Spacecraft engine

Abstract

The invention relates to an engine (1) for a spacecraft comprising an injection system (2) for injecting a first substance, the injection system comprising an injection element (5) that conveys the first substance and an injection plate (12), a decomposition chamber (8) comprising a second substance (20) and a nozzle (6). The second substance is retained in the decomposition chamber between the injection plate of the injection system and a retaining element (14). The injection plate comprises at least one through-hole (36) allowing the first substance to pass from the injection system into the decomposition chamber so as to allow the second substance to decompose when the first substance is introduced into the decomposition chamber and at least one reaction product to be formed, the at least one reaction product being discharged through at least one through-hole (38) of the retaining element so as to reach the nozzle and produce propulsion energy.

Description

[0001] P608600PC0

[0002] Title of the invention: SPACECRAFT ENGINE

[0003] TECHNICAL FIELD

[0004] The present invention relates to a spacecraft engine. It relates in particular, but not exclusively, to a spacecraft engine, a propulsion device, a spacecraft, and a manufacturing method.

[0005] CONTEXT

[0006] Spacecraft propulsion systems are used to move the spacecraft, for example by expelling a propellant from a nozzle. The propellant provides the thrust needed to move the spacecraft, for example during takeoff (from the ground to space) or movement in space or orbit, for example in low Earth orbit (LEO) or geostationary orbit (GEO).

[0007] Since every additional gram added to a spacecraft requires extra force to lift it from the ground into space using only the spacecraft's propulsion system, more efficient propulsion systems are necessary. A more efficient engine, and therefore a more efficient propulsion system, can compensate for the extra weight by converting more energy into useful work to lift the spacecraft.

[0008] One of the objectives of this disclosure is to improve upon prior art engines.

[0009] Certain aspects and embodiments of the invention relate to an engine for a spacecraft, a propulsion device, a spacecraft and a manufacturing method, as indicated in the attached claims.

[0010] This objective is achieved by a spacecraft engine comprising a first substance injection system, the injection system comprising an injection element carrying the first substance and an injection plate, and a decomposition chamber comprising a second substance and a nozzle. The second substance is retained in the decomposition chamber between the injection plate of the injection system and a retaining element, and the injection plate includes at least one through-hole allowing the first substance from the injection system to pass into the decomposition chamber, so as to permit the decomposition of the second substance when the first substance is introduced into the decomposition chamber, and the creation of at least one reaction product, said at least one reaction product being discharged through at least one through-hole in the retaining element to reach the nozzle and create propulsion energy.The engine advantageously provides a means of storing and retaining a second substance before using it within the engine. Thus, the second substance can be separated from the first until the engine needs energy to propel itself.

[0011] The injection system may further include a flow homogenization chamber for the first substance located between the injection element and the injection plate.

[0012] The first substance flow homogenization chamber can homogenize the flow of the first substance as it is conveyed to the decomposition chamber. Homogenizing the flow reduces the likelihood of incomplete reactions and / or areas (or pockets) of more vigorous reaction in the decomposition chamber due to a more uniform mixing of the first and second substances.

[0013] Said at least one hole in the injection plate may be perpendicular to the surface of the injection plate.

[0014] By arranging at least one hole perpendicular to the injection plate, the flow of the first substance can enter the decomposition chamber while being substantially aligned with the nozzle.

[0015] Said at least one hole in the injection plate may have an oblique angle relative to the surface of the injection plate.

[0016] Thanks to an oblique angle relative to the injection plate, the flow of the first substance can enter through said hole into the decomposition chamber in a manner that is not substantially aligned with the nozzle, which promotes the mixing of the first and second substances during use.

[0017] The injection plate may include a plurality of through holes.

[0018] By providing several through holes, it is possible to increase the flow rate of the first substance into the decomposition chamber during use.

[0019] At least one hole in the plurality of through holes in the injection plate may have a diameter different from at least one other hole in the plurality of through holes in the injection plate.

[0020] By using holes of different diameters, the flow rate can be adapted to specific locations on the injection plate. For example, when the flow rate needs to be higher in the center of the injection plate than at its periphery, the diameter of the central hole can be larger than that of a second hole located at the periphery.

[0021] The plurality of through holes in the injection plate may be located in an annular portion of the injection plate situated on the outer periphery of the injection plate; optionally, the annular portion may have a width representing less than 80% of the radius of the injection plate, preferably less than 60% of the radius of the injection plate, and more preferably, less than 50% of the radius of the injection plate.

[0022] The arrangement of through holes around an outer peripheral annular area of ​​the injection plate may promote the mixing of the first substance with the second substance during use.

[0023] At least one through hole in the retaining element may be perpendicular to the surface of the retaining element.

[0024] By placing at least one hole perpendicular to the retaining element, the reaction product flow exiting the decomposition chamber can be substantially aligned with the nozzle.

[0025] At least one through hole in the retaining element may have an oblique angle to the surface of the retaining element.

[0026] Thanks to an oblique angle relative to the retaining element, the flow of the reaction product exiting the decomposition chamber and heading towards the nozzle may not be substantially aligned with the nozzle.

[0027] The retaining element may be provided with a plurality of through holes.

[0028] By providing several through holes, it is possible to limit the pressure losses of the reaction product exiting the decomposition chamber during use.

[0029] At least one hole in the plurality of through holes in the retaining element may have a diameter different from at least one other hole in the plurality of through holes in the retaining element.

[0030] By providing holes of different diameters, the flow rate can be adapted to specific locations through the retaining element.

[0031] The engine may further include a post-retaining chamber between the retaining element and the nozzle capable of homogenizing the flow of said at least one reaction product and / or accelerating the flow of said at least one reaction product.

[0032] Homogenizing the flow can promote stable flow in the nozzle during use.

[0033] The after-retained chamber may have a shape that converges towards the nozzle.

[0034] By having a convergent shape, the flow is concentrated towards the nozzle. The injection element may include at its end a reducing element, the reducing element having a through hole whose diameter may be smaller than the diameter of the outlet of the injection element.

[0035] The presence of such a reducing element makes it possible to increase the flow velocity due to the restricted diameter of the orifice.

[0036] A filter can be positioned at the end of the injection element, before the reducing element. Placing the filter before the reducing element reduces the likelihood of the reducing element or any other downstream component becoming clogged during operation.

[0037] The decomposition chamber may further include a heating element; optionally, the heating element may be located on the outer periphery of the decomposition chamber.

[0038] The heating element can advantageously increase the temperature of the decomposition chamber to promote any reaction occurring within it. The decomposition chamber may further include a cooling means; optionally, this cooling means may be located on the outer periphery of the decomposition chamber.

[0039] Cooling methods can help keep the decomposition chamber cold and within a temperature range best suited to the reaction occurring in the decomposition chamber.

[0040] The cooling system may include several heat dissipation fins. By using heat dissipation fins, the decomposition chamber can be passively cooled by thermal radiation without the need for active cooling.

[0041] The post-retention chamber may further include a pressure sensor capable of measuring the pressure in the post-retention chamber.

[0042] The presence of a pressure sensor at this location allows the reaction to be monitored.

[0043] The injection system may further include a means of heat dissipation suitable for cooling the injection element.

[0044] The heat dissipation method can conduct heat away from the injection system to keep it cool.

[0045] The injection system may further include a means for attaching the engine to a spacecraft. By providing a means of heat dissipation along with the means for attaching the engine to a spacecraft, the heat dissipation means can perform more than one function and, consequently, reduce the total number of engine components, thus reducing the need for additional components that could add weight to the entire system.

[0046] The first substance may include hydrogen peroxide (H2O2).

[0047] The second substance may be a catalyst.

[0048] The catalyst may include alumina.

[0049] The catalyst may include at least one of the following metals: platinum, silver, and niobium.

[0050] The second substance may be in the form of granules.

[0051] The use of a granular catalyst creates a porous medium that facilitates the exchange between the first and second substances. This increases the reaction surface area. The same objective is achieved by a spacecraft propulsion system comprising at least one engine according to one of the previously described embodiments, and at least one reservoir containing the first substance, said reservoir being connected to said engine.

[0052] The propulsion system incorporates all the advantages of the engine it includes.

[0053] The propulsion device may further include at least one valve controlling the supply of the first substance to said at least one engine.

[0054] The presence of a valve allows the flow of the first substance to be controlled, restricted or stopped as needed.

[0055] A filter can be positioned near said valve at least.

[0056] The propulsion system may include a plurality of motors.

[0057] Adding extra engines increases the thrust of the propulsion system.

[0058] In this case, the propulsion system may include a plurality of tanks containing the first substance, each engine being able to be connected to at least one tank.

[0059] The propulsion system may include a controller capable of independently controlling the motors.

[0060] By allowing independent control, any spacecraft incorporating the propulsion device can be maneuvered by activating one or more of the engines, which can allow any spacecraft to turn.

[0061] The propulsion system may include at least one valve for each engine. By providing one valve per engine, each engine can be operated independently of the others.

[0062] The invention also relates to a spacecraft comprising an engine according to one of the previously described embodiments or a propulsion device according to one of the previously described embodiments.

[0063] Advantageously, the spacecraft benefits from the propulsion system and / or engine it includes.

[0064] The invention also relates to a method for manufacturing a spacecraft engine comprising a system for injecting a first substance, the injection system comprising an injection element transporting the first substance, a decomposition chamber and a nozzle for converting thermal energy into propulsion energy, the method comprises the following steps: a step of positioning a retaining element in the decomposition chamber near the nozzle, a step of welding the retaining element to hold the retaining element in the decomposition chamber, a step of filling the decomposition chamber with a second substance up to the vicinity of an opening in the decomposition chamber to allow assembly of the decomposition chamber with the injection system, a step of introducing an injection plate into the decomposition chamber,a step of positioning a connection interface of the injection system at the opening of the decomposition chamber, in order to assemble the injection system with the decomposition chamber, and a step of welding the connection interface of the injection system and the decomposition chamber.

[0065] Using such a method allows the second substance to be encapsulated during the manufacture of an engine.

[0066] The welding step of the connection interface of the injection system and the decomposition chamber may include a transparent weld.

[0067] The decomposition chamber may include a shoulder; the step of introducing the injection plate into the decomposition chamber then includes a step of positioning the injection plate element at the shoulder. The method may further include a step of welding a reducing element having a through hole whose diameter is smaller than the diameter of the injection element's outlet to the injection element.

[0068] A filter can be positioned between the end of the injection element outlet and the reducing element before the reducing element is welded.

[0069] The welding step of the reducing element may include a through-weld.

[0070] The decomposition chamber and the nozzle can be manufactured to form a single piece.

[0071] The method may further include a step of positioning a heating element on the decomposition chamber.

[0072] BRIEF DESCRIPTION OF THE DIFFERENT DRAWINGS

[0073] One or more methods of disclosure will now be described, by way of example only, with reference to the figures in the drawings accompanying this document, in which:

[0074] FIG. 1 illustrates an engine for a spacecraft in accordance with one embodiment of disclosure.

[0075] FIG. 2 illustrates the engine of FIG. 1 in cross-section to show the internal components of the engine.

[0076] FIG. 3 illustrates the engine of FIG. 1 in an exploded view with some engine components removed.

[0077] FIG. 4 is a schematic diagram of a propulsion device which includes one or more engines of FIG. 1 according to one embodiment of the disclosure.

[0078] FIG. 5 is a schematic illustration of a spacecraft including the engine and / or propulsion device according to one embodiment of the disclosure.

[0079] FIG. 6 is a flowchart that describes a number of manufacturing steps for an engine for a spacecraft.

[0080] DETAILED DESCRIPTION

[0081] An engine 1 for a spacecraft 500, a propulsion device 400, a spacecraft 500, and a manufacturing method 600 will be described with the aid of FIGS. 1 to 6. The engine 1 can be part of a propulsion device 400 and / or a spacecraft 500, as will be described in more detail below. The engine 1 is shown in FIGS. 1, 2, and 3. It comprises a system for injecting a first substance, also called the injection system 2, a decomposition chamber 8, and a nozzle 6. As the informed reader will understand, the propellant is expelled from the nozzle 6 to provide thrust. Indeed, the nozzle allows the transformation of thermal (or chemical) energy into kinetic energy, and thus into propulsion energy.

[0082] The injection system 2 includes an element, namely the injection element 5, for transporting the first substance, and an injection plate 12. The injection element 5 is illustrated in more detail in FIG. 2 and FIG. 3.

[0083] The injection element 5 can be connected, for example at one end, to a fixing means 3 by one or more heat dissipation means 4, and a conduit 7. The heat dissipation means 4 is a thermal support which, during use, helps to dissipate the thermal energy of the injection element 5. It can also help to dissipate the thermal energy of the injection plate 12.

[0084] In the example shown in FIG. 1, the fastening means 3 may consist of a fixing device. This could be, for example, a plate, in particular a circular plate. However, the plate could be square, circular, rectangular, triangular, hexagonal, or any other conceivable shape. The fastening means also contributes to heat dissipation.

[0085] Conduit 7 defines a fluid path through which a fluid can flow between an inlet 9 and an outlet 17 of the injection element. Conduit 7 can be connected to a primary substance source, as will be described in more detail below. Conduit element 7 is connected to injection element 5.

[0086] Conduit 7 can be a hollow pipe or a hollow cylinder.

[0087] Entry 9 is notably located on the fixing means 3.

[0088] In the illustrated example, there is only one conduit 7. However, there may be two or more conduits 7, for example, two, three, four, five, or more. Each of the conduits 7 can transport fluid as described previously.

[0089] The fastening means 3 may have one or more through holes 10. The through holes 10 are sized to receive a fastener for connecting the fastening means 3, and thus the motor 1, to a structure (not shown in Fig. 1). The structure may be a part of the spacecraft 500, for example, a wall or enclosure of the spacecraft 500. The structure may also be a workbench or test bench. The fastener may be a bolt, screw, quick-release fastener, explosive bolt, or any other known fastener. Once the fastening means is attached to a structure, such as a spacecraft, the thrust forces are transmitted to the spacecraft.

[0090] The connection between the injection element 5 and the fastening means 3 can be ensured by the heat dissipation means 4 and the conduit 7, as shown in FIG. 1 and FIG. 2. In the example shown in FIG. 1, several heat dissipation means 4 connect the injection element 5 to the fastening means 3. The heat dissipation means 4 are arranged, for example, circumferentially around the conduit 7. In the example shown, the conduit 7 is located at the center or substantially at the center of the supports 4.

[0091] The heat dissipation means 4 may be connected to a ring extending from the surface of the fixing means 3 to the injection element 5. In other configurations, the ring may not be present and the heat dissipation means 4 may be connected directly to the surface of the fixing means 3.

[0092] In the example shown in FIG. 1 and FIG. 2, there are six heat dissipation means 4, but there can be any number of heat dissipation means 4, and the example shown is not intended to be limiting. For example, there can be one, two, three, four, five, six, seven, eight, nine, or ten supports, or any subset or range thereof.

[0093] The heat dissipation means 4 may optionally include a window 30 arranged between each of the heat dissipation means 4. The windows 30 reduce the overall weight of the engine 1 and may further facilitate the cooling of the injection element 5.

[0094] In other arrangements, the injection element 5 and the fastening means 3 can be connected by a single cylindrical heat dissipation means 4 or a single frustoconical heat dissipation means. These arrangements are not shown in the figures.

[0095] The mounting means 3, the heat dissipation means 4, and the injection element 5 are illustrated in more detail in FIG. 3 in an exploded view, with parts of the motor 1 removed for clarity. As can be seen, the injection element 5 may include, in particular within a recessed portion 28, a reducing element 26 with an orifice 16. Optionally, a filter 18 may be inserted upstream of the reducing element, in particular within the recessed portion 28.

[0096] Filter 18 can be a mesh filter with a mesh size of 5 µm to 50 µm, preferably 25 µm. Alternatively, filter 18 can be an open-cell foam with an average pore size of 5 µm to 50 µm, preferably an average pore size of 25 µm. Filter 18 is configured to allow fluid to flow through it. The filter prevents particles from rising.

[0097] Filter 18 is sized, for example, to be received in the recessed part 28.

[0098] The reducing element 26 has an orifice 16, namely a through hole. The diameter of the orifice 16 is smaller than that of the outlet 17. The orifice 16 is a through hole in the reducing element 26. The orifice 16 is in fluidic communication with the inlet 9. The reducing element 26 creates a pressure drop, which stabilizes the fluid flow and facilitates the calibration of the fluid flow rate.

[0099] The reducing element 26 can be dimensioned to be complementary to the embedded part 28 so that at least a part of the reducing element 26 is received in the embedded part 28.

[0100] The filter 18 can be placed in the recessed part 28 and is held there by the reducing element 26.

[0101] The injection system further includes an injection plate 12 which has one or more injection orifices 36, the injection orifice 36 being a hole through the injection plate 12. The orifice of the injection plate 36 fluidically connects the inlet 9 to the decomposition chamber to allow the flow of the first substance into the decomposition chamber 8, in particular into the volume 20 of the decomposition chamber.

[0102] There can be a plurality of orifices, namely through holes, of injection plate 36, for example from two to ten orifices of injection plate 36. The orifices of injection plate 36 in the example shown in FIG. 2 are arranged equidistantly around the injection plate 12.

[0103] The plurality of orifices 36 of the injection plate may be located in an annular portion of the injection plate 12. The annular portion has a width less than or equal to 80% of the radius of the injection plate 12, preferably less than or equal to 60% of the radius of the injection plate 12 and more preferably less than or equal to 40% of the radius of the injection plate 12.

[0104] At least one of the orifices of the injection plate 36 may be arranged perpendicular to the surface of the injection plate 12 so as to be aligned (i.e., parallel or substantially parallel) with the longitudinal axis X of the decomposition chamber 8. Optionally, one or more of the orifices of the injection plate 36 may be arranged at an oblique angle to the surface of the injection plate 12, so as to form an angle with the longitudinal axis X of the decomposition chamber 8. Optionally, one or more subsets of orifices of the injection plate 36 may have a diameter different from the rest of the orifices of the injection plate 36.

[0105] Between the injection plate 12 and the reducing element 26 is a flow homogenization chamber for the first substance 22. The flow homogenization chamber for the first substance 22 is illustrated in FIG. 2. It is a chamber whose side wall can be conical, the cone passing from a first diameter to a second diameter along the longitudinal axis X, from the reducing element 26 to the injection plate 12. The flow homogenization chamber for the first substance 22 helps to guide the fluid flow from the orifices 16 to the injection plate 12 and the orifices of the injection plate 36.

[0106] One or more sensors may be located in the flow homogenization chamber of the first substance 22. For example, the sensor may be one or more of the following: a temperature sensor, a pressure sensor. One or more sensors may also be located at the flow homogenization chamber of the first substance 22. For example, the sensor may be a force sensor. The sensor may be electrically connected to a controller to allow unidirectional or bidirectional data communication.

[0107] Returning to FIG. 1 and FIG. 2, the decomposition chamber 8 will now be described in more detail. The decomposition chamber 8 is located between the injection plate 12 and the nozzle 6. The decomposition chamber 8 contains a second substance 20, as described in more detail below.

[0108] The decomposition chamber 8 is essentially cylindrical. However, the decomposition chamber 8 can have any imaginable shape, for example cubic or hexagonal.

[0109] The decomposition chamber 8 includes a retaining element 14. The second substance 20 is retained in a volume 20 of the decomposition chamber 8, defined between the injection plate 12 and the retaining element 14 during use. The injection plate and the retaining element thus act as a first and second barrier to the second substance in the decomposition chamber.

[0110] The injection plate 12 of the injection system is located at a first end of the decomposition chamber 8, for example on an injection plate shoulder 32 defined by an internal wall of the decomposition chamber 8.

[0111] A side wall of the injection plate 12 is complementary to the shape of the inner wall at the first end of the decomposition chamber. The shoulder of the injection plate 32 is complementary to the shape of the injection plate 12 and is preferably annular. The injection plate 12 is welded to the inner wall at the first end and / or to the shoulder of the injection plate 32. The weld may be one or more spot welds or a continuous weld around part or all of the perimeter of the injection plate 12. Preferably, the weld is a through weld.

[0112] The retaining element 14 is located at a second end of the decomposition chamber 8, for example on a shoulder of retaining element 34. The second end is spaced away from the first, the first being located towards the injection element 5 and the second being located towards the nozzle 6, in particular in close proximity to it.

[0113] The shoulder of the retaining element 34 is complementary to the shape of the retaining element 14 and preferably annular.

[0114] The retaining element 14 can be a retaining plate but can also take other more complex forms.

[0115] A side wall of the retaining element 14 is complementary to the shape of the inner wall at the first end. The retaining element 14 is welded to the inner wall of the first end and / or to the shoulder of the retaining element 34. The weld may be one or more spot welds or a continuous weld over part or all of the perimeter of the retaining plate 14. Preferably, the weld is a through weld.

[0116] The retaining element 14 has one or more retaining element orifices 38, the retaining element orifice 38 being a hole through the retaining element 14. The retaining element orifice 38 connects the decomposition chamber 8 to the nozzle 6.

[0117] According to a particular embodiment, the retaining element is entirely perforated with through holes.

[0118] There may be several retaining element orifices 38, for example from two to sixty retaining element orifices 38.

[0119] At least one of the orifices of the retaining element 38 may be arranged perpendicular to the surface of the retaining element 14 so as to be aligned (i.e., parallel or substantially parallel) with the longitudinal axis X of the decomposition chamber 8. Optionally, one or more of the orifices of the retaining element 38 may be arranged at an oblique angle to the surface of the retaining element 14, so as to form an angle with the longitudinal axis X of the decomposition chamber 8. Optionally, one or more subsets of orifices of the retaining element 38 may have a diameter different from the rest of the orifices of the retaining element 38.

[0120] Between the retaining element 14 and the nozzle 6 is a post-retaining chamber 42 for homogenizing the flow of at least one reaction product created when the first substance is introduced into the decomposition chamber and / or accelerating the flow of said at least one reaction product. The post-retaining chamber 42 is illustrated in FIG. 2. It is a chamber whose lateral wall may be conical, the conicity decreasing from a first diameter to a second diameter along the longitudinal axis X, from a first point to a second point. In other words, the post-retaining chamber 42 has a shape that converges towards the nozzle 6. The first point is adjacent to or near the retaining element 14 and the second point is adjacent to or near the inlet orifice of the nozzle 6. The angle of convergence is, for example, 45° but can be within a range, in particular, from 30° to 60°.

[0121] The nozzle notably has a diverging side wall which may be conical. In particular, the nozzle has the shape of a bell, which is defined as a parabola with a semi-angle, for example, of 15°, the angle being notably within a range from 10° to 40°.

[0122] One or more sensors can be arranged in the post-retention chamber 42. For example, the sensor can be one or more of the following: a temperature sensor, a pressure sensor. One or more sensors can also be arranged at the level of the post-retention chamber 42. For example, the sensor can be a force sensor. The sensor can be electrically connected to a controller to allow unidirectional or bidirectional data communication. The sensors are, in particular, as illustrated in FIG. 1, formed, for example, of a pressure measuring tube 11 and a temperature measuring tube 13. These tubes are inserted into openings 15 of the second homogenization chamber.

[0123] The motor 1 may also include a heating element (not shown in the figures). The heating element may be an electric heating element that can be connected to an electrical power source. The heating element is configured to heat the decomposition chamber 8. As such, the heating element may be disposed on, around, or at least partially around, the outer periphery of the decomposition chamber 8. The heating element may also be placed in a chamber within the wall of the decomposition chamber 8. The heating element may be used to heat the second substance located in the decomposition chamber 8 within volume 20. The heating element is optional. Indeed, the motor according to the invention allows for cold starting.

[0124] The motor 1 may also include a cooling means (not shown in the figures). The cooling means may be an electrically powered means that can be connected to an electrical power source. Alternatively, the cooling means may be a passive cooling means such as a heat sink or a plurality of heat-dissipating fins, or the like. The cooling means is configured to cool the decomposition chamber 8. As such, the cooling means may be disposed on, around, or at least partially around, the outer periphery of the decomposition chamber 8. Alternatively, the cooling means may be disposed in a chamber located in a wall of the decomposition chamber 8.

[0125] Engine 1 can be part of a monergoL system. In this case, the first substance can be a fuel source and the second substance is a catalyst capable of breaking down the fuel source.

[0126] An example of the first substance that can be used with engine 1 is hydrogen peroxide, H2O2, and the second substance is a catalyst capable of decomposing H2O2. The decomposition of H2O2 is given by equation 1:

[0127] 2H2O2 2H2O +O2 ... (eq. 1)

[0128] Thus, the decomposition will create at least one reaction product. In this case, the reaction products include a gaseous mixture made up of water and oxygen.

[0129] The presence of the catalyst increases the reaction rate compared to the reaction without a catalyst.

[0130] The catalyst may include one or more catalytic elements such as rare or precious metals, for example: platinum, silver, and niobium. These catalysts may be placed on a support (either on the surface of the support or dispersed within it). The support may be alumina.

[0131] The catalyst can be in the form of granules or powder with an average particle size of between 0.5 and 2.0 mm, measured using a powder sieving method commonly used in the art of powder metallurgy and materials science.

[0132] The products of the reaction in equation 1 are discharged from the decomposition chamber through the through-hole(s) of the retaining element to reach the nozzle 6 and then discharged to provide propulsion energy, namely the thrust enabling movement. A propulsion device 400 will now be described with reference to FIG. 4. The propulsion device 400 comprises one or more engines 1 according to one of the embodiments described previously and a tank 401. In the example shown in FIG. 4, there are four identical engines 1; for ease of examination, these engines have been labeled engine 404a, engine 404b, engine 404c, and engine 404d. Although FIG.4 shows four 404a-404d engines, it is not intended to be limiting and there can be any number of 1 engines, for example there can be from 1 to 10 1 engines, from 1 to 5 1 engines or from 2 to 5 1 engines or 3 1 engines or 4 1 engines or any range or subset of these.

[0133] Tank 401 contains a source of the first substance; for example, when the first substance is H2O2, tank 401 contains a fluid source of H2O2. The H2O2 can be in gaseous or liquid form.

[0134] According to one embodiment, the reservoir 401 is connected to each of the engines 404a-404d by one or more fluid lines 403.

[0135] Each of the 404a-404d motors can have a calibrated orifice 420a-420d, a filter 418a-418d, and / or a control valve 406a-406d upstream of the motor 404a-404d. The control valves 406a-406d are configured to control the supply of the first substance to the motors 404a-404d. The control valves 406a-406d can be solenoid valves, hydraulically actuated valves, or pneumatically actuated valves. The control valves 406a-406d are controlled by a controller 412 to which they are connected by one or more electrical connections 414. As will be seen, the controller 412 can command the control valves 406a-406d to open and close or partially open independently of each other, which allows each motor 404a-404d to be controlled independently of each other.

[0136] Each of the 404a-404d motors can be equipped with a 410a-410d sensor. The 410a-410d sensors are electrically connected to the 412 controller. The 410a-410d sensors are configured to detect one or more parameters of the 404a-404d motor, as described previously.

[0137] Between tank 401 and motors 404a-404d, there may be a tank outlet sensor 402. The tank outlet sensor 402 can be configured to detect the pressure, temperature, or other information of the first substance leaving tank 401. The tank outlet sensor 402 is electrically connected to the controller 412 via an electrical connection 414.

[0138] Between the reservoir 401 and the motors 404a-404d, there may be optional additional filters 418 and valves 416 to provide further control of the motors 404a-404d. The valves 416 are configured to open, close, or partially open the fluid circuit through which they flow. The valves 416 are connected to the controller 412 by one or more electrical connections 414.

[0139] Between the valves 416 and the motors 404a-404d, there may be a pressure sensor 422. The pressure sensor 422 is electrically connected to the controller 412 by one or more electrical connections 414 so as to be able to read the pressure in the fluid line 403. For example, to check the line pressure after the valve 416 in order to verify whether the valve 416 is open or closed.

[0140] As the discerning reader will notice, 414 electrical connections can be configured to transmit power, but also to communicate data in either direction. 414 electrical connections can include one or more wires or electrical cables.

[0141] The propulsion device 400 may include one or more service valves 424. The service valves 424 may be used to fill or empty the tank 401 as required.

[0142] Spacecraft 500 will now be described using FIG. 5. Spacecraft 500 is shown schematically in FIG. 5 and includes engine 1 and / or propulsion device 400 as described previously.

[0143] A spacecraft is, for example, a satellite, capsule or other space vehicle, a space object or a space platform such as an upper stage of a launch vehicle.

[0144] The manufacturing method 600 will now be described in more detail with the help of FIG. 6. FIG. 6 shows a flowchart describing a number of steps in the manufacturing method of an engine 1 for a spacecraft 500.

[0145] The flowchart describes a number of manufacturing steps for an engine 1 as described previously in one of the embodiments above. The method includes the following steps:

[0146] First, step 602 includes the positioning of a retaining element 14 in the decomposition chamber near the nozzle 6.

[0147] Step 604 includes welding the retaining element 14 into the decomposition chamber 8.

[0148] Next, in step 606, the decomposition chamber 8 is filled with the second substance to a fill level close to an opening in the decomposition chamber 8 to allow assembly of the decomposition chamber 8 with the injection system 2. Then, in step 608, the injection plate 12 is introduced into the decomposition chamber 8.

[0149] Next, in step 610, a connection interface for the injection system 2 is positioned at the opening of the decomposition chamber 8 in order to assemble the injection system 2 with the decomposition chamber 8.

[0150] Next, in step 612, the connection interface between the injection system 2 and the decomposition chamber 8 is welded. The engine 1 is thus at least partially assembled or fully assembled, the second substance being contained within the decomposition chamber 8 in volume 20.

[0151] Optionally, when the step includes a welding step, for example step 604 or 612, the weld can be a see-through weld. A see-through weld is a laser welding technique in which a laser passes through a first layer of material to melt a second layer at a certain depth, joining the two components at a junction not exposed externally.

[0152] When the decomposition chamber 8 includes a shoulder, such as the shoulder of the retaining element 34, step 602 of introducing the retaining element 14 into the decomposition chamber 8 includes the additional step of positioning the retaining element 14 on the shoulder of the retaining element 34.

[0153] When the decomposition chamber 8 includes a shoulder, such as the shoulder of the injection plate 32, the step 608 of introducing the injection plate 12 into the decomposition chamber 8 includes the additional step of positioning the injection plate 12 on the shoulder of the injection plate 32.

[0154] Optionally, manufacturing method 600 may include an additional step of welding a reducing element 26 of any type described previously and preferably with an orifice 16 smaller than that of the conduit 7. The weld may be a through weld.

[0155] The decomposition chamber 8 and the nozzle 6 can be manufactured as a single piece. For example, using a lathe or other turning machine, or by casting the components together, or by 3D printing, also known as additive manufacturing.

[0156] The components of the engine 1, such as the heat dissipation means 3, the decomposition chamber 8, and / or the nozzle 6, can be manufactured by one of the following processes: a casting process, an additive manufacturing process, a powder metallurgy process, or a machining process. The engine 1 and any component or element thereof can be manufactured from a high-temperature alloy, for example, a nickel superalloy, such as a nickel-chromium superalloy, preferably an Inconel alloy (registered trademark), for example, Inconel 718, Inconel 625, Inconel 617, or Inconel 600.

[0157] Optionally, manufacturing method 600 may include an additional step of positioning a heating element on, in, or through the decomposition chamber 8. The heating element may be one of those described previously.

[0158] Optionally, manufacturing method 600 may include an additional step of positioning a cooling means on, in, or through the decomposition chamber 8. The cooling means may be one of those described previously.

[0159] LIST OF DRAWING ELEMENTS

[0160] 1 Engine

[0161] 2. Injection System

[0162] 3. Means of attachment

[0163] 4. Heat dissipation methods

[0164] 5 Injection element

[0165] 6 Nozzle

[0166] 7 Conduit

[0167] 8 Decomposition Chamber

[0168] 10 Through hole

[0169] 11 First sensor

[0170] 13 Second sensor

[0171] 9 Entrance

[0172] 12 Injection plate 14 Retaining element

[0173] 15 Sensor port

[0174] 16 Orifice

[0175] 17 Exit

[0176] 18 Filter

[0177] Volume 20

[0178] 22 First Substance Flow Homogenization Chamber

[0179] 26 Reducing element

[0180] 28 Embedded part

[0181] 30 Window

[0182] 32 Injection plate shoulder

[0183] 34 Retaining element shoulder

[0184] 36 Injection plate orifice

[0185] 38 Retaining element orifice

[0186] X Longitudinal axis

[0187] 42 Post-detention room

[0188] 400 Propulsion Device

[0189] 401 Tank

[0190] 402 Tank outlet sensor

[0191] 403 Fluid Conduit

[0192] 404a Engine

[0193] 404b Engine 404c Engine

[0194] 404d Engine

[0195] 406a Control Valve

[0196] 406b Control Valve

[0197] 406c Control Valve

[0198] 406d Control Valve

[0199] 410a Sensor

[0200] 410b Sensor

[0201] 410c Sensor

[0202] 41 Od Sensor

[0203] 412 Controller

[0204] 414 Electrical connection

[0205] 416 Valve

[0206] 418a Filter

[0207] 418b Filter

[0208] 418c Filter

[0209] 418d Filter

[0210] 418 Filter

[0211] 420a Calibrated Orifice

[0212] 420b Calibrated Orifice

[0213] 420c Calibrated Orifice

[0214] 420d Calibrated Orifice Pressure Sensor Service Valve Spacecraft

Claims

DEMANDS 1. A spacecraft engine (1) comprising an injection system (2) for a first substance, the injection system comprising an injection element (5) carrying the first substance and an injection plate (12), a decomposition chamber (8) comprising a second substance (20), a nozzle (6) in which the second substance is retained in the decomposition chamber between the injection plate of the injection system and a retaining element (14), and the injection plate comprising at least one through hole (36) allowing the passage of the first substance from the injection system into the decomposition chamber, so as to permit decomposition of the second substance when the first substance is introduced into the decomposition chamber, and the creation of at least one reaction product,said at least one product of the reaction being discharged through at least one through hole (38) of the retaining element to reach the nozzle and create the propulsion energy.

2. Engine according to claim 1, wherein the injection system further comprises a flow homogenization chamber of the first substance (22) located between the injection element and the injection plate.

3. Engine according to any one of the preceding claims, wherein said at least one hole in the injection plate is perpendicular to the surface of the injection plate.

4. Engine according to any one of the preceding claims, wherein said at least one hole in the injection plate has an oblique angle with respect to the surface of the injection plate.

5. Engine according to any one of the preceding claims, wherein the injection plate comprises a plurality of through holes.

6. Engine according to the preceding claim, wherein at least one hole of the plurality of through holes in the injection plate has a diameter different from at least one other hole of the plurality of through holes in the injection plate.

7. Engine according to claim 5 or claim 6, wherein the plurality of through holes in the injection plate is located in an annular portion of the injection plate situated on the outer periphery of the injection plate, optionally the annular portion has a width representing less than 80% of the radius of the injection plate, preferably less than 60% of the radius of the injection plate and more preferably less than 50% of the radius of the injection plate.

8. Motor according to any one of the preceding claims, wherein at least one through hole of the retaining element is perpendicular to the surface of the retaining element.

9. Motor according to any one of the preceding claims, wherein at least one through hole of the retaining element has an oblique angle with respect to the surface of the retaining element.

10. Motor according to any one of the preceding claims, wherein the retaining element is provided with a plurality of through holes.

11. Motor according to the preceding claim, wherein at least one hole of the plurality of through holes of the retaining element has a diameter different from at least one other hole of the plurality of through holes of the retaining element.

12. Motor according to any one of the preceding claims, wherein the motor further comprises a post-retaining chamber (42) between the retaining element and the nozzle capable of homogenizing the flow of said at least one reaction product and / or accelerating the flow of said at least one reaction product.

13. Engine according to the preceding claim, in which the after-retained chamber has a shape converging towards the nozzle.

14. Engine according to any one of the preceding claims, wherein the injection element comprises at its end a reduction element (26), the reduction element having a through hole whose diameter is less than the diameter of the outlet (17) of the injection element.

15. Engine according to the preceding claim, in which a filter (18) is positioned at the end of the injection element, before the reducing element.

16. Motor according to any one of the preceding claims, wherein the decomposition chamber further comprises a heating element, optionally the heating element is located on the outer periphery of the decomposition chamber.

17. Engine according to any one of the preceding claims, wherein the decomposition chamber further comprises a cooling means, optionally the cooling means is located on the outer periphery of the decomposition chamber.

18. Engine according to the preceding claim, in which the cooling means comprises several heat dissipation fins.

19. Motor according to any one of the preceding claims, wherein the post-retention chamber further comprises a pressure sensor capable of measuring the pressure in the post-retention chamber.

20. Engine according to any one of the preceding claims, wherein the injection system further comprises a heat dissipation means (4) suitable for cooling the injection element (5).

21. Engine according to the preceding claim, wherein the injection system further comprises a means for attaching the engine to a spacecraft.

22. Motor according to any one of the preceding claims, wherein the first substance comprises hydrogen peroxide (H2O2).

23. Engine according to any one of the preceding claims, wherein the second substance is a catalyst.

24. Engine according to the preceding claim, in which the catalyst comprises alumina.

25. Engine according to claim 23 or 24, wherein the catalyst comprises at least one of the metals platinum, silver and niobium.

26. Motor according to any one of the preceding claims, wherein the second substance is in the form of granules.

27. Propulsion device (400) for a spacecraft comprising: at least one engine (1) according to any one of claims 1 to 26, at least one tank (410) containing the first substance, said at least one tank being connected to said at least one engine.

28. Propulsion device according to the preceding claim, further comprising at least one valve (406) controlling the supply of the first substance to said at least one motor.

29. Propulsion device according to claim 28, wherein a filter (418) is positioned near said at least one valve.

30. Propulsion device according to any one of claims 27 to 29, comprising a plurality of motors (404).

31. Propulsion device according to the preceding claim, which comprises a plurality of tanks containing the first substance, each engine being connected to at least one tank.

32. Propulsion device according to any one of claims 30 to 31, which includes a controller (412) capable of independently controlling the motors.

33. Propulsion device according to any one of claims 30 to 32, which includes at least one valve for each motor.

34. Spacecraft (500) comprising an engine (1) according to any one of claims 1 to 26 or a propulsion device (400) according to any one of claims 27 to 33.

35. Method of manufacturing a spacecraft engine (1) comprising an injection system (2) for a first substance, the injection system comprising an injection element (5) carrying the first substance, a decomposition chamber (8) and a nozzle (6) for converting thermal energy into propulsion energy, wherein the method comprises the following steps: a step of positioning a retaining element (14) in the decomposition chamber near the nozzle, a step of welding the retaining element to hold the retaining element in the decomposition chamber, a step of filling the decomposition chamber with a second substance to near an opening in the decomposition chamber for assembling the decomposition chamber with the injection system, a step of introducing an injection plate (12) into the decomposition chamber,a step of positioning a connection interface of the injection system at the opening of the decomposition chamber, in order to assemble the injection system with the decomposition chamber, and a step of welding the connection interface of the injection system and the decomposition chamber.

36. Manufacturing method according to the preceding claim, wherein the welding step of the connection interface of the injection system and the decomposition chamber comprises a transparent weld.

37. Manufacturing method according to any one of claims 35 to 36, wherein the decomposition chamber includes a shoulder (32), the step of introducing the injection plate into the decomposition chamber including a step of positioning the injection plate element at the shoulder.

38. A manufacturing method according to any one of claims 35 to 37, further comprising a step of welding a reducing element having a through hole with a diameter smaller than the diameter of the outlet (17) of the injection element, to the injection element.

39. A manufacturing method according to the preceding claim, wherein a filter is positioned between the end of the outlet (17) of the injection element and the reducing element before welding the reducing element.

40. Manufacturing method according to any one of claims 35 to 39, wherein the welding step of the reducing element includes a through-weld.

41. A manufacturing method according to any one of claims 35 to 40, wherein the decomposition chamber and the nozzle are manufactured to form a single piece.

42. A manufacturing method according to any one of claims 35 to 41, wherein the method further comprises a step of positioning a heating element on the decomposition chamber.

Images