Actuator systems for aircraft doors

Abstract

The present invention relates to an actuator system for an aircraft cabin door, comprising: a gas storage and monitoring unit (20), which is used to store high-pressure gas that generates power to open the aircraft cabin door and monitor the pressure of the high-pressure gas; a gas generation unit (10), which is used to release the high-pressure gas in the gas storage and monitoring unit (20); and a buffer actuation unit (40), which is used to provide a buffer for the actuator system during the process of the actuator system actuating the aircraft cabin door. The actuator system also includes a gas pressure-stabilizing buffer device (30) arranged between the gas generation unit (10) and the buffer actuation unit (40), which guides the high-pressure gas to enter the buffer actuation unit (40) in a stable state and adjusts the pressure of the high-pressure gas to a preset value. The above-mentioned actuator system can reduce the weight of the system itself without affecting the performance and function of the system.

Description

Technical Field

[0001] The present invention relates to an actuator system, in particular to an actuator system for an aircraft cabin door, and more specifically to an actuator system for emergency opening of an aircraft cabin door. Background Art

[0002] Aircraft doors primarily provide access to the aircraft cabin for passengers and crew, and allow them to quickly evacuate the cabin in an emergency. To this end, aircraft doors are typically designed to complete emergency opening in no more than 10 seconds, including the inflation of devices such as slides to facilitate this rapid evacuation.

[0003] Most of the existing aircraft doors store high-pressure nitrogen as energy storage for emergency opening of the doors. Some aircraft doors also use mechanical springs as energy storage, or use chemicals as energy storage.

[0004] When storing high-pressure gas, it needs to be depressurized after release to meet actuation requirements. Existing door actuators are almost always equipped with dedicated pressure-reducing devices, which not only increase the manufacturing cost of the actuator but also increase its weight.

[0005] Ideally, a hatch door actuator would maintain a stable buffer pressure throughout the entire operating process. However, to achieve this pressure stability throughout the entire operating process, the pneumatic actuators of existing actuators typically have a complex structure, which increases the weight of the actuator itself.

[0006] For example, in PCT application WO2004 / 041639A1, entitled "System for Emergency Door Actuation," filed by Eator Inc. on November 6, 2003, an emergency door opening device for an aerospace vehicle is disclosed, which is used to move the vehicle door from a closed position to an open position. The device includes a fluid cylinder and a piston operably connected to the door and the vehicle, as well as a supply or gas generating chemical. When ignited, the supply or gas generating chemical can quickly generate a sufficient amount of gas and supply it to the fluid cylinder to move the fluid cylinder and the piston, thereby achieving the opening of the door. However, as previously mentioned, in order to achieve pressure stability throughout the entire working process, the pneumatic actuator it is equipped with is relatively complex in structure, and the actuator itself is heavy, which is not conducive to the operator's operation.

[0007] In order to solve the above problems, the industry has developed various improved actuator systems.

[0008] For example, Chinese patent application CN113251010A, entitled "Emergency Door Actuation," filed by Radie-Fiac GmbH on February 9, 2021, discloses an emergency actuation device for opening a door. The emergency actuation device includes at least one pressurized gas supply; an actuator comprising an actuator chamber; an actuator piston movable between a retracted position and a fully extended position to open the door; and a vent for venting the actuator chamber when the actuator piston is in its extended position. The emergency actuation device also includes an impact device comprising an impact piston movable between a stored position and an activated position upon activation of the impact device. In the stored position, the pressurized gas supply is isolated from the actuator; in the activated position, the pressurized gas supply is coupled to the actuator. The actuator is coupled to the impact device and is configured such that movement of the actuator piston toward its activated position resets the impact piston.

[0009] These emergency actuation devices utilize only the pressurized gas required to operate the actuator. Therefore, no excess gas is wasted because the flow of pressurized gas into the system is stopped after the actuator is operated. Furthermore, because a limited amount of pressurized gas is exhausted from the device, the device takes less time to vent than conventional devices. This means the actuator can return to atmospheric pressure more quickly, allowing the door to reclose in a shorter time after activation.

[0010] However, the above design still has disadvantages. Although this emergency actuating device also utilizes compressed air as a power source and drives the piston to expand and contract so as to output power, its internal structure, especially the structure of the impact device, is very complicated.

[0011] Therefore, it is necessary to design an actuator system for an aircraft door, which can reduce the weight of the system itself without affecting the performance and function of the system. Summary of the Invention

[0012] An object of the present invention is to provide an actuator system for an aircraft cabin door, wherein the actuator system can reduce the weight of the system itself without affecting the performance and function of the system.

[0013] The present invention discloses an actuator system for an aircraft cabin door, comprising:

[0014] a gas storage and monitoring unit, which is used to store high-pressure gas for generating power to open the aircraft door and monitor the pressure of the high-pressure gas;

[0015] a gas generating unit for releasing high-pressure gas in the gas storage and monitoring unit; and

[0016] A buffer actuation unit, which is used to provide buffering for the actuator system during the process of the actuator system actuating the aircraft cabin door,

[0017] Among them, the actuator system also includes a gas pressure-stabilizing buffer device arranged between the gas generating unit and the buffer actuating unit. The gas pressure-stabilizing buffer device guides the high-pressure gas into the buffer actuating unit in a stable state and adjusts the pressure of the high-pressure gas to a preset value.

[0018] In a preferred embodiment, the gas pressure stabilizing buffer device may include:

[0019] A gas check assembly, which is used to guide high-pressure gas to flow into the buffer actuation unit in a one-way manner; and

[0020] A pressure stabilizing component is used to adjust the pressure of the high-pressure gas flowing to the buffer actuating unit through the gas check component to a preset value.

[0021] In a more preferred embodiment, the pressure stabilizing component may be a surrounding spiral air duct, which surrounds the gas storage volume of the gas storage and monitoring unit and is buried in the peripheral wall of the gas storage volume.

[0022] In another preferred embodiment, the gas check assembly may be disposed within the first sealing component of the gas generating unit and include:

[0023] a gas outflow channel provided in the first sealing member;

[0024] a gas inlet and a gas outlet located at both ends of the gas outflow channel; and

[0025] A non-return element movably placed in the gas outflow passage, the non-return element:

[0026] As the high-pressure gas enters the gas outflow channel, the internal gas pressure of the gas check assembly begins to rise when it reaches a critical point, so that the gas outflow channel opens, causing the high-pressure gas to enter the pressure stabilizing assembly through the gas outlet; and

[0027] When the internal gas pressure of the gas check assembly drops below the critical point, it falls back to its original position to close the gas outflow channel.

[0028] The term "movably" indicates that the check element can move within the gas outflow passage. In other words, there is space within the gas outflow passage that allows the check element to remain in a certain position and move out of that position. When the check element remains in that position, the gas outflow passage is blocked by the check element, thus being closed. When the check element moves out of that position, the gas outflow passage is no longer blocked by the check element and is therefore open.

[0029] In a preferred embodiment, the non-return element may be made of metal, and its outer surface is covered with a sealing material.

[0030] In an alternative embodiment, an elastic component for applying an external force to the non-return element may be provided between the non-return element and the gas flow channel.

[0031] In this alternative embodiment, the critical point at which the gas outflow passage switches from a closed state to an open state is when the force exerted by the high-pressure gas on the non-return element equals the sum of the elastic force exerted by the elastic component on the non-return element and the weight of the non-return element itself. In other words, compared to the previous embodiment, the elastic force exerted by the elastic component on the non-return element is increased.

[0032] Additionally, the gas generating unit may include:

[0033] a trigger end that moves in response to an external force applied thereto;

[0034] a safety pin receptacle that prevents movement of the trigger end after a safety pin is inserted therein;

[0035] a safety hole fixing end, the safety hole fixing end being used to fix the trigger end to the gas storage and monitoring unit; and

[0036] The generating end is associated with the triggering end so as to move along with the movement of the triggering end.

[0037] In a preferred embodiment, the generating end may be in the form of a sharp needle with a pointed end, and the pointed end punctures the sealing diaphragm of the gas storage and monitoring unit and releases the high-pressure gas in the gas storage and monitoring unit as the generating end moves.

[0038] In a more preferred embodiment, a first sealing component may be further included, and the first sealing component is arranged at the interface between the gas generating unit and the gas storage and monitoring unit to prevent gas from leaking out.

