CN219969987U - Unmanned aerial vehicle wing leading edge detachable structure oil tank - Google Patents

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and particularly discloses an unmanned aerial vehicle wing front edge detachable structure oil tank, which comprises a connecting component, an oil tank body and a fuel system component arranged on the oil tank body; the outer side surface of the oil tank body is coplanar with the aerodynamic profile surface of the wing front edge to form a lifting force characteristic surface of the unmanned aerial vehicle wing front edge. The utility model has good interchangeability and maintainability; the front oil tank has small bearing, small deformation and small risk of oil seepage and leakage; and the pneumatic loading deformation of the front edge skin can be counteracted by the gravity action of the fuel oil, so that the pneumatic lift effect of the unmanned aerial vehicle wing is ensured, and the aerodynamic force is improved.

Description

Unmanned aerial vehicle wing leading edge detachable structure oil tank

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an oil tank with a detachable wing front edge structure of an unmanned aerial vehicle.

Background

At present, in the prior art, most aircraft's structure oil tank is all arranged in wing box region, is the main load-carrying structure of wing, can't realize the holistic convenient dismantlement of oil tank and the functional requirement of low-cost change maintenance, and wing box region structure bears the weight of the load greatly, and mechanical connection or the gluey connection deformation between oil tank region structure and each part are big after the load, therefore the oil tank takes place to leak oil, the risk of oil leak is great. The flexible oil tank made of the thin-wall rubber material is of a non-bearing structure, and although the flexible oil tank is replaceable, the service life of the flexible oil tank is short, and more mounting structures are required to be designed in the inner space of the machine body to fix the flexible oil tank, so that the flexible oil tank is complex in structure and has more weight increment; meanwhile, the regions with complex internal structures of the wings are difficult to arrange, and the risks of oil seepage and oil leakage are high in use.

Meanwhile, in the prior art, the front edge skin of the unmanned aerial vehicle wing with the lightweight design is thin, the number of ribs is small, the front edge skin is easy to deform under the action of the aerodynamic load of the flying, and therefore the front edge appearance of the wing and the designed front edge theory aerodynamic appearance have poor compliance, the aerodynamic lift effect of the unmanned aerial vehicle wing cannot be effectively ensured, and the aerodynamic efficiency of the wing is reduced.

Disclosure of Invention

The utility model aims to solve the technical problem of providing an oil tank with a detachable structure of an unmanned aerial vehicle wing front edge. Firstly, the wing front edge detachable structural oil tank has the advantages of simple structure, good molding manufacturability and strong practicability, can effectively realize the improvement of the fuel load capacity of the unmanned aerial vehicle, and can adapt to the different requirements of different task configurations of the large unmanned aerial vehicle on the fuel load capacity; secondly, the structural oil tank is connected with the wing main body structure through a plurality of supporting plate nuts and bolts, and can be integrally detached from the wing, so that the wing main body structure has good interchangeability and maintainability; furthermore, the oil tank is arranged at the front edge of the wing, the connection load between the front edge and the wing is small, the load of the oil tank structure is small, the deformation of the oil tank is small, and the risk of oil seepage and oil leakage is small; and finally, the pneumatic loading deformation of the front edge skin can be counteracted by the gravity action of the fuel oil, so that the pneumatic lift force effect of the unmanned aerial vehicle wing is ensured, and the aerodynamic force is improved.

The utility model solves the technical problems by adopting the following solution:

the unmanned aerial vehicle wing front edge detachable structure oil tank comprises a connecting component, an oil tank body and a fuel system component, wherein the connecting component is installed in a wing, the oil tank body is connected with the connecting component and is positioned on one side of the wing front edge, and the fuel system component is installed on the oil tank body; the outer side surface of the oil tank body is coplanar with the aerodynamic profile surface of the wing leading edge and forms a lifting force characteristic surface of the unmanned aerial vehicle wing leading edge.

According to the utility model, the oil tank is detachably arranged in the front edge of the wing, and the front edge of the wing has small load, so that the connection load between the front edge of the wing and the wing is small, the mechanical connection between the front edge independent structure and the wing main body structure is easy to realize, and meanwhile, the deformation of the oil tank is small, and the risks of oil leakage and oil seepage of the oil tank are small due to the small load; meanwhile, the oil tank is arranged in the front edge of the wing, so that the weight of the front edge of the wing is increased, and the deformation of the front edge of the wing is reduced without adding additional structures; simple structure and strong practicability.

In some possible embodiments, the fuel tank is mounted in the wing leading edge for efficient implementation and so that it does not interfere with normal flight;

the fuel tank body comprises a fuel tank skin which is connected with the connecting component and is coplanar with the aerodynamic profile surface of the front edge of the wing, and a skeleton component which is matched with the fuel tank skin and forms a fuel volume cavity; the section of the fuel tank skin is of a U-shaped structure and is matched with the framework component to form a fuel volume cavity with a section of a D-shaped structure.

