Patent Grant
8043396
The present invention relates to propellant tanks for space platforms, launchers and every sort of space transport craft.
More specifically, the present invention relates to the need to decrease the launch mass of the space vehicle, to reduce production and development costs and, simultaneously, to reduce the time required for commissioning a tank.
Tanks for transporting propellant are used to store the two components of the hypergolic mixture (fuel and oxidiser), aboard the space vehicle, throughout its operating life.
The constituents of the hypergolic mixture must be fed to the engines at a well defined supply pressure.
This specific function is carried out using pressurising gases, normally inert gases, which thus assure compatibility with the propellant.
To avoid the ingestion of gas bubbles into the engines, which can generate their malfunction, it is necessary to separate the liquid phase of the propellant from the gaseous phase of the pressurising fluid, at the time the propellant is fed into the engine supply lines.
The need to lower costs and to provide ever higher performance, required from new generation space vehicles, both for telecommunication purposes, and for interplanetary exploration missions, lead to specify the use of light-weight components with short development and construction times.
The weight of the propellant tanks varies from a minimum of 25% to 70% of the entire propulsion system, if considered without the propellant itself.
These values support recent efforts by the industry in the development of tanks made of composite materials, which require a liner that is compatible with the propellant, which is then enveloped by carbon fibre, which provides structural strength.
Normally, such liners are made of Titanium and their weight is 30% of the total weight of the tank.
Moreover, the surface tension device for propellant feeding also needs to be integrated with the liner. Said device is also called PMD, or Propellant Management Device.
With said device, with traditional technologies, 40% of the total weight of the tank is covered.
Lastly, recent requirements are for a drastic reduction in the development time of the tanks. This, together with the reduction in development costs, can be obtained by using alternative materials, more rapidly obtained, and innovative designs, which markedly reduce construction and control activities.
These are the novelties introduced by the present invention of the integrated plastic liner, both in terms of the material considered and of the design guidelines.
The existing technology proposes liners for tanks for spacecraft, made of Titanium and of plastic material. Both incorporate no device for propellant distribution.
In general, plastic liners, as they have been developed heretofore, have a bare configuration: smooth inner walls, without any device supporting any function whatsoever. These are used only for pressurising gas tanks. Currently propellant distribution devices are integrated with metallic liners, during their assembly. They comprise the following elements: bulkheads; tunnels; traps for liquids; sumps, which are welded to each other and, subsequently, are welded to the liner itself.
In addition to the above, there are other three solutions:
The apparatus of the present invention was devised as a result of specific requirements, not yet completely solved, aimed at minimising the weights of the propulsion system of a spacecraft.
The Integrated Plastic Liner is made with PTFE, in such a way as to attain the main objective, which is weight reduction and compatibility both with the fuel and with the oxidiser.
The liner is not a structural element, so its thickness can be reduced to a value that is sufficient to perform its containment function over time.
The liner is thus reinforced by means of high strength fibres, e.g. carbon or Kevlar fibres.
The liner typically has cylindrical or spherical shape and it is moulded in two parts: the lower dome and the upper dome.
The lower dome incorporates the components of the propellant distribution device: sump, liquid trap and bulkheads.
Being integrated with the dome, these components are integral parts thereof and manufactured by means of the same moulding equipment.
The sump can be pre-built, depending on the type of configuration, and moulded with the lower dome, in order to obtain a single final component.
The non-return valve, which is a device that prevents the formation of a hypergolic mixture of fuel and oxidiser, is designed and manufactured completely integrated with the upper dome of the liner. This approach is applicable both to the elastic element (spring) and to the sealing element of the valve itself.
To obtain a higher a higher level of redundancy, a second valve can be provided inside a pipe segment, made of the same material, which is integrated on the first, by ultrasonic welding, and subjected to winding, to assure pressure tightness. Greater reliability is thereby obtained with respect to the sealing function of the non-return device.
The two domes, thus obtained, are then integrated together and welded with ultrasonic welding, to prevent any kind of leak to the exterior.
It is therefore an object of the invention a Tank apparatus able to provide compatibility with different types of fluids, able to contain and distribute fluids without gasses included under micro-gravity conditions, to prevent vapours from flowing back upstream and to minimise the global weight of the tank, characterised in that:
a) the containing component of the tank is produced by means of plastic material, compatible with the fluids the tank has to store, by means of a hot forming technique;
b) it internally contains a device for the distribution of the fluid and a device to prevent vapour back-flow, both devices produced, completely or in part, by means of the same plastic material used for said containing component;
c) it is formed by a lower dome made of plastic, which integrates within it said device for the distribution of the fluid without the pressurising gas, to feeding lines by means of elements such as traps, bullheads and sumps; and by an upper dome made of plastic, which integrates within it the device for the prevention of the vapour back-flow; wherein both domes integrate a pipe segment in order to feed the lines with the fluid contained by the tank, and the tank itself with the gas necessary to keep it under pressure.
Fluid is to be intended as fluid or liquid, particularly fluid or liquid propellant.
Preferably the sump element is made of metallic material and subsequently integrated to the trap for fluids, and introduced inside the mould of the lower dome, in such a way as to obtain the fully integrated final component.
Preferably the trap for fluids is further integrated with an additional trap to retain the fluids in gravitational environment and during a horizontal transport of the tank containing the fluids, partly or completely filled.
Preferably the trap for fluids and the bulkheads are provided for the function of dampening the dynamic loads, due to the displacement of the fluids inside the tank, more preferably the material of the containing structure of the liner is flexible, thereby increasing its lightness, having reduced its thickness, by pressurisation during the process of winding with fibres for the reinforcement of the structure.
