DE102017203302A1 - Landing gear and ground transport vehicle for space transport systems - Google Patents

Abstract

The present application relates to a take-off undercarriage for a space transport vehicle (12) which starts in a horizontal configuration and comprises a trolley (10) with a frame (14) and wheels (16) suitable for non-rail rolling, and a fastening means (20) for transporting the space transport vehicle (12 ) and the trolley (10) releasably attached to each other. The launching trolley is characterized in that the trolley (10) is adapted to be moved under the spacecraft (12) carried by a spacecraft vehicle landing gear (18) to move the spacecraft (12) and trolley (10) through the attachment means (10). 20) to each other.

Description

TECHNICAL AREA

The present invention relates to a launch landing gear for a spacecraft launching in a horizontal configuration comprising a trolley with a frame and wheels suitable for non-track rolling, and a fastener for releasably securing the spacecraft and trolley together. The invention further relates to a space transport system with such a takeoff landing gear and a method for connecting a spacecraft equipped with a landing gear and a take-off landing gear with a trolley.

STATE OF THE ART

Space transport systems can always start vertically or horizontally. Most currently known space transport systems are started vertically. In the vertically deployed systems conventionally used, the vast majority of the space transport system is used and destroyed only for a single flight, which entails very high costs per launch. Therefore, increased efforts are being made to investigate horizontally launching and landing configurations of space transport systems, in particular to reduce costs, increase flexibility and robustness of deployment of such space transport systems, and reuse equipment as much as possible.

A fundamental disadvantage of a horizontally launching space transport system lies in the fact that for the launch of a very strong and therefore relatively heavy starting gear is required, which reduces the payload capacity of such a spacecraft considerably and in many cases even the feasibility of such a configuration in question.

In space transport vehicles, there are significantly higher requirements for the landing gear than for the landing gear, because, firstly, the takeoff mass of a spacecraft is much higher than its landing mass, since an extremely large amount of fuel is consumed for a flight into orbit, and because secondly, it requires a much higher speed for launch than for landing. Herein, the requirements for the landing gear of a horizontally launched spacecraft differ substantially from those of aircraft in which the loads on the landing gear during landing can be quite higher than at takeoff.

Basically known concepts for a horizontal launch of a space transport vehicle therefore provide start-up assistance systems, such as electromagnetic rail acceleration systems. However, these concepts are currently impractical in terms of their flexibility, operational robustness, infrastructure costs and the resulting cost / benefit ratio, so that horizontally launched space transport systems have never been able to reach prototype status or even mass production.

PRESENTATION OF THE INVENTION

In view of the known space transport vehicles, an object of the present invention is to provide a launch gear of the above technical field which is suitable as a flexible, reliable and relatively inexpensive start-up assistance system for a spacecraft launching in a horizontal configuration. In particular, the object of the present invention is to provide a take-off undercarriage for a spacecraft launching in a horizontal configuration, with which it is possible to minimize the empty mass of the spacecraft and thus to maximize its payload. A further aspect of the object of the present invention is to design such a starting chassis as flexibly as possible and in particular without binding to existing rails or similar infrastructure.

This object is achieved by a start chassis according to claim 1. Further, the object is achieved by a space transportation system according to claim 9 and a method for connecting a spacecraft equipped with a landing gear and a launch gear with a trolley according to claim 11. Advantageous developments of these aspects of the invention will become apparent from the respective dependent claims.

An inventive landing gear for a spacecraft launching in a horizontal configuration comprises a trolley with a frame and edges suitable for non-rail rolling, and a fastener for releasably securing the spacecraft and trolley to each other. The launch landing gear according to the invention is characterized in that the rolling truck is adapted to be moved under the space transport vehicle carried by a spacecraft-side landing gear to secure the space shuttle vehicle and the trolley to each other through the attachment means.

The edges suitable for track-less rolling are at least by three wheels, preferably by at least four wheels, these wheels may optionally also as a multiple wheels, especially with twin tires, may be formed.

In order to be rail-unbound, that is not bound to a rail system, the edges are preferably provided with tires, preferably rubber tires, which allow them to roll over an asphalt or concrete surface in a controlled manner and also to make directional changes and braking maneuvers.

The trolley, which is designed according to the invention to be moved under the space transport vehicle carried by the space transport vehicle landing gear spacecraft is particularly dimensioned so that it fits under the space transport vehicle and thereby absorb the space transport vehicle-side landing gear in space or avoid it, so that the Landing gear and the trolley do not interfere with each other. Preferably, the trolley thus comprises means for receiving a nose gear and / or main landing gear and / or supporting landing gear of the space transport vehicle when the trolley moves under the space transport vehicle. It is of course irrelevant whether the trolley moves under the space transport vehicle or whether the spacecraft moves on his landing gear on the trolley. In the context of the present invention, a landing gear is understood to mean a running gear which is not designed merely as a runner or similar grinding surface, but on which the space transport vehicle can roll when landing.

The launch landing gear according to the invention, the trolley of which can be driven under the spacecraft in a state where the spacecraft is on its landing gear, basically eliminates the need for cranes or similar peripherals to equip the spacecraft system with the launch gear. The landing gear can be attached to the spacecraft in support of the landing gear to accommodate the start-up, larger forces on the landing gear or allow the complete retraction of the landing gear before take-off, so that the landing gear in terms of landing on the lower mass and lower Aufsetzgeschwindigkeit can be performed much easier. Thus, the lighter landing gear allows an increase in the payload of the space transport vehicle. Likewise, the use of the trolley allows a further increase in payload, since with the aid of a detachable trolley as a start landing gear higher launch speeds can be realized than when using a conventional, spacecraft-fixed landing gear. The higher launch speed allows the generation of a higher buoyancy force at startup, which can be used to increase the entrained fuel mass.

The space transport vehicle, for which the start landing gear according to the invention is provided, thus still has a specific landing gear on which the space transport vehicle can land after its use. This makes the spacecraft very flexible.

At the same time can be started independently of rails or other Starthilfesystemen on a corresponding launch site by the inventive landing gear, which requires only a runway of sufficient length and orientation. Thus, the take-off run of the space transport vehicle can be essentially analogous to all known from aviation rules and reduces the requirements for infrastructure on the ground, which on the one hand allows greater flexibility and on the other hand, a reduction in the cost of launching a spacecraft.

Preferably, the trolley on a brake system, in particular a wheel brake and / or an aerodynamic brake flap and / or a brake screen. By such a braking system, the starting run can be canceled if necessary faster and safer, which means a shortening of the required for the safe start runway length. In addition, a braking system in the landing gear enables it to decelerate automatically after the take-off run and release of the take-off landing gear from the space transport vehicle and can be safely brought to a standstill.

Depending on the version of the take-off landing gear, this can then be towed off the runway or unrolled on its own accord.

A wheel brake has a particularly high efficiency in the low speed range and is particularly suitable for maneuvering the space transport vehicle on the trolley on the ground. An aerodynamic brake flap has a strong braking force when the forward speed of the spacecraft is high. The brake flap thus advantageously supplements the wheel brake and can also be particularly advantageous in combination with the wheel brake, because it can for example lead to a reduction in the buoyancy of the rolling carriage and thus improve the maximum braking power of the wheel brake. Alternatively and additionally, a brake screen or several brake screens can be used, which can act similar to an aerodynamic brake flap and thereby a very large resistance surface offers. The brake flap and the brake screen are particularly suitable for braking assistance during a launch abort or after the take-off landing gear has been released from the space transport vehicle after the take-off run.

In a preferred embodiment, the braking system is suitable for braking the trolley one-sidedly with respect to a longitudinal axis of the starting running gear. This feature can be accomplished by any form of the above brake systems. For example, it is possible to operate on one side only one or more wheel brakes or unevenly distribute the brake pressure on the wheels. Similarly, it is possible to extend an aerodynamic brake flap only on one side of the longitudinal axis of the takeoff landing gear or extend the same extent as possible, which is basically known from aviation flip systems, provided on both sides of the start chassis. Similarly, a braking screen may be arranged asymmetrically and it is possible to provide a plurality of braking screens, from which selectively only one or a part of the existing brake screens is ejected or will. This can be compensated in particular by a unilateral thrust caused turning moment, which is generated for example in an engine failure during startup by the remaining running engine or the remaining running engines and the stronger, the further the still running engine or the still running engines of the longitudinal axis of the space transport vehicle are removed.

Preferably, the trolley on a motor which is designed as a drive for the trolley for maneuvering. With such an engine, it is therefore particularly well possible to drive the trolley under the space transport vehicle. In addition, by this engine and resting on the trolley space transport vehicle can be ranked on the ground, without the need for additional Rangierhilfen such as towing vehicles. Thus, a space transport vehicle can be maneuvered particularly well on the ground by the preferred landing gear, which in turn has significant advantages in terms of flexibility and deployment cost of the spacecraft. In principle, it is also possible for the motor to be provided with a control which cooperates with a remote condition or enables autonomous maneuvering of the trolley. With such an engine, the starting landing gear can also be used to record a landed spacecraft and transport, for example, to an apron of the landing site. Thus, additional towing vehicles or means of transport for a landed spacecraft can be omitted. Finally, a separate drive of the trolley may assist the take-off run of the spacecraft by exerting an additional accelerating force on the spacecraft resting on the takeoff landing gear.

Since the spacecraft has its own landing gear and thus can stand on its own ground, it is possible to easily carry out the attachment means for attaching the launch gear to the spacecraft compared to approaches used in aviation. Thus, a further cost reduction and, above all, an acceleration of the use of the start landing gear and thus of the entire space transport vehicle can be achieved.

In a preferred embodiment, at least one of the wheels of the trolley is pivotable from a forward direction in a transverse direction 90 ° transverse to the forward direction. Preferably, all wheels of the trolley from the forward direction in the transverse direction are pivotable. Such a design of the start chassis allows extreme maneuverability of the space transport vehicle on the ground and further reduces the demands on the bottom-side infrastructure.

In a further preferred embodiment, the take-off undercarriage comprises a flow guiding device which guides an air flow acting on the starting running gear during start-up in such a way that an aerodynamic output force acting on the trolley and aerodynamic lift force acting on the space-transporting vehicle are generated. This flow guiding device can be, for example, a flow area, a wing or some other device which builds up a force between the starting chassis and the space transport vehicle, provided that the system of space transport vehicle and starting chassis moves forward.

This is especially true at the moment of separation of the launch landing gear from the spacecraft, i. when and after the spacecraft rotates for take-off, beneficial. Such a flow guiding device then facilitates a controlled and safe separation of the starting running gear from the space transport vehicle, which can otherwise become problematic, above all with regard to possible turbulences or an abrupt reduction in the load resting on the starting running gear. Thus, therefore, a collision of the start landing gear with the space transport vehicle after releasing the connection between the landing gear and spacecraft can be prevented.

It is further preferred that the launch landing gear further comprises an aerodynamic fairing for reducing the drag coefficient of the Space transport vehicle has. Such an aerodynamic fairing reduces air resistance during take-off and thereby can reduce the required take-off distance. The fairing may also be important if the take-off landing gear is not removed from the spacecraft. This may be important, for example, for overpass flights or test flights, and the speeds prevailing during flight make aerodynamic fairing of the launch landing gear particularly advantageous.

Alternatively and additionally, it is preferred that the frame for a transfer transport is dismantled. Unless the launch landing gear is to be transferred to the spacecraft fixed, a dismountability of the frame increases the flexibility because it facilitates a transfer of the launch chassis and thus makes more cost-effective.

Another aspect of the present invention relates to a space transportation system comprising a space shuttle vehicle starting in a horizontal configuration and a landing gear as previously described. The starting chassis is fastened to the space transport vehicle.

In a preferred embodiment, the space transport system is configured to release the takeoff landing gear from the spacecraft after a takeoff run, which can be accomplished, for example, by dropping or loosening the fastener during rotation or before liftoff.

A method according to the invention for connecting a spacecraft equipped with a landing gear and a launching gear with a trolley includes moving the spaceport vehicle over the trolley on its landing gear, or moving the trolley under the spacecraft on its landing gear and then moving the trolley to the spacecraft is attached. The start chassis in this method can be designed in particular according to one of the embodiments described above. By this method, a very efficient way is provided to connect a space transport vehicle with a detachable starting gear, in particular a crane or similar lifting tools for connecting the space transport vehicle with the starting gear superfluous. Thus, the required infrastructure can be reduced and the costs required for startup can be reduced.

Advantageously, the landing gear of the space transport vehicle is retracted after the trolley has been attached to the space transport vehicle and before the start of the space transport vehicle begins. The landing gear can be spared, which in turn allows a reduction in the weight required for the landing gear, because the landing gear less massive training. Moreover, in such an embodiment, a landing gear retraction mechanism may be omitted during or after take-off, which also reduces the complexity of the spacecraft and thus increases payload.

Advantageously, the space transport vehicle is refueled after the trolley has been attached to the spacecraft. This makes it possible that the space transport vehicle not only rests on its landing gear in the refueled state, but the very high weight of the required for a reaching out of the earth's atmosphere flight fuel is only or at least largely absorbed by the start landing gear. In this way, the advantages made possible by the starting chassis can be realized particularly well.

Further features and advantages of the invention will become apparent from the following description of the figures and the totality of the claims.

list of figures

• 1a to 1f show a preferred embodiment of a takeoff landing gear with a space transport vehicle before, during and after take-off.
• 2a to 2c show a preferred embodiment of a trolley of the launch landing gear and how it is designed to be moved under the space transport vehicle carried by the spacecraft vehicle-side landing gear.
• 3 shows a variant of the trolley 2a to 2c ,
• 4 shows an example of a flow guiding device according to a preferred embodiment.
• 5a and 5b show various brake systems for a starting gear according to a preferred embodiment and
• 6 shows a further preferred embodiment of a takeoff landing gear with space transport vehicle.

WAYS TO IMPLEMENT THE INVENTION

1a schematically shows a trolley 10 a take-off undercarriage according to a preferred embodiment. The trolley 10 has a frame 14 and wheels suitable for non-rail rolling 16 on. At the wheels 16 they are preferably known from aviation or modified edges with rubber tires or the like.

A space transport vehicle 12 is with a landing gear 18 equipped next to the trolley 10 displayed. An arrow illustrates that the spacecraft 12 in the direction of the trolley 10 emotional. For this purpose, the space transport vehicle 12 for example, be moved by a tractor or similar device.

1b shows the in 1a shown constellation of trolley 10 with frame adjustment 14 and wheels 16 and the spacecraft 12 with suspension 18 , In contrast to 1a Figure illustrates a procedure according to which the trolley 10 of the take-off under the space transport vehicle 12 emotional. This is especially preferable when the starting landing gear has its own drive motor that facilitates maneuvering of the takeoff landing gear to the ground. In contrast, a space transport vehicle 12 For weight reasons, usually not equipped with a motor for movements on the ground, so that a driving under the space transport vehicle 12 through the trolley 10 to be preferred.

1c shows a situation in which the trolley 10 with its frame 14 and the edges 16 under the space transport vehicle 12 with landing gear 18 still deployed. In this position, the trolley 10 preferably by a fastener 20 whose location exemplifies in 1e is indicated on the space transport vehicle 12 be attached.

After the spaceport vehicle 12 and the takeoff landing gear through the fastener 20 attached to each other, the landing gear can 18 be retracted. The result of this procedure is in 1d Illustrates where the spacecraft 12 completely on the trolley 10 with frame 14 and wheels 16 rests. In the in 1d shown configuration, the space transport vehicle 12 then maneuvered to a departure point on a runway using the takeoff landing gear. Previously, it is possible the space transport vehicle 12 refueling on the takeoff landing gear without the landing gear 18 to overload, because the starting chassis for the load of the fuel mass of the refueling space transport vehicle 12 is designed while the landing gear 18 according to the much lower landing weight weaker and thus easier to be interpreted.

During take-off, the spacecraft takes 12 one in 1e illustrated rotated position. This leads the nose of the space transport vehicle 12 a pitching upwards, which can be made possible, for example, that the attachment between the start chassis and the space transport vehicle 12 has already been solved in the front area, while the fastener 20 in the rear of the trolley 10 the trolley 10 still with the space transport vehicle 12 combines. It is also possible that no separate fastening means is provided in the front region of the start chassis, but the space transport vehicle 12 here only on the trolley 10 rests. In the in 1e shown relative arrangement of the start landing gear and spacecraft 12 In particular, a flow guiding device described below by way of example may act which provides an additional buoyancy force on the space-transporting vehicle 12 and / or an additional output force on the trolley 10 generated. This will cause a separation of the spacecraft 12 from the trolley 10 made easier to control during startup.

1f shows the trolley 10 with frame 14 and wheels 16 after the spaceport vehicle 12 has detached from the start landing gear and the start chassis can now drive, for example, by its own drive to a position at the example, again connect to another space transport vehicle 12 can be done.

2a to 2c show schematic plan views of a trolley 10 a preferred starting gear. The trolley 10 has the already mentioned elements, the frame 14 and the wheels 16 , on.

As in 2 B can be seen, is the frame 14 of the trolley 10 designed so that it is a recording for a landing gear 18 a space transport vehicle has. For this purpose, individual webs 22 of the frame 14 be folded down to an lane for the landing gear 18 to form the space transport vehicle.

As in 2c can be seen, the webs 22 be folded back after the landing gear 18 the space transport vehicle was taken in the lane, for example, the stability of the trolley 10 for the starting run to increase.

3 shows a variant of the in the 2a to 2c shown trolley 10 in which the wheels 16 from the forward direction can be swiveled by 90 ° transversely to the forward direction. That way, one on the trolley 10 stationary space transport vehicle can also be moved transversely to its longitudinal axis on the ground without having to go through larger curves. This enables a particularly good maneuverability of the space transport vehicle on the ground.

4 shows a schematic view of an exemplary flow guide device 24 of the starting landing gear. Through an inclined surface 24 can be a gap 28 between the sloping surface 24 and a planar bottom 26 of the spacecraft to be formed so that a pressure in this space 28 is increased, which has a buoyancy of the space transport vehicle and an output of the start chassis result. This makes the separation of the space transport vehicle from the starting landing gear particularly safe and controllable.

5a and 5b show preferred braking systems for a start chassis. In 5a It can be seen that on both sides of a longitudinal axis L, which in 5b is indicated, two brake flaps 30 and one brake screen each 32 were extended. In particular, these braking systems serve to decelerate the launch landing gear at high speeds, such as during a launch abort or after the spacecraft transports itself from the trolley 10 has solved. This allows the trolley 10 be stopped within a relatively short distance.

In 5b It can be seen that the braking systems preferred here can also be triggered on one side. Here are only on the right in the direction of the longitudinal axis L sides two brake flaps 30 and a brake screen 32 triggered, which may be useful, for example, if on the right side still a strong driving force acts on the spacecraft, which would otherwise lead to a left turn and probably leaving the runway. In particular, in the event of a start abort, it may take some time before engines set to start power no longer deliver any significant thrust if one or more engines on one side of the space transport vehicle have failed and the launch is aborted. The one-sided operation of the brake system can lead to a faster effect simultaneously with the immediate shutdown of the engines still running and prevent the otherwise threatening directional control loss.

6 shows a further preferred embodiment, in which an aerodynamic fairing 34 of the trolley 10 with frame 14 and wheels 16 is provided. This embodiment is particularly suitable for transfer flights in which the takeoff landing gear is not during take-off or immediately after the spacecraft 12 separated, but with the space transport vehicle 12 is taken.

The above described examples are merely illustrative of the invention in some preferred embodiments and are not intended to be limiting. Moreover, it is possible to combine individual features of individual embodiments with other features of other embodiments.

Claims (13)

A landing gear for a space shuttle (12) launching in a horizontal configuration, comprising a trolley (10) with a frame (14) and wheels (16) suitable for non-track rolling, and attachment means (20) for securing the space shuttle (12) and trolley (12). 10) releasably fastened together, characterized in that the trolley (10) is adapted to be moved under the space transport vehicle (12) carried by a spacecraft vehicle landing gear (18) to move the spacecraft (12) and trolley (10). by the fastening means (20) to fasten together. Start suspension to Claim 1 wherein the trolley (10) comprises a brake system, in particular a wheel brake and / or an aerodynamic brake flap (30) and / or a brake screen (32). Start suspension to Claim 2 , Wherein the brake system is suitable for one-sided braking of the trolley (10) relative to a longitudinal axis (L) of the starting chassis. Take-off landing gear according to one of the preceding claims, wherein the trolley (10) has a motor, which is designed as a drive for the trolley (10) for maneuvering. A landing gear according to any one of the preceding claims, wherein at least one of the wheels (16) of the trolley (10) is pivotable from a forward direction in a transverse direction 90 ° transverse to the forward direction, preferably all wheels (16) of the trolley (10) from the forward direction are pivotable in the transverse direction. Starting landing gear according to one of the preceding claims, further comprising a flow guiding device (24), one on the Starting landing gear acting air flow during a takeoff run such that on the trolley (10) acting aerodynamic output force and on the spacecraft (12) acting aerodynamic buoyancy force is generated. The landing gear of any one of the preceding claims, further comprising an aerodynamic fairing (34) for reducing the coefficient of drag of the launch landing gear. Starting landing gear according to one of the preceding claims, wherein the frame (14) for a transfer transport is dismantled. A space transportation system comprising a space shuttle vehicle (12) launching in a horizontal configuration and a launch gear according to any one of the preceding claims attachable to the space transport vehicle (12). Space transport system after Claim 9 , which is configured to release the takeoff landing gear after a take-off run from the spacecraft (12). Method for connecting a space transport vehicle (12) equipped with a landing gear (18) and a take-off trolley with a trolley (10), wherein the space transport vehicle (12) is moved on its landing gear (18) via the trolley (10) or the trolley (10 ) is moved under the on its landing gear (18) stationary space transport vehicle (12) and wherein subsequently the trolley (10) on the space transport vehicle (12) is attached. Method according to Claim 11 in that the landing gear (18) of the space transport vehicle (12) is retracted after the trolley (10) has been attached to the space transport vehicle (12) and before a take-off run of the space transport vehicle (12) is started. Method according to Claim 11 or 12 wherein the space transport vehicle (12) is refueled after the trolley (10) has been attached to the space transport vehicle (12).

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