Aircraft propulsion module and aircraft

Abstract

An aircraft propulsion module, comprising: a hydrogen storage system (9); at least one electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electrical energy; and at least one electric motor (5) electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate a thrust; wherein the propulsion module comprises a first part (1) and a second part (2), each of the first part and the second part comprising a respective fairing (4, 10); the first part and the second part are separable from each other; the first part comprises the at least one electrochemical converter and the at least one electric motor; and the second part comprises a hydrogen storage housing of the hydrogen storage system for storing reusable hydrogen storage units. An aircraft comprising at least one such aircraft propulsion module.

Description

Technical Field

[0001] This invention relates to an aircraft propulsion module comprising: a hydrogen storage system; at least one electrochemical converter connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electrical energy; and at least one electric motor electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust. The invention also relates to an aircraft comprising at least one such propulsion module. The invention further relates to a method of operating such a propulsion module. Background Technology

[0002] In the context of aviation, modules can be defined as airborne equipment anchored to dedicated points on the structure of an aircraft. Primarily used in the military field, these modules can provide various functions, such as expansion of fuel capacity or weapons, and external sensor mounts. In June 2013, this was proposed by the Swiss Federal Institute of Technology in Lausanne (EPFL). In the Clip Air project proposed by Polytechnique Fédéralede Lausanne, modules can even represent independent cabins for transporting passengers.

[0003] It is also known from the prior art to provide an "electric propulsion module" distributed along the wingspan of an aircraft wing, wherein the propulsion module is embedded within the wing structure and only the hydrogen storage is movable. It is also known from the prior art to have a propulsion module in which the wing structure is constructed around a module having a fused fairing.

[0004] WO 2020 / 003181 A1 discloses a pod for a mobile vehicle and also provides a net for interchangeable pods. The pod includes an energy storage and power supply unit and an engine compartment. The engine compartment includes an enclosure for surrounding the energy storage and power supply unit and a coupling structure for attaching the enclosure to the vehicle. The energy storage and power supply unit includes a power generation module, a propulsion module, and an electronics module. The propulsion module includes an electric motor with a propeller module. The electronics module is configured to actuate the power generation module to provide electrical power to the electric motor, wherein the electric motor actuates the propeller module for moving the vehicle. Summary of the Invention

[0005] The object of this invention is to at least partially overcome the problems associated with the prior art. A specific object of this invention is to provide a hydrogen fuel cell electric propulsion aircraft of the type described above, exhibiting improved operational safety.

[0006] This objective is achieved through the subject matter of the independent claims. Advantageous embodiments may be found, for example, in the dependent claims and / or the description.

[0007] This objective is achieved through an aircraft propulsion module, which includes at least:

[0008] - Hydrogen storage system,

[0009] - At least one electrochemical converter, connected to a hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electrical energy, and

[0010] - At least one electric motor, the at least one electric motor being electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust;

[0011] Generally, a movable propulsion module provides an independent, autonomous, and movable component (“module”) for thrust generation, which, in principle, can be adapted to any aircraft. Specifically, the propulsion module is not embedded in the wing or fuselage of the aircraft, but can be added to the aircraft structure, such as a wing, via a simple fastening interface. In particular, the movable propulsion module includes all the components for aircraft propulsion and only needs to be mechanically attached to the aircraft (e.g., via at least one fastening device), and can potentially communicate data with the aircraft (e.g., via wired and / or wireless communication interfaces) to receive data for the operation of the propulsion module and potentially to provide feedback status data, such as fuel level, potential defects, etc.

[0012] Hydrogen storage systems can be adapted to store gaseous, liquid, and / or solid hydrogen. A hydrogen storage system may include at least one hydrogen storage unit for physical storage of hydrogen, such as a hydrogen tank for storing gaseous and / or liquid hydrogen, or specialized materials (e.g., metal hydrides, porous carbon, etc.) for chemical or physical solid hydrogen storage. The hydrogen storage system may also include a housing for at least one hydrogen storage unit. The hydrogen storage system may also include or be connected to at least one piping network dedicated to supplying hydrogen from the hydrogen storage unit to at least one electrochemical converter, and / or at least one piping network that allows for replenishment of external hydrogen on the ground without having to detach the hydrogen storage system from the propulsion module (also known as a "pod").

