Aircraft fuel system quick-release connector assembly and aircraft

Abstract

The present invention relates to an aircraft fuel system quick-release connector assembly and an aircraft. The aircraft fuel system quick-release connector assembly includes a male component on the aircraft fuel system side and a female component on the engine side. The male component on the aircraft fuel system side includes an externally threaded portion at one end thereof, a flange located behind the externally threaded portion, and a boss located on the flange. The female component on the engine side includes an inner slidable sleeve, an intermediate sleeve, a second internally threaded sleeve, and an outermost slidable sleeve, which are arranged in sequence from the inside to the outside. The internally threaded portion of the second internally threaded sleeve is used to cooperate with the externally threaded portion to form a threaded connection, and the outermost slidable sleeve is provided with a slot for forming a snap fit with the boss. The female component on the engine side also includes a first return spring and a second return spring. The first return spring is fixed to the second internally threaded sleeve and the outermost slidable sleeve, and the second return spring is fixed to the intermediate sleeve and the inner slidable sleeve.

Description

Technical Field

[0001] The present invention relates to an aircraft fuel system quick-disconnect connector assembly and an aircraft incorporating the assembly, specifically to the technical field of aircraft fuel system pipeline connections. The aircraft fuel system quick-disconnect connector assembly enables rapid connection and disconnection between the aircraft fuel system's fuel supply pipeline and the engine's fuel pipeline. It is primarily used to connect the interface pipeline between the aircraft fuel system and the engine, facilitating disconnection between the fuel system and the engine during airline operations and maintenance. Background Art

[0002] The fuel supply line of the civil aircraft fuel system and the engine fuel line need to be connected through a pipe connector. Considering the importance of the engine fuel supply system, the convenience of operation and maintenance, and the inconsistency of the working environment of the pipelines on both sides, it is necessary to design a high-reliability quick-disconnect connector device that can be quickly disassembled.

[0003] Due to the small space inside the suspension, the operating space for maintenance personnel is extremely limited. Therefore, the quick-release connector needs to be operable with one hand. There is no need to observe the movement of the device. The successful docking or disconnection of the pipelines on both sides can be judged only by the sound and feel of the device when connected.

[0004] Quick-release connectors are generally installed on the firewall inside the aircraft's suspension. The fuel supply pipeline environment on the aircraft's fuel system side is a non-fire zone, while the fuel pipeline environment on the engine side is a fire zone. Therefore, quick-release connectors must have certain fire resistance properties.

[0005] Since flammable fuel flows in the pipeline, in order to prevent fuel from leaking from the pipeline connection and causing the fire to spread when a fire occurs, the quick-release joint must have highly reliable sealing properties.

[0006] However, there is no quick-release connector specifically designed for use in aircraft fuel system engine fuel supply scenarios in the prior art. Summary of the Invention

[0007] One object of the present invention is to provide an aircraft fuel system quick-disconnect connector assembly that is specifically designed for aircraft fuel system engine fuel supply scenarios and can be used to connect the aircraft fuel system fuel supply line and the engine fuel line, enabling rapid connection and disconnection between the aircraft fuel system fuel supply line and the engine fuel line while meeting the stringent fire resistance requirements of airworthiness requirements and the convenience requirements of route operations and maintenance.

[0008] The above objectives of the present invention are achieved by an aircraft fuel system quick-disconnect connector assembly, the aircraft fuel system quick-disconnect connector assembly comprising an aircraft fuel system-side male component and an engine-side female component, the aircraft fuel system-side male component and the engine-side female component being adapted to engage with each other when the aircraft fuel system quick-disconnect connector assembly is in a connected state;

[0009] The aircraft fuel system side male component includes an external threaded portion at one end thereof, a flange located at the rear side of the external threaded portion, and a boss located on the flange;

[0010] The engine-side female component includes, arranged in order from the inside out, an inner slidable sleeve, an intermediate sleeve, a second internally threaded sleeve, and an outermost slidable sleeve. The internal threaded portion of the second internally threaded sleeve is configured to cooperate with the externally threaded portion of the aircraft fuel system-side male component to form a threaded connection. The outermost slidable sleeve has a retaining groove at its end proximal to the aircraft fuel system-side male component for retaining engagement with a boss on the aircraft fuel system-side male component.

[0011] Among them, the engine-side female head component also includes a first return spring and a second return spring, one end of the first return spring is fixed to the second layer of internally threaded sleeve, and the other end is fixed to the outermost sliding sleeve, and one end of the second return spring is fixed to the middle layer sleeve, and the other end is fixed to the inner layer sliding sleeve.

