Abstract:
A model rocket and launch system in which a rocket is launched by combustion produced from a mixture of water and calcium carbide. The water and calcium carbide are combined in a mixing container and launch tube and create a combustible gas. The container and launch tube incorporates a spark chamber consisting of a spark element device and electrode. Both the rocket body tube and launch tube includes a conductive coupling device and is designed to be co-dependent of each other in order to complete an electrical circuit for ignition purposes. The launch tube conductive coupling device and is electrically connected to a spark element device. Electrical current is sent to the spark element device and electrode when the electrical current provided from a high voltage generator passes through both the model rocket unit and the launch system unit via the combined conductive coupling devices. The spark element device and electrode located in the mixing container create a spark and ignites the calcium carbide gas mixture. The rapidly expanding gases from combustion enters the launch tube. A model rocket mounted over the launch tube is thrust forward from the expanding gases and launched into flight. The model rocket and launch system further incorporates safety devices designed to prevent accidental ignition and misuse and tampering of the launch system.

Description:
This application claims the benefit of U.S. Provisional Patent Application No. 60/665,877 filed on Mar. 29, 2005 entitled “CARBIDE MODEL ROCKETRY SYSTEM” and is hereby incorporated herein by reference. 
    
    
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates broadly to model rocketry and launch systems and more particularly to model rockets that utilize “pressurized gases” to launch rockets in lieu of “solid” or “liquid” propellants. 
     2. Description of the Prior Art 
     For over 100 years the prior art model rockets have been launched and powered by rocket engines consisting of solid fuel rocket propellants and liquid rocket fuels; Because of the recent increase of safety requirements and law regulations, the availability of solid rocket propellants and liquid rocket fuels have become limited and prohibited in use to most amateur model rocketeers. The result is diminishing the hobby of model rocketry. Concerned manufactures are producing alternate means and safer rocketry where the rocket engines consisting of propellants and fuels are eliminated. Model rocket manufactures have alternately switched to “pressurized gas” systems to launch rockets safely. An air rocket  1  as shown in the prior art  FIG. 1 , utilizes manually operated hand and/or foot air pumps  2  and  3  respectively to pressurize the launch system  4  and release them into the air rocket  1  to launch and thrust them into flight. 
     A hydrogen model rocket  5  as shown in  FIG. 2 , utilizes a solution of citric acid crystals and water and is broken down by electrolysis in a fuel generator  6 , where the gas is collected into a reaction chamber  7  and then heated by an element  8  to ignite the “hydrogen gas”. The hydrogen gas expands to thrust the hydrogen rocket  5  into flight. Alternately, solutions are mixed such as vinegar and baking soda to create expanding gases by a chemical reaction (not shown) to launch and thrust some model rockets. However, prior art model rocket “pressurized systems” suffer certain drawbacks whereas the air rockets “hand” and “foot pump” pressurization process requires physical and laborious time and effort actions to launch a model rocket and there is always the possibility of suffering a hand, wrist, or foot and ankle injury. 
     The hydrogen rocket launch system is a complex unit that contains to many sensitive parts where many things can go wrong. The hydrogen rocket has a delayed launching cycle whereas it takes between 2-5 minutes to generate and produce hydrogen from the solution and another several seconds to heat up and ignite the hydrogen for launching. The generator and ignition system require an extensive battery pack of 6 “D” sized batteries located in base  9  and if the battery pack is not fresh, ignition time is further delayed and/or misfire occurs. If the heating element and igniter get wet from the water solution this will further delay the launch process again and possibly a misfire may occur. 
     SUMMARY OF THE INVENTION 
     The present invention is a new improved model rocketry system as compared to the prior arts. It is therefore an object of the present invention to provide for a novel, safe and reliable easy-to-use model rocketry system. 
     In accordance with the present invention, the model rocketry system comprises of a model rocket unit and a launch system unit. Whereas, the model rocket unit includes a hollow rocket body tube and the launch system unit includes a hollow launch tube that is compatibly designed as to structurally slip-fit to one another. Both the rocket body tube and launch tube includes a conductive coupling device and is designed to be co-dependent of each other in order to complete an electrical circuit for ignition purposes. The launch system unit further comprising of an upper portion and lower portion, with the lower portion including a mixing container constructed of a bottle or jar supported by a base and incorporating at least one internally mounted electrode affixed in the mixing container. The mixing container having a dual function, whereas the mixing container is utilized to combine a solution of water and calcium carbide to form a gas and utilized to create a spark and ignite the solution to launch a model rocket. The launch system unit upper portion consisting of a closure cap provided with means to accept a spark element device and launch tube. Whereas the launch tube includes an end portion flange with a length of hollow tubing. The launch tubing portion further incorporates an internally affixed conductive coupling device and is electrically connected to a spark element device. The upper and lower portions of the launch system unit are connectively combined via the closure cap whereas, the launch tube end flange portion and spark element device are mounted atop of the mixing container and then encapsulated and affixed by the closure cap by threading or other locking means. The launch system unit works when a solution of water and calcium carbide media are combined to create a combustible gas. The carbide media can be made of a consistency of powder, partially granulated particles, or solid form. Carbide media is measured and introduced either manually by pouring or spooning into the opening of the launch tube to meet with the water in the mixing container, or by mechanical means by a loader integrally built into the mixing container. 
     The mixing container further incorporates a spark element device and electrode. Electrical current is sent to the spark element device and electrode when the electrical current provided from a high voltage generator passes through both the model rocket unit and the launch system unit via the combined conductive coupling devices. The spark element device and electrode located in the mixing container create a spark and ignites the calcium carbide gas mixture. The rapidly expanding gases from combustion enters the launch tube. A model rocket mounted over the launch tube is thrust forward from the expanding gases and launched into flight. 
     The model rocket unit further comprising of an upper portion and lower portion, with the lower portion including a rear conductive portion, two or more stabilizing fins, and whereas at least one stabilizing fin is conductive. The upper portion including a rocket body tube and a nose cone, and a conductive coupling device affixed within the rocket body tube. The model rocket unit upper and lower portions are electrically connected to one another. A wire from a spark generator is connected to a conductive stabilizing fin via an alligator clip. Current passes through the conductive stabilizing fin and transferred to the rocket conductive coupling device. The model rocket unit and launch system unit conductive coupling devices are inherent safety devices designed to prevent accidental ignition and misuse and tampering of the launch system. The model rockets are flight-recyclable and there are several types of flight recovery systems for repeated launch uses. 
     In accordance with the first embodiment of the present invention, the model rocketry system is comprised of a model rocket unit and a launch system unit. The launch system unit includes a first mixing container with an electrode, a closure cap, a first spark element device, a first launch tube, a first conductive coupling device and a spark generator. The mixing container is fitted and supported into a base. The base contains different diametrical size cavities and is suitable to fit and support multiple sized mixing containers. The launch tube contains a first internally affixed conductive coupling device and is electrically connected to the spark element device. The spark element device is located below the closure cap and situated nearest the electrode in the mixing container. 
     The spark element device and the electrode are spaced accordingly with an air gap to promote a spark to travel between the two points. The model rocket unit includes a model rocket having a nose cone, stabilizing fins and a hollow body tube that is receiveably mountable via a slip-fit over the launch tube. The rocket body tube further incorporates a first internally affixed conductive coupling device and is electrically connected to a first conductive stabilizing fin. When the model rocket unit is mounted to the launch tube, both the conductive coupling devices make contact with one another to complete an electrical circuit. At least one wire from a spark generator is connected to a conductive stabilizing fin and the other wire connected to the launch system electrode. 
     In accordance with the second embodiment of the present invention, the model rocket unit incorporates a tube within a tube, whereas the lower portion of the rocket body tube has a second diametrically smaller hollow tube extending out towards the rear of the model rocket, and substantially further extending a length beyond the stabilizing fins. The smaller diameter extended tube is conductive and is compatibly designed as to structurally slip-fit into the launch tube and acts as both the conductive coupling device and spark element device when used in conjunction with a modified launch system unit. The modified launch system unit in accordance with the second embodiment of the present invention consisting of a single-unit mixing container and base. The modified launch system unit further comprising of a hollow launch tube incorporating a spring-loaded, swinging-door mechanism, actively moved open or closed by action of connecting and disconnecting the model rocket. 
     In accordance with the third embodiment of the present invention, the model rocket unit incorporates a tube within a tube, whereas the lower portion of the rocket body tube has a second diametric hollow conductive tube extending out towards the rear of the model rocket. The inner diameter of the extended tube is compatibly designed as to structurally slip-fit over the launch tube, whereas, the outer diameter portion of the extended tube is compatibly designed as to structurally slip-fit and seat into a hub located at the base of a modified launch tube. Below the hub and seat portion of the modified launch tube is a spark element device. The extended tube makes contact with the spark element device and acts as a conductive coupling device to complete the electrical circuit. 
     In accordance with the fourth embodiment of the present invention, the model rocket unit nose cone, body tube and stabilizing fins are constructed of a conductive material such as a conductive foam, plastic or combination thereof. The launch system unit includes a hollow launch tube that is also constructed of a conductive foam or plastic. The model rocket can be structurally designed as to slip-fit over or into the conductive launch tube to complete the electrical circuit. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       Other objects and advantages of the invention will become apparent from a study of the following specification when viewed in light of the accompanying drawings, wherein: 
         FIG. 1  is a perspective view showing an air model rocket and launch system of the prior art; 
         FIG. 2  is a perspective view showing a hydrogen model rocket and launch system of the prior art; 
         FIG. 3  is a perspective view of a carbide model rocket and launch system in accordance with the first embodiment of the present invention; 
         FIG. 4A ,  4 B,  4 C,  4 D,  4 E,  4 F,  4 G, are perspective views of model rocket units in accordance with the first exemplary embodiment of the present invention showing different structural arrangements of model rocket conductive coupling devices; 
         FIG. 5A ,  5 B,  5 C,  5 D,  5 E,  5 F,  5 G,  5 H,  5 I,  5 J, are perspective views of launch system units in accordance with the first exemplary embodiment of the present invention showing different structural arrangements of launch tube conductive coupling device, electrodes and spark element devices; 
         FIG. 6  is a perspective view of a carbide model rocket and launch system in accordance with the second embodiment of the present invention; 
         FIG. 7A ,  7 B,  7 C,  7 D are perspective views of model rocket units and launch system units in accordance with the second exemplary embodiment of the present invention showing different structural arrangements of model rocket and launch tube conductive coupling devices, electrodes and spark element devices; 
         FIG. 8  is a perspective view of a carbide model rocket and launch system in accordance with the third exemplary embodiment of the present invention; 
         FIG. 9A ,  9 B,  9 C, are perspective views of model rocket units in accordance with the third exemplary embodiment of the present invention, showing different structural arrangements of a model rocket conductive coupling device; 
         FIG. 9D  is a perspective view of a launch system unit in accordance with the third exemplary embodiment of the present invention showing a launch tube conductive coupling device, electrode and spark element device; 
         FIG. 10  is a perspective view of a carbide model rocket and launch system in accordance with the fourth embodiment of the present invention; 
         FIG. 11A ,  11 B,  11 C,  11 D are perspective and exploded views of launch tube assemblies, spark element devices, and mixing containers with a loader, in accordance with the present invention; 
         FIGS. 12 ,  13  &amp;  14  are perspective views of multiple launch system in accordance with the present invention; 
     
    
    
     DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS 
     The preferred embodiments of the present invention will now be described with reference to accompanying drawings. 
     Referring now to  FIG. 3  an improved model rocketry system in accordance with the first embodiment of the present invention illustrated generally at  40  and comprises a model rocket unit  10 , a launch system unit  24  and a base  30 . Whereas the model rocket unit  10  includes a hollow rocket body tube  13  with attached conductive stabilizing fins  14  and a nose cone  12  having an integral conductive coupling device  15  in the form of a solid extended shaft member shown in better detail at  FIG. 4E   1 . The rocket conductive coupling device  15  is affixed inside rocket body tube  13  and is electrically connected to a conductive stabilizer fin  14  via a strip of metallic foil tape or wire  15 A attached to the rocket body tube  13  shown in better detail at  FIG. 4E . 
     Whereas the launch system unit at  24  comprises of a mixing container  21  in the form of a jar or bottle, a closure cap  20 , an internally mounted elbow-shaped electrode  22 , a hollow launch tube  17  with an integral end flange  17 A, a launch tube conductive coupling device  18  in the form of a conductive ring as shown in better detail at  FIG. 5A   1 . Conductive ring  18  is attached to the inside diameter of launch tube  17  with glue and is electrically connected to a spark element device  19  with a strip of metallic foil tape or wire  18 A affixed to the inner diameter of launch tube  17 . The spark element device  19  is shaped in the form of a large washer as shown in better detail at  FIG. 11B . The spark element device  19  and launch tube  17  are combined to form an assembly, whereas the spark element device washer  19  rests on top of mixing container threads  20 A and the launch tube end flange  17 A rests on top of the spark element device  19 . Threaded closure cap  20  with integral centering hole  20 B is then placed over the launch tube  17  and fastened to mixing container threads  20 A to encapsulate the assembly as shown in better detail at  FIG. 11B . A spark generator  23  is electrically connected between the model rocket unit  10  and the launch system unit  24  with a grounding wire  23 A and positive wire  23 B. Whereas grounding wire  23 A is electrically connected to electrode  22  and positive wire  23 B is electrically connected by attaching alligator clip  23 C to a conductive stabilizing fin  14 . Spark generator  23  can be in the form of a push button piezo electrical igniter, a battery generated spark produced by a coil or any other appropriate method that are well known in the prior arts is within the scope of the present invention. Mixing container  21  is fitted into a base  30  whereas base  30  has multiple cavities  31  and  31 A that can receive and support multiple sized mixing containers  21 . Multiple spaced support legs  32  are integral to base  30 . 
     The model rocket unit  10  and launch system  24  are co-dependent of each other because the two units need to be joined in order to produce continuity and complete the electrical circuit to have ignition occur properly. Thus, it will be appreciated that when the model rocket unit  10  is properly joined to the launch system unit  24  the rocket conductive coupling device  15  will engage and touch the launch tube conductive coupling device  18  activating continuity and transfer of electrical conductivity between the two units. 
     The rocket conductive coupling device  15  and the launch tube conductive coupling device  18  are mechanical coupling devices that are designed to engage and touch one another in order to transfer the electrical power produced from the spark generator  23  to the electrode  22  and spark element device  19 . Those skilled in the art will appreciate that the rocket conductive coupling device  15  and the launch tube conductive coupling device  18  may be of any appropriate design to facilitate continuity and transfer of electrical conductivity between the model rocket and launch system. 
       FIGS. 4A-4G  are model rocket units  10  in accordance with the first exemplary embodiment of the present invention showing the different structural arrangements of model rocket conductive coupling devices  15  that are integral to or attached to nose cone  12  and that are affixed inside the rocket body tube  13 . Whereas  FIGS. 4A-4D  utilizes a conductive coupling device in the form of conductive brush fibers  15   2  and  15   3  supported by a conductive wire wound stem  16  and attached to nose cone  12 .  FIG. 4A  and  FIG. 4B  utilize a tapered brush  15   2  made from conductive plastic or foam as shown in detail at  FIG. 4A   1 .  FIG. 4C  and  FIG. 4D  utilize a bristled bottle or tube brush  15   3  made from soft conductive fibers or wire shown in detail at  FIG. 4C   1 .  FIG. 4F  utilizes a conductive coupling device in the form of a hollow conductive tube  15   4  as shown in detail at  FIG. 4F   1 .  FIG. 4G  utilizes a conductive coupling device in the form of a mechanical spring  15   5  as shown in detail at  FIG. 4G   1 . Varying the length of the rocket conductive coupling device  15  changes the engagement and placement of the reciprocal launch tube conductive coupling device  18  accordingly. 
       FIGS. 5A-5J  are launch system units  24  in accordance with the first exemplary embodiment of the present invention showing the different structural arrangements of the launch tube conductive coupling devices  18  that are affixed inside launch tube  17  and the various arrangements of the electrode  22  and spark element devices  19  as mounted in mixing container  21 . Whereas  FIG. 5B  and  FIG. 5C  utilizes a launch tube  17  with an end flange  17 A and a conductive coupling device in the form of a mechanical spring  18   2  having an integral flange  18 A that bisects spring  18   2  into upper and lower half portions as better shown in detail at  FIG. 5B   1  and  FIG. 5C   1 . Integral flange  18 A supports the upper spring portion  18   2  in the launch tube  17  and supports the lower spring portion  18   2  in mixing container  21 . Electrode  22 A in the form of a straight pin or shaft is mounted in mixing container  21  and aligned next to lower spring portion  18   2  to create a spark gap  22   1 . In this configuration, the lower spring portion of  18   2  is utilized and substituted as the spark element device  19 . 
       FIG. 5D  utilizes a launch tube coupling device in the form of a hollow conductive tube  18   3  with an integral conductive end flange  18 B shown in better detail at  FIG. 11C . The conductive tube  18   3  is structurally made to slip-fit into the bottom of launch tube  17  with conductive end flange  18 B supporting the assembly atop of mixing container  21 . Electrode  22  is mounted in mixing container  21  and aligned directly under the conductive end flange  18 B to create a spark gap  22   1 . In this configuration, the conductive end flange  18 B is utilized and substituted as the spark element device. 
       FIG. 5E  utilizes a launch tube  17  with an end flange  17 A shown in better detail at  FIG. 11A , and a conductive coupling device in the form of metal foil or metallized finish  18   4 . The metallizing covers a portion of the inner diameter of launch tube  17  and extends the length of tube  17  and out the bottom to cover and metallize a portion of end flange  17 A. The metallic finish  18   4  can be applied by spraying, dipping, plating, impregnating or a combination thereof; and the metallic foil  18   4  applied by tape or glue. Launch tube  17  is supported by end flange  17 A atop of mixing container  21 . Electrode  22  is mounted in mixing container  21  and aligned directly under the metallized end flange  17 A to create a spark gap  22   1 . In this configuration, the launch tube end flange  17 A is utilized and substituted as the spark element device. 
       FIGS. 5F-5J  are launch system units  24  comprising of a launch tube  17  with integral end flange  17 A utilizing the conductive coupling device arrangements aforementioned in  FIG. 5A ,  FIG. 5D  and  FIG. 5E . However, there are variations of the electrode and spark element devices shown in  FIGS. 5F-5J  that can be achieved and are both safety and novel arrangements that will be apparent and explained here further, that are in accordance with the first exemplary embodiment of the present invention. 
     Whereas,  FIG. 5F  utilizes a spark element device  19  as shown in better detail at  FIG. 11B  and a spark assisting assembly  21 A shown in detail at  FIG. 5F   1 . The spark assisting assembly  21 A at  FIG. 5F   1  consisting of a conductive angle plate  19 A with an integral base  19 A 1 , a conductive spring  19 B mounted to base  19 A 1 , the conductive spring  19 B having a conductive weighted end tip or mounted ball  19 C. The spark assisting assembly  21 A is fitted inside mixing container  21  whereas conductive angle plate  19 A rests against a side of mixing container  21  and integral base  19 A sits on bottom of mixing container  21 . When mixing container  21  is resting on a level surface, both the conductive spring  19 B and the conductive mounted ball  19 C align with electrode  22 , mounted in mixing container  21  to create a spark gap  22   1 . If mixing container  21  is tilted at more than 25 degrees conductive spring  19 B will move in a direction away from electrode  22  and misalign conductive mounted ball  19 C creating too large of a spark gap  22   1  preventing a spark to occur. Thus the spark assisting assembly  21 A acts as a safety tilt switch preventing model rockets from being launched with an angle in excess of 25 degrees. Now, with spark element device  19  resting on top of mixing container  21 , the spark element device  19  makes physical contact with the conductive angle plate  19 A making it possible to transfer electrical power to the spark assisting assembly  21 A. 
       FIG. 5G  utilizes a spark assisting assembly  21 B as shown in detail  5 G 1 . The spark assisting assembly  21 B consisting of a conductive base  19 A 2  in the form of a flat washer, a conductive spring  19 B 1  and a conductive weighted end tip or mounted ball  19 C 1 . The spark assisting assembly  21 B is mounted with base  19 A 2  atop of mixing container  21  with conductive spring  19 B 1  and mounted ball  19 C 1  facing downward toward the inside of mixing container  21  and aligned with electrode  22 . When mixing container  21  is resting on a level surface, both the conductive spring  19 B 1  and the conductive mounted ball  19 C 1  align with electrode  22  mounted in mixing container  21  to create a spark gap  22   1 . If mixing container  21  is tilted at more than 25 degrees conductive spring  19 B 1  will move in a direction away from electrode  22  and misalign conductive mounted ball  19 C 1  creating too large of a spark gap  22   1  preventing a spark to occur. Thus the spark assisting assembly  21 B acts as a safety tilt switch preventing model rockets from being launched with an angle in excess of 25 degrees. The spark assisting assembly  21 B can be electrically connected to the launch tube coupling device  18  with a strip of metallic foil tape or wire  18 A affixed to the inner diameter of launch tube  17 . As an alternate configuration, the launch tube  17  with conductive end flange  18 B detailed at  FIG. 5D  can be utilized to transmit the electrical connection by making intimate contact by sitting on top of the spark assisting assembly  21 B in  FIG. 5G . 
       FIG. 5H  utilizes a spark element device  19  and a spring elbow electrode  22 B consisting of a conductive spring  22 B 1  and a conductive weighted end tip or mounted ball  22 B 2 . Spring elbow electrode  22 B is mounted in mixing container  21  and is set just below the spark element device  19 . When mixing container  21  is resting on a level surface, both the conductive spring  22 B 1  and the conductive mounted ball  22 C 1  align straight up under the spark element device to create a spark gap  22   1 . If mixing container  21  is tilted at more than 25 degrees conductive spring  22 B 1  will move in a direction away from the spark element device  19  and misalign conductive mounted ball  22 C 1  creating too large of a spark gap  22   1  preventing a spark to occur. Thus the spring elbow electrode  22 B acts as a safety tilt switch preventing model rockets from being launched with an angle in excess of 25 degrees. 
       FIG. 5I  utilizes a spark assisting assembly  21 C as shown in detail  5 I 1 . The spark assisting assembly  21 C consisting of a conductive base  19 A 3  in the form of a flat washer, and a conductive rigid pin  19 B 2 . The spark assisting assembly  21 C is mounted with base  19 A 3  atop of mixing container  21  with conductive pin  19 B 2  facing downward toward the inside of mixing container  21  and aligned with electrode  22 A to create a spark gap  22   1 . The spark assisting assembly  21 C can be electrically connected to the launch tube coupling device  18  with a strip of metallic foil tape or wire  18 A affixed to the inner diameter of launch tube  17 . As an alternate configuration, the launch tube  17  with conductive end flange  18 B detailed at  FIG. 5D  can be utilized to transmit the electrical connection by making intimate contact by sitting on top of the spark assisting assembly  21 C in  FIG. 5I . 
       FIG. 5J  utilizes a spark element device  19 D that is in the form of a thick conductive foam or plastic gasket shown in detail  5 J 1 . Spark element device  19 D is attached to the end of launch tube  17  to become an end flange and is installed atop of mixing container  21 . Electrode  22  is mounted in mixing container  21  just below spark element device  19  to create a spark gap  22   1 . 
     It will be appreciated by those skilled in the art that the model rocket units and the launch system units as described in the first embodiment are adaptable and interchangeably used with one another to form one or more combinations of model rocketry systems in accordance with the present invention. 
     It will be appreciated further by those skilled in the art that the model rocketry system can be made of any appropriate lightweight materials such as plastic, foam, balsa wood, cardboard, paper, conductive plastics and foams, metallic foils and tapes, as well as metal wire and springs or any combination thereof. Model rocketry components can be formed by die-cutting, injection molding or shaped from solid materials and can be assembled by press-fit and gluing methods. However, any other appropriate methods of manufacturing the model rocketry system that are well known in the prior arts are also within the scope of the present invention. 
     The second embodiment of the present invention shown in  FIG. 6  is an improved model rocketry system illustrated generally at  50  comprises of a model rocket unit  11  and a modified launch system unit  25 . Whereas, the model rocket unit  11  includes a hollow rocket body tube  13   1  with attached conductive stabilizer fins  14   1  and nose cone  12   1  shown in better detail at  FIG. 7A . The model rocket unit  11  further incorporating a conductive tube assembly  41  comprising of a hollow extended conductive tube  41 A with attached body ring  41 B. The conductive tube assembly  41  is fitted into rocket body tube  13   1  and is attached by the body ring  41 B with glue. The conductive tube  41 A extends out towards the rear of body tube  13   1  and substantially further extending a length beyond the conductive stabilizer fins  14   1 . The conductive tube assembly  41  is electrically connected to the conductive stabilizer fins  14   1  with a strip of metallic foil tape or wire  18 A affixed to diameter of launch tube  17  and then attached to body ring  41 B. 
     The modified launch system unit  25  in accordance with the second embodiment of the present invention as shown in detail at  FIG. 7A  consists of a hollow launch tube  17  with an integral end flange  17 A, closure cap  20 , a mixing container  21  with integral base  32   1 , an electrode  22 A mounted in mixing container  21  and a spark generator  23 . 
     Now, the model rocket unit  11  is structurally designed to join the modified launch system unit  25  by way of the conductive tube  41 A slip-fitting into launch tube  17  and with rocket body tube  13   1  slip-fitting over launch tube  17 . With model rocket unit  11  fully joined with launch system unit  25  the conductive tube  41 A is aligned with electrode  22 A to create a spark gap  22   1 . In this configuration, the conductive tube  41 A is utilized and substituted to perform as the conductive coupling device and spark element device as described in the first embodiment. 
       FIG. 7B  and  FIG. 7C  are identical rocket model units  11  as described and shown in  FIG. 7A . However,  FIG. 7B   1  and  FIG. 7C   1  are modified launch system units  25  consisting of a launch tube  17  with end flange  17 A incorporating a first spring-loaded, swinging-door mechanism  17   1 . The swing-door mechanism  17   1  is affixed inside the lower portions of launch tube  17  and is actively moved open or closed by conductive tube  41 A by action of connecting and disconnecting the model rocket unit  11  to launch tube  17 . When carbide material is introduced through the opening of launch tube  17 , the carbide material falls to the bottom of launch tube  17  and rests on top of the swinging-door mechanism  17   1 . As the model rocket unit  11  is joined to the launch tube system unit and the swinging-door mechanism is activated, the carbide material is then released into the mixing container  21  and combines with the water to make a solution that turns to a gas. The gas is ignited when a spark is initiated from a spark generator  23  between the electrode  22 A and conductive tube  41 A. Spark generator  23  is electrically connected to the launch system unit  25  with the ground wire  23 A connected to electrode  22 A and to the model rocket unit  11  with the positive wire  23 B connected to a conductive stabilizer fin  14   1  with alligator clip  23 C. 
       FIG. 7D  is an alternate model rocket unit  11  in accordance with the second embodiment of the present invention having a conductive tube assembly  42  consisting of a hollow extended conductive tube  42 A with two body rings  42 B as shown in detail at  FIG. 7D   1 . The conductive tube assembly  42  is fitted into rocket body tube  13   1  and is attached by the two body rings  42 B with glue. The conductive tube  42 A extends out towards the rear of body tube  13   1  and substantially further extending a length beyond the conductive stabilizer fins  14   1 . The conductive tube assembly  42  is electrically connected to the conductive stabilizer fins  14   1  with a strip of metallic foil tape or wire  18 A affixed to diameter of launch tube  17  and then attached to body rings  42 B. 
     It will be appreciated by those skilled in the art that the model rocket unit  11  in accordance with the second embodiment of the present invention are adaptable and interchangeably used with launch system units  24  of the first embodiment of the present invention. 
     The third embodiment of the present invention shown in  FIG. 8  is an improved model rocketry system illustrated generally at  60  comprising of a model rocket unit  100  and a modified launch system unit  26 . Whereas, the model rocket unit  100  shown in detail at  FIG. 9A  and  FIG. 9B  includes a hollow rocket body tube  13  with attached conductive stabilizer fins  14  and nose cone  12 , and a conductive tube assembly  43 . The conductive tube assembly  43  consisting of an inner hollow conductive tube  43 A with two conductive tube rings  43 B and a conductive cover tube  43 C as shown in better detail at  FIG. 9A   1 . The conductive tube assembly  43  is fitted into the rear of rocket body tube  13  and is attached by conductive cover tube  43 C with glue. The conductive cover tube  43 C extends out towards the rear of body tube  13  extending a length beyond the conductive stabilizer fins  14 . The conductive tube assembly  43  is electrically connected to the conductive stabilizer fins  14  with a strip of metallic foil tape or wire  18 A affixed to diameter of launch tube  17 .  FIG. 9C  is an alternate rocket model unit  100  whereas the conductive tube assembly is fitted into the rear of rocket body tube  13  and is set to extend even length with the conductive stabilizer fins  14 . 
     The modified launch system unit  26  in accordance with the third embodiment of the present invention as shown at  FIG. 9D  consists of a hollow launch tube  17  with an integral conductive end flange  17 B, and a hub assembly  19 A shown in detail at  FIG. 9D   2 . The hub assembly  19 A includes a conductive end flange  19 A 1 , a non-conductive hub  19 A 2  with an integral thru hole  19 A 3 . The launch system unit further including a closure cap  20 , a mixing container  21  with integral base  32   1 , an electrode  22  mounted in mixing container  21  and a spark generator  23 . 
     Now, the launch tube  17  and hub assembly  19 A are combined to form a unit with mixing container  21  when the launch tube  17  is mounted with the conductive end flange  17 B resting atop of mixing container  21 , and then the hub assembly  19 A placed onto the launch tube  17  and seated to rest atop of conductive end flange  17 B. The conductive end flange  17 B and hub assembly  19 A are then encapsulated and affixed to the mixing container with closure cap  20 . 
     Model rocket unit  100  works in conjunction with the modified launch system unit  26  when the model rocket conductive tube assembly  43  is receivably joined to the launch tube  17  and hub assembly  19 A. Whereas, the inner diameter of model rocket conductive tube  43 A is compatibly designed as to structurally slip-fit over launch tube  17 , and whereas, a portion of the outer diameter of the model rocket conductive cover tube  43 C is compatibly designed as to structurally slip-fit and seat into hub assembly  19 A. Now, with the model rocket unit  100  joined properly to the modified launch system unit  26 , the bottom portion of the model rocket conductive tube assembly  43  makes physical contact with conductive end flange  19 A 1  of hub assembly  19 A and then the model rocket unit  100  and launch system unit  26  become a completed circuit and are electrically connected to each other. Now, mixing container  21  incorporates an electrode  22  spaced properly under the launch tube conductive end flange  17 B to create a spark gap  22   1 . A spark is initiated from a spark generator  23  between the electrode  22  and launch tube conductive end flange  17 B. Spark generator  23  is electrically connected to the launch system unit  26  with the ground wire  23 A connected to electrode  22  and to the model rocket unit  100  with the positive wire  23 B connected to a conductive stabilizer fin  14  with alligator clip  23 C. In this configuration the launch tube conductive end flange  17 B acts as a spark element device in conjunction with the hub assembly  19 A and the model rocket conductive tube assembly  43  acts as the conductive coupling device. 
     The fourth embodiment of the present invention shown in  FIG. 10  is an improved model rocketry system illustrated generally at  70  comprising of a model rocket unit  200  and a modified launch system unit  27 . Whereas, the model rocket unit  200  is a single unit molded rocket made from conductive foam or conductive plastic, consisting of a hollow body tube  13 , stabilizer fins  14  and nose cone  12 . 
     The modified launch system unit  27  in accordance with the fourth embodiment of the present invention consists of a molded, hollow launch tube  17  with integral end flange  17 A made from conductive foam or conductive plastic, a closure cap  20 , a mixing container  21  with integral base  32   1 , an electrode  22  mounted in mixing container  21  and a spark generator  23 . The molded launch tube  17  is mounted with integral end flange  17 A resting atop of mixing container  21  and then encapsulated and affixed to the mixing container with closure cap  20 . 
     The body tube  13  of model rocket unit  200  is structurally designed to slip-fit over molded launch tube  17 . Both the model rocket  200  and the molded launch tube  17  are made of conductive material and when joined become a completed circuit and are electrically connected to each other. 
     Now, mixing container  21  incorporates an electrode  22  spaced properly next to the launch tube end  17 A 1  to create a spark gap  22   1 . A spark is initiated from a spark generator  23  between the electrode  22  and launch tube end  17 A 1 . Spark generator  23  is electrically connected to the launch system unit  27  with the ground wire  23 A connected to electrode  22  and to the model rocket unit  200  with the positive wire  23 B connected to a conductive stabilizer fin  14  with alligator clip  23 C. In this configuration the entire model rocket unit  200  acts as a conductive coupling device and the entire launch tube  17  acts as a conductive coupling device and integral end flange  17 A is the spark element device. 
       FIG. 11A-11C  are launch system units  24  of different configurations and arrangements showing a mechanical loader  35  integral to mixing container  21 . Whereas, mechanical loader  35  includes a filling chamber  39  with lid  39 A to store carbide media  38  within, a spring loaded plunger  36  with handle  36 A. When spring loaded plunger  36  is activated by pull back on handle  36 A, a small amount of carbide media  38  is allowed to fall in front of plunger tip  36 B. When handle  36 A is released, the spring plunger  36  retracts and plunger tip  36 B pushes the carbide media  38  into the mixing container  21 . Carbide media  38  then falls into and mixes with the water  37  at the bottom of mixing container  21  to form a gas. Handle  36 A can be made in the configuration of a lever, knob or ring as shown in  FIG. 11A-11C  respectively. 
       FIG. 11D  is a launch system unit  24  showing an alternate design mechanical loader  35 A. The mechanical loader  35 A further including a spout chamber  35 B and attached retractable spring  36 A as shown in better detail at  FIG. 11D   1 . When spout chamber  35 B is held in the open position, carbide media is then poured to fill the spout chamber  35 B. When spout chamber  35 B is released the retractable spring  36 A pulls back spout chamber  35 B dumping the carbide media into mixing container  21 . Carbide media falls into and mixes with water  37  at the bottom of mixing container  21  to form a gas. It will be appreciated by those skilled in the art that the mechanical loader can be constructed of any appropriate design that attaches too or is integral too the mixing container and can be adapted to mount as a top loader or side loader typically. 
       FIG. 12  is a multiple launch system  80  in accordance with the fifth embodiment of the present invention including a mixing container  21 , multiple launch tube assembly  300 , closure cap  20  and electrode  22 . The multiple launch tube assembly  300  further comprises of two individual launch tubes  17   2  and  17   3  integrally mounted to conductive end flange  17 B 1 . Whereas, multiple launch tube assembly  300  is mounted with conductive end flange  17 B 1  to top of mixing container  21  and encapsulated by closure cap  20 . An electrode  22  spaced properly under conductive end flange  17 B 1  creates a spark to ignite the combustible gas. Each launch tube  17   2  and  17   3  can receive a model rocket unit and upon ignition of the combustion gas the rapidly expanding gases will simultaneously launch the multiple rocket units into the air. One skilled in the art will appreciate that multiple launch system  80  can be adapted and designed to launch two or more model rockets simultaneously from a single mixing container with any of the model rocket and launch system embodiments in accordance with the present invention. 
       FIG. 13  is a multiple launch system  81  in accordance with the sixth embodiment of the present invention including a minimum of at least two mixing containers  21 , two launch tubes  17 , with the first launch tube having an integral end flange  17 A, and with the second launch tube having an integral conductive end flange  17 B. Whereas first launch tube  17  is mounted with integral end flange  17 A to top of one mixing container  21  and encapsulated by closure cap  21  and the second launch tube  17  is mounted with integral conductive end flange  17 B to top of a second mixing container  21  and encapsulated by closure cap  21 . Whereas, two or more mixing containers  21  can be joined together with a connecting pipe  81 A into reciprocal bosses  80 A to form a gang or chain of multiple launch tubes  17  and mixing containers  21 . Each additional launch tube can receive a model rocket unit and each mixing container can receive carbide and water mixture. Now, an electrode  22  is included in the second mixing container  21  and is spaced directly under conductive end flange  17 B 1 . A spark from the single mixing container  21  will ignite the combustion gases and in turn set off and/or ignite the joining mixing container(s) and simultaneously launch multiple rockets into the air. One skilled in the art will appreciate that multiple launch system  81  can be adapted and designed to launch multiple model rockets simultaneously from two or more mixing containers with any of the model rocket and launch system embodiments in accordance with the present invention. 
       FIG. 14  shows an alternate multiple launch system  82  in accordance with the sixth embodiment of the present invention whereas, two or more mixing containers  21  can be joined together with a connecting shut-off valve  82 A into reciprocal bosses  80 A to form a gang or chain of multiple launch tubes  17  and mixing containers  21 . Additionally all launch tubes  17  include an integral conductive end flange  17 B 1  and all mixing containers include an electrode  22 . Now, when shut-off valve  82 A is in the open position the adjoining model rockets can be launched simultaneously. When the shut-off valve  82 A is in the closed position the adjoining rockets can be ignited independently. The shut-off valve  82 A allows the user to choose various combinations of the ignition sequence and method to launch model rockets. 
     One skilled in the art will appreciate that the alternate multiple launch system  82  can be adapted and designed to launch multiple model rockets simultaneously or individually from two or more mixing containers with any of the model rocket and launch system embodiments in accordance with the present invention. 
     The foregoing description of the preferred embodiments of the present invention has been presented for the purpose of illustration in accordance with the provisions of the Patent Statutes. It is not intended to be exhaustive or to limit the invention to the precise forms disclosed. Obvious modifications or variations are possible in light of the above teachings. The embodiments disclosed hereinabove were chosen in order to best illustrate the principles of the present invention and its practical application to thereby enable those of ordinary skill in the art to best utilize the invention in various embodiments and with various modifications as are suited to the particular use contemplated, as long as the principles described herein are followed. Thus, changes can be made in the above-described invention without departing from the intent and scope thereof. It is also intended that the scope of the present invention be defined by the claims appended thereto.