WO2008010180A2 - Launching a flight vehicle - Google Patents
Launching a flight vehicle Download PDFInfo
- Publication number
- WO2008010180A2 WO2008010180A2 PCT/IB2007/052827 IB2007052827W WO2008010180A2 WO 2008010180 A2 WO2008010180 A2 WO 2008010180A2 IB 2007052827 W IB2007052827 W IB 2007052827W WO 2008010180 A2 WO2008010180 A2 WO 2008010180A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flight vehicle
- launch
- shaft
- propulsion system
- launching
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41B—WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE OR COMBUSTIBLE PROPELLANT CHARGE; WEAPONS NOT OTHERWISE PROVIDED FOR
- F41B6/00—Electromagnetic launchers ; Plasma-actuated launchers
- F41B6/003—Electromagnetic launchers ; Plasma-actuated launchers using at least one driving coil for accelerating the projectile, e.g. an annular coil
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
- F41A1/02—Hypervelocity missile propulsion using successive means for increasing the propulsive force, e.g. using successively initiated propellant charges arranged along the barrel length; Multistage missile propulsion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41B—WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE OR COMBUSTIBLE PROPELLANT CHARGE; WEAPONS NOT OTHERWISE PROVIDED FOR
- F41B6/00—Electromagnetic launchers ; Plasma-actuated launchers
-
- 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
- F41F3/073—Silos for rockets, e.g. mounting or sealing rockets therein
Definitions
- THIS INVENTION relates to the launching of flight vehicles, particularly, but not limited to, spacecraft.
- the invention relates to a method of launching flight vehicles.
- the invention extends to a flight vehicle launch installation and to a flight vehicle launch system.
- a method of launching a flight vehicle using an elongate, sub-terranean, generally upwardly directed launch shaft of at least about 300 m length is provided.
- the Applicant is desirous of limiting acceleration if desired in specific cases as may be determined by the load carried by the flight vehicle, and yet be able to accelerate the flight vehicle to a useful minimum velocity, which may be lower than escape velocity.
- the Applicant is of opinion that about 300 m is a practical minimum length for application of this invention. However, preferably the length may be longer than 300 m, even considerably longer than 300 m.
- the launch shaft may be a mine shaft, advantageously an amortized or de-commissioned or abandoned mine shaft.
- the mine shaft may have a length of, advantageously, 500 m or more; preferably 1000 to 2000 m, even up to about 4 km.
- the method may include propelling the flight vehicle along the launch shaft exclusively or mainly by means of at least one propulsion system including components external of the flight vehicle.
- the method may include employing a plurality of propulsion systems, each including components external of the flight vehicle, in combination.
- the plurality of propulsion systems may operate in series, or generally in series with some overlap.
- the propulsion system or each propulsion system may be selected from: a propulsion system using expansion of gas to produce a pressure gradient to propel the flight vehicle along an enclosed barrel; an electromagnetic propulsion system or Lorentz-type actuator such as a linear motor (for example a linear induction motor or a linear synchronous motor), a coil gun or gauss gun, or a rail gun. If the first propulsion system mentioned (i.e. expansion of gas) is selected, it will be a first stage or initial propulsion system.
- the method may include accelerating the flight vehicle within the launch shaft to a final, selected speed, e.g. but not necessarily, escape velocity such that the flight vehicle would travel as a ballistic missile or glider to a designated target or into orbit.
- the method may include further accelerating the flight vehicle after exiting of the launch shaft by an internal or on-board propulsion system; such as a rocket engine; an aircraft engine for example a ram jet engine, to a desired velocity.
- the method may include guiding the flight vehicle along the launch route at a predetermined angle to the vertical such as to launch the flight vehicle to be in its intended trajectory, i.e. so as not to require steering or tilting after launch.
- the method may include ameliorating drag on the flight vehicle while it is in the launch shaft, for example by moving air within the launch shaft in the direction of an exit from the launch shaft, or by partial evacuation of the area ahead of the flight vehicle.
- the flight vehicle may be in the form of a space vehicle, such as a space shuttle; a payload delivery vehicle, such as a rocket for launching satellites into low earth orbit; a manned aircraft or spacecraft for high altitude terrestrial or inter-planetary travel; a rocket, such as a missile or the like (e.g. an intercontinental ballistic missile); an unmanned scientific spacecraft, for example for conducting geological surveys; or the like.
- a space vehicle such as a space shuttle
- a payload delivery vehicle such as a rocket for launching satellites into low earth orbit
- a manned aircraft or spacecraft for high altitude terrestrial or inter-planetary travel
- a rocket such as a missile or the like (e.g. an intercontinental ballistic missile); an unmanned scientific spacecraft, for example for conducting geological surveys; or the like.
- a flight vehicle launch installation for launching a flight vehicle, including a subterranean launch shaft which extends generally upwardly to an exit at the surface, which launch shaft is at least about 300 m long, and which includes guide formations along the launch shaft defining a launch route and adapted to guide the flight vehicle along the launch route; propulsion system components operatively positioned and mounted in relation to the launch shaft to interact with complemental components on a flight vehicle to be launched, in combination with said complemental components to propel the flight vehicle along the launch route.
- the guide formations may include an enclosed launch tube of predetermined cross-sectional shape and size snugly, slidingly to accommodate a flight vehicle for which it is intended and extending at least along a lower portion of the launch route, and in which the propulsion system components include a combustion chamber at a lower end of the launch route, an introduction device for introducing a combustible substance into the combustion chamber and an ignition device for igniting the combustible substance.
- the guide formations may include a set of rails or tracks along at least a portion of the launch route, and magnetic levitation or maglev components operatively connected with the set of rails or tracks for co-operation with complemental magnetic levitation components on the flight vehicle, the propulsion systems then comprising components of an electromagnetic propulsion system or a Lorentz-type actuator operatively associated with the set of rails or tracks for co-operation with complemental components of the electromagnetic propulsion system or Lorentz-type actuator on the flight vehicle for propelling the flight vehicle along said at least a portion of the launch route.
- the electromagnetic propulsion system or Lorentz-type actuator in one variant, may be a linear motor, preferably a linear induction motor, although it may, instead, be a linear synchronous motor.
- the electromagnetic propulsion system or Lorentz-type actuator in another variant, instead, may be in the form of a coil gun or gauss gun.
- the coil or gauss gun will be of the multistage type.
- the electromagnetic propulsion system or Lorentz-type actuator in yet a further variant, may be in the form of a rail gun, the components of the electromagnetic propulsion system or Lorentz-type actuator then comprising a set of rails along said at least a portion of the launch route, rail contact mechanisms along the set of rails for contacting the flight vehicle to effect electrical contact, and electrical power means for electrically powering the rail gun, the complemental components of the electromagnetic propulsion system or Lorentz-type actuator in the form of the rail gun on the flight vehicle then comprising an electrical conduction member across a body or fuselage of the flight vehicle and complemental body contact mechanisms to co-operate with the rail contact mechanisms to establish electrical contact.
- Figure 1 shows a side elevational of a flight vehicle system in accordance with the invention
- Figure 2 shows a view corresponding to Figure 1 in which a flight vehicle is propelled in a launch shaft by linear synchronous motors;
- Figure 3 shows a view corresponding to Figure 1 , in which a flight vehicle is propelled along a launch shaft by propellant injected into the launch shaft behind the flight vehicle;
- Figures 4 and 5 show views corresponding to Figure 1 of launch systems in which a flight vehicle is accelerated along a launch shaft by an electromagnetic thrust arrangement.
- reference numeral 10 generally indicates a system for launching a flight vehicle in the form of a spacecraft 20.
- the flight vehicle may be in the form of a launchable aircraft.
- the system 10 includes a mineshaft 12 for use as a subterranean launch shaft 14 along which the spacecraft 20 is accelerated before reaching ground level.
- the mine shaft 12 is an amortised or de-commissioned or abandoned mine shaft formerly used in mining, advantageously deep level gold mining. Such shafts may extend up to 3 or 4 km in the ground and the mine shaft 12 therefore provides a lengthy launch shaft 14.
- the mine shaft 12 extends roughly vertically, therefore making it useful for launching a spacecraft 20 with a roughly vertical trajectory.
- an inclined shaft i.e. an inclined mine shaft
- a vertical or near vertical shaft i.e. mine shaft
- the system 10 of this embodiment includes a secondary thrust arrangement in the form of rocket engines carried by the spacecraft 20 in conventional fashion, but additionally includes a primary thrust arrangement separate from the spacecraft 20 for accelerating the spacecraft 20 initially, therefore delaying full utilization or engaging of the rocket engines.
- the primary thrust arrangement may be provided, in use, in a number of different ways (refer to Figures 2 and 3).
- the flight vehicle may not have an internal or onboard thrust or propulsion arrangement and may be launched into orbit or to a target in the manner of a ballistic missile or glider.
- the primary thrust arrangement is at least partially separate or external of the spacecraft 20, so that the mass of the spacecraft 20 is minimised. It is to be appreciated that during conventional rocket launches (e.g. from ground level), the rocket requires a heavy payload of fuel, which adds to the mass of the rocket, therefore necessitating more thrust to compensate for the added mass, so that more fuel is needed, and so forth. It is therefore an aim of the invention as exemplified to provide a method of launching a rocket or other flight vehicle such that the rocket or other flight vehicle already has a considerable speed by the time its onboard or internal thrust arrangement is fully engaged, so that a smaller fuel payload is required.
- the spacecraft 20 is launched using pressurised or explosive gas 42.
- the launch shaft 14 includes a lining 30 which is of a heat resistant material (e.g. ceramics) and which renders the launch shaft 14 a uniform right-circular cylindrical shape.
- a tube or duct of uniform right-circular cylindrical shape may be installed along the shaft.
- Reference numeral 30 can then be regarded as denoting such a tube or duct.
- the spacecraft 20 includes a frusto-conical plate or collar 22 which fits in the launch shaft 14 with a working clearance only, such that pressure can be built up beneath the spacecraft 20.
- the collar 22 is of a heat resistant material to protect the rest of the spacecraft 20 from heat from the combustion of the gas 42.
- the collar 22 is detachable so that it may be jettisoned shortly after launch.
- the gas e.g. in the form of air or burning oxygen and hydrogen or a hydro-carbon
- the gas is injected under pressure into the duct 30 lining the launch shaft 14 beneath the spacecraft 20 via a nozzle 40.
- a pressure differential is created across the collar 22, with a high pressure zone beneath the spacecraft 20, and initially ambient pressure (or a vacuum / partial vacuum) above the spacecraft 20.
- the spacecraft 20 is thus urged upwardly piston- or plunger fashion by the pressure differential, as indicated by arrow 24.
- the gas 42 is ignited by ignition means (e.g. a spark or pilot flame) to increase the back-pressure further and propel the spacecraft 20 upwardly.
- ignition means e.g. a spark or pilot flame
- the launch shaft 14 can include a series of vertically spaced doors, for example spaced 200 m apart along the length of the launch shaft 14, thereby creating a plurality of successive chambers.
- an actuator also not shown
- More propellant e.g. gas 42
- the spacecraft 20 can engage its own rocket engines at any stage to provide additional thrust.
- the propulsion system of Figure 3 acts as a single stage operative along a lower portion of the launch path only, and is used as a first stage of a plural stage or composite propulsion system, in which a successive stage or stages is / are provided by another propulsion system or systems in accordance with the invention.
- the spacecraft illustrated in the form of a rocket 20, can be launched using an electromagnetic thrust arrangement, more specifically in the form of a multi-stage coil gun or gauss gun.
- a plurality of groups of coils or electromagnets 50 to 53 are arranged along the length of the launch shaft 14.
- Each group of coils is individually activateable, having control circuitry and a power source conceptually indicated by reference numeral 55.
- a guiding arrangement 32 in the form of a set of rails or tracks in combination with an electromagnetic guiding arrangement, such as a maglev or magnetic levitation guiding arrangement is used to guide the spacecraft 20 as it moves upwardly.
- the spacecraft 20 also includes a magnetically responsive element, for example a mass of magnetic material or an electromagnet (e.g. located along its body) which is magnetically attracted to or repelled from activated coils.
- a magnetically responsive element for example a mass of magnetic material or an electromagnet (e.g. located along its body) which is magnetically attracted to or repelled from activated coils.
- the coil groups above the spacecraft 20 are activated, and electromagnetic fields form within them.
- the coil groups e.g. 50, 51
- the activated coil groups 50, 51 attract the spacecraft upwardly, as shown by arrows 58.
- the spacecraft 20 passes a coil group (e.g. coil group 52) the coil group can be deactivated.
- the propulsion arrangement of Figure 4 can be used in combination with, for example following in series on, the propulsion arrangement of Figure 3.
- the flight vehicle 20 is propelled along the launch route 14 by means of linear motors, generally indicated by reference numerals 50.
- Stationary components 50.1 corresponding to (rolled out) stators are positioned laterally adjacent the launch route, and components corresponding to a (rolled out) rotor are provided fast with the flight vehicle 20, to form the linear motors 50, which are preferably in the form of linear induction motors.
- the flight vehicle 20 is guided along the launch route 14 by means of rails or tracks and a magnetic levitation system arranged in conjunction with the rails or tracks.
- the propulsion system is generally indicated by reference numeral 60 and is in the form of a rail gun.
- the rail gun 60 has stationary propulsion components including diametrically opposed tracks 62 and 64 extending along the launch route 14.
- An electrical power source schematically indicated by reference numeral 66, is provided to conduct power via conductors 68 to the respective tracks 62, 64.
- Each track 62, 64 has a track contact mechanism 62.1 , 64.1 which is complemental to a respective body contact mechanism 20.1 at correspondingly diametrically opposed sides of a body of the flight vehicle 20.
- the body contact mechanisms 20.1 are electrically connected to the body 20 which is of electrically conductive material such that the body of the flight vehicle 20 completes the electrical contact between the tracks 62, 64 such that, in conjunction with the power source 66, a rail gun is formed.
- the electrical power source 66 is actuated, the flight vehicle 20 is then propelled and accelerated rail gun-fashion in the direction 70.
- a further set of tracks or rails is positioned along the launch path 14 and a magnetic levitation guiding system is provided in conjunction with such tracks and with complemental components on the flight vehicle 20 to guide the flight vehicle 20 along the launch path 14 by means of magnetic levitation.
- the propulsion system of Figure 5 can be used in series combination with the propulsion system of Figure 3, or the propulsion system of Figure 4, or the propulsion system of Figure 2. Instead, it can be used in combination with two or more of the propulsion systems of Figures 3, 4 and 2.
- the Applicant believes that, if the propulsion system of Figure 3 is used, that will be an initial propulsion system. Furthermore, the Applicant believes that if the propulsion system of Figure 5 is used, that will be the ultimate propulsion system.
- the primary thrust arrangement exerts a sufficient force on the flight vehicle 22 accelerated at an acceleration which is tolerable by the sensitive equipment which is typically carried by satellite delivery vehicles, or by manned spacecraft.
- the primary thrust arrangement is constructed such that the speed of sound can be achieved while the initial acceleration of the flight vehicle 22 along the shaft 14 is less than 20 g.
- the force which is required to achieve this acceleration is smaller than is usually the case for rocket launched spacecraft, as the weight of the flight vehicle is substantially reduced by the reduced fuel which it carries, or no fuel if it is in the form of a flight vehicle without an inboard propulsion system.
- the concept of smaller than usual forces would remain applicable even for higher accelerations.
- the flight vehicle 22 When the flight vehicle 22 exits the mouth of the shaft 14, it can travel as a projectile until its speed reduces such that further thrust is required, at which stage an inboard propulsion system of the flight vehicle 22 can be activated. Instead, the inboard propulsion system can be actuated immediately upon exit from the shaft 14, or even slightly before exit, to continue to exert thrust on the flight vehicle 22.
- acceleration of the flight vehicle 22 by the primary thrust arrangement is sufficient for the flight vehicle 22 to reach escape velocity before it exits the shaft 14, so that the inboard propulsion system of the flight vehicle 22 need only maintain the exit velocity of the flight vehicle 22.
- the thrust provided by the inboard propulsion system in such case need only be equal to the weight of the flight vehicle 22.
- the ultimate velocity obtained by the primary propulsion system may be sufficient and no further propulsion may be required, in which case there need not be an inboard propulsion system.
- Flight vehicles e.g. rockets may therefore be smaller and lighter, using smaller engines and substantially reduced amounts of expensive fuel.
- This invention finds particular application for using draught rockets to launch satellites into orbit.
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU2007274625A AU2007274625A1 (en) | 2006-07-17 | 2007-07-16 | Launching a flight vehicle |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ZA200605887 | 2006-07-17 | ||
ZA2006/05887 | 2006-07-17 |
Publications (3)
Publication Number | Publication Date |
---|---|
WO2008010180A2 true WO2008010180A2 (en) | 2008-01-24 |
WO2008010180A3 WO2008010180A3 (en) | 2008-03-06 |
WO2008010180A8 WO2008010180A8 (en) | 2008-04-17 |
Family
ID=38814426
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IB2007/052827 WO2008010180A2 (en) | 2006-07-17 | 2007-07-16 | Launching a flight vehicle |
Country Status (3)
Country | Link |
---|---|
AU (1) | AU2007274625A1 (en) |
WO (1) | WO2008010180A2 (en) |
ZA (1) | ZA200900811B (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014152778A1 (en) * | 2013-03-15 | 2014-09-25 | Palmer Labs, Llc | Launch vehicle and system and method for economically efficient launch thereof |
CN105836152A (en) * | 2016-03-25 | 2016-08-10 | 济南环太机电技术有限公司 | Heavy-duty spacecraft ejection system and distributed energy storage central synchronized acting ejection method thereof |
WO2018158746A1 (en) * | 2017-03-02 | 2018-09-07 | 8 Rivers Capital, Llc | Systems and methods for improving efficiency of electroantimagnetic launchers |
US11667405B2 (en) | 2016-12-13 | 2023-06-06 | 8 Rivers Capital, Llc | Vehicle launch system and method |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105667835A (en) * | 2016-03-25 | 2016-06-15 | 济南环太机电技术有限公司 | Heavy lift launch vehicle catapult and ejection method thereof |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3024729A (en) * | 1948-04-24 | 1962-03-13 | Cornell Aeronautical Labor Inc | Ram jet projectile |
US3523483A (en) * | 1962-06-28 | 1970-08-11 | Us Air Force | Shelter pit |
US4709883A (en) * | 1985-04-22 | 1987-12-01 | Giuliani Robert L | Launch and ascent system |
US4884489A (en) * | 1987-04-22 | 1989-12-05 | Board Of Regents University Of Texas System | High performance electromagnetic railgun launcher |
WO2005019761A2 (en) * | 2003-08-01 | 2005-03-03 | Lockheed Martin Corporation | Electromagnetic missile launcher |
US20050285452A1 (en) * | 2004-06-09 | 2005-12-29 | Phil Putman | Linear motor geometry for use with persistent current magnets |
DE102005041177A1 (en) * | 2004-09-08 | 2006-06-22 | Christoph Gerstenhauer | Floating launch system for spacecraft has tube that is closed at the bottom floating upright or inclined in water as launch system for spacecraft, is held stable by grid construction |
-
2007
- 2007-07-16 WO PCT/IB2007/052827 patent/WO2008010180A2/en active Application Filing
- 2007-07-16 AU AU2007274625A patent/AU2007274625A1/en not_active Abandoned
-
2009
- 2009-02-03 ZA ZA200900811A patent/ZA200900811B/en unknown
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3024729A (en) * | 1948-04-24 | 1962-03-13 | Cornell Aeronautical Labor Inc | Ram jet projectile |
US3523483A (en) * | 1962-06-28 | 1970-08-11 | Us Air Force | Shelter pit |
US4709883A (en) * | 1985-04-22 | 1987-12-01 | Giuliani Robert L | Launch and ascent system |
US4884489A (en) * | 1987-04-22 | 1989-12-05 | Board Of Regents University Of Texas System | High performance electromagnetic railgun launcher |
WO2005019761A2 (en) * | 2003-08-01 | 2005-03-03 | Lockheed Martin Corporation | Electromagnetic missile launcher |
US20050285452A1 (en) * | 2004-06-09 | 2005-12-29 | Phil Putman | Linear motor geometry for use with persistent current magnets |
DE102005041177A1 (en) * | 2004-09-08 | 2006-06-22 | Christoph Gerstenhauer | Floating launch system for spacecraft has tube that is closed at the bottom floating upright or inclined in water as launch system for spacecraft, is held stable by grid construction |
Non-Patent Citations (1)
Title |
---|
JULES VERNE: "De la terre à la lune" 1 January 1865 (1865-01-01), , XP002462880 [URL: http://web.archive.org/web/19990117033804/ http://www.fourmilab.ch/etexts/www/talune/ talune.html] [Retreived on 19-12-2007] Chapter "L'histoire du canon" Chapter "Derniers détails" * |
Cited By (13)
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---|---|---|---|---|
US10562648B2 (en) | 2013-03-15 | 2020-02-18 | 8 Rivers Capital, Llc | Launch vehicle and system and method for economically efficient launch thereof |
JP2016516172A (en) * | 2013-03-15 | 2016-06-02 | パルマー ラボ,エルエルシー | Launch transportation means and system and its economical and efficient launch method |
WO2014152778A1 (en) * | 2013-03-15 | 2014-09-25 | Palmer Labs, Llc | Launch vehicle and system and method for economically efficient launch thereof |
US10202209B2 (en) | 2013-03-15 | 2019-02-12 | 8 Rivers Capital, Llc | Launch vehicle and system and method for economically efficient launch thereof |
CN110027730A (en) * | 2013-03-15 | 2019-07-19 | 八河流资产有限责任公司 | Emission system and method for launch payload |
EA033502B1 (en) * | 2013-03-15 | 2019-10-31 | Palmer Labs Llc | Launch vehicle, launch system and method of launching a payload |
CN105836152A (en) * | 2016-03-25 | 2016-08-10 | 济南环太机电技术有限公司 | Heavy-duty spacecraft ejection system and distributed energy storage central synchronized acting ejection method thereof |
US11667405B2 (en) | 2016-12-13 | 2023-06-06 | 8 Rivers Capital, Llc | Vehicle launch system and method |
WO2018158746A1 (en) * | 2017-03-02 | 2018-09-07 | 8 Rivers Capital, Llc | Systems and methods for improving efficiency of electroantimagnetic launchers |
JP2020509294A (en) * | 2017-03-02 | 2020-03-26 | 8 リバーズ キャピタル,エルエルシー | System and method for increasing the efficiency of an electromagnetic non-magnetic launch device |
US10669046B2 (en) | 2017-03-02 | 2020-06-02 | 8 Rivers Capital, Llc | Systems and methods for improving efficiency of electroantimagnetic launchers |
CN110536837B (en) * | 2017-03-02 | 2023-03-14 | 八河流资产有限责任公司 | System and method for improving efficiency of an electromagnetic emission prevention device |
CN110536837A (en) * | 2017-03-02 | 2019-12-03 | 八河流资产有限责任公司 | System and method for improving the efficiency of the antimagnetic emitter of electricity |
Also Published As
Publication number | Publication date |
---|---|
ZA200900811B (en) | 2010-03-31 |
WO2008010180A8 (en) | 2008-04-17 |
WO2008010180A3 (en) | 2008-03-06 |
AU2007274625A1 (en) | 2008-01-24 |
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