CN109131821B - Slidable connecting structure - Google Patents
Slidable connecting structure Download PDFInfo
- Publication number
- CN109131821B CN109131821B CN201810932955.9A CN201810932955A CN109131821B CN 109131821 B CN109131821 B CN 109131821B CN 201810932955 A CN201810932955 A CN 201810932955A CN 109131821 B CN109131821 B CN 109131821B
- Authority
- CN
- China
- Prior art keywords
- heat insulation
- slidable
- cabin body
- fairing
- flanging
- 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.)
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Links
- 238000009413 insulation Methods 0.000 claims abstract description 76
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 12
- 230000000712 assembly Effects 0.000 claims description 10
- 238000000429 assembly Methods 0.000 claims description 10
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 239000002131 composite material Substances 0.000 claims description 4
- 239000010453 quartz Substances 0.000 claims description 4
- 239000000377 silicon dioxide Substances 0.000 claims description 4
- 229920002379 silicone rubber Polymers 0.000 claims description 4
- 239000011324 bead Substances 0.000 claims description 2
- 239000004945 silicone rubber Substances 0.000 claims 1
- 235000012239 silicon dioxide Nutrition 0.000 description 5
- 239000000835 fiber Substances 0.000 description 3
- 230000002265 prevention Effects 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B1/00—Devices for securing together, or preventing relative movement between, constructional elements or machine parts
- F16B1/02—Means for securing elements of mechanisms after operation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/028—Composition or method of fixing a thermally insulating material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/029—Shape or form of insulating materials, with or without coverings integral with the insulating materials layered
Abstract
The invention provides a slidable connecting structure, which comprises a cabin body, a fairing and a plurality of connecting components which are arranged at intervals and used for slidably connecting the cabin body and the fairing, wherein the main body structure of the fairing is approximately U-shaped, the upper edges of the two side walls of the U-shaped fairing are outwards flanged, the flanges are used for being connected with the cabin body, and any one of the connecting components comprises: the heat insulation cushion is arranged on one side face, facing the cabin body, of the flanging, the heat insulation pressing strip is arranged on one side face, facing away from the cabin body, of the flanging, and the heat insulation cushion, the flanging and the heat insulation pressing strip form a sandwich structure; each connecting piece be used for compressing tightly the sandwich structure the cabin body is gone up, and in the connection structure, the turn-ups is slidable setting respectively for heat insulating mattress and thermal-insulated layering. The slidable connecting structure provided by the invention can solve the technical problem of unmatched thermal deformation existing in the connection of the cabin body and the fairing in the prior art.
Description
Technical Field
The invention relates to a slidable connecting structure, in particular to a slidable connecting structure between a cold structure and a hot structure, which is particularly suitable for connecting a hot structure and a cold structure made of fragile materials.
Background
The hypersonic aerocraft flies in the atmosphere at a high speed for a long time, and the surface of the hypersonic aerocraft continuously has high temperature in the flying process. The fairing is a dimensional component outside the engine main body, the C/SiC material is adopted to bear the high temperature of the hood body, the cabin body adopts an external heat-proof and internal bearing mode, the internal bearing structure is made of aluminum alloy material, and the temperature of the whole flight process is close to the normal temperature, so that the thermal deformation mismatching condition caused by the temperature difference exists between the fairing and the cabin body. In addition, the connecting interfaces are arranged between the fairing and the engine jet pipe as well as between the fairing and the nacelle body, and the engine jet pipe and the nacelle body are relatively deformed in flight, so that the two interfaces of the fairing have relative mechanical motion.
The maximum temperature of the fairing in flight is about 950 ℃, the maximum temperature of the joint is about 500 ℃, the maximum temperature of the connection part of the cabin body is about 80 ℃, and the X-direction length of the fairing is about 700mm, so that the X-direction relative deformation exists between the joint and the cabin body.
At present, the relative deformation requirements are difficult to meet through a common structural connection mode, and if the structural connection mode is adopted, the complexity of design and maintenance is increased, and the structural weight reduction requirements cannot be met. A simple form and reliable performance of the connection is required for this purpose.
Disclosure of Invention
The invention provides a slidable connecting structure which can solve the technical problem that the thermal deformation of the connection of a cabin body and a fairing in the prior art is not matched.
The technical scheme of the invention is as follows:
the invention provides a slidable connection structure, which comprises a cabin body, a fairing and a plurality of connection assemblies which are arranged at intervals and used for slidably connecting the cabin body and the fairing, wherein the main body structure of the fairing is approximately U-shaped, the edges of the two side walls of the U-shaped fairing are outwards flanged, the flanges are used for being connected with the cabin body, the connection assemblies are arranged at intervals along the length direction of the flanges, and any one of the connection assemblies comprises: the heat insulation cushion is arranged on one side surface of the flanging, which faces the cabin body, the heat insulation pressing strip is arranged on one side surface of the flanging, which faces away from the cabin body, and the heat insulation cushion, the flanging and the heat insulation pressing strip form a sandwich structure; each connecting piece is used for compressing tightly the sandwich structure on the cabin body, and in the connecting structure, the flanging is respectively arranged in a slidable manner relative to the heat insulation pad and the heat insulation pressing strip.
Furthermore, for any connecting assembly, the connecting piece is a screw, the cabin body is provided with a threaded hole for fixing a plurality of screws, the heat insulation pad, the flanging and the pressing strip are respectively provided with a plurality of through holes for the plurality of screws to pass through, and the plurality of through holes are arranged at intervals along the length direction of the flanging; wherein, the plurality of through-holes of turn-ups include locating hole and slidable hole.
Furthermore, through holes positioned at the end side are arranged in the through holes of the flanging to serve as positioning holes; the slidable hole of the flanging is a long round hole.
Further, the movement allowance of the long round hole is not less than 2 mm.
Further, the screw is preferably a countersunk head screw, the countersunk head screw sinks into the heat insulation pressing strip, a countersunk hole is further formed in the head of the countersunk head screw of the heat insulation pressing strip, and a heat-proof plug used for plugging the countersunk hole screw is further arranged in the countersunk hole.
Further, the heat insulation pad is also bonded with the cabin body.
Furthermore, the heat insulation pad is bonded with the cabin body by adopting silicon rubber.
Furthermore, the heat insulation pad and the heat insulation pressing bar are both prepared from quartz fiber reinforced silicon dioxide composite materials.
The slidable connecting structure is applied, a sliding connecting mode is designed to adapt to thermal deformation mismatching or relative mechanical movement of two contacting parties, and the connecting structure has the functions of bearing and heat prevention, has the advantages of simple form, convenience in assembly, light structure and reliable performance, and has good application prospect in engineering.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic structural diagram illustrating a slidable coupling structure according to an embodiment of the present invention;
FIG. 2 illustrates a cross-sectional view of any of the connection assemblies in the slidable connection configuration provided in accordance with an embodiment of the present invention;
FIG. 3 illustrates three views of a molding provided in accordance with an embodiment of the present invention;
FIG. 4 illustrates a schematic structural view of a fairing provided in accordance with an embodiment of the present invention.
Wherein the figures include the following reference numerals:
10. a cabin body; 20. a cowling; 30. a heat insulating pad; 40. layering; 50. a connecting member; 60. an engine.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
As shown in fig. 1 and 2, the present invention provides a slidable connection structure, which includes a nacelle body 10, a fairing 20, and a plurality of connection assemblies arranged at intervals and used for slidably connecting the nacelle body 10 and the fairing 20, wherein the fairing 20 is a U-shaped structure with an outer flange, the flange is used for connecting with the nacelle body, the connection assemblies are arranged at intervals along a length direction of the flange, and any one of the connection assemblies includes: the heat insulation structure comprises a heat insulation pad 30, a heat insulation pressing strip 40 and a plurality of connecting pieces 50, wherein the heat insulation pad 30 is arranged on one side surface of a flanging, which faces to the cabin body 10, the heat insulation pressing strip 40 is arranged on one side surface of the flanging, which faces away from the cabin body 10, and the heat insulation pad 30, the flanging and the heat insulation pressing strip 40 form a sandwich structure; each connecting member 50 is used for pressing the sandwich structure onto the cabin 10, and in the connecting structure, the flanges are slidably disposed with respect to the heat insulation pad 30 and the heat insulation pressing bar 40, respectively.
By determining the heat insulation material, the position and the connection mode, the slidable connection structure is installed in a combined mode of the cabin body 10, the heat insulation pad 30, the fairing flanging and the heat insulation pressing strip 40, the fairing flanging is clamped between the heat insulation pad 30 and the heat insulation pressing strip 40 to form a sandwich structure, the heat insulation pad 30 and the heat insulation pressing strip 40 form a straight track on the surface, the controllable directional sliding of the fairing 20 is ensured, and the sliding is adopted to adapt to the thermal deformation mismatching or relative mechanical movement of two contact sides; in addition, by arranging a plurality of connecting components at intervals, the local pressing force of the connecting component can be dispersed, and the damage to each component of the connecting component can be prevented.
Further, as shown in fig. 4, the main structure of the fairing 20 is substantially U-shaped, and the upper edges of the two side walls of the U-shape are flanged outwards; specifically, the main structure of the fairing 20 is U-shaped along the length direction of the fairing 20 (the length direction of the flanging is also the length direction of the fairing 20), and in general, the length direction of the fairing 20 is the heading direction, that is, along the heading direction, the main structure of the fairing 20 is U-shaped, and the fairing 20 has a very long flanging along the heading direction, and preferably, the two side flanging are symmetrically arranged. The invention utilizes the outward flanging of the fairing 20 to be connected with the cabin body 10, thereby being beneficial to realizing sliding connection.
As a specific embodiment of the present invention, the slidably connected connecting assemblies for connecting the nacelle 10 and the fairing 20 are respectively located at two side flanges of the fairing 20, wherein the number of the connecting assemblies is 16, and the two side flanges are respectively 8, for example, a to h, and are sequentially arranged at intervals along the heading direction, wherein for any one connecting assembly, for example, the connecting assembly a, it includes: an insulation mat 30, an insulation bead 40, and a plurality of connectors 50.
Further, as an embodiment of the present invention, as shown in fig. 2 and 3, the connection member 50 is a screw, the cabin 10 is provided with a threaded hole for fixing a plurality of screws, the heat insulation pad 30, the turned-over edge and the heat insulation pressing strip 40 are all provided with a plurality of through holes for the plurality of screws to pass through, and the plurality of through holes are arranged at intervals along the heading direction; the plurality of through holes of the turned edges include positioning holes and slidable holes, and in addition, the heat insulation pad 30 and the heat insulation pressing strip 40 are both configured to be long-strip-shaped. By applying the configuration mode, the connecting assembly is set to be a screw, the turned edge is simultaneously provided with the positioning hole and the slidable hole, and the heat insulation pad 30 and the heat insulation pressing strip 40 are both set to be strip-shaped, so that the heat insulation pad 30 and the heat insulation pressing strip 40 form a straight rail on the surface and the fairing 20 can realize controllable directional sliding.
Further, as an embodiment of the present invention, in order to achieve better compatibility between positioning and sliding, a through hole located on an end side is provided as the positioning hole among the plurality of through holes of the burring, and it is more preferable that the first through hole in the course direction is the positioning hole, and the slidable hole of the burring is the oblong hole.
Further, as an embodiment of the present invention, the movement allowance of the oblong hole is not less than 2mm according to the relative deformation in the X direction existing between the cabin 10 and the fairing flange.
Further, as an embodiment of the present invention, in order to prevent a thermal bridge, the screw is preferably a countersunk screw, the countersunk screw sinks into the heat insulation pressing strip 40, the heat insulation pressing strip 40 is further provided with a counter bore on the head of the countersunk screw, and the counter bore is further provided with a heat-proof plug (not shown in the figure) for plugging the counter bore screw.
Further, as an embodiment of the present invention, in order to ensure that the heat insulation pad 30, the heat insulation pressing strip 40, the cabin 10 and the screws have no relative displacement, the heat insulation pad 30 is further bonded to the cabin 10, and the heat insulation pad 30 is bonded to the cabin 10 by using silicon rubber.
Specifically, the sandwich structure is pressed tightly on the cabin body 10 through a countersunk head screw, a threaded hole is designed on the cabin body 10, a countersunk hole is designed on the heat insulation pressing strip 40, a through hole is formed in the turnup of the fairing and the heat insulation pad 30, the heat insulation pad 30 is firstly adhered to the cabin body 10 during assembly, then the fairing 20 and the heat insulation pressing strip 40 are sequentially placed in place, finally the countersunk head screw is screwed in, the heat insulation pressing strip 40 is pressed tightly to complete installation, the heat insulation pad 30, the heat insulation pressing strip 40, the cabin body 10 and the countersunk head screw do not have relative displacement during working, and therefore, the structure can meet the sliding requirement only by designing a long hole with the movement allowance not less than 2mm on the turnup of.
In the invention, the sunk screw realizes looseness prevention through a screwing torque and thread gluing mode. Two factors need to be considered for setting the tightening torque, namely, the tightening torque is kept in work and is not loosened, the problem that the connection is too tight and the normal sliding cannot be realized due to too large positive pressure of the connection surface of the fairing is avoided, and particularly, when the fairing is pulled and sheared, the fairing can slide in time, the internal stress of the fairing is released, and the structural damage is avoided.
Further, as a preferred embodiment of the present invention, the heat insulating pad and the heat insulating pressing bar are both made of a silica composite material reinforced by quartz fiber. The reason is that: the outer surfaces of the fairing and the pressing strip are pneumatic outer surfaces of a cabin body, the outer surfaces of the fairing and the pressing strip are heated by airflow in flight, continuous high temperature exists on the surfaces, meanwhile, the fairing mainly bears surface pneumatic pressure in flight and generates an extrusion effect on the heat insulation pad along the normal direction of a contact surface, and in consideration of the two factors, the heat insulation pad and the pressing strip are made of quartz fiber reinforced silicon dioxide composite materials with certain heat insulation and bearing performance, so that the temperature of the cabin body can be effectively reduced, and the extrusion of the fairing can be borne; in addition, the contact surface of the heat insulation pad is scraped with fine powder when the fairing slides, so that the friction coefficient of the contact surface is reduced, and the sliding of the fairing is facilitated.
The following illustrates the slidable coupling structure provided by the present invention:
the heat insulation cabin comprises 16 pressing strips which are arranged in total in the figure 1, 8 pressing strips are arranged on the left and right sides, the number of the pressing strips can be adjusted, the local thickness of a cabin body 10 at a threaded hole is 12mm, the diameter of a threaded hole is M5, the effective depth of the thread is 7mm, the thickness of a heat insulation pad 30 is 12.7mm, a phi 5.5mm through hole is designed at the position of a sunk screw, two sides of a fairing 20 are respectively provided with a flanging structure, the flanging thickness is 7mm, the two sides are symmetrical, a long hole with a circular arc section of phi 5.5mm and a straight line section of 3mm is designed at the position of the sunk screw, the thickness of the heat insulation pressing strip is 10mm, a 90-degree sunk hole with a small diameter of phi 5.5mm and a large diameter of phi 9.5mm is designed at the position of the sunk screw, HB 1-205-M5-5 g6gx26 standard components are adopted for the sunk screws, the two rows are 14, a KH-C L-RTV-2 silicon rubber layer is coated between the heat insulation pad 30 and the cabin body 10 to realize the adhesion of.
In addition, the dimensions of the trim strips and the connecting structures of the fairing can be adjusted according to the shape, the loading environment and the like of the fairing. It is recommended that the attachment screws be as small as possible to reduce thermal bridge heat transfer.
The embodiment of the invention provides a slidable connecting structure, which adapts to thermal deformation mismatching or relative mechanical movement of two contacting parties by designing a sliding connecting mode, has the functions of bearing and heat prevention, has the advantages of simple form, convenience in assembly, light structure and reliable performance, and has good application prospect in engineering.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The utility model provides a slidable connection structure, characterized in that, connection structure includes that the cabin body (10), radome fairing (20) and a plurality of interval set up be used for cabin body (10) and radome fairing (20) slidable connection's coupling assembling, wherein, the major structure of radome fairing (20) roughly be the U-shaped, and along all outside turn-ups on the U-shaped both sides wall, the turn-ups is used for being connected with cabin body (10), coupling assembling follows turn-ups length direction interval sets up, arbitrary one coupling assembling include: the heat insulation structure comprises a heat insulation pad (30), a heat insulation pressing strip (40) and a plurality of connecting pieces (50), wherein the heat insulation pad (30) is arranged on one side surface of the flanging, which faces towards the cabin body (10), the heat insulation pressing strip (40) is arranged on one side surface of the flanging, which faces away from the cabin body (10), and the heat insulation pad (30), the flanging and the heat insulation pressing strip (40) form a sandwich structure; each connecting piece (50) be used for with the sandwich structure compresses tightly on the cabin body (10), just in the connection structure, the turn-ups for but heat insulating mattress (30) and thermal-insulated layering (40) are the slidable setting respectively.
2. The slidable connection structure of claim 1, wherein for any one of the connection assemblies, the connection member (50) is a screw, the cabin (10) is provided with a threaded hole for fixing a plurality of screws, the heat insulation pad (30), the flange and the heat insulation pressing bar (40) are provided with a plurality of through holes for the plurality of screws to pass through, and the plurality of through holes are arranged at intervals along the length direction of the flange; the through holes of the flanging comprise positioning holes and slidable holes.
3. The slidable connecting structure according to claim 2, wherein of the plurality of through holes of the burring, through holes located on the end side are provided as positioning holes; the slidable hole of the flanging is a long round hole.
4. A slidable connection according to claim 3, wherein the slotted hole has a play margin of not less than 2 mm.
5. The slidable connecting structure as claimed in claim 2, wherein the screw is a countersunk screw, the countersunk screw sinks into the heat insulation pressing strip (40), the heat insulation pressing strip (40) is further provided with a counter bore on the head of the countersunk screw, and the counter bore is further provided with a heat-proof plug for plugging the counter bore screw.
6. A slidable connection according to claim 1, wherein the insulation pads (30) are further bonded to the enclosure (10).
7. A slidable connection according to claim 6, wherein the insulation pads (30) are bonded to the enclosure (10) using silicone rubber.
8. A slidable connection according to any one of claims 1-7, wherein the insulating mat (30) and the insulating beads (40) are made of a silica composite reinforced with quartz fibres.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810932955.9A CN109131821B (en) | 2018-08-16 | 2018-08-16 | Slidable connecting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810932955.9A CN109131821B (en) | 2018-08-16 | 2018-08-16 | Slidable connecting structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109131821A CN109131821A (en) | 2019-01-04 |
| CN109131821B true CN109131821B (en) | 2020-07-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810932955.9A Active CN109131821B (en) | 2018-08-16 | 2018-08-16 | Slidable connecting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131821B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110834712B (en) * | 2019-10-17 | 2021-03-26 | 中国运载火箭技术研究院 | Be applicable to high temperature resistant thermal plug structure of dismantling |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4702439A (en) * | 1987-01-20 | 1987-10-27 | The United States Of America As Represented By The Secretary Of The Navy | Support for thermally expanding conical heatshield |
| CN102614749A (en) * | 2011-01-26 | 2012-08-01 | 北京星旋世纪科技有限公司 | Vortex type hot and cold gas separation apparatus |
| CN108138895A (en) * | 2015-10-09 | 2018-06-08 | 霓佳斯株式会社 | Connecting piece |
| CN207500012U (en) * | 2017-10-27 | 2018-06-15 | 洛阳神飞航空科技有限公司 | A kind of solid rocket motor case being easily installed |
| CN207647495U (en) * | 2017-12-14 | 2018-07-24 | 东营华辰石油装备有限公司 | A kind of Thickened oil injection-production heat-insulation retractor device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9567113B2 (en) * | 2013-05-03 | 2017-02-14 | The Boeing Company | Thermal seal with thermally induced shape change |
-
2018
- 2018-08-16 CN CN201810932955.9A patent/CN109131821B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4702439A (en) * | 1987-01-20 | 1987-10-27 | The United States Of America As Represented By The Secretary Of The Navy | Support for thermally expanding conical heatshield |
| CN102614749A (en) * | 2011-01-26 | 2012-08-01 | 北京星旋世纪科技有限公司 | Vortex type hot and cold gas separation apparatus |
| CN108138895A (en) * | 2015-10-09 | 2018-06-08 | 霓佳斯株式会社 | Connecting piece |
| CN207500012U (en) * | 2017-10-27 | 2018-06-15 | 洛阳神飞航空科技有限公司 | A kind of solid rocket motor case being easily installed |
| CN207647495U (en) * | 2017-12-14 | 2018-07-24 | 东营华辰石油装备有限公司 | A kind of Thickened oil injection-production heat-insulation retractor device |
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| Publication number | Publication date |
|---|---|
| CN109131821A (en) | 2019-01-04 |
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