CN112193402B - Constant-temperature heat shield structure capable of being stored for long time - Google Patents
Constant-temperature heat shield structure capable of being stored for long time Download PDFInfo
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- CN112193402B CN112193402B CN202010976169.6A CN202010976169A CN112193402B CN 112193402 B CN112193402 B CN 112193402B CN 202010976169 A CN202010976169 A CN 202010976169A CN 112193402 B CN112193402 B CN 112193402B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
- B64C1/403—Arrangement of fasteners specially adapted therefor, e.g. of clips
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- Aviation & Aerospace Engineering (AREA)
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Abstract
A long-shelf-life, constant temperature heat shield structure comprising: bearing structure, high temperature thermal-protective coating and support ring. The high-temperature heat-insulating layer and the bearing structure are used as gas flow passages and are fixedly provided with a plurality of support rings; the bearing structure is provided with an exhaust channel, water in a gel state stored in the bearing structure is vaporized to absorb heat, and the exhaust channel is used for discharging gaseous liquid solid three-phase flow substances including water vapor, water drops and aerogel residues from the exhaust channel. The support rings are arrayed along the axial direction of the cylinder structure and have the functions of decelerating the gas-state liquid-state three-phase flow substances discharged from the small holes, reducing the flying of water drops and aerogel residues along with water vapor, storing the water drops and the aerogel residues, improving the phase change ratio of water and relieving the air flow impact on the interface of the heat-proof layer. The invention solves the problems of lower structural efficiency, complex system and low reliability of the existing heat-proof system.
Description
Technical Field
The invention relates to a constant-temperature heat shield structure capable of being stored for a long time, which can be used for an aircraft structure bearing force heat load and belongs to the field of thermal structure design.
Background
When the aircraft flies at high speed in the atmosphere, aerodynamic and aerodynamic thermal loads are borne, and in order to ensure the integrity of the aircraft and provide a suitable environment for personnel and equipment, the aircraft needs to be provided with a thermal protection system.
Current thermal protection systems can be divided into passive, semi-active and active thermal protection: passive heat protection is used for heat protection by absorbing and radiating aerodynamic heat, mainly adopts a heat sink structure and a heat insulation type structure, is the most mature heat protection technology, but has lower structural efficiency, and has larger structural weight when the heat flow load is more severe; the semi-active and active cooling heat protection systems both utilize cooling working media (solid, liquid and gas) to prevent or take away heat flow, the active cooling heat protection system generally adopts propellant as the cooling working media, a pressurization system is required to ensure the supply and circulation of the cooling working media, the system is relatively complex, and if the structure is not provided with the pressurization system, additional configuration is required, and the structure efficiency is reduced; the semi-active thermal protection system adopts a certain material in the structure as a cooling working medium (generally, low-melting-point metal), an additional system is not needed for providing the cooling working medium or circulating the cooling working medium, the structure is simpler, the thermal protection structure efficiency is higher, but the semi-active thermal protection system is rarely applied at present, and the main problems that local burnthrough (called hot spots) can occur due to uneven heating of the outer wall surface, sweat pores are easily blocked by incomplete phase change working medium, fusant and ablator, the phase change working medium cannot be smoothly removed, and the reliability of the thermal protection system is influenced are solved.
Passive thermal protection systems and ablative thermal protection systems have been used in large numbers on aircraft, but the structural efficiency is low; the active thermal protection system is complex, and the special configuration of the auxiliary driving system can reduce the structural efficiency; the semi-active sweating cooling system with simple structure and higher efficiency is less applied, and the main problems that sweating holes are easily blocked by incomplete phase change working media, melts and ablates and the working media cannot be smoothly removed are faced.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the constant-temperature heat shield structure capable of being stored for a long time is provided, the heat-proof bearing integrated system is high in heat-proof efficiency, simple and reliable in system, comfortable in thermal environment in a cabin and capable of being stored for a long time, and the problems that the existing heat-proof system is low in structural efficiency, complex in system and low in reliability are solved.
