(19) United States (12) Patent Application Publication (10) Pub. No.: US 2006/0102795 A1 (54) FUSION ENERGY SYSTEM AND PLASMA PROPULSION AIRCRAFT TO PRODUCE ELECTRICITY FROM A CONTROLLED NUCLEAR FUSION REACTION (76) Inventor: Gary Richard Gochnour, Seattle, WA Correspondence Address: Gary Richard Gochnour 1415 E. Olive Street Seattle, WA 98122 (US) Related U.S. Application Data (63) Continuation-in-part of application No. 10/841,702, filed on May 6, 2004. (60) Provisional application No. 60/468.598, filed on May Publication Classification (57) ABSTRACT The invention relates to plasma based aircraft maintained in a flight-mode by an uplifting Larmor gyro orbiting particle field, and an extensive capacitor system. Said aircraft is comprised of chromium steel, or higher ferrochromium steel can also be used. Said aircraft system can operate utilizing only energy required to initiate operation of said craft. The energy to start said craft is from energy stored within said capacitor system, and said energy also obtained from the operating environment. Said craft, is immediately capable of space flight, use as a submersible craft, or use as an energy Source in an artificial environment. Said craft is opaque, invisible within the visible spectrum, invisible to electro magnetic radiation, and absorbs radiation it produces. Said aircraft is capable of soundless flight. Said aircraft is capable of verticle ascent, descent and landing. Said aircraft can operate within earth radiation belts. Said aircraft is capable of speeds in excess of the fastest aerodynamic aircraft, said aircraft navigates within a particle field at a faster rate than conventional aerodyamic aircraft within the atmosphere. Said aircraft, with two larger, faster aircraft, comprised of magnesium aluminum material, can attain ignition of a formed fusion spherical plasma on roof of said ferromag netic, smaller craft, utilizing the fuels boron B-11 isotope and regular hydrogen with no radiation, cooling needed. Patent Application Publication May 18, 2006 Sheet 1 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 2 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 3 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 6 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 7 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 8 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 9 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 10 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 11 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 12 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 13 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 14 of 18 Patent Application Publication May 18, 2006 Sheet 15 of 18 US 2006/0102795 A1 Fig. 12E f f fic 111e Patent Application Publication May 18, 2006 Sheet 16 of 18 Patent Application Publication May 18, 2006 Sheet 17 of 18 US 2006/0102795 A1 Patent Application Publication May 18, 2006 Sheet 18 of 18 US 2006/0102795 A1 FUSON ENERGY SYSTEMAND PLASMA PROPULSION AIRCRAFT TO PRODUCE ELECTRICITY FROMA CONTROLLED NUCLEAR FUSION REACTION CROSS-REFERENCE TO RELATED APPLICATIONS 0001. This application is a continuation in part of Ser. No. 10/841702, filed 2004, May 6, by present inventor, now abandoned, which claims the priority to provisional patent application with Ser. No. 60/468.598, filed 2003, May 6, by the present inventor. BACKGROUND OF THE INVENTION Field of Invention 0002 This invention relates to a new type multi-func tional electro-magnetic, plasma based aircraft, capable of operation in the atmosphere as an aircraft, underwater as a Submersible craft, in outer space as a space craft, or as a boring device, or a lifting device. Three of the aircraft described, utilized in an aircraft mode, being craft of vari able sizes, utilized together, are able to be used in a process with resultant nuclear fusion reaction to obtain electricity. The fusion process will be explained in detail in a process portion of this utility patent. Negligible radiation will be produced, only charged particles. OBJECTS AND ADVANTAGES 0003. This invention will make possible travel in space at small cost. Depletion of the world's resources will no longer be a problem. This invention is on a par with the discovery of fire, insofar as mans future is concerned. SUMMARY OF THE INVENTION 0004. In the present invention, an aircraft operates within a plasma environment of charged particles. The aircraft operations will be performed in a hyperdynamic state. The fusion energy portion of this utility patent, utilizes the aircraft in fusion process. 0005. In the aircraft of present invention, ions will be produced by the aircraft. 0006. In the present invention, ions will be placed into Larmor gyro orbiting particle fields around the aircraft. 0007. In the present invention, an orbiting particle field, possessing a rotational direction for upward motional move ment, will lift the aircraft off the ground or other surface. 0008. In the present invention, navigation will be by means of utilizing ailerons possessing a charge within the particle fields, and by use of rotating plasma Vortices placing aircraft in direction of travel by means of ailerons. 0009. In the present invention, only energy from capaci tors Sufficent to begin operation, will be required for opera tion of aircraft. 0010. In the present invention, the aircraft will produce operational energy for aircraft from the plasma fields. 0011. In the present invention, the aircraft with two or more larger similar aircraft can produce electricity, from a fusion process. 0012. In this invention, the aircraft can be used as an aircraft, a spacecraft, Submersible craft, boring or lifting BRIEF DESCRIPTION OF THE DRAWINGS 0013 FIG. 1 is a side view of the aircraft showing lenticular configuration of aircraft, and a side view of the annular bladed ring assembly encircling the aircraft, and extending out from the sides of aircraft. 0014 FIG. 2 is a top plan view of the aircraft showing the circular configuration of aircraft, and a top plan view show ing the annular bladed ring assembly. 0015 FIG. 3 is a bottom plan view showing the circular configuratin of aircraft, and a bottom plan view showing the annular bladed ring assembly. 0016 FIG. 4 is a top plan view of capacitor, electric system attached to top of top planar Surface showing bottom half of aircraft hull, and a top plan view showing the annular bladed ring assembly. 0017 FIG. 5 is a cross section side view of the aircraft showing an ion acceleration system and the central shaft containing an induction coil. Also shown is a cross section side view of the annular bladed ring, capacitor system, and electrolysis system. 0018 FIG. 6A is a diagram showing the space between the upper and lower hulls for attachment of ailerons to multi-bladed annular ring. 0.019 FIG. 6B is a side view of the opening between the aircraft hulls to extract worn or burnt ailerons, or to attach replacement ailerons. 0020 FIG. 6C is a side view of the aircraft using particle impact on ailerons to determine banking direction. 0021 FIG. 6D is a side view of the aircraft using particle impact on ailerons to determine banking direction. 0022 FIG. 6E is a side view of the aircraft. The charged particles are impacting ailerons on bottom Surface. The aircraft will rise in altitude. 0023 FIG. 6F is a side view of the aircraft using particle impact on ailerons to determine altitude direction. Particles will impact top surfaces of ailerons. The aircraft will 0024 FIG. 7A is a side view of an aircraft within rotating vortices. Ailerons have determined the position for direction of travel. Increase in rotation of vortices will propel the aircraft diagonal to Earth. 0.025 FIG. 7B is a side view of an aircraft within rotating vortices being propelled horizontal with Earth. 0027 Increase in rotation of vortices will propel the aircraft vertical to Earth. 0028 FIG. 8A is a top view of extricated capacitor system from aircraft, combined negative charge is moving aircraft away from lesser positive charge in direction of FIG.7C is a side view of an aircraft within rotating 0029 FIG. 8B is a top view of extricated capacitor system from aircraft. Combined positive charge greater than negative is moving craft away from negative charge in direction of arrow. 0030 FIG. 9 is a top view of the aircraft plasma propul sion system with capacitor, electric system and radial plasma 0031 FIG. 10 is a side view of aircraft in electric force propulsion mode interacting with Earths magnetic field. 0032 FIG. 11A is a perspective view of the top surface of aircraft showing exit electrodes for fusion fuels and propulsion fuels. FIG. 11B is a side view of aircraft showing raised pyramid and ion acceleration system, and ball elec 0033 FIG. 12A is a side view of three aircraft positioned to effect a nuclear fusion reaction. 0034 FIG. 12B is a side view of the fusion spherical plasma and two adjacent spherical plasmas showing direc tions of plasma rotation. 0035 FIG. 12C is a top view of the induced Larmor orbiting particle field and a top view of the spherical plasma for ignition. 