Storage tank bottom structure, storage tank and carrier rocket

Abstract

The embodiment of the utility model provides a storage tank bottom structure, a storage tank and a carrier rocket, the storage tank bottom structure comprises a shell and a top cover, the shell is of a hollow arc-shaped revolving body structure which is through in the front-back direction, the two ends of the shell are the small-diameter end and the large-diameter end respectively in the axis direction of the shell, and the small-diameter end of the shell is fixedly connected with the top cover; a propellant is arranged on the top cover; a plurality of protruding structures are evenly distributed on the outer side face of the shell in the circumferential direction in the axis direction of the shell. According to the technical scheme, the bottom structure of the thrust bearing type storage tank is simple in process, easy to manufacture in batches and beneficial to achieving light weight of a carrier rocket.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of carrier rockets, and particularly relates to a tank bottom structure, a tank and a carrier rocket. BACKGROUND

[0002] Liquid rockets are mainly used as space carriers and propelling parts of missile nuclear weapons, and the propellant tank of a liquid carrier rocket is a main component of the liquid carrier rocket, which is used for storing propellants, delivering liquid fuel and oxidants to the rocket engine, and bearing various static loads, dynamic loads and thermal loads in flight, and some equipment is also installed on the tank bottom of the propellant tank.

[0003] The tank bottom structure that transmits engine thrust (i.e., a thrust-bearing tank bottom structure) is a new design method that has recently attracted widespread attention, which can fully utilize the structural bearing capacity brought by tank pressurization and is an important direction of lightweight carrier rocket technology research.

[0004] In the existing method of transmitting engine thrust through the tank bottom, a conical shell frame structure is mainly used, and the delivery pipeline is led out from the conical shell opening, which has poor operability. In addition, the diameters of the frame and the engine thrust ring are relatively large, and the size and weight of the frame are limited. Some improved forms, such as the method proposed in CN116291964A, set a plurality of fins on the inside of the tank bottom to bear the engine thrust. The fins need to be welded after the tank bottom is formed, which has high requirements for the size of the tank bottom surface and the size of the fin surface, and the fin welding workload is very large and the process flow is complex, so it is difficult to apply in batches.

[0005] Therefore, how to improve the method of transmitting engine thrust through the tank bottom to realize a thrust-bearing tank bottom structure that is easy to manufacture in batches is a problem to be solved. UTILITY MODEL CONTENTS

[0006] The utility model embodiment provides a tank bottom structure, a tank and a carrier rocket, to realize a thrust-bearing tank bottom structure that is simple in process and easy to manufacture in batches, thereby helping to realize lightweight carrier rockets.

[0007] To achieve the above purpose, the utility model embodiment provides a tank bottom structure, which comprises a shell and a top cover, the shell is an arc-shaped revolving body structure that is through and hollow from front to back, along the axial direction of the shell, the two ends of the shell are a small-diameter end and a large-diameter end, wherein the small-diameter end of the shell is fixedly connected with the top cover; a propellant is arranged on the top cover; a plurality of convex structures are uniformly distributed on the outer side of the shell in the circumferential direction and along the axial direction of the shell.

[0008] Further, the convex structure and the shell form an integral structure.

[0009] Further, the convex structure is an arc-shaped strip hollow structure with an open inner side, and the front end of the convex structure faces the large-diameter end of the shell, and the rear end of the convex structure faces the top cover.

[0010] Further, the front end of the convex structure has the same width as the rear end of the convex structure, and the height of the front end of the convex structure protruding from the outer side of the shell is the same as the height of the rear end of the convex structure protruding from the outer side of the shell.

[0011] Further, the front end and the rear end of the convex structure are further respectively provided with a circular arc.

[0012] Further, the convex structure comprises first convex structures and second convex structures staggered in the circumferential direction, the arc length of the first convex structure is greater than the arc length of the second convex structure, and the width of the first convex structure is greater than the width of the second convex structure.

[0013] Further, the large-diameter end of the shell is 1800mm, and the convex structure has 30 convex structures.

[0014] Further, the utility model further comprises a thrust ring, the thrust ring is connected with the top cover through a plurality of circumferentially distributed trapezoidal reinforcing ribs, the small end of the trapezoidal reinforcing rib is fixedly connected with the thrust ring, and the large end of the trapezoidal reinforcing rib is fixedly connected with the top cover.

[0015] In addition, the utility model embodiment further provides a storage tank, which comprises the storage tank bottom structure as described above.

[0016] Meanwhile, the utility model embodiment further provides a carrier rocket, which comprises a rocket engine, a storage tank body, and the storage tank bottom structure as described above; the rocket engine is connected with the storage tank bottom structure through a connecting frame, and the rocket engine is connected with the propellant outlet through a conveying pipe.

[0017] The above technical scheme has the following beneficial effects:

[0018] In the technical scheme, a plurality of outward convex convex structures are arranged on the shell in a uniform manner, the convex structure can improve the external pressure stability, bear the thrust of the rocket engine, thereby simplifying the overall structure of the storage tank bottom, the manufacturing cost is low, the cycle is fast, the layout between the rocket engine is reasonable, the propellant conveying device is light in weight, thereby helping to realize the light weight of the carrier rocket, and the conveying efficiency is greatly improved.

[0019] In addition, the technical scheme has the following characteristics:

[0020] In the technical scheme, the shell is a spinning integral forming light shell structure, or a melon-seed type tailor-welded thin shell structure, and then the convex structure is machined on the outer side surface of the shell in a stamping manner, thereby further simplifying the process flow and facilitating batch manufacturing. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings described below are only some of the embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0022] Figure 1 is a structural schematic view of a tank bottom structure of an embodiment of the present application;

[0023] Figure 2 is a schematic view of a plurality of protruding structures in an embodiment of the present application;

[0024] Figure 3 is a structural schematic view of a carrier rocket in an embodiment of the present application;

[0025] Figures:

[0026] 10, tank connecting ring; 20, shell; 21, protruding structure; 211, first protruding structure; 212, second protruding structure; 30, top cover; 31, oxidizer outlet flange; 32, combustion agent outlet flange; 40, thrust ring; 41, trapezoidal reinforcing rib; 42, connecting frame; 51, first conveying pipe; 52, second conveying pipe; 60, rocket engine. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0028] As Figure 1 shown, an embodiment of the present application provides a tank bottom structure, which comprises a shell 20 and a top cover 30. The shell 20 is a hollow arc-shaped revolving body structure penetrating from front to back. Along the axial direction of the shell 20, the two ends of the shell 20 are small-diameter ends and large-diameter ends, respectively. The small-diameter end of the shell 20 is fixedly connected with the top cover 30. The top cover 30 is provided with a propellant outlet. The outer side surface of the shell 20 is circumferentially and uniformly provided with a plurality of protruding structures 21 along the axial direction of the shell 20.

[0029] In the technical solution, the tank bottom is composed of a tank connecting ring 10, a shell 20, a top cover 30, a propellant outlet and the like, wherein the shell 20 is a thin-walled shell structure, and the top cover 30 is an integral machining structure, the ellipsoidal inner surface of which can bear the propellant pressure, and the whole tank bottom is a welded assembly structure, which has high forming efficiency, light structure weight and short manufacturing cycle. The rocket engine 60 can be connected with the thrust ring 40 through the connecting frame 42 to realize the transmission of thrust load, and the propellant (including combustion agent and oxidant) can be delivered to the rocket engine 60 through the propellant outlet (including the combustion agent outlet flange 32 and the oxidant outlet flange 31) located at the bottom of the top cover 30 through the pipeline, so that the propellant delivery efficiency is high, the pipeline structure is simple and light in weight, and the structure weight can be effectively reduced and the carrying efficiency can be improved.

[0030] The shell 20 is a rotating ellipsoidal thin-walled structure, the ellipsoidal surface of which can bear the propellant pressure, and a plurality of outwardly protruding protruding structures 21 are uniformly arranged on the shell 20 to improve the external pressure stability and bear the thrust of the rocket engine 60.

[0031] Further, the protruding structure 21 is preferably formed in an integral structure with the shell 20, rather than being assembled to the shell 20 after being separately machined, so that the production can be simplified, the workload of later assembly and the like is reduced, the difficulty of batch application is reduced, and the technology is easier to be popularized. The protruding structure 21 can be made by sheet metal stamping forming, or can be realized by extrusion forming or machining forming after casting, and the appropriate machining method can be selected according to the actual situation.

[0032] It should be noted that although the protruding structure 21 is in an integral structure with the shell 20, the shell 20 itself can be a rotating integral formed light shell structure, or can be formed by a plurality of melon-seed-shaped thin shell structures. For example, a small thickness plate can be formed into the shell 20 by rotating, or stamping, or creep forming, and then the protruding structure 21 can be machined by stamping or die protruding hole method; or the melon-seed-shaped thin shell structure can be formed by welding, the shell 20 is evenly divided into a plurality of parts in the circumferential direction, and the protruding structure 21 of the ellipsoidal surface and the side surface of each part is machined by a die support, and then the whole is welded.

[0033] Further, the protruding structure 21 is an arc-shaped strip hollow structure with an open inner side, since the protruding structure 21 is preferably made by sheet metal stamping forming, and is formed by stamping the container wall of the shell 20 from the inside to the outside by a punch, therefore the protruding structure 21 is a thin-walled structure like the shell 20, is connected to the outer side of the shell 20, and the top of the protruding structure 21 is an arc-shaped structure coaxial with the outer side of the shell 20. The front end of the protruding structure 21 faces the tank connecting ring 10 (i.e. the large diameter end of the shell 20), and the rear end of the protruding structure 21 faces the top cover 30.

[0034] Further, in order to facilitate processing, the front end width of the protruding structure 21 is the same as the rear end width; the height of the front end of the protruding structure 21 protruding from the outer side surface of the shell 20 is the same as the height of the rear end of the protruding structure 21 protruding from the outer side surface of the shell 20, at this time, the protruding structure 21 forms a "capsule type" structure which is attached to the outer side surface of the shell 20 in an arc-shaped manner.

[0035] Further, the front end and the rear end of the protruding structure 21 are also respectively provided with a circular arc, that is, the projection of the protruding structure 21 on a plane perpendicular to the central depth direction of the protruding structure 21 is a shape composed of a semicircle at both ends and a rectangle in the middle, and the design of the circular arc helps to eliminate stress concentration points, ensures that the shell 20 will not crack during stamping and other processing, and ensures the processing quality.

[0036] Further, when the size of the storage tank is large, the geometric defects and other processing and manufacturing deviations also increase, at this time, a plurality of sizes (preferably two) of the capsule type protruding structure 21 can be arranged on the shell 20 to improve the external pressure bearing capacity of the tank bottom. As shown in Figure 2 The protruding structure 21 includes a first protruding structure 211 and a second protruding structure 212, which are arranged in a staggered manner along the circumferential direction, that is, one second protruding structure 212 is arranged between every two adjacent first protruding structures 211, and one first protruding structure 211 is arranged between every two second protruding structures 212, wherein the first protruding structure 211 is larger than the second protruding structure 212, that is, the arc length of the first protruding structure 211 is greater than the arc length of the second protruding structure 212, and the width of the first protruding structure 211 is greater than the width of the second protruding structure 212.

[0037] Further, in a specific embodiment, the diameter of the large diameter end of the shell 20 is 1800mm, and the protruding structure 21 has a total of 30, at this time, better effects can be achieved.

[0038] Further, the tank bottom structure further comprises a thrust ring 40, and the thrust ring 40 is connected with the top cover 30 through a plurality of circumferentially distributed trapezoidal reinforcing ribs 41; the small end of the trapezoidal reinforcing rib 41 is fixedly connected with the thrust ring 40, and the large end of the trapezoidal reinforcing rib 41 is fixedly connected with the top cover 30, and the trapezoidal reinforcing rib 41 can uniformly diffuse the concentrated load of the connecting frame 42 to the shell 20.

[0039] The utility model embodiment further provides a storage tank, which comprises the tank bottom structure as described above, wherein the tank connecting ring 10 and the front tank body (not shown in the figure) are connected into one body through welding to form a complete.

[0040] AsFigure 3 As shown in the figure, the utility model embodiment further provides a carrier rocket, including rocket engine 60, storage tank body, and the storage tank bottom structure as described above;The rocket engine 60 is connected with the thrust ring 40 through the connecting frame 42, the rocket engine 60 is connected with the oxidant outlet flange 31 through the second conveying pipe 52, and the rocket engine 60 is connected with the combustion agent outlet flange 32 through the first conveying pipe 51.The connecting frame 42 is the structure of compression rod, and the included angle between the compression rod bus and the central axis of the rocket engine 60 is 45 °, at this time, the transmission efficiency of the rocket engine 60 thrust load is highest, and each compression rod of the connecting frame 42 is uniformly distributed along the circumference, and at the same time, the space between the compression rods is open, which can be used for the arrangement of the storage tank pressurization system pipeline.

[0041] The conveying pipe (including the first conveying pipe 51 and the second conveying pipe 52) is composed of a metal hose and a tee (the tee structure is arranged on the side of the conveying pipe, and is a filling flange intersecting with the conveying pipe), and the storage tank and the rocket engine 60 are connected through the butt flanges (including the oxidant outlet flange 31, the combustion agent outlet flange 32 and the corresponding flange arranged on one side of the rocket engine 60) arranged at both ends, wherein the metal hose is used for compensating the deformation of the storage tank under pressure and the manufacturing tolerance, and the tee is used for filling and discharging the propellant in the storage tank.

[0042] In addition, in the utility model, the convex structure 21 is not limited to the capsule type shown in the figure, and whether the distribution mode is uniform can also be designed according to the rocket engine thrust load distribution mode.

[0043] In the above detailed description, various features are combined together in a single embodiment to simplify the disclosure. Such disclosure method should not be interpreted as reflecting the intention that the embodiments of the claimed subject matter require more features than the features clearly stated in each claim. On the contrary, as reflected in the appended claims, the utility model is in a state of less than all the features of the disclosed single embodiment. Therefore, the appended claims are hereby clearly incorporated into the detailed description, wherein each claim is independently a separate preferred embodiment of the utility model.

[0044] To enable any person skilled in the art to implement or use the utility model, the disclosed embodiments are described above. Various modifications of these embodiments are obvious to those skilled in the art, and the general principles defined herein can also be applied to other embodiments without departing from the spirit and protection scope of the disclosure. Therefore, the disclosure is not limited to the embodiments given herein, but is consistent with the broadest scope of the principles and novel features disclosed in the present disclosure.

[0045] The above specific embodiments explain the purpose, technical scheme and beneficial effects of the present application in further detail, and it should be understood that the above description is only a specific embodiment of the present application and is not used to limit the protection scope of the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A storage tank bottom structure, characterized in that, Includes a housing (20) and a top cover (30). The housing (20) is a hollow arc-shaped rotating structure that runs through the front and back. Along the axial direction of the housing (20), the two ends of the housing (20) are a small diameter end and a large diameter end, respectively. The small diameter end of the housing (20) is fixedly connected to the top cover (30). The top cover (30) has a propellant outlet; The outer surface of the housing (20) is circumferentially covered with a plurality of protruding structures (21) evenly distributed along the axial direction of the housing (20).

2. The tank bottom structure as described in claim 1, characterized in that, The protruding structure (21) and the shell (20) form an integral structure.

3. The tank bottom structure as described in claim 1, characterized in that, The protruding structure (21) is an arc-shaped hollow structure with an open inner side, and the front end of the protruding structure (21) faces the large diameter end of the shell (20), while the rear end of the protruding structure (21) faces the top cover (30).

4. The tank bottom structure as described in claim 3, characterized in that, The front end width of the protruding structure (21) is the same as the rear end width; the height at which the front end of the protruding structure (21) protrudes beyond the outer side of the housing (20) is the same as the height at which the rear end of the protruding structure (21) protrudes beyond the outer side of the housing (20).

5. The tank bottom structure as described in claim 1, characterized in that, The front and rear ends of the protruding structure (21) are respectively provided with arcs.

6. The tank bottom structure as described in claim 1, characterized in that, The protruding structure (21) includes a first protruding structure (211) and a second protruding structure (212) arranged alternately in the circumferential direction. The arc length of the first protruding structure (211) is greater than the arc length of the second protruding structure (212), and the width of the first protruding structure (211) is greater than the width of the second protruding structure (212).

7. The tank bottom structure as described in claim 1, characterized in that, The large-diameter end of the housing (20) has a diameter of 1800 mm, and there are a total of 30 protrusions (21).

8. The tank bottom structure as described in claim 1, characterized in that, It also includes a thrust ring (40), which is connected to the top cover (30) by a plurality of circumferentially distributed trapezoidal reinforcing ribs (41); the small end of the trapezoidal reinforcing rib (41) is fixedly connected to the thrust ring (40), and the large end of the trapezoidal reinforcing rib (41) is fixedly connected to the top cover (30).

9. A storage tank, characterized in that, Includes the tank bottom structure as described in any one of claims 1-8.

10. A launch vehicle, characterized in that, It includes a rocket engine (60), a tank body, and a tank bottom structure as described in any one of claims 1-8; The rocket engine (60) is connected to the bottom structure of the storage tank via a connecting frame (42), and the rocket engine (60) is connected to the propellant outlet via a delivery pipe.

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