CN216546788U - Interior guarantor's type support is used in assembly of weak rigidity aircraft - Google Patents
Interior guarantor's type support is used in assembly of weak rigidity aircraft Download PDFInfo
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- CN216546788U CN216546788U CN202220227332.3U CN202220227332U CN216546788U CN 216546788 U CN216546788 U CN 216546788U CN 202220227332 U CN202220227332 U CN 202220227332U CN 216546788 U CN216546788 U CN 216546788U
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Abstract
The utility model provides an internal shape-preserving support for weak-rigidity airplane assembly, and relates to the technical field of helicopter assembly. The internal shape-preserving support for weak-rigidity airplane assembly comprises an upper support assembly (1), two side support assemblies (2), two lower support assemblies (3), a mandril assembly (4) and an elbow clamp assembly (5), wherein the two side support assemblies (2) are arranged on two sides of an airplane and are connected with the lower support assemblies (3) through support mounting plates; the upper support assembly (1) is arranged at the top in the airplane and is connected with the two side support assemblies (2); the upper support component (1), the side support component (2) and the lower support component (3) are all provided with a mandril component (4); the upper support component (1) and the lower support component (3) are both provided with toggle clamp components (5). The utility model can quickly adjust the airplane to the theoretical appearance, and solves the technical problems of poor accuracy and large deformation of the existing weak-rigidity airplane during butt joint.
Description
Technical Field
The utility model relates to the technical field of helicopter assembly, in particular to an internal shape-preserving support for weak rigidity aircraft assembly.
Background
When helicopter sections are assembled in an abutting manner, the rigidity of the helicopter sections is low, so that the helicopter sections in the assembled state are different from the theoretical shape. And each section of the engine body needs to reach the theoretical appearance and the theoretical assembly pose, so that the assembly accuracy of the engine body is ensured, the key intersection point needs to meet the finish machining allowance, the assembly accuracy of the transmission mechanism of the engine is ensured, and the butt joint parts are free of interference, uniform in gap and free of stress.
In order to meet the requirements, an inner shape-preserving tool and an outer shape-preserving tool need to be designed for the airplane. Wherein, interior shape-preserving frock can guarantee the lower carriage transportation rigidity, guarantees that the shape of the one end of end frame disappearance is correct. In the existing assembly tool, a structural form that a positioning flat plate and a support body are welded is usually adopted, but the size and the weight of the traditional shape-preserving tool are large because the space in the airplane is very narrow, and personnel are very difficult to install and disassemble in the airplane.
In patent CN201510664888.3, a novel docking jig is disclosed, which is used for coordinating the separating surfaces of two components in the frame-type docking process of an airplane. The jig butt joint flat plate component is used for controlling butt joint coordination of a butt joint hole at a separation surface and the appearance of a butt joint separation surface of two parts of the airplane surrounding frame type butt joint, so that the accuracy of airplane manufacturing is guaranteed. In the existing assembly tool, a structural form that a positioning flat plate and a support body are welded is adopted for a jig butt joint flat plate component, and the jig butt joint flat plate component is connected in a non-detachable mode. This patent provides a modified butt joint type frame, has solved because of the problem that the frock that the model conversion arouses adds that the worker design, the manufacturing work degree of difficulty is big, reduces frock cost input simultaneously, shortens frock research and development cycle. Because the butt joint flat plate component adopts a detachable structural form, the modification difficulty and the workload during the model conversion are greatly reduced.
In patent CN202020456051.6, an aircraft skin butt joint frock is disclosed, including support, sliding sleeve, traveller, first vacuum chuck, second vacuum chuck, handle, activity card lamella, card strip, first spring and second spring, the support is domes, can dismantle under the support one end and connect first vacuum chuck, the embedded sliding sleeve of the support other end, traveller sliding connection is in the traveller, it has the draw-in groove to open the traveller both sides. This patent is treating fixed covering laminating installation position through the traveller removal messenger owing to adopted first vacuum chuck and second vacuum chuck can adsorb fixed covering and treat fixed covering simultaneously. Due to the adoption of the pushing handle, the vacuum sucker can be pushed more easily when being used for sucking, and the vacuum sucker can be more firmly sucked. Due to the adoption of the movable clamping flap, when the handle moves, the sliding column can be pushed to move upwards through the movable clamping flap, so that the skin is attached to the mounting position.
