CN109955392A - A kind of heat insulation structural method for repairing and mending - Google Patents
A kind of heat insulation structural method for repairing and mending Download PDFInfo
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- CN109955392A CN109955392A CN201811450028.XA CN201811450028A CN109955392A CN 109955392 A CN109955392 A CN 109955392A CN 201811450028 A CN201811450028 A CN 201811450028A CN 109955392 A CN109955392 A CN 109955392A
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- repairing
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- heat insulation
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- insulation structural
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B28—WORKING CEMENT, CLAY, OR STONE
- B28D—WORKING STONE OR STONE-LIKE MATERIALS
- B28D1/00—Working stone or stone-like materials, e.g. brick, concrete or glass, not provided for elsewhere; Machines, devices, tools therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mining & Mineral Resources (AREA)
- Mechanical Engineering (AREA)
Abstract
The present invention provides a kind of heat insulation structural method for repairing and mending: the damage location of heat insulation structural being handled, the damage location of non-specification is processed into the repairing hole of regular shape；Processing repairing block similar with repairing hole shape, and draw glue groove in the repairing longitudinally positioned n item of block；High-temperature-resistant adhesive is uniformly smeared into each face of the side for repairing block and bottom surface, repairing hole；Repairing block is placed in repairing hole, guarantees that high-temperature-resistant adhesive can be full of repairing block and repair the gap between hole；Curing process is used to high-temperature-resistant adhesive, after the completion, then is handled with surface of the high-temperature-resistant adhesive to repairing block and septum primum heat structure, makes that treated and repair having a smooth surface transition for block and heat insulation structural.Method of the invention solves the problems, such as the reparation after hypersonic aircraft outer surface heat safeguard structure is impaired, effectively reduces the maintenance period and cost of hypersonic aircraft.
Description
Technical field
The present invention relates to a kind of heat insulation structural method for repairing and mending, belong to thermal protection structure maintenance technology field.
Background technique
It is carried out currently, external hypersonic aircraft generallys use the anti-heat insulating function integrated ceramic based composites of lightweight
Thermal protection structure design, such material while with the performances such as excellent antiscour, heatproof, heat-insulated, that there is also intensity is low,
Brittleness is big, the problems such as damaging of easily colliding in ground operations.Heat-insulated knot is prevented for hypersonic aircraft outer surface ceramic base
The case where structure damages, common practice is changed to the anti-heat insulation structural of the ceramic base for occurring damaging at present, as U.S. spaceflight flies
Machine uses SiO 2-ceramic watt and is used as its thermal protection structure scheme, and the thermal insulation tile quantity being damaged after flight every time accounts for about total block
The 1/3 of number (totally two ten thousand muti-piece), changed the time more than 6 months.On the one hand, ceramic insulation watt prepare raw material valuableness, preparation
With assembly cost height；On the other hand, ceramic insulation watt preparation/assembly technology is complicated, and the period that changes the outfit is long, difficult using the method changed
To meet the requirement of hypersonic aircraft maintenance period anxiety and low cost.
In existing online repair technology, there is repairing block and repair binder between hole cannot be full of, and there are bubbles
The case where, this is in an environment of high temperature, it is desirable that is fatal defect in the reliable situation of heat-proof quality；The material of ceramic insulation watt
Characteristic determines that the toughness of this material is small, secondary damage is easily caused when repairing punching, during making punching
Damage field extends to the outside and influences zone of intact.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, a kind of heat insulation structural method for repairing and mending is provided, is solved superb
Reparation problem after velocity of sound aircraft outer surface thermal protection structure is impaired, effectively reduces the maintenance period of hypersonic aircraft
And cost.
Technical solution of the invention is as follows,
A kind of heat insulation structural method for repairing and mending:
The first step handles the damage location of heat insulation structural, and irregular damage location is processed into regular shape
Repairing hole, and process method be the slow-speed of revolution process, repair hole circumferential size it is 5mm bigger than the radial dimension of damage location with
On；
Second step, processing and the similar repairing block of repairing hole shape, and block is longitudinally positioned draws glue groove in repairing；
High-temperature-resistant adhesive is uniformly smeared in each face of the side for repairing block and bottom surface, repairing hole by third step；
4th step, will repairing block be placed in repairing hole in, guarantee high-temperature-resistant adhesive can full of repairing block and repairing hole it
Between gap；
5th step polishes repairing block upper surface to high-temperature-resistant adhesive using after curing process, make to repair block with
The shape of heat insulation structural matches, then is handled with surface of the high-temperature-resistant adhesive to repairing block and septum primum heat structure, makes to locate
Repairing block and heat insulation structural after reason have a smooth surface transition.
