CN107664465B - A kind of guided missile endpiece bottom thermal protection and heat seal structure - Google Patents
A kind of guided missile endpiece bottom thermal protection and heat seal structure Download PDFInfo
- Publication number
- CN107664465B CN107664465B CN201710718674.9A CN201710718674A CN107664465B CN 107664465 B CN107664465 B CN 107664465B CN 201710718674 A CN201710718674 A CN 201710718674A CN 107664465 B CN107664465 B CN 107664465B
- Authority
- CN
- China
- Prior art keywords
- annular
- sealing ring
- flexible graphite
- metal
- metal substrate
- 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.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
- F16J15/102—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing characterised by material
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Gasket Seals (AREA)
Abstract
The present invention provides a kind of bottom thermal protections of guided missile endpiece and heat seal structure, it should include the cyclic annular high silicone/phenolic resin heat shield panel of lamination, Metal Substrate flexible graphite sealing ring and annular metal bottom plate, annular metal bottom plate inside cross-sectional is in step-like, annular metal bottom plate is fixedly connected with high silicone/phenolic resin heat shield panel is laminated, an annular groove is formed in inside, Metal Substrate flexible graphite sealing ring is spliced by planar annular and ring wall surface, its ring section is " Γ " shape, the planar annular of Metal Substrate flexible graphite sealing ring is embedded in annular groove, the Metal Substrate flexible graphite sealing ring ring wall surface vertical with planar annular extends to annular metal bottom plate direction, annular metal bottom plate is fixedly mounted on missile tail bottom metal shell, Metal Substrate flexible graphite sealing ring ring wall surface is sleeved on the outside of engine jet pipe, Metal Substrate is soft Property the graphite-seal ring coefficient of expansion and temperature rise be less than engine jet pipe, deformed with engine jet pipe, realize dynamic thermal protection and heat seal.
Description
Technical field
The present invention designs a kind of thermal protection and heat seal structure, is particularly suitable for supersonic cruising guided missile solid engines
The thermal protection and heat seal structure of endpiece bottom, belong to the anti-Design on thermal insulation skill in supersonic cruising guided missile solid engines endpiece bottom
Art field.
Background technique
Supersonic cruising guided missile has extremely with every war technical ability power such as outstanding " intercept, destroy, motor-driven, threat "
Important business and application value in army.With the continuous improvement of missile flight speed, the thermal environment as caused by Aerodynamic Heating becomes
Must be more and more harsher, it is mainly shown as that Aerodynamic Heating temperature is higher and higher, heating time is more and more lasting.Especially supersonic speed is patrolled
The high density radiant heat flux heating of SRM Nozzle flame is born in the endpiece bottom of boat guided missile SRM Nozzle always,
Thermal environment condition is extremely harsh, and endpiece bottom is up to 1400 DEG C~1600 DEG C close to the temperature of jet pipe attachment.In solid engines
Working time section, the radial unilateral dilatancy about 3mm of engine, and engine jet pipe exit end face is relative to nozzle throat end
Face extends about 2.5mm, the radial unilateral dilatancy about 1mm of jet pipe.Installation is controlled by steering engine controller, de- insert in endpiece shell section
The instrument and equipments such as device, operating temperature requirements are 155 DEG C or less.Therefore, supersonic cruising guided missile solid engines endpiece bottom tail
Section bottom thermal protection structure need to meet thermal deformation matching, thermal protection and heat seal and require.
Inside bury endpiece shell section shape envelope Φ 600mm × φ 589mm × 550mm of intermediate range supersonic speed air-to-ground guided missile, bottom
The installation space 10.0mm of heat shield panel, the prominent endpiece shell section outer end face 1mm of engine jet pipe exit end face.Motors in boost phase penetration solid starts
Machine operating time about 21s, greatest irradiation hot-fluid are 508.88kW/m2。
The base heat protection plate of current endpiece shell section mostly uses TR-42B thermal protective coating+metallic matrix thermal protection struc ture shape
Formula, this method form is simple, be only applicable to the prominent endpiece shell section outer end face super large distance of engine jet pipe exit end face (L >=
150mm) and base heat protection plate and engine jet pipe are not necessarily to the design condition of seal approach, are not suitable for engine jet pipe outlet end
The work operating condition in the face prominent extra small distance of endpiece shell section outer end face (L=1.0mm).
