An aircraft external store pylon seal apparatus and method

Abstract

The application discloses an aircraft external hanging port sealing device and sealing method, and relates to the field of aircraft structure design. An installation support plate is fixedly arranged on the aircraft skin in the external hanging port. Longitudinal guide rail frames are arranged on the bottom surface of the installation support plate and correspond to the two sides of the external hanging port. Two mutually matched opening and closing plates are slidably installed on the longitudinal guide rail frames through slide rail joints. Tension springs are arranged between the end portions of the two opening and closing plates and can make the two opening and closing plates close. The end portion of a synchronous connecting rod is correspondingly hingedly connected to the end portion of one opening and closing plate. A synchronous pin shaft is slidably and limitingly installed in a horizontal slot of the installation support plate. When the two opening and closing plates are opened or closed, the two opening and closing plates keep synchronous relative movement under the limiting action of the double connecting rod structure. Sealing cover plates are hung below each opening and closing plate through multiple connecting rods. The energy dependence and response lag are overcome. The sealing locking is automatically triggered and completed at the moment when the external hanging object is abandoned only by relying on the built-in tension spring energy storage and release.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft structure design, in particular to an aircraft external hanging port sealing device and sealing method. BACKGROUND

[0002] With the development of aviation technology, the requirements of modern aircraft for multi-task adaptability and rapid task conversion capability are increasingly stringent. In order to improve the task flexibility, the aircraft generally sets external hanging points under the fuselage and wings for carrying various equipment, such as pods, auxiliary fuel tanks and other loads. During a specific task phase, these external hanging objects will be actively discarded. After the external hanging objects are discarded, the connection structure is disconnected, which will leave multiple opening structures on the aircraft skin. If these openings are not sealed in time and effectively, serious consequences will be caused: the continuity of the local aerodynamic shape is destroyed, which leads to a sharp increase in high-speed flight resistance and instability of high maneuverability; at the same time, the radar stealth performance is significantly weakened, and the risk of structure flutter caused by non-steady-state airflow pouring is induced, which poses a systematic threat to flight safety.

[0003] The existing sealing technology has significant limitations: the traditional flap relies on manual operation and cannot meet the task continuity requirement; the hydraulic drive mechanism has a slow response in low temperature environment and the system is heavy; the electric drive sealing device has defects such as insufficient control accuracy, weak anti-interference ability and continuous dependence on external energy. Therefore, a mechanical automatic filling flap is urgently needed, which can be automatically triggered instantly after the external hanging object is discarded without relying on external energy; the final sealing surface needs to maintain high aerodynamic conformity with the original aircraft surface; and it has the ability to resist high-speed airflow disturbance and reliably lock in a wide temperature range environment, so as to meet the stringent comprehensive requirements of modern aircraft for high speed, high maneuverability, stealth and reliability. SUMMARY

[0004] The purpose of the present application is to overcome the deficiencies of the prior art and provide an aircraft external hanging port sealing device and sealing method to solve the problem of safe and effective mechanical sealing of the aircraft external hanging port.

[0005] The present application is achieved by the following technical solutions:

[0006] An aircraft external hanging port sealing device, comprising an aircraft skin, a double connecting rod structure and an external hanging joint, a plurality of external hanging ports are formed on the aircraft skin, a mounting support plate is fixedly arranged on the aircraft skin in the external hanging port, a longitudinal guide rail frame is arranged on the bottom surface of the mounting support plate corresponding to both sides of the external hanging port, two mutually matched opening and closing plates are slidably installed on the longitudinal guide rail frame through a sliding rail joint, a tension spring capable of closing the two opening and closing plates is arranged between the end portions of the two opening and closing plates, the double connecting rod structure comprises two synchronous connecting rods hingedly connected through a synchronous pin shaft, the end portion of one synchronous connecting rod is hingedly connected to the end portion of one opening and closing plate, the synchronous pin shaft is slidably and limitingly installed in a longitudinal slot horizontally formed in the mounting support plate, when the two opening and closing plates are opened or closed, the two opening and closing plates are kept synchronous relative movement under the limiting action of the double connecting rod structure.

[0007] A sealing cover plate is hung below each opening and closing plate through a plurality of connecting rods, one end of the connecting rod is hingedly connected to the opening and closing plate, the other end of the connecting rod is hingedly connected to the sealing cover plate, a reset torsion spring is arranged on the hinged shaft connecting the connecting rod with the opening and closing plate or the sealing cover plate, under the action of the reset torsion spring, the two sealing cover plates hung below the two opening and closing plates tend to be butt-jointed and closed in real time; the external hanging joint is hung on the aircraft through the external hanging port.

[0008] Further, two sets of double connecting rod structures are respectively arranged corresponding to the two end portions of the two opening and closing plates.

[0009] Further, an external hanging port sealing control assembly corresponding to one set of double connecting rod structures is arranged on the top surface of the mounting support plate, the external hanging port sealing control assembly comprises an electric push rod and a synchronous pin shaft limiting frame, the synchronous pin shaft limiting frame is a T-shaped structure, a long limiting frame matched with the longitudinal slot is arranged on the horizontal frame of the synchronous pin shaft limiting frame, a long connecting slot movably connected with the electric push rod is arranged on the outer end of the longitudinal frame of the synchronous pin shaft limiting frame, the longitudinal frame of the synchronous pin shaft limiting frame is installed on the mounting support plate through a limiting rotating shaft at the middle position, when the longitudinal frame is perpendicular to the longitudinal slot, the long limiting frame is aligned with the longitudinal slot up and down;

[0010] The electric push rod is fixedly installed on the mounting support plate in parallel with the longitudinal slot, by controlling the electric push rod, when the telescopic rod of the electric push rod is half extended, the long limiting frame is aligned with the longitudinal slot up and down, the synchronous pin shaft of the double connecting rod structure is freely slid in the longitudinal slot, when the telescopic rod of the electric push rod is operated to the contracted state, the long limiting frame pushes the synchronous pin shaft to the inner end of the longitudinal slot, so that the two opening and closing plates are completely opened; when the telescopic rod of the electric push rod is operated to the extended state, the long limiting frame pushes the synchronous pin shaft to the outer end of the longitudinal slot, so that the two opening and closing plates are completely closed.

[0011] Further, the installation support plate top surface corresponding to another set of double connecting rod structure is provided with a travel switch trigger structure, the travel switch trigger structure includes a travel switch and a dial lever, the travel switch is provided with a dial lever for controlling the opening and closing of the travel switch, when the corresponding double connecting rod structure on the synchronous pin shaft is not at the outer end of the slot, the travel switch is in a closed state, the travel switch transmits a signal to the aircraft central control, and the aircraft central control displays the opening state of the external hanging port; when the corresponding double connecting rod structure on the synchronous pin shaft is at the outer end of the slot, the travel switch is in an open state, the travel switch transmits a signal to the aircraft central control, and the aircraft central control displays the closing state of the external hanging port.

[0012] Further, the electric push rod is connected to the aircraft central control, and the electric push rod can be controlled by the aircraft central control to realize three gear switching: the telescopic rod is in a half-elongated state, an elongated state and a retracted state; when the aircraft central control is operated to separate the external hanging joint from the aircraft, the aircraft central control does not receive the travel switch opening signal within a set time, and the aircraft central control controls the electric push rod to operate to the elongated state, the long limiting frame pushes the synchronous pin shaft to the outer end of the slot, and the two hinged plates are completely closed, so that the two sealing cover plates seal the external hanging port.

[0013] Further, the abutting surfaces of the two hinged plates are stopper surfaces, and the abutting surfaces of the two sealing cover plates are also stopper surfaces. When the sealing cover plates are in the state of being attached to the hinged plates, a gap is left between the sealing cover plates and the aircraft skin, and a stealth coating capable of absorbing radar waves is coated on the outer side surface of the sealing cover plates.

[0014] Further, the hinged plate locking structure includes a lock hook, a lock block, a guide rod and a return spring, the lock hook is a T-shaped structure, the longitudinal lock rod bottom end of the lock hook is installed on the upper side surface of one hinged plate through a rotating shaft, the longitudinal lock rod upper end is provided with a hook head, the transverse lock rod of the lock hook is movably connected with the guide rod vertically arranged on the hinged plate, the guide rod is inserted into the guide cylinder arranged on the hinged plate, and the return spring is sleeved on the guide rod; the lock block is arranged on the upper side surface of the other hinged plate corresponding to the hook head, the guide rod is elongated under the action of the return spring, when the two hinged plates are closed, the hook head at the longitudinal lock rod upper end is locked on the lock block, when the guide rod is retracted, the longitudinal lock rod rotates around the rotating shaft, and the hook head is separated from the lock block.

[0015] Further, the bottom end of the guide rod is connected to the maintenance interface through a pull rope, and the maintenance interface is arranged on the aircraft skin. When the two hinged plates are closed, the lock hook and the lock block are locked, when the two hinged plates need to be manually opened, the maintenance interface is rotated, the pull rope is retracted, the guide rod is retracted, the hook head is separated from the lock block, and the pull rope is further retracted, the two hinged plates are pulled to open, and the two sealing cover plates are also opened.

[0016] The present invention is achieved through the following another technical solution:

[0017] A method for sealing an aircraft external attachment port comprises the following steps:

[0018] Step 1: Open the opening and closing plate and the sealing cover by controlling the electric push rod or tightening the pull rope. The tension spring is in a stretched state. Install the external attachment on the aircraft through the external attachment connector.

[0019] Step 2: Control the electric push rod to make the telescopic rod in the semi-extended state, align the long limit frame with the straight slot, and adjust the maintenance interface to make the pull rope in a relaxed state; the docking surface of the two sealing cover plates rests on the external attachment joint;

[0020] Step 3: Use the aircraft's central control panel to detach the external attachment connector from the aircraft. Once the external attachment connector falls off the attachment port,

[0021] Step 4: The two opening and closing plates are closed under the action of the tension spring; during the closing process of the opening and closing plates, the two sealing cover plates are first butted and closed under the action of the return torsion spring, and the two sealing cover plates are aligned with the external hanging opening. As the two opening and closing plates gradually close, the connecting rod suspending the sealing cover plates gradually extends vertically. When the two opening and closing plates are completely closed, the two sealing cover plates are also sealed in the external hanging opening.

[0022] Step 5: When the two opening and closing panels are completely closed, the lock hook is locked on the lock block, and the two opening and closing panels are closed and locked.

[0023] Furthermore, when the external attachment connector falls from the external attachment port in step 3, the aircraft central control does not receive the travel switch on signal; the telescopic rod of the electric push rod of the aircraft central control is automatically triggered to run to the extended state gear, and the long limit frame pushes the synchronization pin shaft to the outer end of the slot, so that the two opening and closing plates are completely closed, and the two sealing cover plates are sealed in the external attachment port.

[0024] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0025] 1. The present invention provides an aircraft external attachment port sealing device and sealing method. The present invention creatively overcomes energy dependence and response hysteresis, achieving the goal of automatically triggering and completing the sealing and locking at the moment the external attachment is discarded without the need for additional actuating force or control signal, relying solely on the release of energy stored in a built-in tension spring. High-precision aerodynamic conformality is achieved, ensuring that the resulting sealing surface is smooth and continuous with the original aircraft surface, effectively maintaining the aerodynamic shape. The present invention solves the problem of unstable or failed closure in existing solutions under high-speed airflow impact and wide temperature range environments. Through a dual-mode architecture with pure mechanical main drive and electric backup, the risk of system paralysis caused by tension spring failure is fundamentally eliminated.

[0026] 2. The present invention provides a sealing device and a sealing method for an aircraft external hanging port. When the tension spring fails and the device cannot be closed after the external hanging is dropped, the travel switch detects the position state of the synchronization pin in real time, converts the physical displacement into an electrical signal and triggers the electric push rod to start. The electric push rod drives the synchronization pin limit frame to operate, so that the long limit frame on the synchronization pin limit frame directly moves the synchronization pin in the synchronization six-bar linkage mechanism, forcibly driving the entire synchronization six-bar linkage mechanism to move. This operating force replaces the failed tension spring and continuously drives the opening and closing plate and the sealing cover plate to close toward the middle until the locking hook and the locking block complete the mechanical locking, and at the same time the sealing cover plate is completely filled into the opening of the aircraft skin, ultimately achieving sealing and conformality between the sealing cover plate and the aircraft skin opening.

[0027] 3. The present invention provides an aircraft external port sealing device and a sealing method. The present invention provides a design of an external port sealing control component. The external port sealing control component includes an electric push rod and a synchronous pin shaft limit frame. It is a simple mechanical structure that realizes three control states of the double-link structure. The core point is that when the external port sealing device normally achieves sealing through the mechanical structure, the external port sealing control component will not produce interference. When the mechanical structure fails to achieve sealing, the external port sealing control component can effectively control the sealing structure to achieve sealing or opening. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The drawings described herein are used to provide a further understanding of the embodiments of the present invention, constitute a part of this application, and do not constitute a limitation of the embodiments of the present invention. In the drawings:

[0029] Figure 1 The present invention is a structural schematic diagram of an aircraft external attachment port sealing device after the external attachment joint is installed.

[0030] Figure 2 This is a structural schematic diagram of the opening and closing plate and the sealing cover plate of the present invention in a fully opened state.

[0031] Figure 3 This is a structural schematic diagram of the opening and closing plate and the sealing cover plate of the present invention in a fully closed state.

[0032] Figure 4 This is a schematic structural diagram of the opening and closing plate and the sealing cover plate before the external attachment joint is deployed in the present invention.

[0033] Figure 5 This is a structural diagram of the state of the opening and closing plate and the sealing cover plate in the closing process after the external attachment joint is deployed in the present invention.

[0034] Figure 6 This is a schematic structural diagram of the sealing cover plate in a closed state after the external attachment joint is deployed.

[0035] Figure 7Structure schematic diagram of the state that the docking surface of the opening and closing plate is closed, and the sealing cover plate is closed in the external hanging port after the external hanging object joint is put in.

[0036] Figure 8 Structure schematic diagram of the opening and closing plate locking structure of the present application.

[0037] Figure 9 Structure schematic diagram of the state that the telescopic rod of the electric push rod is in a half-elongated state, and the external hanging object joint is installed.

[0038] Figure 10 Structure schematic diagram of the state that the opening and closing plate and the sealing cover plate are completely opened by the electric push rod.

[0039] Figure 11 Structure schematic diagram of the state that the opening and closing plate and the sealing cover plate are completely closed by the electric push rod.

[0040] Figure 12 Structure schematic diagram of the state that the telescopic rod of the electric push rod is in a half-elongated state.

[0041] Figure 13 Structure schematic diagram of the state that the telescopic rod of the electric push rod is in an elongated state.

[0042] Figure 14 Structure schematic diagram of the state that the telescopic rod of the electric push rod is in a retracted state.

[0043] Figure 15 Principle schematic diagram of the electric push rod and the travel switch controlled by the aircraft central control.

[0044] Markings in the drawings and corresponding component names:

[0045] 1-aircraft skin, 2-external hanging object joint, 3-external hanging port, 4-installation support plate, 5-longitudinal guide rail frame, 6-opening and closing plate, 7-sliding rail joint, 8-tension spring, 9-synchronous pin shaft, 10-synchronous connecting rod, 11-slotted hole, 12-connecting rod, 13-sealing cover plate, 14-return torsional spring, 15-electric push rod, 16-synchronous pin shaft limiting frame, 17-long limiting frame, 18-long connecting groove, 19-longitudinal frame, 20-telescopic rod, 21-travel switch, 22-pull rod piece, 23-aircraft central control, 24-lock hook, 25-lock block, 26-guide rod, 27-return spring, 28-longitudinal lock rod, 29-lock hook head, 30-transverse lock rod, 31-guide cylinder, 32-pull rope, 33-maintenance interface. DETAILED DESCRIPTION

[0046] The technical solutions of the present application will be further described below by combining the drawings and through specific embodiments.

[0047] Among them, the accompanying drawings are only for illustrative purposes and represent only schematic diagrams rather than actual pictures, and should not be understood as limiting the present invention. In order to better illustrate the embodiments of the present invention, some parts of the accompanying drawings may be omitted, enlarged or reduced, and do not represent the dimensions of actual products. For those skilled in the art, it is understandable that some well-known structures and their descriptions may be omitted in the accompanying drawings.

[0048] The same or similar numbers in the drawings of the embodiments of the present invention correspond to the same or similar parts; in the description of the present invention, it should be understood that if the terms "upper", "lower", "left", "right", "inside", "outside" and the like indicate directions or positional relationships, they are based on the directions or positional relationships shown in the drawings, which are 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 direction, be constructed and operated in a specific direction. Therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes and cannot be understood as limiting the present invention. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances.

[0049] In the description of the present invention, unless otherwise expressly specified or limited, when the term "connection" or the like appears to indicate a connection relationship between components, such term should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be internal communication between two components or an interaction between two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood in specific circumstances.

[0050] Example 1

[0051] like Figures 1-15 As shown, the present invention provides an aircraft external attachment port sealing device, comprising an aircraft skin 1, a double-link structure, and an external attachment joint 2. The aircraft skin 1 is a dimensional component that surrounds the aircraft frame structure and is fixed to the frame with adhesive or rivets to form the aircraft's aerodynamic shape. The skin structure formed by the aircraft skin and the frame has a large load-bearing capacity and rigidity, while being very light in weight, and plays a role in bearing and transmitting aerodynamic loads. Figure 5 and Figure 6 As shown, a plurality of external attachment openings 3 are provided on the aircraft skin 1, such as Figure 4 As shown, the external attachment connector 2 is hung on the aircraft through the external attachment port 3 from the outside of the aircraft, as shown in FIG. Figures 1-3As shown, a mounting support plate 4 is fixedly provided on the aircraft skin 1 inside the external attachment port 3. The mounting support plate 4 is fixedly mounted inside the aircraft skin 1 corresponding to the external attachment port 3. An opening is also provided at a position corresponding to the external attachment port 3 for installing a channel for the external attachment connector 2. The external attachment connector 2 is the main supporting structure of the sealing device. The main sealing components are all installed in the cavity between the aircraft skin 1 and the mounting support plate 4; the external attachment port sealing control assembly and the travel switch are installed on the top surface of the mounting support plate 4.

[0052] like Figures 1-3 When the two opening and closing plates 6 are opened or closed, the two opening and closing plates 6 are kept in a state of synchronization with each other, and the two opening and closing plates 6 are kept in a state of synchronization with each other, and the two opening and closing plates 6 are kept in a state of synchronization with each other, and the two opening and closing plates 6 are kept in a state of synchronization with each other, and the two opening and closing plates 6 are kept in a state of synchronization with each other, and the two opening and closing plates 6 are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates are kept in a state of synchronization with each other, and the two opening and closing plates

[0053] like Figures 4-7 As shown, a sealing cover plate 13 is suspended below each opening and closing plate 6 through a plurality of connecting rods 12. In the embodiment, as shown in FIG. Figure 3 As shown, two parallel slots are provided on each opening and closing plate 6, and a connecting rod 12 is connected to each end of each slot via a hinge shaft. The lower end of the connecting rod 12 is also connected to the sealing cover plate 13 via a hinge shaft. The sealing cover plate 13, the opening and closing plate 6, and the connecting rod 12 form a parallelogram mechanism, which is used for sealing and conforming the external attachment port 3 at the opening of the aircraft skin 1.

[0054] One end of the connecting rod 12 is hinged to the opening and closing plate 6, and the other end is hinged to the sealing cover plate 13. A return torsion spring 14 is provided on the hinge axis connecting the connecting rod 12 to the opening and closing plate 6 or the sealing cover plate 13. Under the action of the return torsion spring 14, the two sealing cover plates 13 suspended below the two opening and closing plates 6 tend to mate and close in real time. The return torsion spring 14 is the power source for returning the sealing cover plates 13 when the device is opened. The sealing device uses the return torsion spring 14 as the return power source for the sealing cover plates 13. During the device opening process, it drives the sealing cover plates 13 to retract and return to their original position along the mechanism trajectory to avoid interference and collision with the aircraft skin 1. The external attachment connector 2 is mounted on the aircraft through the external attachment port 3.

