CN207292364U - Horn clamping device and aircraft for aircraft - Google Patents
Horn clamping device and aircraft for aircraft Download PDFInfo
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- CN207292364U CN207292364U CN201720701869.8U CN201720701869U CN207292364U CN 207292364 U CN207292364 U CN 207292364U CN 201720701869 U CN201720701869 U CN 201720701869U CN 207292364 U CN207292364 U CN 207292364U
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- horn
- lantern ring
- aircraft
- clamping piece
- hole
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Abstract
According to the horn clamping device for aircraft of the utility model embodiment, clamping device includes：The lantern ring and clamping piece, the lantern ring have mounting hole, and mounting hole is used to install horn, and outer peripheral wall of the collar is equipped with lug boss, and lug boss extends along the circumferential direction of the lantern ring.Clamping piece has opposite first surface and second surface, and clamping piece is equipped with through hole, and through hole is penetrated through to second surface, the lantern ring from first surface and is contained in through hole, and the inner wall of through hole is equipped with the holding tank for the lug boss for being used to house the lantern ring.Horn clamping device according to the present utility model for aircraft, by the way that encapsulation ring set is arranged on horn, and the lug boss of the lantern ring is accommodated to clamping piece holding tank, the horn that can make to be equipped with the lantern ring is firmly secured to clamping piece, and the internal perisporium backstop of lug boss and holding tank is spacing, prevent and relatively moved between the lantern ring and clamping piece, so as to enhance the fixed stably solidity of horn, and then improve the structural stability of aircraft.
Description
Technical field
Vehicle technology field is the utility model is related to, specifically, more particularly to a kind of horn for aircraft presss from both sides
Hold mechanism and aircraft.
Background technology
In recent years, with the development of aircraft, because its require with maneuverability, rapid reaction, unmanned flight, operation it is low
The advantages that, multi-party concern is caused, and be applied in multiple fields such as agricultural, explorations.
Aircraft generally includes fuselage, the multiple horns being connected with fuselage (can be four, six, eight or more
It is more), be arranged on each horn and be used to drive the power set of the aircraft flight and control for controlling the aircraft
System.
Loaded in aircraft operation process it is larger, the horn of aircraft required with fuselage bonding strength it is high, in correlation technique,
The connection mode of horn and fuselage is not firm, is easy to cause horn loosens, and seriously affects the operating efficiency of agricultural aircraft.
Utility model content
The utility model is intended at least solve one of technical problem existing in the prior art.For this reason, the utility model carries
Go out a kind of horn clamping device for aircraft, the clamping device has the advantages that simple in structure, fixation.
The utility model also proposes a kind of aircraft, and the aircraft includes the horn for aircraft described above and presss from both sides
Hold mechanism.
According to the horn clamping device for aircraft of the utility model embodiment, clamping device includes：The lantern ring, it is described
The lantern ring has mounting hole, and the mounting hole is used to install horn, and the outer peripheral wall of the collar is equipped with lug boss, the lug boss
Extend along the circumferential direction of the lantern ring；And clamping piece, the clamping piece has opposite first surface and second surface, described
Clamping piece is equipped with through hole, and the through hole is penetrated through to the second surface from the first surface, and the lantern ring is contained in described
In through hole, the inner wall of the through hole is equipped with the holding tank for the lug boss for being used to house the lantern ring.
According to the horn clamping device for aircraft of the utility model embodiment, by the way that encapsulation ring set is arranged on horn
On, and the lug boss of the lantern ring is accommodated to clamping piece holding tank, the horn for being equipped with the lantern ring can be made to be firmly secured to clamping
Part, and the internal perisporium backstop of lug boss and holding tank is spacing, it is therefore prevented that relatively moved between the lantern ring and clamping piece, so that
The fixed stably solidity of horn is enhanced, and then improves the structural stability of aircraft.
In some embodiments of the utility model, the clamping piece includes：Clamping piece body, the clamping piece body tool
There are the first surface, the second surface, and connect the lateral surface of the first surface and the second surface, it is described outer
Side is equipped with installation gap；And compact heap, adjacent to the installation gap, the compact heap includes being equipped with the appearance compact heap
Receive groove.Thus, it is possible to the horn for being cased with the lantern ring is firmly fixed between clamping piece body and compact heap, and by the convex of the lantern ring
The portion of rising is contained in holding tank, the internal perisporium of lug boss and holding tank is only supported, and enhances the firm reliability of horn fixation.
Some embodiments according to the present utility model, the surface extending into the through hole of the compact heap include supporting
Face, the inner peripheral surface of the supporting surface and the through hole limit the through hole, and the supporting surface is equipped with the holding tank.By
The lantern ring, can be firmly secured in through hole by this.
In some embodiments of the utility model, set at the position of the close installation gap of the clamping piece body
There is installation groove, the end of the compact heap is detachably secured in the installation groove.Thus, easy to compact heap and clamping
Dismounting between part.
Some embodiments according to the present utility model, in the installation gap, the clamping piece body close to described
Surface at installation gap is transition face, and the transition face is plane.Thus, easy to the processing and manufacturing of transition face, so as to
Reduce production cost.Moreover, transition face has guiding role, easy to being linked and packed between compact heap and clamping piece.
Further, the internal perisporium of the through hole has inner plane section, have the installation gap the lateral surface with
Angle between the inner plane section is 90 ° -95 °.Thus, easy to the assembling between horn and clamping piece, and can prevent
Recurring structure is interfered when compact heap is assembled with clamping piece.
Some embodiments according to the present utility model, the lug boss is in a ring.Thus, easy to the processing system of lug boss
Make, so as to reduce production cost.
In some embodiments of the utility model, the lug boss is multiple for what is be spaced apart, and the holding tank corresponds to institute
It is multiple for what is be spaced apart to state lug boss.Thus, it is possible to further enhance the fastness of clamping device fixation.
Some embodiments according to the present utility model, the first surface or second surface of the clamping piece body are neighbouring described
Through hole abuts the lug boss.Thus, it is possible to only supported with lug boss by the first surface or second surface of clamping piece body
It is spacing, prevent the lantern ring to be moved, and then improve the fastness of horn fixation.
According to the aircraft of the utility model embodiment, aircraft includes：Fuselage；At least one horn；And clamping device,
The clamping device is clamping device described above, and the clamping piece body of the clamping device is connected with the fuselage, institute
The lantern ring for stating clamping device is set on the horn.
According to the aircraft of the utility model embodiment, by being connected compact heap with clamping piece to close installation gap,
And accommodate lug boss to holding tank, the horn that can make to be equipped with the lantern ring is firmly secured between clamping piece and compact heap,
And the internal perisporium backstop of lug boss and holding tank is spacing, it is therefore prevented that opposite move occurs between the lantern ring and clamping piece and compact heap
It is dynamic, so as to enhance the fixed stably solidity of horn, and then improve the structural stability of aircraft.
The additional aspect and advantage of the utility model will be set forth in part in the description, partly by from following description
In become obvious, or recognized by the practice of the utility model.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the utility model will in the description from combination accompanying drawings below to embodiment
Become obvious and be readily appreciated that, wherein：
Fig. 1 is the stereogram according to the aircraft of the utility model embodiment；
Fig. 2 is the stereogram of the part-structure of the aircraft (removing battery, Article holding box and fuselage roof) in Fig. 1；
Fig. 3 is the partial enlarged view of the part A shown in Fig. 2；
Fig. 4 is the three-dimensional installation diagram of the horn and the lantern ring in Fig. 2；
Fig. 5 is the stereogram of first lantern ring in Fig. 4；
Fig. 6 is the side view of first lantern ring of Fig. 5；
Fig. 7 is the stereogram of second lantern ring in Fig. 4；
Fig. 8 is the front view of the end clamping members in Fig. 2；
Fig. 9 is the stereogram of the end clamping members of Fig. 8；
Figure 10 is the stereogram of the end compact heap in Fig. 2；
Figure 11 is the stereogram of the fixing piece in Fig. 2；
Figure 12 is the stereogram of the counterpart in Fig. 2；
Figure 13 is the front view according to the clamping piece body of the utility model embodiment；
Figure 14 is the stereogram of clamping piece body in Figure 13；
Figure 15 is the stereogram according to the compact heap of the utility model embodiment；
Figure 16 is the front view of compact heap in Figure 15；
Figure 17 is the stereogram of compact heap other direction in Figure 15.
Reference numeral：
Aircraft 100,
Fuselage 1, bottom plate 11, top plate 12,
Horn 2, the body of rod 21,
End clamping members 31, arc section 301, planar section 302, changeover portion 303, the 3rd surface 311, the 4th surface 312, side
Face 313, top surface 314, bottom surface 315, mounting hole 316, assembling groove 317, positioning convex column 318, boss 319, end compact heap 32,
Locking portion 321, connecting portion 322, locks face 323,
Fixing piece 33, base portion 331, holding section 332, the first catch surface 333, counterpart 34, the second catch surface 341,
The lantern ring 39, mounting hole 3900, arc section 3901, planar section 3902, changeover portion 3903, glue groove 3904, first set
Ring 391, second lantern ring 392, lug boss 3921,
Clamping device 4, clamping piece 40, clamping piece body 41, first surface 411, second surface 412, lateral surface 430, peace
Fill notch 4131, transition face 4132, through hole 416, inner circle segmental arc 4161, inner plane section 4162, interior changeover portion 4163, installation groove
417, compact heap 42, holding tank 420, body 421, connecting pin 422, supporting surface 423,
Power set 5, undercarriage 6, battery 7, Article holding box 8,
Fixing device 9, installation space 900, the first installation space 901, the second installation space 902.
