CN117602091A - Composite unmanned aerial vehicle body assembly frame and assembly method thereof - Google Patents
Composite unmanned aerial vehicle body assembly frame and assembly method thereof Download PDFInfo
- Publication number
- CN117602091A CN117602091A CN202311621149.7A CN202311621149A CN117602091A CN 117602091 A CN117602091 A CN 117602091A CN 202311621149 A CN202311621149 A CN 202311621149A CN 117602091 A CN117602091 A CN 117602091A
- Authority
- CN
- China
- Prior art keywords
- positioning
- module
- skin
- pressurizing
- inner beam
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention provides a composite material unmanned aerial vehicle fuselage assembly frame which comprises a base, a lower skin positioning module, a bulkhead positioning module, an upper skin positioning and pressurizing module, an inner beam positioning module and an inner beam positioning and pressurizing module, wherein the lower skin positioning module and the bulkhead positioning module are distributed on the base, the upper skin positioning and pressurizing module and the inner beam positioning and pressurizing module are positioned at the upper part, the inner beam positioning module is used independently, and a reference hole and a positioning module mounting reference surface are further formed on the base. When the machine body is assembled, the internal beam is glued outside the frame, and then the skin, the frame and the beam assembly are glued integrally, so that the gluing gap of the machine body is ensured by controlling the gluing gap of the skin and each positioning module. The invention solves the technical problems of poor adaptability, low assembly precision, slow production rhythm and untimely development iteration response of the existing assembly method.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a composite material unmanned aerial vehicle body assembly type frame and an assembly method thereof.
Background
The assembly of the composite unmanned aerial vehicle body is an important link in the assembly of the whole structure, the assembly profile directly influences the flight quality of the whole structure, and the assembly period occupies a larger specific gravity of the assembly period of the whole structure. At present, more and more unmanned aerial vehicle wings and fuselages made of composite materials adopt integral design structures, the original fuselages and wings are manufactured as independent components, and a mode of closing and assembling is not suitable any more. Therefore, there is an urgent need for an unmanned aerial vehicle body assembly method, which needs to satisfy:
1) The device is suitable for the integration of the wing bodies and even the fuselage structure of the flying wing layout, and can be suitable for the existing single fuselage structure;
2) Ensuring the profile of the assembly profile of the fuselage and the wing;
3) The device can meet the current requirement of short assembly period, and is convenient for mass production;
4) The mold frame needs to be capable of rapidly adapting to design change iteration in the development process and has a certain flexibility function.
Through the search of the prior art, the invention patent of the patent document CN213832083U discloses a manufacturing method of a co-cured composite material unmanned aerial vehicle body, wherein a skin, a bulkhead and a truss are integrally formed by co-curing. The method has thermal stress deformation after co-curing molding, and has adverse effect on the profile of the machine body; the method is only suitable for a cylindrical single-body structure, and needs to be folded and butted with the wing part for the second time; if the design change occurs to the molding surface of the machine body, the change amount of the mold is large, and the rapid iteration of the product is seriously affected.
The invention is suitable for unmanned aerial vehicle with wing body fusion structure, and the fuselage and the wing are integrated when the cementing and solidification are carried out, and the secondary folding and butt joint of the wing parts are not involved.
Patent document CN206455092U discloses a helicopter tail beam skin riveting tool and a positioning clamping plate assembly thereof, the helicopter tail beam skin riveting tool comprises a base and a positioning clamping plate assembly, the positioning clamping plate assembly comprises two upright posts and a cross beam connected to the upright posts, the cross beam is provided with a spacer frame positioning plate arranged vertically, and a spacer frame to be positioned can be fixed on the spacer frame positioning plate through bolts; a side clamping plate is arranged on one side of the two upright posts opposite to each other, and a distance which is the same as the thickness of the skin is arranged between the side clamping plate and the bulkhead; an upper clamping plate and a lower clamping plate are further arranged between the two upright posts, and a space which is the same as the thickness of the skin is formed between the lower end of the upper clamping plate and the bulkhead; the upper end of the lower clamping plate and the bulkhead are provided with a distance which is the same as the thickness of the skin.
