CN115465476A - Squeeze isolation device for propellant management - Google Patents
Squeeze isolation device for propellant management Download PDFInfo
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- CN115465476A CN115465476A CN202210898665.3A CN202210898665A CN115465476A CN 115465476 A CN115465476 A CN 115465476A CN 202210898665 A CN202210898665 A CN 202210898665A CN 115465476 A CN115465476 A CN 115465476A
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- 239000003380 propellant Substances 0.000 title claims abstract description 74
- 238000002955 isolation Methods 0.000 title abstract description 7
- 229910052751 metal Inorganic materials 0.000 claims abstract description 103
- 239000002184 metal Substances 0.000 claims abstract description 103
- 239000007800 oxidant agent Substances 0.000 claims abstract description 25
- 239000000446 fuel Substances 0.000 claims abstract description 24
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 22
- 230000001590 oxidative effect Effects 0.000 claims abstract description 19
- 239000012212 insulator Substances 0.000 claims description 7
- 239000012528 membrane Substances 0.000 claims 6
- 238000009413 insulation Methods 0.000 claims 2
- 238000000605 extraction Methods 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 4
- 239000007788 liquid Substances 0.000 description 15
- 238000001125 extrusion Methods 0.000 description 8
- 239000000084 colloidal system Substances 0.000 description 4
- 230000007774 longterm Effects 0.000 description 4
- 229910052755 nonmetal Inorganic materials 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000010485 coping Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000035772 mutation Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Classifications
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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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
Abstract
The invention relates to the field of aircraft propellant storage and management, and provides a squeezing isolation device for managing propellant, which comprises a storage box shell, a first metal diaphragm and a second metal diaphragm, wherein the first metal diaphragm and the second metal diaphragm are arranged inside the storage box shell; the first metal diaphragm and one side wall of the storage box shell form a fuel agent storage cavity, the second metal diaphragm and the other side wall of the storage box shell form an oxidant storage cavity, an air storage cavity is formed between the first metal diaphragm and the second metal diaphragm, and the fuel agent storage cavity, the oxidant storage cavity and the air storage cavity are respectively connected with a first pipe orifice, a second pipe orifice and a third pipe orifice on the storage box shell; the invention breaks through the traditional metal diaphragm form, realizes the metal diaphragm type propellant management mode of cylindrical storage tanks with circular and non-circular (special-shaped) sections through the diaphragm corrugation design, and simultaneously realizes the common storage and management requirements of the binary propellant of a single cylindrical storage tank through a double-film structure.
Description
Technical Field
The invention relates to the field of aircraft propellant storage and management, in particular to an extrusion isolation device for propellant management, and particularly relates to a cylindrical metal diaphragm storage tank for liquid/colloid propellant management of a corrugated metal diaphragm.
Background
The metal diaphragm type storage tank is one of important propellant storage tank types, the metal diaphragm of the metal diaphragm type storage tank is tightly attached to the liquid level under the action of gas extrusion, the propellant is prevented from shaking, the metal diaphragm type storage tank has the advantages of large discharge flow, high discharge efficiency, capability of being in long-term contact with the propellant, high reliability, capability of reliably discharging under the lateral overload condition, strong working condition mutation adaptability and the like, and is widely applied to the fields of various spacecrafts such as bullets, arrows, stars, vessels and the like.
The existing metal diaphragm is limited in that the working principle of the existing metal diaphragm can only be spherical, ellipsoidal and quasi-spherical structures with finite cone column sections, and propellant management of a column-shaped storage tank cannot be realized. For the spacecraft, the cylindrical storage tank is beneficial to structural layout and improves space utilization rate, and is the best choice for the form of the storage tank. The current cylindrical propellant tanks mainly use non-metallic bladders or surface tension devices to manage the propellant. The non-metallic bag can not be in long-term contact with the propellant, and the surface tension device can not avoid the propellant from shaking. Meanwhile, with the development of spacecraft technology, the requirement for carrying more propellants becomes more obvious, and a cylindrical storage tank assembly with a reasonable special-shaped section (such as a fan-shaped section) can make full use of installation space compared with a large single storage tank with a traditional shape. In addition, aiming at the spacecraft adopting the binary propulsion, the storage and management of the binary propellant in a whole body are also effective ways for solving the problem of carrying amount of the propellant in the limited space of the spacecraft. It is therefore desirable to design a metal diaphragm to address the above-mentioned deficiencies of the prior art.
Patent document CN114044169A discloses a refillable tension type propellant tank and a method of manufacturing the same. The tank comprises a tank housing (1) for propellant storage, a management device (2) for propellant supply and replenishment and a protection device (3) for coping with liquid sloshing; the storage box shell (1) is formed by connecting a liquid end shell (11), a middle section shell (12) and an air end shell (13), and the management device (2) is formed by sequentially connecting a supplementary vent window (21), a bubble trap (22), a liquid end channel (23), a communicating seat (24), a communicating pipe (25), an air end channel (26) and a communicating ring (27); the protection device (3) is composed of a vent window anti-sloshing plate (31) and a channel anti-sloshing plate (32), but the design still cannot solve the problems of storage tanks with special-shaped cross sections and storage of binary propellant workpieces, and needs to be further improved. Patent document CN103407590B discloses a propellant storage tank for a spacecraft ground test, which includes a storage tank shell with an opening at one end, a liquid cavity cylinder arranged in the storage tank shell and used for storing propellant, a rotation-proof and shake-proof component, and a fixing component, wherein the opening of the storage tank shell is fixed at the upper end of the fixing component; the lower end of the fixed part penetrates through the storage box shell and is inserted into the liquid cavity cylinder, and an elastic element is transversely arranged at a gap between the fixed part and the liquid cavity cylinder; the lower end of the liquid cavity barrel body is directly fixed with the storage tank shell, the lower end of the liquid cavity barrel body is further provided with an anti-shaking and anti-rotating component, and the problem of double-propellant work body storage cannot be solved due to the design.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide a squeeze insulator for propellant management.
According to the invention, the extrusion isolation device for managing propellant comprises a tank shell, a first metal diaphragm and a second metal diaphragm, wherein the first metal diaphragm and the second metal diaphragm are arranged inside the tank shell;
the first metal diaphragm and one side wall of the storage box shell form a fuel agent storage cavity, the second metal diaphragm and the other side wall of the storage box shell form an oxidant storage cavity, an air storage cavity is formed between the first metal diaphragm and the second metal diaphragm, and the fuel agent storage cavity, the oxidant storage cavity and the air storage cavity are respectively connected with a first pipe orifice, a second pipe orifice and a third pipe orifice on the storage box shell;
the first metal diaphragm and the second metal diaphragm are both annular corrugated films, and can be attached to the inner wall of the storage box shell when the volume of the air storage cavity is maximum; and when the volume of the air storage cavity is minimum, the first metal diaphragm is attached to the second metal diaphragm.
Preferably, the gas is filled into or pumped out of the gas storage cavity through the third pipe orifice, so that the input or output of the fuel agent in the fuel agent storage cavity and the oxidant in the oxidant storage cavity can be realized.
Preferably, the first metal diaphragm and the second metal diaphragm have the same or different geometric structures.
Preferably, the first metal diaphragm and the second metal diaphragm each comprise an inner core corrugation, an annular edge corrugation and an inner side corrugation with multiple rings, wherein two sides of the inner core corrugation and the annular edge corrugation are respectively connected with the inner core corrugation and the annular edge corrugation in a seamless mode;
the inner core corrugations, the inner side corrugations and the annular edge corrugations are sequentially connected to form a corrugated film together, and the corrugated film and the inner wall of the storage box shell form a storage cavity for storing the propellant.
Preferably, the inner core corrugations comprise inner core straight corrugations and two inner core semicircular corrugations arranged at two ends of the inner core straight corrugations, and the cross sections of the inner core straight corrugations are provided with arc-shaped wave crests or wave troughs;
and two sides of the straight corrugation of the inner core are respectively provided with a half arc-shaped wave trough or a half arc-shaped wave crest.
Preferably, the annular edge corrugation is configured to have two edge straight corrugations and two edge semicircular corrugations arranged at two ends of the two edge straight corrugations so that the annular edge corrugation is annular, and the edge straight corrugations and the edge semicircular corrugations have the same cross-sectional shape, wherein the edge straight corrugations and the edge semicircular corrugations each have a circular arc-shaped peak, the outer side of the circular arc-shaped peak is connected with a circular arc-shaped inclined wave, and the inner side of the circular arc-shaped peak is sequentially connected with a straight-line inclined wave and a half circular arc-shaped trough.
Preferably, the rings in the inner corrugation are seamlessly connected in sequence in a radial outward direction and become larger gradually;
each ring in the inner side corrugations is provided with two inner side straight corrugations, two ends of each inner side straight corrugation are connected with two inner side semicircular corrugations, the inner side straight corrugations and the inner side semicircular corrugations have the same cross section shape, each inner side straight corrugation and each inner side semicircular corrugation are provided with an arc-shaped peak, and two sides of each arc-shaped peak are respectively connected with a straight line inclined wave and a half arc-shaped wave trough.
Preferably, the inner core straight corrugation and the annular edge corrugation have an edge straight corrugation and an inner side straight corrugation, respectively, having an inner side straight corrugation length equal to each other.
Preferably, the semicircular corrugation of the inner core has the same centroid as that of the semicircular corrugation of the edge and the semicircular corrugation of the inner side of the annular edge.
Preferably, the inner core corrugation, the annular edge corrugation and the inner side corrugation have corrugations with adjacent circular arc-shaped peaks and troughs with equal radius.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention breaks through the traditional metal diaphragm form of the propellant storage tank, realizes the metal diaphragm type propellant management mode of the conventional round section sphere-column shaped storage tank, and compared with the traditional sphere-like metal diaphragm, the corrugated metal diaphragm has the advantages of low deformation pressure difference, regular deformation, high storage tank discharge efficiency and good resistance to mechanical environment.
2. According to the invention, by designing the initial ripple form, size and number of the metal diaphragm, the final working profile of the non-circular (special-shaped) section can be realized, so that propellant management of the cylindrical storage tank with the special-shaped section is realized, and more special application scenes can be met.
3. The non-metal bag type cylindrical propellant storage tank effectively solves the problem that the existing non-metal bag type cylindrical propellant storage tank cannot be contacted with a propellant for a long time and the problem that the surface tension type cylindrical propellant storage tank propellant shakes through the use of a metal diaphragm management mode.
4. The invention adopts the storage tank with the non-circular section, which not only can realize the miniaturization of the whole storage tank, but also can be reasonably designed according to the internal space of the spacecraft, thereby solving the problems that the propellant storage tank has large space and is limited by the regular placement space.
5. The invention can realize the storage and management requirements of a plurality of propellants of a single cylindrical storage tank through two metal diaphragms in the extruding/isolating device, has strong practicability and is convenient to adjust.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural view of example 1 of the present invention;
FIG. 2 is a schematic structural view of the cross-section of FIG. 1;
fig. 3 is a schematic structural view of the first metal separator or the second metal separator in example 1;
FIG. 4 is a schematic structural view of the first metal diaphragm in example 1, in which the broken line shows the expanded structure of the first metal diaphragm after the air storage chamber is inflated;
FIG. 5 is a schematic structural view of the cross-section of FIG. 4;
FIG. 6 is a schematic structural view of embodiment 2 of the present invention;
FIG. 7 is a structural schematic diagram of the cross section of FIG. 6;
fig. 8 is a schematic structural view of the first metal separator or the second metal separator in embodiment 2;
FIG. 9 is a schematic structural view of a second metal diaphragm in example 2, in which the broken line shows the expanded structure of the second metal diaphragm after the air storage chamber is inflated;
FIG. 10 is a schematic view of the cross-section of FIG. 9;
FIG. 11 is a schematic view of the structure of the assembly of the non-circular (irregular) section prismatic metal diaphragm tank of example 2;
fig. 12 is a top view of fig. 11.
The figures show that:
Inner core semicircular corrugation 12
Edge semicircular corrugations 22
Inner straight corrugation 31
Inner semi-circular corrugation 32
Spherical cylindrical profile 4
Rhombus-column shaped surface 5
Fuel agent storage chamber 101
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will aid those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any manner. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1:
the invention aims to solve the problems that the conventional spherical cylindrical storage tank with a circular section in the prior art can not adopt a metal diaphragm to carry out propellant management, the propellant management of a cylindrical storage tank with a non-circular (special-shaped) section, the long-term storage of a non-metal bag type cylindrical storage tank propellant, the shaking of the surface tension type cylindrical storage tank propellant and the storage and management of multiple propellants in a single cylindrical storage tank, and provides an extrusion isolation device for managing the propellant, which is composed of a group of corrugated metal diaphragms. By designing the initial corrugation pattern, each geometric dimension and the number of the metal diaphragms, different final expansion profiles can be realized, and different storage tank forms can be further met.
Figure 1 illustrates a conventional round section, spherical cylindrical metal diaphragm tank that can achieve two propellant storage and management. The fuel tank comprises a tank shell 100, and a first metal diaphragm 200 and a second metal diaphragm 300 which are arranged inside the tank shell 100, wherein a fuel agent storage cavity 101 is formed by the first metal diaphragm 200 and one side wall of the tank shell 100, an oxidant storage cavity 102 is formed by the second metal diaphragm 300 and the other side wall of the tank shell 100, an air storage cavity 103 is formed between the first metal diaphragm 200 and the second metal diaphragm 300, the fuel agent storage cavity 101, the oxidant storage cavity 102 and the air storage cavity 103 are respectively connected with a first nozzle 104, a second nozzle 105 and a third nozzle 106 on the tank shell 100, wherein the first nozzle 104 is used as a passage for fuel agent entering and exiting from the fuel agent storage cavity 101, the second nozzle 105 is used as a passage for oxidant entering and exiting from the oxidant storage cavity 102, and the third nozzle 106 is used as a passage for gas entering and exiting from the air storage cavity 103.
It should be noted that the input or output of the fuel agent in the fuel agent storage chamber 101 and the oxidant in the oxidant storage chamber 102 can be realized by filling or extracting gas into or from the air storage chamber 103 through the third pipe orifice 106. Specifically, in use, the gas-holding chamber 103 can be charged through the third nozzle 106 as a motive force for fuel and oxidant output. The air can be pumped out of the air storage cavity 103 through the third pipe orifice 106 to be used as power for inputting fuel agent and oxidant; alternatively, when the propellant is replenished into the fuel agent storage chamber 101 and the oxidizer storage chamber 102, the gas in the gas storage chamber 103 can be discharged through the third nozzle 106, and the propellant is filled.
Further, as shown in fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, both the first metal diaphragm 200 and the second metal diaphragm 300 are annular corrugated films, the geometric structures of the first metal diaphragm 200 and the second metal diaphragm 300 are the same, and when the volume of the air storage cavity 103 is the largest, both the first metal diaphragm 200 and the second metal diaphragm 300 can be attached to the inner wall of the storage tank housing 100; when the volume of the gas storage chamber 103 is minimized, the first metal diaphragm 200 and the second metal diaphragm 300 are bonded together, and the interiors of the fuel agent storage chamber 101 and the oxidizer storage chamber 102 are filled with the propellant.
In this embodiment, as shown in fig. 3, 4, and 5, the first metal diaphragm 200 and the second metal diaphragm 300 are arranged in a central symmetry manner with respect to the center of the tank casing 100, each of the first metal diaphragm 200 and the second metal diaphragm 300 includes an inner core corrugation 1, an annular edge corrugation 2, and an inner side corrugation 3 having multiple rings and having two sides seamlessly connected to the inner core corrugation 1 and the annular edge corrugation 2, respectively, the inner core corrugation 1, the inner side corrugation 3, and the annular edge corrugation 2 are sequentially connected to form a complete corrugated diaphragm and form a storage cavity with the inner wall of the tank casing 100 to store propellant, so as to form a complete liquid/gel propellant management apparatus, and after the corrugated diaphragm is completely unfolded, the profile of the corrugated diaphragm is expanded and deformed from an initial corrugated profile to a spherical cylindrical profile 4 having a circular final cross-section, thereby realizing extrusion supply of the liquid/gel propellant in the tank casing 100 formed by the initial profile and the final profile of the diaphragm.
The inner core corrugation 1 comprises an inner core straight corrugation 11 and two inner core semicircular corrugations 12 arranged at two ends of the inner core straight corrugation 11, the cross section of the inner core straight corrugation 11 is provided with arc-shaped wave crests or wave troughs, and two sides of the inner core straight corrugation 11 are respectively provided with half arc-shaped wave troughs or wave crests.
The annular edge corrugation 2 is configured to have two edge straight corrugations 21 and two edge semicircular corrugations 22 arranged at two ends of the two edge straight corrugations 21 so that the annular edge corrugation 2 is in an annular shape, the edge straight corrugations 21 and the edge semicircular corrugations 22 have the same cross-sectional shape, wherein each of the edge straight corrugations 21 and the edge semicircular corrugations 22 has a circular arc-shaped peak, the outer side of the circular arc-shaped peak is connected with a circular arc-shaped inclined wave, and the inner side of the circular arc-shaped peak is sequentially connected with a straight-line inclined wave and a half circular arc-shaped trough.
The rings in the inner corrugations 3 are connected in a seamless manner and gradually become larger along the radial outward direction, each ring in the inner corrugations 3 is provided with two inner straight corrugations 31, two ends of each inner straight corrugation 31 are connected with two inner semi-circular corrugations 32, the inner straight corrugations 31 and the inner semi-circular corrugations 32 have the same cross section shape, each inner straight corrugation 31 and each inner semi-circular corrugation 32 are provided with an arc-shaped crest, and two sides of each arc-shaped crest are respectively connected with a straight inclined wave and a half arc-shaped trough.
In the embodiment, the length of the inner core straight corrugation 11 is equal to that of the edge straight corrugation 21 and that of the inner side straight corrugation 31, and the lengths are both 600mm; the inner core semicircular corrugation 12 has the same centroid as the edge semicircular corrugation 22 and the inner side semicircular corrugation 32. The corrugation shape and size of the annular edge corrugation 2 and the annular inner corrugation 3 are kept constant in their respective circumferential directions.
The inner core corrugation 1, the annular edge corrugation 2 and the inner side corrugation 3 have corrugations with equal radiuses of adjacent circular arc-shaped wave crests and wave troughs.
The corrugation inclination angle alpha and the corrugation height h of the annular edge corrugation 2 are larger than those of the annular inner corrugation 3, and the corrugation inclination angle alpha and the corrugation height h of the annular inner corrugation 3 finally forming the diaphragm of the spherical cylindrical profile 4 gradually increase from inside to outside.
In this embodiment, the inclination angle α of the annular edge corrugation 2 is 87 °, the corrugation height h =60mm, the inclination angle α of the annular inner corrugation 3 gradually increases from 30 ° to 85 ° from inside to outside, the corrugation height gradually increases from 10mm to 30mm, and the thickness of the diaphragm is 0.5mm.
In the embodiment, the corrugated diaphragm is made of pure aluminum 1050A, and the thickness of the diaphragm is 0.2 mm-1.5 mm.
When the storage tank works, as the pressure in the air storage cavity 103 rises, the first metal diaphragm 200 and the second metal diaphragm 300 are expanded and deformed from the initial corrugated profile to the spherical cylindrical profile 4 with a round final section and are jointed with the inner profile of the storage tank shell 100, so that the extrusion supply of the combustion agent and the oxidizing agent is realized.
Example 2:
this example is a modification of example 1.
In this embodiment, the geometric structures of the first metal diaphragm 200 and the second metal diaphragm 300 are different, and the propellant management function of the prismatic metal diaphragm tank with higher installation space adaptability is realized by the difference in the geometric dimensions of the first metal diaphragm 200 and the second metal diaphragm 300, as shown in fig. 11 and 12.
As shown in fig. 6, 7, 8, 9 and 10, after the corrugated diaphragm is completely unfolded, the profile of the corrugated diaphragm is expanded and deformed from the initial corrugated profile to the diamond-shaped profile 5 with a fan-shaped final section, the inclination angle α and height h of the ring-shaped inner corrugation 3 of the diaphragm finally forming the diamond-shaped profile 5 are kept constant from inside to outside,
specifically, the annular edge corrugation 2 of the first metal diaphragm 200 has a corrugation inclination angle α of 87 °, and a corrugation height h =60mm;
specifically, the annular edge corrugation 2 of the second metal diaphragm 300 has a corrugation inclination angle α of 85 °, and a corrugation height h =30mm;
specifically, the corrugation inclination angle α of the annular inside corrugations 3 of the first and second metal diaphragms 200 and 300 gradually increases from 30 ° to 85 ° from inside to outside, and the corrugation height gradually increases from 10mm to 30mm;
specifically, the inclination angles α of the corrugations 3 of the annular inner side of the second metal diaphragm 300 are kept constant from inside to outside and are both 60 °, and the heights of the corrugations are kept constant from inside to outside and are both 10mm.
The invention relates to an extrusion isolation device for adjusting liquid/colloid propellant by installing a corrugated diaphragm in the field of aerospace propulsion, wherein an inner core corrugation 1 positioned in the central area of the inner part of a storage box shell 100, an annular edge corrugation 2 positioned in the outer side area of the diaphragm and a plurality of annular inner side corrugations 3 positioned between the inner core corrugation 1 and the annular edge corrugation 2 are seamlessly connected to form a complete diaphragm, the two diaphragms form a liquid/colloid propellant extrusion isolation device, and after the corrugated diaphragm is completely unfolded, the profile of the corrugated diaphragm is expanded and deformed into a final round or non-round (special-shaped) profile from an initial corrugated profile, so that the supply of the liquid/colloid propellant is realized. The invention effectively solves the problems that the conventional spherical cylindrical storage tank with a circular section in the prior art can not adopt a metal diaphragm to carry out propellant management, the propellant management problem of a cylindrical storage tank with a non-circular (special-shaped) section, the long-term storage problem of a non-metal bag type cylindrical storage tank propellant, the shaking problem of a surface tension type cylindrical storage tank propellant and the co-body storage and management problems of a single cylindrical storage tank and a double-element propellant.
The working principle of the invention is as follows:
in use, the air in the air storage chamber 103 is charged through the third nozzle 106 to be used as the power for outputting the fuel agent and the oxidant, and specifically, the valves on the first nozzle 104 and the second nozzle 105 can be simultaneously adjusted to adjust the output volume ratio of the fuel agent and the oxidant when the air is charged in the air storage chamber 103.
During propellant filling, the propellant can be filled by evacuating air from the air storage chamber 103 through the third nozzle 106 as a motive force for feeding the fuel agent and the oxidant, and simultaneously opening the valves on the first nozzle 104 and the second nozzle 105.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, are not to be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A squeeze insulator for propellant management, comprising a tank housing (100) and a first metal membrane (200), a second metal membrane (300) arranged inside the tank housing (100);
the first metal diaphragm (200) and one side wall of the tank shell (100) form a fuel agent storage cavity (101), the second metal diaphragm (300) and the other side wall of the tank shell (100) form an oxidant storage cavity (102), an air storage cavity (103) is formed between the first metal diaphragm (200) and the second metal diaphragm (300), and the fuel agent storage cavity (101), the oxidant storage cavity (102) and the air storage cavity (103) are respectively connected with a first nozzle (104), a second nozzle (105) and a third nozzle (106) on the tank shell (100);
the first metal diaphragm (200) and the second metal diaphragm (300) are both annular corrugated films, and when the volume of the air storage cavity (103) is maximum, the first metal diaphragm (200) and the second metal diaphragm (300) can be attached to the inner wall of the storage box shell (100); when the volume of the air storage cavity (103) is minimum, the first metal diaphragm (200) is attached to the second metal diaphragm (300).
2. The squeeze insulator for propellant management of claim 1, wherein the input or output of the fuel in the fuel storage chamber (101) and the oxidizer in the oxidizer storage chamber (102) is enabled by the filling or the extraction of gas into or out of the air storage chamber (103) through the third nozzle (106).
3. The squeeze isolator for managing propellant of claim 1, wherein the geometry of the first metal membrane (200) and the second metal membrane (300) is the same or different.
4. The squeeze insulator for propellant management according to claim 1, wherein the first metal membrane (200) and the second metal membrane (300) each include an inner core corrugation (1), an annular edge corrugation (2), and an inner side corrugation (3) having multiple rings, both sides of which are seamlessly connected to the inner core corrugation (1) and the annular edge corrugation (2), respectively.
5. The squeeze insulator for managing propellant according to claim 4, characterized in that the inner core corrugation (1) includes an inner core straight corrugation (11) and two inner core semicircular corrugations (12) disposed at both ends of the inner core straight corrugation (11), the inner core straight corrugation (11) having a cross section with circular arc-shaped peaks or valleys;
two sides of the straight corrugation (11) of the inner core are respectively provided with a half circular arc-shaped wave trough or a half circular arc-shaped wave crest.
6. The squeeze insulator for propellant management according to claim 4, wherein the annular edge corrugation (2) is configured to have two edge flat corrugations (21) and two edge semi-circular corrugations (22) disposed at both ends of the two edge flat corrugations (21) so that the annular edge corrugation (2) is formed in an annular shape, the edge flat corrugations (21) and the edge semi-circular corrugations (22) have the same cross-sectional shape, wherein the edge flat corrugations (21) and the edge semi-circular corrugations (22) each have one circular arc shaped peak, an outer side of the circular arc shaped peak is connected with one circular arc shaped inclined wave, and an inner side of the circular arc shaped peak is connected with one straight inclined wave and one half circular arc shaped wave trough in sequence.
7. The squeeze insulator for managing propellant according to claim 4, characterized in that the rings in the inside corrugation (3) are successively seamlessly connected and progressively larger in a radially outward direction;
each ring in the inner side corrugations (3) is provided with two inner side straight corrugations (31), two ends of each inner side straight corrugation (31) are connected with two inner side semi-circular corrugations (32), the inner side straight corrugations (31) and the inner side semi-circular corrugations (32) have the same cross section shape, each inner side straight corrugation (31) and each inner side semi-circular corrugation (32) are provided with a circular arc-shaped peak, and two sides of each circular arc-shaped peak are respectively connected with a straight line inclined wave and a half circular arc-shaped trough.
8. Compressed insulation for propellant management according to claim 5, characterized in that the inner core straight corrugation (11) has an edge straight corrugation (21) equal to the annular edge corrugation (2) and the inner side corrugation (31) of the inner side corrugation (3).
9. Compressed isolating device for propellant management according to claim 5, characterised in that the inner core half-circular corrugation (12) has the same centroid as the edge half-circular corrugation (22) of the annular edge corrugation (2) and as the inner half-circular corrugation (32) of the inner corrugation (3).
10. Squeeze-insulation device for managing propellant according to claim 1 characterized in that the core corrugations (1), the annular edge corrugations (2) and the inside corrugations (3) have corrugations with adjacent circular arc shaped crests and troughs of equal radius.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210898665.3A CN115465476A (en) | 2022-07-28 | 2022-07-28 | Squeeze isolation device for propellant management |
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