DE102010063452B4 - A cooled system exposed to hot gas flow, a drive device, a reentrant body, a method of operating a hot gas flow charged system, and a method of manufacturing a refrigerated system - Google Patents

Abstract

A cooled system exposed to hot gas flow comprising at least one wall (18; 92) and cooling means (30) at least partially integrated in the wall (18; 92), the at least one wall (18; 92) passing through At least one magnetic field generating coil (74; 102) made of superconducting material is arranged in the at least one wall (18; 92), characterized in that the at least one wall (18; 92) at least in one Partial region is made of a porous ceramic material, and that the at least one coil (74, 102) is made of a porous ceramic material.

Description

The invention relates to a cooled system, which is exposed to a hot gas flow, comprising at least one wall and a cooling device, which is at least partially integrated into the wall, wherein the at least one wall is cooled by transpiration cooling and / or effusion cooling, and in the at least one wall at least one magnetic field generating coil of superconducting material is arranged.

The invention further relates to a drive device for a missile.

Furthermore, the invention relates to a reentrant body.

Furthermore, the invention relates to a method for producing a cooled system.

From the WO 99/04156 A1 a combustion chamber is known, comprising a combustion chamber, an inner jacket surrounding the combustion chamber, an outer jacket surrounding the inner jacket and coolant channels formed between the inner jacket and the outer jacket, wherein the outer jacket is formed from a fibrous ceramic material and the inner jacket is formed from a fibrous ceramic material or from graphite.

From the DE 39 03 602 A1 a rocket motor with a combustion chamber and a connected expansion nozzle is known, wherein at least in the exit region of the combustion gases from the combustion chamber, an electrically energizable coil arrangement for generating an electromagnetic field is arranged.

From the US Pat. No. 7,506,497 B2 For example, an electric drive arrangement is known which comprises an anode and a cathode.

From the US 6,334,302 B1 For example, a motor is known which has a plasma generator with a controllable output, a controllable heater and a nozzle.

From the US 3,243,954 a plasma accelerator is known.

From the US 6,938,406 B2 a drive device is known, which has an injection chamber and a nozzle.

From the US 4,815,279 is a spacecraft known. The invention has for its object to provide a cooled system of the type mentioned, which provides effective protection with respect to hot gas flows with a simple structure and in particular simple geometric structure.

This object is achieved according to the invention in the cooled system mentioned above in that the at least one wall is made of a porous ceramic material at least in a partial region, and that the at least one coil is made of a porous ceramic material.

The at least one coil is integrated in the wall. The cooling of the at least one wall can be used to cool the material of the at least one coil to a temperature below the superconducting transition temperature. As a result, a high magnetic field can be generated in an energy-saving manner. This magnetic field, in turn, can be used to influence an ionized hot gas flow and, in particular, to divert it so that the wall is minimally stressed by the hot gas flow.

The cooling of the wall ensures that the superconducting transition temperature is reached. It is formed on the wall, a film which also protects against hot gas flow. Furthermore, in the case of the transpiration cooling and / or effusion cooling, heat is removed from the at least one wall by the passage of fluid through the at least one wall, which is produced by remaining heating of the at least one wall.

In principle, the wall can then be made geometrically simpler, since at least part of the function of the hot gas flow guide, for which otherwise specific wall forms and in particular special nozzle shapes are necessary, can at least partially be replaced by a "magnetic nozzle".

Furthermore, the at least one coil, when made of a high-temperature superconductor and in particular a ceramic superconductor, can be easily integrated into the wall in the production process of a porous wall, if it is made of a ceramic material.

The at least one wall is made of a ceramic material in the at least one subregion. Such a ceramic material can be produced porous with high temperature resistance.

The at least one coil is made of a porous ceramic material. This results in ease of manufacture effective management of cooling fluid.

It is favorable if the material for the at least one coil is selected so that the temperature at the at least one coil is below the transition temperature of the superconducting material at an operating point or in an operating point range of the cooling device. As a result, the cooling device simultaneously ensures that the at least one coil is operated in the superconducting region.

It is particularly advantageous if the at least one wall with the at least one coil is formed at least in the partial region as a deflection device and / or magnetic nozzle for the ionized hot gas flow. In the embodiment as a deflection device, an admission of the at least one wall with the hot gas flow can be at least reduced. In the design as a magnetic nozzle, the hot gas flow can be performed in accordance with a geometric nozzle shape such as a Laval nozzle, for example, by a thrust chamber. As a result, the same effect as in a geometrically more complex thrust chamber can be achieved, wherein in the solution according to the invention, for example, the thrust chamber can be formed as a cylindrical tube.

It can also be provided that the at least one wall with the at least one coil is formed at least in a partial region as an acceleration device for ions of the hot gas flow. As a result, for example, after passing through the hot gas flow through a thrust chamber subsequent acceleration of ions and thus the hot gas flow can be achieved.

In particular, a passage direction for fluid at the at least one wall for transpiration cooling and / or effusion cooling leads from a first side to a second side of the at least one wall, wherein the second side is directly loaded by the hot gas flow. As a result, on the one hand cool the wall and it can thereby dissipate heat. On the second side can form a film, which additionally protects the wall from Heißgasbeaufschlagung.

It is advantageous if the at least one wall is made of a fiber-ceramic material on the at least one subregion.

The at least one wall is produced in the at least one subregion from an electrically insulating material and / or the at least one coil is assigned an electrical insulation device to the at least one wall. By way of example, the at least one wall is made of an oxide-ceramic material which has electrically insulating properties. In principle, it is also possible to produce the at least one wall, for example, from a C / C material, if sufficient electrical insulation is provided in order to avoid a short circuit, in particular when the superconducting energy collapses.

It is particularly advantageous if the at least one coil is embedded in the at least one wall. This makes it easy to achieve a compact system.

It is particularly favorable if the at least one coil is located in the at least one wall between layers of fabric of the at least one wall. As a result, the wall with integrated at least one coil can be produced in a simple manner. In particular, if a ceramic material is used for the wall and a ceramic material is used for the at least one coil, the similar production steps can be used for an integral production.

According to the invention, fluid is used both for cooling the at least one wall and / or forming a protective film on the at least one wall and for cooling the superconducting material below the transition temperature. The fluid is then a corresponding cooling fluid.

It is favorable if the fluid is also used as fuel. For example, if the refrigerated system includes a thrust chamber and the wall is a wall of that thrust chamber, then there is no contamination in the thrust chamber by the cooling fluid when the fuel used to operate the thrust chamber is also used as the cooling fluid. In this case, the fluid for the transpiration cooling or effusion cooling (ie for wall cooling or formation of a protective film) for cooling the superconductor is used below the transition temperature and as fuel.

In one embodiment, the at least one wall forms a chamber and defines a cavity or a recess. For example, the at least one wall forms a thrust chamber which limits a thrust chamber. It is also possible, for example, that the at least one wall forms a reentrant body and thereby limits an interior space.

In particular, a fluid for transpiration cooling and / or effusion cooling is coupled into the cavity or into the recess. In a thrust chamber, for example, fuel is coupled via the at least one porous wall into a thrust chamber as a cavity. In a reentrant body, for example, a fluid is coupled into the cavity or the recess so that this can pass through the wall in an outer space, in particular to produce a film on an outer side of the reentrant body.

In one embodiment, the chamber has an inlet opening and an outlet opening outside pores of the at least one porous wall. As a result, a main flow of a fuel can be performed, for example, by a thrust chamber.

In another embodiment, the chamber has an inlet opening and no outlet opening outside pores of the at least one porous wall. Such a chamber is used, for example, in connection with a reentrant body. The inlet opening serves solely to provide fluid for the transpiration cooling and / or effusion cooling to the at least one wall.

According to the invention, a propulsion device for a missile is provided which comprises at least one combustion chamber and / or thrust chamber, wherein a cooled system according to the invention is used.

A missile is generally understood to mean an aircraft or spacecraft.

A reentrant body can also be provided with a cooled system according to the invention.

In a method for operating a system loaded with a hot gas flow, in which an effective hot gas guide is achieved with minimal wall load, at least one coil of a superconducting material is arranged in the at least one wall and the transpiration cooling and / or effusion cooling cools the at least one coil below the transition temperature, and by the at least one coil, a magnetic field is generated which acts on an ionized hot gas flow and deflects ions and / or accelerated.

It is advantageous if a cooling fluid for the transpiration cooling and the cooling of the superconducting material is also used as fuel. As a result, a transpiration cooling or effusion cooling with simultaneous cooling of the superconductor can be achieved below the critical temperature in a simple manner, wherein a protective film can be formed on the at least one wall, and wherein the cooling fluid can be used as fuel in a thrust chamber, for example.

The method can be carried out in particular by means of the cooled system according to the invention.

The invention is further based on the object to provide an aforementioned production method with which can be realized in a simple manner, a cooled system.

This object is achieved according to the invention in the production method mentioned above, wherein the at least one wall is fabric layers, which are or are infiltrated with resin, wherein at least one spiral conductor housing is inserted between layers of fabric in the preform manufacture.

It can thereby produce a preform, which forms a porous wall or can be used to produce a porous wall, in which at least one coil or a part thereof is integrated.

For example, the preform is subsequently pyrolyzed after its production (with integrated at least one spiral-shaped conductor housing).

If the porous wall is made of a ceramic material and the at least one coil is made of a ceramic material, then the similar manufacturing steps can be used to integrate the at least one coil in the at least one wall.

The following description of preferred embodiments is used in conjunction with the drawings for further explanation of the invention. Show it:

1 a schematic representation of an embodiment of a drive device for a missile;

2 a partial view of a wall of an embodiment of a cooled system according to the invention;

3 a variant of the wall according to 2 with a partial area in which a further acceleration of ions is possible; and

4 a schematic representation of another embodiment of a cooled system, which is realized on a reentrant body.

An embodiment of a drive device of a missile (in particular a Rocket), which is in 1 shown schematically and there with 10 is designated, comprises a thrust chamber 12 , This thrust chamber 12 extends in an axial direction 14 , A thrust room 16 the thrust chamber 12 is in particular rotationally symmetrical to the axial direction 14 educated. There are also other geometries such as a cuboid formation with a rectangular contour possible.

The push chamber has a wall 18 on which is formed circumferentially and the thrust room 16 limited.

The thrust chamber 12 has an inlet opening 20 , It has a first area 22 on which the inlet opening 20 sits, being in the axial direction 14 from the inlet opening 20 away the thrust room 16 in a first area 22 rejuvenated.

At the first area 22 closes in the axial direction 14 a second area 24 at. In this second area 24 the pusher space is cylindrical. There are also other geometries such as a cuboid formation with a rectangular contour possible.

To the second area 24 closes in the axial direction 14 a third area 26 at. The thrust room expands in this third area 26 from the second area 24 path.

It can also be provided that to the third area 26 a fourth area 28 followed. This is designed in particular as a nozzle extension.

The wall 18 the thrust chamber 12 includes one as a whole 30 designated cooling device through which the wall 18 is coolable. The cooling takes place by transpiration cooling (sweat cooling with phase transition) or effusion cooling (sweat cooling without phase transition).

The wall 18 is porous. She has a first page 32 on which on an outside of the thrust chamber 12 lies, and has a second page 34 on which directly the thrust room 16 limited. The second page 34 is directly loaded with a hot gas flow.

During the transpiration cooling and according to the effusion cooling becomes the first page 32 a fluid and in particular supplied fuel. This flows through in a direction of passage 36 which is between the first page 32 and the second page 34 lies, the wall 18 and flows into the thrust room 16 one. During transpiration cooling, a gaseous fluid is passed through the wall 18 guided. It forms on the second side 34 a (liquid) film 38 , There is a cooling of the wall 18 and by the film formation on the second side 34 becomes a direct contact of the hot gas flow with the wall 18 avoided.

In one embodiment, the drive device comprises 10 (at least) one tank 40 for fuel. This tank 40 is a mixing device 42 downstream. An exit 44 of the tank 40 is fluid effective with an input 46 the mixing device 42 connected.

In the tank 40 In particular, liquid fuel such as hydrogen is stored. A typical storage temperature is 20K.

The tank 40 is a check valve 48 assigned.

An exit 50 the mixing device 42 is fluid effective with a pump 52 connected. Through the pump 52 will fuel over one or more lines 54 the inlet opening 20 fed. It can thereby fuel in the pusher chamber 16 inject.

In the line 54 may be a check valve / throttle valve 56 be arranged.

On the line 54 is also a branching device 58 arranged. Through this fuel is diverted and the first page 32 the wall 18 fed, for example via one or more lines 60 , The fuel is doing accordingly via a distributor on the first page 32 distributed so that fuel over a large area in the passage direction 36 through the wall 18 in the thrust room 16 can occur.

In one embodiment, in the pusher room 16 especially in the first area 22 one or more fuel rods and in particular nuclear fuel rods 62 arranged. Such a fuel rod 62 heats up the fuel without combustion. It must then be carried no oxidizer and the molecular weight of the reaction products is not increased by reacting oxidizer.

The hot, by the one or more fuel rods 62 heated fuel forms in the pusher chamber 16 a hot gas flow from which the wall 18 loaded.

By transpiration cooling (and / or effusion cooling) with the cooling device 30 lets go the wall 18 cool.

Through one or more openings in the wall 18 hot gas can be removed ( so-called tap-off). This hot gas can be used in a mixing device 64 with cold fuel from the pipe 54 be mixed. The cold fuel is via a throttle valve 72 guided. About the throttle valve 72 can be mass flow and temperature of the mixing device 64 control and / or regulate. The corresponding fluid flow can then be, for example, to a permissible operating temperature of a turbine 66 cooling down. He becomes the turbine 66 fed and drives this.

The turbine 66 can turn the pump 52 and / or the electric generator 68 drive. From the turbine 66 Coming "cooled" hot gas is sent to the entrance 70 the mixing device 42 directed.

In the wall 18 is (at least) in one or more subregions (at least) a magnetic field generating coil 74 embedded. At the in 1 shown embodiment are in the second area 24 the third area 26 and the fourth area 28 one or more coils each 74 embedded.

The coil or coils 74 generate a magnetic field which is due to ions in the hot gas flow in the pusher chamber 16 acts. The magnetic field is selected by appropriate coil arrangement or formation and control in such a way that the ions and thus at least a portion of the hot gas flow is deflected and on the second side 34 the wall 18 is passed. It is formed a magnetic nozzle, which acts on the hot gas and a direct contact of the wall 18 avoids with the hot gas.

Since the hot gas has a temperature of several 1000 K, it is ionized to a considerable extent. The magnetic field of the at least one coil 74 is selected so strong and chosen with such a field line course, that in particular the hot gas flows in the form of a convergent-divergent Laval nozzle is directed without such a Laval nozzle as "hardware" must be present. By adjusting the field strength of the magnetic field, it is possible in particular to control or regulate a neck cross-section and thus also a thrust during operation. It is accordingly a control / regulation device 76 provided by which the magnetic nozzle via current loading of the coils 74 is controlled or regulated or adjusted.

The coil or coils 74 have a coil axis which is at least approximately coaxial with the axial direction 14 is.

The at least one coil 74 is made of a superconductive material and in particular high-temperature superconductor material. The material is chosen so that in an operating point or in an operating point range of the cooling device 30 for cooling the wall 18 the transition temperature of the superconducting material is exceeded, so that the coil 74 is operated in the superconducting region.

The fuel, which for the transpiration cooling or effusion cooling from the first page 32 to the second page 34 occurs, cools the wall 18 (which can be heated by radiation). It forms on the inside of the wall 18 that is on the second page 34 which the thrust room 16 limited, the movie 38 from which the wall 18 protects. The coil or coils 74 are made of a high temperature superconductor. The passing fuel cools the wall 18 embedded superconductors (in particular high-temperature superconductors) at the operating temperature below the critical temperature. This in turn allows a strong magnetic field to form the hot gas flow guide.

This is in 2 illustrated again. With the arrow 78 is a main flow direction of the hot gas flow indicated. Fuel enters for transpiration cooling from the first page 32 in the direction of passage 36 to the second page 34 through the wall 18 and forms on the second page 34 the movie 38 on the wall 18 out.

Through the magnetic field of the coil and coils 74 can be with the reference number 80 reach indicated course with respect to the guidance of ions, so that a magnetic nozzle is realized.

It is also possible in principle that one or more coils 82 in a wall area 84 are arranged and thereby arranged and / or configured or driven so that ions are accelerated in the hot gas flow and in particular are inductively accelerated ( 3 ). Such a wall area 84 is advantageously outside the thrust chamber 12 and for example on a nozzle extension 28 , The wall area 84 is then a wall area (in particular the thrust chamber 12 ) downstream, on which a magnetic nozzle is formed.

The porous wall 18 is preferably made of a ceramic material and in particular fiber-ceramic material. One possible material is, for example, C / C.

The coil or coils 74 have to face the wall 18 be isolated. This can be achieved by using the wall 18 itself made of an electrically insulating material. This can be achieved, for example, if the wall 18 is made of an oxide ceramic material such as alumina.

If the wall 18 is made of a material having a certain electrical conductivity (for example, due to carbon fibers contained), then it is preferable that a sufficient electrical insulation between an inner boundary surface of the wall 18 and the at least one coil 74 provided in order to prevent in particular the collapse of the superconductivity an electrical short circuit.

The superconducting material of the coil or coils 74 is preferably a ceramic material and more preferably a porous ceramic material. For example, the material used for this purpose is YBa ₂ Cu ₃ O ₇ .

For example, for the production of the thrust chamber 12 first a preform made, which is then pyrolyzed. The preform is produced for example by means of fabric layers which are resin-infiltrated or infiltrated with resin. Between fabric layers, one or more spiral-shaped conductor housings of the starting material for the production of the superconductor are arranged before the pyrolysis. The preform is made by consolidation. For example, this is done in an autoclave process.

In principle, the temperatures and process times of the pyrolysis process for the production of the material for the porous wall 18 similar to those for the preparation of the superconducting material.

For example, segments for a thrust chamber or the like are cut out of finished preforms.

The drive device 10 includes with the thrust chamber 12 an actively cooled system 86 , Another embodiment of an (actively) cooled system 88 which is in 4 is shown schematically is at a reentrant body 90 realized. The reentry body 90 includes a wall 92 with a first page 94 and a second page 96 , The second page 96 is an outside and the first side 94 is an inside. (At the thrust chamber 12 is the second page 34 an inside and the first page 32 an outside.) The wall 92 forms a front part (front tip) of the reentry body 90 ,

The second page 96 is a hot gas flow 98 exposed. Upon re-entry into the atmosphere (which is ionized), the hot gas flow acts 98 on the reentry body 90 , There may be temperatures of the order of 10,000 K in this case.

The wall 92 is designed to have an interior space 100 encloses. It is for example conical.

In the wall 92 is (at least) a coil 102 arranged from a superconducting material.

The first page 94 is about the interior 100 a fluid for transpiration cooling or effusion cooling supplied, which then from the first page 94 in a direction of passage 104 on the second page 96 exit and there a movie 106 forms. This movie 106 protects against the hot gas flow 98 ,

The coil or coils 92 from a high-temperature superconductor generate a magnetic field 108 , which is designed such that ions of the hot gas flow at the reentrant body 90 be steered past.

At the reentry body 90 is over the porous wall 92 with integrated cooling device and the one or more superconducting coils 102 a thermal protection system (TPS) realized, on the heat input of the over the ionized atmosphere caused hot gas flow 98 Reduce when re-entering. In addition, the aerodynamic properties of the reentry body can be 90 selectively adjust or influence.

By means of the solution according to the invention, in connection with transpiration cooling or effusion cooling, it is possible to provide a magnetic field generating system which generates strong magnetic fields. It superconducting coils are used, which are made for example of a superconducting ceramic material. As a result, embedding of superconducting coil tracks in a ceramic porous wall can be achieved in a simple manner and the manufacturing outlay can be reduced. The superconductor does not require separate cooling, but it is on the integrated cooling device in the wall 30 cooled below the transition temperature.

This gives a constructive simplification with regard to the shaping of the wall, since the magnetic field generated contributes to the flow guidance. Thus, for example, a geometrically complicated nozzle contour, which otherwise has to be realized via the wall, can be replaced by the magnetic nozzle realized via the at least one coil.

The solution according to the invention can be used, for example, for a drive device of a missile. For example, this can be used to implement a drive device for interplanetary missions or for exploration missions in the cis -unun space.

Furthermore, this can be used, for example, to realize a reentrant body with a thermal protection system.

The solution according to the invention can be realized, for example, in a nuclear-thermal drive device or in other non-heat-thermal drive devices.

LIST OF REFERENCE NUMBERS

10

driving device

12

thrust chamber

14

Axial direction

16

thrust space

18

wall

20

inlet port

22

First area

24

Second area

26

Third area

28

Fourth area

30

cooling device

32

First page

34

Second page

36

Passage direction

38

Movie

40

tank

42

mixing device

44

output

46

entrance

48

check valve

50

output

52

pump

54

management

56

Shutoff valve / throttle valve

58

branching means

60

management

62

fuel rods

64

mixing device

66

turbine

68

Electric generator

70

entrance

72

throttle valve

74

Kitchen sink

76

Control / regulating device

78

Main flow direction

80

course

82

Kitchen sink

84

wall region

86

Cooled system

88

Cooled system

90

Re-entry

92

wall

94

First page

96

Second page

98

Hot gas flow

100

inner space

102

Kitchen sink

104

Passage direction

106

Movie

108

magnetic field

Claims (20)

Cooled system exposed to hot gas flow comprising at least one wall ( 18 ; 92 ) and a cooling device ( 30 ), which at least partially into the wall ( 18 ; 92 ), wherein the at least one wall ( 18 ; 92 ) is cooled by transpiration cooling and / or effusion cooling, and in the at least one wall ( 18 ; 92 ) at least one magnetic field generating coil ( 74 ; 102 ) is arranged from superconducting material, characterized in that the at least one wall ( 18 ; 92 ) is produced at least in a partial region from a porous ceramic material, and that the at least one coil ( 74 ; 102 ) is made of a porous ceramic material. Cooled system according to claim 1, characterized in that the material for the at least one coil ( 74 ; 102 ) is selected such that at an operating point or in an operating point range of the cooling device ( 30 ) the temperature at the at least one coil ( 74 ; 102 ) is below the transition temperature of the superconducting material. Cooled system according to one of the preceding claims, characterized in that the at least one wall ( 18 ; 92 ) with the at least one coil ( 74 ; 102 ) is formed at least in the partial area as a deflection device and / or magnetic nozzle for an ionized hot gas flow. Cooled system according to one of the preceding claims, characterized in that the at least one wall ( 18 ; 92 ) with the at least one coil ( 74 ; 102 ) is formed at least in a partial region as an accelerating device for ions in the hot gas flow. Cooled system according to one of the preceding claims, characterized in that a passage direction ( 36 ; 104 ) for fluid at the at least one wall ( 18 ; 92 ) for transpiration cooling and / or effusion cooling from a first side ( 32 ; 94 ) to a second page ( 34 ; 96 ) of the at least one wall ( 18 ; 92 ), the second page ( 32 ; 94 ) is directly loaded by the hot gas flow. Cooled system according to claim 5, characterized in that on the second side ( 34 ; 96 ) of the at least one wall ( 18 ; 92 ) a film formation of the fluid takes place. Cooled system according to one of the preceding claims, characterized in that the at least one wall ( 18 ; 92 ) is made in the at least one portion of a fiber-ceramic material. Cooled system according to one of the preceding claims, characterized in that the at least one wall ( 18 ; 92 ) in which at least a portion of an electrically insulating material is made and / or the at least one coil ( 74 ; 102 ) an electrical insulation device to the at least one wall ( 18 ; 92 ) assigned. Cooled system according to one of the preceding claims, characterized in that the at least one coil ( 74 ; 102 ) into the at least one wall ( 18 ; 92 ) is embedded. Cooled system according to claim 9, characterized in that the at least one coil ( 74 ; 102 ) in the at least one wall between fabric layers of the at least one wall ( 18 ; 92 ) lies. Cooled system according to one of the preceding claims, characterized in that fluid for cooling both the at least one wall ( 18 ; 92 ) and / or forming a protective film on the at least one wall ( 18 ; 92 ) as well as for cooling the superconducting material is used. Cooled system according to claim 11, characterized in that the fluid is also used as fuel. Cooled system according to one of the preceding claims, characterized in that the at least one wall ( 18 ; 92 ) a chamber ( 12 ) and a cavity ( 16 ; 100 ) or a recess limited. Cooled system according to claim 13, characterized in that a fluid for transpiration cooling and / or effusion cooling into the cavity ( 16 ; 100 ) or is coupled into the recess. Cooled system according to claim 13 or 14, characterized in that the chamber ( 12 ) is composed of segments. Cooled system according to one of claims 13 to 15, characterized in that the chamber ( 12 ) an inlet opening ( 20 ) and an outlet opening outside of pores of the at least one porous wall ( 18 ) having. Cooled system according to one of claims 13 to 15, characterized in that the chamber has an inlet opening and no outlet opening outside of pores of the at least one porous wall ( 92 ) having. Propulsion device for a missile, which has at least one thrust chamber and / or thrust chamber ( 12 ), which is designed as a cooled system according to one of claims 1 to 16. Reentry body comprising a refrigerated system according to any one of claims 1 to 15 or 17. A method of manufacturing a refrigerated system according to any one of claims 1 to 17, wherein the at least one wall is made via a preform, the preform comprising layers of fabric infiltrated or infiltrated with resin, characterized in that at least one spiral Conductor housing is inserted between fabric layers.

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