CN117145654B - Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe - Google Patents
Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe Download PDFInfo
- Publication number
- CN117145654B CN117145654B CN202311407022.5A CN202311407022A CN117145654B CN 117145654 B CN117145654 B CN 117145654B CN 202311407022 A CN202311407022 A CN 202311407022A CN 117145654 B CN117145654 B CN 117145654B
- Authority
- CN
- China
- Prior art keywords
- tail
- sealing ring
- spray pipe
- heat
- proof plate
- 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
- 238000007789 sealing Methods 0.000 title claims abstract description 197
- 239000007921 spray Substances 0.000 title claims abstract description 104
- 229920001971 elastomer Polymers 0.000 claims description 49
- 239000002184 metal Substances 0.000 abstract description 17
- 238000003860 storage Methods 0.000 abstract description 10
- 239000002131 composite material Substances 0.000 description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 6
- 229910002804 graphite Inorganic materials 0.000 description 6
- 239000010439 graphite Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 229920002379 silicone rubber Polymers 0.000 description 6
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 239000003365 glass fiber Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000010923 batch production Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 239000003292 glue Substances 0.000 description 3
- BKGYVGAGCKBQTL-UHFFFAOYSA-N phenoxybenzene;silicon Chemical compound [Si].C=1C=CC=CC=1OC1=CC=CC=C1 BKGYVGAGCKBQTL-UHFFFAOYSA-N 0.000 description 3
- 239000000377 silicon dioxide Substances 0.000 description 3
- BKUKXOMYGPYFJJ-UHFFFAOYSA-N 2-ethylsulfanyl-1h-benzimidazole;hydrobromide Chemical compound Br.C1=CC=C2NC(SCC)=NC2=C1 BKUKXOMYGPYFJJ-UHFFFAOYSA-N 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000000748 compression moulding Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- -1 phenolic aldehyde Chemical class 0.000 description 2
- 239000004945 silicone rubber Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000012763 reinforcing filler Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gasket Seals (AREA)
Abstract
The invention provides a low-cost bullet tail heat-resistant sealing structure capable of adapting to deformation of a spray pipe, which solves the problems of bullet tail sealing of a missile in a storage and transportation state and failure of a metal sealing ring of the missile in a working state; the scheme adopted by the invention is that a sealing ring with a flanging is arranged at the tail of the bullet, and the sealing ring is embedded into a groove of a heat-proof plate of the tail of the bullet; the gap value reserved between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe is larger than the sum of the unilateral thermal expansion deformation and the radial swing amplitude when the engine spray pipe works; when the engine works, thermal expansion deformation of the engine spray pipe can compensate the gap between the outer wall of the spray pipe and the inner ring of the tail sealing ring, and when the engine spray pipe drives the tail sealing ring to swing radially together, the tail sealing ring flanging moves in a cavity formed by the tail heat-proof plate and the tail cabin rear end frame, and dynamic sealing putty is filled in the tail sealing ring flanging and the bottom surface of the tail heat-proof plate groove, so that the tightness of the engine spray pipe and the tail cabin is ensured while the engine spray pipe is adapted to radial swing.
Description
Technical Field
The invention belongs to the technical field of remote rocket structure design, and particularly relates to a heat-seal-preventing composite structure of a tail of a bullet.
Background
The tail cabin is a cabin section arranged on the rear skirt of the rocket engine, the engine spray pipe penetrates through the cabin section, and a control system executing mechanism and equipment are arranged in the cabin in an adhering manner. Under the working state of the engine, the engine rear end enclosure can drive the jet pipe to extend along the axial direction, and meanwhile, the engine jet pipe can also generate radial thermal expansion deformation and radial swing. Engineering researches show that when the composite material shell engine with the diameter of a combustion chamber of 1000mm and the diameter of a spray pipe of 600mm works, the rear end face of the spray pipe of the engine has the axial elongation of about 15mm, the thermal expansion deformation with a single side of about 1mm is generated along the radial direction, and the radial swing amplitude can reach 5mm. If the heat-proof sealing structure of the engine spray pipe and the tail cabin is unreasonable in design, on one hand, the tightness of the tail cabin in a storage and transportation state cannot be guaranteed, the long storage performance of the missile is affected, and on the other hand, high-temperature fuel gas working by the engine can flow through a gap between the spray pipe and the tail cabin and enter the tail cabin, so that high-temperature failure of equipment, cables, an actuating mechanism and the like in the cabin is caused. Radial swing of the engine spray pipe can also cause collision of the outer wall of the spray pipe and the tail cabin, so that reliability of equipment and an actuating mechanism in the tail cabin is affected, and in severe cases, the engine spray pipe is damaged to cause a flight accident.
