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WO2025051864A1 - Dispositif de lancement d'objets aéroportés - Google Patents

Dispositif de lancement d'objets aéroportés Download PDF

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Publication number
WO2025051864A1
WO2025051864A1 PCT/EP2024/074842 EP2024074842W WO2025051864A1 WO 2025051864 A1 WO2025051864 A1 WO 2025051864A1 EP 2024074842 W EP2024074842 W EP 2024074842W WO 2025051864 A1 WO2025051864 A1 WO 2025051864A1
Authority
WO
WIPO (PCT)
Prior art keywords
launch
tunnel
missile
drive unit
separate drive
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.)
Pending
Application number
PCT/EP2024/074842
Other languages
German (de)
English (en)
Inventor
Frank Heinrich
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Citius Altius GmbH
Original Assignee
Citius Altius GmbH
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 Citius Altius GmbH filed Critical Citius Altius GmbH
Publication of WO2025051864A1 publication Critical patent/WO2025051864A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F41F3/073—Silos for rockets, e.g. mounting or sealing rockets therein
    • 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
    • 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
    • F41F3/077—Doors or covers for launching tubes

Definitions

  • the present invention relates to a device for launching missiles, in particular a rocket and/or a capsule.
  • Rockets When rockets are launched into space or into orbit outside the atmosphere, most of the energy is used to launch the rocket or missile from the Earth's surface and transport it through the atmosphere. This involves multiple propulsion stages, which are then detached and burn up after they have burned up. This means that these multiple propulsion stages are not reusable. Rockets are usually launched from space centers near the equator in order to achieve optimal entry into orbit from there. Due to the multiple propulsion stages, a rocket weighs several hundred tons at launch, which is essentially achieved by the multiple propulsion stages and the fuel they contain. This means that the payload that can ultimately be transported into space or into orbit is very small compared to the fuel.
  • one of the most commonly used rockets weighs approximately 550 tons at launch, with approximately 23 tons of payload available for reaching low-Earth orbit (LEO). This means that the payload represents only 4.2% of the total weight.
  • LEO low-Earth orbit
  • the payload drops further to 8.3 tons, or 1.5% of the total launch weight.
  • the object of the invention is therefore to increase the payload of missiles or to reduce fuel consumption and/or to increase the safety when launching missiles.
  • the invention therefore proposes a device for launching missiles, in particular a rocket or a capsule, in which the rocket or missile is not launched from the earth's surface, but from a launch tunnel projecting substantially vertically into the earth's interior.
  • this launch tunnel is located at a higher level than the sea surface, for example in a mountain range near the equator. Consequently, the first 3,000 to 5,000 m compared to sea level can be covered solely by the higher level in Reaching sea level is achieved using a starting tunnel on a high plateau already present in a mountain. Such high plateaus near the equator are found, for example, in Mexico or Ecuador. Such high plateaus often contain shafts originating from abandoned or still-operating mining operations.
  • a launch tunnel according to the invention preferably extends up to 2 km into the Earth's interior and is dimensioned to accommodate a conventional rocket. However, efficiency improvements are already achieved with a tunnel length of 200 m.
  • the launch tunnel can be equipped with a concrete or steel casing that can withstand the temperatures during rocket launch and accommodate the necessary equipment for the inventive equipment. This means that the rocket travels the first 2,000 meters in a tunnel.
  • a device for launching a missile comprising:
  • a launch tunnel projecting substantially vertically into the earth's interior, the launch tunnel being limited in its lower region, at least one propulsion unit separate from the missile and arranged below the missile in the launch tunnel.
  • a device for launching a missile comprising a launch tunnel projecting substantially vertically into the earth's interior, the launch tunnel being delimited in its lower region, a covering device at least in the upper region of the launch tunnel, and an air extraction device for evacuating air from the launch tunnel.
  • the device according to the invention has an air extraction device that can evacuate the air from the interior of the launch tunnel into another space. This means that the rocket no longer has to overcome the air resistance within the launch tunnel, which reduces the The energy required for launch can be reduced. In other words, the launch energy, i.e., the required fuel, does not have to be carried by the rocket and therefore does not contribute to the total launch weight.
  • a fundamental aspect is the use of a launch tunnel and a launch of the missile from the Earth's interior, preferably from a high plateau.
  • Another aspect is the evacuation of a volume to reduce air resistance during launch within the launch tunnel.
  • Another aspect to reduce the launch weight of the missile is that, unlike conventional rockets, the missile is not powered by multiple propulsion stages of this rocket, but at least one separate propulsion unit is located in the launch tunnel, which is responsible for propelling the missile or rocket within the launch tunnel.
  • the first acceleration from a standstill to, for example, 200 km/h is achieved by one or more separate propulsion units that are not permanently connected to the rocket or missile. At least one separate propulsion unit is located at the lower end of the missile and propels it upwards by igniting or activating the separate propulsion unit. This has the advantage that the separate propulsion unit can remain in the launch tunnel or, after leaving the launch tunnel, be detached from the rocket and fall to the Earth's surface with a parachute, and can therefore be reused if necessary.
  • the separate propulsion unit can only remain in the launch tunnel and thus release the rocket when the exit surface is reached, so that the rocket has already reached the first speed stage of, for example, 500 km/h and only then is a rocket's own propulsion stage ignited, which then provides propulsion to higher orbits or through the atmosphere.
  • This has the advantage that the payload of the rocket can be significantly increased.
  • cover device which is located, for example, at the exit level near the ground surface.
  • This cover device can also consist of several layers that are opened in stages depending on the pressure difference. Different volumes can be separated and evacuated independently using several cover devices.
  • the area of the launch tunnel in which the separate propulsion unit is launched is preferably not evacuated. This means that above the nose of the missile or rocket there is a first layer of a covering device, which forms the lower area of the evacuated space.
  • the upper area or upper cover of the evacuated area is formed by a lid or a layer of the covering device, which is formed at the level of the exit level in the area of the earth's surface. In between is the space that is evacuated. This means that when the separate propulsion stage is launched, the missile begins to move vertically in the launch tunnel and, due to this movement, builds up a pressure wave in front of it.
  • the lower layer of the cover This either causes the lower layer of the cover to open when the pressure falls below the lower layer, or the lower layer of the cover is set so that when a predetermined pressure in the lower area of the launch tunnel is exceeded, this layer of the cover opens and clears the way for the rocket or missile to pass through.
  • a sensor can detect the position of the rocket and control the cover. By opening the lower layer of the cover, the vacuum in the upper area of the launch tunnel is connected to the lower area, so that the rocket is still exposed to lower air resistance, since the total pressure in the combined volume of the launch tunnel is then lower than atmospheric pressure.
  • the rocket then moves further within the launch tunnel towards the exit opening or towards the upper layer of the cover device, whereby the upper layer also consists either of a flexible rubber seal which is then penetrated by the rocket or the upper cover device is opened by a control device using position sensors and/or pressure sensors below the upper layer of the cover device.
  • the separate propulsion unit can, for example, be filled with pressurised steam, which is released during the start-up process in order to generate initial propulsion thrust.
  • the separate drive unit can also be filled with fuel, which is ignited during the starting process.
  • a hydraulic system may be present within the launch tunnel, which controls or drives the separate drive unit and thus moves the separate drive unit with the rocket or missile arranged above it towards the exit opening of the launch tunnel.
  • the separate propulsion unit can be driven by tensioning cables with counterweights.
  • a similar principle to that used for elevators can be used, so that the propulsion unit is guided, for example, in lateral guides in the inner wall of the launch tunnel. Cables are attached to these lateral guides and are coupled to weights or to electric motors that actuate the cables during the launch process and/or pull them downwards via pulleys, thus transporting the propulsion unit upwards, or in the case of an electric motor, the cable is wound onto a winch to achieve initial acceleration of the rocket or missile.
  • the propulsion unit may additionally or alternatively contain one or more explosive charges, which, if appropriately dimensioned, are detonated shortly before the missile exits the launch tunnel, thus moving the separate propulsion unit back into the launch tunnel and ensuring safe detachment of the separate propulsion unit from the missile.
  • the additional explosive charges also provide the rocket with an additional propulsion impulse toward the exit port.
  • the various separate propulsion units can be combined with each other, but they all have in common that the propulsion unit as such remains in the launch tunnel or is reusable and is not firmly connected to the rocket and is not blown off by it, but at most has a connection when the rocket sits on the upper end of the separate propulsion unit, which, however, detaches from the lower part of the propulsion unit when the upper part of the missile or rocket is further accelerated.
  • Another alternative possibility is to first accelerate the propulsion unit with water pressure and later ignite it with a fuel, whereby the water that has escaped from the separate propulsion unit can then be used to cool the exhaust gases in the launch tunnel.
  • the separate propulsion unit may also comprise a container that encloses the missile and opens shortly before or after exiting the launch tunnel to release the missile.
  • the separate propulsion unit comprises a container for the missile and a propulsion stage, which is preferably arranged below the container or the missile in the container.
  • the launch tunnel has a guide device on its inner wall, which is provided for guiding the missile and/or for guiding the separate propulsion unit.
  • This guide device can be a contact-based or a contactless guide device.
  • the drive body is held or guided on its outer circumference by the guidance device, whereby the guidance device is then moved, for example, in lateral slots in the inner wall of the launch tunnel in a vertical direction along the launch tunnel and the drive unit with the missile located thereon is set in motion.
  • Another possibility for driving the rocket or the separate propulsion unit is the use of electromagnets in the form of linear motors.
  • permanent magnets can be arranged in the outer wall of the missile or the separate propulsion unit, and windings that generate magnetic fields can be arranged behind or in the inner wall of the launch tunnel. By controlling the various windings, a vertical movement of the missile or the separate propulsion unit is achieved. It is also possible to set the missile or the propulsion unit into rotation by generating magnetic fields on the coils on the inner wall of the launch tunnel, so that the missile rotates around its own axis in order to have more stabilization when exiting the launch tunnel.
  • the guidance device can also be formed by a carriage that surrounds the rocket or the separate propulsion unit and is accelerated in the sense of a rail-gun.
  • the launch tunnel is connected to a compensation chamber, which can be connected to the lower end of the launch tunnel via pipes or lines and valves.
  • the compensation chamber can, for example, be provided by a parallel tunnel, as is often found in abandoned mines.
  • the medium pumped from the compensation chamber into the launch tunnel can be, for example, compressed air or water.
  • the cross-section of the compensating medium connection must be sufficiently large, e.g. several meters, otherwise the friction on the walls could lead to turbulence and possibly cavitation.
  • an upper edge of the launch tunnel is enlarged in diameter compared to the lower area of the launch tunnel. This allows the missile to move in a launch tunnel with an enlarged diameter shortly before exit.
  • This enlarged launch tunnel can either additionally or without an extension have a Ring above the earth's surface or an upwardly projecting shaft that protrudes from the launch tunnel and is arranged above the earth's surface in order to provide a final guide for the exiting missile.
  • the ring or shaft above the earth's surface can have openings on its side walls to discharge exhaust gases or compressed air to the side.
  • the shaft can also be provided with at least one flap located on a side wall, so that when the pressure is sufficient, the exhaust gases cause the flap to open and the exhaust gases can escape through the open flap.
  • Wind deflection devices can be provided on the launch tunnel above the exit level or around the launch tunnel to deflect the crosswind upwards in order to reduce the influence on the upwardly moving rocket.
  • the launch tunnel usually has a length below the earth's surface of at least 200 m or more, in particular 1 km, and preferably the launch tunnel has a length between 500 m and 2 km.
  • a conventional rocket has flown 500 m far or high after about 17 seconds, traveled at about 200 km/h and burned about 40 tons of fuel. This means that even a 200 m deep tunnel would have a measurable effect. The longer the launch tunnel, the better the effect.
  • the shaft above the exit opening is at least 10 m long, preferably at least half the length of the rocket or missile or with a shaft that essentially corresponds to the length of the rocket or missile.
  • the missile is implemented as a capsule that is launched from the launch tunnel and flies back to Earth with a parachute, in order to use unused rocket launchers as an additional leisure attraction for visitors.
  • the capsule can be either fully transparent or partially transparent and/or can be equipped with screens inside so that visitors can experience the capsule's launch.
  • the device according to the invention for launching missiles enables a reduction in the amount of propellant required to propel the missile into orbit.
  • safety risks when detaching propulsion stages from conventional rockets are reduced in that the remaining missile ejected from the launch tunnel either requires a smaller number of propulsion stages or, ideally, no further propulsion stage needs to be detaching, so that ultimately only the separate propulsion unit in the launch tunnel is required for the initial acceleration and, after exiting the launch tunnel, a rocket-specific propulsion stage is ignited, which, however, does not need to be detaching and therefore cannot entail any risk when detaching.
  • the energy required to reach the top of the tunnel is external energy that the rocket does not have to carry, and the rocket's payload can be increased by every ton of rocket fuel saved. For example, if the rocket could be accelerated to 1,000 km/h in the launch tunnel, the payload could be at least quadrupled, or the launch costs reduced by 75%.
  • the rocket already has a relatively high speed when exiting the launch tunnel and is therefore less susceptible to environmental influences such as wind.
  • the external energy to drive the separate drive unit can, for example, be generated regeneratively by charging accumulators to drive electric motors between starts.
  • the system according to the invention is not limited to a specific type of rocket and can be adapted to different types of rockets, that is to say, any further development of a missile can be used with the existing device according to the invention for launching missiles, since the separate propulsion unit and/or the evacuated airspace above the missile can be used with any type of further development of rockets.
  • Fig. 1 shows a schematic overview of a device according to the invention for launching a missile.
  • Fig. 2 shows an alternative embodiment of a device according to the invention for launching a missile during the launch process.
  • Fig. 3 shows a device according to the invention at the time before the launch of the missile.
  • Fig. 4 shows the device according to the invention at the time the missile exits the launch tunnel.
  • Fig. 5 shows a further alternative embodiment of the device according to the invention with a shaft
  • Fig. 6 and 7 show further embodiments of the separate drive unit of the device according to the invention.
  • Fig. 1 shows the device according to the invention for launching a missile 20.
  • the launch tunnel 10 projects essentially vertically into the Earth's interior.
  • the Earth's surface is marked E.
  • the launch tunnel 10 is provided at its upper end with an upper covering device 41.
  • the covering device has a lower covering device 42, which is arranged above the missile 20 and defines the lower end of the space of the launch tunnel to be evacuated.
  • an evacuation space 62 is provided, which belongs to the evacuation device 60 and is connectable to the launch tunnel.
  • the evacuation device 60 or the evacuation chamber 62 is connected to the upper end of the launch tunnel via an evacuation valve 61 and can thus evacuate the air from the upper region of the launch tunnel between the upper layer of the covering device 41 and the lower layer of the covering device 42. This may also require, for example, a pump driven by a control unit (not shown) to evacuate the chamber 10a in the upper region of the launch tunnel.
  • a control unit not shown
  • the missile 20 Located in the lower region 10b of the launch tunnel is the missile 20, depicted here as a rocket equipped with two separate propulsion stages 20b and 20c.
  • the upper region of the missile 20 is designed as a space capsule and, after its stay in space, is returned to the atmosphere to transport the astronauts and/or payload back to Earth.
  • the lower part of the launch tunnel is divided by a further covering device 43 into an area 10b for the missile 20 and the area 10c for the separate drive unit 30.
  • the separate drive unit 30 is located in the lower area 10c.
  • the separate drive unit 30 can be equipped with or driven by various drive energies.
  • the drive unit 30 can be driven electrically, hydraulically, with steam pressure or externally supplied water or steam pressure.
  • a compensation chamber 70 is shown, which is accessible via an operating tunnel 12.
  • the operating tunnel 12 is connected to the launch tunnel 10 via another horizontally running tunnel 14 in order to carry out installation work on the rocket or missile 20.
  • the compensation chamber 70 is connected to the lower chamber 10c of the launch tunnel 10 via a compensation medium connection 13, which also has a valve.
  • FIG. 2 shows a state of the device according to the invention in which both the separate drive unit 30 and the missile 20 have already been moved in the vertical direction within the launch tunnel 10.
  • both the lower layer of the covering device 43 and the middle layer of the covering device 42 were opened.
  • the rocket 20 and also the drive unit 30 have passed through these two covering device layers 42 and 43 within the launch tunnel and the upper part of the missile 20 is already located above the exit opening and the upper layer of the covering device 41 is also already open.
  • the separate drive unit 30 is provided here on its outer circumference with guide devices 50, for example in the form of a carriage which is guided in the inner side wall of the launch tunnel 10 and thus takes over or supports the drive of the separate drive unit 30.
  • the drive unit 30 can, for example, be driven by a linear motor via the guide device 50 or the linear motor can be combined with a combustion stage within the separate drive unit 30 in order to achieve a targeted acceleration of the separate drive unit and, as a result, an efficient acceleration of the missile 20 located above it.
  • a further seal 12a is provided in the operating shaft 12 in order to be able to control the different pressures in the individual tunnels, which are temporarily connected to each other.
  • FIG. 3 shows an alternative embodiment of the system according to the invention at the time before launch.
  • the missile 20 is arranged above a movable carriage 50, which is designed as a guidance device, in the lower region 10b of the launch tunnel.
  • the separate drive unit 30 is arranged below the movable carriage 50.
  • the lower part of the launch tunnel is divided into the spaces 10b and 10c, so that, for example, by supplying a compensating medium from the compensating space 70 via the Compensating medium connection 13 provides an initial acceleration for the separate drive unit 30, and the separate drive unit 30, with the carriage 50 and the flying object 20 located above it, is transported or moved upwards in the launch tunnel.
  • the cover is opened, so that the flying object 20, with the guide carriage 50 and the separate drive unit 30, penetrates the evacuated space 10a and can thus be transported upwards with less effort or with less energy.
  • a combustion stage of the separate drive unit 30 can be ignited, which, together with the guide carriage 50, which can be coupled, for example, to a linear motor, takes over the further drive above the separate drive unit 30 and the guide carriage 50 and the missile 20.
  • the missile 20 comes close to the outlet opening, the pressure between the upper end of the missile 20 and the upper layer 41 of the covering device increases, so that the latter is opened.
  • pressure sensors could be present, for example, which inform a control device about a threshold value being exceeded, which then carries out the opening.
  • the upper layer 41 of the covering device it is also possible for the upper layer 41 of the covering device to open automatically because the pressure below this upper layer 41 becomes so great that the upper layer also oscillates.
  • position sensors can be used to control the covering device.
  • the upper layer 41 it is also possible for the upper layer 41 to consist of a flexible rubber membrane, which is pierced by the upwardly moving rocket 20 as it passes through the exit opening.
  • Fig. 4 shows the device according to the invention, in which the missile 20 with the guide carriage 50 and the separate drive unit 30 has already been transported upwards in the launch tunnel 10 and already protrudes from the exit opening.
  • a special feature of this exemplary embodiment is that the guide carriage 50 extends in a ring shape around the drive unit 30 in the upper region of the drive unit 30, so that the drive unit 30 projects, for example, into a central lower region of the annular carriage 50 and is connected there in a form-fitting and/or force-fitting manner.
  • the annular guide carriage 50 forms a seal between the lower space 10c of the launch tunnel and the central space 10b of the launch tunnel, so that different pressures can arise in these two spaces.
  • a further advantage of this embodiment is that, for example, by electromagnetic guidance of the guide carriage 50 within the launch tunnel 10, the guide carriage 50 can be stopped at the end of the launch tunnel in the area of the exit opening, in order to to remain in the launch tunnel 10.
  • the use of the guide carriage 50 also results in a structural separation from the propulsion unit 30, so that the missile 20 or the rocket's own propulsion stage (not shown here) and the exhaust gases of this rocket's own propulsion stage are separated from the exhaust gases of the separate propulsion unit upon ignition.
  • the guide carriage is essentially made of metal and can also comprise thermally resilient ceramics in order to thus keep the heat away from the separate propulsion unit arranged beneath the carriage.
  • the upper layer 41 of the covering device is open.
  • Fig. 5 shows another embodiment of the device according to the invention for launching missiles.
  • an upwardly projecting shaft 45 is provided, which projects above the earth's surface E.
  • the separate propulsion unit 30 is still located in the launch tunnel 10 and is blasted off the missile 20 in the region of the exit opening, for example by an explosive charge.
  • the resulting outlet gases can escape laterally through openings not shown in detail in the shaft 45, which can also be provided, for example, with flaps 46.
  • the exhaust gases produced when the rocket's own propulsion stage (not shown) is ignited can also escape.
  • Fig. 6 shows an embodiment in which the missile 20 and the separate drive unit 30 are located in the launch shaft and a schematically illustrated guide device is located on the sides of the launch shaft 10.
  • the guide device is provided in the form of grooves in the wall of the launch tunnel, into which the guide elements 50 of the drive unit 30 engage and ensure a stable vertical movement when guiding the separate drive unit 30 upwards. Because the lateral guide grooves 51 end at the end of the launch shaft, the separate drive unit 30 automatically remains in the launch tunnel.
  • Fig. 7 shows an embodiment in which the drive unit 30 and/or the missile 20 are provided with permanent magnets in their outer wall, which are driven by coils 53 arranged along the inner wall of the launch shaft.
  • the coils 53 are arranged circumferentially around the cylindrical launch shaft and can thus cause a linear movement of the missile 20 or the separate drive unit 30 through targeted control.
  • the missile or the drive unit 30 can be set in rotation in order to achieve further stabilization of the flight behavior.
  • the exit opening is closed with the upper layer 41 of the covering device and opens when the missile approaches the launch shaft, so that it can pass through the exit opening unhindered.
  • these embodiments do not provide a cylindrical launch shaft, but rather a funnel-shaped wind deflection device 47 that widens towards the top. This wind deflection device 47 not only serves to deflect the wind, but also to retain the exhaust gases emitted by the missile.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Plasma & Fusion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention concerne un dispositif de lancement d'objets aéroportés, en particulier de fusées et/ou d'une capsule. Afin d'augmenter la charge utile d'objets aéroportés ou de réduire la consommation de carburant et/ou d'augmenter le degré de fiabilité lors du lancement d'objets aéroportés, un dispositif est divulgué pour lancer un objet aéroporté (20), ce dispositif comprenant : un tube de lancement (10) faisant saillie sensiblement verticalement dans le sol, ledit tube (10) étant délimité dans sa région inférieure, et au moins une unité d'entraînement (30) séparée de l'objet aéroporté (20) et disposée dans le tube de lancement (10) au-dessous de l'objet aéroporté (20), ou un dispositif pour lancer un objet volant (20), comprenant : un tube de lancement (10) faisant saillie sensiblement verticalement dans le sol, ledit tube (10) étant délimité dans sa région inférieure, un dispositif de couverture (40) au moins dans la région supérieure du tube de lancement (10), et un dispositif d'aspiration d'air (60) afin d'évacuer l'air du tube de lancement (10).
PCT/EP2024/074842 2023-09-05 2024-09-05 Dispositif de lancement d'objets aéroportés Pending WO2025051864A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102023123898.1 2023-09-05
DE102023123898.1A DE102023123898A1 (de) 2023-09-05 2023-09-05 Vorrichtung zum Start von Flugkörpern

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WO2025051864A1 true WO2025051864A1 (fr) 2025-03-13

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3131597A (en) * 1961-03-27 1964-05-05 Babcock & Wilcox Co Method of and apparatus for launching missiles
CN1459614A (zh) * 2003-02-21 2003-12-03 孙学年 火箭助力发射装置及其方法
DE10212653A1 (de) * 2001-03-27 2005-12-29 Mbda Uk Ltd., Stevenage Verbesserung bezüglich des Starts von Lenkwaffen
WO2008010180A2 (fr) * 2006-07-17 2008-01-24 Spacego Technologies (Proprietary) Limited Lancement d'un véhicule volant
CN201021884Y (zh) * 2006-05-23 2008-02-13 郑倩 隐式节能高效火箭装配及助射系统

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Publication number Priority date Publication date Assignee Title
DE102008012473A1 (de) * 2008-03-04 2009-09-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Vorrichtung und Verfahren zur Beförderung einer Nutzlast in den Weltraum
US10577129B1 (en) * 2015-05-19 2020-03-03 Peter Davis Poulsen Apparatus and methods for launching a payload
WO2018236938A1 (fr) * 2017-06-19 2018-12-27 EnergeticX.net, L.L.C. Systèmes et techniques de lancement de charge utile
US11041692B1 (en) * 2020-05-12 2021-06-22 Michael Chromych System and method for launching and acceleration of objects
US20230417499A1 (en) * 2022-06-27 2023-12-28 Pipeline2Space, Inc. Dynamic ram accelerator system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3131597A (en) * 1961-03-27 1964-05-05 Babcock & Wilcox Co Method of and apparatus for launching missiles
DE10212653A1 (de) * 2001-03-27 2005-12-29 Mbda Uk Ltd., Stevenage Verbesserung bezüglich des Starts von Lenkwaffen
CN1459614A (zh) * 2003-02-21 2003-12-03 孙学年 火箭助力发射装置及其方法
CN201021884Y (zh) * 2006-05-23 2008-02-13 郑倩 隐式节能高效火箭装配及助射系统
WO2008010180A2 (fr) * 2006-07-17 2008-01-24 Spacego Technologies (Proprietary) Limited Lancement d'un véhicule volant

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