Summary of the invention
Technology of the invention solves the problems, such as: it is anti-to overcome the deficiencies of the prior art and provide a kind of guided missile endpiece Base Heat
Shield and heat seal structure, the structure is using the high silicone/phenolic resin heat shield panel+Metal Substrate flexible graphite sealing ring+endless metal of lamination
Plate realizes the extra small dynamic heat seal under of the prominent endpiece shell section outer end face of engine jet pipe exit end face.
The technical solution of the invention is as follows: a kind of guided missile endpiece bottom thermal protection and heat seal structure, feature exist
In including the high silicone/phenolic resin heat shield panel of cyclic annular lamination, Metal Substrate flexible graphite sealing ring and annular metal bottom plate, it is laminated high silicon
Oxygen/carbon/phenolic heat insulating plate is annular, and internal diameter is greater than the engine jet pipe outer diameter after expanded by heating, and outer diameter is less than or equal to endpiece gold
Belong to diameter of the housing, annular metal bottom plate inside cross-sectional is in step-like, annular metal bottom plate and to be laminated high silicone/phenolic resin heat shield panel solid
Fixed connection forms an annular groove in inside, Metal Substrate flexible graphite sealing ring by planar annular and ring wall surface splicing and
At ring section is " Γ " shape, and the planar annular of Metal Substrate flexible graphite sealing ring is embedded in annular groove, and Metal Substrate is soft
Property the graphite-seal ring ring wall surface vertical with planar annular extend to annular metal bottom plate direction, the fixed peace of annular metal bottom plate
On missile tail bottom metal shell, Metal Substrate flexible graphite sealing ring ring wall surface is sleeved on the outside of engine jet pipe,
The Metal Substrate flexible graphite sealing ring coefficient of expansion and temperature rise are less than engine jet pipe, deform with engine jet pipe, realize to guided missile
The dynamic thermal protection of tail portion bottom radiant heat flux and heat seal.
In axial direction, Metal Substrate flexible graphite sealing ring in groove with High-SiliconOxygen composites solar heat protection bottom plate and ring-type
Retain preset axial matching gap between metal base plate, the axial matching gap is greater than engine jet pipe in the axial direction
Thermal expansion deformation amount；Radially, the outer diameter of the outer diameter of the planar annular of Metal Substrate flexible graphite sealing ring and annular groove
Between retain preset radial matching gap, the radial matching gap is greater than engine jet pipe thermal expansion deformation in the radial direction
Amount.
The Metal Substrate flexible graphite sealing ring is that flexible expanded graphite adds stainless steel sleeve socks formula silk screen to enhance sealing ring.
The manufacturing process of the Metal Substrate flexible graphite sealing ring are as follows:
(1), soft graphite is made after compound acidification and high temperature puffing higher than 90% natural flake graphite using purity
Plate, and it is processed into flexible graphite strip or flexible graphite belt；
(2), graphite composite band is woven into using Inconel600 stainless steel wire and flexible graphite strip or flexible graphite belt；
(3), sealing ring is wound in using graphite composite band；
(4), a compression moulding in precision press molding mold by sealing ring.
Inconel600 of the diameter specifications are Φ 0.1mm~Φ 0.2mm.
The Metal Substrate flexible graphite sealing ring and the annular sealing surface surface roughness of engine jet pipe cooperation are Ra1.6
~Ra3.2.
The cyclic annular high silicone/phenolic resin heat shield panel of lamination is with a thickness of 6mm~7mm.
The annular metal base plate thickness is 3mm~4mm.
Ring-type is laminated high silicone/phenolic resin heat shield panel and uses the high silicon oxygen cloth glass epoxy BBS-CW116-86 material system of phenolic aldehyde
At.
Annular metal bottom plate is made of stainless steel 1Cr18Ni9Ti material.
Compared with the prior art, the invention has the advantages that:
(1), the present invention is less than the Metal Substrate flexible graphite sealing ring of engine jet pipe by the loop wire coefficient of expansion and temperature rise
Engine jet pipe is sealed, ensure that sealing ring is deformed with jet pipe, realizes the heat seal to radiant heat flux；
(2), the present invention is used to heat release, the temperature control upper limit 155 of opposite general requirement using high silicone/phenolic resin heat shield panel is laminated
DEG C index request, design safety surplus is 69.0%, realizes efficient anti-heat insulation；
(3), the present invention is using endless metal bottom plate as support plate, connection of the overall structure in radiant heating and aerodynamic loading
Under cooperation is used, the strong rigidity of structure is all satisfied overall objective requirement, realizes " solar heat protection carrying integration " target.