The invention patent with the publication number of CN107664465B provides a heat protection and heat sealing structure of a missile tail section, which mainly comprises a laminated high silica/phenolic aldehyde heat-proof plate, a metal base flexible graphite sealing ring and an annular metal bottom plate, wherein the annular plane of the metal base flexible graphite sealing ring is embedded into an annular groove formed by the heat-proof plate and the metal bottom plate, and the annular wall is sleeved outside an engine spray pipe in an inward facing manner, so that the dynamic heat protection and sealing of the missile tail are realized. The patent reserves a gap between the metal-based flexible graphite sealing ring and the heat-proof plate as well as between the metal-based flexible graphite sealing ring and the metal bottom plate, and the sealing treatment is not carried out, so that the tail sealing of the missile in the storage and transportation state cannot be realized, and the long storage of the missile is not facilitated; the metal-based flexible graphite sealing ring is woven by adopting stainless steel wires and flexible graphite strips, is formed by a winding and compression molding process, has complex forming process and high cost, and is not beneficial to low-cost batch production.
The invention patent with the application publication number of CN115143847A sets up the metal seal ring between engine spray tube and the tail cabin, adopts the rubber seal ring to realize sealedly between spray tube and metal seal ring, designs to have the sunken in the tail anti-hot plate and the matched side of tail cabin, and the turn-ups card of rigid seal ring is gone into this sunken to can slide in the local sunken district between tail anti-hot plate and tail cabin along with the spray tube is whole, thereby prevent engine spray tube vibration transmission to the tail cabin. Although the manufacturing cost of the metal sealing ring is low, the clearance reserved between the metal sealing ring and the engine spray pipe needs to be effectively compressed to realize sealing, and the clearance value is difficult to adapt to the thermal expansion deformation of the engine spray pipe working for a long time; and for the engine spray pipe with larger radial swing amplitude, the clearance reserved between the inner ring of the bullet tail heat-proof plate and the outer wall of the engine spray pipe exposes an internal metal sealing ring, and the metal sealing ring is too high in temperature under the action of engine tail flame, so that the sealing ring contacted with the metal sealing ring is invalid.
Disclosure of Invention
The invention provides a low-cost tail heat-resistant sealing structure capable of adapting to spray pipe deformation, which aims to solve the problems of tail sealing of a missile in a storage and transportation state and failure of a metal sealing ring of the missile in a working state.
The technical scheme adopted for solving the technical problems is as follows:
a low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of a spray pipe comprises a tail cabin body, an engine spray pipe, a bullet tail sealing ring, a sealing rubber pad, a bullet tail heat-proof plate, dynamic sealing putty and screws; the tail cabin body is sleeved on the outer side of the engine spray pipe, and the rear end face of the tail cabin body is annular; the outer wall surface of the tail part of the jet nozzle of the engine is a cylindrical section; a gap is arranged between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe; a tail sealing ring is arranged at the annular inner diameter of the rear end face of the tail cabin body; the tail sealing ring is of a circular ring structure with a flanging, and the cross section of the tail sealing ring is L-shaped; the annular flanging of the tail sealing ring is attached to the rear end face of the tail cabin body; the ring-shaped structure of the tail sealing ring is sleeved on the outer wall of the sealing ring rubber pad; the sealing ring rubber pad is a cylindrical ring body with a rectangular cross section; the inner wall of the cylindrical ring body of the rubber gasket of the sealing ring is fixedly connected with the cylindrical section of the outer wall of the tail part of the engine spray pipe; the tail cabin body is provided with a tail heat-proof plate at the rear end face; the bullet tail heat-proof plate is a circular flat plate; the inner ring edge of the tail heat-proof plate is provided with a circular groove; the bullet tail heat-proof plate is provided with a plurality of countersunk holes; the tail heat-proof plate is fixed with the rear end face of the tail cabin body through screws; after the tail heat-proof plate is fixed, the flanging of the tail sealing ring is positioned in the tail heat-proof plate groove; and gaps in the flanging of the tail sealing ring and the groove of the tail heat-proof plate are filled with dynamic sealing putty.
