ROCKET AND LAUNCHING SYSTEM

FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

Not Applicable.

TECHNICAL FIELD

The present disclosure generally relates to a rocket launching system and rocket, and in particular, to a children's toy air-powered rocket launching system and drone landing-assist rocket.

BACKGROUND

Rocket launching systems are well known in the art. While such rocket launching systems according to the prior art provide a number of advantages, they nevertheless have certain limitations. The present invention seeks to overcome certain of these limitations and other drawbacks of the prior art, and to provide new features not heretofore available. A full discussion of the features and advantages of the present invention is deferred to the following detailed description, which proceeds with reference to the accompanying drawings.

SUMMARY

According to one embodiment, the disclosed subject technology relates to toy rocket launching system.

The disclosed technology further relates to a rocket launching system, comprising: a launch base having a pressure chamber, the pressure chamber having an inlet and an outlet; a launch tube connected to the launch base adjacent the outlet of the pressure chamber; a rocket that slidingly engages the launch tube; a carrier for supporting a pressurized gas container, the carrier moving from a first position to a second position, wherein the pressurized gas container is not in fluid communication with the pressure chamber in the first position, and wherein the pressurized gas container is in fluid communication with the pressure chamber in the second position; a carrier transfer mechanism to move the carrier from the first position to the second position; a vent pin engaging the pressurized gas container connected to the carrier when the carrier is in the second position; and, a controller having a selector that provides a signal to initiate the carrier transfer mechanism.

The disclosed technology further relates to a rocket launching system wherein the controller communicates wirelessly with the rocket launching system to initiate the carrier transfer mechanism.

The disclosed technology further relates to a rocket launching system wherein the carrier transfer mechanism is a spring loaded hammer to transition the carrier from the first position to the second position. In an alternate embodiment the carrier transfer mechanism is a motor to transition the carrier from the first position to the second position.

The disclosed technology further relates to a rocket launching system comprising a plurality of propellers connected to the rocket, each of the propellers having an individual motor. In one embodiment, the plurality of propellers are connected to a first end of the rocket, and wherein the first end of the rocket is separable from a fuselage of the rocket during a flight of the rocket. In one embodiment the controller communicates wirelessly with the rocket, and in another embodiment the controller has drone-style controls to control flight characteristics of the rocket.

The disclosed technology further relates to a rocket launching system having a vent pin engaging the pressurized gas container connected to the carrier when the carrier is in the second position. In one embodiment, the vent pin extends through a portion of the carrier.

The disclosed technology further relates to a rocket launching system having an air release member between the outlet of the pressure chamber and the launch tube. In one embodiment, the air release member is a rupturable membrane.

The disclosed technology further relates to a rocket launching system wherein the carrier moves from a first position to a second position, wherein the pressurized gas container does not contact the vent pin in the first position, wherein the pressurized gas container is not in fluid communication with the pressure chamber in the first position, wherein the pressurized gas container contacts the vent pin in the second position, and wherein the contents of the pressurized gas container are in fluid communication with the pressure chamber in the second position.

The disclosed technology further relates to a rocket launching system, comprising: a launch base having a pressure chamber, the pressure chamber having an inlet and an outlet; a launch tube connected adjacent the outlet of the pressure chamber; a rocket that slidingly engages the launch tube; a launch tower pivotally connected to the launch base, the launch tower pivoting from a first position to a second position; and, a pressure source capable of being in fluid communication with the inlet to the pressure chamber when the launch tower is in the second position, the launch tower preventing the pressure source from being in fluid communication with the inlet to the pressure chamber when the launch tower is in the first position.

It is understood that other embodiments and configurations of the subject technology will become readily apparent to those skilled in the art from the following detailed description, wherein various configurations of the subject technology are shown and described by way of illustration. As will be realized, the subject technology is capable of other and different configurations and its several details are capable of modification in various other respects, all without departing from the scope of the subject technology. Accordingly, the drawings and detailed description are to be regarded as illustrative in nature and not as restrictive.

BRIEF DESCRIPTION OF THE DRAWINGS

To understand the present disclosure, it will now be described by way of example, with reference to the accompanying drawings in which embodiments of the disclosures are illustrated and, together with the descriptions below, serve to explain the principles of the disclosure.

FIG. 1 is a front top perspective view of a rocket launching system according to exemplary implementations of the present disclosure.

FIG. 2 is an exploded perspective view of the rocket launching system of FIG. 1.

FIG. 3 is a partial cross-sectional schematic view of one embodiment of a rocket launching system in the pre-launch mode.

FIG. 4 is the partial cross-sectional schematic view of the rocket launching system of FIG. 3 in the launch mode.

FIG. 5 is a partial cross-sectional schematic view of another embodiment of a rocket launching system in the pre-launch mode.

FIGS. 6A-6D are schematics of a rocket having a payload according to exemplary implementations of the present disclosure.

FIGS. 7A-7D are schematics of a rocket having a payload to exemplary implementations of the present disclosure.

FIGS. 8A-8D are schematics of a rocket having a payload according to exemplary implementations of the present disclosure.

FIG. 9 is a schematic view of aspects of a rocket launching system according to exemplary implementations of the present disclosure.

FIG. 10 is a schematic view of aspects of the rocket launching system of FIG. 9.

FIG. 11 is a schematic view of aspects of the rocket launching system of FIG. 9, in particular showing a compressed gas cartridge contacting an O-ring.

FIG. 12 is a schematic view of aspects of the rocket launching system of FIG. 9, in particular showing compressed gas entering a pressure chamber.

FIG. 13 is a schematic view of aspects of the rocket launching system of FIG. 9, in particular showing the breakage of a pressure threshold device.

FIG. 14 is a side view of a rocket, according to exemplary implementations of the present disclosure.

FIG. 15 is a side view of the rocket of FIG. 14, further showing a separation of a drone and a fuselage.

FIG. 16 is a perspective view of the drone of FIG. 15.

FIG. 17 is a perspective view of a second implementation of a rocket, according to exemplary implementations of the present disclosure.

FIG. 18 is a perspective view of aspects of a rocket launching system according to exemplary implementations of the present disclosure.

FIG. 19 is a perspective view of the rocket launching system of FIG. 18 with a portion of the launching tower removed.

FIG. 20 is a side elevation view of the rocket launching system of FIG. 18 with the rocket and launcher removed.

FIG. 21 is a perspective view of the pressure chamber and carrier of the rocket launching system of FIG. 18.

FIG. 22 is a cross-sectional side view of the rocket launching system of FIG. 18, prior to loading of the system.

FIG. 23 is a cross-sectional side view of the rocket launching system of FIG. 18, in the loaded prelaunch position prior to the tower being placed in the use position.

FIG. 24 is a cross-sectional side view of the rocket launching system of FIG. 23, with the tower being moved to the use position.

FIG. 25 is a cross-sectional side view of the rocket launching system of FIG. 18, in the loaded prelaunch position.

FIG. 26 is a cross-sectional side view of the rocket launching system of FIG. 18, following ignition.

FIG. 27 is a top perspective view of another embodiment of a rocket for the rocket launching system of FIG. 18, in the prelaunch position.

FIG. 28 is a top perspective view of the rocket of FIG. 27, in the partially open position.

FIG. 29 is a top perspective view of the rocket of FIG. 27, in the open position.

FIG. 30 is a front view of a launch controller.

DETAILED DESCRIPTION

While the rocket launching system discussed herein is susceptible of embodiments in many different forms, there is shown in the drawings, and will herein be described in detail, preferred embodiments with the understanding that the present description is to be considered as an exemplification of the principles of the rocket launching system and is not intended to limit the broad aspects of the disclosure to the embodiments illustrated.

Referring now to FIGS. 1-4, a first implementation of a rocket launching system 10 is shown. According to one embodiment, the rocket launching system 10 may include a launch housing 12, a launcher 14, a pressurizer 16, a power supply 18, an air chamber 20, a smoker/fogger 22, an air release member 24, a controller 26, and a rocket 28. The rocket launching system 10 is designed to be more kid friendly by providing: a launching system that does not require tools for assembly; a realistic pre-launch sequence, possibly including one or more of lights, sounds, smoke effects, vibrations, etc.; a more realistic controller; a safer non-combustion launch; and, an auto parachute for safe and easy recovery of the rocket 28.

As best shown in FIG. 2, in a first implementation the launch housing 12 is preferably a container that, in one embodiment, houses the pressurizer 16, power supply 18, and air chamber 20. The launch housing 12 may also retain the smoker/fogger 22, if provided. In an alternate embodiment, not shown, the launch housing 12 may also house the rocket 28 during periods of non-use. The launch housing 12 may be comprised of multiple housing components, such as shown in one example in FIG. 2, that join together to form the complete housing 12. The multiple housing components may snap together, or alternately they may be hinged together and secured with a closure.

Propulsion for the rocket 28 may preferably be achieved through the use of air 30 at high pressure that is provided by the pressurizer 16 and that is stored in the air chamber 20. The high pressure air 30 is released from the air chamber 20 into the launcher 14 to propel the rocket 28 into the sky and away from the launcher 14. The pressurizer 16 may have stored within it high pressure air 30, such as with a compressed air tank, or the pressurizer 16 may create the high pressure air 30. In one embodiment the pressurizer 16 is an electric air compressor 16 that is stored in the launch housing 12. The electric air compressor 16 converts power into potential energy stored in pressurized air.

In one embodiment the pressurizer 16 is powered by the power supply 18, which is also preferably located within the launch housing 12. Preferably, the power supply 18 is a rechargeable battery, such as a lithium ion battery or a lead acid battery. Alternately, non-rechargeable batteries may be utilized to supply power to the electric compressor. Further alternately, the power supply 18 need not be a battery, but instead may be a generator or simply the electricity provided from a standard wall outlet.

Referring to FIGS. 2 and 3, the compressed air 30 that is provided by the pressurizer 16 is stored within the air chamber 20. The air chamber 20 is preferably a container 20, such as a tank, with a fixed volume and which has a wall strength sufficient to withstand a high internal pressure from the compressed air therein. In a preferred embodiment, the pressurizer 16 is able to pressurize the air up to 150 psi, and most preferably about 100-110 psi, and the air chamber 20 must have sufficient wall strength to retain and withstand the pressure of the air created by the pressurizer 16. In one embodiment the air chamber 20 is a polyethylene tank.

As shown in FIGS. 3-5, an air release member 24 is provided between the air chamber 20 and the launcher 14. The air release member 24 retains the pressurized air 30 within the air chamber 20 until the pressure within the air chamber 20 reaches a release pressure sufficient to overcome the air release member 24. In one embodiment the air release member 24 is a valve. In an alternate embodiment the release member 24 is a burstable membrane, such as a polyethylene sheet membrane. In the embodiment where the release member 24 is a polyethylene sheet membrane, the polyethylene sheet membrane 24 is able to retain the pressurized air 30 within the air chamber 20 until the pressure within in the air chamber 30 reaches a release pressure. The release pressure for the membrane-style release member 24 will generally be set by the thickness and material that makes up the membrane 24. In a preferred embodiment the membrane-style release member 24 will be approximately 0.015625″ thick and be made of polyethylene. At that thickness and material properties, the membrane release member 24 will fail when the air pressure within the air chamber 20 reaches approximately 100-110 psi, and preferably 100 psi. As explained herein, the pressurizer 16 can be adjusted such that the air pressure within the air chamber 20 reaches approximately 100-110 psi, and preferably 100 psi, at a certain time period from initiation of the launch. That way, each time a launch is requested, the launch will occur at the same amount of time after the launch button 44 is depressed on the controller 26 to allow for proper sequencing of pre-launch activities. When the release member 24 opens or fails, as shown in FIGS. 5-7, the air within the air chamber 20 is immediately released into the launcher 14 to propel the rocket 28 into the sky.

The launcher 14 is a component that retains the rocket 28 and which directs the compressed air 30 released from the air chamber 20 to the rocket 28. Preferably, the launcher 14 is secured to the launch housing 12 at the exit to the air chamber 20. And, most preferably, the release member 24 is provided between the exit to the air chamber 20 and the launcher 14. In one embodiment the launcher 14 is a cylindrical component having an outer wall 32 and an inner cavity 34, such as a tubular member. The compressed air 30 that is expelled from the air chamber 20 and through the release member 24 preferably enters the inner cavity 34 of the launcher 14. In one embodiment the launcher 14 is removably fixed to the exit of the air chamber 20, such as by a male/female mating arrangement, via a bayonette connection, via a threaded connection, via a hinge and fastener, or by some other relationship that allows for removably fixing the launcher 14 to the exit of the air chamber 20 with the release member 24 therebetween.

The rocket 28 is fitted onto the launcher 14 prior to launch. Once on the launcher 14, the rocket 28 is able to receive the pressurized air 30 from the air chamber 20, which provides the propulsion for the rocket 28. In one embodiment, the rocket 28 is a tubular member having an outer wall 36 and an inner cavity 38. In one embodiment, as shown in FIGS. 3 and 4, the rocket 28 is placed on the launcher 14 such that the launcher 14 fits within the inner cavity 38 of the rocket 28. As shown in FIG. 4, in one embodiment when pressurized air 30 is released from the air chamber 20 it fills the inner cavity 34 of the launcher 14 and contacts the rocket 28, thereby providing propulsion to the rocket 28 to launch the rocket 28 from the launcher 14.

In an alternate embodiment as shown in FIG. 5, the rocket 28 has a piston 40 within the inner cavity 38 of the rocket 28. In this embodiment, when the rocket 28 is placed on the launcher 14, the piston 40 fits within the inner cavity 34 of the launcher 14. In such embodiment, the pressurized air 30 that escapes from the air chamber 20 immediately contacts the piston 40, rather than having to fill the inner cavity 34 of the launcher 14 before engaging the rocket 28. This provides for initially engaging the piston 40 of the rocket 28 with essentially the full energy and full pressure of the pressurized air, and also provides for higher air pressure at the exit of the launcher 14 than the embodiment shown in FIG. 4 without the piston 40.

Referring to FIGS. 1 and 30, the launch of the rocket 28 and the pre-launch activities may be controlled by the controller 26. The controller 26 may be hard wired to the launch housing 12 and directly connected to the various electrical components of the rocket launching system 10, or the controller 26 may be wirelessly connected, such as by Bluetooth or radio frequency, to a wireless receiver in the launch housing 12. Additionally, the controller 26 may have multiple buttons or switches. One such button/switch 42 may be a toggle switch 42 to arm the rocket launching system 10. This system arm toggle switch 42 may be in either the disable position or the enable position. Another such button or switch 44 may be a launch button 44 which initiates the pre-launch and launch activities of the rocket launching system 10. In one embodiment, the launch button 44 is disabled until the system arm toggle switch 42 is placed in the enable position. Accordingly, until the system arm toggle switch 42 is in the enable position, depressing the launch button 44 will not activate the prelaunch and launch activities.

Prelaunch activities include activities that enable the rocket 28 to be launched, and that provide for a better user experience for the operator and those viewing the rocket launching system 10. One of the prelaunch activities is to open a switch to provide power from the power supply 18 to the pressurizer 16 to turn the pressurizer 16 on. When the pressurizer 16 is turned on the pressurizer 16 will provide compressed air 30 into the air chamber 20. Additional optional prelaunch activities include the creation of smoke by a smoker 22, the creation of noise or rocket rumble by a rumble making apparatus 46, and the counting down of the rocket launch by an audible count down timer 48, however additional prelaunch activities may also be provided.

The preferred smoker/fogger 22 is a traditional fog machine that creates fog or smoke by vaporizing water and glycol-based or glycerin-based fluids. The fluid is referred to as smoke juice or fog juice, and it vaporizes or atomizes inside the fog machine 22. Upon exiting the fog machine 22 and mixing with the cooler outside air the vapor condenses, resulting in a thick visible fog or smoke. As shown in FIG. 1, the smoke/fog is created at the base of the rocket 28 after the launch button 44 is engaged and prior to liftoff to provide the effect to the user of a real rocket launch. The user will fill the fog machine 22 with fog juice to ready the rocket launching system 10 and to further engage in the entire prelaunch experience.

As explained above, another of the prelaunch activities is to provide a rumble noise and rumble feel (i.e., vibration), similar to what a spectator would feel and hear prior to a real rocket launch. In one embodiment, an offset or vibrating motor (not shown) is used to create the vibration and rumble noise. The vibrating motor may be located either in the controller 26 or in the launch housing 12. In one embodiment, the vibrating motor is a small motor that is improperly balanced. Furthermore, in one embodiment, there may be an off-centered weight attached to the motor output shaft that causes the motor to wobble. The amount of wobble can be changed by the amount of weight that is attached to the output shaft, the weight's radial distance outwardly from the shaft, and the speed at which the motor shaft rotates. Further, the offset weight may contact the housing, either the inside of the housing of the controller 26 or the inside of the launcher housing 12, to create additional rumble noise and vibration.

The audible countdown timer 48 may be provided either in the controller 26 or the launch housing 12, however in a preferred embodiment the countdown timer 48 is in the controller 26. The audible countdown timer 48 is preferably timed with the filling of the air chamber 20 with pressurized air 30 and the subsequent rupture/opening of the release member 24 such that when the countdown timer 48 reaches “0” or “liftoff”, the air chamber 20 will be properly pressurized and the release member 24 will burst/open causing a liftoff of the rocket 28.

Accordingly, one example of a sequence of prelaunch activities includes the user first moving the arm toggle switch 42 on the controller 26 from the disable position to the enable position. At any time after the arm toggle switch 42 is moved to the enable position the launch button 44 may be depressed to initiate a launch. Prior to the arm toggle switch 42 being moved to the enable position (i.e., when the arm toggle switch 42 is in the disable position) the launch button 44 is inactive. In one embodiment, a light in the launch button 44 may illuminate when the arm toggle switch 42 is in the enable position to alert the user that a launch may be conducted. Additionally, after the launch button 44 is depressed the arm toggle switch 42 will return to the disable position.

Once the system is enabled via the arm toggle switch 42 and the launch button 44 is depressed, prelaunch activities that result in a launch of the rocket 28 will occur. For example, the pressurizer 16 will begin filling the air chamber 20 with compressed air 30 as shown in FIGS. 3 and 5. The amount of time required to fill the air chamber 20 with compressed air at the pressure required to burst or open the release member 24 is known to the manufacturer. Accordingly, it is known exactly how much time elapses from depressing the launch button 44 and bursting or opening of the release member 24, shown in FIG. 4, to provide for liftoff of the rocket 28. By knowing the time to liftoff from engaging the launch button 44, the other prelaunch activities such as the countdown timer, the providing of smoke/fog and the providing of the prelaunch rumble and vibration can occur and be sequenced and timed properly as they would occur if this were a real rocket launch. In one embodiment the amount of air pressure within the air chamber 20 to burst or open the release member 24 is preferably between 100 psi and 110 psi, and most preferably 100 psi. At that pressure the rocket 28 will be launched approximately 100-300 feet in the air, depending on the conditions and the rocket 28 configuration.

In an alternate embodiment, not shown, the launcher 14 may transition from a horizontal position to a vertical launch position. The transition of the launcher 14 from the rest position to the launch position may occur manually by the user prior to initiating a launch, or it may occur automatically after the user moves the arm toggle switch 42 from the disable position to the enable position.

Referring to FIGS. 5-8, in different embodiments the rocket 28 has different configurations. For example, the rocket 28 may have a rocket body 50 and a rocket nose cone 52. In one embodiment the rocket nose cone 52 may be made of a soft polymeric material to provide a cushion for the rocket 28 during descent of the rocket 28. Additionally, in a preferred embodiment, fins or other stabilizers 54 are provided toward the distal end 56 of the rocket body 50 to aid in a more linear vertical flight of the rocket 28. The rocket 28 may also carry a payload 58, such as a parachute 58, in a cargo area 60 of the rocket 28. The cargo area 60 of the rocket 28 varies in different embodiments. For example, in the embodiments shown in FIGS. 6 and 7 the cargo area 60 is in the rocket body 50, whereas in the embodiment shown in FIG. 8, the cargo area 60 is in the nose cone 52 of the rocket 28. Additionally, access to the cargo area 60 varies in different embodiments. For example, access to the cargo area 60 in the embodiment of FIG. 6 is provided via a sliding door 62 on the rocket body 50, access to the cargo area 60 in the embodiment of FIG. 7 is provided by removing the nose cone 52, and access to the cargo area 60 in the embodiment of FIG. 8 is provided by opening the nose cone 52. In embodiments where the nose cone 52 is disengaged from the rocket body 50 during deployment of the parachute 58, the nose cone 52 will preferably be tethered to the rocket body 50 so that the nose cone 52 is not lost.

Preferably, the parachute 58 is deployed just after the rocket 28 reaches its apex of flight. The rocket 28 may have a sensor (not shown), such as a pressure sensor or a tilt sensor, so that the rocket 28 knows when to deploy the parachute 58. In one embodiment, when a pressure sensor is utilized the pressure sensor is able to sense when the rocket height has decreased a certain distance, such as, for example, three feet, and the sensor will then send a signal to a solenoid (not shown) to deploy the parachute 58. In an alternate embodiment, a mechanical counterweight system may be utilized to determine proper deployment time for the parachute 58. By utilizing a parachute 58, a slower and more controlled descent of the rocket 28 may occur.

Referring now to FIGS. 9-17, another implementation of a rocket launching system 110 is shown. In this disclosure, like components in different implementations may be similarly named, but they may not necessarily share the same reference number. In one embodiment, the rocket launching system 110 includes a launching base 114, a launch tube 118, a burst membrane 122, a pressure chamber 126, a vented pin 130, an O-ring 134, a threaded male post 138, a gearbox 142 and a cartridge carrier 146. A pressurized gas container 150, which may be a Carbon Dioxide cartridge, is releasably connected to the cartridge carrier 146. The pressurized gas container 150 may be threadably connected to the cartridge carrier 146. As shown in FIG. 9, the pressurized gas container 150 is initially not in contact with the vented pin 130.

In one embodiment, the rocket launching system 110 includes a gearbox 142 and a gearbox motor 158 to assist in fluidly connecting the pressurized gas container 150 with the pressure chamber 126 of the launching base 114. In one embodiment the gearbox 142 and a gearbox motor 158 assist in rotating the cartridge carrier 146 and the attached pressurized gas container 150 relative to the launching base 114, as best shown in FIG. 10. Due to a threaded interaction between the cartridge carrier 146 and the threaded male post 138, the cartridge carrier 146 and attached pressurized gas container 150 are moved towards the vented pin 130 while rotating relative to the launching base 114. The gearbox motor 158 may be powered by a base battery 159 or another electrical power source. As is understood, the carrier 146 is for supporting a pressurized gas container 150, and the carrier moves from a first position (see FIG. 9) to a second position (see FIG. 12). The pressurized gas container is not in fluid communication with the pressure chamber in the first position of the carrier, but the pressurized gas container is in fluid communication with the pressure chamber in the second position of the carrier. In one embodiment the gearbox and gearbox motor is referred to as the carrier transfer mechanism because it transitions the carrier from the first position to the second position.

A portion of the pressurized gas container 150 contacts the O-ring 134 before the portion of the pressurized gas container 150 contacts the vented pin 130, as shown in FIG. 11. The contact between the pressurized gas container 150 and the O-ring 134 prevents an escape of compressed gasses to undesired areas upon a puncture of the pressurized gas container 150.

Following contact between the pressurized gas container 150 and the O-ring 134, the cartridge carrier 146 and the attached pressurized gas container 150 continue to rotate and translate such that the pressurized gas container 150 is contacted, and pierced, by the vented pin 130 in the second position. Compressed gas formerly stored in the pressurized gas container 150 travels into the pressure chamber 126 through vents in the vented pin 130, as indicated in FIG. 12. Due to the interface between the O-ring 134 and the pressurized gas container 150, and because the vented pin 130 pierces the pressurized gas container 150 only at an area disposed substantially within the O-ring 134, the compressed gas formerly stored in the pressurized gas container 150 travels only into the pressure chamber 126 without entering other areas. Accordingly, an internal pressure rises in the pressure chamber 126 following the piercing of the pressurized gas container 150.

As pressure increases in the pressure chamber 126 from the piercing of the pressurized gas container 150, a burst membrane 122 maintains a pressure-tight seal. However, upon the pressure chamber 126 reaching a certain threshold pressure, and the burst membrane 122 experiencing the same threshold pressure, the burst membrane 122 ruptures, as best shown in FIG. 13. This allows the pressurized gas in the pressure chamber 126 to pass through the ruptured burst membrane 122 and enter the launch tube 118, providing a motive force to launch a rocket 170 from the launch tube 118.

Following the launch of a rocket 170 as described above, the gearbox motor 158 is operated in a reversed direction, causing the cartridge carrier 146 and attached pressurized gas container 150 to rotate and translate upwardly and away from the O-ring 134 and vented pin 130 due to the threaded connection between the threaded male post 138 and the cartridge carrier 146. The pressurized gas container 150 is then removed from the cartridge carrier 146 and a new, and sealed, pressurized gas container 150 can be connected to the cartridge carrier 146 in preparation for another rocket 170 launch. It is to be understood that the launch tube 118 can be affixed to, or located remotely from, the launching base 114.

Some implementations of the launching base 114 include a plurality of folding covers (not shown) that enclose the rocket 170 mounted on the launch tube 118 when the folding covers are arranged in an upright position. The folding covers may be adjustable downwardly to a launch position. In the launch position, the folding covers no longer enclose the rocket and allow the rocket to launch from the launch tube. The folding covers may also stabilize the launching base on a ground surface when arranged in the launch position. In some implementations the folding covers are manually adjustable between upright and launch positions, while in other implementations the folding covers are electrically adjustable between upright and launch positions by electric motors (not shown). Further, the folding covers may be remotely adjustable between upright and locked positions by a controller, which will be described below in detail.

FIGS. 9-14 shows aspects of the rocket launching system 110, including the rocket 170, a launching base 114 and a landing pad (not shown). Also shown are a drone 180 and a fuselage 190. Turning to FIG. 14, some implementations of the rocket 170 include the drone 180 releasably connected to the fuselage 190. As shown, in one embodiment, the drone 180 is disposed at a forward end 192 of the rocket 170. A trailing end 194 of the rocket 170 includes aerodynamic stabilizers 193 and further releasably mates to the launch tube 118. The drone 180 includes a nose cone 191 for aerodynamic and aesthetic purposes, and the nose cone 191 can be formed of a soft or resilient material, such as foam.

During a rocket 170 flight, the drone 180 separates from the fuselage 190 in some implementations of the present disclosure, as shown in FIG. 15. The rocket 170 may be powered by the pressurized gas container 150, a compressor or a combustible engine. The drone 180 may separate from the fuselage 190 at the apogee of the rocket 170 flight. The drone 180 may include a control system 189 including a printed circuit board and multiple sensors which may include, but are not limited to, a 3-axis accelerometer, a gyroscope, a barometric pressure sensor, a Global-Positional System sensor, a radio-frequency communication device and a Bluetooth communication device. The sensors allow the tracking and recording of various performance metrics by the rocket launching system 110, such as maximum speed, maximum height and flight duration.

Turning to FIG. 16, the drone 180 includes a plurality of propellers 195 powered by one or more propulsion motors 196. The propellers 195 and propulsion motors 196 are attached to a drone main body 181 by arms 197. The geometric arrangement of the propellers 195, in conjunction with drone 180 weight distribution and various drone 180 pitch, yaw and roll maneuvers allows the drone 180 to fly autonomously or via remote control. In some implementations, the drone 180 separates from the fuselage 190 by an operation of the propellers 195 and propulsion motors 196. The propellers 195 and propulsion motors 196 may also operate during the rocket 170 launch and ascent. For example, the propellers 195 and propulsion motors 196 may be set to generate 20% of their maximum thrust during launch and ascent and may then briefly generate 50% of their maximum thrust to separate the drone 180 from the fuselage 190. However, other mechanical devices such as springs and latches can also be used to separate the drone 180 from the fuselage 190. During launch and ascent, the drone 180 is releasably connected to the fuselage 190 by various mechanical means, such as clips, tabs or biased members.

In some implementations, a streamer (not shown) may be connected to the fuselage 190. The streamer may be loosely engaged with a portion of the drone 180 such that the separation of the drone 180 and the fuselage 190 results in the streamer being deployed from the fuselage 190 after drone 180 separation. The streamer, which may be highly visible with various colors, lights or reflective properties, helps slow the fuselage's descent to the ground after separation with the drone and also aids in visual tracking of the descending fuselage. In some implementations, a parachute or rigid aerodynamic surfaces can be used to slow the descent of the fuselage. In some implementations, the fuselage simply descends to the ground without aerodynamic assistance. The fuselage may include foam or other resilient surfaces to preserve the structural integrity of the fuselage upon contact with a ground surface.

FIG. 17 shows a second implementation of a rocket 170. In this implementation, the rocket 170 does not separate into a drone 180 and a fuselage 190 during flight. Instead, the drone 180 is fixedly connected to the fuselage 190 of the rocket 170, and includes motors and propellers, as described above, for controlled flight after launch.

A controller 26 is shown in FIG. 30. The controller 26 is operable by a user and controls various operations of the launching base 114, rocket 170 and drone 180. Some aspects of the controller 26 are used to control the operations of the launching base 114 and other aspects of the controller 26 are used to control the drone 180 and/or rocket 170 during flight.

The controller 26 may include an LCD screen 198 for displaying various rocket 170, launching base 114 and drone 180 information. In particular, data gathered from the aforementioned sensors and components of the control system 189 can be displayed on the LCD screen 198. A first control 42, or an arming control, initiates a pre-launch sequence. Such a sequence can include audible sounds, such as rocket sounds or a numerical countdown, produced by the controller 26, rocket 170 and/or launching base 114. The pre-launch sequence can also include the operation of various lights on the controller 26, rocket 170 and/or launching base 114. The launching base 114 and/or rocket 170 can also generate a visible gas, or fog, during the pre-launch sequence by vaporizing fluids, such as fog juice.

A second control 44, which may be operable only after the pre-launch sequence, initiates the rocket 170 launch using the pressurized gas container 150, as described above. Following the rocket 170 launch, the drone 180 is remotely operable by the user. In particular, drone controls 199 are used to wirelessly control flight operations of the drone 180. In some implementations, the drone controls 199 can control pitch, roll, yaw, trim, altitude and speed characteristics of the flying drone 180. The drone 180 may also include an autonomous mode that automatically brings the drone 180 into contact with the ground surface. Such a mode may be activated by a loss of wireless signal between the controller 26 and the drone 180. The controller 26 may also remotely adjust the folding covers between upright and locked positions.

Further, the controller 26 can include multiple levels of user control. Such an implementation allows users of various ages or abilities to control various aspects of the rocket launching system 110. In particular, three levels of user control could be selectable by a user. A first mode may include automatic drone 180 separation from the fuselage 190 based on sensors of the control system 189, and the drone 180 automatically returns to the launching base 114 or landing pad. A second mode may include automatic drone 180 separation based on sensors of the control system 189 while the user controls drone 180 thrust and direction to land the drone 180 in conjunction with auto-stabilizing drone 180 software. A third mode may include drone 180 separation induced by a user control and complete, or partially-assisted from auto-stabilizing software, user control of drone 180 flight following separation.

Referring now to FIGS. 18-29, another implementation of a rocket launching system 210 is shown. In one embodiment, the rocket launching system 210 includes a launch base 212, a cartridge carrier 214, a pressure chamber 216, a vent pin 218, a launch tower 220, a burst membrane 222, a launch tube 224, and a rocket 226. The rocket slidingly engages the launch tube in various embodiments. The drawing in FIG. 18 shows the rocket launching system 210 with the launch tube 224, but without the rocket 226. A variety of rockets, as described herein, may be utilized with the rocket launching system 210.

The rocket launching system 210 is preferably energized by pressurized gas. In one embodiment, a pressurized gas container 228, which may be a Carbon Dioxide cartridge, is releasably connected to the cartridge carrier 214. The pressurized gas container 228 may be threadably connected to the cartridge carrier 214. As shown in FIGS. 23-25, the pressurized gas container 228 is not contacted by the vent pin 218 until a launch is initiated as shown in FIG. 26.

In one embodiment, the rocket launching system 210 includes a launch tower 220 having a launch hammer 230, a loading lever 232, a trigger 234, and a solenoid 236. The solenoid 236 is powered by a battery 238 located in the battery chamber 240 of the launch tower 220. The launch hammer 230 is spring biased with a compression launch spring 242 to transmit the launch hammer 230 against the pressurized gas container 228 during the launch sequence. Similarly, the trigger 234 is spring biased with an extension spring 244 to retain the launch hammer 230 against the force of the solenoid 236. In one embodiment the launch hammer is referred to as the carrier transfer mechanism because it transitions the carrier from the carrier first position to the carrier second position.

The rocket launching system 210 also includes a launch controller 26, one example of which is shown in FIG. 30. The launch controller 26 may be mechanically connected to the rocket launching system 210, such as by tether or electrical wire, or it may be remote and transmit data to the rocket launching system 210 wirelessly. In one embodiment, not shown, the launch controller is wired to a controller (not shown) in either the launch base 212 or the launch tower 220. In an alternate embodiment, the launch controller 26 sends wireless signals to the controller in the launching system 210.

To operate the rocket launching system 210 a burst membrane 222 is placed in the launch receiver 248 to cover an opening 250 in the launch base 212. This opening 250 in the launch base 212 is typically referred to as the outlet 250 to the pressure chamber 216. Next, the launch tube 224 is connected to the receiver 248 of the launch base 212, with the burst membrane 222 closing the opening 250 from the pressure chamber 216 of the launch base 212 to the launch tube 224. In one embodiment, the launch tube 224 has a threaded member 252 that threads into the launch receiver 248 of the launch base 212. The launch tube 224 is therefore preferably connected to the launch base 212 adjacent the outlet 250 of the pressure chamber 216. In one embodiment, the pressure chamber 216 comprises a cavity 216 within the launch base 212, and the launch base 212 is comprised of a lower housing 254 and an upper housing 256 connected to the lower housing 254. FIGS. 22-26 illustrate the rocket launching system 210 with a burst membrane 222 provided at the opening 250 to the pressure chamber 216 that is held in place with the threaded member 252 of the launch tube 224. As shown in FIGS. 22-25, the vent pin 218 does not contact the pressurized gas container 228 on the cartridge carrier 214 until a launch is initiated.

Next, the launch hammer 230 is set. As shown in FIG. 26, after a launch has occurred the launch hammer 230 is not retained by the trigger 234 in the ready for launch position. To set the launch hammer 230 in the ready for launch position, as shown in FIG. 25, the launch tower 220 is pivoted away from the launch tube 224 as shown in FIGS. 22-24. The launch tower 220 is preferably pivotally connected to the launch base 212. As shown in FIGS. 18-21, including with the launch tower 220 removed in FIG. 21, in one embodiment the launch base 212 has upwardly extending flanges 258 to which the launch tower 220 is pivotally connected, preferably with the use of a shoulder bolt. The flanges 258 have inwardly facing vertical slots 260 into which a shaft 262 extending from the cartridge carrier 214 can slide, as best shown in FIG. 21, to maintain the cartridge carrier 214 properly aligned as it moves vertically from the neutral or load position to the launch position.

As shown in FIGS. 19 and 21, the cartridge carrier 214 also has a shoulder 264 extending therefrom. The shoulder 264 is able to ride on a cam surface 266 extending from an inside of the launch tower 220. Accordingly, when the launch tower 220 is pivoted away from the launch tube 224 as shown in FIGS. 23 and 24, the shoulder 264 of the cartridge carrier 214 rides on the cam surface 266 of the launch tower 220, along with the shaft 262 of the cartridge carrier 214 riding in the vertical slot 260 of the flanges 258 extending from the base 212, causing the cartridge carrier 214 to be lifted vertically. A compression spring 268 within the pressure chamber 216 (see FIGS. 22-26) also exerts a vertical force on the cartridge carrier 214 to bias the cartridge carrier 214 upwardly and away from the vent pin 218, which resides in the central bore 270 of the cartridge carrier 214. A seal or O-ring 272, as shown in FIGS. 19 and 22-26, seals the cartridge carrier 214 against an opening 274 in the upper housing 256 of the launch base 212. This opening 274 in the launch base 212 is also referred to as the inlet to the pressure chamber 216. An O-ring type seal 272 is preferred since the cartridge carrier 214 moves vertically in the opening 274 and the seal between the cartridge carrier 214 and the opening 274 must be maintained at all times to maintain the integrity of the pressure chamber 216 (except during pressure release events for safety purposes).

When the launch tower 220 is tilted backwards, one end of the loading lever 232 slides in a slide track 276 in the launch tower 220 and the end of the loading lever 232 will engage the launch hammer 230. The launch hammer 230 is slidingly connected to the launch tower 220 and is able to slide about a longitudinal axis of the launch tower 220. The compression launch spring 242 biases the launch hammer 230 toward the base of the launch tower 220 (i.e., toward the cartridge carrier 214). As shown in FIGS. 22 and 23, the loading lever 232 pushes the launch hammer 230 until the launch hammer 230 is positioned above the trigger 234. At that point the trigger 234 maintains the launch hammer 230 in the cocked or ready position. Once the launch hammer 230 is in the ready position the pressurized gas container 228 can be connected to the cartridge carrier 214.

When the launch tower 220 is tilted backwards (the first position of the launch tower 22) the user has access to remove an old/used pressurized gas container 228 and insert a new gas container 228 to prepare for another launch of the rocket 226. The pressurized gas container 228 is connected to the rocket launching system 210 via the cartridge carrier 214. Typically, the pressurized gas container 228 is connected to the cartridge carrier 214 via a threading engagement, however alternate mating methods such as via a bayonet connection, a luer lock connection or via other connection means. Access to the cartridge carrier 214 is provided via a cutout 278 in the launch tower 220. The cutout 278 is preferably sized such that only an appropriately sized gas container 228 may be utilized with the rocket launching system 210, as shown in FIG. 20. Specifically, inappropriately sized gas containers 228, such as gas containers 228 that contain a higher gas pressure, will typically be larger either in height or width/diameter than appropriately sized gas containers. Such larger gas containers will not fit through the cutout 278 in the launch tower 220, and even if connected to the cartridge carrier 214 when the launch tower 220 is tilted backwards, if the gas cartridge that is connected to the cartridge carrier 214 will not fit through the cutout 278 the launch tower 220 cannot be placed into a ready for launch position. Accordingly, the size of the cutout 278 in the launch tower 220 provides a first level of safety to preclude inappropriately sized gas containers 228 from being connected for use with the rocket launching system 210.

When the cartridge carrier 214 is accessible for removal/insertion of the gas cartridge 228 as shown in FIG. 23, the shoulder 264 of the cartridge carrier 214 engages the cam surface 266 of the launch tower 220 and is maintained in the up position as shown in FIG. 23. In this position the opening to the gas cartridge 228 is maintained a distance from the tip of the vent pin 218 to prevent the vent pin 218 from piercing the opening to the gas cartridge 228. Accordingly, the launch tower prevents the pressure source from being in fluid communication with the inlet to the pressure chamber when the launch tower is in the first position.

Accordingly, once an appropriately sized gas container 228 is connected to the cartridge carrier 214 as shown in FIG. 23, the launch tower 220 can be tilted backward toward the vertical as shown in FIG. 24 (the second position of the launch tower). During the initial portion of the tilting of the launch tower 220 from the horizontal to the vertical, the shoulder 264 of the cartridge carrier 214 will generally remain engaged to the cam surface 266 of the launch tower 266. However, once the launch tower 220 is sufficiently pivoted/rotated such that the gas container 228 is within the launch tower 220, the shoulder 264 of the cartridge carrier 214 will break contact with the cam surface 266 due to the geometry of the cam surface 266 and the force of the compression spring 268 within the pressure chamber 216 that exerts a vertical force on the cartridge carrier 214 to bias the cartridge carrier 214 upwardly and away from the vent pin 218.

Additionally, as seen in FIG. 24, as the launch tower 220 is tilted back to the vertical (i.e., the position shown in FIG. 25), the launch hammer 230, which has been set in the cocked or ready for launch position and held in place with the trigger 234, is maintained in the cocked or ready for launch position by the trigger 234. In the ready for launch position of FIG. 25, the rocket launching system 210 is ready to initiate a launch of the rocket 226 once the rocket launching system 210 receives a launch request.

As shown in FIG. 25, in the ready for launch position the launch hammer 230 is in the cocked and ready position, with the launch spring 242 in the compressed orientation. The launch hammer 230 is held in place with the trigger 234. Additionally, the loading lever 232 is held in place at one end via connection to the base of the launch tower 220 and at the other end via the sliding engagement within the slide track 276 of the launch tower 220. Accordingly, when the launch tower 220 is in the vertical position the loading lever 232 is maintained clear from the launch hammer 230 so that the loading lever 232 does not interfere with the movement of the launch hammer 230. Further, while the shaft 262 of the cartridge carrier 214 rides in the vertical slot 260 of the flanges 258 extending from the base 212 (see FIG. 21) to only allow the cartridge carrier 214 to move vertically in a sealed manner with respect to the launch base 212, the shoulder 264 of the cartridge carrier 214 is maintained a slight distance above the cam surface 266 of the launch tower 220 by the compression spring 268 exerting an upward force on the cartridge carrier 214. In this position the end of the gas container 228 is still maintained a distance from the end of the vent pin 218.

To initiate a launch of the rocket 226, in one embodiment a signal must be provided, such as a signal to the solenoid 236 or some other mechanical means, to initiate a launch by moving the trigger 234. The signal is preferably provided by the launch controller 26, either wirelessly or via wired connection. Once the launch signal is provided to the solenoid 236, the solenoid 236 moves the trigger 234 to disengage the trigger 234 from the launch hammer 230. In an alternate embodiment, no solenoid 236 is used and a simple mechanical mechanism, such as a wire or spring, transitions the trigger 234 to release the launch hammer 230. Once the trigger 234 is moved this allows the launch spring 242 to propel the launch hammer 230 toward the gas container 228 connected to the cartridge carrier 214. The launch hammer 230 contacts the gas container 228 and forces the cartridge carrier 214, with the gas container 228 connected thereto, sufficiently downwardly into the pressure chamber 216 of the launch base 212, overcoming the force of the compression spring 268 within the pressure chamber 216. The vent pin 218 pierces the end of the gas container 228 causing the compressed gas formerly stored in the pressurized gas container 228 to travel into the pressure chamber 216, possibly including through vents in a hollow vent pin 218. Because the opening 274 in the upper housing 256 of the launch base 212 is sealed to the cartridge carrier 214 with the O-ring 272, the compressed gas formerly stored in the pressurized gas container 228 travels only into the pressure chamber 216. Accordingly, an internal pressure rises in the pressure chamber 216 following the piercing of the pressurized gas container 228. As is understood, the carrier 214 is for supporting a pressurized gas container 228, and the carrier moves from a first position (see FIG. 25) to a second position (see FIG. 26). The pressurized gas container is not in fluid communication with the pressure chamber in the first position of the carrier, but the pressurized gas container is in fluid communication with the pressure chamber in the second position of the carrier. In one embodiment the launch hammer is referred to as the carrier transfer mechanism because it transitions the carrier from the first position to the second position.

As pressure increases in the pressure chamber 216 from the piercing of the pressurized gas container 228, the burst membrane 222 maintains a pressure-tight seal at the only other opening in the pressure chamber 216 at the launch receiver 248 portion of the launch base 212. Preferably, when the pressure chamber 216 reaches a certain threshold pressure the burst membrane 222 will rupture allowing the pressurized gas in the pressure chamber 216 to pass through the ruptured burst membrane 222 and enter the launch tube 224, providing a sufficient force to launch the rocket 226 from the launch tube 224.

In one embodiment, immediately following the release of the pressurized gas from the gas container 228 into the pressure chamber 216 and prior to the launch of the rocket 226, the combination of the gas pressure in the pressure chamber 216 in addition to the spring pressure of the compression spring 268 on the cartridge carrier 214 within the pressure chamber 216, will cause the cartridge carrier 214 to be raised slightly. As the cartridge carrier 214 is raised out of the pressure chamber 216 slightly the shaft 262 of the cartridge carrier 214, which also is present in an internal cam track 282 in the sidewall of the launch tower 220, as shown in FIGS. 19 and 21, will force the launch tower 220 to be pivoted slightly backwards at an angle of approximately 15° to 30°. The internal cam track 282, however, is fairly short and will operate as a stop for the cartridge carrier 214 so that the cartridge carrier 214 is only raised an appropriate amount out of the pressure chamber 216 prior to launch. Preferably at the point where the shaft 262 of the cartridge carrier 214 engages the stop of the internal cam track 282 of the launch tower 220 and the launch tower 220 stops pivoting, the pressure within the pressure chamber 216 will be sufficient to rupture the burst membrane 222 and launch the rocket 226.

If, however, the burst membrane 222 does rupture and the pressure chamber 216 is retained at high pressure, the rocket launching system 210 has a means for safely releasing the pressurized gas from the pressure chamber 216. In one embodiment, the user can release the pressure from the pressure chamber 216 by tilting the launch tower 220 away from the launch tube 224 and rocket 226. When the launch tower 220 is pivoted backwards the cam surface 266 of the launch tower 220 will lift the cartridge carrier 214 back out of the pressure chamber 216 due to the engagement of the cam surface 266 of the launch tower 220 with the shoulder 264 of the cartridge carrier 214. When the launch tower 220 is tilted sufficiently backwards, such as shown in FIGS. 23 and 24, a relief 280 in the cartridge carrier 214 will allow the pressurized gas in the pressure chamber 216 to be safely released. The relief 280 in the cartridge carrier 214 may be in the form of an aperture 280 in the sidewall of the cartridge carrier 214 as shown in FIG. 19, or the outside diameter of the cartridge carrier 214 may be stepped down, and when the cartridge carrier 214 is raised sufficiently above the seal 272 such that the relief 280 is outside the pressure chamber 216, the gas may be released out of the relief 80 in the cartridge carrier 214.

Following the launch of a rocket 226 as described above, the launch tower 220 can be pivoted away from the launch tube 224 as explained above and shown in FIGS. 23 and 24 to expose the gas container 228 connected to the cartridge carrier 214. At that point, or following the release of the pressure from the pressure chamber 216 if the burst membrane 222 does not rupture, the gas container 228 can be removed from the cartridge carrier 214.

As shown in FIGS. 19 and 25, the rocket 226 may merely comprise a rocket body 284 having a first end 286 with a nose cone 288, and a second end 290 with aerodynamic stabilizers 292. The rocket body 284 may be comprised of a hollow tube such that the second end 290 of the rocket body 284 can be placed over the launch tube 224 for preparing the rocket 226 for launch. As such, the rocket 226 is releasably connected to the launch tube 224. In a preferred embodiment, the nose cone 288 can be formed of a soft or resilient material, such as foam, to soften the landing of the rocket 226.

Another embodiment of the rocket 226 is shown in FIGS. 27-29. In this embodiment, the rocket 226 has drone features connected to the second end 290 of the rocket body 284. The drone features may include a control system (not shown, but preferably housed in the nose cone 288) including a printed circuit board and multiple sensors which may include, but are not limited to, a 3-axis accelerometer, a gyroscope, a barometric pressure sensor, a Global-Positional System sensor, a radio-frequency communication device and a Bluetooth communication device. The sensors may allow the tracking and recording of various performance metrics by the rocket launching system 10, such as maximum speed, maximum height and flight duration.

The drone features may include a plurality of propellers 293 powered by one or more propulsion motors 294. The propellers 293 and propulsion motors 294 are attached to the rocket body 284 by arms 295. In one embodiment a slidable collar 296 is connected around the rocket body 284 and the arms 295 are connected to the slidable collar 296. Pivot arms 297 are also provided and connect between the arms 295 and a lower fixed collar 298. The combination of the slidable collar 296, arms 295, pivot arms 297 and fixed collar 298 forms a three-bar mechanism that allows the drone features to transition from the collapsed state, as shown in FIG. 27, which would be the state used for launch, to the open state as shown in FIG. 29. FIG. 28 shows a transition from the collapsed state to the open state. The propellers 293 allow the user to fly the rocket 226 back to the ground after the rocket 226 has launched and generally after the rocket 226 reaches its apex following launch. The user operates the controller 26 to fly the rocket 226 back to the ground as desired.

One embodiment of the controller 26 is shown in FIG. 30. This embodiment of the controller 26 is operable by a user and controls various operations of the launch and subsequent flight of the rocket 226. The controller 26 may include an LCD screen 198 for displaying various launch and flight information. In particular, data gathered from the aforementioned sensors and components of the control system can be displayed on the LCD screen 198. A first control 42, or an arming control, initiates a pre-launch sequence. Such a sequence can include audible sounds, such as rocket sounds or a numerical countdown, produced by the controller 26, rocket 226 and/or launch base 212. The pre-launch sequence can also include the operation of various lights on the controller 26, rocket 226 and/or launch base 212. The launching base 212 and/or rocket 226 can also generate a visible gas, or fog, during the pre-launch sequence by vaporizing fluids, such as fog juice.

A second control 44 which may be operable only after the pre-launch sequence, initiates the rocket 226 launch using the pressurized gas container 228, as described above. Following the rocket launch, the propellers 293 are controllable by the user. In particular, drone-style controls 199 are used to wirelessly control flight operations of the propellers of the rocket. In some implementations, the drone-style controls 199 can control pitch, roll, yaw, trim, altitude and speed characteristics of the propellers. The rocket with propellers may also include an autonomous mode that automatically brings the rocket into contact with the ground surface. Such a mode may be activated by a loss of wireless signal between the controller 26 and the rocket 226.

Several alternative embodiments and examples have been described and illustrated herein. A person of ordinary skill in the art would appreciate the features of the individual embodiments, and the possible combinations and variations of the components. A person of ordinary skill in the art would further appreciate that any of the embodiments could be provided in any combination with the other embodiments disclosed herein. Additionally, the terms “first,” “second,” “third,” and “fourth” as used herein are intended for illustrative purposes only and do not limit the embodiments in any way. Further, the term “plurality” as used herein indicates any number greater than one, either disjunctively or conjunctively, as necessary, up to an infinite number. Additionally, the term “having” as used herein in both the disclosure and claims, is utilized in an open-ended manner.

It will be understood that the invention may be embodied in other specific forms without departing from the spirit or central characteristics thereof. The present examples and embodiments, therefore, are to be considered in all respects as illustrative and not restrictive, and the invention is not to be limited to the details given herein. Accordingly, while the specific embodiments have been illustrated and described, numerous modifications come to mind without significantly departing from the spirit of the invention and the scope of protection is only limited by the scope of the accompanying Claims.

Number	Date	Country
62423243	Nov 2016	US
62473050	Mar 2017	US
62548491	Aug 2017	US

ROCKET AND LAUNCHING SYSTEM

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Date Published

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CPC

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Abstract

Description

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CROSS-REFERENCE TO RELATED APPLICATIONS

Provisional Applications (3)