CN117068410A - Rear fuselage structure of bell-and-spigot type unmanned aerial vehicle and unmanned aerial vehicle comprising rear fuselage structure - Google Patents
Rear fuselage structure of bell-and-spigot type unmanned aerial vehicle and unmanned aerial vehicle comprising rear fuselage structure Download PDFInfo
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 35
- 210000001503 joint Anatomy 0.000 claims abstract description 29
- 238000009434 installation Methods 0.000 claims abstract description 13
- 230000002787 reinforcement Effects 0.000 claims description 13
- 238000005728 strengthening Methods 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 abstract description 13
- 238000013461 design Methods 0.000 abstract description 8
- 230000005540 biological transmission Effects 0.000 abstract description 7
- 238000012360 testing method Methods 0.000 abstract description 5
- 239000003351 stiffener Substances 0.000 description 8
- 239000011324 bead Substances 0.000 description 7
- 238000003032 molecular docking Methods 0.000 description 6
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 239000003292 glue Substances 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/70—Constructional aspects of the UAV body
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/70—Constructional aspects of the UAV body
- B64U20/75—Constructional aspects of the UAV body the body formed by joined shells or by a shell overlaying a chassis
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Abstract
The invention provides a rear fuselage structure of a sleeved unmanned aerial vehicle and an unmanned aerial vehicle comprising the rear fuselage structure. The rear fuselage structure of the sleeved unmanned aerial vehicle comprises a skeleton assembly and a skin assembly, wherein the skeleton assembly comprises a middle-rear fuselage butt joint frame, an engine mounting frame, a plurality of short beams and an engine hanging piece, the middle-rear fuselage butt joint frame is sleeved on a fuselage section of the unmanned aerial vehicle, one end of each short beam is connected to the middle-rear fuselage butt joint frame, and the other end of each short beam is connected to the engine mounting frame. The skin assembly comprises a rear fuselage skin, a reinforcing frame and a tail frame, wherein one end of an engine hanging piece is connected to the engine mounting frame, and the other end of the engine hanging piece is connected to the reinforcing frame. According to this structure, the installation and the dismantlement space of engine are uncovered, need not to design the flap and carry out dismouting maintenance, and maneuverability is strong, can effectively promote the assembly efficiency of engine, reduces the time human cost of equipment maintenance test such as back fuselage section engine, steering wheel. The problems of overlarge bearing and stress concentration of the engine mounting frame structure are avoided, and the force transmission efficiency of the rear fuselage structure is improved.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle structural design, in particular to a rear fuselage structure of a bell-and-spigot type unmanned aerial vehicle and an unmanned aerial vehicle comprising the rear fuselage structure of the bell-and-spigot type unmanned aerial vehicle.
Background
The rear fuselage structure of the unmanned aerial vehicle is a key of the structural design of the unmanned aerial vehicle body and is also a difficulty of the structural design of the whole unmanned aerial vehicle. The requirements of the rear fuselage structure design are firstly to give consideration to the theoretical appearance, the weight of the engine, the interface form of the engine and the steering engine, the tail fin connection, the rear fuselage material, the forming process and the manufacturing cost thereof, and secondly to make the installation and disassembly operation space of the engine open, the maintenance time is short and the maintenance cost is low. This means that the installation of the core equipment such as the engine, the steering engine and the like is considered; the connection of structural components such as the stabilizer, the control surface and the like of the tail wing is weighed; and also coordinates equipment and structure gap control, thermal radiation protection, etc.
The common unmanned aerial vehicle rear fuselage structure can be divided into a bearing type rear fuselage structure and a non-bearing type rear fuselage structure according to whether the weight of an engine or a steering engine is born:
(1) The bearing type rear fuselage structure is characterized in that an engine is directly arranged on a rear fuselage, and then the rear fuselage is in butt joint with a middle fuselage section. The rear fuselage structure of this structural style has the advantages of ensuring enough strength and rigidity, and has the disadvantages of narrow disassembly and assembly space of the engine, inconvenient operation and poor disassembly and maintenance;
(2) The unmanned aerial vehicle engine of non-bearing type rear fuselage structure is directly connected with the middle fuselage skeleton. The rear fuselage structure of the structural form only has the capability of maintaining the molded surface and bearing the pneumatic load, and has poor force transmission form; the engine is suitable for the rear engine body structure of a small engine, has special limitation on the installation form of the engine, generally needs to be installed, dismounted and maintained by adopting a mode of designing a maintenance cover at the corresponding position of the engine body, and has a certain influence on the force transmission of the engine body; for the engine of the medium-sized and large-sized unmanned aerial vehicle, the weight of the engine reaches hundred kilograms, the connection direction and the constraint form of the engine are various, and the installation requirement of the non-bearing type rear fuselage structure cannot be met.
