CN109606746B - Gas cylinder heat protection structure and gas cylinder to big plume influence of appearance accuse engine - Google Patents
Gas cylinder heat protection structure and gas cylinder to big plume influence of appearance accuse engine Download PDFInfo
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- CN109606746B CN109606746B CN201811378259.4A CN201811378259A CN109606746B CN 109606746 B CN109606746 B CN 109606746B CN 201811378259 A CN201811378259 A CN 201811378259A CN 109606746 B CN109606746 B CN 109606746B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C13/00—Details of vessels or of the filling or discharging of vessels
- F17C13/001—Thermal insulation specially adapted for cryogenic vessels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/01—Shape
- F17C2201/0104—Shape cylindrical
- F17C2201/0109—Shape cylindrical with exteriorly curved end-piece
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/03—Orientation
- F17C2201/035—Orientation with substantially horizontal main axis
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/05—Size
- F17C2201/056—Small (<1 m3)
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2203/00—Vessel construction, in particular walls or details thereof
- F17C2203/03—Thermal insulations
- F17C2203/0304—Thermal insulations by solid means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2221/00—Handled fluid, in particular type of fluid
- F17C2221/03—Mixtures
- F17C2221/031—Air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
- F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
- F17C2223/0107—Single phase
- F17C2223/0123—Single phase gaseous, e.g. CNG, GNC
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2270/00—Applications
- F17C2270/01—Applications for fluid transport or storage
- F17C2270/0186—Applications for fluid transport or storage in the air or in space
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Abstract
The invention relates to a hot protective structure of a gas cylinder and the gas cylinder aiming at the large plume influence of a posture control engine, wherein the hot protective structure comprises a flexible heat-proof layer and a plurality of layers of heat-insulating assemblies, the plurality of layers of heat-insulating assemblies are coated on the surface of a cylindrical section of the gas cylinder, the flexible heat-proof layer is coated on the surfaces of hemispheres at two ends of the gas cylinder, and the surfaces of the plurality of layers of heat-insulating assemblies in the cylindrical section of the gas cylinder; the multilayer heat insulation assembly comprises n reflecting layers, n-1 isolating layers and 1 outer coating layer, wherein the n reflecting layers and the n-1 isolating layers are alternately arranged, the innermost layer and the outermost layer are both reflecting layers, the reflecting layer of the innermost layer is in contact with the outer surface of the cylindrical section of the gas cylinder, the outermost reflecting layer is in contact with the outer coating layer, the outer coating layer is in contact with the flexible heat-proof layer, n is a positive integer, and the following relational expression is satisfied: n ═ k ρnλmli/hmli(ii) a The thermal protection structure of the invention not only ensures that the gas cylinder meets the temperature control requirement, but also ensures the design quality of the heat-proof material, effectively reduces the weight and saves the product cost.
Description
Technical Field
The invention relates to a design method for thermal protection of a gas cylinder of a spacecraft, in particular to a gas cylinder thermal protection structure and a gas cylinder aiming at large plume influence of an attitude control engine, and belongs to the technical field of thermal protection of aircrafts.
Background
The traditional carrier rocket thermal protection design method adopts a low thermal diffusivity heat protection material (such as glass fiber reinforced plastics), and ensures that the protected object does not exceed the required upper temperature limit within a specified time range by reducing the propagation speed of high temperature to the protected object. The design method of thermal protection of spacecrafts such as satellites and the like adopts a high-temperature resistant multi-layer heat insulation assembly formed by alternately combining a low-emissivity reflecting layer and a low-thermal-conductivity spacing layer, and utilizes the layer-by-layer reflection of a screen surface to form high thermal resistance to radiation heat flow so as to reduce the heat flow reaching a protected object and enable the temperature to meet the requirement.
As an upper-stage auxiliary power system, the attitude control engine system mainly completes attitude control, propellant bottom sinking and final speed correction of the whole flight stage of the upper stage, and has the characteristics of long working time and multiple starting times compared with the traditional carrier rocket and a general satellite attitude control engine system. The position of a certain type of upper-level gas cylinder is close to an attitude control engine, and the thermal environment of the gas cylinder is very severe due to plume convective heat transfer and radiation heating of the upper-level gas cylinder during the working period of the attitude control engine; meanwhile, during the period that the attitude control engine does not work, the gas cylinder is also influenced by the cold and black environment of the space. The safety of the gas cylinder can be influenced by overhigh temperature of the gas cylinder, the supercharging capacity of the gas cylinder is influenced by overlow temperature of the gas cylinder, and the existing carrier rocket and satellite thermal protection technology generally only meets one thermal protection requirement. In order to prevent the normal work of the gas cylinder from being influenced by overhigh or overlow temperature, a gas cylinder thermal protection design method aiming at the influence of the big plume of the upper-level attitude control engine must be developed to guide the thermal design of a thermal protection structure.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a gas cylinder thermal protection structure aiming at large plume influence of an attitude control engine, fills the gap in the prior art, is suitable for the large plume influence of the upper-level attitude control engine, is also suitable for gas cylinder thermal protection of long-time on-orbit cold and black space environment influence, and ensures that the temperature of a gas cylinder meets the temperature control requirement.
Another object of the invention is to provide a gas cylinder adopting the gas cylinder thermal protection structure.
The above purpose of the invention is mainly realized by the following technical scheme:
a gas cylinder thermal protection structure aiming at large plume influence of a posture control engine comprises a flexible heat-proof layer and a plurality of layers of heat-proof components, wherein the plurality of layers of heat-proof components are coated on the surface of a cylindrical section of a gas cylinder; the multilayer heat insulation assembly comprises n reflecting layers, n-1 isolating layers and 1 outer coating layer, wherein the n reflecting layers and the n-1 isolating layers are alternately arranged, the innermost layer and the outermost layer are both reflecting layers, the reflecting layer of the innermost layer is in contact with the outer surface of the cylindrical section of the gas cylinder, the outermost reflecting layer is in contact with the outer coating layer, the outer coating layer is in contact with the flexible heat-proof layer, n is a positive integer, and the following relational expression is satisfied:
n＝kρnλmli/hmli
wherein: h ismliIs equivalent heat transfer coefficient, lambda, of the multilayer heat insulation assemblymliEquivalent thermal conductivity, rho, for a multilayer insulation assemblynK is a correction factor for the layer density of the multi-layer insulation assembly.
In the gas cylinder thermal protection structure aiming at large plume influence of the attitude control engine, the equivalent heat exchange coefficient h of the multilayer heat insulation assemblymliDetermined by the following formula:
wherein: t isHIs the hot side temperature, T, of the multi-layer insulation assemblyCCold side temperature of multilayer insulation Assembly, AmliSurface area of the multi-layer insulation assembly, QmliIs the flow of heat through the multi-layer insulation assembly.
And the temperature T of the cold surface of the multilayer heat insulation assemblyCThe following conditions are satisfied:
wherein:
express get
And TpMinimum value of (d); c is the heat capacity of the gas cylinder assembly, ApIs the heated area of the gas cylinder assembly, hpIs the equivalent heat transfer coefficient of the gas cylinder assembly, T is the heating time, delta T is the maximum temperature rise limit of the gas cylinder assembly, T0Is the initial temperature, T, of the gas cylinder assemblypIs the temperature requirement of the gas cylinder assembly.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the value of the correction coefficient k is 1.2-1.6.
In the gas cylinder heat protection structure aiming at the large plume influence of the attitude control engine, the thickness of the flexible heat protection layer coated on the surface of the cylindrical section of the gas cylinder is 8-10mm, and the thickness of the flexible heat protection layer coated on the surfaces of hemispheres at two ends of the gas cylinder is 3-5 mm.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the flexible thermal protection layer is a combined structure of quartz glass fiber cotton and quartz glass fiber cloth, and the quartz glass fiber cotton is clamped and sewn by the quartz glass fiber cloth on the inner surface and the outer surface.
In the above thermal protection structure for the gas cylinder against the large plume of the attitude control engine, the flexible thermal protection layer coated on the surface of the cylindrical section of the gas cylinder is partially coated, and the flexible thermal protection layer is coated on the surface of the cylindrical section of the gas cylinder in the area affected by the large plume of the attitude control engine.
In the gas cylinder thermal protection structure for large plume influence of the attitude control engine, part of the surface of the cylindrical section of the gas cylinder coated with the flexible heat-proof layer is a semi-cylindrical surface.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the thickness of the reflecting layer is 20-30 μm, the thickness of the isolating layer is 30-50 μm, and the thickness of the outer cladding layer is 20-30 μm.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the reflecting layer is a double-sided aluminum-plated polyimide film, the isolating layer is glass fiber cloth, and the outer cladding layer is a single-sided aluminum-plated polyimide film secondary surface mirror.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the multilayer thermal insulation assembly is a medium-temperature multilayer thermal insulation assembly, and the tolerance temperature is not more than 400 ℃.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the multilayer heat insulation assembly is coated on the outer surface of the cylindrical section of the gas cylinder and is fixed by adopting the nylon fastener tape in a lap joint manner; the flexible heat-proof layers coated on the surfaces of hemispheres at the two ends of the gas cylinder and the flexible heat-proof layer coated on the cylindrical section of the gas cylinder are sewn into a whole, and the gas cylinder is bound and fixed by quartz glass fiber belts respectively sewn on the two sides of the flexible heat-proof layer coated on the cylindrical section of the gas cylinder, so that the gas cylinder is completely coated by a semi-cylindrical surface influenced by a large plume of a posture control engine towards the space.
In the gas cylinder thermal protection structure aiming at the large plume influence of the attitude control engine, the thermal conductivity coefficient of the flexible heat-proof layer is not more than 0.04W/m.K; the multilayer insulation assembly has an equivalent thermal conductivity of no greater than 10-4W/m·K。
The utility model provides a gas cylinder to big plume influence of appearance accuse engine, adopts above-mentioned gas cylinder heat protection structure to carry out the thermal protection.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention develops the thermal protection design of the gas cylinder aiming at the influence of the large plume of the attitude control engine, adopts a combined heat-proof structure of a flexible heat-proof layer and a medium-temperature multilayer heat-insulating assembly through a thermal design method of sectional design and integrated installation, ensures that the gas cylinder meets the temperature control requirement, ensures the design quality of heat-proof materials, effectively reduces the weight and saves the product cost.
(2) The invention combines the theory research into a wholeThe quantity test gives out the determination method of the unit number of the reflecting layer and the isolating layer in the multilayer heat insulation assembly, and also gives out the cold surface temperature T of the multilayer heat insulation assemblyCThe value requirement ensures that the thermal design performance of the medium-temperature multilayer heat insulation assembly reaches the optimum.
(3) The invention provides the material selection and the thickness value of the reflecting layer, the isolating layer, the outer coating layer and the flexible heat-proof layer of the multilayer heat-insulating assembly through reasonable design, further improves the heat-proof performance of the heat-proof structure and achieves the aim of reducing weight.
(4) The flexible heat-proof layer is subjected to segmented design, integral sewing and integrated installation, so that the flexible heat-proof layer is convenient to install on the basis of reducing weight and cost, and has strong operability.
Drawings
FIG. 1 is a schematic view of the thermal protection structure of the gas cylinder of the present invention;
1-a cylindrical section flexible heat-proof layer, 2-an upper hemispherical section flexible heat-proof layer, 3-a lower hemispherical section flexible heat-proof layer and 4-a multilayer heat insulation assembly;
FIG. 2 is a schematic view of a multi-layer insulation assembly of the present invention;
FIG. 3 is a profile view of a flexible thermal barrier of the present invention; fig. 3a is a cylindrical segment flexible heat protection layer, fig. 3b is an upper hemispherical segment flexible heat protection layer, and fig. 3c is a lower hemispherical segment flexible heat protection layer;
FIG. 4 is a thermal design model of the gas cylinder of the present invention;
FIG. 5 is a flow chart of the flexible thermal barrier design of the present invention;
FIG. 6 is a flow chart of a multi-layer insulation assembly design of the present invention.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
as shown in fig. 1, which is a schematic view of the thermal protection structure of the gas cylinder of the present invention, it can be seen that the thermal protection structure of the gas cylinder of the present invention includes a flexible thermal protection layer and a plurality of layers of thermal insulation components, wherein the plurality of layers of thermal insulation components are coated on the surface of the cylindrical section of the gas cylinder, the flexible thermal protection layer is coated on the surfaces of the hemispheres at both ends of the gas cylinder, and the surfaces of the plurality of layers of thermal insulation components in the cylindrical. As shown in fig. 1, the heat insulating layer comprises a cylindrical section 1, an upper hemispherical section 2, a lower hemispherical section 3 and a multi-layer heat insulating assembly 4.
The multilayer heat insulation assembly comprises n reflecting layers, n-1 isolating layers and 1 outer coating layer, wherein the n reflecting layers and the n-1 isolating layers are alternately arranged, the innermost layer and the outermost layer are both reflecting layers, the reflecting layer of the innermost layer is in contact with the outer surface of the cylindrical section of the gas cylinder, the outermost reflecting layer is in contact with the outer coating layer, the outer coating layer is in contact with the flexible heat-proof layer, n is a positive integer, and the following relational expression is satisfied:
n＝kρnλmli/hmli
wherein: h ismliIs equivalent heat transfer coefficient, lambda, of the multilayer heat insulation assemblymliEquivalent thermal conductivity, rho, for a multilayer insulation assemblynK is a correction factor for the layer density of the multi-layer insulation assembly.
Equivalent heat transfer coefficient h of multilayer heat insulation assemblymliDetermined by the following formula:
wherein: t isHIs the hot side temperature, T, of the multi-layer insulation assemblyCCold side temperature of multilayer insulation Assembly, AmliSurface area of the multi-layer insulation assembly, QmliIs the flow of heat through the multi-layer insulation assembly.
And the temperature T of the cold surface of the multilayer heat insulation assemblyCThe following conditions are satisfied:
wherein:
express get
And TpMinimum value of (d); c is the heat capacity of the gas cylinder assembly (gas cylinder, pipeline), ApIs a gas cylinder groupArea of heated part, hpIs the equivalent heat transfer coefficient of the gas cylinder assembly, T is the heating time, delta T is the maximum temperature rise limit of the gas cylinder assembly, T0Is the initial temperature, T, of the gas cylinder assemblypIs the temperature requirement of the gas cylinder assembly.
Specifically, the value of the correction coefficient k in the embodiment of the present invention is 1.2 to 1.6.
FIG. 3 is a schematic view of the flexible thermal barrier layer of the present invention; fig. 3a is a cylindrical segment flexible heat protection layer, fig. 3b is an upper hemispherical segment flexible heat protection layer, and fig. 3c is a lower hemispherical segment flexible heat protection layer; the thickness of the flexible heat-proof layer coated on the surface of the cylindrical section of the gas cylinder is 8-10mm, and the thickness of the flexible heat-proof layer coated on the surfaces of hemispheres at two ends of the gas cylinder is 3-5 mm. The flexible heat-proof layer is a combined structure of quartz fiber cotton and quartz fiber cloth, and is obtained by sewing the quartz fiber cotton clamped between the quartz fiber cloth on the inner surface and the quartz fiber cloth on the outer surface.
The flexible heat-proof layer coated on the surface of the cylindrical section of the gas cylinder is partially coated, and the flexible heat-proof layer is coated on the surface of the cylindrical section of the gas cylinder, which is influenced by the large plume of the attitude control engine. Specifically, in the embodiment of the invention, part of the surface of the cylindrical section of the gas cylinder coated with the flexible heat-proof layer is a semi-cylindrical surface, the flexible heat-proof layer coated on the surfaces of hemispheres at two ends of the gas cylinder and the flexible heat-proof layer coated on the cylindrical section of the gas cylinder are sewn into a whole, and the cylindrical surface of the gas cylinder, which is influenced by large plume of the attitude control engine and faces the space, is completely coated by binding and fixing quartz glass fiber belts respectively sewn on two sides of the flexible heat-proof layer coated on the cylindrical section of the gas cylinder.
As shown in figure 2, the appearance of the multilayer heat insulation assembly is shown, the multilayer heat insulation assembly is covered on the outer surface of the cylindrical section of the gas cylinder, and the multilayer heat insulation assembly is fixed in an overlapping mode through the nylon fastener tape. The multilayer heat insulation assembly is a medium-temperature multilayer heat insulation assembly and can resist the temperature of not more than 400 ℃. Wherein the thickness of the reflecting layer is 20-30 μm, the thickness of the isolating layer is 30-50 μm, and the thickness of the outer cladding layer is 20-30 μm. Specifically, in the embodiment of the invention, the reflecting layer is a double-sided aluminum plated polyimide film, the isolating layer is glass fiber cloth, and the outer cladding layer is a single-sided aluminum plated polyimide film secondary surface mirror.
Heat conduction of flexible heat-proof layer in the inventionThe coefficient is not more than 0.04W/(m.K); the multilayer insulation assembly has an equivalent thermal conductivity of no greater than 10-4W/(m·K)。
The invention provides a gas cylinder thermal protection structure aiming at the influence of a large plume of an upper-level attitude control engine, which is mainly based on the premise of meeting the requirements of thermal protection of the attitude control plume and a space cold and black background at the same time, carries out the overall thermal design of the thermal protection structure, and determines the appearance, the installation mode, the equivalent heat exchange coefficient requirement of a thermal insulation material and the surface radiation property of the thermal protection structure; and (3) carrying out thermal design on the heat insulation material, and determining the specific composition, the thermal parameter requirement and the temperature resistance requirement of the heat insulation material.
1. Thermal protection structure overall thermal design
The method comprehensively considers the thermal protection requirement of the plume of the gas cylinder attitude control and overcomes the thermal insulation requirement of the cold and black environment in space, analyzes and calculates the thermal protection effect of different thermal protection structure shapes, and determines that the gas cylinder adopts the thermal protection structure scheme of 'sectional design and integrated installation' of a cylindrical section and hemispheres at two ends (see figure 1).
(1) Cylinder section thermal design of gas cylinder
The cylinder section of the gas cylinder is coated with a middle-temperature multilayer, then the cylinder surface facing the space and affected by the plume of the attitude control engine is coated with the flexible heat-proof layer, the back temperature (back temperature for short) is reduced to a middle-temperature multilayer temperature-resistant range by utilizing a flexible heat-proof material formed by quartz glass fiber cotton and quartz glass fiber cloth with certain thickness, and then the good heat-insulating performance of the middle-temperature multilayer is utilized to control the temperature of the gas cylinder to meet the requirements. The heat conductivity coefficient of the flexible heat-proof material is not more than 0.04W/(m.K), and the surface has the radiation properties of low absorption and high emission; the multilayer insulation assembly has an equivalent thermal conductivity of not greater than 10-4W/(m.K), the outer cladding layer adopts a single-sided aluminized polyimide film secondary surface mirror with low absorption/emission ratio, and the temperature of the cylinder section of the gas cylinder can meet the temperature control requirement. One side of the multilayer heat insulation assembly, which faces the flexible heat-proof layer, is a hot side, and the other side of the multilayer heat insulation assembly is a cold side.
(2) Gas cylinder hemispherical section thermal design
The hemispheres at the two ends of the gas cylinder are subjected to small plume heat flow of the attitude control engine, and the hemispheres are only coated by a flexible heat-proof material with a certain thickness, so that the temperature of the hemispherical section of the gas cylinder is ensured not to exceed a high temperature limit.
(3) Integrally mounted
The middle-temperature multilayer heat insulation assembly is coated on the outer surface of the cylindrical section of the gas cylinder and is fixed in a lap joint mode by adopting a nylon hasp (as shown in figure 2); quartz glass fiber belts with certain width and length are respectively sewn on two sides of the cylindrical section flexible heat-proof material, the hemispherical section conical heat-proof materials at two ends and the cylindrical section heat-proof material are sewn into a whole, and the outer surface of the cylindrical section is bound and fixed through the quartz glass fiber belts (as shown in figure 3), so that the semi-cylindrical surface of the gas cylinder facing to the space is completely coated.
2. Thermal design of insulation material
The flexible heat-proof layer and the multilayer heat-insulation assembly are respectively designed by adopting a regression iteration design idea, the thickness, the thermophysical property and the optical property of the heat-insulation material are preset, a thermal analysis model (shown in figure 4) is established, parameter values are adjusted according to a calculation result, the design in a whole period is carried out according to the technical state determination of design-verification-redesign-redetermination until the design requirements are met, and verification and adjustment are carried out through a large number of tests.
3. Thermal design of flexible heat-proof material
According to the plume effect influence and the heat conductivity coefficient, the surface radiation property and the back temperature requirement determined by the overall thermal design, the thicknesses of the flexible heat-proof materials of the cylindrical section and the hemispherical section of the gas cylinder are determined through thermal analysis calculation, and verification and adjustment are performed through a large number of tests.
4. Multi-layer insulation assembly thermal design
According to the characteristics of a vacuum environment and equivalent heat exchange coefficients, cold and hot surface temperatures and surface radiation properties determined by overall thermal design, the unit number, thermal parameters and temperature resistance requirements of the multilayer heat insulation assembly are determined through thermal analysis calculation, and verification and adjustment are performed through a large number of tests. In an optional embodiment of the invention, the multilayer heat insulation assembly of the cylinder section of the gas cylinder adopts 5 units of medium-temperature multilayer heat insulation materials, the reflecting layer is a double-sided aluminum-plated polyimide film, the spacing layer is glass fiber cloth, the coating layer is a single-sided aluminum-plated polyimide film secondary surface mirror, and the solar absorption ratio is required to be not more than 0.44, and the infrared hemisphere emissivity is required to be not less than 0.64.
The specific design method of the flexible heat-proof layer and the specific design method of the multilayer heat-insulating assembly are given as follows:
thermal design of flexible heat-proof layer
The method comprises the following steps:
(1) controlling the plume heat flow Q of the engine according to the attitude of the gas cylinderFArea A of flexible heat-proof materialFCoefficient of thermal conductivity lambdaFAnd front surface temperature TETemperature of back surface TBIt is required to preliminarily determine the thickness L of the flexible heat shielding material.
(2) And calculating whether the temperature of each section of the gas cylinder meets the back temperature requirement by establishing a thermal model of the gas cylinder and the flexible heat-proof material and utilizing thermal analysis software, and if not, adjusting L and calculating (see figure 5). For example, Sinda fluid/ThermalDesktop software was used.
Thermal design of two-layer or multi-layer thermal insulation assembly
The method comprises the following steps:
(1) according to the back temperature T of the flexible heat-proof layerBDetermining the hot-face temperature T of the multi-layer insulation assemblyH. Because the back of flexible heat protection layer and multilayer thermal-insulated subassembly surface contact get during preliminary design:
TH＝TB(1)
(2) according to the initial temperature T of the gas cylinder component (gas cylinder, pipeline)0And maximum temperature rise limit Δ T and surface temperature requirement TpDetermining the design value T of the cold surface temperature of the multilayer heat insulation assemblyC。
C is the heat capacity of the gas cylinder assembly (gas cylinder, pipeline), ApIs the heated area of the gas cylinder assembly, hpIs the equivalent heat exchange coefficient of the gas cylinder component, t is the heating time,delta T is the maximum temperature rise limit of the gas cylinder assembly, T0Is the initial temperature, T, of the gas cylinder assemblypIs the temperature requirement of the gas cylinder assembly.
(3) selecting an outer coating layer according to the design value of the hot surface temperature of the multilayer heat insulation assembly, namely preliminarily setting the multilayer optical property (solar absorption ratio alpha)s,mliInfrared hemispherical emissivityH,mli)。
(4) According to the cold and hot surface temperatures and the area A of the multilayer heat insulation assemblymliDetermining the equivalent heat exchange coefficient h of the multi-layer heat-insulating materialmil。
Wherein Q ismliThis value is not easily determined at design time for heat flow through the multi-layer insulation assembly and is iterated with step 4).
(5) According to the equivalent heat exchange coefficient requirement and the equivalent heat conduction coefficient lambda of the medium-temperature multilayer heat insulation assemblymliLayer density ρnThe number of cells n is determined.
n＝kρnλmli/hmli(3)
Wherein: h ismliIs equivalent heat transfer coefficient, lambda, of the multilayer heat insulation assemblymliEquivalent thermal conductivity, rho, for a multilayer insulation assemblynK is a correction factor for the layer density of the multi-layer insulation assembly.
According to the invention, a value of the correction coefficient k is preferably 1.2-1.6 determined through a large number of tests, and the unit number n is corrected through the correction coefficient, so that the heat insulation and heat preservation performance of the multilayer heat insulation assembly is better.
(6) Calculating the heat transfer q through the multi-layer insulation assemblymli：
Wherein σ is Stefan-Boltzmann constant.
The number of units (the number of layers) n of the multilayer determines the thickness of the multilayer, the thickness of the multilayer can be changed by changing n, and if the calculated surface temperature of the gas cylinder is higher or lower, the temperature of the gas cylinder can be ensured to meet the requirement by reducing or increasing the number of units.
(7) Calculating whether the surface temperature of the cylindrical section of the gas cylinder meets the requirement by establishing a thermal model of the multilayer heat insulation assembly and utilizing thermal analysis software, and if not, adjusting alphas,mli、H,mli、λmliAnd (or n) are recalculated (see fig. 6) until the requirements are met. For example, Sinda fluid/Thermal Desktop software was used.
While the invention has been described with reference to specific preferred embodiments, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (13)
1. The utility model provides a hot protective structure of gas cylinder to big plume of appearance accuse engine influence which characterized in that: the flexible heat-proof layer is coated on the surfaces of hemispheres at two ends of the gas cylinder and the surfaces of the multiple layers of heat-insulating assemblies in the cylindrical section of the gas cylinder; the multilayer heat insulation assembly comprises n reflecting layers, n-1 isolating layers and 1 outer coating layer, wherein the n reflecting layers and the n-1 isolating layers are alternately arranged, the innermost layer and the outermost layer are both reflecting layers, the reflecting layer of the innermost layer is in contact with the outer surface of the cylindrical section of the gas cylinder, the outermost reflecting layer is in contact with the outer coating layer, the outer coating layer is in contact with the flexible heat-proof layer, n is a positive integer, and the following relational expression is satisfied:
n＝kρnλmli/hmli
wherein: h ismliIs equivalent heat transfer coefficient, lambda, of the multilayer heat insulation assemblymliEquivalent thermal conductivity, rho, for a multilayer insulation assemblynK is a correction factor for the layer density of the multi-layer insulation assembly.
2. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 1, characterized in that: equivalent heat transfer coefficient h of the multilayer heat insulation assemblymliDetermined by the following formula:
wherein: t isHIs the hot side temperature, T, of the multi-layer insulation assemblyCCold side temperature of multilayer insulation Assembly, AmliSurface area of the multi-layer insulation assembly, QmliIs the heat flow through the multi-layer insulation assembly;
and the temperature T of the cold surface of the multilayer heat insulation assemblyCThe following conditions are satisfied:
wherein:
express get
And TpMinimum value of (d); c is the heat capacity of the gas cylinder assembly, ApIs the heated area of the gas cylinder assembly, hpIs the equivalent heat transfer coefficient of the gas cylinder assembly, T is the heating time, delta T is the maximum temperature rise limit of the gas cylinder assembly, T0Is the initial temperature, T, of the gas cylinder assemblypIs the temperature requirement of the gas cylinder assembly.
3. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 1, characterized in that: the value of the correction coefficient k is 1.2-1.6.
4. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 1, characterized in that: the thickness of the flexible heat-proof layer coated on the surface of the cylindrical section of the gas cylinder is 8-10mm, and the thickness of the flexible heat-proof layer coated on the surfaces of hemispheres at two ends of the gas cylinder is 3-5 mm.
5. A gas cylinder thermal protection structure against large plume influence of an attitude control engine according to one of claims 1 to 4, characterized in that: the flexible heat-proof layer is a combined structure of quartz glass fiber cotton and quartz glass fiber cloth, and is obtained by clamping and sewing the quartz glass fiber cotton in the quartz glass fiber cloth on the inner surface and the outer surface.
6. A gas cylinder thermal protection structure against large plume influence of an attitude control engine according to one of claims 1 to 4, characterized in that: the flexible heat-proof layer coated on the surface of the cylindrical section of the gas cylinder is partially coated, and the flexible heat-proof layer is coated in the area of the surface of the cylindrical section of the gas cylinder, which is affected by the large plume of the attitude control engine.
7. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 6, characterized in that: and part of the surface of the cylindrical section of the gas cylinder coated with the flexible heat-proof layer is a semi-cylindrical surface.
8. A gas cylinder thermal protection structure against large plume influence of an attitude control engine according to one of claims 1 to 4, characterized in that: the thickness of the reflecting layer is 20-30 μm, the thickness of the isolating layer is 30-50 μm, and the thickness of the outer cladding layer is 20-30 μm.
9. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 8, characterized in that: the reflecting layer is a double-sided aluminum plated polyimide film, the isolating layer is glass fiber cloth, and the outer cladding layer is a single-sided aluminum plated polyimide film secondary surface mirror.
10. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 1, characterized in that: the multilayer heat insulation assembly is a medium-temperature multilayer heat insulation assembly, and the tolerance temperature of the multilayer heat insulation assembly is not more than 400 ℃.
11. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 1, characterized in that: the multilayer heat insulation assembly is coated on the outer surface of the cylindrical section of the gas cylinder and is fixed in an overlapping manner by adopting a nylon hasp; the flexible heat-proof layers coated on the surfaces of hemispheres at the two ends of the gas cylinder and the flexible heat-proof layer coated on the cylindrical section of the gas cylinder are sewn into a whole, and the gas cylinder is bound and fixed by quartz glass fiber belts respectively sewn on the two sides of the flexible heat-proof layer coated on the cylindrical section of the gas cylinder, so that the gas cylinder is completely coated by a semi-cylindrical surface influenced by a large plume of a posture control engine towards the space.
12. The gas cylinder thermal protection structure for attitude control engine large plume influence of claim 1, characterized in that: the heat conductivity coefficient of the flexible heat-proof layer is not more than 0.04W/m.K; the multilayer insulation assembly has an equivalent thermal conductivity of no greater than 10-4W/m·K。
13. The utility model provides a gas cylinder to big plume influence of appearance accuse engine which characterized in that: use of a cylinder thermal protection structure according to any one of claims 1 to 12.
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| CN110990965B (en) * | 2019-11-07 | 2023-03-07 | 西安空间无线电技术研究所 | Easy-shape-following space thermal protection assembly and protection method |
| CN113148239A (en) * | 2021-02-25 | 2021-07-23 | 北京空间飞行器总体设计部 | Spacecraft plume guiding device suitable for take-off of extraterrestrial celestial body |
| CN113071718B (en) * | 2021-02-26 | 2023-06-02 | 北京空间飞行器总体设计部 | Lunar surface take-off lifter heat protection device and heat insulation performance calculation method thereof |
| CN113255072B (en) * | 2021-04-25 | 2022-04-12 | 上海新力动力设备研究所 | Method for rapidly calculating heat transfer process of solid rocket engine cladding sleeve structure |
| CN114571649B (en) * | 2022-03-11 | 2024-03-08 | 北京玻钢院复合材料有限公司 | Method for rapidly pressing heat-proof product formed by integrally forming heat-proof layer with metal piece and large length-diameter ratio for aerospace vehicle and heat-proof product formed by integrally forming heat-proof layer with metal piece |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1154071A1 (en) * | 2000-05-12 | 2001-11-14 | Didier Royaerts | Thermal insulating material |
| CN103883871A (en) * | 2014-03-19 | 2014-06-25 | 湖北三江航天江北机械工程有限公司 | Lightened high-temperature and high-pressure composite cylinder and manufacturing method thereof |
| DE102013015888A1 (en) * | 2013-09-23 | 2015-03-26 | Audi Ag | Fuel tank of a motor vehicle and method for producing a fuel tank |
| CN105922674A (en) * | 2016-04-22 | 2016-09-07 | 北京航天动力研究所 | Lightweight composite structure heat insulation layer |
| CN106442612A (en) * | 2016-09-06 | 2017-02-22 | 哈尔滨工业大学 | Testing method of thermal insulation performance of vacuum high temperature thermal protection product |
| DE102016220993A1 (en) * | 2016-10-25 | 2018-04-26 | Bayerische Motoren Werke Aktiengesellschaft | A pressure vessel having an outlet for fuel accumulated between a liner and a fiber reinforced layer |
| WO2018149772A1 (en) * | 2017-02-14 | 2018-08-23 | University Of Ulster | Composite pressure vessel for hydrogen storage |
-
2018
- 2018-11-19 CN CN201811378259.4A patent/CN109606746B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1154071A1 (en) * | 2000-05-12 | 2001-11-14 | Didier Royaerts | Thermal insulating material |
| DE102013015888A1 (en) * | 2013-09-23 | 2015-03-26 | Audi Ag | Fuel tank of a motor vehicle and method for producing a fuel tank |
| CN103883871A (en) * | 2014-03-19 | 2014-06-25 | 湖北三江航天江北机械工程有限公司 | Lightened high-temperature and high-pressure composite cylinder and manufacturing method thereof |
| CN105922674A (en) * | 2016-04-22 | 2016-09-07 | 北京航天动力研究所 | Lightweight composite structure heat insulation layer |
| CN106442612A (en) * | 2016-09-06 | 2017-02-22 | 哈尔滨工业大学 | Testing method of thermal insulation performance of vacuum high temperature thermal protection product |
| DE102016220993A1 (en) * | 2016-10-25 | 2018-04-26 | Bayerische Motoren Werke Aktiengesellschaft | A pressure vessel having an outlet for fuel accumulated between a liner and a fiber reinforced layer |
| WO2018149772A1 (en) * | 2017-02-14 | 2018-08-23 | University Of Ulster | Composite pressure vessel for hydrogen storage |
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