In some possible embodiments, to effectively achieve the connection of the skeleton assembly to the connector and the tank skin;

the framework component comprises a cross beam arranged along the span direction of the aircraft, and a rib component respectively connected with the cross beam and the oil tank skin;

the rib assembly comprises an outer rib arranged at one end of the cross beam, which is close to the outer side of the front edge of the wing, an inner rib arranged at one end of the cross beam, which is close to the inner side of the front edge of the wing, and a middle rib arranged between the outer rib and the inner rib; the middle rib divides the fuel volume into two volume cavity sections.

In some possible embodiments, to effectively increase the volume of the fuel volume chamber and effectively achieve an effective connection with the connection assembly;

the cross section of the cross beam is in an arch-shaped structure and comprises an upper edge strip, an upper turning section, a web, a lower turning section and a lower edge strip which are connected from top to bottom;

the upper turning section, the web plate and the lower turning section are sequentially connected to form a U-shaped groove with an opening facing to one side of the front edge of the wing;

the outer rib, the inner rib and the middle rib are arranged in the U-shaped groove and extend into the fuel volume cavity to be bonded with the inner side surface of the fuel tank skin; and an oil passing hole communicated with the fuel volume cavity is formed between the outer side surface of the middle rib and the lower turning section.

In some possible embodiments, in order to effectively achieve the connection of the connection assembly with the tank body;

the connecting assembly comprises a wing front beam arranged along the wing span direction and two groups of mounting ribs which are arranged on one side of the wing front beam close to the oil tank body and are arranged in parallel; the wing front beam and the two groups of mounting ribs are respectively connected with the oil tank skin;

the section of the wing front beam is of a C-shaped structure, and an opening of the wing front beam faces the front edge side of the wing and is sleeved with the cross beam; the upper turning section, the web plate and the lower turning section extend into the C-shaped structure;

the oil tank body is located between two sets of mounting ribs.

In some possible embodiments, in order to allow good operability of both the installation and the removal of the present utility model;

the fuel tank skin is provided with a mechanical connection laminated board area which is respectively in threaded connection with the wing front beam and the two groups of mounting ribs, a fuel system component mounting laminated board area for mounting a fuel system component and a honeycomb sandwich area.

In some possible embodiments, in order to facilitate the sealing operation of the inside of the tank after the assembly of the tank body is completed;

the outer rib, the inner rib and the web are respectively provided with a process hole for communicating the fuel volume cavity; and a sealing cover which is matched with the process hole is arranged on the outer side of the cross beam.

In some of the possible embodiments of the present utility model,

the inner side of the web plate is provided with annular mouth frames which are arranged in one-to-one correspondence with the plurality of process holes.

In some of the possible embodiments of the present utility model,

the outer rib and the inner rib have the same structure and comprise a connecting section sleeved in a U-shaped groove of the cross beam and a mounting section which is integrally formed with the connecting section and extends into the fuel volume cavity to be connected with the fuel tank skin; the section of the mounting section is of a C-shaped structure;

a D-shaped opening load shedding area is formed between one side of the middle rib far away from the U-shaped groove and the inner side surface of the oil tank skin;

in order to ensure that the contact gaps between the inner side rib, the outer side rib and the middle rib and the adhesive joint surface of the oil tank skin are uniform and meet the thickness requirement of an adhesive joint layer when the oil tank body is assembled;

in some of the possible embodiments of the present utility model,

and an outer edge strip connected with the oil tank skin is arranged on the outer side of the mounting section and the middle rib, and the width D of the outer edge strip is larger than the thickness D of the outer edge rib or the inner edge rib.

In some of the possible embodiments of the present utility model,

the fuel system component comprises a ventilation float valve, a fuel filler base, a ventilation valve fairing, a fuel drain base and an oil delivery pipe joint, wherein the ventilation float valve, the fuel filler base, the ventilation valve fairing, the fuel drain base and the oil delivery pipe joint are arranged on the fuel tank body;

the ventilation float valve, the oil filler base and the ventilation valve fairing are respectively arranged above the oil tank body and are positioned on one side of the oil tank body, which is close to the outer side of the front edge of the wing; the oil drain port base is arranged at the bottom of the oil tank body and is positioned at one side of the oil tank body close to the inner side of the front edge of the wing; the oil delivery pipe joint is arranged on the inner side rib.

The forming method of the unmanned aerial vehicle wing front edge detachable structure oil tank specifically comprises the following steps:

step S1, paving, adhering and solidifying all parts in an oil tank body;

step S2: holes are formed in each part of the oil tank body;

s3, clamping and positioning the oil tank skin;

the method comprises the steps of supporting an oil tank skin at two ends and the middle position of the oil tank skin by using an appearance clamping plate tool, adjusting the appearance of the oil tank skin, manufacturing a process lug and a positioning hole, and expanding, pressing and fixing the oil tank skin on the appearance clamping plate tool through a pin rod and an inner positioning block on the inner surface of the oil tank skin, so that the clamping and positioning of the oil tank skin are completed;

s4, clamping and positioning a framework component in the oil tank body;

positioning the inner side rib, the outer side rib and the middle rib through positioning pieces;

