CN204776049U - Aircraft sensor safety cover fixing device - Google Patents
Aircraft sensor safety cover fixing device Download PDFInfo
- Publication number
- CN204776049U CN204776049U CN201520430487.7U CN201520430487U CN204776049U CN 204776049 U CN204776049 U CN 204776049U CN 201520430487 U CN201520430487 U CN 201520430487U CN 204776049 U CN204776049 U CN 204776049U
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- protective case
- aircraft
- bolt
- safety cover
- earless
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Abstract
The utility model provides an aircraft sensor safety cover fixing device, relates to aircraft structural design technical field for when the aircraft is parked stationary sensor safety cover (1), install in the ring channel at purpose -built bolt (2) polished rod middle part circlip (3), and the oval head does not have ear sealed layer board self -locking nut (6) and purpose -built bolt (2) interference fit to be fixed sensor safety cover (1) in sensor safety cover (1) the fixed orifices on fuselage covering (4) and reinforcing plate (5) integrated configuration. The utility model provides an aircraft sensor safety cover fixing device simple structure, the damage of having avoided a lot of dismouting to cause fuselage covering (5), dismouting sensor safety cover (1) need not the operation tool, has improved work efficiency.
Description
Technical field
The utility model relates to technical field of aircraft structure design, in particular to a kind of aircraft sensors protective case anchor fitting.
Background technology
Many military aircrafts are all when ground is parked, and are directly connected with bolt by the sensor protective covers such as metal incidence vane protective case, sideslip sensor protective case with fuselage skin, prevent that sensor is touched makes its sensitivity decrease.When flying; removal sensor protective case, directly connects the mounting hole of protective case on fuselage skin with countersunk-heat bolt, can cause damage like this because bolt being dismounted for multiple times unloads screw thread to fuselage skin; and need operation tool during protective case dismounting, such being dismounted for multiple times inefficiency.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, provide a kind of simple and reasonable, avoid being dismounted for multiple times sensor protective cover on fuselage skin and fuselage skin caused to the aircraft sensors protective case anchor fitting of damage.
The purpose of this utility model is achieved through the following technical solutions: a kind of aircraft sensors protective case anchor fitting, fixation of sensor protective case when parking for aircraft, comprise bolt of rear end plate, bolt of rear end plate is special bolt, also comprise circlip, brace panel, oval head earless sealing supporting plate self-lock nut, wherein, the screw portion of special bolt is polished rod near nut length-specific, circular groove is provided with in the middle part of polished rod, polished rod lower end is thread rod, oval head earless sealing supporting plate self-lock nut is installed in the sensor protective cover fixed orifice on fuselage skin and brace panel, circlip is installed in the circular groove in the middle part of special bolt polished rod, oval head earless sealing supporting plate self-lock nut and special screw rod interference fit fixation of sensor protective case.
Preferably, on special bolt, the length of thread rod is identical with the degree of depth that described oval head earless seals supporting plate self-lock nut band internal threaded regions, and the wall panel thickness of the distance in the middle part of polished rod between circular groove with nut and the cover body of sensor protective cover is identical for such scheme.
In above-mentioned either a program preferably, fuselage skin and brace panel paste merga pass rivet and are fixedly connected with.
The beneficial effect of aircraft sensors protective case anchor fitting provided by the utility model is; structure is simple; at the sensor protective cover fixed orifice of fuselage skin and brace panel, oval head earless is installed and seals supporting plate self-lock nut; and coordinate fixation of sensor protective case with special bolt; only special bolt need be taken off from oval head earless sealing supporting plate self-lock nut during removal sensor protective case; avoid and the damage that fuselage skin directly contacts and being dismounted for multiple times causes fuselage skin; disassembling sensor protective case, without the need to operation tool, improves work efficiency.
Accompanying drawing explanation
Fig. 1 is the structure installment schematic diagram of the preferred embodiment according to aircraft sensors protective case anchor fitting of the present utility model;
Fig. 2 is the cross-sectional view embodiment illustrated in fig. 1 according to aircraft sensors protective case anchor fitting of the present utility model;
Fig. 3 is the structural representation of the special bolt embodiment illustrated in fig. 1 according to aircraft sensors protective case anchor fitting of the present utility model;
Fig. 4 is the structural representation of the circlip embodiment illustrated in fig. 1 according to aircraft sensors protective case anchor fitting of the present utility model.