The slow-speed of revolution processing refers to that the revolving speed of machining tool is no more than 15 revolutions per seconds.
The shape in the repairing hole can be any regular shape, the cylinder being preferably easily worked in engineering.
The height of the repairing block is 0.3~1 millimeter smaller than the height for repairing hole, repairs the radial dimension of block than repairing hole
Radial dimension it is 0.5~1.5 millimeter small.
The repairing block while need to also have preferable anti-burning with the same or similar Characteristics of Thermal deformation of hot composite material
Erosion and high temperature resistance, and there is outstanding processing performance, it can not be limited by processing dimension.
The glue groove of drawing refers to that, in the longitudinally through groove-like structure in repairing block, uniformly distributed and quantity is greater than on repairing block
Equal to 4.
The present invention compared with prior art the utility model has the advantages that
(1) present invention uses the structure processed on repairing block and draw glue groove, it is ensured that high-temperature-resistant adhesive in operation
Inside there is not vacuole, repair and uniformly filled between block and repairing hole by high-temperature-resistant adhesive, the structure after ensure that repairing
With good high temperature resistant and heat-proof quality.
(2) method that the present invention is processed using the slow-speed of revolution and increases repairing hole, avoids mistake of the heat-barrier material because of reprocessing
Secondary damage caused by journey improves the reliability of repairing.
(3) method for repairing and mending for the heat insulation structural that the present invention uses, can be in the case where not dismantling septum primum heat structure to damage
The position of wound is repaired, and time and the cost of repairing are shortened, and shortens the maintenance period of aircraft；
(4) present invention guarantees heat insulation structural using the repairing block having with the same or similar Characteristics of Thermal deformation of heat insulation structural
It is consistent with deformation of the repairing hole after heated, avoid generating because deform it is inconsistent caused by bulge break-off；
(5) present invention is guaranteed in harsh heated situation using the repairing block with preferable anti-ablation and heat-resisting quantity,
The performance of repairing block, which remains unchanged, is able to satisfy the performance requirement of heat insulation structural；
(6) the repairing block with excellent processability that the present invention uses, without being repaired using the material of ontology, one
Aspect can guarantee the convenience and rapidity of processing, and can satisfy the requirement that patching material first prepares post-processing, and raising is repaired
The efficiency of benefit, the upper surface on the other hand repairing block can polish, and can be very good to adapt to the flat of irregular surface shape
It slips over and crosses.
Detailed description of the invention
Fig. 1 is monoblock type composite heat-insulating tile structural schematic diagram；
Fig. 2 is that monoblock type composite heat-insulating tile repairs schematic diagram；
Fig. 3 is that repairing block draws glue groove structural schematic diagram；
Specific embodiment
Below with reference to specific example and attached drawing, the present invention is described in detail.
A kind of heat insulation structural method for repairing and mending: the damage location of heat insulation structural is handled, by irregular damage location
It is processed into the repairing hole of regular shape, and the method processed is slow-speed of revolution processing, repairs the radial dimension in hole than damage location
The big 5mm or more of radial dimension；Processing repairing block similar with repairing hole shape, and draw glue groove in the repairing longitudinally positioned n item of block；
High-temperature-resistant adhesive is uniformly smeared into each face of the side for repairing block and bottom surface, repairing hole；Repairing block is placed in repairing hole
It is interior, guarantee that high-temperature-resistant adhesive can be full of the gap between repairing block and repairing hole；Curing process is used to high-temperature-resistant adhesive
Afterwards, repairing block upper surface is polished, the shape for repairing block and heat insulation structural is made to match, then with high-temperature-resistant adhesive to repairing
The surface of patch and septum primum heat structure is handled, and the repairing block that makes that treated and heat insulation structural have a smooth surface transition.
Below as the method for monoblock type composite heat-insulating tile structure repair shown in FIG. 1 does specific introduction.
