Rocket fairing reverse taper structure

Abstract

The present application provides a rocket fairing reverse cone structure, solves the problem that the mechanical environment of the reverse cone part of the rocket fairing is harsh, the traditional sandwich structure cannot be directly applied, and the process of adding axial stringers to the composite sandwich is difficult. The rocket fairing reverse cone structure comprises a reverse cone-shaped inner skin and an outer skin, and the inner skin and the outer skin are fixedly connected through a sandwich; a plurality of embedded blocks are uniformly arranged in the sandwich in a ring shape, the embedded blocks are C-shaped structures with an inner ring, and the C-shaped structures are used for fixedly connecting with explosion bolt boxes of the rocket fairing reverse cone structure; a first reinforcing plate is fixed between the inner skin and the embedded blocks; and a second reinforcing plate is fixed between the outer skin and the embedded blocks. The scheme of the present application gradually disperses and transmits the load of the explosion bolt box of the transversely separated surface to the reverse cone structure through the embedded blocks and the reinforcing plates, and uniformly transmits the load to the fairing column segment, which can obviously reduce the process difficulty and ensure the strength and stability of the fairing structure.

Description

Technical Field

[0001] This invention relates to the field of rocket fairing technology, and in particular to an inverted cone structure for a rocket fairing. Background Technology

[0002] The satellite fairing is one of the most important components of a launch vehicle, possessing a good aerodynamic shape, light structural mass, and reliable separation capability. Its main function is to maintain the aerodynamic shape of the launch vehicle during pre-launch and flight, protecting the payload within the fairing from the influence of the external natural environment and aerodynamic erosion, and ensuring reliable separation from the rocket after exiting the atmosphere. Currently, satellite fairings mainly fall into two categories: metal riveted structures and composite material structures. Metal material structures result in higher quality fairings due to the material's properties. With the rapid development of composite materials, fairing products are gradually shifting towards composite material structures.

[0003] Currently, domestic solutions for the inverted cone structure of large launch vehicle fairings include metal-reinforced panels and composite-reinforced panels. However, a lighter inverted cone composite sandwich design has not yet emerged. This is because the mechanical requirements of the inverted cone structure's ring reinforcement are stringent, and the design of the force transmission path for the composite sandwich is difficult. To optimize the force transmission path of the composite inverted cone structure, a design scheme with pre-embedded axial stringers can be adopted to effectively connect the upper and lower panels of the sandwich structure. However, this scheme requires high precision in the molding of composite materials and is prone to stress-induced assembly due to process inaccuracies. Summary of the Invention

[0004] This invention provides an inverted cone structure for rocket fairings, which solves the problems of harsh mechanical environment in the inverted cone part of rocket fairings, the inability to directly apply traditional sandwich structures, and the difficulty in implementing the process of adding axial stringers to composite material sandwiches.

[0005] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0006] A rocket fairing inverted cone structure includes:

[0007] The inner and outer skins are inverted cone shapes, and the inner and outer skins are fixedly connected by a sandwich structure.

[0008] Within the interlayer, a plurality of pre-embedded blocks are uniformly arranged in a circumferential direction. The pre-embedded blocks are C-shaped structures with an inner ring. The C-shaped structures are used for fixed connection with the explosive bolt box of the rocket fairing inverted cone structure.

[0009] A first reinforcing plate is fixed between the inner skin and the embedded block;

[0010] A second reinforcing plate is fixed between the outer skin and the embedded block.

[0011] Optionally, both the inner skin and the outer skin are annular structures, the radius of the inner skin is smaller than the radius of the outer skin, and the inner skin is fitted inside the outer skin.

[0012] Optionally, a preset interval is provided between the inner skin and the outer skin.

[0013] Optionally, the inner skin and the outer skin are provided with a plurality of openings, which are evenly distributed along the ends of the inner skin and the outer skin.

[0014] Optionally, the embedded block is engaged within the preset interval between the inner skin and the outer skin.

[0015] Optionally, the explosive bolt box includes: a square explosive bolt box body, with a first connecting plate and a second connecting plate parallel to each other along the first side, the second side and the third side of the explosive bolt box body; the first side and the second side are adjacent, the second side and the third side are adjacent, and the first side and the third side are arranged opposite to each other.

[0016] Optionally, the inner ring of the embedded block is connected to the first connecting plate and the second connecting plate of the explosion bolt box by bolts.

[0017] Optionally, the interlayer is a honeycomb interlayer, and the inner skin and the outer skin are bonded and cured to the honeycomb interlayer.

[0018] Optionally, the first reinforcing plate is bonded between the embedded block and the inner skin;

[0019] The second reinforcing plate is bonded between the embedded block and the outer skin.

[0020] Optionally, the reinforcing plate is bonded inside the opening.

[0021] The above-described solution of the present invention has at least the following beneficial effects:

[0022] The rocket fairing inverted cone structure of this invention includes: an inverted cone-shaped inner skin and an outer skin, the inner skin and the outer skin being fixedly connected by a sandwich layer; within the sandwich layer, a plurality of pre-embedded blocks are uniformly arranged circumferentially, the pre-embedded blocks being C-shaped structures with an inner ring, the C-shaped structures being used for fixed connection with the explosive bolt boxes of the rocket fairing inverted cone structure; a first reinforcing plate is fixed between the inner skin and the pre-embedded blocks; a second reinforcing plate is fixed between the outer skin and the pre-embedded blocks. The technical solution of this invention, through the pre-embedded blocks and reinforcing plates, gradually disperses and transfers the load of the explosive bolt boxes on the transverse separation surface to the inverted cone structure, and uniformly transfers it to the fairing column section, which can significantly reduce the manufacturing difficulty and ensure the strength and stability of the fairing structure. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the rocket fairing according to an embodiment of the present invention;

[0024] Figure 2 This is a schematic diagram of the inverted cone structure of the rocket fairing according to an embodiment of the present invention;

[0025] Figure 3 This is a schematic diagram of the inverted cone structure of the rocket fairing according to an embodiment of the present invention;

[0026] Figure 4 This is a schematic diagram of the embedded block structure according to an embodiment of the present invention;

[0027] Figure 5 This is a schematic diagram of the connection between the embedded block and the explosive bolt box in an embodiment of the present invention;

[0028] Figure 6 This is a schematic diagram of the honeycomb sandwich structure according to an embodiment of the present invention;

[0029] Figure 7 This is a schematic diagram of the installation position of the reinforcing plate according to an embodiment of the present invention;

[0030] Among them, 11. Outer skin; 12. Inner skin; 2. Explosion bolt box; 3. Inverted cone structure; 4. Embedded block; 51. First reinforcing plate; 52. Second reinforcing plate; 6. Honeycomb sandwich. Detailed Implementation

[0031] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0032] like Figure 1 and Figure 2 As shown, an embodiment of the present invention proposes a rocket fairing inverted cone structure, comprising:

[0033] The inner skin 12 and the outer skin 11 are inverted cone shapes, and the inner skin 12 and the outer skin 11 are fixedly connected by a sandwich structure.

[0034] Within the interlayer, a plurality of pre-embedded blocks 4 are uniformly arranged in a circumferential direction. The pre-embedded blocks 4 are C-shaped structures with an inner ring. The C-shaped structures are used to fix and connect with the explosive bolt box 2 of the rocket fairing inverted cone structure.

[0035] A first reinforcing plate 51 is fixed between the inner skin 12 and the pre-embedded block 4;

[0036] A second reinforcing plate 52 is fixed between the outer skin 11 and the embedded block 4.

[0037] In this embodiment, during the flight phase, the inverted cone structure of the rocket fairing is subjected to a combination of axial force, bending moment, and shear force. Considering the inverted cone structure as a separate research object, the force transmitted from the rocket fairing column section to the inverted cone structure is relatively uniform. The force transmitted from the lateral separation surface to the inverted cone structure is mainly concentrated in the explosive bolt box 2. The load on the explosive bolt box 2 is large and the force transmission is uneven. Therefore, the focus of the structural design is to reduce the load on the explosive bolt box 2 and distribute it to the inner skin 12 and outer skin 11 of the inverted cone structure 3.

[0038] In this embodiment, the rocket fairing inverted cone structure 3 has two inverted cone-shaped inner and outer skins, namely an inner skin 12 and an outer skin 11, which are fixedly connected by a sandwich structure 3. The inner skin 12 and the outer skin 11 are made of composite materials, which have the advantages of high efficiency in wave transmission, light weight, and high load-bearing capacity, and are currently widely used in the aerospace field. In the sandwich structure, a plurality of pre-embedded blocks 4 are uniformly arranged in a circumferential direction. The pre-embedded blocks 4 are C-shaped structures with an inner ring. The C-shaped structures are used to fix and connect with the explosive bolt box 2 of the rocket fairing inverted cone structure, so as to realize the embedded installation of the explosive bolt box 2 in the sandwich structure and avoid placing the explosive bolt box 2 outside the inverted cone structure 3, which would cause the inverted cone to be embedded in the sandwich structure. Structure 3 generates additional bending moments. A first reinforcing plate 51 is fixed between the inner skin 12 and the embedded block 4, and a second reinforcing plate 52 is fixed between the outer skin 11 and the embedded block 4. After adding the reinforcing plates, the circumferential stiffness of the inverted cone structure 3 increases significantly. The stress on the embedded block 4 is preferentially transmitted along the circumferential direction through the reinforcing plates. The force diffusion path in the circumferential direction is from the embedded block 4 to the first reinforcing plate 51 and the second reinforcing plate 52, and from the first reinforcing plate 51 and the second reinforcing plate 52 to the inner skin 12 and the outer skin 11. Through the reinforcing plates, the circumferential stiffness of this area can be improved, so that the force is preferentially dispersed along the circumferential direction, better reducing the stress level at the interface of the reinforcing plate and the outer skin, and avoiding debonding at the interface of the sandwich structure.

[0039] The technical solution of the present invention gradually distributes and transfers the load of the explosion bolt box 2 on the transverse separation surface to the inverted cone structure 3 through the pre-embedded block 4 and the reinforcing plate, and evenly transfers it to the fairing column section, which can significantly reduce the difficulty of the process and ensure the strength and stability of the fairing structure.

[0040] An optional embodiment of the present invention, such as Figures 2 to 5 As shown, both the inner skin 12 and the outer skin 11 are annular structures, the radius of the inner skin 12 is smaller than the radius of the outer skin 11, and the inner skin 12 is fitted inside the outer skin 11.

[0041] A preset interval is provided between the inner skin 12 and the outer skin 11;

[0042] The inner skin 12 and the outer skin 11 are provided with a plurality of openings, which are evenly distributed along the ends of the inner skin 12 and the outer skin 11;

[0043] The embedded block 4 is a C-shaped structure with an inner ring, and the embedded block is snapped into the preset interval between the inner skin 12 and the outer skin 11;

[0044] The explosive bolt box 2 includes: a square explosive bolt box body, and a first connecting plate and a second connecting plate that are parallel to each other along the first side, the second side and the third side of the explosive bolt box body; the first side and the second side are adjacent to each other, the second side and the third side are adjacent to each other, and the first side and the third side are arranged opposite to each other;

[0045] The inner ring of the pre-embedded block 4 is connected to the first connecting plate and the second connecting plate of the explosion bolt box 2 by bolts.

[0046] In this embodiment, the inner skin 12 and the outer skin 11 are annular structures, with the radius of the inner skin 12 being smaller than the radius of the outer skin 11. The inner skin 12 is fitted inside the outer skin 11. Multiple openings are provided on the inner skin 12 and the outer skin 11, evenly distributed along the ends of the inner skin 12 and the outer skin 11. The openings on the inner skin 12 and the outer skin 11 are arranged in pairs facing each other, evenly distributed along the ends of the skins. Each layer of skin typically has 12 openings. A predetermined interval is provided between the inner skin 12 and the outer skin 11; this interval adopts a honeycomb sandwich structure. The interlayer thickness is usually more than 30mm. The pre-embedded block 4 is snapped into the pre-set space of the honeycomb interlayer, and the honeycomb structure near the pre-embedded block is reinforced by foam adhesive. The explosion bolt box 2 includes: a square explosion bolt box body, and a first connecting plate and a second connecting plate that are parallel to each other along the first side, the second side and the third side of the explosion bolt box body; the first side and the second side are adjacent, the second side and the third side are adjacent, and the first side and the third side are arranged opposite to each other; the inner ring of the pre-embedded block 4 is connected to the first connecting plate and the second connecting plate of the explosion bolt box 2 by bolts respectively.

[0047] The technical solution of the present invention embeds the explosive bolt box 2 into the inverted cone structure 3. Compared with the solution where the explosive bolt box 2 is not embedded in the sandwich structure, the thickness of the sandwich structure is reduced by more than 40%, thereby achieving a significant increase in the structural bearing capacity.

[0048] An optional embodiment of the present invention, such as Figure 6 As shown, the sandwich structure 3 is a honeycomb sandwich structure, and the inner skin 12 and the outer skin 11 are bonded and cured to the honeycomb sandwich.

[0049] In this embodiment, the sandwich structure 3 is a honeycomb sandwich structure, and the inner skin 12 and the outer skin 11 are bonded and cured with the honeycomb sandwich. The honeycomb sandwich structure has high damping, good buffering and vibration isolation performance, good heat insulation performance, good sound insulation performance, and its strength, stiffness and thermal expansion coefficient can be designed.

[0050] An optional embodiment of the present invention, such as Figure 7 As shown, the first reinforcing plate 51 is bonded between the embedded block 4 and the inner skin 11;

[0051] The second reinforcing plate 52 is bonded between the embedded block and the outer skin 12;

[0052] The reinforcing plate is glued inside the opening.

[0053] In this embodiment, the first reinforcing plate 51 is bonded between the embedded block and the inner skin, and the second reinforcing plate 52 is bonded between the embedded block 4 and the outer skin 12. After the reinforcing plates are bonded in the inverted cone structure 3, the circumferential stiffness of the structure is significantly increased. The force of the embedded block is preferentially transmitted along the circumferential direction through the reinforcing plates. The force diffusion path in the circumferential direction is from the embedded block 4 to the first reinforcing plate 51 and the second reinforcing plate 52, and from the first reinforcing plate 51 and the second reinforcing plate 52 to the inner skin 12 and the outer skin 11. Through the reinforcing plates, the circumferential stiffness of this area can be improved, so that the force is preferentially dispersed along the circumferential direction, which can better reduce the stress concentration level at the interface between the reinforcing plate and the outer skin 11 and avoid debonding at the interface of the inverted cone structure 3.

[0054] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A rocket fairing inverted cone structure, characterized in that, include: The inner skin (12) and outer skin (11) are inverted cone-shaped, and the inner skin (12) and the outer skin (11) are fixedly connected by a sandwich structure; Within the interlayer, a plurality of pre-embedded blocks (4) are uniformly arranged in the circumferential direction. The pre-embedded blocks (4) are C-shaped structures with an inner ring. The C-shaped structures are used to fix and connect with the explosive bolt box (2) of the rocket fairing inverted cone structure. A first reinforcing plate (51) is fixed between the inner skin (12) and the pre-embedded block (4); A second reinforcing plate (52) is fixed between the outer skin (11) and the embedded block (4); The explosive bolt box (2) includes: a square explosive bolt box body, with a first connecting plate and a second connecting plate parallel to each other along the first side, the second side and the third side of the explosive bolt box body; the first side and the second side are adjacent, the second side and the third side are adjacent, and the first side and the third side are arranged opposite to each other; The inner ring of the pre-embedded block (4) is connected to the first connecting plate and the second connecting plate of the explosion bolt box (2) by bolts respectively; The interlayer is a honeycomb interlayer (6), and the inner skin (12) and the outer skin (11) are respectively bonded and cured to the honeycomb interlayer (6); The first reinforcing plate (51) is bonded between the embedded block (4) and the inner skin (12); The second reinforcing plate (52) is bonded between the embedded block (4) and the outer skin (11); The load of the explosion bolt box (2) on the transverse separation surface is gradually distributed and transferred to the inverted cone structure (3) through the pre-embedded block (4) and the reinforcing plate, and is evenly transferred to the fairing column section; The embedded block (4) is snapped into the pre-set space of the honeycomb interlayer (6), and the honeycomb structure near the embedded block (4) is reinforced by foam adhesive.

2. The rocket fairing inverted cone structure as described in claim 1, characterized in that, Both the inner skin (12) and the outer skin (11) are annular structures. The radius of the inner skin (12) is smaller than the radius of the outer skin (11). The inner skin (12) is fitted inside the outer skin (11).

3. The rocket fairing inverted cone structure as described in claim 1, characterized in that, A preset interval is provided between the inner skin (12) and the outer skin (11).

4. The rocket fairing inverted cone structure as described in claim 1, characterized in that, The inner skin (12) and the outer skin (11) are provided with a plurality of openings, which are evenly distributed along the ends of the inner skin (12) and the outer skin (11).

5. The rocket fairing inverted cone structure as described in claim 3, characterized in that, The embedded block (4) is engaged within the preset interval between the inner skin (12) and the outer skin (11).

6. The rocket fairing inverted cone structure as described in claim 4, characterized in that, The reinforcing plate is bonded inside the opening.

Images