The patent document CN206455092U is a caulking type frame, not a glue-fitted type frame, and a suitable object thereof is a cabin section (revolving structure). The invention is applicable to the whole structure of the wing of the fuselage. The invention defines the positioning layout and design modes of parts such as skins, bulkhead, ribs and the like in the assembly type frame. And (3) positioning layout and tooling design modes outside the frame of the wing spar assembly. Through the transfer of the positioning reference among the positioning pieces, the cementing gap can be effectively controlled, and reworking and repairing are reduced. Meanwhile, the assembly mode in the invention has good operability and ensures the profile contour degree.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a composite material unmanned aerial vehicle body assembly type frame and an assembly method thereof.
According to the invention, the composite material unmanned aerial vehicle body assembly type frame comprises:
the device comprises a base 1, a lower skin positioning module 2, a bulkhead positioning module 3, an upper skin positioning and pressurizing module 4, an inner beam positioning module 5 and an inner beam positioning and pressurizing module 6;
the lower skin positioning module 2, the bulkhead positioning module 3, the upper skin positioning pressurizing module 4, the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are detachably connected to the base 1;
the lower skin positioning module 2 and the bulkhead positioning module 3 are distributed on the base 1, the upper skin positioning pressurizing module 4 and the inner beam positioning pressurizing module 6 are positioned above the base 1, and the inner beam positioning module 5 is used independently.
Preferably, the lower skin positioning module 2, the bulkhead positioning module 3, the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are adapted to the structures of an individual fuselage structure, a wing body fusion fuselage structure and an all-wing aircraft layout fuselage;
the lower skin positioning module 2, the bulkhead positioning module 3, the upper skin positioning pressurizing module 4, the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are adjusted for the wing body fusion structure, the working faces of the lower skin positioning module 2 and the upper skin positioning pressurizing module 4 are attached to the wing skin of the fuselage, the working faces of the bulkhead positioning module 3 are attached to the web faces of the bulkhead, and the working faces of the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are attached to the flanging faces of the inner wing body fusion beam.
Preferably, the position of the lower skin positioning module 2 is correspondingly arranged with the positions of the fuselage bulkhead and the rib, skin positioning holes are reserved on the lower skin positioning module 2, and the mold tread is attached to the lower skin;
the working surface of the bulkhead positioning module 3 is attached to one side of the die attaching surface of the bulkhead of the machine body, and positioning is carried out by means of holes in the bulkhead;
the position of the upper skin positioning and pressurizing module 4 is correspondingly arranged with the positions of the fuselage bulkhead and the rib, skin positioning holes are reserved on the upper skin positioning and pressurizing module 4, the mold tread is attached to the upper skin, and the upper skin positioning and pressurizing module 4 is in positioning connection with the lower skin positioning module 2 or the base 1 through a guide pillar or a pin;
the internal beam positioning module 5 is used for positioning the web plates and flanging surfaces of the beam and the rib of the machine body respectively;
the internal beam positioning and pressurizing module 6 is used for positioning and pressurizing the flanging surfaces of the beams and ribs which are positioned originally, and is in positioning connection with the lower skin positioning module 2 or the base 1 through a guide pillar or a pin.
Preferably, the lower skin positioning module 2 is connected with the base 1 through a form of a guide pillar or a pin, the bulkhead positioning module 3, the upper skin positioning pressurizing module 4 and the inner beam positioning pressurizing module 6 are connected with the base 1 or the lower skin positioning module 2 through a form of a guide pillar or a pin, and the inner beam positioning module 5 is used separately.
Preferably, the base 1 is provided with a reference structure and a positioning module mounting reference surface.
Preferably, the reference structure comprises a reference hole or a reference block;
the reference structures are distributed in a cross or a square shape, and provide measurement references for the processing, checking and repairing processes of the tool.
Preferably, the glue gap is controlled by the transfer of the positioning references between the respective positioning members.
According to the composite unmanned aerial vehicle body assembling method provided by the invention, the composite unmanned aerial vehicle body assembling frame is adopted;
the internal beam of the machine body is glued outside the frame of the prior frame; then integrally gluing the skin, the frame and the beam assembly; when the machine body is assembled, the gluing gap of the machine body is ensured by controlling the gluing gap of the skin and the positioning module.
