CN207565827U - A kind of radome bindiny mechanism - Google Patents
A kind of radome bindiny mechanism Download PDFInfo
- Publication number
- CN207565827U CN207565827U CN201721653358.XU CN201721653358U CN207565827U CN 207565827 U CN207565827 U CN 207565827U CN 201721653358 U CN201721653358 U CN 201721653358U CN 207565827 U CN207565827 U CN 207565827U
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- CN
- China
- Prior art keywords
- radome
- mounting base
- fuselage
- strut
- bindiny mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The utility model discloses a kind of radome bindiny mechanisms, belong to radome mounting technique field.Including：Radome (1), hinge (2), hook lock (3) and strut (4)；The radome (1) is arranged in front fuselage opening, and opening can be closed；The radome (1) is locked (3) by hook close to the side of ventral and is connect with fuselage；Side of the radome (1) far from ventral is connect by hinge (2) with fuselage；The strut (4) is arranged in the inside of fuselage opening, and one end is connect with radar mounting platform, and the other end is connect with the radome (1)；The strut (4) is provided with self-locking device, and the strut (4) remains unchanged strut (4) length after radome (1) fully opens, by self-locking device.Its is convenient for disassembly and assembly for the utility model, solves the problem of helicopter radar cover take-down time is long, and plant maintenance is inconvenient, simple in structure, easy to operate.
Description
Technical field
The utility model belongs to radome mounting technique field, and in particular to a kind of radome bindiny mechanism.
Background technology
Existing helicopter radar cover generally use quick-detachable lock or bolt are attached with fuselage, and this connection mode is in equipment
When safeguarding, need to dismantle multiple quick-release pinnings or bolt, could be safeguarded after radome is dismantled, the take-down time is long, to dimension
Shield brings inconvenience.
Utility model content
The purpose of this utility model：To solve the above-mentioned problems, the utility model proposes a kind of radome bindiny mechanism,
It is easy to maintain convenient for open-and-close using the connection mode of hook lock and hinge.
The technical solution of the utility model：A kind of radome bindiny mechanism, including：Radome, hinge, hook lock and support
Bar；
The radome is arranged in front fuselage opening, and opening can be closed；
The radome is locked close to the side of ventral by hook to be connect with fuselage；
Side of the radome far from ventral is connect by hinge with fuselage；
The strut is arranged in the inside of fuselage opening, and one end is connect with radar mounting platform, the other end and the thunder
It is connected up to cover；
The strut is provided with self-locking device, and the strut makes strut after radome fully opens, by self-locking device
Length remains unchanged.
Preferably, the hinge is made of the first mounting base and the second mounting base；
First mounting base is mounted on fuselage, and second mounting base is mounted on the radome；
The first mounting base both sides are provided with waist-shaped hole, and there are two mounting ears for middle section setting；
Second mounting base is provided with installation axle, and the installation axle is mounted between the mounting ear.
Preferably, the installation axle is equipped with insurance with the mounting ear by insuring pin connection, described safety plug one end
Silk.
Preferably, castellated plates are provided between first mounting base and the fuselage；
First mounting base is provided with and the matched installation tooth of the castellated plates.
Preferably, the castellated plates are bolted on first mounting base on the plate nut of fuselage interior.
Preferably, the hook lock is made of lock tongue and lock；
The lock tongue is mounted on radome, and the lock is mounted at fuselage opening, and the lock tongue is pacified with snap fit
Dress.
Technical solutions of the utility model advantageous effect：A kind of radome bindiny mechanism of the utility model, convenient for disassembly and assembly, solution
It has determined the problem of helicopter radar cover take-down time is long, and plant maintenance is inconvenient, it is simple in structure, it is easy to operate.
Description of the drawings
Fig. 1 is the structure diagram of a preferred embodiment of the utility model radome bindiny mechanism；
Fig. 2 is the opening schematic diagram of a preferred embodiment of the utility model radome bindiny mechanism；
Fig. 3 is the structure diagram of embodiment illustrated in fig. 1 hinge.
Wherein, 1- radomes, 2- hinges, 3- hooks lock, 4- struts, the first mounting bases of 21-, the second mounting bases of 22-, 23-
Waist-shaped hole, 24- mounting ears, 25- installation axles, 26- castellated plates, 31- lock tongues, 32- locks.
Specific embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Described reality
It is the utility model part of the embodiment to apply example, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and it is not intended that limitation to the utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained without creative efforts
Example, shall fall within the protection scope of the present invention.The embodiment of the utility model is described in detail below in conjunction with the accompanying drawings.
In the description of the present invention, it is to be appreciated that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of description the utility model and simplifies description rather than instruction or imply signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that this practicality
The limitation of novel protected range.
As shown in Figure 1 to Figure 3, a kind of radome bindiny mechanism, including：Radome 1, hinge 2, hook lock 3 and strut 4；
Radome 1 is arranged in front fuselage opening, and opening can be closed；
Radome 1 is connect close to the side of ventral by hook lock 3 with fuselage；
Side of the radome 1 far from ventral is connect by hinge 2 with fuselage；
Strut 4 is arranged in the inside of fuselage opening, and one end is connect with radar mounting platform, and the other end connects with radome 1
It connects；
Strut 4 is provided with self-locking device, and strut 4 makes 4 length of strut after radome 1 fully opens, by self-locking device
It remains unchanged.
In the present embodiment, hinge 2 is made of the first mounting base 21 and the second mounting base 22, and the first mounting base 21 is mounted on machine
With, the second mounting base 22 is mounted on radome 1；
Wherein, 21 both sides of the first mounting base are provided with waist-shaped hole 23, can adjust its installation site, facilitate the first mounting base
21 with the installation of airframe structure.
There are two mounting ears 24 for the setting of first mounting base, 21 middle section, and installation point is provided for the second mounting base 22.
Second mounting base 22 is provided with installation axle 25, and installation axle 25 is mounted between mounting ear 24, therefore radome 1 passes through
Second mounting base is installed on fuselage, and can be rotated around fuselage.
It is appreciated that：Installation axle 25 is equipped with fuse with mounting ear 24 by insuring pin connection, safety plug one end,
It prevents installation axle 25 from coming off from mounting ear 24, improves the reliability of hinge 2.
Castellated plates 26 are provided between first mounting base 21 and fuselage, the first mounting base 21 is provided with to match with castellated plates 26
The installation tooth of conjunction, and 26 and first mounting base 21 of castellated plates is bolted on the plate nut of fuselage interior.
First mounting base 21 by flute profile is intermeshed and combines the waist-shaped hole 23 of setting with castellated plates 26, can adjust the
The installation site of one mounting base 21.
In the present embodiment, hook lock 3 is made of lock tongue 31 and lock 32, and lock tongue 31 is mounted on radome 1,32 peace of lock
At fuselage opening, lock tongue 31 is installed with 32 cooperation of lock；It is latched by pressing, lock tongue can be unlocked, facilitate radome 1
It opens.
It when the radome 1 of the utility model is opened, is supported using strut 4, radome 1, which is opened, arrives maximum rating, and strut 4 is logical
Self-locking device automatic blocking is crossed, maintenance channel is provided for plant maintenance；When radome 1 is closed, radar is closed after strut 4 is unlocked
Cover.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model rather than it is limited
System.Although the utility model is described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should manage
Solution：It can still modify to the technical solution recorded in foregoing embodiments or to which part technical characteristic into
Row equivalent replacement；And these modifications or replacement, various embodiments of the utility model that it does not separate the essence of the corresponding technical solution
The spirit and scope of technical solution.
Claims (6)
1. a kind of radome bindiny mechanism, which is characterized in that including：Radome (1), hinge (2), hook lock (3) and strut
(4)；
The radome (1) is arranged in front fuselage opening, and opening can be closed；
The radome (1) is locked (3) by hook close to the side of ventral and is connect with fuselage；
Side of the radome (1) far from ventral is connect by hinge (2) with fuselage；
The strut (4) is arranged in the inside of fuselage opening, and one end is connect with radar mounting platform, the other end and the radar
Cover (1) connection；
The strut (4) is provided with self-locking device, and the strut (4) is made after radome (1) fully opens by self-locking device
Strut (4) length remains unchanged.
2. radome bindiny mechanism according to claim 1, it is characterised in that：The hinge (2) is by the first mounting base
(21) it is formed with the second mounting base (22)；
First mounting base (21) is on fuselage, and second mounting base (22) is on the radome (1)；
First mounting base (21) both sides are provided with waist-shaped hole (23), and there are two mounting ears (24) for middle section setting；
Second mounting base (22) is provided with installation axle (25), the installation axle (25) mounted on the mounting ear (24) it
Between.
3. radome bindiny mechanism according to claim 2, it is characterised in that：The installation axle (25) and the mounting ear
(24) by insuring pin connection, described safety plug one end is equipped with fuse.
4. radome bindiny mechanism according to claim 2, it is characterised in that：First mounting base (21) and the machine
Castellated plates (26) are provided between body；
First mounting base (21) is provided with and the matched installation tooth of the castellated plates (26).
5. radome bindiny mechanism according to claim 4, it is characterised in that：The castellated plates and first mounting base
(21) it is bolted on the plate nut of fuselage interior.
6. radome bindiny mechanism according to claim 1, it is characterised in that：Hook lock (3) by lock tongue (31) and
Latch (32) composition；
The lock tongue (31) on radome (1), it is described lock (32) at fuselage opening, the lock tongue (31) with
Latch (32) cooperation installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721653358.XU CN207565827U (en) | 2017-12-01 | 2017-12-01 | A kind of radome bindiny mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721653358.XU CN207565827U (en) | 2017-12-01 | 2017-12-01 | A kind of radome bindiny mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207565827U true CN207565827U (en) | 2018-07-03 |
Family
ID=62689580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721653358.XU Active CN207565827U (en) | 2017-12-01 | 2017-12-01 | A kind of radome bindiny mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207565827U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3798114A1 (en) * | 2019-09-27 | 2021-03-31 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A radome cover shell and opening kinematic |
| US11643182B2 (en) | 2020-10-22 | 2023-05-09 | Airbus Helicopters Deutschland GmbH | Radome cover shell and opening kinematic |
-
2017
- 2017-12-01 CN CN201721653358.XU patent/CN207565827U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3798114A1 (en) * | 2019-09-27 | 2021-03-31 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A radome cover shell and opening kinematic |
| EP3805094A1 (en) | 2019-09-27 | 2021-04-14 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A radome cover shell and opening kinematic |
| US11643182B2 (en) | 2020-10-22 | 2023-05-09 | Airbus Helicopters Deutschland GmbH | Radome cover shell and opening kinematic |
| US11697488B2 (en) | 2020-10-22 | 2023-07-11 | Airbus Helicopters Deutschland GmbH | Radome cover shell and opening kinematic |
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