WO2006119056A2 - Lighter than air supersonic vehicle - Google Patents

Lighter than air supersonic vehicle Download PDF

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Publication number
WO2006119056A2
WO2006119056A2 PCT/US2006/016336 US2006016336W WO2006119056A2 WO 2006119056 A2 WO2006119056 A2 WO 2006119056A2 US 2006016336 W US2006016336 W US 2006016336W WO 2006119056 A2 WO2006119056 A2 WO 2006119056A2
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WO
WIPO (PCT)
Prior art keywords
vehicle
load envelope
framework
pumps
lift gas
Prior art date
Application number
PCT/US2006/016336
Other languages
French (fr)
Other versions
WO2006119056A3 (en
Inventor
Alfred Differ
Original Assignee
General Orbital Corporation
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Orbital Corporation filed Critical General Orbital Corporation
Priority to JP2008509189A priority Critical patent/JP2008539131A/en
Publication of WO2006119056A2 publication Critical patent/WO2006119056A2/en
Publication of WO2006119056A3 publication Critical patent/WO2006119056A3/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft

Definitions

  • This invention pertains to lighter than air vehicles and methods for placing crew and cargo in orbit.
  • US 6,119,983 and US 6,357,700 teach using an energetic lifting gas, hydrogen, as fuel to power a spherical airship/spaceship to orbit.
  • the airship/spaceship taught therein travels from the surface of the earth all the way to orbit.
  • the spherical shape is not ideal because high drag diminishes efficiency.
  • the present inventor is not aware of any prior art where a lighter than air vehicle is optimized for supersonic flight in the upper atmosphere and space.
  • the present inventor is not aware of any lighter than air vehicle that has a shape for efficient supersonic flight.
  • An object of the invention is to provide a means to transport crew and cargo from about 30,000 feet to orbit efficiently without subjecting them to heavy thrust loads associated with conventional spacecraft.
  • a further object of the invention is to provide a lighter than air space vehicle 200 with the ability to start at subsonic speed at an altitude of about 30 km and efficiently reach orbital speed and altitude, deliver payloads and a crew, cruise for a determined period, and then slow down to subsonic speed while performing a controlled descent to an altitude near 30 kilometers.
  • a feature of the space vehicle 200 is that its shape improves the lift/drag ratio and allows the space vehicle 200 greater efficiency at supersonic speeds.
  • Another feature of the invention is that the space vehicle 200 can safely descend from orbital altitude and speed using the broad surface of the load envelope 1 for heat dissipation and remain reusable.
  • Another feature of the space vehicle 200 is the ability to dock with other aircraft 100 and spacecraft.
  • Figure 1 depicts an ascent vehicle 100.
  • Figure 2 depicts an ascent vehicle's 100 flight profile.
  • Figure 3 depicts two ascent vehicles 100 performing a docking maneuver.
  • Figure 4 depicts the vehicles' 100, 200 internal components.
  • Figure 5 depicts a space vehicle 200.
  • Figure 6 depicts a space vehicle's 200 flight profile.
  • Figure 7 depicts a space vehicle's 200 low cruise approach toward an ascent vehicle 100.
  • Figure 8 depicts a space vehicle 200 docking with an ascent vehicle 100.
  • the present invention comprises the space vehicle 200 of Figure 5, which is optimized for supersonic speeds and altitudes from 30,000 feet to space.
  • Structural rigidity and load transfer are the main functions of the load envelope 1. Passage through mach one and then to higher speeds place dynamic pressures on the outside of the envelope 1 with the potential to distort its shape. The shape of this envelope 1 accounts for this through the type and placement of a framework 7, and the ability to change the pressures in the framework 7.
  • the preferred shape for the load envelope 1 is something like a wedge.
  • the cone angle on the wedge is somewhere around 15 degrees and will be determined by analysis with a good CFD application.
  • the framework 7 for this vehicle may comprise carbon composite poles and connectors in certain sections.
  • the framework 7 will be a set of pressurized tubes of fabric similar to what is used for the load envelope. A variety of fabrics will be used because a variety of pressures are likely to be needed.
  • Baffles 5 will perform the duty of separating lift cells 3 and ballonet cells 2. Pumps 4, 6 will be present to remove lift gas from cells 3 and store it in pressurized tanks 8. These units will help reduce the over pressurization of the load envelope 1 from within when the vehicle 200 is operating at very high altitudes and relatively low velocities. 3. Power Storage, Production, and Distribution
  • the space vehicle 200 will use equipment for power storage and production, and it will also include an AC grid.
  • a DC grid will be broken up into smaller regional grids with AC paths connecting them across large distances. This will require AC/DC converters, RFI protection measures, and other well-known components.
  • the space vehicle 200 has systems on board to produce thrust. Small chemical rockets and electric plasma/gas thrusters will be required to manage attitude changes.
  • this vehicle will have relatively large chemical rockets 9 attached that will push it to a high altitude and a high speed. These rockets will push the vehicle to some large percentage of the velocity and altitude needed to achieve orbit. After they are done, electric plasma engines will take over and deliver the rest of the momentum required. The switchover point between operation of the chemical engines 9 and electric engines depends on the design of the vehicle and has yet to be determined. It is very likely that the electric engines won't be used until the space vehicle 200 is almost in orbit.
  • Control units will be attached to the tcp/ip network to control the engines, pumps, and motors.
  • Heat dissipation will be managed much the same as on a satellite, through shading and refrigeration fluids. Thickening and hardening the cabin walls will provide radiation protection.
  • the communications hardware deal with Doppler shifts at orbital velocities, but the payloads will be isolated from that complexity.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Plasma Technology (AREA)
  • Lighters Containing Fuel (AREA)