Reference numeral:
1-sensor protective cover, 2-special bolt, 3-circlip, 4-fuselage skin, 5-brace panel, 6-oval head earless sealing supporting plate self-lock nut.
Detailed description of the invention
In order to understand the aircraft sensors protective case anchor fitting according to the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to aircraft sensors protective case anchor fitting of the present utility model.
As Figure 1-4, the aircraft sensors protective case anchor fitting that the utility model provides, fixation of sensor protective case when parking for aircraft, comprise bolt of rear end plate, bolt of rear end plate is special bolt 2, also comprise circlip 3, brace panel 5, oval head earless sealing supporting plate self-lock nut 6, wherein, the screw portion of special bolt 2 is polished rod near nut length-specific, circular groove is provided with in the middle part of polished rod, polished rod lower end is thread rod, oval head earless sealing supporting plate self-lock nut 6 is installed on fuselage skin 4 with in sensor protective cover 1 fixed orifice on brace panel 5, circlip 3 is installed in the circular groove in the middle part of special bolt 2 polished rod, oval head earless sealing supporting plate self-lock nut 6 and special screw rod 2 interference fit fixation of sensor protective case 1.On special bolt 2, the length of thread rod is identical with the degree of depth that described oval head earless seals the band internal threaded regions of supporting plate self-lock nut 6, and the wall panel thickness of the cover body of the distance in the middle part of polished rod between circular groove with nut and sensor protective cover 1 is identical.Fuselage skin 4 and brace panel 5 paste merga pass rivet and are fixedly connected with.Special bolt 2, directly through sensor protective cover 1, blocks with circlip 3 in the circular groove of below and prevents from dropping, need special tool when circlip 3 is installed, and time hand twists bolt, circlip rotates thereupon
Military aircraft generally in ground parking time much larger than aloft flight time, it is when ground is parked, for this protrusion such as incidence vane and sideslip sensor fuselage skin 4 profile and the sensor class equipment high to sensitivity requirement, sensitivity decrease is made in order to prevent it touched, usually can do a protective cover to be arranged on fuselage skin 4 and to be protected, i.e. sensor protective cover 1, before each flight, sensor protective cover 1 can be disassembled, mounting hole installs a countersunk-heat bolt, therefore protective case needs being dismounted for multiple times, and being dismounted for multiple times not only consumes manpower, time, also certain damage is caused itself to fuselage skin 4.The aircraft sensors protective case anchor fitting that the utility model provides overcomes the defect to sensor protective cover dismounting in the middle of prior art.
In the concrete aircraft sensors protective case anchor fitting process using the utility model to provide; on fuselage skin 4 and brace panel 5, the fixed orifice of protective case installs oval head earless sealing supporting plate self-lock nut 6; no matter when aircraft flight or when ground is parked; oval head earless sealing supporting plate self-lock nut 6 is fixed on fuselage skin 4 and brace panel 5 always, and oval head earless sealing supporting plate self-lock nut 6 is equivalent on covering and brace panel, secure a protection lining.Aircraft, before flight, installs countersunk-heat bolt at connection location; When aircraft floor is parked, pull down bolt, the special screw 2 of sensor installation protective case 1; Special screw 2 (or bolt) is just kept apart with fuselage skin 4, brace panel 5 by such oval head earless sealing supporting plate self-lock nut 6; sensor protective cover 1 is when dismantling or install; oval head earless sealing supporting plate self-lock nut 6 just plays the effect of protection fuselage skin 4 and brace panel 5; after repeatedly using, oval head earless sealing supporting plate self-lock nut 6 damages, and changes.
Special bolt 2 is directly installed on the cover body wallboard of protective case 1, and the circular groove then on bolt 2 polished rod installs circlip 3, prevents special bolt 2 from coming off, and special bolt 2 is just fixed on protective case 1 always, and without the need to removing, convenient next time uses.Sensor protective cover 1 with special bolt is placed in oval head earless sealing supporting plate self-lock nut 6, tightens by hand special bolt 2 and fix by sensor protective cover 1; Special bolt 2 of directly back-outing during dismounting can reach the object of dismounting.