[0013] In one embodiment, the electrochemical converter includes at least one fuel cell.

[0014] The electric motor is supplied with electrical energy from an electrochemical converter. In one embodiment, the electric motor is connected to at least one propeller or at least one duct fan, or even other propulsion device, and thus drives at least one propeller or at least one duct fan, or even other propulsion device.

[0015] One embodiment of the propulsion module includes at least one other device (“electric load”) for using or storing electrical energy generated by an electrochemical converter. Such an electrical load may, for example, include at least one other electric motor (e.g., for moving a retractable eddy current generator), at least one electric actuator (also an electric motor) of a separation device, at least one electrical or electronic control device, at least one voltage / current converter, at least one valve, at least one electric switch, and / or at least one pump, etc. In one embodiment, the at least one voltage / current converter is a DC / DC converter, an AC / DC converter, and / or a DC / AC converter. The at least one electrical or electronic control device may include at least one control unit or at least one control unit adapted to control the operation of at least one component of the propulsion module, particularly an energy, power, and / or torque management unit, etc. The at least one electrical or electronic control device may include a microcontroller, ASIC, FPGA, and / or a data communication interface, such as an Ethernet interface, etc.

[0016] One embodiment of the propulsion module further includes at least one energy storage unit, which comprises, for example, at least one rechargeable battery and / or at least one supercapacitor (e.g., a gold capacitor). This provides the advantage that at least one electrical load component of the propulsion module can be supplied with power even if the power generated by the electrochemical converter is insufficient (e.g., during peak demand) or malfunctions. This also improves operational safety. In this embodiment, the energy storage unit is electrically connected to the electrochemical converter. This provides the advantage that the energy storage unit can be charged during flight if the power generated by the electrochemical converter is greater than the power used by other components.

[0017] The operation of the propulsion module under normal conditions (i.e., without component failure) may include at least one of the following operational phases:

[0018] - "Normal Operation": During cruise, descent, or glide, the electrochemical converter is designed to fully supply the electric motor that generates thrust. For this effect, hydrogen is pumped from the storage system to the electrochemical converter and converted into electricity.

[0019] - "Peak Supply": If the propulsion module, particularly the electric motor that generates thrust, requires more power than the maximum power generated by the electrochemical converter during a specific flight phase, the power difference can be supplied by the energy storage unit. The energy storage unit can be electrically connected to the electrochemical converter in parallel.

[0020] - "Recharging": This can be done on the ground or in flight. The electrochemical converter generates electricity, and if the propulsion module requires less power than the electrochemical converter can supply, the excess energy is stored in the energy storage unit.

[0021] - "Refilling": This only relates to the hydrogen storage system. Advantageously, during refilling, the hydrogen storage unit can be separated from other components, allowing maintenance tasks such as those on the electric motor and / or powertrain equipment to be performed while hydrogen is being refilled. Alternatively, the hydrogen storage unit can remain within the propulsion module and can be refilled via the propulsion module and / or the aircraft's piping / pipeline.

[0022] - "Maintenance": This involves the replacement and / or inspection of a portion and / or component of the pod on the ground. Such inspection can be performed directly using the pod mounted on the aircraft, or by disassembling a component and / or portion of the pod and inspecting that part and / or component in a workshop. Meanwhile, the removed portion can be replaced with a fully functional part without damaging the aircraft.

[0023] One embodiment of the propulsion module also includes at least one cooling system. The cooling system can be an active and / or passive cooling system (or any other form of cooling), and in the case of an active cooling system, the cooling system can therefore also be considered an electrical load component. The cooling system may include a heat exchanger.