The clearance value between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe is larger than the sum of the unilateral thermal expansion deformation and the radial swing amplitude when the engine spray pipe works.
The distance between the two bottom surfaces of the cylindrical section of the outer wall of the engine spray pipe is larger than the sum of the axial elongation of the engine spray pipe and the width of the tail sealing ring.
And a gap is arranged between the outer diameter of the groove of the bullet tail heat-proof plate and the outer diameter of the annular flanging of the bullet tail sealing ring.
The clearance value between the outer diameter of the bullet tail heat-proof plate groove and the outer diameter of the bullet tail sealing ring annular flanging is larger than the radial swing amount of the engine spray pipe during working.
And a gap is arranged between the outer diameter of the circular structure of the tail sealing ring and the inner diameter of the tail heat-proof plate.
The clearance value between the outer diameter of the bullet tail sealing ring and the inner diameter of the bullet tail heat-proof plate is larger than the radial swing amount of the engine spray pipe during working.
The depth of the tail heat-proof plate groove is larger than the flanging thickness of the tail sealing ring.
The contact length of the tail sealing ring flanging and the bottom surface of the tail heat-resistant plate groove along the radial direction is larger than the radial swing amount of the engine spray pipe.
The inner diameter of the bullet tail sealing ring is equal to the outer diameter of the sealing rubber pad bonded or vulcanized on the outer wall of the engine spray pipe.
The distance between the two bottom surfaces of the hollow cylindrical ring body of the sealing rubber gasket is equal to the width of the tail sealing ring, and the distance between the two bottom surfaces of the hollow cylindrical ring body of the sealing rubber gasket is smaller than the axial elongation of the engine spray pipe during working.
The difference between the outer ring radius and the inner ring radius of the hollow cylindrical ring body of the sealing rubber gasket is the same as the unilateral thermal expansion deformation amount of the engine spray pipe during working.
The sealing ring rubber pad is fixedly connected with the cylindrical section of the outer wall of the tail part of the engine spray pipe to be bonded by room temperature vulcanized silicone rubber.
The dynamic sealing putty is uncured phenyl ether silicon putty glue.
The tail heat-proof plate and the tail sealing ring are made of nonmetallic heat-proof composite materials.
The material of the bullet tail heat-proof plate and the bullet tail sealing ring is glass fiber/phenolic composite material or high silica/phenolic composite material.
The sealing rubber pad is made of silicon rubber.
The beneficial effects of the invention are as follows:
(1) In a missile storing and transporting state, the sealing rubber pad of the outer wall of the spraying pipe column section of the engine is sealed by the inner ring of the tail sealing ring, the flanging of the tail sealing ring and the bottom surface of the groove of the tail heat-proof plate are sealed by dynamic sealing putty, so that the sealing of the cabin body of the tail cabin is realized, a good storage environment is provided for the cabin body of the tail cabin of the missile, and long storage of the missile is facilitated.
(2) In the working state of the engine, the engine nozzle is axially stretched together with the sealing rubber gasket, the sealing rubber gasket can completely leave the inner ring of the tail sealing ring, and the thermal expansion deformation of the engine nozzle can compensate the gap between the outer wall of the nozzle and the inner ring of the tail sealing ring; when the engine spray pipe drives the tail sealing ring to swing radially together, the tail sealing ring flanging moves in a cavity formed by the tail heat-proof plate and the tail cabin body rear end frame, and dynamic sealing putty is filled in the tail sealing ring flanging and the tail heat-proof plate groove bottom surface, so that the tightness of the engine spray pipe and the tail cabin body can be ensured while the engine spray pipe is adapted to the radial swing of the engine spray pipe. The clearance reserved between the outer wall of the engine spray pipe and the rear end frame of the tail cabin body and between the tail sealing ring and the tail heat-proof plate can ensure that the engine spray pipe cannot collide with the tail heat-proof plate.
(3) The bullet tail heat-proof plate and the bullet tail sealing ring are both in flat plate annular structures, and the material is generally formed by adopting a glass fiber/phenolic aldehyde composite material with lower cost in a compression molding mode, so that the forming process is simple, the ablation resistance is excellent, and the cost is more beneficial to low-cost batch production compared with the prior art.
