CN205998165U - A kind of fuselage floor load charger - Google Patents
A kind of fuselage floor load charger Download PDFInfo
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- CN205998165U CN205998165U CN201620978263.4U CN201620978263U CN205998165U CN 205998165 U CN205998165 U CN 205998165U CN 201620978263 U CN201620978263 U CN 201620978263U CN 205998165 U CN205998165 U CN 205998165U
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Abstract
The utility model discloses a kind of fuselage floor load charger, belong to aeronautic structure experimental technique field.Described device acts on fuselage floor through fuselage skin, main inclusion monaural joint (4), ears joint (7) and rubber corrugated Taper Pipe (5), described monaural joint (4) connects floor and loads lever (1), ears joint (7) connects the load applying mechanism of engine body exterior through after the perforate of fuselage skin, monaural joint is connected with ears joint screw thread, rubber corrugated Taper Pipe (5) has expansion performance, and be socketed on ears joint, rubber corrugated Taper Pipe is being provided with annular groove with fuselage skin junction, adaptation installs the ring side at fuselage skin opening.Thus ensure that charger passes through fuselage skin not destroy fuselage air-tightness, solve the airtight problem that traditional load mode causes.
Description
Technical field
This utility model belongs to aeronautic structure experimental technique field and in particular to a kind of fuselage floor load charger.
Background technology
Aircraft cargo bay floor is often positioned in fuselage air-tight section, and simultaneously in order to meet the requirement of its transportation function, floor makes
With during to bear larger inertial load.In full machine slow test, the stand under load on floor in using for true simulated aircraft
State, needs to apply the external applied load of larger magnitude on floor, simultaneously because the requirement of punching press operating mode can not destroy airframe structure
Air-tightness.The design of the applying mode of floor load and charger becomes an importance for EXPERIMENTAL DESIGN.
The applying of full machine slow test heavy type external applied load is all loaded by ground pressurized strut at present, and ground pressurized strut will be made to make
For the floor of fuselage interior, need in fuselage wallboard perforate so that charger pass through fuselage wallboard.But eyelid covering perforate
The air-tightness of airframe structure, the enforcement of impact pressurising operating condition of test can be destroyed.
Utility model content
In order to solve the above problems, this utility model middle fuselage floor load charger passes through using a rubber corrugated
Taper Pipe, its upper surface and charger are tightly connected, and lower end is fitted tightly with fuselage skin tapping, simultaneously can with through it
Internal loading joint is servo-actuated, thus compensate for that airframe structure that floor load leads to eyelid covering perforate is airtight to ask due to applying
Topic.
This utility model fuselage floor load charger, acts on fuselage floor through fuselage skin, main inclusion
Monaural joint, ears joint and rubber corrugated Taper Pipe, one end of described monaural joint is provided with pin-and-hole, adds for connecting floor
Carry lever, the other end is provided with tapped cylindrical recesses, and described ears joint includes first paragraph, the setting being provided with pin-and-hole
There are externally threaded second segment and the 3rd section that is arranged between first paragraph and second segment, described 3rd section sets and second segment between
It is equipped with cylinder boss, described second segment is cylinder shaft body, adaptation is arranged in described cylindrical recesses, described rubber corrugated Taper Pipe is set
Barrel structure, it includes be arranged on two ends the 4th section and the 5th section, and is arranged between described 4th section and described 5th section
The be made up of the ripple struction that can stretch the 6th section, described 4th section socket described ears joint cylinder boss, described
5th section of be used for being socketed described ears joint with described 6th section the 3rd section, described 5th section is being deviated from described ears joint
Annular recess is provided with outer ring surface, for accommodating the ring side at described fuselage skin opening.
Preferably, scribble fluid sealant at the annular recess of described rubber corrugated Taper Pipe and fuselage skin contact surface, thus
Ensure that Taper Pipe is sealed with fuselage skin junction.Ground pressurized strut can be connected with loading lever thus by this device, will
The load of ground pressurized strut puts on floor, and does not produce airtight problem after guarantee connection.
