CN115889130A - Thermal convection rapid curing device and method for heat insulation layer of rocket tank - Google Patents
Thermal convection rapid curing device and method for heat insulation layer of rocket tank Download PDFInfo
- Publication number
- CN115889130A CN115889130A CN202211608785.1A CN202211608785A CN115889130A CN 115889130 A CN115889130 A CN 115889130A CN 202211608785 A CN202211608785 A CN 202211608785A CN 115889130 A CN115889130 A CN 115889130A
- Authority
- CN
- China
- Prior art keywords
- air
- storage tank
- curing
- rocket
- inlet
- 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.)
- Pending
Links
Images
Landscapes
- Coating Apparatus (AREA)
Abstract
The invention belongs to the field of rocket design, and particularly relates to a thermal convection rapid curing device and method for a thermal insulation layer of a rocket storage tank. At present, the main technical means adopted for curing the heat insulating layer are natural curing and surface convection heating curing, the curing time is long, the production efficiency is low, and the surface has a skinning effect. The invention comprises a storage box roller carrier which is supported at two ends and enables a storage box to rotate, an air inlet assembly which is arranged on an upper hemispherical shell of the storage box, an air outlet assembly which is arranged on a lower hemispherical shell of the storage box, infrared temperature sensors which are axially distributed near a cylindrical section of the storage box and a controller, wherein the controller receives the sampling temperature of the cylindrical section of the storage box at each position, controls the temperature and the flow of hot air entering the storage box and controls the rotation speed of the storage box. The curing time of the heat insulating layer of the rocket tank is greatly reduced; the heat insulating layer is solidified layer by layer from bottom to top, the heat conduction is uniform, the solvent residue and bubbles of the heat insulating layer are reduced on the solidification principle, and the surface crust of the coating is slowed down.
Description
Technical Field
The invention belongs to the field of rocket design, and particularly relates to a thermal convection rapid curing device and method for a thermal insulation layer of a rocket tank.
Background
In order to keep the temperature of the ultra-low temperature liquid hydrogen liquid oxygen propellant propeller contained in the rocket storage tank, the outer surface of the storage tank needs to be coated with a heat insulation layer. The shell structure of the rocket tank is shown in figure 1 and comprises rocket tank shell metal 102, DW-3 adhesive 103, DW-1 adhesive 104, polyurethane foam 105, HT100 (106), HT200 (107), polyurea 108, four-prevention primer 109, four-prevention finish 110 and red paint 111 from inside to outside. The coating process for the heat insulating layer of the rocket tank mainly comprises the following steps: the method comprises the following steps of cleaning the surface of a storage box, spraying and curing DW-3 adhesive, spraying and curing DW-1 adhesive, spraying and polishing polyurethane, spraying and curing HT100/HT200, spraying and curing four-prevention paint, and spraying and curing red paint.
The main technical means adopted by the heat insulation layer curing at present are natural curing and surface convection heating curing. The natural curing time is long, the production efficiency is low, and the production waiting is easy to cause; surface convection heat curing promotes the layer-by-layer curing of the insulation layer from top to bottom by increasing the temperature of the air surrounding the tank. However, the hot air convection heating can promote the skinning effect on the surface of the heat insulation layer, the surface of the heat insulation layer is firstly cured to form a hard film shell, so that the solvent and the like in the heat insulation layer cannot escape, and then various defects are formed in the heat insulation layer, such as: residual bubbles, wrinkles, crusts, orange peel, stress concentrations, and the like. In addition, the traditional hot air convection heating needs to build a special drying plant, and particularly, aiming at large-size components such as a rocket storage box, the plant building and the heat energy consumption are huge.
Therefore, research on a high-quality rapid curing method of the heat insulating layer of the rocket tank needs to be developed aiming at the curing characteristics of the heat insulating layer of the rocket tank, so that the defects of the heat insulating layer are reduced as much as possible while the curing time of the heat insulating layer is greatly shortened, and the molding quality of the heat insulating layer is improved.
Disclosure of Invention
The invention aims to solve the technical problem of providing a device and a method for quickly curing the heat insulating layer of a rocket tank by thermal convection, which greatly reduce the curing time and energy consumption of the heat insulating layer and simultaneously reduce the curing defect of the heat insulating layer, thereby compressing the production period of the rocket tank and improving the overall production efficiency.
