CN212006943U - Gas film heat insulation and temperature reduction device for gas source of solid gas generator - Google Patents
Gas film heat insulation and temperature reduction device for gas source of solid gas generator Download PDFInfo
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- CN212006943U CN212006943U CN202020046624.8U CN202020046624U CN212006943U CN 212006943 U CN212006943 U CN 212006943U CN 202020046624 U CN202020046624 U CN 202020046624U CN 212006943 U CN212006943 U CN 212006943U
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Abstract
A gas film heat insulation and temperature reduction device of a gas source of a solid gas generator consists of an aircraft hood, a generator fixing support, the solid gas generator, a gas filtering and rectifying storage box, a gas adjusting and conveying system and a gas distribution device; the generator fixing support is fastened on the inner walls of the upper side and the lower side of the aircraft hood through screws, and the solid gas generator is fastened on the right side of the middle of the generator fixing support through bolts; the gas filtering and rectifying storage tank is connected with the solid gas generator by adopting a flange and is sealed by adopting an O-shaped ring; the gas regulating and conveying system and the gas filtering and rectifying storage box are connected by a pipe joint and sealed by a spherical conical surface, and the gas distributing device and the gas regulating and conveying system are connected by a pipe joint and sealed by a spherical conical surface. The utility model discloses can obtain the gas that the temperature is lower, clean, delivery pressure is stable, can simplify air supply system greatly, alleviate the ablation of aircraft hood material by a wide margin.
Description
Technical Field
The utility model relates to a gas film heat insulation and cooling device of solid gas generator air supply for the active of hypersonic aircraft hood surface is thermal-insulated, belongs to the thermal-insulated technical field of hypersonic aircraft heat protection.
Background
When high-speed aircrafts (hereinafter referred to as 'aircrafts') such as aerospace planes, space shuttles, missiles, rockets and the like fly in the atmosphere at high speed for a long time, high dynamic pressure and strong pneumatic heating effect can be generated on the outer surface of the hood. The high temperatures generated by the harsh aerodynamic heating effects can significantly reduce the strength limitations and structural load carrying capacity of the aircraft shell material. The basic purpose of thermal protection of an aircraft is to ensure the structural safety of the aircraft and to maintain the internal walls of the aircraft within the allowable temperature and pressure ranges in the harsh environment of pneumatic heating.
The heat-proof and heat-insulating technology of the existing aircraft mainly comprises three major categories of passive heat-proof, active heat-proof and semi-active heat-proof, wherein: the passive heat protection mainly depends on a heat-proof structure and a material to absorb or radiate heat without working media, and the scheme is simple and reliable, is widely adopted at present, but has short heat-proof time; the active cooling mainly depends on a cooling working medium to take away most heat flow and reflect a small part of heat, the scheme has long heat-proof time, but a cooling working medium storage box and a conveying system need to be designed in the device, the structure is complex, and the occupied space is large; the semi-active heat protection is between passive heat protection and active heat protection, mainly adopts two forms of a heat pipe structure and an ablation structure, has long heat protection time, does not need a storage tank and a conveying system in the semi-active heat protection, and has a complicated heat pipe structure and larger occupied space relative to the ablation structure.
Considering that the pneumatic structure on the surface of an aircraft hood is complex, and is limited by multiple aspects such as the use temperature of a metal shell and internal elements, the diameter of a bullet and the like, the single passive heat protection (such as a heat protection tile, a carbon-carbon material and a carbon-silicon material) or semi-active heat protection (such as an ablation structure) cannot meet the heat protection requirements at higher speed for longer time. The bad pneumatic heating effect generated by high-speed and long-time flight can cause the change of the pneumatic outer profile of the aircraft, thereby influencing the flight stability of the aircraft.
