DE102016111556A1 - track vehicle - Google Patents

Abstract

In order to improve a rail vehicle comprising a vehicle base structure, it is proposed that this comprises an energy absorption device having an at least partially modular construction of a plurality of modules, wherein at least one module comprises an inner shell element and an outer shell element, wherein the inner shell element and the outer shell element to a main axis in a circumferential direction closed around and run the outer shell member has a greater radial distance from the main axis than the inner shell member, so that in the radial direction between the inner shell member and the outer shell member, an intermediate region is arranged to the main axis and in the intermediate region a support device is arranged.

Description

The invention relates to a rail vehicle comprising a vehicle base structure.

Such rail vehicles are known from the prior art.

For example, the rail vehicle includes wheels rotatably mounted on the vehicle base structure.

For example, the rail vehicle is magnetically coupled to a guide rail, in particular, the rail vehicle is a component of a magnetic levitation railway.

The object of the invention is to improve a rail vehicle of the generic type.

This object is achieved in a rail vehicle according to the invention by an energy absorbing device, which has a, at least partially, modular construction of a plurality of modules, wherein at least one module comprises an inner shell member and an outer shell member, wherein the inner shell member and the outer shell member closed about a major axis in a circumferential direction run around and the outer shell member has a greater radial distance from the main axis than the inner shell member, so that in the radial direction between the inner shell member and the outer shell member, an intermediate region is arranged, and in the intermediate region, a support device is arranged.

An advantage of the solution according to the invention is the fact that the energy absorbing device absorbs energy released during an impact of the rail vehicle on an obstacle in the impact and thus protects the energy absorption device in the impact of the vehicle base structure of the rail vehicle from damaging action.

Preferably, the energy absorbing device is arranged in a front region of the rail vehicle, wherein in particular the front region is an end region of the rail vehicle with respect to a direction axial to the main axis, for example, the front region is a front region of the rail vehicle with respect to a direction of travel of the rail vehicle.

Thus, in an impact, the energy absorption device in a particularly favorable manner between the rail vehicle and the obstacle.

Another advantage of the solution according to the invention is the fact that after the impact only those modules are to be replaced, which are destroyed and undamaged modules can be reused.

Furthermore, rail vehicles according to the invention can be used with such an energy absorption device even without a mechanical coupling, which are partially energy-absorbing in rail vehicles from the prior art and thus also fulfill a protective function.

Another advantage of the solution according to the invention is that the rail vehicle and the energy absorption device can be produced in lightweight construction.

It is advantageously provided that the energy absorption device is integrated into an outer structure of the rail vehicle.

Particularly preferably, the energy absorption device is formed self-supporting, that is, in such an energy absorption device no separate support structure is provided, whereby weight is saved.

With regard to the design of the outer shell element so far no details have been made.

Conveniently, the outer shell element is connected to the support device.

In particular, it is provided that the outer shell element is supported on the support device and thus a stable construction of the module is achieved.

In principle, various shapes for the outer shell element are conceivable.

Preferably, the outer shell member is formed streamlined, that is, the outer shell member is formed according to aerodynamic specifications, so that a low air resistance is achieved.

For example, the outer shell element increases with increasing extent in axial direction to the main axis.

In particular, the outer shell element widens with increasing extent in the axial direction to the main axis, wherein a width of the outer shell element is measured transversely to the axial direction of the main axis.

It is advantageous if a radial distance of the outer shell element to the main axis at least partially increases along the main axis.

In a particularly preferred embodiment it is provided that the outer shell element is formed with increasing extent in the axial direction to the main axis substantially in the radial direction to the main axis diverging, in particular the outer shell element with increasing extent in the axial direction to the main axis substantially to the main axis of the radial direction diverging formed is when the radial distance of the outer shell member to the main axis with increasing extension of the outer shell member in the axial direction to the main axis, preferably monotonously increases.

Preferably, the radial distance of the outer shell element to the main axis in the circumferential direction about the main axis decreases monotonically from a maximum value to a minimum value and monotonically from the minimum value to the maximum value, wherein in particular the radial distance of the outer shell element to the main axis in the circumferential direction about the main axis of the minimum value and the Maximum value at most twice, in particular only once accepted.

It is particularly advantageous if the minimum value and the maximum value of the radial distance of the outer shell element to the main axis increase monotonically with increasing extent of the outer shell element in the axial direction to the main axis.

For example, it is provided that the outer shell element extends substantially in a reference surface closed around the main axis, wherein a radial distance of the reference surface in the circumferential direction around the main axis monotonically increases from a minimum value to a maximum value and monotonically decreases from the maximum value to the minimum value and the minimum value and the maximum value monotonously increase in the axial direction to the major axis.

In particular, the outer shell element extends substantially in the reference surface when an extension of the outer shell element within the reference surface larger, in particular by a factor of 5 larger, preferably by a factor 10 greater than an extension of the outer shell element transverse to the reference surface.

In particular, the radial distance of the reference surface in the direction of rotation about the main axis assumes the minimum value and the maximum value in each case at most twice, in particular only once.

This achieves a stable and aerodynamic design of the outer shell element.

In a particularly advantageous embodiment, it is provided that a thickness of the outer shell element increases with increasing extent of the outer shell member in the axial direction to the main axis, wherein the thickness of the outer shell member from one of the main axis averted outside of the outer shell member to a main axis facing inside of the outer shell member measured becomes.

Thus, a progressive destructive behavior of the outer shell element is achieved, that is, in an axial direction to the main axis acting force, the outer shell member in the axial direction increasingly piecewise deformed and thus exploited the energy absorption potential of the outer shell element particularly favorable.

For example, the thickness of the outer shell element is greater than 0.5 mm, preferably greater than 1 mm, preferably greater than 3 mm, in particular greater than 5 mm.

For example, the thickness of the outer shell element is less than 25 mm, preferably less than 20 mm, in particular less than 15 mm.

In a particularly preferred manner, it is provided that the ratio of the radial distance of the outer shell element to the main axis with respect to the thickness is smaller than 10, more preferably smaller than 7, wherein in particular when the radial distance and the thickness along the extension in the axial direction to the main axis vary, the ratio of the radial distance to the thickness along the entire extent of the outer shell element in the axial direction to the main axis is smaller than 10, in particular smaller than 7.

In principle, the outer shell element may comprise a wide variety of materials.

In particular, the outer shell element comprises a, in particular thermosetting plastic, for example epoxy resin.

For example, the outer shell element comprises a thermoplastic material.

In particular, the outer shell element is formed from a high-performance thermoplastic.

Preferably, the outer shell element is at least partially formed from a polymer composition.

It is particularly advantageous if the outer shell element is formed from a fiber-reinforced material composition.

In particular, the outer shell element comprises glass fibers.

For example, the outer shell element comprises aramid, in particular aramid fibers.

In a preferred embodiment, the outer shell member comprises carbon fibers.

It is particularly favorable if the fibers are aligned substantially isotropically.

By way of example, the fibers are arranged isotropically in a reference surface that is closed in the circumferential direction in a circumferential direction.

In a further particularly advantageous embodiment it is provided that the fibers are oriented substantially in the axial direction to the main axis, for example, an orientation of at least 80% of the fibers at an angle to the axial direction to the main axis, which is smaller than 40 °, preferably less than 20 °.

In a particularly advantageous embodiment, it is provided that the outer shell element is formed from a fiber-plastic composite, for example from a glass-fiber-epoxy resin composite.

With regard to the design of the inner shell element so far no further details have been made.

Conveniently, the inner shell member and the support device are interconnected.

In particular, it is provided that the inner shell element supports the support device.

In a particularly preferred embodiment, it is provided that the inner shell element, in particular by means of the support device, supports the outer shell element.

For a particularly stable construction of the module is realized, in which the module has a large energy absorption potential.

In principle, different shapes of the inner shell element are possible.

For example, the inner shell element extends substantially in the axial direction to the main axis substantially parallel to the main axis, for example cylindrical.

Preferably, the inner shell element increases with increasing extent in the axial direction to the main axis.

It is particularly favorable if the inner shell element widens with increasing extent in an axial direction to the main axis, wherein a width of the inner shell element is measured transversely to the axial direction of the main axis.

In particular, a radial distance of the inner shell element to the main axis at least partially increases along the main axis.

In a particularly preferred embodiment it is provided that the inner shell element is formed with increasing extent in the axial direction to the main axis substantially in the radial direction to the main axis diverging, in particular the inner shell element with increasing extent in the axial direction to the main axis substantially diverging in the radial direction to the main axis is formed when the radial distance of the inner shell member to the main axis with increasing extension of the inner shell member in the axial direction to the main axis, preferably monotonously increases.

Thus, a stable construction of the inner shell element is achieved with a progressive path-force ratio.

For example, it is provided that the inner shell element and the outer shell element extend substantially parallel to the main axis in the axial direction.

However, it is particularly advantageous if the inner shell element extends in an axial direction to the main axis at a smaller angle to the main axis than the outer shell element.

This is provided in a particularly preferred manner, that the radial distance of the outer shell member increases toward the main axis with increasing extent of the outer shell member in the axial direction to the main axis stronger than the radial distance of the inner shell member to the main axis with increasing extension of the inner shell member in the axial direction increases towards the main axis and so on Distance in the radial direction to the main axis between the inner shell element and the outer shell element with increasing extent of the inner shell element and the outer shell member increases in axial direction to the main axis.

This results in an advantageous axial direction to the main axis progressive destruction behavior of the module and the energy absorption potential of the module is exploited particularly favorable.

For example, the distance between the inner shell element and the outer shell element in the radial direction to the main axis is greater than 3 mm, in particular greater than 5 mm, preferably greater than 10 mm, for example greater than 20 mm.

In particular, it is provided that the distance in the radial direction between the inner shell element and the outer shell elements is less than 300 mm, advantageously less than 250 mm, preferably less than 200 mm, in particular less than 150 mm.

In a preferred manner, it is provided that the inner shell element is made stiffening.

Various possibilities are conceivable, such as the stiffening takes place.

For example, stiffening elements, in particular stringers and frames, are provided.

In a particularly advantageous embodiment, the inner shell element is stiffening geometrically structured, that is, that the inner shell element is formed stiffening by its geometric structure.

Thus, the inner shell element itself is advantageously made more stable and in particular no additional stiffening elements are necessary, so that a lighter construction of the module is achieved.

For example, the inner shell element comprises at least one bead.

It is particularly advantageous if the inner shell element has at least one depression which is embodied in a direction radial to the main axis, in particular if the inner shell element has a plurality of depressions which are formed in a direction radial to the main axis.

In this case, the recess which is formed in radial direction to the main axis, in particular wall sections which extend transversely to the direction of rotation of the main axis and radially inwardly to the main axis radially inwardly and a bottom portion which has a smaller radial distance from the main axis than a portion of the inner shell member , which is arranged on the recess.

In particular, the depression is arranged between two sections of the inner shell element, which both have a greater radial distance from the main axis than the bottom section.

In a particularly favorable manner, the recess, which is formed in the radial direction to the main axis, elongated in the axial direction to the main axis, for example, an extension of the recess in the axial direction to the main axis is greater than an extension of the wall portion of the recess in the radial direction to the main axis.

In a particularly preferred embodiment it is provided that the inner shell element extends in the direction of rotation about the main axis wave-shaped.

It is particularly advantageous if the inner shell element is curved in the direction of rotation about the main axis alternately in the direction of rotation and concave curved in the direction of rotation, in particular the curvature considered from a radial direction to the main axis outside, convex or concave.

This stiffening of the inner shell element is achieved in a particularly favorable manner and advantageously increases the energy absorption potential of the inner shell element.

For example, a thickness of the inner shell element is substantially constant along an extension of the inner shell element in the axial direction to the main axis, wherein the thickness of the inner shell element is measured from an outer axis of the inner shell element facing away from the main axis to an inner side of the inner shell element facing the main axis.

However, it is particularly preferred if the thickness of the inner shell element increases with increasing extent of the inner shell element in the axial direction to the main axis, so that the inner shell element has a progressive path-force ratio.

In a particularly preferred embodiment, it is provided that the thickness of the inner shell element is less than the thickness of the outer shell element, wherein the thicknesses of the inner shell element and the outer shell element respectively from one of the main axis averted outside of the respective element to one of Main side facing inside of the respective element to be measured.

This advantageously achieves that the outer shell absorbs most of the energy released during the impact.

For example, the thickness of the inner shell element is less than 25 mm, preferably less than 20 mm, in particular less than 15 mm.

In particular, it is provided that the thickness of the inner shell element is greater than 0.5 mm, for example, greater than 1 mm, in particular greater than 3 mm, in particular greater than 5 mm.

It is particularly advantageous if the ratio of the radial distance of the inner shell element to the main axis to the thickness of the inner shell element is smaller than 10, in particular smaller than 7.

It is provided in particular that when the radial distance of the inner shell element to the main axis and / or the thickness of the inner shell element along the extension of the inner shell member in the axial direction to the main axis vary along the entire extent of the inner shell member in the axial direction to the main axis, the ratio of the radial distance Inner shell element to the thickness of the inner shell element is preferably less than 10, in particular smaller than 7.

In principle, the inner shell element may be formed from a wide variety of materials.

In an advantageous embodiment, the inner shell element comprises a plastic.

For example, the inner shell element comprises a thermoplastic material.

In particular, the inner shell element is formed from a high-performance thermoplastic.

It is advantageous if the inner shell element comprises a thermosetting plastic, for example epoxy resin.

In particular, the inner shell member comprises a polymer composition.

It is particularly favorable if the inner shell element is formed from a fiber-reinforced material composition.

Preferably, the inner shell member comprises glass fibers.

In a particularly preferred embodiment, the inner shell element comprises aramid, in particular aramid fibers.

In particular, the inner shell element comprises carbon fibers.

It is particularly advantageous if the inner shell element is formed from a fiber-reinforced plastic composite.

For example, the inner shell element is formed from a glass-fiber-epoxy composite.

In a particularly favorable embodiment, an orientation of the fibers is distributed substantially isotropically.

By way of example, the fibers are arranged isotropically in a reference surface which is closed in the direction of rotation and closes the main axis.

In a further advantageous embodiment, it is provided that the fibers are oriented substantially in the axial direction to the main axis, for example, that at least 80% of the fibers extend at an angle up to 40 °, preferably up to 20 ° in the axial direction to the main axis.

With regard to the design of the support device so far no details have been made.

For example, the energy absorption device also comprises at least one intermediate shell element, in particular a plurality of intermediate shell elements.

In this case, the at least one intermediate shell element and / or the plurality of intermediate shell elements are formed analogously to the inner shell element and the outer shell element, so the at least one intermediate shell element extends in particular closed in the circumferential direction around the main axis and is in radial direction to the main axis between the inner shell element and the Arranged outer shell element, wherein when a plurality of intermediate shell elements are provided, these are closed around the main axis in the circumferential direction and are arranged in radial direction relative to the main axis between the inner shell element and the outer shell element.

In this case, it is advantageously provided that a part of the supporting device extends from the inner shell element to the at least one intermediate shell element and / or up to one of the several intermediate shell elements.

In particular, it is provided that a part of the supporting device extends from the outer shell element to the at least one intermediate shell element and / or up to one of the several intermediate shell elements.

For example, it is provided that a further part of the support device extends from one of the several intermediate shell elements to another of the plurality of intermediate shell elements.

In a particularly preferred embodiment, however, it is provided that the support device extends from the outer shell element to the inner shell element in a direction radial to the main axis.

Preferably, at least one module is designed as a sandwich component.

In particular, the support device comprises a sandwich core of the at least one module designed as a sandwich component.

For example, the sandwich core is formed isotropic.

It is particularly favorable if the sandwich core is designed as a directional core, for example a stiffness of the directional core in a preferred direction is greater than transverse to the preferred direction.

In a particularly advantageous embodiment, it is provided that the support device, in particular the sandwich core, has a honeycomb structure.

It is advantageous if the support device, in particular the sandwich core is tube-like, for example, forms a tube core.

For example, the support device comprises at least one strut.

In particular, the support device comprises at least one stiffening web.

It is particularly favorable if the support device is formed at least partially from ribs.

The support device preferably has a thickness in the direction radial to the main axis which is greater than 5 mm, in particular greater than 10 mm, for example greater than 20 mm.

In particular, the thickness of the support device in the radial direction to the main axis is less than 300 mm, advantageously less than 250 mm, preferably less than 200 mm, for example less than 150 mm.

It is particularly favorable if the supporting device extends in an axial direction to the main axis from a first end region of the module to a second end region of the module.

In a particularly preferred embodiment, the supporting device comprises a filling material, for example a polymer composition, which fills the intermediate area.

As a result, a structurally simple supporting device is provided, wherein, for example, the filling material is filled in a liquid or liquid-like, for example, viscous state into the intermediate region and cures in the intermediate region.

In particular, it is provided that the support device comprises a foam-like structure made of a porous material, for example of epoxy foam.

In this case, the porous material encloses pores of the foam-like structure at least in regions.

Preferably, a characteristic size of the pores is less than 800 .mu.m, in particular less than 400 .mu.m.

In particular, the characteristic size of the pores is greater than 10 microns, for example greater than 50 microns.

This is realized in a particularly favorable manner, a stable yet lightweight support device, which is particularly suitable for lightweight construction.

In a particularly preferred embodiment, it is provided that the support device comprises a plurality of leg parts which form a framework structure, so that the support device is designed to be particularly stable and offers additional energy absorption potential.

In this case, at least some leg parts are arranged, for example, at an acute angle to each other and thus form the framework structure.

In particular, it is provided that at least some leg portions are arranged at an obtuse angle to one another and thus form the framework structure.

In principle, different embodiments of the leg parts are possible.

In particular, it is provided that at least one leg portion is plate-shaped, that is, for example, the leg portion extends substantially in two mutually transverse extension directions.

In a particularly preferred embodiment it is provided that at least one leg part is tubular, that is to say that at least one leg part extends in an elongated extension direction and extends in a second extension direction, the second extension direction corresponds to a circumferential direction about an axis and the axis is aligned substantially parallel to the first direction of extent.

It is particularly favorable if at least one leg part is rod-shaped, that is, for example, at least one leg part extends essentially in an elongated extension direction and a width of the leg part is smaller, in particular smaller by a factor of 5, preferably by a factor of 10 is smaller than an extension of the leg part in the elongated extension direction, wherein the width of the leg part is measured transversely to the elongated extension direction.

For example, each two leg parts are arranged together.

Preferably, three leg parts are arranged each other.

For example, each three leg parts are arranged such that they are arranged triangular in cross section.

In a particularly advantageous embodiment, it is provided that each six leg parts are arranged honeycomb-shaped to each other and thus a particularly stable framework structure is realized.

The leg parts preferably form a core of the at least one module designed as a sandwich component.

For example, the leg parts form a tube core.

It is particularly preferred if the leg parts form a honeycomb core.

For example, it is provided that the filling material is arranged between the leg parts.

In a particularly advantageous embodiment, the support device comprises at least one gas guide channel, in particular for discharging gas from the intermediate region, so that compressed in an impact of the rail vehicle compressed gas from the intermediate region can escape through the gas guide channel and thus an overpressure of existing in the intermediate region Gas is avoided.

For example, the gas guide channel extends through the inner shell element into an interior of the module.

With regard to the design of further modules, no further information has been provided so far.

For example, several modules are constructed analogously.

In a particularly favorable embodiment, it is provided that an elongated extent in the direction of the axial direction of the axial direction of those, in particular analogously formed, modules is larger, which are arranged closer to the vehicle base structure of the rail vehicle.

This is achieved in an advantageous manner that the energy absorption potential of the modules increases in the axial direction to the main axis.

In a particularly advantageous embodiment, it is provided that at least one module of the plurality of modules is designed to be elastically deformable.

This ensures that in a collision of the rail vehicle at a low speed, only the elastically deformable module is deformed and thus no permanent damage to the elastically deformable module and thus also in the entire energy absorbing device and no repair is necessary after such an impact.

Advantageously, it is provided that the individual modules are interchangeable, fixed to each other.

Thus, the modules are fixedly attached to one another in an operating state and are, however, separable again after an impact, so that those modules which have been deformed by the impact are easily exchangeable in the energy absorption device by new modules and thus non-deformed modules can continue to be used, whereby further costs can be saved.

Further features and advantages of the invention are the subject of the following description as well as the graphic representation of several embodiments.

In the drawing show:

1 a partial view of a rail vehicle according to the invention;

2 an exploded view of a first embodiment of an energy absorption device according to the invention;

3 an axial section through a module of the first embodiment of an energy absorption device according to the invention;

4 a schematic path-force diagram of an energy absorption device according to the invention;

5 an axial section through a module of a second embodiment of an energy absorption device according to the invention;

6 a perspective view of an inner shell element of a third embodiment of an energy absorption device according to the invention;

7 a radial section through a module of a fourth embodiment of an energy absorption device according to the invention;

8th a perspective view of a framework structure of the fourth embodiment of an energy absorption device according to the invention;

9 a perspective view of a framework structure of a fifth embodiment of an energy absorption device according to the invention and

10 a perspective view of a framework structure of a sixth embodiment of an energy absorption device according to the invention.

One as a whole 10 designated rail vehicle extends from a first end portion 12 elongated in to a major axis 16 axial direction up to a second end region (by way of example in detail in FIG 1 shown) and includes a vehicle base structure 22 ,

For example, at the vehicle base structure 22 of the rail vehicle 10 bikes 24I . 24II . 24III rotatable about one axis of rotation 26I . 26II . 26III arranged and with the wheels 24 is the rail vehicle 10 on tracks 28 mobile.

Here are the axes of rotation 26 the wheels 24 substantially perpendicular to the major axis 16 oriented, that is an angle between the axial direction of the main axis 16 and the axes of rotation 26 deviates from 90 ° by no more than ± 10 °.

The axial direction of the main axis 16 is in a straight ahead of the rail vehicle 10 essentially parallel to a direction of travel 32 , wherein during a journey of the rail vehicle 10 in the direction of travel 32 the end area 12 a front portion of the rail vehicle 10 corresponds to and in a direction of travel, which is opposite to the direction of travel 32 is, is the end area 12 a rear area of the rail vehicle 10 ,

The rail vehicle 10 includes an energy absorption device 40 which are in the end area 12 is arranged.

The energy absorption device 40 is intended to be at a ride of the rail vehicle 10 in the direction of travel 32 against an obstacle 42 That is, in a collision of the rail vehicle 10 in the area of the end area 12 on an obstacle 42 to absorb energy released by deformation during the impact.

In particular, the energy absorbing device takes 40 at least most of the energy released in the impact, so that no or at most only a small amount of energy to the vehicle base structure 22 is transferred and thus the vehicle base structure 22 no harmful effect is experienced during the impact.

The energy absorption device 40 extends in to the main axis 16 axial direction from a first end 44 to a second end 46 ,

At the second end 46 is the energy absorption device 40 to the vehicle base structure 22 , in particular detachable, mounted and extending from the second end 46 from the vehicle base structure 22 taking off in to the main axis 16 axial direction to the first end 44 ,

This is the first end 44 during a journey of the rail vehicle 10 in the direction of travel 32 the front end of the rail vehicle 10 ,

The energy absorption device 40 widens starting from the first end 44 with increasing extent in to the major axis 16 axial direction to the second end 46 so that a width of the energy absorption device 40 from the first end 44 to the second end 46 increases and the width of the The energy absorbing device 40 transverse to the axial direction of the major axis 16 is measured.

An extension of the energy absorption device 40 in to the main axis 16 radial direction decreases with increasing extension from the first end 44 to the second end 46 too, so that the energy absorption device 40 having different widths, wherein the width transverse to the main axis 16 is measured.

It is preferably provided that the main axis 16 Radial expansion of the energy absorption device 40 in the direction of rotation about the main axis 16 varies around.

In particular, the radial extent of the energy absorption device 40 in the direction of rotation about the main axis 16 around a minimum value and a maximum value, wherein the radial extent of the energy absorption device 40 decreases continuously in the circulation direction from the maximum value to the minimum value and continuously increases from the minimum value to the maximum value.

The minimum value and the maximum value preferably increase with increasing extent in relation to the main axis 16 axial direction from the first end 44 to the second end 46 ,

This is an outside 48 the energy absorption device 40 formed streamlined, so that an air resistance of the energy absorption device 40 during a journey of the rail vehicle 10 in the direction of travel 32 is low.

The energy absorption device 40 is modularly constructed from several modules 52 . 54 , for example, from a front module 52 and three other modules 54I . 54II and 54III ( 2 ).

Here are the modules 52 . 54 from the first end 44 along the axial direction of the major axis 16 one behind the other to the second end 46 arranged and in this embodiment forms the module 54III the second end 46 ,

Preferably, the modules 52 . 54 releasably firmly attached to each other so that the modules 52 . 54 in an operating state are arranged fixed to each other and, for example, after an impact, the modules 52 . 54 can be separated from each other, preferably a deformed module 52 . 54 against a new module 52 . 54 exchange.

The module 52 which is the first end 44 forms, extends from a first end 72 in to the main axis 16 axial direction to a second end 74 , where the first end 72 of the module 52 the first end 44 the energy absorption device 40 forms.

The module 52 includes a fairing 76 and a back wall element 78 ,

The rear wall element 78 is at the second end 74 arranged and the panel 76 extends from the rear wall element 78 until the first end 72 ,

The rear wall element 78 is flat, that is, the rear wall element 78 extends substantially in a direction transverse to the main axis 16 extending plane, so is the back wall element 78 for example, a plate.

The rear wall element 78 is stably formed so that it is at one in to the main axis 16 axial direction acting force forwards them.

The costume 76 is at the second end 74 to the rear wall element 78 arranged there and has one of a size of the rear wall element 78 corresponding radial distance to the main axis 16 on.

The radial distance of the panel 76 from the main axis 16 decreases with increasing extension of the fairing 76 from the second end 74 until the first end 72 from and to the first end 72 closes the panel 76 the module 52 from.

This encloses the panel 76 an interior of the module 52 which is different from the main axis 16 in the radial direction up to the panel 76 extends and in to the main axis 16 axial direction of the rear wall element 78 at the second end 74 is limited and at the first end 72 from the panel 76 is limited.

In the interior of the module 52 is an energy-absorbing core element 82 arranged.

In particular, the fairing 76 and the core element 82 formed elastically deformable, and thus preferably is the module 52 formed elastically deformable.

For example, the core element 82 a feather.

In one variant, the core element comprises 82 an elastically deformable foam.

Furthermore, the module comprises 52 a mounting device 92 , which at the second end 74 is arranged.

The mounting device 92 is as a releasably lockable mounting device 92 designed, for example as a screw.

To the mounting device 92 is another module 54 anmontierbar.

The modules 54I . 54II and 54III are essentially formed analogously, so that these are described below, as far as possible, together and the description of a module 54 completely on the modules 54I . 54II and 54III refers. When describing differently designed elements of the modules 54I . 54II and 54III or if on an element of one of these modules 54I . 54II . 54III Reference is made, the reference number of the corresponding element with the corresponding number I, II or III of the corresponding module 54I . 54II or 54III characterized.

The module 54 extends in to the main axis 16 axial direction from a first end portion 112 up to a second end area 114 ( 3 ).

The module 54 includes an inner shell element 122 , an outer shell element 124 and a support device 126 ,

Furthermore, the module comprises 54 a first limiting element 132 and a second limiting element 134 , wherein the first limiting element 132 in the first end area 112 is arranged and the second limiting element 134 in the second end region 114 is arranged.

The boundary elements 132 and 134 are substantially plate-shaped, that is, the limiting elements 132 and 134 each extend in one plane 136 respectively 138 ,

The first level 136 runs in the first end area 112 and the second level 138 runs in the second end area 114 ,

This is where the levels go 136 and 138 transverse to the main axis 16 For example, an angle between the major axis 16 and one of the levels 136 . 138 in about 90 °, that is the angle deviates by at most ± 5 ° from 90 °.

The levels 136 and 138 are substantially parallel to each other, preferably the planes run 136 and 138 at an angle smaller than 2 ° to each other.

The boundary elements 132 and 134 each comprise a passage opening 142 and 144 , where the main axis 16 through the access openings 142 and 144 passes through.

The first boundary element 132 extends in to the main axis 16 radial direction from an inner edge portion 152 which the passage opening 142 bordered, to an outer edge portion 154 , wherein the outer edge portion 154 the inner edge section 152 bordered and a radial distance to the main axis 16 which has approximately the radial extent of the module 54 in the first end area 112 equivalent.

The second boundary element 134 extends from an inner edge portion 156 which the passage opening 144 bordered, to an outer edge portion 158 , which is the inner edge section 156 bordered and at a radial distance to the main axis 16 this revolves, which is approximately the radial extent of the module 54 in the second end region 114 equivalent.

The boundary elements 132 and 134 are stably formed so that one in to the main axis 16 axial direction acting force is passed from this and in fact is forwarded areally, so that the force acting over the entire surface of the limiting element 132 . 134 on elements which are connected to the limiting element 132 . 134 are arranged, forwarded.

The inner shell element 122 extends from a first end portion 212 essentially in to the main axis 16 axial direction to a second end portion 214 and runs in the direction of rotation closed around the main axis 16 around.

The inner shell element 122 is formed like a ring, that is one of the main axis 16 facing inside 216 extending from the first end portion 212 to the second end portion 214 extends, bounded in the radial direction to the main axis an interior space 218 of the module 54 and the inner shell member 122 extends in to the main axis 16 radial direction from the inside 216 up to one of the inside 216 and the main axis 16 averted outside 222 ,

In particular, the inner shell element extends 122 essentially in a geometric reference surface 224 , where the reference surface 224 the main axis 16 encloses and the inner shell element 122 essentially in the reference area 224 extends when an extension of the inner shell member 122 in the reference area 224 considerably larger, for example by a factor of 5 larger, preferably by a factor of 10 larger than an extension of the inner shell element 122 transverse to the reference surface 224 ,

A radial distance from the main axis 16 the geometric reference surface 224 points in the direction of rotation about the main axis 16 around a minimum value and a maximum value, and the radial distance of the reference surface continuously increases from the minimum value in the direction of the circulation direction to the maximum value and continuously decreases from the maximum value in the direction of rotation to the minimum value, preferably the minimum value and the maximum value the radial distance of the reference surface 224 from the main axis 16 in to the main axis 16 increase in axial direction.

Thus, the reference surface encloses 224 in a section transverse to the main axis 16 a, for example oval-shaped, surface, wherein a surface area of the enclosed area with increasing extent of the reference surface 224 in to the main axis 16 axial direction from the first end portion 212 to the second end portion 214 increases.

Thus, in particular, the first end section 212 of the inner shell element 122 a smaller radial distance to the main axis 16 on as the second end portion 214 of the inner shell element 122 ,

A thickness D1 of the inner shell element 122 preferably takes from the first end portion 212 to the second end portion 214 to, wherein the thickness D1 of the inner shell element 122 in to the main axis 16 Radial direction is measured, ie in particular transversely to the reference surface 224 ,

The inner shell element 122 is formed of a fiber composite material, wherein the fibers, for example, substantially parallel to the reference surface 224 are oriented, so for example, the fibers at an angle less than 20 ° to the reference surface 224 run.

In a variant of the embodiment, however, it is provided that the fibers are arranged substantially isotropically oriented.

In a further variant, it is provided that the fibers are substantially in the main axis 16 Oriented axially oriented, for example, the orientation of at least 80% of the fibers at an angle of at most 40 ° to the main axis 16 axial direction.

The first end section 212 of the inner shell element 122 is in the first end area 112 of the module 54 , in particular to the inner edge portion 152 of the first limiting element 132 , arranged and the second end portion 214 of the inner shell element 122 is in the second end region 114 of the module 54 , in particular to the inner edge portion 156 of the second limiting element 134 arranged.

This encloses the inside 216 of the inner shell element 122 the interior 218 of the module 54 and the interior 218 extends from the access opening 142 of the first limiting element 132 up to the access opening 144 of the second limiting element 134 ,

The outer shell element 124 extends from a first end portion 252 in to the main axis 16 axial direction to a second end portion 254 and runs in the direction of rotation closed around the main axis 16 around.

In to the main axis 16 radial direction, the outer shell element extends 124 from one of the main axis 16 facing inside 256 up to one of the inside 256 averted outside 262 where the inside 256 and the outside 262 each from the first end portion 252 to the second end portion 254 extend.

In particular, the outside forms 262 of the module 54 in the area of the module 54 the outside 48 the energy absorption device 40 ,

The outer shell element 124 is cup-shaped, that is, a thickness D2 of the outer shell member 124 is smaller, for example smaller by a factor of 5, preferably smaller by a factor of 10, than the extension of the outer shell element 124 from the first end portion 252 to the second end portion 254 , wherein the thickness D2 of the outer shell element 124 essentially in to the main axis 16 Radial direction is measured, ie in particular from the inside 256 up to the outside 262 ,

Preferably, the thickness D2 of the outer shell element increases 124 with increasing extent of the outer shell element 124 in to the main axis 16 axial direction from the first end portion 252 to the second end portion 254 ,

The first end section 252 is in the first end area 112 of the module 54 arranged and the second end portion 254 is in the second end region 114 of the module 54 arranged.

Here is the first end section 252 with the outer edge portion 154 of the first limiting element 132 connected and the second end 254 is with the outer edge section 158 of the second limiting element 134 connected.

In this case, the outer shell element extends 124 essentially in a geometric reference surface 264 extending from the first end portion 252 to the second end portion 254 extends and around the main axis 16 around, wherein the outer shell element 124 essentially in the reference area 264 extends when an extension of the outer shell member 124 in the reference area 264 substantially, for example by a factor of 5, preferably by a factor of 10, is greater than an extension of the outer shell element 124 transverse to the reference surface 264 ,

The geometric reference surface 264 has a radial distance to the main axis 16 on, which in the direction of rotation about the main axis 16 decreases continuously from a maximum value to a minimum value and continuously increases from the minimum value to the maximum value, preferably the minimum value and the maximum value of the radial distance of the reference surface 264 in to the main axis 16 axial direction from the first end portion 252 to the second end portion 254 grow.

In particular, the radial distance of the reference surface increases 264 to the main axis 16 its minimum value and maximum value at most twice, for example only once, per revolution around the main axis 16 in the direction of rotation.

This encloses the reference surface 264 in one to the main axis 16 transverse section one, for example, oval-shaped surface and a surface area of the enclosed area increases the closer the section, which between the first end portion 252 and the second end portion 254 takes place, at the second end portion 254 lies.

For example, the outer shell element comprises 124 a fiber composite material, wherein in particular the fibers substantially parallel to the reference surface 264 run, in particular, the fibers of the fiber composite material at an angle to the reference surface 264 run, which is smaller than 20 °.

In a variant of the embodiment, however, it is provided that the fibers are arranged substantially isotropically oriented.

In a further variant, it is provided that the fibers are substantially in the main axis 16 Oriented axially oriented, for example, the orientation of at least 80% of the fibers at an angle of at most 40 ° to the main axis 16 axial direction.

The outer shell element 124 has a greater radial distance to the main axis 16 on as the inner shell element 122 , so in to the main axis 16 radial direction between the inner shell element 122 and the outer shell member 124 an intermediate area 312 lies.

The intermediate area 312 extends from the outside 222 of the inner shell element 122 in to the main axis 16 radial direction to the inside 256 of the outer shell element 124 and runs like the inner shell element 122 and the outer shell member 124 around the main axis 16 around.

In particular, the radial distance of the outer shell element increases 124 with increasing extent in to the major axis 16 axial direction stronger from the first end portion 112 to the second end area 114 to as the radial distance of the inner shell element 122 in to the main axis 16 axial direction from the first end portion 112 to the second end area 114 increases, leaving a radial extent A between the inner shell element 122 and the outer shell member 124 of the intermediate area 312 in to the main axis 16 axial direction from the first end portion 112 to the second end area 114 gets bigger.

In particular, the reference surface runs 264 of the outer shell element 124 at a greater angle to the main axis 16 as the reference surface 224 of the inner shell element 122 ,

In to the main axis 16 axial direction extends the intermediate region 312 from the first end area 112 to the second end area 114 and in particular of the first limiting element 132 and the second limiting element 134 limited.

In the intermediate area 312 is the support device 126 arranged.

At the support device 126 the outer shell element is supported 124 and in particular prevents the support device 126 in an impact, a kinking of the outer shell element 124 in the direction of the main axis 16 ,

The support device 126 in turn is supported on the inner shell element 122 so that slipping radially inward toward the main axis 16 through the inner shell element 122 is prevented.

In this embodiment, the support device comprises 126 a filler, which in particular the entire intermediate area 312 fills.

For example, the filler material forms a foam-like structure 324 , So fill material limits comprehensive sections fine-pored cavities at least partially.

In particular, the fine-pored cavities are about 150 microns in size, for example, cavities are to be understood in about 150 micron cavities, in which a characteristic extent thereof is 150 microns ± 50 microns in size.

Furthermore, the module comprises 54 a first mounting device 352 which are in the first end area 112 is arranged and a second mounting device 354 which in the second end region 114 is arranged.

The mounting devices 352 and 354 are as releasably lockable mounting device 352 . 354 designed, for example as screw.

The mounting devices 352 and 354 are provided by modules 52 . 54 to assemble one another.

A separate support structure for the modules 52 . 54 is not scheduled.

The module 52 and the module 54I are with their mounting devices 92 and 352i releasably firmly connected to each other.

Here are the mounting devices 92 and 352i through the access openings 142I and 144I as well as the interior 218i for the assembly of the modules 52 and 54I accessible to each other and for disassembly.

The radial dimensions of the module 52 at its second end 74 and the module 54I in its first end area 112I are essentially the same size, so the energy absorption device 40 also in the transition from the module 52 to the module 54I on its outside 48 is streamlined.

Furthermore, there are two modules of the modules 54 with their mounting devices 352 respectively 354 mounted to each other, the mounting devices 352 and 354 through the access openings 142 and 144 and the interior 218 for assembly and disassembly of the modules 54 are accessible.

Thus, in this embodiment, the modules 54I and 54II with their mounting devices 354I and 352II releasably firmly attached to each other and the modules 54II and 54III are with their mounting devices 354II and 352III releasably firmly attached to each other.

Here are the respective mounting devices 352 and 354 through the access openings 142III . 144III , the interior 218III as well as the access openings 142II . 144II and the interior 218II and optionally the passage opening 144I and the interior 218i for the assembly and disassembly of the modules 54I . 54II . 54III accessible.

Furthermore, the radial extent of a module 54 in the second end region 114 essentially the same size as the radial extent of one on this module 54 mounted module 54 in its first end area 112 so that the energy absorption device 40 even in the transition from a module 54 on another module 54 is streamlined and formed with a lower air resistance.

Thus, in this embodiment, the radial extent of the module 54I in its second end area 114I essentially the same size as the radial extent of the module 54II in its first end area 112II ,

Furthermore, the radial extent of the module 54II in its second end area 114II essentially the same size as the radial extent of the module 54III in its first end area 112III ,

The module 54III is with his mounting device 354III to the vehicle base structure 22 releasably fixed.

In this embodiment it is provided that to the main axis 16 axial extent L of, in particular formed in an analogous manner, modules 54 at those modules 54 larger, which is closer to the second end 46 are arranged.

Thus, in this embodiment, the axial extent LI of the module 54I related to the other modules 54 , in particular the front module 52 except, smallest.

The axial extent LII of the module 54II is greater in this embodiment than the axial extent LI of the module 54I and is smaller than the axial extent LIII of the module 54III ,

Thus, in this embodiment, the axial extent L that module 54 largest, which to the vehicle base structure 22 disposed is, in this example, the axial extent LIII of the module 54III ,

It is further provided that the reference surfaces 264 of modules mounted on each other 54 So for example the reference surface 264I and the reference area 264II , or the reference surfaces 264II and 264III , continuously merge, that is, the minimum value or maximum value of the reference surface 264I in the second end region 114I the minimum value or maximum value of the reference surface 264II in the first end area 112II corresponds and the minimum value or maximum value of the reference surface 264II in the second end region 114II the minimum value or maximum value of the reference surface 164III in the first end area 112III equivalent.

In short, the rail vehicle works 10 with the energy absorption device 40 as explained below.

Drives the rail vehicle 10 in the direction of travel 32 on the obstacle 42 on, so in a collision of the rail vehicle 10 on the obstacle 42 , so enters the end area 12 in contact with the obstacle 42 and especially first touches the first end 44 the energy absorption device 40 the obstacle 42 ,

The impact causes a force F between the obstacle 42 and the rail vehicle 10 , in particular the energy absorption device 40 through which the rail vehicle 10 , At least slightly, is decelerated and the energy absorption device 40 is deformed.

By, at least slight, deceleration of the rail vehicle 10 decreases, at least slightly, the kinetic energy of the rail vehicle 10 and the energy released by the reduction in kinetic energy is at least partially, advantageously for the most part, as deformation energy from the energy absorbing device 40 added.

By absorbing the released energy through the energy absorption device 40 No or less energy is applied to the vehicle base structure 22 transmitted and a damaging effect by the released energy in the impact on the vehicle base structure 22 is prevented or reduced.

The deformation of the energy absorption device 40 depends on the size of the force F and is exemplary in 4 sketched a path S-force F-diagram.

For small forces F, for example, smaller than a threshold value F1, the module 52 located at the first end of the energy absorption device 40 is arranged, deformed.

In this embodiment, the module is 52 elastically deformable, so that the module 52 is reversibly compressed by a distance S, wherein a length of the distance S is determined by the applied force F, and is smaller than a threshold value S1, which is substantially the axial extent L of the module 52 equivalent.

Thus, in an impact in which a force F, which is smaller than the force threshold F1, acts, no damage to the energy absorption device 40 on.

In the event of a collision, a larger force will not act through the front module 52 can be compensated, so for example, a force which is greater than the force threshold F1, then part of the energy released by the front module 52 absorbed and part of the force F is via the front module 52 , in particular via its rear wall element 78 , on the module 54I , which is connected to the front module 52 mounted, transferred.

If an even greater force F, for example a force greater than a threshold value F2, acts on the impact, the modules can 52 and 54I does not completely absorb the energy released and the force F also acts on the module 54I mounted module 54II ,

Analogously, a force is applied to the modules 52 . 54I and 54II can not fully compensate, for example, a force F which exceeds a threshold F3, also on the module 54III transmitted, which is also deformed by the force F occurring and also absorbs energy.

With an even greater force F, for example, at a force F which is greater than another threshold F4, each module 52 . 54 the energy absorption device 40 deformed and the energy absorption device 40 can not absorb all the released energy, so that the applied force F also on the vehicle base structure 22 acts.

Thus offers the energy absorption device 40 in particular a protection against acting forces F, which are smaller than the threshold value F4.

At this time, a force F smaller than the threshold value F2 deformed the energy absorbing device 40 by a distance S, which is smaller is a threshold value S2, where the threshold S2 is substantially the common axial extent of the modules 52 and 54I equivalent.

Accordingly, the energy absorption device becomes 40 for an applied force F, which is smaller than the threshold values F3 or F4, deformed by a distance S which is smaller than a threshold value S3 or S4, wherein the value S3 substantially the axial extent of the modules 52 . 54I and 54II and the value S4 is substantially the axial extent of the modules 52 . 54I . 54II and 54III equivalent.

The deformation of the modules takes place 54I . 54II and 54III essentially analog, so these below for the modules 54I . 54II and 54III is described together.

The acting force F acts on the first limiting element 132 and from this to the outer shell element 124 and also on the inner shell element 122 and the support device 126 transfer.

Preferably takes the outer shell element 124 the most energy.

The acting force F becomes the outer shell element 124 transverse to the axial direction of the major axis 16 bent, in particular transversely to the reference surface 264 ,

In this case, the outer shell element 124 from the support device 126 in the transverse direction to the main axis 16 supported, so that a complete buckling of the outer shell element 124 transverse to the main axis 16 is avoided.

This supports the support device 126 in turn on the inner shell element 122 off, allowing a pushing away of the support device 126 radially inward to the main axis 16 is avoided.

This is especially the outer shell element 124 only in each case piece by piece with increasing force in to the main axis 16 axial direction from the first end portion 112 increasingly to the second end region 114 deformed and so is the largest possible deformation of the outer shell element 124 achieved, with a maximum of energy absorption by the outer shell element 124 is reached.

Due to the advantageously increasing thickness D2 of the outer shell element 124 In addition, a progressive path-force ratio is achieved, that is, for a deformation over a larger path S, a larger force F is required.

Likewise, the advantageously increasing thickness D1 of the inner shell element leads 122 to a progressive path-power relationship.

Because the radial extent of the module 54II is greater than the radial extent of the module 54I and thus at a deformation over an equal extent in to the main axis 16 axial direction in the module 54II more material has to be deformed than with the module 54I are larger forces for deformation of the module 54II necessary as for a deformation of the module 54I ,

In particular, therefore, the force threshold F2 for the deformation of the module 54II greater than the force threshold F1 for the deformation of the module 54I ,

Analogously, a larger force F is necessary for the deformation of the module 54III as for the deformation of the module 54II and therefore also the force threshold F3 for the deformation of the module 54III greater than the force threshold F2 for the deformation of the module 54II ,

In a second embodiment of a solution according to the invention, shown by way of example in FIG 5 , those parts which are identical to those of the first embodiment are provided with the same reference numerals, so that with respect to the description thereof, the contents of the first embodiment can be fully referenced.

In the second embodiment comprises an inner shell element 122a a module 54a breakthroughs 362 , where in 5 only individual breakthroughs 362i . 362ii . 362iii are provided with reference numerals.

The breakthroughs 362 extend from the inside 216 to the outside 222 of the inner shell element 122a and connect so, especially for gas permeable, the interior 218 and the intermediate area 312 ,

Further, in the second embodiment, gas guide channels 364 provided, in 5 only a few gas ducts 364I . 364ii . 364iii are provided with a reference numeral.

The gas guide channels 364 go through the intermediate area 312 , in particular the foam-like structure 324 ,

The gas guide channels 364 extend from one to the main axis 16 radially outer outer portion 366 of the intermediate area 312 to a radially inner portion 368 of the intermediate area 312 ,

For example, it borders on the outer section 366 of the intermediate area 312 the outer shell element 124 at.

In particular, adjoins the interior section 368 of the intermediate area 312 the inner shell element 122a at.

The gas supply channels run 364 transverse to the axial and radial directions of the major axis 16 ,

With increasing extent of the gas guide channel 364 from the outside section 366 to the interior section 368 extends the gas guide channel 364 in to the main axis 16 axial direction closer to the second end region 114 of the module 54a out.

This is an outdoor area 372 of the gas guide channel 364 , which is from the main axis 16 is further away in the radial direction, in to the main axis 16 axial direction closer to the first end portion 112 as an interior area 374 of the gas guide channel 364 which is radially closer to the main axis 16 lies as the outdoor area 372 ,

The gas feed-through channels 364 each lead into one of the breakthroughs 362 and are thus with the interior 218 connected.

Thus, for example, in an impact, in which the module 54a deformed, compressed air from pores of the foam-like structure 324 through one of the gas guide channels 364 from the intermediate area 312 in the interior 218 escape.

This can be an overpressure by compressed gas in the intermediate area 312 be avoided.

At an overpressure in the intermediate area 312 could be the outer shell element 124 in the to the main axis 16 radially outward direction instead of being deformed by the applied force F, and thus energy absorption potential would be lost.

Furthermore, all other components of the second embodiment are identical to those of the first embodiment, so that with respect to the description of the same fully referenced to the statements in connection with the first embodiment.

In a third embodiment of a solution according to the invention those components which are identical to those of one of the preceding embodiments, provided with the same reference numerals, so that with respect to the description thereof may be made in full to the comments on the preceding embodiments reference.

In the third embodiment, an inner shell member 122b in sections in to the main axis 16 radial direction depressions 412 and is therefore structurally structured to increase stability ( 6 ).

Here are in 6 only a few wells 412i . 412ii . 412iii provided with a reference numeral.

The depression 412 has a first wall section 414 and a second wall section 416 and a bottom section 418 on.

The wall sections 414 and 416 limit the depression 412 in the direction of the circulation around the main axis 16 and the bottom section 418 connects the first wall section 414 with the second wall section 416 and limits the depression 412 in to the main axis 16 radial direction.

For example, the bottom section 418 in the direction of rotation about the main axis 16 concavely curved from one to the main axis 16 viewed radially outside.

The wall sections run 414 and 416 especially transverse to the main axis 16 radial direction and transverse to the direction of rotation of the main axis 16 ,

Preferably, a wall section 414i the depression 412i with an intermediate section 422 of the inner shell element 122b with a wall section 416ii the depression 412ii connected, the depression 412ii in the direction of rotation about the main axis 16 the on the deepening 412i following recess 412 is.

In this case, the intermediate section extends 422 essentially in the direction of rotation about the main axis 16 ,

In particular, the intermediate section 422 , from to the main axis 16 Seen radially outer view with respect to the direction of rotation about the major axis 16 convexly curved.

This is the inner shell element 122b in the direction of rotation about the main axis 16 around by successive wall sections in this order 414 , Floor sections 418 , Wall sections 416 and intermediate sections 422 educated.

Furthermore, the inner shell element 122b in the direction of the circulation around the main axis 16 around alternately concave and convex curved.

The depression 412 extends substantially in to the main axis 16 axial direction, wherein an extension of the wall sections 414 and 416 and the bottom section 418 in to the main axis 16 axial direction is greater than an extension of these sections 414 . 416 . 418 transverse to the axial direction of the major axis 16 ,

For example, the depression extends 412 from the first end portion 212 to the second end portion 214 of the inner shell element 122b ,

The inner shell element 122b runs with increasing extent in to the main axis 16 axial direction substantially in to the main axis 16 radial direction apart.

It takes a radial distance of the inner shell element 122b , in particular a radial distance of the wall section 414 and 416 and a radial distance of the bottom portion 418 to the main axis 16 and preferably a radial distance of the intermediate portion 422 to the main axis 16 , with increasing extent of the inner shell element 122b in to the main axis 16 axial direction too.

The inner shell element 122b runs in the direction of rotation about the main axis 16 in some areas transversely to a reference surface 224b ,

The reference surface runs 224b closed in the direction of rotation about the main axis 16 around, with a radial distance of the reference surface 224b in the direction of rotation about the main axis 16 decreases continuously from a maximum value to a minimum value and continuously increases again from the minimum value to the maximum value.

The reference surface 224b extends in to the main axis 16 axial direction and preferably the minimum value and the maximum value starting from a value in the first end section 212 with increasing extent of the reference surface 224b in to the main axis 16 axial direction to the second end portion 214 to.

In particular, the radial distance of the reference surface increases 224b its maximum value and minimum value at most twice, for example only once, per revolution around the major axis 16 in the direction of rotation.

This has the inner shell element 122b in outer sections 432 a greater radial distance than the reference surface 224b and in inner sections 434 has the inner shell element 122b a smaller radial distance to the main axis 16 as the reference surface 224b ,

There are in the 6 only some outer sections 432i . 432ii . 432iii and some inner sections 434i . 434ii . 434iii provided with a reference numeral.

The outer section 432 is through a connecting section 436 with the inner section 434 connected, wherein at the connecting portion 436 the inner shell element 122b transverse to the reference surface 224b runs.

In 6 are just a few connecting sections 436i . 436ii . 436iii provided with a reference numeral.

This is with the inner shell element 122b its radial distance to the main axis 16 in the direction of rotation about the main axis 16 around alternately larger and smaller than the radial distance of the reference surface 224b ,

Preferably, the outer portion 432 and the inner section 434 in to the main axis 16 axial direction formed elongated, so that an extension of these sections 432 . 434 transverse to the axial direction of the major axis 16 smaller than an extension in the axial direction.

For example, the outer portion extends 432 and the inner section 434 from the first end portion 212 to the second end portion 214 of the inner shell element 122b ,

Incidentally, all the other parts in the third embodiment are identical to those of one of the preceding embodiments, so that with respect to the description of the same can be made in full to the comments on the above embodiments.

In a fourth embodiment of the solution according to the invention those components which are identical to those of one of the preceding embodiments, provided with the same reference numerals, so that with respect to the description of the same fully referenced to the comments on the above embodiments.

In the fourth embodiment comprises a support device 126c a module 54c a framework structure 452 , which consists of leg parts 454 is trained ( 7 and 8th ).

In the 7 and 8th are just a few leg parts 454 . 454i . 454ii . 454iii provided with a reference numeral.

In particular, the leg parts form 454 a honeycomb scaffold structure 452 out.

Preferably, that is from the leg parts 454 trained framework structure 452 a honeycomb core of a sandwich structure.

The framework structure 452 preferably passes through the intermediate area 312 from the first end area 112 to the second end area 114 ,

The framework structure 452 extends from the outer shell element 124 to the inner shell element 122 ,

In particular, the outer shell element is supported 124 on the framework structure 452 which, in turn, on the inner shell element 122 supported.

In this embodiment is between the leg parts 454 the framework structure 452 a filling material, in particular in a foam-like structure 324 arranged.

The leg parts 454 are at edge sections 462 . 464 arranged together.

For example, at a border section 464i a leg part 454i two more leg parts 454ii . 454iii arranged, with their edge portions 462ii and 462iii ,

Here are six leg parts 454 arranged honeycomb to each other, so at one to the main axis 16 transverse section has the framework structure 452 a honeycomb structure.

In this embodiment, the leg parts 454 plate-like design.

In this case, the leg portion extends 454 elongated in a first direction of extent 472 and transverse to the first direction of extent 472 in a second extension direction 474 , wherein the extension of the leg portion 454 in the first extension direction 472 is greater than the extension in the second direction of extent 474 ,

A thickness of the leg part 454 is significantly lower, for example, by a factor of 5 less, preferably by a factor of 10 less than the extensions of the leg portion 454 in the extension directions 472 and 474 , wherein the thickness of the leg portion 454 transverse to that of the first direction of extent 472 and the second direction of extent 474 clamped surface is measured.

In particular, the edge portions extend 462 and 464 in the first extension direction 472 and the leg part 454 extends from the first edge portion 462 in the direction of the second direction of extent 474 to the second edge portion 464 ,

In particular, the first extension direction 472 of the leg part 454 essentially in the axial direction of the main axis 16 oriented, that is, the two directions, for example, by less than 20 ° from each other.

In this embodiment, the leg portion extends 454 from the first end area 112 to the second end area 114 of the module 54c ,

In a variant, it is provided that at least some leg parts 454 Breakthroughs for the gas duct 364 include.

Incidentally, all other components in this embodiment are identical to one of the preceding embodiments, so that with respect to the description of the same can be made in full to the comments on the above embodiments.

In a fifth embodiment of the solution according to the invention those components which are identical to those of one of the preceding embodiments, provided with the same reference numerals, so that with respect to the description of the same fully referenced to the comments on the above embodiments.

In the fifth embodiment, a leg part 454d a framework structure 452d tube-shaped ( 9 ).

In particular, the framework structure 452d formed like a tube, preferably designed as a tube-like core of a sandwich structure.

Preferably, the framework structure comprises 452d several trained as a tube leg parts 454d ,

In this case, the leg portion extends 454d in an elongated first direction of extent 472d and a second extension direction 474d essentially corresponds to a direction of rotation about an axis whose axial direction in the direction of the first extension direction 472d is oriented.

Two leg parts 454d are at edge sections 462d and 464d arranged together.

In this case, the edge portions extend 462d and 464d for example in the first extension direction 472d ,

One of the thigh parts 454d is on six more leg parts 454d arranged.

Thus, the leg member comprises 454d six edge sections 462d (i, ii, iii), 464d (i, ii, iii).

The leg part 454d each extends from one of the edge sections 462d to the nearest edge sections 464d ,

Incidentally, all other components are identical to those of one of the preceding embodiments, so that with respect to the description of the same reference may be made to the comments on the above embodiments.

In a sixth embodiment of the solution according to the invention those components which are identical to those of one of the preceding embodiments, provided with the same reference numerals, so that with respect to the description of the same fully referenced to the comments on the above embodiments.

In the sixth embodiment, a skeleton structure comprises 452e leg parts 454e (i, ii, iii, iv), which are designed as struts ( 10 ).

A leg part 454e is with a first edge section 462e on an outer shell element 124e and with a second edge portion 464e on an inner shell element 422e a module 54e arranged.

In this case, the leg portion extends 454e elongated in an extension direction 472e from the first edge portion 462e to the second edge portion 464e and is formed in particular rod-like.

A width of the leg part 454e is much lower, for example, by a factor of 5 less than an extension of the leg portion 454e in the elongated extension direction 472e , wherein the width of the leg portion 454e transverse to the direction of extent 472e is measured.

Incidentally, all other components are identical to those of one of the preceding embodiments, so that with respect to the description of the same fully referenced to the comments on the above embodiments.

Claims (20)

Rail vehicle ( 10 ) comprising a vehicle base structure ( 22 ), characterized by an energy absorption device ( 40 ), which is an, at least in part, modular construction of several modules ( 52 . 54 ), wherein at least one module ( 54 ) an inner shell element ( 122 ) and an outer shell element ( 124 ), wherein the inner shell element ( 122 ) and the outer shell element ( 124 ) about a major axis ( 16 ) run closed in a direction of rotation and the outer shell element ( 124 ) a greater radial distance to the main axis ( 16 ) than the inner shell element ( 122 ), so that in to the main axis ( 16 ) radial direction between the inner shell element ( 122 ) and the outer shell element ( 124 ) an intermediate area ( 312 ), and in the intermediate area ( 312 ) a supporting device ( 126 ) is arranged. Rail vehicle ( 10 ) according to claim 1, characterized in that the outer shell element ( 124 ) on the supporting device ( 126 ) is supported. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the outer shell element ( 124 ) with increasing extent in to the main axis ( 16 ) axial direction substantially in the main axis ( 16 ) is formed diverging radial direction, wherein in particular the outer shell element ( 124 ) with increasing extent in to the main axis ( 16 ) axial direction substantially in the main axis ( 16 ) is formed diverging radial direction, when the radial distance of the outer shell element ( 124 ) to the main axis ( 16 ) with increasing extent of the outer shell element ( 124 ) in to the main axis ( 16 ) axial direction, preferably monotonically, increases. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that a thickness of the outer shell element ( 124 ) with increasing extent of the outer shell element ( 124 ) in to the main axis ( 16 ) axial direction increases, wherein the thickness of the outer shell element ( 124 ) from one of the main axes ( 16 ) averted outside ( 262 ) of the outer shell element ( 124 ) to one of the main axes ( 16 ) facing inside ( 256 ) of the outer shell element ( 124 ) is measured. Rail vehicle ( 10 ) according to one of the preceding claims, characterized that the outer shell element ( 124 ) on the supporting device ( 126 ) is supported. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the inner shell element ( 122 ), in particular by means of the supporting device ( 126 ), the outer shell element ( 124 ). Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the inner shell element ( 122 ) with increasing extent in to the main axis ( 16 ) axial direction substantially in the main axis ( 16 ) is formed diverging radial direction, wherein in particular the inner shell element ( 122 ) with increasing extent in to the main axis ( 16 ) axial direction substantially in the main axis ( 16 ) is formed diverging radial direction, when the radial distance of the inner shell element ( 122 ) to the main axis ( 16 ) with increasing extent of the inner shell element ( 122 ) in to the main axis ( 16 ) axial direction, preferably monotonically, increases. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the inner shell element ( 122 ) in to the main axis ( 16 ) axial direction at a smaller angle to the main axis ( 16 ) extends as the outer shell element ( 124 ). Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the inner shell element ( 122 ) stiffening is geometrically structured. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the inner shell element ( 122 ) at least one depression ( 412 ), which in towards the main axis ( 16 ) is formed in the radial direction. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the inner shell element ( 122 ) in the direction of rotation about the main axis ( 16 ) is alternately curved in the direction of the direction of rotation and convexly curved in the direction of rotation. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that a thickness of the inner shell element ( 122 ) is smaller than the thickness of the outer shell element ( 124 ), wherein the thicknesses of the inner shell element ( 122 ) and the outer shell element ( 124 ) each of one of the main axis ( 16 ) averted outside ( 222 and 262 ) of the respective element ( 122 . 124 ) to one of the main axis ( 16 ) facing inside ( 216 and 256 ) of the respective element ( 122 . 124 ) are measured. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the outer shell element ( 124 ) and / or the inner shell element ( 122 ) are formed from a fiber plastic composite / is. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the supporting device ( 126 ) comprises a filler material, for example a polymer composition, which comprises the intermediate region ( 312 ). Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the supporting device ( 126 ) a foam-like structure ( 324 ) of a porous material, for example epoxy foam. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the supporting device ( 126 ) several limb parts ( 454 ) comprising a framework structure ( 452 ) form. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the leg parts ( 454 ) form a core, for example a tube core and / or a honeycomb core. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the supporting device ( 126 ) at least one gas guide channel ( 364 ), in particular for removing gas from the intermediate region ( 312 ). Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that at least one module ( 52 ) of the several modules ( 52 . 54 ) is formed elastically deformable. Rail vehicle ( 10 ) according to one of the preceding claims, characterized in that the individual modules ( 52 . 54 ) interchangeable, are firmly attached to each other.

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