FIELD OF THE INVENTION
This invention relates to spacecraft propulsion. As is scientifically well know magnetic flux is a physical force (i.e. the Lorentz force and Ampere's force). This invention utilizes a plurality of electromagnetic and or plasma coils to create high pressure, high velocity magnetic flux directed through variable exhaust nozzles or a cone shaped coil to create thrust for spacecraft.
BACKGROUND OF THE INVENTION
For many years extensive research has been done by private and government entities directed towards creating practical long-term infinite distance propulsion systems for spacecraft. Electromagnetic flux exists throughout the known universe. Accordingly, a spacecraft propulsion system that utilizes electromagnetic flux by directing magnetic flux is desirable.
SUMMARY OF THE INVENTION
The present invention relates to spacecraft propulsion systems which utilize magnetic flux as a physical force to propel spacecraft through the vacuum of outer space. The system uses a plurality of coils of electrically conductive material, super conducting material, or plasma coils designed to create high density, high magnetic flux pressure, high velocity electromagnetic flux fields routed through a variable exhaust nozzle or a cone shaped coil to create thrust.
The system may initially be powered by banks of capacitors or super capacitors. The magnetic fields initially produced will interact with a plurality of coils designed to create electric power for the system. Solar power or a miniature nuclear reactor may optionally power the system.
This invention utilizes a plurality of electromagnetic and or plasma coils to produce high pressure, high velocity magnetic flux (Lorentz force, Ampere force) to create thrust for spacecraft.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 shows a side cutaway view of a magnetic flux engine 99 for spacecraft propulsion.
FIG. 2 shows a detailed side cutaway view of a magnetic flux engine 99 with flux pressure controllers 105 at both ends.
FIG. 3 shows a diagonal view of the optional two separate halves of the inner central conduit 103 with retainer rings 110 and a flux pressure controller 105.
FIG. 4a shows a diagonal view of inner central conduit 203 with two formed, unwound pressure controllers 210 and 220 affixed.
FIG. 4b shows a detailed side cutaway view of inner central conduit 203 with two formed, wound pressure controllers 210 and 220 affixed.
FIG. 5 shows a detailed side cutaway view of inner central conduit 303 with two formed, wound pressure controllers 310 and 320 affixed.
FIG. 6a shows a detailed side cutaway view of two formed, wound pressure controllers 410 and 420 wherein one is concentrically enclosed in the other.
FIG. 6b shows detailed side cutaway view of an alternative embodiment using a single formed, wound pressure controller 420.
DETAILED DESCRIPTION OF THE INVENTION
The invention is not limited to the embodiments shown which only represent examples of the current invention.
FIG. 1 shows a side cross-sectional cutaway view of a magnetic flux engine 99 for spacecraft propulsion. The system uses a plurality of coils of electrically conductive material 102 and 104, super conducting material, or plasma coils designed to create high density, high magnetic flux pressure 100, high velocity electromagnetic flux fields routed through a variable exhaust nozzle 107 or a cone shaped coil to create thrust. The present invention shows a plurality of different layered materials 101, 102, 103, 104, and 105. Inner central conduit 103 may be constructed of high permeability magnetic material. Inner central conduit 103 also shows a flux pressure controller 105 with an inner electric coil 104 that may be used to create a controllable counter magnetic field to create magnetic flux pressure. Also shown are venturi acceleration coils 106a, 106b, and 106c, variable exhaust nozzle 107 or a cone shaped coil, and a plurality of power coils 108 that will interact with magnetic flux 100 designed to produce electric power. Also shown is a layer of electrical conductors 102 and or super conductors, that, when energized will create and/or draw in high density, high velocity magnetic flux 100, through inner central conduit 103, through high velocity venturi 106 and its associated venturi acceleration coils 106a, 106b, and 106c, and through variable exhaust nozzle 107 or a cone shaped electrical coil constructed of non-ferrous magnetic material designed to deflect and/or create high pressure, high velocity magnetic flux thrust. Those having skill in the art will recognize that embodiments of the invention may be constructed with multiple layers of electrical conductors 102 and or super conductors. Also shown is an outer layer 101 constructed of non-ferrous magnetic material designed to contain high velocity magnetic flux 100 and prevent magnetic flux leakage.
Referring now to FIG. 2, the diagrams show a side cutaway view of an alternative embodiment of a magnetic flux engine 99 The present invention is designed to create high pressure, high velocity magnetic flux for spacecraft propulsion. Inner central conduit 103 is constructed of high and/or ultrahigh permeability magnetic material including, but not limited to, iron based composite nanocrystalline foil, or nickel-plated neodymium composites. Inner central conduit 103 is wrapped with multiple layers of electrical conductors 102 and or super conductors such that when energized creates and/or draws in high density, high pressure, high velocity magnetic flux through the inner central conduit 103 in either direction depending on the polarity of electric power applied to electrical conductors 102. Also shown are flux pressure controllers 105 located at both ends with inner electric coils 104 to create counter electric fields to create controllable magnetic flux pressure and velocities. Optionally, inner central conduit 103 may be constructed of separate portions and joined together by outer retainer rings 110 located at both ends.
Referring now to FIG. 3, the diagram shows a partially disassembled diagonal view of the optional two separate halves of the inner central conduit 103 with retainer rings 110 and a flux pressure controller 105. Note that the inner central conduit 103 may be manufactured monolithically or in two or more pieces.
Referring now to FIG. 4a, the diagram shows inner central conduit 203 with two formed, unwound pressure controllers 210 and 220 affixed. Note that inner central conduit may be threaded so that pressure controllers 210 and 220 may be placed at different locations with respect to one another on inner central conduit 203.
Referring now to FIG. 4b, the diagram shows a side cutaway view of inner central conduit 203 with two formed, wound pressure controllers 210 and 220 affixed. Inner central conduit 203 may be threaded so that pressure controllers 210 and 220 may be placed at different locations with respect to one another on inner central conduit 203. Alternately, pressure controllers 210 and 220, may be electrically, electromechanically, or hydraulically configured to be placed at different locations with respect to one another on inner central conduit 203. Inner center conduit 203 may be constructed of high permeability magnetic material. Inner center conduit 203 also shows formed, wound pressure controllers 210 and 220 wrapped with multiple layers of electrical conductors 211 and 221 and or super conductors, respectively. Formed, wound pressure controllers 210 and 220 are juxtaposed next to each other on inner central conduit 203 such that when simultaneously energized the electromagnetic flux 230 created by their north (N) poles is directed towards one another. Since wound pressure controller 210 is physically larger than wound pressure controller 220, the combined electromagnetic flux 230 is directed rearward (to the right) of wound pressure controller 220. This creates a minute thrust of the entire assembly forward (to the left). The amount of thrust is proportional to the current applied to the electrical conductors 211 and 221 and or super conductors. The amount of thrust may also be controlled by changing the horizontal distance between pressure controllers 210 and 220 on inner central conduit 203.
Referring now to FIG. 5, the diagram shows a side cutaway view of inner central conduit 303 with two formed, wound pressure controllers 310 and 320 affixed. Inner central conduit 303 may be threaded so that pressure controllers 310 and 320 may be placed at different locations with respect to one another on inner central conduit 303. Alternately, pressure controllers 310 and 320, may be electrically, electromechanically, or hydraulically configured to be placed at different locations with respect to one another on inner central conduit 303. Inner central conduit 303 may be constructed of high permeability magnetic material. Inner central conduit 303 also shows formed, wound pressure controllers 310 and 320 wrapped with a single layers of electrical conductors 311 and 321 and or super conductors, respectively. Those having skill in the art will recognize that formed, wound pressure controllers 310 and 320 may be wrapped with multiple layers of electrical conductors 311 and 321 and or super conductors, respectively. Formed, wound pressure controllers 310 and 320 are juxtaposed next to each other on inner central conduit 303 such that when simultaneously energized the electromagnetic flux 330 created by their north (N) poles is directed towards one another. Since wound pressure controller 310 is physically larger than wound pressure controller 320, the combined electromagnetic flux 330 is directed rearward (to the right) of wound pressure controller 320. This creates a minute thrust of the entire assembly forward (to the left). The amount of thrust is proportional to the current applied to the electrical conductors 311 and 321 and or super conductors. The amount of thrust may also be controlled by changing the horizontal distance between pressure controllers 310 and 320 on inner central conduit 303.
Referring now to FIG. 6a, the diagram shows a side cutaway view of cylindrical peripheral conduit 403 with two cylindrical formed, wound pressure controllers 410 and 420 affixed. Cylindrical peripheral conduit 403 may be threaded on its inside and/or outside surfaces so that cylindrical pressure controllers 410 and 420 may be placed at different locations with respect to one another on cylindrical peripheral conduit 403. Alternately, cylindrical pressure controllers 410 and 420, may be electrically, electromechanically, or hydraulically configured to be placed at different locations with respect to one another on cylindrical peripheral conduit 403. Cylindrical peripheral conduit 403 may be constructed of high permeability magnetic material. Cylindrical peripheral conduit 403 also shows formed, wound cylindrical pressure controllers 410 and 420 wrapped with multiple layers of electrical conductors 411 and 421 and or super conductors, respectively. Formed, wound cylindrical pressure controllers 410 and 420 are juxtaposed adjacent to each other inside and outside, respectively, of cylindrical peripheral conduit 403 such that when simultaneously energized the electromagnetic flux 430 created by their north (N) poles is directed towards one another. Since wound cylindrical pressure controller 410 is formed with its leading (rightmost) surface at approximately a 45° angle with respect to the central axis of cylindrical peripheral conduit 403, wound cylindrical pressure controller 410, and wound cylindrical pressure controller 420, the combined electromagnetic flux 430 is directed rearward (to the right) of cylindrical peripheral conduit 403, wound cylindrical pressure controller 410, and wound cylindrical pressure controller 420. This creates a minute thrust of the entire assembly forward (to the left). The amount of thrust is proportional to the current applied to the electrical conductors 411 and 421 and or super conductors. The amount of thrust may also be controlled by changing the horizontal distance between cylindrical pressure controllers 410 and 420 on cylindrical inner cent conduit 403.
Referring now to FIG. 6b, the diagram shows a side cutaway view of an alternative embodiment of cylindrical peripheral conduit 403 with a single cylindrical formed, wound pressure controller 420 affixed. Cylindrical peripheral conduit 403 may be threaded on its inside and/or outside surfaces so that cylindrical pressure controller 420 may be placed at different locations with respect to cylindrical thrust vectoring unit 410 on cylindrical peripheral conduit 403. Alternately, cylindrical pressure controller 420 and cylindrical thrust vectoring unit 410 may be electrically, electromechanically, or hydraulically configured to be placed at different locations with respect to one another on cylindrical peripheral conduit 403. Cylindrical peripheral conduit 403 may be constructed of high permeability magnetic material. Cylindrical peripheral conduit 403 also shows formed, wound cylindrical pressure controller 420 wrapped with multiple layers of electrical conductors 421 and or super conductors. Formed, wound cylindrical pressure controller 420 and cylindrical thrust vectoring unit 410 are juxtaposed adjacent to each other inside and outside, respectively, of cylindrical peripheral conduit 403 such that when energized the electromagnetic flux 430 created by the north (N) poles of formed, wound cylindrical pressure controller 420 is directed towards cylindrical thrust vectoring unit 410. Since cylindrical thrust vectoring unit 410 is formed with its leading (rightmost) surface at approximately a 45° angle with respect to the central axis of cylindrical peripheral conduit 403, cylindrical thrust vectoring unit 410, and wound cylindrical pressure controller 420, the electromagnetic flux 430 is directed rearward (to the right) of cylindrical peripheral conduit 403, cylindrical thrust vectoring unit 410, and wound cylindrical pressure controller 420. This creates a minute thrust of the entire assembly forward (to the left). The amount of thrust is proportional to the current applied to the electrical conductors 421 and or super conductors. The amount of thrust may also be controlled by changing the horizontal distance between cylindrical pressure controllers 420 and cylindrical thrust vectoring unit 410 on cylindrical peripheral conduit 403.
It is to be understood that the present invention is not limited to the illustrations and details shown. Those skilled in the art may modify elements and aspects described but may not deviate from the spirit and scope of the claims. For example, those having skill in the art will recognize that the direction of thrust of the elements disclosed and shown in FIGS. 4b, 5, and 6 may be essentially reversed by changing the polarity of the electrical circuit energizing the electrical conductors 211, 311, 411, 221, 321, and 421 and or super conductors. By this means, S (south) poles are juxtaposed adjacent to one another and N (north) poles are placed at the different ends of the element. Also, those having skill in the art will recognize that some of the magnetic flux 230, 330, and 430 disclosed and shown in FIGS. 4b, 5, and 6 may interact with power generation coils (not shown) to generate electric power.
Also, it will be obvious to those having skill in the art that electric power for the devices disclosed and shown in FIGS. 1, 2, 4b, 5, and 6 may be provided by several options, e.g. solar panels and/or nuclear power devices. The disclosed invention is primarily designed to function in the environment of space for space craft propulsion systems that require only electric power thereby serving as a possible alternative for long range space travel.
Patent Application
20210009287