Disclosure of Invention
The technical solution problem of the utility model is that: the defects of the prior art are overcome, the gas film heat insulation and cooling device of the gas source of the solid gas generator is provided, the low-temperature solid gas generator is used as the gas source, the gas with low temperature, cleanness and stable conveying pressure is conveyed into the gas film heat insulation holes of the aircraft hood after filtration, rectification and pressure stabilization, the uniform low-temperature gas film can be formed on the outer surface of the hood, the pneumatic heating effect on the outer surface of the aircraft hood can be effectively reduced, ablation of the aircraft hood material is greatly reduced, and therefore the thermal protection requirements of the aircraft at higher speed and for longer time are met.
The technical solution of the utility model is that:
a gas film heat insulation and temperature reduction device using a low-temperature solid gas generator as a gas source mainly comprises an aircraft hood (1), a generator fixing support (2), a solid gas generator (3), a gas filtering and rectifying storage box (4), a gas adjusting and conveying system (5) and a gas distribution device (6); wherein the generator fixing support (2) is fastened on the inner walls of the upper side and the lower side of the aircraft hood (1) by screws, and the solid gas generator (3) is fastened on the right side of the middle part of the generator fixing support (2) by bolts; the gas filtering and rectifying storage tank (4) is integrally conical, the head of the gas filtering and rectifying storage tank is blunt, the gas filtering and rectifying storage tank is positioned on the right side of the solid gas generator (3), and the gas filtering and rectifying storage tank is connected with the solid gas generator (3) by a flange and sealed by an O-shaped ring; the gas regulating and conveying system (5) is positioned at the outer side of the solid gas generator (3) and the left side of the gas filtering and rectifying storage tank (4), is connected with the gas filtering and rectifying storage tank (4) by a pipe joint and is sealed by a spherical conical surface, the inner side and the outer side of the gas distributing device (6) are both conical, the head of the gas distributing device is blunt, the gas regulating and conveying system (5) is positioned at the inner side of the aircraft hood (1), is connected with the gas filtering and rectifying storage tank (4) by the pipe joint and is sealed by the spherical conical surface, a boss is arranged on the inner wall of the left end of the gas distributing device (6), and is fastened with a support lug at the left side edge of the gas;
the solid gas generator (3) consists of a generator shell (9), a low-temperature solid propellant (10), an ignition device (11), a primary filter screen (12) and a spray pipe (13); the low-temperature solid propellant (10) is filled in the generator shell (9); the ignition device (11) is bonded on the right end combustion surface of the low-temperature solid propellant (10) and ignites the low-temperature solid propellant (10) when receiving an ignition instruction; the primary filter screen (12) is of a metal net structure, is limited between the inner side of the right end of the generator shell (9) and the inner side of the left end of the spray pipe (13) by steps, and performs primary filtration on the gas; the spray pipe (13) is in a cone-column shape, the inner molded surface of the throat liner adopts a Laval spray pipe structure, and is in threaded connection with the right end of the generator shell (9) and sealed by an O-shaped ring, so that the internal pressure of the generator is stable, and the stable combustion of the low-temperature solid propellant (10) is ensured;
the fuel gas filtering and rectifying storage tank (4) consists of a filter screen (14) and a rectifying storage tank (15); the filter screen (14) is of a metal net structure, the meshes of the filter screen are smaller than those of the primary filter screen (12), and the filter screen is fastened on the inner wall of the middle part of the left end of the rectification storage box (15) through screws to carry out secondary filtration on the fuel gas; the rectification storage box (15) is integrally conical, the head of the rectification storage box is blunt, and the gas after secondary filtration is rectified and stored;
