Rocket propulsion system, method, and spacecraft

Abstract

The present invention relates to a rocket propulsion system (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), the first tank filled with fuel and the second tank filled with an oxidizer, such as liquid hydrogen peroxide, for supplying at least one, preferably repeatable, main engine (120) of the rocket propulsion system. A gas generator (140) is disposed in the rocket propulsion system and is designed to generate hydrogen peroxide vapor. After passing through at least one turbine, the hydrogen peroxide may be supplied, at least in part, to a separation unit (160) designed to decompose the hydrogen peroxide vapor into water vapor and oxygen gas. Alternatively, or additionally, the hydrogen peroxide may be supplied to an electrolysis unit (302, 402) designed to produce oxygen gas and hydrogen gas from the supplied hydrogen peroxide and / or water vapor located downstream. Furthermore, the present invention relates to a rocket propulsion system and a method for operating a spacecraft.

Description

[Technical Field]

[0001] The present invention relates primarily to a rocket propulsion system comprising a first tank and a second tank, the first tank filled with fuel and the second tank filled with an oxidizer, such as liquid hydrogen peroxide, intended to supply at least one, preferably re-ignitable, main engine of the rocket propulsion system. Furthermore, the present invention relates to a method for operating such a rocket propulsion system and to a spacecraft equipped with such a rocket propulsion system. [Background technology]

[0002] Remote sensing or reuse poses significant challenges for autonomous propulsion systems for rockets and spacecraft. For long-duration missions, cryogenic spacecraft are not always the first choice. Maintaining cryogenic liquids in a liquid state (the so-called "boil-off" problem) and achieving a relatively high density, resulting in small propellant tanks, requires significant effort. Traditional storable propellants are a known prior art for remote sensing and long-duration operations in orbit. Toxic propellants such as NTO (nitrogen tetroxide) and MMH (monomethylhydrazine) are often used in rocket stages and satellites. These propellants have the disadvantage of no longer being environmentally compatible with national regulations. Furthermore, considering reusable or recoverable systems, they present a drawback for remote exploration of near-Earth planets such as the Moon or Mars. For such reusable or recoverable systems, the ability to generate the propellants and working gases needed for the return flight on-site is crucial. However, such conventional propellants as NTO and MMH can only be synthesized at great expense or not at all on Mars or the Moon, and conventional high-performance compressed gases such as helium are also only available there under difficult conditions and are already becoming increasingly scarce on Earth. Summary of the Invention [Problem to be solved by the invention]

[0003] One object of the present invention is to identify an autogenous rocket propulsion system that operates on an environmentally compatible propellant and utilizes the properties of hydrogen peroxide for additional functions of the rocket propulsion system. A further object of the present invention is to identify a method for operating such a rocket propulsion system and a spacecraft equipped with such a rocket propulsion system. [Means for solving the problem]

[0004] These objects are 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 dependent claims, the description and the figures.

[0005] One of these objectives is achieved in that the rocket propulsion system is provided with a gas generator designed to generate hydrogen peroxide vapor, which is fed completely or partially to at least one turbine, after which at least a portion of the passing hydrogen peroxide is fed to a separation unit designed to decompose the hydrogen peroxide vapor into water vapor and oxygen gas, and / or the passing hydrogen peroxide is fed to an electrolysis unit, which produces oxygen gas and hydrogen gas from the hydrogen peroxide vapor or the downstream water vapor.

[0006] This method allows rocket propulsion systems to operate under difficult environmental conditions, such as on near-Earth planets like the Moon or Mars, using environmentally friendly propellants that can be synthesized with relatively little effort. Furthermore, the non-toxic oxidizer ensures that spacecraft, rocket stages, satellites, etc. equipped with the rocket propulsion system of the present invention can be reused. This method also makes it possible to realize recoverable and reusable space units. Hydrogen peroxide, initially liquid, is catalytically converted into vaporized hydrogen peroxide, or the so-called "working gas mixture," in a gas generator. This is at least partially decomposed into water vapor, i.e., water and oxygen, in a separation unit, and / or separated into oxygen and hydrogen directly or subsequently in an electrolysis unit. A separation unit located downstream of the gas generator can separate the working gas mixture hydrodynamically, electrothermally, or using centrifugal force. The utilization of these decomposition products of hydrogen peroxide can achieve optimized operation of self-generating rocket propulsion systems and their auxiliary systems. For example, the tank can be pressurized with oxygen and / or water vapor, completely or at least partially obviating the need for conventional inert gas systems for tank pressurization. Tank pressurization allows for reliable and repeatable firing of the main engines.