In addition, the invention also provides a thought for curing coatings in other fields, such as: vehicle equipment coating, ship coating and the like, and can further promote the development of national economy.
The invention provides a thermal convection rapid solidification device for a heat insulation layer of a rocket storage tank, which comprises a storage tank roller carrier, an air inlet assembly, an air outlet assembly, an infrared temperature sensor and a controller, wherein the storage tank roller carrier is supported at two ends and enables the storage tank to rotate, the air inlet assembly is arranged on an upper hemispherical shell of the storage tank, the air outlet assembly is arranged on a lower hemispherical shell of the storage tank, the infrared temperature sensor and the controller are axially distributed near a cylindrical section of the storage tank, the controller is used for receiving sampling temperatures of the cylindrical section of the storage tank at various positions, controlling the temperature and the flow of hot air entering the storage tank and controlling the rotation speed of the storage tank.
Advantageously, the air intake assembly comprises an inlet pipe, an air filter valve, a flow proportional valve check valve and an air slip ring connected in sequence.
Advantageously, the air slide ring is connected to the rocket tank inlet via an inlet air slide ring connection flange and an inlet sealing ring.
Advantageously, the air slide ring is supported on the ground by an air slide ring support frame.
Advantageously, the controller is connected with the infrared temperature sensor through an infrared temperature sensor signal line and is connected with the flow proportional valve through a flow proportional valve signal line.
Advantageously, the air outlet assembly comprises an overflow valve and an outlet pipe which are connected in sequence.
Advantageously, the overflow valve is connected to the rocket tank outlet via an inlet-gas slide ring connection flange and an inlet sealing ring.
Advantageously, the upper hemispherical shell of the tank is also provided with a rocket tank air port sealed by an air port sealing end cover and an air port sealing ring.
The invention also provides a thermal convection rapid curing method of the thermal insulation layer of the rocket tank, which utilizes the thermal convection rapid curing device and comprises the following steps:
s1, cleaning and airing the excess on the outer surface of the storage box;
s2, spraying a first layer of sizing material of the heat insulation layer;
s3, mounting the storage tank on a storage tank roller frame, connecting the storage tank with an air inlet assembly and an air outlet assembly, placing an infrared temperature sensor, and connecting a controller with each control object;
s4, introducing hot air, the temperature T0 of the hot air and the flow Q1 of the hot air into the storage tank through the air inlet assembly, and setting the pressure of the overflow valve as an air pressure Pmax which can be borne by the storage tank;
s5, starting the storage tank roller carrier to enable the storage tank to rotate around the axial direction;
s6, comparing the average sampling temperature T1 of the infrared temperature sensor with the curing process temperature T2 of the heat insulating layer, and keeping the temperature and the flow of the introduced hot air unchanged if | T1-T2| < delta T;
otherwise, the average temperature T1 of the temperature sensor is further compared with the curing process temperature T2 of the heat insulating layer, and if T1 is larger than T2, the air flow Q1 is reduced or the hot air temperature T0 is reduced; otherwise, increasing the air flow Q1 or increasing the hot air temperature T0;
s7, waiting for the layer of sizing material to be completely cured;
and S8, spraying a next layer of glue stock, and returning to S4 until the curing of all the coatings is completed.
The positive effects are as follows:
(1) The curing time of the heat insulating layer of the rocket tank is greatly reduced;
(2) The heat insulating layer is cured layer by layer from bottom to top, so that the solvent residue and bubbles of the heat insulating layer are reduced in the curing principle, and the surface skinning of the coating is slowed down;
(3) By adopting a rapid thermal convection curing method in the heat insulating layer of the rocket tank, the heat conduction is uniform, and the stress concentration of the heat insulating layer caused by uneven temperature is greatly reduced;
(4) By adopting a rapid thermal convection curing method in the heat insulating layer of the rocket tank, the thermal energy consumption is greatly reduced by controlling the air temperature and the flow and the mode of heat conduction from inside to outside;
(5) The whole device is relatively little in modification, and mainly relates to the arrangement of pipelines and valves. Because the storage tank can also be equipped with the flap in the spraying process, consequently can further practice thrift behind the unified flap and reform transform the cost, also can compress process time.
