ELECTROMAGNETIC PROPULSION SYSTEM FOR SPACECRAFT MOVEMENT WITHOUT THE EMISSION OF REACTION MASS Field of the art

The invention relates to an innovative propulsion system for spacecraft, by means of a technology which eliminates any type of emission of reaction mass.

Such technology is essential for the movement of satellites and spacecraft already in orbit, since the mass which characterises them does not affect performance.

Known art

Most space designs have taken place thanks to the discovery of the appropriate propulsion means; technology must be prepared which allows a considerable mass to reach the Earth's orbit. It is also essential to provide spacecraft with a movement system capable of operating even if oxygen is not present.

The most commonly adopted solutions are ion thrusters.

Said ion thrusters use ion rays (atoms or electrically charged molecules) to create a thrust in accordance with the third principle of dynamics. The method for accelerating the ions varies, but all the designs benefit from the ratio of charge to ion mass. This ratio can mean that even relatively small potential differences can create high velocities in the exhaust gases. This reduces the amount of reactive mass or fuel required, but increases the amount of specific power needed compared to that of chemical rockets. Ion thrusters are therefore capable of obtaining very high specific pulses. The disadvantage of the low thrust is a poor acceleration of the craft, since the mass of the electric current units is directly proportional to the amount of energy supplied. This makes ion thrusters unsuitable for launching vehicles into orbit, but ideal for the propulsion applications in space.

The main limiting factor of ion thrusters is their low thrust force. This thrust is the result of the high velocity of the exhaust gases, which requires a lot of energy, and performance is further limited by the specific power of the energy sources. Furthermore, many thrusters are capable of managing only small flows of propellant, for example the models with an electrostatic grid suffer from "spatial charge" effects in high flows. This poor acceleration results in the need to provide a continuous thrust for a long time to obtain a reasonable change in speed. To achieve these speed variations, ion thrusters are designed to last from weeks to years.

Although they do not contain moving parts subject to friction, these engines are nevertheless subject to wear phenomena mainly due to the impacts between the ions and the electrostatic grid, which cause the erosion thereof.

In the patents previously filed, no further innovations have emerged exploiting ion thrusters.

In US Patent 2012/137652, a method for developing the thrust from a current flow is disclosed.

In a first embodiment, a plurality of coils of wire wound according to an asymmetrical pattern is physically connected to an electrical energy source, developing the thrust in a single direction.

Patent EP 1071610, on the other hand, claims a propulsion system for spacecraft which uses dipole radiators in an interlayer space between the outer and inner layers of the craft's hull. The microwaves are sent through a control console to the radiators.

On 12 May 1987, US 4663932 was published, which deals with a propulsion system which exploits a dipole force field comprising a source coming from an alternating electric field to produce electromotive force lines which extend in a first direction and which vary at a selected frequency, comprising an electric field intensity of a predetermined magnitude.

US 2006/038081 discloses an invention related to the creation of a rotating spacecraft which produces an electric dipole on four spherical and rotating conductive domes, generating a lift force on the hull.

The object of the patent, described in the present application, is therefore to create a propulsion system by means of electromagnetic fields, adapted to move spacecraft without emitting reaction mass.

Description of the invention

According to the present invention, an electromagnetic propulsion system is created for spacecraft movement without the emission of reaction mass which effectively solves the aforementioned problems.

The propulsion system in question, exploits the Lorentz force, deriving from the Law of Lorentz, which is emanated from the two arms of a V dipole, made of conductive material. The two arms meet, always mutually isolated, in a point called "feedpoint", said point creates an acute angle in which the emitted thrust of the system is greater with respect to the opposite ends of the arms.

Said arms, in an embodiment thereof, comprise therein a plurality of thin and enamelled copper wires, in order to increase the surface available to the current and thus to increase the current flow, since at high frequencies the so-called "skin effect" occurs. Once the current flow begins to flow within the V dipole, at a UHF frequency, the Lorentz forces tend to impart to the arms a force orthogonal to each arm adapted to open the feedpoint angle, since the force generated by the first arm towards the other is equal only in absolute values to that generated by the second. Said forces, given the incidence of the vectors for a feedpoint angle between 1 and 179 degrees, lead to a positive result, adapted to move the system in question by means of electrical energy, exploiting the electromagnetic fields. In fact, it is the non-null result of the vectors on the arms which generates the necessary thrust. Said arms, comprised within a common V dipole, due to problems deriving from adaptation of impedance for frequencies between 430 and 435 Mhz, are between 14 and 18 cm long, with an acute angle therebetween comprised between 28 and 30 degrees.

To increase said propulsive thrust, in the system in question, it is possible to add a plurality of V dipoles, thus modulating the system.

However, adding a greater number of V dipoles forces implementing the system, adding a phase shifter, adapted to phase the plurality of dipoles in order to synchronise the resulting forces, facilitating the operation of the propulsion system. A rigid structure, preferably made of wood or any other insulating material, is adapted to hold the V dipole in place, inside an external container.

