Rocket block (options), and the manufacturing method (variants)

 

(57) Abstract:

The invention relates to rocket and space technology and can be used in the construction of tank compartments made of composite materials. The proposed missile block contains the front and rear skirts, docking profiles and fuel compartment in the form of two tanks with a common intermediate bottom. This rocket can be made of separate sections. In its manufacture according to one variant of each plate is performed with a cylindrical section in the form of a two-layer shell. The inner layer is a polymeric liner and the outer - fiber. Spread on a cylindrical section between the upper and lower ends three-layer shell with the formation of the front and rear skirts. The shell includes an inner and outer skin of carbon fiber and filler with mating profiles in its ends. On the cylindrical parts of the bottoms of applied adhesive. Curing of the layers and gluing the bottoms carried out in an autoclave. Alternatively make a separate section of the rocket block. First lay out a double layer bottom with a cylindrical section and an adhesive film on it, and then a layer of polymeric liner and three-layer shell. If this is the profiles. The joints sealed. The invention provides high strength weight reduction of the structure rocket unit. 4 S. p. f-crystals, 5 Il.

The invention relates to space technology and can be used in the construction of buildings missile tanks made of composite materials such as carbon fiber, which contain oxygen, hydrogen or kerosene.

Known two-chamber pressure vessel made from a composite material and method of manufacture containing a composite container provided by the serial-wound polymeric liner and a layer of fiberglass, including the first and second cameras (see European application 0638759, CL F 17 C 1/16, publ. 15.02.95).

Corps tanks of liquid-propellant rockets, manufactured from composite materials, the method of winding is not possible to simultaneously optimize the circuit layout in the sides and bottoms because these missiles, at low pressure in the tanks, their walls turn out to be very thin and they are impacted mainly the longitudinal forces in contrast to the pressure vessel, in which the main load is not longitudinal, and circular. The disadvantages of this design solution can be attributed great weight of Polym will fetter the permeability with respect to liquid rocket fuels.

Famous rocket block containing the front and rear skirts, docking struck and fuel compartment, made in the form of block tanks, including two tank with a common intermediate plate (see "boosters" under the General editorship of Professor C. O. Osipov, M.: Voenizdat, 1981, S. 40-44, 170, 177-182).

From the same source is known a method of manufacturing a rocket unit, including the manufacture of front and rear skirts, jackets and bottoms of tanks and connect them in the rocket block.

A disadvantage of the known device and method is a great weight design, made from aluminium.

The technical result of the proposed invention is to reduce the weight of the structure.

This result is achieved in that in the rocket block containing the front and rear skirts, docking profiles and fuel compartment, made in the form of block tanks, including two tank with a common intermediate plate, in accordance with the invention by variant 1 front and back of the skirt zuzelo with tanks shells in the form of a three-layer shell comprising inner and outer skin of carbon fiber and the filler between them, the ends of which are installed docking profiles of preplate, including an inner layer of polymeric liner and outer ply of carbon fiber, and a cylindrical portion inner lining of the shell between the upper and lower ends mounted polymeric liner, to which by means of the adhesive film attached to the said bottom.

This result of the present invention by variant 2 is achieved by the fact that in the known missile block containing the front and rear skirts, docking profiles and fuel compartment, made in the form of block tanks, including two tank with a common intermediate plate, the peculiarity lies in the fact that the rocket unit is made in separate sections, each of which is made in the form of a three-layer shell comprising inner and outer skin of carbon fiber and the filler between them, the ends of which are installed docking profiles of carbon fiber, and the bottom with a cylindrical section made in the form of a two-layer shell, including an inner layer of polymeric liner and outer ply of carbon fiber, while on the inner lining of the shell is selected polymer liner, to which by means of the adhesive film with the formation of the protruding skirt attached to the bottom, and the sections are connected with ptx2">

Specified single technical result in the exercise of invention the object of the method according to option 1 is achieved by the fact that in the known method of manufacturing a rocket unit, including the manufacture of front and rear skirts, jackets and bottoms of the tanks and connect them to the missile unit, the peculiarity lies in the fact that put on the ends of the technological mandrels mounted on shaft technological, layers of polymeric liner and carbon with the formation of the upper, intermediate and lower ends of the cylindrical sections, followed by curing of the layers of carbon fiber in the autoclave, mounted on a shaft technological along the edges of the resulting assemblies two additional technological mandrel, put the adhesive tape on the cylindrical sections of each plate, spread a layer of polymeric liner on the cylindrical section between the upper and lower ends of the adhesive films, consistently spread over the entire length of the Assembly with the formation of the front and rear skirts the inner cladding layer of the fiber filler installed in the ends of the connecting profiles of the carbon fiber layer and the outer skin of carbon fiber, followed by curing of the layers and gluing the practical mandrel.

