CN110682058A - Hole making method for large-curvature position of super-thick honeycomb sandwich structure - Google Patents
Hole making method for large-curvature position of super-thick honeycomb sandwich structure Download PDFInfo
- Publication number
- CN110682058A CN110682058A CN201910937460.XA CN201910937460A CN110682058A CN 110682058 A CN110682058 A CN 110682058A CN 201910937460 A CN201910937460 A CN 201910937460A CN 110682058 A CN110682058 A CN 110682058A
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- CN
- China
- Prior art keywords
- hole
- sandwich structure
- honeycomb sandwich
- making
- reaming
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B47/00—Constructional features of components specially designed for boring or drilling machines; Accessories therefor
- B23B47/28—Drill jigs for workpieces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B49/00—Measuring or gauging equipment on boring machines for positioning or guiding the drill; Devices for indicating failure of drills during boring; Centering devices for holes to be bored
- B23B49/02—Boring templates or bushings
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Abstract
The invention relates to the technical field of airplane assembly hole making, in particular to a hole making method at a large-curvature position of an ultra-thick honeycomb sandwich structure. The method comprises the following steps: firstly, drilling a primary hole with a certain diameter, reaming the primary hole, and finally completing hole making through reaming operation; the diameter of the initial hole is larger than or equal to 4mm, the tool consumption of each cutter in reaming operation is not more than 1mm, the tool consumption of each time of reaming operation is 0.1-0.2 mm, and final hole making is completed at least twice in reaming. The hole making method for the large-curvature position of the super-thick honeycomb sandwich structure is provided, and the hole making precision of the special object is improved.
Description
Technical Field
The invention relates to the technical field of airplane assembly hole making, in particular to a hole making method at a large-curvature position of an ultra-thick honeycomb sandwich structure.
Background
For similar structures, when the hole making quantity is large, machine tool machining or semi-automatic machining equipment is generally adopted for making holes. Under the conditions of less holes, less batches, insufficient equipment configuration, outfield repair and the like, the manual hole making is simple, efficient and low in cost, but in the manual hole making process on a large-curvature ultra-thick honeycomb sandwich structure with the thickness of more than 60mm, the faults of aperture out-of-tolerance, inclined holes, hole edge layering and the like caused by tool deflection easily occur, and the hole making quality cannot be ensured.
Disclosure of Invention
The technical problems solved by the invention are as follows: the hole making method for the large-curvature position of the super-thick honeycomb sandwich structure is provided, and the hole making precision of the special object is improved.
The technical scheme of the invention is as follows: a method for making holes at positions with large curvature of an ultra-thick honeycomb sandwich structure comprises the following steps:
firstly, drilling a primary hole with a certain diameter, reaming the primary hole, and finally completing hole making through reaming operation;
the diameter of the initial hole is larger than or equal to 4mm, the tool consumption of each cutter in reaming operation is not more than 1mm, the tool consumption of each time of reaming operation is 0.1-0.2 mm, and final hole making is completed at least twice in reaming.
Preferably, the thickness of the super-thick honeycomb sandwich structure is more than or equal to 60mm, and the super-thick honeycomb sandwich structure is suitable for various cabin doors and other members of large airplanes.
Preferably, the honeycomb sandwich structure assembly fixture is designed with a positioning surface matched with the pneumatic outer surface of the structure, so that the deformation of composite parts can be effectively controlled, and the assembly state is simulated during the assembly and hole making of the honeycomb sandwich structure.
Preferably, the accurate positioning of the product in a full-machine coordinate system can be realized by fixing the fabrication holes of the honeycomb sandwich structure with an assembly fixture.
Preferably, the assembling clamp is provided with a drilling template, the drilling template and the assembling clamp are integrally designed, the position accuracy of the drilling template is ensured, and the cost is saved.
Preferably, the guide length of the drill bushing for processing is 30-40mm, and the drill bushing is matched with a drill plate for use, so that the perpendicularity of the hole diameter is ensured.
Preferably, when the thickness of the honeycomb sandwich structure is 60-80mm, the guide length of the drill bushing is 30-35 mm; when the thickness of the honeycomb sandwich structure exceeds 80mm, the guide length of the drill bushing is 35-40 mm. Too long a drill bushing can cause the cutter to be lengthened and easily break, and too short a drill bushing can cause the aperture to be deflected.
Preferably, the tool used for the preliminary hole machining is a 135 ° double-edged drill.
Preferably, the drill bit head is provided with the diamond, and the drill bit is sharp, wear-resisting, can effectively avoid the hole limit layering, and the back margin of driling helps promoting the concentricity of driling.
Preferably, the honeycomb sandwich structure needs to be naturally cooled for at least 5 minutes before each reaming operation, so that the thermal damage of the composite material is prevented, and the quality of the final hole is ensured.
Drawings
Fig. 1 is a schematic view of the honeycomb sandwich structure in practice.