checking the gap distribution condition of the to-be-bonded surfaces of the inner side rib, the outer side rib, the middle rib and the oil tank skin, polishing the outer side surface of the outer side strip according to the gap distribution condition, and controlling the fit gap between the inner side rib and the outer side rib and between the bonding surfaces of the oil tank skin and the gap between the inner side rib and the outer side rib within 0.1-0.3 mm;

uniformly coating normal-temperature curing structural adhesive on the surfaces to be glued of the inner side rib, the outer side rib, the middle rib and the oil tank skin, and clamping the surfaces to be glued by using a bow clamp;

grinding the surfaces to be bonded of the cross beam, the oil tank skin, the inner side rib, the outer side rib and the middle rib by sand paper to ensure that the roughness of the surfaces to be bonded meets the bonding process requirement, and positioning the cross beam;

checking and controlling fit gaps between the cross beam and the surfaces to be glued of the oil tank skin, the inner side rib, the outer side rib and the middle rib to be within 0.1-0.3 mm, coating normal-temperature curing structural adhesive on the surfaces to be glued of the cross beam, the oil tank skin, the inner side rib, the outer side rib and the middle rib, and clamping the surfaces to be glued by using an arch clamp;

s5, performing normal-temperature cementing solidification and nondestructive detection on the oil tank skin and the skeleton assembly;

s6, sealing the outside of the oil tank body seam;

uniformly coating sealant on the edge line of the cementing interface through the process holes on the web plate, the inner edge rib and the outer edge rib so as to perform the seam external sealing operation of the oil tank;

step S7: and installing a fuel system assembly and a sealing flap.

Compared with the prior art, the utility model has the beneficial effects that:

according to the utility model, the detachable mounting structure oil tank is designed on the front edge of the wing, so that the improvement of the fuel load capacity of the unmanned aerial vehicle can be effectively realized, the different requirements of different task configurations of the large unmanned aerial vehicle on the fuel load capacity can be adapted, and meanwhile, the oil tank is simple in structure, good in molding manufacturability and strong in practicability;

when the oil tank with the wing leading edge structure is filled with fuel oil, the deformation of the leading edge skin under the action of pneumatic load can be counteracted under the action of gravity, so that the pneumatic appearance of the wing leading edge in flight is more in accordance with the designed pneumatic appearance, thereby ensuring the pneumatic lift effect of the unmanned aerial vehicle wing and improving the pneumatic efficiency of the wing;

the oil tank is positioned at the front edge of the wing, and is used as a bearing structure of the wing and bears the flying load of the unmanned aerial vehicle wing together with other structures of the wing, but the bearing load of the front edge structure of the wing is smaller, the connecting load of the front edge and the wing is small, the mechanical connection is easy to realize, and meanwhile, the deformation of the oil tank at the front edge is smaller due to the small bearing, and the risks of oil leakage and oil seepage of the oil tank are small;

the oil tank is detachably arranged on the wing front beam and the mounting rib, so that the front edge oil tank can be integrally detached from the wing of the unmanned aerial vehicle, and the interchangeability function of the oil tank and the convenient maintenance and replacement requirements are realized.

Drawings

FIG. 1 is a schematic view of a fuel tank according to the present utility model;

FIG. 2 is a schematic diagram of the structure of the fuel tank body, the connecting assembly and the fuel system assembly according to the present utility model;

FIG. 3 is a schematic view of the installation of the fuel tank body and fuel system components of the present utility model;

FIG. 4 is a schematic structural view of a skeleton assembly according to the present utility model;

FIG. 5 is an enlarged schematic view of FIG. 4 at A;

FIG. 6 is an enlarged schematic view at B in FIG. 4;

FIG. 7 is a cross-sectional view of the middle rib, cross-beam, tank skin of the present utility model;

FIG. 8 is a cross-sectional view of the inner rib, cross-beam, tank skin of the present utility model;

wherein: 1. a connection assembly; 11. a wing front beam; 12. a mounting rib; 2. an oil tank body; 21. an oil tank skin; 22. a skeleton assembly; 221. a cross beam; 2211. an upper edge strip; 2212. an upper vertical plate; 2213. an upper cross plate; 2214. a web; 2215. a lower cross plate; 2216. a lower vertical plate; 2217. a lower edge strip; 222. an outer rib; 223. a middle rib; 2231. an intermediate connection section; 2232. a suppression section; 2233. an oil passing hole; 2234. an opening load shedding area; 224. an inner side rib; 225. a process hole; 226. an annular mouth frame; 220. an outer edge strip; 3. a fuel system component; 4. sealing the mouth cover; I. an upper turning section; II. A lower turning section; 100. a wing; 200. a wing leading edge.

Detailed Description

In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. Reference to "first," "second," and similar terms herein do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. Likewise, the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. In the implementation of the present utility model, "and/or" describes the association relationship of the association object, which means that there may be three relationships, for example, a and/or B may mean: a exists alone, A and B exist together, and B exists alone. In the description of the embodiments of the present utility model, unless otherwise indicated, the meaning of "a plurality" means two or more. For example, a plurality of positioning posts refers to two or more positioning posts. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

The present utility model will be described in detail below.