[0012] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: it can realize the rapid connection and disconnection between the aircraft fuel system fuel supply line and the engine fuel line, while meeting the stringent fire resistance requirements of airworthiness requirements and the convenience requirements of route operation and maintenance.

[0013] Preferably, the engine-side female component further includes a hollow air layer formed between the second layer of internally threaded sleeve and the outermost layer of slidable sleeve.

[0014] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: in response to the stringent fire resistance requirements at the interface between the aircraft fuel system fuel supply line and the engine fuel line, a specially designed insulating hollow air layer is used to slow the conduction of heat into the quick-disconnect connector, thereby better meeting the stringent fire resistance requirements.

[0015] Preferably, the engine-side female head component further includes a self-sealing head base and a detachable self-sealing head installed within the inner slidable sleeve, and the detachable self-sealing head is detachably connected to the self-sealing head base.

[0016] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: a unique detachable self-sealing head is designed on the female side of the quick-disconnect connector to ensure the self-sealing properties of the female head and facilitate the removal and replacement of the self-sealing part there.

[0017] Preferably, the engine-side female head component further includes a first self-sealing member located between the detachable self-sealing head and the inner slidable sleeve.

[0018] Preferably, the engine-side female head component further includes a second self-sealing member located between the inner slidable sleeve and the middle sleeve.

[0019] Preferably, the aircraft fuel system quick-disconnect joint assembly further comprises a first joint seal located between the inner slidable sleeve and the inner side of the aircraft fuel system-side male component.

[0020] Preferably, the aircraft fuel system quick-disconnect joint assembly further comprises a second joint seal located between the intermediate sleeve and the front end of the aircraft fuel system-side male component.

[0021] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: a quadruple sealing pair is designed to ensure sealing in the docking state and to ensure that no leakage occurs in the working state.

[0022] Preferably, the bosses are symmetrically arranged on the flange, and the grooves are also symmetrically arranged on the end of the outermost slidable sleeve.

[0023] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: through the symmetrical arrangement of bosses and slots, the male and female components are better aligned and limited, making it easier to confirm the docking status of the connectors on both sides during installation.

[0024] Preferably, the engine-side female head component further includes a friction reducing element provided between the second layer of internally threaded sleeve and the outermost layer of slidable sleeve.

[0025] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: it can reduce the friction resistance when the outermost slidable sleeve and the second layer of the internally threaded sleeve move relative to each other.

[0026] The above object of the present invention is also achieved by an aircraft, comprising the aircraft fuel system quick-disconnect connector assembly according to any one of the above aspects.

[0027] According to the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: it can realize the rapid connection and disconnection between the aircraft fuel system fuel supply pipeline and the engine fuel pipeline, while meeting the stringent fire resistance requirements of airworthiness requirements and the convenience requirements of route operation and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1A The figure is a front view of a quick-disconnect connector assembly for an aircraft fuel system according to an embodiment of the present invention.

[0029] Figure 1B FIG2 is a perspective view of an aircraft fuel system quick-disconnect connector assembly according to an embodiment of the present invention.

[0030] Figure 2A The figure is a cross-sectional schematic diagram of an aircraft fuel system quick-disconnect connector assembly in a docking (connected) state according to an embodiment of the present invention.

[0031] Figure 2B The figure is a cross-sectional schematic diagram of an aircraft fuel system quick-disconnect connector assembly in a separated (disconnected) state according to an embodiment of the present invention.

[0032] Figure 3 Schematic diagram of the installation of a first return spring of an aircraft fuel system quick-disconnect connector assembly according to another embodiment of the present invention.

[0033] Reference Signs List

[0034] 0: Female connector on the engine side;

[0035] 1: Aircraft fuel system side male components;

[0036] 2: Inner sliding sleeve;

[0037] 3: middle layer sleeve;

[0038] 4: The second layer has an internal threaded sleeve;

[0039] 5: Outermost sliding sleeve;

[0040] 6: Self-sealing head base;

[0041] 7: first self-sealing member;

[0042] 8: first joint seal;

[0043] 9: Hollow air layer;

[0044] 10: second joint sealing member;

[0045] 11: second self-sealing member;

[0046] 12: first return spring;

[0047] 13: Anti-friction element

[0048] 14: Second return spring;

[0049] 15: internal thread part;

[0050] 16: card slot;

[0051] 17: Detachable self-sealing head;

[0052] 18: Anti-slip pattern;

[0053] 21: external thread portion;

[0054] 22: flange;

[0055] 23: Boss. DETAILED DESCRIPTION

[0056] The specific embodiments of the present invention will be described below. It should be noted that in the specific description of these embodiments, in order to provide a concise description, this specification cannot provide a detailed description of all the features of the actual embodiments. It should be understood that in the actual implementation of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the present invention, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means and should not be understood as the content of this disclosure being insufficient.

[0057] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the usual meaning understood by persons of ordinary skill in the technical field to which the invention belongs. The words "first", "second" and similar terms used in the description and claims of the patent application of the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. Words such as "one" or "a" do not indicate a quantity limitation, but rather indicate the existence of at least one. Words such as "include" or "comprising" mean that the elements or objects appearing before "include" or "comprising" cover the elements or objects listed after "include" or "comprising" and their equivalent elements, and do not exclude other elements or objects. Words such as "connected" or "connected" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0058] In the following description, in order to clearly show the structure and working mode of the present invention, many directional words will be used for description, but words such as "front", "back", "left", "right", "outside", "inside", "outward", "inward", "up", and "down" should be understood as convenient terms and should not be understood as restrictive terms.

[0059] Figure 1A The figure is a front view of a quick-disconnect connector assembly for an aircraft fuel system according to an embodiment of the present invention. Figure 1B FIG2 is a perspective view of an aircraft fuel system quick-disconnect connector assembly according to an embodiment of the present invention. Figure 2A The figure is a cross-sectional schematic diagram of an aircraft fuel system quick-disconnect connector assembly in a docking (connected) state according to an embodiment of the present invention. Figure 2B The figure is a cross-sectional schematic diagram of an aircraft fuel system quick-disconnect connector assembly in a separated (disconnected) state according to an embodiment of the present invention. Figure 3 Schematic diagram of the installation of a first return spring of an aircraft fuel system quick-disconnect connector assembly according to another embodiment of the present invention.

[0060] like Figures 1A to 3 As shown, according to some embodiments of the present invention, an aircraft fuel system quick-disconnect connector assembly includes an aircraft fuel system-side male component 1 and an engine-side female component 0, wherein the aircraft fuel system-side male component 1 and the engine-side female component 0 are configured to interface with each other when the aircraft fuel system quick-disconnect connector assembly is in a connected state;

[0061] The aircraft fuel system side male component 1 includes an external threaded portion 21 at one end thereof, a flange 22 located at the rear side of the external threaded portion 21, and a boss 23 located on the flange 22;

[0062] The engine-side female component 0 includes, arranged sequentially from the inside out, an inner slidable sleeve 2, an intermediate sleeve 3, a second internally threaded sleeve 4 (the so-called second layer refers to the second layer counted from the outside in), and an outermost slidable sleeve 5. The internal threaded portion 15 of the second internally threaded sleeve 4 is configured to mate with the external threaded portion 21 of the aircraft fuel system-side male component 1 to form a threaded connection. The outermost slidable sleeve 5 has a retaining groove 16 at its end proximal to the aircraft fuel system-side male component 1 for retaining engagement with a boss 23 on the aircraft fuel system-side male component 1.

[0063] Among them, the engine-side female head component 0 also includes a first return spring 12 and a second return spring 14. One end of the first return spring 12 is fixed to the second layer of internally threaded sleeve 4, and the other end is fixed to the outermost sliding sleeve 5. One end of the second return spring 14 is fixed to the middle layer sleeve 3, and the other end is fixed to the inner layer sliding sleeve 2.

[0064] According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: it can realize the rapid connection and disconnection between the aircraft fuel system fuel supply line and the engine fuel line, while meeting the stringent fire resistance requirements of airworthiness requirements and the convenience requirements of route operation and maintenance.

[0065] Specifically, after the quick-release connector assembly rotates into position, the female component's slot engages the male component's boss under the force of the spring, creating a crisp metallic clashing sound and a noticeable change in the operating feel. This design allows ground crew to connect and disconnect the connector assembly in confined spaces without visual inspection and to determine the connection status. Furthermore, the unique return spring design limits its circumferential movement, resolving the issue of the outermost sliding sleeve easily rotating after docking.

[0066] In some embodiments, as Figure 1A to Figure 1B As shown, the male connector 1 on the aircraft fuel system side is mounted on the aircraft structure via a flange 22. The mounting surface is typically the firewall at the front end of the aircraft pylon. The mounting screws are inserted from the threaded side and, after tightening, are coated with a fire-retardant sealant to protect the structural integrity of the firewall and prevent flames from penetrating the firewall structure. The flange 22 must be made of a fire-resistant material.