Abstract

The present invention comprises a lighter than air space vehicle which is optimized for supersonic speeds and altitudes from 30,000 feet to space.

Description

LIGHTER THAN AIR SUPERSONIC VEHICLE
BACKGROUND
This invention pertains to lighter than air vehicles and methods for placing crew and cargo in orbit.
It is well known in the art to launch rockets at high altitude from balloons, taking advantage of the buoyancy of the balloon to gain altitude and save rocket fuel.
US 6,119,983 and US 6,357,700 teach using an energetic lifting gas, hydrogen, as fuel to power a spherical airship/spaceship to orbit. The airship/spaceship taught therein travels from the surface of the earth all the way to orbit. For supersonic speeds the spherical shape is not ideal because high drag diminishes efficiency.
The present inventor is not aware of any prior art where a lighter than air vehicle is optimized for supersonic flight in the upper atmosphere and space.
The present inventor is not aware of any lighter than air vehicle that has a shape for efficient supersonic flight.
SUMMARY
An object of the invention is to provide a means to transport crew and cargo from about 30,000 feet to orbit efficiently without subjecting them to heavy thrust loads associated with conventional spacecraft.
A further object of the invention is to provide a lighter than air space vehicle 200 with the ability to start at subsonic speed at an altitude of about 30 km and efficiently reach orbital speed and altitude, deliver payloads and a crew, cruise for a determined period, and then slow down to subsonic speed while performing a controlled descent to an altitude near 30 kilometers. A feature of the space vehicle 200 is that its shape improves the lift/drag ratio and allows the space vehicle 200 greater efficiency at supersonic speeds. Another feature of the invention is that the space vehicle 200 can safely descend from orbital altitude and speed using the broad surface of the load envelope 1 for heat dissipation and remain reusable.
Another feature of the space vehicle 200 is the ability to dock with other aircraft 100 and spacecraft.
BRBF DESCRIPTION OF THE DRAWINGS
Figure 1 depicts an ascent vehicle 100. Figure 2 depicts an ascent vehicle's 100 flight profile. Figure 3 depicts two ascent vehicles 100 performing a docking maneuver. Figure 4 depicts the vehicles' 100, 200 internal components. Figure 5 depicts a space vehicle 200. Figure 6 depicts a space vehicle's 200 flight profile.
Figure 7 depicts a space vehicle's 200 low cruise approach toward an ascent vehicle 100.
Figure 8 depicts a space vehicle 200 docking with an ascent vehicle 100.
DESCRIPTION
The present invention comprises the space vehicle 200 of Figure 5, which is optimized for supersonic speeds and altitudes from 30,000 feet to space.
Space Vehicle
1. Load Envelope and Framework
2. Gas Containment and Movement
3. Power Storage, Production, and Distribution
4. Thrust Production 5. Command and Control Avionics
6. Life Support
7. Payload Support
1. Load Envelope and Framework
Structural rigidity and load transfer are the main functions of the load envelope 1. Passage through mach one and then to higher speeds place dynamic pressures on the outside of the envelope 1 with the potential to distort its shape. The shape of this envelope 1 accounts for this through the type and placement of a framework 7, and the ability to change the pressures in the framework 7.
The preferred shape for the load envelope 1 is something like a wedge. The cone angle on the wedge is somewhere around 15 degrees and will be determined by analysis with a good CFD application.
The framework 7 for this vehicle may comprise carbon composite poles and connectors in certain sections. Preferably the framework 7 will be a set of pressurized tubes of fabric similar to what is used for the load envelope. A variety of fabrics will be used because a variety of pressures are likely to be needed.
2. Gas Containment and Movement
Baffles 5 will perform the duty of separating lift cells 3 and ballonet cells 2. Pumps 4, 6 will be present to remove lift gas from cells 3 and store it in pressurized tanks 8. These units will help reduce the over pressurization of the load envelope 1 from within when the vehicle 200 is operating at very high altitudes and relatively low velocities. 3. Power Storage, Production, and Distribution
The space vehicle 200 will use equipment for power storage and production, and it will also include an AC grid. A DC grid will be broken up into smaller regional grids with AC paths connecting them across large distances. This will require AC/DC converters, RFI protection measures, and other well-known components.
4. Thrust Production
The space vehicle 200 has systems on board to produce thrust. Small chemical rockets and electric plasma/gas thrusters will be required to manage attitude changes.
In the preferred embodiment, this vehicle will have relatively large chemical rockets 9 attached that will push it to a high altitude and a high speed. These rockets will push the vehicle to some large percentage of the velocity and altitude needed to achieve orbit. After they are done, electric plasma engines will take over and deliver the rest of the momentum required. The switchover point between operation of the chemical engines 9 and electric engines depends on the design of the vehicle and has yet to be determined. It is very likely that the electric engines won't be used until the space vehicle 200 is almost in orbit.
5. Command and Control Avionics
Control units will be attached to the tcp/ip network to control the engines, pumps, and motors.
6. Life Support
Heat dissipation will be managed much the same as on a satellite, through shading and refrigeration fluids. Thickening and hardening the cabin walls will provide radiation protection.
7. Payload Support
The communications hardware deal with Doppler shifts at orbital velocities, but the payloads will be isolated from that complexity.
The foregoing discussion discloses and describes merely exemplary embodiments of the present invention. One skilled in the art will readily recognize from such discussion, and from the accompanying drawings and claims, that various changes, modifications and variations to be made therein without departing from the spirit and scope of the invention as defined in the following claims.

Claims

CLAIMSWhat is claimed is:
1. A lighter than air vehicle comprising: a. a framework; b. propulsion means attached to said framework; c. a load envelope fixedly attached to said framework and optimally shaped for supersonic travel at altitudes higher than 30 kilometers above sea level, said load envelope having a top and a bottom, and containing therein: i. lift gas cells containing a lighter-than-air lift gas adjacent to said load envelope top providing buoyancy to said vehicle, ii. lift gas pumps attached to said load envelope or said framework, iii. plumbing connecting said lift gas cells to said lift gas pumps allowing lift gas to be pumped to and from said lift gas cells to change the buoyancy and attitude of said vehicle, d. lift gas tanks fixedly attached to said load envelope or said framework; e. plumbing connecting said lift gas tanks to said lift gas pumps; f. means for pressurizing said load envelope; g. control systems comprising control units for valves, said lift gas pumps, other pumps, and said propulsion means; and h. means for power production and storage.
2. The vehicle of claim 1, wherein said vehicle is capable of accelerating from subsonic speed to faster than Mach 25.
3. The vehicle of claim 1, wherein said propulsion means comprises: a. chemical rocket engines and electric plasma engines; b. propellant tanks fixedly attached to said framework; and c. plumbing connecting said propellant tanks to said engines.
4. The vehicle of claim 1, wherein said propulsion means comprises: a. large chemical rocket engines and electric plasma engines capable of providing primary acceleration means to said vehicle; b. small chemical rockets, electric plasma thrusters, or gas thrusters capable of altering the attitude of said vehicle; c. propellant tanks fixedly attached to said framework; and d. plumbing connecting said propellant tanks to said engines and thrusters.
5. The vehicle of claim 1, further comprising a shaded, temperature controlled cabin and life support systems capable of supporting manned space flight.
6. The vehicle of claim 1, wherein said control units connect to a tcp/ip network.
7. The vehicle of claim 1, wherein said control system compensates for external loads on said load envelope by causing pumps to pump ballast gas to and from said load envelope or ballonet cells.
8. The vehicle of claim 1, wherein said equipment for power storage and production comprises: a. an AC grid; b. a DC grid comprising a plurality of regional DC grids connected across large distances by AC paths; c. AC/DC converters; and d. RFI protection measures.
9. The vehicle of claim 1, wherein said framework comprises poles and connectors made from high strength to weight ratio materials.
10. The vehicle of claim 1, wherein said framework comprises pressurized fabric tubes, and poles and connectors made from carbon composite materials.
11. The vehicle of claim 1, wherein the shape of said envelope is an approximately 15 degree wedge.
12. The vehicle of claim 1, wherein said load envelope contains baffles connecting said load envelope top to said load envelope bottom.
13. The vehicle of claim 1, wherein said load envelope contains inflatable baffles connecting said load envelope top to said load envelope bottom.
14. The vehicle of claim 1, wherein said lift gas cells are fixedly attached to said load envelope bottom.
15. The vehicle of claim 1, wherein: a. said load envelope additionally contains: i. ballonet cells adjacent to said load envelope bottom; and ii. plumbing connecting said ballonet cells to ballast gas pumps allowing ballast gas to be pumped to and from said ballonet cells changing the buoyancy and attitude of said vehicle; b. ballast gas tanks are fixedly attached to said framework or said load envelope; and c. plumbing connects said ballast gas tanks to said ballast gas pumps;
16. The vehicle of claim 1, wherein said means for pressurizing said load envelope comprises: a. ballast gas tanks fixedly attached to said framework or said load envelope; b. ballast pumps fixedly attached to said framework or said load envelope; c. plumbing connecting said ballast gas tanks to said ballast pumps; and d. plumbing connecting said ballast pumps to said load envelope.
17. The vehicle of claim 1, further comprising a means for docking with other vehicles and spacecraft.
18. The vehicle of claim 1, further comprising a means for transferring payloads from one vehicle to another.
19. The vehicle of claim 1, further comprising a means for delivering payloads to orbit.
20. A lighter than air vehicle comprising: a. a framework comprising pressurized tubes of fabric and poles and connectors made from carbon composite materials; b. propulsion means comprising: i. propellant tanks fixedly attached to said framework; ii. large chemical rocket engines and electric plasma engines capable of providing primary acceleration means for said vehicle; iii. small chemical rockets, electric plasma thrusters, or gas thrusters attached to said framework capable of changing the attitude of said vehicle; and iv. plumbing connecting said propellant tanks to said rockets and said thrusters; c. a load envelope fixedly attached to said framework and optimally shaped as an approximately 15 degree wedge for allowing acceleration from subsonic speed to faster than Mach 25 at altitudes higher than 30 kilometers above sea level, said load envelope having a top and a bottom, and containing therein: i. baffles connecting said load envelope top to said load envelope bottom; ii. lift gas cells adjacent to said load envelope top and fixedly attached to said load envelope bottom between said baffles, said lift gas cells containing therein lighter-than-air lift gas that providing buoyancy to said vehicle; iii. lift gas pumps attached to said load envelope, said baffles, or said framework; iv. plumbing connecting said lift gas cells to said lift gas pumps allowing lift gas to be pumped to and from said lift gas cells altering the buoyancy and attitude of said vehicle; v. lift gas tanks fixedly attached to said framework, said load envelope, or said baffles; vi. plumbing connecting said lift gas tanks to said lift gas pumps; vii. ballonet cells adjacent to said load envelope bottom; viii. ballast gas pumps fixedly attached to said framework, said load envelope, or said baffles; and ix. plumbing connecting said ballonet cells to said ballast gas pumps allowing ballast gas to be pumped to and from said ballonet cells altering the buoyancy and attitude of said vehicle; x. ballast gas tanks fixedly attached to said framework, said baffles, or said load envelope and connected by plumbing to ballast pumps; xi. control systems connected to a tcp/ip network and comprising control units for valves, said pumps, and propulsion means wherein said control system compensates for external loads on said load envelope by causing said ballast pumps to pump ballast gas to and from said load envelope or to and from said ballonet cells; xii. means for power storage and production comprising:
1. an AC grid;
2. a DC grid comprising a plurality of regional DC grids connected across large distances by AC paths;
3. AC/DC converters; and
4. RFI protection measures; d. a shaded, temperature controlled cabin fixedly attached to said framework and life support systems for manned space flight; and e. a means for docking with other vehicles and spacecraft.
PCT/US2006/016336 2005-04-29 2006-04-29 Lighter than air supersonic vehicle WO2006119056A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2008509189A JP2008539131A (en) 2005-04-29 2006-04-29 Supersonic light flight vehicle

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US67645005P 2005-04-29 2005-04-29
US60/676,450 2005-04-29

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Publication Number Publication Date
WO2006119056A2 true WO2006119056A2 (en) 2006-11-09
WO2006119056A3 WO2006119056A3 (en) 2007-03-01

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011008136A1 (en) * 2009-07-17 2011-01-20 Kostyuk Anatoliy Ivanovich Spacecraft for interplanetary and intergalactic flight
US8061647B1 (en) 2007-04-13 2011-11-22 John Powell High altitude two balloon airship
WO2014021741A2 (en) * 2012-07-31 2014-02-06 Aleksandrov Oleg Aleksandrovich Method for multiply lifting a wide load into and returning the latter from space, and apparatus for carrying out said method
US8777156B2 (en) 2011-04-20 2014-07-15 Lockheed Martin Corporation Heavier than air internal ballast
WO2016068751A1 (en) * 2014-10-29 2016-05-06 Илья Владимирович САЕНКО Stratospheric platform
RU2621805C2 (en) * 2015-11-25 2017-06-07 Виктор Маркович Гурвич Vehicle for interplanetary communication (versions)
US9694910B2 (en) 2013-02-22 2017-07-04 World View Enterprises Inc. Near-space operation systems
US10124875B1 (en) 2017-01-09 2018-11-13 World View Enterprises Inc. Continuous multi-chamber super pressure balloon
US10336432B1 (en) 2017-01-09 2019-07-02 World View Enterprises Inc. Lighter than air balloon systems and methods
US10787268B2 (en) 2015-03-09 2020-09-29 World View Enterprises Inc. Rigidized assisted opening system for high altitude parafoils
WO2020249987A1 (en) 2019-03-21 2020-12-17 Takacs Szabolcs A floating platform for launching a space rocket from a height and method for launching a rigid -walled balloon into the space
US10988227B2 (en) 2016-02-11 2021-04-27 World View Enterprises Inc. High altitude balloon systems and methods using continuous multi-compartment super pressure balloon

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US6471159B1 (en) * 2000-09-05 2002-10-29 Mutsuro Bundo Airship shaped space craft
US6648272B1 (en) * 2001-06-28 2003-11-18 Keith L. Kothmann Airship
US20050263642A1 (en) * 2003-11-04 2005-12-01 Daniel Geery Highly maneuverable powered airship
US20050279880A1 (en) * 2004-06-18 2005-12-22 Mutsuro Bundo Multi-purpose airship
US7093789B2 (en) * 2004-05-24 2006-08-22 The Boeing Company Delta-winged hybrid airship

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Publication number Priority date Publication date Assignee Title
US6471159B1 (en) * 2000-09-05 2002-10-29 Mutsuro Bundo Airship shaped space craft
US6648272B1 (en) * 2001-06-28 2003-11-18 Keith L. Kothmann Airship
US20050263642A1 (en) * 2003-11-04 2005-12-01 Daniel Geery Highly maneuverable powered airship
US7093789B2 (en) * 2004-05-24 2006-08-22 The Boeing Company Delta-winged hybrid airship
US20050279880A1 (en) * 2004-06-18 2005-12-22 Mutsuro Bundo Multi-purpose airship

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8061647B1 (en) 2007-04-13 2011-11-22 John Powell High altitude two balloon airship
WO2011008136A1 (en) * 2009-07-17 2011-01-20 Kostyuk Anatoliy Ivanovich Spacecraft for interplanetary and intergalactic flight
US8777156B2 (en) 2011-04-20 2014-07-15 Lockheed Martin Corporation Heavier than air internal ballast
WO2014021741A2 (en) * 2012-07-31 2014-02-06 Aleksandrov Oleg Aleksandrovich Method for multiply lifting a wide load into and returning the latter from space, and apparatus for carrying out said method
WO2014021741A3 (en) * 2012-07-31 2014-06-12 Aleksandrov Oleg Aleksandrovich Method of multiply launching outsized payloads into space and retrieving same and apparatus for the implementation thereof
US11613364B2 (en) 2013-02-22 2023-03-28 World View Enterprises Inc. Near-space operation systems
US9694910B2 (en) 2013-02-22 2017-07-04 World View Enterprises Inc. Near-space operation systems
US10829229B2 (en) 2013-02-22 2020-11-10 World View Enterprises Inc. Near-space operation systems
RU2630946C2 (en) * 2014-10-29 2017-09-14 Илья Владимирович Саенко Stratospheric platform for launching objects in space
WO2016068751A1 (en) * 2014-10-29 2016-05-06 Илья Владимирович САЕНКО Stratospheric platform
US11608181B2 (en) 2015-03-09 2023-03-21 World View Enterprises Inc. Rigidized assisted opening system for high altitude parafoils
US10787268B2 (en) 2015-03-09 2020-09-29 World View Enterprises Inc. Rigidized assisted opening system for high altitude parafoils
RU2621805C2 (en) * 2015-11-25 2017-06-07 Виктор Маркович Гурвич Vehicle for interplanetary communication (versions)
US10988227B2 (en) 2016-02-11 2021-04-27 World View Enterprises Inc. High altitude balloon systems and methods using continuous multi-compartment super pressure balloon
US10336432B1 (en) 2017-01-09 2019-07-02 World View Enterprises Inc. Lighter than air balloon systems and methods
US10829192B1 (en) 2017-01-09 2020-11-10 World View Enterprises Inc. Lighter than air balloon systems and methods
US11447226B1 (en) 2017-01-09 2022-09-20 World View Enterprises Inc. Lighter than air balloon systems and methods
US11511843B2 (en) 2017-01-09 2022-11-29 World View Enterprises Inc. Lighter than air balloon systems and methods
US10737754B1 (en) 2017-01-09 2020-08-11 World View Enterprises Inc. Continuous multi-chamber super pressure balloon
US10124875B1 (en) 2017-01-09 2018-11-13 World View Enterprises Inc. Continuous multi-chamber super pressure balloon
US11904999B2 (en) 2017-01-09 2024-02-20 World View Enterprises Inc. Lighter than air balloon systems and methods
WO2020249987A1 (en) 2019-03-21 2020-12-17 Takacs Szabolcs A floating platform for launching a space rocket from a height and method for launching a rigid -walled balloon into the space
EP3941832A4 (en) * 2019-03-21 2023-01-25 Takács, Szabolcs A floating platform for launching a space rocket from a height and method for launching a rigid -walled balloon into the space

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JP2008539131A (en) 2008-11-13

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