CN111828200A - Thermal protection structure suitable for ramjet sensor - Google Patents
Thermal protection structure suitable for ramjet sensor Download PDFInfo
- Publication number
- CN111828200A CN111828200A CN202010505260.XA CN202010505260A CN111828200A CN 111828200 A CN111828200 A CN 111828200A CN 202010505260 A CN202010505260 A CN 202010505260A CN 111828200 A CN111828200 A CN 111828200A
- Authority
- CN
- China
- Prior art keywords
- sensor
- heat insulation
- supporting plate
- ramjet
- insulation layer
- 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
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Classifications
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- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
Abstract
The invention discloses a thermal protection structure suitable for a ramjet sensor, which comprises: the device comprises a bracket, a supporting plate, a cover plate, a heat insulation layer, a measuring pipe and a clamping ring; the heat insulation layer is coated outside the sensor, and the supporting plate and the cover plate are respectively sleeved outside the heat insulation layer; the clamping ring is sleeved outside the supporting plate and the cover plate, and two ends of the clamping ring are locked through bolts; the two brackets are respectively fixed on the semi-annular plates at the two ends of the supporting plate; one end of the measuring tube is connected with the measuring end of the sensor, and the other end of the measuring tube is communicated with a combustion chamber of the ramjet engine; the invention is a compact and efficient heat insulation structure, has good damping effect, and can meet the heat insulation and damping requirements of the sensor under the working condition of a ramjet with long time and high Mach number.
Description
Technical Field
The invention belongs to the technical field of thermal protection, and particularly relates to a thermal protection structure suitable for a ramjet sensor.
Background
With the development of missile technology, the flying missile has higher flying speed and more compact missile body mechanism. The working temperature of the sensor working along with the bomb is higher and higher, the vibration magnitude is multiplied, and the thermal protection space is close to the limit. The commonly adopted sensor thermal protection scheme can not meet the requirement of high-speed flight of the missile, and often causes the sensor to be damaged midway and the acquisition of the missile flight data is interrupted. The missile can be caused to be out of control by interruption of important control data, or the missile can cause the prior loss of the party in the war, and huge economic loss is caused.
Disclosure of Invention
In view of the above, the invention provides a thermal protection structure suitable for a ramjet sensor, which is a compact and efficient thermal insulation structure and has a good damping effect, and can meet the thermal insulation and damping requirements of the sensor under the long-time and high-mach-number working condition of the ramjet.
The invention is realized by the following technical scheme:
a thermal protection structure adapted for a ramjet sensor, comprising: the device comprises a bracket, a supporting plate, a cover plate, a heat insulation layer, a measuring pipe and a clamping ring;
the supporting plate and the cover plate are both of a semi-cylindrical structure A, and both ends of the semi-cylindrical structure A are provided with semi-annular plates; the open end of the supporting plate and the open end of the cover plate are in butt joint at a set distance to form a cylinder A, and two semi-annular plates at the same end are in butt joint to form a circular plate with a central hole;
the heat insulation layer is of a split structure and is a cylinder B formed by butting two semi-cylinder structures B, and axial through holes are processed at two ends of the cylinder B;
the heat insulation layer is made of aerogel materials;
the bracket, the supporting plate and the cover plate are all made of metal materials;
the overall connection relationship is as follows: the heat insulation layer is coated outside the sensor, the supporting plate and the cover plate are respectively sleeved outside the heat insulation layer, and the opening end of the supporting plate and the opening end of the cover plate are oppositely arranged at a set distance; axial through holes at two ends of the heat insulation layer are respectively coaxial with central holes at two ends of a cylinder A consisting of the supporting plate and the cover plate; the lead end and the measuring end of the sensor respectively penetrate through the axial line through holes at two ends of the heat insulation layer and the central holes at two ends of the cylinder A;
the clamping ring is sleeved outside the cylinder A, and two ends of the clamping ring are locked through bolts;
the two brackets are respectively fixed on the semi-annular plates at the two ends of the supporting plate, so that the sensor, a heat insulation layer fixed outside the sensor, the supporting plate and the cover plate are supported in a stamping engine shell of the missile;
one end of the measuring tube is connected with the measuring end of the sensor, and the other end of the measuring tube is communicated with a combustion chamber of the ramjet engine; the air pressure in the measuring tube is the same as the air pressure in the combustion chamber, and the sensor is used for measuring the air pressure in the measuring tube so as to obtain the air pressure in the combustion chamber of the ramjet engine.
Further, the diameter of the integral structure formed by the heat insulation layer, the supporting plate and the cover plate after installation is 6mm larger than that of the sensor.
Furthermore, the support is connected with the semi-annular plate of the supporting plate through a countersunk head screw and a self-locking nut.
Furthermore, GH2696 is adopted by the support, the supporting plate and the cover plate.
Furthermore, the measuring tube is bent to be of a damping arc structure.
Further, the wall thickness of the measuring tube is 0.5mm, and the length is 200 mm.
Has the advantages that: (1) when the missile flies around Ma4, the temperature of the missile wall surface is above 750 ℃, the thermal insulation layer of the missile is coated outside the sensor by aerogel with low thermal conductivity coefficient and low strength, the heat conducted from the missile wall surface to the sensor through the bracket, the supporting plate and the cover plate is blocked, and the temperature of the sensor is controlled within 100 ℃ in the environment of 750 ℃ wall surface for 1500 s; meanwhile, the aerogel is a flexible material with low rigidity, can deform and absorb energy under the action of pressure, and can play a good role in shock absorption when being used together with a metal supporting plate and a metal cover plate, so that the sensor and the missile are prevented from generating resonance, and the requirements of heat insulation and shock absorption of the sensor under the long-time high-Mach-number working condition of the ramjet can be met;
(2) the diameter of the thermal protection structure is only 6mm larger than that of the sensor, the structure is compact, and the protection space is reduced.
(3) The heat insulation layer of the invention adopts a split structure, and is convenient and rapid to install.
(4) The supporting plate and the cover plate can protect the heat insulation layer made of low-strength aerogel, and the strength and the rigidity of the heat protection structure are improved.
(5) The measuring tube is of a damping arc structure and has the characteristics of small installation space, low assembly stress and good damping effect.
Drawings
FIG. 1 is a structural component diagram of the present invention;
FIG. 2 is a schematic view of the assembly of the thermal shield and the sensor;
FIG. 3 is a schematic view showing the assembly relationship of the cover plate, the support plate and the heat insulation layer;
FIG. 4 is a schematic view of the bracket and pallet connection;
FIG. 5 is a schematic view of a shock absorbing arc configuration of a measurement tube;
the device comprises a support 1, a supporting plate 2, a cover plate 3, a heat insulation layer 4, a measuring tube 5, a countersunk head screw 6, a bolt 7, a sensor 8 and a clamping ring 9.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The present embodiment provides a thermal protection structure suitable for a ramjet sensor, see fig. 1, comprising: the device comprises a bracket 1, a supporting plate 2, a cover plate 3, a heat insulation layer 4, a measuring pipe 5, a countersunk screw 6, a bolt 7 and a clamping ring 9;
referring to the attached drawing 3, the supporting plate 2 and the cover plate 3 are both of a semi-cylindrical structure A, and both ends of the semi-cylindrical structure A are provided with semi-annular plates; the open end of the supporting plate 2 and the open end of the cover plate 3 are butted at a set distance to form a cylinder A, and two semi-annular plates at the same end are butted to form a circular plate with a central hole;
referring to the attached drawing 2, the heat insulation layer 4 is a split structure and is a cylinder B formed by butting two semi-cylinder structures B, and axial through holes are formed in two ends of the cylinder B;
the heat insulation layer 4 is made of a flexible material with low heat conductivity, and the embodiment adopts an aerogel material with low heat conduction coefficient and low strength;
the bracket 1, the supporting plate 2 and the cover plate 3 are made of metal GH2696, so that the requirements on supporting strength and rigidity in the stamping engine can be met;
the overall connection relationship is as follows: the heat insulation layer 4 is coated outside the sensor 8, the supporting plate 2 and the cover plate 3 are respectively sleeved outside the heat insulation layer 4, and the open end of the supporting plate 2 and the open end of the cover plate 3 are oppositely arranged at a set distance; the axial through holes at the two ends of the heat insulation layer 4 are respectively coaxial with the central holes at the two ends of the cylinder A consisting of the supporting plate 2 and the cover plate 3; the lead end and the measuring end of the sensor 8 respectively penetrate through the axial line through holes at two ends of the heat insulation layer 4 and the central holes at two ends of the cylinder A;
the clamping ring 9 is sleeved outside the cylinder A, and two ends of the clamping ring 9 are locked through the bolts 7, so that the heat insulation layer 4, the supporting plate 2 and the cover plate 3 are fixed outside the sensor 8; the diameter of the whole structure formed by the heat insulation layer 4, the supporting plate 2 and the cover plate 3 after installation is only 6mm larger than that of the sensor 8, the structure is compact, and the space is not occupied;
referring to the attached drawing 4, the two brackets 1 are respectively fixed on the semi-annular plates at the two ends of the supporting plate 2 through countersunk screws 6 and self-locking nuts, so that the sensor 8, the heat insulation layer 4 fixed outside the sensor 8, the supporting plate 2 and the cover plate 3 are supported in the shell of the ramjet engine of the missile;
referring to fig. 5, one end of the measuring tube 5 is connected with the measuring end of the sensor 8, the other end of the measuring tube is communicated with the combustion chamber of the ramjet, the measuring tube 5 is bent into a damping arc structure with a ring, and the measuring ends of the measuring tube 5 and the sensor 8 are locked and locked by a fuse; the air pressure in the measuring tube 5 is the same as the air pressure in the combustion chamber, and the sensor 8 is used for measuring the air pressure in the measuring tube 5 so as to obtain the air pressure in the combustion chamber of the ramjet; since the measuring tube 5 is made of metal, the measuring tube 5 conducts the heat of the combustion chamber of the ramjet to the sensor 8, and therefore, the temperature rise of the sensor 8 is less than a set value by extending the length of the measuring tube 5 and reducing the wall thickness of the measuring tube 5; in this example, the wall thickness of the measuring tube 5 is 0.5mm and the length is 200mm, and the heat conducted by the measuring tube 5 is calculated to heat the sensor 8 to less than 30 ℃.
The design process of the thermal protection structure is as follows:
step 1, fully estimating the sensor environment, and preliminarily providing a design model of the thermal protection structure;
4, carrying out heat insulation, rigidity and strength recalculation on the thermal protection structure;
and 5, finishing the final structural design of the thermal protection structure.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A thermal protection structure adapted for a ramjet sensor, comprising: the device comprises a bracket (1), a supporting plate (2), a cover plate (3), a heat insulation layer (4), a measuring pipe (5) and a clamping ring (9);
the supporting plate (2) and the cover plate (3) are both of a semi-cylindrical structure A, and both ends of the semi-cylindrical structure A are provided with semi-annular plates; the open end of the supporting plate (2) and the open end of the cover plate (3) are butted at a set distance to form a cylinder A, and two semi-annular plates at the same end are butted to form a circular plate with a central hole;
the heat insulation layer (4) is of a split structure and is a cylinder B formed by butting two semi-cylinder structures B, and axial through holes are formed in two ends of the cylinder B;
the heat insulation layer (4) is made of aerogel materials;
the bracket (1), the supporting plate (2) and the cover plate (3) are made of metal materials;
the overall connection relationship is as follows: the heat insulation layer (4) is coated outside the sensor (8), the supporting plate (2) and the cover plate (3) are respectively sleeved outside the heat insulation layer (4), and the open end of the supporting plate (2) and the open end of the cover plate (3) are oppositely arranged at a set distance; axial through holes at two ends of the heat insulation layer (4) are respectively coaxial with central holes at two ends of a cylinder A consisting of the supporting plate (2) and the cover plate (3); the lead end and the measuring end of the sensor (8) respectively penetrate through the axial line through holes at two ends of the heat insulation layer (4) and the central holes at two ends of the cylinder A;