Preferably, the method specifically comprises the following steps:
step S1: the lower skin of the fuselage is placed on the lower skin positioning module 2 and positioned through a process hole;
step S2: placing a bulkhead of the fuselage on the lower skin, and positioning by using a bulkhead positioning module 3, wherein the bulkhead is glued with the lower skin at the moment;
step S3: the inner beam of the fuselage is glued by the inner beam positioning module 5 to form an inner beam assembly;
step S4: the whole inner beam assembly is placed on the lower skin, positioning and pressurizing are carried out by utilizing an inner beam positioning and pressurizing module 6, and at the moment, the inner beam assembly is glued with the lower skin;
step S5: placing the upper skin on the upper parts of the bulkhead and the inner beam assembly, and then integrally pressing and positioning by using an upper skin positioning and pressurizing module 4, and at the moment, bonding the bulkhead, the inner beam assembly, the lower skin and the upper skin;
step S6: and a whole lower frame.
Preferably, the fit clearance between the skin, the frame, the beam and the rib of the fuselage and the working surface of the composite material unmanned aerial vehicle fuselage assembly frame serving as a tool is less than or equal to 0.1mm.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention can adapt to the assembly of an independent fuselage structure, a wing body fusion structure, an all-wing aircraft layout structure and the like through the size and the contour adjustment of each module.
2. According to the invention, the inner frame and the beam take the profile surface as a transmission reference, so that the uniformity of the cementing gap can be ensured, the outer skin can control the jointing gap between each skin and the skin positioning module, and further the profile of the fuselage can be intuitively improved.
3. The internal beam component and the main body structure are synchronously glued and assembled, the assembly rhythm is strong, the pulsating assembly is facilitated, the assembly efficiency is improved, the state change of a design party can be responded conveniently and rapidly, and only the corresponding module is required to be changed or replaced.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of the main structure of a composite unmanned aerial vehicle fuselage assembly frame of the present invention;
FIG. 2 is a schematic view of the structure of an internal beam positioning module of the composite unmanned aerial vehicle fuselage assembly frame of the present invention;
fig. 3 is a reference hole feature diagram of the composite unmanned aerial vehicle fuselage assembly frame of the present invention.
The figure shows:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
As shown in fig. 1 to 3, in the embodiment of the present invention, a fuselage of a wing-body fusion structure is manufactured, and is divided into an upper skin, a lower skin, a plurality of internal formers, and an internal stiffening beam assembly in the entire span direction of the wing fuselage section. The overall profile of the fuselage wing is required to be within 0.5 mm.
According to the invention, the composite material unmanned aerial vehicle body assembly type frame comprises: the device comprises a base 1, a lower skin positioning module 2, a bulkhead positioning module 3, an upper skin positioning and pressurizing module 4, an inner beam positioning module 5 and an inner beam positioning and pressurizing module 6; the lower skin positioning module 2, the bulkhead positioning module 3, the upper skin positioning pressurizing module 4, the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are detachably connected to the base 1.
The lower skin positioning module 2 and the bulkhead positioning module 3 are distributed on the base 1, the upper skin positioning pressurizing module 4 and the inner beam positioning pressurizing module 6 are positioned on the upper portion, the inner beam positioning module 5 is used independently, and the base 1 is also provided with a reference hole and a positioning module mounting reference surface.
The lower skin positioning module 2, the bulkhead positioning module 3, the inner beam positioning module 5, the inner beam positioning pressurizing module 6 and other positioning modules can be structurally adjusted, and are suitable for the structures such as an independent fuselage structure, a wing body fusion fuselage structure, an all-wing aircraft layout fuselage and the like. The number of the reference holes is 4, the reference holes are distributed in a cross or a square shape, measurement references are provided for the processing, inspection, repair and other processes of the tool, and the reference holes can be changed into reference blocks or the number of the reference blocks to be increased or decreased under specific conditions, so that the same measurement effect is achieved.
The position of the lower skin positioning module 2 is correspondingly arranged with the positions of the fuselage bulkhead and the rib, skin positioning holes are reserved on the lower skin positioning module 2, and the mold tread is attached to the lower skin.