In such scheme preferably, the 6th section of described rubber corrugated Taper Pipe is connected and composed by multiple frustum collars, cone
One end with less internal diameter of the platform collar connects one end with larger interior diameter of another frustum collar, described rubber corrugated cone
Minimum with the maximum inner diameter of the described 4th section of frustum collar being connected in multiple frustum collars of the 6th section of pipe, with the 6th section of company
The maximum inner diameter of the frustum collar connecing is maximum, and described maximum inner diameter refers to the internal diameter at the bottom surface of the described frustum collar.
In such scheme preferably, 3 10 frustum collars of the 6th section of inclusion of described rubber corrugated Taper Pipe.
The beneficial effects of the utility model are：Using this charger it is ensured that fuselage air-tight cabin is not during slow test
Airtight sex chromosome mosaicism is caused due to the applying of floor load, and this device is simple, general.
Brief description
Fig. 1 is the structural representation of a preferred embodiment of this utility model fuselage floor load charger.
Fig. 2 is the front view of this utility model embodiment illustrated in fig. 1.
Fig. 3 is the ears joint design schematic diagram of this utility model embodiment illustrated in fig. 1.
Fig. 4 is the rubber corrugated conical tube structure schematic diagram of this utility model embodiment illustrated in fig. 1.
Wherein, 1 load lever for floor, 2 is nut, 3 is bolt, 4 is monaural joint, and 5 is rubber corrugated Taper Pipe, and 6 are
Fuselage skin, 7 is ears joint, and 8 is bolt, and 9 is nut, and 10 is cylinder shaft body, and 11 is cylinder boss upper surface, and 12 is that cylinder is convex
Platform, 13 is earhole, and 14 is rubber corrugated Taper Pipe upper end flange, and 15 is rubber corrugated Taper Pipe upper end cylindrical tube, and 16 is annular recess.
Specific embodiment
For making purpose, technical scheme and advantage that this utility model is implemented clearer, below in conjunction with this utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in this utility model embodiment.In the accompanying drawings, ad initio
To the element that same or similar label represents same or similar element or has same or like function eventually.Described reality
Applying example is a part of embodiment of this utility model, rather than whole embodiments.Embodiment below with reference to Description of Drawings
It is exemplary it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.New based on this practicality
Embodiment in type, the every other enforcement that those of ordinary skill in the art are obtained under the premise of not making creative work
Example, broadly falls into the scope of this utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is described in detail.
In description of the present utility model it is to be understood that term " " center ", " longitudinal ", " horizontal ", "front", "rear",
The orientation of instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " or position relationship are based on accompanying drawing institute
The orientation showing or position relationship, are for only for ease of description this utility model and simplify description, rather than instruction or hint indication
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The restriction of novel protected scope.
This utility model gives a kind of fuselage floor load charger, acts on fuselage floor through fuselage skin
On, by using a rubber corrugated Taper Pipe, its upper surface and charger are tightly connected, lower end is tight with fuselage skin tapping
Closely connected conjunction, simultaneously can be servo-actuated with through its internal loading joint, thus compensate for due to applying floor load, eyelid covering being opened
The airtight problem of airframe structure that hole leads to.
As shown in figure 1, this utility model fuselage floor load charger mainly include monaural joint 4, ears joint 7 with
And rubber corrugated Taper Pipe 5, one end connection floor of monaural joint 4 loads lever 1, other end connection rubber corrugated Taper Pipe 5, ears
One end of joint 7 connects the load load maintainer outside airframe, and the other end is connected to monaural through rubber corrugated Taper Pipe 5 and connects
On 4.