[0007] In an advantageous configuration, a gas generator can be used to supply the hydrogen peroxide vapor to at least one of the position control thrusters, thereby eliminating the need for a separate supply to the position control thrusters. The turbine can be provided with a bypass branch that is specifically designed to affect, among other tasks, the volumetric flow rate of the hydrogen peroxide vapor through the turbine, i.e., to increase or decrease that flow rate.

[0008] Preferably, the generator and / or at least one fuel pump and / or oxidizer pump are driven by at least one turbine. This results in a generator that can be used, for example, to provide electrical energy for the rocket propulsion system and its auxiliary systems, and / or the entire spacecraft. The generator can also be used, for example, to provide the electrical energy required for an optional electrolysis unit. In the hydrodynamic operation mode of the separation unit, the turbine can also directly drive the separation unit by mechanical rotation. In the thermal operation mode, on the other hand, the separation unit requires electrical power generated by the generator to operate. The turbine can also directly drive the fuel pump and / or oxidizer pump electrically or mechanically.

[0009] In an advantageous configuration, the first tank is pressurizable by the steam leg of the separation unit, and the second tank is configured to be pressurizable by the oxidizer leg of the separation unit. This method facilitates pressurizing the tanks with the decomposition products of hydrogen peroxide, i.e., the products of the oxidizer already present. As used herein, the term "leg" defines a pipeline, or multiple pipelines, and in the case of multiple lines, the arrangement resembles the topology of a cable or line harness, with each leg or line carrying the same chemical, such as H2, O2, H2O2, or fuel, which may exist in different physical states.

[0010] An embodiment in which the rocket propulsion system comprises at least one container with an inert gas for at least auxiliary pressurization of the first and / or second tank is advantageous, so that the tanks can be pressurized independently of the decomposition products of hydrogen peroxide.

[0011] According to an advantageous embodiment, the second tank can be pressurized by the oxidizer leg of the separation unit, and the electrolysis unit is connected to the separation unit by a steam leg, the electrolysis unit having high-energy hydrogen and oxygen legs. The electrolysis unit, which preferably operates at high temperature and pressure, can also extract hydrogen and oxygen from the water or steam separated in the separation unit. The hydrogen and 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 when hydrogen peroxide is supplied.

[0012] According to an advantageous embodiment, the rocket propulsion system according to the invention has at least one working gas leg for the working gas mixture discharged from the turbine, i.e., for the mixture of water vapor and oxygen, in a variant in which hydrogen peroxide vapor is at least partially fed to an electrolysis unit after passing through at least one turbine. This working gas leg preferably includes, on the one hand, an oxidizer leg for pressurizing the second tank. On the other hand, in such an embodiment, the working gas leg preferably also includes a conversion leg in which the working gas mixture is fed to the electrolysis unit for operation. Here, the electrolysis unit preferably includes high-energy hydrogen and oxygen legs. The electrolysis unit, which preferably operates at high temperature and pressure, can also extract hydrogen and oxygen from the existing water vapor / oxygen mixture from the working gas in the conversion leg. This hydrogen and oxygen can be used, for example, to supply a position-controlled thruster, thereby generating a significantly higher thrust or specific impulse than when hydrogen peroxide is fed.

[0013] The first high-pressure accumulator is preferably allocated to the high-energy hydrogen leg, and the second high-pressure accumulator is preferably allocated to the high-energy oxygen leg, so that a buffer or storage action is achieved in the hydrogen leg and the oxygen leg.

[0014] The first tank can be pressurized, preferably using the high energy hydrogen leg, thereby eliminating the need for a separate pressurization with an inert gas that would otherwise be required.

[0015] In an advantageous development, the main nozzle of the main engine can be filled with hydrogen by a first high-pressure accumulator and with oxygen by a second high-pressure accumulator, which makes it possible, for example, to increase the thrust of the main engine or, if necessary, to control the thrust vector of the main engine and thereby change the flight path.

[0016] Preferably, at least one position control thruster, at least one defense unit, and / or high-energy / high-pressure unit can be supplied by first and second high-pressure accumulators. Among other features, this allows for improved performance of the position control thrusters compared to supplying them with pure hydrogen peroxide. Furthermore, defense units such as recoilless light gas weapons or other high-energy units can also be supplied. The defense units can also be net harpoons or similar devices for capturing out-of-control satellites, for example, before they risk collision with other objects in orbit. The high-pressure units can also be in the form of interfaces to expandable structures such as habitats.

[0017] The oxygen storage unit is preferably assigned to the oxidizer leg of the separation unit, and the water storage unit is preferably assigned to the steam leg of the separation unit, so that an accumulator is available to provide water and oxygen to the spacecraft life support systems.