The first step determines the maximum length L of damage location according to monoblock type composite heat-insulating tile degree of impairment1, maximum width
W1With depth capacity H1, wherein L1≥W1。
Second step determines length, width and the depth for needing to repair according to degree of impairment.To composite heat-insulating tile damage zone
Domain carries out punching processing, and the lower power hand tool of revolving speed can be used, and selects the cylindrical bistrique of 5~10 turns/s of revolving speed, choosing
The further expansion that can effectively avoid working process process composite heat-insulating tile from damaging with suitable revolving speed and tool, and guarantee
Processing efficiency.It punches diameter and selects L2=L1+ (5~8) mm, punching depth select H2=H1+ (0.5~1) mm repairs needs
The position of benefit carries out scribing line positioning, and is punched using tool to scribing line position, and damage location will become rule after punching
The repairing hole of cylindrical shape.The floor space in hole is S2=π × (L2/2)2, the volume V in hole2=π × (L2/2)2×H2。
The repairing block 4 that third step, processing and fabricating and repairing hole are adapted.The material for repairing fast 4 uses moulding process size
Unrestricted and processing performance more preferably refractory ceramics, such as quartz fibre enhancing SiO 2-ceramic or SiO 2-ceramic
Watt.The diameter of repairing block 4 is selected as L3=L2The height of -1mm, repairing block 4 are selected as H3=H2- 0.5mm adds on repairing block 4
Work it is longitudinally through draw glue groove 7, as shown in figure 3, drawing glue groove 7 generally no less than 4, diameter draws glue groove greater than the repairing block of 20mm
7 quantity are no less than 6, and drawing projection of the glue groove 7 on repairing block can be rectangle, or other arbitrary shapes.At this
In example, draw glue groove 7 width 2mm, depth 1mm, drawing 7 quantity of glue groove is 4, i.e. the floor space of repairing block 4 is S3=π × (L3/2)2-
8, repair the volume V of block 43=(π × (L3/2)2-8)×H3。
4th step, will be all equal on each face in the cylindrical side/bottom surface and repairing hole of repairing block 4 using banister bruss brush
Even smearing high-temperature-resistant adhesive 5, smear high-temperature-resistant adhesive 5 thickness T >=1mm, will repairing block 4 be placed in monoblock type it is compound every
In heat watt repairing hole, is pressed by finger and observe high-temperature-resistant adhesive 5 and overflow situation, guarantee that high-temperature-resistant adhesive 5 can be full of
It repairs block 4 and repairs the gap between hole, selected high-temperature-resistant adhesive is using high temperature resistant, resistance to ablation, normal temperature solidified
Inorganic material system such as phosphate or silicate.
5th step, room temperature 24 hours, after the completion of high-temperature-resistant adhesive 5 solidifies, using milling tools such as sand paper to repairing
Patch surface is polished, and is allowed to match with thermal insulation tile shape, is then carried out using 5 pairs of repairing block surfaces of high-temperature-resistant adhesive
Processing smoothly transits after guarantee processing with surrounding monoblock type composite heat-insulating tile.Repair the monoblock type compound heat-insulation tile structure completed
As shown in Figure 2.
Unspecified part of the present invention is known to the skilled person technology.
Claims (5)
1. a kind of heat insulation structural method for repairing and mending, it is characterised in that: it is realized by following steps,
Step 1 handles the damage location of heat insulation structural, and irregular damage location is processed into repairing for regular shape
Perforations adding, and the method processed is slow-speed of revolution processing, the radial dimension for repairing hole is 5mm or more bigger than the radial dimension of damage location；
Step 2 processes repairing block similar with the repairing hole shape in step 1, and draws glue in the repairing longitudinally positioned n item of block
Slot；High-temperature-resistant adhesive is uniformly smeared into each face of the side for repairing block and bottom surface, repairing hole；
Repairing block obtained in step 2 is placed in repairing hole by step 3, guarantees that high-temperature-resistant adhesive can be full of repairing block
Gap between repairing hole；
Repairing block upper surface is polished to the high-temperature-resistant adhesive in step 3 using after curing process, makes to repair by step 4
The shape of patch and heat insulation structural matches, then with high-temperature-resistant adhesive to repairing block at the surface of septum primum heat structure
Reason, the repairing block that makes that treated and heat insulation structural have a smooth surface transition.
