WO2022264177A1 - Système de propulsion électromagnétique pour mouvement d'engin spatial sans l'émission d'une masse de réaction - Google Patents

Système de propulsion électromagnétique pour mouvement d'engin spatial sans l'émission d'une masse de réaction Download PDF

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Publication number
WO2022264177A1
WO2022264177A1 PCT/IT2022/050131 IT2022050131W WO2022264177A1 WO 2022264177 A1 WO2022264177 A1 WO 2022264177A1 IT 2022050131 W IT2022050131 W IT 2022050131W WO 2022264177 A1 WO2022264177 A1 WO 2022264177A1
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WO
WIPO (PCT)
Prior art keywords
propulsion system
emission
reaction mass
arms
dipole
Prior art date
Application number
PCT/IT2022/050131
Other languages
English (en)
Inventor
Emidio LAURETI
Original Assignee
Laureti Emidio
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Laureti Emidio filed Critical Laureti Emidio
Publication of WO2022264177A1 publication Critical patent/WO2022264177A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/409—Unconventional spacecraft propulsion systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H99/00—Subject matter not provided for in other groups of this subclass

Definitions

  • the invention relates to an innovative propulsion system for spacecraft, by means of a technology which eliminates any type of emission of reaction mass.
  • 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.
  • ion thrusters 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.
  • 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 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • the container is made of bakelite, teflon, or vitronite, in order to reduce any impedance disturbances or electromagnetic interactions.
  • the V dipoles tend to overheat, due to the resistance that the current encounters during its path.
  • 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.
  • 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.
  • 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.
  • the entire system 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.
  • 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.
  • -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.
  • a plurality of sheets of vitronite 12 are used to increase the dielectric permeability of the entire system.
  • FIG. 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.
  • 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 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.
  • V dipole 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.
  • 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.
  • 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.
  • 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.
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Vehicles With Linear Motors And Vehicles That Are Magnetically Levitated (AREA)
  • Motorcycle And Bicycle Frame (AREA)
  • Details Of Aerials (AREA)

Abstract

Système de propulsion électromagnétique pour mouvement d'engin spatial sans émission de masse de réaction, caractérisé en ce qu'il comprend deux bras (10) qui partagent un de leurs sommets en un point appelé point d'alimentation (14) ; ledit point d'alimentation (14) étant alimenté par une fréquence électromagnétique UHF adaptée à faire un flux de courant variable dans les bras (10) générant un champ électromagnétique qui interagit avec le courant des deux bras (10) par la loi de Lorentz, créant un effet d'auto-propulsion du système au moyen d'énergie électrique.
PCT/IT2022/050131 2021-06-18 2022-05-18 Système de propulsion électromagnétique pour mouvement d'engin spatial sans l'émission d'une masse de réaction WO2022264177A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT102021000015986 2021-06-18
IT102021000015986A IT202100015986A1 (it) 2021-06-18 2021-06-18 Sistema di propulsione elettromagnetica per la movimentazione di veicoli spaziali senza l'emissione di massa di reazione.

Publications (1)

Publication Number Publication Date
WO2022264177A1 true WO2022264177A1 (fr) 2022-12-22

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Family Applications (1)

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PCT/IT2022/050131 WO2022264177A1 (fr) 2021-06-18 2022-05-18 Système de propulsion électromagnétique pour mouvement d'engin spatial sans l'émission d'une masse de réaction

Country Status (2)

Country Link
IT (1) IT202100015986A1 (fr)
WO (1) WO2022264177A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4663932A (en) 1982-07-26 1987-05-12 Cox James E Dipolar force field propulsion system
EP1071610A2 (fr) 1999-02-10 2001-01-31 Laurence G. Waters Systeme de propulsion de vehicule aerospatial
US20060038081A1 (en) 2004-08-04 2006-02-23 St Clair John Q Electric dipole spacecraft
US20120137652A1 (en) 2005-10-07 2012-06-07 Asprey Margaret W Electromagnetic Thrust System

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN209366480U (zh) 2019-01-09 2019-09-10 酷黑科技（北京）有限公司 一种涵道推进器

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4663932A (en) 1982-07-26 1987-05-12 Cox James E Dipolar force field propulsion system
EP1071610A2 (fr) 1999-02-10 2001-01-31 Laurence G. Waters Systeme de propulsion de vehicule aerospatial
US20060038081A1 (en) 2004-08-04 2006-02-23 St Clair John Q Electric dipole spacecraft
US20120137652A1 (en) 2005-10-07 2012-06-07 Asprey Margaret W Electromagnetic Thrust System

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Publication number Publication date
IT202100015986A1 (it) 2022-12-18

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