Drawings
FIG. 1 is a schematic diagram of a method for rapid thermal convection curing inside a thermal insulation layer of a rocket tank;
wherein: 101 is hot air, 102 is rocket storage tank shell metal, 103 is DW-3 adhesive, 104 is DW-1 adhesive, 105 is polyurethane foam, 106 is HT100, 107 is HT200, 108 is polyurea, 109 is four-proofing primer, 110 is four-proofing finish paint, and 111 is red paint
FIG. 2 is a schematic view (in elevation) of a thermal convection rapid solidification device inside the thermal insulation layer of a rocket tank;
wherein: 201 is ground, 202 is a storage tank roller frame, 203 is an air slip ring support frame, 204 is an inlet pipeline, 205 is an air filter valve, 206 is a flow proportional valve, 207 is a one-way valve, 208 is an air slip ring, 209 is a storage tank upper hemispherical shell, 210 is a storage tank cylindrical section, 211 is a storage tank lower hemispherical shell, 212 is an overflow valve, 213 is an outlet pipeline
FIG. 3 is a schematic view (isometric view) of a thermal convection rapid solidification device within a thermal insulation layer of a rocket tank;
wherein: 301 is an inlet-air slip ring connecting flange, 302 is an inlet sealing ring, 303 is an air port sealing end cover, 304 is an air port sealing ring, 305 is a rocket storage tank air port, 306 is a rocket storage tank inlet, 307 is an infrared temperature sensor, 308 is an infrared temperature sensor signal wire, 309 is a controller, 310 is a flow proportional valve signal wire
FIG. 4 is a flow chart of a method for rapid thermal convection curing inside a thermal insulation layer of a rocket tank.
Detailed Description
Referring to the apparatus for rapid thermal convection curing of rocket tank insulation as shown in FIGS. 2 and 3, a port seal 304 is placed in a seal groove of a port seal cover 303, and the port seal cover 303 is fastened to a rocket tank port 305 with screws; the inlet sealing ring 302 is arranged in a sealing groove at one side of the inlet-air slip ring connecting flange 301, and the inlet-air slip ring connecting flange 301 is fastened at the inlet 306 of the rocket tank by screws; an air filter valve 205 is connected behind the inlet pipe 204 and is used for filtering impurities and water vapor in the air; a flow proportional valve 206 is connected behind the air filter valve 205 for controlling the flow of air into the rocket tank; a check valve 207 is connected behind the flow proportional valve 206 for controlling the air flow direction; one side of the air slip ring 208 is connected with an outlet pipeline of the one-way valve 207, the other side of the air slip ring 208 is connected with the inlet-air slip ring connecting flange 301 through screws, and the top end of the air slip ring 208 is fixed on the air slip ring supporting frame 203 through screws; the air slip ring is mainly used for controlling the highest pressure in the storage tank not to exceed a safety range under the condition that the air path is not influenced and the storage overflow valve 212 is connected to the front of the outlet pipeline 213.
The rocket storage tank is placed on a storage tank roller frame 202, and the storage tank roller frame 202 is fixed on the ground 201. The rocket tank can rotate around the X direction.
The infrared temperature sensors 307 are uniformly arranged along the cylindrical section 210 of the tank, and the number is set according to the length of the tank; one side of an infrared temperature sensor signal wire 308 is connected with an infrared temperature sensor 307, and the other side is connected with a controller 309; the flow proportional valve signal line 310 is connected to the flow proportional valve 206 on one side and to the controller 309 on the other side.
The embodiment of the thermal convection rapid curing method of the thermal insulation layer of the rocket tank comprises the following steps:
cleaning the excess materials in the rocket storage tank, airing, and uniformly spraying a first layer of glue material DW-3 on the heat insulation layer; after the spraying is finished, an air inlet and an air outlet are reserved, and an inlet or an air port is generally reserved. The thermal convection rapid curing device for the heat insulation layer of the rocket tank is characterized in that various pipelines, valves, air slip rings, supporting seats, infrared temperature sensors and the like are assembled on the rocket tank.