Embodiment
The embodiment of the utility model is described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning
Same or similar element is represented to same or similar label eventually or there is same or like element.Below by ginseng
The embodiment for examining attached drawing description is exemplary, and is only used for explaining the utility model, and it is not intended that to the utility model
Limitation.
In the description of the utility model, it is to be understood that term " " center ", " on ", " under ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " top ", " bottom " " interior ", " outer ", " axial direction ", " radial direction ", " circumferential direction " be based on
Orientation shown in the drawings or position relationship, are for only for ease of description the utility model and simplify description, rather than instruction or dark
Show that the device of meaning or element there must be specific orientation, with specific azimuth configuration and operation, thus it is it is not intended that right
The limitation of the utility model.In addition, define " first ", the feature of " second " can express either implicitly include one or
More this feature.In the description of the utility model, unless otherwise indicated, " multiple " are meant that two or more.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in the description of the utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can mechanically connect or be electrically connected；It can be directly connected, can also be indirectly connected by intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the utility model.
Clamping device 4 and aircraft 100 below with reference to Fig. 1-Figure 17 descriptions according to the utility model embodiment.
As shown in Figures 2 and 3, included according to the clamping device 4 of the utility model embodiment, clamping device 4：The lantern ring 39,
With clamping piece 40.
Specifically, the lantern ring 39 has mounting hole 3900, and mounting hole 3900 is used to install horn 2, as shown in Figure 3 and Figure 4,
The lantern ring 39 can be coated at the periphery wall of horn 2 by mounting hole 3900.Thus, the lantern ring 39 can undertake horn 2 and other portions
Assembling transition piece between part, easy to the fixing assembling between horn 2 and miscellaneous part, and the lantern ring 39 is imitated with damping, buffering
Fruit.As shown in figure 4, the periphery wall of the lantern ring 39 is equipped with lug boss 3921, lug boss 3921 extends along the circumferential direction of the lantern ring 39.
Thus, can be spacing with backstop between lug boss 3921 and miscellaneous part when the fixing assembling lantern ring 39, enhance the lantern ring 39 and fix
Fastness.
As shown in Figure 13 and Figure 14, clamping piece 40 has opposite first surface 411 and second surface 412, clamping piece 40
Also there is the lateral surface 430 being connected between first surface 411 and second surface 412.Clamping piece 40 is equipped with through hole 416, leads to
Hole 416 penetrates through to second surface 412, the lantern ring 39 from first surface 411 and is contained in through hole 416, and the inner wall of through hole 416, which is equipped with, to be used
In the holding tank 420 for housing lug boss 3900.
It should be noted that in fixed horn 2, the lantern ring 39 first can be sheathed on horn 2 by through hole 3900, and make
Connection is consolidated between the lantern ring 39 and horn 2.The horn 2 for being equipped with the lantern ring 39 is stretched in the through hole 416 of clamping piece 40, makes set
The periphery wall of ring 39 is bonded with the internal perisporium of through hole 416, and lug boss 3921 is embedded in holding tank 420, so that by the lantern ring 39
Be fixed in through hole 416, and lug boss 3921 and the internal perisporium backstop of holding tank 420 are spacing, it is therefore prevented that the lantern ring 39 with
Clamping piece 40 relatively moves, so that horn 2 is only fixed in clamping device 4.
According to 2 clamping device 4 of horn for aircraft 100 of the utility model embodiment, by by 39 sets of encapsulation ring
Accommodated on horn 2, and by the lug boss 3921 of the lantern ring 39 to the holding tank 420 of clamping piece 40, can make to be equipped with set
The horn 2 of ring 39 is firmly secured to clamping piece 40, and lug boss 3921 and the internal perisporium backstop of holding tank 420 are spacing, prevent
Relatively moved between the lantern ring 39 and clamping piece 40, so as to enhance 2 fixed stably solidity of horn, and then improve aircraft
100 structural stability.
In some embodiments of the utility model, clamping piece 40 includes：Clamping piece body 41 and compact heap 42, clamping piece
Body 41 has first surface 411, second surface 412 and the lateral surface 430 of connection first surface 411 and second surface 412,
Lateral surface 430 is equipped with installation gap 4131.Compact heap 42 includes body 421, body adjacent to installation gap 4131, compact heap 42
421 are equipped with holding tank 420.