[0024] One embodiment of the propulsion module includes a first part and a second part, each of the first and second parts including a respective fairing. The first and second parts can be separated / disconnected from each other, for example, by actuation of a separation device and / or during maintenance.

[0025] Specifically, the first section includes the power generation function of the propulsion module. For this purpose, the first section includes at least one electrochemical converter and at least one electric motor. This provides the advantage that maintenance of the components of the first section can be performed separately from refilling, saving time. The first section may also include an energy storage unit and a cooling system.

[0026] The first fairing section offers the following advantages: particularly when the first section is the forward portion of the wing profile (as can also be seen below), drag loss is reduced. Advantageously, the shape of the first fairing section is continuous with the wing profile at the contact area, i.e., there is no abrupt change at the transition between the wing profile and the first fairing section. Furthermore, the fairing protects the components located in the first section from external damage. In this embodiment, the thrust vector of the propulsion module is aligned with the wing chord.

[0027] In one embodiment, the first part includes a support member in the form of a frame, which is surrounded by a fairing. At least one component of the first part, such as at least one electric motor, at least one energy storage unit, and / or at least one electrochemical converter, is fixed / attached to the frame. Other components of the first part, such as a cooling system, may also be attached / fixed to the frame.

[0028] The second part includes a hydrogen storage system. For this purpose, the second part may include at least one hydrogen storage unit, such as a hydrogen tank, and optionally at least one network of pipes, located within a fairing of the second part. The fairing of the second part protects the hydrogen storage unit from external damage. The fairing can also establish a mechanical connection between the wing and the hydrogen storage unit without requiring modification of the hydrogen storage unit. This is particularly advantageous when using readily available hydrogen storage units, such as readily available reusable hydrogen cylinders. This significantly reduces the time and tools required to replace hydrogen storage units using functional hydrogen storage units and / or complete hydrogen storage units.

[0029] One implementation is that the hydrogen storage unit can be removed from its housing during maintenance operations and replaced by another similar hydrogen storage unit in the event of a failure of the initial unit. In another implementation, this replacement can be performed in any state between a full and empty hydrogen storage unit.

[0030] In one embodiment, the second part of the fairing can be a hydrogen storage unit housing. This hydrogen storage unit housing can include two parts: a core and a cap. The core is preferably cylindrical (not necessarily having a circular cross-section), with one end open and the other end having a shape that matches one of the ends of the hydrogen storage unit. This end is perforated / has holes to allow the head of the hydrogen storage unit (e.g., the bottle head) to be accessed when the hydrogen storage unit is positioned in the housing. The cap can be cylindrical, with one end open and the other end closed. The closed end can include perforations to allow air circulation, thus preventing hydrogen buildup in the enclosed environment.

[0031] The hydrogen storage unit can slide through the open end of the core until the surface of the hydrogen storage unit contacts the end of the housing. At this point, the head of the hydrogen storage unit can, for example, protrude from the hydrogen storage unit housing and can be connected to the at least one piping network, particularly at least one piping network of the first portion. When the hydrogen storage unit is inserted into the housing, the cover can be secured to the core and hold the hydrogen storage system in place.

[0032] Alternatively, the hydrogen storage unit housing and the fairing can be two separate parts, wherein, for example, for aerodynamic reasons, the fairing surrounds the housing. In this case, the housing can be attached to the wing and hold both the hydrogen storage unit and the fairing. Alternatively, the fairing can be attached to the wing and hold both the hydrogen storage unit and the housing.

[0033] Therefore, the aircraft propulsion module may include:

[0034] - Hydrogen storage system,

[0035] - At least one electrochemical converter, connected to a hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electrical energy, and

[0036] - At least one electric motor, the at least one electric motor being electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust;

[0037] in,

[0038] -The propulsion module includes a first part and a second part, each of which includes a corresponding fairing;

[0039] -The first and second parts can be separated from each other;

[0040] The first part includes at least one electrochemical converter and at least one electric motor; and

[0041] - The second part includes the hydrogen storage housing of the hydrogen storage system for storing reusable hydrogen storage units.