[0055] A set of double-link structures are respectively provided at the two ends of the two opening and closing plates 6. The two opening and closing plates 6 and four synchronization links 10 form a six-link mechanism. The synchronization pin 9 serves as the connecting axis of the two synchronization links 10 and moves within the slot 11 on the mounting support plate 4, allowing the opening and closing plates 6 on both sides to open and close synchronously.

[0056] like Figures 1-7 As shown, the present invention provides an aircraft external attachment port sealing device, the working principle of which is as follows: an external attachment is installed on the aircraft through the external attachment joint 2; the mating surfaces of two sealing cover plates 13 are pressed against the external attachment joint 2; the external attachment joint 2 is separated from the aircraft by operating the aircraft central control 23, and the external attachment joint 2 falls from the external attachment port 3; the two opening and closing plates 6 are closed under the action of the tension spring 8; during the closing process of the opening and closing plates 6, the two sealing cover plates 13 are first butted and closed under the action of the return torsion spring 14, and the two sealing cover plates 13 are aligned with the external attachment port 3 in upper and lower directions; when the two opening and closing plates 6 are gradually closed, the connecting rod 12 suspending the sealing cover plates 13 gradually extends vertically; when the two opening and closing plates 6 are completely closed, the two sealing cover plates 13 are also sealed in the external attachment port 3.

[0057] Example 2

[0058] like Figures 1-15 As shown, the present invention is an aircraft external attachment port sealing device, based on the above embodiment, as Figures 9-11 As shown, an external hanging port sealing control component is provided on the top surface of the mounting support plate 4 corresponding to a set of double-link structures. In order to show the structural relationship between the external hanging port sealing control component and the double-link structure, Figure 10 and Figure 11 The structural diagram of the mounting support plate 4 has been deleted, and the external port sealing control assembly includes an electric push rod 15 and a synchronous pin limit frame 16. The synchronous pin limit frame 16 is a T-shaped structure, and the horizontal frame of the synchronous pin limit frame 16 is provided with a long limit frame 17 that matches the one-shaped groove 11. The slots of the one-shaped groove 11 and the long limit frame 17 are the same size, and together they play a limiting role on the synchronous pin 9. The outer end of the longitudinal frame 19 of the synchronous pin limit frame 16 is provided with a long connecting groove 18 that is movably connected to the electric push rod 15. The middle position of the longitudinal frame 19 of the synchronous pin limit frame 16 is installed on the mounting support plate 4 through a limiting shaft. When the longitudinal frame 19 is perpendicular to the one-shaped groove 11, the long limit frame 17 is aligned with the one-shaped groove 11 up and down.

[0059] like Figures 9-11As shown, the electric push rod 15 is fixedly installed in the installation support plate 4 in parallel with the slot 11, and the electric push rod 15 is controlled to be in a half-extended state, so that the long limiting frame 17 is aligned with the slot 11, and the synchronous pin shaft 9 of the double-link structure is freely slid in the slot 11; when the electric push rod 15 is in a retracted state, the long limiting frame 17 pushes the synchronous pin shaft 9 to the end of the slot 11, so that the two opening and closing plates 6 are completely opened; when the electric push rod 15 is in an extended state, the long limiting frame 17 pushes the synchronous pin shaft 9 to the end of the slot 11, so that the two opening and closing plates 6 are completely closed.

[0060] The design of the external hanging port sealing control assembly includes the electric push rod 15 and the synchronous pin shaft limiting frame 16, which is a simple mechanical structure, and three control states of the double-link structure are realized, and the core point is that when the external hanging port sealing device is normally sealed through the mechanical structure, the external hanging port sealing control assembly does not interfere, and when the mechanical structure fails to seal, the external hanging port sealing control assembly can effectively control the sealing structure to realize sealing or opening.

[0061] As shown in the figure, Figures 9-11 The installation support plate 4 is provided with a travel switch triggering structure corresponding to another set of double-link structures on the top surface, the travel switch triggering structure includes a travel switch 21 and a lever 22, the travel switch 21 is provided with the lever 22 for controlling the opening and closing of the travel switch 21, when the synchronous pin shaft 9 on the corresponding double-link structure is not at the end of the slot 11, the travel switch 21 is in a closed state, the travel switch 21 transmits a signal to the aircraft central control 23, and the aircraft central control 23 displays the opening state of the external hanging port 3; when the synchronous pin shaft 9 on the corresponding double-link structure is at the end of the slot 11, the travel switch 21 is in an open state, the travel switch 21 transmits a signal to the aircraft central control 23, and the aircraft central control 23 displays the closing state of the external hanging port 3.

[0062] As shown in the figure, Figure 15 The electric push rod 15 is controlled by the aircraft central control 23, and the aircraft central control 23 can control the electric push rod 15 to realize three gear shifts: the electric push rod 15 is in a half-extended state, an extended state and a retracted state, as shown in the figure Figures 12-14 The state of the electric push rod 15 and the synchronous pin shaft limiting frame 16 is shown, when the aircraft central control 23 is operated to separate the external hanging connector 2 from the aircraft, the aircraft central control 23 does not receive the opening signal of the travel switch 21 within a set time, the aircraft central control 23 controls the electric push rod 15 to be in an extended state, the long limiting frame 17 pushes the synchronous pin shaft 9 to the end of the slot 11, so that the two opening and closing plates 6 are completely closed, and the two sealing cover plates 13 are linked to seal the external hanging port 3.