As shown in fig. 1-8:

the fuel tank detachably mounted on the wing front edge 200 of the unmanned aerial vehicle comprises a connecting assembly 1 mounted in the wing 100, a fuel tank body 2 connected with the connecting assembly 1 and positioned on one side of the wing front edge 200, and a fuel system assembly 3 mounted on the fuel tank body 2; the outer side surface of the oil tank body 2 is coplanar with the aerodynamic profile surface of the wing leading edge 200 and is a lifting characteristic surface of the wing leading edge of the unmanned aerial vehicle.

The oil tank is detachably arranged in the wing 100, the outer side surface of the oil tank is coplanar with the aerodynamic profile surface of the wing front edge 200, and all the oil tanks are detachably arranged at the position, so that the load bearing capacity of the wing front edge 200 is small, the connecting load of the wing front edge 200 and the wing 100 is small, and the mechanical connection of the independent structure of the wing front edge 200 and the wing 100 is easy to realize; meanwhile, as the bearing load is small, the deformation of the oil tank is small, and the risks of oil leakage and oil seepage of the oil tank are small; simultaneously, the oil tank is arranged on the wing front edge 200, so that the weight of the wing front edge 200 is increased, and the deformation of the wing front edge 200 is reduced without adding extra structure; simple structure and strong practicability.

In some possible embodiments, the fuel tank is mounted in the wing leading edge 200 for efficient implementation and so that it does not interfere with normal flight;

the fuel tank body 2 comprises a fuel tank skin 21 connected with the connecting assembly 1 and coplanar with the aerodynamic profile of the wing leading edge 200, and a skeleton assembly 22 matched with the fuel tank skin 21 and forming a fuel volume cavity; the section of the fuel tank skin 21 is of a U-shaped structure, and a fuel volume cavity with a D-shaped section is formed after the fuel tank skin is glued with the framework assembly 22.

The oil tank skin 21 is an outer boundary surface of the oil tank and is also used as a pneumatic appearance characteristic surface of the wing front edge 200; the oil tank skin 21 is a honeycomb sandwich structure composite material piece, and can effectively improve the overall rigidity, and the oil tank skin 21 is provided with a mechanical connection laminated board area, a fuel system component installation laminated board area and a honeycomb sandwich area, wherein the mechanical connection laminated board area is formed by integrally forming the oil tank skin 21 and is connected with the connection component 1, and the fuel system component installation laminated board area is used for installing the fuel system component 3; the thickness of the honeycomb sandwich area is 4mm, and the honeycomb sandwich is mainly used for increasing the bending rigidity of the oil tank skin 21 and resisting deformation caused by oil pressure;

in some possible embodiments, to effectively achieve the connection of the skeleton assembly 22 to the connector and the tank skin 21;

the skeleton assembly 22 comprises a cross beam 221 arranged along the length direction of the wing 100, and a rib assembly arranged on the cross beam 221 and positioned in the oil tank;

as shown in fig. 4, the rib assembly includes an outer rib 222 disposed at an end of the cross beam 221 adjacent to the outside of the wing leading edge 200, an inner rib 224 disposed at an end of the cross beam 221 adjacent to the inside of the wing leading edge 200, and an intermediate rib 223 disposed between the outer rib 222 and the inner rib 224.

The contact surfaces of the fuel tank skin 21, the inner side rib 224, the outer side rib 222 and the middle rib 223 are subjected to secondary gluing and curing through structural adhesive to form a fuel volume cavity with a D-shaped section;

the intermediate rib 223 divides the fuel volume of the tank body 2 into two volume chamber sections.

In some possible embodiments, in order to effectively increase the volume of the fuel volume chamber and to effectively achieve an effective connection with the connection assembly 1;

as shown in fig. 5 and 7, the cross section of the beam 221 is in an arcuate structure, and includes an upper edge strip 2211, an upper turning section I, a web 2214, a lower turning section II, and a lower edge strip 2217 connected from top to bottom;

the upper turning section I and the upper edge strip 2211 form a clamping groove one with an opening arranged at one side close to the connecting component 1, the lower edge strip 2217 and the lower turning section II form a clamping groove two with an opening towards one side of the wing front edge 200, namely, the clamping groove two is arranged at one side close to the connecting component 1, and the upper turning section I, the web 2214 and the lower turning section II are sequentially connected to form a U-shaped groove with an opening towards one side of the wing front edge 200, namely, one side of the U-shaped groove, which is arranged at the opening far away from the connecting component 1;

wherein, the outer sides of the upper edge strip 2211 and the lower edge strip 2217 are respectively connected with the inner side of the oil tank skin 21 in a gluing way;

the outer rib 222, the inner rib 224 and the middle rib 223 are arranged in the U-shaped groove and extend into the fuel volume cavity to be glued with the inner side surface of the fuel tank skin 21;

further, the inner side rib 224, the outer side rib 222, the middle rib 223 are bonded with the inner surface of the U-shaped groove by structural adhesive to form the longitudinal and transverse boundary surfaces of the fuel tank.