Preferably the outer surface of the containing structure of the liner is appropriately shaped to generate a correct adhesion of the fibre, during the fibre winding process.
Preferably said non-return device is doubled.
The present invention shall now be described by means of non limiting examples, in reference to the following Figures:
The main characteristics of uniqueness of the invention are highlighted by the details of the drawings. Said details were numbered to facilitate search and comprehension.
The components of the present invention can be dimensioned differently, according to the requirements of the mission and the consequent propellant distribution need.
Therefore, provided that the main guideline of the present invention is the possibility of obtaining the containment structure of the liner and of the device components, both for propellant distribution and for vapour retention, in integrated fashion, by a single moulding operation, the description of the details of the component does not have the intention of limiting the scope of the invention.
The present invention encloses a new liner configuration, a new method for manufacturing and assembling the liner, in such a way as to incorporate three different basic functions for a propellant tank in the same unit:
a. Containment of the fuel and of the oxidiser
b. Distribution of the fuel and of the oxidiser without gas inclusions.
c. Retention of the vapours of fuel and oxidiser.
The current technology, the one still in use and overtaken by the present invention, provides for the second and the third function to be carried out by components built separately and assembled with the tank at a subsequent time:
The present invention consists of a design that, together with the fabrication method for moulding, integrates all functions in a single element, obtained by PTFE moulding, compatible both with the fuel and with the oxidiser.
Said element, for the intrinsic characteristics of the moulding process, is manufactured in two halves (see
The lower dome (11),as shown by
Traps (32)
Bulkheads (33)
The Sump (31), depending on the configuration, could be obtained separately and introduced into the mould, to obtain the finished product by co-moulding.
The Sump (31), the trap (32) and the bulkheads (33) have the characteristic of retaining the liquid propellant, during the orbital phases of the mission of the spacecraft, exploiting the surface tension properties of the propellant itself. In this way, once it is filled and wet on the ground, during the filling of the tank, the liquid phase of the propellant is maintained separate from the gaseous phase of the pressuriser.
The elements of the propellant distribution device, as described, are not limited to performing the function of preventing the ingestion of gas in the propellant lines, but they also perform, intrinsically, the function of dampening the forces induced by the dynamics of the propellant inside the tank, during the acceleration phases.
The liquid trap (32) is typically configured with star shape, whose outer radius, depth and number of plates which constitute it, are defined by the propellant distribution requirement (
The present invention is not limited to a few specific missions, but it enables to generate a broad range of different configurations and dimensions.
A similar statement can be made for the bulkheads (33).
Typically, they are equally distributed along the inner walls of the liner, in circumferential fashion.
They can be obtained according to a broad range of different configurations and dimensions.
The lower dome has, in its bottom, a pipe segment which incorporates a metallic cylinder, co-moulded with the plastic dome, which allows to integrate the tank with the propellant feed pipeline. This pipe segment is reinforced, together with the entire structure of the liner, by means of fibres.
The reinforcement is necessary to allow to withstand the pressure levels reached during the working life of the tank.
The same approach is applied to the upper dome (12), as shown in
The upper dome (12), as shown by
The pipe segment (21)
The spring (23)
The valve (22)
The valve seat (24)
The pipe segment is typically cylindrical (21), incorporates the valve seat (24) of the non-return device.
This device serves the purpose of preventing fuel and oxidiser vapours from flowing back, upstream of the respective tanks, which, obviously, to maintain separate the two components of the hypergolic mixture, are two distinct units.
The second half of the check device is formed by the valve (22), which is held in pressure by an S spring (23) against its seat (24).
The S spring also serves the function of physical connection between the valve (22) and the pipe segment (21), which serves as a container of the device itself, as shown by
The two domes (11 & 12), which can have a semi-spherical, cylindrical, elliptical shape or any other axisymmetrical shaped, concur in defining the final configuration, as highlighted by
The two domes are welded together (10) with the ultrasonic technique, to obtain the definitive configuration (
The need to prevent fuel and oxidiser vapours from flowing back upstream is determined by the need to maintain constant the pressure inside the propellant tanks, by admitting gas from outside the tanks.
Generally, the pressurising gas system simultaneously feeds both the fuel and the oxidiser tank.
These generate vapours which can flow back upstream. Therefore, it is necessary to avoid at all costs any contact between the fuel and the oxidiser and prevent the formation of a hypergolic mixture, when it must not be formed.
The non-return device, as it is conceived, can be made redundant in series, increasing the efficiency of its function.
Redundancy can be obtained by manufacturing, with a dedicated mould, an additional non-return device (20).
A sub-assembly as shown in
The functions described above, in their integration with the liner, are not limited to use for propulsion systems. More in general, all those hydraulic systems, to be used for space applications or in the absence of gravity, which need a distribution of gas-free liquids and/or the prevention of vapour back-flow, can benefit from the present invention.
One or more elements of the invention can be made of metal and, subsequently, co-moulded with the main structure of the liner (10), in such a way as to be integral parts of the component.
The present invention can be embodied in the most varied forms, and with the most varied materials, without thereby deviating from its constituent and essential characteristics, as claimed below.
Shapes and materials are generally selected according to the needs of the mission for which it is provided and of the liquids it has to transport/store.
The description of the invention must be considered solely by way of illustration and it shall for no reason be seen as restrictive.
Therefore, the scope of the invention shall be construed as indicated by the appended claims, rather than by the preceding description.
Any modification that falls within the scope and a sphere of equivalency with respect to the appended claims shall be considered included within the scope of the claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| RM2005A0347 | Jun 2005 | IT | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/IT2006/000500 | 6/28/2006 | WO | 00 | 7/24/2009 |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2007/004248 | 1/11/2007 | WO | A |
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