Ground hatch portable device, landing gear hatch opening and closing system and method, and aircraft comprising system

Abstract

The invention discloses a portable device for opening a cabin door on the ground. The portable device comprises an external interface of the portable device, wherein the external interface of the portable device comprises an external unlocking interface; the portable device control module is in communication connection with the portable device external interface; and the energy storage unit is connected with the portable device control module so as to supply power to the portable device control module. The ground cabin door opening portable device can be used in an aircraft landing gear cabin door opening and closing system. The ground-open hatch portable device and the landing gear hatch opening and closing system including the same allow reliable opening and closing operations of a hatch lock without significantly increasing the complexity of the overall structure of the aircraft. The invention further provides an undercarriage cabin door opening and closing system comprising the ground cabin door opening portable device, an aircraft comprising the system and an aircraft undercarriage cabin door opening and closing method using the system.

Description

Technical Field

[0001] The present application belongs to the field of aircraft design, and specifically relates to a system and method for opening and closing landing gear doors of civil aircraft, especially opening and closing them on the ground. Background Art

[0002] For larger aircraft such as civil aircraft, it is often necessary to open the landing gear door on the ground during maintenance to inspect and repair the landing gear.

[0003] There are several ways to open the door from the ground. One is to install a special mechanical cable on the aircraft to control the hydraulic components to open and close the door lock of the landing gear door, so that the landing gear door can be opened and closed. The other is to use the aircraft's own power supply to open and close the door lock of the landing gear door to open and close the landing gear door.

[0004] These two methods of opening the landing gear doors have their own advantages and disadvantages. Among them, the mechanical cable controls the hydraulic components to open and close the landing gear doors without the need for power supply. However, this opening method requires the installation of a dedicated ground door opening and closing system on the aircraft, which will increase the weight of the aircraft and thus affect the flight efficiency of the aircraft. In the case of using the aircraft power supply to open and close the landing gear door, the aircraft needs to be able to provide power for unlocking. However, if there is a power failure in the aircraft or the aircraft is severely damaged and cannot provide power normally, or if the aircraft cannot provide power due to long-term storage, it is necessary to restore the power supply of the aircraft's own power supply before the landing gear door can be opened.

[0005] Therefore, there is a need to further improve the way of opening and closing the landing gear door of the aircraft to overcome the technical problems existing in the above-mentioned prior art. Summary of the invention

[0006] The present application is made to solve the problems existing in the prior art mentioned above. The purpose of the present application is to provide an improved landing gear door opening and closing solution, which allows maintenance personnel to reliably open the aircraft landing gear door on the ground without complicating the aircraft structure.

[0007] The present application provides a portable ground door opening device, which is included in the landing gear door opening and closing system of an aircraft. The portable ground door opening device includes: a portable device external interface, which includes an external unlocking interface; a portable device control module, which is communicatively connected to the portable device external interface; and an energy storage unit, which is connected to the portable device control module to provide power to the portable device control module.

[0008] The portable ground door opening device can be used as an opening and closing system for the landing gear door of an aircraft, so that no matter whether the power supply on the aircraft can normally provide power, the door lock of the landing gear door can be reliably unlocked and reset by the external portable ground door opening device, thereby opening the landing gear door. Moreover, such a solution will not significantly increase the complexity of the overall structure of the aircraft.

[0009] Preferably, the external interface of the portable device also includes a charging interface, which can be connected to an external power source to charge the energy storage unit. It is known that the charging interface here is an optional structure, and in some cases the charging interface may not be provided, for example, the energy storage unit can be replaced by a disposable battery, in which case the charging interface structure can be omitted.

[0010] Preferably, the portable device for opening the hatch door on the ground further comprises a human-machine interface, which is in communication with the portable device control module, so that maintenance personnel can conveniently perform unlocking operations. The human-machine interface comprises: a power switch, which controls the power supply state of the energy storage unit to the electrical control module; and an unlocking switch, which is used to issue an instruction to open the hatch door lock.

[0011] Furthermore, the human-computer interaction interface also includes at least one of the following indication units: a charging status indication unit, the charging status indication unit is configured to send a first signal when the energy storage unit is charged, and send a second signal when the energy storage unit is fully charged; a low power indication unit, the low power indication unit is configured to send a third signal when the power in the energy storage unit is lower than a predetermined threshold; a connection status indication unit, the connection status indication unit is configured to send a fourth signal when the circuit connection in the landing gear door opening and closing system is abnormal and / or the door lock function is abnormal, and send a fifth signal when the connection is normal; and an unlocking completion indication unit, the unlocking completion indication unit is configured to send a sixth signal when unlocking is completed.

[0012] The first to sixth signals may be lights of different colors, or may be text, icons, sound signals, or a combination of these forms.

[0013] It also relates to an aircraft landing gear door opening and closing system, which includes: a power supply; an electrical control module, the power supply and the electrical control module are connected to provide power to the power supply; at least one landing gear uplock, the landing gear uplock is communicatively connected to the electrical control module; and at least one door lock, the door lock is communicatively connected to the electrical control module. In the present application, the landing gear door opening and closing system also includes the ground-based portable door opening device as described above and an aircraft-side external interface assembly. The aircraft-side external interface assembly is arranged on the aircraft, connected between the electrical control module and the door lock, and is arranged to be connected to an external unlocking interface, thereby allowing the opening and closing of the landing gear door to be manipulated by the ground-based portable door opening device.

[0014] In the case of a specific civil aircraft, three landing gears may be included, namely the front landing gear, the left main landing gear and the right main landing gear. Correspondingly, the landing gear uplock includes the front landing gear uplock, the left landing gear uplock and the right landing gear uplock, which are used to lock the front landing gear, the left main landing gear and the right main landing gear respectively. Further, the cabin door lock may also include a front cabin door lock, a left cabin door lock and a right cabin door lock, which are used to lock the front landing gear door, the left main landing gear door and the right main landing gear door respectively. At this time, the aircraft side external interface assembly may include three interfaces, which are respectively connected between the front cabin door lock, the left cabin door lock and the right cabin door lock and the electrical control module. In this way, the three interfaces can independently control the front cabin door lock, the left cabin door lock and the right cabin door lock respectively.

[0015] In other embodiments, as an alternative, the aircraft-side external interface assembly may also include two interfaces, one of which controls the front door lock, and the other controls the left door lock and the right door lock.

[0016] Alternatively, as another alternative, the aircraft-side external interface assembly may also include only one interface, which is used to simultaneously control the front door lock, the left door lock, and the right door lock.

[0017] Preferably, the aircraft-side external interface assembly is provided with an interface protection cover, which can protect the aircraft-side external interface assembly from external environmental pollution when the aircraft-side external interface assembly is not in use.

[0018] The present application also proposes an aircraft, which comprises a landing gear door opening and closing system having the structure as described above.

[0019] A method for opening and closing a landing gear door is also proposed. The method uses the landing gear door opening and closing system as described above and comprises the following steps:

[0020] Connect the charging port of the ground-mounted door-opening portable device to the aircraft-side external interface assembly on the aircraft;

[0021] Turn on the portable ground door opening device to confirm whether the power in the energy storage unit is sufficient and whether the circuit connection in the landing gear door opening and closing system is normal; and

[0022] After confirming that there is sufficient power in the energy storage unit and that the circuit connection in the landing gear door opening and closing system is normal, operate the portable ground door opening device to unlock and reset the door lock.

[0023] Preferably, after the unlocking is completed, the portable ground door opening device is turned off, and the connection between the external unlocking interface and the aircraft-side external interface assembly is disconnected.

[0024] Preferably, after the ground hatch opening portable device is turned on, if it is detected that the power in the energy storage unit is insufficient, the energy storage unit is charged first. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The preferred embodiments of the present invention are shown in the accompanying drawings, from which the specific implementation of the present invention can be more clearly understood, wherein:

[0026] Figure 1 A schematic structural block diagram of the landing gear door opening and closing system of the present application is shown.

[0027] Figure 2 Shows Figure 1 A schematic structural block diagram of a ground-based portable door opening device for a landing gear door opening and closing system.

[0028] Figure 3 Shows Figure 2 A schematic perspective view of a portable ground-based hatch opening device.

[0029] Figure 4 A schematic structural diagram of an aircraft-side external interface assembly on an aircraft is shown.

[0030] (Explanation of symbols)

[0031] 1Landing gear door opening and closing system

[0032] 10Electrical control module

[0033] 11 Backup switch

[0034] 12Ground door switch

[0035] 20 Power Supply

[0036] 31 Landing gear up lock

[0037] 31-1 Front landing gear up position lock

[0038] 31-2 Left landing gear uplock

[0039] 31-3 Right landing gear uplock

[0040] 32 landing gear

[0041] 32-1 front landing gear

[0042] 32-2 Left main landing gear

[0043] 32-3 right main landing gear

[0044] 33 Hatch door lock

[0045] 33-1 Front door lock

[0046] 33-2 Left door lock

[0047] 33-3 Right door lock

[0048] 34 Landing gear door

[0049] 34-1 Nose landing gear door

[0050] 34-2 Left main landing gear door

[0051] 34-3 Right main landing gear door

[0052] 35 spare release selector valve

[0053] 40 Aircraft side external interface assembly

[0054] 41 First Interface

[0055] 42 Second interface

[0056] 43 Third interface

[0057] 44 Protective cover

[0058] 45 interface cover

[0059] 50 Ground hatch opening portable device

[0060] 51 Portable device external interface

[0061] 52 external unlocking interface

[0062] 53 Charging port

[0063] 54 Energy storage unit

[0064] 55 Portable Device Control Module

[0065] 60 Human-computer interaction interface

[0066] 61 Power switch

[0067] 62 unlock switch

[0068] 63 Charging status indicator

[0069] 64 Low battery indicator

[0070] 65 connection status indicator

[0071] 66 Unlocking completion indication unit DETAILED DESCRIPTION

[0072] The specific implementation methods of the present application will be described in detail below in conjunction with the accompanying drawings. It should be understood that what is shown in the accompanying drawings is only a preferred embodiment of the present application, which does not constitute a limitation on the scope of the present application. Those skilled in the art can make various obvious modifications, variations, and equivalent substitutions to the present application based on the embodiments shown in the accompanying drawings, and under the premise of no contradiction, the technical features in the different embodiments described below can be arbitrarily combined with each other, which all fall within the scope of protection of the present application.

[0073] Figure 1 A schematic structural block diagram of a landing gear door opening and closing system 1 for an aircraft, especially a civil aircraft, according to the present application is shown.

[0074] The landing gear door opening and closing system 1 includes an electrical control module 10 and a power supply 20 for supplying power to the electrical control module 10. The power supply 20, for example, supplies 28V power to the electrical control module 10. The landing gear door opening and closing system 1 also includes a backup release switch 11, which is connected to the electrical control module 10, and controls the lowering and retracting of the landing gear and the opening and closing of the landing gear door through the electrical control module 10.

[0075] Further Figure 1 As shown, the electrical control module 10 is in communication connection with at least one landing gear uplock 31, and is used to control the unlocking and resetting of the landing gear uplock 31, and further control the lowering and retracting of the landing gear 32. The communication connection between the electrical control module 10 and the landing gear uplock 31 can be achieved by wired or wireless means.

[0076] In a specific structure of a civil aircraft, three landing gears 32 are included, namely, a front landing gear 32-1, a left main landing gear 32-2, and a right main landing gear 32-3. Correspondingly, three landing gear uplocks 31 are also included, namely, a front landing gear uplock 31-1, a left landing gear uplock 31-2, and a right landing gear uplock 31-3, which are used to lock the front landing gear 32-1, the left main landing gear 32-2, and the right main landing gear 32-3, respectively.

[0077] The electrical control module 10 is also connected in communication with at least one door lock 33 to control unlocking and resetting of the door lock 33. The communication connection between the electrical control module 10 and the door lock 33 may also be achieved in a wired or wireless manner, for example.

[0078] In the case of three landing gears, three landing gear doors 34 are also included, namely, a front landing gear door 34-1, a left main landing gear door 34-2, and a right main landing gear door 34-3. Accordingly, three door locks 33 are included, namely, a front door lock 33-1, a left door lock 33-2, and a right door lock 33-3, which are used to lock the front landing gear door 34-1, the left main landing gear door 34-2, and the right main landing gear door 34-3, respectively.

[0079] The electrical control module 10 can also be connected to the standby release selection valve 35 in a wired or wireless manner to connect the hydraulic circuit of the retraction system with the return oil pipeline so that the landing gear can be placed at the terminal position.

[0080] In the landing gear door opening and closing system of the present application, a ground-based portable door opening device 50 is also included, and the ground-based portable door opening device 50 includes a portable device external interface 51. Correspondingly, an aircraft-side external interface assembly 40 capable of docking with the portable device external interface 51 is provided on the aircraft. The aircraft-side external interface assembly 40 is connected between the electrical control module 10 and the door lock 33, and is located at a position on the aircraft that is convenient for maintenance personnel to access. For example, the aircraft-side external interface assembly 40 can be exposed on the outer surface of the lower part of the aircraft fuselage. Alternatively, the aircraft-side external interface assembly 40 can be set in the cockpit of the aircraft. The specific setting position of the aircraft-side external interface assembly 40 can be selected as needed.

[0081] Preferably, the aircraft side external interface assembly 40 is covered with a protective cover 44 (see Figure 4 ) to protect the aircraft-side external interface assembly 40 from external contaminants when the landing gear door 34 is not opened or closed.

[0082] In the case of three landing gears 32 and corresponding three landing gear doors 34 as described above, the aircraft side external interface assembly 40 may include three interfaces, which are respectively connected at the positions between the front door lock 33-1, the left door lock 33-2 and the right door lock 33-3 and the electrical control module 10.

[0083] Figure 2 The functional structure block diagram of the ground-based portable door opening device 50 is shown. The ground-based portable door opening device 50 includes a portable device external interface 51. The portable device external interface 51 includes an external unlocking interface 52, which can be connected to the aircraft-side external interface assembly 40 on the aircraft fuselage, so as to provide power and control the door lock 33 of the landing gear door opening and closing system 1. Preferably, the portable device external interface 51 also includes a charging interface 53, through which the ground-based portable door opening device 50 can be charged.

[0084] The portable device 50 for opening the door on the ground also includes an energy storage unit 54 and a portable device control module 55 connected to the energy storage unit 54. The portable device control module 55 is connected to the external unlocking interface 52 of the portable device external interface 51, and can transmit power and send control signals to the external unlocking interface 52, thereby providing power and sending control signals to the door lock 33 of the landing gear door opening and closing system 1 through the aircraft side external interface assembly 40, thereby controlling the door lock 33 to open and close the landing gear door 34. The portable device control module 55 is also connected to the charging interface 53. When the charging interface 53 is connected to an external power source, the energy storage unit 54 can be charged through the portable device control module 55 via the charging interface 53.

[0085] An exemplary embodiment of the energy storage unit 54 is a rechargeable battery. Of course, the energy storage unit 54 can also be a replaceable disposable battery. In this case, the charging interface 53 mentioned above can be omitted.

[0086] The portable ground door opening device 50 further includes a human-machine interaction interface 60 , through which an operator can operate the portable ground door opening device 50 to open and close the landing gear door.

[0087] Figure 3 A schematic stereogram of a portable ground door opening device 50 is shown. A human-machine interface 60 is provided on one side surface of the portable ground door opening device 50. The human-machine interface 60 includes a power switch 61, which is used to control the power supply state of the portable ground door opening device 50, such as power on, power off, etc. The human-machine interface 60 also includes an unlocking switch 62. By operating the unlocking switch 62, the maintenance personnel can issue an instruction to open the door lock 33 of the landing gear door 34. The instruction is transmitted to the door lock 33 through the portable device control module 55 of the portable ground door opening device 50 and then through the external unlocking interface 52 and the aircraft-side external interface component 40 on the aircraft.

[0088] The human-machine interaction interface 60 may also be provided with a plurality of indicator parts. Figure 3 In the case shown in , the human-machine interaction interface 60 further includes a charging status indicator 63 , a low battery indicator 64 , a connection status indicator 65 and an unlocking completion indicator 66 .

[0089] The charging status indicator 63 is configured to be unlit in the default state, emit a first color of light when charging the energy storage unit 54, and emit a second color of light when the energy storage unit 54 is full. Generally speaking, the first color is yellow and the second color is green.

[0090] The low battery indicator 64 is configured to be off in a default state, and to emit a third color of light when the power level of the energy storage unit 54 is lower than a predetermined threshold value. The third color of light is usually red.

[0091] The connection status indicator 65 is configured to be unlit in a default state, such as in a non-operating state, and in an operating state, such as when the external unlocking interface 52 is connected to the aircraft-side external interface assembly 40 on the aircraft, if the circuit connection between the ground door opening portable device 50 and the door lock 33 is abnormal, or the function of the door lock 33 is abnormal, the connection status indicator 65 emits a fourth color of light, and if the connection is normal, the connection status indicator 65 emits a fifth color of light. Here, generally speaking, the fourth color is red and the fifth color is green.

[0092] The unlocking completion indicator 66 is configured not to light up in a default state, but to emit light of a sixth color, for example, green light, when the portable device control module 55 detects that the unlocking is completed.

[0093] In addition to the above disclosed method of indicating the various states of the landing gear door opening and closing system 1 by emitting light of different colors, other methods can also be used for indication. For example, for the charging state indicator 63, when the energy storage unit 54 is charged, the charging state indicator 63 displays the word "charging" or an icon indicating charging, and when the energy storage unit 54 is fully charged, the charging state indicator 63 displays the word "full" or similar words, or displays an icon indicating full. In addition, the charging state indicator 63 can also emit sound signals, using different sounds to indicate states such as the start of charging and full charging.

[0094] Similarly, the low power indicator 64, the connection status indicator 65 and the unlocking completion indicator 66 may also display text signals, icon signals, etc., and may also emit sound signals. These variant implementations are all within the scope of the present application.

[0095] Figure 4 The schematic structural diagram of the aircraft side external interface assembly 40 is shown. The aircraft side external interface assembly 40 is arranged on the aircraft, and includes at least one ground door opening equipment interface, for example, in the case of the above-mentioned three landing gears 32 and the corresponding three landing gear doors 34, it includes three interfaces, namely the first interface 41, the second interface 42 and the third interface 43, which correspond to the left main landing gear door, the right main landing gear door and the front landing gear door respectively.

[0096] In addition to the protective cover 44 mentioned above, each interface can also be covered by an interface cover 45. When the external unlocking interface 52 of the ground-based portable door opening device 50 is connected to the corresponding interface of the aircraft-side external interface assembly 40 to control the corresponding door lock, the interface cover 45 can be removed to expose each interface. The interface cover 45 can preferably be connected to the aircraft fuselage through a structure such as a tether / chain, such as Figure 4 In this way, when the interface cover 45 is removed from the interface, the interface cover 45 can be prevented from accidentally falling off.

[0097] The illustrated structure includes three interfaces, which are used for the left main landing gear door, the right main landing gear door and the front landing gear door, respectively, so that the left door lock, the right door lock and the front door lock can be controlled separately. In addition, other number of interfaces can be provided as required. For example, the aircraft side external interface assembly 40 can include only one interface, through which the left door lock, the right door lock and the front door lock can be controlled simultaneously. For another example, two interfaces can be included, one of which corresponds to the front landing gear door, and the other corresponds to the left main landing gear door and the right main landing gear door. In this case, the front door lock can be controlled separately, while the left door lock and the right door lock are controlled together. These variant structures are also within the scope of the present application.

[0098] The following will describe the operation method of opening and closing the landing gear door of the present application with respect to the structure of the landing gear door opening and closing system 1 described above:

[0099] When the landing gear door needs to be opened on the ground, if there is a situation where the aircraft's power system fails, the aircraft is sealed for too long and loses power, etc., and cannot provide power, the maintenance personnel can choose to open the interface protection cover of the corresponding aircraft-side external interface assembly 40 on the aircraft, and connect the portable device external interface 51 of the ground door opening portable device 50 to the corresponding aircraft-side external interface assembly 40 of the landing gear door 34 to be opened through a connecting wire. Of course, in this step, if the aircraft-side external interface assembly 40 does not have an interface protection cover, the action of opening the interface protection cover can be omitted.

[0100] Next, the ground-based door opening portable device 50 is turned on, for example, by pressing the power switch 61 on the human-machine interface 60. After that, the low-battery indicator 64, the connection status indicator 65 and other indicators on the human-machine interface 60 are used to determine whether the ground-based door opening portable device 50 has sufficient power and is connected normally.

[0101] After confirming that the ground door opening portable device 50 has sufficient power and is connected normally, the unlocking switch 62 is pressed, and the signal of pressing the unlocking switch 62 is transmitted to the portable device control module 55, and an unlocking signal is generated in the portable device control module 55.

[0102] The unlocking signal is transmitted to the corresponding cabin door lock 33 through the external unlocking interface 52 and the aircraft-side external interface assembly 40 , completing the operations of opening and resetting the cabin door lock 33 .

[0103] After detecting that the door lock 33 is opened, the unlocking completion indicator 66 on the human-machine interface 60 lights up, indicating that the unlocking is completed. At this time, the maintenance personnel can turn off the power switch 61 on the human-machine interface 60 of the ground door opening portable device 50 and disconnect the connection with the aircraft side external interface assembly 40 on the aircraft.

[0104] Additionally, if the low power indicator 64 shows that the power of the energy storage unit 54 in the ground door opening portable device 50 is low after the ground door opening portable device 50 is opened, the energy storage unit 54 of the ground door opening portable device 50 can be charged first through the charging interface 53.

[0105] The preferred embodiments of the present application are described in detail above. Those skilled in the art can make various obvious variations and modifications based on the above disclosure, and these are still within the scope of the present application.

Claims

1. A portable ground door opening device, the portable ground door opening device being included in an aircraft landing gear door opening and closing system, characterized in that: The portable device for opening a hatch door on the ground comprises: A portable device external interface, the portable device external interface comprising an external unlocking interface; a portable device control module, the portable device control module being communicatively connected to the portable device external interface; and An energy storage unit is connected to the portable device control module so as to provide power to the portable device control module.

2. The portable ground door opening device according to claim 1, characterized in that: The portable device external interface also includes a charging interface, and the charging interface can be connected to an external power source to charge the energy storage unit.

3. The portable ground door opening device according to claim 1, characterized in that: The ground-based portable door opening device further comprises a human-machine interaction interface, which is communicatively connected with the portable device control module, and the human-machine interaction interface comprises: a power switch, the power switch controlling the power supply state of the energy storage unit to the electrical control module of the landing gear door opening and closing system; and An unlock switch is used to issue an instruction to open the door lock of the landing gear door opening and closing system.

4. The portable ground door opening device according to claim 3, characterized in that: The human-computer interaction interface further includes at least one of the following indication parts: A charging status indicator, the charging status indicator is configured to send a first signal when the energy storage unit is charged, and send a second signal when the energy storage unit is fully charged; A low-battery indicator configured to send a third signal when the amount of electricity in the energy storage unit is lower than a predetermined threshold; a connection status indicator configured to send out a fourth signal when the circuit connection in the landing gear door opening and closing system is abnormal and / or the door lock function is abnormal, and to send out a fifth signal when the connection is normal; and The unlocking completion indicating unit is configured to emit a sixth signal when unlocking is completed.

5. A landing gear door opening and closing system for an aircraft, the landing gear door opening and closing system comprising: power supply; an electrical control module, the power source and the electrical control module to provide power to the power source; at least one landing gear uplock, the landing gear uplock being communicatively connected to the electrical control module; and at least one door lock, wherein the door lock is in communication with the electrical control module; wherein the landing gear door opening and closing system further comprises: The portable ground door opening device according to any one of claims 1 to 4; and An aircraft-side external interface component is arranged on the aircraft, connected between the electrical control module and the door lock, and is configured to be connectable to the external unlocking interface, thereby allowing the opening and closing of the landing gear door to be manipulated by the ground-based portable door opening device.

6. The landing gear door opening and closing system according to claim 5, characterized in that: The landing gear uplock includes a front landing gear uplock, a left main landing gear uplock and a right main landing gear uplock, which are used to lock the front landing gear, the left main landing gear and the right main landing gear respectively; and The door locks include a front door lock, a left door lock and a right door lock, which are used to lock the front landing gear door, the left main landing gear door and the right main landing gear door respectively; The structure of the aircraft-side external interface assembly is one of the following: The aircraft-side external interface assembly includes three interfaces, which are respectively connected between the front cabin door lock, the left cabin door lock, the right cabin door lock and the electrical control module; The aircraft-side external interface assembly includes two interfaces, one of which is connected between the front door lock and the electrical control module, and the other is connected between the left door lock and the right door lock and the electrical control module; The aircraft-side external interface assembly includes an interface, and the interface is connected between the front door lock, the left door lock, the right door lock and the electrical control module.

7. The landing gear door opening and closing system according to claim 5, characterized in that: The aircraft-side external interface assembly is provided with an interface protection cover.

8. An aircraft, characterized in that: The aircraft comprises the landing gear door opening and closing system according to any one of claims 5 to 7.

9. A method for opening and closing a landing gear door, characterized in that: The method uses the landing gear door opening and closing system according to any one of claims 5 to 7, and comprises the following steps: Connecting the charging interface of the ground-based portable device for opening the cabin door to the aircraft-side external interface assembly on the aircraft; Turning on the portable ground door opening device to confirm whether the power in the energy storage unit is sufficient and whether the circuit connection in the landing gear door opening and closing system is normal; as well as After confirming that the energy storage unit has sufficient electricity and the circuit connection in the landing gear door opening and closing system is normal, the ground-based portable door opening device is operated to unlock and reset the door lock.

10. The method according to claim 9, characterized in that After the unlocking is completed, the ground-based portable door opening device is turned off, and the connection between the external unlocking interface and the aircraft-side external interface assembly is disconnected.

11. The method according to claim 9, characterized in that After the ground-based portable door opening device is turned on, if it is detected that the power in the energy storage unit is insufficient, the energy storage unit is charged first.

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