[0063] AsFigure 11 As shown, when the external attachment connector 2 falls from the external attachment opening 3, the aircraft central control 23 does not receive the on signal from the travel switch 21; the aircraft central control 23 is automatically triggered to control the telescopic rod 20 of the electric push rod 15 to run to the extended state gear, and the long limit frame 17 pushes the synchronization pin 9 to the outer end of the straight groove 11, so that the two opening and closing plates 6 are completely closed, and the two sealing cover plates 13 are sealed in the external attachment opening 3.

[0064] Example 3

[0065] like Figures 1-15 As shown, the present invention is an aircraft external attachment port sealing device, based on the above embodiment, as Figure 3 As shown, the butt joint surfaces of the two opening and closing panels 6 are butt joint surfaces, and at the same time, the butt joint surfaces of the two sealing cover panels 13 are also butt joint surfaces. The butt joint surfaces make the butt joint seam not a straight line, which can increase the sealing performance. When the sealing cover panel 13 and the opening and closing panel 6 are in a fit state, a gap is left between the sealing cover panel 13 and the aircraft skin 1, and the outer surface of the sealing cover panel 13 is coated with a stealth coating that can absorb radar waves.

[0066] Example 4

[0067] like Figures 1-15 As shown, the present invention is an aircraft external hanging port sealing device, which, on the basis of the above embodiment, further includes an opening and closing plate locking structure, wherein the locking hook 24 and the locking block 25 are respectively installed on the two opening and closing plates 6, and are the locking structure when the device is closed; the opening and closing plate locking structure includes a locking hook 24, a locking block 25, a guide rod 26 and a return spring 27, the locking hook 24 is a T-shaped structure, the bottom end of the longitudinal locking rod 28 of the locking hook 24 is installed on the upper side of a door opening and closing plate 6 through a rotating shaft, the upper end of the longitudinal locking rod 28 is provided with a locking hook head 29, the transverse locking rod 30 of the locking hook 24 is vertically arranged The guide rod 26 on the opening and closing plate 6 is movably connected. The guide rod 26 is inserted into a guide cylinder 31 provided on the opening and closing plate 6, and a return spring 27 is sleeved on the guide rod 26. The return spring 27 is the power source for returning the lock hook 24. The lock block 25 and the lock hook head 29 are correspondingly provided on the upper side of the other opening and closing plate 6. When the guide rod 26 is extended by the return spring 27, the lock hook head 29 at the upper end of the longitudinal lock rod 28 locks with the lock block 25 when the two opening and closing plates 6 are closed. When the guide rod 26 is pulled back, the longitudinal lock rod 28 rotates about the rotation axis, and the lock hook head 29 is separated from the lock block 25. The lower end of the guide rod 26 that passes through the guide cylinder 31 is also provided with a limit end to limit the extension of the guide rod 26.

[0068] The bottom end of the guide rod 26 is connected to the maintenance interface 33 through the pull rope 32, and the maintenance interface 33 is arranged on the aircraft skin 1. When the two hinged plates 6 are closed, the locking hook 24 is locked with the locking block 25. When the two hinged plates 6 need to be opened manually, the maintenance interface 33 is rotated, the pull rope 32 is retracted, the guide rod 26 is retracted, the locking hook head 29 is separated from the locking block 25, and the two hinged plates 6 are pulled open. At the same time, the two sealing cover plates 13 are also opened. The maintenance interface 33 is a rotating and locking shaft structure, and the pull rope 32 can be wound.

[0069] The working principle of the device is that the synchronous six-bar linkage mechanism is used to realize the synchronous opening and closing of the hinged plates 6, and the parallelogram mechanism is used to realize the sealing and conforming of the sealing cover plates 13 to the aircraft skin 1.

[0070] When the external hanging object is maintained or installed on the ground, the locking hook 24 and the locking block 25 are separated to realize unlocking by using a tool to operate the guide rod 26 through the maintenance interface 33. Then, the device is opened by continuing to overcome the pulling force of the reset spring 27. In this process, the sealing cover plates 13 are retracted and reset under the action of the reset torsion spring 14 and the parallelogram mechanism, so as to avoid collision with the aircraft skin 1 and damage the coating on the sealing cover plates 13. At the same time, the sealing cover plates 13 are opened to the two sides synchronously with the hinged plates 6 under the action of the longitudinal guide rail frame 5 and the synchronous six-bar linkage mechanism. After the external hanging object connector 2 is installed, the hinged plates 6 are clamped on both sides of the external hanging object connector 2 under the action of the tension spring 8.

[0071] After the external hanging object is discarded, the hinged plates 6 on both sides are opened to the middle under the action of the tension spring 8 and the synchronous six-bar linkage mechanism without the external hanging object connector 2 blocking. In the movement process, the sealing cover plates 13 on both sides will first contact, and the hinged plates 6 on both sides have not yet closed. When the device continues to move, the sealing cover plates 13 sink and fill into the opening of the aircraft skin 1 under the action of the parallelogram mechanism. In this process, the locking block 25 on one side of the hinged plate 6 will abut against the locking hook 24 on the other side of the hinged plate 6, and the locking hook 24 will be forced to rotate to pass over the locking block 25 by using the inclined surface on the locking hook 24. Then, the locking hook 24 is reset and hooked on the locking block 25 under the action of the reset spring 27, so as to realize the locking of the device. When the device is closed and locked, and the extension step of the sealing cover plate 13 abuts against the aircraft skin 1, the sealing and conforming between the sealing cover plate 13 and the opening of the aircraft skin 1 are realized.

