Honeycomb sandwich rocket fairing structure

Abstract

The utility model discloses a honeycomb sandwich rocket fairing structure, which relates to the field of rocket fairing, solves the problems that the effective load capacity is influenced by the larger overall weight of the existing fairing assembly and the subsequent assembly and maintenance cost is higher, and adopts the following scheme that the honeycomb sandwich rocket fairing structure comprises a first end cap and a second end cap which are positioned on the top side and are opposite to each other, a first half cover and a second half cover which are opposite in position are arranged on the bottom sides of the first end cap and the second end cap, the first end cap and the second end cap as well as the first half cover and the second half cover are assembled through L-shaped annular belt plates, and the first half cover and the second half cover are assembled through L-shaped ribs; according to the honeycomb sandwich rocket fairing structure, by adopting the composite materials and optimizing the structural design, the weight of the rocket fairing structure is low, the cost is low, the effective load capacity of a rocket is improved, and compared with a traditional rocket fairing structure, the rocket fairing structure designed by the patent has the better capacity of being low in weight and cost.

Description

Technical Field

[0001] This utility model relates to the field of rocket fairing technology, specifically a honeycomb sandwich rocket fairing structure. Background Technology

[0002] In rocket fairing design, the fairing is used to protect the satellite and other payloads from harmful environmental effects such as aerodynamic forces, aerodynamic heating, and acoustic vibration. It is an important component of the launch vehicle.

[0003] A search revealed that patent application number 201921299630.8 discloses an improved overall structure for the fairing, namely, the addition of an envelope section. On the one hand, the envelope section is fixedly connected to the rocket section to accommodate the satellites installed on the rocket section; on the other hand, the envelope section also uses the half-envelope of the fairing to install the satellites, thereby maximizing the rational layout of multiple satellites on a single rocket. Compared with the existing technology that uses satellite brackets to install multiple satellites, the installation method provided by this technical solution can reduce weight while retaining the necessary gaps between satellites. At the same time, it can make full use of the fairing space, thereby effectively increasing the overall carrying capacity of the rocket and reducing the launch cost of a single rocket, making it suitable for widespread application.

[0004] The aforementioned application documents reduce launch costs to some extent by using a satellite bracket mounting method, but there are still two main drawbacks:

[0005] 1. Relatively heavy: Traditional rocket fairings typically use semi-monocoque aluminum alloy structures and monocoque aluminum honeycomb sandwich structures, but the overall weight is still relatively large, increasing the overall weight of the rocket and thus affecting the rocket's thrust and payload capacity.

[0006] 2. High cost: Manufacturing and maintaining these traditional fairings requires high technology and high cost, which increases the overall cost of the rocket.

[0007] Therefore, we propose a honeycomb sandwich rocket fairing structure. Utility Model Content

[0008] To address the shortcomings of existing technologies, this utility model provides a honeycomb sandwich rocket fairing structure, which solves the problems of the large overall weight of existing fairing components affecting effective load capacity and the high cost of subsequent assembly and maintenance.

[0009] To achieve the above objectives, this utility model is implemented through the following technical solution: a honeycomb sandwich rocket fairing structure, including a first end cap and a second end cap located opposite each other on the top side, a first half-cover and a second half-cover located opposite each other on the bottom side of the first end cap and the second end cap, the first end cap and the second end cap and the first half-cover and the second half-cover being assembled together by an L-shaped annular belt plate, the first half-cover and the second half-cover being assembled together by an L-shaped rib, and the bottom of the fairing being equipped with an explosion bolt mounting seat by an Omega-shaped annular rib.

[0010] As a preferred embodiment of this utility model, an air conditioning vent cover is fixedly installed on the outer wall of the upper half of the fairing, and a spring-operated vent cover is provided on the outer wall of the lower half of the fairing, and an inlet cover is also provided on the outer wall of the fairing. The air conditioning vent cover, the inlet cover, and the spring-operated vent cover all adopt a T700 unidirectional honeycomb sandwich structure with prepreg paper, and are connected to the first half of the fairing and the second half of the fairing by 90° countersunk bolts HB1-129 and GB / T 930 support plate nuts.

[0011] As a preferred embodiment of this utility model, the first end cap and the second end cap are made of E-glass / barium phenolic material.

[0012] As a preferred embodiment of this utility model, the first half-cover and the second half-cover are T700 unidirectional paper honeycomb sandwich structures with prepreg.

[0013] As a preferred embodiment of this utility model, the first end cap and the first half cover are assembled by using an HB6509 smooth rod with R6 shear-resistant 100° countersunk titanium alloy high-lock bolt and an L-shaped annular belt plate, and the second end cap and the second half cover are assembled by using an HB6509 smooth rod with R6 shear-resistant 100° countersunk titanium alloy high-lock bolt end cap and J-133 structural adhesive to act as a liquid gasket.

[0014] As a preferred embodiment of this utility model, an explosion bolt box and a mounting base are provided at the joint between the first half-cover and the second half-cover. The mounting base adopts a 7050-T7451 aluminum alloy frame structure and is connected by bolts and nuts. The bolts are selected as 90° countersunk bolts HB1-129, and the nuts are selected as hexagonal self-locking nuts GB1337. J-133 structural adhesive can be used as a liquid gasket on the connection surface of the mounting base.

[0015] As a preferred embodiment of this utility model, the explosive bolt box and the fairing are connected by bolts and nuts. The bolts and nuts are mechanically connected using 90° countersunk bolts HB1-129, HB1-521 washers and hexagonal self-locking nuts GB1337. The connection surface of the explosive bolt box may use J-133 structural adhesive as a liquid gasket.

[0016] This invention provides a honeycomb sandwich rocket fairing structure. It has the following advantages:

[0017] This honeycomb sandwich rocket fairing structure, through the use of composite materials and optimized structural design, achieves low weight and low cost, while increasing the rocket's payload capacity. Compared with traditional rocket fairing structures, this patented design has better weight and cost reduction capabilities, solving the problems of existing fairing components having a large overall weight that affects payload capacity and high subsequent assembly and maintenance costs. Attached Figure Description

[0018] Figure 1 This is a front view structural diagram of the present invention;

[0019] Figure 2 This utility model Figure 1 Enlarged structural diagram in the middle.

[0020] In the diagram: 1. First end cap; 2. Second end cap; 3. First half cover; 4. Second half cover; 5. L-shaped annular strip; 6. L-shaped rib; 7. Omega-shaped annular rib; 8. Air conditioning vent cover; 9. Inlet cover; 10. Spring operating vent cover; 11. Explosion bolt mounting base; 12. Explosion bolt box; 13. Mounting base. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] Please see Figure 1 and 2 This utility model provides a technical solution: a honeycomb sandwich rocket fairing structure, including a first end cap 1 and a second end cap 2 located opposite each other on the top side. The bottom sides of the first end cap 1 and the second end cap 2 are provided with a first half cover 3 and a second half cover 4 located opposite each other. The first end cap 1 and the second end cap 2 and the first half cover 3 and the second half cover 4 are assembled by an L-shaped annular strip 5. The first half cover 3 and the second half cover 4 are assembled by an L-shaped rib 6. The bottom of the fairing is equipped with an explosion bolt mounting seat 11 by an omega-shaped annular rib 7.

[0023] The honeycomb sandwich rocket fairing structure, through the use of composite materials and optimized structural design, makes the rocket fairing structure lightweight and low-cost, increasing the rocket's payload capacity. Compared with traditional rocket fairing structures, the rocket fairing structure designed in this patent has better lightweight and low-cost capabilities, solving the problem that the overall weight of existing fairing components affects the effective payload capacity and that subsequent assembly and maintenance costs are high. Example

[0024] An air conditioning vent cover 8 is fixedly installed on the outer wall of the upper half of the fairing, and a spring-operated vent cover 10 is opened on the outer wall of the lower half of the fairing, and an inlet cover 9 is also provided on the outer wall of the fairing. The air conditioning vent cover 8, the inlet cover 9 and the spring-operated vent cover 10 are all made of T700 unidirectional honeycomb sandwich structure with prepreg paper, and are connected to the first half cover 3 and the second half cover 4 with 90° countersunk bolts HB1-129 and GB / T 930 support plate nuts.

[0025] The first end cap 1 and the second end cap 2 are made of E-glass / barium phenolic material.

[0026] The first half-cover 3 and the second half-cover 4 are T700 unidirectional prepreg paper honeycomb sandwich structures.

[0027] The first end cap 1 and the first half-cover 3 are assembled by using an HB6509 smooth rod with R6 shear-resistant 100° countersunk titanium alloy high-lock bolt and an L-shaped annular belt plate 5. The second end cap 2 and the second half-cover 4 are assembled by using an HB6509 smooth rod with R6 shear-resistant 100° countersunk titanium alloy high-lock bolt end cap and J-133 structural adhesive to act as a liquid gasket.

[0028] An explosion bolt box 12 and a mounting base 13 are provided at the joint between the first half-cover 3 and the second half-cover 4. The mounting base 13 adopts a 7050-T7451 aluminum alloy frame structure and is connected by bolts and nuts. The bolts are 90° countersunk bolts HB1-129, and the nuts are hexagonal self-locking nuts GB1337. J-133 structural adhesive is allowed to be used as a liquid gasket on the connection surface of the mounting base 13.

[0029] The explosive bolt box 12 is connected to the fairing by bolts and nuts. The bolts and nuts are 90° countersunk bolts HB1-129, HB1-521 washers and hexagonal self-locking nuts GB1337 mechanical connection. J-133 structural adhesive is allowed to be used as a liquid gasket on the connection surface of the explosive bolt box 12.

[0030] In addition, the inverted conical section connection structure, the Omega-shaped annular rib 7 is screwed to the second end cap 2 and the first half cover 3. The bolts are HB6509 smooth rod tolerance R6 shear-resistant 100° countersunk titanium alloy high-locking bolts. J-133 structural adhesive is used as a liquid gasket between the Omega-shaped annular rib 7 and the second end cap 2 and the first half cover 3. An explosion bolt mounting seat 11 is set on the outside of the half cover. The half cover and the Omega-shaped annular rib 7 are screwed together in three layers. The bolts are 90° countersunk bolts HB1-129, HB1-521 washers and hexagonal self-locking nuts GB1337 bolts.

[0031] The working principle and usage process of this utility model are as follows: The first end cap 1, the second end cap 2, the first half-cover 3 and the second half-cover 4 are assembled by using various bolts, smooth rods, nuts and J-133 structural adhesive. By setting the materials, the weight of the overall fairing can be reduced while ensuring strength. At the same time, the cost is low and the rocket's effective payload capacity is increased.

[0032] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. It will be apparent to those skilled in the art that this utility model is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or basic characteristics of this utility model. Therefore, the embodiments should be considered exemplary and non-limiting in all respects. The scope of this utility model is defined by the appended claims rather than the foregoing description, and thus all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this utility model. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0033] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A honeycomb sandwich rocket fairing structure, characterized by: The fairing includes first and second end caps (1, 2) located opposite each other on the top side, and first and second half covers (3, 4) located opposite each other on the bottom side of the first and second end caps (1, 2), the first and second end caps (1, 2) and the first and second half covers (3, 4) are assembled by L-shaped ring-shaped band plates (5), the first and second half covers (3, 4) are assembled by L-shaped ribs (6), and the bottom of the fairing is assembled with an explosion bolt mounting seat (11) by an omega-shaped ring-shaped rib (7).

2. A honeycomb sandwich rocket-missile fairing structure according to claim 1, characterized in that: Opposite air conditioner covers (8) are fixedly installed on the outer wall of the upper half of the fairing, opposite spring operation covers (10) are formed on the outer wall of the lower half of the fairing, and a personnel cover (9) is arranged on the outer wall of the fairing, the air conditioner covers (8), the personnel cover (9) and the spring operation covers (10) are all of T700 one-way band pre-impregnated paper honeycomb sandwich structure, and are connected with the first and second half covers (3, 4) by 90° countersunk bolts HB1-129 and GB / T 930 plate nuts.

3. The honeycomb sandwich rocket-motor fairing structure of Claim 1, wherein: The first and second end caps (1, 2) are made of E-glass / barium phenolic material.

4. The honeycomb sandwich rocket-motor fairing structure of Claim 1, wherein: The first and second half covers (3, 4) are of T700 one-way band pre-impregnated paper honeycomb sandwich structure.

5. The honeycomb sandwich rocket-motor fairing structure of Claim 1, wherein: The first end cap (1) and the first half cover (3) are assembled by an HB6509 light pole tolerance band R6 shear-resistant 100° countersunk titanium alloy high-lock bolt, the L-shaped ring-shaped band plate (5), and the second end cap (2) and the second half cover (4) are assembled by an HB6509 light pole tolerance band R6 shear-resistant 100° countersunk titanium alloy high-lock bolt end cap and J-133 structural glue, which acts as a liquid gasket.

6. A honeycomb sandwich rocket-missile fairing structure as defined in claim 1, wherein: Explosion bolt boxes (12) and mounting bases (13) are arranged at the joint of the first and second half covers (3, 4), the mounting base (13) is of 7050-T7451 aluminum alloy rack structure, is connected by bolts and nuts, the bolt is a 90° countersunk bolt HB1-129, the nut is a hexagonal self-locking nut GB1337, and the connecting surface of the mounting base (13) allows J-133 structural glue to act as a liquid gasket.

7. A honeycomb sandwich rocket-missile fairing structure according to claim 6, characterized in that: The mounting base (13) is assembled with an explosion bolt box, the explosion bolt box (12) and the fairing are connected by bolts and nuts, the bolts and nuts are 90° countersunk bolts HB1-129, HB1-521 washers and hexagonal self-locking nuts GB1337, and the connecting surface of the explosion bolt box (12) allows J-133 structural glue to act as a liquid gasket.

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