[0018] The above-mentioned object is also achieved by a method for operating a rocket propulsion system as set forth in claim 12, in which fuel is supplied to a main engine via a first main supply line, and liquid hydrogen peroxide is at least partially extracted from a second main supply line of the main engine and supplied to a gas generator. As a result, only a relatively small proportion of the liquid hydrogen peroxide is supplied to the gas generator, while the remaining (most) liquid hydrogen peroxide is used to generate thrust after the main nozzle and the combustion chamber of the main engine are cooled. The liquid hydrogen peroxide supplied via the second main supply line can be divided between the main engine and the gas generator for catalytic conversion of the liquid hydrogen peroxide into gaseous or vaporous hydrogen peroxide, for example, by a controllable distributor (a so-called "divider"), a controllable three-way valve with corresponding hydraulic ports, or the like. When the main engine operates with fuel cooling, a first proportion of the hydrogen peroxide is supplied directly to the main engine, and a second (remaining) proportion is returned to the combustion chamber of the main engine after passing through a turbine. The ratio of the first and second fractions varies depending on the requirements of the rocket propulsion system's auxiliary systems for tank pressurization and energy conversion.

[0019] According to a development of this method, at least a portion of the hydrogen peroxide vapor discharged from the gas generator is supplied to the turbine. This allows, among other features, turbine power control. The portion of the hydrogen peroxide vapor not supplied to the turbine can be supplied to the combustion chamber of the main engine via an appropriate distribution device. In principle, depending on the deployment scenario of the rocket propulsion system, only a portion of the hydrogen peroxide is supplied to the turbine. To achieve the highest possible specific power, as much hydrogen peroxide as possible must be supplied to the main engine or, using an appropriate return line (not shown in the drawings), returned to the main engine after passing through the turbine. This ratio can vary depending on the deployment scenario. The pure pressurization requirements of the tank can be lower than the power output required for the auxiliary systems, thereby lowering the requirements for oxidizer or hydrogen peroxide taken from the main supply line to the main engine. The highest possible proportion of oxidizer should always be used to directly supply the main engine, i.e., remain within the so-called main cycle, primarily for generating thrust and impulse power.

[0020] A rocket propulsion system according to the present invention may preferably have a propulsion cycle capable of operating in a monopropellant mode when the inert fuel legs are turned off, thereby achieving improved throttling capabilities in the main propulsion system. Alternatively, or additionally, the rocket system may have an engine cycle that allows the rocket propulsion system to be used to operate a position control system (possibly only), pressurize fuel tanks, and / or (through appropriately developed interfaces) provide working gas to external systems such as space stations or habitats (e.g., inflatable structures) when the main engine is off. Such engine cycles may be implemented by appropriate auxiliary systems and / or interfaces.

[0021] Furthermore, the above-mentioned other objects are achieved by a spacecraft according to the invention, which comprises at least one rocket propulsion system according to the invention, in particular in one of the forms of the above-mentioned embodiments, so that an optimized self-generating rocket propulsion system can be used for the spacecraft.

[0022] The invention will be explained in more detail in the following description with reference to example embodiments shown in the figures, in which identical design elements are respectively provided with the same reference numerals, and in which dashed lines respectively represent optional lines or components. [Brief explanation of the drawings]

[0023] [Figure 1] 1 shows a schematic flow diagram of a first embodiment of a rocket propulsion system. [Figure 2] 1 shows a schematic flow diagram of a second embodiment of a rocket propulsion system. [Figure 3] 10 shows a schematic flow diagram of a third embodiment of a rocket propulsion system. [Figure 4] 10 shows a schematic flow diagram of a fourth embodiment of a rocket propulsion system. DETAILED DESCRIPTION OF THE INVENTION

[0024] 1 shows a schematic flow diagram of a first embodiment of a rocket propulsion system. The rocket propulsion system 100 comprises, inter alia, a first tank 102 for fuel 104 and a second tank 106 for oxidizer 108, preferably in the form of hydrogen peroxide 110. The fuel 104 is in the form of a liquid, storable fuel such as paraffin, which, like the hydrogen peroxide 110 used as oxidizer 108, is as low in toxicity as possible.

[0025] Fuel 104 may be supplied by a fuel pump P1 via a main supply line 126 to a combustion chamber 122 of at least one main engine 120. Correspondingly, an oxidizer 108, here preferably hydrogen peroxide 110, may also be supplied to the combustion chamber 122 after passing through a main nozzle 124 by an oxidizer pump P2 and a second main supply line 128. After the fuel 104 and the oxidizer 108 are thoroughly mixed in the combustion chamber 122 of the main engine 120, combustion occurs therebetween to generate thrust.

