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

[0001] Rocket propulsion, processes and spacecraft

[0002] Description

[0003] The invention relates primarily to a rocket engine 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 oxidizer, such as liquid hydrogen peroxide, for feeding at least one preferably repeatedly ignitable main engine of the rocket engine. Furthermore, the invention relates to a method for operating such a rocket engine and a spacecraft with such a rocket engine.

[0004] Remote sensing or reuse are major challenges for autonomous propulsion systems of rockets and spacecraft. For long-duration missions, cryogenic spacecraft are not always the first choice, as great efforts are required to keep the cryogenic liquids liquid (the so-called "boil-off" problem) in order to ensure a relatively high density and thus small propellant containers. Conventional, storable propellants are known from the state of the art for remote sensing or long operation times in orbit (satellites). Toxic propellants such as NTO (dinitrogen tetroxide) or MMH (monomethylhydrazine) are often used for rocket stages or satellites. These propellants have the

[0005] One disadvantage is that, due to national regulations, they are no longer environmentally compliant. There are also disadvantages in the remote sensing of the Moon and near-Earth planets, such as Mars, when reusable or return systems are considered. For such reusable or return systems, the ability to produce the propellant and working gases required for the return flight on site is of key importance. However, NTO and MMH, as representatives of these conventional propellant types, can only be synthesized on Mars or the Moon to a limited extent and with great effort, or not at all. Even traditional high-performance, high-pressure gases such as helium are only accessible there under difficult conditions and are already becoming increasingly scarce on Earth.The object of the invention is, among other things, to provide an autogenous rocket engine that operates with environmentally friendly propellants and utilizes the special properties of hydrogen peroxide for additional rocket propulsion functions. A further object of the invention is to provide a method for operating such a rocket engine and a spacecraft equipped with such a rocket engine.

[0006] The object is achieved by a rocket propulsion system according to claim 1, a method according to claim 13 and a spacecraft according to claim 16. Advantageous embodiments are disclosed in the subclaims, the description and the figures.

[0007] The problem is initially solved by assigning a gas generator to the rocket engine, which is designed to generate vaporous hydrogen peroxide, which is fed entirely or partially to at least one turbine. After flowing through the turbine, the flowing hydrogen peroxide can be fed at least partially to a separator unit, which is designed to decompose vaporous hydrogen peroxide into water vapor and gaseous oxygen, and / or the flowing hydrogen peroxide can be fed to an electrolysis unit, by means of which gaseous oxygen and gaseous hydrogen are produced from the vaporous hydrogen peroxide or from the water vapor stored downstream of it.

[0008] This allows the rocket engine to be operated with environmentally friendly propellants that can be synthesized with relatively little effort, even under difficult environmental conditions, such as those found on the moon or near-Earth planets like Mars. Furthermore, the reusability of spacecraft, rocket stages, satellites, or the like equipped with the rocket engine according to the invention is ensured due to the non-toxic oxidizer. This also allows for the creation of 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 in the separator unit into water vapor or water and oxygen, and / or directly or further in the electrolysis unit into oxygen and hydrogen.The separator unit downstream of the gas generator can separate the working gas mixture electrothermally or fluidically-dynamically using centrifugal force. Utilizing these decomposition products of hydrogen peroxide enables optimized operation of the autogenous rocket engine and its subsystems. For example, the tanks can be pressurized with oxygen and / or steam, making a conventional inert gas system for tank pressurization entirely or at least partially unnecessary. The tank pressurization ensures reliable, repeated ignition of the main engine.

[0009] In an advantageous embodiment, at least one attitude control engine can be supplied with vaporous hydrogen peroxide by means of the gas generator. This eliminates the need for a separate supply to the attitude control engines. The turbine can have a bypass branch or "bypass," which is designed, among other things, to influence the volume flow of gaseous hydrogen peroxide flowing through the turbine, i.e., in particular, to increase or decrease it.

[0010] Preferably, an electric generator and / or at least one fuel pump and / or an oxidizer pump can be driven by means of the at least one turbine. As a result, an electric generator is available which can be used, for example, to supply the rocket engine and its subsystems and / or the entire spacecraft with electrical energy. By means of the electric generator, for example, an optional electrolysis unit can also be supplied with the necessary electrical energy. In the case of a fluidic-dynamic mode of operation of the separator unit, the turbine can also directly drive the separator unit in a mechanically rotating manner, whereas in a thermal mode of operation the current generated by the electric generator is necessary to operate the separator unit. Furthermore, it is possible to drive a fuel and / or oxidizer pump electrically or directly in a mechanically rotating manner by means of the turbine.

[0011] In a favorable embodiment, the first tank can be pressurized by means of a steam line of the separator unit, and the second tank can be pressurized by means of an oxidizer line of the separator unit. This allows the tanks to be easily pressurized with decomposition products of the hydrogen peroxide, i.e., the oxidizer already present. In the context of this description, the term "line" defines a pipeline or multiple pipelines, the arrangement of which, in the case of multiple lines, can resemble the topology of a cable or line harness, with each line or line carrying the same chemical substances such as H2, O2, H2O2, fuel, etc., and these can be present in different aggregate states.

[0012] Embodiments are advantageous in which the rocket engine has at least one container with an inert gas for at least supplementary pressurization of the first and / or second tank, as a result of which pressurization of the tanks is possible independently of the decomposition products of the hydrogen peroxide.

[0013] According to advantageous embodiments, the second tank can be pressurized by means of an oxidizer line of the separator unit, an electrolysis unit is connected to the separator unit via a steam line, and the electrolysis unit has a high-energy hydrogen and oxygen line. Due to the electrolysis unit, which preferably operates at high temperatures and high pressures, it is also possible to extract hydrogen and oxygen from the water or steam separated by the separator unit. The hydrogen and oxygen can be used, for example, to supply an attitude control engine, which can thereby generate significantly higher thrust or specific impulse compared to supplying it with hydrogen peroxide.According to advantageous embodiments, a rocket engine according to the invention, in the variant in which the vaporous hydrogen peroxide can be fed at least partially to an electrolysis unit after flowing through the at least one turbine, has at least one working gas line for a working gas mixture exiting the turbine, i.e., for mixed portions of water vapor and oxygen. The working gas line then preferably comprises, on the one hand, a

[0014] Oxidizer line for pressurizing the second tank. Secondly, in such embodiments, the working gas line preferably comprises a conversion line, in which the working gas mixture can be fed to the electrolysis unit for its operation. The electrolysis unit preferably has a high-energy hydrogen and oxygen line. Due to the electrolysis unit, which preferably operates in high-temperature and high-pressure mode, it is also possible to extract hydrogen and oxygen from the working gas in the conversion line from the existing water vapor-oxygen mixture. The hydrogen and oxygen can be used, for example, to supply an attitude control engine, which can thereby generate significantly higher thrust or specific impulse compared to feeding it with hydrogen peroxide.

[0015] Preferably, a first high-pressure accumulator is assigned to the high-energy hydrogen line, and a second high-pressure accumulator is assigned to the high-energy oxygen line. Consequently, a buffer or storage effect is realized in the hydrogen and oxygen lines.

[0016] Preferably, the first tank can be pressurized using the high-energy hydrogen stream. This eliminates the need for a separate pressurization with an inert gas, which would otherwise be necessary.

[0017] In a favorable further development, it is provided that a main nozzle of the main engine can be supplied with hydrogen via the first high-pressure accumulator and with oxygen via the second high-pressure accumulator. This allows, for example, an increase in the thrust of the main engine, thrust vector control of the main engine to change the flight path, etc.

[0018] Preferably, the first and second high-pressure accumulators can be used to supply at least one attitude control engine, at least one defense unit, and / or a high-energy unit / high-pressure unit. This can, among other things, increase the performance of the attitude control engines compared to supplying them with pure hydrogen peroxide. In addition, a defense unit, such as a recoilless light gas weapon or other high-energy units, can be supplied. The defense unit can also be a net harpoon or a similar device for capturing, for example, out-of-control satellites before they risk colliding with other objects in orbit. The high-pressure unit can be an interface to an inflatable structure, such as a habitat.

[0019] Preferably, an oxygen storage unit is assigned to the oxidizer line of the separator unit, and a water storage unit is assigned to the water vapor line of the separator unit. Consequently, a storage unit is available for supplying a life support system of the spacecraft with water and oxygen.

[0020] The object mentioned at the outset is further achieved by a method for operating the rocket propulsion system according to patent claim 12, according to which the fuel is fed to the main engine via a first main feed line and the liquid hydrogen peroxide is at least partially tapped from a second main feed line of the main engine and fed to the gas generator. As a result, if necessary, only a relatively small portion of the liquid hydrogen peroxide can be fed to the gas generator, while the remaining (major) portion of the liquid hydrogen peroxide, after cooling the main nozzle and combustion chamber of the main engine, is used to generate thrust. The distribution of the liquid hydrogen peroxide fed via the second main feed line between the main engine and the gas generator for the catalytic conversion of the liquid into gas orVaporous hydrogen peroxide can be distributed, for example, using an adjustable distributor (so-called "divider") or an adjustable three-way valve with appropriate hydraulic connections or the like. If the main engine operates with fuel cooling, a first portion of the hydrogen peroxide is fed directly to the main engine, while the remaining second portion is returned to the main engine's combustion chamber after passing through the turbine. The ratio of the distribution between the first and second portions depends on the needs of the rocket engine subsystems for pressurizing the tanks and energy conversion.