Drawings
FIG. 1 is a schematic view of a heat seal construction for a tail of a bullet;
FIG. 2 is a schematic cross-sectional view of a tail heat seal;
FIG. 3 is a schematic view of the structure of the tail shield;
FIG. 4 is a schematic cross-sectional view of the structure of the tail shield;
FIG. 5 is a schematic structural view of a tail seal ring;
FIG. 6 is a schematic structural cross-sectional view of a tail seal ring;
FIG. 7 is a schematic illustration of the attachment of a sealing rubber gasket to the outer wall of an engine nozzle.
Wherein 1 is a tail cabin body; 2 is a bullet tail heat-proof plate; 3 is a screw; 4 is dynamic sealing putty; 5 is a bullet tail sealing ring; 6 is a sealing rubber pad; 7 is an engine spray pipe; 8 is a bullet tail heat-proof plate groove outer ring; 9 is the bottom surface of the groove of the tail heat-proof plate; 10 is the depth of the groove of the tail heat-proof plate; 11 is the inner ring of the tail heat-proof plate; 12 is the flanging thickness of the tail sealing ring; 13 is a tail seal ring flanging; 14 is the width of the tail seal ring; 15 is a circular outer ring of the bullet tail sealing ring; 16 is a circular inner ring of the bullet tail sealing ring;
Detailed Description
The invention adopts the scheme that:
a low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of a spray pipe comprises a tail cabin body, an engine spray pipe, a bullet tail sealing ring, a sealing rubber pad, a bullet tail heat-proof plate, dynamic sealing putty and screws; the tail cabin body is sleeved on the outer side of the engine spray pipe, and the rear end face of the tail cabin body is annular; the outer wall surface of the tail part of the jet nozzle of the engine is a cylindrical section; a gap is arranged between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe; a tail sealing ring is arranged at the annular inner diameter of the rear end face of the tail cabin body; the tail sealing ring is of a circular ring structure with a flanging, and the cross section of the tail sealing ring is L-shaped; the annular flanging of the tail sealing ring is attached to the rear end face of the tail cabin body; the ring-shaped structure of the tail sealing ring is sleeved on the outer wall of the sealing ring rubber pad; the sealing ring rubber pad is a cylindrical ring body with a rectangular cross section; the inner wall of the cylindrical ring body of the rubber gasket of the sealing ring is fixedly connected with the cylindrical section of the outer wall of the tail part of the engine spray pipe; the tail cabin body is provided with a tail heat-proof plate at the rear end face; the bullet tail heat-proof plate is a circular flat plate; the inner ring edge of the tail heat-proof plate is provided with a circular groove; the bullet tail heat-proof plate is provided with a plurality of countersunk holes; the tail heat-proof plate is fixed with the rear end face of the tail cabin body through screws; after the tail heat-proof plate is fixed, the flanging of the tail sealing ring is positioned in the tail heat-proof plate groove; and gaps in the flanging of the tail sealing ring and the groove of the tail heat-proof plate are filled with dynamic sealing putty.
The clearance value between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe is larger than the sum of the unilateral thermal expansion deformation and the radial swing amplitude when the engine spray pipe works.
The distance between the two bottom surfaces of the cylindrical section of the outer wall of the engine spray pipe is larger than the sum of the axial elongation of the engine spray pipe and the width of the tail sealing ring.
And a gap is arranged between the outer diameter of the groove of the bullet tail heat-proof plate and the outer diameter of the annular flanging of the bullet tail sealing ring.
The clearance value between the outer diameter of the bullet tail heat-proof plate groove and the outer diameter of the bullet tail sealing ring annular flanging is larger than the radial swing amount of the engine spray pipe during working.
And a gap is arranged between the outer diameter of the circular structure of the tail sealing ring and the inner diameter of the tail heat-proof plate.
The clearance value between the outer diameter of the bullet tail sealing ring and the inner diameter of the bullet tail heat-proof plate is larger than the radial swing amount of the engine spray pipe during working.
The depth of the tail heat-proof plate groove is larger than the flanging thickness of the tail sealing ring.
The contact length of the tail sealing ring flanging and the bottom surface of the tail heat-resistant plate groove along the radial direction is larger than the radial swing amount of the engine spray pipe.
The inner diameter of the bullet tail sealing ring is equal to the outer diameter of the sealing rubber pad bonded or vulcanized on the outer wall of the engine spray pipe.