Detailed description of the invention
Fig. 1 is guided missile endpiece of the present invention bottom thermal protection and heat seal structural schematic diagram；
Fig. 2 is the high silicone/phenolic resin solar heat protection base plate size of the embodiment of the present invention；
Fig. 3 (a) is metal flexible of embodiment of the present invention graphite-seal ring overall dimension；
Fig. 3 (b) is the detailed dimensions in metal flexible of embodiment of the present invention graphite-seal ring section；
Fig. 3 (c) is the material structure of metal flexible of embodiment of the present invention graphite-seal ring；
Fig. 4 (a) is endless metal of embodiment of the present invention bottom plate overall dimension；
Fig. 4 (b) is the detailed dimensions in endless metal of embodiment of the present invention bottom plate section；
Fig. 4 (c) is that the de- of endless metal of embodiment of the present invention bottom plate inserts separation jack schematic diagram；
Fig. 4 (d) is that the anchor locking-nuts with twolug of endless metal of embodiment of the present invention bottom plate rivets schematic diagram；
Fig. 5 is the thermal protection of bottom of the embodiment of the present invention and each layer temperature curve for heating seal structure.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
Endpiece thermal protection and heat seal structure are mounted on the bottom of SRM Nozzle, for bottom radiant heat flux
Protection and sealing.
For supersonic cruising guided missile SRM Nozzle, a kind of bottom thermal protection of guided missile endpiece and heat is described below
The specific embodiment of sealing structure.
As shown in Figure 1, the thermal protection and heat seal structure are laminated high silicone/phenolic resin heat shield panel 1, Metal Substrate flexibility by ring-type
Graphite-seal ring 2 and annular metal bottom plate 3 form.High silicone/phenolic resin heat shield panel 1 is laminated as annular, internal diameter is swollen greater than being heated
Engine jet pipe outer diameter after swollen, outer diameter are less than or equal to endpiece metal shell diameter, and 3 inside cross-sectional of annular metal bottom plate is in platform
Scalariform, annular metal bottom plate 3 are fixedly connected with high silicone/phenolic resin heat shield panel 1 is laminated, and form an annular groove, gold in inside
Belong to base flexible graphite sealing ring 2 to be spliced by planar annular and ring wall surface, ring section is " Γ " shape, and Metal Substrate is flexible
The planar annular of graphite-seal ring 2 is embedded in annular groove, the ring vertical with planar annular of Metal Substrate flexible graphite sealing ring 2
Shape wall surface extends to 3 direction of annular metal bottom plate, and annular metal bottom plate 3 is fixedly mounted on missile tail bottom metal shell,
2 ring wall surface of Metal Substrate flexible graphite sealing ring is sleeved on the outside of engine jet pipe, the expansion of Metal Substrate flexible graphite sealing ring 2 system
Several and temperature rise is less than engine jet pipe, deforms with engine jet pipe, realizes anti-to the Dynamic Thermal of missile tail bottom radiant heat flux
Shield and heat seal.
In the present embodiment, engine jet pipe outer diameter is Φ 418mm, and endpiece metal shell diameter is Φ 589mm.It is sent out in solid
Motivation working time section, the radial unilateral dilatancy about 3mm of engine, and engine jet pipe exit end face is relative to jet pipe larynx
End surface extends about 2.5mm, the radial unilateral dilatancy about 1mm of jet pipe.
As shown in Fig. 2, it is laminated high 1 shape envelope of silicone/phenolic resin heat shield panel having a size of Φ 587mm × φ 430mm × 6mm,
It is made of the high silicon oxygen cloth glass epoxy BBS-CW116-86 material of phenolic aldehyde.Outer diameter with it is smaller than endpiece metal shell outer diameter, with it
Retain the gap 1mm, the gap 5mm is retained between internal diameter and booster jet pipe.
As shown in Fig. 3 (a), Fig. 3 (b), Fig. 3 (c), 2 shape envelope of Metal Substrate flexible graphite sealing ring is having a size of Φ 452mm
× φ 420mm × 25mm, cross sectional shape are " Γ " shape, and the Metal Substrate flexible graphite sealing ring 2 is that flexible expanded graphite adds not
The steel bushing socks formula silk screen that becomes rusty enhances sealing ring, density 1.9g/cm3, metal net core worked out using stainless steel wire, form ankle socks
Formula.Wherein, flexible expanded graphite can select QDa1036-2007, and metal net core should be well combined with flexible graphite layer, up and down
Two layers of flexible graphite is evenly distributed symmetrically, no obvious deviation.Sealing ring periphery should be neat, and sealing surface surface roughness is Ra3.2,
Piece surface is smooth, without obvious impurity, crackle, fold, scratch.Do not allow to be layered between graphite linings.
Metal Substrate flexible graphite sealing ring density is 1.9g/cm3, tensile strength be greater than 4.5MPa, compression ratio be greater than 18%,
Rebound degree, which is greater than at 15%, 1200 DEG C, keeps 10min thermal weight loss rate less than 10%.
As shown in Fig. 4 (a), Fig. 4 (b), Fig. 4 (c), Fig. 4 (d), annular metal bottom plate shape envelope having a size of Φ 587mm ×
φ 440mm × 8mm, material use stainless steel 1Cr18Ni9Ti.Retain the gap 1mm, internal diameter between outer diameter and endpiece metal shell
Retain the gap 5mm between soft Metal Substrate flexible graphite sealing ring.Annular metal bottom plate is as metal profile, for fixed peace
It fills flexible expanded graphite and heats seal structure, while de- slotting separating support function can also be integrated, as the circular hole in Fig. 4 (a) is
It is de- to insert separatory jack.In this way, the design and assembly of dedicated de- slotting bracket are reduced.
Overall structure is fixed on endpiece metal shell using 12 M6 screws by self-locking nut.High silicone/phenolic resin is multiple
It is connected using 8 M5 screws by self-locking nut between condensation material solar heat protection bottom plate and annular metal bottom plate.
Retain the gap 1mm between integrally-built outer diameter and endpiece metal shell.In the axial direction, Metal Substrate flexibility stone
Retain the gap 1mm between black sealing ring 2 and High-SiliconOxygen composites solar heat protection bottom plate, annular metal bottom plate；In radial directions, golden
Belong to and retain the gap 5mm between base flexible graphite sealing ring 2 and annular metal bottom plate, for the deformation of booster bottom jet pipe
Matching and coordination.
In conclusion endpiece thermal protection of the invention and heat seal structure, by 6mm be laminated high silicone/phenolic resin heat shield panel+
Metal Substrate flexible graphite sealing ring+3mm annular metal bottom plate composition, the structure technology are stablized, and installing and dismounting is easy, thermal protection with
And heat seal significant effect, easily fabricated and batch production.May be implemented model critical product " low cost, quick response, quickly
The target of manufacture ".Specific production process is as follows:
Firstly, requiring according to design drawing, processing and manufacturing 6mm is laminated high silicone/phenolic resin heat shield panel, and material property is according to mark
Quasi- specification " BBS-CW116-86 high silicone/phenolic resin cloth glass epoxy " is examined.Fabricate the ring of the stainless 1Cr18Ni9Ti of 3mm
Shape metal base plate rivets 8 M5 anchor locking-nuts with twolug at the annular metal bottom plate back side using sunk head rivet 2.5 × 8.
Then, design and processing precise press-moulding die prepare Metal Substrate flexible graphite sealing ring.
The manufacturing process of the Metal Substrate flexible graphite sealing ring are as follows:
(1), soft graphite is made after compound acidification and high temperature puffing higher than 90% natural flake graphite using purity
Plate, and it is processed into flexible graphite strip or flexible graphite belt；
(2), graphite composite band is woven into using Inconel600 stainless steel wire and flexible graphite strip or flexible graphite belt；
Inconel600 of the diameter specifications are Φ 0.1mm~Φ 0.2mm
(3), sealing ring is wound in using graphite composite band；
(4), by sealing ring, a compression moulding obtains the gold for meeting design drawing requirement in precision press molding mold
Belong to base flexible graphite sealing ring, " the Q/Dp030-2016 soft graphite metallic composite sealing of material property establishing criteria specification
Ring " it examines.It is as shown in Figure 5 by the metal flexible graphite-seal ring product pictorial diagram of precision press molding.