[0042] In one embodiment, the first part includes a frame, at least one electrochemical converter, at least one electric motor, and a second part, particularly the second part, a hydrogen storage housing attached to the frame.

[0043] In one embodiment, the hydrogen storage housing includes a core and a cover, one end of the core being an open end for inserting a hydrogen storage unit, and the other end including a hole that allows the head of the hydrogen storage unit to be accessed.

[0044] In one implementation, the cover includes a hole, such as a drilled hole, to prevent hydrogen buildup.

[0045] In one embodiment, the hydrogen storage housing is adapted to attach the aircraft propulsion module to the aircraft's wing.

[0046] In this embodiment, the hydrogen storage housing is the shroud of the second part.

[0047] In one embodiment, the hydrogen storage system includes at least one network of pipes adapted to refill the hydrogen storage unit when it is positioned within the hydrogen storage housing.

[0048] Regarding the connection between the hydrogen storage unit housing or fairing and the wing, a guide rail can be fixed to the outer side of the fairing of the storage system, parallel to the axis of rotation of the housing. The guide rail has one or more side rods. A portion with corresponding tracks cut into it can be installed on the wing. When needed, the hydrogen storage unit housing guide rail can slide within the track to secure the hydrogen storage unit housing to the wing. The guide rail can have a specific shape to prevent the hydrogen storage unit housing from falling due to gravity. Movement may be restricted by locking elements or the ends of the track. For example, one of the following alternative locking systems can be used:

[0049] - Rotary locking element. In one embodiment of the rotary locking element, the element is attached about an axis and can be rotated only by a certain angle using a stop. As the hydrogen storage unit housing moves in the track, the side rod of the hydrogen storage unit housing contacts the inclined plane of the rotating element, causing the rotating element to rotate about its axis while allowing the hydrogen storage unit housing to remain in motion. As the hydrogen storage unit housing remains in motion, the rod is no longer in contact with the rotating element, thus allowing the rotating element to be pushed back by a mechanical device or attracted back to its initial state by gravity. If the hydrogen storage unit housing now moves in the opposite direction, the element blocks the movement and cannot rotate due to the stop. To release the hydrogen storage unit housing, an external action is required to push the hydrogen unit system housing to rotate the locking element and similarly retain the locking element, while pulling the hydrogen storage unit housing out of the guide rail.

[0050] - Sliding locking element. In one embodiment of the sliding locking element, the element is guided by a portion on the side of the track. As the hydrogen storage unit housing moves, the side rod of the hydrogen storage unit housing contacts the inclined plane of the sliding element, causing the sliding element to rise while simultaneously allowing the hydrogen storage unit housing to remain in motion. As the hydrogen storage unit housing remains in motion, the rod reaches a notch in the contact plane, and the sliding element can be moved back to its initial state by gravity or by a mechanical device, thereby locking the rod in the notch. The hydrogen storage unit housing is held in place and cannot move forward or backward. To release the hydrogen storage unit housing, an external action is required to push the locking element to release the notch and similarly hold the locking element while simultaneously pulling the hydrogen storage unit housing out of the guide rail.

[0051] The first and second parts are connected via at least one fluid connection line (e.g., a supply line / pipe for allowing hydrogen fluid to flow from the second part to the first part). Electrical connection lines may connect to different electronic components in the first and / or second parts of the module for, for example, monitoring purposes. Mechanical connection lines may be mechanically connected to certain components and may be, for example, thin metal wires, plastic cables, etc. In the following, fluid connection lines (e.g., for supplying hydrogen), electrical connection lines (e.g., for supplying voltage, transmitting electrical signals, and / or data communication), and mechanical connection lines (e.g., mechanical connection lines for component separation devices) may be collectively referred to as connection lines or “channels.”