the clamping ring (9) is sleeved outside the cylinder A, and two ends of the clamping ring (9) are locked through bolts (7);
the two brackets (1) are respectively fixed on the semi-annular plates at the two ends of the supporting plate (2), so that the sensor (8), the heat insulation layer (4) fixed outside the sensor (8), the supporting plate (2) and the cover plate (3) are supported in a ramjet shell of the missile;
one end of the measuring pipe (5) is connected with the measuring end of the sensor (8), and the other end of the measuring pipe is communicated with a combustion chamber of the ramjet engine; the atmospheric pressure in the survey buret (5) with atmospheric pressure in the combustion chamber is the same, sensor (8) are used for measuring the atmospheric pressure in surveying buret (5), and then obtain atmospheric pressure in the combustion chamber of ramjet.
2. A thermal protection structure for a ramjet sensor according to claim 1, characterized in that the thermal insulation layer (4), the carrier plate (2) and the cover plate (3) after the installation form an integral structure with a diameter 6mm larger than the diameter of the sensor (8).
3. A thermal protection structure for ramjet sensors according to claim 1, characterized in that said bracket (1) is connected to the semi-annular plate of the pallet (2) by means of countersunk screws (6) and self-locking nuts.
4. The thermal protection structure for the ramjet sensor according to claim 1, characterized in that the bracket (1), the supporting plate (2) and the cover plate (3) are all GH 2696.
5. A thermal protection structure for ramjet sensors according to claim 1, characterized in that the measuring tube (5) is bent into a damped arc structure.
6. A thermal protection structure for ramjet sensors according to claim 1, characterized in that the measuring tube (5) has a wall thickness of 0.5mm and a length of 200 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010505260.XA CN111828200A (en) | 2020-06-05 | 2020-06-05 | Thermal protection structure suitable for ramjet sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010505260.XA CN111828200A (en) | 2020-06-05 | 2020-06-05 | Thermal protection structure suitable for ramjet sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111828200A true CN111828200A (en) | 2020-10-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010505260.XA Pending CN111828200A (en) | 2020-06-05 | 2020-06-05 | Thermal protection structure suitable for ramjet sensor |
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| Country | Link |
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| CN (1) | CN111828200A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203918372U (en) * | 2014-06-26 | 2014-11-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of device for sensor installation joint |
| CN204591524U (en) * | 2015-01-30 | 2015-08-26 | 北京宇航系统工程研究所 | Sensor fixing structure at the bottom of a kind of adjustable highly reliable case |
| CN206258189U (en) * | 2016-12-14 | 2017-06-16 | 马天贵 | A kind of easy-to-dismount rubber sheath formula temperature sensor |
| CN109264663A (en) * | 2018-09-27 | 2019-01-25 | 中北大学 | High-temp pressure sensor rear end encapsulating structure and its packaging method |
-
2020
- 2020-06-05 CN CN202010505260.XA patent/CN111828200A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203918372U (en) * | 2014-06-26 | 2014-11-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of device for sensor installation joint |
| CN204591524U (en) * | 2015-01-30 | 2015-08-26 | 北京宇航系统工程研究所 | Sensor fixing structure at the bottom of a kind of adjustable highly reliable case |
| CN206258189U (en) * | 2016-12-14 | 2017-06-16 | 马天贵 | A kind of easy-to-dismount rubber sheath formula temperature sensor |
| CN109264663A (en) * | 2018-09-27 | 2019-01-25 | 中北大学 | High-temp pressure sensor rear end encapsulating structure and its packaging method |
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Application publication date: 20201027 |