The technical scheme of the invention is as follows:
a long-shelf-life, constant temperature heat shield structure comprising: the device comprises a bearing structure, a high-temperature heat insulation layer, a support ring and a sealing structure;
the high-temperature heat insulation layer is sleeved outside the bearing structure to form a cylinder structure;
the high-temperature heat-insulating layer and the bearing structure are used as gas flow passages and are fixedly provided with a plurality of support rings;
the bearing structure is a hollow structure, and water in a gel state is stored in the hollow structure; the bearing structure is provided with an exhaust channel, water in a gel state stored in the bearing structure is vaporized to absorb heat, and the exhaust channel is used for discharging gaseous liquid solid three-phase flow substances including water vapor, water drops and aerogel residues from the exhaust channel;
the high-temperature heat insulation layer is used for shielding external heat flow;
a plurality of support rings arrayed in an axial direction of the cylindrical structure;
the support ring includes: the transverse airflow deceleration cover and the longitudinal airflow deceleration cover;
the transverse airflow speed reducing cover is of an annular structure with a concave section, and the opening direction of the annular structure of the transverse airflow speed reducing cover is towards the exhaust channel of the force bearing structure; one free end of the concave annular structure of the transverse airflow speed reducing cover is fixedly connected with a bearing structure, and the other free end of the concave annular structure of the transverse airflow speed reducing cover does not contact with the bearing structure to form a gap;
the transverse airflow deceleration cover has the functions of decelerating gaseous liquid state solid state three-phase flow substances discharged from the small holes, reducing the flying of water drops and aerogel residues along with water vapor, storing the water drops and the aerogel residues, improving the phase change ratio of water and simultaneously slowing down airflow impact on an interface of the heat-proof layer;
the longitudinal airflow speed reducing cover is of an annular structure with a concave section, the longitudinal airflow speed reducing cover is positioned at the lower part of the transverse airflow speed reducing cover, and the opening direction of the annular structure with the concave section of the longitudinal airflow speed reducing cover faces to the transverse airflow speed reducing cover at the upper part of the longitudinal airflow speed reducing cover; two free ends of the longitudinal airflow speed reducing cover are respectively fixedly connected with the bearing structure and the high-temperature heat insulation layer;
the bottom of the longitudinal airflow speed reducing cover is provided with a conical hole protruding upwards, and the conical hole is used as a discharge channel of water vapor.
A plurality of partition plates are fixedly installed in the bearing structure, and divide the hollow structure of the bearing structure into a plurality of independent hollow strengths which are not communicated with each other by the partition plates.
Each hollow is filled with hydrogel.
And a small hole is processed on the wall surface of one side of each hollow intensity facing the high-temperature heat-insulating layer and is used as an exhaust channel after hydrogel is heated and vaporized.
The sealing structure is fixedly arranged at the top of the gas flow passage.
And during storage, the air outlet of the sealing structure is sealed by the filling material.
When the air-out structure works, the material in the air outlet hole of the sealing structure falls off under the action of temperature and pressure, so that the air flow passage is communicated with the outside.
The high-temperature heat insulation layer is made of high-density ablation materials or heat insulation prevention materials. The material of the support ring is aluminum alloy.
Compared with the prior art, the invention has the beneficial effects that:
1) the invention combines the advantages of heat shield of the high-temperature heat-insulating layer and the advantages of high phase-change latent heat of water, improves the heat-proof efficiency of the structure, and provides a stable 'comfortable' environment for the internal structure by utilizing the advantages of low and stable water phase temperature change;
2) the water is stored in the hollow bearing structure in a hydrogel mode, so that the heat-proof bearing integration is realized, the working medium is gasified and removed by heating, an additional driving device is not needed, and the structural efficiency is improved;
3) the transverse flow channel is designed in the airflow channel, the working medium has strong transverse fluidity, the problem of 'hot spots' during local severe heating is solved, and the structural reliability is improved;
4) the airflow discharge channel is separated from the heat-proof layer, is not positioned at the outermost layer, has lower temperature, and solves the problem that the sweat pores are blocked by melts or ablates.
Drawings
FIG. 1 is an overall view of the thermostatic heat shield structure of the present invention;
FIG. 2 is a cross-sectional view of the thermostatic heat shield structure of the present invention;
FIG. 3 is a view showing a structure of a seal at the top of the air flow path according to the present invention;
FIG. 4 is an enlarged, fragmentary view of a support ring according to the present invention;
FIG. 5 is a view of the construction of the support ring of the present invention;
fig. 6 is a graph comparing the weight and the heat shielding effect of two heat shielding structures.
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description.