[0021] According to a further development of the method, the vaporous hydrogen peroxide emerging from the gas generator is at least partially fed to the turbine. This enables, among other things, turbine power control. The portion of the vaporous hydrogen peroxide not fed to the turbine can be fed to the combustion chamber of the main engine via a suitable distribution unit. In principle, depending on the rocket engine's application scenario, only a portion of the hydrogen peroxide is ever fed to the turbine. To achieve the greatest possible specific power, as much hydrogen peroxide as possible should be fed to the main engine or, after passing through the turbine, returned to it via a suitable return line (not shown in the drawings). This ratio can vary depending on the application scenario.The pure pressurization requirement of the tanks can be lower than the required power of the sub- or auxiliary systems and thus the requirement for the oxidizer or hydrogen peroxide branched or tapped from the main feed line of the main engine. In this case, the highest possible proportion of the oxidizer should always be used directly to feed the main engine or remain in the so-called main cycle in order to primarily achieve thrust and impulse power. A rocket engine according to the invention can preferably have an engine cycle with which it can be operated in a mono-propellant mode when the fuel train is switched off and inactive. This can achieve improved throttleability in the main engine. Alternatively or additionally, the rocket system can have an engine cycle with which the rocket engine can be used to operate (if necessary) the main engine when the main engine is switched off.only) of the attitude control system, to pressurize the propellant tanks, and / or (with a suitably developed interface) to provide working gas for external systems such as a space station or habitat (e.g., inflatable structures). Such a propulsion cycle can be implemented using suitable subsystems and / or interfaces.

[0022] Furthermore, the object mentioned above is achieved by a spacecraft according to the invention, which is equipped with at least one rocket propulsion system according to the invention (in particular one of the aforementioned embodiments). Consequently, the optimized, autogenous rocket propulsion system can be used for a spacecraft.

[0023] The invention is explained in more detail in the following description using exemplary embodiments shown in the figures. In the figures, the same structural elements have the same reference numerals. Dashed lines symbolize optional lines or components.

[0024] Figure 1 is a schematic diagram of a first embodiment of a rocket engine,

[0025] Figure 2 is a schematic diagram of a second embodiment of a rocket engine,

[0026] Figure 3 is a schematic diagram of a third embodiment of a rocket engine, and

[0027] Figure 4 is a schematic diagram of a fourth embodiment of a rocket engine.

[0028] Figure 1 illustrates a schematic circuit diagram of a first embodiment of a rocket propulsion system. A rocket propulsion system 100 includes, among other things, a first tank 102 for a fuel 104 and a second tank 106 for an oxidizer 108, which is preferably hydrogen peroxide 110. The fuel 104 is any liquid and storable fuel, such as kerosene, which, like the hydrogen peroxide 110 used as the oxidizer 108, also has the lowest possible toxicity.

[0029] The fuel 104 can be fed to a combustion chamber 122 of at least one main engine 120 by means of a fuel pump P1 via a main feed line 126. Accordingly, the oxidizer 108, or here preferably the hydrogen peroxide 110, can also be fed to the combustion chamber 122 by means of an oxidizer pump P2 and a second main feed line 128 after passing through the main nozzle 124. In the combustion chamber 122 of the main engine 120, after the fuel 104 and the oxidizer 108 are thoroughly mixed, they are combusted to generate thrust.

[0030] A gas generator 140 is connected to the second main feed line 128 by means of a branch line 130. The volume flow of liquid hydrogen peroxide supplied to the gas generator 140 via the branch line 130 can be varied by means of an adjustable distributor (not shown in the figures for the sake of clarity). The gas generator 140 is designed to generate vaporous hydrogen peroxide, preferably by catalytic means, which can be fed to a turbine 150 or a turbomachine via a line L1. After flowing through the turbine 150, the hydrogen peroxide reaches a separator unit 160 via a further line L2.

[0031] The lines L 1,2are connected by a bypass branch 154 to create a bypass for the turbine 150, whereby the volume flow of hydrogen peroxide passing through the turbine 150 can be adjusted by means of valves, etc. (not shown). Connected to the optional bypass branch 154 here, merely as an example, is a likewise optional line L3, which is intended to supply a thruster 170 with vaporous hydrogen peroxide. Valves (not shown) are also provided in the line L3 to enable differentiated control of the thrust or specific impulse of the thruster 170.

[0032] The vaporous hydrogen peroxide flowing into the separator unit 160 via line L2 or the optional bypass branch 154 from the gas generator 140 is split into oxygen O2 and water or water vapor H2O, which is illustrated graphically by the two dotted marking circles and the chemical designations O2 and H2O entered therein. The two dotted marking circles serve merely to illustrate the fact that within a pipe- or line-like oxidizer line 180 and a water vapor line 182, each of which is connected to the separator unit 160, the aforementioned substances (O2, vapor or gaseous H2O) can be diverted from the separator unit 160 toward the two tanks 102, 106 to pressurize them.

[0033] The first tank 102 containing the fuel 104 can be pressurized with the separated water vapor by means of the water vapor line 182 connected to the separator unit 160, and the second tank 106 containing the liquid hydrogen peroxide 110 can be pressurized with the separated gaseous oxygen by means of an oxidizer line 180 connected to the separator unit 160, as illustrated by the two white arrows 184, 186.

[0034] The turbine 150 can drive an optional electric generator 152 (shown in dashed lines) to generate electrical energy. The fuel pump P1 and the oxidizer pump P2 can be directly driven by the turbine 150 or, if an electric generator is available,

[0035] Generator 152 may be electrically driven by means of electric motors not shown.

[0036] 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 fluidically-dynamically using centrifugal force. In the case of the electrothermal mode of operation of the separator unit 160, the electrical energy generated by the generator 152 is used for its operation. However, if the splitting of the hydrogen peroxide into oxygen and water or water vapor is based on the fluidic-dynamic principle utilizing centrifugal force, the separator unit 160 can be driven directly by the turbine 150 in a mechanically rotating manner.

[0037] Hydrogen peroxide 110, used here as the oxidizer of the rocket engine 100, is largely environmentally friendly, non-toxic, and also comparatively easy to synthesize even under difficult environmental conditions such as those found on the moon and near-Earth planets like Mars. In conjunction with a storable, liquid fuel 104 having similar properties, a spacecraft 136 equipped with the rocket engine 100 can, under certain circumstances, also be reused or returned to Earth. Furthermore, the splitting of hydrogen peroxide 110 within the rocket engine 100 by means of the separator unit 160 into oxygen O2 and vaporous water vapor H2O simultaneously allows the first and second tanks 102, 106 to be pressurized. Therefore, in the first embodiment of Fig. 1, no additional tank containing an inert gas such as helium, etc., is required to pressurize the tanks 102, 106.The spacecraft 136 may be, for example, a rocket, a satellite, a space capsule, a space station, or the like.

[0038] Furthermore, if necessary, valves or actuators (not shown for the sake of clarity) can be provided in all lines or tubular strands of the rocket propulsion system 100, which can be controlled by an electronic control and / or regulating device (also not shown) of the rocket propulsion system 100 and / or the spacecraft 136. The same applies to connection nodes between two or more lines or connection nodes formed by (multi-way) valves. The at least one electronic control and / or regulating device is designed to control all sequences or processes within the rocket propulsion system 100. Fig. 2 illustrates a schematic circuit diagram of a second embodiment of a rocket propulsion system.The second embodiment of a rocket engine 200 again comprises the first and second tanks 102, 106, wherein the first tank 102 is filled with the fuel 104 and the second tank 106 is filled with the oxidizer 108 in the form of liquid hydrogen peroxide 110. The fuel 104 can be fed directly to the combustion chamber 122 of the main engine 120 by means of the fuel pump P1 via the first main feed line 126. Accordingly, the oxidizer 108 can be fed to the combustion chamber 122 by means of the oxidizer pump P2 via the second main feed line 128, wherein the oxidizer 108 or the hydrogen peroxide 110 cools the combustion chamber 122 and the main nozzle 124 before entering it. Within the combustion chamber 122, the fuel 104 and the gaseous oxidizer 108 are thoroughly mixed and burned to generate pulses.

[0039] By means of the branch line 130 connected to the second main feed line 128, an adjustable portion of the liquid hydrogen peroxide 110 can be transferred into the gas generator 140 in order to catalytically generate gaseous hydrogen peroxide. The gaseous hydrogen peroxide 110 is supplied via the lines L 1,2The gas can be supplied to and removed from the turbine 150 and then flows into the separator unit 160. The gaseous hydrogen peroxide generated by the gas generator 140 can be partially or completely bypassed by the turbine 150 ("bypass") with the aid of the bypass branch 154 and thus at least partially fed directly into the separator unit 160. With the aid of the bypass branch 154 and the line L3, the attitude control engine 170 can also be supplied with gaseous hydrogen peroxide if necessary. The oxidizer line 180 and the steam line 182, which serve to pressurize the fuel 104 stored in the tanks 102, 106 and the oxidizer 108, are connected to the separator unit 160. The optional electric generator 152 can be driven by means of the turbine 150 to generate electrical energy.

[0040] As a key difference from the first embodiment, the second embodiment of the rocket engine 200 has a container 202 filled with an inert gas 210, such as helium, neon, argon, etc. The first tank 102 can be pressurized or charged with the inert gas 210 via a line L4 connected to the water vapor line 182. Furthermore, the second tank 106 can also be charged with the inert gas 210 via an optional line L5. The second line L5 can branch off from the line L4, as illustrated in Figure 2, or can be connected directly to the container 202 independently of the latter (not shown).

[0041] The advantage of the second embodiment of the rocket engine 200 can be seen, among other things, in the fact that, in addition to the possibility of pressurizing the tanks 102, 106 with the fission products (O2, H2O) of the hydrogen peroxide, i.e., one of the fuel components of the rocket engine 200, there is the possibility of at least supplementing the pressurization of at least one of the tanks 102, 106 with the inert gas 210 from the container 202. The pressurization of the tanks 102, 106 again occurs in the direction of the arrows 184, 186.

[0042] According to a method for operating the rocket propulsion system 200, the fuel 104 is supplied to the main engine 120 via the first main feed line 126, and the liquid hydrogen peroxide from the second main feed line 128 of the main engine 120 is at least partially tapped or branched off and supplied to the gas generator 140. As a result, the mechanical power of the turbine 150 can be varied within wide limits under the control of the control and / or regulating device. According to the method, the vaporous hydrogen peroxide emerging from the catalytic gas generator 140 can be at least partially bypassed by the turbine 150 with the aid of the bypass branch 154 and / or supplied to the attitude control engine 170, which occurs under the permanent control of the control and / or regulating device.This means that the gaseous hydrogen peroxide exiting the gas generator 140—except for the amounts supplied to the attitude control engine 170—passes entirely via the turbine 150 and / or the bypass branch 154 into the separator unit 160. Figure 3 illustrates a schematic circuit diagram of a third embodiment of a rocket engine. This embodiment of a rocket engine 300 again comprises the two tanks 102, 106, which are at least partially filled with the fuel 104 and the oxidizer 108 in the form of hydrogen peroxide 110. The fuel 104 can be fed into the combustion chamber 122 of the main engine 120 by means of the fuel pump P1 via the first main feed line 126 and the oxidizer 108 can be fed into the combustion chamber 122 of the main engine 120 by means of the oxidizer pump P2 via the second main feed line 128, wherein the cooling of the main nozzle 124 or the nozzle extension and the combustion chamber 122 takes place by means of the oxidizer 108 or the hydrogen peroxide 110.

[0043] The gas generator 140 is again connected to the second main feed line 128 via the branch line 130. The turbine 150 can be supplied with gaseous hydrogen peroxide from the gas generator 140 via the line L1, which, after passing through the turbine 150, can be discharged into the separator unit 160 via the line L2. In contrast to the first two embodiments, the optional bypass branch 154 ("bypass") of the turbine 150 as shown in Figs. 1 and 2 is omitted here. The electrical generator 152 (shown with a solid line) which is mandatory here can be driven by the turbine 150 to generate electrical energy. The displacement control engine 170 can be supplied, among other things, via the line L3. Any desired volume flow distribution can be provided between the line L1 and the line L3 using a valve (not shown).The oxidizer 108 in the second tank 106, in the form of liquid hydrogen peroxide 110, can be pressurized, analogously to the embodiments of Figs. 1 and 2, with the aid of the oxygen line 180 extending from the separator unit 160, as indicated by the white arrow 186. The dotted circles in the oxidizer and water vapor lines 180 and 182 of the separator unit 160, analogously to Figs. 1 and 2, serve merely to illustrate the chemical compounds flowing in these lines (O2, vaporous or gaseous H2O). The rocket engine 300 is again integrated into the spacecraft 136. As a significant difference to the two embodiments of Fig. 1, 2, the third embodiment has, among other things, 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 oxygen-ion-conducting solid oxide electrolysis cell, is connected to the separator unit 160 by means of the water vapor line 182. The electrolysis unit 302 can be supplied with the electrical energy required for operation, for example, by means of the electrical generator 152 driven by the turbine 150 or by an external additional 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 discharging the reaction products H2 and O2 produced by the electrolysis from the supplied water. The two dotted circles with the chemical designations H2 and O2 contained therein serve again only to illustrate the substances discharged from the electrolysis cell 302 in the strands 310, 312 which are under high pressure and / or high temperature.The oxygen line 312 of the electrolysis cell 302 is coupled to the oxidizer line 180 of the separator unit 160. As a further difference, in the third embodiment, a first high-pressure reservoir 320 is connected to the hydrogen line 310 for storing the hydrogen H2 supplied by the electrolysis cell 302. A further line L6 branches off from the hydrogen line 310, by means of which line the fuel 104 stored in the first tank 102 can also be pressurized in the direction of the white arrow 184, so that both tanks 102, 106 are permanently pressurized and reliable repeated ignition of the main engine 120 is ensured if necessary. The oxygen line 312 of the electrolysis unit 302 is further connected by means of a line L7 to a second high-pressure reservoir 322 for receiving the oxygen O2 supplied by the electrolysis unit 302.

[0044] The two high-pressure accumulators 320, 322 further permit the operation of a number of exemplary subsystems or auxiliary systems of the rocket engine 300, briefly explained below. For example, a further line L8 is connected to the first high-pressure accumulator 320 for hydrogen H2, which is connected to the main nozzle 124 of the main engine 120. Accordingly, a further line L9 leads from the second high-pressure accumulator 322 for oxygen O2 to the main nozzle 124 of the main engine 120. This allows, if necessary, for example, a specific impulse increase of the main engine 120, a complex thrust vector control of the main engine 120 to change the trajectory of the spacecraft 136, or the like, which is not possible with the first two embodiments of the rocket engine according to Figs. 1, 2.

[0045] Furthermore, two lines L 10,11from the two high-pressure accumulators 320, 322 to the attitude control engine 170, so that the latter can be operated with high-energy oxygen O2 and hydrogen H2. This, in comparison to the supply with gaseous hydrogen peroxide via line L3 from the gas generator 140 - as provided in the embodiments of Fig. 1, 2 - allows the generation of significantly higher specific impulses by means of the attitude control engine 170.

[0046] Furthermore, in contrast to the embodiments according to Figs. 1, 2, a defense unit 330 and / or a high-energy unit 332 are provided with the aid of further lines L 12,13connected to the high-pressure accumulators 320, 322. The defense unit 330 can, for example, be a light gas cannon (not shown) with a preferably integrated recoil compensation for accelerating a projectile to an exit velocity of up to 60 km / s. The light gas cannon can be operated using 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) functions as the actual propellant charge instead of black powder, etc. As a result, a considerable weight reduction can be achieved compared to the use of black powder cartridges, while the exit velocity is simultaneously increased.A defined ejection of the accelerating gas H2 simultaneously ensures momentum compensation by means of a suitably positioned counter nozzle, so that the position of the spacecraft 136 remains essentially unchanged.

[0047] In addition, the defense 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 as well as with the power of the electrical generator 152.

[0048] The high-energy unit 332 may also be any other device that also requires high-pressure hydrogen H2 and oxygen O2 for its operation.

[0049] In the area of ​​unmarked connection or connection points (nodes) between the lines L 8, 10 L 9,11 L 10, 12 L 11,13and others, preferably valves (not shown) are provided for flow control and / or distribution of the respective material flows (O2, H2, H2O2, fuel, etc.), which may also be in the liquid and / or gaseous phase. Furthermore, valves can be provided on or in any section of the lines.

[0050] 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 spacecraft 136 can be permanently supplied with oxygen O2 and water H2O for a human crew, for example, on board the spacecraft 136. This makes longer stays in space or, if necessary, trips to the moon and / or near-Earth planets such as Mars possible. For this purpose, the oxygen storage unit 340 is connected to the spacecraft 136 by means of an additional line L 14connected to the oxidizer line 180 of the separator unit 160 and the water storage unit 342 is connected via a line L 15 connected to the water line 182 of the separator unit 160.

[0051] The third embodiment of the rocket propulsion system 300 can also be operated or used advantageously in an optimal manner with the aid of a plurality of methods or sequences controlled by the control and / or regulating device.

[0052] 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 140 and then converted into electricity by means of the turbine 140 and the electric generator 150.

[0053] The gaseous hydrogen peroxide exiting turbine 150 via line L2 is split into oxygen O2 and water H2O by separator unit 160. The oxygen O2 and the liquid and / or vaporous water H2O can then be stored for further use in an oxygen storage unit 340 and a water storage unit 342 for a longer period of time. The water H2O exiting separator unit 160 is split into hydrogen H2 and oxygen O2 by electrolysis unit 302, which are stored separately and permanently in a first high-pressure storage unit 320 for H2 and a second high-pressure storage unit 322 for O2 for any further use.

[0054] Possible uses of the hydrogen H2 and oxygen O2 stored under high pressure in the high-pressure storage units 320, 322 include, for example, injection into the main nozzle 124 of the main engine 120, feeding the attitude control engine 170, and supplying the defense unit 330 in the form of a light gas cannon or the high-energy unit 332 (sub- or auxiliary drives).

[0055] It goes without saying that a multitude of further methods or processes, each under the control of the electronic control and / or regulating device (not shown), are possible for operating the rocket engine 300 in accordance with the third embodiment of Fig. 3.

[0056] Figure 4 illustrates a schematic circuit diagram of a fourth embodiment of a rocket engine. This embodiment of a rocket engine 400 comprises an electrolysis unit (402), which in this case comprises a proton-conducting solid oxide electrolysis cell. Compared to the embodiment shown in Figure 3, the separator unit 160 is omitted, and the exhaust gas from the turbine 150 can be fed directly to the electrolysis unit 402. In this embodiment, the oxidizer line 180' carries not only oxygen but also water vapor, and the water vapor line 182' becomes the conversion line, which, like the oxidizer line 180', contains a water vapor-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 oxidizer line 180'.

[0057] The invention relates to a rocket engine 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 oxidizer, such as liquid hydrogen peroxide, for feeding at least one preferably repeatedly ignitable main engine of the rocket engine. A gas generator designed to generate vaporous hydrogen peroxide is assigned to the rocket engine. After flowing through at least one turbine, the hydrogen peroxide can be fed at least partially to a separator unit designed to decompose vaporous hydrogen peroxide into water vapor and gaseous oxygen. Alternatively or additionally, the hydrogen peroxide can be fed to an electrolysis unit designed to generate gaseous oxygen and gaseous hydrogen from the hydrogen peroxide supplied to it and / or the water vapor downstream of it.

[0058] This allows the rocket engine, including all its subsystems, to be operated with hydrogen peroxide H2O2 as an environmentally friendly oxidizer in conjunction with a liquid, storable fuel that also has the lowest possible toxicity.

[0059] Furthermore, the invention relates to a method for operating the rocket engine and a spacecraft. List of reference symbols

[0060] 100 Rocket Engine (1st Var.)

[0061] 102 first tank

[0062] 104 Fuel

[0063] 106 second tank

[0064] 108 Oxidizer

[0065] 110 Hydrogen peroxide

[0066] 120 main engine

[0067] 122 Combustion chamber (main engine)

[0068] 124 Main nozzle (main engine, nozzle extension)

[0069] 126 first main feed line (oxidizer)

[0070] 128 second main feed line (fuel)

[0071] 130 branch line

[0072] 136 spacecraft

[0073] 140 gas generator

[0074] 150 turbines

[0075] 152 electric generator

[0076] 154 Bridging branch (turbine)

[0077] 160 separator unit

[0078] 170 attitude control engine

[0079] 180, 180' oxidizer strand (separator unit)

[0080] 182, 182' steam train (separator unit)

[0081] 184 white arrow

[0082] 186 white arrow

[0083] 200 Rocket Engine (2nd Var.)

[0084] 202 containers (inert gas)

[0085] 210 Inert gas

[0086] 300 Rocket Engine (3rd Var.)

[0087] 302 Electrolysis unit (high pressure / high temperature)

[0088] 310 (high-energy) hydrogen train

[0089] 312 (high-energy) oxygen strand

[0090] 320 first high-pressure storage (hydrogen)

[0091] 322 second high-pressure storage tank (oxygen)

[0092] 330 Defense Unit

[0093] 332 High Energy Unit 340, 340' Oxygen Storage Unit

[0094] 34:2, 342' water storage unit

[0095] 400 Rocket Engine (4th Var.)

[0096] 402 Electrolysis unit L1 line (turbine)

[0097] L2 line (turbine) L3 line (attitude control engine)

[0098] L4 line (pressurization of first tank) L5 line (pressurization of second tank)

[0099] L6 line (pressurization of first tank)

[0100] L7 line (connection of first high-pressure reservoir)

[0101] L8 line (main jet)

[0102] L9 line (main jet)

[0103] L 10 Line (attitude control engine)

[0104] L 11Line (attitude control engine)

[0105] L 12 Management (Defense / High Energy Unit)

[0106] L 13 Management (Defense / High Energy Unit)

[0107] L 14 Line (oxygen storage unit)

[0108] L 15 Line (water storage unit)

[0109] P1Fuel pump P2Oxidizer pump

Claims

Patent claims 1. Rocket propulsion (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), wherein the first tank (102) is filled with a fuel (104) and the second tank (106) is filled with an oxidizer (108), such as liquid hydrogen peroxide (110), for feeding at least one preferably repeatedly ignitable main engine (120) of the rocket propulsion (100, 200, 300, 400), characterized in that the rocket propulsion (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 be fed at least partially to a separator unit (160) which is designed to to decompose vaporous hydrogen peroxide into water vapor and gaseous oxygen, and / or can be fed at least partially to an electrolysis unit (302, 402) which is designed toto produce gaseous oxygen and gaseous hydrogen from the hydrogen peroxide supplied to it and / or the steam downstream of it.

2. Rocket propulsion (100) according to claim 1, characterized in that at least one attitude control engine (170) can be supplied with vaporous hydrogen peroxide by means of the gas generator (140).

3. Rocket propulsion (100) according to claim 1 or 2, characterized in that an electric generator (152) and / or at least one fuel pump (P1) and / or an oxidizer pump (P2) can be driven by means of the at least one turbine (150).

4. Rocket propulsion (100) according to claim 1, 2 or 3, wherein the vaporous hydrogen peroxide can be fed at least partially to a separator unit (160) after flowing through the at least one turbine (150), characterized in that the first tank (102) can be pressurized by means of a water vapor line (182) of the separator unit (160) and the second tank (106) can be pressurized by means of an oxidizer line (180) of the separator unit (160).

5. Rocket propulsion system (200) according to claim 4, characterized in that the rocket propulsion system (200) comprises at least one container (202) with an inert gas (210) for at least supplementary pressurization of the first and / or second tank (102, 106).

6. Rocket propulsion (300) according to claim 1, 2 or 3, wherein the vaporous hydrogen peroxide can be fed at least partially to a separator unit (160) after flowing through the at least one turbine (150), characterized in that the second tank (106) can be pressurized by means of an oxidizer line (180) of the separator unit (160) and an electrolysis unit (302) is connected to the separator unit (160) by means of a water vapor line (182) and the electrolysis unit (302) has a high-energy hydrogen and oxygen line (310, 312).

7. Rocket propulsion (300) according to claim 6, characterized in that an oxygen storage unit (340) is assigned to the oxidizer line (180) of the separator unit (160) and a water storage unit (342) is assigned to the water vapor line (182) of the separator unit (160).

8. Rocket propulsion (400) according to one of the preceding claims, in which the vaporous hydrogen peroxide can be fed at least partially to an electrolysis unit (302, 402) after flowing through the at least one turbine (150), wherein the rocket propulsion has a working gas line for a working gas mixture emerging from the turbine, wherein the working gas line comprises a conversion line (182') for feeding the working gas mixture to the electrolysis unit (402) and an oxidizer line (180') for pressurizing the second tank (106), and wherein the electrolysis unit (402) has a high-energy hydrogen and oxygen line (310, 312).

9. Rocket propulsion (300) according to one of the claims 6 to 8, characterized in that the high-energy hydrogen train (310) is provided with a first high-pressure accumulator (320) and the high-energy A second high-pressure accumulator (322) is assigned to the oxygen line (312).

10. Rocket propulsion system (300) according to one of claims 6 to 9, characterized in that the first tank (102) can be pressurized by means of the high-energy hydrogen strand (310).

11. Rocket propulsion (300) according to one of claims 6 to 10, characterized in that a main nozzle (124) of the main engine (120) can be supplied with hydrogen by means of the first high-pressure accumulator (320) and with oxygen by means of the second high-pressure accumulator (322).

12. Rocket propulsion system (300, 400) according to one of claims 6 to 11, characterized in that the at least one attitude control engine (170), at least one defense unit (330) and / or a high-energy unit (332) can be supplied by means of the first and the second high-pressure accumulator (320, 322). 13, Rocket engine according to one of the preceding claims, which has an engine cycle in which the rocket engine is to be operated with the fuel train switched off in a mono-propellant mode and / or with the main engine switched off for operating an attitude control system, for pressurizing the first and / or second tank and / or for providing working gas for at least one external system.

14. A method for operating a rocket engine (100, 200, 300, 400) according to one of claims 1 to 13, characterized in that the fuel (104) is supplied to the main engine (120) via a first main feed line (126) and the liquid hydrogen peroxide is at least partially tapped from a second main feed line (128) of the main engine (120) and supplied to the gas generator (140).

15. Method according to claim 14, characterized in that the vaporous hydrogen peroxide emerging from the gas generator (140) is at least partially fed to the turbine (150).

16. Spacecraft (136), characterized in that it is equipped with at least one rocket engine (100, 200, 300, 400) according to one of claims 1 to 13.

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