[0052] If the electric motor used to generate thrust is connected to the front propeller, the first part can be the front section, and the second part is the rear section located behind the front section. This achieves a particularly compact design.

[0053] One embodiment involves the first portion being attached to the second portion and / or to the wing. Another embodiment involves the second portion being attached to the first portion and / or to the wing. If the second portion is attached to the wing, it can be positioned below the wing profile. Another embodiment involves the first portion being attached only to the second portion, and the second portion being attached to the wing. In this case, one embodiment allows the first portion / front portion to be detached separately while the second portion / rear portion remains on the aircraft. Another embodiment requires the first portion to be removed in order to detach the second portion of the aircraft. Another embodiment allows the hydrogen storage unit to be detached from the second portion without removing the first or rear portion fairing / shell from the wing. Attached Figure Description

[0054] The foregoing features and advantages of the invention, as well as the types of ways in which these features and advantages are implemented, will now be described in more detail, schematically, by way of at least one embodiment, with the aid of one or more accompanying drawings.

[0055] Figure 1 A cross-sectional side view of a propulsion module according to another embodiment of the present invention is shown;

[0056] Figure 2 Shown in cross-sectional side view Figure 2 A schematic diagram of the hydrogen storage system of the propulsion module;

[0057] Figure 3 A sketch of a rotary locking mechanism is shown in a cross-sectional side view, which locks the connection between the hydrogen storage unit housing system and the aircraft's wing.

[0058] Figure 4A side view sketch shows a sliding locking element that locks the connection between the hydrogen storage unit housing and the aircraft's wing; and

[0059] Figure 5 A schematic diagram of the connection between the hydrogen storage unit housing system and the matching attachment components of the wing is shown in oblique view. Detailed Implementation

[0060] Figure 1 A cross-sectional side view of one possible implementation of propulsion modules 1 and 2 is shown.

[0061] To reduce costs and maintain the program, the propulsion modules 1 and 2 were divided into multiple parts.

[0062] The first part 1, which constitutes the power generation section, is attached to the wing (outline) W of the aircraft A to align the thrust vector with the chord of the wing W. The first part 1 includes a frame 3 surrounded by a fairing 4 to reduce drag loss. At least the following components are fixed / attached to the frame 3: a propulsion device 5 (e.g., a motor / engine / fan, without loss of generality), a battery 6, an electrochemical converter 7 in the form of a fuel cell, and a cooling system 8. Other components may also be fixed to the frame.

[0063] As shown, a second section 2, which can be located below the wing W, houses the hydrogen storage system 9 within the fairing 10. The fairing 10 protects the hydrogen storage system 9 from external damage. The second section 2 also establishes a connection between the wing W and the storage system 9 without requiring modification to the storage system 9. This is particularly advantageous if the storage system 9 uses readily available, reusable hydrogen storage units 11, such as hydrogen cylinders.

[0064] The two parts 1 and 2 are connected at least via a connecting line that takes the form of a supply channel 12 for exchanging hydrogen fluid between the first part 1 and the second part 2. At least one channel may be connected to different elements of the first part 1 and / or the second part 2 of the module, for example, for monitoring purposes.

[0065] The operations of modules 1 and 2 may include at least one of the following five groups:

[0066] - "Normal operation": For example, without loss of generality, cruising and / or descending and / or coasting, the fuel cell 6 is designed to fully supply the electric motor 5, and hydrogen is discharged from the storage system 9 and converted into electrical energy through at least one electrochemical converter 7;

[0067] - "Peak supply": If the power required by modules 1 and 2 during a specific flight phase is greater than the maximum power produced by the electrochemical converter 7, the difference can be provided by the battery 6 connected in parallel with the electrochemical converter 7;

[0068] - "Battery charging": This task involves two parts of the module and is performed either on the ground or in flight. The electrochemical converter 7 generates electricity. If the electric motor 5 requires less power than the electrochemical converter 7 can supply, the excess energy is stored in the battery 6.