Then, during the installation process, annular metal bottom plate is first packed by tail end shell according to quadrant wire tag, Metal Substrate is soft
Property graphite-seal ring is sleeved on SRM Nozzle, the hickey of jet pipe and solid engines is spirally connected fixation, at this time
Metal Substrate flexible graphite sealing ring naturally falls in annular metal bottom plate and the cyclic annular groove being laminated between high silicone/phenolic resin heat shield panel
It is interior.High silicone/phenolic resin heat shield panel is packed into tail end shell again according to quadrant wire tag, at this time high silicone/phenolic resin heat shield panel pressure
In annular metal substrate, Metal Substrate flexible graphite sealing can radial motion 5mm, axial movement in the groove that the two is formed
1.0mm。
Finally, overall structure is fixed on endpiece metal shell by self-locking nut using 12 M6 screws.High silicon oxygen
It is connected using 8 M5 screws by self-locking nut between composite material solar heat protection bottom plate and annular metal bottom plate.Loading moment fastening,
It completes endpiece thermal protection and heats seal integrally-built connection.
Embodiment
Soft graphite as defined in standard and Metal Substrate flexible graphite sealing ring physical mechanical property are as shown in Table 1 and Table 2.
Soft graphite and the Metal Substrate flexible graphite sealing ring physical mechanical property for surveying product are as shown in Table 3 and Table 4.Measured value with
Better than set quota.
The physical mechanical property of soft graphite as defined in table 1
| Performance | Index |
| Density (g/cm3) | 1.1±0.05 |
| Tensile strength (MPa) | >3.5 |
| Compression ratio (%) | ≥40 |
| Rebound degree (%) | ≥15 |
| 670 DEG C of thermal weight loss rate, 1h (%) | <3 |
The physical mechanical property of Metal Substrate flexible graphite sealing ring as defined in table 2
| Performance | Index |
| Density (g/cm3) | 1.9±0.1 |
| Tensile strength (MPa) | ≥4.5 |
| Compression ratio (%) | 18~30 |
| Rebound degree (%) | ≥15 |
| 1200 DEG C of thermal weight loss rate, 10min (%) | ≤10 |
The physical mechanical property for the soft graphite that table 3 is surveyed
| Performance | Index |
| Bulk density (g/cm3) | 1.1 |
| Tensile strength (MPa) | 3.6 |
| Compression ratio (%) | 47 |
| Rebound degree (%) | 19 |
| 670 DEG C of thermal weight loss rate, 1h (%) | 0.95 |
The physical mechanical property for the Metal Substrate flexible graphite sealing ring that table 4 is surveyed
| Performance | Index |
| Density (g/cm3) | 1.9 |
| Tensile strength (MPa) | 4.71 |
| Compression ratio (%) | 23.73 |
| Rebound degree (%) | 23.40 |
| 1200 DEG C of thermal weight loss rate, 10min (%) | 5.34 |
As indicated with 6, the mild most radiant heat stream 508.88kW/m as at the beginning of 35 DEG C2It calculates, using made of the method for the present invention
6mm is laminated high silicone/phenolic resin heat shield panel+Metal Substrate flexible graphite sealing ring+3mm annular metal bottom plate thermal protection and heat seal is tied
Structure inner wall temperature is only up to 48 DEG C, 155 DEG C of the temperature control upper limit of index request of opposite general requirement, and design safety surplus is
69.0%, realize efficient anti-heat insulation.
The prominent endpiece shell section outer end face distance of engine jet pipe exit end face is only 1mm, in the solid engines working time
Section, engine is radial and axial and jet pipe is radial has expansion in various degree.Metal Substrate flexible graphite sealing ring is sleeved on
On engine jet pipe, sealing ring linear expansion coefficient and temperature rise are less than engine jet pipe, therefore ensure that sealing ring is deformed with jet pipe,
Realize the heat seal to radiant heat flux.It is prominent that the endpiece thermal protection and heat seal structure realize engine jet pipe exit end face
The extra small dynamic heat seal under of endpiece shell section outer end face.
It is greater than 168MPa, bending greater than 130MPa, compressive strength in addition, being laminated high silicone/phenolic resin heat shield panel tensile strength
Intensity is greater than 200MPa, line ablation velocity is less than 0.0587mm/s, and solar heat protection back has stainless 1Cr18Ni9Ti annular metal bottom
Plate is as support plate, and under the synergy of radiant heating and aerodynamic loading, the strong rigidity of structure is all satisfied to be referred generally to overall structure
Mark requires, and realizes " solar heat protection carrying integration " target.
The content not being described in detail in description of the invention belongs to the common knowledge of those skilled in the art.
