Compact solid-fuel propulsion system

Abstract

The invention relates to a propulsion system (1) which is capable of generating a modular thrust, the propulsion system (1) comprising a body (10) which encloses a combustion chamber (8) in communication with at least one nozzle or propulsion valve (6) situated outside the body (10), the body (10) further enclosing a solid-fuel gas generator (9) which is configured to generate gases in the combustion chamber (8), wherein the gas generator (9) comprises a plurality of unit modules (5) which can be ignited independently by at least one combustion triggering device (40) and are separated from one another by a thermal insulator (30), the unit modules (5) being housed inside the body (10) and these unit modules (5) extending along the axis (A) while being distributed around the axis (A).

Description

Description Title of the invention: Compact solid fuel propulsion system Technical Field

[0001] The present invention relates to the field of propulsion systems comprising a solid fuel gas generator. Previous technique

[0002] The use of solid fuel gas generators for engine propulsion systems is well known.

[0003] Such a solid fuel gas generator typically comprises a combustion triggering device and a solid fuel block. The combustion triggering device initiates the combustion of the solid fuel block, generating a large quantity of gas. The generated gas is then channeled, directed, and ejected through nozzles or propulsion valves to propel the engine.

[0004] However, such propulsion systems lack flexibility in solid fuel management. Indeed, these propulsion systems are poorly suited when alternating between standby phases, low-speed combustion phases, and active phases.

[0005] To address these drawbacks, document EP 1 972 775 B1 proposes a propulsion system comprising several pyrotechnic charges that can be ignited independently of each other. Specifically, document EP 1 972 775 B1 proposes placing a plurality of pyrotechnic holding charges outside the body of the propulsion system. Each pyrotechnic holding charge is connected to an ignition means.

[0006] However, such a system is bulky and the ignition means are poorly protected. Description of the invention

[0007] The present invention aims to remedy the aforementioned drawbacks by proposing a compact propulsion system capable of delivering adjustable thrust.

[0008] To this end, the invention proposes a propulsion system capable of generating modular thrust, the propulsion system comprising a body extending along an axis which contains a combustion chamber in communication with at least one nozzle or propulsion valve located outside the body, the body further containing a solid fuel gas generator configured to generate gases in the combustion chamber, the gas generator comprising at least one combustion triggering device, the gas generator comprising a plurality of unit modules independently ignitable by said at least one combustion triggering device and separated from each other by thermal insulation, the unit modules being housed in a support structure positioned inside the body and these unit modules extending along the axis and being distributed around said axis.

[0009] Thus, the presence of several independently ignitable unit modules allows for modulation of the thrust generated by the gas generator. The propulsion system can therefore be used in several different modes by varying the number of unit modules ignited over time. This makes it possible, in particular, to achieve several phases of high thrust separated by periods of inactivity or lower thrust (so-called "multipulse" operation). Furthermore, such an architecture has the advantage of being particularly compact.

[0010] According to a particular aspect of the invention, each unit module comprises at least a first stage comprising at least one solid fuel block and a second stage adjacent to the first stage comprising an energy amplifier means, the second stages of the unit modules being connected to the combustion triggering device(s).

[0011] The energy amplifier medium makes it easier to ignite the solid fuel block by increasing heating.

[0012] The energy-amplifying device can be non-flammable. Thus, the energy-amplifying device can include a heating element, such as an electrical resistor. Such an energy-amplifying device has the advantage of being inexpensive and easy to implement.

[0013] The energy amplifier is preferably flammable. Thus, the energy amplifier can be formed from flammable pellets or from a monolithic flammable pyrotechnic block. A flammable energy amplifier generates a flow of hot gas, ensuring uniform heating of the fuel block. Such energy amplifiers also have the advantage of being compact, easy to integrate, and reliable.

[0014] In particular, the flammable pellets act as a relay charge. They amplify the heat flux of the initiation chain to facilitate the ignition of the solid fuel block.

[0015] According to a particular aspect of the invention, a first grid is interposed between the second stage of the unit modules and the combustion chamber. Such a first grid limits the passage of unwanted particles or waste into the combustion chamber.

[0016] According to a particular aspect of the invention, a second grid separates the first floor from the second floor of the unit modules.

[0017] In particular, according to a particular aspect of the invention, the flammable pellets are present in a defined volume between a first grid and a second grid, the first grid being interposed between the flammable pellets and the combustion chamber and the second grid separating the first stage from the second stage of the unit modules.

[0018] The grids help to retain the flammable pellets and limit the passage of unwanted particles or waste into the combustion chamber.

[0019] According to a particular aspect of the invention, each unit module is separated from the combustion chamber by an insulating flap configured to rupture when the unit module is in combustion.

[0020] Such an insulating seal helps limit the risk of unwanted ignition of a single module due to the hot gas present in the combustion chamber. Its rupture then allows the gases generated by the single module to escape.

[0021] According to a particular aspect of the invention, the gas generator comprises at least one passage channel extending along the axial direction, preferably along the axis, between the unit modules, the passage channel being surrounded by the thermal insulation, the passage channel housing the combustion triggering device.

[0022] Such a configuration is particularly compact while still providing significant protection for the combustion triggering device.

[0023] According to a particular aspect of the invention, the gas generator further comprises an electrical system configured to power the combustion triggering device(s), the electrical system being located opposite the combustion chamber along the axis.

[0024] Thus, the electrical system is protected from hot gases, and the gas generator can be integrated as close as possible to the internal walls of the body.

[0025] According to one particular aspect of the invention, the propulsion system comprises a plurality of propulsion valves. The propulsion system may also comprise a plurality of nozzles.

[0026] Thus, the directional control of the vehicle enabled by the propulsion system is improved.

[0027] The invention also relates to a method of directional control of a machine comprising a propulsion system as described above, the method comprising the ejection of gases generated by the gas generator through the propulsion nozzle(s) or valve(s) oriented in a determined manner to obtain thrust in the desired direction.

[0028] According to a particular aspect of the invention, said method makes it possible to control the altitude of the craft.

[0029] According to a particular aspect of the invention, the method comprises a first push phase in which a first part of the unit modules is lit and a second push phase in which a second part of the unit modules different from the first part is lit, the second part of the unit modules being lit after the first part. Brief description of the drawings

[0030] [Fig. 1] Figure 1 is a schematic exploded perspective view of an example of a propulsion system according to the invention.

[0031] [Fig. 2] Figure 2 is a schematic cross-sectional view of the propulsion system of Figure 1.

[0032] [Fig. 3] Figure 3 is a graph illustrating the thrust generated during the ignition of all solid fuel blocks.

[0033] [Fig. 4] Figure 4 is a graphic illustrating the thrust generated when solid fuel blocks are ignited in series.

[0034] [Fig. 5] Figure 5 is a graphic illustrating the thrust generated when solid fuel blocks are ignited in series with inactive phases. Description of the implementation methods

[0035] Figures 1 and 2 illustrate an example of propulsion system 1. Propulsion system 1 is capable of generating modular thrust.

[0036] The propulsion system 1 comprises a body 10. The body 10 extends axially along an axial direction DA. The body 10 extends radially along a radial direction DR. The body 10 may have a circular or elliptical cross-section. The body 10 extends about an axis A. The axis A defines the axial direction DA. The axis A is preferably located at the center of the body 10. The axis A may correspond to a common line between several planes of symmetry of the body 10. The body 10 may have a shape of revolution about the axis A. The body 10 may have a dome shape.

[0037] The propulsion system 1 includes at least one nozzle or propulsion valve 6. Preferably, in order to improve the directional control of the system The propulsion system comprises a plurality of propulsion valves 6 or a plurality of nozzles. The nozzle(s) or propulsion valve(s) 6 are preferably steerable. In the example illustrated in Figures 1 and 2, the propulsion system 1 comprises six propulsion valves 6. The nozzle(s) or propulsion valve(s) 6 are located outside the body 10. The nozzle(s) or propulsion valve(s) 6 may extend from one of the axial ends of the body 10, as illustrated in Figures 1 and 2. The opening area of ​​the nozzle(s) or propulsion valve(s) 6 is controllable. The nozzle(s) or propulsion valve(s) 6 may be controlled in an "on / off" mode, in which the nozzle(s) or propulsion valve 6 is either fully open or fully closed. The nozzle(s) or propulsion valve(s) 6 may also be controlled in a proportional mode, in which the opening of the nozzle(s) or propulsion valve 6 varies.In particular, in proportional mode, the propulsion nozzle or valve 6 may have one or more intermediate opening positions between the fully open and fully closed positions. The propulsion nozzles or valves 6 may be controlled by an electropneumatic device. The propulsion nozzles or valves 6 may also be controlled by a hydraulic device. The propulsion nozzles or valves 6 may be configured to allow the propulsion system 1 to move along three perpendicular axes.

[0038] The body 10 contains a combustion chamber 8. The nozzle(s) or propulsion valve(s) 6 are in communication with the combustion chamber 8. The body 10 may contain a single combustion chamber 8.

[0039] The body 10 further contains a solid fuel gas generator 9. The gas generator 9 is configured to generate gases in the combustion chamber 8. The gas generator 9 is adjacent to the combustion chamber 8 and offset from it along the axial direction DA OR along axis A. The gas generator 9 can extend along the radial direction DR over substantially the entire cross-section of the body 10. Thus, the gas generator 9 can be in contact with the internal walls of the body 10. The gas generator 9 can be located on the side of a second axial end of the body 10 that is opposite the first axial end on which the Nozzles or valves 6 are present. The gas generator 9 can be located on the side of the second axial bottom which defines a base of the dome.

[0040] The propulsion system 1 may include a spacer 80 configured to axially fix the gas generator 9 within the body 10. The spacer 80 allows the axial positioning of the gas generator 9 within the body 10 to be adapted according to the length of the solid fuel blocks 20 used. Indeed, the length of the solid fuel blocks 20 used depends on the mission that the vehicle equipped with the propulsion system 1 will perform. The spacer 80 extends radially over the entire cross-section of the body 10. The spacer 80 may be in the shape of a disc, a cylinder, or a truncated cone. The gas generator 9 may be located between the spacer 80 and the combustion chamber 8. The spacer 80 may be located on the side of the second axial end.

[0041] The gas generator 9 comprises a plurality of unit modules 5. The unit modules 5 may have an elongated shape extending along the axial direction DA. The unit modules 5 are distributed around the axis A. The unit modules 5 may be offset from the axis A with respect to the radial direction DR (not located on the axis A) and are situated around it. The gas generator 9 may comprise at least four, for example at least eight, unit modules 5 housed within the body 10. The number of unit modules 5 depends on the mission to be performed by the vehicle equipped with the propulsion system and the dimensions of said vehicle.

[0042] The unit modules 5 extend along the axial direction DA between a front face 5a and a rear face 5b. The front face 5a and the rear face 5b of the unit modules 5 may be perpendicular to the axis A. The front face 5a and the rear face 5b of the unit modules 5 are connected by one or more lateral faces 5c. The front face 5a of the unit modules 5 faces the combustion chamber 8. The rear face 5b of the unit modules 5 may be in contact with the wedge 80. The unit modules 5 may have a cylindrical shape of revolution, as illustrated in Figures 1 and 2. The unit modules 5 then take the form of bars. Such a cylindrical shape of revolution is preferred to ensure a constant and controlled gas flow for a given pressure. Such a cylindrical shape of revolution also facilitates the manufacturing. The unit modules 5 may also have a frustoconical shape. Of course, this does not depart from the scope of the invention if the unit modules 5 have other shapes. The unit modules 5 are offset along the radial direction DR. A single plane transverse to axis A intersects several unit modules 5.

[0043] Preferably, to simplify the design, all unit modules 5 are identical. However, the unit modules 5 may have different shapes and / or dimensions, for example to adapt to geometric constraints for the layout in the propulsion system 1 and / or to adapt to the desired thrust profile.

[0044] The five individual modules are separated from each other by a thermal insulator 30. Thus, the lateral faces 5c of the individual modules 5 can be covered by the thermal insulator 30. The thermal insulator 30 can be a pourable varnish. The thermal insulator 30 can contain polyurethane.

[0045] The unit modules 5 are housed within a retaining structure. The retaining structure holds the unit modules 5 in a predetermined position. The retaining structure is located within the body 10. The retaining structure may be in contact with the internal walls of the body 10. The retaining structure acts as reinforcement. The retaining structure defines a plurality of cavities that accommodate the unit modules 5. Thus, the unit modules 5 are positioned within the cavities of the retaining structure. Preferably, each cavity accommodates a single unit module 5. A space may be defined between the internal walls of the cavities of the retaining structure and the unit modules 5, this space being filled by thermal insulation 30. Thermal insulation 30 may also be present between the cavities of the retaining structure. The retaining structure may be made of metal.The support structure can also be made of an insulating material. Thermal insulation 30 can form the support structure.

[0046] Each unit module 5 comprises at least one solid fuel block 20. Each unit module 5 may comprise a single solid fuel block 20, as illustrated in Figures 1 and 2. The solid fuel block may conventionally, propellant is included. The unit modules 5 can include fuel blocks with different compositions to adapt to the desired thrust profile. Thus, a first unit module 5 of the propulsion system 1 can include a solid fuel block 20 with a first composition, and a second unit module 5 of the propulsion system 1 can include a solid fuel block 20 with a second composition different from the first.

[0047] The solid fuel blocks 20 extend along the axial direction DA between a front face 20a and a rear face 20b. The front face 20a and the rear face 20b of the solid fuel blocks 20 may be perpendicular to the axis A. The front face 20a and the rear face 20b of the solid fuel blocks 20 are connected by one or more lateral faces 20c. The solid fuel blocks 20 are configured to be ignited from their front face 20a. The solid fuel blocks 20 may have a cylindrical shape of revolution, as illustrated in Figures 1 and 2. The solid fuel blocks 20 are then in the form of bars. Such a cylindrical shape of revolution is preferred to ensure a constant and controlled gas flow at a given pressure. This cylindrical shape also facilitates manufacturing. The solid fuel blocks 20 may also have a frustoconical shape.The invention remains within the scope of this invention even if the solid fuel blocks 20 have other shapes. The solid fuel blocks 20 are offset along the radial direction DR. A single plane transverse to axis A intersects several solid fuel blocks 20. All of the unit modules 5, or solid fuel blocks 20, can be located inside the body 10.

[0048] Preferably, to simplify the design, all solid fuel blocks 20 are identical. However, the solid fuel blocks 20 may have different shapes and / or dimensions, for example to adapt to geometric constraints for fitting in the propulsion system 1 and / or to adapt to the desired thrust profile.

[0049] The rear face 20b of the solid fuel blocks 20 can form the rear face 5b of the unit modules 5. The side faces 20c of the fuel blocks The solid fuel blocks 20 can define, at least in part, the lateral faces 5c of the unit modules 5. Thus, the lateral faces 20c of the solid fuel blocks 20 can be covered by the thermal insulation 30. The solid fuel blocks 20 are separated from each other by the thermal insulation 30. The lateral faces 20c of the solid fuel blocks 20 can be in direct contact with the thermal insulation 30.

[0050] The gas generator 9 further includes one or more combustion triggering devices 40. The combustion triggering device(s) 40 are configured to ignite the unit modules 5. The combustion triggering device(s) 40 may be configured to ignite the unit modules 5 by means of an electrical signal. The combustion triggering device(s) 40 may include a plurality of branches. Each branch is configured to ignite a single unit module 5. Each unit module 5 is connected to a combustion triggering device 40. In particular, each unit module 5 is connected to a branch of a combustion triggering device 40.

[0051] For example, the combustion triggering device 40 shown in Figure 2 comprises six branches, each branch serving a unit module 5 adjacent to the illustrated combustion triggering device 40. In the example shown in Figure 2, the two unit modules 5 closest to axis A are served by the illustrated combustion triggering device 40, and the two unit modules 5 furthest from axis A can each be served by a combustion triggering device 40 not present in the cross-sectional plane shown in Figure 2. In one alternative, all the unit modules 5 can be served by the same combustion triggering device 40.

[0052] The gas generator 9 includes at least one flow channel 90 configured to accommodate a combustion triggering device 40. The flow channel(s) 90 extend along the axial direction DA. The flow channel(s) 90 extend between the unit modules 5. The flow channel(s) 90 are thermally insulated from the combustion chamber 8. The flow channel(s) 90 are separated from the solid fuel blocks 20 by the thermal insulation 30. Thus, the passage channel(s) 90 are thermally insulated by the thermal insulation 30. Thus, the passage channel 90 is away from the walls of the body 10 and can serve several unit modules 5. Each passage channel 90 preferably serves at least two unit modules 5. The passage channel 90 illustrated in figure 2, for example, serves six unit modules 5. The passage channel(s) 90 are made in the support structure.

[0053] The passage channel(s) 90 are preferably distributed so as to serve all the unit modules 5 while limiting the number of passage channels 90 required. Preferably, at least one passage channel 90 extends along axis A. At least one passage channel 90 may be located on axis A. Thus, the passage channel 90 is located at the center of the body 10 and is therefore capable of serving a very large number of unit modules 5. This configuration is particularly suitable when a single combustion triggering device 40 serves all the unit modules 5.

[0054] The gas generator 9 further includes an electrical system (not shown) configured to power the combustion triggering device(s) 40, which is located at the rear of the gas generator 9 along the axial direction DA. Thus, the electrical system is separated from the combustion chamber 8 by the unit modules 5 and by the thermal insulation 30.

[0055] Thus, the combustion triggering device(s) 40 and the corresponding electrical system are properly protected while allowing a compact configuration of the gas generator 9.

[0056] Each unit module 5 may include an insulating lid 70. The insulating cover 7 separates the unit module 5 from the combustion chamber 8. The insulating covers 70 are configured to rupture when the associated unit module 5 is in combustion. The insulating covers 70 form the front face 5a of the unit modules 5. The insulating covers 70 can advantageously be made of silicone elastomer.

[0057] According to a particular embodiment, the unit modules 5 may comprise a first floor and a second floor. The first floor and the The second stage of the unit modules 5 is superimposed along the axial direction DA. The first stage comprises the solid fuel block(s) 20. The second stage may include an energy amplifier means 50. The combustion triggering device(s) 40 are connected to the second stage of the unit modules 5, as illustrated in Figure 2. Thus, the energy amplifier means is configured to ignite or facilitate the ignition of the solid fuel blocks 20 when they are activated. The second stage of the unit modules 5 is interposed between the combustion chamber 8 and the first stage of the unit modules 5 along the axial direction DA.

[0058] The energy amplifier may be non-flammable. Thus, the energy amplifier may include a heating element, such as an electrical resistor. The energy amplifier is then configured to heat by Joule heating when activated.

[0059] The energy amplifier is preferably flammable. Thus, the energy amplifier can be formed from flammable pellets or from a monolithic flammable pyrotechnic block. A flammable energy amplifier generates a flow of hot gas, ensuring uniform heating of the fuel block.

[0060] Flammable pellets 50 comprise a pyrotechnic composition, for example one or more compressed aluminum and potassium perchlorate powders.

[0061] The monolithic flammable block comprises a pyrotechnic composition, for example one or more compressed aluminum and potassium perchlorate powders.

[0062] The unit modules 5 may include a first grid 61 interposed between the combustion chamber 8 and the second stage. The unit modules 5 may include a second grid 62 interposed between the first stage and the second stage. The first grid 61 extends between the lateral face(s) 5c of the unit module 5. The second grid 62 extends between the lateral face(s) 5c of the unit module 5. The first grid 61 may be in contact with the insulating cover 70 if present. The second grid 62 may be in contact with the front face 20a of the solid fuel block 20.

[0063] In the case where flammable pellets 50 are used as an energy amplifier, they can be held in a cage. The cage can be formed by the first grid 61 and the second grid 62. The flammable pellets 50 are located between the first grid 61 and the second grid 62. The first grid 61 is interposed between the flammable pellets 50 and the combustion chamber 8. The second grid 62 is interposed between the flammable pellets 50 and the solid fuel block 20.

[0064] The first grid, 61, can be made of metal. The second grid, 62, can be made of metal.

[0065] The propulsion system as described above is configured to propel a vehicle. The vehicle could, for example, be an endo-atmospheric or exo-atmospheric glider, such as a hypersonic glider. The vehicle could also be a missile or an interceptor. It could also be a launch vehicle.

[0066] The propulsion system as described above can be configured to provide directional control or trajectory control of the craft comprising said propulsion system. Thus, the invention also relates to a method for directional control of a craft comprising the propulsion system as described above. Such a method includes the ejection of gases generated by the gas generator 9 through propulsion nozzles or valves 6 oriented in a specific manner to obtain thrust in the desired direction. In particular, the propulsion system as described above can be configured to provide altitude control of the craft comprising said propulsion system.

[0067] In general, the propulsion system as described above can have at least a first thrust phase and a second thrust phase. A first set of the five unit modules is ignited during the first thrust phase. A second set of the five unit modules, different from the first set, is ignited during the second thrust phase. A phase The boost phase is characterized by the number of unit modules 5 that are lit. A boost phase may involve the lighting of a single unit module 5. Conversely, a boost phase may involve the simultaneous lighting of several unit modules 5.

[0068] In particular, the propulsion system as described above can have several modes of operation. These modes of operation may include one or more different thrust phases.

[0069] The propulsion system as described above can exhibit, in particular, a first mode of operation illustrated in Figure 3. In this first mode of operation, all five unit modules are activated to generate a very powerful thrust. Thus, the first mode of operation comprises a single thrust phase.

[0070] The propulsion system as described above can also have a second operating mode, illustrated in Figure 4. In this second operating mode, the five unit modules are ignited sequentially to continuously generate thrust. The ignition of the five unit modules can be performed at regular intervals, as shown in Figure 4, or at irregular intervals. This mode extends the operating time of the propulsion system. Thus, the second operating mode comprises multiple thrust phases. In the example shown in Figure 4, all thrust phases have the same maximum power output. Of course, the second operating mode remains valid even if the thrust phases have different maximum power outputs. This is the case, for example, when the five unit modules have different dimensions or solid fuel blocks of different compositions.

[0071] The propulsion system as described above can also have a third operating mode, illustrated in Figure 5. In this third operating mode, the five unit modules are ignited sequentially, with the next unit module igniting only after the previous one has extinguished. The unit modules can be ignited at regular or irregular intervals, as shown in Figure 5. This mode allows for This extends the operating time of the propulsion system. Such a mode also allows for inactive phases during which no unit module 5 is activated. Thus, the third operating mode comprises a plurality of thrust phases. In the example illustrated in Figure 5, all thrust phases have the same maximum power. Of course, this does not deviate from the third operating mode if the thrust phases have different maximum power outputs. This is the case, for example, when the unit modules 5 have different dimensions or solid fuel blocks of different compositions.

Claims

Demands

1. Propulsion system (1) capable of generating modular thrust, the propulsion system (1) comprising a body (10) extending along an axis (A) which encloses a combustion chamber (8) in communication with at least one nozzle or propulsion valve (6) located outside the body (10), the axis (A) defining an axial direction (DA), the body (10) further enclosing a solid fuel gas generator (9) configured to generate gases in the combustion chamber (8), the gas generator (9) comprising at least one combustion triggering device (40), the gas generator (9) comprising a plurality of unit modules (5) independently ignitable by said at least one combustion triggering device (40) and separated from each other by a thermal insulator (30),the unit modules (5) being housed in a support structure positioned inside the body (10) and these unit modules (5) extending along the axis (A) and being distributed around said axis (A), the gas generator (9) comprising at least one passage channel (90) extending along the axial direction (DA) between the unit modules (5), the passage channel (90) being surrounded by the thermal insulation (30), the passage channel (90) housing the combustion triggering device (40).

2. Propulsion system (1) according to claim 1, wherein each unit module (5) comprises at least one first stage comprising at least one solid fuel block (20) and a second stage adjacent to the first stage comprising an energy amplifier means (50), the second stages of the unit modules (5) being connected to the combustion triggering device(s) (40).

3. Propulsion system (1) according to claim 2, wherein a first grid (61) is interposed between the second stage of the unit modules (5) and the combustion chamber (8).

4. Propulsion system (1) according to claim 2 or 3, wherein the energy-amplifying means is formed by a plurality of flammable pellets (50) or by a monolithic flammable block.

5. Propulsion system (1) according to claim 4, wherein a second grid (2) separates the first stage from the second stage of the unitary modules (5).

6. Propulsion system (1) according to any one of claims 1 to 5, wherein each unit module (5) is separated from the combustion chamber (8) by an insulating cover (70) configured to rupture when the unit module (5) is in combustion.

7. Propulsion system (1) according to any one of claims 1 to 6, wherein said at least one passage channel (90) extends along the axis (A).

8. Propulsion system (1) according to any one of claims 1 to 7, wherein the gas generator (9) further comprises an electrical system configured to power the combustion triggering device(s) (40), the electrical system being located opposite the combustion chamber (8) along axis (A).

9. Propulsion system (1) according to any one of claims 1 to 8, the propulsion system (1) comprising a plurality of propulsion nozzles or valves (6).

10. Method of directional control of a machine comprising a propulsion system (1) according to any one of claims 1 to 9, the method comprising the ejection of gases generated by the gas generator (9) through the propulsion nozzle(s) or valve(s) (6) oriented in a determined manner to obtain thrust in the desired direction.

11. Directional control method according to claim 10, said method enabling control of the altitude of the craft.

12. Directional control method according to claim 10 or 11, wherein the method comprises a first push phase in which a first part of the unit modules (5) is lit and a second push phase in which a second part of the unit modules (5) different from the first part is lit, the second part of the unit modules being lit after the first part.

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