[0072] When the pull spring 8 fails to close the device after the external object is dropped, the travel switch 21 detects the position of the synchronization pin shaft 9 in real time, converts the physical displacement into an electrical signal, and triggers the electric push rod 15 to start. The electric push rod 15 drives the synchronization pin shaft limit rack 16 to act, and the long strip limit frame 17 on the synchronization pin shaft limit rack 16 directly drives the synchronization pin shaft 9 in the synchronization six-link mechanism, forcing the entire synchronization six-link mechanism to move. The actuation force replaces the failed pull spring 8 to continuously drive the opening and closing plate 6 and the sealing cover plate 13 to close to the middle, until the lock hook 24 and the lock block 25 complete mechanical locking, and at the same time the sealing cover plate 13 is completely filled into the opening of the aircraft skin 1, finally realizing the sealing and conformal between the sealing cover plate 13 and the opening of the aircraft skin 1.

[0073] Embodiment 5

[0074] As shown in the figure, a method for sealing an aircraft external hanging port, comprising the following steps: Figures 1-15

[0075] Step 1, open the opening and closing plate 6 and the sealing cover plate 13 by controlling the electric push rod 15 or the tensioned pull rope 32, the pull spring 8 is in a stretched state, and the external object is installed on the aircraft through the external object connector 2;

[0076] Step 2, control the electric push rod 15 to make the telescopic rod 20 in a semi-extended state, the long strip limit frame 17 is aligned with the slot 11, and the maintenance interface 33 is adjusted to make the pull rope 32 in a relaxed state; the two sealing cover plates 13 are butted against the external object connector 2;

[0077] Step 3, operate the aircraft central control 23 to make the external object connector 2 separate from the aircraft, and after the external object connector 2 falls from the external hanging port 3;

[0078] Step 4, the two opening and closing plates 6 are closed under the action of the pull spring 8; in the process of closing the opening and closing plate 6, the two sealing cover plates 13 are first closed under the action of the return torsion spring 14, the two sealing cover plates 13 are aligned with the external hanging port 3, when the two opening and closing plates 6 gradually close, the connecting rod 12 suspending the sealing cover plate 13 gradually vertically extends, when the two opening and closing plates 6 are completely closed, the two sealing cover plates 13 are also sealed in the external hanging port 3;

[0079] Step 5, after the two opening and closing plates 6 are completely closed, the lock hook 24 is locked on the lock block 25, and the closing of the two opening and closing plates 6 is locked.

[0080] When the external object connector 2 falls from the external hanging port 3 in step 3, the aircraft central control 23 does not receive the opening signal of the travel switch 21; the telescopic rod 20 of the electric push rod 15 is automatically triggered to run to an extended state, the long strip limit frame 17 pushes the synchronization pin shaft 9 to the outer end of the slot 11, so that the two opening and closing plates 6 are completely closed, and the two sealing cover plates 13 are also sealed in the external hanging port 3.​

[0081] The device utilizes a synchronous six-link mechanism to drive the opening and closing plate 6 and the sealing cover plate 13 to open and close synchronously, and combines with a parallelogram mechanism to convert the horizontal movement of the opening and closing plate 6 into the vertical movement of the sealing cover plate 13, thereby achieving precise filling and sealing of the opening of the aircraft skin 1; using a tension spring 8 as a closing driving force source, the device is automatically driven to close after the external attachment is discarded, and a pneumatic conformal seal between the cover and the aircraft surface is achieved.

[0082] The device utilizes a lock hook 24 and a lock block 25 mounted on the opening and closing plates 6 on both sides to form an automatic locking mechanism, and a return spring 27 serves as the return power of the lock hook 24; at the end of closing, the lock block 25 squeezes the inclined surface of the lock hook 24 to cause the lock hook 24 to rotate out of position, and the return spring 27 drives the lock hook 24 to automatically return to the hook and lock, thereby realizing automatic and reliable mechanical locking in the closed state.

[0083] The device utilizes a return torsion spring 14 as a return power source for the sealing cover plate 13 , and drives the sealing cover plate 13 to retract and return to its original position along the mechanism track during the opening process of the device, thereby avoiding interference and collision with the aircraft skin 1 .

[0084] The present invention creatively overcomes energy dependence and response hysteresis, and achieves the goal of not requiring additional actuating force or control signals, relying solely on the stored energy release of the built-in tension spring 8, automatically triggering and completing the sealing and locking at the moment the external attachment is discarded; achieving high-precision aerodynamic conformality, ensuring that the final sealing surface can be smooth and continuous with the original aircraft surface, effectively maintaining the aerodynamic shape; solving the problem of unstable or failed closure in existing solutions under high-speed airflow impact and wide temperature range environments; and fundamentally eliminating the risk of system paralysis caused by failure of the tension spring 8 through a dual-mode architecture of pure mechanical main drive and electric backup.

