CN206241902U - A kind of aircraft radars device changes the outfit special tooling - Google Patents
A kind of aircraft radars device changes the outfit special tooling Download PDFInfo
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- CN206241902U CN206241902U CN201621336559.2U CN201621336559U CN206241902U CN 206241902 U CN206241902 U CN 206241902U CN 201621336559 U CN201621336559 U CN 201621336559U CN 206241902 U CN206241902 U CN 206241902U
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Abstract
A kind of aircraft radars device changes the outfit special tooling, belongs to disassemblerassembler technical field, and it includes fuselage trusses fixed mount, front end cuff, three dimensions support frame and positioning deckle board；The fuselage trusses fixed mount is made up of one group of channel-section steel trusses, the course trusses fixing assembling of the channel-section steel trusses and aircraft, locator tabs are set each channel-section steel trusses front end, all locator tabs front end faces are consistent with the radar installations fixed seat flatness of aircraft the first framework of original；The front end cuff is arranged in the course trusses inner side of aircraft, and is assembled by bolt assembly and fuselage trusses fixed mount；The three dimensions support frame is arranged between front end cuff and the framework of aircraft second；The positioning deckle board matches with the radar installations fixed seat of aircraft the first framework of original.The utility model avoids the damage to former mechanism member during aircraft radars device changes the outfit, and meets the key technology requirement of radar installations replacement project experiment.
Description
Technical field
The utility model is related to a kind of tooling device, especially it is a kind of suitable for radar installations on aircraft change the outfit it is special
Frock, belongs to disassemblerassembler technical field.
Background technology
In order to improve the resolving power and Position location accuracy of aircraft radars device, expand observation visual angle, it is necessary to airborne thunder
Technological innovation and product renewal are constantly carried out up to device.Because airborne radar device is arranged on aircraft foremost, by flying
First framework of device body is supported and fixed, when the innovation of airborne radar device technique and product renewal pilot project is carried out, is needed
Remove the original radar installations on aircraft body first, then aircraft body the first framework of original removed, change the outfit with
New first framework of replacement radar installations matching, then installs the radar installations of the replacement on new first framework.
The operation that changes the outfit of above-mentioned radar installations must assure that and meet following condition：One is the centre bit of replacement radar installations positioning
Put intersection point (the i.e. positioning of radar installations datum clamp face that should precisely align horizontal datum and vertical axis on datum clamp face
Datum mark)；Two is that the former first framework interface of fixed pan and the aircraft of replacement radar installations coincide consistent, and it is vertical
Direction and course axis angle α degree.Because the assembling of former airborne radar device is completed in aircraft manufacturers, and fly
First framework 1 of device body, between the second framework 2, the 3rd framework 3 (as shown in Figure 1) is connected by course trusses 5, in frame
Frame and trusses outside also fixedly mount unit aluminium sheet 4 by riveting or screw connection manner, are carrying out airborne radar device technique innovation
When being tested with product renewal project, the position of the fastener such as bolt hole, dowel hole, fixed angles box for fixed radar device
Variation is there occurs, former first framework 1 can not be reused, it is necessary to make new first framework；In addition, when former on aircraft body
After first framework 1 is removed, losing the former mechanism member of the solid seat constraint of framework can deform displacement and scatter under erection stress effect, make
Changed therewith into the pin-and-hole on component, screw, angle cartridge apertures position, if the member pin after new first framework is deformed with displacement
Hole, screw, angle cartridge apertures are equipped with by force, it is impossible to meet key technology requirement, therefore before the first framework 1 of body is removed,
A set of aircraft radars device should be first designed and produced to change the outfit special tooling.
Utility model content
The utility model provides a kind of aircraft radars device and changes the outfit special tooling, it is intended to solves aircraft radars device and changes
The problem of stress concentration and injury of primary mechanism member is caused during dress, it is ensured that the aircraft radars device centre of location essence after changing the outfit
Standard aligns the positioning datum point of radar installations datum clamp face on aircraft body, and the radar installations fixed pan after making to change the outfit
It is coincide with the former first framework interface of aircraft consistent.
To achieve the above object, the technical scheme that the utility model is used is：
A kind of aircraft radars device changes the outfit special tooling, including fuselage trusses fixed mount, front end cuff, three dimensions branch
Support and positioning deckle board；The fuselage trusses fixed mount is made up of one group of channel-section steel trusses, the boat of the channel-section steel trusses and aircraft
To trusses fixing assembling, locator tabs are set each channel-section steel trusses front end, all locator tabs front end faces are former with aircraft
The radar installations fixed seat flatness of the first framework is consistent；The front end cuff is arranged in the course trusses inner side of aircraft, and
Assembled by bolt assembly and fuselage trusses fixed mount；The three dimensions support frame is arranged on front end cuff and aircraft second
Between framework；The positioning deckle board matches with the radar installations fixed seat of aircraft the first framework of original.
Above-mentioned aircraft radars device changes the outfit special tooling, and the three dimensions support frame is provided with support bar and intermediate
Body；The support bar is divided into two groups, and one of which support bar is arranged in before middle spheroid, support rod rear end and middle spheroid with
Thread connecting mode is assembled, and is fixed by locking nut locking, and support bar front end is assembled by attachment lug with front end cuff；
Another group of support bar is arranged in behind middle spheroid, and support bar front end is assembled with middle spheroid with thread connecting mode, and is led to
Cross locking nut locking to fix, support rod rear end is assembled by attachment lug with the framework of aircraft second.
Above-mentioned aircraft radars device is changed the outfit special tooling, and the front end cuff is made of angle steel material, is two-part
Split type structure, the circular cuff with annular end face and the side face of cylinder, its annular end are combined as by dismountable connected mode
Face is used to fix positioned at one group of attachment lug of support bar before intermediate body in three dimensions support frame, and its side face of cylinder is used for
The channel-section steel trusses locator tabs of fixed main body trusses fixed mount, aircraft course trusses be located at the channel-section steel trusses locator tabs with
Between the side face of cylinder of front end cuff, cushion block is set in the groove of aircraft course trusses.
Above-mentioned aircraft radars device changes the outfit special tooling, and the front end cuff is provided with auxiliary support frame, the auxiliary branch
Support is in " mouth " font structure, by its corner location and the annular end face fixing assembling of front end cuff.
Above-mentioned aircraft radars device changes the outfit special tooling, and the positioning deckle board is disc structure, on positioning deckle board periphery
The pilot hole that setting is matched with channel-section steel trusses locator tabs.
Above-mentioned aircraft radars device changes the outfit special tooling, is also set up for determining aircraft on the positioning deckle board periphery
The location hole of " ten " course axis.
Above-mentioned aircraft radars device is changed the outfit special tooling, and one group of lightening hole is set on the positioning deckle board.
The utility model is after adopting the above technical scheme, the effect with following technological progress：
Consolidate to the reinforcement protection of former mechanism member and to the radar installations that changes the outfit during being changed the outfit for radar installations on aircraft
The plane positioning of reservation, its middle fuselage trusses fixed mount, front end cuff, three dimensions support frame be bracing means, by this plus
It is fixedly mounted with to put and solves former mechanism member after former first framework is removed on aircraft body and deform displacement under erection stress effect and dissipate
The problem opened；Positioning deckle board is positioner, for carrying out plane positioning to radar installations mounting seat on new first framework, it is ensured that
The centre of location position of replacement radar installations precisely aligns positioning datum point.The utility model not only avoid aircraft radars dress
Damage to former mechanism member during displacement dress, and radar installations fixed pan after making to change the outfit and aircraft former first frame
Frame interface coincide unanimously, so as to ensure that the aircraft radars device centre of location after changing the outfit precisely is aligned on aircraft body
Positioning datum point on radar installations datum clamp face, meets the innovation of airborne radar device technique and the experiment of product renewal project
Key technology requirement.
Brief description of the drawings
Fig. 1 is the aircraft front portion housing construction schematic diagram involved by the utility model；
Fig. 2 is structural representation of the present utility model；
Fig. 3 is A direction views in Fig. 2；
Fig. 4 is partial enlarged drawing at I in Fig. 3；
Fig. 5 is partial enlarged drawing at II in Fig. 3；
Fig. 6 is channel-section steel truss structure schematic diagram；
Fig. 7 is front end cuff structural representation；
Fig. 8 is posting plate structure schematic diagram；
Fig. 9 is supporting bar structure schematic diagram；
Figure 10 to Figure 12 is that aircraft radars device changes the outfit process schematic.
Each label is expressed as in figure：1st, the first framework, the 2, second framework, the 3, the 3rd framework, 4, unit aluminium sheet, 5, course purlin
Beam, 6, channel-section steel trusses, 6-1, locator tabs, 7, front end cuff, 7-1, annular end face, 7-2, the side face of cylinder, 8, positioning deckle board, 8-
1st, pilot hole, 8-2, lightening hole, 8-3, location hole, 9, support bar, 9-1, attachment lug, 10, middle spheroid, 11, Auxiliary support
Frame, 12, cushion block, 13, bolt assembly, 14, locking nut, 15, new first framework.
Specific embodiment
Below in conjunction with the accompanying drawings and embodiment is described in further details to the utility model：
A kind of aircraft radars device changes the outfit special tooling, as shown in Figures 2 and 3, including fuselage trusses fixed mount, front end
Cuff 7, three dimensions support frame and positioning deckle board 8；The fuselage trusses fixed mount is made up of one group of channel-section steel trusses 6, the groove
The quantity of steel truss girder 6 be eight, they respectively with the corresponding fixing assembling of aircraft course trusses 5；The front end cuff 7 is arranged in
The inner side of course trusses 5 of aircraft, and assembled by bolt assembly 13 and fuselage trusses fixed mount；The three dimensions support frame
Between front end cuff 7 and the second framework of aircraft 2；The positioning deckle board 8 is filled with the radar of aircraft the first framework 1 of original
Fixed seat is put to match.
Referring to Fig. 2, Fig. 3, Fig. 6, in aircraft radars device described in the utility model changes the outfit special tooling, the groove
The front end of steel truss girder 6 sets the radar installations of locator tabs 6-1, all locator tabs 6-1 front end faces and aircraft the first framework of original
Fixed seat flatness is consistent.
Referring to Fig. 2, Fig. 3, Fig. 5, Fig. 9, in aircraft radars device described in the utility model changes the outfit special tooling, institute
State three dimensions support frame and be provided with support bar 9 and middle spheroid 10；The quantity of the support bar 9 is ten six roots of sensation, is divided into two groups, wherein
One group of eight support bar is arranged in before middle spheroid 10, and support rod rear end is assembled with middle spheroid 10 with thread connecting mode,
And fixed by the locking of locking nut 14, support bar front end is assembled by attachment lug 9-1 with front end cuff 7；Another group eight
Support bar is arranged in behind middle spheroid 10, and support bar front end is assembled with middle spheroid 10 with thread connecting mode, and is passed through
The locking of locking nut 14 is fixed, and support rod rear end is assembled by attachment lug 9-1 with the second framework of aircraft 2.
Referring to Fig. 2, Fig. 3, Fig. 4, Fig. 7, in aircraft radars device described in the utility model changes the outfit special tooling, institute
State front end cuff 7 to be made of angle steel material, be two-section separated structure, be combined as with ring by dismountable connected mode
The circular cuff of shape end face 7-1 and side face of cylinder 7-2, during its annular end face 7-1 is used to fix and be located in three dimensions support frame
Between one group of attachment lug 9-1 of support bar before spheroid, its side face of cylinder 7-2 is used for the channel-section steel purlin of fixed main body trusses fixed mount
Beam locator tabs 6-1, aircraft course trusses 5 is located at the side face of cylinder of the channel-section steel trusses locator tabs 6-1 and front end cuff
Between 7-2, in the groove of aircraft course trusses 5 set cushion block 12, the cushion block 12 be used for bear assembling front end cuff 7 with
The pressure of bolt assembly 13 of fuselage trusses fixed mount, it is to avoid the flight that front end cuff 7 is caused after being assembled with fuselage trusses fixed mount
The problem on deformation of device course trusses 5；The front end cuff 7 is provided with auxiliary support frame 11, and the auxiliary support frame 11 is in " mouth " font
Structure, by its corner location and the annular end face 7-1 fixing assemblings of front end cuff 7.
Referring to Fig. 2, Fig. 3, Fig. 8, in aircraft radars device of the present invention changes the outfit special tooling, the posting
Plate 8 is disc structure, and the pilot hole 8-1 matched with channel-section steel trusses locator tabs 6-1 is set on positioning deckle board periphery；Described fixed
The position periphery of deckle board 8 also sets up the location hole 8-3 for determining positioning deckle board positioning datum point；Also set on the positioning deckle board 8
Put one group of lightening hole 8-2.
Referring to Figure 10 to Figure 12, when aircraft radars device changes the outfit operation, carried out by following operative step：
First, former aircraft radars device is removed；
2nd, the mounting hole consistent with pilot hole on aircraft course trusses 5 is prepared on eight channel-section steel trusses 6；
3rd, eight channel-section steel trusses 6 are fixed by bolts on the course trusses 5 of aircraft；
The 4th, the front end cuff 7 of two-section separated structure is placed in the inner side of course trusses 5 of aircraft, and is assembled into circle
After cuff, the auxiliary support frame 11 of " mouth " font structure is installed in front end cuff 7；
The 5th, eight front ends of channel-section steel trusses 6 are fixed on the side face of cylinder 7-2 of front end cuff by bolt assembly 13 respectively
On, in this case, aircraft course trusses 5 is located at the side face of cylinder of the channel-section steel trusses locator tabs 6-1 and front end cuff 7
It is the problem on deformation of aircraft course trusses 5 for avoiding front end cuff 7 from being caused after being assembled with fuselage trusses fixed mount between 7-2,
Cushion block 12 is installed in the groove of aircraft course trusses 5, assembling front end cuff 7 and fuselage trusses fixed mount are born using cushion block 12
The pressure of bolt assembly 13, eight rear ends of channel-section steel trusses 6 are fixed in the outer rim of aircraft the second framework 2 or the 3rd framework 3；
6th, eight locator tabs 6-1 front end faces of eight front ends of channel-section steel trusses 6 and aircraft original are made by grinding process
The front end face of one framework 1 is in the same plane, it is ensured that the flatness ≯ 0.2mm of the plane；
7th, the disk blank of positioning deckle board 8 is made, and lightening hole 8-2 is opened up on positioning deckle board disk blank, than
Eight pilot hole 8-1 and four location hole 8-3 are prepared on the positioning disk blank of deckle board 8 to former first framework 1, respectively to four
Two hole lines of centres positioned opposite in individual location hole 8-3, the intersection point for determining two lines is the positioning datum for positioning deckle board
Point, completes the making of positioning deckle board 8；
8th, aircraft the first framework 1 of original is removed；
9th, it is template to position deckle board 8, according to pilot hole 8-1, positioning datum point position and flatness on positioning deckle board 8
It is required that making new first framework 15 matched with the radar installations that changes the outfit；
Tenth, new first framework 15 is arranged on aircraft body correspondence position, makes the positioning datum of new first framework 15
Point precisely aligns the positioning datum point on aircraft body on radar installations datum clamp face；
11, remove aircraft radars device to change the outfit special tooling, aircraft radars dress is installed on new first framework 15
Put, complete aircraft radars device and change the outfit operation.
Claims (8)
1. a kind of aircraft radars device changes the outfit special tooling, it is characterised in that：The aircraft radars device changes the outfit special tool
Dress includes fuselage trusses fixed mount, front end cuff (7), three dimensions support frame and positioning deckle board (8)；The fuselage trusses is fixed
Frame is made up of one group of channel-section steel trusses (6), course trusses (5) fixing assembling of the channel-section steel trusses (6) and aircraft, at each
Channel-section steel trusses (6) front end sets locator tabs (6-1), all locator tabs (6-1) front end faces and aircraft the first framework of original
Radar installations fixed seat flatness is consistent；The front end cuff (7) is arranged in course trusses (5) inner side of aircraft, and passes through
Bolt assembly (13) is assembled with fuselage trusses fixed mount；The three dimensions support frame is arranged on front end cuff (7) and aircraft
Between second framework (2)；Positioning deckle board (8) matches with the radar installations fixed seat of aircraft the first framework of original.
2. aircraft radars device according to claim 1 changes the outfit special tooling, it is characterised in that：The three dimensions branch
Support is provided with support bar (9) and middle spheroid (10)；The support bar (9) is divided into two groups, during one of which support bar is arranged in
Between before spheroid (10), support rod rear end is assembled with middle spheroid (10) with thread connecting mode, and by locking nut (14)
Locking is fixed, and support bar front end is assembled by attachment lug (9-1) with front end cuff (7)；Another group of support bar is arranged in centre
Behind spheroid (10), support bar front end is assembled with middle spheroid (10) with thread connecting mode, and by locking nut (14)
Locking is fixed, and support rod rear end is assembled by attachment lug (9-1) with the framework of aircraft second (2).
3. aircraft radars device according to claim 2 changes the outfit special tooling, it is characterised in that：The front end cuff
(7) it is made of angle steel material, is two-section separated structure, is combined as with annular end face by dismountable connected mode
The circular cuff of (7-1) and the side face of cylinder (7-2), during its annular end face (7-1) is used to fix and be located in three dimensions support frame
Between one group of attachment lug of support bar (9-1) before spheroid, its side face of cylinder (7-2) is used for the groove of fixed main body trusses fixed mount
Steel truss girder locator tabs (6-1), aircraft course trusses (5) is positioned at the channel-section steel trusses locator tabs (6-1) and front end cuff
The side face of cylinder (7-2) between, in the groove of aircraft course trusses (5) set cushion block (12).
4. aircraft radars device according to claim 3 changes the outfit special tooling, it is characterised in that：The front end cuff
(7) auxiliary support frame (11) is provided with, the auxiliary support frame (11) is bound round in " mouth " font structure by its corner location and front end
Cover annular end face (7-1) fixing assembling of (7).
5. aircraft radars device according to any one of claim 1 to 4 changes the outfit special tooling, it is characterised in that：Institute
It is disc structure to state positioning deckle board (8), and the pilot hole matched with channel-section steel trusses locator tabs (6-1) is set on positioning deckle board periphery
(8-1)。
6. aircraft radars device according to claim 5 changes the outfit special tooling, it is characterised in that：In the positioning deckle board
(8) periphery also sets up the location hole (8-3) for determining positioning deckle board positioning datum point.
7. aircraft radars device according to claim 6 changes the outfit special tooling, it is characterised in that：In the positioning deckle board
(8) one group of lightening hole (8-2) is set on.
8. aircraft radars device according to claim 7 changes the outfit special tooling, it is characterised in that：The fuselage trusses is consolidated
Channel-section steel trusses (6) quantity for determining frame is eight；Support bar (9) quantity of the three dimensions support frame is ten six roots of sensation, wherein eight
Root support bar is arranged in before middle spheroid (10), and eight support bars are arranged in behind middle spheroid (10) in addition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621336559.2U CN206241902U (en) | 2016-12-07 | 2016-12-07 | A kind of aircraft radars device changes the outfit special tooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621336559.2U CN206241902U (en) | 2016-12-07 | 2016-12-07 | A kind of aircraft radars device changes the outfit special tooling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206241902U true CN206241902U (en) | 2017-06-13 |
Family
ID=59004197
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621336559.2U Withdrawn - After Issue CN206241902U (en) | 2016-12-07 | 2016-12-07 | A kind of aircraft radars device changes the outfit special tooling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206241902U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106625331A (en) * | 2016-12-07 | 2017-05-10 | 中国人民解放军第五七二工厂 | Special tool for replacing aircraft radar device and replacing method |
-
2016
- 2016-12-07 CN CN201621336559.2U patent/CN206241902U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106625331A (en) * | 2016-12-07 | 2017-05-10 | 中国人民解放军第五七二工厂 | Special tool for replacing aircraft radar device and replacing method |
| CN106625331B (en) * | 2016-12-07 | 2017-10-03 | 中国人民解放军第五七二一工厂 | A kind of aircraft radars device changes the outfit special tooling and costume changing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170613 Effective date of abandoning: 20171003 |
|
| AV01 | Patent right actively abandoned |