CA2587212C - Balloon launch assembly for space rocket - Google Patents
Balloon launch assembly for space rocket Download PDFInfo
- Publication number
- CA2587212C CA2587212C CA 2587212 CA2587212A CA2587212C CA 2587212 C CA2587212 C CA 2587212C CA 2587212 CA2587212 CA 2587212 CA 2587212 A CA2587212 A CA 2587212A CA 2587212 C CA2587212 C CA 2587212C
- Authority
- CA
- Canada
- Prior art keywords
- balloon
- rocket
- launch
- hybrid
- launch tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
- B64G1/005—Air launch
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- General Engineering & Computer Science (AREA)
- Tents Or Canopies (AREA)
Abstract
A simple rocket launching assembly includes a hot air balloon carrying a launch tube, which extends completely through the center of the balloon. A jet propulsion system in the bottom of the launch tube is used to propel the assembly to a launch location. A plurality of gas cells are connected to a platform extending radially outwardly from the launch tube and when inflated they increase the buoyancy of the assembly. The cells are housed in a tent, the bottom end of which is attached to the platform. The tent stabilizes the cells against the launch tube.
Description
2 DESCRIPTION OF THE INVENTION
BACKGROUND
Commercial launch of space rockets and space cargoes is still in its infancy and until now there has not been any commercially viable space launch venture without significant governmental subsidies. Numerous factors are responsible. One of them is the high insurance cost because nearly 5% of all launches failed and failed catastrophically, mostly at the ignition and lift-off, which invariably resulted in fire that destroyed the launch vehicle as well as the valuable cargoes. A safer method would be to use a buoyant balloon system as a high altitude launch pad. A space rocket would only start the ignition and lift-off at an altitude of ten of thousands of feet above ground, thus allowing plenty of time for a recovery of the valuable cargoes by mean of parachutes should a launching failure occur.
Another factor is that the present space vehicles are venerable single-use rockets, it would be very difficult for them to become anymore economical.
For any space launch system to be commercially viable it would have to be not only affordable but also that it can be done routinely and safely.
Numerous balloon based rocket launch systems have been proposed and experimented. But none has gone beyond the task of launching relatively small space rockets using unrecoverable weather balloons. This multi-use buoyant gas and hot air hybrid balloon launch system proposes a lower-cost yet safer method for the launch of up to mid-size rockets into space, thus it promises improved economical viability to the commercial space ventures.
Typical balloons and airships are shown, for example, in the following Canadian patents:
And United States of America patents:
BACKGROUND
Commercial launch of space rockets and space cargoes is still in its infancy and until now there has not been any commercially viable space launch venture without significant governmental subsidies. Numerous factors are responsible. One of them is the high insurance cost because nearly 5% of all launches failed and failed catastrophically, mostly at the ignition and lift-off, which invariably resulted in fire that destroyed the launch vehicle as well as the valuable cargoes. A safer method would be to use a buoyant balloon system as a high altitude launch pad. A space rocket would only start the ignition and lift-off at an altitude of ten of thousands of feet above ground, thus allowing plenty of time for a recovery of the valuable cargoes by mean of parachutes should a launching failure occur.
Another factor is that the present space vehicles are venerable single-use rockets, it would be very difficult for them to become anymore economical.
For any space launch system to be commercially viable it would have to be not only affordable but also that it can be done routinely and safely.
Numerous balloon based rocket launch systems have been proposed and experimented. But none has gone beyond the task of launching relatively small space rockets using unrecoverable weather balloons. This multi-use buoyant gas and hot air hybrid balloon launch system proposes a lower-cost yet safer method for the launch of up to mid-size rockets into space, thus it promises improved economical viability to the commercial space ventures.
Typical balloons and airships are shown, for example, in the following Canadian patents:
And United States of America patents:
3 DESCRIPTION OF THE PRIOR ARTS
Hybrid balloon system is a type of balloon that has separate chambers for a non-heated lifting gas such as helium as well as a heated lifting gas such as hot air.
This type of balloon has been around for a long time. Its creator Jean-Francois Pilatre de Rozier first used it in the 1700s. Basically it was a hot air balloon with a large hydrogen cell inside.
Few improvements have been made since De Rozier. A modern version of this type of balloon can be seen in the Breitling Orbiter 3 that rose to 39,000 feet and circled the earth in 20 days in 1999.
Advance in gas cell material has allowed CargoLifter AG of Germany in 2001, to build a 200-foot-diameter helium cell that can lift 75 tons at ground level.
The use of balloons in launching of space rockets is not a new concept. Cmdr.
Lee Lewis, Cmdr. G. Halvorson, S. F. Singer, and James Allen developed the concept Rockoon (Rocket/Balloon) in 1949. 8 years later in 1957, US AirForce's experimental project Farside using a four-stage rocket hung below a 3,750,000 cubic feet balloon and sent it to an altitude of 4000 miles above the earth.
Most recently, Da Vinci Project planned in 2004 to launch their Wild Fire Mark IV space rocket aboard a helium balloon but they never could.
Canadian Pat. No. 2391252 referred above was issued to COLTING for a spherical shape airship that has limited mobility. It is useful in communication and high altitude weather research. This airship essentially has no load-bearing structure to support significant weight as the present balloon system.
Canadian Pat. 2518970 issued to PEDRETTI is for an over-pressurized blimp that has been reinforced with tendon cables to provide greater rigidity thus increasing its weight-bearing capacity without which an airship would suffer a sagging to its general body when carrying heavy load. A tense elongated aerial structure such as this lifting body would flex violently
Hybrid balloon system is a type of balloon that has separate chambers for a non-heated lifting gas such as helium as well as a heated lifting gas such as hot air.
This type of balloon has been around for a long time. Its creator Jean-Francois Pilatre de Rozier first used it in the 1700s. Basically it was a hot air balloon with a large hydrogen cell inside.
Few improvements have been made since De Rozier. A modern version of this type of balloon can be seen in the Breitling Orbiter 3 that rose to 39,000 feet and circled the earth in 20 days in 1999.
Advance in gas cell material has allowed CargoLifter AG of Germany in 2001, to build a 200-foot-diameter helium cell that can lift 75 tons at ground level.
The use of balloons in launching of space rockets is not a new concept. Cmdr.
Lee Lewis, Cmdr. G. Halvorson, S. F. Singer, and James Allen developed the concept Rockoon (Rocket/Balloon) in 1949. 8 years later in 1957, US AirForce's experimental project Farside using a four-stage rocket hung below a 3,750,000 cubic feet balloon and sent it to an altitude of 4000 miles above the earth.
Most recently, Da Vinci Project planned in 2004 to launch their Wild Fire Mark IV space rocket aboard a helium balloon but they never could.
Canadian Pat. No. 2391252 referred above was issued to COLTING for a spherical shape airship that has limited mobility. It is useful in communication and high altitude weather research. This airship essentially has no load-bearing structure to support significant weight as the present balloon system.
Canadian Pat. 2518970 issued to PEDRETTI is for an over-pressurized blimp that has been reinforced with tendon cables to provide greater rigidity thus increasing its weight-bearing capacity without which an airship would suffer a sagging to its general body when carrying heavy load. A tense elongated aerial structure such as this lifting body would flex violently
4 in turbulence weather while a balloon system, which has a more compact shape with centralizing load-bearing tendons, tends not flex at all.
US Pat. No. 6142414 issued to DOOLITTLE presents a spherical airship having a rotor assembly system of heavy design, comprising of very large axle with very large mast and very long cables. Doolittle has none of the low weight construction represented in the present hybrid balloon system.
US Pat. No. 7131613 issued to KELLY presents vertically lift-off airship platform with numerous segments and wings built for aerodynamic flight. Kelly's method for launching of space rockets is similar to the launching of missiles from a warplane.
Kelly does not have a vertical rocket launching capacity of this present balloon system.
None of the above inventions and patents, taken either singly or in combination, is seen to describe the present invention as claimed.
SUMMARY OF THE INVENTION
The invention pertains to a hybrid balloon system utilizing a combination of a propulsion engine system, a buoyant gas, in the form of helium, and heated air to raise a space rocket to a higher altitude. The purpose is simply to put a space rocket up to where it has a safety margin and where the air is much thinner, thus posing less drag to the rocket during its flight toward space.
Accordingly, a hybrid balloon system employing a plurality of buoyant gas cells, arranged in symmetry about a rocket-housing tube and enclosed within a hot air balloon system that is also equipped with a jet engine is provided.
More specifically stated, the invention provides a hybrid balloon system of the above character employing elongated helium gas cells, which are bundled together inside a pressure resistance tent in a parallel relation, and around a centrally positioned rocket-housing tube.
The distinctive pressure resistance tent featured in this invention prevents the helium cells from sloshing about inside the hot air balloon as well as provides a proper guiding structure for them to expand. With this feature the hybrid balloon launch system can be very economical to manufacture, operate and maintain.
It is also an object of this invention to provide a hybrid balloon system of the above construction that has a low center of gravity.
BRIEF DESCRIPTION OF THE DRAWINGS
The description of the invention becomes clearer with drawings, which form a part of this specification.
FIG. 1 is the side cross sectional view of the balloon system at ground level showing partially inflated helium cells.
FIG. 2 is the side cross sectional view of the balloon system at a high altitude showing the expansion of the helium cells.
FIG. 3 is the top semi-transparent view of the balloon system showing a rocket housing tube bundled within four helium cells within a pressure-resistance cylindrical shaped tent.
The radial lines on the balloon's envelope represent its load tendons.
FIG. 4 is the bottom view of the balloon system showing the interior of the hot air balloon through its mouth.
DETAIL DESCRIPTION OF THE INVENTION
FIGs. 1,2,3 and 4, respectively, designate four helium gas cells I of elongated construction that are arranged in parallel relation and secured rigidly at their bases to a frame structure that extends out from a rocket launch tube 2 (FIGs. l and 2). The main portion of which has a shape resembling the shape of an inverted cone. This frame structure thus provided would also serve as a water tank 3. It will be stated here that the features of constructions related to this compartment maybe of the same general construction as those embodied in the launch tube.
As well as depicted in FIGs. 1 and 2, is the pressure resistance tent 4, cylindrical in form and approximately equal in length to the helium gas cells 1 at their limit of expansion. It would be made up of a thermal resistance light fabric meshed with load tendons. It extends in a length to contain and to girdle the helium gas cells 1 with the launch tube 2 therein. The top end of the pressure resistant tent 4 has a centrally located round collar 5, that would fit loosely around the launching tube 2 to facilitate the inflation or deflation of the elongated helium gas cells 1 in a general longitudinal direction. Loose straps 6 at the base of the pressure resistant tent 4 would prevent it from being pulled over the helium gas cells 1. It will also be stated here that the features of constructions related to this pressure resistance tent maybe of the same general construction as those embodied in the hot air balloon.
The rocket launch tube 2, best illustrated in FIGs. 1 and 2, has an interior diameter that is substantially uniform in cross-section from bottom to the top and has an extending platform 7 adapted to receive a space rocket. This launch tube 2 is sized and shaped to allow a space rocket 8 to slide longitudinally upward and to be expelled from it via an opening top 9. It is made up of heat, pressure and fire resistance material such as titanium or aluminum alloys that would substantially retain its structural integrity under the explosive force of a rocket blast.
In addition, a plurality of water sprinkler nozzles 10 is imbedded on the interior sidewall of the launch tube (not shown) as well as on its exterior sidewall at the top opening 9. During the ignition of a space rocket, the intense heat generated by the rocket's blast would boil off water droplets that will be sprayed into the launch tube 2 by these sprinkler nozzles 10 thus cooling off the exhausting gas to within tolerable temperatures.
While the balloon system is in an ascending mode, a vertically mounted jet propulsion system 11 that is positioned below the space rocket's extending platform 7 would contribute a downwardly thrust as shown in FIGs. 1 and 2.
Still in reference to the FIGs. I and 2, a conventional hot air balloon of very large size is provided. In accordance to the art it comprises an envelope 12, suspension cables assemblies, 13a and 13b, and a burner assembly. A fuel supply associated with said burner is also provided. For clarity purpose, the conventional burner system that may be suspended from the mouth 14 of the envelope or rigidly supported on its interior cablesl3b is not shown in the drawings.
The said envelope 12 is ideally composed of a lightweight material such as ripstop nylon or dacron fabric with high strength load tendons 15, which runs from the top to the bottom of the envelope 12, carrying the pressure load of the system.
A plurality of mechanical fasteners 16, in an encircling pattern and in a way that conforms to the natural contour of a balloon and where that is no substantial stress concentration on the envelope 12, secures it to the launch tube's wall at their intersection.
The said envelope 12 also has a carbonaceous fibers flame and scorch protective layer 17 on its exterior upper portion around its crown (FIG. 3) in addition to the other known to the art flame and scorch protective layer that coats its interior (not shown).
With reference to FIGs. 1, 2 and 4, a conventional suspension cables assembly 13a connects the launch tube 2 at its base 18 to the envelope's mouth 14.
Additional suspension cables assembly 13b within the hot air balloon further helps spread the load evenly to the other parts of the balloon's envelope 12 as shown in FIGs. 1 and 2.
Although the invention has been described in connection with a preferred embodiment. It should be understood that various modifications, additions and alterations may be made to the invention by one skilled in the art without departing from the spirit and scope of the invention as defined in the appended claims.
US Pat. No. 6142414 issued to DOOLITTLE presents a spherical airship having a rotor assembly system of heavy design, comprising of very large axle with very large mast and very long cables. Doolittle has none of the low weight construction represented in the present hybrid balloon system.
US Pat. No. 7131613 issued to KELLY presents vertically lift-off airship platform with numerous segments and wings built for aerodynamic flight. Kelly's method for launching of space rockets is similar to the launching of missiles from a warplane.
Kelly does not have a vertical rocket launching capacity of this present balloon system.
None of the above inventions and patents, taken either singly or in combination, is seen to describe the present invention as claimed.
SUMMARY OF THE INVENTION
The invention pertains to a hybrid balloon system utilizing a combination of a propulsion engine system, a buoyant gas, in the form of helium, and heated air to raise a space rocket to a higher altitude. The purpose is simply to put a space rocket up to where it has a safety margin and where the air is much thinner, thus posing less drag to the rocket during its flight toward space.
Accordingly, a hybrid balloon system employing a plurality of buoyant gas cells, arranged in symmetry about a rocket-housing tube and enclosed within a hot air balloon system that is also equipped with a jet engine is provided.
More specifically stated, the invention provides a hybrid balloon system of the above character employing elongated helium gas cells, which are bundled together inside a pressure resistance tent in a parallel relation, and around a centrally positioned rocket-housing tube.
The distinctive pressure resistance tent featured in this invention prevents the helium cells from sloshing about inside the hot air balloon as well as provides a proper guiding structure for them to expand. With this feature the hybrid balloon launch system can be very economical to manufacture, operate and maintain.
It is also an object of this invention to provide a hybrid balloon system of the above construction that has a low center of gravity.
BRIEF DESCRIPTION OF THE DRAWINGS
The description of the invention becomes clearer with drawings, which form a part of this specification.
FIG. 1 is the side cross sectional view of the balloon system at ground level showing partially inflated helium cells.
FIG. 2 is the side cross sectional view of the balloon system at a high altitude showing the expansion of the helium cells.
FIG. 3 is the top semi-transparent view of the balloon system showing a rocket housing tube bundled within four helium cells within a pressure-resistance cylindrical shaped tent.
The radial lines on the balloon's envelope represent its load tendons.
FIG. 4 is the bottom view of the balloon system showing the interior of the hot air balloon through its mouth.
DETAIL DESCRIPTION OF THE INVENTION
FIGs. 1,2,3 and 4, respectively, designate four helium gas cells I of elongated construction that are arranged in parallel relation and secured rigidly at their bases to a frame structure that extends out from a rocket launch tube 2 (FIGs. l and 2). The main portion of which has a shape resembling the shape of an inverted cone. This frame structure thus provided would also serve as a water tank 3. It will be stated here that the features of constructions related to this compartment maybe of the same general construction as those embodied in the launch tube.
As well as depicted in FIGs. 1 and 2, is the pressure resistance tent 4, cylindrical in form and approximately equal in length to the helium gas cells 1 at their limit of expansion. It would be made up of a thermal resistance light fabric meshed with load tendons. It extends in a length to contain and to girdle the helium gas cells 1 with the launch tube 2 therein. The top end of the pressure resistant tent 4 has a centrally located round collar 5, that would fit loosely around the launching tube 2 to facilitate the inflation or deflation of the elongated helium gas cells 1 in a general longitudinal direction. Loose straps 6 at the base of the pressure resistant tent 4 would prevent it from being pulled over the helium gas cells 1. It will also be stated here that the features of constructions related to this pressure resistance tent maybe of the same general construction as those embodied in the hot air balloon.
The rocket launch tube 2, best illustrated in FIGs. 1 and 2, has an interior diameter that is substantially uniform in cross-section from bottom to the top and has an extending platform 7 adapted to receive a space rocket. This launch tube 2 is sized and shaped to allow a space rocket 8 to slide longitudinally upward and to be expelled from it via an opening top 9. It is made up of heat, pressure and fire resistance material such as titanium or aluminum alloys that would substantially retain its structural integrity under the explosive force of a rocket blast.
In addition, a plurality of water sprinkler nozzles 10 is imbedded on the interior sidewall of the launch tube (not shown) as well as on its exterior sidewall at the top opening 9. During the ignition of a space rocket, the intense heat generated by the rocket's blast would boil off water droplets that will be sprayed into the launch tube 2 by these sprinkler nozzles 10 thus cooling off the exhausting gas to within tolerable temperatures.
While the balloon system is in an ascending mode, a vertically mounted jet propulsion system 11 that is positioned below the space rocket's extending platform 7 would contribute a downwardly thrust as shown in FIGs. 1 and 2.
Still in reference to the FIGs. I and 2, a conventional hot air balloon of very large size is provided. In accordance to the art it comprises an envelope 12, suspension cables assemblies, 13a and 13b, and a burner assembly. A fuel supply associated with said burner is also provided. For clarity purpose, the conventional burner system that may be suspended from the mouth 14 of the envelope or rigidly supported on its interior cablesl3b is not shown in the drawings.
The said envelope 12 is ideally composed of a lightweight material such as ripstop nylon or dacron fabric with high strength load tendons 15, which runs from the top to the bottom of the envelope 12, carrying the pressure load of the system.
A plurality of mechanical fasteners 16, in an encircling pattern and in a way that conforms to the natural contour of a balloon and where that is no substantial stress concentration on the envelope 12, secures it to the launch tube's wall at their intersection.
The said envelope 12 also has a carbonaceous fibers flame and scorch protective layer 17 on its exterior upper portion around its crown (FIG. 3) in addition to the other known to the art flame and scorch protective layer that coats its interior (not shown).
With reference to FIGs. 1, 2 and 4, a conventional suspension cables assembly 13a connects the launch tube 2 at its base 18 to the envelope's mouth 14.
Additional suspension cables assembly 13b within the hot air balloon further helps spread the load evenly to the other parts of the balloon's envelope 12 as shown in FIGs. 1 and 2.
Although the invention has been described in connection with a preferred embodiment. It should be understood that various modifications, additions and alterations may be made to the invention by one skilled in the art without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (9)
1. A hybrid balloon launch system for a space rocket comprising of a hybrid hot air balloon.
2. The hybrid balloon launch system of claim 1 further comprised a centrally positioned rocket launch tube assembly.
3. The hybrid balloon launch system of claim 1 further comprised a plurality of elongated buoyant gas cells that are bundled together inside a pressure resistance tent in a parallel relation and around the said centrally positioned rocket launch tube assembly.
4. The hybrid balloon launch system of claim 1 further has an envelope that is equipped with a fire and scorch resistance material on its upper exterior surface.
5. The hybrid balloon launch system of claim 1 further states that an inexpensive buoyant gas such as ammonia may be used in the place of the heated air.
6. The hybrid balloon launch system of claim 1 further comprised an additional suspension cables assembly that is within the said hot air balloon to spread its heavy load.
7. The rocket launch tube assembly mentioned in claim 2 further has an opening top.
8. The rocket launch tube assembly mentioned in claim 2 further comprised a cooling system such as a water sprinkler on its interior and on its exterior upper portion.
9. The rocket launch tube assembly mentioned in claim 2 further comprised at least a mean of storing a coolant such as water.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA 2587212 CA2587212C (en) | 2007-04-24 | 2007-04-24 | Balloon launch assembly for space rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA 2587212 CA2587212C (en) | 2007-04-24 | 2007-04-24 | Balloon launch assembly for space rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2587212A1 CA2587212A1 (en) | 2008-10-24 |
| CA2587212C true CA2587212C (en) | 2010-06-08 |
Family
ID=39876359
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA 2587212 Expired - Fee Related CA2587212C (en) | 2007-04-24 | 2007-04-24 | Balloon launch assembly for space rocket |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2587212C (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2394489B1 (en) * | 2010-09-27 | 2013-12-12 | Fundacion Centauri | SPACE VEHICLE MULTIETAPA TRANSFER TO LOW TERRESTRIAL ORBIT |
| US20160001899A1 (en) * | 2014-07-07 | 2016-01-07 | Daniel J. Adcock | Gas Envelope Propulsion System and Related Methods |
-
2007
- 2007-04-24 CA CA 2587212 patent/CA2587212C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CA2587212A1 (en) | 2008-10-24 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20210426 |