Said container is adapted to accommodate all the components necessary to obtain the resulting thrust, obtained from the electromagnetic fields of the V dipole. In an embodiment thereof, the container is made of bakelite, teflon, or vitronite, in order to reduce any impedance disturbances or electromagnetic interactions. During the operation of the present system, the V dipoles tend to overheat, due to the resistance that the current encounters during its path. To cool the system, a plurality of ferrites are used, of a thickness of less than 4 mm arranged in an L shape, but also in other shapes, along the arms, in order to dissipate the accumulated heat outwards.

Said ferrites are advantageously used for enhancing the magnetic field and for adapting the impedance, in addition to being useful for preventing the current from bouncing back towards the amplifier.

A plurality of sheets of vitronite, 0.5 mm thick, are used to fix said ferrites. Thanks to the use of the vitronite sheets, the system improves its dielectric permeability.

Upstream of the container, which comprise the V dipoles therein, an amplifier with a power of at least 600W is installed, adapted to provide the necessary power to the system to obtain the thrust useful for propulsion. It is further necessary to add "circulating" elements to prevent the energy reflected by one or more dipoles from returning to the amplifier and damaging it.

Before the amplifier, a preamplifier is installed from where the frequency is regulated, comprised between 430 and 435 Mhz, and the power delivered by the amplifier to the dipoles. All the various elements are connected by coaxial cables at 50 ohms of impedance.

Being powered by means of electrical energy, the entire system can count on a plurality of batteries, adapted to accumulate the energy which will be subsequently required during the trip. It is important to specify that the increase in weight of the entire system, due to the increase in propulsion power, is irrelevant during space travel where the force of gravity is zero or almost zero compared to that of the earth.

A plurality of solar panels are installed outside said container, in order to charge the batteries installed therein. In an embodiment thereof, the present propulsion system is powered by means of nuclear energy, making the system completely autonomous and independent from sunlight.

A CPU is located inside the present system, and is adapted to manage the information obtained from the inertial sensor regarding the flight attitude. The propulsion system in question is advantageously remotely operable, also favouring the transport and movement of satellites and goods in orbit without the need for a pilot. The advantages offered by the present invention are apparent in the light of the description set forth herein and will be further clarified by the accompanying figures and the detailed description.

Description of the figures The invention will be described below in at least one preferred embodiment by way of non-limiting example and with the aid of the accompanying figures, in which:

-FIGURE 1 shows a section of the container 11 adapted to comprise the V dipole therein by using an internal structure 15 made of wood. Said internal structure 15 branches off within the container 11, in order to fix the position of the V dipole in the drive phases of the propulsion system.

Said V dipole comprises two arms 10, which are joined in a single point defined feedpoint 14. A plurality of ferrites 13 are fixed on the aforesaid arms 10, in order to also dissipate the heat emitted during the inflow of electric current.

To fix the ferrites 13, a plurality of sheets of vitronite 12 are used to increase the dielectric permeability of the entire system.

-FIGURE 2 shows a diagram which simplifies the system necessary for the operation of the propulsion system in question. A plurality of solar panels 16 are installed to recharge the batteries 17 which, in turn, power the transceiver which acts as a preamplifier 18.

Downstream of the preamplifier 18, an amplifier 19 is installed adapted to provide the necessary power to the V dipole, comprised within the container 11. Detailed description of the invention

The present invention will now be illustrated by way of non-limiting or binding example, using the figures which illustrate some embodiments in relation to the present inventive concept.

With reference to FIG.l, the content of the container 11, the main subject of the present invention, adapted to propel any spacecraft without emitting reaction mass, is illustrated.

The propulsion is provided by a strong inflow of very high frequency current, adapted to flow along the arms 10 of a V dipole. Said arms 10 are made of conductive material and can also comprise therein 600 thin and enamelled copper wires. Both arms 10 are joined in a shared point, called feedpoint 14, where the greatest thrust occurs due to the electromagnetic fields emitted.

The entire V dipole is supported by an internal wooden structure 15, adapted to fix the position of the arms 10 and their feedpoint 14 even in the most eventful phases of travel.

In order to cool the plurality of copper wires forming the arms 10 of the dipole, a plurality of ferrites 13 of a thickness of 1 mm are installed, adapted to dissipate the heat accumulated thanks to their characteristic "L" shape.

To facilitate the installation of the ferrites 13, a plurality of sheets of vitronite 12, 0.5 mm thick, are used to increase the magnetic permeability of the entire propulsion system also as a function of the impedance adaptation.

The container 11 comprising the V dipole can be made of any fireproof material but bakelite or teflon are preferable.

With reference to FIG.2, the diagram of the system which characterises the propulsion system in question is illustrated.

In fact, a plurality of solar panels 16 are installed in order to recharge the batteries 17 present within the propulsion system.

The solar panels 16 are replaced, in an embodiment thereof, by the energy obtained by nuclear cleavage, in order to make the system in question independent from sunlight.

Once recharged, the batteries 17 power the preamplifier 18, consisting of a common transceiver suitable for working with frequencies between 430 and 435 MHz. Said preamplifier 18 guides the amplifier 19 during the performance of its functions. In fact, said preamplifier 19 is adapted to provide the necessary power for driving the V dipole, comprised within the container 11.

The most commonly used amplifier 19 is the 600W Archimede.

Lastly, it is clear that the invention described up to now may be subjected to modifications, additions or variants obvious to those skilled in the art, without departing from the scope of protection outlined by the attached claims.