Detailed Description
A manual hole making method for a large-curvature position of an ultra-thick honeycomb sandwich structure comprises the following steps:
the first step is as follows: clamping of large-curvature super-thick honeycomb sandwich structure
Aiming at the characteristics of the large-curvature and ultra-thick honeycomb sandwich structure, a special assembly fixture is designed, the fixture takes a structure pneumatic outer surface or a forming and pasting tool surface as a positioning reference surface, and is matched with a process hole in a cutting line or outside the cutting line to clamp the large-curvature and ultra-thick honeycomb sandwich structure on the assembly fixture.
The second step is that: design and manufacture of drilling template
The drill plate with the large-curvature and super-thick honeycomb sandwich structure and the positioning reference surface assembling clamp are designed and manufactured integrally.
The third step: design and manufacture of quick-change drill bushing
The guide length of the quick-change drill bushing is 30-40mm, and the quick-change drill bushing is matched with a drill plate for use. When the thickness of the honeycomb sandwich structure is 60-80mm, the guide length of the drill bushing is 30-35 mm; when the thickness of the honeycomb sandwich structure exceeds 80mm, the guide length of the drill bushing is 35-40 mm. Too long a drill bushing can cause the cutter to be lengthened and easily break, and too short a drill bushing can cause the aperture to be deflected.
The fourth step: selection of initial hole cutter
Aiming at the problem that an operator is labored in the feeding process when drilling a primary hole on a large-curvature super-thick honeycomb sandwich structure, a 135-degree double-blade zone is used for coating/embedding a diamond drill bit to make a hole, the diamond coating/embedding diamond drill bit is sharp, the layering of the hole edge can be effectively avoided, and the blade zone after drilling is beneficial to improving the concentricity of the drilled hole.
The fifth step: drilling a primary hole
The diameter of the initial hole cutter is more than or equal to 4mm, and the cutter can be effectively prevented from deflecting and breaking in the hole making process.
And a sixth step: cleaning the excess;
the seventh step: reaming operation
The reaming consumption of each cutter is required to be less than or equal to 1mm, and the diameter of the reaming final hole is equal to the diameter of the reaming final hole, namely-0.4 mm. And (4) cleaning the excess after each reaming operation is finished, cooling for 10 minutes after the last reaming operation is finished, and then performing the next operation.
Eighth step: reaming operation
Reaming operation is finished at least 2 times, the reaming cutting consumption is 0.1-0.2 mm/time, reaming is carried out for the last time by using a reamer with the working diameter being the final hole diameter, excess is cleaned after each reaming operation is finished, and the workpiece is cooled for 10 minutes and then the next reaming operation is carried out;
the ninth step: and (5) checking the quality of the final hole after the hole is made in the large-curvature super-thick honeycomb sandwich structure.
The invention can ensure the quality of the final hole of the manual hole making of the large-curvature super-thick honeycomb sandwich structure. The problems of aperture damage, aperture deflection and the like after hole making are solved by analyzing from the process flow; the analysis from the process operation angle greatly improves the production efficiency, avoids the fault repair of the hole with over-poor quality, and saves the labor cost and the period; the method has the advantages that the safety performance of the airplane is analyzed, the failure rate of manual hole making is reduced, and the service life of the structural part is ensured. The invention is suitable for manual hole making operation of similar honeycomb sandwich structures of various machine types.
Examples
A composite panel of a cabin door in a main landing gear of a certain type is shown in a schematic structure in figure 1, and a phi 8H8mm fastener connecting hole is reamed in the composite panel by a manual hole making method. The total thickness of the composite panel is 63mm, wherein the thickness of the laminated board 1 is 1mm, the thickness of the honeycomb 2 is 20mm, the thickness of the adhesive film 3 is 0.5mm, the thickness of the honeycomb 4 is 20mm, the thickness of the adhesive film 5 is 0.5mm, the thickness of the honeycomb 6 is 20mm, and the thickness of the laminated board 7 is 1 mm.
The first step is as follows: clamping of composite panel of inner cabin door of main undercarriage
And (3) taking the pneumatic outer surface of the composite panel of the inner door of the main landing gear as a positioning reference surface, and clamping the composite panel on the assembly tool of the inner door of the main landing gear by matching with 3 phi 10H8mm process holes outside the cutting line of the composite panel.
The second step is that: design and manufacture of drilling template
And the composite panel drill plate and the envelope plate for positioning the appearance of the composite panel on the assembly tool of the inner cabin door of the main landing gear are integrally designed and manufactured.
The third step: design and manufacture of quick-change drill bushing
The guide length of the quick-change drill bushing is 35mm, and the quick-change drill bushing is matched with a drill plate for use.
The fourth step: selection of initial hole cutter
A 135 ° double-edged diamond drill was used.
The fifth step: drilling a primary hole
The aperture of the initial hole is phi 4 mm.