Accordingly, there is a need for an improved structure for the rear fuselage of an unmanned aerial vehicle.
Disclosure of Invention
The invention provides a rear fuselage structure of a bell-joint type unmanned aerial vehicle and an unmanned aerial vehicle comprising the rear fuselage structure of the bell-joint type unmanned aerial vehicle, which aim at solving the defects that the rear fuselage structure of the existing unmanned aerial vehicle has narrow engine disassembly and assembly space and poor force transmission form and is required to design a flap for disassembly, assembly and maintenance of the engine.
The technical scheme of the invention is as follows:
the utility model provides a fuselage structure behind bell and spigot joint unmanned aerial vehicle which characterized in that: the rear body structure of the bell-and-spigot type unmanned aerial vehicle is used for being in bell-and-spigot connection with a fuselage section in the unmanned aerial vehicle, and comprises a skeleton assembly and a skin assembly;
the skeleton assembly comprises a middle-rear machine body butt joint frame, an engine mounting frame and a plurality of short beams,
the middle and rear fuselage butt joint frames are used for sleeving the middle fuselage section of the unmanned aerial vehicle,
the engine mounting frame and the middle-rear body docking frame are arranged in the front-rear direction of the unmanned aerial vehicle side by side, and the engine mounting frame is provided with a first engine mounting hole,
one end of each of the plurality of short beams is connected to the middle-rear fuselage butt frame and the other end is connected to the engine mounting frame;
the skin assembly comprises a rear fuselage skin, a reinforcing frame and a tail frame, wherein the reinforcing frame is provided with a second engine mounting hole, and the reinforcing frame is positioned between the engine mounting frame and the tail frame;
the skeleton assembly further comprises an engine hanging piece, wherein the engine hanging piece extends along the front-back direction of the unmanned aerial vehicle, one end of the engine hanging piece is connected to the engine mounting frame, and the other end of the engine hanging piece is connected to the reinforcing frame;
the rear fuselage skin is used for enclosing the middle and rear fuselage butt joint frame, the engine mounting frame, the reinforcing frame and the tail frame in the rear fuselage skin.
Further, the middle and rear fuselage butt joint frame is provided with a butt joint frame web plate, a butt joint frame edge strip and a plurality of butt joint frame reinforcing ribs, and the engine mounting frame is provided with a mounting frame web plate, a mounting frame edge strip and a plurality of mounting frame reinforcing ribs;
the cross section of every lintel in the direction of perpendicular to unmanned aerial vehicle's fore-and-aft direction personally submits C shape and includes connecting rod and two landing legs, and two terminal surfaces of every lintel contact with butt joint frame web and installation frame web respectively, and the both ends of connecting rod of every lintel contact with butt joint frame rim strip and installation frame rim strip respectively and link firmly, and the both ends of two landing legs of every lintel contact with corresponding butt joint frame strengthening rib and corresponding installation frame strengthening rib respectively and link firmly.
Further, one end of the engine hanger is inserted between and fixedly connected with the mounting frame rim strip and the mounting frame reinforcing rib, and the other end of the engine hanger is fixed to a rest portion of the reinforcing frame for rest of the engine hanger.
Further, the rear fuselage skin is connected to the middle and rear fuselage butt-joint frames and the engine mounting frame by means of pallet nuts that are respectively riveted in advance on the middle and rear fuselage butt-joint frames and the engine mounting frame.
Further, the middle fuselage section skin of the fuselage section in the unmanned aerial vehicle is connected to the middle and rear fuselage butt-joint frame by means of a pallet nut which is riveted in advance on the middle and rear fuselage butt-joint frame.
Further, the reinforcing frame and the tail frame are bonded to the rear fuselage skin by glue and are connected to the rear fuselage skin by countersunk rivets.
Further, a pallet nut is riveted on the rest portion of the reinforcing frame, and the engine hanger and the reinforcing frame are connected together by countersunk screws and the pallet nut.
Further, the number of short beams is five, the short beams are symmetrically arranged about a central axis of the engine mounting frame in the left-right direction of the unmanned aerial vehicle and are arranged at intervals along the circumferential direction of the engine mounting frame.
An unmanned aerial vehicle comprising the bell-and-spigot unmanned aerial vehicle rear fuselage structure.
The beneficial effects of the invention are as follows:
1. the rear fuselage structure of the bell-and-spigot unmanned aerial vehicle is connected with the middle fuselage section in a bell-and-spigot mode, and comprises the skeleton assembly and the skin assembly, when the rear fuselage structure is connected, the skeleton assembly is firstly connected with the middle fuselage section, then the engine is fixed to the engine mounting frame in the skeleton assembly, finally the rear fuselage skin, the reinforcing frame and the tail frame which form the skin assembly are integrally mounted to the skeleton assembly, and when the engine is dismounted, the skin assembly can be integrally dismounted from the skeleton assembly and the engine is maintained, so that the mounting and dismounting space of the engine is thoroughly opened, the disassembly and maintenance of a design flap are not needed, the operability is strong, the assembly working efficiency of the engine can be effectively improved, and the time and labor cost of maintenance and test of equipment such as the engine, the steering engine and the like of the rear fuselage section are reduced.
2. According to the bell-and-spigot type unmanned aerial vehicle rear body structure, the frame beam framework consisting of the middle and rear body butt joint frames, the engine mounting frames and the short beams in the framework assembly bears the main load of the engine, and part of the engine load is transferred to the reinforcing frame and the rear body skin through the engine hanging pieces in the framework assembly, so that the concentrated load of the engine is transferred to the body structure in a distributed mode, the problems of overlarge bearing of the engine mounting frame structure and stress concentration are avoided, and the force transfer efficiency of the rear body structure is improved.
3. According to the sleeved unmanned aerial vehicle rear fuselage structure, the rear fuselage skin and the middle fuselage section skin share the middle and rear fuselage butt joint frame, the rear fuselage skin and the middle and rear fuselage butt joint frame are respectively fastened through the screw nuts, and in addition, the rear fuselage skin is also fastened with the engine mounting frame through the screw nuts, so that the whole torsion resistance of the rear fuselage structure is high.
4. Compared with the existing unmanned aerial vehicle, the unmanned aerial vehicle has the advantages that due to the fact that the rear body structure of the sleeved unmanned aerial vehicle is arranged, the assembly efficiency of the unmanned aerial vehicle engine is improved by enabling the installation and disassembly spaces of the unmanned aerial vehicle engine to be opened, the overall maintenance and test cost of the unmanned aerial vehicle is reduced, and the overall force transmission efficiency of the unmanned aerial vehicle is improved by enabling the concentrated load of the engine to be transmitted to the body structure in a distributed mode. In addition, the unmanned aerial vehicle only needs to disassemble the original rear fuselage structure and add the sleeved unmanned aerial vehicle rear fuselage structure when in use, is easy to realize, low in improvement cost and high in applicability.
Drawings
The features and advantages of the present invention will become more readily understood from the following description with reference to the accompanying drawings, which are not drawn to scale, and some features are exaggerated or reduced to show details of particular components, in which:
fig. 1 is a schematic perspective view of a rear fuselage structure of a bell and spigot unmanned aerial vehicle according to an exemplary embodiment of the present invention when connected together with a fuselage section in the unmanned aerial vehicle;
fig. 2 is a schematic perspective view illustrating a connection relationship of a rear fuselage structure of a bell-type unmanned aerial vehicle with a fuselage section in the unmanned aerial vehicle according to an exemplary embodiment of the present invention;
FIG. 3 is a schematic perspective view of a rear fuselage structure of a bell and spigot unmanned aerial vehicle showing the backbone assembly and skin assembly when disassembled, in accordance with an exemplary embodiment of the present invention;
FIG. 4 is a schematic perspective view of a skeletal assembly in a rear fuselage structure of a bell and spigot unmanned aerial vehicle in accordance with an exemplary embodiment of the present invention;
FIG. 5 is a schematic front view of a skeletal assembly in a rear fuselage structure of a bell and spigot unmanned aerial vehicle in accordance with an exemplary embodiment of the present invention;
FIG. 6 is a cross-sectional view of a backbone assembly in a rear fuselage structure of a bell and spigot unmanned aerial vehicle, taken along line A-A of FIG. 5, showing an engine mounting frame and a short beam in the backbone assembly, in accordance with an exemplary embodiment of the present invention;
FIG. 7 is a schematic exploded perspective view of a skin assembly in a rear fuselage structure of a bell and spigot unmanned aerial vehicle in accordance with an exemplary embodiment of the invention;
FIG. 8 is a schematic assembled perspective view of a skin assembly in a rear fuselage structure of a bell and spigot unmanned aerial vehicle according to an exemplary embodiment of the invention;
fig. 9 is a schematic assembled perspective view showing a connection relationship of a backbone assembly and a skin assembly in a rear fuselage structure of a bell and spigot type unmanned aerial vehicle according to an exemplary embodiment of the present invention.
