JP2009115069A - Electric propulsion system by electromagnetic field - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To solve problems wherein since in many cases, a conventional electric propulsion system used in the aerospace is an ion jet type most of which have a structure for ionizing and injecting a propellant, the electric propulsion system has small thrust force and increased weight due to the propellant and interstellar matter is too thin to obtain thrust force if used. <P>SOLUTION: Magnetic poles and electrodes are installed in a body so that the electromagnetic field in which the magnetic poles and electrodes are approximately orthogonal to each other has an annular shape. In this annular electromagnetic field, supply and discharge of electric charges or bias of electric charges by an electric field is generated. Thus, ring current is generated in the annular electromagnetic field to generate a magnetic field. Due to the action of the magnetic field generated by the body and the magnetic field generated by the ring current, propulsive force is generated by the magnetic force. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a propulsion device for propulsion by an electric force using a magnetic field and an electric field.

  Conventional electric propulsion devices used in outer space have many ion jet systems, but most of them have a structure in which a propellant is ionized and ejected, and the thrust is small and the increase in weight due to the propellant has also been a problem. Also, to use interstellar matter, it was too thin and almost no thrust was obtained.

  In order to explain the principle of this propulsion device, FIG. The airframe has a cylindrical shape and is made of an insulator. There are a magnetic pole 1 and a magnetic pole 2 in a form that goes around the body of the body 9. Similarly, there are an electrode 3 and an electrode 4 that go around the body. 5 is a cathode and 6 is an anode. The electrodes 3 and 4 are insulated from the outside.

  FIG. 2 shows in the cross-sectional view of FIG. 1 elements that are important for understanding the principles of the present invention. Since the figure is difficult to see, the cross section of the body 9 is not hatched. In space, gas is ionized and is in a plasma state, and this propulsion device exists in such a space.

  An electric current is passed through the coil 7 to magnetize the magnetic body 8 shaped like a dumbbell, and a magnetic field B of which the magnetic pole 1 is N and the magnetic pole 2 is S is generated. A negative voltage is applied to the electrode 3 inside the magnetic field B, and a positive voltage is applied to the electrode 4 on the magnetic pole side to generate an electric field A.

  Both the magnetic poles and the electrodes make a round around the body, and an electromagnetic field in which the magnetic field B and the electric field A are almost orthogonal can be formed in an annular shape. As a result, the charged particles existing around the body 9 begin to drift in the direction perpendicular to the magnetic field B and the electric field A, that is, the direction C that makes a round of the body.

  In this state, there are approximately the same amount of electrons and + ions, but electrons are positively supplied from the cathode 5 into the magnetic field, and the anode absorbs the electrons. Since the movement of the charge is limited by the magnetic field, there are many electrons on the side close to the electrode 3 of the magnetic field B, and there are many + ions on the side close to the electrode 4, resulting in a charge bias.

  Electrons inside the magnetic field close to the electrode 3 in a state where the charge is biased move around the fuselage of the fuselage. Therefore, the movement of this electron becomes a ring current that goes around the airframe and acts like a coil to generate a magnetic field D.

  The magnetic field D generated by the electrons acts on the magnetic field B originally generated by the airframe, and this propulsion device generates a propulsive force in the direction F due to this effect.

  At this time, propulsive force and reverse force are also applied to the electron as a reaction, but the electron moves to some extent along the magnetic field lines, and the kinetic energy received by the electron collides with other particles and is lost. Does not act on the aircraft. + Ions also generate a magnetic field due to a ring current. However, since they are ions, there is little generation of magnetic force, and the place where they are generated is outside the fuselage and has less influence on propulsion than electrons.

  The present invention finally obtains a propulsive force by a magnetic force, and during operation, the plasma continues to travel around the airframe, and a stable propulsive force can be generated even in space without the need for a propellant.

  The higher the propulsive force, the more intense the plasma motion that exists around the aircraft, which has the effect of decomposing and detoxifying space debris approaching the aircraft.

  In the present invention, the entire airframe is a propulsion device, and the structure is extremely simple. Therefore, it is easy to manufacture a solid airframe with excellent airtightness, and the performance and safety of the spacecraft can be dramatically improved.

  The propulsion device embodying the present invention has a high degree of freedom in shape, and can be implemented almost as long as the basic shape is a rotary type. In addition to the columnar type of FIG. 1, a disc type or a spherical type is also possible.

  Further, the direction of the magnetic field and the polarity of the electrode and the cathode, whose principle is explained in detail in FIG. 2, are not limited to the combinations in FIG. 2, but other combinations are possible. The propulsive force can be controlled by changing the direction of travel by changing the direction of the magnetic field, or by changing the propulsive force by changing the polarity of the electrodes.

Various aircrafts are shown as examples, and their configurations and applications will be described. Unless otherwise specified, it should be understood that the fuselage is made of an insulating material and the electrodes are insulated from the outside.
All cross-sectional views are cut longitudinally along the central axis of the rotation type.

  FIG. 3 is a small disk shape and shows a cross-sectional view seen from the side. The cylindrical magnetic body 8a generates a magnetic field B in which the upper magnetic pole 2a is S and the lower magnetic pole 1a is N. A positive voltage is applied to the electrode 3a, and a negative voltage is applied to the spherical electrode 4a to generate an electric field A. As a result, two annular electromagnetic fields in which the magnetic field B and the electric field A are approximately orthogonal to each other are generated near the center of the propulsion device. Reference numeral 9a denotes an outer wall of the machine body, and 13a denotes an internal space. The magnetic body 8a may be a permanent magnet.

  In this embodiment, electrons are not supplied from the cathode, but negative charges are naturally collected in the vicinity of the electrode 3a due to the action of the electric field, and + ions are collected in the vicinity of 4a, and the charge is deviated. The electron drift motion is in the direction C and generates a magnetic field D. As a result, the propulsion device in FIG. 3 generates a propulsive force in the upward direction in the figure.

  In the embodiment of FIG. 3, since charged particles are attracted to the electrode, the electrode has a function of collecting charges, and a more stable operation can be expected. It can be said that FIG. 2 is a configuration emphasizing power and FIG. 3 is a configuration emphasizing stability. Of course, it is also possible to supply electrons at the cathode.

  FIG. 4 is a disk shape and shows a cross-sectional view seen from the side. The magnetic body 8b is installed in a ring shape with a large diameter to generate a magnetic field. The upper surface of the body 9b is a magnetic pole 1b, and the lower surface is a magnetic pole 2b. An electrode 4b is installed inside the magnetic pole and an electrode 3b is installed outside the magnetic pole to generate an electric field. Description of the cathode, magnetic field, electric field, and principle is omitted.

  With this structure, the area of the magnetic material is expanded, and an improvement in propulsive force can be expected while being small and thin. In addition, a wide space 13b that can be used for loading is created in the center of the aircraft. The magnetic body 8b may use a magnet.

  FIG. 5 is also a disk type, and shows a cross-sectional view seen from the side. The difference from FIG. 4 is that a U-shaped magnetic body 8c facing downward is installed in a ring shape, and the magnetic poles 1c and 2c are on the same plane, that is, the N pole and the S pole are on the same plane. Around the magnetic pole 3c. 4c1.4c2 is installed.

  By doing so, the magnetic field is generated limited to the lower surface, and the effect of the propulsion device on the upper portion is reduced. It can be applied to small machines and elevators.

  FIG. 6 shows an external view of a cylindrical and large body. This is an example in which a plurality of the present inventions are installed on a cylindrical airframe.

  The present invention having the structure described with reference to FIGS. 4 and 5 can be installed on the plane or curved surface of the outer wall of the airframe. If a plurality of attachments are attached to the main parts of the airframe as in 11d, complicated attitude control can be performed by switching and operating them. Also in the axial direction, improvement of propulsive force can be expected by installing a plurality of propulsion devices 12d of the present invention having the structure of FIG. Therefore, the cylindrical type is suitable for large aircraft.

  FIG. 7 shows a simplified cross-sectional view of the internal structure of a cylindrical airframe as shown in FIG. The magnetic body 8d is intensively installed on the outer wall portion of the body 9d. As a result, a magnetic cavity is created inside. This space 13d1 can be made into a living space or a space for storing equipment. 13d2 is a room where the entire room can be rotated to create a centrifugal force to live like the ground.