Special bolt 2 directly limits it and does cross motion through the oppose cover body wallboard of both sides of sensor protective cover 1 perpendicular to special bolt 2, with coordinating of circlip 3, sensor protective cover 1 is limited it along special bolt 2 longitudinal movement by special bolt 2.
Because sensor protective cover 1 only uses when aircraft floor is parked, itself and fuselage skin 4 are fixed with the assembly set of brace panel 5, and the effect of brace panel 6 is the intensity increasing fuselage skin 5, avoids fuselage skin 5 to damage.The aircraft sensors protective case anchor fitting preferred embodiment that the utility model provides only needs to bear sensor protective cover 1 own wt load; trip ring 4 uses thinner spring, like this when pressing spring compressor 2 and extracting spring compressor 2 without the need to using excessive strength.
The head of oval head earless sealing supporting plate self-lock nut 6 is oval head, during installation, need special tool at fuselage skin 4 nest oval with Huo in brace panel 5 unitized construction, oval head earless sealing supporting plate self-lock nut 6 need use special tool to install in fuselage skin 4 and brace panel 5 unitized construction lateral, oval head coordinates with oval nest, there is weakening region at oval head earless sealing supporting plate self-lock nut 6 endoporus place, utilizes weakening region bulge to be shaped and realizes the connection of itself and framing member; The afterbody of oval head earless sealing supporting plate self-lock nut 6 has negative thread, and negative thread has auto-lock function.
More than be described in detail in conjunction with aircraft sensors protective case anchor fitting specific embodiment of the present utility model; but be not to restriction of the present utility model; everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments; also it should be noted that, comprise the combination in any between each part mentioned above according to the category of aircraft sensors protective case anchor fitting technical scheme of the present utility model.
Claims (3)
1. an aircraft sensors protective case anchor fitting, fixation of sensor protective case (1) when parking for aircraft, comprise bolt of rear end plate, it is characterized in that: described bolt of rear end plate is special bolt (2), also comprise circlip (3), brace panel (5), oval head earless sealing supporting plate self-lock nut (6), wherein, the screw portion of special bolt (2) is polished rod near nut length-specific, circular groove is provided with in the middle part of polished rod, polished rod lower end is thread rod, oval head earless sealing supporting plate self-lock nut (6) is installed on fuselage skin (4) with in sensor protective cover (1) fixed orifice on brace panel (5), circlip (3) is installed in the circular groove in the middle part of special bolt (2) polished rod, oval head earless sealing supporting plate self-lock nut (6) and special screw rod (2) interference fit fixation of sensor protective case (1).
2. aircraft sensors protective case anchor fitting as claimed in claim 1; it is characterized in that: the length of the upper thread rod of described special bolt (2) seals supporting plate self-lock nut (6) with described oval head earless and is with the degree of depth of internal threaded regions identical, and the wall panel thickness of the cover body of the distance in the middle part of polished rod between circular groove with nut and sensor protective cover (1) is identical.
3. aircraft sensors protective case anchor fitting as claimed in claim 1, is characterized in that: fuselage skin (4) pastes merga pass rivet with brace panel (5) and is fixedly connected with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520430487.7U CN204776049U (en) | 2015-06-19 | 2015-06-19 | Aircraft sensor safety cover fixing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520430487.7U CN204776049U (en) | 2015-06-19 | 2015-06-19 | Aircraft sensor safety cover fixing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204776049U true CN204776049U (en) | 2015-11-18 |
Family
ID=54516151
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520430487.7U Active CN204776049U (en) | 2015-06-19 | 2015-06-19 | Aircraft sensor safety cover fixing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204776049U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109845030A (en) * | 2016-08-15 | 2019-06-04 | 赫思曼汽车通讯有限公司 | The overhead guard antenna of vehicle is fixed by cross revolving part |
-
2015
- 2015-06-19 CN CN201520430487.7U patent/CN204776049U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109845030A (en) * | 2016-08-15 | 2019-06-04 | 赫思曼汽车通讯有限公司 | The overhead guard antenna of vehicle is fixed by cross revolving part |
| US11095015B2 (en) | 2016-08-15 | 2021-08-17 | Hirshmann Car Communication GmbH | Locking of a roof antenna of a vehicle by means of a star wheel |
| CN109845030B (en) * | 2016-08-15 | 2022-01-25 | 赫思曼汽车通讯有限公司 | Top cover antenna for fastening vehicle through cross rotating piece |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |