Aircraft propulsion module and aircraft

Abstract

An aircraft propulsion module, comprising: a hydrogen storage system; an electrochemical converter (7) connected to the hydrogen storage system, wherein at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system (12) into electrical energy; and an electric motor (5) electrically connected to the electrochemical converter, wherein the electric motor is adapted to generate a thrust; wherein the propulsion module comprises at least one separation device (9) adapted to separate at least one component of the propulsion module from the propulsion module. An aircraft comprising at least one such aircraft propulsion module. A method for operating a propulsion module, comprising: during operation of the propulsion module, at least one separation device is actuated, at least one component of the propulsion module is separated from the remaining propulsion module by the actuation and then falls from the remaining propulsion module.

Description

[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 including at least one such propulsion module. Furthermore, the invention relates to a method of operating such a propulsion module.

[0002] In the aviation field, modules can be defined as onboard equipment anchored to a dedicated point on the structure of an aircraft. Primarily used in the military, modules can provide various functions, such as increased fuel capacity or expansion of weapon and external sensor payloads. In the Clip-Air project, presented by the EPFL in June 2013, modules could even represent independent cabins to transport passengers.

[0003] It is also known from the prior art that an "electric propulsion module" is provided, distributed along the wingspan of an aircraft wing, wherein the propulsion module is embedded within the wing structure, and only the hydrogen storage is removable. It is also known from the prior art that a propulsion module is provided, wherein the wing structure is constructed around a module having a merging fairing.

[0004] WO 2020 / 003181 A1 discloses a pod for moving a vehicle and also provides a network of interchangeable pods. The pod includes an energy storage unit, a power unit, and a cabin. The cabin includes a housing for enclosing the energy storage unit and the power unit, and a connection structure for attaching the housing to the vehicle. The energy storage unit and the power unit include a power generation module, a propulsion module, and an electronic module. The propulsion module includes an electric motor with a thruster module. The electronic module is configured to activate the power generation module to provide electrical energy to the electric motor, wherein the electric motor actuates the thruster module to move the vehicle.

[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-electric aircraft of the type described above, exhibiting improved operational safety.

[0006] This objective is achieved through the subject matter of the independent claims. For example, advantageous embodiments may be found 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, said at least one electrochemical converter being connected to a hydrogen storage system, wherein said 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, said at least one electric motor being electrically connected to said at least one electrochemical converter, wherein the electric motor is adapted to generate thrust;

[0011] in,

[0012] - The module includes at least one separation device adapted to separate at least one component of the propulsion module from the rest of the propulsion module.

[0013] The advantage of this approach is that if a detachable component becomes inoperable, for example due to fire or leakage, the cause of inoperability will not propagate to other components. This, in turn, improves operational safety, particularly during aircraft flight.

[0014] Typically, a removable propulsion module provides a separate, autonomous, and removable component (“module”) for generating thrust, which can, in principle, be adapted to any aircraft. Specifically, the propulsion module is not embedded in the aircraft's wing or fuselage, but can be added to the aircraft structure, such as the wing, via a simple fastening interface. In particular, a removable propulsion module includes all the means for aircraft propulsion, and the removable propulsion module 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 its operation, and potentially provide feedback on status data such as fuel levels, potential defects, etc.

[0015] Hydrogen storage systems can be adapted to store gaseous hydrogen, liquid hydrogen, and / or solid hydrogen. A hydrogen storage system may include at least one hydrogen storage unit for physically storing hydrogen, such as a hydrogen tank for storing gaseous and / or liquid hydrogen, and specialized materials (e.g., metal hydrides, porous carbon, etc.) for chemical or physical solid hydrogen storage. The hydrogen storage system may also include at least one network of piping dedicated to supplying hydrogen from the hydrogen storage unit to at least one electrochemical converter and / or at least one network of piping allowing external hydrogen refueling.

[0016] In one embodiment, the electrochemical converter includes at least one fuel cell.

[0017] The electric motor is supplied with electrical energy from an electrochemical converter. In one embodiment, the electric motor is connected to and thus drives at least one thruster or at least one ducted fan, or even other propulsion device.

[0018] In one implementation, the propulsion module includes at least one additional device (“electric load”) that uses or stores electrical energy generated by an electrochemical converter. This electrical load may, for example, include at least one additional electric motor (e.g., for moving a retractable eddy current generator), at least one electric actuator (which may also be an electric motor) of the separation device, at least one electrical control device or electronic control device, at least one voltage / current converter, at least one valve, at least one electric switch, at least one lamp, etc. In another implementation, 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 control device or electronic control device may include or be at least one control unit adapted to control the operation of at least one component of the propulsion module, particularly an energy unit, a power unit, and / or a torque management unit, etc. The at least one electrical control device or electronic control device may include a microcontroller, an ASIC, an FPGA, and / or a data communication interface, such as an Ethernet interface, etc. The electrical load may include at least one electric actuator of the separation device, such as an electric motor (the separation device may also be an electric motor).

[0019] In one implementation, 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 cap). This provides the advantage that at least one electrical load 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 implementation, the energy storage unit is electrically connected to the electrochemical converter. This provides the advantage that if the power generated by the electrochemical converter is greater than the power used by other components, the energy storage unit can be charged during flight.

[0020] The operation of the propulsion module under normal conditions (i.e., without component failure) may include at least one of the following operational phases:

[0021] - "Normal Operation": During cruise, descent, or glide, the electrochemical converter is designed to fully power the electric motor that generates thrust. To do this, hydrogen is pumped from the storage system to the electrochemical converter, where it is converted into electrical energy.

[0022] - "Peak Supply": If the propulsion module, particularly the electric motor that generates thrust, requires more power than the maximum power produced by the electrochemical converter during a specific flight phase, the power difference can be provided by the energy storage unit. The energy storage unit can be electrically connected in parallel to the electrochemical converter.

[0023] - "Charging": This phase can be performed on the ground or in flight. The electrochemical converter generates electricity, and if the propulsion module requires less power than the electrochemical converter provides, the excess electrical energy is stored in the energy storage unit.

[0024] - "Refilling": This stage involves only the hydrogen storage system. Advantageously, during refilling, the hydrogen storage unit can be separated from other components so that maintenance tasks such as electric motors and / or power system equipment can be performed while hydrogen is being refilled.

[0025] In one implementation, 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, it can therefore also be considered an electrical load. The cooling system may include a heat exchanger.

[0026] In this implementation, the propulsion module includes a first part and a second part, each of which includes a corresponding fairing. The first and second parts can be separated from each other, for example, by actuation of a separation device and / or during maintenance.

[0027] The first part includes the power generation function of the propulsion module. For this purpose, the first part includes at least one electrochemical converter and at least one electric motor. The first part may also include an energy storage unit and a cooling system. This provides the advantage that maintenance of the components of the first part can be performed separately from refilling, saving time.

[0028] The first fairing section has the advantage of reducing drag loss, especially if the first section is the forward portion located ahead of the wing profile (see also below). Advantageously, the shape of the first fairing section is continuous with the wing profile in the contact area, i.e., there is no abrupt change at the transition between the first fairing section and the wing profile. Furthermore, the fairing protects 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.

[0029] In one embodiment, the first part includes a support member in the form of a frame surrounded by a fairing. At least one component of the first part is fixed / attached to the frame, such as at least one electric motor, at least one separation device, at least one energy storage unit, and / or at least one electrochemical converter. Other components of the first part, such as a cooling system, may also be attached / fixed to the frame.

[0030] 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 at least one piping network within its fairing. The fairing of the second part protects the hydrogen storage unit and the at least one piping network from external damage. The fairing also establishes a mechanical connection between the wing and the hydrogen storage unit without requiring modification of the hydrogen storage unit. This is particularly advantageous because it allows for the use of readily available hydrogen storage units.

[0031] The first and second parts are connected via at least one fluid connection line (e.g., a feed line 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 example, for 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.”

[0032] If the electric motor used to generate thrust is connected to the front thruster, the first part can be the front section, and the second part is the rear section located behind the front section. This makes the design particularly compact.

[0033] In one implementation, the first portion is attached to the second portion and / or the wing. In another implementation, the second portion is attached to the first portion and / or the wing. If the second portion is attached to the wing, it can be positioned below the wing profile.

[0034] In this implementation, the first part is attached only to the second part, and the second part is attached only to the wing. In this case, if the first part separates from the second part by the actuation of the separation device, the first part also separates from the aircraft to which the propulsion module is attached, and can, for example, freely land on the ground during flight.

[0035] In this embodiment, at least one separation device suitable for separating at least one component of the propulsion module includes separating / removing said at least one component from a support to which it is attached. Actuation of said at least one separation device is remotely controllable, for example, by a pilot or automatically controlled via a control system. The support can generally be any suitable structure adapted to attach at least one component, particularly to a frame of a first part of the propulsion module.

[0036] In this embodiment, at least one component capable of being separated by actuation of the separation device includes or is at least one electrochemical converter, at least one energy storage unit, and / or at least one electric motor. However, there may also be components that cannot be separated from the support, such as a cooling system.

[0037] The support component can also be another part of the propulsion module, or even a wing. This allows the first and / or second parts to be separated as a whole. In this implementation, the first and second parts can be disconnected from each other during operation of the propulsion module, such as in flight. This provides the advantage that if one of the two components is damaged or malfunctions, subsequent damage or malfunction of the other component can be avoided, even in flight. In this implementation, the first and second parts can also be disconnected from each other when the module is not in operation, such as on the ground, for example, for parts exchange, maintenance, or repair.

[0038] In one implementation, the first part is detachable from the rest of the aircraft via at least one separation device. The second part may be non-detachable.

[0039] Therefore, it is possible to: (a) separate one or more components from one or both of the first and / or second parts, and / or (b) separate the first and / or second parts as a whole, both based on the actuation / activation of at least one separation device. The at least one separation device can be actuated / activated during flight (i.e., taxiing, ascent, cruise, descent, etc.).

[0040] In this implementation, at least one separable component (via at least one separation device) can be removed from the remaining propulsion module after its separation. This provides the advantage that faulty or malfunctioning components of the propulsion module can be removed from the vicinity of other components, thereby improving operational safety. "Removable" can include components that can be moved outside the propulsion module's fairing. For example, components of the first section can be ejected from the fairing of the first section.

[0041] Alternatively, the detached component can remain inside the propulsion module, but in a location that provides enhanced operational safety compared to the original attachment.

[0042] The implementation involves completely removing the detached component from the (remaining) propulsion module. This provides the advantage that the detached component will reliably no longer interfere with the aircraft. For example, the detached component might be ejected from the propulsion module and then free-fall to the ground. This implementation is applicable, for example, to a component detached from the first section, while the remainder of the first section, including its fairing, remains on the aircraft. This implementation is also applicable, for example, to separating the entire first section (including its fairing) from the second section and / or wing remaining on the aircraft.

[0043] In this implementation, at least one detachable component is tethered to the (remaining) propulsion module, even after removal. This provides the advantage that the detached component can be more easily retrieved for repair and / or safe disposal compared to complete removal. This implementation is applicable, for example, to components detached from the first section while the remainder of the first section, including its fairing, remains on the aircraft, and to the detachment of the entire first section (including its fairing).

[0044] In this implementation, at least one detachable component is attached to a tether, the other end of which is attached to a spool. This allows the tether in the propulsion module to be arranged compactly and orderly before separation, and to be reliably unwound after separation.

[0045] In this implementation, the spool attachment end can be remotely released from the spool canister, i.e., it can be released from the spool, for example, via a pilot's command. This provides the advantage that the spool attachment end can be released while flying over a safe landing zone, and the component can land on the ground in a known area when it can be retrieved. Furthermore, during the deceleration phase, the aircraft lands safely without the risk of the tether becoming entangled with the propellers or wheels.

[0046] Under normal circumstances, this separable component can be held, for example, by one or more shafts (also called pins or bolts) to ensure reliable attachment to the frame. The shafts can be held by fixing elements, such as R-clamps or snap rings that act as mechanical circuit breakers, but other methods are also possible. Snap rings are designed to withstand loads under normal flight conditions but allow them to fly off under higher loads.

[0047] To achieve this, in one embodiment, the shaft can be pulled or pushed by a separation device. The pull / push load is determined to be greater than the load experienced under normal conditions, and large enough to fail one or more mechanical circuit breakers. One or more shafts can then be pulled away, thereby separating the associated components from the support. When all attachment points are free, gravity can pull the separated components downwards out of their module and / or mechanical system (e.g., when the components are attached, the springs are already in a compressed or extended state), thereby pushing them out of the propulsion module.

[0048] In a particular embodiment, at least one separable component is slidably connected to a support, particularly a frame, and is held in place at the support by at least one shaft passing through corresponding coherent holes in the component and the support, the at least one shaft being held in place by a fixing element attached to its free end section, and at least one separation device is adapted to overcome resistance from the corresponding fixing element to remove the at least one shaft from the corresponding hole, for example by pushing or pulling the shaft along its longitudinal axis.

[0049] The component and the support are slidably connected, which specifically means that, without being held in place by an axis (e.g., because it has been removed by a separation device), the separated component can slide along the support, but cannot be lifted from the support. In an embodiment, the component can slide down the support under the drive / pull of its own weight. The slidable connection can be a rail-track connection, wherein the component includes at least one rail that can be inserted into at least one track of the support, or at least one track of the support can be inserted into the at least one rail.

[0050] In this implementation, components detached from the frame of the first part fall out of the first part through a hatch located in the fairing, particularly on the lower side of the fairing.

[0051] In one embodiment, at least one separation device includes an electrically driven actuator that, when actuated (e.g., switched on), applies a force (e.g., a pulling load) along the longitudinal axis of at least one shaft. The actuator may be an electric motor.

[0052] In one embodiment, at least one separation device includes a mechanical linkage that, when actuated, applies a force along the longitudinal axis of at least one shaft. This embodiment is particularly cost-effective and consumes no electricity. The linkage may include at least one bar (e.g., used as a rod) and / or at least one cable. The linkage may be specifically connected to the head of the shaft when the actuated linkage applies a tensile force on the shaft.

[0053] The attachment can also be achieved by other fastening elements that can be removed by a separation device rather than a shaft, such as a latch of the component that can be rotated to release the component and / or a movable resting element on which the component rests, so that the component falls freely when the resting element moves from below the component.

[0054] In one embodiment, at least one separation device includes an electrically driven actuator that operates a mechanical linkage connected to at least one shaft.

[0055] However, the separation device is not limited to the examples described above, but can be any suitable device, including, for example, explosives. Generally, the separation device can be used to separate at least one component of a propulsion module from the rest of the propulsion module, for example, to separate a component from a frame to which it is attached, or to separate a first part of the module from a second part of the module. In one embodiment, the separation device opens, removes, or breaks the connection between the at least one component to be separated and a support to which it is attached (e.g., the frame or the second part). Alternatively, the component to be separated is attached to the support via the separation device. Actuating the separation device can include breaking, disassembling, or opening the separation device itself, thereby making it no longer possible to hold the at least one component to be separated.

[0056] In one embodiment, the support and at least one separable component attached to the support include a coaxial hole through which at least one connecting line is laid. This allows fluid and / or electrical signals to be transmitted through a pathway created by the hole. This pathway can be within a first and / or second portion of the connecting line for a particular component. Alternatively, the pathway is between the first and second portions. In the latter case, "at least one separable component" can be, for example, the first portion and the support is provided by the second portion. When at least one component (e.g., at least one component of the first portion or the first portion itself) is separated, the edges of the two holes generate shear forces that cut or sever at least one connecting line passing through the two holes. This provides the advantage that the separation of at least one component is not obstructed by the remaining connecting lines.

[0057] In one embodiment, at least one of the holes includes a cutting edge, such as a sharp edge or edge segment, particularly shaped like a blade. This greatly enhances the ability to cut at least one connecting line laid through the hole. The cutting edge is positioned such that it cuts through the connecting line when the support and component close the hole after separation, thereby separating the support and component. It is possible that only one of the holes has a cutting edge. In another variation, both holes have their own cutting edges, wherein the cutting edges face each other on the holes.

[0058] In this implementation, at least one of the holes is an elongated hole. This provides the advantage that cutting can be even more efficient due to the potentially higher speed / impact of the moving component at the connection point after separation. In this implementation, all holes are elongated.

[0059] To further facilitate the cutting / separation of the connecting lines, an embodiment is made in which at least one cutting edge is angled, particularly in a "gate" manner. An angled edge advantageously concentrates the shear load on a specific side of the connecting line to be cut, thereby increasing localized stress and facilitating the cutting process.

[0060] Therefore, the separation device is generally adapted to (a) mechanically separate / disassemble / isolate at least one component of the propulsion module from the rest of the propulsion module (e.g., the frame), and / or to (b) cut at least one connecting line between the separated entities. Specifically, the separation device can be actuated to separate at least one component from the frame of the first part, such that the component can fall from the fairing of the first part. The separated at least one component can fall to the ground or can be tethered to the first part. Furthermore, the separation device can be actuated to separate the first part from the second part in such a way that the second part is attached to the wing of the aircraft and the first part is attached only to the second part. The first part is then separated from the aircraft. In the latter case, if at least one connecting line (e.g., a fluid line, mechanical and / or electrical line) connects the first and second parts, it is particularly advantageous when the opening of the first or second part is designed with a cut edge, particularly a beveled cut edge, through which at least one connecting line is laid. The reason for this is that, in the event of the first part separating, the movement of the first part relative to the second part causes the cutting edge to cut at least one connecting line, thereby completely releasing the first part—if the connecting line is not cut, the first part may still be dangling around the aircraft.

[0061] This objective can also be achieved by an aircraft comprising at least one of the aircraft propulsion modules as described above. The aircraft can be implemented in a manner similar to a module, and the module can be implemented in a manner similar to an aircraft.

[0062] In this implementation, at least one of the aircraft propulsion modules is attached to the corresponding wing of the aircraft.

[0063] The implementation method is that each wing of the aircraft includes at least three aircraft propulsion modules.

[0064] This objective is also achieved by a method for operating the propulsion module as described above, wherein, during operation of the propulsion module, at least one separation device is actuated, thereby separating at least one component of the propulsion module from the remaining propulsion modules, and then falling from the remaining propulsion modules. This method can be implemented similarly to an aircraft and a propulsion module, and the aircraft and propulsion module can be implemented similarly to this method.

[0065] For example, a component may fall off the rest of the propulsion module simply due to gravity, or it may be pulled by mechanical force, such as spring force, to assist or make gravity pull possible.

[0066] The above-described features and advantages of the invention, and how such features and advantages are implemented, will now be described in more detail, in the context of one or more accompanying drawings, by way of at least one embodiment.

[0067] Figure 1 A cross-sectional side view of a propulsion module attached to the wing of an aircraft is shown;

[0068] Figure 2 A cross-sectional side view of a cut-off portion of a component of a propulsion module, which is attached to the frame of the propulsion module by means of an R-shaped clamp according to a first embodiment, is shown.

[0069] Figure 3 A cross-sectional side view of the components of the propulsion module before attachment and the cut-off portion of the frame of the propulsion module, according to the second embodiment, is shown.

[0070] Figure 4 A cross-sectional side view of the cut-off portion of the second embodiment prior to the actuation separation device is shown, wherein components of the propulsion module are attached to the frame of the propulsion module.

[0071] Figure 5 A cross-sectional side view of the cut-off portion of the second embodiment following the actuation separation device is shown, but in which the components of the propulsion module are still attached to the frame;

[0072] Figure 6 A cross-sectional side view of the cut-off portion of the second embodiment is shown, wherein the components of the propulsion module are separated from the frame;

[0073] Figure 7 A cross-sectional top view of the components of the propulsion module and the frame of the propulsion module in possible shapes of cut-off portions at their contact areas is shown.

[0074] Figure 8 A cross-sectional top view of the components of the propulsion module and the frame of the propulsion module in cut-off portions of other possible shapes at their contact areas is shown;

[0075] Figure 9 A cross-sectional side view of the wing and the propulsion module with batteries attached to the frame is shown.

[0076] Figure 10 It shows Figure 9 A cross-sectional side view of the wing and propulsion module, showing the battery separating from the frame in the early stages of separation;

[0077] Figure 11 It shows Figure 9 A cross-sectional side view of the wing and propulsion module, showing the battery separating from the frame in the later stages of separation;

[0078] Figure 12 An oblique view of the cut-off portion of the frame of the propulsion module 1, which has elongated holes or slots, is shown;

[0079] Figure 13 An oblique view of the cut-off portion of a separable component of the propulsion module 1, which has an elongated hole or slot, is shown.

[0080] Figure 14 It shows Figure 12 The frame and the parts attached to the frame Figure 13 A cross-sectional side view of the cut-off portion of the component, in which the connecting pipeline runs through both portions;

[0081] Figure 15 It shows Figure 14 A cross-sectional side view of the cut-off portions of the frame and components in the early stages of separation;

[0082] Figure 16 It shows Figure 14 A cross-sectional side view of the cut-off portions of the frame and components in the later stages of separation;

[0083] Figure 17 It shows the attachment to Figure 1 A simplified cross-sectional side view of the propulsion module of the aircraft's wing;

[0084] Figure 18 It shows something similar to Figure 17 The view shows the front portion of the propulsion module in an early stage of separation; and

[0085] Figure 19 It shows something similar to Figure 17 The view shows the front portion of the propulsion module in the later stages of separation.

[0086] Figure 1 A cross-sectional side view of the propulsion module 1 attached to the wing 2 of the aircraft 3 is shown. To reduce costs and maintenance, the propulsion module 1 is divided into several parts, namely, a first (“front”) part 1a and a second (“rear”) part 1b. In the embodiment described herein, the front part 1a, representing the power generation and thrust components, is attached only to the rear part 1b, which in turn is attached to the wing 2.

[0087] The front portion 1a includes a frame 12 surrounded by a fairing 4a (see [link]). Figures 3 to 8 To reduce drag loss. Fixed / attached to the frame are an electric motor 5 driving the thruster 6, an electrochemical converter in the form of at least one fuel cell 7, an energy storage unit in the form of a battery 8, a DC / DC converter 10 for converting the DC voltage / current provided by the fuel cell 7 and / or battery 8 into voltage / current for operating the electric motor 5, and a cooling system including a heat exchanger 11. Other components may also be fixed to the frame.

[0088] A separation device 9 for component isolation is also shown. For this purpose, the separation device 9 is adapted to separate at least one component fixed to the frame 12 from the frame 12. In one embodiment, the separation device 9 opens, removes, or breaks the connection between the component to be separated, such as the battery 8, and the frame 12. Alternatively, the component to be separated is attached to the frame 12 via the separation device 9. Actuating the separation device 9 may then include breaking, disassembling, or opening the separation device 9 itself, making it no longer possible to hold the component in the frame 12.

[0089] As shown, a hydrogen storage system, comprising a hydrogen tank 12 within a fairing 4b, can be housed in the tail section or aft section 1b below the wing 2. The fairing 4b protects the hydrogen storage system from external damage. The fairing 4b also creates a mechanical connection between the wing 2 and the storage system without requiring modification of the storage system. This is particularly advantageous if readily available hydrogen tanks 12 are used.

[0090] Both parts 1a and 1b are connected via at least one fluid connection line 36 for exchanging hydrogen between the second part 1b and the first part 1a, and both are connected via at least one electrical connection line 37 (see below). Figures 14 to 19 ).

[0091] The operation of propulsion module 1 may include at least one operation from a group consisting of the following four operation phases or states:

[0092] - "Normal operation": For example, cruising and / or descent and / or coasting without loss of generality. The fuel cell 7 is designed / sized to supply electrical energy entirely to the electric motor 5. The electrical energy is generated by the fuel cell 7 based on the conversion of hydrogen stored in the hydrogen tank 12.

[0093] - "Peak supply": If the power required by propulsion module 1 during a specific flight phase is greater than the maximum power generated by fuel cell 7, the difference can be provided by battery 8;

[0094] - "Recharging": This phase can be performed on the ground or in flight. If the propulsion module 1, particularly the electric motor 5, requires less power than the fuel cell 7 can supply, then the excess energy is stored in the battery 8.

[0095] - "Refilling": This stage involves only the storage system. Advantageously, during refilling, the rear portion 1b can be separated from the front portion, allowing maintenance tasks for the components of the front portion 1a to be performed simultaneously.

[0096] like Figure 2As shown, during normal operation, the components of the front portion 1a (shown here as battery 8 in one example) are attached to the frame 13 via one or more shafts 14, which are engaged through consistent through holes 15 and 16 in both the frame 13 and the battery 8. On one side, the head 17 of the shaft 14 is wider than the hole 15 and therefore will not be inserted into the hole 15. The head 17 may be equipped with a through hole 16a.

[0097] On the other side of shaft 14, outside of hole 15, when shaft 14 is already locked through both holes 15, 16, shaft 14 includes through hole 18 into which a pin or R-shaped clip 19, as shown, can be locked. Thus, head 17 on one side and R-shaped clip 19 on the other side hold shaft 14 in both holes 15, 16. Therefore, battery 8 is held in place in frame 13 as long as shaft 14 is not removed.

[0098] Under normal conditions, components such as battery 8 can be held by several shafts 14 to ensure that they are securely attached to frame 13.

[0099] Figure 3 With similar Figure 2 The view illustrates another possibility for attaching the battery 8 to the frame 13. Here, shown in a non-attached state, the shaft 20 includes an annular notch 21 at its front section, as indicated by the vertical arrows. After the shaft 20 is inserted through holes 15 and 16, a retaining ring 22 can engage in this notch 21. Also shown in the front view, the retaining ring 22 is designed to withstand loads during normal flight but will fly off under higher loads.

[0100] However, if a component of the propulsion module 1, particularly a component of the front portion 1a, has degraded or malfunctioned, it may be advantageous from a safety perspective to remove / separate the malfunctioning component before it damages other components. When such a degraded state or emergency concerning a component (e.g., battery 8) is noticed by the pilot or automatically by the control system, the present invention proposes the possibility of separating the component from the rest of the propulsion module 1, particularly the front portion 1a.

[0101] For this purpose, propulsion module 1 includes at least one separation device 23 (see...). Figures 4 to 6 The separation device 23 is adapted to separate the component from the frame 13. Then, the weight of the component causes it to fall.

[0102] The separation or disassembly of one or more components from the rest of the propulsion module 1 can also be referred to as “component isolation,” and the corresponding mechanism is called a “component isolation mechanism,” especially if the separated component is removed from the fairing. Aspects involving the disconnection / severance of connecting lines or “channels” such as fluid connection lines, electrical connection lines, and / or mechanical connection lines can be referred to as “disconnection” or “disconnection technology.”

[0103] In the above-described embodiment, the separation of the battery 8 from the frame 13 is equivalent to "component isolation". Component isolation can be achieved, for example, by a separation device 23, which includes a remotely actuable actuator and / or a link connected to the head 17 through a hole 17a.

[0104] When the actuator is actuated (e.g., by activating an electric motor) and / or when the linkage is actuated (e.g., by the pilot mechanically manipulating a linkage leading to the cabin), the separation device 23 pulls the head 17 of the shaft 20 along the longitudinal axis of the shaft 20, as if by... Figure 4 The tensile load F in the figure indicates this.

[0105] The tensile load F is greater than the load it experiences under normal conditions. This, in turn, causes the R-clamp 19, the retaining ring 22, or any other component or system acting as a mechanical circuit breaker to fail. For example, the retaining ring 22 may bend first (e.g., Figure 5 (as shown in the image), and then fly off axis 20 (as shown in the image). Figure 6 As shown in the diagram, the R-shaped clip 19 may break or deform so much that it can be pulled through holes 15, 16, etc. Shafts 14, 20 are then pulled out from holes 15, 16, thereby separating the battery 8 from the frame 13 at this attachment point. When all attachment points are free, gravity can pull the released battery 8 downwards (as shown in the diagram). Figure 6 (As shown in the diagram). The battery 8 can then be further lowered from the front portion 1a (e.g., through a hatch). Alternatively or additionally, the battery 8 can be ejected from the front portion 1a by a mechanical system, such as a mechanical system comprising one or more compression and / or extension springs.

[0106] Of course, instead of being pulled out of holes 15 and 16, shafts 14 and 20 can be pushed out of holes 15 and 16 by applying pressure to their free ends. Alternatively, shafts 14 and 20 can be locked in holes 15 and 16 in the opposite direction, i.e., the head 17 is positioned at the part to be separated.

[0107] Figure 7A cross-sectional top view of the possible shapes of components of propulsion module 1 (e.g., battery 8) and frame 13 of propulsion module 1 at their contact areas is shown. Holes 15 and 16 are also shown. Battery 8 includes two parallel rails 22 into which corresponding guide rails 25 of frame 13 are inserted. Rails 24 and guide rails 25 have the same basic shape that widens inside battery 8. Therefore, battery 8 can only move relative to frame 13 along rails 24 (i.e., along the contact area), but cannot be lifted from frame 13 (i.e., perpendicular to the contact area). When shaft 14 or shaft 20 is inserted into holes 15, 16, it prevents relative movement of battery 8 along frame 13. This arrangement is particularly advantageous because it prevents the application of force along the shaft in normal operating conditions, and thus prevents shaft 14 or shaft 20 from being displaced without actuation separation device 23. Due to the weight of battery 8, rails 24 are open at least at the top in order to separate battery 8 from frame 13.

[0108] Figure 8 A cross-sectional top view of the components of propulsion module 1 (e.g., battery 8) and the frame 13 of propulsion module 1 at their contact areas is shown. The arrangement shown is similar to... Figure 7 The cross-sectional shape of track 26 and guide rail 27 is now trapezoidal.

[0109] Of course, rails 24 and 25, as well as rails 26 and 27, can be arranged in interchangeable configurations. For example, rails 24 and 26 may be in the frame 13, while rails 25 and 27 may be in the battery 8. In this case, due to the weight of the battery 8, rails 24 and 26 are open at least at the bottom in order to separate the battery 8 from the frame 13.

[0110] In this implementation, rails 24 and 25 and / or rails 26 and 27 are aligned at least in a generally vertical direction. This provides the advantage that when shafts 14 and 20 are removed, battery 8 can slide down along frame 13 by gravity and / or by spring force.

[0111] Figure 9 A cross-sectional side view of the front portion 1a of the wing 2 and the propulsion module 1 with the battery 8 attached to the frame 13 is shown. The rear portion 1b is not shown.

[0112] The lower part of the fairing 4a of the front section 1a includes a hatch 28, which opens to release the disassembled / detached battery 8 from the fairing 4a. Without any other measures, the battery 8 will fall freely to the ground upon release from the fairing 4a.

[0113] In an advantageous embodiment, the battery 8 is secured to a spool 29 located in the front portion 1a via a mechanical cable / tether 30. This prevents the battery 8 from falling uncontrollably and avoids potential injury or damage from its free fall. Specifically, one end of the tether 30 is attached to the battery 8 and the other end is attached to the spool 29. When the battery 8 is attached to the frame, the tether 30 is wound around the spool 29.

[0114] Optionally, the battery 8 is slidably connected to the extendable rod 31. The advantage of the rod 31 is that, since the rod 31 is adapted to guide the battery 8 during the initial phase of its descent, it prevents the battery 8 from impacting the front portion 1a, the rear portion 1b, or the wing 2. When the battery 8 is attached to the frame, the rod 31 is in a retracted state and is therefore very short, allowing it to fit into the fairing 4a.

[0115] Figure 10 It shows something similar to Figure 9 A cross-sectional side view showing the battery 8 already separated from the frame (e.g., caused by actuation of the separation device 23 in the initial stage of separation, where the hatch 28 has opened and the battery 8 slides down the now extended rod 31). As it slides downward, the tether 30 is unwound from the spool 29.

[0116] Figure 11 It shows a similar situation in the later stages of separation. Figure 10 A cross-sectional side view showing that the battery 8 has slid off the rod 31, has been removed from the rod 31, and is now suspended at a safe distance from any structural part of the aircraft 3 by the unwound tether 30.

[0117] When flying near an airport and / or over a safe drop zone, the end of the spool attached to tether 30 can be released on command, and then battery 8 will drop to the ground within the known drop zone. The aircraft 3 lands safely without the risk of tether 30 becoming entangled in the thrusters 6 or wheels during the deceleration phase. Depending on the drop zone, battery 8 and tether 30 can be retrieved.

[0118] Figure 12 An oblique view of a cut-off portion of the frame 13 of the propulsion module 1 is shown, the propulsion module 1 having a hole 32 that is elongated or slotted in the vertical direction. This hole 32 may also exist in addition to one or more holes 15 described above.

[0119] The frame 12 is also equipped with parallel rails 34, such as in the form of rails 24 or 26 as described above, which are shown as vertically aligned.

[0120] Figure 13An oblique view of a cut-off portion of a detachable component of propulsion module 1 (here, battery 8 is used as an example) is shown, which has an elongated or slotted hole 33 that is also vertically elongated. This hole 33 may also exist in addition to one or more holes 16 described above.

[0121] The battery 8 is also equipped with a parallel guide rail 35, such as in the form of rails 25 or 27 described above, which is shown as vertically aligned and fitted into rails 34 of the frame 13. If the battery 8 is not held in place by at least one shaft 14 or shaft 20, the battery 8 will slide vertically off the frame 13 along rails 34.

[0122] One or more connecting channels / connecting lines 36, 37 may pass through / be laid in holes 32 and 33 (see, for example). Figures 14 to 16 The connecting channels / connecting lines 36 and 37 are in the form of at least one fluid connecting line 36 (e.g., in the form of a pipe) and / or at least one electrical connecting line 37 (e.g., a data cable and / or a power line) and / or at least one mechanical line (e.g., a thin metal wire or a plastic cable).

[0123] Typically, when components of the propulsion module 1, particularly those of the front portion 1a, are connected to connecting lines 36 and 37, the separation of these components from the frame 13 may be insufficient to also separate the connecting lines 36 and 37, resulting in incomplete separation and / or excessive tensile loads on at least one connecting line 36 or 37. One solution to this problem is to provide mechanically weak connection interfaces and / or predetermined break points for connecting lines 36 and / or 37. However, this may also negatively impact stability and reliability under normal operating conditions, especially if the connecting line 36 is a pressurized fluid connecting line. To overcome this problem, the following implementation, equivalent to a disconnection technique, is proposed:

[0124] At least one of the elongated holes (here: hole 33) includes a cut edge 38, i.e., an edge that cuts through at least one connecting conduit 36, 37 when the battery 8 falls after being separated from the frame 13, such as Figure 14 , Figure 15 and Figure 16 As shown in the sequence. In the case of hole 33, the cutting edge 38 corresponds to the upper section of hole 33. To cut at least one connecting line 36, 37 particularly efficiently, the cutting edge 38 is formed as an inclined line in a gate-like manner. Because hole 33 is elongated, the cutting edge 38 has higher velocity / impact and shearing force when cutting at least one connecting line 36, 37 compared to a smaller rounded hole. Alternatively or additionally, the lower section of hole 32 can be the cutting edge.

[0125] Figures 2 to 8 The component isolation mechanism shown in the figure and Figures 14 to 16 The disassembly technique shown can be applied not only to the separation of a component from the front part 1a, but also to the separation of the entire front part 1a from the rear part 1b and / or the wing 2.

[0126] Figure 17 It shows Figure 1 A simplified cross-sectional side view of the aircraft 3, wherein the propulsion module 1 is attached to the wing 2. Specifically, the front portion 1a remains attached to the wing 2 and / or the rear portion 1b, for example, by using a method similar to... Figures 2 to 8 Shaft 14 or shaft 20 is attached to wing 2 and / or rear section 1b. At least one fluid connection line 36, in the form of, for example, a flexible plastic tube, extends between the front section 1a and the rear section 1b, for example, to supply hydrogen stored in hydrogen tank 11 in the rear section 1b for use with fuel cell 7 in the front section 1a. Additionally, at least one electrical connection line 36, in the form of a cable, may extend between the front section 1a and the rear section 1b, for example, to supply electrical energy generated by fuel cell 7 to at least one valve (not shown) of the hydrogen supply system. These connection lines 36, 37 are configured in a manner similar to... Figures 14 to 16 The hole extends through the front portion 1a and the rear portion 1b in a manner that is consistent with the flow pattern.

[0127] Figure 18 It shows something similar to Figure 17 The view shows that the front portion 1a of the propulsion module 1 is in a position similar to Figure 15 This is an early stage of separation after the front part 1a has separated from the rear part 1b and / or wing 2 by the operation of the separation device 23. The front part 1a falls and will cut the connecting pipes 36, 37.

[0128] Figure 19 It shows something similar to Figure 17 The view shows the front portion 1a of the propulsion module 1 in a late stage of separation after the connecting pipes 36 and 37 have been cut. The front portion 1a can be in a free-fall state or can be tethered to the rear portion 1b, for example, similar to... Figures 9 to 11 .

[0129] Of course, the present invention is not limited to the embodiments described.

Claims

1. An 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 at least one separation device adapted to separate at least one component of the propulsion module from the propulsion module. - At least one separable component is slidably connected to a support and is held in place at the support by at least one shaft passing through corresponding holes in the component and the support. - The at least one shaft is held in place by a fixing element attached to the free end section of the shaft, and - At least one separation device is adapted to overcome the resistance from the corresponding fixing element and remove the at least one shaft from the corresponding hole.

2. The aircraft propulsion module according to claim 1, wherein, At least one detachable component can be removed from the propulsion module after separation.

3. The aircraft propulsion module according to claim 1, wherein, At least one detachable component is tethered to the propulsion module after removal.

4. The aircraft propulsion module according to claim 3, wherein, The detachable component is tethered to one end of a tether, the other end of which is connected to a spool of the aircraft propulsion module.

5. The aircraft propulsion module according to claim 4, wherein, The end of the tether connected to the spool can be remotely released from the spool.

6. The aircraft propulsion module according to any one of claims 1 to 5, wherein, The at least one separable component includes at least one electrochemical converter, at least one energy storage unit and / or at least one electric motor, or is the at least one electrochemical converter, the at least one energy storage unit and / or the at least one electric motor.

7. The aircraft propulsion module according to any one of claims 1 to 5, wherein, The slidable connection allows the detached component to slide down the support under the weight of the detached component and then fall out of the fairing of the propulsion module when the at least one shaft is removed.

8. The aircraft propulsion module according to any one of claims 1 to 5, wherein, At least one separation device includes an electric actuator and / or a mechanical linkage that, when operated, applies a force along the longitudinal axis of the at least one axis toward the at least one axis.

9. The aircraft propulsion module according to any one of claims 1 to 5, wherein, - The at least one separable component includes at least one elongated hole, and / or the support includes at least one elongated hole, wherein when the component is attached to the support, at least one connecting line is laid through at least one elongated hole of the at least one separable component and at least one elongated hole of the support, and wherein, - At least one of the holes includes a cut edge.

10. The aircraft propulsion module according to any one of claims 1 to 5, wherein, The at least one electrochemical converter, the at least one energy storage unit, and the at least one electric motor are located in a first part of the propulsion module, wherein the hydrogen storage system is located in a second part of the propulsion module, and wherein the first part is separable from the second part by the at least one separation device.

11. The aircraft propulsion module according to claim 10, wherein, - The first portion and / or the second portion includes at least one elongated hole, and when the first portion is attached to the second portion, at least one connecting line is laid through the at least one elongated hole, and wherein, - At least one of the holes includes a cutting edge designed such that when the first portion is separated from the second portion by the at least one separating device, the cutting edge cuts the at least one connecting line.

12. An aircraft comprising at least one aircraft propulsion module according to any one of claims 1 to 11.

13. A method for operating a propulsion module according to any one of claims 1 to 11, wherein, during operation of the propulsion module, at least one separation device is actuated, and at least one component of the propulsion module is separated from and then falls from the remaining propulsion module by the actuation.

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