[0039] In addition, the gas storage and monitoring unit may include a gas release switch, a gas storage volume and an air pressure monitoring component, wherein the gas release switch and the air pressure monitoring component are arranged at both ends of the gas storage volume to at least reduce the interference with the monitored pressure when the gas flows out of the gas storage volume.

[0040] In a preferred embodiment, the gas release switch can be arranged adjacent to the sealing diaphragm of the gas storage and monitoring unit. When the generating end of the gas generating unit punctures the sealing diaphragm, the gas release switch opens and releases the high-pressure gas in the gas storage volume.

[0041] In addition, the buffer actuation unit may include:

[0042] A buffer actuating unit body associated with the gas pressure-stabilizing buffer device;

[0043] An actuator cylinder is sleeved inside the buffer actuator unit body and is reciprocatingly movable relative to the buffer actuator unit body;

[0044] An inner oil cavity and an outer oil cavity;

[0045] an air inlet formed at one end of the buffer actuating unit body; and

[0046] An air cavity is formed inside the buffer actuating unit body.

[0047] In a preferred embodiment, the buffer actuation unit may further include an oil pressure compensation component, which is disposed in the oil cavity to compensate for changes in the oil volume.

[0048] Specifically, the oil pressure compensation component may be composed of a baffle and an elastic member that applies elastic force to the baffle.

[0049] In another preferred embodiment, a second sealing assembly may be arranged between the actuating cylinder and the buffer actuating unit body to prevent the gas in the air cavity from leaking into the oil outer cavity.

[0050] The actuator system for an aircraft door according to the present invention can achieve the following advantages:

[0051] (1) The buffer actuation unit of the actuator system has the advantages of simple structure and low manufacturing cost, and can effectively reduce the deadweight of the actuator system;

[0052] (2) The pressure stabilizing component of the gas pressure stabilizing buffer device of the actuator system adopts a surrounding spiral airway, the structure of which is integrated with the gas storage volume of the gas storage and monitoring unit of the actuator system, without the need for additional separate design, which can effectively reduce the deadweight of the actuator system and has high pressure stabilization efficiency;

[0053] (3) The airflow check assembly of the gas pressure-stabilizing buffer device of the actuator system relies on the gravity of the check element and / or the external force applied to the check element to prevent the airflow from checking. It has a simple structure, high operational reliability, low manufacturing difficulty, and a long service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] In order to further illustrate the technical effects of the actuator system for an aircraft cabin door according to the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments, wherein:

[0055] Figure 1 is an overall front sectional view showing an actuator system for emergency opening of an aircraft door according to the present invention;

[0056] Figure 2 is with Figure 1 a similar elevational cross-sectional view showing more detail of the actuator system;

[0057] Figure 3 Schematically shows the state of the actuator system according to the present invention in which the piston rod is extended after the gas is released;

[0058] Figure 4A and 4B Shown in an enlarged manner Figure 1 the closed and opened working states of the airflow check assembly of the gas pressure stabilizing buffer device; and

[0059] Figure 5A and 5B The closed and opened working states of another airflow check component of the gas pressure stabilizing and buffering device are respectively shown in an enlarged manner.

[0060] Reference numerals

[0061] 10 Gas generation unit

[0062] 11 Trigger terminal

[0063] 12 Safety pin socket

[0064] 13 Safety hole fixed end

[0065] 14 First sealing component

[0066] 15 Occurrence end

[0067] 151 Originator

[0068] 152 air barrier

[0069] 153 Sealing gasket

[0070] 20 Gas storage and monitoring unit

[0071] 21 Gas release switch

[0072] 22 Gas storage capacity

[0073] 23 Gas Monitoring Components

[0074] 24 Storage device fixing assembly

[0075] 30 Gas pressure stabilizing buffer device

[0076] 31 Gas check assembly

[0077] 311 Gas Outflow Channel

[0078] 312 Gas Inlet

[0079] 313 non-return element

[0080] 314 Gas outlet

[0081] 315 elastic components

[0082] 32 voltage stabilizing components

[0083] 40 Buffer actuator

[0084] 41 Buffer actuator body

[0085] 42 Actuator

[0086] 43 Oil cavity

[0087] 44 Oil outer cavity

[0088] 45 air intake

[0089] 46 air cavity

[0090] 47 Oil pressure compensation assembly

[0091] 48 Second sealing assembly

[0092] 49 spherical plain bearings

[0093] F Airflow DETAILED DESCRIPTION

[0094] The structure and technical effects of the actuator system for an aircraft door according to the present invention will be described below with reference to the accompanying drawings.

[0095] It should be understood that the embodiments described in this specification only cover some embodiments of the present invention, not all embodiments. Based on the embodiments described in this specification, all other embodiments obtained by persons of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0096] Unless otherwise defined, all technical and scientific terms used in the present invention have the same meaning as commonly understood by those skilled in the art to which the present invention pertains. The terms used in the specification of the present invention are for the purpose of describing specific embodiments only and are not intended to limit the present invention. The terms "including" and "having" and any variations thereof in the specification and claims of the present invention and the above-mentioned description of the drawings are intended to cover non-exclusive inclusions. The singular forms "a", "said" and "the" used in the embodiments of the present invention and the appended claims are also intended to include plural forms unless the context clearly indicates otherwise.

[0097] Based on the same understanding of orientation, in the description of the present invention, the orientation or position relationship indicated by the terms "length", "inside", "outside", "front", "back", etc. is based on the orientation or position relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0098] Figure 1 and 2 Both show an actuator system for an aircraft door according to the present invention. Figure 1 As shown, the actuator system is composed of a gas generating unit 10, a gas storage and monitoring unit 20, a gas pressure stabilizing buffer device 30, and a buffer actuating unit 40, wherein the gas pressure stabilizing buffer device 30 is arranged between the gas generating unit 10 and the buffer actuating unit 40. The above components will be described one by one below.

[0099] Gas generation unit

[0100] like Figure 2 The gas generating unit 10 is used to release the high-pressure gas in the gas storage and monitoring unit 20 , and includes but is not limited to a trigger end 11 , a safety pin insertion hole 12 , a safety hole fixing end 13 , a first sealing component 14 and a generating end 15 .

[0101] The trigger end 11 is generally flat in shape so as to be moved by the external force applied by the operator. Of course, the trigger end 11 may be modified, such as by adding a recess at the location where the external force is applied to accommodate the operator's finger. Such modifications are obvious to those skilled in the art.

[0102] The safety pin insertion hole 12 is used to receive a safety pin (not shown). When the safety pin is inserted into the safety pin insertion hole 12, the trigger end 11 is prevented from moving after receiving an external force. When the safety pin is removed from the safety pin insertion hole 12, the trigger end 11 can move after receiving an external force.

[0103] The safety hole fixing end 13 is used to fix the trigger end 11 of the gas generating unit 10 to the gas storage and monitoring unit 20 on the one hand, and to fix the trigger end 11 after the safety pin is inserted into the safety pin insertion hole 12 on the other hand.

[0104] The generating end 15 is associated with the triggering end 11 so as to move with the movement of the triggering end 11. The generating end 15 preferably has a sharp needle form with a pointed end, which can pierce the sealing membrane of the gas storage and monitoring unit 20 and release the high-pressure gas in the gas storage and monitoring unit 20 as the generating end 15 moves.

[0105] The first sealing member 14 is provided at the interface between the gas generating unit 10 and the gas storage and monitoring unit 20. Specifically, the first sealing member 14 is provided around the space required for the telescopic movement of the generating end 15 to prevent gas from the gas storage and monitoring unit 20 from escaping.

[0106] Gas storage and monitoring unit

[0107] The gas storage and monitoring unit 20 is used to store high-pressure gas for generating power to open the aircraft door, and monitor the pressure of the high-pressure gas stored therein.

[0108] The gas storage and monitoring unit 20 includes, but is not limited to, a gas release switch 21, a gas storage volume 22, and a gas pressure monitoring assembly 23. The gas storage volume 22 constitutes the main body of the unit. The gas release switch 21 is disposed at the outlet of the gas storage volume 22, and the gas pressure monitoring assembly 23 is disposed at any location suitable for monitoring the internal pressure of the gas storage volume 22, thereby monitoring the gas pressure within the gas storage volume 22. Preferably, the gas release switch 21 and the gas pressure monitoring assembly 23 are disposed at both ends of the gas storage volume 22 to minimize or avoid interference with the monitored pressure when gas flows out of the gas storage volume 22.

[0109] The gas release switch 21 is arranged adjacent to the sealing diaphragm of the gas storage and monitoring unit 20. When the tip of the generating end 15 of the gas storage and monitoring unit 20 punctures the sealing diaphragm, the gas release switch 21 opens under the action of the generating end 15 and releases the high pressure gas in the gas storage volume 22.

[0110] The gas storage volume 22 is used to store high-pressure gas. It can be integrated, that is, it is integrated with other units of the actuator system (for example, the buffer actuator unit 40), or it can be separated, that is, the gas storage volume 22 can be removed from other units of the actuator system.

[0111] Where a separate gas storage volume 22 is employed, the gas storage volume 22 is preferably secured by means of a storage device securing assembly 24 .

[0112] Gas pressure stabilizing buffer device

[0113] The gas pressure-stabilizing buffer device 30 is arranged between the gas generating unit 10 and the buffer actuation unit 40, and is used to guide the high-pressure gas leaving the gas storage and monitoring unit 20 into the buffer actuation unit 40 in a stable state, and adjust the pressure of the high-pressure gas to a preset value so that the actuator system has the required stable force when it starts to actuate, and can also prevent gas backflow.

[0114] The gas pressure-stabilizing buffer device 30 includes but is not limited to a gas check assembly 31 and a pressure-stabilizing assembly 32 .

[0115] The gas check assembly 31 is used to guide the unidirectional flow of high-pressure gas into the buffer actuation unit 40. In other words, it fixes the gas flow direction to prevent the gas from flowing back due to external forces. The gas check assembly 31 is disposed within the first sealing component 14 of the gas generating unit 10. This ensures that the high-pressure gas from the gas storage and monitoring unit 20 only enters the first sealing component 14 and reaches the buffer actuation unit 40 after the tip of the trigger end 11 punctures the sealing diaphragm of the gas storage and monitoring unit 20 and opens the gas release switch 21 to release the gas.

[0116] Figure 4A and 4B The diagram shows the operating states of the airflow check assembly 31 in both closed and open states. The airflow check assembly 31 includes a gas outflow channel 311 defined in the first sealing member 14 of the gas generating unit 10, a gas inlet 312 and a gas outlet 314 located at both ends of the gas outflow channel 311, and a check element 313 movably positioned within the gas outflow channel 311.

[0117] As previously mentioned, the generating end body 151 in the generating end 15 for puncturing the sealing diaphragm has a needle shape. An air blocking plate 152 is mounted on the generating end body 151. The size of the air blocking plate 152 is roughly the same as the internal size of the space enclosed by the first sealing component 14 and the gas release switch 21 (that is, the space required for the generating end 15 to move telescopically as mentioned previously), so that it abuts against the inner surface of the first sealing component 14, so that when the pressure on both sides of the air blocking plate 152 changes, the air blocking plate 152 is pushed and the generating end body 151 is driven to move back and forth in the above space without gas leakage. In order to further enhance the anti-leakage capability, a sealing gasket 153 can also be added to the air blocking plate 152, and the sealing gasket 153 and the air blocking plate 152 are concentrically and continuously mounted on the generating end body 151.

[0118] The working process of the airflow check assembly 31 will be described in detail below.

[0119] As the tip of the generating end body 151 of the generating end 15 moves downward and punctures the sealing diaphragm of the gas release switch 21, the gas release switch 21 opens and releases the high-pressure gas stored in the gas storage volume 22. Once the high-pressure gas is released, the pressure on both sides of the air blocking plate 152 changes. The high-pressure airflow pushes the air blocking plate 152 and, together with the generating end body 151, rises until the gas inlet 312 of the gas outflow channel 311 opens. At this point, the high-pressure gas enters the airflow check assembly 31 through the gas inlet 312. As the high-pressure gas continues to enter the gas outflow channel 311, the check element 313 placed within the gas outflow channel 311 gradually rises, completely opening the gas outflow channel 311. The gas then enters the pressure stabilizing assembly 32 through the gas outlet 314. When the internal gas pressure of the gas check assembly 31—that is, the gas pressure at the gas inlet 312 and the gas outlet 314—reaches a certain critical point, the check element 313 falls back to its original position due to its own gravity, sealing the gas outflow channel 311 and thus preventing the return of the gas flow.

[0120] It is easy for those skilled in the art to understand that the non-return element 313 is only an example, and any component that relies on gravity to prevent airflow from non-return should fall within the protection scope required by the present invention.

[0121] The check element 313 can be a check ball made of metal to ensure that it has sufficient gravity to close the gas outflow channel 311. The outer surface of the check ball can be covered with a sealing material, such as a rubber layer, to prevent high-pressure gas leakage or gravity impact from causing structural damage.

[0122] The gas outflow channel 311 includes an internal space for the check element 313 to rise and a shaped structure within which the check element 313 is seated. Of course, those skilled in the art may modify the internal structure of the gas outflow channel 311 to accommodate different check components placed within the gas flow channel 311, and such modifications are intended to fall within the scope of the present invention.

[0123] Figure 5A and 5B Another improved airflow check assembly 31 is shown in its working states of being closed and opened.

[0124] and Figure 4A and 4B Compared to the example shown, Figure 5A and 5B The improvement of the airflow check assembly 31 shown is that an elastic assembly 315 for applying an external force to the check element 313 is further provided between the check element 313 and the gas flow channel 311 .

[0125] With the help of the elastic component 315, when no high-pressure gas is being released, the airflow check assembly 31 uses the elastic force exerted by the elastic component 315 combined with the weight of the check element 31 itself to press down the check element 313. At this point, the airflow check assembly 31 is in a normally closed state. After the high-pressure gas is released, once the internal gas pressure reaches a critical pressure, the check element 313 is lifted by the airflow F, thereby opening the airflow check assembly 31 and releasing the airflow F. As the airflow F continues to be released, the internal gas pressure of the gas check assembly 31 gradually decreases and tends to fall below the critical pressure. At this point, the elastic component 315 presses the check element 313 downward again to its original position, closing the gas outflow channel 311 and thus preventing the return of airflow.

[0126] and Figure 4A and 4B Compared to the example shown, Figure 5A and 5B Since the airflow check assembly 31 shown is subjected to two different forces at the same time, its working state will be more stable, which helps to reduce or even eliminate the undesirable working state caused by the pressure disturbance of the high-pressure gas.

[0127] The pressure stabilizing assembly 32 is used to adjust the pressure of the high-pressure gas flowing to the buffer actuation unit 40 through the airflow check assembly 31 to a preset value, so that the actuator system has the required stable force when it starts to actuate.

[0128] The pressure stabilizing device 32 is preferably a surrounding spiral air duct, which surrounds the gas storage volume 22 of the gas storage and monitoring unit 20 and is embedded in the peripheral wall of the gas storage volume 22 in a spiral form. Figure 2 As shown, one end of the spiral air channel is positioned adjacent to the gas outlet 314 of the gas outflow channel 311, and the other end is positioned adjacent to, for example, the storage device fixing assembly 24, so as to introduce the reduced-pressure airflow flowing in the spiral air channel into the buffer actuation unit 40. The spiral air channel can be distributed within the peripheral wall of the gas storage volume 22 along the entire length of the peripheral wall, or can be distributed only in a portion of the peripheral wall of the gas storage volume 22.

[0129] During the gas flow process, the airflow is depressurized by means of friction, and the heat generated by friction is efficiently absorbed when the high-pressure gas is released.

[0130] Buffer actuator

[0131] The buffer actuation device 40 is used to provide a buffer for the actuator system during its actuation process, so as to enable the actuator system to brake smoothly and avoid collision between the piston and the cylinder body / cylinder head.

[0132] The buffer actuating unit 40 includes but is not limited to a buffer actuating unit body 41 , an actuating cylinder 42 , an oil inner cavity 43 , an oil outer cavity 44 , an air inlet 45 , an air cavity 46 , an oil pressure compensation assembly 47 , a second sealing assembly 48 and a spherical bearing 49 .

[0133] The buffer actuation unit body 41 is associated with the gas pressure-stabilizing buffer device 30 , that is, the buffer actuation unit body 41 and the gas pressure-stabilizing buffer device 30 are integrated, or fixed together with the gas pressure-stabilizing buffer device 30 by means of the storage device fixing assembly 24 .

[0134] The actuator cylinder 42 is concentrically mounted inside the buffer actuator unit body 41 and can move back and forth relative to the buffer actuator unit body 41. The interior of the actuator cylinder 42 is filled with oil. Figure 3 As shown, the space inside the actuator cylinder 42 can be defined as an oil inner cavity 43 , and the space between the actuator cylinder 42 and the buffer actuator unit body 41 can be defined as an oil outer cavity 44 .

[0135] An air inlet 45 is formed at one end of the buffer actuating unit body 41. This air inlet 45 communicates with the air outlet 314 of the air outflow passage 311 of the airflow check assembly 31. As the actuating cylinder 42 moves outward relative to the buffer actuating unit body 41, air from the air outflow passage 311 enters the buffer actuating unit body 41 through the air inlet 45, forming an air cavity 46 within the buffer actuating unit body 41.

[0136] A second sealing assembly 48 is disposed between the actuating cylinder 42 and the buffer actuating unit body 41 to prevent the gas in the gas cavity 46 from leaking into the oil outer cavity 44 .

[0137] An oil pressure compensation assembly 47 is provided in the oil chamber 43 to compensate for changes in the oil volume. The oil pressure compensation assembly 47 typically comprises a baffle and an elastic member (e.g., a spring) that applies an elastic force to the baffle, thereby compensating for changes in the oil volume in the oil chamber 43 caused by actuation or temperature changes.

[0138] The operating principle of the buffer actuator unit 40 will be described in detail below: As the airflow from the pressure stabilizing device 32 is introduced into the buffer actuator unit 40, it enters the air chamber 46 in the buffer actuator unit body 41 through the air inlet 45. As the pressure in the air chamber 46 gradually increases, the actuator cylinder 42 is pushed outward and actuated. As the actuator cylinder 42 moves outward, the buffer hydraulic oil in the oil outer chamber 44 is squeezed and enters the oil inner chamber 43, providing a buffer during the actuation of the actuator cylinder 42, allowing the actuator system to brake smoothly and preventing collision between the actuator cylinder 42 and the body / cylinder head. During the actuation process, the change in the oil volume in the oil inner chamber 43 is compensated by the oil pressure compensation component 47.

[0139] While the structure and operating principles of the actuator system for an aircraft door according to the present invention have been described above in conjunction with preferred embodiments and accompanying drawings, those skilled in the art will recognize that the above examples are for illustrative purposes only and are not intended to limit the present invention. For example, the check ball of the airflow check assembly may be replaced with a block of substantially equal weight. Therefore, modifications and variations of the present invention may be made within the spirit of the claims, and such modifications and variations will fall within the scope of the claims.

Claims

1. An actuator system for an aircraft door, comprising: A gas storage and monitoring unit (20), the gas storage and monitoring unit (20) is used to store high-pressure gas for generating power to open the aircraft door, and to monitor the pressure of the high-pressure gas; A gas generating unit (10), the gas generating unit (10) being used to release the high-pressure gas in the gas storage and monitoring unit (20); as well as A buffer actuation unit (40), the buffer actuation unit (40) is used to provide buffering for the actuator system during the process of the actuator system actuating the aircraft cabin door, The actuator system further comprises a gas pressure stabilizing buffer device (30) disposed between the gas generating unit (10) and the buffer actuating unit (40), wherein the gas pressure stabilizing buffer device (30) guides the high-pressure gas to enter the buffer actuating unit (40) in a stable state and adjusts the pressure of the high-pressure gas to a preset value. The gas pressure stabilizing buffer device (30) comprises: A gas check assembly (31), the gas check assembly (31) being used to guide the high-pressure gas to flow unidirectionally into the buffer actuation unit (40); and A pressure stabilizing component (32), the pressure stabilizing component (32) being used to regulate the pressure of the high-pressure gas flowing to the buffer actuating unit (40) via the gas check component (31) to the preset value, It is characterized in that the pressure stabilizing component (32) is a surrounding spiral air duct, and the spiral air duct surrounds the gas storage volume (22) of the gas storage and monitoring unit (20) and is buried in the peripheral wall of the gas storage volume (22).

