CN206984300U - Unmanned vehicle fuselage reinforcement structure - Google Patents

Abstract

The utility model proposes a kind of unmanned vehicle fuselage reinforcement structure, including fuselage and stiffener assembly；Accommodating framework is provided with the fuselage；The stiffener assembly is arranged on the horizontal strengthening part of the inside of the fuselage including horizontal cross and longitudinally reinforced part, at least one of the horizontal strengthening part and longitudinally reinforced part are connected with the accommodating framework.Unmanned vehicle fuselage reinforcement structure of the present utility model, airframe structure can be made to be strengthened and more firm.

Description

Unmanned vehicle fuselage reinforcement structure

Technical field

Unmanned vehicle technical field is the utility model is related to, more particularly to a kind of unmanned vehicle fuselage strengthens knot Structure.

Background technology

With the continuous improvement of development in science and technology and economic level, unmanned vehicle has been fade-in the daily of people Life.Unmanned vehicle bears certain active force due to being needed in flight course, and needs to convert posture flight, stress Direction is also indefinite, thus needs to ensure that fuselage possesses certain intensity.Fuselage especially made of foamed plastics material, even It solid foamed plastics fuselage, can withstand forces still less, be very easy to be broken off under wind-force or the effect of other external force.When The fuselage of right other materials can also have that structure is insecure, easily snaps off due to the reason such as relatively thin.It is then desired to ensure fuselage Can possess certain intensity, be not easy to be broken off.

Utility model content

Technical problem to be solved in the utility model is to provide a kind of unmanned vehicle fuselage reinforcement structure, can make fuselage Structure is strengthened and more firm.

To solve the above problems, the utility model proposes a kind of unmanned vehicle fuselage reinforcement structure, including fuselage and add Strong component；Accommodating framework is provided with the fuselage；The stiffener assembly includes the inside that horizontal cross is arranged on the fuselage Horizontal strengthening part and longitudinally reinforced part, at least one of the horizontal strengthening part and longitudinally reinforced part and the appearance Framework is put to be connected.

According to one embodiment of the present utility model, the middle part of the horizontal strengthening part connects with the accommodating framework Connect fixation；The longitudinally reinforced part is symmetricly set on the accommodating framework both sides, and is connected admittedly with the horizontal strengthening part It is fixed.

According to one embodiment of the present utility model, the horizontal strengthening part is including an at least root long bracing piece and at least Two short bracing pieces；The content dress that the long bracing piece does not influence the accommodating framework is connected admittedly with taking with the accommodating framework It is fixed；Two short bracing pieces are located along the same line, and relative end is connected admittedly with the both sides of the accommodating framework respectively It is fixed.

According to one embodiment of the present utility model, the two-end part of the long bracing piece and two short bracing pieces Opposite end the horizontal strengthening part is connected by connecting bracket.

According to one embodiment of the present utility model, the long bracing piece and two short bracing pieces are in tubular construction.

According to one embodiment of the present utility model, the longitudinally reinforced part includes two groups of reinforcement structures, every group of reinforcement Structure is longitudinally located in the side main wing connecting portion of fuselage, and the longitudinal direction is fuselage fore-and-aft direction.

According to one embodiment of the present utility model, every group of reinforcement structure includes horizontal reinforced sheet and vertical reinforcement Piece, the vertical reinforced sheet is arranged on horizontal reinforced sheet length direction and mutual vertical connection.

According to one embodiment of the present utility model, the vertical reinforced sheet is provided with some positioning tooths in the longitudinal direction, The positioning hole of the corresponding positioning tooth is offered on the horizontal reinforced sheet, the horizontal reinforced sheet and vertical reinforced sheet pass through institute State positioning hole and the vertical grafting of positioning tooth.

According to one embodiment of the present utility model, the both sides main wing connecting portion of the fuselage longitudinally offers level Groove, the bottom land of the level trough longitudinally offer vertical slot, and the vertical reinforced sheet, which plugs, to be fixed in the vertical slot, the level Reinforced sheet is in the level trough.