Reference numerals:
1-a fuselage section in an unmanned aerial vehicle;
2-a rear fuselage structure of the bell-and-spigot joint unmanned aerial vehicle;
21-a middle-rear fuselage butt-joint frame;
22-an engine mounting frame, 221-a first engine mounting hole, 222-a mounting frame web, 223-a mounting frame edge strip, 224-a mounting frame reinforcing rib;
23-short beams, 231-connecting rods and 232-supporting legs;
24-engine hangers;
31-aft fuselage skin;
32-a reinforcing frame, 321-a second engine mounting hole, 322-a rest;
33-tail frame;
f-common nail connecting area.
Detailed Description
The invention will be described in detail below with the aid of exemplary embodiments of the invention with reference to the accompanying drawings. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to be limiting. Furthermore, the same reference numerals are used to denote the same parts throughout the various figures.
The invention provides a rear fuselage structure of a sleeved unmanned aerial vehicle and an unmanned aerial vehicle comprising the rear fuselage structure of the sleeved unmanned aerial vehicle.
First, a general description of a rear fuselage structure of a bell and spigot type unmanned aerial vehicle according to the present invention will be described with reference to fig. 1 and 2. Fig. 1 is a schematic perspective view of a rear fuselage structure of a bell and spigot unmanned aerial vehicle according to an exemplary embodiment of the present invention when connected together with a fuselage section in the unmanned aerial vehicle. Fig. 2 is a schematic perspective view illustrating a connection relationship of a rear fuselage structure of a bell-type unmanned aerial vehicle with a fuselage section in the unmanned aerial vehicle according to an exemplary embodiment of the present invention.
As shown in fig. 1 and 2, a rear fuselage structure 2 of a bell and spigot unmanned aerial vehicle as an exemplary embodiment of the present invention may be used for bell and spigot connection with a fuselage section 1 in the unmanned aerial vehicle. In particular, the end of the rear fuselage structure 2 of the telescopic unmanned aerial vehicle, which is connected to the fuselage section 1 in the unmanned aerial vehicle, may be located inside the fuselage section 1 in the unmanned aerial vehicle.
In general, the bell and spigot unmanned rear fuselage structure 2 may include a skeleton assembly and a skin assembly. This may be with reference to fig. 3, which is a schematic perspective view of a rear fuselage structure of a socket type unmanned aerial vehicle, showing the backbone assembly and skin assembly when disassembled, according to an exemplary embodiment of the present invention.
The skeleton assembly in the rear fuselage structure of the bell and spigot joint type unmanned aerial vehicle provided by the invention will now be described in detail with reference to fig. 4 to 6. Fig. 4 is a schematic perspective view of a skeleton assembly in a rear fuselage structure of a socket type unmanned aerial vehicle according to an exemplary embodiment of the present invention. Fig. 5 is a schematic front view of a skeleton assembly in a rear fuselage structure of a socket type unmanned aerial vehicle according to an exemplary embodiment of the present invention. Fig. 6 is a cross-sectional view of a backbone assembly in a bell and spigot unmanned aircraft rear fuselage structure, taken along line A-A of fig. 5, showing an engine mounting frame and a short beam in the backbone assembly, according to an exemplary embodiment of the invention.
The skeletal assembly may include a mid-aft fuselage interface frame 21, an engine mounting frame 22, and a plurality of short beams 23.
The middle rear fuselage butt-joint frame 21 may be used for sleeving to the unmanned aerial vehicle middle fuselage section 1, in particular, the middle rear fuselage butt-joint frame 21 may be sleeved into the middle fuselage section skin of the unmanned aerial vehicle middle fuselage section 1. In an exemplary embodiment of the present invention, the middle fuselage section skin of the unmanned aerial vehicle middle fuselage section 1 may be connected to the middle and rear fuselage butt-joint frame 21 by means of a pallet nut that is riveted in advance on the middle and rear fuselage butt-joint frame 21, in particular, screws sequentially pass through the middle fuselage section skin and the middle and rear fuselage butt-joint frame 21 and are screwed to the pallet nut on the middle and rear fuselage butt-joint frame 21. It should be noted that the pallet nuts on the middle and rear fuselage butt frames 21 are circumferentially spaced around the middle and rear fuselage butt frames 21, the number of which is not particularly limited. The middle to rear fuselage butt frame 21 may be generally annular in shape and may have a central aperture. In particular, in an exemplary embodiment of the present invention, the mid-aft fuselage butt-joint frame 21 may have a butt-joint frame web, a butt-joint frame rim strip, and a plurality of butt-joint frame stiffeners to facilitate connection of the short beams 23. It should be noted that the butt frame webs, butt frame strips, and butt frame ribs of the middle-rear-body butt frame 21 are not shown in the drawings, and the structure thereof can be seen from the following description of the engine mounting frame 22. The middle-rear fuselage butt-joint frame 21 is an important structural part for connecting the middle fuselage section and the rear fuselage section, and in the exemplary embodiment of the present invention, the middle-rear fuselage butt-joint frame 21 may be obtained by numerical control machining using an advanced high-strength aluminum alloy 7050 series material.
The engine mounting frame 22 may be arranged in the front-rear direction of the unmanned aerial vehicle side by side with the center-rear-body docking frame 21. The shape of the engine mounting frame 22 may be similar to the shape of the middle-rear fuselage docking frame 21, all designed according to aerodynamic profiles. The engine mounting frame 22 may be provided with a first engine mounting hole 221, the first engine mounting hole 221 for receiving an engine of the unmanned aerial vehicle. The engine mounting frame 22 is the only fixed structure of the main engine mounting section and is also a direct structure for bearing the weight and overload of the engine. In some embodiments of the invention, similar to the mid-aft fuselage butt-joint frame 21, the engine mounting frame 22 may have a mounting frame web 222, a mounting frame bead 223, and a plurality of mounting frame ribs 224, as best shown in FIG. 6, to facilitate connection of the stubs 23 and connection of the engine hangers 24. The mounting frame bead 223 may extend along the outer periphery of the engine mounting frame 22, the mounting frame web 222 may extend inwardly from the mounting frame bead 223 and around the mounting frame bead 223, and the mounting frame stiffener 224 may extend inwardly from the mounting frame bead 223.
One end of each of the plurality of short beams 23 is connected to the center rear fuselage butt frame 21 and the other end is connected to the engine mounting frame 22. The short beam component is a force transmission structure for connecting the middle and rear frame and the engine mounting frame. The short beam 23 may be formed by numerical control machining of an aluminum alloy material. In some embodiments of the invention, as shown in fig. 6, each short beam 23 may be generally C-shaped in cross-section in a direction perpendicular to the fore-aft direction of the drone and include a link 231 and two legs 232. It should be noted that the cross-sectional shape of each of the stubs 23 may not be identical but slightly different depending on the structures of the middle-to-rear fuselage butt-joint frame 21 and the engine mounting frame 22. The two end surfaces of each short beam 23 may be respectively contacted with the docking frame web and the mounting frame web 222, the two ends of the connecting rod 231 of each short beam 23 may be respectively contacted with the docking frame rim and the mounting frame rim 223 and fixedly connected, in particular by screws and self-locking nuts, and the two ends of the two supporting legs 232 of each short beam 23 may be respectively contacted with the corresponding docking frame reinforcing ribs and the corresponding mounting frame reinforcing ribs 224 and fixedly connected, in particular by screws and self-locking nuts.
In a particular embodiment of the invention, the number of short beams 23 is preferably five as shown, but this is not limiting to the invention, as the number of short beams 23 may be three, four, six, etc. These short beams 23 may be symmetrically arranged about a central axis of the engine mount frame 22 in the left-right direction of the unmanned aerial vehicle and spaced apart along the circumferential direction of the engine mount frame 22, which may be seen in fig. 6. As observed, the two legs of the one short beam 23 that is the most upper in the up-down direction of the unmanned aerial vehicle are parallel and have substantially equal lengths, the two legs of the two short beams 23 that are the most lower in the up-down direction of the unmanned aerial vehicle are non-parallel, and the link connecting the two legs is curved, and the two legs of the two short beams 23 that are located in the middle in the up-down direction of the unmanned aerial vehicle are parallel but have different lengths.
In a preferred embodiment of the present invention, the skeletal assembly may also include an engine hanger 24. In some embodiments, the engine hangers 24 may be rod-shaped and the engine hangers 24 may extend in a fore-aft direction of the drone.
Next, a skin assembly in a rear fuselage structure of a bell and spigot type unmanned aerial vehicle according to the present invention will be described in detail with reference to fig. 7 to 9. Fig. 7 is a schematic exploded perspective view of a skin assembly in a rear fuselage structure of a socket unmanned aerial vehicle according to an exemplary embodiment of the present invention. Fig. 8 is a schematic assembled perspective view of a skin assembly in a rear fuselage structure of a bell and spigot unmanned aerial vehicle according to an exemplary embodiment of the invention. Fig. 9 is a schematic assembled perspective view showing a connection relationship of a backbone assembly and a skin assembly in a rear fuselage structure of a bell and spigot type unmanned aerial vehicle according to an exemplary embodiment of the present invention.