In order to prevent dead oil in the whole fuel volume cavity, an oil passing hole 2233 communicated with the fuel volume cavity is formed between the outer side surface of the middle rib 223 and the lower turning section II; of course, an oil passing hole 2233 communicating with the fuel volume chamber may be formed between the outer side surface of the middle rib 223 and the upper turning section I;

the fuel volume cavity is divided into two volume cavity sections by the middle rib 223, and the two volume cavity sections are communicated through the oil passing hole 2233, so that dead oil in the fuel volume cavity is avoided, and the purpose that the fuel tank body 2 is free of dead oil is achieved;

in some possible embodiments, in order to effectively achieve the connection of the connection assembly 1 with the tank body 2;

the connecting assembly 1 comprises a wing front beam 11 arranged along the extending direction of the wing 100, and two groups of mounting ribs 12 which are arranged on one side of the wing front beam 11 close to the oil tank body 2 in parallel; the wing front beam 11 and the two groups of mounting ribs 12 are respectively connected with the oil tank skin 21;

the fuel tank body 2 is positioned between two sets of mounting ribs 12, wherein the outer rib 222 and the inner rib 224 are positioned between two sets of mounting ribs 12;

the section of the wing front beam 11 is of a C-shaped structure and comprises an upper wing plate, a middle web plate and a lower wing plate; the opening of the device is arranged towards the front edge side of the wing and is sleeved with a cross beam 221 in an arch-shaped structure; namely, the upper turning section I, the web 2214 and the lower turning section II extend into the C-shaped structure; thereby increasing the volume of the fuel volume cavity as much as possible and improving the fuel loading capacity of the fuel tank;

the upper turning section I comprises an upper transverse plate 2213 connected with the top of the web 2214, an upper vertical plate 2212 connected with the upper transverse plate 2213 and parallel to the middle web, and an upper edge strip 2211 connected with one side of the upper vertical plate 2212 far from the upper transverse plate 2213;

the lower turning section II comprises a lower transverse plate 2215 connected with the bottom of the web 2214, a lower vertical plate 2216 connected with the lower transverse plate 2215 and parallel to the middle web, and a lower edge strip 2217 connected with one side of the lower vertical plate 2216 away from the lower transverse plate 2215; the upper cross plate 2213 is arranged in parallel with the lower cross plate 2215 and is matched with the web 2214 to form a U-shaped groove;

the outer side surface of the upper bead 2211, the outer side surface of the inner side rib 224, the outer side surface of the outer side rib 222, and the outer side surface of the intermediate rib 223 are connected to the inner side surface of the tank skin 21 as adhesive bonding surfaces.

As shown in fig. 8, the web 2214 is located in the C-shaped structure of the wing front beam 11, one end of the upper cross plate 2213 and the lower cross plate 2215 extend into the C-shaped structure of the wing front beam 11 to be connected with the web 2214, and the C-shaped structure of the other end of the upper cross plate 2213 and the lower cross plate 2215 extending out of the wing front beam 11 is connected with the corresponding upper vertical plate 2212 or lower vertical plate 2216;

the upper wing plate and the lower wing plate of the front wing beam 11 are respectively positioned outside the upper cross plate 2213 and the lower cross plate 2215, and form a gap between the upper wing plate and the lower wing plate; the oil tank skin 21 is in threaded connection with the upper wing plate and the lower wing plate; the upper cross plate 2213 is coplanar with the outer side of the upper wing plate to form a surface connected with the top inner side of the fuel tank skin 21, and the lower cross plate 2215 is coplanar with the outer side of the lower wing plate to form a surface connected with the bottom inner side of the fuel tank skin 21.

In some of the possible embodiments of the present utility model,

the two groups of the installation ribs 12 are made of aluminum alloy materials, the installation rib 12 positioned at the inner side of the wing 100 is an inner side oil tank installation rib, and the installation rib 12 positioned at the outer side of the wing 100 is an outer side oil tank installation rib and is made of a carbon fiber composite material laminated board; the cross beam 221 is made of carbon fiber laminate.

The outer side surface of the mechanical connection laminated board area is on the same plane with the outer side surface of the oil tank skin, and is an installation connection functional area of the whole oil tank on the wing 100, and the mechanical connection laminated board area comprises a front beam edge strip connection laminated board area connected with a wing front beam 11 through a countersunk bolt and a supporting plate nut wing, a wing inner side oil tank installation rib connection laminated board area connected with an inner side oil tank installation rib through a countersunk bolt and a supporting plate nut, and a wing outer side oil tank installation rib connection laminated board area connected with an outer side oil tank installation rib through a countersunk bolt and a supporting plate nut.

The inner oil tank installation rib 12 is positioned in the wing inner oil tank installation rib connecting laminate area, and the outer oil tank installation rib 12 is positioned in the wing outer oil tank installation rib connecting laminate area;

countersunk holes are formed in the region of the connecting laminate of the oil tank mounting rib on the inner side of the wing, and then the countersunk holes are mechanically connected with the upper wing plate and the lower wing plate respectively through countersunk bolts and supporting plate nut assemblies; the method comprises the steps that counter sunk holes are formed in the region of the connecting laminate of the oil tank mounting rib on the outer side of the wing, and the counter sunk holes are mechanically connected with the upper wing plate and the lower wing plate respectively through a plurality of counter sunk bolts and supporting plate nut assemblies; meanwhile, at the position of the mechanical connection area, structural adhesive is adopted to carry out glue connection after the assembly is completed.