The working surface of the bulkhead positioning module 3 is attached to one side of the die attaching surface of the bulkhead, and positioning is carried out by means of holes in the bulkhead.
The position of the upper skin positioning and pressurizing module 4 is correspondingly arranged with the positions of the fuselage bulkhead and the rib, skin positioning holes are reserved on the upper skin positioning and pressurizing module 4, the mold tread is attached to the upper skin, and the upper skin positioning and pressurizing module 4 is in positioning connection with the lower skin positioning module 2 or the base 1 through a guide pillar or a pin.
The inner beam positioning module 5 respectively positions the web plates and flanging surfaces of the beams and the ribs.
The internal beam positioning and pressurizing module 6 is used for positioning and pressurizing the flanging surfaces of the beams and ribs which are positioned originally, and is in positioning connection with the lower skin positioning module 2 or the base 1 through a guide pillar or a pin.
The lower skin positioning module 2 is connected with the base 1 through a guide pillar or a pin, the bulkhead positioning module 3, the upper skin positioning pressurizing module 4 and the inner beam positioning pressurizing module 6 are connected with the base 1 or the lower skin positioning module 2 through the guide pillar or the pin, and the inner beam positioning module 5 is used independently.
The base 1 is formed by welding or casting 45# steel plates, steel blocks and steel pipes, and the rest of the base 1, the lower skin positioning module 2, the bulkhead positioning module 3, the upper skin positioning and pressurizing module 4, the inner beam positioning module 5, the inner beam positioning and pressurizing module 6 and other positioning modules are formed by welding or casting 6061 aluminum plates and aluminum pipes, and the positioning holes are inlaid with wear-resistant steel sleeves. The tool needs to be annealed to remove internal stress before finishing the last time, so that the machining precision is ensured.
The lower skin positioning module 2, the bulkhead positioning module 3, the upper skin positioning pressurizing module 4, the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are adjusted for the wing body fusion structure, the working faces of the lower skin positioning module 2 and the upper skin positioning pressurizing module 4 are attached to the wing skin of the fuselage, the working faces of the bulkhead positioning module 3 are attached to the web faces of the bulkhead, and the working faces of the inner beam positioning module 5 and the inner beam positioning pressurizing module 6 are attached to the flanging faces of the inner wing body fusion beam.
As shown in FIG. 3, the reference hole of the frame is characterized in that a small reference plane is arranged on the hole site, and the hole site is chamfered, so that the target ball is convenient to mount and fix and center.
The invention provides an assembly method of a composite unmanned aerial vehicle, which adopts the form of firstly bonding an inner beam outside a frame and then bonding a skin, a frame and a beam assembly integrally. Specifically, when the machine body is assembled, the internal beam is glued outside the frame, and then the skin, the frame and the beam assembly are glued integrally, so that the gluing gap of the machine body is ensured by controlling the gluing gap of the skin and each positioning module. The method solves the technical problems of poor adaptability, low assembly precision, slow production rhythm and untimely development iteration response of the existing assembly method.
The method specifically comprises the following steps:
(1) The lower skin is placed on the lower skin positioning module 2 and positioned through a process hole;
(2) Placing the bulkhead on the lower skin, and positioning by using a bulkhead positioning module 3, wherein the bulkhead is glued with the lower skin;
(3) The inner beam is glued first by means of the inner beam positioning module 5 to form an assembly. The beams of the internal beam assembly (without the aid of other frames, can be parallel to the above steps)
(4) The whole internal beam assembly is placed on the lower skin, positioning and pressurizing are carried out by utilizing an internal beam positioning and pressurizing module 6, and at the moment, the internal beam assembly is glued with the lower skin;
(5) Placing the upper skin on the upper parts of the bulkhead and the inner beam assembly, and then integrally pressing and positioning by using an upper skin positioning and pressurizing module 4, and at the moment, bonding the bulkhead, the inner beam assembly, the lower skin and the upper skin;
(6) And a whole lower frame.