A constant temperature heat shield structure of the present invention, which can be stored for a long period of time, is shown in FIGS. 1 and 2, and includes: a bearing structure 1, a high-temperature heat-insulating layer 3 and a support ring 4. The high-temperature heat insulation layer 3 is sleeved outside the bearing structure 1 to form a cylinder structure; the high-temperature heat-insulating layer 3 and the bearing structure 1 are used as a gas flow passage 2 and are fixedly provided with a plurality of support rings 4; the bearing structure 1 is a hollow structure, and water in a gel state is stored in the hollow structure; the bearing structure 1 is provided with an exhaust channel, water in a gel state stored in the bearing structure 1 is vaporized to absorb heat, and the exhaust channel is used for discharging gaseous liquid solid three-phase flow substances including water vapor, water drops and aerogel residues from the exhaust channel.
The high-temperature heat insulation layer 3 is used for shielding external heat flow.
A plurality of support rings 4 are arrayed in the axial direction of the cylindrical structure. The support ring 4 comprises: a transverse air flow decelerating cover 7 and a longitudinal air flow decelerating cover 8, as shown in fig. 4 and 5.
The transverse airflow speed reducing cover 7 is of an annular structure with a concave section, and the opening direction of the annular structure with the concave section of the transverse airflow speed reducing cover 7 faces the exhaust channel of the bearing structure 1; one free end of the concave annular structure of the transverse airflow speed reducing cover 7 is fixedly connected with the bearing structure 1, and the other free end of the concave annular structure of the transverse airflow speed reducing cover 7 is not contacted with the bearing structure 1 to form a gap.
The transverse airflow deceleration cover 7 has the functions of decelerating gaseous liquid state and solid state three-phase flow substances discharged from the small holes 12, reducing the flying of water drops and aerogel residues along with water vapor, storing the water drops and the aerogel residues, improving the phase change ratio of water and simultaneously slowing down airflow impact on an interface of the heat-proof layer.
The longitudinal airflow speed reducing cover 8 is of an annular structure with a concave section, the longitudinal airflow speed reducing cover 8 is positioned at the lower part of the transverse airflow speed reducing cover 7, and the opening direction of the concave annular structure of the longitudinal airflow speed reducing cover 8 faces to the transverse airflow speed reducing cover 7 at the upper part of the longitudinal airflow speed reducing cover; two free ends of the longitudinal airflow speed reducing cover 8 are respectively fixedly connected with the bearing structure 1 and the high-temperature heat insulation layer 3.
The bottom of the longitudinal airflow speed reducing cover 8 is provided with conical holes 9 protruding upwards, and the conical holes 9 are uniformly distributed in the circumferential direction. The conical hole 9 serves as a discharge passage for water vapor.
The longitudinal air flow decelerating cover 8 further decelerates the air flow, reduces water drops and aerogel residues in the air flow and serves as a liquid water storage.
A plurality of partition plates 11 are fixedly installed in the bearing structure 1, and the hollow structure of the bearing structure 1 is divided into a plurality of independent cavities 6 which are not communicated with each other by the partition plates 11. Hydrogel is filled in each cavity 6, and is heated to be vaporized into water vapor, so that heat is absorbed by vaporization; the temperature of the internal structure is ensured not to exceed the vaporization temperature of water.
The wall surface of one side of each cavity 6 facing the high-temperature heat-insulating layer 3 is provided with small holes 12 which are uniformly distributed in the circumferential direction, and the small holes 12 are used as exhaust passages after hydrogel is heated and vaporized. The hydrogel heated discharge is a gas-liquid-solid three-phase flow, and comprises: water vapor, water droplets, aerogel residues. The high-temperature heat insulation layer 3 is made of high-density ablation materials or heat insulation prevention materials, and utilizes the surface high temperature to block pneumatic heat flow and the radiation heat dissipation capacity of the pneumatic heat flow.
A constant temperature heat shield structure that can be stored for a long period of time of the present invention is shown in fig. 3, and further includes: and a seal structure 5. The sealing structure 5 is fixedly installed on the top of the gas flow passage 2. During storage, the air outlet 10 of the sealing structure 5 is sealed by filling material paraffin. When the gas flow passage 2 works, the material in the gas outlet 10 of the sealing structure 5 falls off under the action of temperature and pressure, so that the gas flow passage 2 is communicated with the outside.