0036 FIG. 12D is a top plan view of the array of barrel shaped devices and electrodes for electrolysis. 0037 FIG. 12E is a perspective view from the side of a cutaway view of an array of containment barrels and an electrolysis system. 0038 FIG. 13 is a side view of three aircraft positioned to effect a nuclear fusion reaction close to ignition of spherical plasma. 0039 FIG. 14 is a spherical plasma between the three aircraft in the process of ignition by land based laser and neutral beam. 0040 FIG. 15, shows end phase of fusion process, stor ing electricity. DESCRIPTION OF THE PREFERRED EMBODIMENT 0041. The operation of aircraft as a system and device will be described first. Said aircraft being the central device. This will be followed by a description of the preferred embodiment pertaining to aircraft. Next a process portion of this utility patent will describe a process producing funnel shaped spirals of particles. Next a process portion of this patent will describe a fusion energy process utilizing air craft. Said processes will be described first, followed by descriptions relating to the preferred embodiments for said processes. Reference numbers where required are furnished following a brief literary exposition describing aircraft. Craft is comprised of the material chromium steel. When starting operation, the remnant magnetism of the ferromag netic hull of said craft, will be charged from an array of capacitors connected in parallel within an oscillatory circuit containing inductance. Said starting charge establishes a magnetic field around said craft. At the same time, said capacitor system will provide a weak current through unin sulated field windings around blades within an array of 32 blades encircling said aircraft. Said uninsulated tungsten wire, preferred embodiment, will produce an abundance of free ions on said uninsulated wire Surfaces. 0042. Ions will be, freed with current from capacitors through wires by the uninsulated field windings, and upon being energized by field windings, will depart said annular ring of blades at a Voltage recognized to energize ions. Said ions will depart said array of blades energized charged particles, and as the craft has a developed magnetic field, said ions will be warped into Larmor gyro orbits around said aircraft. The more energetic particlies, electrons, will ascend to the apices of said Larmor plasma particle fields, forming funnel shaped Vortices on the top and bottom Surfaces of said annular bladed ring assembly. 0043 Said ions will be affected by a Lorentz force at right angles to the magnetic and electric fields of said aircraft. The narrowing orbits of the more energetic particles will also affect general shape of said plasma Vortices. 0044) The Larmor gyro orbiting particle field, a plasma field, a diamagnetic, moving magnetic field, passing over the top and bottom Surfaces of said conducting field windings 20, FIG. 2, on fixed array of blades 2, FIGS. 2 and 5, generates electricity. The moving magnetic field is the rotor, the field windings are the fixed stator armature. This is a new form of electric generator. Said strong current exiting will be stored within said capacitance inductance system. Said air craft possesses an oscillatory circuit. Usually an oscillatory circuit loses energy as it emits some, or all energy as electromagnetic radiation. Within this system, the overarch ing plasma Vortices will reabsorb this emitted radiation, perhaps through the Debye effect. The area under said Vortices is also a vacuum area. This cyclic increase in energy will continue until the large wave form of plasma is reached, at which time it will be self perpetuating, not requiring additional energy. As conceived, said aircraft does not require fuel to be provided for aircraft to operate. Energy is nondepleting from environment. 0045 Fuel for said aircraft is stored starting energy. In the event of depletion of said stored energy, energy can be obtained from an on-board electrolysis system. Said system utilizes ferromagnetic cored columns with rotating remnant ions circling said fertomagnetic columns within craft. Said system will initiate production of ions from water with on-board electrodes, until capacitor System is again storing energy. The same ions will be simultaneously, circling, charging said ferromagnetic hull. 0046) Operation of the aircraft. Referring to FIGS. 1, 2 and 3, a multi-functional aircraft (MFA), also called craft or device, is shown. From the side, aircraft has a lenticular shape, as shown in FIG. 1. When viewed from the top, said aircraft has a circular shape as shown in FIG. 2. When viewed from the bottom, aircraft has a circular shape as shown in FIG. 3. Said aircraft is comprised of a top half body hull 1, FIGS. 1 and 2, and a bottom half body hull 1", FIGS. 1 and 3. 