Rocket engine, method and spacecraft

Abstract

The invention relates to a rocket engine (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), wherein the first tank is filled with a fuel and the second tank with an oxidising agent, such as liquid hydrogen peroxide, for feeding at least one main engine (120) of the rocket engine, which main engine can preferably be repeatedly ignited. A gas generator (140) is assigned to the rocket engine and is designed to produce vaporous hydrogen peroxide. After flowing through at least one turbine, the hydrogen peroxide can be at least partially supplied to a separator unit (160) which is designed to break down vaporous hydrogen peroxide into steam and gaseous oxygen. Alternatively or in addition, the hydrogen peroxide can be supplied to an electrolysis unit (302, 402) which is designed to generate gaseous oxygen and gaseous hydrogen from the hydrogen peroxide supplied to it and / or the steam downstream of it. The invention also relates to a method for operating the rocket engine and to a spacecraft.

Description

The invention relates firstly to a rocket propulsion system comprising a first tank and a second tank, wherein the first tank is filled with a fuel, and the second tank is filled with an oxidiser, such as liquid hydrogen peroxide, for purposes of supplying at least one, preferably re-ignitable, main engine of the rocket propulsion system. In addition, the invention relates to a method for the operation of such a rocket propulsion system, and to a space vehicle with such a rocket propulsion system. Remote sensing or reuse are major challenges for autonomous propulsion systems of rockets and space vehicles. In the case of long-term missions, cryogenic space vehicles are not always the first choice, as great efforts are required to keep the cryogenic liquids in liquid form (the so-called "boil-off" problem) so as to ensure a relatively high density and thus small propellant tanks. Conventional, storable propellants are of known prior art for remote sensing and long operating times in orbit (satellites). Toxic propellants such as NTO (= dinitrogen tetroxide) or MMH (= monomethyl hydrazine) are often used for rocket stages or satellites. These propellants have the disadvantage that they are no longer environmentally compliant with national regulations. In addition, there are disadvantages in the remote sensing of the Moon and near-Earth planets, such as Mars, when considering reusable or returnable systems. For such reusable or returnable systems, the ability to generate on site the propellants and working gases required for the return flight is of major importance. However, as representatives of these conventional types of propellant, NTO and MMH can only be synthesised on Mars or the Moon at great expense, or not at all. Conventional high-performance, high-pressure, gases, such as helium, are also only accessible there under difficult conditions, and are already becoming increasingly scarce on Earth. One of the objects of the invention is to specify an autogenous rocket propulsion system that operates with environmentally-compatible propellants, and utilises the particular properties of hydrogen peroxide for other additional functions of the rocket propulsion system. Further objects of the invention are the specification of a method for the operation of such a rocket propulsion system, and a space vehicle equipped with such a rocket propulsion system. These objects are achieved by a rocket propulsion system in accordance with Claim 1, a method in accordance with Claim 13, and a space vehicle in accordance with Claim 16. Advantageous forms of embodiment are disclosed in the subsidiary claims, the description, and the figures. Here one of the objects is first achieved in that the rocket propulsion system is assigned a gas generator that is designed to produce vaporous hydrogen peroxide, which is supplied completely or partially to at least one turbine. After it has flowed through the turbine, at least some of the hydrogen peroxide flowing through can be supplied to a separator unit, which is designed to break down the vaporous hydrogen peroxide into water vapour and gaseous oxygen, and / or the hydrogen peroxide flowing through can be supplied to an electrolysis unit, by means of which gaseous oxygen and gaseous hydrogen are produced from the vaporous hydrogen peroxide, or from water vapour that is located downstream. By this means, the rocket propulsion system can be operated with environmentally-compatible propellants that can be synthesised with relatively little effort, even under difficult environmental conditions, such as those prevailing on the Moon or near-Earth planets such as Mars. In addition, the non-toxic oxidiser ensures that space vehicles, rocket stages, satellites or similar that are equipped with the inventive rocket propulsion system can be reused. By this means, it may also be possible to achieve returnable and reusable space units. The initially liquid hydrogen peroxide is catalytically converted in the gas generator into vaporous hydrogen peroxide or a so-called "working gas mixture", which is, at least partially, split into water vapour, that is to say, water and oxygen, in the separator unit, and / or is directly or subsequently split into oxygen and hydrogen in the electrolysis unit. The separator unit located downstream of the gas generator can separate the working gas mixture electrothermally or fluid-dynamically with the aid of centrifugal force. By virtue of the utilisation of these decomposition products of the hydrogen peroxide, an optimised operation of the autogenous rocket propulsion system and its subsidiary and ancillary systems can be achieved. The tanks can, for example, be pressurised with oxygen and / or water vapour, making a conventional inert gas system for tank pressurisation completely, or at least partially, unnecessary. The tank pressurisation ensures that the main engine can be reliably ignited repeatedly. In an advantageous configuration, the gas generator can be used to supply at least one position control thruster with vaporous hydrogen peroxide. This eliminates the need for a separate supply to the position control thrusters. The turbine can have a bypass branch, which is designed, amongst other tasks, to influence the volumetric flow of the gaseous hydrogen peroxide flowing through the turbine, in particular, that is to say, to increase or reduce it. An electrical generator, and / or at least one fuel pump, and / or an oxidiser pump, can preferably be driven by means of the at least one turbine. As a consequence, an electrical generator is available that can be used, for example, to supply the rocket propulsion system and its subsidiary systems, and / or the entire space vehicle, with electrical energy. The electrical generator can also, for example, be used to supply an optional electrolysis unit with the necessary electrical energy. In a fluid-dynamic mode of operation of the separator unit, the turbine can also drive the separator unit directly by mechanical rotation, whereas in a thermal mode of operation, the power generated by the electric generator is required to operate the separator unit. It is also possible to drive a fuel pump, and / or an oxidiser pump, electrically, or directly by mechanical rotation, by means of the turbine. In an advantageous configuration, provision is made such that the first tank can be pressurised by means of a water vapour leg of the separator unit, and the second tank can be pressurised by means of an oxidiser leg of the separator unit. By this means it is easy to pressurise the tanks with decomposition products of the hydrogen peroxide, that is to say, products of the oxidiser that is already present. In the context of the present description, the term "leg" defines a pipeline, or a plurality of pipelines, the arrangement of which, in the case of a plurality of lines, can resemble the topology of a cable harness or line harness, whereby each leg, or each line, carries the same chemical substances, such as H2, O2, H2O2, fuel, etc., and whereby these can be present in different physical states. Forms of embodiment in which the rocket propulsion system has at least one vessel with an inert gas for at least supplementary pressurisation of the first and / or second tank, are advantageous. Consequently, it is possible to pressurise the tanks independently of the decomposition products of the hydrogen peroxide. In accordance with advantageous forms of embodiment, the second tank can be pressurised by means of an oxidiser leg of the separator unit, an electrolysis unit is connected to the separator unit by means of a water vapour leg, and the electrolysis unit has a high-energy hydrogen and oxygen leg. By virtue of the electrolysis unit, which preferably operates at high-temperature and high-pressure, it is also possible to extract hydrogen and oxygen from the water, or water vapour separated with the aid of the separator unit. The hydrogen and the oxygen can be used, for example, to supply a position control thruster, which can thereby generate a significantly higher thrust, or specific impulse, compared to a supply with hydrogen peroxide. In accordance with advantageous forms of embodiment, an inventive rocket propulsion system, in the variant in which the vaporous hydrogen peroxide, after flowing through the at least one turbine, can, at least partially, be supplied to an electrolysis unit, has at least one working gas leg for a working gas mixture exiting from the turbine, that is to say, for mixed proportions of water vapour and oxygen. The working gas leg then preferably comprises on the one hand an oxidiser leg for the pressurisation of the second tank. On the other hand, in such forms of embodiment, the working gas leg preferably comprises a conversion leg, in which the working gas mixture can be supplied to the electrolysis unit for the operation of the latter. Here the electrolysis unit preferably has a high-energy hydrogen and oxygen leg. By virtue of the electrolysis unit, which preferably operates at high temperature and high pressure, it is also possible to extract hydrogen and oxygen from the existing water vapour / oxygen mixture from the working gas in the conversion leg. The hydrogen and oxygen can be used, for example, to supply a position control thruster, which by this means can generate a significantly higher thrust or specific impulse in comparison to one supplied with hydrogen peroxide. A first high-pressure accumulator is preferably assigned to the high-energy hydrogen leg, and a second high-pressure accumulator is preferably assigned to the high-energy oxygen leg. As a consequence, a buffer or storage action is achieved in the hydrogen and oxygen leg. The first tank can preferably be pressurised using the high-energy hydrogen leg. This eliminates the need for separate pressurisation with an inert gas, which would otherwise be necessary. In an advantageous development, provision is made for a main nozzle of the main engine to be charged with hydrogen by means of the first high-pressure accumulator, and with oxygen by means of the second high-pressure accumulator. By this means it is possible, for example, to increase the thrust of the main engine, and to control the thrust vector of the main engine so as to change the flight path, etc., when required. The at least one position control thruster, at least one defensive unit, and / or a high-energy unit / high-pressure unit can preferably be supplied by means of the first and second high-pressure accumulators. Amongst other features, this can increase the performance of the position control thrusters, in comparison to supplying them with pure hydrogen peroxide. In addition, a defensive unit such as a recoilless light gas weapon, or other high-energy units, can be supplied. The defensive unit can also be a net harpoon, or a similar device, for capturing satellites that have got out of control, for example, before there is a risk of collision with other objects in the orbit. The high-pressure unit can take the form of an interface to an inflatable structure, such as a habitat. An oxygen storage unit is preferably assigned to the oxidiser leg of the separator unit, and a water storage unit is preferably assigned to the water vapour leg of the separator unit. As a consequence, an accumulator is available for supplying a life support system of the space vehicle with water and oxygen. Another object cited earlier is furthermore achieved by a method for the operation of the rocket propulsion system in accordance with Claim 12, in which the fuel is supplied to the main engine via a first main supply line, and the liquid hydrogen peroxide is at least partially tapped from a second main supply line of the main engine, and supplied to the gas generator. As a consequence, only a relatively small proportion of the liquid hydrogen peroxide may be supplied to the gas generator, while the remaining (main) proportion of the liquid hydrogen peroxide is used to generate thrust, after the main nozzle and the combustion chamber of the main engine have been cooled. The liquid hydrogen peroxide supplied via the second main supply line can, for example, be divided between the main engine and the gas generator for purposes of the catalytic conversion of the liquid hydrogen peroxide into gaseous or vaporous hydrogen peroxide, by means of a controllable distributor (a so-called "divider"), or a controllable three-way valve with corresponding hydraulic ports, or similar. If the main engine operates with fuel cooling, a first proportion of the hydrogen peroxide is supplied directly to the main engine, while the remaining (residual) second proportion is returned to the combustion chamber of the main engine, after passing through the turbine. The ratio of the distribution between the first and second proportions depends on the requirements of the subsidiary systems of the rocket propulsion system for pressurisation of the tanks and energy conversion. In accordance with a development of the method, the vaporous hydrogen peroxide exiting from the gas generator is at least partially supplied to the turbine. This makes it possible, amongst other features, to control the power output of the turbine. The proportion of the vaporous hydrogen peroxide not supplied to the turbine can be supplied to the combustion chamber of the main engine via a suitable distribution unit. In principle, only a proportion of the hydrogen peroxide is supplied to the turbine, depending on the deployment scenario of the rocket propulsion system. In order to achieve the highest possible specific power output, as much hydrogen peroxide as possible should be supplied to the main engine, or returned to it after passing through the turbine with the aid of a suitable return line (not illustrated in the drawings). This ratio can vary as a function of the deployment scenario. The pure pressurisation requirement of the tanks can turn out to be lower than the power output required for the subsidiary systems or auxiliary systems, and thus the requirement for the oxidiser or hydrogen peroxide tapped from the main supply line of the main engine. The highest possible proportion of the oxidiser should always be used directly to supply the main engine, that is to say, it should remain in the so-called main cycle in order primarily to generate thrust and impulse power. A rocket propulsion system in accordance with the invention can preferably have a propulsion cycle with which it can be operated in a monopropellant mode when the inactive fuel leg is switched off. This enables an improved throttling capability to be achieved in the main propulsion system. Alternatively or additionally, the rocket systems can have an engine cycle with which, in a switched-off state of the main engine, the rocket propulsion system can be used to operate (possibly only) the position control system, to pressurise the fuel tanks, and / or (with a suitably developed interface) to provide working gas for external systems such as a space station or a habitat (e.g. inflatable structures). Such an engine cycle can be implemented by means of suitable subsidiary systems and / or interfaces. In addition, another object cited earlier is achieved by a space vehicle in accordance with the invention, which is equipped with at least one rocket propulsion system in accordance with the invention (in particular in one of the forms of embodiment cited). As a consequence, the optimised, autogenous rocket propulsion system can be used for a space vehicle . The invention is explained in more detail in the following description, with reference to the examples of embodiment illustrated in the figures. In the figures, the same design elements have the same reference numbers in each case. Dashed lines symbolise in each case optional lines or components. Here : Figure 1 shows a schematic flow diagram of a first form of embodiment of a rocket propulsion system, Figure 2 shows a schematic flow diagram of a second form of embodiment of a rocket propulsion system, Figure 3 shows a schematic flow diagram of a third form of embodiment of a rocket propulsion system, and Figure 4 shows a schematic flow diagram of a fourth form of embodiment of a rocket propulsion system. Figure 1 illustrates a schematic flow diagram of a first form of embodiment of a rocket propulsion system. A rocket propulsion system 100 comprises, inter alia, a first tank 102 for a fuel 104, and a second tank 106 for an oxidiser 108, which preferably takes the form of hydrogen peroxide 110. The fuel 104 takes the form of any liquid and storable fuel, such as paraffin, which, like the hydrogen peroxide 110 used as an oxidiser 108, also has the lowest possible toxicity. The fuel 104 can be supplied by means of a fuel pump Pi to a combustion chamber 122 of at least one main engine 12 0 by way of a main supply line 126. Accordingly, the oxidiser 108, that is to say, here preferably the hydrogen peroxide 110, can also be supplied to the combustion chamber 122 by means of an oxidiser pump P2 and a second main supply line 128, after passing through the main nozzle 124. After intimate mixing of the fuel 104 and the oxidiser 108 in the combustion chamber 122 of the main engine 120, their combustion takes place to generate thrust. A gas generator 140 is connected to the second main supply line 128 by means of a branch line 130. The volumetric flow of liquid hydrogen peroxide supplied to the gas generator 140 by means of the branch line 130 can be varied by means of a controllable distributor, which is not shown in the figures in the interests of a better overview. The gas generator 140 is designed to generate vaporous hydrogen peroxide, preferably catalytically; this can be supplied to a turbine 150 or another item of turbomachinery by means of a line Li. After flowing through the turbine 150, the hydrogen peroxide reaches a separator unit 160 by means of a further line L2. The lines Li,2 are connected by means of a bypass branch 154 in order to create a bypass for the turbine 150, whereby the volumetric flow of the hydrogen peroxide passing through the turbine 150 can be adjusted by means of valves, etc. (not shown) . Here another optional line L3 is connected to the optional bypass branch 154 as an example; this is used to supply a position control thruster 170 with vaporous hydrogen peroxide. Valves (not shown) are also provided in the line L3 so as to be able to control the thrust or the specific impulse of the position control thruster 170 in a differentiated manner. The vaporous hydrogen peroxide flowing to the separator unit 160, via the line L2 or the optional bypass branch 154 from the gas generator 140, is split in the latter into oxygen O2, and water or water vapour H2O; this is illustrated graphically by the two dotted circles and the chemical symbols O2 and H2O entered in the latter. The two dotted circles serve merely to illustrate the fact that within an oxidiser line 180, in the form of a pipe or a conduit, and a water vapour line 182, each of which is connected to the separator unit 160, the above-mentioned substances (O2, vaporous or gaseous H2O) can be discharged from the separator unit 160 in the direction of the two tanks 102, 106 in order to pressurise the latter. The first tank 102 containing the fuel 104 can preferably be pressurised with the separated water vapour by means of the water vapour line 182 connected to the separator unit 160, and the second tank 106 containing the liquid hydrogen peroxide 110 can correspondingly be pressurised with the separated gaseous oxygen by means of an oxidiser line 180 connected to the separator unit 160, as illustrated in each case by the two white arrows 184, 186. The turbine 150 can drive an optional electrical generator 152 (shown by a dashed line) in order to generate electrical energy. The fuel pump Pi and the oxidiser pump P2 can be driven directly by the turbine 150, or, if an electric generator 152 is present, can be driven electrically with the aid of electric motors (not shown). The separator unit 160 located downstream of the gas generator 140 can separate the supplied vaporous hydrogen peroxide, or the "working gas mixture", electrothermally or fluid-dynamically with the aid of centrifugal force. In the case of an electrothermal mode of operation of the separator unit 160, the electrical energy obtained with the aid of the generator 152 is utilised. If, on the other hand, the splitting of the hydrogen peroxide into oxygen and water or water vapour is based on the fluid-dynamic operating principle utilising centrifugal force, the separator unit 160 can be driven directly by the turbine 150 by means of mechanical rotation. Hydrogen peroxide 110 as the oxidiser used here in the rocket propulsion system 100 is largely environmentally compatible, non-toxic, and also comparatively easy to synthesise, even under difficult environmental conditions, such as those prevailing on the Moon and near-Earth planets such as Mars. In conjunction with a storable liquid fuel 104 with similar properties, a space vehicle 136 equipped with the rocket propulsion system 100 can also be reused or returned to Earth under certain circumstances. In addition, the splitting of hydrogen peroxide 110 within the rocket propulsion system 100 by means of the separator unit 160 into oxygen O2 and vaporous water vapour H2O allows the first and second tanks 102, 106 to be pressurised simultaneously. Therefore, in the first form of embodiment in Fig. 1, no additional tank with an inert gas such as helium, etc. is required for the pressurisation of the tanks 102, 106. The space vehicle 136 can take the form, for example, of a rocket, a satellite, a space capsule, a space station, or similar. Furthermore, valves or actuators, which are not shown in the interests of clarity, can be provided in all lines or pipework of the rocket propulsion system 100 as required; these can be controlled by an electronic controller or regulator, likewise not shown, of the rocket propulsion system 100 and / or the space vehicle 136. The same applies to connection nodes between two or more lines, or connection nodes formed by (multi-path) valves. Here the at least one electronic controller and / or regulator is designed to control all sequences or processes within the rocket propulsion system 100. Fig. 2 illustrates a schematic flow diagram of a second form of embodiment of a rocket propulsion system. The second form of embodiment of a rocket propulsion system 200 once again comprises the first and second tanks 102, 106, whereby the first tank 102 is filled with the fuel 104, and the second tank 106 is filled with the oxidiser 108 in the form of liquid hydrogen peroxide 110. The fuel 104 can be supplied directly via the first main supply line 126 to the combustion chamber 122 of the main engine 120 by means of the fuel pump Pi. Correspondingly, the oxidiser 108 can be supplied via the second main supply line 128 to the combustion chamber 122 by means of the oxidiser pump P2, whereby the oxidiser 108, or the hydrogen peroxide 110, cools the combustion chamber 122 and the main nozzle 124 before entering the combustion chamber 122. Within the combustion chamber 122, the fuel 104 and the gaseous oxidiser 108 are intimately mixed and combusted so as to generate an impulse. By means of the branch line 130 connected to the second main supply line 128, an adjustable proportion of the liquid hydrogen peroxide 110 can in turn be transferred to the gas generator 140 in order to generate gaseous hydrogen peroxide catalytically. The gaseous hydrogen peroxide 110 can be supplied to and discharged from the turbine 150 by means of the lines Li,2, and then passes into the separator unit 160. The gaseous hydrogen peroxide produced by the gas generator 140 can partially or completely bypass the turbine 150 with the aid of the bypass branch 154, and thus can, at least partially, also be led directly into the separator unit 160. With the aid of the bypass branch 154 and the line L3, the position control thruster 170 can still be supplied with gaseous hydrogen peroxide when required. The oxidiser line 180 and the water vapour line 182, which serve to pressurise the fuel 104 and the oxidiser 108 stored in the tanks 102, 106, are in turn connected to the separator unit 160. The optional electrical generator 152 can be driven by means of the turbine 150 so as to generate electrical energy. In a major difference from the first form of embodiment, the second form of embodiment of the rocket propulsion system 200 has a vessel 202, which is filled with an inert gas 210, such as helium, neon, argon, etc. By means of a line L4, which is connected to the water vapour line 182, the first tank 102 can be pressurised, that is to say, charged, with the inert gas 210. Furthermore, the second tank 106 can also be charged with the inert gas 210 by means of an optional line Ls . As illustrated in Figure 2, the second line Ls can branch off from the line L4, or can be connected directly to the vessel 202 independently of the line L4 (not shown). One advantage, amongst others, of the second form of embodiment of the rocket propulsion system 200 is to be seen in the fact that in addition to the possibility of pressurising the tanks 102, 106 with the fission products (O2, H2O) of the hydrogen peroxide, that is to say, one of the fuel components of the rocket propulsion system 200, there is the possibility of at least supplementary pressurisation of at least one of the tanks 102, 106 with the inert gas 210 from the vessel 202. The pressurisation of the tanks 102, 106 again takes place in the direction of the arrows 184, 186 . In accordance with a method for the operation of the rocket propulsion system 200, provision is made for the fuel 104 to be supplied to the main engine 120 via the first main supply line 126, and the liquid hydrogen peroxide is at least partially tapped, that is to say, diverted, from the second main supply line 128 of the main engine 120 and supplied to the gas generator 140. As a consequence, a mechanical power output of the turbine 150 can be varied within wide limits under the control of the controller and / or regulator. The vaporous hydrogen peroxide exiting from the catalytic gas generator 140 can, in accordance with the method, be at least partially bypassed around the turbine 150 and / or supplied to the position control thruster 170 with the aid of the bypass branch 154; this takes place under the permanent control of the controller and / or regulator. This means that the gaseous hydrogen peroxide escaping from the gas generator 140 - apart from the quantities supplied to the position control thruster 170 - passes completely via the turbine 150, and / or the bypass branch 154, into the separator unit 160. Fig. 3 illustrates a schematic flow diagram of a third form of embodiment of a rocket propulsion system. This form of embodiment of a rocket propulsion system 300 again comprises the two tanks 102, 106, which are, at least partially, filled with the fuel 104 and the oxidiser 108 in the form of hydrogen peroxide 110. The fuel 104 can be supplied by means of the fuel pump Pi via the first main supply line 126, and the oxidiser 108 can be supplied by means of the oxidiser pump P2 via the second main supply line 128, into the combustion chamber 122 of the main engine 120, whereby the cooling of the main nozzle 124 or the nozzle skirt and the combustion chamber 122 takes place by means of the oxidiser 108 or the hydrogen peroxide 110. The gas generator 140 is once again connected to the second main supply line 128 by means of the branch line 130. The turbine 150 can be charged with gaseous hydrogen peroxide from the gas generator 140 by means of the line Li; this can be discharged into the separator unit 160 via the line L2 after passing through the turbine 150. In contrast to the first two forms of embodiment, the optional bypass branch 154 of the turbine 150 that is shown in Figs. 1, 2 is missing here. The electrical generator 152 (illustrated with a solid line), which here is obligatory, can be driven by means of the turbine 150 to generate electrical energy. The position control thruster 170 can, amongst other options, be supplied by means of line L3 . Any desired division of the volumetric flows between the line Li and the line L3 can be provided by means of a valve (not shown) . The oxidiser 108 located in the second tank 106 in the form of the liquid hydrogen peroxide 110 can be pressurised by means of the oxygen line 180 exiting from the separator unit 160, as indicated by the white arrow 186, in an analogous manner to the forms of embodiment of Figs. 1, 2 . As in Figs. 1, 2, the dotted circles in the oxidiser and water vapour lines 180, 182 of the separator unit 160 just serve to illustrate the chemical compounds (O2, vaporous or gaseous H2O) flowing in these lines. The rocket propulsion system 300 is once again integrated into the space vehicle 136. In a significant difference from the two forms of embodiment of Figs. 1, 2, the third form of embodiment has, amongst other features, an electrolysis unit 302 together with associated lines, which is designed for high-pressure and / or high-temperature operation. The electrolysis unit 302, which preferably comprises at least one solid oxide electrolysis cell that conducts oxygen ions, is connected to the separator unit 160 by means of the water vapour line 182. The electrolysis unit 302 can, for example, be supplied with the electrical energy that is required for its operation by the electrical generator 152 that is driven by the turbine 150, or by another external electrical energy source (not shown). The electrolysis unit 302 is also assigned a high-energy hydrogen line 310 and a high-energy oxygen line 312 for purposes of discharging the reaction products H2 and O2 produced from the water supplied during electrolysis. The two dotted circles with the chemical symbols H2 and O2 contained therein, again merely serve to illustrate the substances discharged from the electrolysis cell 302 in the high-pressure and / or high-temperature legs 310, 312. The oxygen leg 312 of the electrolysis cell 302 is coupled to the oxidiser leg 180 of the separator unit 160. In a further difference, in the third form of embodiment a first high-pressure storage tank 320 is connected to the hydrogen leg 310 for purposes of storing the hydrogen H2 supplied by the electrolysis cell 302. A further line Ls branches off from the hydrogen leg 310, by means of which line the fuel 104 stored in the first tank 102 can also be pressurised in the direction of the white arrow 184, so that both tanks 102, 106 are permanently pressurised and a reliable repeated ignition of the main engine 120 is ensured when required. In addition, the oxygen leg 312 of the electrolysis unit 302 is connected by means of a line L7 to a second high-pressure accumulator 322 for purposes of receiving the oxygen O2 supplied by the electrolysis unit 302 . The two high-pressure accumulators 320, 322 further allow the operation of a number of exemplary subsidiary or auxiliary systems of the rocket propulsion system 300, which are briefly explained below. Thus, a further line Lg for hydrogen H2 is connected to the first high-pressure accumulator 320; this is connected to the main nozzle 124 of the main engine 120. Correspondingly, a further line L9 for oxygen O2 leads from the second high-pressure accumulator 322 to the main nozzle 124 of the main engine 120. In the event of an emergency, for example, this allows an increase in the specific impulse of the main engine 120, and the implementation of a complex thrust vector control of the main engine 12 0 in order to change the trajectory of the space vehicle 136 or similar; this is not possible with the first two forms of embodiment of the rocket propulsion system that are shown in Figs. 1, 2. Furthermore, two lines Lio, 11 lead from the two high-pressure accumulators 320, 322 to the position control thruster 170, so that the latter can be operated with high-energy oxygen O2 and hydrogen H2. Compared to the supply with gaseous hydrogen peroxide via the line L3 starting from the gas generator 140 that is provided in the forms of embodiment of Figs. 1, 2, this permits the generation of substantially higher specific impulses by means of the position control thruster 170. In addition, in a deviation from the forms of embodiment in Figs. 1, 2, a defensive unit 330, and / or a high-energy unit 332, are here connected to the high-pressure accumulators 320, 322 with the aid of further lines L(i2, 13) ■ The defensive unit 330 can, for example, be a light gas cannon (not shown), with a preferably integrated recoil compensation for purposes of accelerating a projectile to an exit velocity of up to 60 km / s. The light gas cannon can be operated by means of the hydrogen H2 and / or oxygen O2 stored in the high-pressure accumulators 320, 322. The hydrogen H2 serves as the light gas that accelerates the projectile, while a mixture of hydrogen H2 and oxygen O2 (oxyhydrogen gas) acts as the actual propellant charge, instead of black powder, etc. As a consequence, a considerable reduction in weight can be achieved compared to the use of black powder cartridges, while at the same time the discharge velocity is increased. A defined ejection of the acceleration gas H2 also ensures impulse equalisation by means of a suitably positioned counter-nozzle, so that the position of the space vehicle 136 remains essentially unchanged. In addition, the defensive unit 330 can be formed with a laser system (not shown) , which can also be supplied with the oxygen O2 and hydrogen H2 from the two high-pressure accumulators 320, 322, and with the power from the electric generator 152. The high-energy unit 332 can also take the form of any other device that also requires high-pressure hydrogen H2 and oxygen O2 for its operation. In the area of undesignated connection or junction points (nodes) between the lines La, 10 L9, 11 Lio, 12 Ln, 13 and others, valves, not shown, are preferably provided for purposes of controlling the passage and / or splitting of the respective material flows (O2, H2, H2O2, fuel, etc.), which may also be present in a liquid and / or a gaseous phase. In addition, valves can be provided on or in any sections of the lines. As a further difference, an oxygen storage unit 340 and a water storage unit 342 can optionally be provided, so that a life support system (not shown) of the space vehicle 136 can, for example, be permanently supplied with oxygen O2 and water H2O for a human crew on board the space vehicle 136. This makes it possible to achieve longer stays in space or, as required, journeys to the Moon and / or near-Earth planets such as Mars. For this purpose, the oxygen storage unit 340 is connected to the oxidiser leg 180 of the separator unit 160 by means of a further line L14 and the water storage unit 342 is connected to the water leg 182 of the separator unit 160 via a line L15. The third form of embodiment of the rocket propulsion system 300 can also be operated or utilised in an optimum manner with the aid of a large number of processes or sequences controlled by the controller and / or regulator. Thus, for example, liquid hydrogen peroxide H2O2 from the second tank 106 can first be converted into gaseous hydrogen peroxide H2O2 by means of the gas generator 14 0, and then converted into electricity by means of the turbine 140 and the electric generator 150. The gaseous hydrogen peroxide exiting from the turbine 150 via the line L2 is split into oxygen O2 and water H2O using the separator unit 160. The oxygen O2 and the liquid and / or vaporous water H2O can then be stored for longer periods in an oxygen storage unit 340 and in a water storage unit 342 for further use. The water H2O exiting from the separator unit 160 is decomposed by means of the electrolysis unit 302 into hydrogen H2 and oxygen O2; these are permanently stored separately from one another, in a first high-pressure storage unit 320 for H2, and in a second high-pressure storage unit 322 for O2, for any future use. Possible uses of the hydrogen H2 and oxygen O2 stored under high-pressure in the high-pressure accumulators 320, 322 include, for example, injection into the main nozzle 124 of the main engine 120, supplying the position control thruster 170, and supplying the defensive unit 330 in the form of a light gas canister, or the high-energy unit 332 (for subsidiary or auxiliary drives). Needless to say, a large number of other methods or processes are possible, in each case under the control of the electronic controller and / or regulator (not shown), for purposes of operating the rocket propulsion system 300 in accordance with the third form of embodiment of Fig. 3. Fig. 4 illustrates a schematic flow diagram of a fourth form of embodiment of a rocket propulsion system. This form of embodiment of a rocket propulsion system 400 comprises an electrolysis unit (402), which in the present case comprises a proton-conducting solid oxide electrolysis cell. In comparison to the form of embodiment shown in Figure 3, the separator unit 160 is thus omitted, and the exhaust gas from the turbine 150 can be supplied directly to the electrolysis unit 402. In this form of embodiment, the oxidiser leg 180' carries not only oxygen but also water vapour, and the water vapour leg 182 ' becomes a conversion leg which, like the oxidiser leg 180', contains a water vapour / oxygen mixture, except that the supply is directly to the electrolysis unit 402. The optional water unit 342' and oxygen storage unit 340' can be accommodated together on the oxidiser leg 180'. The invention relates to a rocket propulsion system comprising a first tank and a second tank, wherein the first tank is filled with a fuel, and the second tank is filled with an oxidiser, such as liquid hydrogen peroxide, for purposes of supplying at least one preferably repeatedly ignitable main engine of the rocket propulsion system. A gas generator is associated with the rocket propulsion system; this is designed to generate vaporous hydrogen peroxide. After flowing through at least one turbine, the hydrogen peroxide can, at least partially, be supplied to a separator unit, which is designed to break down vaporous hydrogen peroxide into water vapour and gaseous oxygen. 5 Alternatively, or additionally, the hydrogen peroxide can be supplied to an electrolysis unit, which is designed to generate gaseous oxygen and gaseous hydrogen from the hydrogen peroxide supplied to it, and / or from water vapour that is located downstream. By this means, the rocket 10 propulsion system, including all its subsidiary systems, can be operated with hydrogen peroxide H2O2 as an environmentally compatible oxidiser in conjunction with a liquid, storable fuel that is also as low in toxicity as possible. 15 The invention also relates to a method for the operation of the rocket propulsion system, and to a space vehicle. List of reference symbols 100 102 Rocket propulsion system (1st variant) First tank 5 104 Fuel 106 Second tank 108 Oxidiser 110 Hydrogen peroxide 120 Main engine 10 122 Combustion chamber (main engine) 124 Main nozzle (main engine, nozzle skirt) 126 First main supply line (oxidiser) 128 Second main supply line (fuel) 130 Branch line 15 136 Space vehicle 140 Gas generator 150 Turbine 152 Electric generator 154 Bypass branch (turbine) 20 160 Separator unit 170 Position control thruster 180, 180' Oxidiser leg (separator unit) 182 , 182' Water vapour leg (separator unit) 184 White arrow 25 186 White arrow 200 Rocket propulsion system (2nd variant) 202 Vessel (inert gas) 210 Inert gas 300 Rocket propulsion system (3rd variant) 30 302 Electrolysis unit (high pressure / high temperature) 310 (High-energy) hydrogen leg 312 (High-energy) oxygen leg 320 First high-pressure accumulator (hydrogen) 35 322 Second high-pressure accumulator (oxygen) 330 Defensive unit 332 High-energy unit 340, 340' Oxygen storage unit 342 , 342 ' Water storage unit 400 Rocket propulsion system (4th variant) 402 Electrolysis unit Li Line (turbine) l2 Line (turbine) l3 Line (position control thruster) l4 Line (pressurisation of first tank) l5 Line (pressurisation of second tank) l6 Line (pressurisation of first tank) l7 Line    (connection   to   first   high-pressure accumulator) l8 Line (main nozzle) l9 Line (main nozzle) Lio Line (position control thruster) Ln Line (position control thruster) L12 Line (defensive / high-energy unit) L13 Line (defensive / high-energy unit) L14 Line (oxygen storage unit) L15 Line (water storage unit) Pl Fuel pump p2 Oxidiser pump

Claims

PATENT CLAIMS1. Rocket propulsion system (100,   200,   300,   400)comprising a first tank (102) and a second tank (106), whereinthe first tank (102) is filled with a fuel (104), and the second tank (106) is filled with an oxidiser (108), such as liquid hydrogen peroxide (110), for purposes of supplying at least one preferably repeatedly ignitable main engine (120) of the rocket propulsion system (100, 200, 300, 400), whereinthe rocket propulsion system (100, 200, 300, 400) is assigned a gas generator (140), which is designed to generate vaporous hydrogen peroxide, which, after flowing through at least one turbine (150)- can, at least partially, be supplied to a separator unit (160), which is designed to separate vaporous hydrogen peroxide into water vapour and gaseous oxygen, and / or- can, at least partially, be supplied to an electrolysis unit (302, 402), which is designed to generate gaseous oxygen and gaseous hydrogen from hydrogen peroxide supplied to it, and / or from water vapour that is located downstream.2 . Rocket propulsion system (100) in accordance with Claim 1, wherein the gas generator (140) can be used to supply at least one position control thruster (170) with vaporous hydrogen peroxide.

3. Rocket propulsion system (100) in accordance with Claims 1 or 2, wherein an electrical generator (152), and / or at least one fuel pump (Pi) , and / or an oxidiser pump (P2) , can be driven by means of the at least one turbine (150) .

4. Rocket propulsion system (100) in accordance with Claims 1,  2 or 3, in which the vaporous hydrogenperoxide can at least partially be supplied to a separator unit (160) after flowing through the at least one turbine (150), wherein the first tank (102) can be pressurised by means of a water vapour leg (182) of the separator unit (160), and the second tank (106) can be pressurised by means of an oxidiser leg (180) of the separator unit (160).

5. Rocket propulsion system (200) in accordance with Claim 4, wherein the rocket propulsion system (200) has at least one vessel (202) with an inert gas (210) for at least supplementary pressurisation of the first and / or second tank (102, 106).

6. Rocket propulsion system (300) in accordance with Claims 1,  2 or 3, in which the vaporous hydrogenperoxide can, at least partially, be supplied to a separator unit (160) after flowing through the at least one turbine (150), wherein the second tank (106) can be pressurised by means of an oxygen leg (180) of the separator unit (160), and an electrolysis unit (302) is connected to the separator unit (160) by means of a water vapour leg (182), and the electrolysis unit (302) has a high-energy hydrogen and oxygen leg (310, 312) .

7. Rocket propulsion system (300) in accordance with Claim 6, wherein an oxygen storage unit (340) is assigned to the oxidiser leg (180) of the separator unit (160), and a water storage unit (342) is assigned to the water vapour leg (182) of the separator unit (160) .

8. Rocket propulsion system (400) in accordance with one of the preceding claims, in which the vaporous hydrogen peroxide can, at least partially, be supplied to anelectrolysis unit (302, 402) after flowing through the at least one turbine (150), whereinthe rocket propulsion system has a working gas leg for a working gas mixture exiting from the turbine, whereinthe working gas leg comprises a conversion leg (182') for purposes of supplying the working gas mixture to the electrolysis unit (402), and an oxidiser leg (180') for purposes of pressurising the second tank (106), and whereinthe electrolysis unit (402) has a high-energy hydrogen and oxygen leg (310, 312).

9. Rocket propulsion system (300) in accordance with one of the Claims 6 to 8, wherein a first high-pressure accumulator (320) is assigned to the high-energy hydrogen leg (310), and a second high-pressure accumulator (322) is assigned to the high-energy oxygen leg (312) .

10. Rocket propulsion system (300) in accordance with one of the Claims 6 to 9, wherein the first tank (102) can be pressurised by means of the high-energy hydrogen leg (310) .

11. Rocket propulsion system (300) in accordance with one of the Claims 6 to 10, wherein a main nozzle (124) of the main engine (120) can be charged with hydrogen by means of the first high-pressure accumulator (320), and can be charged with oxygen by means of the second high-pressure accumulator (322) .

12. Rocket propulsion system (300, 400) in accordance with one of the Claims 6 to 11, wherein the at least one position control thruster (170), at least one defensiveunit (330), and / or a high-energy unit (332), can be supplied by means of the first and second high-pressure accumulators (320, 322) .

13. Rocket propulsion system in accordance with one of the preceding claims, which has an engine cycle in which the rocket propulsion system is to be operated with the fuel leg switched off - in a monopropellant mode, and / or- with the main propulsion system switched off, for purposes of operating a position control system, for purposes of pressurising the first and / or second tank, and / or for purposes of providing a working gas for at least one external system.

14. Method for the operation of a rocket propulsion system (100, 200, 300, 400) in accordance with one of the Claims 1 to 13, wherein, the fuel (104) is supplied to the main engine (120) via a first main supply line (126), and the liquid hydrogen peroxide is, at least partially, tapped from a second main supply line (128) of the main engine (12 0) and supplied to the gas generator (140).

15. Method in accordance with Claim 14, wherein in that, the vaporous hydrogen peroxide exiting from the gas generator (140) is, at least partially, supplied to the turbine (150).

16. Space vehicle (136), wherein this is equipped with at least one rocket propulsion system (100, 200, 300, 400) in accordance with one of the Claims 1 to 13.

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