2. heat insulation structural method for repairing and mending according to claim 1, it is characterised in that: the shape in the repairing hole can be to appoint
It anticipates regular shape, it is preferably cylindrical in engineering.
3. heat insulation structural method for repairing and mending according to claim 1, it is characterised in that: the height of the repairing block is than repairing
The height in hole is 0.3~1 millimeter small, and the radial dimension for repairing block is 0.5~1.5 millimeter smaller than the radial dimension for repairing hole.
4. heat insulation structural method for repairing and mending according to claim 3, it is characterised in that: the repairing block need to be with hot composite wood
Expect the same or similar Characteristics of Thermal deformation, while also having preferable anti-ablation, high temperature resistance and processing performance.
5. heat insulation structural method for repairing and mending according to claim 1, it is characterised in that: it is described draw glue groove and refer to passed through longitudinally
The groove-like structure of repairing block is passed through, and quantity is more than or equal to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811450028.XA CN109955392A (en) | 2018-11-30 | 2018-11-30 | A kind of heat insulation structural method for repairing and mending |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811450028.XA CN109955392A (en) | 2018-11-30 | 2018-11-30 | A kind of heat insulation structural method for repairing and mending |
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| CN109955392A true CN109955392A (en) | 2019-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811450028.XA Pending CN109955392A (en) | 2018-11-30 | 2018-11-30 | A kind of heat insulation structural method for repairing and mending |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115536436A (en) * | 2021-06-30 | 2022-12-30 | 航天特种材料及工艺技术研究所 | Repairing method of carbon fiber toughened ceramic matrix composite material member |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4330572A (en) * | 1980-07-25 | 1982-05-18 | Nasa | Method for repair of thin glass coatings |
| US5985433A (en) * | 1997-03-13 | 1999-11-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | High temperature resistant organopolysiloxane coating for protecting and repairing rigid thermal insulation |
| US7198860B2 (en) * | 2003-04-25 | 2007-04-03 | Siemens Power Generation, Inc. | Ceramic tile insulation for gas turbine component |
| CN103612441A (en) * | 2013-11-20 | 2014-03-05 | 北京中新图锐科技有限公司 | Composite sandwich plate, mold and manufacturing method |
| CN106433143A (en) * | 2016-09-14 | 2017-02-22 | 航天特种材料及工艺技术研究所 | Repair material for repairing composite material and method for repairing composite material with repair material |
| CN107554814A (en) * | 2017-08-25 | 2018-01-09 | 北京星航机电装备有限公司 | A kind of restorative procedure of multi-layer combined thermal protection component |
| CN207487746U (en) * | 2017-10-24 | 2018-06-12 | 广东奥迪威传感科技股份有限公司 | A kind of ultrasonic flow sensor |
-
2018
- 2018-11-30 CN CN201811450028.XA patent/CN109955392A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4330572A (en) * | 1980-07-25 | 1982-05-18 | Nasa | Method for repair of thin glass coatings |
| US5985433A (en) * | 1997-03-13 | 1999-11-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | High temperature resistant organopolysiloxane coating for protecting and repairing rigid thermal insulation |
| US7198860B2 (en) * | 2003-04-25 | 2007-04-03 | Siemens Power Generation, Inc. | Ceramic tile insulation for gas turbine component |
| CN103612441A (en) * | 2013-11-20 | 2014-03-05 | 北京中新图锐科技有限公司 | Composite sandwich plate, mold and manufacturing method |
| CN106433143A (en) * | 2016-09-14 | 2017-02-22 | 航天特种材料及工艺技术研究所 | Repair material for repairing composite material and method for repairing composite material with repair material |
| CN107554814A (en) * | 2017-08-25 | 2018-01-09 | 北京星航机电装备有限公司 | A kind of restorative procedure of multi-layer combined thermal protection component |
| CN207487746U (en) * | 2017-10-24 | 2018-06-12 | 广东奥迪威传感科技股份有限公司 | A kind of ultrasonic flow sensor |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115536436A (en) * | 2021-06-30 | 2022-12-30 | 航天特种材料及工艺技术研究所 | Repairing method of carbon fiber toughened ceramic matrix composite material member |
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Application publication date: 20190702 |
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