Specifically, as shown in Fig. 2 one end of described monaural joint 4 is provided with pin-and-hole, after bolt 3 passes through this pin-and-hole, it is used for
Monaural joint and floor are loaded lever 1 be connected with each other, and be fixed by nut 2, the other end of monaural joint 4 is provided with
Tapped cylindrical recesses, for being connected with ears joint screw thread, adaptation, it is externally threaded that described ears joint 7 has band
End, specifically, described ears joint 7 includes being provided with the first paragraph of pin-and-hole, is provided with externally threaded second segment and setting
Between first paragraph and second segment the 3rd section, as shown in figure 3, giving the schematic diagram of ears joint 7, in this schematic diagram, double
Terminal lug 7 upper end includes three cylinders, and lower end is the auricle of ears, and specifically, the auricle of ears is first paragraph, and two oval
Post is respectively second segment and the 3rd section, and described second segment is cylinder shaft body 10, is that band is externally threaded, it can be threaded connection
Mode is adapted in the cylindrical recesses being arranged on described monaural joint 4, and described 3rd section is provided with cylinder boss and second segment between
12, the diameter with diameter greater than cylinder shaft body 10 of cylinder boss 12, thus formed between cylinder boss 12 and cylinder shaft body 10 crimp
Surface, i.e. cylinder boss upper surface 11, when the second segment cylinder shaft body 10 by ears joint 7 is screwed into the cylindrical recesses of monaural joint 4
When interior, rubber corrugated Taper Pipe upper end flange 14 can be compressed it is ensured that the sealing of the two junction by cylinder boss upper surface 11, such as schemes
Shown in 2, thick lines represent rubber corrugated Taper Pipe 5, and the flange of its upper end is pressed in cylinder boss upper surface 11 and monaural joint 4
Lower surface between.
The first paragraph of ears joint 7 is ears piece, and including two relative earholes 13, bolt 8 passes through this earhole 13 and leads to
Cross nut 9 fixing, ground pressurized strut can be connected with loading lever thus by this device, the load of ground pressurized strut is applied
It is added on floor.
Structure for rubber corrugated Taper Pipe 5 refer to Fig. 4, and described rubber corrugated Taper Pipe 5 is tube-in-tube structure, and it is used for covering
Connect a part for ears joint, as shown in Fig. 2 the 3rd section of this partly concrete cylinder boss 12 and cylinder boss 12 lower end.Again
Secondary with reference to Fig. 4, rubber corrugated Taper Pipe 5 include being arranged on the 4th section of two ends with the 5th section, and be arranged on described 4th section with
Between described 5th section the be made up of the ripple struction that can stretch the 6th section, as it was previously stated, described 4th section of inclusion rubber
Ripple Taper Pipe upper end cylindrical tube 15, its internal diameter is identical with the external diameter of cylinder boss 12, for being socketed the cylinder of described ears joint 7
Boss 12, described 5th section be used for being socketed described ears joint 7 with described 6th section the 3rd section, described 5th section deviating from
Annular recess 16 is provided with the outer ring surface stating ears joint 7, for accommodating the ring side at described fuselage skin 6 opening.Permissible
It is understood by, annular recess 16 external diameter is identical with eyelid covering perforate bore, due to the elasticity of elastomeric material, achievable groove and eyelid covering
Perforate coordinates.
In an alternate embodiment, apply fluid sealant at annular recess 16 with eyelid covering opening contacts further it is ensured that
Taper Pipe is sealed with fuselage skin junction.
With reference to Fig. 4, the 6th section of described rubber corrugated Taper Pipe 5 is connected and composed by multiple frustum collars, the tool of the frustum collar
Have less internal diameter one end connect another frustum collar the one end with larger interior diameter, the 6th of described rubber corrugated Taper Pipe 5 the
Minimum with the maximum inner diameter of the described 4th section of frustum collar being connected in multiple frustum collars of section, with the 6th section of frustum being connected
The maximum inner diameter of the collar is maximum, and described maximum inner diameter refers to the internal diameter at the bottom surface of the described frustum collar.
In the present embodiment, 3 10 frustum collars of the 6th section of inclusion of described rubber corrugated Taper Pipe 5.
Using this charger it is ensured that during slow test fuselage air-tight cabin do not caused due to the applying of floor load
Airtight sex chromosome mosaicism, and this device is simple, general.
Last it is to be noted that：Above example is only in order to illustrating the technical solution of the utility model, rather than it is limited
System.Although being described in detail to this utility model with reference to the foregoing embodiments, those of ordinary skill in the art should manage
Solution：It still can be modified to the technical scheme described in foregoing embodiments, or wherein some technical characteristics are entered
Row equivalent；And these modifications or replacement, do not make the essence of appropriate technical solution depart from each embodiment of this utility model
The spirit and scope of technical scheme.