In some possible embodiments, to facilitate the sealing operation of the inside of the tank after the assembly of the tank body 2 is completed;

the outer rib 222, the inner rib 224 and the web 2214 are respectively provided with a process hole 225 which is used for sealing and is communicated with the fuel volume cavity; the process hole 225 is circular, the process hole 225 is a construction channel for sealing operation in the later-stage oil tank, and is used for coating sealant on the sealing boundary in the oil tank body after assembly is completed so as to perform sealing operation outside the sealing seam boundary of the oil tank;

the outside of the beam 221 is provided with a sealing cover 4 which is matched with the process hole 225;

preferably, sealing gaskets are arranged between the sealing flap 4 and the outer rib 222, the inner rib 224 and the web 2214 respectively;

in some possible embodiments, the process holes 225 on the web 2214 are multiple and disposed spanwise along the wing 100 for easy sealant application;

because the cross beam 221 is made of a carbon fiber laminated board, the thickness is thinner, and for this purpose, an annular opening frame 226 which is arranged in one-to-one correspondence with a plurality of process holes 225 is arranged on the inner side of the web 2214, and the sealing flap 4 is connected with the annular opening frame 226 through countersunk bolts and air-tight supporting plate nut assemblies, so as to ensure the sealing effect. The provision of the annular mouth frame 226 will effectively strengthen the connection of the cross beam 221 with the sealing mouth cover 4.

In some of the possible embodiments of the present utility model,

the outer rib 222 and the inner rib 224 have the same structure and comprise a connecting section sleeved in the U-shaped groove of the beam 221 and a mounting section which is integrally formed with the connecting section and extends into the fuel volume cavity to be connected with the fuel tank skin 21; the section of the mounting section is of a C-shaped structure; the U-shaped groove of the cross beam 221 is a U-shaped groove with an opening facing one side of the wing leading edge 200, wherein the upper turning section I, the web 2214 and the lower turning section II are sequentially connected;

in order to effectively reduce deformation of the fuel tank skin 21 caused by fuel pressure or pressurization, so as to keep the leading edge fuel tank in a state of larger fuel internal pressure in maneuvering flight of the unmanned aerial vehicle, the aerodynamic profile of the wing leading edge 200 of the unmanned aerial vehicle can still meet the aerodynamic performance requirement of the unmanned aerial vehicle; the intermediate rib 223 of the present utility model will serve as a deformation inhibiting rib of the tank body 2; a small cavity is formed between the side of the middle rib 223, which is far away from the cross beam 221, and the inner side of the fuel tank skin 21, and the small cavity is in a D shape and is an opening load relief area 2234;

as shown in fig. 6 and 7, the middle rib 223 comprises a middle connecting section 2231 which is partially installed in the U-shaped groove and the other part of which extends into the fuel volume cavity, and a suppressing section 2232 which is connected with the middle connecting section 2231 and is positioned in the fuel volume cavity, wherein the upper side and the lower side of the suppressing section 2232 are glued with the fuel tank skin 21; a D-shaped opening load relief area 2234 is formed between the side of the suppression section 2232, which is far from the intermediate connection section 2231, and the inner side surface of the fuel tank skin 21; an oil hole 2233 is formed between the lower vertical plate 2216 and the upper vertical plate 2212 and on one side of the suppression section 2232 near the intermediate connection section 2231.

In order to ensure that the contact gaps between the inner side rib 224, the outer side rib 222 and the middle rib 223 and the adhesive joint surface of the oil tank skin 21 are uniform and meet the thickness requirement of the adhesive joint layer when the oil tank body 2 is assembled;

as shown in fig. 6, an outer edge strip 220 glued to the tank skin 21 is provided on the outside of the mounting section, the middle rib 223, the width D of the outer edge strip 220 being greater than the thickness D of the outer edge rib 222 or the inner edge rib 224.

In some of the possible embodiments of the present utility model,

the fuel system assembly 3 comprises a ventilation float valve, a fuel filler base, a ventilation valve fairing, a fuel drain base and an oil delivery pipe joint, wherein the ventilation float valve, the fuel filler base, the ventilation valve fairing, the fuel drain base and the oil delivery pipe joint are arranged on the fuel tank body 2 and are respectively positioned in a layer plate area of the fuel system assembly 3;

the ventilation float valve, the oil filler base and the ventilation valve fairing are respectively arranged above the oil tank body 2 and are positioned on one side of the oil tank body 2, which is close to the outer side of the wing front edge 200; the oil drain port base is arranged at the bottom of the oil tank body 2 and is positioned at one side of the oil tank body 2 close to the inner side of the wing front edge 200; the oil delivery pipe joint is disposed on the inner side rib 224.