[0067] In some embodiments, as Figure 1A to Figure 1B As shown, the pipelines outside the fuel tank of a typical aircraft fuel system are all double-sleeved, so the quick-disconnect connector assembly is connected to the aircraft fuel system side with a double-sleeved connector. The quick-disconnect connector assembly is designed with a fuel supply hose connector (e.g., a threaded connector) at the end connecting to the engine side.

[0068] In some embodiments, as Figures 2A to 2B As shown, the engine-side female connector component 0 further includes a hollow air layer 9 formed between the second internally threaded sleeve 4 and the outermost slidable sleeve 5. According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: To meet the stringent fire resistance requirements at the interface between the aircraft fuel system fuel supply line and the engine fuel line, a specially designed insulating hollow air layer is designed to slow heat transfer into the quick-disconnect connector, thereby better meeting these stringent fire resistance requirements.

[0069] In some embodiments, as Figures 2A to 2BAs shown, the engine-side female connector component 0 further includes a self-sealing head base 6 mounted within the inner slidable sleeve 2 and a detachable self-sealing head 17. The detachable self-sealing head 17 is detachably connected (e.g., threadedly connected) to the self-sealing head base 6. According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: a unique detachable self-sealing head is designed on the female side of the quick-disconnect connector to ensure the self-sealing properties of the female connector component and facilitate the removal and replacement of the self-sealing member therein.

[0070] Preferably, if Figures 2A to 2B As shown, the self-sealing head base 6 can be fixed by a three-claw bracket to ensure stability while ensuring fuel flow.

[0071] Preferably, if Figures 2A to 2B As shown, the head of the detachable self-sealing head 17 has a unique spherical flow guide design.

[0072] In some embodiments, as Figures 2A to 2B As shown, the engine side female head component 0 further includes a first self-sealing member 7 (eg, a sealing ring) located between the detachable self-sealing head 17 and the inner slidable sleeve 2. In some embodiments, as shown in FIG. Figures 2A to 2B As shown, the engine side female head component 0 further includes a second self-sealing member 11 (eg, a sealing ring) located between the inner slidable sleeve 2 and the middle sleeve 3. In some embodiments, as shown in FIG. Figures 2A to 2B As shown, the aircraft fuel system quick-disconnect connector assembly further includes a first connector seal 8 (e.g., a sealing ring) located between the inner slidable sleeve 2 and the inner side of the aircraft fuel system side male component 1. In some embodiments, as shown in FIG. Figures 2A to 2B As shown, the aircraft fuel system quick-disconnect connector assembly further includes a second connector seal 10 (e.g., a sealing ring) positioned between the intermediate sleeve 3 and the front end of the aircraft fuel system-side male connector 1. Based on the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention achieves the following beneficial technical effects: a quadruple sealing pair is designed to ensure tightness in the mated state, preventing leakage during operation.

[0073] In some embodiments, as Figure 1A to Figure 1B As shown, the bosses 23 are symmetrically arranged on the flange 22, and the slots 16 are also symmetrically arranged on the end of the outermost slidable sleeve 5. Figure 1A to Figure 1B As shown, two bosses 23 are symmetrically arranged on either side of the diameter of flange 22, and two retaining grooves 16 are also symmetrically arranged on either side of the diameter of the end of the outermost slidable sleeve 5. According to the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: the symmetrical arrangement of bosses and retaining grooves improves the alignment and positioning of the male and female components, facilitating confirmation of the mating state of the two connectors during installation.

[0074] Preferably, if Figure 1A to Figure 1B As shown, the cross section of the boss 23 may be rectangular, and the cross section of the latching groove 16 may also be rectangular accordingly.

[0075] In some embodiments, as Figures 2A to 2B As shown, the engine-side female connector component 0 further includes a friction-reducing element 13 (e.g., a ball bearing) disposed between the second internally threaded sleeve 4 and the outermost slidable sleeve 5. Based on the above technical solution, the aircraft fuel system quick-disconnect connector assembly of the present invention can achieve the following beneficial technical effects: it can reduce frictional resistance during relative motion between the outermost slidable sleeve and the second internally threaded sleeve.

[0076] In some embodiments, as Figure 1A to Figure 1B As shown, the outermost slidable sleeve 5 is provided with anti-slip grooves 18 on its outer surface, preferably two circles of anti-slip grooves.

