Patent Application
20220332439
There is known a document (KR20070113934A) that refers to a hypothetical process of hanging and transporting through space a lift cabin between the planet Earth and the natural satellite, for the transport of water and cargo and to people, reducing the cost of transporting space rockets and classic satellites with the hypothetical resistance of the carrier cable. The proposals for the creation of a space lift system with counterweight located on the Geostationary Orbit of the Earth were hypothetically defined by scientist Konstantin Tiolkovsky in 1895 and by the writer Arthur C. Clarke in 1979 in the work “Fontaines du paradis”. Another system proposed for the transport of wind electricity by cables, from balloons raised in the tropopause (mentioned by Alvin Toffler, “Third Wave”, Chapter 12, “Peaks”, at the Romania, Politics Publishing House, in 1983).
The document (WO2016170951) refers to a process of transport of fine droplets, of liquids, on a relative distance in air under reduced pressure, on a trajectory, through controlled vibrations of some machines without connections between them;
It is known the document (WO0161188A3) that uses flying machines of the special type with “rotary shape”, with cross engines combining the different types of combustion and propulsion crossed according to the physical theorem of inertia, of “Huygens-Steiner”;
There are also known two fuel supply systems, with liquid fuels, between tankers, as: “flying boom” (system with arm and rigid hose) and “hose-and-drug” (system with mobile hose and catch basket) used on McDonnell Douglas KC10, Pegasus Boeing KC46 (767), Ilyushin An Il-78M and Boeing KC 135 Stratotanker, Airbus A330 MRTT-powered robotic aircraft, Myasishchev VM-T Atlant and others.
It is known that: the companies “Northrop Grumman Corporation”, “Defense Advanced Research Projects Agency (DARPA)” and “NASA Dryden Flight Research Center”, in their test of 2011—(Northrop Grumman's Proteus), made with two autonomous airplanes (NASA Global Hawk), flew without pilots near each other from 13 m distance and at an altitude of 13.7 km, setting a record through the fuel test between two airplanes of the same type, without pilot, (type “buddy-to-buddy”), without a tanker plane, together with the hose-and-drogue system, with hoses that in other planes far exceed their fuselage, depending on their size- and capabilities.
In 2014, the company “Northrop Grumman Systems Corp.” expanded the operations for refueling “X-47B jet” drones through the US military.
It is also known that in 1960 three American navy aircraft were powered together forming a flight in formation as a “chain”.
In year 1958, the record recorded by two people who fueled a speeding motor vehicle, a private Cessna 172 aircraft, which ran 65 days without landing, is notorious in the USA.
The X20-X37, “MiG-105 Hurricane” and “Dream Chaser—Nevada” reusable aircraft are used since 1960 for descents between altitudes from 500 km-40 km, have thermal shields with resistances up to 1,400° C., and they were made to be able to transport fuels for stars and human crew, to the Earth's Low Orbit, in case of emergencies.
The document is known (U.S. Pat. No. 9,085,897B2 also published as WO2008101346A1), which describes a fixed, floor-mounted, ground-connected inflatable tower, approximately 20 km high, which is used for the operation of an elevator towards a faster launch and landing ramp for scientific space flights and travel.
The technical problem that the invention solves consists in grouping for a longer period technically (in accordance with the environmental conditions: wind, temperature, air density, meteor dust, gravity), of at least three flying vehicles, regardless of their dimensions and regardless of the types of fuel, vehicles moving in the air, and through these groups, to transport at increased altitude the various materials or liquid fuels (or similar to the transport through an elevator, to the interplanetary space), by reducing the travel time the distance to space, by reducing the gravitational effect and the classic transport costs (such as rockets with chemical combustion engines and balloon transporters with satellites or platforms).
