Spacecraft interface component and method of manufacture

Abstract

The application relates to the technical field of aerospace component structure design, in particular to an aerospace interface component and a manufacturing method. The aerospace interface component comprises a skin, a first boss arranged on the skin, a plurality of second bosses arranged on the skin, a plurality of reinforcing ribs arranged on the skin, the first boss and the plurality of second bosses being connected through the reinforcing ribs, the plurality of reinforcing ribs being connected with each other in a cross mode, first fillets being arranged at the connecting positions of the reinforcing ribs and the skin, the connecting positions of the first boss and the skin, and the connecting positions of the second bosses and the skin, the skin, the first boss, the plurality of second bosses and the plurality of reinforcing ribs being made of carbon fiber composite materials. The aerospace interface component is made through the first fillet structure design and the carbon fiber composite materials, the continuity of the fibers of the aerospace interface component is ensured, the machining time is shortened by 85%, the material utilization rate reaches 90%, and the specific rigidity and the specific strength are higher than those of metal parts.

Description

Technical Field

[0001] This invention relates to the field of aerospace component structural design technology, specifically to an aerospace interface component and its manufacturing method. Background Technology

[0002] An existing type of aerospace interface component, such as Figure 1 As shown, it includes: a skin 1, a first boss 3 and five second bosses 4 disposed on the skin 1, and a plurality of reinforcing ribs 2 disposed on the skin 1; the skin 1 is circular, and one of the five second bosses 4 is located at the center of the skin 1; the first boss 3 and the five second bosses 4 are connected by the plurality of reinforcing ribs 2; the height of the five second bosses 4 is the same as the height of the plurality of reinforcing ribs 2, and the height of the first boss 3 is higher than the height of the second bosses 4; a first machining hole 5 is provided at the center of the first boss 3 and the five second bosses 4, and a plurality of second machining holes 6 are respectively provided on the first boss 3 and the five second bosses 4 around the first machining hole 5. The above-mentioned aerospace interface component is a metal machined part, which has a long machining time and low material utilization rate during processing. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defects of aerospace interface components being metal machined parts, which have long machining time and low material utilization during processing.

[0004] To overcome the above-mentioned defects, the present invention provides an aerospace interface component, comprising:

[0005] Skin;

[0006] A first protrusion is provided on the skin;

[0007] Multiple second protrusions are disposed on the skin; a first machining hole is provided at the center of each of the first and second protrusions; around the first machining hole, multiple second machining holes are also provided on the first protrusion and the multiple second protrusions respectively.

[0008] Multiple reinforcing ribs are disposed on the skin, and the first boss and multiple second bosses are connected by the reinforcing ribs; the multiple reinforcing ribs are interconnected; the height of the multiple second bosses is the same as the height of the multiple reinforcing ribs, and the height of the first boss is higher than the height of the second bosses; a first rounded corner is provided at the connection between the reinforcing ribs and the skin, the connection between the first boss and the skin, and the connection between the second bosses and the skin; the skin, the first boss, the multiple second bosses, and the multiple reinforcing ribs are all made of carbon fiber composite material.

[0009] Optionally, a second fillet is provided at the intersections of multiple reinforcing ribs, at the connection between the reinforcing rib and the first boss, and at the connection between the reinforcing rib and the second boss.

[0010] Optionally, the first outer sidewall of the first and second bosses respectively inclines to the respective center, and the angle between the first outer sidewall and the skin surface is greater than 90 degrees.

[0011] Optionally, the second outer sidewall of the stiffener respectively inclines to the respective axis, and the angle between the second outer sidewall and the skin surface is greater than 90 degrees.

[0012] Optionally, the radius of the first fillet is 2 mm.

[0013] Optionally, the radius of the second fillet is 5 mm.

[0014] Optionally, the angle between the first outer sidewall and the skin surface is 94.5 degrees; and the angle between the second outer sidewall and the skin surface is 94.5 degrees.

[0015] The application also provides a manufacturing method of the aerospace interface component, comprising:

[0016] Preparation of prepreg;

[0017] Blanking of the prepreg;

[0018] Cleaning of the mold, which is a female mold;

[0019] Laying of the prepreg in the mold;

[0020] Putting the prepreg laid in the mold into a sealed bag;

[0021] Vacuumizing of the sealed bag;

[0022] Curing;

[0023] Demolding and cleaning;

[0024] Cutting of the first and second machining holes;

[0025] Polishing of the surface of the aerospace interface component.

[0026] Optionally, the laying of the prepreg in the mold comprises:

[0027] Laying of a whole layer of prepreg on the mold;

[0028] Laying of a first part of prepreg on the mold corresponding to the region of the first boss;

[0029] When the height of the first part of prepreg is flush with the height of the stiffener, laying of a second part of prepreg on the mold corresponding to the regions of the stiffener, the first boss and the second boss;

[0030] When the height of the first part of prepreg is flush with the height of the skin, laying of a third part of prepreg on the mold until the thickness of the skin is reached.

[0031] Optionally, when laying the first, second and third portions of prepreg, a vacuum is drawn once for every three layers of prepreg laid.

[0032] The above technical solutions of the present application have the following advantages compared with the prior art:

[0033] 1. The aerospace interface part provided by the present application comprises: a skin; a first boss provided on the skin; a plurality of second bosses provided on the skin; a first machining hole is provided at the center of each of the first boss and the second bosses; a plurality of second machining holes are further provided on the first boss and the plurality of second bosses around the first machining hole; a plurality of reinforcing ribs are provided on the skin, and the first boss and the plurality of second bosses are connected by the reinforcing ribs; the plurality of reinforcing ribs are connected to each other; the height of the plurality of second bosses is the same as the height of the plurality of reinforcing ribs, and the height of the first boss is higher than the height of the second boss; a first fillet is provided at the connection between the reinforcing rib and the skin, the connection between the first boss and the skin, and the connection between the second boss and the skin; the skin, the first boss, the plurality of second bosses and the plurality of reinforcing ribs are all made of carbon fiber composite material; the above technical solutions are adopted in the present application, the carbon fiber composite material is used to make the aerospace interface part through the design of the first fillet structure, and the continuity of the fiber of the aerospace interface part is ensured; the machining time is shortened by 85%, the material utilization rate reaches 90%, the weight is reduced by 48.8%, and the specific degree and the specific strength are higher than those of metal parts; compared with the aerospace interface part made of aluminum alloy or titanium alloy, the density of the carbon fiber composite material is 59.2% of the density of the aluminum alloy, and the density of the carbon fiber composite material is 33.5% of the density of the titanium alloy; thus, the weight of the product is reduced, and the carrying capacity of the aerospace launch vehicle is greatly improved.

[0034] 2. A second fillet is provided at the connection between the plurality of reinforcing ribs, the connection between the reinforcing rib and the first boss, and the connection between the reinforcing rib and the second boss; the above technical solutions are adopted in the present application, and the continuity of the fiber of the aerospace interface part is further ensured.

[0035] 3. The first outer side wall of the first boss and the second boss respectively inclines to the center thereof, and the angle between the first outer side wall and the surface of the skin is greater than 90 degrees; the above technical solutions are adopted in the present application, which is beneficial to the demolding of the molded aerospace interface part.

[0036] 4. The second outer side wall of the reinforcing rib respectively inclines to the axis thereof, and the angle between the second outer side wall and the surface of the skin is greater than 90 degrees; the above technical solutions are adopted in the present application, which is beneficial to the demolding of the molded aerospace interface part.

[0037] 5. The method for manufacturing the aerospace interface component provided by the application comprises the following steps: preparing a prepreg; blanking the prepreg; cleaning a mold, which is a female mold; laying up the prepreg in the mold; placing the prepreg laid up in the mold into a sealed bag; vacuumizing the sealed bag; curing; demolding and cleaning; cutting a first processing hole and a second processing hole; and polishing the surface of the aerospace interface component. The machining time is shortened by 85%, the material utilization rate reaches 90%, the weight is reduced by 48.8%, and the specific degree and the specific strength are higher than those of the metal piece. Compared with the aerospace interface component made of aluminum alloy or titanium alloy, the density of the carbon fiber composite material is 59.2% of the density of the aluminum alloy, and the density of the carbon fiber composite material is 33.5% of the density of the titanium alloy, so that the weight of the product is reduced, and the carrying weight of the aerospace lifter is greatly improved.

[0038] 6. The laying up of the prepreg in the mold comprises the following steps: laying up a whole layer of the prepreg on the mold; laying up a first part of the prepreg on the mold at a region corresponding to the first boss; when the height of the first part of the prepreg is flush with the height of the reinforcing rib, laying up a second part of the prepreg on the mold at a region corresponding to the reinforcing rib, the first boss and the second boss; and when the height of the first part of the prepreg is flush with the height of the skin, laying up a third part of the prepreg on the mold until the thickness of the skin is reached. The continuity of the fibers of the aerospace interface component is realized through the continuous laying up of the prepreg, so that higher strength and rigidity are obtained.

[0039] 7. When the first part of the prepreg, the second part of the prepreg and the third part of the prepreg are laid up, a vacuum is extracted once every three layers of the prepreg. The close adhesion between the layers of the prepreg is ensured, and the quality of the aerospace interface component is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0040] In order to more clearly illustrate the specific embodiments of the application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the specific embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can also be obtained by those skilled in the art without any creative labor.

[0041] Figure 1 It is a schematic diagram of the three-dimensional structure of the aerospace interface component in the prior art.

[0042] Figure 2 It is a schematic diagram of the three-dimensional structure of the aerospace interface component provided in the embodiment of the application.

[0043] Explanation of reference signs:

[0044] 1. Skin; 2. Reinforcing rib; 3. First boss; 4. Second boss; 5. First machining hole; 6. Second machining hole; 7. First fillet; 8. Second fillet. Detailed Implementation

[0045] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0046] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0047] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0048] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0049] like Figure 2 One specific embodiment of the aerospace interface component shown includes: a skin 1, a first boss 3 and five second bosses 4 disposed on the skin 1, and a plurality of reinforcing ribs 2 disposed on the skin 1.

[0050] The first boss 3 is arranged on the skin 1, and the skin 1 is circular. Five second bosses 4 are arranged on the skin 1, and a first machining hole 5 is arranged at the center of the first boss 3 and the second boss 4. One of the five second bosses 4 is located at the center of the skin 1. A plurality of second machining holes 6 are arranged around the first machining hole 5 on the first boss 3 and the five second bosses 4. Specifically, the first boss 3 and the five second bosses 4 are square. A plurality of reinforcing ribs 2 are arranged on the skin 1, and the first boss 3 and the five second bosses 4 are connected by the reinforcing ribs 2. The plurality of reinforcing ribs 2 are connected by crossing. The height of the five second bosses 4 is the same as the height of the plurality of reinforcing ribs 2, and the height of the first boss 3 is higher than the height of the second boss 4. A first fillet 7 is arranged at the connection between the reinforcing rib 2 and the skin 1, the connection between the first boss 3 and the skin 1, and the connection between the second boss 4 and the skin 1. Specifically, the radius of the first fillet 7 is 2 mm. The skin 1, the first boss 3, the five second bosses 4 and the plurality of reinforcing ribs 2 are all made of carbon fiber composite material. A second fillet 8 is arranged at the connection between the plurality of reinforcing ribs 2, the connection between the reinforcing rib 2 and the first boss 3, and the connection between the reinforcing rib 2 and the second boss 4. Specifically, the radius of the second fillet 8 is 5 mm. The first outer side wall of the first boss 3 and the second boss 4 respectively inclines to the center thereof, and the angle between the first outer side wall and the surface of the skin 1 is greater than 90 degrees. The second outer side wall of the reinforcing rib 2 respectively inclines to the axis thereof, and the angle between the second outer side wall and the surface of the skin 1 is greater than 90 degrees. Specifically, the angle between the first outer side wall and the surface of the skin 1 is 94.5 degrees, and the angle between the second outer side wall and the surface of the skin 1 is 94.5 degrees.

[0051] After the above technical scheme is adopted, the weight of the aerospace interface part is 2.5 kg. The weight of the aerospace interface part in the form of an aluminum part is 4.01 kg, and the weight of the aerospace interface part in the form of a titanium alloy part is 6.824 kg. The weight reduction of the technical scheme of the present application is 48.8% and 63.3%, respectively.

[0052] The present application also provides a manufacturing method of the aerospace interface part, comprising the following steps:

[0053] S1, preparing a prepreg;

[0054] S2, cutting the prepreg;

[0055] S3, cleaning the mold, and the mold is a concave mold;

[0056] S4, laying up the prepreg in the mold;

[0057] S5, putting the prepreg laid up in the mold into a sealed bag;

[0058] S6, vacuumizing the sealed bag;

[0059] S7, curing, specifically, curing by autoclave;

[0060] S8, demolding and cleaning;

[0061] S9, cutting the first machining hole 5 and the second machining hole 6;

[0062] S10, polishing the surface of the aerospace interface component.

[0063] Finally, the polished aerospace interface component is subjected to quality inspection.

[0064] Specifically, the step S4 comprises the following steps:

[0065] S41, laying a first layer of prepreg on the mold;

[0066] S42, laying a first part of prepreg on the mold at the region corresponding to the first boss 3;

[0067] S43, when the height of the first part of prepreg is flush with the height of the reinforcing rib 2, laying a second part of prepreg on the mold at the region corresponding to the reinforcing rib 2, the first boss 3 and the second boss 4;

[0068] S44, when the height of the first part of prepreg is flush with the height of the skin 1, laying a third part of prepreg on the mold until the thickness of the skin 1 is reached.

[0069] Further, when laying the first part of prepreg, the second part of prepreg and the third part of prepreg, vacuumizing is performed once every three layers of prepreg.

[0070] Obviously, the above-mentioned embodiments are only examples for the purpose of clarity, and are not intended to limit the embodiments. Based on the above description, other different forms of changes or variations can be made by those of ordinary skill in the art. Here, it is not necessary and impossible to exhaust all the embodiments. The obvious changes or variations derived therefrom are still within the protection scope of the present application.

Claims

1. A method for manufacturing a spaceflight interface component, the spaceflight interface component comprising: a skin (1); a first boss (3) disposed on the skin (1); a plurality of second bosses (4) disposed on the skin (1); a first machining hole (5) disposed at the center of each of the first boss (3) and the second boss (4); a plurality of second machining holes (6) disposed on the first boss (3) and the plurality of second bosses (4) around the first machining hole (5); and a plurality of reinforcing ribs (2) disposed on the skin (1), the first boss (3) and the plurality of second bosses (4) being connected by the reinforcing ribs (2), the plurality of reinforcing ribs (2) being connected to each other, the height of the plurality of second bosses (4) being the same as the height of the plurality of reinforcing ribs (2), and the height of the first boss (3) being higher than the height of the second boss (4), wherein the first boss (3) and the plurality of second bosses (4) are made of carbon fiber composite material, and wherein the first boss (3) and the second boss (4) each have a first outer sidewall that is inclined toward the center of the first boss (3) and the second boss (4), respectively, and the angle between the first outer sidewall and the surface of the skin (1) is greater than 90 degrees.

2. The method of claim 1, wherein the method comprises: preparing a prepreg; cutting the prepreg; cleaning a mold; laying up the prepreg in the mold; placing the prepreg laid up in the mold into a sealed bag; vacuumizing the sealed bag; curing; demolding and cleaning; cutting the first machining hole (5) and the second machining hole (6); and polishing the surface of the spaceflight interface component.

3. The method of claim 1, wherein the laying up the prepreg in the mold comprises: laying up a first layer of the prepreg on the mold; laying up a first portion of the prepreg on the mold corresponding to the first boss (3); when the height of the first portion of the prepreg is the same as the height of the reinforcing rib (2), laying up a second portion of the prepreg on the mold corresponding to the reinforcing rib (2), the first boss (3) and the second boss (4); and when the height of the first portion of the prepreg is the same as the height of the skin (1), laying up a third portion of the prepreg on the mold until the thickness of the skin (1) is reached.

4. The method of claim 1, wherein the first boss (3) and the plurality of second bosses (4) each have a first outer sidewall that is inclined toward the center of the first boss (3) and the second boss (4), respectively, and the angle between the first outer sidewall and the surface of the skin (1) is 94.5 degrees.

5. The method of claim 1, wherein the reinforcing rib (2) has a second outer sidewall that is inclined toward the axis of the reinforcing rib (2), and the angle between the second outer sidewall and the surface of the skin (1) is 94.5 degrees.

6. The method of claim 1, wherein the radius of the first fillet (7) is 2 mm, and the radius of the second fillet (8) is 5 mm.

7. The method of claim 1, wherein a vacuum is extracted once every three layers of the prepreg when laying up the first portion of the prepreg, the second portion of the prepreg and the third portion of the prepreg. ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ 2. The method of manufacturing a spaceflight interface component of claim 1, wherein, ​ 3. The method of claim 1, wherein ​ 4. The method of claim 1-3, wherein ​ 5. The method of claim 2, wherein ​ 6. The method of claim 3, wherein ​ 7. The method of claim 1, wherein ​

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