  The magnetic body 8d is arranged at key points in a ring shape, an axial direction or a radial shape, and the coil 7d is also arranged in a ring shape or a straight line shape. By controlling the electrical and magnetic circuits of these coils and magnetic materials, the shape and strength of the magnetic field and electric field around the aircraft are controlled. In accordance with the change in the electromagnetic field, a large number of cathodes 5d arranged at important points of the airframe also control the polarity and voltage.

  The airframe having the structure as shown in FIG. 7 does not have a clear installation place of the present invention, and the propulsion device can be generated in any part of the airframe by controlling the electric circuit and the magnetic circuit. As a result, the stress caused by the propulsive force can be evenly distributed in the aircraft. In addition, since the magnetic core is covered with an outer wall like a beam, it is possible to manufacture a robust and large body.

  This propulsion device does not work in the atmosphere of the earth's low sky because the air is insulative. However, if a high-frequency electromagnetic field generator or a laser irradiation device is installed around the aircraft and the air can be converted into plasma or ionized effectively, the present invention will not release charged particles, but charged particles around the aircraft. It is characterized by operating in a cohesive manner, and moving charged particles cause ionization and excitation of the atmosphere. For this reason, once it is in an operating state, the ionization of air is continuously performed and stable operation is possible even in the atmosphere.

  If the present invention can exert a propulsive force exceeding gravity, it will be able to ascend slowly and go to space without receiving acceleration G due to launch. In other words, a large aircraft with multiple propulsion devices can be moved by MHD propulsion according to Fleming's law using magnetic poles, electrodes and cathodes installed on the surface of the aircraft at sea and in the sea. It is possible to fly into the atmosphere by turning the atmosphere into a plasma, fly as an aircraft in the atmosphere, and move as it is to the moon and move to the moon and other planets.

  Moreover, after arriving at a star other than the Earth, it may be possible to fly in the atmosphere and land, land on the sea, or dive. And it is possible to return to the earth as it is. Such a space trip will be possible even for untrained scientists and the general public. In this way, the application of this embodiment is unlimited as a universal spacecraft.

  Of course, this device can be operated by converting seawater into plasma even in the sea, but MHD propulsion may be used in consideration of the burden on the environment.

  FIG. 8 shows a spherical shape with a medium skirt and a cross-sectional view seen from the side. The magnetic body 8e1 has a cylindrical shape penetrating vertically through the center of the airframe, and a magnetic body 8e2 is installed in a ring shape on the outer wall portion of the airframe.

  Reference numeral 13e denotes an internal living space. Reference numeral 15e denotes a device for converting the atmosphere into a plasma such as a high-frequency electromagnetic field source or a laser. FIG. 8 shows a medium-sized aircraft configured for the purpose of carrying people in the atmosphere.

  A current is passed through the coil 7e1 to magnetize the magnetic body 8e1, and a magnetic field having the magnetic pole 1e1 as the N pole is generated. A reverse current flows through the coil 7e2, and a magnetic field having the magnetic pole 2e2 as the S pole is generated from the magnetic body 8e2. The magnetic field exits 1e1 and enters 2e2, and then exits 1e2 and enters 2e1. That is, the magnetic field is divided up and down across the skirt 10e, and looks like a four-leaf clover when viewed from the side.

  The coils 7e3 to 7c6 are auxiliary coils and are mainly intended to adjust the strength and distribution of the electric field. The magnetic body 8e1 may be an electromagnet around which a coil is wound.

  If the bias of electric charges is reduced at the cathode 5e and the anode 6e with this magnetic field structure and the voltage application to the electrodes 3e1 and 4e1 is stopped, the upper plasma-like ring current can be eliminated.

  The reason why such a thing is done is that it is extremely dangerous for people to approach because the surroundings of the aircraft where the present invention is installed are moving with a strong charge. However, if the propulsion unit is completely stopped in the atmosphere, it may be difficult to restart. Therefore, the purpose is to stop only the upper part when getting on and off, to make it safe to get on and off from the entrance 21e, and to install a skirt to block the lower part during operation, thereby improving safety. Of course, the entrance is sealed during the flight.