The distance between the two bottom surfaces of the hollow cylindrical ring body of the sealing rubber gasket is equal to the width of the tail sealing ring, and the distance between the two bottom surfaces of the hollow cylindrical ring body of the sealing rubber gasket is smaller than the axial elongation of the engine spray pipe during working.
The difference between the outer ring radius and the inner ring radius of the hollow cylindrical ring body of the sealing rubber gasket is the same as the unilateral thermal expansion deformation amount of the engine spray pipe during working.
The sealing ring rubber pad is fixedly connected with the cylindrical section of the outer wall of the tail part of the engine spray pipe to be bonded by room temperature vulcanized silicone rubber.
The sealing ring rubber pad is fixedly connected with the outer wall cylindrical section of the tail part of the engine spray pipe to be vulcanized on the outer wall cylindrical section of the engine spray pipe.
The dynamic sealing putty is uncured phenyl ether silicon putty glue.
The tail heat-proof plate and the tail sealing ring are made of nonmetallic heat-proof composite materials.
The material of the bullet tail heat-proof plate and the bullet tail sealing ring is glass fiber/phenolic composite material or high silica/phenolic composite material.
The sealing rubber pad is made of silicon rubber.
The invention will be further described with reference to the drawings and examples.
Referring to fig. 1 and 2, the low-cost bullet tail heat-proof sealing structure capable of adapting to nozzle deformation provided by the invention mainly comprises a tail cabin body 1, a bullet tail heat-proof plate 2, screws 3, dynamic sealing putty 4, bullet tail sealing rings 5, sealing rubber pads 6 and an engine nozzle 7.
The solid rocket engine with the working time of 50s and the outer diameter of the outer wall column section of the jet pipe of 600mm is taken as an embodiment, the axial elongation of the jet pipe of the engine is 15mm when the engine works, the radial unilateral thermal expansion deformation is 1mm, and the unilateral radial swing amount of the engine is 5mm when the engine works according to design analysis and ground static test. Referring to fig. 1 to 6, the rear end frame of the tail cabin body 1 is circular, two circles of threaded holes for installing the tail heat-proof plate 2 are arranged on the bottom surface, and the diameter of the rear end frame of the tail cabin body 1 is 614mm. The outer wall of the engine spray pipe 7 is a cylindrical section close to the outlet, the diameter of the cylindrical section is 600mm, the length of the cylindrical section is 30mm, the engine spray pipe 7 is nested and arranged inside the tail cabin body 1 and coaxially installed with the rear end frame of the tail cabin body 1, the clearance value between the cylindrical section of the outer wall of the engine spray pipe 7 and the rear end frame of the tail cabin body 1 is 7mm, and the clearance value is larger than the sum of the unilateral thermal collision deformation and the unilateral radial swing quantity of the engine spray pipe 7. The sealing rubber gasket 6 is adhered to the cylindrical section of the outer wall of the engine spray pipe 7; the width of the sealing rubber pad 6 is equal to the width of the tail sealing ring 5 and is 10mm; the thickness of the sealing rubber gasket 6 is equal to the unilateral thermal expansion deformation of the engine spray pipe 7 and is 1mm; after the sealing rubber gasket 6 is adhered to the outer wall of the engine nozzle 7, the diameter of the sealing rubber gasket is 602mm. The tail sealing ring 5 is of a circular ring structure with a flanging, and the cross section of the tail sealing ring is L-shaped; the diameter of the inner ring of the bullet tail sealing ring 5 is 602mm, and the diameter of the outer ring is 610mm; the diameter of the flanging outer ring of the tail sealing ring 5 is 640mm, and the flanging thickness is 4.8mm; for the convenience of installation, the inner ring of the bullet tail sealing ring 5 is chamfered at one side close to the flanging. The tail seal ring 5 is sleeved on the sealing rubber gasket 6 on the outer wall of the engine spray pipe 7, and the inner ring of the tail seal ring 5 can compress the sealing rubber gasket 6 to realize sealing after the tail seal ring 5 is installed in place because the diameter of the tail seal ring 5 is smaller than that of the sealing rubber gasket 6. The bullet tail heat-proof plate 2 is of a circular ring type flat plate structure, and the diameter of the inner ring of the bullet tail heat-proof plate is 622mm; the bullet tail sealing ring 2 is provided with a circular groove on one side close to the installation surface of the tail cabin body 1, the depth of the groove is 5mm, and the diameter of the groove is 652mm; two circles of countersunk head mounting holes are formed in the periphery of one side, close to the tail, of the tail heat-proof plate 2. The tail heat-proof plate 2 is arranged on the rear end frame of the tail cabin body 1 through screws 3. After the tail sealing ring 2 is installed in place, an annular cavity with the cross section of the inverted T shape is formed by the tail cabin body 1 and the cylindrical section of the outer wall of the engine spray pipe 7, the tail sealing ring 5 is just in the annular cavity with the cross section of the inverted T shape, at the moment, the gap between the outer ring of the tail sealing ring 5 and the inner ring of the tail heat-proof plate 2 is 6mm, the gap between the flanging outer ring of the tail sealing ring 5 and the outer ring of the groove of the tail heat-proof plate 2 is 6mm, and the tail sealing ring 5 and the groove outer ring of the tail heat-proof plate are equal and are both larger than the radial swing quantity of the engine spray pipe 7. The gap between the flanging of the bullet tail sealing ring 5 and the bottom surface of the groove of the bullet tail heat-proof plate 2 is 0.2mm, and the gap is filled with dynamic sealing putty 4.