According to one embodiment of the present utility model, the accommodating framework is plastic frame, and the fuselage is foamed plastics Fuselage.

According to one embodiment of the present utility model, the horizontal strengthening part and longitudinally reinforced part be glass fibre, Plastic cement or carbon fiber portion material.

According to one embodiment of the present utility model, the fuselage includes the upper fuselage being connected and lower fuselage, described Stiffener assembly is between the upper fuselage and lower fuselage.

According to one embodiment of the present utility model, the center of gravity position of the fuselage falls within the horizontal strengthening part and indulged Into the intersection region of strengthening part, the intersection region is the portion that horizontal strengthening part connects with longitudinally reinforced element crosswise The region that position or horizontal strengthening part and longitudinally reinforced element crosswise surround.

After adopting the above technical scheme, the utility model has the advantages that compared with prior art：

Because horizontal strengthening part and longitudinally reinforced part are intersected in fuselage in length and breadth so that fuselage is in all directions Power ability to bear strengthens, and is not easily broken during stress on any direction so that airframe structure is more firm；Due to accommodating framework and its Content occupies larger weight, and compares concentration, by being fixedly connected on horizontal strengthening part and/or longitudinally reinforced part On, the active force of accommodating framework can be caused to share to stiffener assembly, when avoiding the fuselage from being collided by external force, cause accommodating framework Inertia impact and the problem of easily puncture fuselage.

Brief description of the drawings

Fig. 1 is the configuration schematic diagram of the unmanned vehicle fuselage reinforcement structure of the embodiment of the utility model one；

Fig. 2 is the X partial enlargement structural representations of Fig. 1 unmanned vehicle fuselage reinforcement structure；

Fig. 3 is the self-contained structural representation of the unmanned vehicle fuselage reinforcement structure of the embodiment of the utility model one.

Description of symbols in figure：

1- fuselages, 101- main wing connecting portions, the upper fuselages of 11-, fuselage under 12-, 121- level troughs, 122- vertical slots, 21- length Bracing piece, the short bracing pieces of 22-, the horizontal reinforced sheets of 31-, the vertical reinforced sheets of 32-, 311- positioning holes, 321- positioning tooths, 4- accommodating boxes Frame, 5- connecting brackets.

Embodiment

To enable above-mentioned purpose of the present utility model, feature and advantage more obvious understandable, below in conjunction with the accompanying drawings to this The embodiment of utility model is described in detail.

Many details are elaborated in the following description in order to fully understand the utility model.But this practicality is new Type can be to be much different from other manner described here to implement, and those skilled in the art can be new without prejudice to this practicality Similar popularization is done in the case of type intension, therefore the utility model is not limited by following public specific implementation.

Referring to Fig. 1-3, in one embodiment, unmanned vehicle fuselage reinforcement structure includes fuselage 1 and stiffener assembly, can To be applicable to strengthen in any unmanned vehicle of airframe structure, to be especially suitable for the toy flying of plastic foam fuselage In device.

Accommodating framework 4 is provided with fuselage 1, set battery structure can be used in accommodating framework 4, naturally it is also possible to be used for House part needed for other fuselages.Accommodating framework 4 can be that the cover plate can be machine with the frame structure that can open cover plate A part for body, the concrete structure of certainly accommodating framework 4 are also not necessarily limited to this, can be used for housing the portion's material housed needed for fuselage i.e. Can.Accommodating framework 4 can be arranged on the centre of fuselage, machine gravity can more be balanced.