[0077] In some embodiments, as Figure 3 As shown, one end of the first return spring 12 is fixed to the second-layer internally threaded sleeve 4, and the other end is fixed to the outermost slidable sleeve 5. Preferably, the two ends of the first return spring 12 are bent 90 degrees, with one end inserted into the corresponding hole in the second-layer internally threaded sleeve 4, and the other end inserted into the corresponding hole in the outermost slidable sleeve 5. This design ensures that the outermost slidable sleeve 5 can move axially relative to the second-layer internally threaded sleeve 4. After docking, the outermost slidable sleeve 5 is reset under the action of the spring force. When the outermost slidable sleeve 5 rotates circumferentially, it can drive the second-layer internally threaded sleeve 4 to rotate together and dock with the male component on the other side. At the same time, after the threads are tightened to the bottom, the side of the first return spring 12 connected to the second-layer internally threaded sleeve 4 is fixed, which can limit the circumferential movement of the other side of the first return spring 12 and ensure the accuracy of the subsequent docking between the boss and the slot.

[0078] In some embodiments, as Figures 2A to 2B As shown, one end of the second return spring 14 is fixed to the middle sleeve 3, and the other end is fixed to the inner slidable sleeve 2. During docking, the inner slidable sleeve 2 is pushed open by the front end of the male component on the other side, forming a connecting channel between the two joints. During separation, the inner slidable sleeve 2 is reset under the action of the spring force, forming a self-seal between the removable self-sealing head 17. Similarly, the two ends of the second return spring 14 can also be bent 90 degrees, with one end inserted into the corresponding hole in the middle sleeve 3 and the other end inserted into the corresponding hole in the inner slidable sleeve 2 to prevent the spring from circumferential movement.

[0079] According to one embodiment of the present invention, an aircraft includes an aircraft fuel system quick-disconnect connector assembly as described in any of the above aspects. Based on the above technical solutions, the aircraft of the present invention can achieve the following beneficial technical effects: it can quickly connect and disconnect the aircraft fuel system supply line and the engine fuel line, while meeting the stringent fire resistance requirements of airworthiness and the convenience required for route operations and maintenance.

[0080] The above describes the specific embodiments of the present invention, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation of the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. An aircraft fuel system quick-release connector assembly, characterized in that: The aircraft fuel system quick-disconnect connector assembly includes an aircraft fuel system side male component and an engine side female component, wherein the aircraft fuel system side male component and the engine side female component are used to connect with each other when the aircraft fuel system quick-disconnect connector assembly is in a connected state; The male component on the aircraft fuel system side includes an external threaded portion at one end thereof, a flange located at the rear side of the external threaded portion, and a boss located on the flange; The engine-side female component includes, arranged in order from the inside out, an inner slidable sleeve, an intermediate sleeve, a second internally threaded sleeve, and an outermost slidable sleeve. The internal threaded portion of the second internally threaded sleeve is configured to cooperate with the externally threaded portion of the aircraft fuel system-side male component to form a threaded connection. The outermost slidable sleeve has a retaining groove at its end proximal to the aircraft fuel system-side male component for retaining engagement with a boss on the aircraft fuel system-side male component. Among them, the engine-side female head component also includes a first return spring and a second return spring, one end of the first return spring is fixed to the second layer of internally threaded sleeve, and the other end is fixed to the outermost sliding sleeve, and one end of the second return spring is fixed to the middle layer sleeve, and the other end is fixed to the inner layer sliding sleeve.

2. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The engine-side female component further includes a hollow air layer formed between the second layer of the internally threaded sleeve and the outermost layer of the slidable sleeve.

3. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The engine-side female head component further includes a self-sealing head base and a detachable self-sealing head installed within the inner slidable sleeve, wherein the detachable self-sealing head is detachably connected to the self-sealing head base.

4. The aircraft fuel system quick-disconnect connector assembly according to claim 3, wherein: The engine-side female head component further includes a first self-sealing member located between the detachable self-sealing head and the inner slidable sleeve.

5. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The engine-side female component further includes a second self-sealing member located between the inner slidable sleeve and the middle sleeve.

6. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The aircraft fuel system quick-disconnect joint assembly further includes a first joint seal located between the inner slidable sleeve and the inner side of the aircraft fuel system-side male component.

7. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The aircraft fuel system quick-disconnect joint assembly further includes a second joint seal located between the intermediate sleeve and the front end of the aircraft fuel system-side male component.

8. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The bosses are symmetrically arranged on the flange, and the clamping grooves are also symmetrically arranged on the end of the outermost slidable sleeve.

9. The aircraft fuel system quick-disconnect connector assembly according to claim 1, wherein: The engine-side female head component further includes a friction reducing element arranged between the second layer of internally threaded sleeve and the outermost layer of slidable sleeve.

10. An aircraft comprising the aircraft fuel system quick-disconnect connector assembly according to any one of claims 1 to 9.

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