Propellant tank

FIELD: spacecraft tanks for liquid and gaseous components under excessive pressure.

SUBSTANCE: proposed tank has thin-walled shell of revolution and load-bearing attachment member in form of rod piercing the shell. Ends of rod are provided with fittings for securing it to shell. Attachment is mainly made by welding. Ends of rods are also provided with flanges having attachment units for securing them to adjacent structural members of spacecraft. Hollow rod consists of two pipes inserted one in other and welded together. Body of rod has holes in lower and upper parts.

EFFECT: increased net volume of tank; enhanced reliability.

2 cl, 2 dwg

 

The invention relates to the field of space technology, namely the device of the fuel storage tanks on Board the spacecraft liquid and gaseous media under pressure. In addition to storage on Board the spacecraft fuel tanks are used in a constructive nodes that must take and pass a large load, the direction of which is parallel or close to the longitudinal axis of the spacecraft.

Known fuel tank for space purposes (see Itelecom "Technology Assembly and testing of space vehicles", M.: engineering, 1990, p.65, 65), which is made in the form of thin shells of revolution. On its outer surface placed attachment points made in the form of brackets, and placed on the shell capacity in one of its cross section.

The disadvantage of this fuel tank is that it is not intended for inclusion in the overall power circuit: the shell of the fuel tank only works on the perception of internal pressure and does not accept and does not transmit longitudinal and close to the direction of the load.

This deficiency is partially removed in the design of the fuel tank for space purposes (see Itelecom "Technology Assembly and testing of space vehicles", M.: engineering, 1990, p.65, 65, RIS). Fuel tank you who olden in the form of a thin-walled shell of rotation and provided with attachment points in the form of brackets. The attachment points of the fuel tank exploded at his height, with their help, the tank is connected with the adjacent structural elements of the spacecraft.

The placement of the mounting brackets tank exploded at a height relative to the longitudinal (vertical) axis of the tank provides the perception and transmission of the shell of the tank longitudinal or close to it loads from adjacent structural elements of the spacecraft. However, the weight of such fuel tank is large.

The closest in technical essence and the achieved result of the present invention is a fuel tank (capacity)that is described in the patent for the invention №2042873, IPC F 17 C 1/00, B 64 G 1/40, publ. 27.08.95, This technical solution chosen for the prototype.

Known fuel tank is made in the form of thin shells of revolution with located on the outer surface of the attachment points, while the tank is provided with a penetrating shell and bonded with her power rod. To bond the shell to the ends of the rod made two fitting. The connection shell fittings is carried out by welding. Fasteners are attached to the fittings flanges in the form of brackets. If necessary, the flanges can be fitted with additional components for mounting adjacent elements of design space apparatus is ATA.

The advantage of this design of the fuel tank is minimizatio its mass, as well as the ability to perceive and transfer significant external loads in the direction of the longitudinal axis.

The disadvantages of the known constructions of the fuel tank is reduced, the capacity of the fuel tank due to the location within the capacity of the power terminal, and the lack of manufacturability tank located inside its core.

The technical problem solved by the present invention, is to increase the amount of fuel in the tank while minimizing its weight and increase manufacturability of its manufacture.

The problem is solved due to the fact that the fuel tank as in the prototype, contains a thin-walled shell of rotation and the power element mounting, made in the form of a rod, penetrating the shell, with fittings for attaching the shell and flanges, which are the attachment points with the adjacent structural elements.

Claimed fuel tank differs from the prototype in that the rod is made hollow with holes done in his case.

While specified power rod is made of two tubes inserted into each other, and welded together. Holes are located in the upper and lower parts of the stem.

Execution of the fuel tank of the thin-walled shell with whom the combination with a hollow rod, filled with liquid fuel, allows you to increase the amount of fuel placed in the tank in combination with the minimization of the mass of the fuel tank. To ensure the effective discharge of fuel from the internal cavity of the rod into the internal cavity of the tank is provided is made on the body of the stud holes. Execution of the hollow rod made of two pipes allows to compensate the deformation (bending) of the pipe during Assembly of the tank. This improves the manufacturability of the fuel tank.

The invention is illustrated by the following drawings:

figure 1 is a longitudinal section of the fuel tank, figure 2 - cross section of the rod of the fuel tank with a hole,

The fuel tank contains a thin-walled shell of revolution 1, made of aluminum alloy type AMG-6, power terminal 2, inside which is placed an internal cavity 3. In the top and bottom of stud holes 4. Terminal 2 can be made of two pipes 5 and 6, is inserted into each other and welded together (seam - welding two pipes). On the ends of the rod made two fitting 7, connected to the shell 1 capacity. Connection fittings 7 of the shell 1 is made by welding. The fittings 7 are attached to the flanges 8 for attaching the fuel tank to adjacent structural elements of the spacecraft. If necessary, the flanges can be sabrinacastillo sites for attachment of adjacent structural elements of the spacecraft.

For filling the fuel tanks with liquid and gas are the fittings, not shown in the drawings. To ensure the intake of fluid in the space environment the tank is supplied with intake, for example, capillary type. When filling the reservoir is filled with fluid or gas within the shell of the tank and inside the cavity of the rod 3. When you reduce the level of fuel in the tank the fluid from the internal cavity of the rod comes through the bottom hole 4, through the top opening into the internal cavity enters the gas pressurization.

The Assembly of the fuel tank is carried out in the following sequence.

First, the shell 1 is welded with fittings and welded flanges. Then the pipe, forming a power rod, inserted into each other and welded together with fittings. After the pipes are welded together.

The calculations show that the implementation of the rod is hollow with holes allows you to increase the amount of fueling for 5...10 kg when the length of the rod tank of the order of 1 m, to ensure the effective discharge of the fuel from the tank, as well as to simplify and improve the technology of Assembly of the fuel tank. This allows you to increase the stock of the characteristic velocity of the spacecraft.

1. A fuel tank containing a thin-walled shell of revolution and power fastening element in the form of penetrating about the point of the rod, at the ends of the fittings to mount, mainly by welding, to the shell and flanges with attachment points to adjacent structural elements, characterized in that the rod is made of two hollow tubes inserted into each other and welded together, and in the case of rod holes.

2. Fuel tank according to claim 1, characterized in that the apertures are done in upper and lower parts of the stem.



 

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