Claims (10)
1. a kind of bottom thermal protection of guided missile endpiece and heat seal structure, it is characterised in that be laminated high silicone/phenolic resin including ring-type
Heat shield panel (1), Metal Substrate flexible graphite sealing ring (2) and annular metal bottom plate (3), being laminated high silicone/phenolic resin heat shield panel (1) is
Annular, internal diameter are greater than the engine jet pipe outer diameter after expanded by heating, and outer diameter is less than or equal to endpiece metal shell diameter, cyclic annular
Metal base plate (3) inside cross-sectional is in step-like, annular metal bottom plate (3) and the fixed company of the high silicone/phenolic resin heat shield panel (1) of lamination
Connect, inside formed an annular groove, Metal Substrate flexible graphite sealing ring (2) by planar annular and ring wall surface splicing and
At ring section is " Γ " shape, and the planar annular of Metal Substrate flexible graphite sealing ring (2) is embedded in annular groove, metal
Base flexible graphite sealing ring (2) ring wall surface vertical with planar annular extends to annular metal bottom plate (3) direction, annular metal
Bottom plate (3) is fixedly mounted on missile tail bottom metal shell, and Metal Substrate flexible graphite sealing ring (2) ring wall surface is sleeved on
On the outside of engine jet pipe, Metal Substrate flexible graphite sealing ring (2) coefficient of expansion and temperature rise are less than engine jet pipe, spray with engine
Pipe deformation, realizes the dynamic thermal protection to missile tail bottom radiant heat flux and heat seal.
2. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: along axis
To direction, Metal Substrate flexible graphite sealing ring (2) in groove be laminated high silicone/phenolic resin heat shield panel (1) and annular metal bottom
Retain preset axial matching gap between plate (3), the axial matching gap is greater than the heat of engine jet pipe in the axial direction
Dilatancy amount；Radially, the outer diameter of the outer diameter of the planar annular of Metal Substrate flexible graphite sealing ring (2) and annular groove
Between retain preset radial matching gap, the radial matching gap is greater than engine jet pipe thermal expansion deformation in the radial direction
Amount.
3. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: described
Metal Substrate flexible graphite sealing ring (2) is that flexible expanded graphite adds stainless steel sleeve socks formula silk screen to enhance sealing ring.
4. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that described
The manufacturing process of Metal Substrate flexible graphite sealing ring are as follows:
(1), flexible graphite sheet material is made after compound acidification and high temperature puffing higher than 90% natural flake graphite using purity,
And it is processed into flexible graphite strip or flexible graphite belt；
(2), graphite composite band is woven into using Inconel600 stainless steel wire and flexible graphite strip or flexible graphite belt；
(3), sealing ring is wound in using graphite composite band；
(4), a compression moulding in precision press molding mold by sealing ring.
5. a kind of guided missile endpiece bottom thermal protection according to claim 4 and heat seal structure, it is characterised in that: described
Inconel600 diameter specifications are Φ 0.1mm~Φ 0.2mm.
6. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: described
Metal Substrate flexible graphite sealing ring (2) and the annular sealing surface surface roughness of engine jet pipe cooperation are Ra1.6~Ra3.2.
7. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: described
Ring-type is laminated high silicone/phenolic resin heat shield panel (1) with a thickness of 6mm~7mm.
8. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: described
Annular metal bottom plate (3) is with a thickness of 3mm~4mm.
9. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: cyclic annular
High silicone/phenolic resin heat shield panel (1) is laminated to be made of the high silicon oxygen cloth glass epoxy BBS-CW116-86 material of phenolic aldehyde.