The assembly sequence of the heat-proof sealing structure is as follows: firstly, bonding a sealing rubber gasket 6 on a cylindrical section of the outer wall of an engine spray pipe 7 and completely curing; then, the engine spray pipe 7 passes through the tail cabin body and is connected with the engine combustion chamber rear seal head; then, the tail sealing ring 5 is sleeved on a sealing rubber gasket 6 on the outer wall of the engine spray pipe 7, so that the flanging of the tail sealing ring 5 is contacted with the rear end frame of the tail cabin body 1; then, smearing dynamic sealing putty 4 with the thickness of 0.3-0.5 mm on the turned edge of the tail sealing ring 5; and finally, installing the tail heat-proof plate 2 on the rear end frame of the tail cabin body 1 by using the screw 3, and fully extruding dynamic sealing putty 4 in the installation process so as to completely fill in a gap between the flanging of the tail sealing ring 5 and the groove ground of the tail heat-proof plate 2.
In a missile storing and transporting state, the inner ring of the tail sealing ring 5 compresses a sealing rubber gasket 6 on the outer wall of a cylindrical section of the engine spray pipe 7, the flanging of the tail sealing ring 5 is sealed with the bottom surface of a groove of the tail heat-proof plate 2 through dynamic sealing putty, at the moment, a gap between the tail cabin body and the engine spray pipe can be completely sealed, external air cannot enter the tail cabin body, a good storage environment can be provided for the tail cabin body, and long storage of the missile is facilitated.
In the working state of the engine, the engine spray pipe 7 can generate 15mm of axial extension, single-side 1mm of thermal expansion deformation and single-side 5mm of radial swing quantity, at the moment, the rubber sealing gasket 6 adhered to the outer wall of the engine spray pipe 7 can axially extend 15mm along with the engine spray pipe 7, and because the widths of the tail sealing ring 5 and the sealing rubber gasket 6 are 10mm, at the moment, the sealing rubber gasket 6 can completely leave the inner ring of the tail sealing ring 5; radial expansion of the engine nozzle 7 compensates for the clearance between the outer wall of the nozzle and the tail seal ring 5; the engine spray pipe 7 can drive the tail sealing ring 5 to swing radially together, the width of the matching surface between the flanging of the tail sealing ring 5 and the bottom surface of the groove of the tail heat-proof plate 2 is 9mm, the gap between the tail sealing ring 5 and the tail heat-proof plate 2 is 6mm, the maximum radial swing amount of the tail sealing ring 5 along with the engine spray pipe 7 is 5mm, the engine spray pipe 7 can be ensured to be in sealing performance with the tail cabin body 1 while being adapted to the radial swing of the engine spray pipe 7, and the tail sealing ring cannot collide with the tail cabin body 1 and the tail heat-proof plate 2.
The sealing rubber pad 6 is made of a silicon rubber plate, and is adhered to the outer wall of the engine spray pipe 7 through room temperature vulcanized silicon rubber. The dynamic sealing putty 4 is a phenyl ether silicon putty glue material added with reinforcing filler and high-temperature resistant filler, and can keep a viscous state for a long time without solidification.
Both the bullet tail heat-proof plate 2 and the bullet tail sealing ring 5 are molded by adopting glass fiber/phenolic composite materials which are conventional heat-proof materials, and the bullet tail heat-proof plate is low in raw material cost, simple in molding process and very suitable for low-cost batch production.