As shown in Figure 13-Figure 17, installation gap 4131 be arranged on lateral surface 430 and connection through hole 416, installation gap 4131 every
Disconnected lateral surface 430, compact heap 42 are located in installation gap 4131 and are connected with clamping piece body 41 to close installation gap 4131.
, also can be along logical it is understood that the horn 2 after the assembling lantern ring 39 can be assembled in through hole 416 by installation gap 4131
The axial direction in hole 416 is penetrated in through hole 416, is then connected compact heap 42 with clamping piece body 41, thus, compact heap 42 with
Clamping piece body 41, which coordinates, to be tightly clamped in the lantern ring 39 in through hole 416.Compact heap 42 has holding tank 420, lug boss
3921 are housed in holding tank 420.Thus, the internal perisporium of lug boss 3921 and holding tank 420 only supports spacing, limits the lantern ring 39
Movement, and then improve the fixed stably solidity of horn 2.
Some embodiments according to the present utility model, with reference to shown in Figure 14 and Figure 15, compact heap 42 extend into through hole 416
Interior surface forms supporting surface 423, and supporting surface 423 limits through hole 416 with clamping piece body 41.It is understood that compress
Block 42 can be installed in the installation gap 4131 of clamping piece body 41, and the inner surface of compact heap 42 towards through hole 416 is configured to
Supporting surface 423, supporting surface 423 and clamping piece body 41 are bonded with the outer surface of the lantern ring 39, thus, it is possible to which the lantern ring 39 is firmly solid
Due in through hole 416.
As shown in figure 14, installation gap 4131 is provided with the lateral surface 430 of clamping piece body 41, for example, installation gap
4131 can be located at the top surface of clamping piece body 41, and certainly, installation gap 4131 may be located on the following table of clamping piece body 41
On face or side wall.As shown in Figure 15-Figure 17, in the lower end of compact heap 42 (such as the above-below direction as shown in Figure 15-Figure 17) shape
Camber supporting surface 423.When compact heap 42 is installed in the installation gap 4131 of clamping piece body 41, supporting surface 423 and folder
Circular through hole 416, the lantern ring 39 is fixed in through hole 416 at 41 restriction of gripping member body.
In some embodiments of the utility model, it is equipped with the position of the close installation gap 4131 of clamping piece body 41
Installation groove 417, the end of compact heap 42 is located in installation groove 417, and compact heap 42 passes through fastener and clamping piece body
41 connections.As shown in figure 14, it is recessed to be provided with installation for the left and right ends (left and right ends as shown in Figure 14) of installation gap 4131
Groove 417, correspondingly, as shown in Figure 15-Figure 17, the left and right ends of compact heap 42 (such as the left and right directions as shown in Figure 15-Figure 17)
It is provided with connecting pin 422.With reference to shown in Figure 13-Figure 17, when compact heap 42 and clamping piece body 41 are assembled, compact heap 42
Connecting pin 422 is stretched into installation groove 417, and connecting hole is both provided with installation groove 417 and connecting pin 422, thus, it is possible to logical
Cross fastener and securely fix compact heap 42 with clamping piece body 41 and be connected.
Some embodiments according to the present utility model, in installation gap 4131, the close installation of clamping piece body 41 lacks
Surface at mouth 4131 is transition face 4132, and transition face 4132 is plane.By setting transition face 4132, set is equipped with installation
When the horn 2 and compact heap 42 of ring 39, transition face 4132 has the function that to be oriented to guiding, easy to compact heap 42 and clamping piece body
Assembling between 41.As shown in Figure 13 and Figure 14, transition face 4132 can be located at the internal perisporium of installation gap 4131, transition face 4132
Plane is arranged to, easy to the processing and manufacturing of transition face 4132, so as to reduce production cost.
Further, the internal perisporium of through hole 416 has inner plane section 4162, has the lateral surface 430 of installation gap 4131
Angle between inner plane section 4162 is 90 ° -95 °.As shown in figure 13, the internal perisporium of through hole 416 have inner circle segmental arc 4161,
Two inner plane sections 4162 and interior changeover portion 4163.Installation gap 4131 can be arranged at the top surface of clamping piece body 41, clamping
Angle between the top surface and inner plane section 4162 of part body 41 is α, is met：90°≤α≤95°.It is understood that in two
Planar section 4162 can be parallel to each other and is vertically arranged with the top surface of clamping piece body 41；Two inner plane sections 4162 can also be with folder
The top surface inclination of gripping member body 41 is set.Thus, when horn 2 and clamping piece body 41 assemble, inclined inner plane section 4162
Have the function that it is spacing, meanwhile, inclined inner plane section 4162 can with the position of adjustment collar 39 and clamping piece body 41, and then
The angular relationship for being installed on miscellaneous part and 41 top surface of clamping piece body on horn 2 is adjusted, easy to horn 2 from installation gap
4131 are assembled in through hole 416.In some embodiments of the utility model, have installation gap 4131 lateral surface 430 with
Angle α between inner plane section 4162 is 92 °.
In some examples of the utility model, as shown in fig. 7, lug boss 3921 can in a ring, annular lug boss
3921 are looped around on the periphery wall of the lantern ring 39.Further, lug boss 3921 can be formed as oval, as shown in Figure 7, convex
The shape for forming closing can be connected by arc-shaped edges with straight flange by playing the cross section contour in portion 3921.Thus, it is possible to prevent that horn 2 is solid
After fixed, relatively rotate between the lantern ring 39 and clamping piece body 41 and compact heap 42, and then improve the steady of the fixation of horn 2
Gu reliability.
In some embodiments of the utility model, lug boss 3921 can be to be spaced apart multiple, and holding tank 420 can be with
It is multiple for what is be spaced apart.Thus, the backstop by multiple lug bosses 3921 and 420 internal perisporium of holding tank is spacing, can be further
Strengthen fastness fixed between the lantern ring 39 and clamping piece body 41 and compact heap 42, prevent the lantern ring 39 from play occurs.For example, can be with
Two lug bosses 3921 are arranged at intervals in the rear ends of the lantern ring 39, correspondingly, as shown in figure 15, along front and rear in compact heap 42
Direction (anteroposterior direction as shown in Figure 15) is arranged at intervals two holding tanks 420, so as to which lug boss 3921 is embedded
In holding tank 420, prevent from relatively moving between the lantern ring 39 and compact heap 42 and clamping piece body 41.
In other embodiments of the utility model, lug boss 3921 can also be three or more being spaced apart,
Holding tank 420 can be three or more.Some embodiments according to the present utility model, multiple lug bosses 3921 and multiple appearances
Groove 420 of receiving corresponds.Thus, when assembling clamping device 4, lug boss 3921 can be embedded in correspondingly holding tank 420
It is interior, to further enhance the fixed stably solidity of clamping device 4.
Some embodiments according to the present utility model, the first surface 411 or second surface 412 of clamping piece body 41 are neighbouring
Lug boss 3921 is abutted at through hole 416.Thus, it is possible to by the first surface 411 or second surface 412 of clamping piece body 41 with
Lug boss 3921 only support it is spacing, prevent the lantern ring 39 to be moved, so improve horn 2 fixation fastness.It is appreciated that
It is that the lantern ring 39 can be clamped between clamping piece body 41 and compact heap 42, the end face of 3921 side of lug boss of the lantern ring 39 can
Spacing only to be supported with the internal perisporium of holding tank 420, the end face of 3921 opposite side of lug boss can be with 411 or second table of first surface
Face 412 only support it is spacing, so as to improve the fastness assembled between the lantern ring 39 and clamping piece 40, and then enhance horn 2 and fix
Fastness.
According to the aircraft 100 of the utility model embodiment, as shown in Figure 1-Figure 3, aircraft 100 includes：Fuselage 1 and upper
The clamping device 4 is stated, at least one horn 2 is provided with fuselage 1, as shown in figure 3, four horns 2 are provided with fuselage 1,
Six or eight horns 2 etc. can also be set on fuselage 1.The clamping piece body 41 of clamping device 4 is connected with fuselage 1, clamping machine
The lantern ring 39 of structure 4 is set on horn 2.
According to the aircraft 100 of the utility model embodiment, by being connected compact heap 42 with clamping piece body 41 to seal
Installation gap 4131 is closed, and lug boss 3921 is accommodated to holding tank 420, the horn 2 for being equipped with the lantern ring 39 can be made firm
It is fixed between clamping piece body 41 and compact heap 42, and lug boss 3921 and the internal perisporium backstop of holding tank 420 are spacing, prevent
Stop and having been relatively moved between the lantern ring 39 and clamping piece body 41 and compact heap 42, so that 2 fixed stably solidity of horn is enhanced,
And then improve the structural stability of aircraft 100.
Flight referring to Fig. 1-Figure 17 with a specific embodiment detailed description according to the utility model embodiment
Device 100.It is worth understanding, it is described below to be merely illustrative, rather than the concrete restriction to the utility model.
As depicted in figs. 1 and 2, aircraft 100 include fuselage 1, horn 2, clamping device 4, power set 5, undercarriage 6,
Battery 7, Article holding box 8 and fixing device 9 etc., wherein, it is suitable for containing article to be sprayed or to be transported in Article holding box 8.