The joint clearance between the skin, the frame, the beam, the rib and the working face of the tooling is controlled to be less than or equal to 0.1mm, so that the requirement of the integral profile of the fuselage wing of 0.5mm is met.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. A composite unmanned aerial vehicle fuselage assembly jig, comprising:
the device comprises a base (1), a lower skin positioning module (2), a bulkhead positioning module (3), an upper skin positioning and pressurizing module (4), an inner beam positioning module (5) and an inner beam positioning and pressurizing module (6);
the lower skin positioning module (2), the bulkhead positioning module (3), the upper skin positioning and pressurizing module (4), the inner beam positioning module (5) and the inner beam positioning and pressurizing module (6) are detachably connected to the base (1);
the lower skin positioning modules (2) and the bulkhead positioning modules (3) are distributed on the base (1), the upper skin positioning pressurizing modules (4) and the inner beam positioning pressurizing modules (6) are located above the base (1), and the inner beam positioning modules (5) are used independently.
2. The composite unmanned aerial vehicle fuselage assembly frame of claim 1, wherein the lower skin positioning module (2), the bulkhead positioning module (3), the inner beam positioning module (5), the inner beam positioning pressurizing module (6) are adapted to the individual fuselage structure, the wing body fusion fuselage structure, and the structure of the flying wing layout fuselage;
the lower skin positioning module (2), the bulkhead positioning module (3), the upper skin positioning pressurizing module (4), the inner beam positioning module (5) and the inner beam positioning pressurizing module (6) are adjusted for the wing body fusion structure, the working face of the lower skin positioning module (2), the upper skin positioning pressurizing module (4) is attached to the wing skin of the aircraft body, the working face of the bulkhead positioning module (3) is attached to the web face of the bulkhead, and the working faces of the inner beam positioning module (5) and the inner beam positioning pressurizing module (6) are attached to the flanging face of the inner wing body fusion beam.
3. The composite material unmanned aerial vehicle fuselage assembly type frame according to claim 2, wherein the position of the lower skin positioning module (2) is arranged corresponding to the positions of the fuselage bulkhead and the rib, skin positioning holes are reserved on the lower skin positioning module (2), and the mold tread is attached to the lower skin;
the working surface of the bulkhead positioning module (3) is attached to one side of the die attaching surface of the bulkhead of the machine body, and positioning is carried out by means of holes in the bulkhead;
the position of the upper skin positioning and pressurizing module (4) is correspondingly arranged with the positions of the frame and the rib of the fuselage, skin positioning holes are reserved on the upper skin positioning and pressurizing module (4), the tread of the mould is attached to the upper skin, and the upper skin positioning and pressurizing module (4) is in positioning connection with the lower skin positioning module (2) or the base (1) through a guide post or a pin;
the inner beam positioning module (5) is used for respectively positioning the web plates and flanging surfaces of the beam and the rib of the machine body;
the internal beam positioning and pressurizing module (6) is used for positioning and pressurizing the flanging surfaces of the originally positioned beams and ribs and is in positioning connection with the lower skin positioning module (2) or the base (1) through a guide pillar or a pin.
4. The composite unmanned aerial vehicle fuselage assembly jig according to claim 1, wherein the lower skin positioning module (2) is connected with the base (1) by means of a guide post or pin, the former positioning module (3), the upper skin positioning pressurizing module (4), the inner beam positioning pressurizing module (6) are connected with the base (1) or the lower skin positioning module (2) by means of a guide post or pin, and the inner beam positioning module (5) is used separately.
5. The composite unmanned aerial vehicle fuselage assembly jig according to claim 1, wherein the base (1) is provided with a reference structure, a positioning module mounting reference surface.
6. The composite unmanned aerial vehicle fuselage assembly jig of claim 5, wherein the datum structure comprises a datum hole or datum block;
the reference structures are distributed in a cross or a square shape, and provide measurement references for the processing, checking and repairing processes of the tool.
7. The composite unmanned aerial vehicle fuselage assembly jig of claim 1, wherein the glue gap is controlled by the transfer of positioning fiducials between the individual positioning members.
8. A method for assembling a composite unmanned aerial vehicle body, characterized in that the composite unmanned aerial vehicle body assembly jig according to any one of claims 1 to 8 is used;
the internal beam of the machine body is glued outside the frame of the prior frame; then integrally gluing the skin, the frame and the beam assembly; when the machine body is assembled, the gluing gap of the machine body is ensured by controlling the gluing gap of the skin and the positioning module.
9. The method for assembling a composite unmanned aerial vehicle fuselage according to claim 8, comprising the steps of:
step S1: the lower skin of the fuselage is placed on a lower skin positioning module (2) and positioned through a process hole;
step S2: placing a bulkhead of the fuselage on the lower skin, and positioning by using a bulkhead positioning module (3), wherein the bulkhead is glued with the lower skin at the moment;
step S3: the inner beam of the machine body is glued by the inner beam positioning module (5) to form an inner beam assembly;
step S4: the whole inner beam assembly is placed on the lower skin, positioning and pressurizing are carried out by utilizing an inner beam positioning and pressurizing module (6), and at the moment, the inner beam assembly is glued with the lower skin;
step S5: placing the upper skin on the upper parts of the bulkhead and the inner beam assembly, and then integrally pressurizing and positioning by using an upper skin positioning and pressurizing module (4), and at the moment, bonding the bulkhead, the inner beam assembly, the lower skin and the upper skin;
step S6: and a whole lower frame.
10. The method for assembling the composite unmanned aerial vehicle body according to claim 8, wherein the attaching gap between the skin, the frame, the beam and the rib of the body and the working surface of the composite unmanned aerial vehicle body assembling type frame serving as a tool is controlled to be less than or equal to 0.1mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311621149.7A CN117602091A (en) | 2023-11-29 | 2023-11-29 | Composite unmanned aerial vehicle body assembly frame and assembly method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311621149.7A CN117602091A (en) | 2023-11-29 | 2023-11-29 | Composite unmanned aerial vehicle body assembly frame and assembly method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117602091A true CN117602091A (en) | 2024-02-27 |
Family
ID=89951190
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311621149.7A Pending CN117602091A (en) | 2023-11-29 | 2023-11-29 | Composite unmanned aerial vehicle body assembly frame and assembly method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117602091A (en) |
-
2023
- 2023-11-29 CN CN202311621149.7A patent/CN117602091A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3134788B1 (en) | Aircraft airframe assembly | |
| US11970289B2 (en) | Method and apparatus for producing shims | |
| CN107775200A (en) | Aluminum alloy thin plate T-joint laser welding robot-assisted welding fixture | |
| CN108557111B (en) | Coordination assembly method for unmanned fixed-wing aircraft body | |
| EP3134781B1 (en) | Airframe production | |
| EP3134782B1 (en) | Object production | |
| CN117602091A (en) | Composite unmanned aerial vehicle body assembly frame and assembly method thereof | |
| GB2526916A (en) | Aircraft airframe assembly | |
| EP3134786B1 (en) | Production of airframe components | |
| CN217598861U (en) | Integrated assembling tool for folding wing unmanned aerial vehicle body | |
| CN113212792A (en) | Aileron assembly fixture | |
| CN114013680A (en) | A kind of assembling frame of wing end rib and assembling method of wing butt mounting seat | |
| EP3134783B1 (en) | Assembly tool production | |
| CN114148541A (en) | Flexible shape-keeping device and method for horizontal assembly of wing ribs of wing box | |
| KR100271064B1 (en) | Method for manufacturing jig for composite aircraft wing and composite aircraft wing | |
| EP2937754A1 (en) | Aircraft airframe assembly | |
| CN117901428A (en) | Composite technological equipment for carbon fiber composite material skin molding and wing part assembly | |
| CN117922039A (en) | Accurate assembly method of composite material workpiece | |
| CN115847839A (en) | Method for controlling quality of frame sealing at end of large-sized bearing cylinder | |
| CN117817315A (en) | Auxiliary positioning tool for press-riveting nut and press-riveting method | |
| EP3134784A2 (en) | Machining fixture production | |
| JP2022533776A (en) | Method and apparatus for producing at least a portion of a vehicle structural frame | |
| CN119370330A (en) | An assembly jig for a large cargo drone fuselage and an assembly method thereof | |
| Hertel | Interchangeability in Modern Production: Methods Adopted in the Engineering, Tooling, Fabrication and Assembly Departments of an American Factory |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |