CN212829137U - A2C airplane rear fuselage assembly jig - Google Patents
A2C airplane rear fuselage assembly jig Download PDFInfo
- Publication number
- CN212829137U CN212829137U CN202021967897.2U CN202021967897U CN212829137U CN 212829137 U CN212829137 U CN 212829137U CN 202021967897 U CN202021967897 U CN 202021967897U CN 212829137 U CN212829137 U CN 212829137U
- Authority
- CN
- China
- Prior art keywords
- frame
- horizontal positioning
- tail rudder
- positioning frame
- supporting
- 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.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
A2C airplane rear fuselage assembly jig comprises an isosceles trapezoid-shaped horizontal positioning frame (5), wherein the front end of the horizontal positioning frame (5) is provided with an opening, the top of the tail end of the horizontal positioning frame (5) is respectively provided with a balance bar opening end supporting fork frame (7) in a bilateral symmetry manner, the top of the front end of the horizontal positioning frame (5) is provided with a pair of balance bar front end supporting blocks (8), the tops of the left side and the right side of the horizontal positioning frame (5) are respectively provided with a plurality of balance bar middle supporting blocks (9) in a symmetry manner, and the horizontal positioning frame (5) is respectively provided with a pair of aileron supporting blocks (10) from front to back; the utility model has the advantages that: the rear airframe of the airplane can be quickly assembled and positioned through the assembly fixture, and the assembling efficiency and the assembling precision are improved.
Description
Technical Field
The utility model relates to a machining technical field, fuselage assembly type frame behind concretely relates to A2C aircraft.
Background
At present, fuselage mainly includes the balancing pole behind the A2C aircraft, a pair of aileron mounting bracket, tail vane mounting bracket and tail vane bracing piece, balancing pole and tail vane bracing piece are the U-shaped pole that is isosceles trapezoid shape, the top at the balancing pole is installed to a pair of aileron mounting bracket, the front end at the balancing pole is installed to tail vane mounting bracket top one end, connect through the tail vane bracing piece between tail vane mounting bracket bottom one end and the balancing pole, all be connected through the connector between tail vane mounting bracket and the tail vane bracing piece and the balancing pole, and it is fixed through the screw rod, how to carry out quick accurate location to each part of fuselage after, the direct relation is to the efficiency and the assembly quality of assembly.
SUMMERY OF THE UTILITY MODEL
The utility model aims at present, fuselage mainly includes the balancing pole behind the A2C aircraft, a pair of aileron mounting bracket, tail vane mounting bracket and tail vane bracing piece, balancing pole and tail vane bracing piece are the U-shaped pole that is isosceles trapezoid shape, the top at the balancing pole is installed to a pair of aileron mounting bracket, the front end at the balancing pole is installed to tail vane mounting bracket top one end, connect through the tail vane bracing piece between tail vane mounting bracket bottom one end and the balancing pole, all be connected through the connector between tail vane mounting bracket and the tail vane bracing piece and the balancing pole, and it is fixed through the screw rod, how to carry out quick accurate location to each part of rear fuselage, direct relation is to the efficiency and the assembly quality of assembly, and provide fuselage assembly type frame behind the A2C aircraft.
The utility model discloses the rear fuselage includes balancing pole, a pair of aileron mounting bracket, tail vane mounting bracket and tail vane bracing piece, balancing pole and tail vane bracing piece are the U-shaped pole that is isosceles trapezoid shape, a pair of aileron mounting bracket is installed in the top of balancing pole, tail vane mounting bracket top one end is installed at the front end of balancing pole, tail vane mounting bracket bottom one end and balancing pole are connected through the tail vane bracing piece, the assembly type frame includes the horizontal location frame that is isosceles trapezoid shape, the front end of horizontal location frame is the opening, horizontal location frame terminal top is the bilateral symmetry respectively and is equipped with balancing pole open end support crotch, horizontal location frame front end top is equipped with a pair of balancing pole front end supporting shoe, the left and right sides top of horizontal location frame is symmetrical respectively and is equipped with a plurality of balancing pole middle part supporting shoes, horizontal location frame is last to be equipped with a pair of aileron supporting;
the horizontal positioning frame front end opening part below is equipped with tail vane bracing piece front end locating piece, and opens on tail vane bracing piece front end locating piece has tail vane mounting bracket to dodge the groove, and the left and right sides of horizontal positioning frame is equipped with tail vane bracing piece open end locating piece respectively, is located and is equipped with tail vane mounting bracket support crotch on the horizontal positioning frame of tail vane bracing piece front end locating piece below.
The front end supporting block and the aileron supporting block of the balance rod are both L-shaped supporting blocks with openings facing the front end of the horizontal positioning frame, and the horizontal sections of the L-shaped supporting blocks are inclined.
The front end of the positioning block at the opening end of the tail vane supporting rod is an inclined plane, and a mounting avoiding groove is formed in the horizontal positioning frame located on the side of the positioning block at the opening end of the tail vane supporting rod.
The utility model has the advantages that: the rear airframe of the airplane can be quickly assembled and positioned through the assembly fixture, and the assembling efficiency and the assembling precision are improved.
Description of the drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic view of the structure of the assembly state of the present invention.
Fig. 3 is a schematic view of the rear body structure of the present invention.
Detailed Description
As shown in the attached drawings, the rear fuselage of the utility model comprises a balancing pole 1 and a pair of aileron mounting racks 2, the tail vane mounting frame comprises a tail vane mounting frame 3 and a tail vane supporting rod 4, wherein the balancing rod 1 and the tail vane supporting rod 4 are both U-shaped rods in an isosceles trapezoid shape, a pair of aileron mounting frames 2 are mounted above the balancing rod 1, one end of the top of the tail vane mounting frame 3 is mounted at the front end of the balancing rod 1, one end of the bottom of the tail vane mounting frame 3 is connected with the balancing rod 1 through the tail vane supporting rod 4, the assembly frame comprises a horizontal positioning frame 5 in an isosceles trapezoid shape, the front end of the horizontal positioning frame 5 is an opening, the top of the tail end of the horizontal positioning frame 5 is respectively provided with a balancing rod opening end supporting fork frame 7 in a bilateral symmetry shape, the top of the front end of the horizontal positioning frame 5 is provided with a pair of balancing rod front end supporting blocks 8, the tops of the left side and the right side of the horizontal positioning frame 5 are respectively and symmetrically provided;
a tail rudder support rod front end positioning block 18 is arranged below the front end opening of the horizontal positioning frame 5, a tail rudder mounting frame avoiding groove is formed in the tail rudder support rod front end positioning block 18, tail rudder support rod opening end positioning blocks 19 are respectively arranged on the left side and the right side of the horizontal positioning frame 5, and a tail rudder mounting frame supporting fork frame 16 is arranged on the horizontal positioning frame 5 below the tail rudder support rod front end positioning block 18.
The balance bar front end supporting block 8 and the aileron supporting block 10 are both L-shaped supporting blocks with openings facing the front end of the horizontal positioning frame 5, so that the parts can be taken after the assembly is completed, the horizontal section of the L-shaped supporting blocks is in an inclined shape, and the aileron mounting frame 2 is placed on the aileron supporting block 10 to avoid sliding.
The front end of the positioning block 19 at the opening end of the tail rudder supporting rod is an inclined plane, the inclined angle of the inclined plane is the same as the inclined angle of the assembled tail rudder supporting rod 4, and a mounting avoiding groove is formed in the horizontal positioning frame 5 located on the side of the positioning block 19 at the opening end of the tail rudder supporting rod.
The working mode is as follows: before assembly, the balance bar 1 is placed at the top of a horizontal positioning frame 5, a pair of balance bar open end supporting fork frames 7 and a pair of balance bar front end supporting blocks 8 are matched and positioned, the aileron mounting frame 2 is placed on the aileron supporting blocks 10, and is positioned above the balancing pole 1, the front end of the tail rudder supporting pole 4 is positioned by a front end positioning block 18 of the tail rudder supporting pole, the two ends of the opening part of the tail rudder supporting pole 4 are respectively placed on the corresponding opening end positioning blocks 19 of the tail rudder supporting pole, finally, the horizontal section of the tail rudder mounting rack 3 is placed on a tail rudder mounting rack supporting fork frame 16, the vertical section of the tail rudder mounting rack 3 is positioned in an avoiding groove of the front end positioning block 18 of the tail rudder supporting pole, the upper end and the lower end of the tail rudder mounting rack 3 are respectively connected with the balancing pole 1 and the tail rudder supporting pole 4 by screws, then, other connecting parts are fixed through screws in sequence, and the rear machine body can be taken away from the horizontal positioning frame 5 by integrally lifting upwards after assembly is completed.
Claims (3)
- An A2C airplane rear fuselage assembly fixture, wherein the rear fuselage comprises a balancing pole (1), a pair of aileron mounting frames (2), a tail rudder mounting frame (3) and a tail rudder supporting pole (4), the balancing pole (1) and the tail rudder supporting pole (4) are both U-shaped poles in isosceles trapezoid shape, the pair of aileron mounting frames (2) are mounted above the balancing pole (1), one end of the top of the tail rudder mounting frame (3) is mounted at the front end of the balancing pole (1), one end of the bottom of the tail rudder mounting frame (3) is connected with the balancing pole (1) through the tail rudder supporting pole (4), the assembly fixture is characterized by comprising a horizontal positioning frame (5) in isosceles trapezoid shape, the front end of the horizontal positioning frame (5) is an opening, the top of the tail end of the horizontal positioning frame (5) is respectively provided with the balancing pole opening end supporting fork frame (7) in bilateral symmetry, the top of the front end of the horizontal positioning frame (5) is provided with a pair of balancing pole, the top parts of the left side and the right side of the horizontal positioning frame (5) are respectively symmetrically provided with a plurality of balance bar middle supporting blocks (9), and the horizontal positioning frame (5) is respectively provided with a pair of aileron supporting blocks (10) from front to back;a tail rudder supporting rod front end positioning block (18) is arranged below an opening at the front end of the horizontal positioning frame (5), a tail rudder mounting frame avoiding groove is formed in the tail rudder supporting rod front end positioning block (18), tail rudder supporting rod opening end positioning blocks (19) are arranged on the left side and the right side of the horizontal positioning frame (5) respectively, and a tail rudder mounting frame supporting fork frame (16) is arranged on the horizontal positioning frame (5) below the tail rudder supporting rod front end positioning block (18).
- 2. The A2C aircraft rear fuselage assembly jig of claim 1, characterized in that the stabilizer bar front end support block (8) and the aileron support block (10) are both L-shaped support blocks that open towards the front end of the horizontal positioning bracket (5), and the horizontal sections of the L-shaped support blocks are inclined.
- 3. The A2C airplane rear fuselage assembly jig according to claim 1, characterized in that the front end of the tail rudder support rod open end positioning block (19) is an inclined plane, and the horizontal positioning frame (5) on the side of the tail rudder support rod open end positioning block (19) is provided with an installation avoiding groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021967897.2U CN212829137U (en) | 2020-09-10 | 2020-09-10 | A2C airplane rear fuselage assembly jig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021967897.2U CN212829137U (en) | 2020-09-10 | 2020-09-10 | A2C airplane rear fuselage assembly jig |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212829137U true CN212829137U (en) | 2021-03-30 |
Family
ID=75146905
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021967897.2U Active CN212829137U (en) | 2020-09-10 | 2020-09-10 | A2C airplane rear fuselage assembly jig |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212829137U (en) |
-
2020
- 2020-09-10 CN CN202021967897.2U patent/CN212829137U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN216781624U (en) | Assembly fixture for wall plate at rear upper part of rear fuselage of airplane | |
| CN212829137U (en) | A2C airplane rear fuselage assembly jig | |
| CN204774592U (en) | Engine suspending bracket | |
| CN107226135B (en) | A kind of splash apron bracket without frock clamp | |
| CN212917746U (en) | A2C aircraft fuselage drilling frock behind aircraft | |
| CN213646553U (en) | Quick positioning mechanism of coil component press-fitting machine | |
| CN211540066U (en) | Box welding frock | |
| CN212240779U (en) | Aircraft rudder assembly fixture | |
| CN209418372U (en) | A kind of switch panel of installation by adhering | |
| CN208732106U (en) | A kind of sucking disc mechanism for automobile back door assembly | |
| CN205254404U (en) | Automobile -used rear axle assembly welding jig supporting seat | |
| CN221113937U (en) | Automobile part transportation frame | |
| CN208253130U (en) | A kind of Combined wall frame | |
| CN219377182U (en) | Quick magnetic rod replacing structure | |
| CN111038733A (en) | Unmanned helicopter frame assembly fixture | |
| CN214186115U (en) | Structure for skillfully arranging frames in cutting machine | |
| CN212128330U (en) | Electroplating hanger that can steadily place uses arm | |
| CN210189611U (en) | Frock is used in equipment of suspension bridge arm | |
| CN216102816U (en) | Multi-functional nacelle stores pylon of unmanned aerial vehicle | |
| CN215393540U (en) | Hanger device | |
| CN212732843U (en) | Spliced type support frame for small aircraft | |
| CN208748836U (en) | A kind of assembled architecture connection component | |
| CN207900977U (en) | A kind of fixed frame of Novel workpiece assembly | |
| CN220838606U (en) | Welding jig for backrest frame of massage chair | |
| CN221251172U (en) | Integrative die-casting structure of revolving rack |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |