Abstract:
A water bottle rocket system for launching single rockets, multistage rockets, multiengine rockets or multistage multiengine rockets. Rocket bodies are comprised of ordinary plastic beverage bottles. The propellant used is preferably water and compressed air. The system offers adjustable launch supports to vary the launch angle for both single engine or multiple engine rockets. A charging manifold is provided for charging with liquid or gas propellant. Multiengine rockets are simultaneously charged with propellant through launch base internal channels.

Description:
BACKGROUND INFORMATION 
   1. Field of the Invention 
   The present invention generally relates to the field of rocket launchers and more particularly to multi-stage rocket launchers and more particularly to parallel or ganged multi-stage rocket launchers. 
   2. Description of Prior Art 
   Rocket launchers are popular with hobby enthusiasts and are used as educational tools to engage students in discovering the laws of physics while solving practical engineering problems. The dramatic release of stored energy during a launch enthralls students. This will peak student interest and lead students to questions concerning physical properties such as acceleration, inertia, friction, aerodynamic drag, and flight distance. Students gain experience in engineering by designing and testing their own nose cones, recovery systems or stabilizing fins. 
   Budgetary restraints require school systems to purchase inexpensive educational systems. In spite of some restraints the apparatus must be safe to use and rugged enough to withstand years of laboratory and field use. Several bottle rocket launchers are known. Kaye (U.S. Pat. No. 2,927,398; 1960) discloses a multi-stage bottle rocket launcher. There are several disadvantages of the Kay system: It lacks versatility and economy of design by not allowing use with a conventional soda bottle. The geometry of the design is complex making it expensive to manufacture. There is no mechanism to prevent pressure leaks from the second-stage into the first stage prior to its separation from the first stage. The base is a combination pressure pump as well as a lock and release mechanism. The Kaye design does not allow use of pressure pumps, such as the ordinary bicycle type, which are widely available. A safety issue exists due to the close proximity of the pressure pump and pressurized rocket body. 
   Jones (U.S. Pat. No. 6,315,629; 2001) discloses a single stage rocket launcher. There are several disadvantages of the Jones launcher. The release mechanism is not suitable for multi-stage applications. The release mechanism utilizes pivotable gripping levers that require assembly thereby increasing costs. Pressurization and water filling is not provided by the same fueling line. The pressure gauge is located at the base of the launcher therefore reading the gauge requires being in close proximity of the pressurized rocket. The safety pin and the release mechanism are attached to a single pull line. The base is not adjustable for uneven terrain. The base can not be adjusted to vary the launch angle. 
   Prior art discloses no launcher that is capable of launching rockets with stages greater than two. No launcher is capable of simultaneously launching rockets in parallel either singly or ganged. No launcher is capable of launching multistage-ganged rockets. There is no launcher capable of adjusting the lift off angle or leveling the launcher for uneven terrain. Furthermore, no launcher supplies a charging system that utilizes a single line for both liquid and gas charging. Nor do the launchers provide a pressure gauge a safe distance from the pressurized rocket. The disclosed launchers are structurally more complicated and thus increases the cost of manufacture. 
   What is needed is a launcher that is inexpensive, rugged, modular and safe to operate. What is further needed is a launcher that can adjust to the variability of launch conditions. What is still yet further needed is a launcher capable of launching single stage rockets or simultaneously launching multiple, single stage rockets or launching multiple, multistage rockets as well as ganged rockets or ganged multistage rockets. 
   SUMMARY OF THE INVENTION 
   Accordingly it is the primary object of the invention to provide a bottle rocket launching system that is safe to operate, modular in design, easy to assemble and affordable. A further object of the invention is to provide a launcher capable of launching single stage rockets or multistage rockets. A still further object is to provide a launcher able to simultaneously launch several single-stage or multi-stage rockets as well as launch a ganged single stage or a ganged multi-stage rocket as a single unit. An even further object is to provide a charging station that safely charges all first-stage and subsequent stage rockets. 
   In accordance with the teachings herein, the present invention provides a bottle rocket launching system with a plurality of pivotable supports. Said pivotable supports are capable of adjusting for uneven terrain or changing the launch angle. The bottle rocket launching system provides a modular, capture and release mechanism that is utilized in single rocket launches, all stages of multi-stage launches, and in ganged rocket launches. Said bottle rocket launching system has a charging station used to charge bottles of the ordinary soda bottle type or any other vessel of similar construction, with fluids such as water and compressed gas. Said charging station is located a safe distance from charged rocket and charges through a single line. Said charging station is equipped with a pressure reading device. 
   In greater detail, the support structure has a support hub that has a plurality of pivotable supports circumferrentialy placed. Said pivotable supports are attached to support hub with ordinary fasteners. The pivotable supports are adjusted for uneven terrain or are set to change the launch angle and are secured in position by said ordinary fasteners. 
   The capture and release mechanism, in the preferred embodiment, is comprised of a capture and release core with a plurality of ordinary seal rings. Said seal rings prevent fluid leakage from the launch vessel prior to launch. Said capture and release mechanism has a central bore that allows passage of charging fluids into rocket vessel. Said capture and release core supports flexible retainers that are circumferentially placed around said capture and release core. 
   The capture and release mechanism is secured to the support structure by a capture and release fastener. Said capture and release fastener is inserted into the lower end of the release core. Charging fluid is prevented from escaping said capture and release fastener and support structure contact area by ordinary seal rings. The capture and release fastener has a central bore that allows passage of charging fluid into said capture and release core. Said capture and release fastener has internal means to prevent charging fluid from flowing back from the rocket vessel. 
   Said flexible retainers provide a lock means to secure the rocket vessel to said support structure when rocket vessel is pressurized with compressed gas. The rocket vessel can be an ordinary soda bottle or any vessel with a flange capable of communication with said flexible retainers. A capture and release cup is slid into position that is furthest away from support structure. When in this position the flexible retainers will rest inside said capture and release cup. The inner side walls of the capture and release cup prevent radial movement of the flexible retainers thereby locking the ends of the flexible retainers around the flange located on the neck of the rocket vessel. In this lock position, the rocket vessel is prevented from launching when the rocket vessel is pressurized with compressed gas. 
   A launch-actuating device is provided to remotely launch the rocket vessel from a safe distance. Said launch actuating device may be any device that causes movement of the capture and release cup downward towards the support structure. Said launch-actuating device may be a simple tether, such as a string, or a more complicated mechanism such as an electrical or electronic device may also be used. 
   A safety control clip is inserted to insure that the capture and release cup is maintained in this lock position. In the preferred embodiment the safety control dip fits partially around the release core between the capture and release cup and the support structure or the previous stage rocket vessel and thereby prevents downward movement of the capture and release cup. Said safety control dip is controlled remotely by any safety release device that would allow removal of said safety control clip. The simplest said safety release device would be a tether such as a string or a more complicated said safety release device such as an electrical or electronic device may also be used. Said safety release device can be independent of said launch actuating device. This embodiment increases safety during launch operations by placing launch approval, removal of said safety control clip, and launch initiate, by downward motion of said capture and release cup, under separate, independent control. The aforesaid description is complete for a single stage rocket. 
   If desired, a second-stage may be added. Said second-stage is added to the first-stage by providing a mounting hole in the end of said first-stage rocket vessel that is opposite to the thrust orifice. The modular design of said capture and release mechanism allows said capture and release mechanism to be mounted in said mounting hole. Said second-stage capture and release mechanism is mounted in the same manner described for the single stage rocket. An additional safety control clip is used to prevent premature release of the second-stage rocket. An additional safety release device is needed to remove said additional safety control clip. For reasons to be explained below there is no launch-actuating device required for said second-stage operation. 
   Subsequent stages may also be added. To add three or more stages, mounting holes are provided in the rocket vessel end, opposite to the thrust orifice end, of every stage except the last stage. Identical capture and release mechanisms are mounted in said mounting hole as described above. The safety control clip is identical to previous stages with the following exception. A stage separation delay device is incorporated into said safety control clip. Said stage separation delay device replaces said safety release device. Said stage separation delay device would be a simple tether that is attached to said third-stage safety control clip and to some point on the first stage rocket vessel. If subsequent stages are incorporated an additional separation delay device is needed. For example, a fourth-stage would require a stage separation delay device to be connected to the fourth-stage safety control clip with the other end of the stage separation device connected to the second-stage rocket. In this embodiment subsequent stage safety control clips prevents movement of the capture and release cup, of said subsequent stages, until the previous stage separation has occurred. More elaborate methods for stage separation delay devices such as an electrical or electronic device may also be used. Stage separation is discussed in greater detail below. 
   A charging station is provided to fill the said first-stage rocket vessel with liquid propellant and all stages with pressurized gas. Said charging station has two inlets and a single outlet. One inlet provides a connection to a liquid propellant source, usually water or any non-reactive liquid, and the other inlet provides a connection to a compressed gas source. Said compressed gas may be air or any other inert gas. Said charging station single outlet is connected to the central bore of said first-stage capture and release fastener. Said charging station has internal back flow prevention devices to ensure that the liquid propellant does not enter the compressed gas source and the compressed gas does not enter the liquid propellant source. A pressure gauge is mounted on said charging station to allow reading of the rocket vessel pressure at a safe distance from the pressurized rocket vessel. 
   Operation of a three-stage rocket launch is as follows. Mount first-stage rocket vessel by placing bottle rocket neck orifice over capture and release core until flexible retainers are in communication with bottle neck flange. The capture and release cup is then slid up to the lock position. The safety control clip is then place around capture and release core bottom. The safety release device is attached the safety control clip and in the case of a simple tether is lead to a position a safe distance away from the multi-stage water rocket system. 
   The second-stage is mounted by first partially filling the second-stage rocket vessel with liquid propellant. The second-stage rocket vessel outlet orifice is slid around the second stage capture and release core, mounted on first-stage rocket vessel, opposite the thrust orifice end, until flexible retainers are in communication with bottle neck flange on second-stage rocket vessel. The capture and release cup is then moved to the lock position. The safety control clip is then placed around the capture and release core between the second stage capture and release cup and the first stage rocket vessel. The safety release device is attached to the second stage safety control clip and is led to a safe distance away from the multi-stage water rocket system. 
   The third-stage rocket vessel is mounted on the second-stage rocket vessel in the same manner as the second-stage rocket vessel is mounted on the first-stage rocket vessel. The stage separation delay device, in this embodiment, is a simple tether with one end connected to the third stage safety control clip and the other end of said stage separation delay device fastened to the first-stage rocket assembly. The connection may be made to the first-stage rocket vessel or the capture and release core mounted on the first-stage rocket vessel. 
   The first-stage rocket vessel is charged with liquid propellant using the said charging station. Liquid propellant passes from the liquid propellant source into the said charging station inlet through the said charging station internal back flow prevention device. Liquid propellant then exits the said charging station and enters the said first-stage capture and release fastener central bore via the said charge line. The charge line connects charging station to the multi-stage water rocket system. Liquid propellant enters the first-stage rocket vessel via the capture and release core central bore. Liquid propellant is prevented from flowing back into the charge line by the back flow prevention means located in the capture and release fastener. 
   All stages are charged with compressed gas using the charging station. Compressed gas passes from the compressed gas source into the charging station compressed gas inlet. Compressed gas passes through the charging station second back flow prevention device. Compressed gas exits the charging station and enters the charge line. The charge line is connected to the first-stage capture and release fastener central bore. Compressed gas passes through the capture and release fastener back flow prevention device and enters the capture and release core central bore. The compressed gas exits the capture and release central bore and flows through the liquid propellant already contained within the first stage rocket vessel. The compressed gas accumulates in the space above the liquid propellant in the first-stage rocket vessel. The compressed gas enters the capture and release fastener central bore, mounted on the first-stage rocket vessel, and charges the second-stage rocket vessel with compressed gas in the same manner described above. Compressed gas charges the third-stage rocket vessel in the same manner as the second-stage rocket vessel. All stages are now charged with compressed gas. The multi-stage rocket system is ready for launch. It should be noted that the above explanation of operation is the same for any amount of stages incorporated. 
   The multi-stage rocket system is safely launched using the following procedure. Safety control clips are removed from the first-stage and the second-stage, capture and release mechanisms. The removal is initiated by actuating the respective safety release device. The multi-stage rocket system is now launched by actuating the first-stage launch-actuating device. The launch actuating device causes the first-stage capture and release cup to move to the launch position. The flexible retainers are no longer restrained from radial movement. The force caused by the pressurized gas in the first-stage rocket vessel causes all three stages to move upward. This upward movement will cause the first-stage rocket vessel  101  to separate from the capture and release mechanism  110  mounted on the support structure  104 . Upon separation, liquid propellant is forced from the first-stage rocket vessel orifice by the compressed gas in the first-stage rocket vessel. All three stages well accelerate upward. 
   Upon initial acceleration the second-stage capture and release cup will move downward to its&#39; release position. The second-stage is now free to separate from the first-stage but is prevented from doing so because the force of acceleration is greater than the force caused by the compressed gas in the second stage. At some point in the flight, the force caused by the compressed gas in the second-stage rocket vessel will be greater than the force of acceleration tending to keep the stages together. At this point the second-stage will separate from the first-stage and accelerate away from the first-stage carrying the third-stage with it. 
   Upon the initial separation of the second-stage from the first stage, the third-stage safety control clip is automatically removed. This is accomplished by the stage separation delay device connected between the first-stage and the safety control clip on the third stage. As the second and third-stage accelerate, the capture and release cup of the third-stage will slide down to its release position. The third-stage will separate and accelerate from the second-stage when forces are balanced in the same manner described above for first and second-stage separation. Additional stages operate in the same manner as the third stage. 
   The modular design of the capture and release mechanism allows operation in a parallel launch configuration. To accomplish this, any number of capture and release mechanisms can be mounted so rocket vessels can be loaded onto the capture and release cores without interference. The capture and release cups are connected with a coupling plate so that all capture and release mechanisms can be moved as a unit. All capture and release cups are held in the capture position by placing one safety control dip under the coupling plate. A safety release mechanism is attached to the safety control clip. A launch-actuating device is attached to the coupling plate. Placement of launch and release mechanisms with an associated coupling plate allows for parallel launches of multiple single stage rocket vessels, multiple multi-stage rockets or multiple rocket vessels ganged as a single rocket. Ganged rockets may also be multi-stage. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The present invention is described in detail with the accompanying drawings. Identical numbers are used to reference components that are functionally equivalent. In should be noted that the drawings are not drawn to scale. 
       FIG. 1  is an isometric view of a multi-stage rocket system with three-stages. 
       FIG. 2  is an exploded view of a single stage rocket launch system. 
       FIG. 3A  is a partial cross sectional view of the capture and release mechanism in the lock position. 
       FIG. 3B  is a partial cross sectional view of the capture and release mechanism just as the rocket is released. 
       FIG. 4  is an exploded view of a second-stage or subsequent stage capture and release mechanism. 
       FIG. 5  is a cross sectional view of the capture and release core and a capture and release fastener. 
       FIG. 6  is a cross sectional view of the charging station. 
       FIG. 7  is an isometric view of a multi-stage rocket system with three stages immediately after launch, just as the rockets are accelerating upward. 
       FIG. 8  is top view of a coupling plate use to gang seven or three rocket configurations. 
       FIG. 9  is a cross sectional view of a capture and release fastener used in parallel launch base showing lateral port for receiving charging fluids. 
       FIG. 10  is a cross sectional view of a capture and release fastener used in the center position of a parallel launch showing charging line and lateral port for supplying peripheral rockets. 
       FIG. 11  cross sectional top view of a parallel launch support structure showing internal charging channels. 
       FIG. 12  is an isometric view of a parallel launch system configured for a seven-rocket vessel launch. 
       FIG. 13  is an isometric view of a parallel launch system with rocket vessels mounted in the locked position. 
   

   DETAILED DESCRIPTION OF THE INVENTION 
   Referring to  FIG. 1 , a multi-stage water bottle rocket system  100  is shown in a three-stage configuration. Although this detailed description explains a three-stage configuration, it is understood that additional stages are possible and that the multi-stage water bottle rocket system  100  is not limited to three stages. 
   The multi-stage water bottle rocket system  100  has a support structure  104 . The support structure  104  has a plurality of circumferentially mounted pivotable supports  105 . Pivotable supports  105  are attached to support hub  107  using ordinary fasteners  106 . The pivotable supports  105  are adjusted using ordinary fasteners  106 . The pivotable supports  105  are used to level the multi-stage water bottle rocket system  100  for uneven terrain or to vary the launch angle. The support hub  107  also provides an attachment point for capture and release mechanism  110 . 
   The capture and release mechanism  110  is used in every stage of the multi-stage water bottle rocket system  100 . The capture and release mechanism  110  is discussed in greater detail below. 
   First-stage rocket vessel  101 , second-stage rocket vessel  102  and third-stage rocket vessel  103  may be any vessel that has the ability of withstanding pressurization and that is capable of communication with capture and release mechanism  110 . Example of said vessel is an ordinary soda bottle or an ordinary water cooler bottle of any size or shape but said vessel is in no way limited to these types of vessels. The said rocket vessels are discussed in greater detail below. 
   Safety release device  113  is provided so that the safety mechanism incorporated in the capture and release mechanism  110 , discussed below, can be actuated from a safe distance from the launch site. The safety release device  113  may be a simple tether; an electrical or electronic device or any mechanism capable of communication with the safety mechanism incorporated in capture and release mechanism  110 . 
   The stage separation delay device  114  functions to delay separation of any stage, greater than the second stage, incorporated in the multi-stage water rocket system  100 . The stage separation delay device  114  may be a simple tether, an electrical or electronic device or any mechanism capable of communication with the capture and release mechanism  110  that provides the proper timing for separation. The separation delay device is discussed in more detail below. 
   The launch-actuating device  112  functions to initiate a launch by communicating with capture and release mechanism  110 . The launch actuating device  112  ensures the launch is initiated a safe distance from the pressurized vessel. The launch-actuating device  112  may be a simple tether, an electrical or electronic device. The launch-actuating device  112  may be any mechanism capable of launch communication with the capture and release mechanism  110 . 
   Charging station  108  provides a means for remotely charging the first-stage rocket vessel  101  with liquid propellant. The charging station  108  provides a means for charging the first-stage rocket vessel  101 , the second-stage rocket vessel  102 , the third-stage rocket vessel  103 , as well as any additional stage rocket vessel, with compressed gas. Said liquid propellant may be any liquid. The preferred liquid is generally water or any liquid that does not pose a hazard to operating personnel or observing bystanders. Said compressed gas may be any compressed gas, generally air or any compressed gas that does not pose a hazard to operating personnel or observing bystanders. Charging station  108  has two inlets. Charging station  108  liquid inlet  115  is connected to any suitable liquid source. Charging station  108  compressed gas inlet  116  is connected to any suitable compressed gas source. Charge line  109  is the fluid outlet for charging station  108 . Charge line  109  is connected to capture and release mechanism  110  via the capture and release fastener  201 , shown in  FIG. 2 . Charge line  109  provides a means for liquid propellant or compressed gas to be fed into the multi-stage water bottle rocket system  100 , a safe distance from the pressurized vessel. Charging station  108  is fitted with an ordinary pressure gauge  111 . Incorporating the ordinary pressure gauge  111  in the charging station  108  allows reading of the pressure supplied to multi-stage water bottle rocket system  100  a safe distance from the pressurized vessel. Charging station  108  has internal back flow prevention devices. The back flow prevention devices are discussed in greater detail below. 
   Referring to  FIG. 2 , the capture and release mechanism  110  has a capture and release core  205 . The capture and release core  205  has a top  205 A and a bottom  205 B. The capture and release core top  205 A is fitted with a plurality of rocket vessel orifice seal rings  209 . The capture and release core top  205 A is inserted in the rocket vessel orifice  206  until first-stage rocket vessel  101  mates with the capture and release core step  210 . In this position the capture and release core seal rings  209  function to prevent liquid propellant and compressed gas from escaping the first-stage rocket vessel  101 . 
   The flexible retainer mechanism  204  has a central orifice  204 A and a plurality of circumferencially placed flexible retainers  204 C. Each flexible retainer  204 C has a curved tip  204 B. Capture and release core bottom  205 B is inserted into flexible retainer central orifice  204 A until flexible retainer mechanism  204  mates with capture and release core step  210 . When the flexible retainer mechanism  204  is in this position the curved tip  204 B grips rocket vessel flange  207 . The assembled unit is comprised of the first-stage rocket vessel  101 , the capture and release core  205  and the flexible retainer mechanism  204 . The assembly is slid, as a unit, into the capture and release cup  203  until the capture and release cup  203  inner bottom mates with flexible retainer mechanism  204 . When the capture and release cup  203  mates with the said assemble mechanism, the top of the capture and release cup  203  is flush with the top of the flexible retainer mechanism  204 . The capture and release fastener  201  is led into the ordinary seal  202  and the entire assembly is fed into bottom of support hub  107  and led into the support hub central orifice  211 . The capture and release fastener  201  is led into the support hub central orifice  211  until fastener step  201 B mates with inside bottom surface of the support hub  107 . Ordinary seal  202 A is placed around fastener top  201 A and led down until the ordinary seal  202 A mates with the top surface of support hub  107 . Ordinary seals  202  and  202 A prevent liquid propellant and compressed gas from escaping the assembly. The capture and release mechanism  110  is secured to the support structure  104  by anchoring the fastener top  201 A into the capture and release core bottom  205 B. 
   In this configuration, the capture and release cup  203  is free to move between the following limits. The capture and release cup  203  is at the upper limit of its&#39; travel when the inside bottom of the capture and release cup  203  mates with the bottom of the flexible retainer mechanism  204 . This is the capture position and the pressurized first-stage rocket vessel  101  is prevented from launching. The capture and release cup  203  is at the lower limit of its&#39; travel when the outside bottom of the capture and release cup  203  mates with the top of the support hub  107 . This is the release position and the pressurized first stage rocket vessel  101  is no longer restrained. The movement of the capture and release cup  203  is explained in greater detail below. When the capture and release cup  203  is in the capture position, the safety control clip  208  is placed around the capture and release core bottom  205 B. The safety control clip  208  when placed around the capture and release core bottom  205 B prevents movement of the capture and release cup  203  to its release position and thereby prevents release of the first-stage rocket vessel  101 . 
     FIGS. 3A and 3B  shows the capture and release mechanism  110  with the capture and release cup  203  cross-sectioned.  FIG. 3A  shows the capture and release cup  203  in the capture position. When the capture and release cup  203  is in the capture position and the first-stage rocket vessel  101  is charged with liquid propellant and compressed gas, the forces acting on the mechanism must be balanced. The pressure of the compressed gas in the first-stage rocket vessel  101  creates a force tending to separate the first-stage rocket vessel  101  from the capture and release core  205 . The first-stage rocket vessel  101  is prevented from separation because the flexible retainer tip  204 B extends above the rocket vessel flange  207  and thereby grabs the rocket vessel flange  207 . The forces acting between the flexible retainer tip  204 B and the rocket vessel flange  207  tend to force the flexible retainer tip  204 B radially outward due to the sloped surface of the flexible retainer tip  204 B. The flexible retainer tip  204 B is prevented from moving radially outward by the capture and release cup sidewall  304 . When the safety control clip  208  is removed, the capture and release cup  203  will remain in the capture position. The capture and release cup  203  remains in the capture position due to the friction between the capture and release cup side wall  304  and the plurality of circumferentially placed flexible retainers  204 C. 
     FIG. 3B  shows the first-stage rocket vessel  101  just as it is released from the capture and release mechanism  110 . If sufficient force is applied, in a direction parallel to the axis of the capture and release cup  203 , and away from the rocket vessel,  101 , the capture and release cup  203  will move towards the release position. As the capture and release cup  203  begins to move, the flexible retainer tip will begin to move radially outward as the first-stage rocket vessel  101  begins to move upward. The flexible retainers  204 C will impart a downward force on the capture and release cup bevel  305 . This downward force will cause the capture and release cup  203  to move downward with increased speed. This action allows the flexible retainers  204 C to move further radially outward. The outward movement of the flexible retainers  204 C causes an increase in the force acting downward on the capture and release cup bevel  305 . Therein the capture and release cup  203  is forced to move toward the release position at a greater speed. In other words, the design of the capture and release mechanism  110  is such that any initial downward movement of the capture and release cup  203  creates a downward force on the capture and release cup bevel  305 . This downward force on the capture and release cup bevel  305  is created by the outward splaying of the flexible retainers  204 C. The advantage is that minimal downward force on the capture and release cup  203  is required to initiate a launch. The first-stage rocket vessel  101  will no longer be constrained from launch at some point in the downward travel of the capture and release cup  203 . The capture and release cup  203  has a capture and release cup flange  302 . The capture and release cup flange functions as a stop for the coupling plate discussed later. 
   Referring to  FIG. 4  the capture and release mechanism  110  is shown as it is mounted on the first-stage rocket vessel  101 . The parts are identical to the capture and release mechanism  110  mounted on the support structure  104  with the one addition. The delay device anchor  402 . The delay device anchor  402  has an anchor attach tab  402 A. The anchor attach tab  402 A provides a means of attachment for the stage separation delay device  114  (see  FIG. 1 ). A rocket vessel hole  401  provides a means for securing the capture and release mechanism  110  to the first-stage rocket vessel  101 . 
   To assemble the capture and release mechanism  110 , used in a second-stage or subsequent stage application, place the ordinary seal  202  around fastener top  201 A until ordinary seal  202  rests against fastener step  201  B. The capture and release fastener  201  is then fed through the rocket vessel orifice  206 , of first-stage rocket vessel  101 . The fastener top  201 A is inserted through the rocket vessel hole  401  until the ordinary seal  202  mates with inside surface of first-stage rocket vessel  101 . The delay device anchor  402  is placed around the fastener top  201 A until the delay device anchor  402  mates with the top of the first-stage rocket vessel  101 . The ordinary seal  202 A is placed around the fastener top  201 A until the ordinary seal  202 A mates with the delay device anchor  402 . The remainder of the capture and release mechanism  110  is assembled in the same manner for first-stage operation described above. When assembled the second stage capture and release mechanism  110  is attached to the first-stage rocket vessel  101 . The capture and release mechanism  110 , in this second-stage application, provides a means for controlling the separation of the second-stage rocket vessel  102  from the first-stage rocket vessel  101 . The capture and release mechanism  110  used in this second-stage application also provides a means for compressed gas to flow into the second-stage rocket vessel  102  from the first-stage rocket vessel  101 . Back flow of liquid propellant or compressed gas from the second-stage rocket vessel  102  into the first-stage rocket vessel  101  is prevented by the back flow prevention mechanism inside the capture and release fastener  201 . The back flow prevention is discussed in greater detail below. It should be noted that the capture and release mechanism  110  used in a third-stage application, or any subsequent stage application, is identical in construction and assembly to the capture and release mechanism  110  used in a second-stage application. 
     FIG. 5  shows a cross section of the capture and release core  205  and the capture and release fastener  201 . The capture and release fastener  201  has a central bore  505 , a back flow stop  501 , a back flow seal  502  and a back flow stop retainer  503 . The back flow stop  501  is free to travel between the back flow seal  502  and the back flow stop retainer  503 . The central bore  505  provides a path for fluid passage between the charge line  109 , when used in first-stage application, or a path for compressed gas passage when used in any subsequent stage application. When fluid enters the central bore  505  and flows towards the release core central bore  504 , the black flow stop  501  is moved towards back flow stop retainer  503 . The back flow stop retainer  503  prevents the back flow stop  501  from leaving the capture and release fastener  201 . When fluid attempts to flow from the release core central bore  504  back to the release fastener central bore  505  the back flow stop  501  is forced down and mates with the back flow seal  502 . This action prevents fluid flow from the release core central bore  504  back to the release fastener central bore  505 . Therefore, any liquid propellant or compressed gas that is admitted, therein, to any stage rocket vessel,  101 ,  102 ,  103  or subsequent stage, will remain in the rocket vessel. The liquid propellant or compressed gas will remain in the rocket vessel as long as the rocket vessel is in communication with the capture and release mechanism  110 . 
     FIG. 6  shows a cross sectional view of the charging station  108 . The charging station  108  has two charging station hose adapters  601 , two charging station back flow housings  602  and one charging station central core  607 . The charging station hose adapter  601  has a connection orifice  608 . The connection orifice  608  provides a connection point for the charging station liquid inlet  115  and the charging station compressed gas inlet  116 . The charging station hose adapters  601  are attached to charging station back flow housing  602  by an appropriate mechanical means such as threads or adhesives that will provide a fluid seal. The charging station back flow housing  602  contains a charging station back flow seal  604 , a charging station back flow stop  603  and a charging station back flow retainer  605 . The charging station back flow stop  603  rests against the charging station back flow retainer  605  when fluid is entering the connection orifice  608 . The charging station back flow retainer  605  prevents the charging station back flow stop  603  from leaving the charging station back flow housing  602 . When fluid is flowing into one charging station back flow housing  602 , from the associated charging station hose adapter  601 , the other charging station back flow stop  603  is forced against the charging station back flow seal  604 . With the charging station back flow stop  603  against the charging station back flow seal  604  no fluid is allowed to flow from that associated charging station back flow housing  602  into the associated charging station hose adapter  601 . Thus fluid flowing into charging station compressed gas inlet  116  is prevented from flowing out of charging station liquid inlet  115 . In addition, when liquid is flowing into charging station liquid inlet  115 , the liquid is prevented from flowing out of charging station compressed gas inlet  116 . It follows that any fluid that enters charging station  108  must exit charging station  108  via charge line  109 . The charging station  108  has an ordinary pressure gauge  111  mounted on the charging station central core  607 . Placement of the ordinary pressure gauge  111  on charging station central core  607  provides a remote means of pressure measurement that is a safe distance away from the pressurized rocket vessel. 
   Referring in general to  FIG. 1 ,  FIG. 2 ,  FIG. 4 ,  FIG. 5 ,  FIG. 6  and  FIG. 7  the operation of the multi-stage rocket launcher  100  is as follows. The pivotable supports  105  on the support structure  104  are adjusted for the desired launch angle. As describe above the capture and release mechanism  110  is attached to the support structure  104 . In addition, as described above the capture and release mechanisms  110  are attached to the first-stage rocket vessel  101  and the second-stage rocket vessel  102 . 
   Insert first-stage rocket vessel orifice  206  over the capture and release core  205  that is mounted on support structure  104  until first-stage rocket vessel flange  207  is gripped by the flexible retainer tip  204 B. Slide the capture and release cup  203  to the capture position. Place the safety control clip  208  around the capture and release core bottom  205 B. The capture and release mechanism  110  that is attached to the support structure  104  is now set in the pre-launch condition. 
   Fill the second-stage rocket vessel  102  partially full with liquid propellant and insert the second-stage rocket vessel  102  over the capture and release core  205  that is mounted on top of the first-stage rocket vessel  101 . Capture the second-stage rocket vessel  102  in the same manner described in the previous paragraph. The second-stage rocket vessel  102  is now in the pre-launch condition. 
   Fill the third-stage rocket vessel  103  partially full with liquid propellant and insert the third-stage rocket vessel  103  over the capture and release core  205  that is mounted on top of the second-stage rocket vessel  102 . The third-stage rocket vessel  103  is captured in the same manner described above. The stage separation delay device  114  is a simple tether in this embodiment. The stage separation delay device  114  is attached to the safety control clip  208  that is clipped to the capture and release core  205  that is mounted on top of the second-stage rocket vessel  102 . The other end of the stage separation delay device  114  is attached to the delay device anchor  402 , anchor attach point  402 A. All three stages of the multi-stage water rocket system are now ready for charging. It should be noted that the above procedure is applicable for single-stage launches as well as two-stage launches, or more stage launches. 
   The first-stage rocket vessel  101  is charged with liquid propellant by allowing liquid propellant to enter the charging station liquid inlet  115 . Liquid propellant will flow into the charging station  108 , through charging station internal back flow prevention mechanism internal to the charging station back flow housing  602  and out of charging station  108  via the charge line  109 . Liquid propellant flows from the charge line  109  into the release fastener central bore  505 . Liquid propellant flows through release fastener central bore  505  and into the release core central bore  504 . Liquid propellant exits the release core central bore  504  and enters the first-stage rocket vessel  101 . Liquid propellant is allowed to flow until first-stage rocket vessel  101  is partially full of liquid propellant. 
   First-stage rocket vessel  101 , the second-stage rocket vessel  102 , and third-stage rocket vessel  103  are simultaneously charged with compressed gas by first allowing compressed gas to flow into the charging station  108  via the charging station compressed gas inlet  116 . Compressed gas flows through the charging station  108  internal back flow prevention device that is internal to the charging station back flow housing  602  and exits the charging station  108  via charge line  109 . Compressed gas flows into the release fastener central bore  505 , of the capture and release fastener  201 , that is mounted on the support structure  104 . The compressed gas then flows into the release core central bore  504 . Compressed gas then enters the first-stage rocket vessel  101 . 
   From the first-stage rocket vessel  101  compressed gas passes through the capture and release mechanism  110  mounted on top of the first-stage rocket vessel  101  in the same manner described in the previous paragraph. The compressed gas then enters the second-stage rocket vessel  102 . The compressed gas passes through the capture and release mechanism  110  mounted on the top of the second-stage rocket vessel  102  in the same manner just described. The compress gas then enters the third-stage rocket vessel  103 . In this manner, all rocket vessels on all stages are simultaneously charged with compressed gas to the same pressurization level. The multi-stage water rocket system  100  is now ready for launch. 
   Referring to  FIG. 7 , the operator must first use the safety release device  113  to remove the safety control clip  208 , that is associated with the capture and release mechanism  110  mounted on the support structure  104 . The other safety release device  113  is used to remove the safety control clip  208  that is associated with the capture and release mechanism  110  mounted on top of the first-stage rocket vessel  101 . 
   Actuating the launch actuating device  112  causes the capture and release cup  203 , associated with the capture and release mechanism  110  mounted on the support structure  104 , to move to the release position. This will allow the first-stage rocket vessel,  101 , the second-stage rocket vessel  102 , and the third-stage rocket vessel  103  to accelerate upward as a single unit. 
   Upon the initial acceleration the capture and release cup  203 , associated with the capture and release mechanism  110  mounted on the top of the first-stage rocket vessel, will move to the release position. The second-stage rocket vessel  102  is prevented from separation from the first-stage rocket vessel  101  because the force of acceleration, which acts to keep the stages together, is greater than the force tending to separate the two stages. The force tending to separate the two stages is caused by the compressed gas in the second-stage rocket vessel  102 . At some point in the flight the force caused by the compressed gas in the second-stage rocket vessel  102  will exceed the force of acceleration. When the force of the compressed gas, in the second stage rocket vessel  102 , exceeds the force of acceleration the second-stage rocket vessel  102  will separate from the first-stage rocket vessel  101 . The second-stage rocket vessel  102  will accelerate upward carrying the third-stage rocket vessel  103  and the associated capture and release mechanism  110  with it. 
   Upon this second-stage separation, the stage separation delay device  114  will remove the safety control clip  208 , associated with the capture and release mechanism  110  mounted on top of the second-stage rocket  102 . This action occurs at the very start of second-stage rocket vessel  102  separation. The capture and release cup  203 , associated with the capture and release mechanism  110 , mounted on top of the second-stage rocket vessel  102 , is no longer restrained in the capture position. The acceleration forces exerted will cause this capture and release cup  203  to move to the release position. The third-stage rocket vessel  103  will separate in the same manner describe above for the second-stage rocket vessel  102 . 
   It should be noted that this invention would operate with one, two, three or more stage rockets. The invention is not limited to the description above. 
   The modularity of the capture and release mechanism  110  allows the capture and release mechanism  110  to be used in a parallel launch configuration. The following explanation describes one embodiment of the capture and release mechanism  110  used in a parallel launch configuration. It should be noted that the capture and release mechanism  110  could be used in a parallel launch configuration of any number of rocket vessel configurations. Parallel configurations using first-stage rocket vessels  101 , second-stage rocket vessels  102  and third-stage rocket vessels  103  as well as additional stages are possible. 
     FIG. 8  is a top view of a coupling plate  801 . The coupling plate  801  has a launch actuating device orifice  802 , coupling plate peripheral orifices  803 , a coupling plate central orifice  804 , and coupling plate inner orifices  805 . The coupling plate  801  is used to connect a number of capture and release mechanisms  110 , capture and release cups  203  to each other. When several capture and release cups  203  are connected with a coupling plate  801  only one safety control clip  208  is required to control the launch. Only one launch-actuating device  112  is required to initiate a launch. In order to gang seven, first-stage rocket vessels  101  together the six coupling plate peripheral orifices  803  and the coupling plate central orifice  804  are used to connect the seven capture and release mechanisms  110 . To create a parallel launch using three, first-stage rocket vessels  101 , the three coupling plate inner orifices  805  are used to connect the three capture and release mechanisms  110 . Operation of a parallel launch is discussed in greater detail below. 
     FIG. 9  is a cross sectional view of a capture and release peripheral fastener  901 . The capture and release peripheral fastener  901  has a central bore  902  and a radial bore  903 . Charging fluid enters the capture and release peripheral fastener  901  through the radial bore  903  and charging fluid exits the peripheral fastener  901  via the central bore  902 . The capture and release peripheral fastener  901  is used to attach the capture and release mechanism  110  for a parallel launch configuration described in greater detail below. 
     FIG. 10  is a cross sectional view of a capture and release central fastener  1001 . The capture and release central fastener  1001  has a bottom bore  1002 , a top bore  1003 , and a radial bore  1004 . The charging line  109  is attached to the bottom bore  1002 . Charging fluid enters the capture and release central fastener  1001 , bottom bore  1002 , from the charging line  109 . Fluid passes from the bottom bore  1002  and exits the capture and release central fastener  1001  through the top bore  1003 . Fluid also exits through the radial bore  1004 . Incorporation of the capture and release central fastener  1001  into a parallel launch system is discussed below. 
     FIG. 11  shows a cross sectional top view of the parallel launch support structure  1103 . The parallel launch support structure  1103  has a plurality of circumferentially placed parallel launch support structure struts  1101 . The parallel launch support structure  1103  has a circumferential inner channel  1104 , circumferential connecting channels  1105 , and radial inner channels  1108 . The parallel launch support structure  1103  has a central orifice  1107  and a plurality of circumferentially placed peripheral orifices  1109 . The parallel launch support structure  1103  also has an actuating orifice  1110 , inner orifices  1106 , and a plurality of circumferentially placed strut orifices  1111 . 
   Now referring to  FIG. 9 ,  FIG. 10 , and  FIG. 11 , in the embodiment shown, the parallel launch support structure  1103  may be used in a seven, first-stage rocket vessel  101  configuration. Six capture and release mechanisms  110  are attached to the parallel launch support structure  1103  in the support structures peripheral orifices  1109  with capture and release peripheral fasteners  901 . The method of attachment is the same as described above for a single capture and release mechanism  110  attachment. The remaining capture and release mechanism  110  is attached to the support structure central orifice  1107  using capture and release central fastener  1001 . The method of attachment is the same described above for a single capture and release mechanism  110  attachment. 
   A plurality of pivotable supports  105  are attached to the parallel launch support structure  1103 , with ordinary fasteners  106 , by placing pivotable supports  105  between the struts  1101 . Pivotable supports  105  are secured by placing ordinary fasteners  106  through the strut orifice  1111  and tightening ordinary fasteners  106 . Pivotable supports  105  may be adjusted to accommodate for uneven terrain or to vary the launch angle by moving pivotable supports  105  to desired position and securing with ordinary fasteners  106 . 
   The parallel launch system is completed by placing a coupling plate  801  over the capture and release mechanisms  110 , until the coupling plate  801  rests on the capture and release cup flange  302 . The final assembly is shown in  FIG. 12 . 
   Referring to  FIG. 12 , the coupling plate  801  connects all the capture and release mechanisms  110  together. All the capture and release mechanisms  110  are held in the capture position by a single safety control clip  208 . A launch is initiated by a single launch-actuating device  112 . In the embodiment shown the launch actuating device  112  is a simple tether which is passed through the support structure actuating orifice  1110  and attached to the coupling plate  801  at the launch actuating device orifice  802 . The safety control clip  208  is removed, by actuating the safety release device  113 . The coupling plate  801  and the coupled capture and release mechanisms  110  are now free to move downward as a single unit, but are held in the capture position, as described above for a single stage launch. Actuating the launch-actuating device  112  causes the coupling plate  802  to move downward. The coupling plate  802  will transmit this downward movement to all the capture and release mechanisms  110 . All capture and release mechanisms  110  will move to the release position simultaneously. Any charged first-stage rocket vessel  110  will then be free to accelerate away from the parallel launch system  1200 . A complete description of charging and launching the parallel launch system is described below. 
   Referring to  FIG. 9 ,  FIG. 10 ,  FIG. 11 ,  FIG. 12 , and  FIG. 13 . With the parallel launch system  1200  assembled as described above. The charging of the first-stage rocket vessels  101  is accomplished simultaneously through the charge line  109 . The charge line  109  is attached to the capture and release central fastener  1001 . The capture and release central fastener  1001  is attached to the center capture and release mechanism  110  via the support structure central orifice  1107 . Charging fluid enters the capture and release central fastener  1001  bottom bore  1002  from the charge line  109 . Any first-stage rocket vessel  101  in charging communication with the capture and release mechanism  110  that is mounted on the capture and release central fastener  1001  is charged with fluid via the central fastener upper bore  1003 . Charging fluid exits the capture and release central fastener  1001  through the central fastener radial bore  1004  and enters the radial inner channels  1108 . The charging fluid flows through the radial inner channels  1108  to the capture and release peripheral fasteners  901  mounted in the support structure peripheral orifices  1109 . The charging fluid leaves the radial inner channel  1108  and enters the peripheral fastener radial bore  903 . The charging fluid then passes into the peripheral fastener central bore  902  and then enters the capture and release mechanism  110  that are in charging communication with the capture and release peripheral fasteners  901 . The charging fluid then enters any first-stage rocket vessel  101  captured by the capture and release mechanisms  110 . The symmetrical design of the channels in the parallel launch support structure  1103  ensures that all rocket vessels are charge with the same amount of liquid propellant and compressed gas. 
   For a parallel launch configuration, with three first-stage rocket vessels  101 , the capture and release mechanisms  110  are mounted in the support structure inner orifices  1106 , using capture and release peripheral fasteners  901 . In this configuration, the charge line  109  is connected to lateral orifice  1112 . Charging fluid leaves the charge line  109  and enters the lateral orifice  1112 . Charging fluid leaves the lateral orifice  1112  and enters circumferential inner channel  1104 . Charging fluid flows through the circumferential inner channel  1104  and enters the circumferential connecting channels  1105 . The circumferential connecting channels  1105  feed charging fluid into the peripheral fastener radial bore  903 , of the capture and release peripheral fasteners  901 , that are mounted in the support structure inner orifices  1106 . Charging fluid leaves the capture and release mechanism peripheral fastener  901  via the peripheral fastener central bore  902 . The charging fluid then enters the capture and release mechanism  110  that is in charging communication with the said capture and release peripheral fasteners  901 . The charging fluid then enters the first-stage rocket vessel  101  in the same manner described above. 
   It should be noted that the invention is not limited to a seven ganged or three-ganged rocket vessel launch described above. The modular design of the lock and release mechanism  110  allows a multiplicity of configurations. Such configurations may be comprised but are not limited to ganged launches consisting of multiple rockets of one, two or more stages simultaneously launched or grouped as a single multi-engine rocket. Subsequent stages may be single or grouped as multi-engine rockets.