Satellite supporting cabin and fairing of space launch vehicle

Abstract

The satellite supporting cabin comprises an upper end frame, a truncated cone shell and a lower end annular flange which are integrally formed by carbon fiber composite materials, the upper end frame is formed by wrapping a first foam sandwich with the carbon fiber composite materials and solidifying the first foam sandwich, and the upper end frame is used for being connected with a satellite support. The lower end annular flange is used for being connected with a substage of an aerospace vehicle. The satellite supporting cabin can achieve the purpose of reducing the weight and has high rigidity.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aerospace vehicle fairing, specifically relates to a satellite support cabin of aerospace vehicle. BACKGROUND

[0002] At present, the satellite support cabin of aerospace vehicle is mostly prepared from metal material, its weight is big and transportation is difficult, along with the size of aerospace vehicle upgrading, the heavy weight of satellite support cabin will affect the launch efficiency of aerospace vehicle.

[0003] Therefore, it is urgent to design a satellite support cabin of aerospace vehicle which is light in weight and meets the stiffness requirement. SUMMARY

[0004] The utility model discloses a satellite support cabin of aerospace vehicle and fairing which overcome the defects of the prior art.

[0005] The utility model provides a satellite support cabin of aerospace vehicle, including carbon fiber composite material integrated molding's upper end frame, truncated cone shell, lower end ring flange, the upper end frame adopts carbon fiber composite material to be wrapped first foam sandwich and is cured to form, the upper end frame is used for connecting satellite support, and the lower end ring flange is used for connecting the sublevel of aerospace vehicle.

[0006] According to one embodiment of the utility model, the thickness of the truncated cone shell increases continuously along the direction of the truncated cone shell generatrix towards the upper end frame and close to the transition zone of the upper end frame.

[0007] According to one embodiment of the utility model, the connecting surface of the lower end ring flange is perpendicular to the flange axis, and in the direction of radially away from the outside of the truncated cone shell, the connecting surface thickness of the lower end ring flange increases continuously.

[0008] According to one embodiment of the utility model, the upper end frame is cylindrical, the upper end frame is divided into inner frame and outer frame, and the length of the outer frame is greater than the length of the inner frame.

[0009] According to one embodiment of the utility model, the first foam sandwich is arranged in the space surrounded by the skin on the inner side of the truncated cone shell, and the shape of the cross section of the first foam sandwich is trapezoidal.

[0010] According to one embodiment of the utility model, the satellite support cabin of aerospace vehicle further comprises a plurality of long bars arranged on the inner wall of the truncated cone shell in the circumferential direction, and each long bar is arranged on the inner wall in the direction of the truncated cone shell generatrix.

[0011] According to one embodiment of the present application, the long string is wrapped with carbon fiber composite material and the second foam sandwich is formed.

[0012] According to one embodiment of the present application, the long string is wrapped with carbon fiber composite material and the second foam sandwich is formed.

[0013] According to one embodiment of the present application, the upper end frame, the truncated cone shell and the lower end annular flange are integrally formed by laying carbon fiber unidirectional tape prepreg on the mold.

[0014] On the other hand, the present application also provides a fairing, which comprises the satellite support cabin of the space vehicle of any one of the above.

[0015] The satellite support cabin of the space vehicle of the present application can effectively enhance the overall strength and stiffness of the support cabin by adopting carbon fiber composite material and foam sandwich to form the upper end frame, the truncated cone shell and the lower end annular flange.

[0016] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the scope of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0017] The following drawings are part of the specification of the present application, which illustrate the example embodiments of the present application, and the accompanying drawings and the description of the specification are used to illustrate the principles of the present application.

[0018] Figure 1 is a schematic view of the satellite support cabin of the space vehicle of one embodiment of the present application;

[0019] Figure 2 is a cross-sectional view of the upper end frame in the satellite support cabin of the space vehicle of one embodiment of the present application;

[0020] Figure 3 is a cross-sectional view of the lower end annular flange in the satellite support cabin of the space vehicle of one embodiment of the present application;

[0021] Figure 4 is a schematic view of the satellite support cabin of the space vehicle of another embodiment of the present application;

[0022] Figure 5 is a cross-sectional view of the long string in the satellite support cabin of the space vehicle of one embodiment of the present application;

[0023] Figure 6 is a schematic view of the forming mold for manufacturing the satellite support cabin of the space vehicle of one embodiment of the present application.