Claims (4)
1. a kind of fuselage floor load charger, act on fuselage floor through fuselage skin it is characterised in that：Including single
Terminal lug (4), ears joint (7) and rubber corrugated Taper Pipe (5), one end of described monaural joint (4) is provided with pin-and-hole, is used for
Connect floor and load lever (1), the other end is provided with tapped cylindrical recesses, described ears joint (7) includes being provided with
The first paragraph of pin-and-hole, it is provided with externally threaded second segment and the 3rd section that is arranged between first paragraph and second segment, described
Three sections are provided with cylinder boss (12) and second segment between, and described second segment is cylinder shaft body (10), and adaptation is arranged on described column
In groove, described rubber corrugated Taper Pipe (5) is tube-in-tube structure, and it includes be arranged on two ends the 4th section and the 5th section, Yi Jishe
Put the be made up of the 6th section between described 4th section and described 5th section, described 4th section of set the ripple struction that can stretch
Connect the cylinder boss (12) of described ears joint (7), described 5th section is used for being socketed described ears joint (7) with described 6th section
The 3rd section, described 5th section is provided with annular recess (16), for accommodating on the outer ring surface deviating from described ears joint (7)
Ring side at described fuselage skin (6) opening.
2. fuselage floor load charger as claimed in claim 1 it is characterised in that：Described rubber corrugated Taper Pipe (5)
Fluid sealant is scribbled at annular recess (16) and fuselage skin contact surface.
3. fuselage floor load charger as claimed in claim 1 it is characterised in that：Described rubber corrugated Taper Pipe (5)
6th section is connected and composed by multiple frustum collars, and one end with less internal diameter of the frustum collar connects the tool of another frustum collar
There is one end of larger interior diameter, be connected with described 4th section in the 6th section of multiple frustum collars of described rubber corrugated Taper Pipe (5)
The frustum collar maximum inner diameter minimum, the maximum inner diameter maximum of the frustum collar being connected with the 6th section, described maximum inner diameter is
Refer to the internal diameter at the bottom surface of the described frustum collar.
4. fuselage floor load charger as claimed in claim 3 it is characterised in that：Described rubber corrugated Taper Pipe (5)
3 10 frustum collars of 6th section of inclusion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620978263.4U CN205998165U (en) | 2016-08-29 | 2016-08-29 | A kind of fuselage floor load charger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620978263.4U CN205998165U (en) | 2016-08-29 | 2016-08-29 | A kind of fuselage floor load charger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205998165U true CN205998165U (en) | 2017-03-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620978263.4U Active CN205998165U (en) | 2016-08-29 | 2016-08-29 | A kind of fuselage floor load charger |
Country Status (1)
| Country | Link |
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| CN (1) | CN205998165U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146655A (en) * | 2017-12-13 | 2018-06-12 | 中国飞机强度研究所 | A kind of fuselage wallboard tests pin-lift arrangement |
| CN110375978A (en) * | 2019-08-23 | 2019-10-25 | 中国商用飞机有限责任公司 | bearing capacity test device |
| CN114441158A (en) * | 2022-01-29 | 2022-05-06 | 中国飞机强度研究所 | Loading structure for aircraft ground strength test |
-
2016
- 2016-08-29 CN CN201620978263.4U patent/CN205998165U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146655A (en) * | 2017-12-13 | 2018-06-12 | 中国飞机强度研究所 | A kind of fuselage wallboard tests pin-lift arrangement |
| CN110375978A (en) * | 2019-08-23 | 2019-10-25 | 中国商用飞机有限责任公司 | bearing capacity test device |
| CN110375978B (en) * | 2019-08-23 | 2021-07-27 | 中国商用飞机有限责任公司 | Bearing capacity test device |
| CN114441158A (en) * | 2022-01-29 | 2022-05-06 | 中国飞机强度研究所 | Loading structure for aircraft ground strength test |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |