Device for launching airborne objects

Abstract

The invention relates to a device for launching airborne objects, in particular rockets and / or a capsule. In order to increase the payload of airborne objects or reduce the fuel consumption and / or increase the degree of reliability when launching airborne objects, a device is provided for launching an airborne object (20), comprising: a launch tube (10) which protrudes substantially vertically into the earth, said launch tube (10) being delimited in the lower region thereof, and at least one drive unit (30), which is separate from the airborne object (20) and which is arranged in the launch tube (10) below the airborne object (20), or a device for launching a flying object (20), comprising: a launch tube (10) which protrudes substantially vertically into the earth, said launch tube (10) being delimited in the lower region thereof, a cover device (40) at least in the upper region of the launch tube (10), and an air suction device (60) in order to evacuate air from the launch tube (10).

Description

Device for launching missiles [1] The present invention relates to a device for launching missiles, in particular a rocket and / or a capsule. [2] 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 uses multiple propulsion stages, which are then blown off 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. [3] For example, one of the most commonly used rockets weighs approximately 550 tons at launch, with approximately 23 tons of payload available to reach a low-Earth orbit (LEO). This means that the payload represents only 4.2% of the total weight. To reach a higher orbit (GTO geostationary transfer orbit), the payload drops further to 8.3 tons, or 1.5% of the total launch weight. [4] To launch the rocket into space or into an orbit outside the atmosphere, a significant portion of the fuel is used to overcome atmospheric drag. For example, a conventional rocket reaches a speed of approximately 1,000 km / h 50 seconds after launch and is then at an altitude of approximately 5.6 km, having already burned 100 tons of fuel. [5] 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. [6] The problem is solved by the features of the independent claims. Advantageous embodiments are specified in the subclaims. [7] 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. [8] Preferably, 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 by the higher level in To achieve this, a starting tunnel is used 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 activities. [9] 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.

[0010] The launch tunnel can be equipped with a concrete or steel casing that can withstand the temperatures encountered during rocket launch and accommodate the necessary equipment for the proposed equipment. This means that the rocket travels the first 2,000 meters in a tunnel.

[0011] If the tunnel were connected to Earth's normal atmosphere, there would be no significant advantage other than the fact that the initial run would take place in a protected environment. However, this protected environment within the launch tunnel requires additional effort to ensure a safe and efficient launch process.

[0012] In one embodiment, a device for launching a missile is specified, comprising:

[0013] 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.

[0014] By using a separate propulsion unit, energy and its weight are shifted away from the missile and no longer need to be transported by the missile. The separate propulsion unit thus lowers the missile's launch weight and reduces the risk typically associated with the detonation of burned propellant stages.

[0015] In another embodiment, a device for launching a missile is specified, 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.

[0016] Launching a missile from a tunnel allows the tunnel to be sealed at least at its top, or exit surface, at the time of launch. Sealing the tunnel allows the interior, or rather the volume, of the launch tunnel to be evacuated before launch, thus further reducing air resistance within the launch tunnel during launch.

[0017] For this purpose, 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 propellant, does not have to be carried by the rocket and therefore does not contribute to the total launch weight.

[0018] That is, there are three essential aspects of the invention which can be applied alone or in combination.

[0019] 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.

[0020] Another aspect is the evacuation of a volume to reduce air resistance during launch within the launch tunnel.

[0021] Another aspect of reducing the launch weight of the missile is that, unlike conventional rockets, the missile is not powered by multiple propulsion stages of this rocket, but rather there is at least one separate propulsion unit in the launch tunnel that is responsible for propelling the missile or rocket within the launch tunnel.

[0022] This means that the initial acceleration from a standstill to, say, 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, can be detached from the rocket and fall to the Earth's surface via a parachute, allowing it to be reused if necessary.Alternatively, the separate propulsion unit can remain in the launch tunnel, releasing the rocket when the exit surface is reached. The rocket has already reached the first speed stage of, say, 500 km / h, and only then is a separate propulsion stage ignited, which then propel it to higher orbits or through the atmosphere. This has the advantage of significantly increasing the rocket's payload.

[0023] With the increasing focus on the commercial use of space, the question of payload transport is of paramount importance, so increasing the payload of rockets can lead to enormous financial savings. Furthermore, safety is a crucial issue when launching missiles or rockets.

[0024] Most safety problems occur during launch or when spent propulsion stages are detached from the rocket body. By using a separate propulsion unit that propels the rocket from below and remains in the launch tunnel upon exiting it, or exits the launch tunnel due to residual energy and then, for example, flies back to Earth's surface via a parachute, the safety risk is greatly reduced, as the rocket is not affected if the propulsion unit is not detached properly or does not burn properly.

[0025] By reducing the air resistance within the launch tunnel due to the evacuation, the fuel consumption can be further or alternatively reduced or the payload can be increased with the same fuel consumption.

[0026] To evacuate the interior of the launch tunnel, a cover device is required, for example, located at the exit level near the 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 multiple cover devices.

[0027] 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 layer of the covering device which is formed at the level of the exit level near the Earth's surface. In between is the space which is evacuated. This means that when the separate propulsion stage is launched, the missile starts moving vertically in the launch tunnel and, due to this movement, builds up a pressure wave in front of it which either leads to the lower layer opening when the pressure reaches a level below the lower layer of the covering device orthe lower layer of the covering device is set in such a way that when a predetermined pressure in the lower area of ​​the launch tunnel is exceeded, this layer of the covering device is opened and clears the way for the rocket or missile to pass through. Alternatively or additionally, a sensor can detect the position of the rocket and control the covering device. By opening the lower layer of the covering device, 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 to the upper layer of the covering device, whereby the upper layer also consists either of a flexible rubber seal, which is then penetrated by the rocket orthe upper cover device is opened by a control device using position sensors and / or pressure sensors below the upper layer of the cover device.

[0028] In a simple design, only an upper cover is used and the lower area of ​​the launch tunnel, where the separate drive unit is located, is also evacuated.

[0029] The separate propulsion unit can, for example, be filled with pressurized steam, which is released during the starting process in order to generate initial propulsion thrust.

[0030] Alternatively or additionally, the separate drive unit can also be filled with fuel, which is ignited during the starting process.

[0031] Alternatively or additionally, a hydraulic system may be present within the launch tunnel, which controls or drives the separate propulsion unit and thus moves the separate propulsion unit with the rocket or missile arranged above it towards the exit opening of the launch tunnel.

[0032] Alternatively or additionally, it is also possible for the separate propulsion unit to be driven by tension cables with counterweights. A similar principle to that used for elevators can be used here, so that the propulsion unit is guided, for example, in lateral guides in the inner wall of the launch tunnel. Attached to these lateral guides are cables coupled to weights or electric motors that actuate the cables during the launch process and / or pull them downwards via pulleys, thus transporting the propulsion unit upwards. In the case of an electric motor, the cable is wound onto a winch to achieve initial acceleration of the rocket or missile.

[0033] The propulsion unit can additionally or alternatively contain one or more explosive charges, which, if appropriately dimensioned, are detonated shortly before the missile exits the launch tunnel. This moves the separate propulsion unit back into the launch tunnel and ensures 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.

[0034] 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 permanently connected to the rocket and is not detached from 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 accelerates further.

[0035] Another alternative possibility is to first accelerate the propulsion unit using water pressure and later ignite it with a propellant, whereby the water that has escaped from the separate propulsion unit can then be used to cool the exhaust gases in the launch tunnel.

[0036] Preferably, the separate propulsion unit can also comprise a container that encloses the missile and opens shortly before or after exiting the launch tunnel to release the missile. This means that the separate propulsion unit comprises a container for the missile and a propulsion stage, which is preferably arranged below the container or the missile within the container.

[0037] In a preferred embodiment, 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.

[0038] This guidance device can be a contact-based or a contactless guidance device.

[0039] In a contact-based guidance 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.

[0040] Another possibility for powering the rocket or the separate propulsion unit is the use of electromagnets in the form of linear motors. For example, permanent magnets could be arranged in the outer wall of the missile or the separate propulsion unit, and windings could be arranged behind or in the inner wall of the launch tunnel to generate magnetic fields. By controlling the various windings, a vertical movement of the missile or the separate propulsion unit is achieved. It is also possible to rotate the missile or the propulsion unit by circulating magnetic fields on the coils of the inner wall of the launch tunnel, causing the missile to rotate around its own axis for greater stability upon exiting the launch tunnel.

[0041] The guidance device can also be formed by a carriage that surrounds the rocket or the separate propulsion unit and is accelerated in the manner of a rail gun.

[0042] In an alternative design, 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 be provided, for example, by a parallel tunnel, such as those often found in abandoned mines. During the launch process, it is then possible to transport a medium from the compensation chamber into the launch tunnel, thus propelling the missile or separate propulsion unit upwards in the launch tunnel.

[0043] The medium pumped from the compensation chamber into the launch tunnel can be compressed air or water, for example. A compensation medium connection exists between the launch tunnel and the compensation chamber, which can be equipped with a valve or lock that can be opened or closed by a control device.

[0044] 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.

[0045] In a further embodiment, the 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 launch. This enlarged launch tunnel can, either in addition to or without an extension, contain 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.

[0046] The ring or shaft above the Earth's surface can have openings in 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 from the expelled exhaust gases reaches a sufficient level, the flap opens, allowing the exhaust gases to escape through the open flap. To counteract the crosswinds that are particularly prevalent on high plateaus, it is advantageous to design the ring or shaft with openings that become increasingly larger towards the top, so that the crosswind acting on the rocket increases progressively towards the top, thus protecting the rocket from crosswind influences for as long as possible, either directly or immediately after exiting the Earth's surface.

[0047] Wind deflectors can be provided on the launch tunnel above the exit level or around the launch tunnel to deflect crosswinds upwards to reduce their impact on the upward-moving rocket. The launch tunnel is typically at least 200 m or more below Earth's surface, particularly 1 km; preferably, the launch tunnel is between 500 m and 2 km long. A conventional rocket will have flown 500 m in 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.

[0048] 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 substantially corresponds to the length of the rocket or missile.

[0049] In an alternative embodiment, the launch vehicle is realized as a capsule that is launched from the launch tunnel and flies back to Earth via a parachute, thus utilizing 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.

[0050] In another alternative embodiment and as a leisure activity and attraction for visitors, it is possible to design a separate propulsion unit as a possibly transparent capsule or as a capsule with transparent areas, so that the user can experience a simulated rocket launch in the launch tunnel, wherein the separate propulsion unit or capsule with the transparent viewing windows is then not ejected from the launch tunnel and is braked at the end of the launch tunnel by means of the guide devices so that the separate propulsion unit or capsule does not exit the launch tunnel.

[0051] When using the compensation chamber, the principle of communicating tubes can be applied, whereby the compensation medium in the form of compressed air or water is then pressed or filled into the launch tunnel in a valve-controlled manner in the other adjacent tunnel(s) in order to push the rocket or separate propulsion unit from bottom to top and thus drive it.

[0052] The missile launch device according to the invention enables a reduction in the amount of propellant required to propel the missile into orbit. In addition, safety risks associated with detaching propulsion stages from conventional rockets are reduced. The remaining missile ejected from the launch tunnel either requires fewer propulsion stages or, ideally, no further propulsion stage needs to be detaching. Ultimately, only the separate propulsion unit in the launch tunnel is required for the initial acceleration. After exiting the launch tunnel, a separate propulsion stage is ignited. This propulsion stage, however, does not need to be detaching and therefore poses no risk upon detachment.

[0053] This means that the energy required to propel the rocket to the top of the tunnel is external energy that the rocket doesn't 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 launch costs reduced by 75%.

[0054] Further advantages of the system are that there is no impact on the environment until the cover device is opened and that large quantities of escaping gases remain within the launch tunnel and can be technically captured and processed there without escaping into the environment.

[0055] In addition, the rocket already has a relatively high speed when it exits the launch tunnel's exit opening and is therefore less susceptible to environmental influences such as wind.

[0056] The external energy to drive the separate drive unit can, for example, be generated regeneratively by charging accumulators to drive electric motors between starts.

[0057] By cleverly combining different propulsion stages, acceleration can be achieved that is gentle on materials, which has a positive effect on the reusability of the components of the missile or the separate propulsion unit.

[0058] Another safety aspect is that if technical irregularities occur, the launch of the rocket can be aborted as long as the rocket is still far enough from the top of the launch tunnel without the launch resulting in the total loss of the rocket.

[0059] The system according to the invention is not limited to a specific type of rocket and can be adapted to various types of rockets, i.e., 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.

[0060] The invention is described in more detail below with reference to figures: 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, and Fig. 6 and 7 show further embodiments of the separate drive unit of the device according to the invention.

[0061] 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. In addition, 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 in this area of ​​the launch tunnel. This evacuation space 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 space 10a in the upper portion of the launch tunnel. Located in the lower portion 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 portion of the missile 20 is designed as a space capsule and, after its stay in space, is returned to the atmosphere to return the astronauts and / or payload to Earth. The lower portion of the launch tunnel is divided by a further covering device 43 into an area 10b for the missile 20 and an 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. For example, the drive unit 30 can be driven electrically, hydraulically, with steam pressure, or with externally supplied water or steam pressure.

[0062] Likewise, combustion of rocket fuel is possible, or movement by means of cables via a guide device 50, which is also indicated here. In the right-hand area of ​​Fig. 1, 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 extending tunnel 14 for performing 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.

[0063] 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. For this purpose, both the lower layer of the covering device 43 and the middle layer of the covering device 42 were opened. This means that 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. It is shown that 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 the drive of the separate drive unit 30 orsupports.

[0064] 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.

[0065] In Fig. 2, 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.

[0066] 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. By means of 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 The compensating medium connection 13 provides an initial acceleration for the separate drive unit 30, and the separate drive unit 30, together with the carriage 50 and the flying object 20 located above it, is transported or moved upwards in the launch tunnel. After approaching the central position 42 of the cover device, the cover device is opened, allowing the flying object 20, together with the guide carriage 50 and the separate drive unit 30, to enter the evacuated space 10a and thus be transported upwards with less effort or less energy.

[0067] After the compensation medium has been introduced from the compensation chamber 70 into the lower region 10c of the launch tunnel 10 and the separate drive unit 30 with the missile 20 and the guide carriage 50 have moved upwards, a combustion stage of the separate drive unit 30 can be ignited, for example. This combustion stage, together with the guide carriage 50, which can be coupled to a linear motor, for example, takes over the further propulsion of the separate drive unit 30 and the guide carriage 50 and the missile 20. When the missile 20 approaches the exit opening, the pressure between the upper end of the missile 20 and the upper layer 41 of the covering device increases, causing the latter to open. For this purpose, pressure sensors could be provided, for example, to inform a control device about a threshold being exceeded, which then initiates the opening.However, 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. Alternatively or additionally, position sensors can be used to control the covering device. 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.

[0068] 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. The guide carriage 50 and the drive body 30, which are either firmly connected to one another or detachably connected to one another, remain in the launch tunnel 10. A special feature of this exemplary embodiment is that the guide carriage 50 extends in a ring 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.

[0069] 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 same applies to the separate propulsion unit 30. Thus, both can be easily reused. 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) separates the exhaust gases of this rocket's own propulsion stage 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.

[0070] Fig. 5 shows another embodiment of the device according to the invention for launching missiles. In this embodiment, an upwardly projecting shaft 45 is provided, which projects above the earth's surface E. As shown in Fig. 5, 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 exit gases can exit laterally through openings not shown in detail in the shaft 45, which can also be provided with flaps 46, for example. Likewise, the exhaust gases generated upon ignition of the rocket's own propulsion stage (not shown) can exit.

[0071] Fig. 6 shows a configuration 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. These guide devices are 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 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.

[0072] Fig. 7 shows an embodiment in which the drive unit 30 and / or the missile 20 are provided with permanent magnets in their outer walls, 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, through targeted control, cause a linear movement of the missile 20 or the separate drive unit 30. By controlling the coils 53 in a rotationally offset manner, the missile or the drive unit 30 can be set in rotation to further stabilize its flight behavior. The exit opening is closed with the upper layer 41 of the cover device and opens as the missile approaches the launch shaft, allowing it to pass through the exit opening unhindered.In order to reduce as much as possible the influence of the missile 20 upon exiting the exit opening, in these embodiments no cylindrical launch shaft is provided, but rather a funnel-shaped wind deflection device 47 which widens towards the top. This wind deflection device 47 not only serves to deflect the wind, but also serves to retain the exhaust gases emitted by the missile.

Claims

Claims 1. Device for launching a missile (20) comprising: a launch tunnel (10) projecting substantially vertically into the earth's interior, the launch tunnel (10) being delimited in its lower region, at least one drive unit (30) separate from the missile (20) and arranged below the missile (20) in the launch tunnel (10).

2. Device according to claim 1, further comprising: a covering device (40) at least in the upper region of the launch tunnel (10), and an air extraction device (60) for evacuating air from the launch tunnel (10).

3. Device for launching a missile (20) comprising: a launch tunnel (10) projecting substantially vertically into the earth's interior, the launch tunnel (10) being delimited in its lower region, a covering device (40) at least in the upper region of the launch tunnel (10), and an air extraction device (60) for evacuating air from the launch tunnel (10).

4. Device according to one of the preceding claims, wherein the separate drive unit (30) remains in the launch tunnel (10) and / or is reusable.

5. Device according to claim 1, 2 or 4, wherein the separate drive unit (30) contains pressurized steam which is released during the starting process and / or contains fuel which is ignited during the starting process and / or wherein the separate drive unit (30) is driven by means of hydraulics within the starting tunnel (10).

6. Device according to one of the preceding claims 1, 2, 4 or 5, wherein the separate drive unit (30) is drivable via tension cables with counterweights; and / or is drivable with one or more electric motors; and / or wherein the separate drive unit (30) contains one or more explosive charges that can be detonated in a targeted manner during the launch process in order to drive the separate drive unit (30) and the missile (20) located above it.

7. Device according to one of the preceding claims 1, 2, 4, 5 or 6, wherein different separate drive units (30) can be combined.

8. Device according to one of the preceding claims 1, 2, 4, 5, 6 or 7, wherein the separate drive unit (30) is first accelerated using water pressure, then a fuel stage of the separate drive unit (30) is ignited, the water serving for cooling and / or subsequently a controlled explosion takes place, which on the one hand further accelerates the missile (20) located above the separate drive unit (30) and on the other hand brakes the separate drive unit (30) in the launch tunnel (10) so that it is not ejected from the launch tunnel (10).

9. Device according to one of the preceding claims 2-8, wherein the covering device (40) comprises a plurality of layers (41, 42, 43) which close a tunnel diameter of the starting tunnel (10).

10. Device according to one of the preceding claims, wherein each layer (41, 42, 43) of the covering device (40) opens at different pressures and releases the launch tunnel (10) upwards and / or wherein at least one layer (41, 42, 43) of the covering device (40) is formed from a flexible material which is penetrated by the missile (20) and / or wherein the missile (20) builds up pressure during an upward movement in the launch tunnel (10) in order to open the covering device (40).

11. Device according to one of the preceding claims, wherein the launch tunnel (10) has on its inner wall a guide device (50) for guiding the missile (20) and / or for guiding the separate drive unit (30).

12. Device according to claim 11, wherein the guide device comprises electromagnets (51) which are attached to an inner wall of the launch tunnel (10) in order to accelerate (railgun) and / or stabilize and / or set into a rotational movement the missile (20), and / or the separate drive unit (30) and / or a carriage (52) surrounding the missile (20).

13. Device according to one of the preceding claims, wherein a compensation chamber (70) is coupled to the launch tunnel (10) and / or during the launch process a medium is conveyed from the compensation chamber (70) into the launch tunnel (10) in order to move the missile (20) and / or the separate drive unit (30) upwards in the launch tunnel (10) and / or air or water serves as the medium.

14. Device according to one of the preceding claims, wherein a compensation medium connection (13) is present between the starting tunnel (10) and the compensation chamber (70), which can be opened or closed by a control device (100).

15. Device according to one of the preceding claims, wherein an upper edge of the launch tunnel (10) is widened compared to the lower region of the launch tunnel (10) and / or wherein the launch tunnel (10) has a ring or shaft (45) above the exit level.

16. Device according to claim 15, wherein the ring or shaft (45) has openings in a side wall to discharge exhaust gases or compressed air laterally and / or the shaft (45) has at least one flap (46) located on the side wall, which opens at a correspondingly high pressure within the shaft (45) to discharge the exhaust gases or compressed air laterally and / or the ring or shaft (45) comprises holes that become increasingly larger towards the top, so that crosswind only increases progressively.

17. Device according to one of the preceding claims, wherein the launch tunnel (10) above the exit level (E) has wind deflection devices (47) which deflect crosswind upwards.

18. Device according to one of the preceding claims, wherein the launch tunnel (10) has a length below the earth's surface of at least 200 m, preferably a length between 500 m and 2 km.

19. Device according to one of the preceding claims, wherein the missile (20) is designed as a capsule, preferably an at least partially transparent capsule, or as a rocket with at least one further propulsion stage (21) and is arranged above the separate propulsion unit (30).

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