This result in the exercise of invention the object of the method according to option 2 is achieved by the fact that in the known method of manufacturing a rocket unit, including the manufacture of front and rear skirts, jackets and bottoms of the tanks and connect them to the missile unit, the peculiarity lies in the fact that made a separate section of the rocket block, which lay at the end of the first process of the mandrel layers of polymeric liner and carbon with the formation of the bottom cylindrical section and install from the mentioned end of the second production mandrel, put adhesive tape on the cylindrical section of the bottom, consistently put on the cylindrical section between the extreme ends of the first and second technological mandrels with the formation of the protruding skirts layer of polymeric liner, the inner cladding layer of the fiber filler installed in the ends of the connecting profiles of the carbon fiber layer and the outer skin of carbon fiber, followed by curing of the layers and gluing the bottom of the autoclave, remove the two technological mandrel, after which connect the received section of the rocket block with fasteners placed in stisim and front and rear skirts.

The essence of the invention is illustrated by drawings, where:

in Fig.1 shows a missile block for option 1;

in Fig.2 - rocket block for option 2;

in Fig.3 - node And on an enlarged scale;

in Fig.4 presents the technological devices used to implement the method of manufacturing a rocket unit, option 1;

in Fig.5 - the same for option 2.

Rocket block for option 1 (Fig.1) contains the fuel compartment, made in the form of block tanks with a common intermediate bottom that includes a tank 1, which is, for example, liquid fuel, and the tank 2, which is, for example, a liquid oxidizer. Shell tanks is a three-layer membrane consisting of the inner 3 and outer 4 covers (sheet fiber and filler 5 between cellular or isoprenoid design. Top 6 intermediate 7 and the bottom 8 bottom made in the form of a two-layer shell with a cylindrical sections, consisting of an inner polymeric liner 9 (Mylar or polyimide film) and the outer layer 10 of carbon fiber. On the inside 3 of the casing shell tanks 1 and 2 on the interval between the top 6 and bottom 8 bottoms installed polymer liner 11 (Mylar or polyimide film), mediate 7 and the bottom 8 of the bottom. Shell tanks form projecting beyond the bottom of the tanks front 12 and rear 13 of the skirt, which with the help of a docking profiles 14 of the fiber installed at the ends of the filler 5, attached transition compartments 15.

Rocket block version 2 (Fig.2) contains a fuel compartment, made in the form of block tanks with a common intermediate plate, and consists of separate sections 16. Each section 16 includes the sides and the bottom. Shell is a three-layer membrane consisting of the inner 3 and outer 4 covers (sheet fiber and filler 5 between cellular or isoprenoid design. At the ends of the filler 5 is installed docking profiles 14 from carbon. The hull is made in the form of a two-layer shell with a cylindrical section, consisting of an inner polymeric liner 9 (Mylar or polyimide film) and the outer layer 10 of carbon fiber. On the inside 3 of the casing shell has a polymeric liner 11 (Mylar or polyimide film), to which by means of the adhesive film deposited on the cylindrical section of the bottom, attached to the bottom with the formation of the protruding skirts. Section 16 are connected together by means of fasteners, such as bolts 17 (Fig.3), ustanovljen liquid polymer sealant 19, and the joints are closed diverter strips 20. United section 16 form a block tanks, including tank 1, which is, for example, liquid fuel, and the tank 2, which is, for example, a liquid oxidizer, with the top 6, intermediate 7 and the bottom 8 bottom, and the front 12 and rear 13 of the skirt, which with the help of a docking profiles 14 attached transition compartments 15 (Fig.2).

A method of manufacturing a rocket unit for option 1 is as follows.

On the ends of the technological frame 21 (Fig.4) installed on technological shaft 22, spread layers of polymeric liner 9 (Mylar or polyimide film) and carbon fiber 10 with the formation of the top 6 and the intermediate 7 heads with cylindrical sections. Mounted on the shaft 22 technological mandrel 23, and laid on her side layers of polymeric liner 9 and carbon 10 forming the bottom 8 of the bottom cylindrical section. Place the resulting Assembly in an autoclave, where the solidification of layers of carbon fiber. Then remove the Assembly from the autoclave and mounted on the shaft 22, two additional technological mandrels 24 and 25 along the edges of the Assembly. Put the adhesive tape on the cylindrical parts of the heads 6, 7 and 8 and vykladyvai the lower 8 bottoms with adhesive films. Then spread the entire length of the Assembly with the formation of the front 12 and rear 13 of the skirt layer 3 internal cladding of the fiber filler 5 cell or isoprenoid design installed in the ends of the connecting profiles 14 of the carbon fiber and the outer layer 4 panels of carbon fiber. Place the Assembly in an autoclave, where the curing of the layers and gluing the bottoms. Then remove the Assembly from the autoclave, technological remove the shaft 22 and the two extreme technological mandrels 24 and 25. Remove, for example, leaching of two internal technological mandrels 21 and 23 through the openings in the bottoms. Then cover with a layer of carbon fiber hole in the top 6 bottom, remaining after the removal process of the shaft 22. The holes in the intermediate 7 and the bottom 8 heads attached consumable pipelines.

A method of manufacturing a rocket unit for option 2 is as follows.

Make a separate section 16 of the rocket block, which at the end of the process mandrel 26 (Fig.5) spread the layers of polymeric liner 9 (Mylar or polyimide film) and carbon fiber 10 with the formation of the bottom cylindrical section. Install side referred to the positive post on the cylindrical section between the extreme ends of the mandrels 26 and 27 with the formation of the protruding skirts layer of polymeric liner 11 (Mylar or polyimide film), layer 3 internal cladding of the fiber filler 5 cell or isoprenoid design installed in the ends of the connecting profiles 14 of the carbon fiber and the outer layer 4 panels of carbon fiber. Place the Assembly in an autoclave, where the curing of the layers and gluing the bottoms. Then remove the Assembly from the autoclave and remove the two technological mandrels 26 and 27. Then, the resulting section 16 of the missile unit is combined with two similar sections, pre-causing the abutting ends of the polymer liquid sealant 19, with the formation of two tanks with the top 6, common intermediate 7 and the bottom 8 bottoms and the front 12 and rear 13 skirts. Section connected with fasteners, such as bolts 17, which is installed through a window 18 in the connecting profiles 14 from carbon. Then place seam closed diverter strips 20 (Fig.2, 3).

Rocket block made according to the second variant, provides additional technical result consists in the simplification of the technology. This is due to the fact that there is no need to use complicated washed out or collapsible mandrel.

The declared design of the rocket block, made of Wildkogel complexity of manufacturing, to improve fatigue and impact strength, and also to facilitate repair work on it if necessary.

1. Rocket block containing the front and rear skirts, docking profiles and fuel compartment, made in the form of block tanks, including two tank with a common intermediate plate, characterized in that the front and back of the skirt in one piece with the shell tanks in the form of a three-layer shell comprising inner and outer skin of carbon fiber and the filler between them, the ends of which are installed docking profiles of carbon, and the upper, intermediate and lower bottoms of these tanks are made in the form of a two-layer shell with a cylindrical sections comprising an inner layer of polymeric liner and the outer layer of the carbon fiber, and on the cylindrical section of the inner lining of the shell between the upper and lower ends mounted polymeric liner, to which by means of the adhesive film attached to the said bottom.

2. Rocket block containing the front and rear skirts, docking profiles and fuel compartment, made in the form of block tanks, including two tank with a common intermediate plate, characterized in that the rocket block wyyy and outer skin of carbon fiber and the filler between them, at the ends of which are installed docking profiles of carbon fiber, and the bottom with a cylindrical section made in the form of a two-layer membrane comprising the inner layer of polymeric liner and the outer layer of carbon fiber on the inner lining of the shell is selected polymer liner, to which by means of the adhesive film with the formation of the protrusion of these skirts attached to the bottom, and the sections are connected by means of fixing elements. placed in a docking profiles, with the sealing seats of the dock sections.

3. A method of manufacturing a rocket unit, including the manufacture of front and rear skirts, jackets and bottoms of the tanks and connect them to the missile unit, characterized in that post on the ends technological mandrels mounted on shaft technological, layers of polymeric liner and carbon with the formation of the upper, intermediate and lower ends of the cylindrical sections and the subsequent curing of the layers of carbon fiber in the autoclave, mounted on a shaft technological along the edges of the resulting assemblies two additional technological mandrel, put adhesive tape on the cylindrical sections of each plate, spread a layer of polymeric liner on the entire length of the Assembly with the formation of the front and rear skirts the inner cladding layer of the fiber filler installed in the ends of the connecting profiles of the carbon fiber layer and the outer skin of carbon fiber, carry out the subsequent curing of the layers and gluing the bottoms in the autoclave, technological remove the shaft, two extreme these additional technological mandrels and two inner specified technological mandrels.

4. A method of manufacturing a rocket unit, including the manufacture of front and rear skirts, jackets and bottoms of the tanks and connect them to the missile unit, characterized in that it is made a separate section of the rocket block, which lay at the end of the first process of the mandrel layers of polymeric liner and carbon with the formation of the bottom cylindrical section and install from the mentioned end of the second production mandrel, put adhesive tape on the cylindrical section of the bottom, consistently put on the cylindrical section between the extreme ends of the first and second technological mandrels with the formation of the protruding skirts layer of polymeric liner, the inner cladding layer of the fiber filler installed in the ends of the connecting profiles of the carbon fiber layer and the outer skin of a technological mandrel, then connect the received section of the fuel compartment with fasteners placed in a docking profiles, with the sealing seats of the dock sections and with the formation of two tanks with a common intermediate bottom, front and rear skirts.

 

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