A gas film insulation and cooling device for gas source of solid fuel gas generator

Abstract

An air film heat insulation and cooling device for a gas source of a solid fuel gas generator is composed of an aircraft hood, a generator fixing bracket, a solid fuel gas generator, a fuel gas filter and rectifying tank, a gas regulating and conveying system, and a gas distribution device; wherein the generator fixing bracket is fastened to the inner walls of the upper and lower sides of the aircraft hood with screws, and the solid fuel gas generator is fastened to the middle right side of the generator fixing bracket with bolts; the fuel gas filter and rectifying tank is connected to the solid fuel gas generator by a flange and sealed by an O-ring; the gas regulating and conveying system is connected to the fuel gas filter and rectifying tank by a pipe joint and sealed by a spherical cone surface, and the gas distribution device is connected to the gas regulating and conveying system by a pipe joint and sealed by a spherical cone surface. The present invention can obtain gas with a relatively low temperature, cleanliness, and stable conveying pressure, can greatly simplify the gas source supply system, and greatly reduce the ablation of the aircraft hood material.

Description

Technical Field

[0001] The invention relates to an air film heat insulation and cooling device for a gas source of a solid fuel gas generator, which is used for active heat insulation of the outer surface of a hypersonic aircraft hood and belongs to the technical field of heat protection and heat insulation of hypersonic aircraft. Background Art

[0002] When hypersonic aircraft such as aerospace planes, space shuttles, missiles, rockets, etc. (hereinafter referred to as "aircraft") fly at high speed for a long time in the atmosphere, the outer surface of the hood will generate very high dynamic pressure and strong aerodynamic heating effect. The high temperature generated by the harsh aerodynamic heating effect will significantly reduce the strength limit and structural bearing capacity of the aircraft shell material. The basic purpose of aircraft thermal protection is to ensure the structural safety of the aircraft in the harsh environment of aerodynamic heating and to keep the inner wall of the aircraft within the allowable temperature and pressure range;

[0003] At present, there are three main types of aircraft heat protection and insulation technologies: passive heat protection, active heat protection, and semi-active heat protection. Among them: passive heat protection mainly relies on the heat protection structure and the material itself to absorb or radiate heat, and does not require working fluid. This solution is simple and reliable, and is currently widely used, but the heat protection time is short; active cooling mainly relies on the cooling working fluid to take away most of the heat flow and reflect a small part of the heat. This solution has a long heat protection time, but the device needs to design a cooling working fluid tank and a transportation system, the structure is relatively complex, and occupies a large space; semi-active thermal protection is between passive heat protection and active heat protection, and mainly adopts two forms: heat pipe structure and ablation structure. The heat protection time is longer, and no tank and transportation system are required. The heat pipe structure is more complex than the ablation structure and occupies a large space;

[0004] Considering the complex aerodynamic structure of the aircraft's nose cover, and the limitations of the metal shell and internal components' operating temperature, bullet diameter, and other factors, a single passive heat protection (such as heat protection tiles, carbon-carbon materials, and carbon-silicon materials) or semi-active heat protection (such as ablative structures) can no longer meet the thermal protection requirements at higher speeds and longer times. The harsh aerodynamic heating effect caused by high-speed and long-term flight will cause the aircraft's aerodynamic shape to change, thereby affecting the aircraft's flight stability. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the defects of the prior art, to propose an air film heat insulation and cooling device for the gas source of a solid fuel gas generator, to use a low-temperature solid fuel gas generator as the gas source, to deliver low-temperature, clean gas with stable delivery pressure to the air film heat insulation hole of the aircraft hood after filtering, rectifying and stabilizing the voltage, to form a uniform low-temperature air film on the outer surface of the hood, to effectively reduce the aerodynamic heating effect on the outer surface of the aircraft hood, to greatly reduce the ablation of the aircraft hood material, thereby meeting the thermal protection requirements of the aircraft at higher speeds and for longer periods of time;

[0006] The technical solution of the present invention is:

[0007] A gas film heat insulation and cooling device using a low-temperature solid gas generator as a gas source, mainly comprising an aircraft head cover (1), a generator fixing bracket (2), a solid gas generator (3), a gas filter and rectifying tank (4), a gas regulating and conveying system (5) and a gas distribution device (6); wherein the generator fixing bracket (2) is fastened to the inner walls of the upper and lower sides of the aircraft head cover (1) by screws, and the solid gas generator (3) is fastened to the middle right side of the generator fixing bracket (2) by bolts; the gas filter and rectifying tank (4) is overall conical in shape, with a blunt head, and is located on the right side of the solid gas generator (3). The flange is connected to the solid gas generator (3) and is sealed by an O-ring; the gas regulating and conveying system (5) is located outside the solid gas generator (3) and on the left side of the gas filter and rectifying tank (4), and is connected to the gas filter and rectifying tank (4) by a pipe joint and a spherical cone surface seal; the gas distribution device (6) is conical inside and outside, and has a blunt head, and is located on the inside of the aircraft head cover (1), and is connected to the gas regulating and conveying system (5) by a pipe joint and a spherical cone surface seal; a boss is provided on the inner wall of the left end of the gas distribution device (6), and is fastened to the lug on the left edge of the gas filter and rectifying tank (4) by screws;

[0008] The solid fuel gas generator (3) is composed of a generator housing (9), a cryogenic solid propellant (10), an ignition device (11), a primary filter (12) and a nozzle (13); the cryogenic solid propellant (10) is loaded in the generator housing (9); the ignition device (11) is bonded to the right end combustion surface of the cryogenic solid propellant (10), and ignites the cryogenic solid propellant (10) when receiving an ignition command; the primary filter (12) is a metal mesh structure, and is limited by a step between the right end inner side of the generator housing (9) and the left end inner side of the nozzle (13) to perform primary filtering of the fuel gas; the nozzle (13) is in a "cone-column" shape, and its throat liner inner profile adopts a Laval nozzle structure, and is threadedly connected to the right end of the generator housing (9) and sealed with an O-ring, so that the internal pressure of the generator is stable, thereby ensuring stable combustion of the cryogenic solid propellant (10);

[0009] The gas filter and rectifying storage tank (4) is composed of a filter screen (14) and a rectifying storage tank (15); the filter screen (14) is a metal mesh structure, the mesh openings of which are smaller than the mesh openings of the primary filter screen (12), and is fastened to the inner wall of the middle part of the left end of the rectifying storage tank (15) by screws to perform secondary filtering on the gas; the rectifying storage tank (15) is generally conical in shape, and the head is blunt in shape, and rectifying and storing the gas after secondary filtering;

[0010] The gas regulating and delivery system (5) is composed of a pressure reducing valve (16), a flow regulating valve (17) and a non-return valve (18), wherein the pressure reducing valve (16) and the flow regulating valve (17) are connected via a gas pipeline and are sealed by a spherical cone surface; the flow regulating valve (17) and the non-return valve (18) are connected via a gas pipeline and are sealed by a spherical cone surface; the non-return valve (18) and the gas distribution device (6) are connected via a gas pipeline and are sealed by a spherical cone surface;

[0011] The gas distribution device (6) is composed of an air nozzle (7) and a distribution tank (8); the air nozzle (7) is threadedly mounted on the shell wall of the outer arc surface of the distribution tank (8), sealed with an O-ring, and then inserted into the inner side of the head of the aircraft hood (1) together with the distribution tank (8), and the outer side of the distribution tank (8) is closely attached to the inner wall of the aircraft hood (1); after the low-temperature, clean gas with stable delivery pressure enters the distribution tank, it is discharged onto the outer surface of the aircraft hood (1) through the air nozzle (7), forming a uniform and stable low-temperature gas film;

[0012] The advantages of the present invention compared with the prior art are:

[0013] (1) It can be combined with passive heat protection or semi-active heat protection to form a more effective combined heat protection method. It not only has a long heat protection time, but also has a simple structure and occupies less space than active heat protection. It greatly simplifies the gas supply system and has a higher overall working reliability.

[0014] (2) Compared with other active cooling methods, the low-temperature combustion gas with less condensed phase has better airflow uniformity after filtering, rectification, voltage stabilization, flow regulation and distribution, and can form a uniform and stable low-temperature air film on the outer surface of the aircraft hood, effectively reducing the aerodynamic heating effect on the outer surface of the aircraft hood and greatly reducing the ablation of the aircraft hood material. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments;

[0016] Figure 1 This is a schematic diagram of the structure of the air film heat insulation and cooling device;

[0017] Figure 2 It is a partial enlarged view of the air nozzle and the air film insulation hole;

[0018] Figure 3 It is a schematic diagram of the structure of a solid fuel gas generator;

[0019] Figure 4 This is a schematic diagram of the gas filtration and rectification tank structure;

[0020] Figure 5 It is a schematic diagram of the structure of the gas regulation and delivery system;

