Thin-wall spacecraft shell, shaping machining tool and shaping machining method

Abstract

The invention discloses a thin-wall spacecraft shell and a shaping machining tool used for the thin-wall spacecraft shell. The thin-wall spacecraft shell is in a semi-cylinder shape and sequentially comprises a first conical section, a cylindrical section and a second conical section in the axial direction. The wall thickness of the thin-wall spacecraft shell ranges from 0.2 cm to 5 cm. The taper of the first conical section ranges from 0.01 to 0.1, and the taper of the second conical section ranges from 0.05 to 0.3. The shaping machining tool comprises a bottom plate, a plurality of first fixing sleeve pieces and a plurality of second fixing sleeve pieces, wherein the first fixing sleeve pieces and the second fixing sleeve pieces are alternately installed on the bottom plate, and the first fixing sleeve pieces and the second fixing sleeve pieces are installed on the bottom plate in a spaced arrangement mode. The invention further discloses a shaping machining method of the thin-wall spacecraft shell. According to the shaping machining tool for the thin-wall spacecraft shell, the thin-wall spacecraft shell can be fixed in two different states; and in addition, through the interval supporting mode, the weight and cost of the shaping machining tool are greatly reduced, and meanwhile hole forming machining can be conveniently conducted on the shell.

Description

Technical Field

[0001] The present invention relates to the technical field of processing large thin-walled parts for aerospace, and in particular to a thin-walled spacecraft shell, a shaping processing tool and a shaping processing method. Background Art

[0002] Ceramic-based composites are a type of composite material made by mixing ceramic powder and fiber and sintering them at high temperature. They have excellent properties such as high temperature resistance, relatively light weight, corrosion resistance, and low dielectric loss. They are widely used in the aerospace field, such as engine casings, missile wings, warheads, space shuttle doors, solar cell panels, antennas and other components.

[0003] As attached Figure 1 A large thin-walled spacecraft shell made of ceramic-based composite material is shown, which has a large size and a small wall thickness. Compared with metal materials, ceramic-based composite materials have lower strength, so they are easily deformed during clamping and processing, which makes them difficult to process, and the processing precision is low and the error is large; in addition, the fracture toughness of ceramic-based composite materials is relatively small, and if the clamping force is too large, it is easy to break the parts. For this type of spacecraft shell, the prior art generally uses a solid tooling with a profiling structure for support and fixation. Although this type of solid tooling can achieve a good fixing effect, due to the large size of the spacecraft shell, the weight of the solid tooling is heavy, generally exceeding 2 tons, which is inconvenient to move and has a high cost; in addition, when using this type of solid tooling for support and fixation, it is obviously inconvenient to perform through-hole processing on the surface of the spacecraft shell, and since the large thin-walled spacecraft shell made of ceramic-based composite materials itself is distorted and deformed, a shaping tooling is required later, and the processing efficiency is low. The prior art has not yet seen a composite tooling that can both mechanically process and shape the large thin-walled spacecraft shell made of ceramic-based composite materials.

[0004] Therefore, how to rationally design tooling to achieve precision machining of thin-walled spacecraft shells and improve machining efficiency and dimensional accuracy is a technical challenge that still needs to be solved. Summary of the invention

[0005] The purpose of the first aspect of the present invention is to provide a thin-walled spacecraft shell, which has the characteristics of light weight and low flight resistance through structural design, and has excellent high temperature resistance and heat insulation, so as to protect the personnel and facilities in the spacecraft.

[0006] The second aspect of the present invention aims to provide a shaping tool for thin-walled spacecraft shells, which can fix the thin-walled spacecraft shells in two different states, and the fixing effect is good, which is conducive to improving the processing accuracy and efficiency; secondly, compared with the physical tooling, the processing tooling is light in weight and low in cost, and it is also convenient for opening holes on the shell; in addition, the tooling can realize both mechanical processing and drilling, and shaping, which improves processing efficiency and product quality.