And a sixth step: and (6) cleaning the excess.
The seventh step: reaming operation
The reaming tool consumption of each tool is required to be less than or equal to 1mm, the diameter phi of the reaming final hole is required to be 7.6mm, excess is cleaned after each reaming operation is finished, and the tool is cooled for 10 minutes after the last reaming operation is finished and then the next operation is carried out.
Eighth step: reaming operation
Reaming operation is finished for 3 times, reaming cutting consumption is respectively 0.2 mm/time, 0.1 mm/time and 0.1 mm/time, reaming is carried out for the last time by using a reamer with the working diameter being the final hole diameter, excess is cleaned after each reaming operation is finished, the assembly part is cooled for 10 minutes, then the next reaming operation is carried out, and the drilling of the connecting hole of the phi 8H8mm fastener is finished.
The ninth step: and inspecting the quality of the final hole of the composite material panel of the inner cabin door of the main landing gear after reaming.
Claims (10)
1. A hole making method at a position with large curvature of an ultra-thick honeycomb sandwich structure is characterized by comprising the following steps:
firstly, drilling a primary hole with a certain diameter, reaming the primary hole, and finally completing hole making through reaming operation;
the diameter of the initial hole is larger than or equal to 4mm, the tool consumption of each cutter in reaming operation is not more than 1mm, the tool consumption of each time of reaming operation is 0.1-0.2 mm, and final hole making is completed at least twice in reaming.
2. The method of claim 1, wherein the ultra-thick honeycomb sandwich structure has a thickness of 60mm or more.
3. The method for making the hole at the position with large curvature of the ultra-thick honeycomb sandwich structure according to claim 1, wherein the used honeycomb sandwich structure assembling jig is designed with a positioning surface matched with the pneumatic outer surface of the structure.
4. The method for making the hole at the position with large curvature of the super-thick honeycomb sandwich structure according to claim 3, wherein the hole is fixed with an assembly fixture through a fabrication hole of the honeycomb sandwich structure.
5. The method for making the hole at the position with large curvature of the ultra-thick honeycomb sandwich structure according to claim 3, wherein a drill plate is designed on the assembling fixture, and the drill plate and the assembling fixture are integrally designed.
6. The method for making the hole at the position with large curvature of the ultra-thick honeycomb sandwich structure according to claim 1, wherein the guide length of the processing drill sleeve is 30-40 mm.
7. The method for making the hole at the position with large curvature of the super-thick honeycomb sandwich structure according to claim 6, wherein when the thickness of the honeycomb sandwich structure is 60-80mm, the guide length of a drill bushing is 30-35 mm; when the thickness of the honeycomb sandwich structure exceeds 80mm, the guide length of the drill bushing is 35-40 mm.
8. The method for making the hole at the position with large curvature of the super-thick honeycomb sandwich structure according to claim 1, wherein a cutter used for primary hole machining is a 135-degree double-edged drill.
9. The method of claim 7, wherein the drill head is provided with diamond.
10. The method of claim 1, wherein the honeycomb sandwich structure is allowed to cool naturally for at least 5 minutes before each reaming operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910937460.XA CN110682058A (en) | 2019-09-29 | 2019-09-29 | Hole making method for large-curvature position of super-thick honeycomb sandwich structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910937460.XA CN110682058A (en) | 2019-09-29 | 2019-09-29 | Hole making method for large-curvature position of super-thick honeycomb sandwich structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110682058A true CN110682058A (en) | 2020-01-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910937460.XA Pending CN110682058A (en) | 2019-09-29 | 2019-09-29 | Hole making method for large-curvature position of super-thick honeycomb sandwich structure |
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| Country | Link |
|---|---|
| CN (1) | CN110682058A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203484706U (en) * | 2013-09-12 | 2014-03-19 | 天津起重设备有限公司 | Motor brake seat drilling tool |
| CN104259503A (en) * | 2014-08-26 | 2015-01-07 | 中国直升机设计研究所 | Large cellular board machining method |
| CN105364237A (en) * | 2015-11-20 | 2016-03-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for controlling honeycomb size of thin-walled honeycomb part |
| CN105666039A (en) * | 2016-03-25 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Quality guarantee method for manually reamed end hole of steel-aluminum interlayer piece |
-
2019
- 2019-09-29 CN CN201910937460.XA patent/CN110682058A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203484706U (en) * | 2013-09-12 | 2014-03-19 | 天津起重设备有限公司 | Motor brake seat drilling tool |
| CN104259503A (en) * | 2014-08-26 | 2015-01-07 | 中国直升机设计研究所 | Large cellular board machining method |
| CN105364237A (en) * | 2015-11-20 | 2016-03-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for controlling honeycomb size of thin-walled honeycomb part |
| CN105666039A (en) * | 2016-03-25 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Quality guarantee method for manually reamed end hole of steel-aluminum interlayer piece |
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Application publication date: 20200114 |