The air transport device at an altitude that is realized by a formation flight of at least three identical or hybrid motorized flight devices, which are connected to each other to feed, support and transport each other and to make a transport system of electricity, light rays generated by high-capacity light-emitting diodes, liquids or goods (physical objects through a crane or lift), to the outer space of atmospheres similar to the terrestrial one, eliminates the disadvantages presented above by helping to reduce costs of space transport to areas with low gravitational attraction, up to the limit of the density of the environment conducive to the flights through the lift (“Coanda effect”), and at the same time supports the flying devices in the form of a grouping depending on the meteorological and geo-physical period of the planetary environment for different periods of time and altitude. In general, planets with atmosphere hold approximately aproximativ ¾ of water vapor up to an altitude of 20 km, as is the case with planet Earth. Thus, in the troposphere, (M,
In the case of the planet Mars due to its mass and different rotation, the gravitational attraction is 38% lower than that of the Earth. Thus, known and recently sent flying vehicles have made it easier to cope with the attraction of Mars. An Mars altitude transport device being at the advantage of the Earth, by its shorter length. But the rarefied atmosphere of the red planet, a disadvantage in front of the load of classic vehicles. Thus the balloons and the blades of the engines or the circumference of the vehicles and the speed of flight, are correspondingly proportionate to Mars, here the atoms being easily removed from the atmosphere, due to the reduced activity of the magnetosphere. Thus the atmosphere of the planet Mars has only 11 km, being very small compared to the one of the Earth's mesosphere up to 90 km (variable to poles). Wind speeds vary and interact in the Martian ionosphere directly with outer cosmic winds, with temperature differences similar to those of the Earth's cold mesosphere (between −110° C. and +70° C.), accepted by flights with known vehicles. In the terrestrial tropopause, in spring, at 25 km altitude, near the equatorial area (Florida), winds of 118.8 km/h (33 m/s) are recorded, and in the northern hemisphere near the temperate-continental zone (Mountain Postavaru), the winds reach 208.8 km/h (58 m/s) in spring. The highest, in the thermosphere, the winds reach up to 750 km/h (208 m/s), and at temperatures of 2000° C. Temperature guard causing vertical and horizontal particle movements.
At more than 30 km altitude the pressure of the atmosphere drops significantly compared to that of the sea where flights over 1224.8 km/h (approx. 1 Mach) take place, depending on the temperatures, the speed of sound being propagated differently.
Helium balloons reached heights of about 65 km from Earth's atmosphere. “Red Sprites” luminous discharges from the troposphere (between 50-90 km), were recorded around the meteorological balloons and have the effect of the rare encounter above the storms created in cumulonimbus clouds, with no effects recorded on the aircraft that are not connected to the ground.
For the mesospheric launches (M.
Above the jurisdictional altitude of the states, theoretically 100 km, the “Karman line”, are used for liquid motor flights (missiles, X15 airplanes, from 1960 or airplanes with engines, ramjet, with speeds up to 6 mach), without restrictions of regional pollution.
According to the US Air Force calculations, refueling air in airplanes reduces the cost of airfares to airplanes by 35-40% for every 3500 km traveled compared to the power supply of the same aircraft from the ground, thus saving the costs of taking off with the tanks. heavier with fuel.
In commercial flights the distance between the antennas on the aircraft fuselage warns the flight as dangerous below the minimum separation distance between 300 m (1000 ft) aircraft, but for military air refueling the hoses also have lengths between aircraft, over 13 meters.
In the case of external mobile departing flights, such as communication pipes or cables, as well as the attached counterweights, they follow the same direction with the vehicles carrying them, opposing the resistance similar to the force of the external winds, with that of the flying vehicles. The verticality of the pipes and cables will be maintained and if the flights take into account the gravitational force of the Earth on cables and hoses over 600 m.
The proposed hose-and-drug coupling system with hoses and chimneys between aircraft already has automatic hose retraction systems in addition to rotating motion compensation systems between aircraft or air turbulence.
In the case of military conflicts, a highly developed nation operates with concomitant air forces of about 40-50 different military aircraft, proving that the world and local economy can sustain fuel consumption corresponding to several months duration similar to the theaters of modern technological operations, generating in plus and consistent economic exchanges on the horizontal, between the air service operators.
It is known that when returning to the atmosphere space shuttles (Atlantis, Buran, Colombia, Discovery, etc.), need to reach from speeds of 27,680 km/h to under 1 speed, computer flight maneuvers, descending, from the less dense atmosphere that prevents the shuttles from stopping, towards the atmosphere with the increased density from about 122 km altitude (between the thermosphere and the mesosphere bays), with the following maneuvers: lifting the shuttle's nose to an attack angle of 40 degrees in the direction of gravity, but at the same time with successive turns to the sides of the shuttle at exact angles, “snaking”, to avoid overheating or rejecting the dense atmosphere of the planet. At the return these types of shuttles not having fuel tanks for speed reduction, but through these computerized maneuvers can reach the normal speed level of refueling planes circulating in the stratosphere, tropopause or similar planetary environments. By means of the transport and feeding device at altitude, the shuttles described, upon return, will now be able to have sufficient fuels for braking when returning from the atmosphere with the help of engines at the stratospheric level.
Flying aircraft known as helicopters and drones that benefit from the air density, can pass into the northern hemisphere, in Romania from the level of the Postavaru or Moldoveanu mountains, as well as from the highest mountain from which a helicopter has stationed and taken off so far, that is, on Mount Everest at 8932 m altitude (the record being recorded in 2005 with a Eurocopter AA3500B3), and the highest flight with a helicopter (SA315 BLAMA), was obtained by lifting up to 12441 km altitude, in 1972. Altitudes three times higher than on Mount Everest are on the planet Mars, on “Olympus Mons” which has 21,230 m altitude being the highest mountain in the Solar System.
The highest human-operated hot air balloon rose to about 20 km, and up to 40.3 km semi-automatic and parasailed (belonging to the Google group—Alain Bustache). The meteorological balloons rose up to 65 km altitude, containing technical installations attached.
For the Earth, prototypes of airplanes are used that can be refueled efficiently with solar energy starting from the altitude of 40 km.
For scramjet engines with speeds between 5-14 mach, with hydrogen and oxygen combustion there are prototypes for interplanetary areas and it is proposed in areas with dense atmosphere of planets known as useful for formation flights. The initial solution of the “ramjet-bassard” engines with funnels (for the capture and reuse as propulsion of hydrogen molecules, where the densities in space reach up to 1 atom/cm3.), Being viable even in the case of group flights between aircraft.
The following advantages are obtained by applying the invention:
The following are examples of embodiments of the invention in relation to
The superimposed aerial device, for transport in space, that is, grouping for as long a period as possible, (in accordance with the environmental conditions: wind, temperature, air density, meteoric dust, gravity), of some vehicles (from the state of the art) of different sizes and with different types of feed in motion in the air, according to the invention, in groups of at least three vehicles with aerodynamic load, uses a flight of devices connected in the group, which are used for the purpose of transporting at high altitude of various materials, similar to a lift to the interplanetary space, by reducing the distance and transport costs, by reducing the gravitational effect. In order to achieve this grouping, according to
In
The A2 tankers take off and avoid the electric discharges from the atmosphere of the F electrons, when they are connected with a group of A-An, or B-Bn, A3 flying devices, making contact with the ground M avoiding the formation of lightning.
The A4 fuel station devices have a concentric flight being permanently connected to the earth stations that have M earthings, to compensate for the electric F discharges.
The A4 fuel station apparatus with M grounding, are connected in favorable weather conditions with A2 tank devices without grounding, only when the tanker carrying in flight is not connected with devices that fly in formation of at least 3 A-An, B flight devices. −Bn, A3 that have static charge due to the lightning F in the atmosphere, avoiding the dangers in the transport of liquid fuels or physical objects or with electrical resources with diodes (atomic, thermal or solar powered).
Devices A3,
On
On
The fuel is necessary for the refueling as close as possible to the mesosphere of an A3 shuttle—so that it can overcome by the centripetal force the gravitational attraction of the Earth, at a speed of about 28,500 km/h until the altitude of about 408 km, corresponding to the connections with the closest space stations, known today,
The speed of the power supplies in operation have an average of 500 km/h sufficient to maintain a flight in formation from A2, A-An, A2 or drone planes, balloons, B-Bn,
The supply hoses between the aircraft, with connecting elements contain systems such as: “flying boom”—system with an arm as a rod containing hose covered with rigid material; and “hose-and-drogue”—a system with mobile air hose and end connection for the lower altitude aircraft. Air transport device for space A2, A4, A-An, B-Bn, A1-A1n, A3 uses for conical hose supply with large base, as a counterweight P1, covered with solid arm, with “Boom refueling” connection for the aircraft of low altitudes. In parallel or simultaneously between the aircraft, a conical hose supply system with a larger base is used, as a counterweight P1, with connection with “house and drug” funnel A2, P1, A4, P1, A, P1, An, B, P1, Bn, A1, P1, A1n, P1, A3.
In the flight of the devices conceded between them the atmospheric pressure decreases rapidly with the altitude. The atmospheric density also decreases with the altitude, at only 3 km altitude the air density decreases by about 30% compared to the ground, which is about 1 kg/m3, the pressure being more efficient for flights over 1 mach, of 1224, 8 km/h, at +25° C. The speed of the devices in formation can be even lower to reach the speed of sound now at 1,076 km/h at the temperature from −50° C. with flight devices A1, A1n, A3,
The similar system for the supply in the mesosphere is that of the liquid transfer “buddy-to-buddy refueling”, on more than three flight devices A1, A1n,
The turbulence between devices A2, A4, A-An, B-Bn, A1-A1n, A3 is compensated by the P1 hoses whose materials are elastic, but with resistance to breakage (similar to nanocarbon or synthetic fibers “Kevlar M5”) and have At the same time, retractable hose clamps supplemented with springs that dampen the differences between the altitude flight apparatus and the lower altitude aircraft, and by compensating, by rotating these clamps with additional hose lengths, retractable hinged cleats. computer.
1
f) The tanker plane A2 which supplies an airplane A which in turn supplies another airplane A, up to a minimum of 3 airplanes, An, A1, A1n, all powered by means of hoses P1, have in parallel or separately connected different connections P, which represents depending on the flight requirement: metal cable, electric cable, light rays generated with diode electrical resources (atomic, thermal or solar powered), or, liquid stream transmitted linearly through vibration devices.
The tanker plane A2 which supplies a flight device B which in turn supplies another device B, up to a minimum of 3 flight devices, Bn, A1, A1n, all powered by the P1 hoses, have different or parallel connections between them. P, which represents according to the flight requirement: metal cable, electric cable, light rays generated by electrical resources with diodes (atomic, thermal or solar powered), or, liquid stream transmitted linearly through vibration devices.
Feeding directly from the ground with groups of devices P1-P-A4, P1-P-A2, P1-P-A, P1-P-An, P-P1-B, P1-P-Bn; P1-P-A1, P1-P-A1n, P1-P-A3 can be made at the altitude of the mountains such as over 1.7 km in the Earth's troposphere, in the Northern hemisphere and in the depopulated areas, or zero km, over the oceans.
In the case of the aerial transport system by tanker A4, A2 to the flight apparatus with “rotating shape” according to the physical theorem of “Steiner” which combines the different types of cross-reaction forms of combustion, to overcome gravity, (also known as the theorem).
Huygens-Steiner or the parallel axis theorem being used in mechanics and allows the calculation of the moment of inertia of a rigid solid with respect to an axis, knowing the moment of inertia with respect to an axis parallel to the first and passing through the center of mass of the body), the theorem described and in document WO0161188A3, the connection is made through hoses P1 to the flight apparatus with the “rotational shape” of higher altitude B, Bn, and then to the devices A1-A1n, A3,
In the air transport system of the tanker type A4, A2, the connection is made by the P1 hose and by the droplets of droplets of fuels and other liquids under reduced pressure realized in the upper atmosphere of the planets (and with a small number of molecules in the air), generated. of vibrations as a column of liquid P (drop column transmitted by vibration under pressure of 10 thousand Pa according to document WO 2016170951), between the A-An aircraft or B-Bn aircraft, up to the high altitude aircraft A1, A1n, A3 FIG.
In the case of the air transport system of electric type aircraft with solar charge and devices with electric accumulation A2, to the flight devices A-An, An-A1n, A3,
1
f) In the case of the aerial system of electrical transport of aircraft type fuel tank plus electric generator A4, A2 the connection is made through hoses P1, plus the electric cables P between the airplanes of type A-An, An-A1n, B-Bn, A3,
In the case of the aerial system of electrical transport of aircraft type with fuel, plus electric generator A4, A2 the connection is made through hoses P1, plus through the light beam realized by laser diodes P, between the airplanes of type A-An, An-A1n, B-Bn, A3,
In the case of the aerial system of electrical transport type aircraft with atomic generator A2, the connection is made through the electrical cables P, plus through the hoses P1, between the devices of type B-Bn, A1-A1n, A3,
In the case of the air transport system of the tanker type aircraft with fuels A4, A2, A3,
And in the case of the air transport system with tanker type A4, A2 with balloon or slow-moving drones B-Bn, A-An, the connections of the P1 hoses or the cables and the P-beams are made by rotating at the appropriate speed of the aircraft. necessary speeds in the turbulent zones A4, A1-A1n, A3
1
f) P1 liquid fuel hoses have a minimum of 13 meters in length on the aircraft to be easily controlled from 13 km altitude, and to use the Coriolis force of the Earth's motion hoses and cables, in the northern hemisphere, for this purpose. from V to E,
Also, to maintain the verticality of the supply and transport hoses other P1 liquids, they will have a larger shape at the bottom and as a counterweight to get as close to the connection of the lower flight apparatus as altitude from formative, geometrically being compared with a cone trunk. Thus, if the hose is like a cone trunk and will be regarded as a geometrical body obtained when sectioning a rotation cone through a plane parallel to its base, the following calculation relation will be considered:
V=⅓π·h(r12+r1·r2+r22);
Thus the volume of the hose (V)=7.79 m3 (˜7 tons kerosene). For a 600 ml conical hose (h) with a width of 4 cm above (r2), plus the radius of the lower circumference, being 20 cm wide (r1).
The descent and the climb from an altitude of a flight apparatus A2, A, A3 for servicing or breaks, from the formation, will be done by leaving the chain from the upper level A-An, A1-A1n, by retracting the connections P, P1, deceleration and the descent to the back of the apparatus column, the column which at a later point will allow it to be reached so that the detached or replacement device enters the formation near another flight device A, A1n. The other devices in the band will take altitude in case of necessity compensating the space left between the band in the band. Identically, for the formation of a flight device, drone with propeller or balloon B, it will exceed the constant speed of the column and will reenter as in a chain, in formation for refueling next to another B-Bn device, the procedure of flight repeating itself using radar telemetry technology.
Airplanes replaced by ground or A2 power supply are connected to airports along the entire flight path of the planet, generally maintaining constant flight direction to E in the direction of Coriolis force.
Commercial and military aircraft with large tanks, with engines operating on the “Coanda reaction principle” A4, A2, A, A1 in the flight up to a maximum of 11 km altitude, with a maximum of only 0.78 mach (and experimental aircraft with X-jet engines). −51A, Mig-25 Faxbat, fly up to 18 km altitude, with maximum 5 mach, and those withdrawn x-15, x-41A, Falcon HTV-2, SR-71, with speeds of about 7.2 mach). These tankers, with engines with the “Coanda reaction principle”, can maintain altitude close to the 100 km limit, with the “Karman line”, through P connections and with P1 hoses, which transport in parallel resources such as those from hydrocarbons, plus oxygen and liquid hydrogen required for the engines of the A4, A2, up to An, Bn, A1n, and high-capacity A3 and D rocket shuttles, through temperatures similar to +70° C. hot and cold Earth's mesosphere. fluctuates near the 80 km altitude limit, at −110° C.
Air transport device at separated altitudes, A2 tankers, statically loaded F, of the formation of at least two, or three and even more A-An, B-Bn flight devices, connecting with A4 fuel station flight devices. with earthing M,
Another example of the invention through the in-flight power supply systems, the “flying boom” (system with arm and short rigid hose), which can transfer approximately 2700 liters/min of liquid fuel at lower altitude, into the Tropsphere. The “hose-and-drug” system (system with long movable hose and clamping basket, approx. 13 m), can transfer 700-900 liters/min of fuel at high altitude at the boundary of the Stratosphere, the clamping system between airplanes requiring more plenty of connection time, but more secure in turbulence. The latter, “hose-and-drug”, noted with the letter P, in
The P-type cords will be connected in this case, in order to extract the fuel to the higher altitude, to the devices of the type An or Bn or A1n or A3, that is, in the opposite direction of the current supplies (from the upper plane to the lower one).
Due to the eventual turbulence, the devices will be connected as much as possible to maintain the fuel from the altitude with fuel or energy, the average connection through a “hose-and-drug” system being about 10 minutes in the troposphere with the possibility of reconnecting band.
For a Boeing 747 the flowing (feed) speed of the fuel in the wings is 2 tonnes/minute and consumes 0.2 tonnes of fuel/minute operating in parallel with the fuel loss operation. To eliminate, for example, 77 tons of fuel in operation, the plane needs 35 minutes. A Boeing 747 consumes 12 tons of fuel/hour, in normal air operation. By analogy it can be used for extraction the speed of movement of the flats for climbing the fuel through vacuum tubes from four altitude devices.
A Boeing 777-200 has a maximum capacity of 117,340 liters of fuel with approximately 9,700 km maximum flight autonomy. To power a Boeing 777-200 in the air (at temperatures up to +200° C.), through the long hose system starting from 13 m “hose-and-drogue”, at 900 liters/minute, it takes 130 minutes, that is 2.17 hours. Thus, to start a system consisting of a system of at least one Boeing 777-200 tank aircraft noted in
It is known that for a classic rocket flight into space, they were used only for the stage with THREE flight stages—that is, to reach the Earth's low orbit (LEO)—liquid fuel tanks (such as: nitrogen, helium, hydrogen and oxygen liquids, kerosene or combinations), in quantities of 325000 liters (716502 lbs) for “Saturn V-USA” or similar for “N1-USSR” recipes. With standard, liquid fuel rocket engines. The useful weights carried with these types of engines are 5% (five percent), of the total weight of the mass of the missile fuels.
The only advantage in terms of fuels through the costs of sending shuttle space through this altitude device is up to 70% more efficient/launch compared to the costs of ground-level rocket launching, as well as through the diversity of transports.
So, for a continuous, minimum connection with, the 6020 km (10 hours) cruise, operating with Boeing 777-200 aircraft, to a liquid transfer through the hose-and-drogue type (900 liters/it takes 10 minutes to fill half of a tank, of connected devices of type A, An, A1, A1n, and finally the tank of a space shuttle type A3 of
Thus, for the 10-hour operation of the aforementioned aircraft, type A2
The cost of the transport device at altitude if purchased from “zero” (and will consist of 83 Boeing aircraft of $104 million/piece), can reach the above example (plus fuel), at 8.69 Billions of dollars, the device being reusable. The combined liquid hydrogen, used for a 325-tonne fuel tank for a Saturn V-US recipe (for a 6-minute pass at LEO's TREI stage), totals about $325,000. Of which the total costs for three fuel tanks/launch are approximately $3 million.
The fuel is consumed up to an hour. But the maximum budget for 1966 of a single Satrun V-USA missile, with four stages of tanks, being estimated today at $1.16 billion, the tanks being completely reused. The entire project for 11 missiles is estimated at $6.4 billion.
In conclusion, the above-mentioned aerial transportation device, totaling $8.69 billion, reaches more than half the costs of launching a conventional Saturn V-US missile program ($6.4 billion), but the advantage is increased, by reusing the air transport device type A2, A, An, A3, from
For a re-launch and return space shuttle system (Atlantis, Discovery this decade), the cost of solid rocket fuel for two tanks is $1.4 million and for the tank with, liquid fuel the cost is 2, $1 million, a total of $3.5 million. Also, recent systems partially reusable for sending to Low Earth Orbit (LEO) with “Falcon 9” rockets, Space X—NASA, maximum costs are $35 million for fuel launches—as liquid oxygen (LOX) or kerosene. without rocket water (RP1)—for a single launch and total project costs of $1.6 billion, costs close to the costs of launching a classic Saturn V-USA rocket from the 1970s.
Airplanes have in addition to the amount of fuel needed for the formation planes and the initial reserves (at departure), used in the utilitarian aviation flight, meaning “Block Fuel” consisting of: “Trip Fuel” (consumption from take-off to landing), “Contingency Fuel” (regular fuel consumption plus 5% of the entire tank), “Extra Fuel”, “Taxi Fuel” (in winter), “Alternate Fuel” (extra fuel for an initially chosen alternative airport), “Final Reserve Fuel (13 minutes reserve)”. “Trip Fuel” consumption from take-off to landing is also calculated according to the planes of grouping of lower order as altitude but also higher, grouped in climb or collection or independently depending on the calculated altitude.
For the airplanes in the group from the troposphere A2, A B, the costs of fuels “Final Reserve Fuel (13 minutes reserve)”, up to 105000 feet (3.2 km) will be higher due to the air resistance compared to the upper level. An extra kg number will be taken into account and “Extra Fuel” will be used for these aircraft more than for commercial aircraft. They will deliver less fuel than the higher level aircraft A1n, Bn, A3, D, with low forwarding resistance.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/EP2020/075920 | 9/16/2020 | WO |