According to the utility model, the edge strip connection laminate area of the wing front beam 11, the inner side oil tank installation rib connection laminate area and the outer side oil tank installation rib connection laminate area of the oil tank skin 21 are installation connection function areas of the oil tank on the wing 100, and the connection with the wing front beam 11, the inner side oil tank installation rib 12 and the outer side oil tank installation rib 12 is realized through countersunk bolts and pallet nuts; meanwhile, the disassembly operation is realized through the countersunk head bolts, and the oil tank has good operability in installation and disassembly based on the connection design;

the forming method of the oil tank specifically comprises the following steps:

step S1, paving, adhering and solidifying all parts in an oil tank body;

paving and curing and forming all parts in the oil tank body 2, paving all parts on a forming die of all parts of the oil tank according to a designed paving sequence, moving the paved parts into an autoclave, setting forming process parameters such as forming temperature, pressure and the like, and curing and forming for a certain time; the components here include a tank skin 21, a cross beam 221, an inner edge rib 224, an outer edge rib 222, an intermediate rib 223, a sealing flap 4;

wherein, the front edges of the two ends of the oil tank skin 21 are reserved with process lugs, and after solidification and demolding, the mold is closed, and the film sticking degree is checked;

the beams 221, the inner side ribs 224, the outer side ribs 222 and the middle ribs 223 are retracted by 0.5mm so as to reserve the demolding resilience and the glue line thickness;

step S2: holes are formed in each part of the oil tank body;

manufacturing process holes 225 and other fuel assembly mounting holes on the cured and molded fuel tank skin 21, the cross beam 221, the inner side rib 224 and the outer side rib 222;

step S3, clamping and positioning the oil tank skin 21 by using a positioning tool, wherein the clamping and positioning means: the oil tank skin 21 is supported by the shape clamping plate tool at the two ends and the middle position of the oil tank skin 21, the shape of the oil tank skin 21 is adjusted, the process lugs and the positioning holes are manufactured, and the oil tank skin 21 is propped up, pressed and fixed on the shape clamping plate tool through the pin rod and the inner positioning block on the inner surface of the oil tank skin 21, so that the clamping and positioning of the oil tank skin 21 are completed;

s4, clamping and positioning a framework assembly 22 in the oil tank body 2;

the carcass assembly 22 described herein includes a cross beam 221, inner side ribs 224, outer side ribs 222, middle ribs 223;

positioning the inner side rib 224 and the outer side rib 222 by two-end positioners and positioning the middle rib 223 by a positioning tool;

then checking the gap distribution condition of the surfaces to be glued of the inner side rib 224, the outer side rib 222 and the middle rib 223 and the oil tank skin 21, polishing the outer edge strips 220 of the inner side rib 224, the outer side rib 222 and the middle rib 223 according to the gap distribution condition, and controlling the fit gap between the glue joint surfaces of the inner side rib 224 and the outer side rib 222 and the oil tank skin 21 to be within 0.1-0.3 mm;

the inner side rib 224, the outer side rib 222, the middle rib 223 and the to-be-glued surface of the oil tank skin 21 are uniformly coated with normal temperature curing structural glue, and the to-be-glued surface is clamped by a proper number of bow clamps;

the beam 221, the to-be-glued surfaces of the oil tank skin 21, the inner side rib 224, the outer side rib 222 and the middle rib 223 are sanded by adopting sandpaper, so that the roughness of the to-be-glued surfaces meets the requirement of a gluing process, and the beam 221 is positioned by using a tool;

then checking and controlling fit gaps between the beam 221 and the surfaces to be glued of the oil tank skin 21, the inner side rib 224, the outer side rib 222 and the middle rib 223 to be within 0.1-0.3 mm, uniformly coating normal-temperature curing structural adhesive on the surfaces to be glued of the beam 221 and the oil tank skin 21, the inner side rib 224, the outer side rib 222 and the middle rib 223, and clamping the surfaces to be glued by using a proper number of bow clamps;

s5, the fuel tank skin 21 and the framework component 22 are glued, solidified and subjected to nondestructive testing at normal temperature;

gluing according to the using standard of the normal-temperature structural adhesive, clamping the to-be-glued surface of the framework component 22 and the oil tank skin 21 by a proper number of arched clamps so as to apply proper gluing pressure to the to-be-glued surface, and standing for a certain time to finish the solidification of the structural adhesive and form a self-sealing structural oil tank;

after the solidification forming is finished, carrying out nondestructive testing, checking the cementing defect, and carrying out nailing connection operation on the cementing defect area;

s6, performing sealing construction on the outer side of the seam of the oil tank body 2;

the sealing agent is evenly coated on the edge line of the cementing interface through the web 2214 of the beam 221, the inner edge rib 224 and the process hole 225 on the outer edge rib 222, so as to carry out the seam external sealing operation of the oil tank;

step S7: the fuel system assembly 3 and the sealing flap 4 are installed.

In the utility model, structural members such as the oil tank skin 21, the cross beam 221, the inner side rib 224, the outer side rib 222, the middle rib 223, the sealing flap 4 and the like are respectively cured and formed firstly, then the bonding surfaces of the structural members are subjected to secondary bonding and curing by adopting structural adhesive to form the oil tank body 2, and then the sealing agent is evenly coated at the bonding interface side line of each part by virtue of the process hole 225 so as to realize the sealing operation in the oil tank body 2; after the coating is completed, the process orifice 225 is closed by a sealing flap.