[0026] The gas generator 140 is connected to the second main supply line 128 by a branch line 130. The volumetric flow rate of the liquid hydrogen peroxide supplied to the gas generator 140 by the branch line 130 can be varied by a controllable distributor, which is omitted for clarity. The gas generator 140 is designed to produce, preferably catalytically, gaseous hydrogen peroxide (hydrogen peroxide vapor), which can be supplied to the turbine 150 or another turbomachine by a line L1. After passing through the turbine 150, the hydrogen peroxide reaches the separation unit 160 by another line L2.

[0027] Line L 1,2 are connected by a bypass branch 154, forming a bypass for the turbine 150. This allows the volumetric flow rate of hydrogen peroxide passing through the turbine 150 to be adjusted by a valve or the like (not shown). Here, another optional line L3 is illustratively connected to the optional bypass branch 154. This is used to supply hydrogen peroxide vapor to the position control thrusters 170. A valve (not shown) is also provided in line L3, allowing the thrust or specific impulse of the position control thrusters 170 to be differentially controlled.

[0028] The hydrogen peroxide vapor flowing from the gas generator 140 via line L2 or optional bypass branch 154 to the separation unit 160 is split into oxygen O2 and water or steam H2O in the separation unit 160. This is illustrated by the two dotted circles with the chemical symbols O2 and H2O entered therein. The two dotted circles simply indicate that, inside the oxidizer line 180 and the steam line 182 in the form of pipes or conduits (respectively connected to the separation unit 160), the aforementioned substances (O2, vaporous or gaseous H2O) are discharged from the separation unit 160 in the direction of the two tanks 102, 106, thereby allowing the tanks 102, 106 to be pressurized.

[0029] The first tank 102 containing the fuel 104 can be pressurized with water vapor, preferably separated by a water vapor line 182 connected to the separation unit 160. The second tank 106 containing the liquid hydrogen peroxide 110 can be pressurized with oxygen gas, similarly separated, by an oxidizer line 180 connected to the separation unit 160, as shown by two white arrows 184, 186, respectively.

[0030] Turbine 150 can drive an optional generator 152 (shown in dashed lines) to generate electrical energy. Fuel pump P1 and oxidant pump P2 can be driven directly by turbine 150 or, if generator 152 is present, can be driven electrically using an electric motor (not shown).

[0031] The separation unit 160, located downstream of the gas generator 140, can separate the supplied hydrogen peroxide vapor, i.e., "working gas mixture," electrothermally or hydrodynamically using centrifugal force. When the separation unit 160 operates in electrothermal mode, electrical energy obtained using the generator 152 is used. On the other hand, when the separation of hydrogen peroxide into oxygen and water or water vapor is based on a hydrodynamic operating principle using centrifugal force, the separation unit 160 can be directly driven by mechanical rotation using the turbine 150.

[0032] The hydrogen peroxide 110 used as an oxidizer in the rocket propulsion system 100 is environmentally friendly, non-toxic, and relatively easy to synthesize, even under harsh environmental conditions such as those commonly found on near-Earth planets like the Moon and Mars. When used in conjunction with a storable liquid fuel 104 with similar properties, the spacecraft 136 carrying the rocket propulsion system 100 can be reused or returned to Earth under certain conditions. Furthermore, the hydrogen peroxide 110 in the rocket propulsion system 100 can be separated into oxygen (O) and water vapor (H)O by a separation unit 160, allowing the first tank 102 and the second tank 106 to be simultaneously pressurized. Therefore, in the first embodiment of FIG. 1 , additional tanks filled with an inert gas such as helium are not required to pressurize the tanks 102 and 106. The spacecraft 136 can take the form of, for example, a rocket, a satellite, a space capsule, a space station, or the like.

[0033] Additionally, valves or actuators, not shown for clarity, may be provided in all lines or piping of rocket propulsion system 100 as needed. These may be controlled by electronic controllers or regulators, also not shown, of rocket propulsion system 100 and / or spacecraft 136. The same applies to connection nodes between two or more lines or connection nodes formed by (multi-path) valves, where at least one electronic controller and / or regulator is designed to control all sequences or processes within rocket propulsion system 100.

[0034] 2 shows a schematic flow diagram of a second embodiment of a rocket propulsion system. The second embodiment of the rocket propulsion system 200 again includes first and second tanks 102, 106, with the first tank 102 filled with fuel 104 and the second tank 106 filled with oxidizer 108 in the form of liquid hydrogen peroxide 110. The fuel 104 may be supplied directly to the combustion chamber 122 of the main engine 120 via a first main supply line 126 by a fuel pump P1. Correspondingly, the oxidizer 108 may be supplied to the combustion chamber 122 via a second main supply line 128 by an oxidizer pump P2, whereby the oxidizer 108, i.e., 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 oxidizer 108 are intimately mixed and combusted to generate thrust.