The above embodiment is a preferred embodiment of the present invention, and it should be understood by those skilled in the art that structural modifications, material replacement, etc. of the parts are made without departing from the basic principles of the present invention.
Claims (8)
1. The utility model provides an adaptable spray tube warp low-cost tail heat protection seal structure, includes the cabin body of tailstock, engine nozzle, tail sealing ring, sealing rubber pad, tail heat-proof plate, dynamic seal putty and screw, its characterized in that: the tail cabin body is sleeved on the outer side of the engine spray pipe, and the rear end face of the tail cabin body is annular; the outer wall surface of the tail part of the jet nozzle of the engine is a cylindrical section; a gap is arranged between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe; a tail sealing ring is arranged at the annular inner diameter of the rear end face of the tail cabin body; the tail sealing ring is of a circular ring structure with a flanging, and the cross section of the tail sealing ring is L-shaped; the annular flanging of the tail sealing ring is attached to the rear end face of the tail cabin body; the circular ring structure of the bullet tail sealing ring is sleeved on the outer wall of the sealing ring rubber pad of the cylindrical ring body with the rectangular cross section; the inner wall of the cylindrical ring body of the rubber gasket of the sealing ring is fixedly connected with the cylindrical section of the outer wall of the tail part of the engine spray pipe; the tail cabin body is provided with a tail heat-proof plate at the rear end face; the bullet tail heat-proof plate is a circular flat plate; the inner ring edge of the tail heat-proof plate is provided with a circular groove; the bullet tail heat-proof plate is provided with a plurality of countersunk holes; the tail heat-proof plate is fixed with the rear end face of the tail cabin body through screws; after the tail heat-proof plate is fixed, the flanging of the tail sealing ring is positioned in the tail heat-proof plate groove; the gap between the flanging of the tail sealing ring and the groove of the tail heat-proof plate is filled with dynamic sealing putty; the clearance value between the side wall of the tail cabin body and the cylindrical section of the outer wall of the tail part of the engine spray pipe is larger than the sum of the unilateral thermal expansion deformation and the radial swing amplitude when the engine spray pipe works; the distance between the two bottom surfaces of the cylindrical section of the outer wall of the engine spray pipe is larger than the sum of the axial elongation of the engine spray pipe and the width of the tail sealing ring.
2. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 1 wherein: and a gap is arranged between the outer diameter of the groove of the bullet tail heat-proof plate and the outer diameter of the annular flanging of the bullet tail sealing ring.
3. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 2 wherein: the clearance value between the outer diameter of the bullet tail heat-proof plate groove and the outer diameter of the bullet tail sealing ring annular flanging is larger than the radial swing amount of the engine spray pipe during working.
4. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 1 wherein: and a gap is arranged between the outer diameter of the circular structure of the tail sealing ring and the inner diameter of the tail heat-proof plate.
5. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 4 wherein: the clearance value between the outer diameter of the bullet tail sealing ring and the inner diameter of the bullet tail heat-proof plate is larger than the radial swing amount of the engine spray pipe during working.
6. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 1 wherein: the contact length of the tail sealing ring flanging and the bottom surface of the tail heat-resistant plate groove along the radial direction is larger than the radial swing amount of the engine spray pipe.
7. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 1 wherein: the distance between the two bottom surfaces of the hollow cylindrical ring body of the sealing rubber gasket is equal to the width of the tail sealing ring, and the distance between the two bottom surfaces of the hollow cylindrical ring body of the sealing rubber gasket is smaller than the axial elongation of the engine spray pipe during working.