[0024] Reference signs:

[0025] 100 - upper end frame, 200 - truncated cone housing, 300 - lower end annular flange, 400 - first foam core, 500 - longeron, 600 - second foam core, 701 - first forming zone, 702 - second forming zone, 703 - third forming zone. DETAILED DESCRIPTION

[0026] The features and exemplary embodiments of each aspect of the present application will be described below in detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely configured to explain the present application and to illustrate the principles of the present application, and are not configured to limit the present application. In addition, the components in the drawings are not necessarily drawn to scale. For example, the size of some components in the drawings can be enlarged for other components or regions to help understand the embodiments of the present application.

[0027] In the following description, the orientation words appearing in the description are the directions shown in the drawings, and are not limited to the specific structure of the embodiments of the present application. In the description of the present application, it should be noted that, unless otherwise specified, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrally connected; it can be directly connected, or it can be indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0028] In addition, the terms "including", "containing", "having" or any other variant thereof are intended to cover non-exclusive inclusion, so that the inclusion of a series of element structures or components not only includes those elements, but also includes other elements not explicitly listed or inherent in the structure, component. Without more limitations, the elements defined by the statement "including" do not exclude the presence of other identical elements in the article or device including the elements.

[0029] Spatially relative terms such as "under", "below", "lower", "above", "upper", "higher", and the like, are used for ease of description to explain the positioning of one element relative to a second element. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in addition to the orientation depicted in the figures. For example, if a device described is turned over, elements described as "below" or "beneath" other elements would then be oriented "above" the other elements - the same will apply to the adjectives "above" and "below". Likewise, if a device is inverted, elements described as "on" or "side" other elements would then be oriented "on" or "side" the other elements - the same will apply to the adjectives "on" and "side". The device will thus take on different orientations. In addition, the term "on" as used herein, including in the context of a first element being "on" a second element, means in contact with the second element.

[0030] The present application can be implemented without some of these specific details, which are known to those skilled in the art. The following description of the embodiments is merely provided to give a better understanding of the present application by showing examples of the present application.

[0031] Figure 1 is a schematic view of a satellite support cabin of a space carrier according to an embodiment of the present application; Figure 2 is a sectional view of an upper end frame in a satellite support cabin of a space carrier according to an embodiment of the present application; Figure 3 is a sectional view of a lower end annular flange in a satellite support cabin of a space carrier according to an embodiment of the present application; Figure 4 is a schematic view of a satellite support cabin of a space carrier according to another embodiment of the present application; Figure 5 is a sectional view of a longeron in a satellite support cabin of a space carrier according to an embodiment of the present application; Figure 6 is a schematic view of a forming die for manufacturing a satellite support cabin of a space carrier according to an embodiment of the present application.

[0032] As shown in Figure 1 and Figure 2 The present application provides a satellite support cabin of a space carrier, comprising an upper end frame 100, a truncated cone shell 200 and a lower end annular flange 300 which are integrally formed of carbon fiber composite material. The upper end frame 100 is formed by wrapping a first foam core 400 with carbon fiber composite material and curing. The upper end frame 100 is used to connect a satellite support frame, and the lower end annular flange 300 is used to connect a sub-stage of the space carrier.

[0033] Specifically, the satellite supporting cabin of the space vehicle in the embodiment adopts a combination of carbon fiber composite and foam sandwich material, compared with the metal material, the satellite supporting cabin of the scheme can not only achieve the purpose of reducing weight, but also effectively enhance the overall strength and rigidity of the supporting cabin. The manufacturing process of the upper end frame 100 is to wrap the first foam sandwich 400 in the long barrel type carbon fiber composite material before it is cured, and then the curing operation of the carbon fiber composite material and the first foam sandwich 400 is carried out together. The upper end frame 100 has a certain thickness, so that the contact surface with the satellite support is more, and the satellite support can be more stably connected.

[0034] As shown in Figure 2 According to one embodiment of the utility model, the thickness of the truncated cone shell 200 increases continuously along the direction of the generatrix of the truncated cone shell 200 towards the upper end frame 100 and close to the transition zone of the upper end frame 100.

[0035] According to one embodiment of the utility model, the upper end frame 100 is cylindrical, and the upper end frame 100 is divided into an inner frame and an outer frame, and the diameter of the outer frame is greater than that of the inner frame.

[0036] According to one embodiment of the utility model, the first foam sandwich 400 is arranged in the space surrounded by the skin on the inner side of the truncated cone shell 200, and the shape of the cross section of the first foam sandwich 400 is trapezoidal.

[0037] As shown in Figure 3 According to one embodiment of the utility model, the connecting surface of the lower end annular flange 300 is perpendicular to the flange axis, and the thickness of the connecting surface of the lower end annular flange 300 increases continuously in the direction of radially away from the outside of the truncated cone shell 200.

[0038] As shown in Figure 4 According to one embodiment of the utility model, the satellite supporting cabin of the space vehicle further comprises a plurality of long stringers 500 arranged on the inner wall of the truncated cone shell in the circumferential direction, and each long stringer 500 is arranged on the inner wall along the direction of the generatrix of the truncated cone shell 200.

[0039] As shown in Figure 5 According to one embodiment of the utility model, the cross section of the long stringer 500 is approximately π type, and the long stringer 500 is wrapped with a second foam sandwich 600 formed by carbon fiber composite material.

[0040] According to one embodiment of the utility model, the long stringer 500 has inclined surfaces on both sides in the width direction, and the cross section of the second foam sandwich 600 wrapped inside is isosceles trapezoidal.

[0041] According to one embodiment of the utility model, the integrally formed upper end frame 100, truncated cone shell 200 and lower end annular flange 300 are formed by laying carbon fiber unidirectional tape prepreg on a mold.

[0042] Specifically, in order to enhance the stability of the truncated cone shell 200, a transition area with gradually increasing thickness is arranged on the truncated cone shell 200 close to the upper end frame 100 with a certain thickness, that is, the thickness of the truncated cone shell 200 increases continuously along the generatrix of the truncated cone shell 200 towards the direction of the upper end frame 100. Similarly, since the lower end annular flange 300 needs to be connected with the sublevel of the space vehicle, the connecting surface of the lower end annular flange 300 is designed to be thickened, and the thickness of the connecting surface of the lower end annular flange 300 increases continuously in the direction away from the outside of the truncated cone shell 200 in the radial direction.

[0043] In the specific operation process, as shown in the figure, Figure 6 The overall satellite support cabin is laid by carbon fiber unidirectional tape prepreg on the surface of the forming mold, wherein the forming mold is provided with three forming areas according to the inclination angles between the upper end frame 100, the truncated cone shell 200 and the lower end annular flange 300. The first forming area 701 is used for laying the upper end frame 100, the second forming area 702 is used for laying the truncated cone shell 200, and the third forming area 703 is used for laying the lower end annular flange 300. First, the carbon fiber unidirectional tape prepreg is laid on the forming mold according to 0 degrees (that is, in the direction along the generatrix of the truncated cone shell 200), and the carbon fiber unidirectional tape prepreg extends from the first forming area 701 to the second forming area 702 and then to the third forming area 703. Then, according to the thickness requirements of the upper end frame 100, the truncated cone shell 200 and the lower end annular flange 300, the carbon fiber prepreg is laid by changing the laying area to form a transition area, and the laying angle can be alternately laid at 0 degrees, ±45 degrees and 90 degrees to enhance the stiffness performance. The satellite support cabin of the application forms a transition area in the transition area of the truncated cone shell 200 close to the end of the upper end frame 100, and the stiffness of the upper end frame 100 to the conical surface can be smoothly transitioned, which can avoid local stress concentration and secondary bending moment caused by sudden change in stiffness.

[0044] For the manufacturing process of the upper end frame 100, the outer side of the long cylindrical carbon fiber prepreg layer formed in the first forming area 701 is placed with a solidified independent trapezoidal first foam core 400, the long cylindrical carbon fiber prepreg layer is folded outward and downward to wrap the pre-solidified first foam core 400, and a cylindrical upper end frame 100 is formed. Since the downwardly folded carbon fiber prepreg layer falls on the truncated cone shell 200 for solidification, the length of the outer frame is greater than that of the inner frame. Then, the entire satellite support cabin is solidified and formed. The support cabin in the application is formed by the forming mold of the male mold, which improves the laying process and improves the laying efficiency.

[0045] In addition, the manufacturing process of the longeron 500 also adopts carbon fiber composite material to wrap the second foam sandwich 600, wherein the carbon fiber composite material is laid on a mold in advance to form a structure with a cross section substantially in the shape of π, and the isosceles trapezoidal second foam sandwich 600 is placed at the lower end of the π-shaped structure, and then the whole curing of the longeron 500 is performed. Compared with the scheme of co-curing and integrally forming the longeron 500 and the support cabin, the secondary bonding of the longeron 500 facilitates the control of the number of the longeron 500, and the distribution adjustment is flexible, and the capacity of expandable configuration is possessed. The side wall of the longeron 500 is designed as an inclined surface, and by controlling the cross-sectional height thereof, the smooth transition of the skin stiffness of the longeron 500 and the truncated cone shell 200 is realized.

[0046] Then, the longeron 500 is positioned on the inner wall of the truncated cone shell 200 along the generatrix direction of the truncated cone shell 200 by riveting, and is connected with the satellite support cabin through a film, and after the film is cured, rivets are connected to the truncated cone shell 200 at different positions of the longeron 500 as needed for further fixation. Figure 1 As shown in FIG. 6, after the assembly is completed, the operation opening of the upper end frame 100 and the side wall opening of the truncated cone shell 200 are processed by a numerical control machine tool.

[0047] The satellite support cabin of the space vehicle in the embodiment uses the skin structure of the carbon fiber composite material reinforced longeron 500, and by arranging the foam sandwich in the inner side cross section of the upper end frame 100 and the longeron 500, the overall strength and stiffness of the satellite support cabin can be effectively enhanced, and the purpose of reducing the weight of the satellite support cabin is achieved. The satellite support cabin uses the foam sandwich longeron 500 and the foam sandwich upper end frame 100, and the overall stiffness of the support cabin can be effectively improved at the weak link of stiffness. The longeron 500 is arranged inside the truncated cone shell 200, so that the space outside the support cabin is sufficient, and the subsequent expansion of the satellite carrying task is facilitated.

[0048] On the other hand, the utility model also provides a fairing, containing the satellite support cabin of any one of the above-mentioned space vehicles.

[0049] The satellite support cabin is an indispensable cabin structure for carrying the satellite of the space vehicle, and the satellite support cabin of the embodiment is used for the final stage of the space vehicle, is located inside the satellite fairing, matches the outer diameter of the space vehicle at the lower end and is connected with the second stage of the space vehicle through the lower end annular flange 300, matches the connection requirement of the satellite at the upper end and is connected with the satellite support through the upper end frame 100, and the weight of the support cabin is significantly reduced by adopting the carbon fiber and the foam material, and the structural reliability is improved.

[0050] The above is only a preferred embodiment of the utility model, and is not used to limit the utility model, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A satellite support capsule for a space launch vehicle, characterized by, The upper end frame, the truncated cone shell and the lower end annular flange are integrally formed by carbon fiber composite material, the upper end frame is formed by wrapping the first foam sandwich with carbon fiber composite material and curing, the upper end frame is used for connecting the satellite support, and the lower end annular flange is used for connecting the sub-stage of the space vehicle.

2. The satellite support capsule of a space launch vehicle according to claim 1, characterized in that, The thickness of the truncated cone shell increases continuously along the direction of the generatrix of the truncated cone shell towards the upper end frame and close to the transition zone of the upper end frame.

3. The satellite support capsule of claim 1, wherein, The connecting surface of the lower end annular flange is perpendicular to the flange axis, and the thickness of the connecting surface of the lower end annular flange increases continuously in the direction of moving away from the outside of the truncated cone shell.

4. The satellite support capsule of claim 1, wherein, The upper end frame is cylindrical, and the upper end frame is divided into an inner frame and an outer frame, and the length of the outer frame is greater than that of the inner frame.

5. The satellite support capsule of a space launch vehicle according to claim 4, wherein, The first foam sandwich is arranged in the space surrounded by the skin on the inner side of the truncated cone shell and the upper end frame, and the cross section of the first foam sandwich is in the shape of a trapezoid.

6. The satellite support capsule of the space vehicle of claim 1, wherein, A plurality of long girders are arranged on the inner wall of the truncated cone shell in the circumferential direction, and each long girder is arranged on the inner wall in the direction of the generatrix of the truncated cone shell.

7. The satellite support capsule of a space launch vehicle according to claim 6, characterized in that The cross section of the long girder is approximately π-shaped, and the long girder is formed by wrapping a second foam sandwich with carbon fiber composite material.

8. The satellite support capsule of claim 7, wherein, The long girder has inclined surfaces on both sides in the width direction, and the cross section of the second foam sandwich wrapped inside is in the shape of an isosceles trapezoid.

9. The satellite support capsule of the space vehicle of claim 1, wherein, The upper end frame, the truncated cone shell and the lower end annular flange are integrally formed by laying up carbon fiber unidirectional tape prepreg on a mold.

10. A fairing characterized by, A satellite support cabin comprising a space vehicle according to any one of claims 1-9.

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