For rocket storage tanks with the diameter of 3m and the length of 6m, economic flow is adopted as much as possible, and the flow Q1 of the flow proportional valve is set to be 0.5m 3 S, temperature T of the air introduced 0 Set at 70 ℃ and the pressure P of the relief valve max The curing process temperature T of the DW-1 glue is set to be 0.11-0.12MPa 2 The setting is 60 +/-2 ℃, and the rotation frequency of the roller frame is set to be 2-8Hz.
Monitoring the average temperature T of a temperature sensor 1 Curing process temperature T of DW-3 glue 2 The difference of (a). If | T 1 -T 2 L > [ Delta ] T and T 1 ＞T 2 The controller sends an electric signal to the flow proportional valve to reduce the air flow Q 1 Or lowering the air temperature T 0 Up to | T 1 -T 2 The | < delta T. If | T 1 -T 2 L > [ Delta T and T 1 ＜T 2 The controller sends an electric signal to the flow proportional valve to increase the air flow Q 1 Or increasing the air temperature T 0 Up to | T 1 -T 2 |≤△T。
After 8h, the DW-3 adhesive is completely cured (48 h is needed for original room-temperature curing).
Spraying DW-1 glue and repeating the above steps.
Until the adhesive layer of the heat insulating layer is completely cured.
Claims (9)
1. A thermal convection rapid curing device for a thermal insulation layer of a rocket tank is characterized in that: the device comprises a storage tank roller frame (202) which is supported at two ends and enables the storage tank to rotate, an air inlet assembly on an upper hemispherical shell inlet (209) of the storage tank, an air outlet assembly on a lower hemispherical shell (211) of the storage tank, infrared temperature sensors (307) which are axially distributed near a cylindrical section (210) of the storage tank and a controller (309), wherein the controller (309) receives the sampling temperature of the cylindrical section (210) of the storage tank at each position, controls the temperature and the flow of hot air entering the storage tank and controls the rotation speed of the storage tank.
2. The apparatus according to claim 1, wherein: the air inlet assembly comprises an inlet pipeline (204), an air filter valve (205), a flow proportional valve (206), a one-way valve (207) and an air slip ring (208) which are connected in sequence.
3. The apparatus according to claim 2, wherein: the air slip ring (208) is connected to the rocket tank inlet (306) through an inlet-air slip ring connecting flange (301) and an inlet sealing ring (302).
4. The apparatus according to claim 2, wherein: the air slip ring (208) is supported on the ground (201) through an air slip ring support frame (203).
5. The apparatus according to claim 2, wherein: the controller (309) is connected with the infrared temperature sensor (307) through an infrared temperature sensor signal line (308) and is connected with the flow proportional valve (206) through a flow proportional valve signal line (310).
6. The apparatus according to claim 1, wherein: the air outlet assembly comprises an overflow valve (212) and an outlet pipeline (213) which are connected in sequence.
7. The apparatus according to claim 6, wherein: the overflow valve (212) is connected to the outlet of the rocket tank through an inlet-air slip ring connecting flange (301) and an inlet sealing ring (302).
8. The apparatus according to claim 1, wherein: the upper hemispherical shell inlet (209) of the storage tank is also provided with a rocket storage tank air port (305) which is sealed by an air port sealing end cover (303) and an air port sealing ring (304).
