DE102013105526B4 - Space propulsion and method of starting a space propulsion - Google Patents

Abstract

A space engine (102) for a spacecraft (100) comprising:
- A fuel tank (108) for holding cryogenic fuel;
- An oxidizer tank (110) for holding cryogenic oxidizer;
- A combustion chamber device (106) for converting the fuel with oxidizer;
- a thrust nozzle device (112) for generating thrust;
- Two turbo pump devices (114) for conveying fuel and oxidizer to the combustion chamber device (106);
- a starting device (128) for starting the turbo pump devices (114), characterized in that the starting device (128) comprises at least one pressure vessel (130) to which fuel can be fed from the fuel tank (108) or oxidizer from the oxidizer tank (110), wherein the starting device (128) further comprises a heat exchanger (142), wherein the pressure vessel (130) for increasing the pressure of the fuel contained therein or the oxidizer contained therein heat can be supplied by means of the heat exchanger (142) and wherein the pressurized fuel or oxidizer for Starting the turbo pump devices (114) is usable.

Description

The present invention relates to a space propulsion system, in particular a rocket propulsion system for space vehicles.

Such drives are for example from the DE 1 626 101 C , of the DE 699 23 944 T2 as well as the DE 21 55 786 A known.

Depending on the intended use of the spacecraft, it may be desirable to start a space drive of the spacecraft not only once, but several times. For this purpose, pyrotechnic systems can be provided, for example, by means of which turbo pump devices of the space propulsion system can be started for conveying oxidizer and fuel to a combustion chamber device of the space travel system.

The present invention is based on the object of providing a space propulsion system which can be reliably reignited multiple times, in particular as often as desired.

• einen Brennstofftank zur Aufnahme von kryogenem Brennstoff;
• einen Oxidatortank zur Aufnahme von kryogenem Oxidator;
• eine Brennkammervorrichtung zur Umsetzung des Brennstoffs mit Oxidator; eine Schubdüsenvorrichtung zur Erzeugung von Schub;
• zwei Turbopumpenvorrichtungen zum Fördern von Brennstoff und Oxidator zu der Brennkammervorrichtung;
• eine Startvorrichtung zum Starten der Turbopumpenvorrichtungen,
• wobei die Startvorrichtung mindestens einen Druckbehälter umfasst, welchem Brennstoff aus dem Brennstofftank oder Oxidator aus dem Oxidatortank zuführbar ist, wobei die Startvorrichtung ferner einen Wärmeüberträger umfasst,
• wobei dem Druckbehälter zur Druckerhöhung des darin enthaltenen Brennstoffs oder des darin enthaltenen Oxidators Wärme mittels des Wärmeüberträgers zuführbar ist und
• wobei der unter Druck gesetzte Brennstoff oder Oxidator zum Starten der Turbopumpenvorrichtung nutzbar ist.
• Dadurch, dass bei dem erfindungsgemäßen Raumfahrtantrieb eine Startvorrichtung vorgesehen ist, welche mindestens einen Druckbehälter zur Aufnahme und zum Erwärmen von kryogenem Brennstoff oder kryogenem Oxidator umfasst, kann der Brennstoff bzw. der Oxidator besonders einfach unter Druck gesetzt und zum Starten der Turbopumpenvorrichtungen genutzt werden. Die Startvorrichtung ist somit vorzugsweise ein verschleißfreies System, welches beliebig oft wiederverwendet werden kann. Der Raumfahrtantrieb ist somit beliebig oft wiederzündbar, insbesondere ohne Verschleißelemente wie pyrotechnische Elemente ersetzen zu müssen.

According to the invention, this object is achieved by a space drive for a spacecraft which comprises the following:

• a fuel tank for holding cryogenic fuel;
• an oxidizer tank for holding cryogenic oxidizer;
• a combustion chamber device for converting the fuel with oxidizer; a thrust nozzle device for generating thrust;
• two turbo pump devices for delivering fuel and oxidizer to the combustor device;
• a starting device for starting the turbo pump devices,
• wherein the starting device comprises at least one pressure vessel, to which fuel from the fuel tank or oxidizer from the oxidizer tank can be fed, wherein the starting device further comprises a heat exchanger,
• wherein heat can be supplied to the pressure vessel by means of the heat exchanger to increase the pressure of the fuel contained therein or the oxidizer contained therein, and
• wherein the pressurized fuel or oxidizer can be used to start the turbo pump device.
• Because a starting device is provided in the space propulsion system according to the invention, which comprises at least one pressure vessel for receiving and heating cryogenic fuel or cryogenic oxidizer, the fuel or oxidizer can be particularly easily pressurized and used to start the turbo pump devices. The starting device is thus preferably a wear-free system which can be reused as often as required. The space propulsion can thus be re-ignited as often as required, in particular without having to replace wearing elements such as pyrotechnic elements.

A pressure vessel of the starting device is preferably connected to the oxidizer tank by means of an oxidizer line, so that the oxidizer can be supplied to the pressure vessel directly from the oxidizer tank.

Alternatively or in addition to this, it can be provided that a pressure vessel, in particular a further pressure vessel, is connected directly to the fuel tank by means of a fuel line, so that fuel can be fed directly to the pressure vessel from the fuel tank.

The at least one pressure vessel is preferably also connected to at least one turbo pump device by means of lines, in particular by means of an oxidizer line, a fuel line and / or an exhaust line, so that the pressurized fuel or the pressurized oxidizer is removed from the pressure vessel for driving and thus starting the turbo pump device can be used.

“Starting” the turbo pump devices is to be understood in particular as driving the turbine devices of the turbo pump devices, so that compressor devices of the turbo pump devices can be driven and thus fuel and oxidizer can be fed to the combustion chamber device under high pressure.

After the turbine devices and thus the compressor devices have been driven, the space drive can preferably be operated in a self-sustaining manner, that is to say without a drive by means of the starting device. The starting process, that is to say starting the turbo pump devices and thus the space propulsion system, is then preferably completed.

It can be favorable if the starting device comprises two pressure vessels, fuel from the fuel tank being able to be supplied to one pressure vessel and an oxidizer from the oxidizer tank being able to be supplied to a further pressure vessel. Preferably, heat can be supplied to both pressure vessels to increase the pressure of the fuel contained therein and the oxidizer contained therein. The pressurized fuel and the pressurized oxidizer are then preferably used to start the turbo pump devices.

It can be advantageous if the turbo pump devices comprise turbine devices for driving compressor devices of the turbo pump devices. The pressurized fuel from one container and / or the pressurized oxidizer from the further pressure container can then preferably be fed to the turbine devices, in particular can be fed directly.

It can be advantageous if the space drive comprises a combustion device which is different from the combustion chamber device and to which fuel and oxidizer can be supplied.

The space propulsion system preferably comprises a combustion device which is different from the combustion chamber device and to which the pressurized fuel from one pressure vessel and / or the pressurized oxidizer from the further pressure vessel can be fed.

It can be advantageous if the turbo pump devices comprise turbine devices for driving compressor devices of the turbo pump devices and if an exhaust gas from the combustion device can be fed to the turbine devices to drive the turbo pump devices.

In particular, in order to start the turbo pump devices, the pressurized fuel can preferably be fed to the combustion device from the one pressure vessel and the pressurized oxidizer from the further pressure vessel. The exhaust gas from the combustion device, which can be obtained by burning the fuel with the oxidizer in the combustion device, is preferably then fed to the turbine devices in order to drive the turbo-pump devices.

The combustion device is preferably designed as a gas generator device.

The space propulsion is then in particular a gas generator engine.

It can be advantageous if the space propulsion system includes at least one valve device, by means of which the supply of fuel from the fuel tank and / or the supply of oxidizer from the oxidizer tank to the combustion device, to the at least one pressure vessel and / or to the combustion chamber device can be controlled or regulated is.

It can be favorable if the space drive includes at least one three-way valve, by means of which it is possible to switch between supplying the combustion device with fuel and oxidizer by the starter device on the one hand and supplying the combustion device with fuel and oxidizer by the turbo pump devices on the other.

The space drive according to the invention is particularly suitable for multiple starts, in particular for re-ignition.

The present invention also relates to a method for starting a space propulsion system.

In this regard, the invention is based on the object of providing a method by means of which a space propulsion system can be reliably reignited several times, in particular as often as desired.

• Zuführen von kryogenem Brennstoff aus einem Brennstofftank zu einem Druckbehälter und/oder Zuführen von kryogenem Oxidator aus einem Oxidatortank zu einem Druckbehälter;
• Erwärmen des Brennstoffs durch Zuführen von Wärme zu dem Druckbehälter mittels eines Wärmeüberträgers, so dass der Brennstoff unter Druck gesetzt wird, und/oder Erwärmen des Oxidators durch Zuführen von Wärme zu dem Druckbehälter mittels eines Wärmeüberträgers, so dass der Oxidator unter Druck gesetzt wird;
• Nutzen des unter Druck stehenden Brennstoffs und/oder des unter Druck stehenden Oxidators zum Starten von Turbopumpenvorrichtungen des Raumfahrtantriebs.

According to the invention, this object is achieved by a method for starting a space propulsion system, which comprises the following:

• Supplying cryogenic fuel from a fuel tank to a pressure vessel and / or supplying cryogenic oxidizer from an oxidizer tank to a pressure vessel;
• Heating the fuel by supplying heat to the pressure vessel by means of a heat exchanger so that the fuel is pressurized and / or heating the oxidizer by supplying heat to the pressure vessel by means of a heat exchanger so that the oxidizer is pressurized;
• Using the pressurized fuel and / or the pressurized oxidizer to start space propulsion turbopump devices.

The method according to the invention preferably has one or more of the features and / or advantages described in connection with the space drive according to the invention.

It can be advantageous if fuel is supplied from the fuel tank to a pressure vessel and oxidizer from the oxidizer tank to a further pressure vessel, heat being supplied to both pressure vessels to increase the pressure of the fuel contained therein and the oxidizer contained therein, and the pressurized fuel and the under Pressurized oxidizer can be used to start the turbo pump devices.

In one embodiment of the invention it is provided that the turbo pump devices are turbine devices for driving Compressor devices of the turbo pump devices and that the pressurized fuel from the one pressure vessel and / or the pressurized oxidizer from the further pressure vessel, in particular directly, is fed to the turbine devices.

The space propulsion system preferably comprises a combustion device different from the combustion chamber device, to which fuel and oxidizer are supplied, in particular to which the pressurized fuel is supplied from one pressure vessel and / or the pressurized oxidizer from the further pressure vessel.

It can be advantageous if the turbo pump devices comprise turbine devices for driving compressor devices of the turbo pump devices and if an exhaust gas from the combustion device is supplied to the turbine devices to drive the turbo pump devices.

In particular, it can be provided that to start the space propulsion, in particular to start the turbopump devices, the combustion device is supplied with the pressurized fuel from one pressure vessel and / or the pressurized oxidizer from the further pressure vessel and that after the space propulsion has started, in particular after starting the turbo pump devices, the combustion device is supplied with fuel and / or oxidizer which has been pressurized by means of the compressor devices of the turbo pump devices.

Furthermore, the space drive according to the invention and / or the method according to the invention for starting a space drive can have one or more of the features and / or advantages described below:

The space engine is preferably a rocket upper stage engine.

In particular, the space propulsion system can be used for spacecraft departing earth orbit. Here it can be desirable and sometimes essential to switch the space propulsion system on and off several times.

By means of the starting device of the space propulsion system according to the invention, fuel and / or oxidizer which are already present to operate the combustion chamber device can preferably also be used to start the turbo pump devices. Undesired contamination of the space propulsion system, in particular the turbo pump devices, due to the use of other fuels, in particular pyrotechnic elements, can thereby preferably be avoided. In particular, contamination by powder vapor residues can preferably be avoided.

In particular, if hot exhaust gas from the gas generator device is used to start the turbo pump devices, in particular to drive the turbine devices of the turbo pump devices, a transition of the drive of the turbine devices from a drive by means of cryogenic propellant gas (such as, for example, when driving the turbine devices directly by means of the under pressure fuel set and / or by means of the pressurized oxidizer) to the drive by means of hot exhaust gases from the combustion device in normal operation of the space propulsion system, preferably avoidable. In this way, the reliability and stability of the space drive, in particular of the turbo pump devices, can preferably be increased significantly.

The method according to the invention for starting a space drive can preferably be repeated as often as desired in the space drive according to the invention.

Further preferred features and / or advantages of the invention are the subject matter of the following description and the graphic representation of an exemplary embodiment.

• 1 eine schematische Darstellung einer Ausführungsform eines Raumfahrtantriebs, bei welchem zum Starten von Turbopumpenvorrichtungen des Raumfahrtantriebs eine Startvorrichtung mit zwei Druckbehältern vorgesehen ist; und
• 2 eine vergrößerte beispielhafte Darstellung eines Druckbehälters aus 1.

In the drawings show:

• 1 a schematic representation of an embodiment of a space drive, in which a starting device with two pressure vessels is provided for starting turbo pump devices of the space drive; and
• 2 an enlarged exemplary representation of a pressure vessel 1 .

Identical or functionally equivalent elements are provided with the same reference symbols in all figures.

One in the 1 and 2 The illustrated embodiment of a spacecraft designated as a whole by 100 comprises a space drive 102 , by means of which the spacecraft 100 is drivable.

Space propulsion 102 is in particular a rocket engine 104 , for example a spacecraft upper stage engine 100 , by means of which the earth orbit can be left.

Space propulsion 102 comprises a combustion chamber device 106 , a fuel tank 108 and an oxidizer tank 110 .

The combustion chamber device 106 is fuel from the fuel tank 108 and oxidizer from the oxidizer tank 110 feedable.

By burning the fuel with the oxidizer, the chemical energy it contains can be converted into kinetic energy. In particular, a thrust nozzle device 112 of space propulsion 102 an expansion of the fuel, the oxidizer and / or the exhaust gas obtainable by combustion of the fuel with the oxidizer take place. Due to the shape of the thruster device 112 the expansion takes place against a desired direction of movement of the spacecraft 100 so that due to the recoil generated thereby, a thrust to propel the spacecraft 100 is produced.

Space propulsion 102 further comprises two turbo pump devices 114 which each have a turbine device 116 and a compressor device 118 include.

The turbine device 116 and the compressor device 118 of each turbo pump device 114 are by means of a shaft 120 mechanically coupled together so that by driving the turbine device 116 the compressor device 118 can be driven.

The compressor device 118 one to the fuel tank 108 associated turbo pump device 114 serves to put the fuel under high pressure, for example 100 bar, and the combustion chamber device 106 and / or the thruster device 112 feed.

The compressor device 118 one to the oxidizer tank 110 associated turbo pump device 114 serves to put the oxidizer under high pressure, for example 100 bar, and the combustion chamber device 106 to feed.

For driving the turbo pump devices 114 includes space propulsion 102 one from the combustion chamber device 106 various combustion device 122 .

The combustion device 122 is in normal operation of the space propulsion system 102 in which the turbo pump devices 114 continuously driven, with fuel and oxidizer, which can be supplied from a fuel line 124 or an oxidizer line 126 to supply the combustion chamber device 106 or the thruster device 112 is branched off with fuel or oxidizer.

In normal operation of the space propulsion system 102 is used to supply the combustion device 122 thus fuel and oxidizer are used, which by means of the compressor devices 118 of the turbo pump devices 114 was pressurized.

To start the space propulsion 102 can the incinerator 122 by means of the compressor devices 118 of the turbo pump devices 114 however, no pressurized fuel and no pressurized oxidizer are supplied because the turbo pump devices 114 before the start of space propulsion 102 are deactivated and thus the compressor devices 118 can also not serve to increase the pressure.

To start the turbo pump devices 114 and thus the entire space propulsion system 102 includes space propulsion 102 a starting device 128 .

The starting device 128 includes two pressure vessels 130 .

One of the pressure vessels 130 is by means of a fuel line 124 directly to the fuel tank 108 connected.

The further pressure vessel 130 is by means of an oxidizer line 126 directly to the oxidizer tank 110 connected.

The pressure vessels 130 can thus fuel from the fuel tank 108 or oxidizer from the oxidizer tank 110 are fed.

Since the fuel is preferably cryogenic fuel, in particular liquid hydrogen, and since the oxidizer is preferably cryogenic oxidizer, in particular liquid oxygen, the pressure of the fuel and the oxidizer in the pressure vessels can increase 130 particularly easily done in that the pressure vessel 130 and thus heat is supplied to the fuel and the oxidizer.

The pressurized fuel in one pressure vessel 130 and the pressurized oxidizer in the further pressure vessel 130 can then use the combustion device 122 are supplied to be chemically reacted with one another there. The resulting exhaust gases from the combustion device 122 are via exhaust pipes 132 the turbo pump devices 114 , especially the turbine devices 116 of the turbo pump devices 114 , feedable and can for driving, in particular for starting, the turbo pump devices 114 be used.

The combustion device 122 is in particular a gas generator device 134 .

Space propulsion 102 is thus in particular a gas generator engine 136 .

For controlling and / or regulating the supply of fuel and oxidizer to the turbo pump devices 114 , to the pressure vessels 130 and / or to the combustion device 112 are valve devices 138 intended.

At least one valve device 138 is for example as a three-way valve 140 educated.

A three-way valve 140 can in particular be used to switch between a supply of the combustion device 122 with fuel or oxidizer from the fuel tank 108 or the oxidizer tank 110 on the one hand and the supply of fuel or oxidizer from a pressure vessel 130 on the other hand to switch.

How in particular 2 can be seen, the starting device 128 also a heat exchanger 142 include.

By means of the heat exchanger 142 is a pressure vessel 130 , in particular the fuel or oxidizer arranged therein, heat can be supplied.

Preferably each pressure vessel 130 at least one heat exchanger 142 assigned.

The starting device 128 can preferably also have a flushing device 144 include, in particular around the at least one pressure vessel 130 between two space propulsion starts 102 to rinse and prepare for another start-up.

• In einem Ruhebetrieb des Raumfahrtantriebs 102, in welchem mittels der Schubdüsenvorrichtung 112 kein Schub erzeugt wird, befinden sich die Turbopumpenvorrichtungen 114 ebenfalls in einem Ruhebetrieb, das heißt, dass insbesondere die Kompressorvorrichtungen 118 der Turbopumpenvorrichtungen 114 nicht angetrieben sind. Mittels der Turbopumpenvorrichtungen 114 kann somit im Ruhebetrieb des Raumfahrtantriebs 102 kein unter Druck stehender Brennstoff und kein unter Druck stehender Oxidator erzeugt werden.

The space engine described above 102 works like this:

• In an idle mode of the space drive 102 , in which by means of the thrust nozzle device 112 no thrust is generated, the turbo pump devices are located 114 also in idle mode, that is, in particular the compressor devices 118 of the turbo pump devices 114 are not driven. By means of the turbo pump devices 114 can thus when the space engine is idle 102 no pressurized fuel or oxidizer are generated.

However, pressurized fuel and / or pressurized oxidizer are included in the 1 and 2 illustrated embodiment of the space drive 102 to operate the space propulsion system 102 absolutely necessary.

Space propulsion 102 therefore includes a starting device 128 to start the space propulsion 102 provide the required pressurized fuel and / or the required pressurized oxidizer.

For this purpose, fuel is taken from the fuel tank 108 a pressure vessel 130 fed. In addition, the oxidizer is removed from the oxidizer tank 110 another pressure vessel 130 fed.

The pressure vessel 130 are then closed and by means of heat exchangers 142 warmed up.

The initially cryogenic fuel and the initially cryogenic oxidizer are thereby heated and pressurized.

Upon reaching a desired pressure level, the pressurized fuel and the pressurized oxidizer are released from the pressure vessels 130 the combustion device 122 fed.

In the incinerator 122 the fuel is burned with the oxidizer.

The resulting hot exhaust gas is under pressure via the exhaust pipes 132 the turbine devices 116 of the turbo pump devices 114 fed.

The turbine devices 116 are thereby driven, in particular set in rotation.

The rotational movement is via the shafts 120 the turbo pump device 114 on the compressor devices 118 of the turbo pump devices 114 transfer. The compressor devices 118 are then ready to use to remove the fuel from the fuel tank 108 supplied fuel or from the oxidizer tank 110 to put supplied oxidizer under pressure, in particular under a pressure of, for example, about 100 bar.

By means of the compressor devices 118 of the turbo pump devices 114 Pressurized fuel or oxidizer is then added to the combustor 106 and the thruster device 112 supplied to be used there to generate thrust.

From the fuel line 124 for supplying fuel under pressure from the compressor device 118 to the combustion chamber device 106 and / or to the thruster device 112 pressurized fuel can be diverted to the combustion device 122 feed.

Correspondingly, from the oxidizer line 126 for feeding by means of the compressor device 118 pressurized oxidizer produced to the combustor 106 pressurized oxidizer can be diverted to the combustion device 122 feed.

The combustion device 122 can thus after starting the turbo pump device 114 be supplied with fuel and oxidizer, which by means of the compressor devices 118 were pressured. The supply of the combustion device 122 with fuel and oxidizer you can start the space propulsion first 102 supplied by means of the pressure vessel 130 on the supply by means of the compressor devices 118 be changed.

After this changeover, for example by changing the three-way valves 140 , can the space propulsion 102 without the assistance of the starting device 128 continue to be operated in normal operation.

If necessary, the supply of fuel and oxidizer to the combustion chamber device 106 and / or the thruster device 112 interrupted to space propulsion 102 to stop, especially to put it back to sleep.

Another start of space propulsion 102 is then, however, at any time by using the starting device again 128 to start the turbo pump devices 114 possible.

By having the starting device 128 is provided, the space drive 102 can be reliably reignited as often as required.

List of reference symbols

100

Spacecraft

102

Space propulsion

104

Rocket engine

106

Combustion chamber device

108

Fuel tank

110

Oxidizer tank

112

Thruster device

114

Turbo pump device

116

Turbine device

118

Compressor device

120

wave

122

Combustion device

124

Fuel line

126

Oxidizer line

128

Starting device

130

pressure vessel

132

Exhaust pipe

134

Inflator device

136

Gas generator engine

138

Valve device

140

Three-way valve

142

Heat exchanger

144

Flushing device

Claims (15)

A space engine (102) for a spacecraft (100), comprising: - a fuel tank (108) for holding cryogenic fuel; - An oxidizer tank (110) for holding cryogenic oxidizer; - A combustion chamber device (106) for converting the fuel with oxidizer; - a thrust nozzle device (112) for generating thrust; - Two turbo pump devices (114) for conveying fuel and oxidizer to the combustion chamber device (106); - a starting device (128) for starting the turbo pump devices (114), characterized in that the starting device (128) comprises at least one pressure vessel (130) to which fuel can be fed from the fuel tank (108) or oxidizer from the oxidizer tank (110), wherein the starting device (128) further comprises a heat exchanger (142), wherein the pressure vessel (130) for increasing the pressure of the fuel contained therein or the oxidizer contained therein heat can be supplied by means of the heat exchanger (142) and wherein the pressurized fuel or oxidizer for Starting the turbo pump devices (114) is usable. Space propulsion (102) after Claim 1 , characterized in that the starting device (128) comprises two pressure vessels (130), one pressure vessel (130) fuel from the Fuel tank (108) and a further pressure vessel (130) oxidizer can be fed from the oxidizer tank (110), both pressure vessels (130) can be supplied with heat to increase the pressure of the fuel contained therein and the oxidizer contained therein, and the pressurized fuel and the pressurized oxidizer can be used to start the turbo pump devices (114). Space propulsion (102) according to one of the Claims 1 or 2 , characterized in that the turbo pump devices (114) comprise turbine devices (116) for driving compressor devices (118) of the turbo pump devices (114) and that the pressurized fuel from the one pressure vessel (130) and / or the pressurized oxidizer from the further pressure vessel (130) can be fed to the turbine devices (116). Space propulsion (102) according to one of the Claims 1 to 3 , characterized in that the space drive (102) comprises a combustion device (122) which is different from the combustion chamber device (106) and to which fuel and oxidizer can be supplied. Space propulsion (102) after Claim 4 , characterized in that the space drive (102) comprises a combustion device (122) which is different from the combustion chamber device (106) and which contains the pressurized fuel from one pressure vessel (130) and / or the pressurized oxidizer from the further pressure vessel ( 130) can be supplied. Space propulsion (102) according to one of the Claims 4 or 5 , characterized in that the turbo pump devices (114) comprise turbine devices (116) for driving compressor devices (118) of the turbo pump devices (114) and that an exhaust gas from the combustion device (122) can be fed to the turbine devices (116) for driving the turbo pump devices (114) is. Space propulsion (102) according to one of the Claims 4 to 6th , characterized in that the combustion device (122) is designed as a gas generator device (134). Space propulsion (102) according to one of the Claims 4 to 7th , characterized in that the space drive (102) comprises at least one valve device (138), by means of which the supply of fuel from the fuel tank (108) and / or the supply of oxidizer from the oxidizer tank (110) to the combustion device (122), to which at least one pressure vessel (130) and / or to the combustion chamber device (106) can be controlled or regulated. Space propulsion (102) according to one of the Claims 1 to 8th , characterized in that the space drive (102) comprises at least one three-way valve (140), by means of which it is possible to switch between supplying the combustion device (122) with fuel and oxidizer by the starting device (128) and supplying the combustion device ( 122) with fuel and oxidizer by the turbo pump devices (114). A method of starting a space engine (102) comprising: - supplying cryogenic fuel from a fuel tank (108) to a pressure vessel (130) and / or supplying cryogenic oxidizer from an oxidizer tank (110) to a pressure vessel (130); - Heating the fuel by supplying heat to the pressure vessel (130) by means of a heat exchanger (142), so that the fuel is pressurized, and / or heating the oxidizer by supplying heat to the pressure vessel (130) by means of a heat exchanger ( 142) so that the oxidizer is pressurized; - Using the pressurized fuel and / or the pressurized oxidizer to start turbo pump devices (114) of the space propulsion system (102). Procedure according to Claim 10 , characterized in that the turbo pump devices (114) comprise turbine devices (116) for driving compressor devices (118) of the turbo pump devices (114) and that the pressurized fuel from the one pressure vessel (130) and / or the pressurized oxidizer from the further pressure vessel (130) is fed to the turbine devices (116). Method according to one of the Claims 10 or 11 , characterized in that the space drive (102) comprises a combustion device (122) different from the combustion chamber device (106), to which fuel and oxidizer are supplied. Procedure according to Claim 12 , characterized in that the space drive (102) comprises a combustion device (122) which is different from the combustion chamber device (106) and which contains the pressurized fuel from one pressure vessel (130) and / or the pressurized oxidizer from the further pressure vessel ( 130) is fed. Method according to one of the Claims 12 or 13 , characterized in that the turbo pump devices (114) comprise turbine devices (116) for driving compressor devices (118) of the turbo pump devices (114) and that an exhaust gas from the combustion device (122) is supplied to the turbine devices (116) for driving the turbo pump devices (114) becomes. Procedure according to Claim 14 , characterized in that to start the space propulsion (102), in particular to start the turbo pump devices (114), the combustion device (122), the pressurized fuel from one pressure vessel (130) and / or the pressurized oxidizer from the other Pressure vessel (130) is supplied and that after starting the space propulsion system (102), in particular after starting the turbo pump devices (114), the combustion device (122) is supplied with fuel and / or oxidizer, which by means of the compressor devices (118) of the turbo pump devices ( 114) was pressurized.

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