[0035] A branch line 130 connected to the second main supply line 128 can in turn deliver an adjustable rate of liquid hydrogen peroxide 110 to a gas generator 140 for catalytically generating hydrogen peroxide vapor. The hydrogen peroxide vapor 110 is supplied via line L 1,2 The hydrogen peroxide vapor generated in the gas generator 140 is supplied to the turbine 150 by a bypass branch 154, discharged from there, and then enters the separation unit 160. The hydrogen peroxide vapor generated in the gas generator 140 can partially or completely bypass the turbine 150 using a bypass branch 154 and thus be directed at least partially directly to the separation unit 160. The bypass branch 154 and line L3 can also be used to supply the hydrogen peroxide vapor to the position control thruster 170, if desired. An oxidizer line 180 and a steam line 182, which pressurize the fuel 104 and oxidizer 108 stored in the tanks 102, 106, are in turn connected to the separation unit 160. An optional generator 152 can be driven by the turbine 150 to generate electrical energy.

[0036] The primary difference from the first embodiment is that the second embodiment of rocket propulsion system 200 includes a container 202 filled with an inert gas 210, such as helium, neon, or argon. Line L4, connected to steam line 182, allows first tank 102 to be pressurized, i.e., filled with inert gas 210. Additionally, optional line L5 allows second tank 106 to also be filled with inert gas 210. As shown in FIG. 2, second line L5 can branch off from line L4 and be connected directly to container 202 independently of line L4 (not shown).

[0037] One advantage of the second embodiment of rocket propulsion system 200 is that in addition to pressurizing tanks 102, 106 with decomposition products (O, HO) of hydrogen peroxide (i.e., one of the fuel components of rocket propulsion system 200), at least one of tanks 102, 106 can be at least supplementally pressurized with inert gas 210 from container 202. Pressurization of tanks 102, 106 occurs in a stacked manner in the directions of arrows 184, 186.

[0038] According to a method for operating the rocket propulsion system 200, fuel 104 is prepared to be supplied to the main engine 120 via the first main supply line 126, and liquid hydrogen peroxide is at least partially removed (i.e., diverted) from the second main supply line 128 of the main engine 120 and supplied to the gas generator 140. As a result, the mechanical power output of the turbine 150 can be varied within a wide range under the control of a controller and / or regulator. According to this method, the hydrogen peroxide vapor discharged from the catalytic gas generator 140 can at least partially bypass the turbine 150 using the bypass branch 154 and / or be supplied to the position control thruster 170. This is done under permanent control of the controller and / or regulator. This means that the hydrogen peroxide vapor released from the gas generator 140 flows entirely into the separation unit 160 via the turbine 150 and / or the bypass branch 154, except for the amount supplied to the position control thruster 170.

[0039] 3 shows a schematic flow diagram of a third embodiment of a rocket propulsion system. This rocket propulsion system 300 embodiment also includes two tanks 102, 106, which are at least partially filled with fuel 104 and oxidizer 108 in the form of hydrogen peroxide 110. Fuel 104 is supplied to a combustion chamber 122 of a main engine 120 by a fuel pump P1 via a first main supply line 126, and oxidizer 108 is supplied by an oxidizer pump P2 via a second main supply line 128. Cooling of the main nozzle 124 or nozzle skirt and the combustion chamber 122 is thereby provided by the oxidizer 108 or hydrogen peroxide 110.

[0040] The gas generator 140 is again connected to the second main supply line 128 by a branch line 130. The turbine 150 can be filled with hydrogen peroxide vapor from the gas generator 140 by line L1, which, after passing through the turbine 150, can be discharged via line L2 to the separation unit 160. In contrast to the first two embodiments, the optional bypass branch 154 of the turbine 150 shown in Figures 1 and 2 is omitted here. A generator 152 (shown in solid lines), which is mandatory here, can be driven by the turbine 150 to generate electrical energy. A position control thruster 170 can be supplied, among other options, by line L3. An optional division of the volume flow between lines L1 and L3 can be provided by a valve (not shown). The oxidizer 108, located in the second tank 106 in the form of liquid hydrogen peroxide 110, can be pressurized by an oxygen line 180 leaving the separation unit 160, as indicated by the white arrow 186, as in the embodiment of Figures 1 and 2. 1 and 2, the dotted circles in the oxidizer and water vapor lines 180, 182 of the separation unit 160 are used only to illustrate the chemical compounds (O, vapor or gaseous H2O) flowing through these lines. The rocket propulsion system 300 is again integrated into the spacecraft 136.

[0041] 1 and 2 , the third embodiment includes, among other features, an electrolysis unit 302 and its associated lines designed for operation at high pressure and / or high temperature. The electrolysis unit 302 preferably includes at least one solid oxide electrolysis cell that conducts oxygen ions and is connected to the separation unit 160 by a water vapor line 182. The electrolysis unit 302 can be supplied with the electrical energy required for its operation, for example, by a generator 152 driven by the turbine 150 or by another external electrical energy source (not shown). The electrolysis unit 302 also includes a high-energy hydrogen line 310 and a high-energy oxygen line 312 for outputting the reaction products H and O produced from the water supplied during electrolysis. The two dotted circles containing the chemical symbols H and O are merely illustrative of the substances output 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 oxidant leg 180 of the separation unit 160.

[0042] A further difference is that in the third embodiment a first high-pressure storage tank 320 is connected to the hydrogen leg 310 for storing hydrogen H2 supplied by the electrolysis cell 302. A line L6 branches off from the hydrogen leg 310, by means of which 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 guaranteed if required. Furthermore, the oxygen leg 312 of the electrolysis unit 302 is connected by a line L7 to a second high-pressure accumulator 322 for receiving oxygen O2 supplied by the electrolysis unit 302.

[0043] The two high-pressure accumulators 320, 322 further enable the operation of several exemplary auxiliary or accessory systems of the rocket propulsion system 300, which are briefly described below.

[0044] Therefore, an additional line L8 for hydrogen H2 is connected to the first high-pressure accumulator 320, which in turn is connected to the main nozzle 124 of the main engine 120. Correspondingly, an additional line L9 for oxygen O2 leads from the second high-pressure accumulator 322 to the main nozzle 124 of the main engine 120. This allows, for example, in an emergency, to increase the specific impulse of the main engine 120 and to perform complex thrust vector control of the main engine 120 in order to change the trajectory of the spacecraft 136, etc., which is not possible with the first two embodiments of the rocket propulsion system shown in Figures 1 and 2.

[0045] In addition, two lines L 10、11 leads from the two high-pressure accumulators 320, 322 to the position control thruster 170, which can be operated with high-energy oxygen O2 and hydrogen H2. Compared to the supply of hydrogen peroxide gas via line L3 originating from the gas generator 140 provided in the embodiment of Figures 1 and 2, this makes it possible to generate a substantially higher specific impulse by the position control thruster 170.

[0046] Furthermore, unlike the embodiment of FIGS. 1 and 2, the defensive unit 330 and / or the high-energy unit 332 may be connected to an additional line L (12、13) The defense unit 330 is connected to the high-pressure accumulators 320, 322 using a neutron oscillating valve. The defense unit 330 can be, for example, a light gas cannon (not shown), preferably incorporating recoil compensation for the purpose of accelerating the projectile to an exit velocity of up to 60 km / s. The light gas cannon can be powered by hydrogen (H2) and / or oxygen (O2) stored in the high-pressure accumulators 320, 322. The hydrogen (H2) serves as the light gas for accelerating the projectile, while the mixture of hydrogen (H2) and oxygen (O2) (hydrogen oxide gas) serves as the actual propellant instead of, for example, black powder. This results in a significant weight reduction and an increased firing rate compared to the use of black powder cartridges. The defined release of the accelerating gas (H2) also ensures impulse equalization through appropriately positioned opposing nozzles, so that the position of the spacecraft 136 remains essentially unchanged.

[0047] Furthermore, the protection unit 330 can be formed by a laser system (not shown), which can also be supplied with oxygen O2 and hydrogen H2 from two high-pressure accumulators 320, 322, and can also be supplied with power from the generator 152.

[0048] The high energy unit 332 can also take the form of any other device that requires high pressure hydrogen H2 and oxygen O2 for its operation.

[0049] Line L 8、10 , L 9、11 , L 10、12 , L 11、13 In the region of unspecified connections or junctions (nodes) between these and other lines, valves (not shown) are preferably provided for the purpose of controlling the passage and / or branching of the respective substance flows (O2, H2, H2O2, fuel, etc.). These substance flows may be in liquid and / or gas phase. Furthermore, valves may be provided at (or within) any section of these lines.

[0050] As a further difference, an oxygen storage unit 340 and a water storage unit 342 can be optionally provided so that the life support system (not shown) of the spacecraft 136 can, for example, permanently supply oxygen O2 and water H2O for the human crew on board the spacecraft 136. This would allow for longer stays in space, or even journeys to near-Earth planets such as the Moon or Mars, if necessary. For this purpose, the oxygen storage unit 340 would be connected to an additional line L 14 to the oxidant leg 180 of the separation unit 160 by line L. The water storage unit 342 is connected to the oxidant leg 180 of the separation unit 160 by line L. 15 182 of the separation unit 160 via the water leg 182.

[0051] The third embodiment of rocket propulsion system 300 may also be operated or utilized in an optimal manner with the aid of a number of processes or sequences controlled by a controller and / or regulator.

[0052] Thus, for example, liquid hydrogen peroxide H2O2 from the second tank 106 is first converted by the gas generator 140 into gaseous hydrogen peroxide H2O2, which is then converted into electricity by the turbine 140 and generator 150.

[0053] The gaseous hydrogen peroxide exiting turbine 150 via line L2 is separated into oxygen O2 and water HO using separation unit 160. The oxygen O2 and liquid and / or vaporous water HO are then stored long term in oxygen storage unit 340 and water storage unit 342 for later use. The water HO exiting separation unit 160 is split into hydrogen H2 and oxygen O2 by electrolysis unit 302, which are permanently stored separately from each other in a first high pressure storage unit 320 for hydrogen H2 and a second high pressure storage unit 322 for oxygen O2 for future use.

[0054] Possible uses for the hydrogen H2 and oxygen O2 stored at high pressure in the high-pressure accumulators 320, 322 include, for example, injection into the main nozzle 124 of the main engine 120, supply to the position control thruster 170, supply to the protection unit 330 in the form of a light gas canister, or supply to the high-energy unit 332 (for auxiliary or backup drive).

[0055] Of course, numerous other methods or processes are possible under the control of an electronic controller and / or regulator (not shown) for operating rocket propulsion system 300 in accordance with the third embodiment of FIG.

[0056] FIG. 4 shows a schematic flow diagram of a fourth embodiment of a rocket propulsion system. This embodiment of the rocket propulsion system 400 includes an electrolysis unit (402), which in this case includes proton-conducting solid oxide electrolysis cells. Compared to the embodiment shown in FIG. 3, the separation unit 160 is omitted, and the exhaust gas from the turbine 150 can be directly supplied to the electrolysis unit 402. In this embodiment, the oxidizer leg 180′ carries water vapor in addition to oxygen, and the water vapor leg 182′ is a conversion leg containing a water vapor / oxygen mixture similar to the oxidizer leg 180′, except that its supply is directly to the electrolysis unit 402. An optional water unit 342′ and an oxygen storage unit 340′ can be housed together in the oxidizer leg 180′.

[0057] The present invention relates to a rocket propulsion system comprising a first tank and a second tank, the first tank filled with fuel and the second tank filled with an oxidizer, such as liquid hydrogen peroxide, for supplying at least one, preferably repeatably ignitable, main engine of the rocket propulsion system. A gas generator is associated with the rocket propulsion system and is designed to generate hydrogen peroxide vapor. After passing through at least one turbine, the hydrogen peroxide is at least partially supplied to a separation unit designed to decompose the hydrogen peroxide vapor into water vapor and oxygen gas. Alternatively or additionally, the hydrogen peroxide is supplied to an electrolysis unit designed to generate oxygen gas and hydrogen gas from the supplied hydrogen peroxide and / or downstream water vapor. This allows the rocket propulsion system and all of its auxiliary systems to operate using a combination of hydrogen peroxide (H2O2), an environmentally compatible oxidizer, and a storable liquid fuel with the lowest possible toxicity.

[0058] The present invention also relates to a method of operating a rocket propulsion system and to a spacecraft. [Explanation of symbols]

[0059] 100 Rocket Propulsion System (1st Transformation) 102 First Tank 104 Fuel 106 Second Tank 108 Oxidizing Agents 110 Hydrogen Peroxide 120 Main Engine 122 Combustion chamber (main engine) 124 Main nozzle (main engine, nozzle skirt) 126 No. 1 Main Supply Line (Oxidizer) 128 Second main supply line (fuel) 130 Branch Line 136 Spaceship 140 Gas Generator 150 turbine 152 Generator 154 Bypass Branch (Turbine) 160 Separation Unit 170 Position Control Thruster 180, 180' Oxidizer leg (separation unit) 182, 182' Steam Leg (Separation Unit) 184 White Arrow 186 White Arrow 200 Rocket Propulsion System (Second Variant) 202 Container (inert gas) 210 Inert Gas 300 Rocket Propulsion System (Third Variant) 302 Electrolysis Unit (High Pressure / High Temperature) 310 High Energy Hydrogen Leg 312 High Energy Oxygen Leg 320 First high pressure accumulator (hydrogen) 322 Second high pressure accumulator (oxygen) 330 defensive units 332 High Energy Unit 340, 340' Oxygen Storage Unit 342, 342' Water Storage Unit 400 Rocket Propulsion System (4th Variant) 402 Electrolysis Unit L1 line (turbine) L2 line (turbine) L3 line (position control thruster) L4 line (pressurization of the first tank) L5 line (pressurization of second tank) L6 line (pressurization of the first tank) L7 line (connection to the first high-pressure accumulator) L8 line (main nozzle) L9 line (main nozzle) L 10 Line (position control thruster) L 11 Line (position control thruster) L 12 Line (Defense / High Energy Unit) L 13 Line (Defense / High Energy Unit) L 14 Line (oxygen storage unit) L 15 Line (water storage unit) P1 fuel pump P2 Oxidizer Pump

Claims

1. A rocket propulsion system (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), the first tank (102) is filled with fuel (104) and the second tank (106) is filled with an oxidizer (108), such as liquid hydrogen peroxide (110), for supplying at least one, preferably repeatably ignitable, main engine (120) of a rocket propulsion system (100, 200, 300, 400); The rocket propulsion system (100, 200, 300, 400) is provided with a gas generator (140) configured to generate hydrogen peroxide vapor, which, after passing through at least one turbine (150), - at least in part, can be fed to a separation unit (160) designed to separate the hydrogen peroxide vapor into water vapor and oxygen gas; and / or A rocket propulsion system capable of supplying, at least in part, an electrolysis unit (302, 402) designed to produce oxygen gas and hydrogen gas from hydrogen peroxide supplied thereto and / or water vapor located downstream.

2. 10. The rocket propulsion system of claim 1, wherein the gas generator is operable to supply vaporized hydrogen peroxide to at least one position control thruster.

3. a generator (152), and / or at least one fuel pump (P １ ), and / or an oxidant pump (P ２ 3. The rocket propulsion system (100) of claim 1 or 2, wherein a plurality of turbines (150) may be driven by the at least one turbine (150).

4. The hydrogen peroxide vapor may be at least partially fed to a separation unit (160) after passing through the at least one turbine (150); 4. The rocket propulsion system of claim 1, wherein the first tank is pressurizable by a steam leg of the separation unit and the second tank is pressurizable by an oxidizer leg of the separation unit.

5. 5. The rocket propulsion system of claim 4, further comprising at least one container containing an inert gas for at least supplemental pressurization of the first tank and / or the second tank.

6. 4. The rocket propulsion system of claim 1, wherein the hydrogen peroxide vapor can be at least partially supplied to a separation unit after passing through the at least one turbine, the second tank can be pressurized by an oxygen leg of the separation unit, and an electrolysis unit is connected to the separation unit by a steam leg, the electrolysis unit having a high-energy hydrogen leg and a high-energy oxygen leg.

7. 7. The rocket propulsion system of claim 6, wherein an oxygen storage unit is assigned to the oxidizer leg of the separation unit, and a water storage unit is assigned to the steam leg of the separation unit.

8. The hydrogen peroxide vapor may be at least partially fed to an electrolysis unit (302, 402) after passing through the at least one turbine (150); the rocket propulsion system includes a working gas leg for a working gas mixture discharged from the turbine; the working gas leg includes a conversion leg (182') for supplying the working gas mixture to the electrolysis unit (402) and an oxidant leg (180') for pressurizing the second tank (106); 8. The rocket propulsion system (400) of claim 1, wherein the electrolysis unit (402) comprises a high-energy hydrogen leg and a high-energy oxygen leg (310, 312).

9. 9. The rocket propulsion system (300) of claim 6, 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. 10. The rocket propulsion system (300) of any one of claims 6 to 9, wherein the first tank (102) is pressurizable by the high-energy hydrogen leg (310).

11. 11. The rocket propulsion system of claim 6, wherein a main nozzle of the main engine can be charged with hydrogen by the first high-pressure accumulator and charged with oxygen by the second high-pressure accumulator.

12. 12. The rocket propulsion system (300, 400) of any one of claims 6 to 11, wherein the at least one position control thruster (170), the at least one defense unit (330), and / or the high energy unit (332) can be supplied by the first and second high pressure accumulators (320, 322).

13. the rocket propulsion system, with the fuel leg off, in monopropellant mode, and / or 13. A rocket propulsion system as claimed in any one of claims 1 to 12, having an engine cycle operated with the main propulsion system off for the purposes of operating the position control system, pressurizing the first tank and / or the second tank, and / or providing working gas to at least one external system.

14. 14. The method of operating a rocket propulsion system (100, 200, 300, 400) of any one of 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 taken from a second main supply line (128) of the main engine (120) and supplied to the gas generator (140).

15. The method of claim 14, wherein the hydrogen peroxide vapor exhausted from the gas generator (140) is at least partially supplied to the turbine (150).

16. A spacecraft (136) comprising at least one rocket propulsion system (100, 200, 300, 400) according to any one of claims 1 to 13.

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