Ordnance – Rocket launching – Having tubular guide means
Reexamination Certificate
1999-11-22
2001-11-20
Jordan, Charles T. (Department: 3641)
Ordnance
Rocket launching
Having tubular guide means
C089S001818, C089S001810
Reexamination Certificate
active
06318229
ABSTRACT:
BACKGROUND OF THE INVENTION
Rockets of a large size burn a tremendous amount of fuel after ignition or light-off in order to merely lift the rocket from a launching pad or platform. In certain cases, 24,000 pounds of fuel are burned every second. Simply eliminating two seconds of burn to propel a rocket into space would represent a tremendous savings in fuel. Such savings would translate into a decrease in the expense of such fuel and the addition of payload to the rocket structure.
U.S. Pat. Nos. 3,425,316 and 4,643,072 show submarine ejection systems in which compressed gases are used to force a rocket from a tube.
U.S. Pat. Nos. 4,185,538 and 4,671,163 describe tube launched missiles in which gases from a compressor or generated by combustion are used to force the missile to a launched condition.
U.S. Pat. No. 3,438,303 shows a system of launching a missile in which an outer auxiliary charge is provided.
U.S. Pat. No. 4,344,592 employs a launching tower in which an auxiliary liquid-propellant motor is used to move a piston, which pushes a rocket through the bore of the tower until the rocket is able to fire its own motors while in motion.
A system for launching rockets which utilizes the waste gas energy generated during ignition, to propel the rocket would be a notable advance in the aeronautical field.
BRIEF SUMMARY OF THE INVENTION
The present invention relates to a system for imparting velocity to a rocket during its initial firing.
The system of the present invention utilizes a container having a bottom and a side wall portion extending outwardly from the bottom. The side wall portion terminates in a peripheral edge. The bottom and side wall portion form a chamber having an opening formed at the peripheral edge. The container may be of any size commensurate with the rocket being launched in conjunction with the system of the present invention.
A platform is also employed in the present invention and includes a first surface for supporting the rocket and a second surface which faces a chamber of the container. The platform is movable along the container side wall portion between the bottom of the container and the peripheral edge of the side wall portion of the container. The platform is initially held by support means at a predetermined level above the bottom of the container. In certain instances the support means may take the form of the rim portion. In other instances, a separate support mechanism may be employed for the platform. Moreover, the rim portions may telescope from the bottom portion of the container. One section of the telescoping rim portion includes the platform which supports the rocket.
Conduit means is also found in the present invention for directing exhaust material from the rocket to the chamber of the container between the second surface of the platform and the bottom of the container. Such exhaust material creates a fluid pressure on the platform second surface to urge the platform away from the bottom, as well as the rocket supported thereupon. A stop limits the travel of the platform relative to the peripheral edge of the container. That is to say, the stop prevents the platform from leaving the chamber of the container. Conduit means may also be formed of a housing connected to the platform. The housing may include at least one opening which communicates with the exhaust material of the rocket. At least one door in the housing opens under pressure from the exhaust material to permit the exhaust material of the rocket to enter the chamber of the container.
In one embodiment of the invention the fluid located in the chamber may be in the form of a liquid, such as water. The rocket exhaust gases entering the chamber would heat the liquid to produce steam which, in turn, exerts a pressure on the second surface of the platform raising it relative to the bottom of the container. The liquid entering the chamber may be preheated by an auxiliary heating unit to permit the more rapid formation of steam when needed to launch a particular rocket. In addition, a heat source, separate from the rocket exhaust, may also be employed to elevate the temperature of the liquid in the chamber.
Vent means is also found in the present invention for relieving the fluid pressure within the chamber and from the second surface of the platform. Such a vent means may take the form of relief valves, or fixed vent openings through the side wall of the chamber at a level which would allow confinement of the liquid to the chamber of the container. Thus, such vent means relieves fluid pressure from the chamber such that the rocket supported by the platform is able to move from the bottom of the chamber to its outer most position during a period of time which the rocket requires to generate sufficient power to depart from the platform. Of course, a rate of venting and, consequently, the rate of lifting of the platform may be easily precalculated.
It may be apparent that a novel and useful system for imparting velocity to a launching rocket has been herein described.
It is therefore an object of the present invention to provide a system for boosting the velocity of a rocket which recovers the normally wasted exhaust gases generated by a rocket during its initial firing.
Another object of the present invention is to provide a system for boosting the velocity of a rocket to increase the range or payload of the rocket through the recovery of normally wasted exhaust gases.
A further object of the present invention is to provide a system for boosting the velocity of a rocket which conserves the fuel needed to launch the rocket, thus, saving a substantial amount of weight and reducing the cost of launching a particular rocket.
Another object of the present invention is to provide a system for increasing the velocity of the rocket which utilizes a container that adds a degree of safety to the launching of a rocket.
The invention possesses other objects and advantages especially as concerns particular characteristics and features thereof which will become apparent as the specification continues.
Reference is made to the following detailed drawings representing an aspect of the invention.
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Nevels Joel P.
Nevels Margaret H.
Bielen, Jr. Theodore J.
Chambers Troy
Jordan Charles T.
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