2. The actuator system according to claim 1, wherein: The gas check assembly (31) is arranged in the first sealing component (14) of the gas generating unit (10) and comprises: a gas outflow channel (311) provided in the first sealing component (14); a gas inlet (312) and a gas outlet (314) located at both ends of the gas outflow channel (311); and A non-return element (313) movably placed in the gas outflow channel (311), wherein the non-return element (313): As the high-pressure gas enters the gas outflow channel (311), the internal gas pressure of the gas check assembly (31) begins to rise when it reaches a critical point, so that the gas outflow channel (311) opens, causing the high-pressure gas to enter the pressure stabilizing assembly (32) through the gas outlet (314); and When the internal gas pressure of the gas check component (31) falls below the critical point, it falls back to its original position, so that the gas outflow channel (311) is closed.

3. The actuator system according to claim 2, wherein: The non-return element (313) is made of metal, and its outer surface is covered with a sealing material.

4. The actuator system according to claim 2, wherein: An elastic component (315) for applying an external force to the non-return element (313) is provided between the non-return element (313) and the gas outflow channel (311).

5. The actuator system according to claim 1, wherein: The gas generating unit (10) comprises: a trigger end (11), the trigger end (11) moving in response to an external force applied thereto; a safety pin insertion hole (12), wherein the safety pin insertion hole (12) is capable of preventing the trigger end (11) from moving after the safety pin is inserted therein; a safety hole fixing end (13), the safety hole fixing end (13) being used to fix the trigger end (11) to the gas storage and monitoring unit (20); and a generating end (15), the generating end (15) being associated with the triggering end (11) so as to move with the movement of the triggering end (11), The generating end (15) is in the form of a sharp needle with a pointed tip at one end, and the pointed tip punctures the sealing diaphragm of the gas storage and monitoring unit (20) and releases the high-pressure gas in the gas storage and monitoring unit (20) as the generating end (15) moves. The actuator system further comprises a first sealing component (14), which is arranged at the interface between the gas generating unit (10) and the gas storage and monitoring unit (20) to prevent gas from leaking out.

6. The actuator system according to claim 5, wherein: The gas storage and monitoring unit (20) comprises a gas release switch (21), a gas storage volume (22) and a gas pressure monitoring assembly (23), wherein the gas release switch (21) and the gas pressure monitoring assembly (23) are arranged at both ends of the gas storage volume (22) to at least reduce interference with the monitored pressure when the gas flows out of the gas storage volume (22). The gas release switch (21) is arranged adjacent to the sealing diaphragm of the gas storage and monitoring unit (20), and when the generating end (15) of the gas generating unit (10) punctures the sealing diaphragm, the gas release switch (21) opens and releases the high-pressure gas in the gas storage volume (22).

7. The actuator system according to claim 1, wherein: The buffer actuation unit (40) comprises: A buffer actuation unit body (41) associated with the gas pressure-stabilizing buffer device (30); an actuating cylinder (42) which is sleeved inside the buffer actuating unit body (41) and is reciprocatingly movable relative to the buffer actuating unit body (41); An oil inner cavity (43) and an oil outer cavity (44); an air inlet (45) formed at one end of the buffer actuating unit body (41); and An air cavity (46) is formed inside the buffer actuation unit body (41).

8. The actuator system according to claim 7, wherein: The buffer actuation unit (40) further includes an oil pressure compensation component (47), which is arranged in the oil inner cavity (43) to compensate for changes in oil volume.

9. The actuator system according to claim 8, wherein: The oil pressure compensation component (47) is composed of a baffle and an elastic member that applies elastic force to the baffle.

10. The actuator system according to claim 7, wherein: A second sealing assembly (48) is arranged between the actuating cylinder (42) and the buffer actuating unit body (41) to prevent the gas in the air cavity (46) from leaking into the oil outer cavity (44).

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