0047 Referring to FIGS. 1, 2, 3, 4, and 5, a multi-bladed annular ring 2, 2', also called bladed ring assembly 2, 2', or ailerons 2, 2', or annular ring 2, 2', additionally called ring assembly 2, 2', or ring 2, 2', is located between bottom portion of top half of hull 2, and the upper portion of the bottom half of hull 1". Individual blades in the ring assembly 2, 2', are called blade 2, 2', individual blades are also called aileron 2, 2. 0.048. The bladed ring assembly 2, 2', possessing a high electric field, and possessing uninsulated field windings 10, 10'. FIGS. 2 and 3, around said blades will produce an abundance of particles and ions. 0049. The extensive capacitor system will immediately upon starting impart a high electric field, and an induced magnetic field around said blades. 0050. An abundance of particles and ions will be pro duced by the uninsulated current within said field windings. Said particles will be warped into perpendicular Larmor gyro orbiting particle fields, a plasma field, 34, 34", FIG. 5, around the aircraft. Said plasma field is perpendicular rela tive to the parallel magnetic field, lines of the craft applied magnetic field. It is an opaque particle field, as plasmas absorb all electromagnetic radiation in the visible spectrum, it is not reflected. In fact, plasmas absorb the electromag netic radiation they produce, as well. In FIG. 1 a Larmor orbiting particle field is shown as a band 42, 42", forming above and below the bladed ring assembly 2, 2', upon starting. More energetic particles have formed the top Vor tex, lifting craft upward. As the bottom vortex forms, the craft is further lifted upward as the motional direction for movement for both Vortices is upward using the right hand rule. The band 42, 42" is not visible, it demonstrates the forces lifting the aircraft off the ground. There are bands of varying charged particles, bands of different charge, but too many to graphically represent. 0051) The Larmor orbiting particles are in orbits around said aircraft, increasing in energy to the speed of light. Over time, the number of rotating particles will increase. The plasma field 34, 34' is part of the oscillatory circuit of the craft. Said plasma is an oscillatory...inhomogeneous plasma field, similar to a magnetically contained, confined, homo geneous plasma field, in that both fields can contain a spherical plasma. The magnetically confined plasma for a transitory period of time, the oscillatory, inhomogeneous plasma, for much longer. Nonhyperdynamic equations from craft electromagnetic oscillatory system, can be used in lieu of the unascertainable equations of the hyperdynamic, inho mogeneous plama field, to control the field. Both oscillatory systems are connected, FIG. 5. 0.052 The preferred embodiment for the capacitors in the capacitance system is seven sets of four capacitors con nected in parallel, a total of 56 capacitor plates. Though seven sets of four capacitors is only seven times as great as one set of four capacitors, it has 70 times as much magnetic force. A single set of the top four capacitors, one set of four capacitors, is depicted in FIG. 4 as capacitors 701a, 701b, 701c and 701d. Additionally, eight smaller capacitors con nected in parallel, 70a, 70b, 70c, 70d, 70e,70?, 70g and 70h, are depicted in FIG. 9 arrayed around central shaft 41, FIG. 9. The capacitance potential of said larger, similar aircraft, to be described, is more than double the smaller craft, without the increased size being a factor. 0053. The following aircraft systems will be connected in sequence: Bladed ring assembly 2, 2', FIG. 4, the blade axel system 4, FIG. 4, a blade attachment ring 26, FIG. 4, the plurality of large capacitors 701a, 701b, 701c, 701d, and FIG. 5, the eight small capacitors 70a, 70b, 70c, 70d, 70e, 70?, 70gand 70h, FIG. 9, the induction coil, also called electric coil 47, 47". FIG. 5, and the interconnecting electric system 20, FIGS. 4 and 5. Said electric coil will be comprised of thick coils, obviating necessity for a large, central magnetic core within coils, a Solid core. Thick metallic coils are preferred embodiment. Also within the electric system 20, is the electrolysis system possessing an electrode 188, FIG. 12D. Said ferromagnetic cores within electrolysis system will increase in magnetic intensity due to orbiting ions, however, during fusion process, the