Patent Publication Number: US-2007113535-A1

Title: Dual-plasma-fusion jet thrusters using DC turbo-contacting generator as its electrical power source

Description:
RELATED APPLICATIONS  
      The present invention is a Continuation in Part of U.S. Ser. No. 10/929,023 filed on Aug. 30, 2004, which a Continuation in Par was U.S. Ser. No. 10/970,152, filed on Oct. 22, 2004, 2004, and both incorporated by reference herein as if fully rewritten. 
    
    
     BACKGROUND OF THE INVENTION  
      1. Field of the Invention  
      The present invention relates generally using DC turbo-contacting generator to electrifying-gases-to-plasmas methods for power and, more particularly to a method of generating useful linear thrust with utilizing dual-plasma, positively and negatively charge-coupled plasmas, which are passed through the latitudinal opening space from opposite sides of a “C” shaped magnet. Plasmas are bent downward according to the electromagnetic right-hand rule, and combusted and neutralized in the combustion space thereafter. And their flue gas (steam) runs turbines which lead to rotate one outer metal surface in one direction and another plastic surface lined with metal surface inside rotate to the opposite direction with some contacting rollers in between, which generate high-power DC electricity to sustain their next processing cycle&#39;s electrifying-plasmas power and thrust demands.  
      2. Background of the Invention  
      In recent years, the conventional single plasma thrusters have generated some current density with a jerky motion which results in less efficiency and requires more physical space. The dual-plasma (‘+&amp;−’ electrified-plasmas) thruster&#39;s process provides improvements and advantages over conventional thruster&#39;s problems of relating to the conversion of its single-plasma into electric propulsion with difficult abrupt (jerky) displacement and its jetting power is truely coming from arc&#39;s thermal jetting energy, but not from their electromagnetic propulsion.  
      A search of the prior art did not disclose any patent that reads directly on the claims of the present invention; however, the following references were considered relating and relevant to the present invention:  
      U.S. Pat. Nos. 6,029,438 and 6,182,441, each issued in the name of Hosick, disclosed a drive circuit for electric propulsion thruster;  
      U.S. Pat. No. 6,293,090, issued in the name of Olson, disclosed a radio frequency plasma thruster for use in electric propulsion spacecraft, the thruster heating single-plasma in a magnetic field and producing axial thrust, not greatly increasing the efficiency of the RF plasma thruster compared to other thrusters;  
      U.S. Pat. No. 6,478,257, issued in the name of Oh et al., disclosed a phase change material such as HDPE to have heater or thermal control for electric propulsion devices (thrusters);  
      U.S. Pat. No. 6,541,916, issued in the name of Decker, disclosed a method and circuit for providing power distribution to electric propulsion thrusters;  
      U.S. Pat. No. 6,644,014, issued in the name of Provitola, disclosed an electric thruster and thrust augmenter which is intaken or compressed atmospheric gas or reaction thruster exhaust is passed through a gap space between electrodes so that the atmospheric or rection thrust exhaust gases are subjected to an electric current of sufficient intensity.  
      U.S. Pat. No. 6,609,363, issued in the name of Dressler et al., disclosed single-iodine-plasma electric propulsion thrusters, wherein a heated tank containing iodine crystals is converted into a gaseous propellant;  
      U.S. Pat. No. 6,651,597, issued in the name of Daniel et al., disclosed a plasmatron having an air jacket, the plasmatron reforming hydrocarbon fuels so as to produce reformed gas further supplied to a remote device such as an internal combustion engine or fuel cell;  
      U.S. Pat. No. 6,745,466, &amp; U.S. Pat. No. 7,003,941, issued in the names of Fryre, et. Al, disclosed a thruster device comprises a frustoconical inner layer and a frustoconical outer layer that surrounds the inner layer such that the inner and outer layers cooperate to define a spiral flow passage therebetween.  
      U.S. Pat. No. 6,755,378, issued in the names of Capozzi, et. Al., disclosed a system and method for controlling a propulsion system of a space-borne object.  
      U.S. Pat. No. 6,786,035, issued in the name of Stickelmaier, disclosed a method and device for clearing an ion thruster grid of contaminants.  
      U.S. Pat. No. 6,986,497, issued in the names of Starken, disclosed a thruster gas control mechanism for controlling a flow of thrust gas through a gas nozzle.  
      U.S. Pat. No. 6,996,972, issued in the name of Song, disclosed a method of ionizing a liquid propellant.  
      U.S. Pat. No. 7,003,942, issued in the names of Le Helley, et. Al., disclosed an invention provides a system for passively controlling pressure oscillations of hydrodynamic origin in a solid propellant thruster.  
     SUMMARY OF THE INVENTION  
      It is the present invention to utilize dual-plasma streams, one of a positive charge and one of a negative charge, in which the streams are electrified by high-voltage DC source and these (+&amp;−) plasmas run toward each other from opposite sides along the latitudinal opening of the C-shaped magnet, thereby generating linear electromagnetic action force and reaction movements according to the right hand rule.  
      An advantage of the present invention is that a higher thrust and higher power density of dual-plasma can be achieved, and therefore less propellant and less physical space being needed.  
      Another advantage of the present invention is its DC electricity is generated by high-power DC turbo-contacting generator which modifies to the conventional Van de Graaff contacting generator.  
      Yet another advantage of the present invention is the inclusion of an electric start system for providing a “warm-up” process for this unit. Before this unit is self-sustaining in replenishing the fuel, oxygen, and humidity, battery&#39;s power is provided to rotate dual-outer-contacting surfaces and rollers generating electricity, which is using for electrifying plasmas and then those plasmas running through nozzles increasing the current of plasmas into a “C” shaped electromagnet opening space.  
      Yet another advantage of the present DC contacting generator invention is with the dual-most-outer moving surfaces rotating oppositely, which are led by turbines. Those dual-outer surfaces can have the most contacting surface area and fast velocities to generate high-power DC electricity by contacting rollers in-between those dual-outer surfaces as the modified contacting method to the Van de Graaff contacting generator. Therefore, the present invention is a reliable high-power device.  
      Yet another advantage of the present invention is the high power density of dual-plasma generated by this high-power DC turbo-contacting generator having lighter weight in comparison to the traditional high-power DC generator, thereby its increasing power and lighter weight make it easy to fly up with enhancing efficiency of using less propellant.  
      Yet another advantage of the present invention is the higher operation temperature range (2,200° C.-2,700° C.) at which the dual-plasma flying object&#39;s turbines operate, thereby generating the higher power of DC electricity by contacting two oppositely-rotated surfaces with different material-made rollers in-between, and further with no heavy armature or stator of the conventional electromagnetic DC generators.  
      In one innovation of the present invention, a new dual-plasma flying object having a “C-shaped” magnet for generating thrusting force is provided to generate a linear motion for use in airplane, space craft or other mobile craft for pushing them forward and upward.  
      Electrical power is needed for starting this [GerTh-DawShien. V] flying object&#39;s (Thruster V) two-outer contacting surfaces with rollers in-between to rotating by batteries, and the contacting surfaces will generate high-power DC after the dual-contacting surface reaching to their steady-states, then the next cycle&#39;s fuel supplies are electrified and transformed them from molecular forms into ionizing forms. The electrifying plasma streams are squeezed out fast from ionizing chamber nozzles, plasmas attracting toward each other, and ejected out from opposite sides into the latitudinal opening of the “C” shaped magnet generating the action plasmas bent-down force and the reaction lifting thrust. And then, combustion and neutralization are conducted also with the action force direction according to the right hand rule and enhancing guided linear reaction motion. The exhaustion stream sustains its turbines power demands for the next electricity generation cycle by leading two-outer contacting surfaces rotating-oppositely in stable ways. 
    
    
     DESCRIPTION OF THE PREFERRED INNOVATIONS  
      The advantages and the present invention will become better understood with referencing to the following more detailed descriptions and claims taken in conjunction with the accompanying drawings, in which like elements are identified with like symbols, and in which:  
       FIG. 1 , is a schematic diagram of a conventional single (one) plasma arc jet according to the PRIOR ART;  
       FIG. 2 , is a schematic diagram of a conventional single (one) plasma thruster according to the PRIOR ART;  
       FIG. 3 , Is a schematic illustration of the slowing abrupt (jerky) motion of a boy standing on the skating board and playing electrical balls with throwing-catching-missing games between his hands;  
       FIG. 4 , is a schematic illustration of the nozzles jetting the dual-plasma out from both sides increasing their electric current amount in useful ways;  
       FIG. 5 , is a schematic diagram of the Fifth [GerTh-DawShien. V] dual-plasma flying object (referred to as [Thruster V]) including an electric starter means;  
       FIG. 6  is a schematic diagram of the Sixth [GerTh-DawShien. VI] dual-plasma-fusion flying object (referred to as [Thruster VI]) with utilizing fuel, oxygen, and dilute heavy water (D 2 O) as plasma sources according to a plasmas-fusion innovation of the present Thruster V&#39;s invention.  
       FIG. 7 , is a schematic diagram of a conventional Van de Graaff contacting generator according to the PRIOR ART; and  
       FIG. 8 , is a schematic diagram of the new Thruster VI&#39;s DC generator (referred to as [ShihHwa. V] dual-plasma-fusion DC turbo-contacting generator) according to the present invention; 
    
    
     DESCRIPTION OF THE PREFERRED INNOVATIONS  
      The best mode for describing the invention is presented in terms of its preferred innovations, herein depicted within the  FIGS. 1 through 8 .  
      1. Detailed Description of the Figures  
      Referring now to  FIG. 1  and  FIG. 2 , the conventional single-plasma arc jet and the plasma thruster according to the PRIOR ART are shown here, which broadly describe the principle of generation of thrust when an electrical source is connected through a cathode  100 , from a battery  102  and electrons transferred to a charge receiver  105 , as propellants, and passed through a magnetic field  103 , and then propellants are neutralized at an electrode  104 , as an anode, or charges missing target to out-space  108 , and the coolant  107  cooled down the shell temperature of the electrifying process, and the throwing-catching-or-missing movements generating little thrust and sustaining in a short time in the prior art.  
       FIG. 2 , the cathode  100  and anode  104  are reversely set up from those of  FIG. 1 , and has an electric power generator  106  as a substitute for the battery  102  of  FIG. 1 . The acceleration interaction of this  FIG. 2  plasma thruster&#39;s electrical field generated through the power generator  106  for the ionized single-plasma  105  accelerating from the anode  104  to the cathodes  100  generates little thrust force as accelerating-neutralizing-missing (as throwing-catching-missing) processes in the prior art. Further, those electric single-plasma processes of charging-neutralizing-missing are not a total closed circuit, which generate an abrupt (jerky) motion for a short displacement and last in a short period of time.  
      For  FIGS. 1 &amp; 2 , their main thrust source is still coming from the arc&#39;s or the single plasma&#39;s thermal jetting power, but not from their electromagnetic force.  
       FIG. 3 , this schematic diagram shows a boy standing on the skating board  160  and playing a throwing-catching-missing game  150  &amp;  108  between his hands. He can throws electric balls  150  between his hands back and forth with miss catching some electric balls  108 , that will generate a rocking movement  170  around the origins. And by losing some balls  108 , he has some velocity in the opposite direction, and he will also miss some rocking power (fewer balls left  150 ) to play with.  
       FIG. 4 , is a schematic illustration of the nozzles  207  &amp;  209  jetting the dual-plasma out from both sides  200  &amp;  202  increasing their electric current amount in useful ways. When plasmas passing through nozzles, increasing their velocities into the opening place. Because of nozzles  207  &amp;  209  functioning, there will be more current flow between two nozzles. Those dual-plasma flows are different from the wire current;  
       FIG. 4 , the wire current [I=nevA] and no matter of the wire resistance or the cross-section area: [I 1 =n 1 e 1 v 1 A 1 ]≈[I 2 =n 2 e 2 v 2 A 2 ]. For plasmas gone through nozzles  207  &amp;  209 , if A 1 &gt;A 2  then v 1 &lt;v 2  for keeping the same flow rate in a steady-state flow [v 1 A 1 =v 2 A 2 ]; then for nozzles&#39; inlet and outlet: electrons&#39; density [n 1 &lt;n 2 ]. If dual-plasma are in higher temperatures, the closer place&#39;s electron&#39;s charges are higher [e 1 &lt;e 2 ]. The current will be as [I 1 =n 1 e 1 v 1 A 1 ]&lt;&lt;[I 2 =n 2 e 2 v 2 A 2 ].  
       FIG. 5 , a [GerTh-DawShien. V] dual-plasma flying object (referred as [Thruster V]) is provided a high-power DC turbo-contacting generator with contacting surfaces, generally denoted as  300 . For warming-up process, two outer-most surfaces are started to rotate by a motor  303  or by turbines  304  which provide any needed initial movements of two-opposite-rotating outer-surfaces  300  that generate high-power DC by its contacting surfaces with different material-made rollers  301 . Their generating high-power DC is required to initiate the positive plasma stream  200  and negative plasma stream  202  at the warm up process. A battery  302  allows for this warm-up transition, as an electricity source. From the warm-up process, the contacting generator generates DC power to electrifying plasmas and these continued plasmas will be combusted and neutralized to forming the flue stream  214 . After high temperature is attained, the flue stream  214  runs two-opposite-rotating-turbines  304  such that lead the turbo-contacting generator is dual-outer-surface  300  and rollers  301  which generate DC power. Then, their current flow is no more supplied by the battery  302 . And their electricity generation of the turbo-contacting generator from the previous thermal combustion heat power  214  and its turbine movements  304  sustain the flying object&#39;s power.  
      After an initial “warm-up” process, in which the unit is permitted to reach and sustain sufficient operating conditions, ensures enough DC power and consistent replenishment of the plasmas, the battery switch  302  is placed in an ‘Charged’ or “off” position. By selectively placing the operation switch  308  in the “on” position, the cable coil  252  is engaged and used to conduct electricity and enhance the electromagnetic field  206  of the magnet  250 . Thus, when the sufficient operating high-power DC electricity is attained, plasmas generation and usage are consistently generated from the electrifying process through a continuous supply of fuel  260 , oxygen  262 , and steam  217 . As such, the unit will generate consistent electromagnetic reaction force (thrust) by using plasmas fast passing through nozzles to the “C” shaped electromagnet  250  from the opposite directions. According to the right hand rule, plasmas will be bent downward, which will generate reaction lifting thrust to push the flying object upward or forward in a powerful linear manner.  
       FIG. 5 , shows the general design of a schematic diagram of the Fifth [GerTh-DawShien. V] dual-plasma flying object (referred as [Thruster V]) in which the electrodes  270  &amp;  272  and cables connected to the high-power DC source surfaces  300 . Then dual plasmas are fast passing through nozzles to an opening end of the C-shaped electromagnet  250  (and magnetic field  206 ) vertically from opposite sides to generate an action force  214  according to the right-hand rule. And the interaction of the electromagnetic field  206  is the “C” shaped magnet  250  with the ionized plasmas  207  and  209 . This lighter weight [GerTh-DawShien. V] dual-plasma flying object will have more reaction thrust and acceleration with no abrupt (jerky) motion.  
      Other improvements in the generation of thrust in utilizing a dual positive and negative plasma streams are shown in which the neutralization and combustion generate sparks and heat  214 , in which this heat source can be utilized to run turbines  304  which lead two-opposite-rotating-outer-surfaces to rotate for generating high-power DC electricity and their electricity will be used for ionizing plasmas in (+&amp;−) ionizing chambers  207  &amp;  209 , separately. By comparison of this new [GerTh-DawShien. V] dual-plasma flying object to the conventional single-plasma arc jet&#39;s and the single-plasma thruster, it changes single-plasma&#39;s internal implicit force as shown in  FIGS. 1, 2 ,  3 , &amp;  4 , to generate of more thrust of this invention and getting through the duel-plasma&#39;s electromagnetic explicit force. When dual-plasmas passing through nozzles increasing their velocities and current into the opening of the C-shaped magnet and jetting out, they will generate more reaction thrust  420  which is much greater than in the prior art.  
      More specifically,  FIG. 5  depicts a lighter weight dual-plasma flying object comprising heat exchangers  211  and  213  coupled to the electric insulated  251  fuel, oxygen, and water storage tanks  260 ,  262 , &amp;  263  which are supplying fuel  260  and oxygen  262  through humidity injected  217  to the thruster&#39;s chambers. Fuel and oxygen are delivered from the electric insulated  251  tanks  260  and  262  through heat exchangers  211  and  213  and humidity injection  217  ready for ionization  207  and  209  of the fuel and oxygen into plasma streams  200  and  202 . In this innovation. The plasmas are humidity injected  217  for having better electric conductivities. Electrodes  270  and  272  are provided within the ionizing chambers  207  and  209 , which are at opposite sides and are adjacent to the insulted C-shaped magnet  250 . The fuel storage tanks  260  and  262 , are electrically well insulated  251 .  
      The combustion and neutralization processes occur at the combustion space  214  of this flying object. The high pressure combustion waste  214  generated by this unit is released through a bottom nozzle  218  provided at bottom of the unit, which acts similarly to a jetting nozzle process for making more lifting thrust.  
      The magnet  250  has cable coil  252  wound about the magnet external surface to generate concurrent electromagnetic fields about the magnet  250 . The cable  252  is oil cooled for extending the life of the unit and optimizing operating insulation conditions  251 . The magnet  250  may include ceramic insulation  251  to protect and/or optimize the electromagnetic field generated by the cable coil  252 .  
      Referring now to  FIG. 6 , a schematic diagram of the Sixth [GerTh-DawShien. VI] dual-plasma-fusion flying object (referred as [Thruster VI]) by utilizing diluted heavy water injected  417  into ionizing chambers  207  and  209 , is depicted in accordance to an alternate plasma-fusion innovation to the present [Thruster V] invention. In this plasma-fusion innovation, as compared to an exemplary innovation described by  FIG. 6 , diluted heavy water  417 , plasmas  200 , and  202  are electrified at the [Thruster VI] ionizing chambers  207  &amp;  209 , respectively. The high-power DC generator  300  provides a continuous flow of charges to each electrode  270 ,  272 . The two-outer-surfaces  300  are made of metal and plastic, separately. The rollers  301  are metallic, or other suitable material-made and shaped to have increased surface contacting area. In this, the positively charged hydrogen plasma with ‘+’ charged heavy water [2H + ;D 2 O + ] and negatively charged oxygen plasma with ‘−’ charged heavy water [O = ;D 2 O − ] of  FIG. 6 , and are same passed through a “C” shaped magnet&#39;s  250  latitudinal opening  254 , such that generate an action plasmas-bent-down force  414  according to the right hand rule, and a reacting lifting-up thrust  420  as in  FIG. 6 .  
      Finally, the [GerTh-DawShien. VI] dual-plasma-fusion flying object&#39;s innovation as shown in  FIG. 6  has a nuclear diluted ‘+&amp;−’ heavy water fusion reaction  414  which also provides more power to turbines for generating more electricity and the flying thrust  420 . Because of its having more power and less weight, less amount of propellant is needed. The fusion energy and combustion heat  414  are released and directed through a bottom nozzle  218  of this invention, as its jetting power to increase its reaction thrust  420  and running turbines  304 .  
      Referring now to  FIG. 7 , a schematic diagram of a conventional Van de Graaff generator according to the PRIOR ART is shown broadly describing the generation of electric power. The conventional Van de Graaff generator is a high-voltage DC generator in which the contacting-surfaces  14  &amp;  16  of this generator are directly converting the different-material-contacting movements into electricity by means of rollers and belt rotating process  18 . The brushes  14  and  16 , are continuously transport charges to the two (+&amp;−) terminals of the generator, anode  20  and cathode  22 . This conventional Van de Graaff generator process takes place in the room temperature ranges of 15° C. to 25° C., but if happening at high temperatures, charges run more wildly and the risk of discharging sparks increased.  
       FIG. 8 , For the new advanced Thruster VI&#39;s DC generator is referred as ([ShihHwa. V] dual-plasma-fusion DC turbo-contacting generator). For purposes of disclosure, and not as a limitation, and for purposes of providing a disclosure under 35 U.S.C. 112, as [Thruster VI] by utilizing diluted heavy water injected  417  into ionizing chambers  207  and  209 , is depicted in accordance to an alternate plasma-fusion innovation to the present [Thruster V] invention. In this plasma-fusion power generation innovation, as compared to an exemplary innovation described by  FIG. 8 , diluted heavy water  417 , plasmas  207 , and  209  are electrified at the chambers, respectively. The high-power DC contacting-generator  300  provides a continuous flow of charges to each electrode  270 ,  272 , respectively. The two-outer-surfaces  300  are made of metal and plastic, separately. The rollers  301  are metallic or plastic, or other suitable material shaped to have increased surface contacting area. In this, the positively charged hydrogen plasma with ‘+’ charged heavy water and negatively charged oxygen plasma with ‘−’ charged heavy water are generated from electrifying of  FIG. 8 .  
      Finally, the innovation as shown has a nuclear diluted ‘+&amp;−’ heavy water fusion reaction  414  which also provides more thermal power to turbines for generating more electricity, and less amount of non-fusion propellant is needed. The fusion energy and combustion heat  414  are released and directed through a nozzle  218  to run turbines  304  and rotate two power generation surfaces  300  of this invention. The dual-plasma-fusion reactions of this innovation are:  
      Positive Electrode side: [2H + +D 2 O + ]; 
 
H 2 +D 2 O+‘+’charged+Cable→[2H + +D 2 O + ]+3e − +3‘+’→→[2H + +D 2 O + ]
 
 Negative Electrode side: [O = +D 2 O − ];  O 2 +2D 2 O+Cable+6e − (electron flow)→2[O = +D 2 O − ]
 
 The equations are shown as: Combustion, Neutralization, &amp; Fusion Reactions:  
           [       2   ⁢     H   +       ;       D   2     ⁢     O   +         ]     +     [       O   =     ;       D   2     ⁢     O   -         ]       →       ⁢           [     H   ⁢     -     ⁢   O   ⁢     -     ⁢   H     ]     ⁢           ⁢   Steam     +     2   ⁢       He     +   2       ⁡     [     α   ⁢             ⁢             ⁢   particles     ]         +     20   =       →       ⁢         [     H   ⁢     -     ⁢   O   ⁢     -     ⁢   H     ]     ⁢           ⁢   Steam     +     2   ⁢     He   ⁡     [     no   ⁢           ⁢     charge   /   no     ⁢           ⁢   radiation     ]         +   20   +     fusion   ⁢           ⁢   heat   ⁢           ⁢   runs   ⁢           ⁢   turbo   ⁢     -     ⁢   contacting   ⁢           ⁢   generator     +     dynamic   ⁢     -     ⁢   plasma   ⁢           ⁢   generate   ⁢           ⁢   lifting   ⁢     -     ⁢   force   ⁢     -     ⁢   of   ⁢     -     ⁢     thruster   ′     ⁢   s             
 
 2. Operation of the Preferred Innovations 
 
      In accordance with the preferred innovations, the various features of the present invention are summarized in Table 1 below.  
               TABLE 1                          The Similarities &amp; Differences Among [GerTh-DawShien. V &amp; VI] Jet       Thrusters And [ShihHwa. V] DC Turbo-Contacting Generator.                                 [GerTh-   [GerTh-               DawShien]   DawShien]   [ShihHwa. V]       Classification   [Thruster V]   [Thruster VI]   [DC generator]               Electric Start   Yes   Yes   Yes       Electric Running   Yes   Yes   Yes       Thermal Energy Run   Yes   Yes   Yes       Generate Electricity   Yes   Yes   Yes       Taken Electric Loads   Yes   Yes   Yes       With “C” shaped   Yes   Yes   No       Electromagnet       Generate Motion   Yes   Yes   No       ‘+’ Plasmas   H + ; (H 2 O + )   H + ; (D 2 O + )   H + ; (D 2 O + ) ions           ions   ions       ‘−’ Plasmas   O = ; (H 2 O − )   O = ; (D 2 O − )   O = ; (D 2 O − ) ions           ions   ions       Plasmas-Fusion   No   Yes   Yes                  
 
      The foregoing descriptions of specific innovations of the present invention are presented for purposes of illustration and application. They are not intended to be exhaustive or to limit the invention to the precise forms disclosed, and obviously many modifications and variations are possible in light of the above disclosure. The innovations were chosen and described in order to best explain the motion principles of the dual-plasma jet thruster V &amp; dual-plasma-fusion jet thruster VI and their practical applications, to thereby enabling others skilled in the art with various advanced modifications as those are suited to the particular use contemplatively. It is intended that the scope of the invention are defined by the Claims appended hereto and their equivalents. Therefore, the scope of the invention is to be limited only by the following claims.