[0007] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0008] A first aspect of the present invention provides a thin-walled spacecraft shell, which is semi-cylindrical and includes a first conical section, a cylindrical section and a second conical section in sequence along the axial direction; the first conical section, the second conical section and the cylindrical section are integrally formed, and are all made of ceramic-based composite materials; the wall thickness of the thin-walled spacecraft shell is 0.2 to 5 cm; the taper of the first conical section is 0.01 to 0.1, and the taper of the second conical section is 0.05 to 0.3.

[0009] A second aspect of the present invention provides a shaping tool, which is used for fixing and shaping the above-mentioned thin-walled spacecraft shell; the shaping tool includes a base plate, a plurality of first fixing kits and a plurality of second fixing kits alternately installed on the base plate, and the plurality of first fixing kits and the plurality of second fixing kits are all installed on the base plate in an interlaced manner; the first fixing kit is used to fix the spacecraft shell in a first state, and the second fixing kit is used to fix the spacecraft shell in a second state.

[0010] Further, the first fixing kit includes a first support member and a pair of clamping members, the first support member has a concave first support surface, and the first support surface has a shape that matches the corresponding position of the outer surface of the spacecraft shell; wherein, in the first state, the first support surface is used to support the outer surface of the spacecraft shell, and the pair of clamping members are used to clamp and fix the two side edges of the spacecraft shell on the first support member;

[0011] The second fixing kit includes a second support member and an annular molding strip, the second support member has an outwardly convex second support surface, and the second support surface has a shape adapted to the corresponding position of the inner wall surface of the spacecraft shell; wherein, in the second state, the second support surface is used to support the inner wall surface of the spacecraft shell, and the annular molding strip is used to press and fix the spacecraft shell to the second support member.

[0012] Furthermore, a width of the first supporting surface and / or the second supporting surface is 3 to 10 cm.

[0013] Furthermore, the number of the first fixing kits is 4 to 8, and the interval between two adjacent first fixing kits is 40 to 80 cm.

[0014] Furthermore, the number of the second fixing sets is 4 to 10, and the interval between two adjacent second fixing sets is 30 to 60 cm.

[0015] Furthermore, the clamping member includes a U-shaped clamping block, one end of which is provided with a fastening screw, and the inner surface of the other end is fitted with a buffer gasket; the two side edges of the spacecraft shell are clamped on the first support member by the U-shaped clamping block and locked by the fastening screw.

[0016] Furthermore, the first fixing kit includes a fixing kit A, a fixing kit B, a fixing kit C, a fixing kit D and a fixing kit E arranged in sequence, wherein the fixing kit A and the fixing kit B support the first conical section, the fixing kit C supports the cylindrical section, and the fixing kit D and the fixing kit E support the second conical section.

[0017] Furthermore, the second fixing kit includes a fixing kit F, a fixing kit G, a fixing kit H, a fixing kit I, a fixing kit J and a fixing kit K arranged in sequence, wherein the fixing kit F and the fixing kit G support the first conical segment, the fixing kit H and the fixing kit I support the cylindrical segment, and the fixing kit J and the fixing kit K support the second conical segment.

[0018] Furthermore, the first support member and the second support member are both detachably fixed to the base plate.

[0019] Furthermore, the bottom plate is provided with a plurality of rows of mounting holes, and the first supporting member and the second supporting member are both fixed to the corresponding mounting holes on the bottom plate by screw locking.

[0020] Furthermore, weight-reducing holes are provided on the first support member and the second support member.

[0021] Furthermore, a reinforcing rib is provided between the second support member and the bottom plate.

[0022] A third aspect of the present invention provides a shaping method for a thin-walled spacecraft shell, comprising the following steps:

[0023] S1. The plurality of first support members are sequentially mounted on the base plate;

[0024] S2. placing the spacecraft shell on the plurality of the first support members so that its outer surface is supported on the first support surface of the first support member; then clamping and fixing the two side edges of the spacecraft shell on the first support member by a pair of clamping members;

[0025] S3. Step surfaces are provided at both sides of the inner wall of the spacecraft shell;

[0026] S4. Remove the spacecraft shell, and then remove the first support member from the base plate; and then sequentially install a plurality of the second support members on the base plate;

[0027] S5. placing the spacecraft shell on the plurality of second support members so that the inner wall surface thereof is supported on the second support surface of the second support member; then installing the annular layering strip on the second support member so that the spacecraft shell is pressed and fixed on the second support member;

[0028] S6. machining a through hole on the outer surface of the spacecraft shell;

[0029] S7. heat-treating the shaping tooling and the spacecraft shell under a protective atmosphere;

[0030] S8. Remove the spacecraft shell from the shaping tooling, and the processing is completed.

[0031] Furthermore, in step S2, after the spacecraft shell is fixed, the step of detecting whether the spacecraft shell and the first fixing kit or the second fixing kit are in close contact with each other is also included;

[0032] If the test passes, proceed to the next step;

[0033] If the detection fails, the position of the spacecraft shell or the clamping tightness of the clamping member is adjusted until the spacecraft shell and the first fixing kit are fitted together.

[0034] Furthermore, in step S5, when installing the annular pressure strip, the pressure between the annular pressure strip and the spacecraft shell is controlled to be 30-80 MPa.

[0035] Furthermore, in step S7, the protective atmosphere includes at least one of nitrogen, helium, and argon.

[0036] Furthermore, in step S7, the temperature of the heat treatment is 400-800° C., and the time of the heat treatment is 30-60 min.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. The thin-walled spacecraft shell provided by the present invention is not only light in weight and easy to assemble, but also has the characteristics of low flight resistance due to its special structural design. It also has excellent high temperature resistance and heat insulation properties, and can protect personnel and facilities in the spacecraft.

[0039] 2. The shaping and processing tooling for thin-walled spacecraft shells provided by the present invention can form two sets of different tooling components by disassembling and assembling parts, thereby realizing the fixation of the thin-walled spacecraft shell in two different states, so that the thin-walled spacecraft shell can be subjected to different processing steps in these two states.

[0040] 3. The shaping tooling for thin-walled spacecraft shells provided by the present invention adopts multiple fixing kits to support and fix the thin-walled spacecraft shells through spaced supports, which can achieve a stable fixing effect; and compared with physical tooling, the shaping tooling of the present invention greatly reduces the weight, is easy to carry, and also greatly reduces the cost.

[0041] 4. The shaping tooling for thin-walled spacecraft shells provided by the present invention adopts a spacing support method, which is convenient for processing through holes on thin-walled spacecraft shells.

[0042] 5. The shaping and processing tooling for thin-walled spacecraft shells provided by the present invention can not only fix the thin-walled spacecraft shells for mechanical punching processing, but also play a role in shaping and correcting the thin-walled spacecraft shells, thereby reducing the deformation of the thin-walled spacecraft shells and helping to improve the processing accuracy and efficiency of the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 It is a schematic diagram of the structure of a thin-walled spacecraft shell;

[0044] Figure 2 is a structural schematic diagram of a first fixing kit;

[0045] Figure 3 A schematic diagram of a thin-walled spacecraft shell being fixed to a base plate by a first fixing kit;

[0046] Figure 4 is a schematic structural diagram of a second fixing kit;

[0047] Figure 5 A schematic diagram showing a thin-walled spacecraft shell being fixed to a base plate by a second fixing kit;

[0048] Explanation of reference numerals in the figure: 100, spacecraft shell; 110, first conical section; 120, cylindrical section; 130, second conical section; 200, bottom plate; 210, reinforcing ribs; 300, first fixing kit; 310, first support member; 311, first support surface; 312, weight-reducing hole; 320, clamping member; 321, U-shaped clamping block; 322, fastening screw; 323, buffer gasket; 400, second fixing kit; 410, second support member; 411, second support surface; 412, threaded hole; 420, annular pressure strip; 421, connecting ear;

[0049] A, fixing kit A; B, fixing kit B; C, fixing kit C; D, fixing kit D; E, fixing kit E; F, fixing kit F; G, fixing kit G; H, fixing kit H; I, fixing kit I; J, fixing kit J; K, fixing kit K. DETAILED DESCRIPTION

[0050] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings and embodiments of the present invention.

[0051] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0052] See also Figure 1 The present invention provides a thin-walled spacecraft shell 100, which is in the shape of a semi-cylinder as a whole. The thin-walled spacecraft shell 100 includes a first conical section 100, a cylindrical section 120 and a second conical section 130 in sequence along the axial direction, wherein the first conical section 100, the second conical section 130 and the cylindrical section 120 are integrally formed, and the diameters of the first conical section 100 and the second conical section 130 gradually increase along the axial direction. The taper of the first conical section 100 is 0.01 to 0.1, and the taper of the second conical section 130 is 0.05 to 0.3. The thin-walled spacecraft shell 100 is made of a ceramic-based composite material, and its wall thickness is relatively small, which is 0.2 to 5 cm.

[0053] The thin-walled spacecraft shell 100 provided by the present invention is semi-cylindrical and easy to assemble. The shell is integrally formed by the first tapered section 100, the cylindrical section 120 and the second tapered section 130 in the axial direction, and the taper of the first tapered section 100 is controlled to be 0.01-0.1, and the taper of the second tapered section 130 is controlled to be 0.05-0.3, which is conducive to reducing the air resistance of the spacecraft during flight. The ceramic-based composite material is integrally formed, which is not only light in weight, but also has excellent high temperature resistance and heat insulation, which helps to protect the internal personnel and facilities of the spacecraft.

[0054] The above-mentioned thin-walled spacecraft shell is made of ceramic-based composite materials, with large size and small wall thickness. Due to the characteristics of ceramic-based composite materials, their strength is relatively low, and they are prone to deformation during clamping and processing, which will directly affect their performance; and due to the low fracture toughness of composite materials, excessive clamping force can easily break parts. In the prior art, a solid tooling with a contoured structure similar to the surface of the spacecraft shell is generally used for support and fixation, and then processing is performed, which can solve the problem of easy deformation and fracture of the shell. However, this type of solid tooling is generally heavy, generally exceeding 2 tons, inconvenient to move, and has a high cost; secondly, the subsequent processing of the spacecraft shell includes through-hole processing, and this type of solid tooling is obviously not convenient for through-hole processing; in addition, the large thin-walled spacecraft shell made of ceramic-based composite materials itself is distorted and deformed, and a shaping tooling is required later, which has low processing efficiency.

[0055] In view of the above-mentioned thin-walled spacecraft shell, the present invention also provides a shaping processing tool, which not only greatly reduces the weight and cost of the processing tool through the interval support method, but also facilitates the hole opening processing on the shell; secondly, the shaping processing tool can realize the fixation and processing of the thin-walled spacecraft shell in different states, thereby improving the processing accuracy and efficiency; in addition, the shaping processing tool can also realize the correction and shaping of the thin-walled spacecraft shell, reduce the deformation of the shell, and help improve the processing efficiency and product quality.

[0056] For details, see Figure 2-5 The shaping tooling includes a base plate 200, a plurality of first fixing kits 300 and a plurality of second fixing kits 400 alternately installed on the base plate 200, and the plurality of first fixing kits 300 and the plurality of second fixing kits 400 are installed on the base plate 200 in an interlaced arrangement.

[0057] In the present invention, the first fixing kit 300 and the second fixing kit 400 are both detachably mounted on the base plate 200, so as to facilitate assembly and disassembly, thereby achieving the fixing of the spacecraft shell 100 in different states. In some embodiments, the base plate 200 is provided with multiple rows of mounting holes, and the first support member 310 and the second support member 410 are both fixed to the corresponding mounting holes on the base plate 200 by screw locking. It can be understood that the first support member 310 and the second support member 410 can also be fixed to the base plate 200 by other detachable methods, and the present invention is not limited to this.

[0058] In the present invention, the first fixing kit 300 and the second fixing kit 400 are alternately installed on the base plate 200, that is, the first fixing kit 300 and the second fixing kit 400 are not installed on the base plate 200 at the same time. When the first fixing kit 300 is installed on the base plate 200, a first set of shaping tooling is obtained, which can fix the spacecraft shell 100 in a first state; when the second fixing kit 400 is installed on the base plate 200, a second set of shaping tooling is obtained, which can fix the spacecraft shell 100 in a second state.

[0059] See also Figure 2-3 The first fixing kit 300 includes a first support member 310 and a pair of clamping members 320. The first support member 310 has a concave first support surface 311, and the first support surface 311 has a shape that matches the corresponding position of the outer surface of the spacecraft shell 100, so that the first support surface 311 can fit tightly with the outer surface of the spacecraft shell 100. Since there are multiple first support members 310, and they are arranged in sequence on the bottom plate 200, the spacecraft shell 100 can be stably supported on the bottom plate 200 through multiple first support members 310, and its outer surface can fit tightly with the first support surface 311. Then, by clamping the clamping members 320, the two side edges of the spacecraft shell 100 can be clamped and fixed on the corresponding first support members 310, so that the spacecraft shell 100 is fixed in the first state.

[0060] Since the spacecraft shell 100 generally has a relatively complex revolution surface, its radius at different positions is not the same. It can be understood that in the plurality of first support members 310, the shape of each first support surface 311 is designed according to the corresponding position of the spacecraft shell 100, so the radius of its arc surface is also different.

[0061] See also Figure 2In some embodiments of the present invention, the clamping member 320 includes a U-shaped clamping block 321, and a fastening screw 322 is inserted into one end of the U-shaped clamping block 321. The two side edges of the spacecraft shell 100 can be clamped on the first support member 310 by the U-shaped clamping block 321 and locked by the fastening screw 322. Preferably, a buffer gasket 323 is attached to the inner surface of the other end of the U-shaped clamping block 321, and the buffer gasket 323 can make the U-shaped clamping block 321 more closely fit the inner wall surface of the thin-walled spacecraft shell 100, thereby obtaining a better clamping and fixing effect; at the same time, the presence of the buffer gasket 323 can also reduce the damage of the rigid U-shaped clamping block 321 to the thin-walled spacecraft shell 100. The buffer gasket 323 can be made of various elastic materials, including but not limited to rubber, latex, foam, etc.

[0062] In some embodiments of the present invention, in order to reduce the weight of the shaping tooling, at least one weight-reducing hole 312 is provided on the first support member 310. In other embodiments, a reinforcing rib 210 is provided between the first support member 310 and the bottom plate 200 to enhance the supporting capacity of the first support member 310 and improve the supporting stability during subsequent processing.

[0063] See also Figure 4-5 , the second fixing kit 400 includes a second support member 410 and an annular bead 420. Among them, the second support member 410 has an outwardly convex second support surface 411, and the second support surface 411 has a shape that matches the corresponding position of the inner wall surface of the spacecraft shell 100, so that the second support surface 411 can fit tightly with the inner wall surface of the spacecraft shell 100. Similarly, since there are multiple second support members 410, and they are arranged in sequence on the base plate 200, the spacecraft shell 100 can be stably supported on the base plate 200 through multiple second support members 410, and its inner wall surface is closely fitted with the second support surface 411. Then, the spacecraft shell 100 can be pressed and fixed on the second support member 410 through the annular bead 420, so that the spacecraft shell 100 is fixed in the second state. It can be understood that the annular pressure strip 420 has an inwardly concave arc surface matching the outer surface of the spacecraft shell 100 , so that the spacecraft shell 100 can be tightly pressed onto the second support member 410 .

[0064] See also Figure 4 In some embodiments of the present invention, the second support member 410 is provided with threaded holes 412 on both sides of the second support surface 411, and the two ends of the annular pressure strip 420 are provided with integrally formed connecting ears 421, and the connecting ears 421 are locked to the second support member 410 by fixing members such as screws. It can be understood that the annular pressure strip 420 can also be fixed to the second support member 410 in other ways, and the present invention is not limited to this.

[0065] In some embodiments of the present invention, in order to reduce the weight of the shaping tooling, at least one weight-reducing hole 312 is provided on the second support member 410. In other embodiments, a reinforcing rib 210 is provided between the second support member 410 and the bottom plate 200 to enhance the supporting capacity of the second support member 410 and improve the supporting stability during subsequent processing.

[0066] In some embodiments of the present invention, in order to obtain a better supporting effect on the thin-walled spacecraft shell 100, the first supporting surface 311 and the second supporting surface 411 need to have a certain width. The width is preferably 3 to 10 cm, for example, 3 cm, 4 cm, 5 cm, 6 cm, 7 cm, 8 cm, 9 cm, 10 cm, etc.

[0067] In order to achieve a stable fixed support effect on the thin-walled spacecraft shell, the number of first fixing kits 300 is preferably 4 to 8, and the spacing distance between two adjacent first fixing kits 300 is preferably 40 to 80 cm. Further, the number of first fixing kits 300 is preferably set to 5. Specifically, in this embodiment, the first fixing kit 300 includes a fixing kit A, a fixing kit B, a fixing kit C, a fixing kit D and a fixing kit E arranged in sequence. Among them, the fixing kit A and the fixing kit B support the first conical section 100, the fixing kit C supports the cylindrical section 120, and the fixing kit D and the fixing kit E support the second conical section 130.

[0068] Similarly, in order to achieve a good fixed support effect, in some embodiments of the present invention, the number of the second fixing kits 400 is 4 to 10, and the interval between two adjacent second fixing kits 400 is 30 to 60 cm. Further, the number of the second fixing kits 400 is preferably set to 6. Specifically, in this embodiment, the second fixing kit 400 includes a fixing kit F, a fixing kit G, a fixing kit H, a fixing kit I, a fixing kit J and a fixing kit K arranged in sequence. Among them, the fixing kit F and the fixing kit G support the first conical section 100, the fixing kit H and the fixing kit I support the cylindrical section 120, and the fixing kit J and the fixing kit K support the second conical section 130.

[0069] The present invention also provides a shaping method for a thin-walled spacecraft shell, the shaping method uses the above-mentioned shaping tooling and comprises the following steps:

[0070] S1. The plurality of first support members are sequentially mounted on the base plate;

[0071] S2. placing the spacecraft shell on the plurality of the first support members so that its outer surface is supported on the first support surface of the first support member; then clamping and fixing the two side edges of the spacecraft shell on the first support member by a clamping member;

[0072] S3. Step surfaces are provided at both sides of the inner wall of the spacecraft shell;

[0073] S4. Remove the spacecraft shell, and then remove the first support member from the base plate; and then sequentially install a plurality of the second support members on the base plate;

[0074] S5. placing the spacecraft shell on the plurality of second support members so that the inner wall surface thereof is supported on the second support surface of the second support member; then installing the annular layering strip on the second support member so that the spacecraft shell is pressed and fixed on the second support member;

[0075] S6. machining a through hole on the outer surface of the spacecraft shell;

[0076] S7. heat-treating the shaping tooling and the spacecraft shell under a protective atmosphere;

[0077] S8. Remove the spacecraft shell from the shaping tooling, and the processing is completed.

[0078] In the above step S2, due to the characteristics of the ceramic-based composite material itself, it is very easy to deform. Therefore, when fixing the spacecraft shell, it is necessary to first place it on the first support member, and apply force to make its outer surface completely fit with the first support surface of the first support member, and then lock it with the clamping member.

[0079] Before processing, it is necessary to ensure that the surface of the fixed spacecraft shell is directly and tightly fitted with the first support surface without any gap, so that the spacecraft shell is not easy to shake or deform during the processing, which is conducive to improving the processing accuracy. Therefore, in a preferred embodiment, after the spacecraft shell is fixed, first check whether the spacecraft shell and the first fixing kit are tightly fitted; if the test passes, proceed to the next step; if the test fails, the gap between the spacecraft shell and the first fixing kit can be adjusted by adjusting the position of the spacecraft shell on the first support, the tightness of the clamping member, etc., until the spacecraft shell and the first fixing kit are tightly fitted. In a feasible embodiment, the "paper insertion method" or vernier caliper can be used to detect whether the spacecraft shell and the first fixing kit are tightly fitted.

[0080] In the above step S5, when installing the annular bead, it is preferred to control the pressure between it and the spacecraft shell to be 30-80MPa. For example, the pressure can be controlled to be 30MPa, 40MPa, 50MPa, 60MPa, 70MPa, 80MPa, etc. This pressure value range can not only produce a good fixing effect on the spacecraft shell, but also facilitate the subsequent shaping of the spacecraft shell. In some embodiments, multiple pressure sensors can be set on the inner wall of the annular bead, and the tested pressure value is calculated to obtain an average pressure value, which is the pressure on the spacecraft shell. During the fixing process, the pressure on the spacecraft shell can be controlled by adjusting the tightness of the screws on the annular bead.

[0081] In the above step S6, the shaping tooling of the present invention adopts an interval support method. When through-hole processing is performed on the outer surface of the spacecraft shell, the intervally arranged second support members will not hinder the movement of the drill bit, which is conducive to processing through-holes on the spacecraft shell.

[0082] In the above step S7, the inventors found that applying a certain pressure to the spacecraft shell under a protective atmosphere and cooperating with heat treatment can fully release the internal stress of the ceramic-based composite material, reduce internal defects, and change the unevenness of the internal structure, thereby helping to reduce the deformation of the spacecraft shell and maintain its structural stability. The presence of a protective atmosphere can reduce the oxidation of the ceramic-based composite material during the heat treatment process and avoid the degradation of the physical and chemical properties of the ceramic-based composite material. The protective atmosphere includes but is not limited to at least one of nitrogen, helium, and argon.

[0083] Further, in step S7, the temperature of the heat treatment is preferably 400-800°C, for example, 400°C, 450°C, 500°C, 550°C, 600°C, 650°C, 700°C, 750°C, 800°C, etc.; the holding time of the heat treatment is 30-60min, for example, 30min, 35min, 40min, 45min, 50min, 55min, 60min, etc. A heat treatment temperature that is too high or too low is not good for the shaping effect. If the temperature is too low, a good shaping effect cannot be achieved; if the temperature is too high, due to the limited thermal conductivity of the ceramic-based composite material, a large temperature gradient will generate thermal stress inside the material, thereby causing deformation.

[0084] Furthermore, in step S7, during the heat treatment process, the heating and cooling rates cannot be too fast. If the rates are too fast, thermal stress accumulation is likely to occur inside the material, thereby causing deformation. Preferably, the heating and cooling rates need to be controlled within 1°C / min.

[0085] After the shaping process of the present invention is performed, the deformation of the spacecraft shell can be controlled within 0.5%.

[0086] In summary, the shaping tooling provided by the present invention can realize the fixation of the thin-walled spacecraft shell in two different states, and the fixing effect is good, which is beneficial to improving the processing accuracy and efficiency; secondly, compared with the physical tooling, the shaping tooling is light in weight and low in cost, and it is also convenient for performing hole opening processing on the shell; thirdly, the use of the shaping tooling can realize the hole processing and correction shaping of the spacecraft shell, which is beneficial to improving the processing efficiency and product quality.

[0087] The above-described embodiments are only preferred embodiments for fully illustrating the present invention, and the protection scope of the present invention is not limited thereto. Equivalent substitutions or changes made by those skilled in the art based on the present invention are within the protection scope of the present invention. The protection scope of the present invention shall be subject to the claims.

Claims

1. A thin-walled spacecraft shell, characterized in that: The thin-walled spacecraft shell is semi-cylindrical, and includes a first conical section, a cylindrical section and a second conical section in sequence along the axial direction; the first conical section, the second conical section and the cylindrical section are integrally formed, and are all made of ceramic-based composite materials; the wall thickness of the thin-walled spacecraft shell is 0.2 to 5 cm; the taper of the first conical section is 0.01 to 0.1, and the taper of the second conical section is 0.05 to 0.

3.

2. A shaping tool, characterized in that: The shaping tooling is used for fixing and shaping the thin-walled spacecraft shell as described in claim 1; the shaping tooling includes a base plate, a plurality of first fixing kits and a plurality of second fixing kits alternately installed on the base plate, and the plurality of first fixing kits and the plurality of second fixing kits are all installed on the base plate in an interlaced arrangement; the first fixing kit is used to fix the spacecraft shell in a first state, and the second fixing kit is used to fix the spacecraft shell in a second state.

3. A shaping tool according to claim 2, characterized in that: The first fixing kit includes a first support member and a pair of clamping members, the first support member has a concave first support surface, and the first support surface has a shape that matches the corresponding position of the outer surface of the spacecraft shell; wherein, in the first state, the first support surface is used to support the outer surface of the spacecraft shell, and the pair of clamping members are used to clamp and fix the two side edges of the spacecraft shell on the first support member; The second fixing kit includes a second support member and an annular molding strip, the second support member has an outwardly convex second support surface, and the second support surface has a shape adapted to the corresponding position of the inner wall surface of the spacecraft shell; wherein, in the second state, the second support surface is used to support the inner wall surface of the spacecraft shell, and the annular molding strip is used to press and fix the spacecraft shell to the second support member.

4. A shaping tool according to claim 3, characterized in that: The width of the first supporting surface and / or the second supporting surface is 3 to 10 cm; and / or, The number of the first fixing sets is 4 to 8, and the distance between two adjacent first fixing sets is 40 to 80 cm; and / or, The number of the second fixing sets is 4 to 10, and the interval between two adjacent second fixing sets is 30 to 60 cm.

5. A shaping tool according to claim 3, characterized in that: The clamping member includes a U-shaped clamping block, one end of which is penetrated by a fastening screw, and the inner surface of the other end is fitted with a buffer gasket; the two side edges of the spacecraft shell are clamped on the first support member by the U-shaped clamping block and locked by the fastening screw.

6. The shaping tool for thin-walled spacecraft shell according to claim 1, characterized in that: The first support member and the second support member are provided with weight-reducing holes; and / or, A reinforcing rib is provided between the second supporting member and the bottom plate.

7. A shaping method for a thin-walled spacecraft shell according to claim 1, characterized in that: The shaping method adopts the shaping tooling according to any one of claims 2 to 6, and comprises the following steps: S1. The plurality of first support members are sequentially mounted on the base plate; S2. placing the spacecraft shell on the plurality of the first support members so that its outer surface is supported on the first support surface of the first support member; then clamping and fixing the two side edges of the spacecraft shell on the first support member by a clamping member; S3. Step surfaces are provided at both sides of the inner wall of the spacecraft shell; S4. Remove the spacecraft shell, and then remove the first support member from the base plate; and then sequentially install a plurality of the second support members on the base plate; S5. placing the spacecraft shell on the plurality of second support members so that the inner wall surface thereof is supported on the second support surface of the second support member; then installing the annular layering strip on the second support member so that the spacecraft shell is pressed and fixed on the second support member; S6. machining a through hole on the outer surface of the spacecraft shell; S7. heat-treating the shaping tooling and the spacecraft shell under a protective atmosphere; S8. Remove the spacecraft shell from the shaping tooling, and the processing is completed.

8. A shaping method for a thin-walled spacecraft shell according to claim 7, characterized in that: In step S2, after the spacecraft shell is fixed, the step of detecting whether the spacecraft shell and the first fixing kit or the second fixing kit are in close contact with each other is also included; If the test passes, proceed to the next step; If the detection fails, the position of the spacecraft shell or the clamping tightness of the clamping member is adjusted until the spacecraft shell and the first fixing kit are fitted together.

9. A shaping method for a thin-walled spacecraft shell according to claim 7, characterized in that: In step S5, when installing the annular pressure strip, the pressure between the annular pressure strip and the spacecraft shell is controlled to be 30-80 MPa.

10. A shaping method for a thin-walled spacecraft shell according to claim 7, characterized in that: In step S7, the protective atmosphere includes at least one of nitrogen, helium and argon; and / or, The temperature of the heat treatment is 400-800° C., and the insulation time of the heat treatment is 30-60 minutes.

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