CN106287101A - The adhering method of solid rocket motor nozzle and flexible blanking cover and sealing frock - Google Patents
The adhering method of solid rocket motor nozzle and flexible blanking cover and sealing frock Download PDFInfo
- Publication number
- CN106287101A CN106287101A CN201610767311.XA CN201610767311A CN106287101A CN 106287101 A CN106287101 A CN 106287101A CN 201610767311 A CN201610767311 A CN 201610767311A CN 106287101 A CN106287101 A CN 106287101A
- Authority
- CN
- China
- Prior art keywords
- blanking cover
- jet pipe
- flexible blanking
- shrouding
- sealing frock
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 54
- 238000000034 method Methods 0.000 title claims abstract description 35
- 239000007787 solid Substances 0.000 title claims abstract description 22
- 238000003825 pressing Methods 0.000 claims description 7
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- 230000015572 biosynthetic process Effects 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 210000001364 upper extremity Anatomy 0.000 claims description 5
- 210000000867 larynx Anatomy 0.000 claims description 3
- 229920006335 epoxy glue Polymers 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 238000007906 compression Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 238000001514 detection method Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 239000003822 epoxy resin Substances 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 229920000647 polyepoxide Polymers 0.000 description 2
- 238000012797 qualification Methods 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910052756 noble gas Inorganic materials 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- 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
- F16L55/00—Devices or appurtenances for use in, or in connection with, pipes or pipe systems
- F16L55/10—Means for stopping flow from or in pipes or hoses
- F16L55/115—Caps
-
- 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
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/002—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by pressing the elements together so as to obtain plastic deformation
-
- 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
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
Abstract
The invention discloses a kind of solid rocket motor nozzle and the adhering method of flexible blanking cover and sealing frock, after described adhering method is flexible blanking cover and jet pipe throat lining pre-bonding, sealing frock is installed on jet pipe, flexible blanking cover is made to form confined space region one after matching with sealing frock, is pressurizeed in confined space region one, the outer mold surface of flexible blanking cover with jet pipe throat lining bonding plane is pressurizeed by the mode using air pressure, and last pressurize solidifies.Utilizing the non-directiveness of air pressure, the flexible blanking cover that applies pressure to acts on the outer mold surface of bonding plane, makes bonding plane every bit normal direction pressurized, it is achieved the face contact uniform-compression of bonding plane, thus improves bonding quality；It addition, the method is simple and convenient to operate, the cycle is short and cheap, it is particularly suited for major diameter solid rocket motor nozzle bonding with flexible blanking cover.
Description
Technical field
The invention belongs to solid rocket motor nozzle field shaping technique, be specifically related to a kind of solid propellant rocket spray
Manage the adhering method with flexible blanking cover and sealing frock.
Background technology
Jet pipe is the important spare part of solid propellant rocket, and solid rocket motor nozzle, when assembling, needs soft
Property blanking cover 11 solidification bonding with jet pipe throat lining 10, then carry out air-tight test examination.The flexible blanking cover of prior art and jet pipe larynx
Lining adhering method, as it is shown in figure 1, be the briquetting 9 using the bonding positive with flexible blanking cover, adds weight on briquetting 9
Or use hand press to pressurize, then cold curing.
Owing to flexible blanking cover is curved surface with the bonding profile of jet pipe throat lining, in the flexible blanking cover adhering method of prior art,
Briquetting and flexible blanking cover are press-fitted face and are difficult to accomplish fully mated, and bonding profile Impact direction is single, and adhesion type surface pressure is uneven
Even, it is easily generated linear contact lay pressure, thus the qualification rate causing flexible blanking cover bonding with jet pipe throat lining is relatively low, often leaks air existing
As, have a strong impact on production efficiency.
Summary of the invention
Present invention aim to the deficiency for traditional diamond-making technique, it is provided that it is solid that one can be effectively improved bonding quality
The adhering method of body rocket tube and flexible blanking cover and sealing frock, thus improve production efficiency.