As shown in fig. 7 and 8, the skin assembly may include an aft fuselage skin 31, a reinforcing frame 32, and a tail frame 33, the aft fuselage skin 31 being generally cylindrical, and the aft fuselage skin 31 may be a structural member obtained from carbon fiber prepregs by a known autoclave curing molding process.
The reinforcing frame 32 and the tail frame 33 can be machined from aluminum alloy. The reinforcement frame 32 may be provided with a second engine mounting hole 321 to receive an engine of the unmanned aerial vehicle, and the reinforcement frame 32 may be located between the engine mounting frame 22 and the tail frame 33. The stiffening frame 32 and the tail frame 33 may each have a ring shape, but the size and configuration of both may vary depending on the configuration of the aft fuselage skin.
One end of the engine hanger 24 may be connected to the engine mounting frame 22 and the other end may be connected to the reinforcement frame 32. The engine mount 24 is a structure that connects the engine secondary mounting sections and is connected to a reinforcement frame 32 of the aft fuselage skin integral assembly.
The aft fuselage skin 31 may be used to enclose the aft and mid-fuselage interface frame 21, the engine mounting frame 22, the reinforcement frame 32 and the tail frame 33 within the aft fuselage skin 31, in particular connected to the aft and mid-fuselage interface frame 21 and the engine mounting frame 22 and interfacing with the unmanned mid-fuselage section 1 to form a bell and spigot unmanned aft fuselage structure 2, as shown in fig. 1 and 2.
Preferably, the rear fuselage skin 31 may be connected to the middle rear fuselage butt-joint frame 21 and the engine mounting frame 22 by means of the pallet nuts riveted in advance on the middle rear fuselage butt-joint frame 21 and the engine mounting frame 22, respectively, specifically, the pallet nuts that pass through the rear fuselage skin 31 and the middle rear fuselage butt-joint frame 21 and are screwed to the middle rear fuselage butt-joint frame 21, and the pallet nuts that pass through the rear fuselage skin 31 and the engine mounting frame 22 and are screwed to the engine mounting frame 22, respectively. Those skilled in the art will appreciate that the pallet nuts are circumferentially spaced around the middle and rear fuselage butt frames 21 and the engine mounting frames 22, the number of which is not particularly limited. The aft fuselage skin 31 may abut the middle fuselage section skin on the middle aft fuselage butt-joint frame 21. According to the description of the middle-rear fuselage butt-joint frame 21 and the middle fuselage section skin, the sleeved unmanned aerial vehicle rear fuselage structure provided by the invention has the advantages that the middle-rear fuselage butt-joint frame is shared by the rear fuselage skin and the middle fuselage section skin, the rear fuselage skin is respectively fastened with the middle-rear fuselage butt-joint frame through screw nuts, and in addition, the rear fuselage skin is also fastened with the engine mounting frame through screw nuts, so that the integral torsion resistance of the rear fuselage structure is strong.
In an exemplary embodiment, the stiffener frame 32 and tail frame 33 may be bonded to the aft fuselage skin 31 by glue and connected to the aft fuselage skin 31 by countersunk rivets. It should be appreciated that any structural adhesive known in the art may be used to effect the attachment of the stiffener 32 and tail 33 frames to the aft fuselage skin 31.
In some embodiments of the invention, the reinforcement frame 32 may include a rest 322 for resting the engine hanger 24. In particular, the rest 322 is a tab extending from the web of the reinforcement frame 32 in the fore-and-aft direction of the unmanned aerial vehicle toward the fuselage section 1 in the unmanned aerial vehicle, however this is only an example.
Illustratively, the rest of the reinforcement frame 32 may be riveted with a pallet nut, and the engine hanger 24 and reinforcement frame 32 are connected together by countersunk screws and pallet nuts. Specifically, countersunk screws pass sequentially through holes in the engine hanger 24 and holes in the reinforcement frame 32 to be brought together with the blade nuts.
Referring to fig. 9, one end of the engine hanger 24 may be interposed between the mounting frame bead 223 and the mounting frame stiffener 224 and fixedly attached to the mounting frame bead 223 and the mounting frame stiffener 224. Referring back to fig. 5 herein, in the co-nailing connection zone F, the engine hanger 24 may be installed so as to be aligned with the upper-most short beam 23, and the rear end of the short beam 23 and the front end of the engine hanger 24 may be inserted between the two mounting frame reinforcing ribs 224 of the engine mounting frame 22, respectively, and co-nailed on the mounting frame web 222 by screws and self-locking nuts.
The other end of the engine hanger 24 may be secured to a rest 322 of the stiffener frame 32 to transfer a portion of the engine load to the stiffener frame 32 and the aft fuselage skin 31.
Those skilled in the art will appreciate that the number of engine hangers 24 may be one or more.
According to the bell-and-spigot type unmanned aerial vehicle rear body structure, the frame beam framework consisting of the middle and rear body butt joint frames, the engine mounting frames and the short beams in the framework assembly bears the main load of the engine, and part of the engine load is transferred to the reinforcing frame and the rear body skin through the engine hanging pieces in the framework assembly, so that the concentrated load of the engine is transferred to the body structure in a distributed mode, the problems of overlarge bearing of the engine mounting frame structure and stress concentration are avoided, and the force transfer efficiency of the rear body structure is improved.
As described above, the rear fuselage structure of the bell and spigot joint type unmanned aerial vehicle of the present invention is connected with the middle fuselage section in a bell and spigot joint manner, and the rear fuselage structure includes the skeleton assembly and the skin assembly, and when the rear fuselage structure is connected, the skeleton assembly is connected with the middle fuselage section first, then the engine is fixed to the engine mounting frame in the skeleton assembly, and finally the rear fuselage skin, the reinforcing frame and the tail frame constituting the skin assembly are integrally mounted to the skeleton assembly together, and when the engine is dismounted, the skin assembly can be integrally removed from the skeleton assembly and the engine is dismounted and maintained, thereby the mounting and dismounting space of the engine is thoroughly opened, the dismounting and maintenance of the design flap is not required, the operability is strong, the work efficiency of the assembly of the engine can be effectively improved, and the time and labor cost of the maintenance test of the equipment such as the engine, the steering engine of the rear fuselage section can be reduced.
The unmanned aerial vehicle comprising the bell-type unmanned aerial vehicle rear fuselage structure provided by the invention is described in detail.
As an example embodiment of the present invention, a unmanned aerial vehicle may include a unmanned aerial vehicle body and an unmanned aerial vehicle wing connected to each other, and the unmanned aerial vehicle body may include a unmanned aerial vehicle front fuselage section, a unmanned aerial vehicle middle fuselage section, and a unmanned aerial vehicle rear fuselage structure employing the above-described bell and spigot type unmanned aerial vehicle rear fuselage structure, the unmanned aerial vehicle middle fuselage section being connected at a front end with the unmanned aerial vehicle front fuselage section and at a rear end with the bell and spigot type unmanned aerial vehicle rear fuselage structure of the present invention.
The rear body structure of the bell-joint unmanned aerial vehicle does not need to change the structure of the existing unmanned aerial vehicle when the rear body structure of the unmanned aerial vehicle is used, and the novel unmanned aerial vehicle with the advantages can be realized by only disassembling the original rear body structure of the unmanned aerial vehicle and adding the rear body structure of the bell-joint unmanned aerial vehicle, is easy to realize, has low improvement cost and strong applicability, improves the assembly efficiency of the engine of the unmanned aerial vehicle by opening the installation and disassembly spaces of the engine of the unmanned aerial vehicle, reduces the maintenance test cost of the whole unmanned aerial vehicle, and improves the transmission efficiency of the whole unmanned aerial vehicle by enabling the concentrated load of the engine to be distributed to the body structure.
The features that are mentioned and/or shown in the above description of exemplary embodiments of the invention may be combined in the same or similar way in one or more other embodiments in combination with or instead of the corresponding features of the other embodiments. Such combined or substituted solutions should also be considered to be included within the scope of the invention.
Claims (9)
1. The utility model provides a fuselage structure behind bell and spigot joint unmanned aerial vehicle which characterized in that: the rear body structure of the bell-and-spigot unmanned aerial vehicle is used for being in bell-and-spigot connection with a body section in the unmanned aerial vehicle, and comprises a skeleton assembly and a skin assembly;
the framework component comprises a middle-rear machine body butt joint frame, an engine mounting frame and a plurality of short beams,
the middle and rear fuselage butt joint frames are used for sleeving the middle fuselage section of the unmanned aerial vehicle,
the engine mounting frame and the middle and rear fuselage butt joint frame are arranged in the front-rear direction of the unmanned aerial vehicle side by side, and the engine mounting frame is provided with a first engine mounting hole,
one end of each of the plurality of short beams is connected to the middle-rear fuselage butt frame and the other end is connected to the engine mounting frame;
the skin assembly comprises a rear fuselage skin, a reinforcing frame and a tail frame, wherein the reinforcing frame is provided with a second engine mounting hole, and the reinforcing frame is positioned between the engine mounting frame and the tail frame;
the skeleton assembly further comprises an engine hanging piece, wherein the engine hanging piece extends along the front-back direction of the unmanned aerial vehicle, one end of the engine hanging piece is connected to the engine mounting frame, and the other end of the engine hanging piece is connected to the reinforcing frame;
the rear fuselage skin is used for enclosing the middle-rear fuselage butt joint frame, the engine mounting frame, the reinforcing frame and the tail frame in the rear fuselage skin.
2. The rear fuselage structure of a bell and spigot joint unmanned aerial vehicle of claim 1, wherein: the middle and rear fuselage butt joint frame is provided with a butt joint frame web plate, a butt joint frame edge strip and a plurality of butt joint frame reinforcing ribs, and the engine mounting frame is provided with a mounting frame web plate, a mounting frame edge strip and a plurality of mounting frame reinforcing ribs;
the cross section of every lintel in the direction of perpendicular to unmanned aerial vehicle's fore-and-aft direction personally submits C shape and includes connecting rod and two landing legs, two terminal surfaces of every lintel respectively with butt joint frame web with installation frame web contact, the both ends of connecting rod of every lintel respectively with butt joint frame border strip with installation frame border strip contact and link firmly, the both ends of two landing legs of every lintel respectively with corresponding butt joint frame strengthening rib and corresponding installation frame strengthening rib contact and link firmly.
3. The rear fuselage structure of a bell and spigot joint unmanned aerial vehicle of claim 2, wherein: the one end of the engine hanger is inserted between the mounting frame edge strip and the mounting frame reinforcing rib and is fixedly connected with the mounting frame edge strip and the mounting frame reinforcing rib, and the other end of the engine hanger is fixedly connected to a rest part of the reinforcing frame for placing the engine hanger.
4. The rear fuselage structure of a bell and spigot joint unmanned aerial vehicle according to claim 1 or 2, wherein: the rear fuselage skin is connected to the middle and rear fuselage butt-joint frame and the engine mounting frame by means of pallet nuts respectively riveted in advance on the middle and rear fuselage butt-joint frame and the engine mounting frame.
5. The rear fuselage structure of a bell and spigot joint unmanned aerial vehicle of claim 4, wherein: the middle fuselage section skin of the middle fuselage section of the unmanned aerial vehicle is connected to the middle and rear fuselage butt-joint frame through a supporting plate nut which is riveted on the middle and rear fuselage butt-joint frame in advance.
6. The rear fuselage structure of a bell and spigot joint unmanned aerial vehicle according to claim 1 or 2, wherein: the reinforcement frame and the tail frame are glued to the rear fuselage skin and are connected to the rear fuselage skin by means of countersunk rivets.
7. A rear fuselage structure of a bell and spigot joint unmanned aerial vehicle as claimed in claim 3, wherein: a blade nut is riveted on the rest portion of the reinforcement frame, and the engine hanger and the reinforcement frame are connected together by a countersunk screw and the blade nut.
8. The rear fuselage structure of a bell and spigot joint unmanned aerial vehicle according to claim 1 or 2, wherein: the number of the short beams is five, and the short beams are symmetrically arranged about a central axis of the engine mounting frame in the left-right direction of the unmanned aerial vehicle and are arranged at intervals along the circumferential direction of the engine mounting frame.
9. A drone comprising a rear fuselage structure of a socket drone according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310902791.6A CN117068410A (en) | 2023-07-21 | 2023-07-21 | Rear fuselage structure of bell-and-spigot type unmanned aerial vehicle and unmanned aerial vehicle comprising rear fuselage structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310902791.6A CN117068410A (en) | 2023-07-21 | 2023-07-21 | Rear fuselage structure of bell-and-spigot type unmanned aerial vehicle and unmanned aerial vehicle comprising rear fuselage structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117068410A true CN117068410A (en) | 2023-11-17 |
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ID=88707004
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310902791.6A Pending CN117068410A (en) | 2023-07-21 | 2023-07-21 | Rear fuselage structure of bell-and-spigot type unmanned aerial vehicle and unmanned aerial vehicle comprising rear fuselage structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117068410A (en) |
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2023
- 2023-07-21 CN CN202310902791.6A patent/CN117068410A/en active Pending
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