The material of the support ring 4 in the embodiment of the invention is aluminum alloy.
Examples
Taking a cylindrical shell section as an example, the pneumatic heat flow conditions are shown in table 1, and the design aim is to control the temperature of the inner wall of the force bearing structure 1 within 120 ℃.
The parameters of the thermal protection structure of the invention are as follows:
1) the outer diameter of the cylindrical shell is 1m, and the height is 500 mm; the total thickness of the bearing structure 1 is 7mm, the width of the airflow channel 2 is 5mm, the high-temperature heat insulation layer 3 is made of high silica/phenolic aldehyde, and the thickness is 5 mm.
2) The bearing structure 1 is made of aluminum alloy, and the wall thickness is 1 mm; the distance between the partition boards 11 is 20mm, and the cavity is filled with hydrogel; the diameter of the air outlet 12 is 1 mm;
3) the support rings 4 in the airflow channel 2 are made of aluminum alloy, the longitudinal distribution distance is 20mm, and the wall thickness is 1 mm; the width of the transverse airflow speed reducing cover 7 is 4mm, the height of the transverse airflow speed reducing cover is 4mm, and the width of the upper end flanging is 2 mm; the distance between the longitudinal airflow speed reducing cover 8 and the transverse airflow speed reducing cover 7 is 4.5mm, the width of the connecting surface with the bearing structure 1 is 4mm, and the width of the connecting surface with the high-temperature heat insulating layer 3 is 4 mm; the diameter of the bottom of the taper hole 9 is 3mm, the diameter of the top is 1mm, and the height is 2 mm; the width of the sealing structure 5 is 5mm, the height is 5mm, the wall thickness is 1mm, and the diameter of the air outlet 10 is 1 mm;
in contrast, the structural parameters of the conventional heat-proof jacket are as follows:
1) the outer diameter of the cylindrical shell is 1m, the height is 500mm, and the cylindrical shell is divided into an inner aluminum alloy bearing shell and an outer heat-proof layer;
2) the internal aluminum alloy shell and the aluminum alloy structure are designed according to equal weight, a heat sink is simulated, and the thickness is 2.5 mm;
the heat-proof layer is made of high-silica/phenolic aldehyde, the weight of the heat-proof layer is the same as that of the hydrogel, and the thickness of the heat-proof layer is 12.3 mm.
The weight and the heat-proof effect of the two heat-proof structures are shown in table 3 and fig. 6, and under the condition that the structure temperature is basically the same in the service time, the heat-proof structure of the invention is reduced by 25.6 percent compared with the traditional heat-proof sleeve structure. Compared with the traditional heat-proof sleeve structure, the structure efficiency of the invention is obviously improved.
TABLE 1 Cold wall Heat flow conditions
TABLE 2 Properties of the materials
TABLE 3 comparison of the structure of the present invention with the structure of the conventional heat-proof jacket
Those skilled in the art will appreciate that the details of the invention not described in detail in the specification are within the skill of those skilled in the art.
Claims (6)
1. A long-shelf, constant temperature heat shield structure comprising: a bearing structure (1), a high-temperature heat insulation layer (3) and a support ring (4);
the high-temperature heat insulation layer (3) is sleeved outside the bearing structure (1) to form a cylinder structure;
the high-temperature heat-insulating layer (3) and the bearing structure (1) are used as a gas flow passage (2) and are fixedly provided with a plurality of support rings (4);
the bearing structure (1) is a hollow structure, and water in a gel state is stored in the hollow structure; the bearing structure (1) is provided with an exhaust channel, water in a gel state stored in the bearing structure (1) is vaporized to absorb heat, and the exhaust channel is used for discharging gaseous liquid solid three-phase flow substances including water vapor, water drops and aerogel residues from the exhaust channel;
the high-temperature heat insulation layer (3) is used for shielding external heat flow;
a plurality of support rings (4) arrayed in the axial direction of the cylindrical structure;
the support ring (4) comprises: a transverse airflow speed reducing cover (7) and a longitudinal airflow speed reducing cover (8);
the cross section of the transverse airflow deceleration cover (7) is of a concave annular structure, and the opening direction of the concave annular structure of the transverse airflow deceleration cover (7) faces the exhaust channel of the bearing structure (1); one free end of the concave annular structure of the transverse airflow deceleration cover (7) is fixedly connected with the bearing structure (1), and the other free end of the concave annular structure of the transverse airflow deceleration cover (7) is not contacted with the bearing structure (1) to form a gap;
