WO2018127603A1

WO2018127603A1 - Hybrid transport carrier system

Info

Publication number: WO2018127603A1
Application number: PCT/EP2018/050460
Authority: WO
Inventors: Thomas Kunze
Original assignee: Thomas Kunze
Priority date: 2017-01-09
Filing date: 2018-01-09
Publication date: 2018-07-12
Also published as: DE102017117461A1

Abstract

The invention relates to a transport carrier system (1), having at least one elongate take-off and landing ramp (2) and at least one flying object (3), which is designed to take off and land on the take-off and landing ramp (2), wherein an electromagnetic catapult (4) associated with the take-off and landing ramp (2) is designed to accelerate or brake the flying object (3) along the take-off and landing ramp (2).

Description

The invention relates to a transport carrier system with at least one elongated take-off and landing ramp, at least one flying object, which is designed to take off and land on the take-off and landing ramps.

Such transport carrier systems have long been known and are used regularly in aviation. A disadvantage of these transport carrier systems that require the flight objects own drives for acceleration. Depending on the field of application, such a drive can make up a large part of the mass of the flying object. The higher the proportion of the drive to the mass of the flying object, the lower the payload of the flying object can be. This makes the transportation of goods and passengers inefficient and costly.

The object of the invention is therefore to provide a device which overcomes the disadvantages described and allows a high payload.

This object is achieved by a device according to claim 1. Because an electromagnetic catapult assigned to the take-off and landing ramp is designed to accelerate or decelerate the flying object along the take-off and landing ramp, the proportion of the drive at the mass of the flying object can be significantly reduced. In addition, can be dispensed with in certain applications entirely on a drive. The fact that the catapult is also designed to decelerate the flying object can also on its own brakes and on a chassis on the Flight object to be waived. This also increases the possible payload of the flying object and thus makes the transport of goods and passengers more efficient and cost-effective.

Advantageous embodiments and modifications of the invention will become apparent from the dependent claims.

According to an advantageous embodiment of the invention, it is provided that the catapult is designed to accelerate the flying object along the take-off and landing ramp to a cruising speed at which the flying object flies independently, essentially due to its own inertia. Such an acceleration ensures that the flying object goes into flight operation even with complete absence of its own drive.

Particularly advantageous is the embodiment that the flying object has at least one auxiliary drive, which is designed to obtain the travel speed achieved on the take-off and landing ramp and serves to increase the range. Such an auxiliary drive makes it possible to maintain the speed of the flying object achieved with the catapult and thus to ensure a longer and safer flight of the flying object.

According to an alternative embodiment of the invention, it is provided that the flying object has at least one auxiliary drive in the form of an electric propeller drive, wherein the flying object preferably has carbon parts which are designed to store electrical energy for the electric propeller drive, the flying object preferably further comprising a photovoltaic paint on the outside to generate electrical energy for the electric propeller drive. With an electric propeller drive, a very effective and low-emission drive for the flying object is given. The storage of electrical energy in the carbon parts of the flying object allows high ranges through the trained as a propeller drive auxiliary drive. The range of the flying object by such a drive can be further increased by the fact that the outside of the flying object is provided with a photovoltaic coating, so that solar radiation can be used for driving the flying object.

A particularly advantageous embodiment of the invention provides that the flying object has at least one auxiliary drive in the form of a jet engine or rocket drive. Depending on the area of application of the transport system, the use of a jet engine or a rocket engine can also be an effective way of increasing the range achievable with the flying object.

Of particular advantage, according to one embodiment, that the catapult has a guided in rails along the take-off and landing ramps recording system for the flying object. Such a guided on rails recording system is particularly suitable to accelerate the flying object during takeoffs along the launch and landing ramp through the connected catapult or decelerate during landings along the launch and landing ramp through the connected catapult. The guidance of the pick-up system in rails along the take-off and landing ramp enables an excellent and targeted acceleration of the pick-up system through the catapult.

An advantageous embodiment is that the recording system has computer-controlled robot arms with grippers arranged thereon, which are designed to detect the flying object at access points arranged thereon. With such arranged on robotic arms grippers, the flying object can be very easily fixate on the recording system. This makes it easy to perform launches and landing operations of the flying object with the recording system. A preferred embodiment provides that the flying object approaches the receiving system on the take-off and landing ramp during landing, wherein the recording system is adapted to accept the speed of the flying object along the take-off and landing ramp, wherein the receiving system upon reaching the speed of the flying object the flying object is detected and decelerated. The acceleration of the recording system on the approach speed of the flying object allows a special simple detection of the flying object by the pick-up system arranged gripper, which are positioned on computer-controlled robot arms so that the gripper engage in provided on the flying object access points. This can be dispensed with in the flying object on a chassis, which allows significant weight savings and significantly increases the possible payload of the flying object.

Further advantageous is the embodiment that the catapult when braking the flying object in the landing process acts as a generator and fills an energy storage with generated electrical energy, wherein the energy stored in the energy storage is used for starting operations of the flying object. The use of the deceleration movement of the flying object allows a particularly efficient energy management of the transport system, as this energy can be reused for starting operations of the flying object. A preferred embodiment provides that the flying object is designed for the transport of logistics units. The logistics units that can be transported with the flying object can be configured very differently and serve different fields of application. With these logistics units that can be transported by the flying object, it is very easy to transport a wide variety of goods or even passengers with the transport carrier system.

Further features, details and advantages of the invention will become apparent from the following description and from the drawings. An embodiment of the invention is shown purely schematically in the following drawings and will be described in more detail below. Corresponding objects are provided in all figures with the same reference numerals. Show it:

Figure 1 according to the invention

Transport carrier system

FIG. 2 detailed view of the receiving system, Figure 3 transport carrier system with two start and

Landing ramps

Figure 4, 5 u. 6 take-off and landing ramp with two parts

Pick-up system, Figure 7 Landing and landing ramp with two-parted

Pick-up system and rope,

FIG. 8 Comparison of drive types in FIG

Aerospace.

In the figures, designated by the reference numeral 1, a device according to the invention is shown purely schematically. 1 shows a transport carrier system 1 with an elongated take-off and landing ramp 2. This take-off and landing ramp 2 is approaching a flying object 3 in the landing process, which is designed to take off and land on the take-off and landing ramp 2. The take-off and landing ramp 2 is associated with a catapult 4, which is designed to accelerate and decelerate the flying object 3 along the take-off and landing ramp 2. The catapult 4 has for this purpose synchronously operating linear actuators. The catapult 4 is designed to accelerate the flying object 3 during the starting process to cruising speed, so that the flying object 3 flies independently, essentially due to the inertia of the flying object 3. As can be seen, the flying object 3 on the wings 1 1 own auxiliary drives 5, which serve to obtain the travel speed achieved on the take-off and landing ramp 2 and are used to increase the range. With these auxiliary drives 5, the flying object 3 can also easily return to the runway 2. The auxiliary drives 5 shown here are designed in the form of electric propeller drives. These auxiliary drives 5 are driven by electrical energy stored in the carbon parts of the flying object 3. On the outside of the flying object 3, a photovoltaic paint is provided, which serves to supply power to the electric propeller drives 5 and the energy storage in the carbon parts. The electric propeller drives 5 have the advantage that the flying object 3 can fly very quietly. Depending on the field of application, the auxiliary drive 5 may also be designed as a jet engine or rocket drive. That the take-off and landing ramp 2 associated catapult 4 has a guided in the rails 6, 7 along the take-off and landing ramp 2 recording system 8 for the tramless flying object 3. The parallel rails 6, 7 are embedded on the right and left in the ground next to the take-off and landing ramp 2. The receiving system 8 is formed as a curved gate, which spans the entire width of the launch and landing ramp 2. This arcuate gate of the receiving system 8 has spaced (distance a) skids, which are connected to the electromagnetic catapult 4, wherein the power supply of the catapult 4 via the recessed rails in the ground 6, 7 takes place. In this way, the recording system 8 can be driven through the catapult 4 along the runway 2 on the rails 6, 7 along. In the landing process shown here, the flying object 3 approaches the receiving system 8 on the runway 2. The movement of the flying object 3 during the landing process is indicated by the arrow 12 below the flying object 3. In the landing process, the flying object 3 sinks in the direction of the recording system 8 and slows down. The recording system 8 is designed to assume the speed of the flying object 3 during the landing process, wherein the recording system 8 detects this on reaching the speed of the flying object 3 with sufficient approach and decelerates. The movement of the receiving system 8 is indicated by a wide arrow 13 below the receiving system 8. The point at which the flying object 3 can be detected by the receiving system 8 is indicated by a transverse line 14 to the take-off and landing ramp 2. For detecting the flying object 3, the recording system 8 has multi-axis, computer-controlled robot arms 9 with grippers 10, which are designed to detect the flying object 3 at access points arranged on the underside. The access points are designed as holding troughs, in which latching devices of the grippers 10 positively engage. At the point 14 at which the movable robot arms 9 with their grippers 10 can detect the flying object 3, the flying height of the flying object 3 over the take-off and landing ramp 2 is very low, as indicated by the distance b. In the embodiment shown here, the receiving system 8 has six robot arms 9 with grippers 10, which can be moved on a carriage 15 transversely to the elongated extent of the launch and landing ramp 2 in order to capture the approaching flying object 3 can. These settings by the Carriage 15 are indicated by the two transverse to the start and Landerampe 2 arrows 1 6. The receiving system 8 may also have a plurality of fixedly arranged on the arcuate gate robot arms 9, in which case only the robot arms 9 detect the flying object 3 in the landing process, which are in range. After detection of the flying object 3 by the skyward gripper 10, the recording system 8 is braked in the catapult 4, so that the detected flying object 3 is decelerated. During deceleration of the flying object 3 in the landing process, the catapult 4 serves as a generator and stores electrical energy generated during the landing process in an energy store of the transport carrier system 1. The energy stored in the energy store of the transport carrier system 1 can be reused to supply the catapult 4 during takeoff operations of the flying object 3. Thus, the flying object 3 needed for take-offs only one remaining on the ground energy source, which can be significantly reduced weight, which is the payload of the flying object 3 to good. The electrical energy generated during the landing process can also be stored in the carbon parts of the flying object 3. The flying object 3 can preferably be controlled remotely, so that a cockpit can be dispensed with. This also allows savings in the weight of the flying object 3 and an increase in the payload possible. In addition, such a remote-controlled flying object 3 can easily control dangerous missions, for example in crisis areas. Particularly preferably, a pilot is equipped in a control center with a VR glasses to take over the remote control of the flying object 3. Via the VR glasses, the remote pilots receive video live images in order to operate the flying object 3 from a safe environment. Such a pilot can work in the control center in shifts and be replaced by a colleague for sufficient rest, which makes the operation of the transport carrier system 1 safer. The flying object 3 can also be accurately controlled by means of a computer by specifying GPS coordinates. The flying object 3 is further designed for transporting logistics units. These logistics units can be ejected to the rear from the flying object 3, which is indicated by the dotted arrow 17 behind the flying object 3. These logistics units can be seats for passengers, which are arranged on a rail system in the flying object 3 and thus in an emergency, an emergency landing require, can be pushed out of the flying object 3 by a rear tailgate on the rails. The ejected benches have GPS-guided paragliders to guide the rescued passengers in this way away from the crash site of the flying object 3 and land safely. The flying object 3 has not shown upper-side breakpoints, through which the flying object 3 can be lifted by means of a crane on the receiving system 8. On the rails 6, 7 of the catapult 4 can also be a snow clearance equipment in the form of a pitch of snow along the runway 2 process, in order to keep these snow-free. In addition, for emergency landing situations, a unit for applying an extinguishing foam carpet along the runway 2 in the rails 6, 7 can be moved. In this way, even conventional aircraft can land safely on the runway 2.

FIG. 2 shows a detailed view of the receiving system 8 with the bridge-like gate. Clearly visible are the parallel skids 18, 19 which engage in the recessed in the ground rails 6, 7 (Fig. 1). About these rails 6, 7 (Fig. 1), the receiving system 8 of the catapult 4 is performed. On the arcuate gate of the receiving system 8 is a transversely to the rail direction of the runners 18, 19 slidable carriage 15 can be seen, are arranged on the multi-axis, computer-controlled robot arms. At the ends of the sky-oriented robot arms 9, grippers 10 are arranged with which the flying object 3 (FIG. 1) can be detected.

FIG. 3 shows a transport carrier system 1 according to the invention for use in orbit. The launch and landing ramp 2 of such a transport carrier system 1 can be arranged in orbit of a planet or moon. The transport carrier system 1 shown here has two interconnected take-off and landing ramps 2, which can be used both on the upper side, as well as on the underside for the take-off and landing of flying objects 3. The flying objects 3 can start and land on the take-off and landing ramps 2 in both directions of the marked x-axis. At the takeoff and landing ramps 2 laterally arranged rocket drives 20 are provided which can be used for targeting and position correction of the takeoff and landing ramps 2. On the take-off and landing ramps 2 are each associated catapults 4 (Fig.1), as they are already and described below. At the side of the take-off and landing ramps 2 there is an impact shield 21 which can be moved in the x-axis along the take-off and landing ramps 2 in order to ward off space debris and other dangerous objects on collision course. On the left start and landing ramp 2 there is a receiving system 8 designed as a double gondola, which will be discussed in more detail below. Between the take-off and landing ramps 2 and the side of the take-off and landing ramps 2 are arranged flying objects 3 which can fulfill different tasks. Some of these flying objects 3 comprise logistics units with energy and crew modules all the way to observatories. The logistics units can be coupled as payload and function modules at the start and landing ramp 2. For this they have a quick connection system of uniform standard. The side-coupled logistics units serve to stiffen the runway 2. They also include active vibration dampers whose vibration is converted and stored as electrical energy. The combination of several launch and landing ramps 2 allows the simultaneous launch of flying objects 3 in opposite directions. This has the advantage that the recoil exerted by starting operations of the flying objects 3 on the take-off and landing ramp 2 can be compensated by opposite starting operations.

With the start of flying objects 3, the position and speed of the launch and landing ramp 2 can be changed. Reciprocal starting operations and landing operations on the take-off and landing ramps 2 lead to a compensation of the movement impulses exerted on the take-off and landing ramps 2. As a result, an effective compensation of the applied motion pulses is possible. With an orbital carrier system 1 according to the invention, flying objects 3 can ultimately be brought together at the same destination despite reciprocal takeoffs in target-opposite directions if a part of the flying objects 3 launched in one direction is deflected by a swing-turn on a massive object. On the other hand, one-way take-offs can be used to accelerate the launch and landing ramps and move them around the universe. The starting of flying objects 3 leads to a massive movement impulse of the flying object 3, passively drives forward due to inertia. Especially in orbit is a supplementary auxiliary drive in the form of a rocket drive to increase the range and for steering maneuvers.

The start and landing ramp 2 shown here is assembled module by module. The individual modules of the take-off and landing ramp 2 themselves represent flying objects 3, which can start in modules from an already assembled take-off and landing ramp 2. Such a modularly disassembled take-off and landing ramp 2 can be assembled during the flight to the destination to a rod-shaped overall structure. The module-disassembled take-off and landing ramp 2 consists of largely identical track sections. These modules are built to a large extent from carbon elements, which are suitable for intermediate storage of electrical energy. In order to decelerate the assembled start and landing ramp 2 at the destination, they can start flying objects 3 in the direction of flight, in order to perform a stepwise pulse feedback and to decelerate the module-assembled start and landing ramp 2 in the target orbit. In this way, an orbital take-off and landing ramp 2 can be decelerated from a speed in the range of 20,000 km / h. Hierdruch can also increase the speed of entrained flying objects 3 again to achieve more distant goals. Arriving at a target planet, the flying object 3 can reduce its speed by swing-by maneuvers in the atmosphere of the target planet until it is possible to use guided parachutes or paragliders for the landing.

The transport carrier system 1 according to the invention can also be used to influence the trajectory of asteroids and comets. For this purpose, runways 2 are saddled up onto the celestial body and the trajectory is briefly and significantly influenced by take-offs of flying objects 3. The Aufsattelung on the celestial body is made by a network of chains or ropes to which the runway 2 can be positioned on the celestial body. To influence the trajectory, several take-off and landing ramps can also be used simultaneously. The launch and landing ramps 2 can be pulled by caterpillar drive, wheel drive or walking drive along the ropes or chains for positioning. Below the Sun paved runway 2 carries a scraper unit underside material from the asteroid or comet and fills this in flying objects 3 start from the runway 2 from. About the recoil impulses of the starting processes of the celestial body can be sufficiently and highly accurately deflected from its trajectory. The trajectory, speed and angular momentum of the celestial body can be changed significantly by starting operations on the take-off and landing ramp 2. The most effective is an alignment of the launch and Landerampe 2 perpendicular to the center of mass of the celestial body, as this is the influence on the trajectory maximum. The flying objects 3 fired by the celestial bodies transport the mined material to other take-off and landing ramps 2, from which the cargo is commercialized or scientifically examined. Typically, they are picked up by orbital runways 2 to be used as a counterbalance for takeoffs in the opposite direction. In order to neutralize recoil pulses in orbital takeoff and landing ramps 2, correspondingly more accelerated flying objects 3 are started in the opposite direction for larger quantities of freight. By changing the trajectory by means of the proposed transport carrier system 1, asteroids can also be crashed as impactors on foreign worlds to serve here as a primer for a terraforming process. In this way, atmospheres on distant planets can be influenced and significantly changed.

An inventive transport carrier system 1 can also be used to eliminate space debris. Due to the elongated extension of the launch and landing ramp 2, this offers a large clearance area for objects that are on a collision course. This can be used by the computer-controlled robot arms 9 (Figure 1) special impact shields 21 are grown, which can assume any angular positions. Potential collision objects are detected by radar and the impact signs 21 are positioned protectively over the runway 2. In this way, collision objects can be diverted from their course and, for example, force them to crash on a planetary surface. As a result, entire orbital areas can be cleared snowplow-like with the transport carrier system according to the invention. Under the above In addition, impact shields can be used to protect astronauts in field operations at Runway 2. To alleviate the symptoms of space sickness, the inside of the baffles 21 is structured, preferably spanned by an artificial firmament. FIG. 4 shows a single launch and landing ramp 2 of a carrier system 1 according to the invention. Such a take-off and landing ramp 2 can also fly as a single element in space, wherein the direction of flight in Figure 4, 5, 6 and 7 from top left coming to the right edge of the picture. On the starting and landing ramp 2 shown there is a flying object 3 with heat shield 22 arranged thereon for entry into atmospheres of larger celestial bodies. The flying object 3 is arranged on a receiving system 8 which is designed as a two-part nacelle 24, 25.

FIG. 5 shows a flying object 3 launched to slow down the take-off and landing ramp 2 in front of the flying take-off and landing ramp 2 with a strong start pulse 26 in the direction of flight of the take-off and landing ramp 2. The return pulse exerted on the take-off and landing ramp 2 by the starting process 23 slows the cruising speed of the launch and landing ramp 2 considerably. Persons who are aboard the flying launch and landing ramp 2 rise before the start of the flying object 3 for braking maneuver the flying launch and landing ramp 2 in the front part 25 of the two-piece gondola 24, 25 of the recording system 8. The on the start - and Landerampe 2 by the start of the flying object 3 acting movement pulse 23 is so high that it is incompatible with people, due to the high-acting G-forces. In the front part 25 of the gondola of the receiving system 8 constructed in two parts, the people located there are subjected to lower G forces, since the movement pulse 23 acting counter to the direction of flight moves the front part 25 of the two-part gondola of the receiving system 8 forwards along the take-off and landing ramps 2 accelerates, which is shown by the indicated above the start and Landerampe 2 acceleration 34. This can also be seen in Figure 6, where the front part of the 2-part gondola of the receiving system 8 is located at the end of the take-off and landing ramp, since the counteracting the direction of flight Motion pulse 23 is greater. During the movement along the runway 2, the front part 25 of the two-part nacelle in which the people are located is braked by the rear part 24 of the two-part nacelle of the take-up system 8. If the length of the take-off and landing ramp 2 of the transport carrier system 1 shown here is not sufficient to brake the front part 25 of the two-part nacelle 24, 25 of the receiving system 8 in an acceptable manner, the front part 25 of the nacelle shoots over the take-off and landing ramps 2 and is braked on a wire rope 27, which is arranged as a role in the rear part 24 of the two-part nacelle and is unrolled during deceleration. The rear part 24 of the two-part nacelle remains at the end of the take-off and landing ramp 2 on this and thus brakes the front part 25 of the nacelle. In this way, the transport carrier system 1 according to the invention can be slowed down in human space in space. The transport carrier system 1 according to the invention is also suitable for launching flying objects 3 from a planetary surface into orbit. Especially in this application area, the advantage that the proposed flying object 3 is accelerated by the electromagnetic catapult 4 assigned to the take-off and landing ramp 2 is advantageous. Because in this way the weight for own drives of the flying object 3 can be reduced, whereby a higher weight portion for load is available. Especially for the launch of flying objects 3 from a planet surface into orbit, the reduction of the weight shares for the drives plays a crucial role, since the weight for the drives due to the overcoming attraction of the planet is currently significant in the conventional rocket engines. The cost of propulsion and fuel per unit of payload is immense in conventional rocket engines. With the use of the acceleration exerted by the catapult 4, the flying object 3 according to the invention on the proposed launch and landing ramp 2 can be transported relatively easily from a planetary surface into orbit. A problem in the acceleration of the flying object 3 by the catapult 4 on the proposed launch and landing ramp 2, however, is the presence of the planetary surface atmosphere that can lead to significant air resistance and the flying object 3 in the acceleration the start and landing ramp 2 would burn up even when equipped with currently known, vulnerable heat shields. For this reason, a shell is additionally proposed, which surrounds the start and landing ramp 2 within this shell is a pressure-reduced environment. This shell thus forms an evacuated, tubular chamber through which the take-off and landing ramp 2 is separated from the atmosphere. In order to maintain the vacuum in the tubular chamber, this has at the end of the runway 2 a computer-controlled mouth flap, which is permanently closed, but opens in time as soon as a flying object 3 approaches it. Through the outlet flap can be maintained in the evacuated chamber relative to the surrounding atmosphere reduced pressure conditions and set an exact metered residual atmosphere. In addition, the chamber has a system for influencing the temperature of the air in the mouth region in order to improve the exit of the flying object 3 through the mouth from the chamber. This upright mouth of the transport carrier system 1 should preferably be arranged at the greatest possible height in order to reduce the negative influences of the surrounding atmosphere largely by reducing the air pressure. For this reason, it lends itself to the start and landing ramp 2 of the proposed transport carrier system 1 in the high mountains to arrange. As a result, the effect of the surrounding atmosphere on a flying object 3 emerging from the mouth of the tubular chamber can be significantly alleviated. In addition, by high-performance blower located outside the mouth air can be accelerated already in the direction of the exiting flying object 3 to preferably 750 km / h, which increases the possible exit velocity from the evacuated chamber and the impact in the transition of the flying object 3 from the evacuated chamber into the Atmosphere reduced. By using a corresponding chamber, the required length of the take-off and landing ramp 2 for launching flying objects 3 into orbit can be significantly reduced, which saves costs.

FIG. 8 shows a comparison of different drive types for the start of flying objects 3 in the orbit of planetary surfaces. The lower horizontal line 28 indicates the sea level at sea level. Here there is a mean air pressure of 1013 hPa on the earth. Slightly higher is the starting position 29 a conventional solid rocket, which is transported with solid fuels in the orbit 30. The trajectory of this conventional solid rocket is indicated by the arrow 31 and is accomplished entirely by the rocket engine. This generates significant emissions and consumes a lot of fuel. In contrast, the trajectory of a flying object 3 is shown by the arrow 32 that is started from a take-off and landing ramp 2 of the transport carrier system 1 according to the invention. The lower dashed portion of this arrow 32 indicates the distance traveled by the flying object 3 by the acceleration of the catapult 4, before an auxiliary drive is used to reach the orbit. The right-hand trajectory 33 shows movement of a flying object 3, which is started by a take-off and landing ramp 2 of a carrier system 1 according to the invention, the ramp being located on a mountainous region. The mouth flap of the chamber surrounding the take-off and landing ramp 2 is arranged here at about 5000 m above sea level. Since there is an air pressure of just 500 hPa, the flight object 3 accelerated via the catapult 4 can cover a significantly longer distance in passive flight before an auxiliary drive is used to reach the orbit 29. This is illustrated by the comparatively higher proportion of the dashed line at the marked trajectory 33. Compared to the conventional drive of rockets, the arrangement in the high mountains and the arrangement of the transport carrier system 1 according to the invention in the lowlands advantages in terms of the required fuel, which must be added to reach the orbit 30. Especially the saving of this fuel increases the payload of the flying object 3 and makes the transport of passengers and goods into orbit 30 cheaper.

The transport carrier system 1 according to the invention is also suitable for extinguishing forest fires or distributing, for example, foods in crisis regions. For this purpose, entire flocks of remote-controlled flying objects 3 can be started from the take-off and landing ramp 2 to supply, for example, rough terrain with extinguishing water. The cost-effective use of the transport carrier system 1 also offers opportunities to use this for plantation irrigation in agriculture. Of particular advantage here is that at the start and landing ramp 2 of a transport carrier system 1 according to the invention at least one float can be arranged so that the launch and landing ramp 2 can be used as a floating base on waters. In this way, the water supply of the starting and landing flying objects 3 can be ensured very easily. As a floating base, the launch and landing ramp 2 of a transport carrier system 1 according to the invention can also be used to supply war zones. With the logistics units of the flying objects 3 it is possible to provide refugees and ground troops with remote control from the air. With their auxiliary drives 5, the flying objects 3 of the transport carrier system 1 are able to arrive precisely determined supply points and drop supplies and weapons and return to the take-off and landing ramp.

Of course, the invention is not limited to the illustrated embodiments. Further embodiments are possible without departing from the basic idea.

- List of Reference Signs -

Bezuaszeichenliste Transport carrier system

Take-off and landing ramp

flying object

catapult

auxiliary drive

Rail A

Rail B

recording system

robot arms

grab

wing

Approaching movement

Movement of the recording system detection point carriage

adjustment

ejection movement

Skid A

Skid B

rocket propulsion

baffle plate

heat shield

Recoil impulse

rear part of the gondola

front part of the gondola

start pulse

Wire rope

sea level

launch site

orbit

Trajectory of full rocket

Trajectory of flying object from lowland Trajectory of flying object from highland 34 Acceleration a Distance of the runners

b parallel altitude at acquisition

- Claims -

Claims

claims

1 . Transport carrier system (1) with

at least one elongated take-off and landing ramp (2), at least one flying object (3), which is designed to take off and land on the take-off and landing ramp (2),

That is, an electromagnetic catapult (4) assigned to the take-off and landing ramp (2) is designed to accelerate or decelerate the flying object (3) along the take-off and landing ramp (2).

2. Transport carrier system (1) according to claim 1, characterized in that the catapult (4) is adapted to accelerate the flying object (3) along the take-off and landing ramp (2) to a cruising speed at which the flying object (3) essentially flies independently due to its own inertia.

3. Transport carrier system (1) according to one of claims 2, characterized in that the flying object (3) has at least one auxiliary drive (5), which is designed to receive the on the take-off and landing ramp (2) reached travel speed and increasing the Range serves.

4. Transport carrier system (1) according to claim 3, characterized in that the flying object (3) has at least one auxiliary drive (5) in the form of an electric propeller drive, wherein the flying object (3) preferably comprises carbon parts, which are adapted to electrical energy for the store electrical propeller drive, wherein the flying object (3) further preferably a photovoltaic paint on the Outside has to generate electrical energy for the electric propeller drive.

5. Transport carrier system (1) according to one of claims 3 or 4, characterized in that the flying object (3) has at least one auxiliary drive (5) in the form of a jet engine or rocket drive.

6. Transport carrier system (1) according to one of claims 1 to 4, characterized in that the catapult (4) in a rail (6, 7) along the take-off and landing ramps (2) guided recording system (8) for the flying object (3 ) having.

7. Transport carrier system (1) according to claim 5, characterized in that the receiving system (8) computer-controlled robot arms (9) with grippers (10) which are adapted to detect the flying object (3) arranged thereon access points.

8. Transport carrier system (1) according to claim 6 or 7, characterized in that the flying object (3) during the landing process the

Receiving system (8) on the take-off and landing ramp (2) approaches, wherein the receiving system (8) is adapted to assume the speed of the flying object (3) along the take-off and landing ramp (2), wherein the receiving system (8) Reaching the speed of the flying object (3) the flying object (3) detects and decelerates.

9. Transport carrier system (1) according to claim 8, characterized in that the catapult (4) during deceleration of the flying object (3) acts as a generator in the landing process and fills an energy storage with generated electrical energy, wherein the energy stored in the energy storage for starting operations of the flying object (3) is used.

10. Transport carrier system (1) according to one of claims 1 to 9, characterized in that the flying object (3) is designed for the transport of logistics units.