[0021] The list of numbers in the figure is: 1. Aircraft head cover, 2. Generator fixing bracket, 3. Solid gas generator, 4. Gas filter and rectifier tank, 5. Air flow regulation and delivery system, 6. Gas distribution device, 7. Jet nozzle, 8. Distribution tank, 9. Generator shell, 10. Cryogenic solid propellant, 11. Ignition device, 12. Primary filter, 13. Nozzle, 14. Filter, 15. Rectifier tank, 16. Pressure reducing valve, 17. Flow regulating valve, 18. Check valve. DETAILED DESCRIPTION

[0022] The structure of the air film heat insulation and cooling device proposed by the present invention is as follows Figure 1 As shown, the invention mainly comprises an aircraft head cover (1), a generator fixing bracket (2), a solid gas generator (3), a gas filter and rectifying tank (4), a gas regulating and conveying system (5) and a gas distribution device (6); wherein the generator fixing bracket (2) is fastened to the inner walls of the upper and lower sides of the aircraft head cover (1) by screws, and the solid gas generator (3) is fastened to the right side of the middle of the generator fixing bracket (2) by bolts; the gas filter and rectifying tank (4) is in a conical shape as a whole, and has a blunt head, and is located on the right side of the solid gas generator (3), and is connected to the solid gas generator (3) by a flange. 3) connected and sealed with an O-ring; the gas regulating and conveying system (5) is located outside the solid fuel gas generator (3) and on the left side of the gas filter and rectifying tank (4), and is connected to the gas filter and rectifying tank (4) by a pipe joint and a spherical cone surface seal; the gas distribution device (6) is conical inside and outside, and has a blunt head, and is located on the inside of the aircraft head cover (1), and is connected to the gas regulating and conveying system (5) by a pipe joint and a spherical cone surface seal; a boss is provided on the inner wall of the left end of the gas distribution device (6), and is fastened to the lug on the left edge of the gas filter and rectifying tank (4) by screws;

[0023] The solid fuel gas generator (3) is composed of a generator housing (9), a cryogenic solid propellant (10), an ignition device (11), a primary filter (12) and a nozzle (13); the cryogenic solid propellant (10) is loaded in the generator housing (9); the ignition device (11) is bonded to the right end combustion surface of the cryogenic solid propellant (10), and ignites the cryogenic solid propellant (10) when receiving an ignition command; the primary filter (12) is a metal mesh structure, and is limited by a step between the right end inner side of the generator housing (9) and the left end inner side of the nozzle (13) to perform primary filtering of the fuel gas; the nozzle (13) is in a "cone-column" shape, and its throat liner inner profile adopts a Laval nozzle structure, and is threadedly connected to the right end of the generator housing (9) and sealed with an O-ring, so that the internal pressure of the generator is stable, thereby ensuring stable combustion of the cryogenic solid propellant (10);

[0024] The gas filter and rectifying storage tank (4) is composed of a filter screen (14) and a rectifying storage tank (15); the filter screen (14) is a metal mesh structure, the mesh openings of which are smaller than the mesh openings of the primary filter screen (12), and is fastened to the inner wall of the middle part of the left end of the rectifying storage tank (15) by screws to perform secondary filtering on the gas; the rectifying storage tank (15) is generally conical in shape, and the head is blunt in shape, and rectifying and storing the gas after secondary filtering;

[0025] The gas regulating and delivery system (5) is composed of a pressure reducing valve (16), a flow regulating valve (17) and a non-return valve (18), wherein the pressure reducing valve (16) and the flow regulating valve (17) are connected via a gas pipeline and are sealed by a spherical cone surface; the flow regulating valve (17) and the non-return valve (18) are connected via a gas pipeline and are sealed by a spherical cone surface; the non-return valve (18) and the gas distribution device (6) are connected via a gas pipeline and are sealed by a spherical cone surface;

[0026] The gas distribution device (6) is composed of an air nozzle (7) and a distribution tank (8); the air nozzle (7) is threadedly mounted on the shell wall of the outer arc surface of the distribution tank (8), sealed with an O-ring, and then inserted into the inner side of the head of the aircraft hood (1) together with the distribution tank (8), and the outer side of the distribution tank (8) is closely attached to the inner wall of the aircraft hood (1); after the low-temperature, clean gas with stable delivery pressure enters the distribution tank, it is discharged onto the outer surface of the aircraft hood (1) through the air nozzle (7), forming a uniform and stable low-temperature gas film;

[0027] When the air film heat insulation and cooling device of the present invention is in operation, the low-temperature solid propellant (10) is first ignited by the ignition device (11) of the solid gas generator (3), and low-temperature gas with few condensed phase particles is continuously generated. The gas passes through the primary filter (12) to filter out the main residues in the gas. Afterwards, the gas enters the gas filtering and rectifying tank (4) through the nozzle (13), is further filtered through the filter (14), and is integrated in the rectifying tank (15) to stabilize the flow state. Finally, the gas is reduced by the pressure reducing valve (16). The pressure and flow regulating valve (17) adjusts the flow rate and then enters the gas distribution device (6). At the same time, the one-way valve (18) prevents the gas from flowing back, thereby obtaining low-temperature, clean gas with stable delivery pressure. The gas distribution device (6) evenly distributes the gas in each gas nozzle (7). After the gas is ejected from the air film insulation hole, a uniform and stable low-temperature air film is formed on the outer surface of the aircraft hood, thereby hindering the heat transfer of aerodynamic heat to the interior of the aircraft, effectively reducing the aerodynamic heating effect on the outer surface of the aircraft hood, and greatly reducing the ablation of the aircraft hood material.

[0028] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

Claims

1. A gas film insulation and cooling device for a gas source of a solid fuel gas generator, characterized in that: The invention comprises an aircraft head cover (1), a generator fixing bracket (2), a solid gas generator (3), a gas filter and rectifying tank (4), a gas regulating and conveying system (5) and a gas distribution device (6); wherein the generator fixing bracket (2) is fastened to the inner walls of the upper and lower sides of the aircraft head cover (1) by screws, and the solid gas generator (3) is fastened to the right side of the middle of the generator fixing bracket (2) by bolts; the gas filter and rectifying tank (4) is in a conical shape as a whole, with a blunt head, and is located on the right side of the solid gas generator (3), and is connected to the solid gas generator (3) by a flange and an O-shaped The gas regulating and conveying system (5) is located on the outside of the solid fuel gas generator (3) and on the left side of the fuel gas filter and rectifying tank (4). The gas regulating and conveying system (5) and the fuel gas filter and rectifying tank (4) are connected by a pipe joint and sealed by a spherical cone surface. The gas distribution device (6) is conical inside and outside and has a blunt head. It is located on the inside of the aircraft head cover (1) and is connected to the gas regulating and conveying system (5) by a pipe joint and sealed by a spherical cone surface. A boss is provided on the inner wall of the left end of the gas distribution device (6), and is fastened to the lug on the left edge of the fuel gas filter and rectifying tank (4) by screws. The gas filtering and rectifying storage tank (4) is composed of a filter screen (14) and a rectifying storage tank (15); the filter screen (14) is a metal mesh structure and is fastened to the inner wall of the middle part of the left end of the rectifying storage tank (15) by screws; the rectifying storage tank (15) is in a cone shape as a whole and has a blunt head shape, and rectify and store the gas after secondary filtration.

2. The gas film insulation and cooling device for the gas source of the solid fuel gas generator according to claim 1 is characterized in that: The solid fuel gas generator (3) is composed of a generator housing (9), a cryogenic solid propellant (10), an ignition device (11), a primary filter (12) and a nozzle (13); the cryogenic solid propellant (10) is loaded in the generator housing (9); the ignition device (11) is bonded to the right end combustion surface of the cryogenic solid propellant (10); the primary filter (12) is a metal mesh structure, and is limited by a step between the right end inner side of the generator housing (9) and the left end inner side of the nozzle (13); the nozzle (13) is in a "cone-column" shape, and its throat lining inner profile adopts a Laval nozzle structure, and is connected to the right end of the generator housing (9) by a threaded connection and an O-ring seal.

3. The gas film insulation and cooling device for the gas source of the solid fuel gas generator according to claim 1 is characterized in that: The gas regulating and delivery system (5) is composed of a pressure reducing valve (16), a flow regulating valve (17) and a one-way valve (18), wherein the pressure reducing valve (16) and the flow regulating valve (17) are connected via a gas pipeline and are sealed by a spherical cone surface; the flow regulating valve (17) and the one-way valve (18) are connected via a gas pipeline and are sealed by a spherical cone surface; the one-way valve (18) and the gas distribution device (6) are connected via a gas pipeline and are sealed by a spherical cone surface.

4. The gas film insulation and cooling device for the gas source of a solid fuel gas generator according to claim 1 is characterized in that: The gas distribution device (6) is composed of an air nozzle (7) and a distribution tank (8); the air nozzle (7) is threadedly mounted on the shell wall of the outer arc surface of the distribution tank (8), sealed with an O-ring, and then inserted into the inner side of the head of the aircraft hood (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 hood (1).

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