SPACECRAFT ENGINE

Abstract

The invention relates to 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) 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 includes at least one through hole (36) allowing the first substance from the injection system to pass into the decomposition chamber, so as to allow 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 (38) in the retaining element to reach the nozzle and create propulsion energy. Abbreviated figure: Figure 1.

Description

Title of the invention: SPACECRAFT ENGINE technical field

[0001] 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 method of manufacture.

[0002] Context

[0003] Spacecraft propulsion systems are used to move the spacecraft, for example by expelling a propellant from a nozzle. The propellant provides the thrust necessary to move the spacecraft, for example during takeoff (from the ground to space) or movement in space or in orbit, for example in low Earth orbit (LEO) or geostationary orbit (GEO).

[0004] Since every additional gram added to a spacecraft requires additional force to lift the craft from the ground into space under the sole action of the spacecraft's propulsion system, it is necessary to provide more efficient propulsion systems. A more efficient engine, and therefore a more efficient propulsion device, can compensate for the additional weight by converting more energy into useful work to lift the spacecraft.

[0005] One of the objectives of this disclosure is to improve upon prior art engines.

[0006] Certain aspects and embodiments of the invention relate to an engine for a spacecraft, a propulsion device, a spacecraft and a manufacturing method.

[0007] 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, 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 comprises at least one through-hole allowing the first substance from the injection system to pass into the decomposition chamber, so as to allow 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.

[0008] The engine advantageously provides a means of storing and retaining a second substance before using it in the engine. Thus, the second substance can be separated from the first until the engine needs energy to propel itself.

[0009] The injection system may further include a flow homogenization chamber for the first substance located between the injection element and the injection plate.

[0010] The homogenization chamber for the first substance 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.

[0011] Said at least one hole in the injection plate may be perpendicular to the surface of the injection plate.

[0012] 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.

[0013] Said at least one hole in the injection plate may have an oblique angle with respect to the surface of the injection plate.

[0014] 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 which is not substantially aligned with the nozzle, which promotes the mixing of the first and second substances during use.

[0015] The injection plate may include a plurality of through holes.

[0016] By providing several through holes, it is possible to increase the flow rate of the first substance in the decomposition chamber during use.

[0017] 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.

[0018] By providing 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.

[0019] 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.

[0020] The arrangement of through holes around an outer peripheral annular area of ​​the injection plate can promote the mixing of the first substance with the second substance during use.

[0021] At least one through hole in the retaining element may be perpendicular to the surface of the retaining element.

[0022] 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.

[0023] At least one through hole in the retaining element may have an oblique angle with respect to the surface of the retaining element.

[0024] 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.

[0025] The retaining element may be provided with a plurality of through holes.

[0026] By providing several through holes, it is possible to limit the pressure losses of the reaction product exiting the decomposition chamber during use.

[0027] 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.

[0028] By providing holes of different diameters, the flow can be adapted to specific locations through the retaining element.

[0029] 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.

[0030] Homogenizing the flow can promote stable flow in the nozzle during use.

[0031] The post-retained chamber may have a shape converging towards the nozzle.

[0032] By having a convergent shape, the flow is concentrated towards the nozzle.

[0033] 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.

[0034] The presence of such a reducing element makes it possible to increase the flow velocity due to the restricted diameter of the orifice.

[0035] A filter can be positioned at the end of the injection element, before the reducing element.

[0036] Placing the filter before the reduction element reduces the probability that the reduction element or any other downstream component will become clogged during use.

[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 that occurs in the decomposition chamber.

[0039] The decomposition chamber may further include a cooling means, optionally, the cooling means may be located on the outer periphery of the decomposition chamber.

[0040] Cooling means can help to keep the decomposition chamber cold and within a temperature range best suited to the reaction that takes place in the decomposition chamber.

[0041] The cooling means may include several heat dissipation fins.

[0042] By using heat dissipation fins, the decomposition chamber can be passively cooled by thermal radiation without the need for active cooling.

[0043] The post-retention chamber may further include a pressure sensor capable of measuring the pressure in the post-retention chamber.

[0044] The presence of a pressure sensor at this location allows the reaction to be monitored.

[0045] The injection system may further include a heat dissipation means suitable for cooling the injection element.

[0046] The heat dissipation means can conduct heat away from the injection system to keep it cool.

[0047] The injection system may further include a means for attaching the engine to a spacecraft.

[0048] By providing a means of heat dissipation with the means of attaching the engine to a spacecraft, the heat dissipation means can fulfill more than one function and, consequently, reduce the total number of engine components, thus reducing the need for additional components that can add weight to the whole system.

[0049] The first substance may include hydrogen peroxide (H2O2).

[0050] The second substance can be a catalyst.

[0051] The catalyst may comprise alumina.

[0052] The catalyst may comprise at least one of the metals from platinum, silver and niobium.

[0053] The second substance may be in the form of granules.

[0054] The use of a granular catalyst makes it possible to obtain a porous medium which promotes the exchange between the first substance and the second substance. This increases the reaction surface area.

[0055] The goal is also achieved by a propulsion device for a spacecraft comprising at least one engine according to one of the embodiments described above, at least one tank containing the first substance, said at least one tank being connected to said at least one engine.

[0056] The propulsion device has all the advantages of the engine it comprises.

[0057] The propulsion device may further include at least one valve controlling the supply of the first substance of said at least one engine.

[0058] The presence of a valve allows the flow of the first substance to be controlled, restricted or stopped as needed.

[0059] A filter can be positioned near said at least one valve.

[0060] The propulsion device may include a plurality of motors.

[0061] The addition of additional engines makes it possible to increase the thrust of the propulsion device.

[0062] In this case, the propulsion device may include a plurality of tanks containing the first substance, each engine being able to be connected to at least one tank.

[0063] The propulsion device may include a controller capable of controlling the motors independently.

[0064] 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.

[0065] The propulsion device may include at least one valve for each motor.

[0066] By providing one valve per motor, each motor can be operated independently of the other.

[0067] 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.

[0068] Advantageously, the spacecraft benefits from the propulsion device and / or engine it includes.

[0069] The invention also relates to a method for manufacturing a spacecraft engine comprising a system for injecting a first substance, the system The injection method comprises an injection element transporting the first substance, a decomposition chamber and a nozzle for converting thermal energy into propulsion energy; the method includes the following steps: - a step involving the positioning of a retaining element in the decomposition chamber near the nozzle, - a welding step of the retaining element to hold the retaining element in the decomposition chamber, - a step of filling the decomposition chamber with a second substance until it is close to an opening in the decomposition chamber that will allow the decomposition chamber to be assembled with the injection system, - a step involving the introduction of 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 welding step of the connection interface of the injection system and the decomposition chamber.

[0070] The use of such a method makes it possible to encapsulate the second substance during the manufacture of an engine.

[0071] The welding step of the connection interface of the injection system and the decomposition chamber may include a transparent weld.

[0072] The decomposition chamber may include a shoulder, the step of introducing the injection plate into the decomposition chamber then including a step of positioning the element of the injection plate at the shoulder.

[0073] The method may further include a step of welding a reducing element having a through hole whose diameter is less than the diameter of the outlet of the injection element, with the injection element.

[0074] A filter can be positioned between the end of the outlet of the injection element and the reducing element before the welding of the reducing element.

[0075] The welding step of the reducing element may include a transparent weld.

[0076] The decomposition chamber and the nozzle can be manufactured to form a single piece.

[0077] The method may further include a step of positioning a heating element on the decomposition chamber.

[0078] Brief description of the different drawings

[0079] One or more embodiments of the disclosure will now be described, by way of example only, with reference to the figures in the drawings accompanying this document, in which:

[0080] Figure 1 illustrates an engine for a spacecraft according to one embodiment of the disclosure.

[0081] Fig. 2 illustrates the engine of Fig. 1 in cross-section to show the internal components of the engine.

[0082] Fig. 3 illustrates the engine of Fig. 1 in an exploded view with some engine components removed.

[0083] The [Fig.4] is a schematic diagram of a propulsion device which includes one or more motors of the [Fig.1] according to an embodiment of the disclosure.

[0084] [Fig.5] is a schematic illustration of a spacecraft comprising the engine and / or propulsion device according to one embodiment of the disclosure.

[0085] Fig. 6 is a flowchart that describes a number of manufacturing steps for an engine for a spacecraft. detailed description

[0086] An engine 1 for a spacecraft 500, a propulsion device 400, a spacecraft 500 and a manufacturing method 600 will be described with reference to FIGs. 1 to 6. The engine 1 may be part of a propulsion device 400 and / or a spacecraft 500, as will be described in more detail below.

[0087] The engine 1 is shown in [Fig. 1], [Fig. 2], and [Fig. 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 transforms thermal (or chemical) energy into kinetic energy, and thus into propulsion energy.

[0088] 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].

[0089] The injection element 5 can be connected, for example at one end, to a fastening 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.

[0090] In the example of [Fig. 1], the fastening means 3 may consist, in particular, of a fastening element. This is, for example, a plate, in particular a circular plate. However, the plate may be square, circular, rectangular, triangular, hexagonal, or of any other conceivable shape. The fastening means also contributes to heat dissipation.

[0091] 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 source of first substance, as will be described in more detail below. Conduit element 7 is connected to injection element 5.

[0092] The conduit 7 can be a hollow pipe or a hollow cylinder.

[0093] The inlet 9 is in particular arranged on the fixing means 3.

[0094] 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 above.

[0095] 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 a housing of the spacecraft 500. The structure may also be a workbench or a test bench. The fastener may be a bolt, a screw, a quick-release fastener, a self-locking bolt, or any other known fastener.

[0096] Once the fastening means is fixed to a structure, such as a spacecraft, the thrust forces are transmitted to the spacecraft.

[0097] 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.

[0098] 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.

[0099] In the example shown in [Fig.1] and [Fig.2], there are six means of heat dissipation 4, but there may be any number of means of heat dissipation 4 and the example shown is not intended to be limiting. For example, there may be one, two, three, four, five, six, seven, eight, nine or ten supports or any subset or range thereof.

[0100] The heat dissipation means 4 may optionally include a window 30 disposed 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.

[0101] In other arrangements, the injection element 5 and the fastening means 3 may 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.

[0102] The fastening 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 in 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 in the recessed portion 28.

[0103] The filter 18 may be a mesh filter with a mesh size of 5 µm to 50 µm, preferably 25 µm. Instead of a mesh, the filter 18 may be an open foam with an average pore size of 5 µm to 50 µm, preferably an average pore size of 25 µm. The filter 18 is configured to allow fluid to flow through it.

[0104] The filter protects against the upward movement of particles.

[0105] The filter 18 is dimensioned, for example, to be received in the recessed part 28.

[0106] 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, namely a pressure drop, and helps to stabilize the fluid flow and facilitates the calibration of the fluid flow rate.

[0107] 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.

[0108] The filter 18 can be placed in the recessed part 28 and is retained there by the reducing element 26.

[0109] The injection system further comprises an injection plate 12 which has one or more injection orifices 36, the injection orifice 36 being a hole passing 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 in decomposition chamber 8, in particular in volume 20 of the decomposition chamber.

[0110] There may 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.

[0111] The plurality of orifices 36 of the injection plate can 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.

[0112] 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.

[0113] 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 may be conical, the cone transitioning 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.

[0114] One or more sensors may be arranged 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 arranged at the level of 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.

[0115] Returning to [Fig. 1] and [Fig. 2], the decomposition chamber 8 will now be described in more detail. The decomposition chamber 8 is arranged between the plate injection 12 and nozzle 6. The decomposition chamber 8 contains a second substance 20, as described in more detail below.

[0116] The decomposition chamber 8 is substantially cylindrical. However, the decomposition chamber 8 can have any imaginable shape, for example cubic or hexagonal.

[0117] 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.

[0118] 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.

[0119] A side wall of the injection plate 12 is complementary to the shape of the internal wall at the first end of the decomposition chamber.

[0120] 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.

[0121] 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.

[0122] The shoulder of the retaining element 34 is complementary to the shape of the retaining element 14 and preferably annular.

[0123] The retaining element 14 can be a retaining plate but can also take other more complex forms.

[0124] 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.

[0125] 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.

[0126] According to a particular embodiment, the retaining element is entirely perforated with through holes.

[0127] There may be several retaining element orifices 38, for example from two to sixty retaining element orifices 38.

[0128] 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.

[0129] Between the retaining element 14 and the nozzle 6 is a post-retention chamber 42 for homogenizing the flow of said 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-retention 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 close to the retaining element 14 and the second point is adjacent to or close to the inlet orifice of the nozzle 6. The angle of convergence is for example 45° but can be included in particular in a range from 30° to 60°.

[0130] 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 half-angle, for example, of 15°, the angle being notably within a range from 10° to 40°.

[0131] One or more sensors may be arranged in the post-retention chamber 42. 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 arranged at the level of the post-retention chamber 42. 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. 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.

[0132] 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, or around, or at least partially around, the outer periphery of the decomposition chamber 8. The heating element may also be placed in a chamber in the wall of the decomposition chamber 8. The heating element may be used to heat the second substance that is in the decomposition chamber 8 in volume 20.

[0133] The heating element is optional. Indeed, the motor according to the invention allows for cold starting.

[0134] 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. The cooling means may also 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.

[0135] The engine 1 can be part of a monopropellant system. In this case, the first substance can be a fuel source and the second substance is a catalyst capable of decomposing the fuel source.

[0136] 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:

[0137] 2H2O2 2H2O +O2 ... (eq. 1)

[0138] Thus, the decomposition will create at least one reaction product. In the present case, the reaction products include a gaseous mixture made up of water and oxygen.

[0139] The presence of the catalyst increases the reaction rate compared to the reaction without a catalyst.

[0140] The catalyst may comprise 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 (disposed on the surface of the support or dispersed within the support). The support may be alumina.

[0141] The catalyst may 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.

[0142] The products of the reaction of equation 1 are evacuated from the decomposition chamber through the through hole(s) of the retaining element to reach the nozzle 6 and then evacuated to provide propulsion energy, namely the thrust enabling movement.

[0143] 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 engines 404a-404d, it is not intended to be limiting, and there may be any number of engines 1, for example, there may be from 1 to 10 engines 1, from 1 to 5 engines 1, or from 2 to 5 engines 1, or 3 engines 1, or 4 engines 1, or any range or subset thereof.

[0144] The tank 401 contains a source of the first substance, for example when the first substance is H2O2, the tank 401 contains a fluid source of H2O2. The H2O2 can be in gaseous or liquid form.

[0145] According to one embodiment, the reservoir 401 is connected to each of the engines 404a-404d by one or more fluid lines 403.

[0146] Each of the motors 404a-404d may 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 may 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.

[0147] Each of the 404a-404d motors can be equipped with a 410a-410d sensor. The 410a-410d sensors are electrically connected to the controller 412. The 410a-410d sensors are configured to detect one or more parameters of the 404a-404d motor, as described previously.

[0148] Between the tank 401 and the motors 404a-404d, there may be a tank outlet sensor 402. The tank outlet sensor 402 may be configured to detect the pressure, temperature, or other information of the first substance leaving the tank 401. The tank outlet sensor 402 is electrically connected to the controller 412 via an electrical connection 414.

[0149] Between the reservoir 401 and the motors 404a-404d, there may be optional additional filters 418 and valves 416 to provide additional control of the motors 404a-404d. The valves 416 are configured to open, close, or partially open the fluid circuit through which they pass. The valves 416 are connected to the controller 412 by one or more electrical connections 414.

[0150] 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.

[0151] As the discerning reader will see, 414 electrical connections can be configured to transmit power, but also to communicate data in either direction. 414 electrical connections can comprise one or more electrical wires or cables.

[0152] 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.

[0153] The spacecraft 500 will now be described with reference to [Fig. 5]. The spacecraft 500 is shown schematically in [Fig. 5] and includes the engine 1 and / or the propulsion device 400 as described previously.

[0154] 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.

[0155] The manufacturing method 600 will now be described in more detail with reference to [Fig. 6]. [Fig. 6] shows a flowchart describing a number of steps in the manufacturing method for an engine 1 for a spacecraft 500.

[0156] 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:

[0157] First, step 602 includes positioning a retaining element 14 in the decomposition chamber near the nozzle 6.

[0158] Step 604 includes welding the retaining element 14 into the decomposition chamber 8.

[0159] Next, in step 606, the decomposition chamber 8 is filled with the second substance up 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.

[0160] Next, in step 608, the injection plate 12 is introduced into the decomposition chamber 8.

[0161] Next, in step 610, a connection interface of 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.

[0162] 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.

[0163] Optionally, when the step includes a welding step, for example step 604 or 612, the weld can be a through-weld. A 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 to join the two components at a junction not exposed externally.

[0164] When the decomposition chamber 8 includes a shoulder, such as the shoulder of the retaining element 34, the 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.

[0165] 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.

[0166] Optionally, the 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.

[0167] 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.

[0168] The engine components 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 molding process, an additive manufacturing process, a powder metallurgy process, a machining process.

[0169] The motor 1 and any component or element thereof may be made 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 or Inconel 625 or Inconel 617 or Inconel 600.

[0170] 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.

[0171] 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.

[0172] List of drawing elements

[0173] 1 Motor

[0174] 2 Injection system

[0175] 3 Means of attachment

[0176] 4 Heat dissipation means

[0177] 5 Injection element

[0178] 6 Nozzle

[0179] 7 Conduit

[0180] 8 Decomposition chamber

[0181] 10 Through hole

[0182] 11 First sensor

[0183] 13 Second sensor

[0184] 9 Entry

[0185] 12 Injection plate

[0186] 14 Retaining element

[0187] 15 Sensor hole

[0188] 16 Orifice

[0189] 17 Exit

[0190] 18 Filter

[0191] 20 Volume

[0192] 22 First substance flow homogenization chamber

[0193] 26 Reducing element

[0194] 28 Embedded part

[0195] 30 Window

[0196] 32 Injection plate shoulder

[0197] 34 Retaining element shoulder

[0198] 36 Injection plate orifice

[0199] 38 Retaining element orifice

[0200] X Longitudinal axis

[0201] 42 Chamber po st-retenue

[0202] 400 Propulsion device

[0203] 401 Reservoir

[0204] 402 Tank outlet sensor

[0205] 403 Fluid conduit

[0206] 404a Motor

[0207] 404b Motor

[0208] 404c Engine

[0209] 404d Engine

[0210] 406a Control valve

[0211] 406b Control valve

[0212] 406c Control Valve

[0213] 406d Control Valve

[0214] 410a Sensor

[0215] 410b Sensor

[0216] 410c Sensor

[0217] 410d Sensor

[0218] 412 Controller

[0219] 414 Electrical connection

[0220] 416 Valve

[0221] 418a Filter

[0222] 418b Filter

[0223] 418c Filter

[0224] 418d Filter

[0225] 418 Filter

[0226] 420a Calibrated Orifice

[0227] 420b Calibrated Orifice

[0228] 420c Calibrated Orifice

[0229] 420d Calibrated Orifice

[0230] 422 Pressure sensor

[0231] 424 Service valve

[0232] 500 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), wherein - 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 comprises 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 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 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 in the retaining element has a diameter different from at least one other hole in the plurality of through holes in 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 reducing element (26), the reducing 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, wherein 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, wherein 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. Engine 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:

28.

29.

30.

31.

32.

33.

34.

35. - at least one motor (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. A 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. A propulsion device according to claim 28, wherein a filter (418) is positioned near said at least one valve. A propulsion device according to any one of claims 27 to 29, comprising a plurality of motors (404). 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. Propulsion device according to any one of claims 30 to 31, which includes a controller (412) capable of independently controlling the motors. A propulsion device according to any one of claims 30 to 32, comprising at least one valve for each engine. A 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. 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 welding step of the retaining element to hold the retaining element in the decomposition chamber, - a step of filling the decomposition chamber with a second substance until it is close to an opening in the decomposition chamber to allow the assembly of 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 includes a transparent weld.

37. A 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 whose diameter is less than the diameter of the outlet (17) of the injection element, with the injection element.

39. 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. A 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