the transverse airflow deceleration cover (7) has the functions of decelerating gaseous liquid state and solid state three-phase flow substances discharged from the small holes (12), reducing the flying of water drops and aerogel residues along with water vapor, storing the water drops and the aerogel residues, improving the phase change ratio of water and simultaneously slowing down the airflow impact on the interface of the high-temperature heat-insulating layer (3);
the longitudinal airflow deceleration cover (8) is of an annular structure with a concave section, the longitudinal airflow deceleration cover (8) is positioned at the lower part of the transverse airflow deceleration cover (7), and the opening direction of the concave annular structure of the longitudinal airflow deceleration cover (8) faces to the transverse airflow deceleration cover (7) at the upper part of the longitudinal airflow deceleration cover; two free ends of the longitudinal airflow speed reducing cover (8) are respectively fixedly connected with the bearing structure (1) and the high-temperature heat insulating layer (3);
the bottom of the longitudinal airflow speed reducing cover (8) is provided with a conical hole (9) protruding upwards, and the conical hole (9) is used as a discharge channel of water vapor;
a plurality of partition plates (11) are fixedly installed in the bearing structure (1), and the hollow structure of the bearing structure (1) is divided into a plurality of independent cavities (6) which are not communicated with each other by the partition plates (11);
the interior of each cavity (6) is filled with hydrogel;
the wall surface of one side of each cavity (6) facing the high-temperature heat-insulating layer (3) is provided with small holes (12), and the small holes (12) are used as exhaust passages after hydrogel is heated and vaporized.
2. A long-term storable constant temperature heat shield structure as recited in claim 1 further comprising: a sealing structure (5);
the sealing structure (5) is fixedly arranged on the top of the gas flow passage (2).
3. A long-term storable constant temperature heat shield structure according to claim 2, characterized in that the gas outlet hole (10) of the sealing structure (5) is sealed by a filler material during storage.
4. A thermostatted heat shield structure as claimed in claim 3, characterized in that, in operation, the material in the outlet opening (10) of the sealing structure (5) falls off under the effect of temperature and pressure, so that the gas channel (2) is connected to the environment.
5. A long-storable constant temperature heat shield structure according to claim 4 characterised in that the high temperature insulation layer (3) is a high density ablative material or an insulation resistant material.
6. A long-storable constant temperature heat shield structure according to claim 5, characterised in that the material of the support ring (4) is an aluminium alloy.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010976169.6A CN112193402B (en) | 2020-09-16 | 2020-09-16 | Constant-temperature heat shield structure capable of being stored for long time |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010976169.6A CN112193402B (en) | 2020-09-16 | 2020-09-16 | Constant-temperature heat shield structure capable of being stored for long time |
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| CN112193402A CN112193402A (en) | 2021-01-08 |
| CN112193402B true CN112193402B (en) | 2022-01-04 |
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| CN113978046B (en) * | 2021-11-09 | 2022-07-29 | 厦门大学 | Thermal protection structure and preparation method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8864073B1 (en) * | 2011-07-27 | 2014-10-21 | The Boeing Company | Aeroshell thermal protection system and method |
| CN106114915A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of safeguard structure of interconnected carrying heat-insulation integrative |
| CN109572985A (en) * | 2018-11-28 | 2019-04-05 | 沈阳航空航天大学 | A kind of micro- truss thermal protection panel containing dual channel |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN110641683A (en) * | 2019-11-04 | 2020-01-03 | 中国航空制造技术研究院 | Thermal protection structure and processing method |
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2020
- 2020-09-16 CN CN202010976169.6A patent/CN112193402B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8864073B1 (en) * | 2011-07-27 | 2014-10-21 | The Boeing Company | Aeroshell thermal protection system and method |
| CN106114915A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of safeguard structure of interconnected carrying heat-insulation integrative |
| CN109572985A (en) * | 2018-11-28 | 2019-04-05 | 沈阳航空航天大学 | A kind of micro- truss thermal protection panel containing dual channel |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN110641683A (en) * | 2019-11-04 | 2020-01-03 | 中国航空制造技术研究院 | Thermal protection structure and processing method |
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