the gas regulating and conveying system (5) consists of a pressure reducing valve (16), a flow regulating valve (17) and a one-way valve (18), wherein the pressure reducing valve (16) is connected with the flow regulating valve (17) through a gas pipeline and is sealed by adopting a spherical conical surface; the flow regulating valve (17) is connected with the one-way valve (18) through a gas pipeline and is sealed by adopting a spherical conical surface; the one-way valve (18) is connected with the gas distribution device (6) through a gas pipeline and sealed by adopting a spherical conical surface;
the gas distribution device (6) consists of a gas nozzle (7) and a distribution tank (8); the air nozzle (7) is installed on the shell wall of the outer cambered surface of the distribution tank (8) by adopting threads, is sealed by an O-shaped ring, is inserted into the inner side of the head of the aircraft nose cover (1) together with the distribution tank (8), and the outer side of the distribution tank (8) is tightly attached to the inner wall of the aircraft nose cover (1); after entering the distribution tank, the low-temperature, clean and stable-pressure gas is discharged to the outer surface of the aircraft hood (1) through the air nozzle (7) to form a uniform and stable low-temperature gas film;
compared with the prior art, the utility model the advantage lie in:
(1) the combined type heat-proof device can be combined with passive heat-proof or semi-active heat-proof to form a more effective combined heat-proof means, has long heat-proof time, simple structure and small occupied space compared with active heat-proof, greatly simplifies an air source supply system, and has higher integral working reliability;
(2) compared with other active cooling modes, after low-temperature fuel gas with less condensed phase is filtered, rectified, stabilized, flow-regulated and distributed, the uniformity of air flow is better, a uniform and stable low-temperature air film can be formed on the outer surface of the aircraft hood, the pneumatic heating effect on the outer surface of the aircraft hood is effectively reduced, and the ablation of the aircraft hood material is greatly reduced.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and embodiments;
FIG. 1 is a schematic structural view of a gas film heat-insulating and temperature-reducing device;
FIG. 2 is an enlarged view of a portion of the air nozzle and the air film heat shield aperture;
FIG. 3 is a schematic illustration of a solid gas generator configuration;
FIG. 4 is a schematic view of a gas filtering and rectifying storage tank;
FIG. 5 is a schematic diagram of a gas conditioning and delivery system;
the list of labels in the figure is: 1. aircraft hood, 2, generator fixed support, 3, solid gas generator, 4, gas filtering and rectifying storage tank, 5, air flow regulating and conveying system, 6, gas distribution device, 7, air nozzle, 8, distribution tank, 9, generator shell, 10, low-temperature solid propellant, 11, ignition device, 12, primary filter screen, 13, spray pipe, 14, filter screen, 15, rectifying storage tank, 16, pressure reducing valve, 17, flow regulating valve, 18 and one-way valve.
Detailed Description
The structure of the gas film heat insulation and temperature reduction device provided by the utility model is shown in figure 1, and mainly comprises an aircraft hood (1), a generator fixing support (2), a solid gas generator (3), a gas filtering and rectifying storage box (4), a gas adjusting and conveying system (5) and a gas distribution device (6); wherein the generator fixing support (2) is fastened on the inner walls of the upper side and the lower side of the aircraft hood (1) by screws, and the solid gas generator (3) is fastened on the right side of the middle part of the generator fixing support (2) by bolts; the gas filtering and rectifying storage tank (4) is integrally conical, the head of the gas filtering and rectifying storage tank is blunt, the gas filtering and rectifying storage tank is positioned on the right side of the solid gas generator (3), and the gas filtering and rectifying storage tank is connected with the solid gas generator (3) by a flange and sealed by an O-shaped ring; the gas regulating and conveying system (5) is positioned at the outer side of the solid gas generator (3) and the left side of the gas filtering and rectifying storage tank (4), is connected with the gas filtering and rectifying storage tank (4) by a pipe joint and is sealed by a spherical conical surface, the inner side and the outer side of the gas distributing device (6) are both conical, the head of the gas distributing device is blunt, the gas regulating and conveying system (5) is positioned at the inner side of the aircraft hood (1), is connected with the gas filtering and rectifying storage tank (4) by the pipe joint and is sealed by the spherical conical surface, a boss is arranged on the inner wall of the left end of the gas distributing device (6), and is fastened with a support lug at the left side edge of the gas;