In patent CN201711033496.2, a digital assembly positioning system and a positioning method for an airplane central wing box are disclosed, and a digital flexible positioning tool related to the digital flexible positioning tool is divided into a bed body main unit, a front beam positioning unit, a back beam positioning unit, a left wing rib shape-preserving unit, a right wing rib shape-preserving unit, an upper tool positioning and compressing unit and a lower tool positioning and compressing unit according to functional modules. The method adopts a method of automatic positioning by taking a framework as a reference, firstly accurately positions framework parts such as a front beam, a rear beam, a wing rib and the like of a large central wing box, and then positions components such as an upper wall plate, a lower wall plate, a longitudinal beam and the like by taking the framework as the reference until the whole positioning process of the central wing box is completed. The digital assembly positioning system and the positioning method can accurately position, automatically control, integrate multiple functions and flexibly design the large central wing box.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defects of the prior art and provides an internal shape-preserving support for weak rigidity aircraft assembly. The elbow fixing clamp assembly, the positioning piece and the positioning pin are arranged, so that the side support assembly can be prevented from toppling; the cross beam can be jacked to a theoretical position by adjusting a screw rod at the front end of the toggle clamp assembly; by adjusting the length of the ejector rod assembly, slight expansion of the skin can occur. The technical problems that an existing weak-rigidity airplane is poor in accuracy and large in deformation during butt joint are solved. Meanwhile, the inner shape-preserving support is subjected to modularization and lightweight design, and the rapidness and convenience of personnel in the installation of the interior of the airplane can be ensured.
The purpose of the utility model is realized by the following technical scheme:
the utility model provides a weak rigidity aircraft assembly is with interior guarantor's type support, includes upper bracket component, side bracket component, lower part bracket component, ejector pin subassembly and toggle clamp subassembly, wherein:
the lower support assembly is arranged on a frame on the ground of the airplane;
the number of the side bracket assemblies is two, the side bracket assemblies are arranged on two sides of the airplane and are connected with the lower bracket assembly through the bracket mounting plate;
the upper support assembly is arranged at the top in the airplane, and two ends of the upper support assembly are connected with the two side support assemblies through support mounting plates;
the number of the ejector rod assemblies is multiple, and the upper support assembly, the side support assembly and the lower support assembly are all provided with ejector rod assemblies;
the number of the toggle clamp assemblies is multiple, and the upper support assembly and the lower support assembly are both provided with the toggle clamp assemblies;
each side bracket component is also provided with a positioning sheet; and the positioning plate is also provided with a positioning pin.
Alternatively or preferably, the upper bracket assembly comprises an upper inner profile bar and an upper bracket mounting plate;
the upper support mounting plate is fixed at two ends of the upper inner molding protection rod through an upper support connecting rod;
the upper support connecting rod is provided with a plurality of screw holes, extends into the upper inner shape-preserving rod and is in screw connection with the upper inner shape-preserving rod;
each side bracket assembly comprises three side internal shape-retaining rods;
the upper end and the lower end of the side bracket component are respectively provided with a side bracket mounting plate;
the side internal protective rod and the side internal protective rod, and the side internal protective rod and the side support mounting plate are connected through joints.
Optionally or preferably, the upper bracket mounting plate is of an Contraband-shaped structure, and both sides of the upper bracket mounting plate are provided with quick hooks;
the side bracket mounting plate is also in an Contraband-shaped structure and is clamped outside the upper bracket mounting plate;
mounting plate handles are arranged on two sides of the side support mounting plate;
a latch hook is arranged on the mounting plate handle;
the mounting plate handle can rotate along the handle rotating shaft;
the latch hook can cooperate with a quick latch hook.
Optionally or preferably, the ejector rod assembly comprises a screw rod, a pull rod, a first nut, a gland, a support leg and a base plate;
the screw rod is a threaded rod, one end of the screw rod is fixed on the support leg, and the other end of the screw rod is provided with a pull rod;
the pull rod penetrates through the screw rod and is perpendicular to the screw rod;
the screw rod is sleeved with a first nut;
one end of the support leg close to the screw rod is provided with a gland;
the gland is arranged on the support leg through a plurality of screws I;
one end of the support leg, which is far away from the screw rod, is provided with a backing plate;
the backing plate is a polyurethane plate.