[0069] - "Refilling": This task involves only the hydrogen storage system 9. Advantageously, during refilling, the hydrogen storage unit 11 is separated from other components, so maintenance tasks on the motor or power generation equipment can be performed simultaneously. Alternatively, the hydrogen storage unit 11 can remain in the propulsion module and can be refilled via the propulsion module and / or the aircraft's piping / pipeline.

[0070] - "Maintenance": This involves the replacement and / or inspection of components or portions of propulsion modules 1 and 2 on the ground. This inspection can be performed directly using propulsion modules 1 and 2 mounted on aircraft A, or by disassembling a component and / or portion of propulsion modules 1 and 2 and inspecting that part in a workshop. Simultaneously, the removed portion can be replaced with a fully functional part without damaging aircraft A.

[0071] The connection between the first part 1 of propulsion modules 1 and 2 and the wing should be as compact as possible to reduce the forward area of ​​the modules and thus reduce drag loss. In one embodiment, a notch can be provided in the wing W to access the spars, which makes attachment easier. This embeds modules 1 and 2 into the wing W, thus reducing the forward area.

[0072] When modules 1 and 2 generate thrust for aircraft A, the fastening system should be able to withstand significant loads and transfer those loads to the structure. Shifts in the center of gravity and thrust vector create torques, which should also be effective.

[0073] This attachment system should be adaptable to every position in every wingspan direction, accommodating variations in chord and thickness, as well as twist and dihedrient.

[0074] like Figure 2 As shown, the hydrogen storage system 9 may include a hydrogen storage unit housing 13 for housing a hydrogen storage unit 11. The hydrogen storage unit housing 13 includes two parts: a core 14 and a cap 15. The core 14 is cylindrical (not necessarily having a circular cross-section), with one end 16 open and the other end 17 having a shape that matches the end of the hydrogen storage unit. The end 17 is perforated to allow the head 18 (e.g., bottle head) of the hydrogen storage unit 11 to be accessed when the hydrogen storage unit 11 is positioned in the housing 13.

[0075] The cap 15 is cylindrical, with one end 19 open and the other end 20 closed. The closed end 20 includes a hole 21 to allow air to circulate, thereby preventing hydrogen buildup in the enclosed environment.

[0076] To store the hydrogen storage unit 11 in the housing 13, the hydrogen storage unit 11 is first slid into the core 14 via its head 18 through the open end 16 until the surface of the hydrogen storage unit 11 contacts the end 17 of the core 14. At this point, the head 18 of the hydrogen storage unit protrudes from the core 14 and can be connected to the supply and distribution network 12. Then, the cover 15 can be secured to the core 14 at its open end 19, for example, by screwing on the cover 15, thus fixing the hydrogen storage unit 11 in place.

[0077] The hydrogen storage unit housing 13, and particularly the core 14 of the hydrogen storage unit housing 13, includes attachment devices, such as rails 22, for establishing a connection with the wing W (see also...). Figure 5 The guide rail 22 is fixed to the outer side of the core 14, parallel to the axis of rotation of the cylindrical core 14, and includes one or more laterally projecting rods (“side rods”) 23. A component 24 is mounted on the wing W, in which at least one track 25 is cut. When needed, the hydrogen storage unit housing guide rail 22 can slide in the track 25 to secure the core 14 of the hydrogen storage unit housing 13 to the wing W. The guide rail 22 has a specific shape so that the hydrogen storage unit housing 13 will not fall due to gravity. Movement is restricted by locking elements and / or the ends of the tracks. For example, one of the following alternative locking systems can be used:

[0078] - Rotary locking element ( Figure 3 Rotary latch 26 is rotatably attached about axis 27 of track component 24 and can be rotated only by a certain angle using stop 28. As guide rail 22 moves in track 25, side bar 23 of guide rail 22 contacts the inclined plane of rotary latch 26, thereby forcing rotary latch 26 to rotate about its axis 27 while allowing core 14 to remain in motion. As side bar 23 remains in motion, side bar will lose contact with rotary latch 26, thereby allowing latch 26 to rotate back to its initial state, for example, by being pushed back by a mechanical device (e.g., a spring) or by being attracted by gravity. If core 14 wants to move in another direction from this position of latch 26, latch 26 blocks the movement, and latch 26 cannot rotate (in the counterclockwise direction shown in the figure) due to stop. In order to release the core 14, an external action is required to push the core 14, causing the latch 26 to rotate and keep the latch 26 open, while pulling the guide rail 22 of the core 14 out of the track 25.

[0079] - Sliding locking element ( Figure 4The sliding latch 29 of the track component 24 is guided slidably on the track component 24 by the fixed part 30. When the guide rail 22 slides onto the track 25, the side rod 23 contacts the inclined plane 31 of the sliding latch 29, causing the sliding latch 29 to move upward while allowing the core 14 to remain in motion. As the core 14 remains in motion (12), the rod 23 reaches the notch 32 in the contact plane of the latch 29. At this position, the sliding latch 29 moves back to its initial state, for example by gravity or by being pushed back by a mechanical device, thereby locking the rod 23 in the notch 32. The core 14 is thus held in place and cannot move forward or backward. To release the core 14, an external action is required to push the latch 29 upward and similarly hold the latch 29 while simultaneously pulling the guide rail 22 out of the track 25.

[0080] The wing W may be equipped with one or more tracks 25, the shape of which will guide the corresponding guide rail 22 along the insertion axis and prevent the guide rail 22 from moving along the other two axes. These tracks 25 will be closed at one end.

Claims

1. An aircraft propulsion module, the aircraft propulsion module comprising: - Hydrogen storage system, - At least one electrochemical converter connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electrical energy, and - At least one electric motor, the at least one electric motor being electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust; in, - The propulsion module includes a first part and a second part, each of the first part and the second part including a corresponding fairing; - The first part and the second part can be separated from each other; - The first part includes at least one electrochemical converter and at least one electric motor; and - The second part includes the hydrogen storage housing of the hydrogen storage system for storing reusable hydrogen storage units.

2. The aircraft propulsion module according to claim 1, wherein, The first part includes a frame, the at least one electrochemical converter, the at least one electric motor, and the second part, particularly the hydrogen storage housing of the second part, are attached to the frame.

3. The aircraft propulsion module according to any one of the preceding claims, wherein, The hydrogen storage housing includes a core and a cover. One end of the core is an open end for inserting the hydrogen storage unit, and the other end includes a hole that allows the head of the hydrogen storage unit to be accessed.

4. The aircraft propulsion module according to claim 3, wherein, The cover includes a hole.

5. The aircraft propulsion module according to any one of claims 1 to 2, wherein, The hydrogen storage housing is adapted to attach the aircraft propulsion module to the aircraft's wing.

6. The aircraft propulsion module according to any one of claims 1 to 2, wherein, The hydrogen storage housing is the fairing of the second part.

7. The aircraft propulsion module according to any one of claims 1 to 2, wherein, The hydrogen storage system includes at least one network of pipes adapted to refill the hydrogen storage unit when it is positioned within the hydrogen storage housing.

8. An aircraft comprising an aircraft propulsion module according to any one of the preceding claims.

9. The aircraft according to claim 8, wherein, When positioned within the hydrogen storage housing, the hydrogen storage unit is connectable to at least one piping network of the aircraft, the at least one piping network being adapted to supply hydrogen from the hydrogen storage unit to at least one electrochemical converter of the aircraft.

10. The aircraft according to any one of claims 8 to 9, wherein, When positioned within the hydrogen storage housing, the hydrogen storage unit is connected to at least one network of pipes on the aircraft, the at least one network of pipes being adapted to refill the hydrogen storage unit using hydrogen from an external source.

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