the solid gas generator (3) consists of a generator shell (9), a low-temperature solid propellant (10), an ignition device (11), a primary filter screen (12) and a spray pipe (13); the low-temperature solid propellant (10) is filled in the generator shell (9); the ignition device (11) is bonded on the right end combustion surface of the low-temperature solid propellant (10) and ignites the low-temperature solid propellant (10) when receiving an ignition instruction; the primary filter screen (12) is of a metal net structure, is limited between the inner side of the right end of the generator shell (9) and the inner side of the left end of the spray pipe (13) by steps, and performs primary filtration on the gas; the spray pipe (13) is in a cone-column shape, the inner molded surface of the throat liner adopts a Laval spray pipe structure, and is in threaded connection with the right end of the generator shell (9) and sealed by an O-shaped ring, so that the internal pressure of the generator is stable, and the stable combustion of the low-temperature solid propellant (10) is ensured;
the fuel gas filtering and rectifying storage tank (4) consists of a filter screen (14) and a rectifying storage tank (15); the filter screen (14) is of a metal net structure, the meshes of the filter screen are smaller than those of the primary filter screen (12), and the filter screen is fastened on the inner wall of the middle part of the left end of the rectification storage box (15) through screws to carry out secondary filtration on the fuel gas; the rectification storage box (15) is integrally conical, the head of the rectification storage box is blunt, and the gas after secondary filtration is rectified and stored;
the gas regulating and conveying system (5) consists of a pressure reducing valve (16), a flow regulating valve (17) and a one-way valve (18), wherein the pressure reducing valve (16) is connected with the flow regulating valve (17) through a gas pipeline and is sealed by adopting a spherical conical surface; the flow regulating valve (17) is connected with the one-way valve (18) through a gas pipeline and is sealed by adopting a spherical conical surface; the one-way valve (18) is connected with the gas distribution device (6) through a gas pipeline and sealed by adopting a spherical conical surface;
the gas distribution device (6) consists of a gas nozzle (7) and a distribution tank (8); the air nozzle (7) is installed on the shell wall of the outer cambered surface of the distribution tank (8) by adopting threads, is sealed by an O-shaped ring, is inserted into the inner side of the head of the aircraft nose cover (1) together with the distribution tank (8), and the outer side of the distribution tank (8) is tightly attached to the inner wall of the aircraft nose cover (1); after entering the distribution tank, the low-temperature, clean and stable-pressure gas is discharged to the outer surface of the aircraft hood (1) through the air nozzle (7) to form a uniform and stable low-temperature gas film;
when the gas film heat insulation and cooling device works, the low-temperature solid propellant (10) is ignited through the ignition device (11) of the solid fuel gas generator (3) to continuously generate low-temperature fuel gas with few condensed phase particles, and the fuel gas filters main residues in the fuel gas through the primary filter screen (12); then, the fuel gas enters a fuel gas filtering and rectifying storage box (4) through a spray pipe (13), is further filtered through a filter screen (14), and is integrated in a rectifying storage box (15) to enable the flowing state to tend to be stable; finally, the gas is decompressed by a decompression valve (16), the flow of the gas is regulated by a flow regulating valve (17), and then the gas enters a gas distribution device (6), meanwhile, a one-way valve (18) prevents gas from flowing back, so that low-temperature, clean and stable-pressure-conveying gas is obtained, the gas is uniformly distributed in each gas nozzle (7) by the gas distribution device (6), and after the gas is sprayed out of a gas film heat insulation hole, a uniform and stable low-temperature gas film is formed on the outer surface of the aircraft hood, so that the heat transfer from pneumatic heat to the interior of the aircraft is blocked, the pneumatic heating effect of the outer surface of the aircraft hood is effectively reduced, and the ablation of the aircraft hood material is;
details not described in the present specification belong to the prior art known to those skilled in the art.