Mechanical connecting bolt holes of the fuel system component 3 and the sealing port cover 4 are formed in the fuel tank cross beam 221, the fuel tank skin 21, the inner side rib 224 and the outer side rib 222, airtight supporting plate nuts are installed, and then the fuel system component 3 and the sealing port cover 4 are installed, so that the assembly is completed.

The utility model is not limited to the specific embodiments described above. The utility model extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.

Claims (9)

1. The unmanned aerial vehicle wing front edge detachable structure oil tank is characterized by comprising a connecting component, an oil tank body and a fuel system component, wherein the connecting component is installed in a wing, the oil tank body is connected with the connecting component and is positioned on one side of the wing front edge, and the fuel system component is installed on the oil tank body; the outer side surface of the oil tank body is coplanar with the aerodynamic profile surface of the wing leading edge and forms a lifting force characteristic surface of the unmanned aerial vehicle wing leading edge.

2. The unmanned aerial vehicle wing leading edge removable structure fuel tank of claim 1, wherein the fuel tank body comprises a fuel tank skin connected with the connecting assembly and coplanar with the aerodynamic profile of the wing leading edge, and a skeleton assembly mated with the fuel tank skin and forming a fuel volume cavity; the section of the fuel tank skin is of a U-shaped structure and is matched with the framework component to form a fuel volume cavity with a section of a D-shaped structure.

3. The unmanned aircraft wing leading edge removable structural fuel tank of claim 2, wherein the skeleton assembly comprises a cross beam disposed in a spanwise direction of the aircraft, and a rib assembly connected to the cross beam and the fuel tank skin, respectively;

the rib assembly comprises an outer rib arranged at one end of the cross beam, which is close to the outer side of the front edge of the wing, an inner rib arranged at one end of the cross beam, which is close to the inner side of the front edge of the wing, and a middle rib arranged between the outer rib and the inner rib; the middle rib divides the fuel volume into two volume cavity sections.

4. The unmanned aerial vehicle wing front edge detachable structural oil tank of claim 3, wherein the cross section of the cross beam is in an arch-shaped structure and comprises an upper edge strip, an upper turning section, a web, a lower turning section and a lower edge strip which are connected from top to bottom;

the upper turning section, the web plate and the lower turning section are sequentially connected to form a U-shaped groove with an opening facing to one side of the front edge of the wing;

the outer rib, the inner rib and the middle rib are arranged in the U-shaped groove and extend into the fuel volume cavity to be bonded with the inner side surface of the fuel tank skin; and an oil passing hole communicated with the fuel volume cavity is formed between the outer side surface of the middle rib and the lower turning section.

5. The unmanned aerial vehicle wing leading edge removable structure fuel tank of claim 4, wherein the connecting assembly comprises a wing front beam arranged along the wing span direction, and two groups of mounting ribs which are arranged on one side of the wing front beam close to the fuel tank body in parallel; the wing front beam and the two groups of mounting ribs are respectively connected with the oil tank skin;

the section of the wing front beam is of a C-shaped structure, and an opening of the wing front beam faces the front edge side of the wing and is sleeved with the cross beam; the upper turning section, the web plate and the lower turning section extend into the C-shaped structure;

the oil tank body is located between two sets of mounting ribs.

6. The unmanned aerial vehicle wing leading edge removable structure fuel tank of claim 5, wherein the fuel tank skin is provided with a mechanical connection laminate section for respectively screwing with the wing front beam, the two sets of mounting ribs, a fuel system component mounting laminate section for mounting the fuel system component, and a honeycomb sandwich section.

7. The unmanned aerial vehicle wing front edge detachable structural oil tank of claim 6, wherein the outer rib, the inner rib and the web are respectively provided with a process hole for sealing; and a sealing cover which is matched with the process hole is arranged on the outer side of the cross beam.

8. The unmanned aerial vehicle wing leading edge detachable structure oil tank of claim 6, wherein the technological holes on the web plate are multiple and are arranged along the wing spanwise direction, and the inner side of the web plate is provided with an annular mouth frame which is arranged in one-to-one correspondence with the multiple technological holes.

9. The unmanned aerial vehicle wing front edge detachable structural fuel tank of any one of claims 4 to 8, wherein the outer rib and the inner rib have the same structure, and the unmanned aerial vehicle wing front edge detachable structural fuel tank comprises a connecting section sleeved in a U-shaped groove of the cross beam and a mounting section integrally formed with the connecting section and extending into the fuel volume cavity to be connected with a fuel tank skin; the section of the mounting section is of a C-shaped structure;

a D-shaped opening load shedding area is formed between one side of the middle rib far away from the U-shaped groove and the inner side surface of the oil tank skin;

and an outer edge strip connected with the oil tank skin is arranged on the outer side of the mounting section and the middle rib, and the width D of the outer edge strip is larger than the thickness D of the outer edge rib or the inner edge rib.