  Once operating, the collected charge induces atmospheric ionization, resulting in a stable operating state. In addition, by changing the direction of the current flowing through the coils 7e1 and 7e2, the operating state can be changed, for example, by reversing the direction of the magnetic field or by operating the magnetic field with the upper and lower parts integrated.

  Reference numeral 16e denotes an electrostatic generator in which two discs rotate in the opposite direction, such as a Wimshurst type electrostatic generator, which rotates around the center of the airframe. This has the purpose of supplying a high voltage to the electrodes and the effect of stabilizing the aircraft by the gyro effect. It is also possible to provide a function of controlling the yaw axis of the airframe by making the rotational speed of the two discs differential.

  17e has a spherical shape, and three are installed at equal intervals in the skirt, and a battery is contained inside. This stores the electricity needed for flight. At the time of landing, the strut 18e is extended and used as a leg. Further, the prop 18e moves during flight, and balance is controlled to control the tilt of the aircraft. A heavy and troublesome battery is taken out of the machine for effective use.

  19e is a device that absorbs ions made of nozzles, belts and brushes, and the absorbed ions are discharged from the magnetic poles. This is intended to increase the bias of charge in the magnetic field and increase efficiency.

  An antenna and a camera are installed at 20e. During operation of the propulsion device, the surroundings of the aircraft are covered with plasma, making external confirmation and communication difficult. The magnetic pole part on the central axis of the fuselage is installed in this part because the plasma is weak.

  The attitude control of small and medium-sized machines cannot be controlled by installing multiple propulsion units like a large machine, so magnetic bodies and heavy objects can be moved, and attitude control coils and magnetic bodies are installed. It is necessary to do this by tilting and controlling the propulsion device itself.

  It is the front view and top view which showed the external appearance of this invention.   Sectional drawing explaining the principle of this invention.   Sectional drawing explaining the disk type propulsion apparatus.   Sectional drawing explaining the disk type propulsion apparatus.   Sectional drawing explaining the propulsion apparatus installed in the single side | surface of a disk type | mold.   An external view illustrating a cylindrical and large body.   A cross-sectional view illustrating the internal structure of a cylindrical and large airframe.   Sectional drawing explaining the medium type body with the spherical type with a skirt.

Explanation of symbols

1 Magnetic pole N (S)
2 Magnetic pole S (N)
3 Electrode-(+)
4 electrode + (-)
5 Cathode (Anode)
6 Anode (cathode)
7 Coil 8 Magnetic body A Electric field B Magnetic field C Drift direction D Magnetic field generated by electrons

Claims (8)

  Magnetic poles and electrodes are installed on the fuselage so that the electromagnetic field, in which the magnetic field and the electric field are almost orthogonal, is annular. In this annular electromagnetic field, charge is biased by supply or discharge of electric charge or electric field. As a result, a ring current is generated in the annular electromagnetic field, and a magnetic field is generated. An electric propulsion device that generates a propulsive force by a magnetic force when a magnetic field generated by a fuselage and a magnetic field generated by a ring current act.   The electric propulsion device according to claim 1, having a function of freely changing the direction of the magnetic field and the polarity of the electrode.   An electric propulsion unit having a plurality of propulsion devices according to claim 2 in one body, and arranging a coil and a magnetic body therefor on an outer wall portion of the body to create a space therein.   The electric propulsion unit according to claim 3, wherein the magnetic poles and electrodes installed on the fuselage are used for MHD propulsion at sea and in the sea.   3. The electric propulsion apparatus according to claim 2, wherein the magnetic body is arranged in the airframe to narrow the magnetic field in the middle, the N pole side and the S pole side are separated, and the N pole side and the S pole side can be operated independently.   6. The electric propulsion apparatus according to claim 1, wherein the rotating disk is used for electrostatic power generation and a gyro, and the yaw axis is controlled by manipulating the rotational speed.   The electric propulsion apparatus according to claim 1, wherein the airframe has a cathode and an anode, and generates a bias of charge by supplying and discharging charged particles.   The electric propulsion device according to any one of claims 1 to 7, further comprising a plasma generation source such as a high-frequency electromagnetic field generation device or a laser irradiation device.

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