CN106586036A - Composite storage tank for launch vehicle with stiffening beam and method for manufacturing the same - Google Patents

Abstract

The invention provides a carrier rocket composite material storage tank with a stiffening beam and a processing method thereof, wherein the storage tank comprises a front bottom cover, a front seal head, a tank barrel section, a rear seal head, a rear bottom cover and a rear bottom tank shell, the front bottom cover is connected with the front seal head, the rear seal head is connected with the rear bottom cover, the front seal head and the rear seal head are respectively fixed with the upper end and the lower end of the tank barrel section through glue layers, and the rear bottom cover is connected with the rear bottom tank shell through bolts; the box-type air conditioner is characterized in that the outer side wall of the box barrel section is uniformly provided with a stiffening beam, and the stiffening beam is arranged in a stiffening beam bracket and is fixedly connected to the outer side of the box barrel section through the stiffening beam bracket. The invention also discloses a processing method of the storage tank, which adopts a fiber winding forming combined with a fiber laying forming adhesive joint co-curing integral forming process. The invention improves the axial bearing capacity of the storage tank by arranging the stiffening beam structure at the outer side of the cylinder section of the storage tank, adopts the composite material winding and laying adhesive joint co-curing molding technology, and has the effects of no need of welding molding, reduction of structural assembly complexity, improvement of production efficiency and the like.

Description

Composite storage tank for launch vehicle with stiffening beam and method for manufacturing the same

technical field

The invention relates to a storage tank for storing liquid at low temperature and a processing method thereof, in particular to a launch vehicle composite material storage tank with a straight-through wall having a rectangular cross-section reinforcing beam, which can replace the traditional aluminum-lithium metal storage tank. It is used in the storage of low-temperature propellant in launch vehicles, the connection of front and rear parts, and the maintenance of the complete shape of the projectile body, etc.

Background technique

Domestically produced liquid propellant tanks generally use metal materials. At present, in order to realize the overall light weight of launch vehicles, the aerospace sector uses advanced aluminum alloys such as aluminum-lithium alloys with high specific strength and high specific stiffness ^[1] . The manufacturing process of metal tanks is generally as follows: a mechanically or chemically milled grid-shaped metal plate is machined and filled with polyethylene squares to form the tank wall. After the panel is formed into the appropriate shape, it is assembled on the fixture and welded by MIG welding. Next, butt-weld the stretched extruded angle material to the two ends of the tank shell, respectively butt-weld two tank bottoms with nine spherical triangular melon petals, and trim the welds to obtain the overall tank structure ^[2] .

Because traditional storage tanks are made of metal materials and the manufacturing process involves a wide range of processes: heat treatment, surface treatment, sheet metal forming, chemical milling, machining, riveting, welding, etc. ^[2] . Therefore, the main defects of traditional metal storage tanks are: large structural mass, complex and diverse processes, long manufacturing cycle, and high cost.

Since carbon fiber reinforced resin-based composite materials have excellent properties such as light weight and high strength, the use of composite material storage tanks has become very common in developed countries. Composite propeller tank molding process mainly adopts the following three types: hand lay-up molding, winding molding and lay-up molding. Hand lay-up molding is a molding process in which fiber-reinforced materials and resin glue are spread on the mold, cured at room temperature (or heating) and without pressure (or low pressure), and demolded into products. Winding molding is a molding process in which the continuous fiber or cloth tape soaked in resin glue is wound on the mandrel according to certain rules, and then solidified and demoulded to become a reinforced plastic product ^[3] . The laying and forming process uses a unidirectional prepreg tape with an insulating backing paper. The cutting and positioning of the predetermined shape are completed in the tape laying head. After heating, it is directly laid under the action of a pressure roller according to a certain design direction until the curvature radius is large and changes. Slow mold surface ^[4] .

The above three processes alone have the following defects: defects of hand lay-up: low production efficiency; difficult control of product quality, poor performance stability; low fiber content in the product and poor mechanical properties. Defects of filament winding molding: winding molding has low adaptability, and products of any structural form cannot be wound; winding molding requires winding machines, mandrels, curing heating furnaces, demoulding machines and skilled technical workers, which is expensive and requires high technical requirements ^{[ 3]} . Compared with the above molding technologies, the automatic lay-up molding technology is a low-cost, automated and digital manufacturing technology for advanced composite components. However, the key to automatic lay-up molding technology is the need for automatic lay-up equipment. Domestic related research is still in its infancy, and only some simple structures or small-sized composite structures can be completed, while large-scale composite structures are still laid by hand. Therefore, it is difficult for the domestic manufacturing process to complete the overall laying and forming of the storage tank ^[5] .

In terms of tank configuration, in order to prevent the leakage of internal propellant liquid, composite propellant tanks of foreign launch vehicles are usually embedded with a metal lining structure inside the composite tank. For metal-lined composite tanks, the metal lining not only increases the weight of the tank, but also considers the connection between the metal lining and the inner wall of the composite tank.

The design of composite storage tanks with lining generally adopts mesh theory, which ignores the contribution of resin matrix to the stiffness of the entire composite laminate, that is, the fiber bears all the stress of the shell membrane ^[1] . When designing a metal-lined composite storage tank, it is only necessary to ensure the strength requirements of the structure, and the functional requirements of the liquid propellant seal are borne by the inner liner, that is, the structural strength design and the liquid propellant sealing function design are compatible. Detached.

At present, the commonly used single-walled barrel-shaped composite material storage tank will be subject to a large axial load during the rocket launch process. The 0° layer in the box section is effective in bearing axial load, but the winding process cannot produce 0° °lamination, so it is necessary to increase the number of small-angle laminates in the composite storage tank section, which will lead to a large overall weight of the storage tank, and it is difficult to complete the aerospace weight index.

[references]

[1] Huang Cheng, Lei Yongjun. Research progress in the design and research of large-scale launch vehicle cryogenic composite tanks [J]. Aerospace Materials Technology, 2015, 45(2).

[2] Xiong Huan. Application of cryogenic storage tanks and aluminum-lithium alloys [J]. Missile and Space Vehicle Technology, 2001(6): 33-40.

[3] Composite material technology and equipment [M], Wuhan University of Technology Press, 1994.

[4] He Yafei, Jiao Weicheng, Yang Fan, et al. The Development of Resin Matrix Composite Molding Technology [J]. Fiber Composite Materials, 2011(2):7-13.

[5] Huan Dajun. Research on CAD/CAM Key Technology for Automatic Laying of Composite Materials [D]. Nanjing University of Aeronautics and Astronautics, 2010.

Contents of the invention

According to the above-mentioned technical problems, a low-temperature composite storage tank for a launch vehicle with a trapezoidal sandwich wall and a processing method thereof are provided. The invention improves the axial bearing capacity of the storage tank by setting a reinforcing beam structure outside the barrel section of the storage tank, and adopts the composite material winding, laying, bonding and co-curing molding technology, thereby achieving no need for welding and forming, reducing the complexity of structural assembly, and improving production efficiency etc.

The technical means adopted in the present invention are as follows:

A carrier rocket composite material storage tank with a reinforcing beam, the storage tank includes a front bottom cover, a front head, a tank section, a rear head, a rear bottom cover and a rear bottom tank shell, the front bottom cover and the The front head is connected, the rear head is connected with the rear bottom cover, the front head and the rear head are respectively fixed to the upper and lower ends of the box section through glue layers, and the rear bottom The cover and the rear bottom tank shell are bolted; it is characterized in that,

A reinforcing beam is evenly arranged on the outer wall of the box section, and the reinforcing beam is arranged in a reinforcing beam bracket and fixedly connected to the outer side of the box section through the reinforcing beam bracket.

Further, the cross-section of the reinforcing beam is rectangular or trapezoidal, and the inner surface of the reinforcing beam bracket is adapted to the outer profile of the cross-section of the reinforcing beam.

Further, the front bottom cover, the rear bottom cover, the rear bottom tank shell, the front head, the reinforcement beam, the reinforcement beam bracket, the box section and the rear head All are made of carbon fiber reinforced resin matrix composites, especially IM7/977-3, IM7/977-2, T700/TDE-86 and AS4/3501-6 carbon fiber reinforced resin matrix composites.

The present invention also discloses a processing method for the above-mentioned carrier rocket composite storage tank with reinforced beams, characterized in that the storage tank adopts a fiber winding molding combined with fiber laying molding, bonding and co-curing integral molding process, wherein, The front head and the rear head adopt fiber winding molding process; the reinforcing beam, the box section and the reinforcing beam support adopt fiber laying molding process; the front bottom cover and the rear bottom The cover and the rear sump shell are formed by autoclave.

Further, the layering method of the box section is [0/90/0] _2s , the total thickness is 1.5mm-1.8mm, and the thickness of a single layer is 0.125mm-0.15mm; the front head and the back seal The modulus of the head is 1.54, the fiber layering method is [±55/±35] _s , the total thickness is 1.0mm-1.2mm, and the single layer thickness is 0.125mm-0.15mm.

Further, when the connection between the reinforcement beam and the reinforcement beam bracket is a rectangular section reinforcement beam structure, the length of the reinforcement beam, the reinforcement beam bracket and the box section is the same, and the cross section of the reinforcement beam is a square , the side length of the section is 50mm-60mm, and the side thickness of the reinforcing beam is 3mm-5mm; The side section thickness of the reinforced beam bracket is 1.5mm-2.5mm.

Further, when the connection between the reinforcing beam and the reinforcing beam bracket is a trapezoidal cross-section reinforcing beam structure, the lower bottom edge of the trapezoid is glued to the box section, and the reinforcing beam, the reinforcing beam bracket and the box The tube sections have the same length, the cross-section of the reinforcing beam is trapezoidal, the length of the upper bottom side of the cross-section is 30mm-50mm, the length of the lower bottom side of the cross-section is 50mm-70mm, and the thickness of the trapezoidal beam side is 3mm-5mm; The length of the side connecting with the box section is 100mm-120mm, the length of the side connecting with the reinforcing beam is 25mm-35mm, and the section thickness of the reinforcing beam support side is 1.5mm-2.5mm.

The present invention has the following advantages:

1. The present invention adopts composite material winding, laying, bonding and co-curing molding technology, which does not require welding and molding, reduces the number of components and the complexity of structural assembly to the greatest extent, greatly shortens the manufacturing cycle and improves production efficiency.

2. The barrel section of the composite material storage tank adopts lay-up molding technology, which can complete the manufacture of 0° lay-ups. Under the condition of the same number of lay-ups, the axial bearing capacity of the storage tank is greatly improved. At the same time, the application of the reinforced beam structure can reduce the weight of the composite storage tank to the greatest extent by reducing the number of plies in the tank section while ensuring the axial bearing capacity of the tank.

3. The layering method of the inner cylinder wall of the composite material of the present invention can well seal the low-temperature medium, save the weight and design cost of the metal lining, and facilitate the overall formation of the composite material storage tank.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description These are some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained according to these drawings without any creative effort.

Fig. 1 is a structural sectional view of the present invention.

Figure 2 is a side view of the present invention.

Fig. 3 is a top view of Fig. 1 of the present invention.

Fig. 4 is a schematic diagram of connection of rectangular cross-section reinforcing beams in the present invention.

Fig. 5 is a schematic diagram of the connection of the reinforcing beams with trapezoidal section in the present invention.

detailed description

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

As shown in Figures 1, 2, and 3, a carrier rocket composite material tank with a reinforced beam, the tank includes a front bottom cover 1, a front head 2, a box section 4, a rear head 5, and a rear bottom Cover 6 and rear bottom pool shell 7, the front bottom cover 1 is connected with the front cover 2, the rear cover 5 is connected with the rear bottom cover 6, the front cover 2, the rear cover The head 5 is respectively fixed to the upper and lower ends of the tank section 4 through the glue layer, and the rear bottom cover 6 is bolted to the rear bottom tank shell 7;

A reinforcing beam 3 is evenly arranged on the outer wall of the box section 4, and the reinforcing beam 3 is arranged in a reinforcing beam bracket 8, and is fixedly connected to the outside of the box section 4 through the reinforcing beam bracket 8 superior.

The cross-section of the reinforcing beam 3 is rectangular or trapezoidal, and the inner surface of the reinforcing beam bracket 8 is adapted to the outer profile of the cross-section of the reinforcing beam 3 .

The front bottom cover 1, the rear bottom cover 6, the rear bottom tank shell 7, the front head 2, the reinforcing beam 3, the reinforcing beam bracket 8, the box section 4 and the The rear end caps 5 are all made of carbon fiber reinforced resin-based composite materials.

A processing method for a carrier rocket composite storage tank with a reinforced beam, characterized in that the storage tank adopts a fiber winding molding combined with fiber laying molding, bonding and co-curing integral molding process, wherein the front head 2, The rear head 5 adopts a fiber winding molding process; the reinforcing beam 3, the box section 4 and the reinforcing beam bracket 8 adopt a fiber laying molding process; the front bottom cover 1 and the rear bottom cover 6 and the thick-bottomed pool shell 7 adopt autoclave molding process.

The layering method of the box section 4 is [0/90/0] _2s , the total thickness is 1.5mm-1.8mm, and the single layer thickness is 0.125mm-0.15mm; the front head 2 and the rear head The modulus of 5 is 1.54, the fiber layering method is [±55/±35] _s , the total thickness is 1.0mm-1.2mm, and the single layer thickness is 0.125mm-0.15mm.

As shown in Figure 4, when the connection between the reinforcing beam 3 and the reinforcing beam bracket 8 is a rectangular section reinforcing beam structure, the reinforcing beam 3, the reinforcing beam bracket 8 and the box section 4 have the same length, The same length means that the reinforcement beam is arranged along the direction of the central axis of the storage tank, the cross section of the reinforcement beam 3 is a square, the side length of the section is 50mm-60mm, and the thickness of the reinforcement beam side is 3mm-5mm; In the cross-section, the length of the side connecting with the box section 4 is 100mm-120mm, the length of the side connecting with the reinforcing beam 3 is 25mm-35mm, and the thickness of the cross-sectional side of the reinforcing beam support is 1.5mm-2.5mm.

As shown in Figure 5, when the connection between the reinforcing beam 3 and the reinforcing beam bracket 8 is a trapezoidal cross-section reinforcing beam structure, the bottom edge of the trapezoid is glued to the box section 4, and the reinforcing beam 3, the The reinforced beam bracket 8 has the same length as the box section 4, the section of the reinforced beam 3 is trapezoidal, the length of the bottom side of the section is 30mm-50mm, the length of the bottom side of the section is 50mm-70mm, and the thickness of the side of the trapezoidal beam is 3mm -5mm; the length of the side connecting with the box section 4 in the cross-section of the reinforcing beam bracket 8 is 100mm-120mm, the length of the side connecting with the reinforcing beam 3 is 25mm-35mm, and the thickness of the side section of the reinforcing beam bracket is 1.5mm- 2.5mm.

Example 1

The winding molding process and laying molding process in the fiber winding molding of the storage tank combined with fiber laying molding, bonding and co-curing overall molding process are as follows: Winding molding process: first, select the core mold of the shape of the tank head, the head mold The number is 1.54, the diameter of the mandrel is 2m-5m, and there is a pole hole at the top, and the diameter of the pole hole is 0.2m-0.5m. Then, under the condition of controlling fiber tension and predetermined line type, select 12K single-bundle carbon fiber to start from the pole hole circumference, bypass the head along the curve tangent to the pole hole on the surface of the head, until the surface of the mandrel is evenly distributed. Until the fibers are full, the winding angles are the same as those in the layup, which are 55° and 35° respectively. When winding, the mandrel rotates at a constant speed around its own axis, and the guide wire reciprocates along the axis of the mandrel at a speed not exceeding 0.9m/s. Finally, the core mold with fibers is immersed in resin, and under heating conditions, it is cured and formed into the shape of the head.

Laying forming process: especially refers to the automatic laying and forming technology, that is, the CNC fiber automatic laying machine is used to respectively realize the forming of the reinforcing beam 3, the box section 4 and the reinforcing beam bracket 8. By setting the dimensional parameters of the reinforcing beam 3, the box section 4 and the reinforcing beam bracket 8 on the computer, the section side length of the rectangular reinforcing beam 3 is 50mm-60mm, and the side thickness of the rectangular beam is 3mm-5mm; the section of the trapezoidal reinforcing beam 3 The length of the upper bottom side is 30mm-50mm, the length of the lower bottom side of the section is 50mm-70mm, the thickness of the trapezoidal beam side is 3mm-5mm; The length is 25mm-35mm, the section thickness is 1.5mm-2.5mm; the length of the box section 4 is 4m-6m, the diameter is 2m-5m, the fiber body ratio is 60%, the layer angle [0/90/0] _2s , the total The thickness is 1.5mm-1.8mm and the thickness of a single layer is 0.125mm-0.15mm; the forming of the tank section 4 can be completed. The configuration of the trapezoidal sandwich wall is obtained by topology optimization technology, which meets the requirements of bearing capacity and reduces the weight of the barrel section of the storage tank.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than limiting them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: It is still possible to modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the various embodiments of the present invention. scope.

Claims (7)

1. a kind of carrier rocket composite tank with buttress brace, the tank includes front bottom (1), front head (2), case Cylinder section (4), rear head (5), rear bottom (6) and rear bottom pond shell (7), the front bottom (1) is connected with the front head (2), institute State rear head (5) to be connected with the rear bottom (6), the front head (2), the rear head (5) by glue-line respectively it is fixed with The upper and lower ends of the case cylinder section (4), the rear bottom (6) and rear bottom pond shell (7) bolt connection；Characterized in that,

Buttress brace (3) is uniformly provided with the lateral wall of the case cylinder section (4), the buttress brace (3) is arranged on reinforcement boom support (8) in, and it is fixedly connected on the outside of the case cylinder section (4) by reinforcement boom support (8).

2. the carrier rocket composite tank with buttress brace according to claim 1, it is characterised in that the reinforcement The rectangular cross-section or trapezoidal of beam (3), the section foreign steamer of the inner surface and the buttress brace (3) for strengthening boom support (8) Exterior feature is adapted.

3. the carrier rocket composite tank with buttress brace according to claim 1 and 2, it is characterised in that described Front bottom (1), the rear bottom (6), the rear bottom pond shell (7), the front head (2), the buttress brace (3), the reinforcement Boom support (8), the case cylinder section (4) and the rear head (5) are made by carbon fiber enhancement resin base composite material.

4. the processing method of the carrier rocket composite tank with buttress brace described in a kind of claim 1 or 2, its feature It is that the tank is glued co-curing integral forming technique using fiber winding forming binding fiber laying forming, wherein, it is described Front head (2), the rear head (5) adopt System of Filament Winding Process；The buttress brace (3), the case cylinder section (4) and described Strengthen boom support (8) using fiber placement moulding process；The front bottom (1), the rear bottom (6) and the rear bottom pond shell (7) autoclave forming process is adopted.

5. processing method according to claim 4, it is characterised in that the ply sequence of the case cylinder section (4) is [0/90/ 0]_2s, gross thickness is 1.5mm-1.8mm, thickness in monolayer 0.125mm-0.15mm；The front head (2) and the rear head (5) Modulus is 1.54, and its fiber ply sequence is [± 55/ ± 35]_s, gross thickness is 1.0mm-1.2mm, thickness in monolayer 0.125mm- 0.15mm。

6. processing method according to claim 4, it is characterised in that the buttress brace (3) and reinforcement boom support (8) When junction is that girder construction is strengthened in square-section, the buttress brace (3), reinforcement boom support (8) and the case cylinder section (4) are long Degree is identical, and the section of the buttress brace (3) is square, and the section length of side is 50mm-60mm, and buttress brace side thickness is 3mm-5mm； Strengthen being connected with the case cylinder section (4) in boom support (8) section edge lengths for 100mm-120mm, be connected with the buttress brace (3) Edge lengths are 25mm-35mm, and buttress brace bracket lip section thickness is 1.5mm-2.5mm.

7. processing method according to claim 4, it is characterised in that the buttress brace (3) and reinforcement boom support (8) When junction is that girder construction is strengthened in trapezoid cross section, trapezoidal bottom is glued with the case cylinder section (4), the buttress brace (3), described Reinforcement boom support (8) is identical with case cylinder section (4) length, and the section of the buttress brace (3) is trapezoidal, and section upper bottom edge is a length of 30mm-50mm, a length of 50mm-70mm in section bottom, ladder beam side thickness is 3mm-5mm；Reinforcement boom support (8) section In be connected edge lengths with the case cylinder section (4) for 100mm-120mm, it is 25mm- that edge lengths be connecteds with the buttress brace (3) 35mm, buttress brace bracket lip section thickness is 1.5mm-2.5mm.