10. a kind of guided missile endpiece bottom thermal protection according to claim 1 and heat seal structure, it is characterised in that: ring
Shape metal base plate (3) is made of stainless steel 1Cr18Ni9Ti material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710718674.9A CN107664465B (en) | 2017-08-21 | 2017-08-21 | A kind of guided missile endpiece bottom thermal protection and heat seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710718674.9A CN107664465B (en) | 2017-08-21 | 2017-08-21 | A kind of guided missile endpiece bottom thermal protection and heat seal structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107664465A CN107664465A (en) | 2018-02-06 |
| CN107664465B true CN107664465B (en) | 2019-06-18 |
Family
ID=61096994
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710718674.9A Active CN107664465B (en) | 2017-08-21 | 2017-08-21 | A kind of guided missile endpiece bottom thermal protection and heat seal structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107664465B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112343737A (en) * | 2020-10-12 | 2021-02-09 | 中国运载火箭技术研究院 | Carrier rocket |
| CN114479679B (en) * | 2022-02-07 | 2023-06-20 | 长春长光宇航复合材料有限公司 | Bonding method for double-matching-surface metal shell of large-size engine spray pipe |
| CN115143847B (en) * | 2022-07-28 | 2024-07-19 | 西安现代控制技术研究所 | Heat-seal-preventing composite structure for tail of remote rocket |
| CN116495162B (en) * | 2023-06-28 | 2023-10-17 | 北京玻钢院复合材料有限公司 | Bottom shielding plate assembly for aircraft and preparation method thereof |
| CN117145654B (en) * | 2023-10-27 | 2024-03-15 | 西安现代控制技术研究所 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
| CN117145655B (en) * | 2023-10-27 | 2024-03-19 | 西安现代控制技术研究所 | Flexible heat-proof sealing structure for jet pipe and tail cabin of solid rocket engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4523765A (en) * | 1983-06-07 | 1985-06-18 | Norton Christensen, Inc. | High pressure sealing means for longitudinally movable parts of deep-well drilling tools |
| CN103322867A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Missile rain-proof cover device |
| CN103759597A (en) * | 2014-01-14 | 2014-04-30 | 北京航空航天大学 | Missile cabin radial monoclinic bushing bolt connection structure |
| CN106678476A (en) * | 2017-02-20 | 2017-05-17 | 江苏丰禾机械制造股份有限公司 | Sleeve-type dynamic seal compensator |
-
2017
- 2017-08-21 CN CN201710718674.9A patent/CN107664465B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4523765A (en) * | 1983-06-07 | 1985-06-18 | Norton Christensen, Inc. | High pressure sealing means for longitudinally movable parts of deep-well drilling tools |
| CN103322867A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Missile rain-proof cover device |
| CN103759597A (en) * | 2014-01-14 | 2014-04-30 | 北京航空航天大学 | Missile cabin radial monoclinic bushing bolt connection structure |
| CN106678476A (en) * | 2017-02-20 | 2017-05-17 | 江苏丰禾机械制造股份有限公司 | Sleeve-type dynamic seal compensator |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107664465A (en) | 2018-02-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107664465B (en) | A kind of guided missile endpiece bottom thermal protection and heat seal structure | |
| EP2781344B1 (en) | Method of manufacturing a portion of a wind turbine blade | |
| CN101648598B (en) | Novel inorganic thermal protection structure and manufacturing method thereof | |
| CN106197938B (en) | Free jet dynamometer check model insulation system | |
| CN111016004B (en) | Heat-proof structure of fairing and forming method thereof | |
| US20080290191A1 (en) | Integral composite rocket motor dome/nozzle structure | |
| CN102562306A (en) | Nose cone assembly | |
| US8813626B2 (en) | 3D braided composited tubes with throat sections and manufacture method thereof | |
| US10641178B2 (en) | Fire protection of a fan casing made of composite | |
| CN110588014B (en) | 2.5D composite material spray pipe expansion section and co-curing forming method thereof | |
| GB2483962A (en) | High voltage bushing flange | |
| CN108183303A (en) | Conformal active radar and passive radar seeker antenna cover and forming method | |
| KR100831309B1 (en) | Method for reinforcement manufacturing a composite sabot applying band/hoop lamination | |
| CN110591356A (en) | Wave-transparent composite material half cover and preparation method thereof | |
| KR100831310B1 (en) | Method for reinforcement manufacturing a composite sabot improving the composite interfacial characteristic as applying a short fiber | |
| CN205997432U (en) | Rocket composite material casing | |
| CN107567381B (en) | Method for producing a composite component | |
| CN107745028B (en) | High magnesium-rare earth coupling barrel deformation temperature field control tooling and control method | |
| EP2913178B1 (en) | Cylindrical case and method for manufacturing cylindrical case | |
| CN111361743B (en) | Composite material air inlet channel and preparation method thereof | |
| US10576671B2 (en) | Method of connecting a skirt to a thruster body casing | |
| CN205837233U (en) | A kind of electromagnetic shielding high-strength interlayer pipe | |
| RU2316088C1 (en) | Flying vehicle antenna fairing | |
| CN213636303U (en) | Assembly structure assembly of radome nose cone and connecting ring | |
| CN107514939B (en) | Rocket Composite Shell |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |