Airtightness detection equipment for storage tank of aerospace craft

Abstract

The utility model discloses an aerospace craft storage box air tightness detection device. The aerospace craft storage box air tightness detection device comprises a circular ring base, an external pressure-bearing tire film, an internal pressure-bearing tire film, a supporting ring and a first pressing ring. The edge of the external pressure-bearing tire membrane is detachably connected to the top surface of the circular ring base; the edge of the internal pressure-bearing tire membrane is connected to the top surface of the circular ring base, the internal pressure-bearing tire membrane is located on the inner side of the external pressure-bearing tire membrane, and a detection cavity is formed between the internal pressure-bearing tire membrane and the external pressure-bearing tire membrane; the supporting ring is located in the detection cavity, and the bottom of the supporting ring is connected to the circular ring base; the first pressing ring is arranged at the top of the supporting ring, extends out of the inner side face of the supporting ring, is detachably connected to the circular ring base and is used for clamping the storage box together with the circular ring base. The aerospace craft storage tank air tightness detection equipment can perform air tightness detection on storage tanks of different specifications, and can detect the internal pressure and the external pressure of the storage tanks.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of fluid airtightness testing, and particularly relates to a spacecraft tank airtightness detection equipment. BACKGROUND

[0002] In the design of fuel and oxidant tanks of a spacecraft, the ellipsoidal structure at the bottom is a core design that is specially optimized. This curved surface modeling can effectively disperse the pressure load inside the tank, avoiding local stress concentration leading to deformation or rupture. Since fuel or oxidant has strong volatility and flammability, once the tank leaks, not only the propellant will be rapidly consumed, but also a violent explosion is more likely to occur when encountering high temperature or static electricity. Therefore, during the manufacturing and assembly of the spacecraft, the tank must be strictly subjected to airtightness detection to ensure the safe operation of the spacecraft.

[0003] However, the existing equipment for airtightness detection of the tank is usually only applicable to a single specification of the tank, and multiple devices are needed for detection of tanks of different specifications. CONTENT OF THE UTILITY MODEL

[0004] The spacecraft tank airtightness detection equipment provided by the embodiments of the present application solves the technical problem that the existing airtightness detection equipment is usually only applicable to a single specification of the tank.

[0005] The spacecraft tank airtightness detection equipment provided by the embodiments of the present application includes: a circular ring base; an outer pressure-bearing tire membrane, the edge of the outer pressure-bearing tire membrane being detachably connected to the top surface of the circular ring base; an inner pressure-bearing tire membrane, the edge of the inner pressure-bearing tire membrane being connected to the top surface of the circular ring base, the inner pressure-bearing tire membrane being located inside the outer pressure-bearing tire membrane and forming a detection cavity with the outer pressure-bearing tire membrane; a support ring, the support ring being located inside the detection cavity and the bottom of the support ring being connected to the circular ring base; and a first pressure ring, the first pressure ring being arranged at the top of the support ring and extending from the inner side surface of the support ring, the first pressure ring being detachably connected to the circular ring base and being used for clamping the tank together with the circular ring base; wherein the tank divides the detection cavity into a first chamber and a second chamber.

[0006] In a possible implementation manner, a plurality of through holes are formed in the circumferential surface of the support ring.

[0007] In a possible implementation manner, a first annular groove is formed in the top surface of the circular ring base; and the spacecraft tank airtightness detection equipment further includes: a first sealing ring, the first sealing ring being installed in the first annular groove and being used for pressing the bottom surface of the outer pressure-bearing tire membrane to seal between the circular ring base and the outer pressure-bearing tire membrane.

[0008] In a possible implementation, the top surface of the circular ring base is provided with a second annular groove; the second sealing ring is installed in the second annular groove, and is used for pressing the storage tank to seal the storage tank and the circular ring base; and the third sealing ring is installed on the outer side surface of the inner pressure-bearing tire membrane, and is used for pressing the side wall of the storage tank to seal the side wall of the storage tank and the inner pressure-bearing tire membrane.

[0009] In a possible implementation, the space vehicle storage tank air tightness detection device further comprises a second compression ring located between the support ring and the storage tank; and a plurality of pressing members detachably connected to the circular ring base and pressing the top surface of the second compression ring, so that the second compression ring presses the second sealing ring.

[0010] In a possible implementation, the second compression ring has a pressure-bearing plane parallel to the top surface thereof and a vertical plane connecting the pressure-bearing plane and the top surface thereof; the pressing member comprises a pressing part and a supporting part; one end of the pressing part is connected to the top of the supporting part, the other end of the pressing part presses the pressure-bearing plane and the vertical plane, and the bottom of the supporting part is used for pressing the top surface of the circular ring base.

[0011] In a possible implementation, the space vehicle storage tank air tightness detection device further comprises a hoisting assembly comprising a plurality of first hoisting members, a plurality of second hoisting members, a plurality of third hoisting members and a plurality of fourth hoisting members; the plurality of first hoisting members are connected to the outer circular surface of the circular ring base, the plurality of second hoisting members are connected to the outer circular surface of the outer pressure-bearing tire membrane, the plurality of third hoisting members are connected to the outer circular surface of the support ring, and the plurality of fourth hoisting members are connected to the outer circular surface of the first compression ring.

[0012] In a possible implementation, the space vehicle storage tank air tightness detection device further comprises a plurality of support assemblies arranged in a circular array at the bottom of the circular ring base.

[0013] In a possible implementation, the support assembly comprises a bottom plate, a base and a plurality of leveling feet; the plurality of leveling feet are installed on the base; the top of the base is connected to the circular ring base, and the bottom of the base is connected to the plurality of leveling feet.

[0014] The technical scheme provided in the embodiments of the present application has at least the following technical effects:

[0015] The embodiment of the present application provides a space vehicle storage tank air tightness detection equipment, when the air tightness of the storage tank is detected, the first compression ring is connected to the top of the supporting ring, so that the storage tank is clamped by the circular ring base and the first compression ring; when the internal pressure of the storage tank needs to be detected, the internal pressure bearing tire membrane is connected to the circular ring base, and distilled water is injected into the second cavity, and whether leakage occurs is observed; when the external pressure of the storage tank needs to be detected, the external pressure bearing tire membrane is connected to the top surface of the circular ring base, and distilled water is injected into the first cavity, and whether leakage occurs is observed. When the air tightness of storage tanks of different specifications needs to be detected, the storage tank is clamped by using supporting rings of different height sizes. Therefore, the space vehicle storage tank air tightness detection equipment can detect the air tightness of storage tanks of different specifications, and can detect the internal pressure and the external pressure of the storage tank. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments of the present application will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0017] Figure 1 The structure schematic diagram of the space vehicle storage tank air tightness detection equipment provided by the embodiment of the present application is shown in the figure.

[0018] Figure 2 The structure schematic diagram of the internal structure of the external pressure bearing tire membrane of the space vehicle storage tank air tightness detection equipment provided by the embodiment of the present application is shown in the figure.

[0019] Figure 3 The structure schematic diagram of the circular ring base and the internal pressure bearing tire membrane provided by the embodiment of the present application is shown in the figure.

[0020] Figure 4 The cross-sectional view of the space vehicle storage tank air tightness detection equipment provided by the embodiment of the present application is shown in the figure.

[0021] Figure 5 The connection schematic diagram of the second sealing ring, the second compression ring and the compression piece provided by the embodiment of the present application is shown in the figure.

[0022] Fig. 1: 1 - ring base; 2 - outer pressure-bearing tire membrane; 3 - inner pressure-bearing tire membrane; 4 - support ring; 41 - through hole; 5 - first compression ring; 6 - first sealing ring; 7 - second sealing ring; 9 - second compression ring; 91 - pressure-bearing plane; 92 - vertical plane; 10 - compression piece; 101 - compression part; 102 - support part; 20 - hoisting assembly; 201 - first hoisting piece; 202 - second hoisting piece; 203 - third hoisting piece; 204 - fourth hoisting piece; 30 - support assembly; 31 - base plate; 32 - base; 33 - leveling foot; 40 - first top water receiving pipe; 50 - second top water receiving pipe; 60 - first bottom water receiving pipe; 70 - second bottom water receiving pipe; 80 - storage tank. DETAILED DESCRIPTION

[0023] Fuel and oxidant of a spacecraft are stored in a storage tank, and during the manufacturing and assembly of the spacecraft, the storage tank must be subjected to strict air tightness detection to ensure the safe operation of the spacecraft. However, the existing equipment for detecting the air tightness of the storage tank is usually only suitable for one specification of the storage tank, and multiple equipment needs to be used for detecting different specifications of the storage tank.

[0024] The embodiment of the present application provides a spacecraft storage tank air tightness detection equipment, which solves the above technical problems. The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0025] In the description of the embodiments of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", "third", "fourth" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance. In addition, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium, or the communication between the two elements. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0026] As Figure 1As shown, the space flight vehicle tank airtightness detection device provided by the embodiment of the application comprises a circular ring base 1, an external pressure-bearing tire membrane 2, an internal pressure-bearing tire membrane 3, a support ring 4 and a first pressure ring 5.

[0027] The edge of the external pressure-bearing tire membrane 2 is detachably connected to the top surface of the circular ring base 1. Before the tank 80 needs to be installed in the space flight vehicle tank airtightness detection device for detection, the external pressure-bearing tire membrane 2 is detached from the circular ring base 1; when the external pressure of the tank 80 needs to be detected, the external pressure-bearing tire membrane 2 is connected to the circular ring base 1. Exemplarily, the external pressure-bearing tire membrane 2 is detachably connected to the circular ring base 1 by bolts,

[0028] The edge of the internal pressure-bearing tire membrane 3 is connected to the top surface of the circular ring base 1, and the internal pressure-bearing tire membrane 3 is located inside the external pressure-bearing tire membrane 2 to form a detection cavity therebetween. The internal pressure-bearing tire membrane 3 can be connected to the circular ring base 1 at all times, and is exemplarily integrally connected to the circular ring base 1; or the internal pressure-bearing tire membrane 3 can be detachably connected to the circular ring base 1 by bolts or other structures, and is connected to the circular ring base 1 before the internal pressure of the tank 80 needs to be detected.

[0029] The support ring 4 is located inside the detection cavity, and the bottom of the support ring 4 is connected to the circular ring base 1. The first pressure ring 5 is arranged on the top of the support ring 4 and extends from the inner side surface of the support ring 4, and is detachably connected to the circular ring base 1 to jointly clamp the tank 80 with the circular ring base 1. The height of the support ring 4 determines the distance between the first pressure ring 5 and the circular ring base 1, and further determines the size of the tank 80 that can be installed. The space flight vehicle tank airtightness detection device can adapt to tanks 80 of different sizes by replacing support rings 4 of different height sizes, so that tanks 80 of different sizes can all use the space flight vehicle tank airtightness detection device for airtightness detection.

[0030] Exemplarily, the first pressure ring 5 is detachably connected to the circular ring base 1 by bolts.

[0031] The tank 80 divides the detection cavity into a first chamber between the external pressure-bearing tire membrane 2 and the tank 80, and a second chamber between the internal pressure-bearing tire membrane 2 and the tank 80. When the internal pressure of the tank 80 needs to be detected, the internal pressure-bearing tire membrane 3 is connected to the circular ring base 1, and distilled water is injected into the second chamber to observe whether leakage occurs; when the external pressure of the tank 80 needs to be detected, the external pressure-bearing tire membrane 2 is connected to the top surface of the circular ring base 1, and distilled water is injected into the first chamber to observe whether leakage occurs.

[0032] Specifically, in the embodiment of the present application, the spacecraft tank airtightness detection device comprises a first top water pipe 40, a second top water pipe 50, a first bottom water pipe 60 and a second bottom water pipe 70. The first top water pipe 40 is connected to the top of the outer pressure-bearing tire membrane 2 and communicates with the first chamber; the second top water pipe 50 is connected to the top of the inner pressure-bearing tire membrane 3 and communicates with the second chamber; the first bottom water pipe 60 is connected to the circular ring base 1 and communicates with the first chamber; and the second bottom water pipe 70 is connected to the circular ring base 1 and communicates with the second chamber.

[0033] When the inner pressure of the tank 80 needs to be detected, distilled water is injected into the second chamber through the second top water pipe 50, and after the inner pressure detection is completed, the distilled water in the second chamber is emptied through the second bottom water pipe 70; when the outer pressure of the tank 80 needs to be detected, distilled water is injected into the first chamber through the first top water pipe 40, and after the outer pressure detection is completed, the distilled water in the first chamber is emptied through the first bottom water pipe 60.

[0034] As shown in Figure 2 , in the embodiment of the present application, a plurality of through holes 41 are formed in the circumferential surface of the support ring 4, and the plurality of through holes 41 communicate the space between the support ring 4 and the side wall of the tank 80 with the first chamber, so that the outer pressure of the side wall of the tank 80 can be detected at the same time when the outer pressure of the ellipsoidal bottom of the tank 80 is detected.

[0035] As shown in Figure 4 , the top surface of the circular ring base 1 is provided with a first annular groove; the spacecraft tank airtightness detection device further comprises a first sealing ring 6 installed in the first annular groove, which is used for pressing the bottom surface of the outer pressure-bearing tire membrane 2 to seal the circular ring base 1 and the outer pressure-bearing tire membrane 2, so as to prevent the distilled water in the first chamber from leaking between the circular ring base 1 and the outer pressure-bearing tire membrane 2.

[0036] Further, continuing to refer to Figure 4 , the top surface of the circular ring base 1 is provided with a second annular groove; the spacecraft tank airtightness detection device further comprises a second sealing ring 7 and a third sealing ring, the second sealing ring 7 is installed in the second annular groove and is used for pressing the tank 80 to seal the tank 80 and the circular ring base 1; and the third sealing ring is installed on the outer side surface of the inner pressure-bearing tire membrane 3 and is used for pressing against the side wall of the tank 80 to seal the side wall of the tank 80 and the inner pressure-bearing tire membrane 3. The second sealing ring 7 and the third sealing ring prevent the first chamber from communicating with the second chamber, so that the structure of the inner pressure detection and the outer pressure detection is more accurate.

[0037] As shown in Figure 5As shown in the embodiment of this application, the spacecraft tank airtightness testing device further includes a second pressure ring 9 and a plurality of clamping components 10; the second pressure ring 9 is located between the support ring 4 and the tank 80; the plurality of clamping components 10 are detachably connected to the circular base 1 and abut against the top surface of the second pressure ring 9, for pressing the second pressure ring 9 against the second sealing ring 7.

[0038] Because the sidewall of the storage tank 80 is relatively thin, when the sidewall of the storage tank 80 presses against the second sealing ring 7, the bearing area of ​​the second sealing ring 7 is small, resulting in a poor sealing effect of the second sealing ring 7. The aforementioned multiple pressing parts 10 are connected to the annular base 1 and press the second pressure ring 9 against the second sealing ring 7, thereby improving the sealing effect of the second sealing ring 7.

[0039] For example, the clamping member 10 is connected to the annular base 1 by bolts.

[0040] Specifically, the second pressure ring 9 has a pressure-bearing plane 91 parallel to its own top surface, and a vertical surface 92 connecting the pressure-bearing plane 91 and its own top surface; wherein, the clamping member 10 includes a clamping part 101 and a supporting part 102; one end of the clamping part 101 is connected to the top of the supporting part 102, the other end of the clamping part 101 abuts against the pressure-bearing plane 91 and the vertical surface 92, and the bottom of the supporting part 102 is used to abut against the top surface of the circular ring base 1.

[0041] The pressing part 101 of the second pressure ring 9 presses against the vertical surface 92 on the one hand, restricting the axial movement of the second pressure ring 9, and presses against the pressure bearing surface 91 on the other hand, so that the second pressure ring 9 presses against the second sealing ring 7.

[0042] like Figures 1 to 3 As shown, the spacecraft tank airtightness testing equipment also includes a lifting assembly 20. Specifically, the lifting assembly 20 includes multiple first lifting components 201, multiple second lifting components 202, multiple third lifting components 203, and multiple fourth lifting components 204. The lifting assembly 20 facilitates the lifting of the circular base 1, the external pressure-bearing membrane 2, the support ring 4, and the first pressure ring 5 by a crane.

[0043] Multiple first lifting components 201 are connected to the outer circular surface of the annular base 1. When it is necessary to install the annular base 1 in a preset position, the crane lifts the annular base 1 and moves it to the preset position through the multiple first lifting components 201.

[0044] Multiple second lifting components 202 are connected to the outer circular surface of the outer pressure-bearing membrane 2. When it is necessary to disassemble the outer pressure-bearing membrane 2, the outer pressure-bearing membrane 2 is first disconnected from the annular base 1, and then a crane is used to lift the annular base 1 and move it to a temporary storage position using multiple second lifting components 202; when it is necessary to install the outer pressure-bearing membrane 2, the crane is first used to lift the annular base 1 from the temporary storage position and move it to the installation position using multiple second lifting components 202, and then the outer pressure-bearing membrane 2 is connected to the annular base 1.

[0045] Multiple third lifting components 203 are connected to the outer circular surface of the support ring 4, and multiple fourth lifting components 204 are connected to the outer circular surface of the first pressure ring 5. When the tank 80 needs to be installed for testing, a crane is first used to lift the tank 80 and move it to the installation position. Then, a crane is used to lift the support ring 4 and move it to the installation position using multiple third lifting components 203. The first pressure ring 5 is then lifted and moved to the installation position using multiple fourth lifting components 204 and connected to the circular base 1. When the tank 80, after completing the test, needs to be removed from the spacecraft tank airtightness testing equipment, the first pressure ring 5 is first disconnected from the circular base 1. A crane is used to lift the first pressure ring 5 and move it to a temporary storage position using the fourth lifting components 204. Then, a crane is used to lift the support ring 4 and move it to a temporary storage position using multiple third lifting components 203. Finally, a crane is used to lift the tank 80 and move it to a temporary storage position.

[0046] like Figures 1 to 3 As shown in the embodiment of this application, the spacecraft tank airtightness testing device also includes multiple support components 30, which are arranged in a circular array at the bottom of the annular base 1 to fix the annular base 1 to the ground.

[0047] Specifically, the support assembly 30 includes a base plate 31, a base 32, and multiple leveling feet 33. The base plate 31 is fixed to the ground by anchor bolts. The multiple leveling feet 33 are installed on the base 32. The top of the base 32 is connected to the circular base 1, and the bottom of the base 32 is connected to the multiple leveling feet 33. When fixing the circular base 1 to the ground, the operator adjusts the leveling feet 33 in each support assembly 30 to make the circular base 1 horizontal, ensuring that the distilled water entering the first chamber and the distilled water entering the second chamber are horizontal, thus guaranteeing the accuracy of the test results.

[0048] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0049] The above examples are only used to illustrate the technical solutions of the present application, and are not intended to limit the present application; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that the technical solutions recorded in the foregoing examples can still be modified, or some or all of the technical features thereof can be replaced by equivalents; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A spacecraft tank leak detection apparatus, comprising: The application relates to a detection device for a storage tank, which comprises the following components: a circular base; an outer pressure-bearing tire film, the edge of which is detachably connected to the top surface of the circular base; an inner pressure-bearing tire film, the edge of which is connected to the top surface of the circular base, and which is located inside the outer pressure-bearing tire film to form a detection cavity with the outer pressure-bearing tire film; a supporting ring, which is located inside the detection cavity, and the bottom of which is connected to the circular base; and a first pressing ring, which is arranged on the top of the supporting ring and extends from the inner side surface of the supporting ring, and which is detachably connected to the circular base to jointly clamp the storage tank with the circular base; wherein the storage tank divides the detection cavity into a first cavity and a second cavity. A plurality of through holes are formed in the circumferential surface of the supporting ring.

2. The spacecraft tank leak detection apparatus of claim 1, wherein, A first annular groove is formed in the top surface of the circular base; 3. The spacecraft tank leak detection apparatus of claim 1, wherein, Further comprising: a first sealing ring, which is arranged in the first annular groove and is used for pressing the bottom surface of the outer pressure-bearing tire film to seal the circular base and the outer pressure-bearing tire film. A second annular groove is formed in the top surface of the circular base; 4. The spacecraft tank leak detection apparatus of claim 3, wherein, Further comprising: a second sealing ring, which is arranged in the second annular groove and is used for pressing the storage tank to seal the storage tank and the circular base; a third sealing ring, which is arranged on the outer side surface of the inner pressure-bearing tire film and is used for pressing against the side wall of the storage tank to seal the side wall of the storage tank and the inner pressure-bearing tire film. Further comprising:

5. The spacecraft tank leak detection apparatus of claim 4, wherein, a second pressing ring, which is located between the supporting ring and the storage tank; a plurality of pressing members, which are detachably connected to the circular base and press against the top surface of the second pressing ring, and are used for pressing the second pressing ring to press the second sealing ring. The second pressing ring has a pressure-bearing plane parallel to the top surface thereof and a vertical plane connecting the pressure-bearing plane and the top surface thereof; 6. The spacecraft tank leak detection apparatus of claim 5, wherein, The pressing member comprises a pressing part and a supporting part; One end of the pressing part is connected to the top of the supporting part, the other end of the pressing part presses against the pressure-bearing plane and the vertical plane, and the bottom of the supporting part is used for pressing against the top surface of the circular base. Further comprising:

7. The spacecraft tank leak detection apparatus of claim 1, wherein, a lifting assembly, which comprises a plurality of first lifting members, a plurality of second lifting members, a plurality of third lifting members and a plurality of fourth lifting members; The plurality of first lifting members are connected to the outer circumferential surface of the circular base, the plurality of second lifting members are connected to the outer circumferential surface of the outer pressure-bearing tire film, the plurality of third lifting members are connected to the outer circumferential surface of the supporting ring, and the plurality of fourth lifting members are connected to the outer circumferential surface of the first pressing ring. Further comprising:

8. The spacecraft tank leak detection apparatus of claim 1, wherein, a plurality of supporting assemblies, which are arranged in a circular array on the bottom of the circular base. The supporting assembly comprises a bottom plate, a base and a plurality of leveling feet; 9. The spacecraft tank leak detection apparatus of claim 8, wherein, The plurality of leveling feet are arranged on the base; The top of the base is connected to the circular base, and the bottom of the base is connected to the plurality of leveling feet. ​

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