Stiffener assembly is arranged on the horizontal strengthening part of the inside of fuselage 1 and longitudinally reinforced part including horizontal cross, horizontal It is connected at least one of strengthening part and longitudinally reinforced part and accommodating framework 4.In other words, if upper and lower with fuselage To for Z axis, then horizontal strengthening part and longitudinally reinforced element crosswise are arranged on the internal vertical of fuselage 1 in the plane of Z axis, house Framework 4 only can be connected with horizontal strengthening part, only can be also connected with longitudinally reinforced part, can also with both It is connected.Horizontal strengthening part is laterally set in fuselage 1, and longitudinally reinforced part is longitudinally disposed in fuselage 1, laterally can be with It is the left and right directions of fuselage 1, can is longitudinally the fore-and-aft direction of fuselage 1, naturally it is also possible to have offset.Intersect both preferably It is to be mutually perpendicular to, naturally it is also possible to out of plumb.

Horizontal strengthening part and longitudinally reinforced part can be any structures that can be played and strengthen fuselage, can be compared with fuselage For stronger portion's material structure is made or compared with structure more abundant for the housing wall of fuselage 1.Preferably, laterally Strengthening part and longitudinally reinforced part are glass fibre, plastic cement or carbon fiber portion material etc., lighter and sound construction.

Because horizontal strengthening part and longitudinally reinforced part intersect in fuselage 1 in length and breadth so that fuselage 1 is in all directions The enhancing of power ability to bear, be not easily broken during stress on any direction so that the structure of fuselage 1 is more firm；Due to housing framework 4 And its content occupies larger weight, and compare concentration, by being fixedly connected on horizontal strengthening part and/or longitudinally reinforced portion On part, the active force of accommodating framework 4 can be caused to share to stiffener assembly, when avoiding the fuselage 1 from being collided by external force, cause to house The inertia impact of framework 4 and the problem of easily puncture fuselage 1.

In one embodiment, the middle part of horizontal strengthening part is connected with accommodating framework 4；Longitudinally reinforced part The accommodating both sides of framework 4 are symmetricly set on, and are connected with horizontal strengthening part.Horizontal strengthening part and longitudinally reinforced part phase Connect fixation, it is ensured that the structural soundness of whole stiffener assembly, and by accommodating box frame be arranged on stiffener assembly center or By the position at center, it can make it that the center of gravity of fuselage 1 is located at or the closer than center of stiffener assembly so that center of gravity is more stable.

Preferably, horizontal strengthening part includes an at least root long bracing piece 21 and at least two short bracing piece 22.It is long to strengthen The content dress that bar 21 does not influence accommodating framework 4 is connected with taking with accommodating framework 4；That is, long bracing piece 21 is with holding The connection for putting framework 4 does not interfere with toward accommodating that framework 4 is built-in takes corresponding contents thing, and in fig. 2, long bracing piece 21 is located at accommodating box One side of frame 4, the connecting bracket carried by housing framework 4 are connected, naturally it is also possible to the underframe of the accommodating framework 4 of connection. Two short bracing piece 22 is located along the same line, and both sides of the relative end respectively with accommodating framework 4 are connected；Namely Say, two short bracing piece 22 can be regarded as the middle bracing piece blocked, and middle position of blocking connects accommodating framework 4 respectively Both sides.The content dress that the connection of long bracing piece 21, short bracing piece 22 and accommodating framework 4 does not interfere with accommodating framework 4 takes, So that dress takes more convenient, and make it that accommodating framework 4 is centrally located.

The opposite end of the two-end part of long bracing piece 21 and two short bracing piece 22 connects horizontal stroke by connecting bracket 5 To strengthening part.Connecting bracket 5, and accommodating framework 4 and long bracing piece 21, the connecting portion of short bracing piece 22, all it is preferably Plastic part material or other more firm portion's materials, the mode of connection can be bonded by colloid or riveted by riveting parts Compression etc. is unlimited.

Preferably, long bracing piece 21 and two short bracing piece 22 be in tubular construction.On the one hand stiffener assembly can be caused more For lightweight, mitigate main screw lift, on the other hand, in the case where main wing is removable, in long bracing piece 21 and two short bracing piece 22 It can also be used to insert the bracing piece that main wing carries, strengthen the structure of main wing connecting portion.

In one embodiment, longitudinally reinforced part includes two groups of reinforcement structures, and every group of reinforcement structure is longitudinally located in machine The side main wing connecting portion 101 of body, longitudinal direction is fuselage fore-and-aft direction.Two groups of reinforcement structures and long bracing piece 21 and it is two short plus Strong bar 22 is arranged in a crossed manner, and reinforcement structure is closer to main wing, then intersection region is bigger, and the scope that strengthened is wider；In addition, two groups add Part with constant weight, such as steering wheel, propeller etc. can also be set in strong structure so that the installation position of these parts Sound construction.

Preferably, every group of reinforcement structure includes horizontal reinforced sheet 31 and vertical reinforced sheet 32, and vertical reinforced sheet 32 is arranged on On the length direction of horizontal reinforced sheet 31 and mutual vertical connection.Reinforcement structure is designed as laminated structure, can avoid External force rotates under driving, and horizontal reinforced sheet 31 and vertical reinforced sheet 32 is arranged into longitudinally perpendicular connection simultaneously, can be with Strengthen shearing force, twisted on vertical and horizontal direction not easy to break.

Referring to Fig. 1 and Fig. 2, vertical reinforced sheet 32 is provided with some positioning tooths 321 in the longitudinal direction, on horizontal reinforced sheet 31 The positioning hole 311 of corresponding positioning tooth 321 is offered, horizontal reinforced sheet 31 and vertical reinforced sheet 32 pass through positioning hole 311 and positioning 321 vertical grafting of tooth, guarantee is mutually located between vertical reinforced sheet 32 and horizontal reinforced sheet 31 relative offset does not occur so that added Strong structure itself is stable and firm.

Referring to Fig. 2, the longitudinal direction of both sides main wing connecting portion 101 of fuselage 1 offers level trough 121, the bottom land of level trough 121 Longitudinal direction offers vertical slot 122.Vertical reinforced sheet 32, which plugs, to be fixed in vertical slot 122, and horizontal reinforced sheet 31 is located at level trough 121 It is interior.Horizontal reinforced sheet 31 and vertical reinforced sheet 32 are placed by level trough 121 and vertical slot 122, plays positioning and fixed work With reinforcement structure is more stable.

In one embodiment, it is plastic frame to house framework 4, and fuselage 1 is foamed plastics fuselage, the reinforcement of stiffener assembly Effect is especially pronounced, can reduce the possibility of foamed plastics fuselage fracture.Foamed plastics can be EPO (by polyolefin and second The foaming of alkenyl aromatic monomer interpolymer resin particles forms) foamed plastics or EPS (expanded polystyrene (EPS)), EPP Other expanded materials such as (Expanded polyproplene, PP foam materials).

Referring to Fig. 1 and Fig. 3, in one embodiment, fuselage 1 includes the upper fuselage 11 being connected and lower fuselage 12, adds Strong component is between upper fuselage 11 and lower fuselage 12.Can be split system between upper fuselage 11 and lower fuselage 12 in processing Into, then in assembling, after stiffener assembly and miscellaneous part are installed between upper fuselage 11 and lower fuselage 12, upper fuselage 11 With lower fuselage 12 reconnect be fixed up, the mode of being connected can be bonding or other.

Preferably, the center of gravity position of fuselage 1 is fallen within the intersection region of horizontal strengthening part and longitudinally reinforced part, is intersected Region is the position or horizontal strengthening part and longitudinally reinforced part that horizontal strengthening part connects with longitudinally reinforced element crosswise Intersect the region surrounded.Complete machine is centrally located at intersection region so that center of gravity is more steady, and structure is more firm.

Although the utility model is disclosed as above with preferred embodiment, it is not for limiting claim, Ren Heben Art personnel are not being departed from spirit and scope of the present utility model, can make possible variation and modification, therefore The scope of protection of the utility model should be defined by the scope that the utility model claims are defined.

Claims (13)

1. a kind of unmanned vehicle fuselage reinforcement structure, it is characterised in that including fuselage and stiffener assembly；Set in the fuselage There is accommodating framework；The horizontal strengthening part that the stiffener assembly includes the inside that horizontal cross is arranged on the fuselage adds with longitudinal direction Strong part；At least one of the horizontal strengthening part and longitudinally reinforced part are connected with the accommodating framework.

2. unmanned vehicle fuselage reinforcement structure as claimed in claim 1, it is characterised in that in the horizontal strengthening part Between position be connected with the accommodating framework；The longitudinally reinforced part is symmetricly set on the accommodating framework both sides, and with The horizontal strengthening part is connected.

3. unmanned vehicle fuselage reinforcement structure as claimed in claim 2, it is characterised in that the horizontal strengthening part includes An at least root long bracing piece and at least two short bracing pieces；The content dress that the long bracing piece does not influence the accommodating framework takes Ground is connected with the accommodating framework；Two short bracing pieces are located along the same line, and relative end respectively with institute The both sides for stating accommodating framework are connected.

4. unmanned vehicle fuselage reinforcement structure as claimed in claim 3, it is characterised in that the both ends of the long bracing piece Position and the opposite end of two short bracing pieces connect the horizontal strengthening part by connecting bracket.

5. unmanned vehicle fuselage reinforcement structure as claimed in claim 3, it is characterised in that the long bracing piece and described two The short bracing piece of root is in tubular construction.

6. unmanned vehicle fuselage reinforcement structure as claimed in claim 2, it is characterised in that the longitudinally reinforced part includes Two groups of reinforcement structures, every group of reinforcement structure are longitudinally located in the side main wing connecting portion of fuselage, and the longitudinal direction is before and after fuselage Direction.

7. unmanned vehicle fuselage reinforcement structure as claimed in claim 6, it is characterised in that every group of reinforcement structure includes Horizontal reinforced sheet and vertical reinforced sheet, the vertical reinforced sheet are arranged on horizontal reinforced sheet length direction and vertical between each other Connection.

8. unmanned vehicle fuselage reinforcement structure as claimed in claim 7, it is characterised in that the vertical reinforced sheet is in length Direction is provided with some positioning tooths, and the positioning hole of the corresponding positioning tooth is offered on the horizontal reinforced sheet, and the level adds Strong piece and vertical reinforced sheet pass through the positioning hole and the vertical grafting of positioning tooth.

9. unmanned vehicle fuselage reinforcement structure as claimed in claim 8, it is characterised in that the both sides main wing of the fuselage connects Socket part position longitudinally offers level trough, and the bottom land of the level trough longitudinally offers vertical slot, and the vertical reinforced sheet plugs fixation In the vertical slot, the horizontal reinforced sheet is in the level trough.

10. the unmanned vehicle fuselage reinforcement structure as described in any one in claim 1-9, it is characterised in that the appearance It is plastic frame to put framework, and the fuselage is foamed plastics fuselage.

11. the unmanned vehicle fuselage reinforcement structure as described in any one in claim 1-9, it is characterised in that the horizontal stroke It is glass fibre, plastic cement or carbon fiber portion material to strengthening part and longitudinally reinforced part.

12. the unmanned vehicle fuselage reinforcement structure as described in any one in claim 1-9, it is characterised in that the machine Body includes the upper fuselage being connected and lower fuselage, and the stiffener assembly is between the upper fuselage and lower fuselage.

13. the unmanned vehicle fuselage reinforcement structure as described in any one in claim 1-9, it is characterised in that the machine The center of gravity position of body is fallen within the intersection region of the horizontal strengthening part and longitudinally reinforced part, and the intersection region is laterally What position that strengthening part connects with longitudinally reinforced element crosswise or horizontal strengthening part and longitudinally reinforced element crosswise surrounded Region.