As shown in Figure 1, fuselage 1 includes the bottom plate 11 and top plate 12 being oppositely arranged along the vertical direction.Aircraft 100 is four rotations
The quantity of rotor aircraft 100, horn 2 and power set 5 is four.As shown in Fig. 2, horn 2 has the body of rod in cylinder
21, one end of the body of rod 21 is fixed between top plate 12 and bottom plate 11 by clamping device 4, and the free end of the body of rod 21 is provided with correspondence
Power set 5, power set 5 can be aircraft 100 provide power.
As shown in Fig. 2, fixing device 9 limits installation space 900, the interval of installation space 900 is divided into the first installation space
901 and second installation space 902.With reference to shown in Fig. 1 and Fig. 2, battery 7 can be installed on the first installation space 901, Article holding box 8
The second installation space 902 can be installed on.
As shown in Fig. 2, multiple clamping piece bodies 41, end clamping members 31 and fixing piece are arranged at intervals with bottom plate 11
33, with reference to shown in Fig. 2, Fig. 3 and Fig. 8-Figure 17, horn 2 can by clamping piece body 41, compact heap 42, end clamping members 31,
End compact heap 32, fixing piece 33, counterpart 34 and the lantern ring 39 are fixedly connected between top plate 12 and bottom plate 11.
As shown in Figure 13 and Figure 14, clamping piece body 41 has opposite first surface 411 and second surface 412, clamping
Part body 41 also has the lateral surface 430 being connected between first surface 411 and second surface 412.Set on clamping piece body 41
There are through hole 416 and installation gap 4131, through hole 416 is penetrated through to second surface 412, the inner peripheral surface of through hole 416 from first surface 411
Including inner circle segmental arc 4161, it is connected to the two of 4161 both ends of arc section and is parallel to each other inner plane section 4162, and positioned at Inner arc
Section 4162 and two between inner plane section 4162 and be oppositely arranged two in changeover portion 4163, between two inner plane sections 4162 and top surface
Angle α can be 90 ° -95 °.The top surface of clamping piece body 41 is provided with the installation gap 4131 of connection through hole 416, and installation lacks
Mouth 4131 separates lateral surfaces 430, and the internal face of 4131 upper end of installation gap is outward-dipping to top surface along two planar sections, 4162 end
Transition face 4132 is formed, installation groove 417 is equipped with the position of the close installation gap 4131 of clamping piece body 41.
Compact heap 42 can be installed in installation gap 4131 and is connected with clamping piece body 41 to close through hole 416.Such as
Shown in Figure 15-Figure 17, compact heap 42 has body 421, in the left and right ends of body 421 (such as the left and right as shown in Figure 15-Figure 17
Direction) it is provided with connecting pin 422.The lower end (such as left and right directions as shown in Figure 15-Figure 17) of body 421 has arc supporting surface
423, in the front and rear sides of supporting surface 423, (anteroposterior direction as shown in Figure 15) is arranged at intervals with two holding tanks 420.
It is understood that the horn 2 after the assembling lantern ring 39 can be assembled in through hole 416 by installation gap 4131,
Also it can penetrate in through hole 416 along the axial direction of through hole 416, then be connected compact heap 42 with clamping piece body 41, thus, pressure
Tight block 42 coordinates with clamping piece body 41 and the lantern ring 39 tightly can be clamped in through hole 416, and lug boss 3921 is housed in appearance
Receive in groove 420.Thus, the internal perisporium of lug boss 3921 and holding tank 420 only supports spacing, limits the movement of the lantern ring 39, and then
Improve the fixed stably solidity of horn 2.
As shown in Figure 8 and Figure 9, end clamping members 31 have the 3rd opposite surface 311 and the 4th surface 312, are connected to
Top surface 314 between the top on the top on the 3rd surface 311 and the 4th surface 312, the bottom and for being connected to the 3rd surface 311
Bottom surface 315 between the bottom on four surfaces 312, and be connected to the 3rd surface 311 both ends and the 4th surface 312 both ends it
Between and be connected to the two sides 313 of top surface 314 and bottom surface 315.End clamping members 31, which are equipped with, runs through the 3rd surface 311 and the 4th
The mounting hole 316 on surface 312.With reference to shown in Fig. 2, the end clamping members 31 of fixed same horn 2 are parallel with clamping piece body 41
Set, also, mounting hole 316 is coaxially disposed with through hole 416.3rd surface 311 and the 4th surface 312 are in the four of mounting hole 316
Week is equipped with some grooves, to mitigate 31 mass of end clamping members.