9. A method of rapid thermal convection curing of rocket tank insulation utilizing a rapid thermal convection curing apparatus as claimed in any one of claims 1 to 8 and comprising the steps of:
s1, cleaning and airing excess objects on the outer surface of a storage box;
s2, spraying a first layer of glue stock of the heat insulation layer;
s3, mounting the storage tank on a storage tank roller frame (202), connecting the storage tank with an air inlet assembly and an air outlet assembly, placing an infrared temperature sensor (307), and connecting a controller (309) with each control object;
s4, introducing hot air into the storage tank through the air inlet assembly, wherein the temperature T0 of the hot air and the flow Q1 of the hot air are set, and the pressure of the overflow valve is set to be the air pressure Pmax which can be borne by the storage tank;
s5, starting a storage tank roller carrier (202) to enable the storage tank to rotate around the axial direction;
s6, comparing the average sampling temperature T1 passing through the infrared temperature sensor (307) with the curing process temperature T2 of the heat insulating layer, and if | T1-T2| is less than or equal to Δ T, keeping the temperature and the flow rate of the introduced hot air unchanged;
otherwise, the average temperature T1 of the temperature sensor is further compared with the curing process temperature T2 of the heat insulating layer, and if T1 is larger than T2, the air flow Q1 is reduced or the hot air temperature T0 is reduced; otherwise, increasing the air flow Q1 or increasing the hot air temperature T0;
s7, waiting for the layer of sizing material to be completely cured;
and S8, spraying a next layer of glue stock, and returning to S4 until the curing of all the coatings is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211608785.1A CN115889130A (en) | 2022-12-14 | 2022-12-14 | Thermal convection rapid curing device and method for heat insulation layer of rocket tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211608785.1A CN115889130A (en) | 2022-12-14 | 2022-12-14 | Thermal convection rapid curing device and method for heat insulation layer of rocket tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115889130A true CN115889130A (en) | 2023-04-04 |
Family
ID=86481373
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211608785.1A Pending CN115889130A (en) | 2022-12-14 | 2022-12-14 | Thermal convection rapid curing device and method for heat insulation layer of rocket tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115889130A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101879504A (en) * | 2010-05-21 | 2010-11-10 | 营口成大机电设备制造有限公司 | Track type full-automatic automobile repairing and varnish baking device and control system |
| CN105834028A (en) * | 2015-01-13 | 2016-08-10 | 上海航天设备制造总厂 | Automatic spray system and method for heat insulating layer of cryogenic tank of rocket |
| CN113369111A (en) * | 2021-05-27 | 2021-09-10 | 常州新华昌国际集装箱有限公司 | Water-based paint coating method for container |
-
2022
- 2022-12-14 CN CN202211608785.1A patent/CN115889130A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101879504A (en) * | 2010-05-21 | 2010-11-10 | 营口成大机电设备制造有限公司 | Track type full-automatic automobile repairing and varnish baking device and control system |
| CN105834028A (en) * | 2015-01-13 | 2016-08-10 | 上海航天设备制造总厂 | Automatic spray system and method for heat insulating layer of cryogenic tank of rocket |
| CN113369111A (en) * | 2021-05-27 | 2021-09-10 | 常州新华昌国际集装箱有限公司 | Water-based paint coating method for container |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| AU2015309506A1 (en) | Vacuum assisted resin infusion protection coating, system and method for permanent magnet motor rotor | |
| CN115889130A (en) | Thermal convection rapid curing device and method for heat insulation layer of rocket tank | |
| CN107399733B (en) | A kind of roll-to-roll graphene film preparation facilities | |
| CN205288373U (en) | Hot melt adhesive reation kettle adds nice and warm cooling system | |
| CN109955505B (en) | Integral forming process method for heat-proof head cover of return airship | |
| CN209276603U (en) | A kind of superaudio induction heating light-alloy vacuum melting pouring furnace | |
| CN106702344B (en) | A kind of powder body material surface coating pyrolytic carbon method and device thereof | |
| CN107756696B (en) | Composite material samming solidification equipment | |
| US20060080769A1 (en) | Resin infused acrylic shell | |
| CN202256329U (en) | Damp-heat aging test device | |
| CN106142589A (en) | There is the manufacture method of the pressure resistant vessel of heater | |
| CN210089127U (en) | Hot air device of packaging laminating equipment | |
| CN208482749U (en) | A kind of handware infrared baking finish device | |
| CN204211492U (en) | A kind of impregnated graphite curing apparatus | |
| CN209069699U (en) | A kind of sample stage is evenly heated equipment | |
| CN207385486U (en) | Penetration enhancer generator | |
| CN105463582B (en) | A kind of high temperature high vacuum annealing device for the processing of low stress suboxides | |
| CN104596092A (en) | Electric water heater and manufacturing method for electric water heater | |
| CN106005767A (en) | Controllable constant-temperature transportation box and temperature control method | |
| CN216378085U (en) | Natural gas hydrate decomposes pressure boost filling device | |
| CN102223948A (en) | Dual vessel reactor | |
| CN205897576U (en) | Improved solar water heater | |
| CN111850511A (en) | Novel pyrolytic graphite vapor deposition device and process | |
| CN218442813U (en) | Explosion-proof electric heater with high efficiency and energy saving | |
| CN215540869U (en) | A reation kettle for producing plastic course red cream |
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 |