For achieving the above object, the solid rocket motor nozzle designed by the present invention and the adhering method of flexible blanking cover,
Described adhering method be flexible blanking cover with jet pipe throat lining pre-bonding after, sealing frock is installed on jet pipe so that flexible blanking cover with
Sealing frock forms confined space region one after matching, and pressurizes confined space region one, uses the mode pair of air pressure
Flexible blanking cover pressurizes with the outer mold surface of jet pipe throat lining bonding plane, and last pressurize solidifies.
Further, described adhering method specifically includes following steps:
1) it is coated with epoxy glue on the bonding plane of jet pipe throat lining, flexibility blanking cover is adhered on jet pipe throat lining in advance；
2) being installed on jet pipe by sealing frock, the edge of sealing frock shrouding is by the fixing peace of bolt and jet pipe diffuser
Dress, the protuberance bottom surface of sealing frock shrouding is against the outer mold surface upper limb of flexible blanking cover bonding plane, the base plate limit of sealing frock base
Edge is against the outer mold surface lower edge of flexible blanking cover bonding plane, and the outer mold surface of protuberance, shrouding, base and flexible blanking cover bonding plane is enclosed successively
Closing and form confined space region one, protuberance, shrouding and jet pipe diffuser enclose formation confined space region two successively；
3) by suppressing joint to confined space region one pressurization, the first Pressure gauge display confined space district of sealing frock
The pressure in territory one, after being pressurized to preset value, room temperature pressurize solidifies, and then removes sealing frock.
Further, described step 3) remove sealing frock after, the jet pipe after bonding is carried out airtight with flexibility blanking cover 11
Property detection.
Further, described step 1) in, after flexible blanking cover 11 adheres on jet pipe throat lining in advance, the axis of flexible blanking cover 11 with
The axis offset distance of jet pipe throat lining 10 must not exceed 1mm.
Further, carrying out described step 1) before, the bonding plane of jet pipe throat lining 10 and the bonding plane of flexible blanking cover 11
All after polishing, clean with acetone.
Further, complete described step 2) after, by the second Pressure gauge detection confined space in confined space region two
Whether region one fully seals；Detailed process is as follows:
After sealing frock is installed on jet pipe, by suppressing joint to confined space region one pressurization, if the second Pressure gauge
Numerical value do not change, then confined space region one fully seals, otherwise, then seal the most intact.
Further, it is lined with between protuberance bottom surface and the outer mold surface upper limb of described flexible blanking cover bonding plane of described shrouding 1
First O-ring seals；It is lined with the 2nd O between bottom edge and the outer mold surface lower edge of described flexible blanking cover bonding plane of described base
Shape sealing ring；It is lined with the 3rd O shape between face, support bar outer peripheral edge and the support bar connecting hole inwall of described shrouding of described base
Sealing ring；It is lined with the 4th O-ring seals between edge and the described jet pipe diffuser of described sealing frock shrouding.
A kind of solid rocket motor nozzle as described above and flexible blanking cover adhering method and the sealing frock that designs, institute
State sealing frock and include that shrouding and base, described base include base plate and the support bar being connected on base plate, described support bar
Upper end is fixedly mounted on the middle part of described shrouding；Described shrouding lower surface has downwardly extended a circle protuberance, and described convex
Portion is positioned at the outside of described base plate；Described sealing frock also includes being positioned at inside described protuberance and being arranged on described shrouding
Suppress joint.
Further, described sealing frock also includes being positioned at inside described protuberance and being arranged on first on described shrouding
Pressure gauge and be positioned at the second Pressure gauge that is outside described protuberance and that be arranged on described shrouding.
Further, during the upper end of described support bar is inserted into the support bar connecting hole of described shrouding middle part until
Extending in the intermediate throughholes of pressing plate, described pressing plate is bolted and is fitted on described shrouding, the support bar of described base
It is lined with the 3rd O-ring seals between the support bar connecting hole inwall of face, outer peripheral edge and described shrouding.
The present invention compared with prior art, has the advantage that adhering method of the present invention is that sealing frock is installed to spray
Guan Shang so that flexible blanking cover forms confined space region one with sealing frock after matching, then use gas pressure, utilize gas
The non-directiveness of pressure, the flexible blanking cover that applies pressure to acts on the outer mold surface of bonding plane, makes bonding plane every bit normal direction pressurized, it is achieved viscous
The face contact uniform-compression of junction, thus improve bonding quality；It addition, the method is simple and convenient to operate, the cycle is short and price
Cheap, it is particularly suited for major diameter solid rocket motor nozzle bonding with flexible blanking cover.
Accompanying drawing explanation
Fig. 1 is flexible blanking cover schematic diagram bonding with jet pipe throat lining in prior art；
Fig. 2 is the bonded structure schematic diagram of solid rocket motor nozzle of the present invention and flexible blanking cover；
Fig. 3 is structure enlarged diagram at I in Fig. 2；
Fig. 4 is structure enlarged diagram at II in Fig. 2；
Fig. 5 is structure enlarged diagram at III in Fig. 2.
Wherein: shrouding 1 (wherein: protuberance 1.1), base 2 (wherein: support bar 2.1, base plate 2.2, upper end 2.3), pressing plate
3, joint the 4, first Pressure gauge the 5, second Pressure gauge 6, bolt the 7, the 3rd O-ring seals 8, briquetting 9, larynx lining 10, flexible stifled is suppressed
Lid 11, second O-ring seals the 12, first O-ring seals 13, confined space region 2 14, confined space region 1, diffuser
16, bonding plane 17, outer mold surface 18, unsettled face 19.
Detailed description of the invention
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings, it is simple to more clearly understands this
Invention, but they do not constitute restriction to the present invention.
Sealing frock employed in following example, shown in Fig. 2, including shrouding 1, base 2, pressing plate 3, suppresses and connects
The 4, first Pressure gauge 5 and the second Pressure gauge 6, when the minimum thickness of this shrouding 1 should meet follow-up use, moulding pressure is strong
Degree requirement；The middle part of shrouding 1 has support bar connecting hole, and base 2 includes base plate 2.2 and propping up of being connected on base plate 2.2
Strut 2.1, the upper end 2.3 of support bar 2.1 is inserted in the support bar connecting hole of shrouding 1 middle part until extending into pressing plate
In the intermediate throughholes of 3, pressing plate 3 is bolted and is fitted on shrouding 1, thus is fixedly connected into whole by shrouding 1 with base 2
It is lined with twice the 3rd O-ring seals 8 between body, and face, support bar 2.1 outer peripheral edge and support bar connecting hole inwall to seal,
As shown in Figure 3；Shrouding 1 lower surface has downwardly extended a circle protuberance 1.1, and this protuberance 1.1 is positioned at the outside of base plate 2.2, the first pressure
Power table the 5, second Pressure gauge 6 and suppress joint 4 and be installed on shrouding 1, and the first Pressure gauge 5 and suppress joint 4 and be respectively positioned on convex
The inner side in portion 1.1, the second Pressure gauge 6 is positioned at the outside of protuberance 1.1.
It is bonding with flexible blanking cover that the present embodiment uses above-mentioned sealing frock to realize solid rocket motor nozzle, flexible
After blanking cover 11 and jet pipe throat lining 10 pre-bonding, sealing frock is installed on jet pipe so that flexible blanking cover 11 matches with sealing frock
Form confined space region 1 after conjunction, is pressurizeed in confined space region 1, thus form a gas cabin environment, use
The outer mold surface 18 of flexible blanking cover 11 with jet pipe throat lining 10 bonding plane 17 is pressurizeed by the mode of air pressure, and last pressurize solidifies.It is concrete
Method is as follows:
1), after first all being polished by the bonding plane of the bonding plane of jet pipe throat lining 10 and flexible blanking cover 11, buffed surface should be kept to put down
Slip over and cross, occur without pit, and clean up with acetone；
2) it is coated with high-temperature-resistant epoxy resin glue (such as High temp. epoxy resins AB glue) on the bonding plane of jet pipe throat lining 10, flexibility is blocked up
Lid 11 adheres on jet pipe throat lining 10 in advance, it is ensured that the flexible axis of blanking cover 11 must not exceed 1mm with the axis offset distance of jet pipe throat lining 10；
3) sealing frock is installed on jet pipe, as in figure 2 it is shown, the edge of sealing frock shrouding 1 is by bolt 7 and jet pipe
Diffuser 16 fixedly mounts, and protuberance 1.1 bottom surface of sealing frock shrouding 1 is against in the outer mold surface 18 of flexible blanking cover 11 bonding plane
Edge, base plate 2.2 edge of sealing frock base 2 is against outer mold surface 18 lower edge of flexible blanking cover 11 bonding plane；Further, shrouding 1
It is lined with three road the first O-ring seals 13, such as Fig. 5 between outer mold surface 18 upper limb of protuberance 1.1 bottom surface and flexible blanking cover 11 bonding plane
Shown in；Second O-ring seals 12 together with being lined with between the bottom edge of base with the outer mold surface lower edge of flexible blanking cover bonding plane, close
It is lined with the 4th O-ring seals between edge and the jet pipe diffuser 16 of envelope frock shrouding 1, as shown in Figure 4, thus ensures protuberance
1.1, the outer mold surface 18 of shrouding 1, base 2 and flexible blanking cover 11 bonding plane encloses formation confined space region 1, protuberance successively
1.1, shrouding 1 and jet pipe diffuser 16 enclose formation confined space region 2 14 successively；
Wherein: the first O-ring seals 13 had both prevented from weighing wounded in the metal position course of exerting pressure of shrouding 1 protuberance 1.1 flexible stifled
Covering 11 surfaces, the unsettled face of flexible blanking cover 11 19 that shrouding 1 lower end can be prevented again corresponding deforms in pressure process；And the first pressure
Table 5 mainly shows that the pressure in confined space region 1, the second Pressure gauge 6 mainly show the pressure in confined space region 2 14；
When confined space region 1 is suppressed, judge whether confined space region 1 seals by observing the second Pressure gauge 6
Well；
4) detect whether confined space region 1 fully seals by second Pressure gauge 6 in confined space region 2 14；
Detailed process is as follows:
After sealing frock is installed on jet pipe, by suppressing joint 4, is pressurizeed in confined space region 1, if the second pressure
The numerical value of table 6 does not changes, then confined space region 1 fully seals, otherwise, then seal the most intact；
5), after sealing property detection, again by suppressing joint 4, is pressurizeed in confined space region 1, sealing frock
The first Pressure gauge 5 show the pressure in confined space region 1, after being pressurized to preset value, the force value of this pressurization is by calculating
Obtaining, such as, require that pressure weight weight is 180kg in certain model flexibility blanking cover technique for sticking code, weight pressure area is
86800mm2, the pressure being computed test pressurization is 0.02MPa, after then room temperature pressurize solidifies 24～48 hours, removes and seals
Frock；
6) step 5) remove after sealing frock, the jet pipe after bonding is carried out air-leakage test with flexible blanking cover 11, in order to
Checking bonding quality.
Above-mentioned steps 4) and step 5) in by suppress joint 4 can to confined space region 1 gas that used of pressurization
To be air, nitrogen or noble gas.
The adhering method of solid rocket motor nozzle of the present invention with flexible blanking cover is applied to 5 kinds (every kind amounts to 10)
Solid rocket motor nozzle and the bonding process of flexible blanking cover, examine through air-tight test, and qualification rate reaches 100%, viscous
Connect quality to significantly improve, and due to the most bonding, the manufacturing cycle of every shortens 40% relatively.
Claims (10)
1. a solid rocket motor nozzle and the adhering method of flexible blanking cover, it is characterised in that: described adhering method is soft
Property blanking cover (11) pre-with jet pipe throat lining (10) viscous after, sealing frock is installed on jet pipe so that flexible blanking cover (11) with seal
Frock forms confined space region one (15) after matching, and pressurizes confined space region one (15), uses the side of air pressure
Formula outer mold surface (18) pressurization to flexible blanking cover (11) with jet pipe throat lining (10) bonding plane (17), last pressurize solidifies.
Solid rocket motor nozzle the most according to claim 1 and the adhering method of flexible blanking cover, it is characterised in that: institute
State adhering method and specifically include following steps:
1) it is coated with epoxy glue on the bonding plane of jet pipe throat lining (10), flexibility blanking cover (11) is adhered on jet pipe throat lining (10) in advance；
2) being installed on jet pipe by sealing frock, the edge of sealing frock shrouding (1) is by bolt (7) and jet pipe diffuser
(116) fixed installation, protuberance (1.1) bottom surface of sealing frock shrouding (1) is against the outer mold surface of flexible blanking cover (11) bonding plane
(18) upper limb, base plate (2.2) edge of sealing frock base (2) is against under the outer mold surface (18) of flexible blanking cover (11) bonding plane
Edge, it is airtight that the outer mold surface (18) of protuberance (1.1), shrouding (1), base (2) and flexible blanking cover (11) bonding plane encloses formation successively
Area of space one (15), protuberance (1.1), shrouding (1) and jet pipe diffuser (16) enclose formation confined space region two successively
(14)；
3) by suppress joint (4) to confined space region one (15) pressurize, first Pressure gauge (5) of sealing frock shows airtight
The pressure of area of space one (15), after being pressurized to preset value, room temperature pressurize solidifies, and then removes sealing frock.
Solid rocket motor nozzle the most according to claim 2 and the adhering method of flexible blanking cover, it is characterised in that: institute
State step 3) remove after sealing frock, the jet pipe after bonding is carried out air-leakage test with flexible blanking cover (11).
4., according to the adhering method of the solid rocket motor nozzle described in Claims 2 or 3 with flexible blanking cover, its feature exists
In: described step 1) in, after flexible blanking cover (11) adheres on jet pipe throat lining (10) in advance, the axis of flexible blanking cover (11) and jet pipe larynx
The axis offset distance of lining (10) must not exceed 1mm.
5., according to the adhering method of the solid rocket motor nozzle described in Claims 2 or 3 with flexible blanking cover, its feature exists
In: carrying out described step 1) before, after the bonding plane of the bonding plane of jet pipe throat lining (10) and flexible blanking cover (11) is all polished, use
Acetone cleans.
6., according to the adhering method of the solid rocket motor nozzle described in Claims 2 or 3 with flexible blanking cover, its feature exists
In: complete described step 2) after, detect confined space region one by second Pressure gauge (6) in confined space region two (14)
(15) whether fully seal；Detailed process is as follows:
After sealing frock is installed on jet pipe, by suppressing joint (4), is pressurizeed in confined space region one (15), if the second pressure
The numerical value of table (6) does not changes, then confined space region one (15) fully seals, otherwise, then seal the most intact.
7., according to the adhering method of the solid rocket motor nozzle described in Claims 2 or 3 with flexible blanking cover, its feature exists
In: it is lined with between protuberance (1.1) bottom surface and outer mold surface (18) upper limb of described flexible blanking cover (11) bonding plane of described shrouding (1)
First O-ring seals (13)；Base plate (2.2) edge of described base (2) and the outer mold surface of described flexible blanking cover (11) bonding plane
(18) the second O-ring seals (12) it is lined with between lower edge；Support bar (2.1) face, outer peripheral edge of described base (2) and described shrouding
(1) it is lined with the 3rd O-ring seals (8) between support bar connecting hole inwall；The edge of described sealing frock shrouding (1) is with described
Jet pipe diffuser is lined with the 4th O-ring seals between (16).
8. the sealing work designed for solid rocket motor nozzle described in claim 1 and flexible blanking cover adhering method
Dress, it is characterised in that: described sealing frock includes shrouding (1) and base (2), and described base (2) includes base plate (2.2) and connects
Support bar (2.1) on base plate (2.2), the upper end (2.3) of described support bar (2.1) is fixedly mounted on described shrouding (1)
Middle part；Described shrouding (1) lower surface has downwardly extended a circle protuberance (1.1), and described protuberance (1.1) is positioned at the described end
The outside of plate (2.2)；Described sealing frock also includes being positioned at inside described protuberance (1.1) and being arranged on described shrouding (1)
Suppress joint (4).
Sealing frock the most according to claim 8, it is characterised in that: described sealing frock also includes being positioned at described protuberance
(1.1) inner side and the first Pressure gauges (5) of being arranged on described shrouding (1) and be positioned at described protuberance (1.1) outside and peace
The second Pressure gauge (6) being contained on described shrouding (1).
Sealing frock the most according to claim 8 or claim 9, it is characterised in that: the upper end (2.3) of described support bar (2.1)
It is inserted in the support bar connecting hole of described shrouding (1) middle part until extending in the intermediate throughholes of pressing plate (3), described pressure
Plate (3) is bolted and is fitted on described shrouding (1), and support bar (2.1) face, outer peripheral edge of described base (2) is with described
It is lined with the 3rd O-ring seals (8) between the support bar connecting hole inwall of shrouding (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610767311.XA CN106287101B (en) | 2016-08-30 | 2016-08-30 | The adhering method and sealing frock of solid rocket motor nozzle and flexible blanking cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610767311.XA CN106287101B (en) | 2016-08-30 | 2016-08-30 | The adhering method and sealing frock of solid rocket motor nozzle and flexible blanking cover |
Publications (2)
| Publication Number | Publication Date |
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| CN106287101A true CN106287101A (en) | 2017-01-04 |
| CN106287101B CN106287101B (en) | 2018-05-22 |
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| CN106979095A (en) * | 2017-05-08 | 2017-07-25 | 湖北航天技术研究院总体设计所 | The integrated jet pipe and its manufacture method of a kind of global formation |
| CN107191291A (en) * | 2017-07-13 | 2017-09-22 | 西安航天动力研究所 | The dust guard and its installation method of a kind of engine |
| CN109014900A (en) * | 2018-09-04 | 2018-12-18 | 湖北三江航天江北机械工程有限公司 | The assembly method of flexible joint nozzle |
| CN109083767A (en) * | 2018-07-26 | 2018-12-25 | 西安航天动力技术研究所 | A kind of solid rocket motor nozzle thin-wall case hydraulic test device |
| CN110259608A (en) * | 2019-06-19 | 2019-09-20 | 湖北三江航天红峰控制有限公司 | A kind of solid rail control engine jet pipe blanking cover |
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| CN112324595A (en) * | 2020-11-03 | 2021-02-05 | 西安航天动力技术研究所 | Putty removal and heat removal protection structure for front swing core flexible spray pipe |
| CN114215834A (en) * | 2021-11-25 | 2022-03-22 | 宁波天擎航天科技有限公司 | Rocket engine nozzle plug assembling device and method |
| CN114986413A (en) * | 2022-06-22 | 2022-09-02 | 四川航天长征装备制造有限公司 | Rocket engine jet pipe bonding clamping device |
| CN115263602A (en) * | 2022-07-28 | 2022-11-01 | 湖北三江航天江北机械工程有限公司 | Method for bonding submerged type plug cover of solid rocket engine nozzle |
| CN116221533A (en) * | 2023-05-09 | 2023-06-06 | 中国航发沈阳发动机研究所 | High-reliability sealing structure of engine pressing joint |
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| CN104696110A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Rubber blanking cap of guided missile engine exhaust nozzle |
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| CN114215834A (en) * | 2021-11-25 | 2022-03-22 | 宁波天擎航天科技有限公司 | Rocket engine nozzle plug assembling device and method |
| CN114986413A (en) * | 2022-06-22 | 2022-09-02 | 四川航天长征装备制造有限公司 | Rocket engine jet pipe bonding clamping device |
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| CN115263602A (en) * | 2022-07-28 | 2022-11-01 | 湖北三江航天江北机械工程有限公司 | Method for bonding submerged type plug cover of solid rocket engine nozzle |
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