It is two arc sections 301 that the inner peripheral surface of mounting hole 316 includes being oppositely arranged, between two arc sections 301 and opposite
And two planar sections 302 being arranged in parallel, and between two arc sections 301 and two planar sections 302 and two mistakes that are oppositely arranged
Section 303 is crossed, wherein, the angle between two flat planar sections 302 and top surface can be 90 ° -95 °.Each changeover portion 303 can be more
A facet composition, changeover portion 303 can also be made of cambered surface.It is additionally provided with end clamping members 31 through top surface 314 and neighbour
The assembling groove 317 of the arc section 301 of nearly top surface 314, assembling groove 317 connect mounting hole 316.The interior table of end clamping members 31
Face is extended with two boss 319 in the center of neighbouring fitting groove 317 and junction towards the mounting hole 316 of mounting hole 316, each convex
Platform 319 is equipped with mounting hole.Bottom surface 315 is equipped with two positioning convex columns 318 and two mounting holes away from top surface 314.Such as Figure 10
Shown, each compact heap 32 includes locking portion 321 and two connecting portions 322 positioned at 321 both sides of locking portion, in locking portion 321
Between depression form locking face 323.
As shown in figure 11, fixing piece 33 includes base portion 331 and the holding section 332 extended from the side of base portion 331.Clamping
The side of the remote base portion 331 in portion 332 is recessed inwardly to form the first catch surface 333.As shown in figure 12, the one of counterpart 34 is lateral
Sunken inside forms the second catch surface 341., can after fixing piece 33 and 34 assembly connection of counterpart with reference to shown in Fig. 2, Figure 11 and Figure 12
Horn 2 is fixed on fuselage 1.
As Figure 4-Figure 7, the lantern ring 39 includes first lantern ring 391 and second lantern ring 392.Wherein, as shown in figure 5, first
It is two arc sections 3901 that the outer surface of the lantern ring 391 includes being oppositely arranged, between two arc sections 3901 and opposite and parallel set
Two planar sections 3902 put, and between two arc sections 3901 and two planar sections 3902 and two changeover portions that are oppositely arranged
3903, the inner surface of first lantern ring 391 is equipped with glue groove 3904.
As shown in fig. 7, the front end (anteroposterior direction as shown in Figure 7) of second lantern ring 392 extends outward lug boss
3921.It is two arc sections 3901 that the outer surface of second lantern ring 392 includes being oppositely arranged, between two arc sections 3901 and opposite
And two planar sections 3902 being arranged in parallel, and between two arc sections 3901 and two planar sections 3902 and be oppositely arranged two
Changeover portion 3903, the inner surface of second lantern ring 392 are equipped with glue groove 3904.
It should be noted that during assembling horn 2, with reference to shown in Fig. 2-Fig. 4, the lantern ring 39 is sheathed on horn 2 first.Specifically
Ground, horn 2 is sheathed on by first lantern ring 391 and second lantern ring 392 respectively.Pass through 3904 He of glue groove in first lantern ring 391
Second lantern ring, 392 glue groove, 3904 dispensing, strengthens the bonding strength of first lantern ring 391 and second lantern ring 392 and horn 2.
Then, by horn 2 be fixed between end clamping members 31 and end compact heap 32 and clamping piece body 41 and pressure
Between tight block 42.Specifically, first lantern ring 391 of the horn 2 assembled is passed through into end clamping members 31 until first lantern ring 391
The internal perisporium of periphery wall and end mounting hole 316 fit, end compact heap 32 is coordinated in corresponding end clamping members 31
Mounting groove 317 in.And second lantern ring 392 until the periphery wall of second lantern ring 392 and is led to through clamping piece body 41 at the same time
The internal perisporium fitting in hole 416, compact heap 42 is assembled in installation gap 4131, solid by connecting pin 422 and installation groove 417
Fixed connection, and the lug boss 3921 on the lantern ring 39 is limited in the holding tank 420 of compact heap 42, and horn 2 and fixing piece
33 and 34 fixing assembling of counterpart.Finally, fixing assembling top plate 12 and bottom plate 11, by horn 2 be held fixedly top plate 12 with
Between bottom plate 11.
Thus, clamping piece body 41 and compact heap 42, end clamping members 31 and end compact heap 32 and fixing piece are passed through
33 and counterpart 34 horn 2 is firmly secured on fuselage 1, and the lug boss 3921 on the lantern ring 39 can be contained in compact heap
In 42 holding tank, lug boss 3921 and the internal perisporium backstop of holding tank 420 are spacing, it is therefore prevented that the lantern ring 39 and clamping piece body 41
Relatively moved between compact heap 42, so as to enhance 2 fixed stably solidity of horn, and then improve the knot of aircraft 100
Structure stability.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means to combine specific features, the knot that the embodiment or example describe
Structure, material or feature are contained at least one embodiment or example of the utility model.In the present specification, to above-mentioned art
The schematic representation of language may not refer to the same embodiment or example.Moreover, description specific features, structure, material or
Person's feature can combine in an appropriate manner in any one or more embodiments or example.
While there has been shown and described that the embodiment of the utility model, it will be understood by those skilled in the art that：
These embodiments can be carried out with a variety of changes, modification in the case where not departing from the principle and objective of the utility model, replaced
And modification, the scope of the utility model are limited by claim and its equivalent.
Claims (10)
- A kind of 1. horn clamping device for aircraft, it is characterised in that including：The lantern ring, the lantern ring have mounting hole, and the mounting hole is used to install horn, and the outer peripheral wall of the collar is equipped with protrusion Portion, the lug boss extend along the circumferential direction of the lantern ring；WithClamping piece, the clamping piece have opposite first surface and second surface, and the clamping piece is equipped with through hole, described logical Hole penetrates through to the second surface, the lantern ring from the first surface and is contained in the through hole, and the inner wall of the through hole is set It is useful for housing the holding tank of the lug boss.
- 2. the horn clamping device according to claim 1 for aircraft, it is characterised in that the clamping piece includes： Clamping piece body, the clamping piece body have the first surface, a second surface, and the connection first surface and The lateral surface of the second surface, the lateral surface are equipped with installation gap；WithCompact heap, the compact heap are equipped with the holding tank adjacent to the installation gap, the compact heap.
- 3. the horn clamping device according to claim 2 for aircraft, it is characterised in that the compact heap stretches into Include supporting surface to the surface in the through hole, the inner peripheral surface of the supporting surface and the through hole limits the through hole, described Supporting surface is equipped with the holding tank.
- 4. the horn clamping device according to claim 2 for aircraft, it is characterised in that the clamping piece body Be equipped with installation groove at the position of the installation gap, the end of the compact heap be detachably secured to it is described install it is recessed In groove.
- 5. the horn clamping device according to claim 2 for aircraft, it is characterised in that in the installation gap Interior, the surface at the close installation gap of the clamping piece body is transition face, and the transition face is plane.
- 6. the horn clamping device according to claim 5 for aircraft, it is characterised in that the through hole internal perisporium tool There is inner plane section, it is 90 ° -95 ° to have the angle between the lateral surface of the installation gap and the inner plane section.
- 7. it is used for the horn clamping device of aircraft according to claim 1-6 any one of them, it is characterised in that the protrusion Portion is in a ring.
- 8. it is used for the horn clamping device of aircraft according to claim 1-6 any one of them, it is characterised in that the protrusion Portion is multiple for what is be spaced apart, and it is multiple for what is be spaced apart that the holding tank corresponds to the lug boss.
- 9. it is used for the horn clamping device of aircraft according to claim 2-6 any one of them, it is characterised in that the clamping The first surface or second surface of part body abut the lug boss adjacent to the through hole.
- A kind of 10. aircraft, it is characterised in that including：Fuselage；At least one horn；WithClamping device, the clamping device are the horn clamping machine according to any one of claim 1-9 for aircraft Structure, the clamping piece body of the clamping device are connected with the fuselage, and the lantern ring of the clamping device is set in institute State on horn.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720701869.8U CN207292364U (en) | 2017-06-15 | 2017-06-15 | Horn clamping device and aircraft for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720701869.8U CN207292364U (en) | 2017-06-15 | 2017-06-15 | Horn clamping device and aircraft for aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN207292364U true CN207292364U (en) | 2018-05-01 |
Family
ID=62450070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720701869.8U Active CN207292364U (en) | 2017-06-15 | 2017-06-15 | Horn clamping device and aircraft for aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN207292364U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436289A (en) * | 2018-12-13 | 2019-03-08 | 广州极飞科技有限公司 | Horn clamping device and aircraft for aircraft |
| EP3895982A4 (en) * | 2018-12-13 | 2022-01-26 | Guangzhou Xaircraft Technology Co., Ltd. | Frame for aircraft and aircraft |
-
2017
- 2017-06-15 CN CN201720701869.8U patent/CN207292364U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436289A (en) * | 2018-12-13 | 2019-03-08 | 广州极飞科技有限公司 | Horn clamping device and aircraft for aircraft |
| EP3895982A4 (en) * | 2018-12-13 | 2022-01-26 | Guangzhou Xaircraft Technology Co., Ltd. | Frame for aircraft and aircraft |
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Address after: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee after: Guangzhou Jifei Technology Co.,Ltd. Address before: 510000, Guangdong, Guangzhou, Gaotang Tianhe District Software Park Road, No. 1, 3A01 Patentee before: Guangzhou Xaircraft Technology Co.,Ltd. |