8. A low cost tail heat seal adapted to accommodate nozzle distortion as set forth in claim 1 wherein: the difference between the outer ring radius and the inner ring radius of the hollow cylindrical ring body of the sealing rubber gasket is the same as the unilateral thermal expansion deformation amount of the engine spray pipe during working.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311407022.5A CN117145654B (en) | 2023-10-27 | 2023-10-27 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311407022.5A CN117145654B (en) | 2023-10-27 | 2023-10-27 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117145654A CN117145654A (en) | 2023-12-01 |
| CN117145654B true CN117145654B (en) | 2024-03-15 |
Family
ID=88884653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311407022.5A Active CN117145654B (en) | 2023-10-27 | 2023-10-27 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117145654B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5125318A (en) * | 1991-12-18 | 1992-06-30 | United States Government As Represented By The Secretary Of The Navy | Inflatable device for excluding sea water from a rocket motor |
| RU2195569C1 (en) * | 2001-04-17 | 2002-12-27 | Федеральное государственное унитарное предприятие "Пермский завод им. С.М. Кирова" | Solid propellant rocket engine |
| CN107664465A (en) * | 2017-08-21 | 2018-02-06 | 中国运载火箭技术研究院 | A kind of guided missile endpiece bottom thermal protection and heat seal structure |
| CN210739356U (en) * | 2019-08-27 | 2020-06-12 | 江西洪都航空工业集团有限责任公司 | Cabin section tail sealing structure |
| CN114992331A (en) * | 2022-07-01 | 2022-09-02 | 西安长剑飞控机电有限责任公司 | Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine |
| CN115143847A (en) * | 2022-07-28 | 2022-10-04 | 西安现代控制技术研究所 | Long-range bullet arrow bullet tail heat-proof seal composite construction |
-
2023
- 2023-10-27 CN CN202311407022.5A patent/CN117145654B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5125318A (en) * | 1991-12-18 | 1992-06-30 | United States Government As Represented By The Secretary Of The Navy | Inflatable device for excluding sea water from a rocket motor |
| RU2195569C1 (en) * | 2001-04-17 | 2002-12-27 | Федеральное государственное унитарное предприятие "Пермский завод им. С.М. Кирова" | Solid propellant rocket engine |
| CN107664465A (en) * | 2017-08-21 | 2018-02-06 | 中国运载火箭技术研究院 | A kind of guided missile endpiece bottom thermal protection and heat seal structure |
| CN210739356U (en) * | 2019-08-27 | 2020-06-12 | 江西洪都航空工业集团有限责任公司 | Cabin section tail sealing structure |
| CN114992331A (en) * | 2022-07-01 | 2022-09-02 | 西安长剑飞控机电有限责任公司 | Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine |
| CN115143847A (en) * | 2022-07-28 | 2022-10-04 | 西安现代控制技术研究所 | Long-range bullet arrow bullet tail heat-proof seal composite construction |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117145654A (en) | 2023-12-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107719631B (en) | Connection structure integrating heat collection protection and assembly installation | |
| CN117145655B (en) | Flexible heat-proof sealing structure for jet pipe and tail cabin of solid rocket engine | |
| CN103267120A (en) | High temperature and high pressure sealing window used for constant volume combustion bomb | |
| CN117145654B (en) | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe | |
| CN115143847B (en) | Heat-seal-preventing composite structure for tail of remote rocket | |
| CN110630404B (en) | Double-pulse solid engine | |
| US20130192215A1 (en) | Thermal insulation of rocket engines | |
| CN110529286B (en) | Integral interlayer type double-pulse engine | |
| CN111520473B (en) | Composite material aircraft fuel tank port cover sealing structure and sealing method | |
| CN210738695U (en) | Solid stamping engine spray pipe blanking cover structure | |
| CN108502400B (en) | Inspection hole structure of condensate water tank | |
| CN107355446B (en) | A kind of piston support structure | |
| CN219119461U (en) | Air inlet nozzle device of rotary vane vacuum pump | |
| CN213176160U (en) | Sealing mechanism for intermediate body and diffusion plate of supercharger | |
| CN101712376B (en) | Breather apparatus on electromechanical actuators for aircraft landing gear systems | |
| CN220249076U (en) | Air valve mounting and sealing structure | |
| CN209098776U (en) | Set hydrogen heat-treatment furnace | |
| CN218719638U (en) | High-pressure-resistant compensator | |
| CN213929575U (en) | Take valve rod axial positioning structure's fire prevention airtight valve | |
| CN213451970U (en) | Detachable flexible high-temperature valve energy-saving shell | |
| CN219242130U (en) | Corrosion-resistant explosion-proof high-tightness hydraulic diaphragm type metering device | |
| CN112623236B (en) | Multidirectional airplane air inlet sealing compensation structure and structural parameter determination method | |
| CN220249273U (en) | T-shaped joint surface sealing structure | |
| CN218439556U (en) | Dynamic sealing structure and adjustable spray pipe | |
| CN220706392U (en) | Helicopter engine front and rear air inlet sealing element convenient to disassemble, assemble and maintain |
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 |