Optionally or preferably, the toggle clamp assembly comprises a mounting plate, a toggle clamp handle, a toggle clamp bracket, a connector, a sliding sleeve and a screw;
the elbow clamp bracket is fixed on the mounting plate through a bolt;
an elbow clamp handle is fixed at one end of the elbow clamp bracket through a pin shaft, and a sliding sleeve shell is arranged at the other end of the elbow clamp bracket;
the sliding sleeve is internally provided with threads, penetrates through the sliding sleeve shell, one end of the sliding sleeve is connected with the elbow clamp handle through the connector, and the other end of the sliding sleeve is provided with a screw rod;
and a second nut is also arranged on the screw rod.
Alternatively or preferably, the lower bracket assembly comprises a lower inner profile bar and a lower bracket mounting plate;
the lower support mounting plate is fixed at two ends of the lower internal molding rod through a lower support connecting rod;
the bottom of the lower internal-protection rod is provided with a plurality of L-shaped positioning sheets;
the L-shaped positioning pieces are back to back two by two and are arranged on the lower inner protective rod through screws.
Alternatively or preferably, the connection between the upper bracket assembly and the side bracket assembly and the connection between the side bracket assembly and the lower bracket assembly are the same.
Based on the technical scheme, the following technical effects can be generated:
the utility model provides an internal shape-preserving support for weak rigidity aircraft assembly, which is suitable for flexible butt joint of large-scale helicopter assembly. The beneficial effects of the utility model include:
(1) according to the aircraft, the toggle clamp assembly is used for clamping the cross beams at the top and the bottom of the aircraft, the skin is slightly expanded through the ejector rod assembly, the aircraft can reach a theoretical assembly pose, and therefore the assembly accuracy of the aircraft body is guaranteed;
(2) the upper support mounting plate, the side support mounting plate, the lower support mounting plate and other components are fixed on the inner shape-preserving rod through a section of connecting rod, the connecting rod is provided with a plurality of screw holes, and the screw holes can be selected to be connected with the inner shape-preserving rod according to needs, so that when other machine types are replaced, the utility model can provide accurate assembly for a new machine type only by adjustment;
(3) the utility model is arranged at one missing end of the end frame of the large helicopter body, can ensure the shape of the end part to be correct, and ensures that the skin is inserted with enough butt joint clearance, thereby ensuring that the insertion is collision-free;
(4) by using the internal shape-preserving support for weak rigidity aircraft assembly, local butt joint has no interference, uniform clearance and no stress concentration;
(5) after the process of multiple off-shelf, transferring and butt joint, the variation of the K hole position of the frame beam skeleton is less than 0.1 mm;
(6) the ejector rod assembly can expand and deviate the skin by 2mm relative to the theoretical position or restore the skin to the theoretical position;
(7) the utility model adopts a modularized and lightweight design, the whole assembly process is not more than 5 minutes, the total weight is not more than 30kg, and the rapid assembly and connection in a narrow space in an airplane section piece can realize rapid correction of the airplane.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the upper bracket assembly of the present invention;
FIG. 3 is a schematic structural view of a side pull assembly of the present invention;
FIG. 4 is a schematic structural view of the tightening unit according to the present invention;
FIG. 5 is a schematic view of the connection of the upper bracket assembly and the side bracket assembly of the present invention;
FIG. 6 is a schematic view of a side bracket assembly of the present invention;
FIG. 7 is a schematic structural view of the lower bracket assembly of the present invention;
the reference numbers in the figures are:
1-upper support assembly, 2-side support assembly, 3-lower support assembly, 4-ram assembly, 5-toggle clamp assembly, 101-upper internal retainer bar, 102-upper support mounting plate, 103-upper support connecting rod, 104-quick hitch, 201-side internal retainer bar, 202-side support mounting plate, 203-mounting plate handle, 204-handle pivot, 205-latch hook, 206-spacer, 207-positioning pin, 208-joint, 301-lower internal retainer bar, 302-lower support mounting plate, 303-lower support connecting rod, 304-L-spacer, 401-lead screw, 402-toggle, 403-nut one, 404-gland, 405-leg, 406-backing plate, 407-screw one, 501-mounting plate, 502-elbow clamp handle, 503-elbow clamp bracket, 504-connector, 505-sliding sleeve, 506-screw rod and 507-nut II.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the utility model and are not intended to limit the utility model.
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1:
as shown in fig. 1-7:
the embodiment provides a weak rigidity aircraft assembly is with interior guarantor's type support, including upper bracket component 1, side bracket component 2, lower part bracket component 3, ejector pin subassembly 4 and toggle clamp subassembly 5, wherein:
the lower bracket component 3 is arranged on a frame on the ground of the airplane;
the number of the side bracket assemblies 2 is two, the side bracket assemblies are arranged on two sides of the airplane and are connected with the lower bracket assembly 3 through bracket mounting plates;
the upper support assembly 1 is arranged at the top in the airplane, and two ends of the upper support assembly 1 are connected with the two side support assemblies 2 through support mounting plates;
the number of the ejector rod assemblies 4 is eleven, the upper support assembly 1 is provided with three, the side support assemblies 2 are provided with three, and the lower support assembly 3 is provided with three;
the number of the toggle clamp assemblies 5 is eight, and four toggle clamp assemblies 5 are arranged on the upper support assembly 1 and the lower support assembly 3;
the position of each toggle clamp assembly 5 is adjustable, and a screw rod 506 on each toggle clamp assembly 5 faces a cross beam of the machine body;
each side bracket assembly 2 is also provided with a positioning sheet 206;
the positioning plate 206 is further provided with a positioning pin 207.
In this embodiment, the upper bracket assembly 1 includes an upper inner shape-retaining bar 101 and an upper bracket mounting plate 102;
the upper bracket mounting plate 102 is fixed at both ends of the upper inner shape-preserving rod 101 through an upper bracket connecting rod 103;
a plurality of screw holes are formed in the upper bracket connecting rod 103;
the upper bracket connecting rod 103 extends into the upper inner shape-preserving rod 101 and is in screw connection with the upper inner shape-preserving rod 101; the extension length of the upper bracket connecting rod 103 is adjustable;
each side bracket assembly 2 comprises three side internal holding rods 201;
the upper end and the lower end of the side bracket assembly 2 are both provided with side bracket mounting plates 202;
the side internal shape-retaining rod 201 and the side internal shape-retaining rod 201, and the side internal shape-retaining rod 201 and the side bracket mounting plate 202 are connected by a joint 208.
In this embodiment, the upper bracket mounting plate 102 is in an "Contraband" shape, and the quick hooks 104 are disposed on both sides of the upper bracket mounting plate 102;
the side bracket mounting plate 202 is also in an Contraband-shaped structure and is clamped outside the upper bracket mounting plate 102;
mounting plate handles 203 are arranged on two sides of the side bracket mounting plate 202;
a latch hook 205 is arranged on the mounting plate handle 203;
the mounting plate handle 203 can rotate along a handle rotating shaft 204; the latch hook 205 is engageable with the quick hitch 104.
In this embodiment, the ram assembly 4 includes a screw 401, a lever 402, a first nut 403, a gland 404, a foot 405, and a pad 406;
the screw rod 401 is a threaded rod, one end of the screw rod is fixed on the supporting leg 405, and the other end of the screw rod is provided with a pull rod 402;
the trigger 402 penetrates through the screw rod 401 and is perpendicular to the screw rod 401;
a first nut 403 is sleeved on the screw rod 401;
a gland 404 is arranged at one end of the supporting leg 405 close to the screw rod 401;
the gland 404 is mounted on the foot 405 by a plurality of screws 407;
a backing plate 406 is arranged at one end of the supporting leg 405 far away from the screw rod 401;
the backing plate 406 is a polyurethane plate;
the ram assembly 4 bears against the skin of the aircraft to enable the skin to expand outwardly or to return to its theoretical configuration.
In this embodiment, the toggle clamp assembly 5 comprises a mounting plate 501, a toggle clamp handle 502, a toggle clamp bracket 503, a connector 504, a sliding sleeve 505, and a screw 506;
the elbow clamp bracket 503 is fixed on the mounting plate 501 through bolts;
an elbow clamp handle 502 is fixed at one end of the elbow clamp bracket 503 through a pin shaft, and a sliding sleeve shell is arranged at the other end;
the sliding sleeve 505 is internally provided with threads, the sliding sleeve 505 penetrates through the sliding sleeve shell, one end of the sliding sleeve is connected with the elbow clamp handle 502 through the connector 504, and the other end of the sliding sleeve is provided with a screw 506;
and a second nut 507 is further arranged on the screw 506.
In this embodiment, the lower bracket assembly 3 includes a lower inner shape-retaining rod 301 and a lower bracket mounting plate 302;
the lower bracket mounting plate 302 is fixed at two ends of the lower inner shape-preserving rod 301 through a lower bracket connecting rod 303;
the bottom of the lower inner shape-preserving rod 301 is provided with a plurality of L-shaped positioning pieces 304;
the L-shaped positioning pieces 304 are opposite to each other in pairs and are installed on the lower inner protective rod 301 through screws.
In this embodiment, the connection between the upper rack assembly 1 and the side rack assembly 2 and the connection between the side rack assembly 2 and the lower rack assembly 3 are the same.
The embodiment has the following advantages:
(1) in the embodiment, the toggle clamp assembly 5 is used for clamping the cross beams at the top and the bottom of the airplane, the skin is slightly expanded through the ejector rod assembly 4, the airplane can reach a theoretical assembly pose, and the assembly accuracy of the airplane body is ensured;
(2) in the embodiment, the upper support mounting plate 102, the side support mounting plate 202, the lower support mounting plate 302 and other components are all fixed on the inner shape-preserving rod through a section of connecting rod, the connecting rod is provided with a plurality of screw holes, and the screw holes can be selected to be connected with the inner shape-preserving rod according to needs, so that when other machine types are replaced, the utility model can provide accurate assembly for a new machine type only by adjustment;
(3) the embodiment is arranged at the missing end of the end frame of the body of the large helicopter, can ensure the shape of the end part to be correct, and ensures that the skin is inserted with enough butt joint clearance, thereby ensuring that the insertion is collision-free;
(4) by using the internal shape-preserving bracket for weak rigidity aircraft assembly provided by the embodiment, the butt joint part has no interference, the gap is uniform, and no stress concentration exists;
(5) in the embodiment, after a plurality of processes of putting off the frame, transferring and butting, the position variation of the K hole of the frame beam skeleton is less than 0.1 mm;
(6) the ejector rod assembly of the embodiment can enable the skin to expand and deviate by 2mm relative to the theoretical position or restore to the theoretical position;
(7) the embodiment adopts modularization and lightweight design, the whole assembly process is not more than 5 minutes, the total weight is not more than 30kg, and the rapid assembly and connection in narrow space in the aircraft section piece can realize rapid model correction of the aircraft.
The foregoing is illustrative of the preferred embodiments of this invention, and it is to be understood that the utility model is not limited to the precise form disclosed herein and that various other combinations, modifications, and environments may be resorted to, falling within the scope of the concept as disclosed herein, either as described above or as apparent to those skilled in the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the utility model as defined by the appended claims.
Claims (7)
1. The utility model provides a weak rigidity aircraft assembly is with keeping type support which characterized in that: including upper portion bracket component (1), side bracket component (2), lower part bracket component (3), ejector pin subassembly (4) and toggle clamp subassembly (5), wherein:
the lower support assembly (3) is arranged on a frame of the ground of the airplane;
the number of the side bracket assemblies (2) is two, the side bracket assemblies are arranged on two sides of the airplane and are connected with the lower bracket assembly (3) through bracket mounting plates;
the upper support assembly (1) is arranged at the top in the airplane, and two ends of the upper support assembly (1) are connected with the two side support assemblies (2) through support mounting plates;
the number of the ejector rod assemblies (4) is multiple, and the ejector rod assemblies (4) are arranged on the upper support assembly (1), the side support assembly (2) and the lower support assembly (3);
the number of the toggle clamp assemblies (5) is multiple, and the toggle clamp assemblies (5) are arranged on the upper support assembly (1) and the lower support assembly (3);
each side bracket component (2) is also provided with a positioning sheet (206); the positioning plate (206) is also provided with a positioning pin (207).
2. The interior support of claim 1, wherein: the upper bracket assembly (1) comprises an upper inner shape-retaining rod (101) and an upper bracket mounting plate (102); the upper support mounting plate (102) is fixed at two ends of the upper inner shape-keeping rod (101) through an upper support connecting rod (103); the upper support connecting rod (103) is provided with a plurality of screw holes, and the upper support connecting rod (103) extends into the upper inner shape-preserving rod (101) and is in screw connection with the upper inner shape-preserving rod (101);
each side bracket assembly (2) comprises three side internal shape-retaining rods (201); the upper end and the lower end of the side bracket component (2) are respectively provided with a side bracket mounting plate (202); the side internal protective rod (201) is connected with the side internal protective rod (201), and the side internal protective rod (201) is connected with the side bracket mounting plate (202) through a joint (208).
3. The interior support of claim 2, wherein: the upper support mounting plate (102) is in an Contraband-shaped structure, and the two sides of the upper support mounting plate (102) are provided with quick hooks (104); the side bracket mounting plate (202) is also in an Contraband-shaped structure and is clamped outside the upper bracket mounting plate (102); mounting plate handles (203) are arranged on two sides of the side bracket mounting plate (202); a latch hook (205) is arranged on the mounting plate handle (203); the mounting plate handle (203) can rotate along a handle rotating shaft (204); the lock hook (205) can be matched with the quick hook (104).
4. The interior support of claim 1, wherein: the ejector rod assembly (4) comprises a screw rod (401), a pull rod (402), a first nut (403), a gland (404), a support leg (405) and a base plate (406); the screw rod (401) is a threaded rod, one end of the screw rod is fixed on the supporting leg (405), and the other end of the screw rod is provided with a pull rod (402); the pull rod (402) penetrates through the screw rod (401) and is perpendicular to the screw rod (401); a first nut (403) is sleeved on the screw rod (401); a gland (404) is arranged at one end of the supporting leg (405) close to the screw rod (401); the gland (404) is arranged on the supporting foot (405) through a plurality of screws I (407); a backing plate (406) is arranged at one end, away from the screw rod (401), of the supporting leg (405); the backing plate (406) is a polyurethane plate.
5. The interior support of claim 1, wherein: the elbow clamp assembly (5) comprises a mounting plate (501), an elbow clamp handle (502), an elbow clamp bracket (503), a connector (504), a sliding sleeve (505) and a screw rod (506);
the elbow clamp bracket (503) is fixed on the mounting plate (501) through bolts; an elbow clamp handle (502) is fixed at one end of the elbow clamp bracket (503) through a pin shaft, and a sliding sleeve shell is arranged at the other end of the elbow clamp bracket; threads are arranged in the sliding sleeve (505), the sliding sleeve (505) penetrates through the sliding sleeve shell, one end of the sliding sleeve is connected with the elbow clamp handle (502) through the connector (504), and the other end of the sliding sleeve is provided with a screw rod (506); and a second nut (507) is also arranged on the screw rod (506).
6. The interior support of claim 1, wherein: the lower bracket assembly (3) comprises a lower inner shape-retaining rod (301) and a lower bracket mounting plate (302); the lower support mounting plate (302) is fixed at two ends of the lower inner shape-keeping rod (301) through a lower support connecting rod (303); the bottom of the lower internal shape-keeping rod (301) is provided with a plurality of L-shaped positioning pieces (304); the L-shaped positioning pieces (304) are opposite to each other in pairs and are installed on the lower inner protective rod (301) through screws.
7. The interior support of claim 1, wherein: the connection modes between the upper support assembly (1) and the side support assembly (2) and between the side support assembly (2) and the lower support assembly (3) are the same.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202220227332.3U CN216546788U (en) | 2022-01-27 | 2022-01-27 | Interior guarantor's type support is used in assembly of weak rigidity aircraft |
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| CN202220227332.3U CN216546788U (en) | 2022-01-27 | 2022-01-27 | Interior guarantor's type support is used in assembly of weak rigidity aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275185A (en) * | 2022-01-27 | 2022-04-05 | 成都九系机器人科技有限公司 | Interior type support for weak rigidity aircraft assembly |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275185A (en) * | 2022-01-27 | 2022-04-05 | 成都九系机器人科技有限公司 | Interior type support for weak rigidity aircraft assembly |
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