Claims (5)
1. The utility model provides a gas film heat-insulating heat sink of solid gas generator air supply which characterized in that: the device consists of an aircraft hood (1), a generator fixing support (2), a solid fuel gas generator (3), a fuel gas filtering and rectifying storage tank (4), a gas regulating and conveying system (5) and a gas distribution device (6); wherein the generator fixing support (2) is fastened on the inner walls of the upper side and the lower side of the aircraft hood (1) by screws, and the solid gas generator (3) is fastened on the right side of the middle part of the generator fixing support (2) by bolts; the gas filtering and rectifying storage tank (4) is integrally conical, the head of the gas filtering and rectifying storage tank is blunt, the gas filtering and rectifying storage tank is positioned on the right side of the solid gas generator (3), and the gas filtering and rectifying storage tank is connected with the solid gas generator (3) by a flange and sealed by an O-shaped ring; the gas regulating and conveying system (5) is located on the outer side of the solid gas generator (3) and on the left side of the gas filtering and rectifying storage box (4), the gas regulating and conveying system (5) and the gas filtering and rectifying storage box (4) are connected through a pipe joint and sealed through a spherical conical surface, the inner side and the outer side of the gas distributing device (6) are conical, the head of the gas distributing device is blunt, the gas regulating and conveying system and the gas filtering and rectifying storage box are located on the inner side of an aircraft hood (1), the gas regulating and conveying system (5) are connected through the pipe joint and sealed through the spherical conical surface, a boss is arranged on the inner wall of the left end of the gas distributing device (6), and the gas regulating and conveying system and the lug on the left.
2. The gas film heat insulation and temperature reduction device according to claim 1, characterized in that: the solid gas generator (3) consists of a generator shell (9), a low-temperature solid propellant (10), an ignition device (11), a primary filter screen (12) and a spray pipe (13); the low-temperature solid propellant (10) is filled in the generator shell (9); the ignition device (11) is bonded on the right combustion face of the low-temperature solid propellant (10); the primary filter screen (12) is of a metal net structure and is limited between the inner side of the right end of the generator shell (9) and the inner side of the left end of the spray pipe (13) by steps; the spray pipe (13) is in a cone-column shape, the inner molded surface of the throat liner adopts a Laval spray pipe structure, and is in threaded connection with the right end of the generator shell (9) and sealed by an O-shaped ring.
3. The gas film heat insulation and temperature reduction device according to claim 1, characterized in that: the fuel gas filtering and rectifying storage tank (4) consists of a filter screen (14) and a rectifying storage tank (15); the filter screen (14) is of a metal net structure and is fastened on the inner wall of the middle part of the left end of the rectification storage box (15) by screws; the rectification storage box (15) is integrally conical, the head of the rectification storage box is blunt, and the gas after secondary filtration is rectified and stored.
4. The gas film heat insulation and temperature reduction device according to claim 1, characterized in that: the gas regulating and conveying system (5) consists of a pressure reducing valve (16), a flow regulating valve (17) and a one-way valve (18), wherein the pressure reducing valve (16) is connected with the flow regulating valve (17) through a gas pipeline and is sealed by adopting a spherical conical surface; the flow regulating valve (17) is connected with the one-way valve (18) through a gas pipeline and is sealed by adopting a spherical conical surface; the one-way valve (18) is connected with the gas distribution device (6) through a gas pipeline and is sealed by adopting a spherical conical surface.
5. The gas film heat insulation and temperature reduction device according to claim 1, characterized in that: the gas distribution device (6) consists of a gas nozzle (7) and a distribution tank (8); the air nozzle (7) is installed on the shell wall of the outer cambered surface of the distribution tank (8) by adopting threads, is sealed by an O-shaped ring, is inserted into the inner side of the head of the aircraft nose cover (1) together with the distribution tank (8), and the outer side of the distribution tank (8) is tightly attached to the inner wall of the aircraft nose cover (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020046624.8U CN212006943U (en) | 2020-01-10 | 2020-01-10 | Gas film heat insulation and temperature reduction device for gas source of solid gas generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020046624.8U CN212006943U (en) | 2020-01-10 | 2020-01-10 | Gas film heat insulation and temperature reduction device for gas source of solid gas generator |
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| Publication Number | Publication Date |
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| CN212006943U true CN212006943U (en) | 2020-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020046624.8U Active CN212006943U (en) | 2020-01-10 | 2020-01-10 | Gas film heat insulation and temperature reduction device for gas source of solid gas generator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212006943U (en) |
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