CN104386263A - Splicing and repairing method of Z-shaped stringer on airplane - Google Patents
Splicing and repairing method of Z-shaped stringer on airplane Download PDFInfo
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- CN104386263A CN104386263A CN201410633843.5A CN201410633843A CN104386263A CN 104386263 A CN104386263 A CN 104386263A CN 201410633843 A CN201410633843 A CN 201410633843A CN 104386263 A CN104386263 A CN 104386263A
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- long purlin
- purlin
- long
- stringer
- splice
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Abstract
The invention discloses a splicing and repairing method of a Z-shaped stringer. The method has the advantages that simplicity is realized, the implementation is easy, and the secondary damage in the airplane repairing process can be effectively reduced. The invention has the technical solution that the splicing and repairing method of the Z-shaped stringer on an airplane adopts a graphite cutting scrap collecting and nuisanceless treatment device and comprises the following steps that 1, the damage position of the stringer is judged, and when the damage is in a position at the front end of the stringer, the stringer is cut in a position with a certain distance in the backward direction; when the damage is in a position at the back end of the stringer, the stringer is cut in a position with a certain distance in the forward direction; 2, a specially-made stringer is manufactured, the specially-made stringer has no holes but has the consistent structure as the cut stringer size, and one end of the specially-made stringer is provided with a stringer splicing element; 3, fastening is carried out: when the specially-made stringer is installed, a gap being 0.03 inch and 0.06 inch is ensured between the specially-made stringer and the rest stringer.
Description
Technical field
The invention belongs to aircraft repair method and technology field, particularly relate to the jionting method of the long purlin of Z-type on a kind of aircraft.
Background technology
in production assembling in a kind of long purlin of aircraft Z-type, often occur install due to assembler or transport accidentally, the situation of badly damaged long purlin.Because the length of long purlin is very long, if integral replacing, manufacturing schedule and manufacturing cost certainly will be affected, and in the process changing long purlin, the probability damaging other framing members increases, and this in turn increases the risk in transporation by plane.
Summary of the invention
The defect that the present invention exists to overcome prior art, the object of this invention is to provide a kind of simple, easy, and the jionting method of the long purlin of the Z-type that can effectively reduce the generation of secondary damage in aircraft repair process.
The technology used in the present invention solution is the jionting method of the long purlin of Z-type on a kind of aircraft, and adopt a kind of graphite chip collection and non-pollution treatment device, its method step is as follows:
Step 1: judge the position that long purlin is damaged, damages the position reserving certain distance when long front end, purlin backward and excises long purlin; Long purlin is excised in damage reserves forward certain distance position when long rear end, purlin;
Step 2: make a special long purlin, described special long purlin is consistent with the long purlin size of cutting away and structure except atresia, and one end of described special long purlin is provided with long purlin splice;
Step 3: fastening: when installing special long purlin, special long purlin and remain the gap that will to ensure 0.03 inch ~ 0.06 inch between long purlin.
Distance in described step 1 is for add 6 fastener spacing from 0 to 1 span length's degree.
The position that described step 1 excises long purlin will be tried one's best near frame erect-position, and scope is from distance frame erect-position 4 fastener spacing to distance frame erect-position 6 fastener spacing.
The length range of the long purlin of excision is selected from 1 across adding 4 fastener spacing to 1 across adding 6 fastener spacing in described step 1.
Described step 2: the length of long purlin splice at least will ensure 4, every side fastener length, the length of totally 8 fasteners at least.
Due to inconsistent at the arrangement pitch of fuselage diverse location place fastener, so all want the on-the-spot length measuring actual needs when determining splice length at every turn.
Long purlin splice described in described step 2, when selecting long purlin splice, when distance below the covering crimp of former long purlin below free crimp is greater than the distance above the covering crimp of long purlin above free crimp, then the section bar consistent with former long purlin section bar is used to do long purlin splice; When distance below the covering crimp of former long purlin below free crimp to be less than or equal to above the covering crimp of long purlin to distance above free crimp, then select stile thickness will equal former long purlin thickness or the section bar that is greater than a grade does long purlin splice.
The fastener selecting former long purlin to adopt in described step 3 in the covering crimp position of long purlin splice carries out fastening, and described fastener is at least 8.
Compared with prior art, the beneficial effect that the present invention has is: placing under repair to the long purlin of Z-type on aircraft by making special long purlin, making to change in the process of long purlin, and the probability damaging other framing members reduces, and reduces the risk in transporation by plane simultaneously; By choosing the position of excising long purlin and length makes the long purlin after repairing have the high advantage of structural strength.
accompanying drawing explanation
Fig. 1 is the schematic diagram of long purlin splicing;
Fig. 2 is A-A section clickwise 90 ° of schematic diagrams in Fig. 1.
In figure:
1, special long purlin, 2, long purlin splice, 3, former long purlin remainder, 4, covering crimp fastener, 5, free crimp, 6, covering crimp, 7, stile, 8, chamfering, 9, frame erect-position, 10, stile fastener.
Detailed description of the invention
Embodiment 1:
As Fig. 1 and Fig. 2 shown in: a kind of jionting method of the long purlin of Z-type on aircraft, adopt a kind of graphite chip collection and non-pollution treatment device, its method step is as follows:
Step 1: judge the position that long purlin is damaged, damages when long front end, purlin, reserves the position that 0 to 1 span length's degree adds the distance of 6 fastener spacing backward, excises long purlin; Damage, when long rear end, purlin, reserves forward the position that 0 to 1 span length's degree adds the distance of 6 fastener spacing, excises long purlin;
Step 2: make a special long purlin, described special long purlin is consistent with the long purlin size of cutting away and structure except atresia, and one end of described special long purlin is provided with long purlin splice; The long purlin of excision is the shortest is span length's degree.One across the distance referred between adjacent two frame erect-positions.Why excise span length's degree from the viewpoint of two, if the length that the first excises long purlin be less than one across, then join domain can be caused too short, affect the transmission of load; If two to excise the length of long purlin long for it, then can cause larger difficulty to removing and installing of long purlin, sometimes even cannot complete.Therefore, the length range selecting the long purlin of excision is all across adding 4 fastener spacing to one across adding 6 fastener spacing from one.
Excision in the middle of the 5th, 6 rivets after frame erect-position in the present embodiment, why not selecting to cut in the middle of the 4th, 5 rivets, is in order to avoid long purlin splice is interfered with frame when mounted.Certainly, if when splice can not be interfered with frame certainly, can cut in the middle of the 4th, 5 rivet after frame erect-position
Step 3: fastening: when installing special long purlin, special long purlin and to remain between long purlin be the gap of 0.06 inch.
The length range of the long purlin of excision is selected from 1 across adding 4 fastener spacing to 1 across adding 6 fastener spacing in described step 1.
Described step 2: the length of long purlin splice will ensure 4, every side fastener length, the length of totally 8 fasteners.
Due to inconsistent at the arrangement pitch of fuselage diverse location place fastener, so all want the on-the-spot length measuring actual needs when determining splice length at every turn.
Long purlin splice described in step 2, when selecting long purlin splice, when distance below the covering crimp of former long purlin below free crimp is greater than the distance above the covering crimp of long purlin above free crimp, then the section bar consistent with former long purlin section bar is used to do long purlin splice; When distance below the covering crimp of former long purlin below free crimp to be less than or equal to above the covering crimp of long purlin to distance above free crimp, then select stile thickness will equal former long purlin thickness or the section bar that is greater than a grade does long purlin splice.
The fastener selecting former long purlin to adopt in described step 3 in the covering crimp position of long purlin splice carries out fastening, and the fastener of described long purlin splice stile is 8 No. 5 raised-head rivets or No. 5 plush copper high locked bolts.
More than show and describe groundwork of the present invention, principal character and advantage of the present invention.The technical personnel of the industry should be understood; the present invention is not restricted to the described embodiments; what describe in above-described embodiment and specification sheets just illustrates principle of the present invention; the present invention also has various changes and modifications without departing from the spirit and scope of the present invention, and these changes and improvements all fall in the claimed scope of the invention.Application claims protection domain is defined by appending claims and equivalent thereof.
Claims (8)
1. the jionting method of the long purlin of Z-type on aircraft, is characterized in that: adopt a kind of graphite chip collection and non-pollution treatment device, its method step is as follows:
Step 1: judge the position that long purlin is damaged, damages the position reserving certain distance when long front end, purlin backward and excises long purlin; Long purlin is excised in damage reserves forward certain distance position when long rear end, purlin;
Step 2: make a special long purlin, described special long purlin is consistent with the long purlin size of cutting away and structure except atresia, and one end of described special long purlin is provided with long purlin splice;
Step 3: fastening: when installing special long purlin, special long purlin and remain the gap that will to ensure 0.03 inch ~ 0.06 inch between long purlin.
2. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 1, is characterized in that: the distance in described step 1 is for add 6 fastener spacing from 0 to 1 span length's degree.
3. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 1 and 2, it is characterized in that: the position that described step 1 excises long purlin will be tried one's best near frame erect-position, and scope is from distance frame erect-position 4 fastener spacing to distance frame erect-position 6 fastener spacing.
4. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 1, is characterized in that: select the length range of the long purlin of excision in described step 1 from 1 across adding 4 fastener spacing to 1 across adding 6 fastener spacing.
5. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 1, is characterized in that: described step 2: the length of long purlin splice at least will ensure 4, every side fastener length, the length of 8 fasteners at least totally.
6. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 5, it is characterized in that: due to inconsistent at the arrangement pitch of fuselage diverse location place fastener, so all want the on-the-spot length measuring actual needs when determining splice length at every turn.
7. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 1, it is characterized in that: the long purlin splice described in step 2, when selecting long purlin splice, when distance below the covering crimp of former long purlin below free crimp is greater than the distance above the covering crimp of long purlin above free crimp, then the section bar consistent with former long purlin section bar is used to do long purlin splice; When distance below the covering crimp of former long purlin below free crimp to be less than or equal to above the covering crimp of long purlin to distance above free crimp, then select stile thickness will equal former long purlin thickness or the section bar that is greater than a grade does long purlin splice.
8. the jionting method of the long purlin of Z-type on a kind of aircraft according to claim 1, is characterized in that: the fastener selecting former long purlin to adopt in described step 3 in the covering crimp position of long purlin splice carries out fastening, and described fastener is at least 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410633843.5A CN104386263A (en) | 2014-11-12 | 2014-11-12 | Splicing and repairing method of Z-shaped stringer on airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410633843.5A CN104386263A (en) | 2014-11-12 | 2014-11-12 | Splicing and repairing method of Z-shaped stringer on airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104386263A true CN104386263A (en) | 2015-03-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410633843.5A Pending CN104386263A (en) | 2014-11-12 | 2014-11-12 | Splicing and repairing method of Z-shaped stringer on airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN104386263A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110150A (en) * | 2018-08-10 | 2019-01-01 | 广州飞安航空科技有限公司 | A kind of Aircraft Metal Structure reinforcement repairing strength and stiffness accordance method and system |
| CN113665783A (en) * | 2021-10-09 | 2021-11-19 | 中国商用飞机有限责任公司 | Repair for aircraft stringers |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006057255A1 (en) * | 2006-12-05 | 2008-06-19 | Airbus Deutschland Gmbh | Method for repairing damage in aircraft skin using patches applied from inside the hull and with outer flush filling |
| CN201660965U (en) * | 2009-10-16 | 2010-12-01 | 北京建筑工程学院 | Beam-end enhanced-flange splice plate weaken improved rigid nodes of steel frame beam column |
| CN102741846A (en) * | 2009-12-17 | 2012-10-17 | 空中客车运营简化股份公司 | Method for designing standardised repair kits for an aircraft fuselage |
-
2014
- 2014-11-12 CN CN201410633843.5A patent/CN104386263A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006057255A1 (en) * | 2006-12-05 | 2008-06-19 | Airbus Deutschland Gmbh | Method for repairing damage in aircraft skin using patches applied from inside the hull and with outer flush filling |
| CN201660965U (en) * | 2009-10-16 | 2010-12-01 | 北京建筑工程学院 | Beam-end enhanced-flange splice plate weaken improved rigid nodes of steel frame beam column |
| CN102741846A (en) * | 2009-12-17 | 2012-10-17 | 空中客车运营简化股份公司 | Method for designing standardised repair kits for an aircraft fuselage |
Non-Patent Citations (1)
| Title |
|---|
| FAA: "《Aviation Maintenance Technician Handbook-Airframe》", 31 December 2012, article "Chapter 4-Aircraft Metal Structural Repair" * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110150A (en) * | 2018-08-10 | 2019-01-01 | 广州飞安航空科技有限公司 | A kind of Aircraft Metal Structure reinforcement repairing strength and stiffness accordance method and system |
| CN113665783A (en) * | 2021-10-09 | 2021-11-19 | 中国商用飞机有限责任公司 | Repair for aircraft stringers |
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Application publication date: 20150304 |