial vehicle, and front beams 130 and rear beams 140 that are disposed at intervals in the front-back direction (arrow ab direction in the figure) of the unmanned aerial vehicle. The top beam 110 and the bottom beam 120 extend in the front-rear direction of the unmanned aerial vehicle, opposite ends of the front beam 130 are connected to front ends of the top beam 110 and the bottom beam 120, respectively, and opposite ends of the rear beam 140 are connected to rear ends of the top beam 110 and the bottom beam 120, respectively. The side frames are enclosed into a closed frame body by a top beam 110, a front beam 130, a bottom beam 120 and a rear beam 140 which are sequentially connected.

It should be understood that the left-right direction, the front-rear direction, and the up-down direction of the unmanned aerial vehicle are all defined by the orientation of the unmanned aerial vehicle in the normal cruise flight state when the fuselage frame 010 is mounted in the unmanned aerial vehicle. When the fuselage frame 010 is assembled in the unmanned aerial vehicle, the top beam 110 is closer to the top end of the unmanned aerial vehicle than the bottom beam 120, and the front beam 130 is closer to the front end of the unmanned aerial vehicle than the rear beam 140.

Optionally, the two side frames can adopt identical structures, and the two side frames are arranged in a mirror image manner in the left-right direction of the unmanned aerial vehicle, so that the left-right balance of the unmanned aerial vehicle is guaranteed; in alternative other embodiments, the size and shape of the two side frames may also be different, depending on different requirements.

Because unmanned aerial vehicle's casing often can connect in fuselage frame 010, so the shape of fuselage frame 010 has influenced unmanned aerial vehicle's appearance to a certain extent. In order to make the unmanned aerial vehicle have a better aerodynamic shape, in this embodiment, the length of the top beam 110 is greater than the length of the bottom beam 120, the angle between the front beam 130 and the top beam 110 is an acute angle, the angle between the front beam 130 and the bottom beam 120 is an obtuse angle, the angle between the rear beam 140 and the top beam 110 is an acute angle, and the angle between the rear beam 140 and the bottom beam 120 is an obtuse angle. Optionally, the top beams 110 and the bottom beams 120 of the same side frame are parallel to each other, and the length of the top beams 110 is greater than the length of the bottom beams 120; the top beams 110 of the two side frames are parallel to each other and of equal length, and the bottom beams 120 of the two side frames are parallel to each other and of equal length. Optionally, the top beam 110, the front beam 130, the bottom beam 120 and the rear beam 140 of the same side frame are sequentially connected to form an inverted isosceles trapezoid structure. As can be seen from fig. 1, the front end and the rear end of the top beam 110 respectively extend beyond the front end and the rear end of the bottom beam 120 in the front-rear direction of the unmanned aerial vehicle, so that the front beam 130 and the rear beam 140 are obliquely arranged, which is advantageous for forming a streamline body of the unmanned aerial vehicle after the housing is installed, and for reducing wind resistance.

In this embodiment, the side frames further include a vertical column, one end of which is connected to the top beam 110 and the other end of which is connected to the bottom beam 120. Through setting up the stand for the structural strength of side frame can be improved. Further, the pillars include a front pillar 150 and a rear pillar 160, and the front pillar 150 and the rear pillar 160 are disposed at intervals in the front-rear direction of the unmanned aerial vehicle. The upper end of the front upright post 150 is connected to the top beam 110 through a hoop assembly, and the lower end of the front upright post 150 is connected to the joint of the front beam 130 and the bottom beam 120; the upper end of the rear pillar 160 is connected to the top beam 110 by a hoop assembly, and the lower end of the rear pillar 160 is connected to the junction of the rear beam 140 and the bottom beam 120.

Further, the side frames also include front diagonal tension beams 170 and rear diagonal tension beams 180. One end of the front oblique pull beam 170 is connected to the front beam 130, and the other end is connected to the connection part of the front upright 150 and the top beam 110; one end of the rear cable-stayed beam 180 is connected to the rear beam 140, and the other end is connected to the junction of the rear pillar 160 and the top beam 110. By arranging the front oblique pull beam 170 and the rear oblique pull beam 180, the stability of the side frame is further improved, and the side frame is not easy to deform. In alternative other embodiments, the front diagonal draw beam 170 may be connected at one end to the front beam 130 and at the other end to the top beam 110 or the front upright 150; one end of the rear cable-stayed beam 180 is connected to the rear beam 140, and the other end may be connected to the top beam 110 or the rear pillar 160; the number of front diagonal braces 170 and rear diagonal braces 180 may be plural in one side frame.

In the embodiment of the utility model, the cross beam is connected with the two side frames, so that the relative positions of the two side frames are fixed. In this embodiment, the plurality of beams includes at least two bottom beams 210, and each bottom beam 210 is arranged at intervals in the front-rear direction of the unmanned aerial vehicle. In this embodiment, the number of bottom beams 210 is two, and in other embodiments, the number of bottom beams 210 may be increased or decreased as needed.

Further, the plurality of cross beams further includes a middle cross beam 220, and two ends of the middle cross beam 220 are respectively connected to the upright posts of the two side frames. In this embodiment, the fuselage frame 010 includes two center cross members 220, with one center cross member 220 connected between the two front uprights 150 and the other center cross member 220 connected between the two rear uprights 160.

In this embodiment, the fuselage frame 010 further includes a front connection beam 230 and a rear connection beam 240. The front connection beam 230 has both ends respectively connected to the front beams 130 of the two side frames, and the rear connection beam 240 has both ends respectively connected to the rear beams 140 of the two side frames. Further, the body frame 010 includes two front connection beams 230 and two rear connection beams 240, the two front connection beams 230 are disposed to cross, and the two rear connection beams 240 are disposed to cross. By arranging the two front connection beams 230 to intersect, and the two rear connection beams 240 to intersect, the connection stability between the two side frames can be further improved.

In this embodiment, by providing the bottom beam 210, the middle beam 220, the front connection beam 230, and the rear connection beam 240 between the two side frames, the connection stability between the two side frames is better, and the fuselage frame 010 is not easily deformed.

In order to facilitate the installation of the gearbox of the unmanned aerial vehicle, the fuselage frame 010 of the present embodiment further includes a gearbox mounting base 300, two ends of the gearbox mounting base 300 are respectively connected to the top beams 110 of the two side frames, and the gearbox mounting base 300 is used for mounting the gearbox. Because fuselage frame 010 of this embodiment is applied to tandem double-rotor unmanned helicopter, the front end and the rear end of this unmanned helicopter all need to set up the gear box, respectively with preceding rotor subassembly and back rotor subassembly transmission connection. Thus, the fuselage frame 010 of the present embodiment includes four gearbox mounts 300, wherein two gearbox mounts 300 are disposed at the front end of the top beam 110 for securing the corresponding gearbox of the front rotor assembly; two gearbox mounts 300 are provided at the rear end of the header 110 for securing the corresponding gearbox of the rear rotor assembly. In this embodiment, the gear box mount 300 may be used not only to mount a gear box, but also to improve the stability of the two top beams 110.

In order to make the unmanned aerial vehicle have better appearance and stability, in this embodiment, the plane that two side frames respectively lie is not parallel to each other, but takes a certain contained angle. Specifically, the distance between the top beams 110 of the two side frames is smaller than the distance between the bottom beams 120 of the two side frames, so that the whole frame 010 of the machine body is in a shape with narrow upper part and wide lower part.

Further, the fuselage frame 010 also includes landing gear 400, and the landing gear 400 is detachably connected to both side frames. Landing gear 400 is used to support the ground during takeoff and landing of the drone.

FIG. 2 is a schematic view of a landing gear 400 in one embodiment of the present utility model; fig. 3 is an enlarged view of part III of fig. 2 (the second connector 414 is omitted). As shown in fig. 2 and 3, in the present embodiment, the landing gear 400 is of a split design, and the landing gear 400 includes two skids 420 and two support frames 410. The two support frames 410 are arranged at intervals in the front-rear direction of the unmanned aerial vehicle, and each support frame 410 is detachably connected to the two side frames. The two skids 420 are arranged at intervals in the left-right direction of the unmanned aerial vehicle, and the two skids 420 are detachably connected to two ends of the supporting frame 410 respectively.

Specifically, the skid 420 is connected to an end of the support frame 410 through a first connection 421.

Further, the support frame 410 includes a left bracket 411 and a right bracket 412, the left bracket 411 and the right bracket 412 are respectively connected to the two side frames, and the left bracket 411 and the right bracket 412 are connected through a second connecting member 414. The second connecting piece 414 may be a hoop assembly, the end portions of the left bracket 411 and the right bracket 412 may be provided with a notch 413, the notch 413 extends from the end surfaces of the left bracket 411 and the right bracket 412 in a direction away from the end portions, and the notch 413 penetrates through the inner side and the outer side of the left bracket 411 and the right bracket 412 (pipe), so that the second connecting piece 414 can be conveniently held tightly. The second connector 414 may be provided with protrusions on the inner side thereof to be engaged with the notches 413 such that the second connector 414 can lock the relative positions of the left bracket 411 and the right bracket 412.

In alternative embodiments, landing gear 400 may also be of unitary design, i.e., with support frame 410 being of unitary construction and welded to skid 420.

In the embodiment of the present utility model, the top beam 110, the bottom beam 120, the front beam 130, the rear beam 140, the upright posts and the cross beams between the side frames may be tubular materials; the front oblique pull beam 170, the rear oblique pull beam 180 and the front connecting beam 230 and the rear connecting beam 240 between the side frames can be made of sectional materials; the support frame 410 and the skid 420 of the landing gear 400 may be made of pipe materials.

The manner in which the various structural members of the fuselage frame 010 are connected will now be described in detail.

Fig. 4 is a schematic view showing the connection of the bottom rail 210, the bottom beam 120, the front column 150, the front beam 130, and the landing gear 400 according to an embodiment of the present utility model. As shown in fig. 4, both ends of the bottom beam 210 are connected to the two bottom beams 120 through first hoop assemblies 211, respectively. Further, the bottom rail 210 and the bottom rail 120 are perpendicular to each other, and are T-shaped at the connection. Therefore, in this embodiment, the first hoop assembly 211 is a T-shaped hoop assembly, and after the first hoop assembly 211 is tightened by screwing the fastening screw, the first hoop assembly 211 can be further fastened and connected with the bottom beam 120 and/or the bottom beam 210 by a fastener (such as a screw, a rivet).

Fig. 5 is a schematic diagram illustrating the connection of the front pillar 150, the roof rail 110, and the front diagonal tension rail 170 according to an embodiment of the present utility model. As shown in fig. 4 and 5, one end of the front pillar 150, one end of the front beam 130, and the front end of the bottom beam 120 are connected by a three-way hoop assembly 121, and the other end of the front pillar 150 is connected to the top beam 110 by a third hoop assembly 151. In this embodiment, the ends of the front upright 150, the front beam 130 and the bottom beam 120 are respectively inserted into three ports of the tee hoop assembly 121, and then the tee hoop assembly 121 is fastened and connected with the front upright 150, the front beam 130 and the bottom beam 120 by fasteners (such as screws and rivets). In this embodiment, the front pillar 150 and the top rail 110 are perpendicular to each other, and are T-shaped at the junction. Therefore, in this embodiment, the third hoop assembly 151 is a T-shaped hoop assembly, and after the third hoop assembly 151 is tightened by screwing the fastening screw, the third hoop assembly 151 may be further fastened and connected with the front pillar 150 and/or the roof rail 110 by a fastener (such as a screw, a rivet).

Further, one end of the rear pillar 160, one end of the rear beam 140 and the rear end of the bottom beam 120 are connected through the three-way anchor ear assembly 121, and the other end of the rear pillar 160 is connected to the top beam 110 through the fourth anchor ear assembly. In this embodiment, the rear pillar 160 and the top rail 110 are perpendicular to each other, and are T-shaped at the junction. Therefore, in this embodiment, the fourth hoop assembly is a T-shaped hoop assembly. In this embodiment, the connection manner of the rear pillar 160 is the same as that of the front pillar 150, and the detailed connection manner is not described here.

As shown in fig. 4, the lower end of the three-way anchor ear assembly 121 is provided with an arc-shaped groove, the arc-shaped groove is matched with the supporting frame 410 of the landing gear 400, and the three-way anchor ear assembly 121 is fixedly connected with the supporting frame 410 through a fastener (such as a screw and a rivet).

Fig. 6 is a schematic diagram illustrating the connection between the front diagonal tension member 170 and the front beam 130 according to an embodiment of the present utility model. Referring to fig. 5 and 6, one end of the front diagonal draw beam 170 is connected to the front beam 130 by a fifth hoop assembly 171, and the other end is detachably connected to the third hoop assembly 151. Specifically, the front diagonal draw beam 170 may be coupled to the third hoop assembly 151 by fasteners such as screws. Further, one end of the rear cable-stayed beam 180 is connected to the rear beam 140 through the sixth hoop assembly, the other end is detachably connected to the fourth hoop assembly, and the connection mode of the rear cable-stayed beam 180 may refer to the connection mode of the front cable-stayed beam 170, which is not described herein. In this embodiment, the fifth hoop assembly 171 and the sixth hoop assembly are P-type hoop assemblies.

Fig. 7 is a schematic diagram illustrating the connection of the middle beam 220 according to an embodiment of the present utility model. In one embodiment, as shown in fig. 7, the two ends of the middle cross member 220 are respectively connected to the posts of the two side frames through second anchor ear assemblies 221. Taking the middle cross member 220 connected to the front pillar 150 as an example, as shown in fig. 7, two ends of the middle cross member 220 are connected to the front pillars 150 of the two side frames through second anchor ear assemblies 221, respectively. Further, the center cross member 220 is T-shaped (both slightly inclined) at the junction with the front upright 150. Therefore, in this embodiment, the second hoop assembly 221 is a T-shaped hoop assembly, and after the second hoop assembly 221 is tightened by screwing the fastening screw, the second hoop assembly 221 can be further fastened and connected with the upright and/or the middle beam 220 by a fastener (such as a screw, a rivet). The connection manner of the middle cross member 220 on the rear pillar 160 is the same as the specific manner of connecting the middle cross member 220 to the front pillar 150, and will not be described here again.

Fig. 8 is a schematic diagram illustrating the connection of the front rail 130, the top rail 110, and the gearbox mount 300 in accordance with an embodiment of the present utility model. As shown in fig. 8, the front beam 130 is connected to the top beam 110 through a seventh anchor ear assembly 111, and since the angle between the front beam 130 and the top beam 110 is an acute angle, the seventh anchor ear assembly 111 is a V-shaped anchor ear assembly. The seventh anchor ear assembly 111 may further be fastened to the front rail 130 and/or the roof rail 110 by fasteners (e.g., screws, rivets) after tightening the fastening screws.

In this embodiment, the back beam 140 is connected to the top beam 110 by an eighth hoop assembly, which is also a V-shaped hoop assembly. The connection manner between the rear beam 140 and the top beam 110 may refer to the connection manner between the front beam 130 and the top beam 110, and will not be described herein.

As shown in fig. 8, both ends of the gear case mount 300 are connected to the top beams 110 of both side frames through eleventh anchor assemblies 310, respectively. The gear box mount 300 is connected with the top beam 110 through the eleventh hoop assembly 310, can be assembled and disassembled conveniently, and has good structural stability. Eleventh anchor assembly 310 after tightening cap 110 by tightening a screw, eleventh anchor assembly 310 may be further fastened to cap 110 by a fastener (e.g., screw, rivet).

Fig. 9 is a schematic diagram illustrating the connection between the front connection beam 230 and the front beam 130 according to an embodiment of the present utility model. As shown in fig. 9, two ends of the front connection beam 230 are respectively connected to the front beams 130 of the two side frames through a ninth hoop assembly 231, and the ninth hoop assembly 231 is a P-type hoop assembly. In this embodiment, two ends of the rear connection beam 240 are respectively connected to the rear beams 140 of the two side frames through a tenth hoop assembly, which is also a P-type hoop assembly, and the rear connection beam 240 is connected to the rear beam 140 in the same manner as the front connection beam 230 is connected to the front beam 130.

Optionally, the fuselage frame 010 is symmetrically arranged in the front-rear direction of the unmanned aerial vehicle, that is, the front beam 130 is arranged in a mirror image with the rear beam 140, the front diagonal beam 170 is arranged in a mirror image with the rear diagonal beam 180, the front upright 150 is arranged in a mirror image with the rear upright 160, the front connection beam 230 is arranged in a mirror image with the rear connection beam 240, and the gear box mounting seat 300 at the front end of the fuselage frame 010 is arranged in a mirror image with the gear box mounting seat 300 at the rear end of the fuselage frame 010. Through making fuselage frame 010 in unmanned aerial vehicle fore-and-aft direction symmetry, be favorable to unmanned aerial vehicle's front-and-back balance.

In the frame 010 provided in the above embodiment, the connection between the bottom beam 210 and the bottom beam 120 is achieved by using the first anchor ear assembly 211; the second hoop component 221 is adopted to realize the connection between the middle cross beam 220 and the upright posts (the front upright post 150 and the rear upright post 160) of the side frame; the third hoop assembly 151 is adopted to realize the connection between the front upright 150 and the top beam 110; the connection between the rear upright 160 and the top beam 110 is realized by adopting a fourth hoop assembly; the connection of the front cable-stayed beam 170 and the front beam 130 is realized by adopting a fifth hoop assembly 171; the connection between the rear cable-stayed beam 180 and the rear beam 140 is realized by adopting a sixth hoop assembly; the seventh hoop assembly 111 is adopted to realize the connection between the front beam 130 and the top beam 110; the eighth hoop assembly is adopted to realize the connection between the back beam 140 and the top beam 110; the ninth hoop assembly 231 is adopted to realize the connection between the front connecting beam 230 and the front beams 130 of the two side frames; the tenth hoop assembly is adopted to realize the connection between the rear connecting beam 240 and the rear beams 140 of the two side frames; the eleventh hoop assembly 310 is adopted to realize the connection between the gear box mounting seat 300 and the top beams 110 of the two side frames; the three-way hoop assembly 121 is used to connect the bottom beam 120, the front beam 130 and the front upright 150, and to connect the bottom beam 120, the rear beam 140 and the rear upright 160. The fuselage frame 010 that the above-mentioned embodiment provided adopts different staple bolt subassemblies according to the structure of difference, adopts staple bolt connection between the structure, can not exist because of the risk of welding fracture appearing in the junction of structure, and the reliability is better. Meanwhile, each structural member is connected by adopting the hoop assembly, and the operations such as polishing, slotting and the like are not needed at the connecting part of the structural member, so that the assembly forming of the frame 010 of the machine body is more efficient compared with the welding forming, and the assembly process difficulty is lower compared with the welding process. When one of the structural members (such as a certain component part of the side frame or the cross beam) is damaged, the structural member can be directly replaced, so that the maintenance is more convenient.

An unmanned aerial vehicle (not shown in the figure) provided by the embodiment of the utility model comprises the airframe 010 provided by the embodiment. The unmanned aerial vehicle can be a tandem double-rotor unmanned helicopter, the engine, the gear box, the radiator and other parts can be mounted on the machine body frame 010, and the machine shell can be further mounted on the machine body frame 010.

In summary, the fuselage frame 010 provided in the embodiment of the present utility model includes two side frames and a plurality of beams, the two side frames are disposed at intervals in the left-right direction of the unmanned aerial vehicle, and two ends of the beams are respectively connected to the two side frames through the anchor ear assembly. Two side frames spaced in the left-right direction of the unmanned aerial vehicle are connected with a beam in the middle of the two side frames through hoop components, the risk of cracking due to welding cannot exist at the joint of the beam and the side frames, and reliability is good. And connect crossbeam and two side frames through staple bolt subassembly, do not need to polish, operation such as fluting to the junction of crossbeam and side frame for the integrated circuit of fuselage frame 010 is more efficient in welding formation compared with, and the technology degree of difficulty of equipment is lower in welding technology moreover. In addition, since the fuselage frame 010 is formed by assembling two side frames with a plurality of cross beams, when one of the structural members (such as the side frames or the cross beams) is damaged, the structural member can be directly replaced, so that the maintenance is more convenient. The unmanned aerial vehicle provided by the embodiment of the utility model comprises the machine body frame 010, so that the unmanned aerial vehicle also has the corresponding beneficial effects.

The above is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims (22)

1. The utility model provides a fuselage frame, is applied to unmanned aerial vehicle, its characterized in that includes two side frames and a plurality of crossbeam, two the side frame is in unmanned aerial vehicle's left and right sides direction interval setting, the both ends of crossbeam are respectively through staple bolt subassembly connection in two the side frame.

2. The airframe as recited in claim 1, wherein said side frames include top and bottom beams spaced apart in an up-down direction of said unmanned aerial vehicle and front and rear beams spaced apart in a fore-aft direction of said unmanned aerial vehicle; the back beam and the bottom beam extend in the front-back direction of the unmanned aerial vehicle, the opposite ends of the front beam are respectively connected with the front ends of the back beam and the top beam, and the opposite ends of the rear beam are respectively connected with the rear ends of the back beam and the bottom beam.

3. The fuselage frame of claim 2 wherein the plurality of cross members comprises at least two bottom cross members, each bottom cross member being spaced apart in a fore-aft direction of the unmanned aerial vehicle, two ends of the bottom cross member being connected to two bottom beams by first anchor ear assemblies, respectively.

4. A fuselage frame according to claim 3, wherein the first hoop assembly is a T-hoop assembly.

5. The airframe as recited in claim 2, wherein said side frames further comprise uprights, one end of said uprights being connected to said top beams and the other end being connected to said bottom beams; the plurality of cross beams comprise middle cross beams, and two ends of each middle cross beam are connected with the upright posts of the two side frames through second hoop assemblies respectively.

6. The airframe as recited in claim 5, wherein said uprights include a front upright and a rear upright, said front and rear uprights being spaced apart in a fore-aft direction of said unmanned aerial vehicle; one end of the front upright post, one end of the front beam and the front end of the bottom beam are connected through a three-way hoop assembly, and the other end of the front upright post is connected with the top beam through a third hoop assembly; one end of the rear upright post, one end of the rear beam and the rear end of the bottom beam are connected through a tee hoop assembly, and the other end of the rear upright post is connected with the top beam through a fourth hoop assembly.

7. The airframe as defined in claim 6, wherein said third and fourth hoop assemblies are T-shaped hoop assemblies.

8. The airframe as recited in claim 6, wherein said side frames further comprise front and rear diagonal stringers; one end of the front oblique pull beam is connected with the front beam through a fifth hoop assembly, and the other end of the front oblique pull beam is detachably connected with the third hoop assembly; one end of the rear oblique pull beam is connected with the rear beam through a sixth hoop assembly, and the other end of the rear oblique pull beam is detachably connected with the fourth hoop assembly.

9. The airframe as recited in claim 8, wherein said fifth hoop assembly and said sixth hoop assembly are P-type hoop assemblies.

10. The airframe as recited in claim 8, wherein said front and rear diagonal draw beams are profiles.

11. The airframe as defined in any one of claims 2-10, wherein the top beam has a length that is greater than the bottom beam, the angle between the front beam and the top beam is an acute angle, the angle between the front beam and the bottom beam is an obtuse angle, the angle between the rear beam and the top beam is an acute angle, and the angle between the rear beam and the bottom beam is an obtuse angle.

12. The airframe as defined in any one of claims 2-10, wherein the top beam and the bottom beam of the same side frame are parallel to each other and the length of the top beam is greater than the length of the bottom beam; the top beams of the two side frames are parallel to each other and have the same length, and the bottom beams of the two side frames are parallel to each other and have the same length.

13. The airframe as defined in any one of claims 2-10, wherein the top beam, front beam, bottom beam, and back beam of the same side frame are connected in sequence to enclose an inverted isosceles trapezoid structure.

14. The airframe as defined in any one of claims 2-10, wherein the spacing between the top beams of two of the side frames is less than the spacing between the bottom beams of two of the side frames.

15. The airframe of any one of claims 2-10 wherein the front beam is connected to the top beam by a seventh hoop assembly and the rear beam is connected to the top beam by an eighth hoop assembly.

16. The airframe as defined in claim 15, wherein said seventh and eighth hoop assemblies are V-shaped hoop assemblies.

17. The airframe as defined in any one of claims 2-10, wherein the airframe further comprises a front connection beam and a rear connection beam; the both ends of preceding tie-beam are respectively through ninth staple bolt subassembly connect in two the side frame the front beam, the both ends of back tie-beam are respectively through tenth staple bolt subassembly connect in two the back beam of side frame.

18. The airframe of claim 17 wherein said airframe comprises two said front connecting beams and two said rear connecting beams, two said front connecting beams being disposed in a cross arrangement and two said rear connecting beams being disposed in a cross arrangement.

19. The airframe as recited in claim 17, wherein said ninth hoop assembly and said tenth hoop assembly are P-type hoop assemblies.

20. The airframe of any one of claims 2-10 further comprising a gearbox mount, wherein the gearbox mount is connected at both ends to the top beams of both side frames by an eleventh hoop assembly, respectively.

21. The airframe of any one of claims 1-10 further comprising a landing gear removably connected to both of the side frames.

22. A drone comprising the airframe of any one of claims 1-21.