[0085] It achieves instantaneous self-triggering sealing without relying on external energy. It relies on the built-in tension spring energy storage drive mechanism to close synchronously, and the parallelogram mechanism guides the filling port cover to sink accurately into the opening to form a pneumatic conformal sealing surface.

[0086] The purely mechanical design features a simple and reliable overall structure, eliminating the need for complex control systems. This fundamentally avoids the low-temperature hysteresis, high failure rate, and maintenance challenges associated with electronic or hydraulic systems, significantly improving system reliability throughout its lifecycle. Rapid and reliable sealing effectively maintains the aerodynamic shape and radar stealth performance, while the safe retraction driven by the reset torsion spring and dedicated maintenance ports further optimize maintainability.

[0087] When the pull spring 8 fails to cause the device to fail to close after the external object is dropped, the travel switch 21 detects the position state of the synchronization pin shaft 9 in real time, converts the physical displacement into an electrical signal, and triggers the electric push rod 15 to start. The electric push rod 15 drives the synchronization pin shaft limit rack 16 to act, so that the long strip limit frame 17 on the synchronization pin shaft limit rack 16 directly drives the synchronization pin shaft 9 in the synchronization six-link mechanism, and forcibly drives the whole synchronization six-link mechanism to move. The actuating force replaces the failed pull spring 8 to continuously drive the opening and closing plate 6 and the sealing cover plate 13 to close to the middle, until the lock hook 24 and the lock block 25 complete mechanical locking, at the same time, the sealing cover plate 13 completely fills into the opening of the aircraft skin 1, finally realizes the sealing and conformal between the sealing cover plate 13 and the opening of the aircraft skin 1.

[0088] The above specific embodiments further illustrate the purpose, technical solutions and beneficial effects of the present application. It should be understood that the above description is only a specific embodiment of the present application and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. An aircraft external attachment port sealing device, comprising an aircraft skin (1), a double-link structure and an external attachment joint (2), wherein a plurality of external attachment ports (3) are provided on the aircraft skin (1), and characterized in that: A mounting support plate (4) is fixedly provided on the aircraft skin (1) in the external hanging opening (3), and longitudinal guide rail frames (5) are respectively provided on the bottom surface of the mounting support plate (4) and on both sides of the external hanging opening (3), and two opening and closing plates (6) that match each other are slidably mounted on the longitudinal guide rail frames (5) through a slide rail joint (7), and a tension spring (8) that can close the two opening and closing plates (6) is provided between the ends thereof, and the double-link structure comprises two synchronous connecting rods (10) hinged by a synchronous pin shaft (9), and the end of one synchronous connecting rod (10) is hinged to the end of one opening and closing plate (6), and the synchronous pin shaft (9) is slidingly limited and mounted in a slot (11) transversely opened on the mounting support plate (4). When the two opening and closing plates (6) are opened or closed, the two opening and closing plates (6) maintain synchronous relative movement under the limiting action of the double-link structure; A sealing cover plate (13) is suspended below each opening and closing plate (6) via a plurality of connecting rods (12), one end of the connecting rod (12) is hinged to the opening and closing plate (6), and the other end of the connecting rod (12) is hinged to the sealing cover plate (13). A return torsion spring (14) is provided on a hinge shaft connecting the connecting rod (12) and the opening and closing plate (6) or the sealing cover plate (13). Under the action of the return torsion spring (14), the two sealing cover plates (13) suspended below the two opening and closing plates (6) tend to dock and close in real time; the external attachment joint (2) is hung on the aircraft via the external attachment port (3).

2. The aircraft external attachment port sealing device according to claim 1, characterized in that: A set of double connecting rod structures is respectively provided at the two ends of the two opening and closing plates (6).

3. The aircraft external attachment port sealing device according to claim 2, characterized in that: An external hanging port sealing control assembly is provided on the top surface of the mounting support plate (4) corresponding to a set of double-link structures. The external hanging port sealing control assembly includes an electric push rod (15) and a synchronous pin shaft limiting frame (16). The synchronous pin shaft limiting frame (16) is a T-shaped structure. A long strip limiting frame (17) matching the straight groove (11) is provided on the horizontal frame of the synchronous pin shaft limiting frame (16). The outer end of the longitudinal frame (19) of the synchronous pin shaft limiting frame (16) is provided with a long strip connecting groove (18) movably connected to the electric push rod (15). The middle position of the longitudinal frame (19) of the synchronous pin shaft limiting frame (16) is mounted on the mounting support plate (4) through a limiting rotating shaft. When the longitudinal frame (19) is in a vertical state with the straight groove (11), the long strip limiting frame (17) is aligned with the straight groove (11) up and down; the electric push rod (15) is fixedly mounted on the mounting support plate (4) in parallel with the straight groove (11).

4. The aircraft external attachment port sealing device according to claim 3, characterized in that: A travel switch trigger structure is provided on the top surface of the mounting support plate (4) corresponding to the other set of double-link structures. The travel switch trigger structure includes a travel switch (21) and a lever member (22). The travel switch (21) is provided with a lever member (22) for controlling its opening and closing. When the synchronous pin shaft (9) on the corresponding double-link structure is not at the outer end of the slot (11), the travel switch (21) is in a closed state, the travel switch (21) transmits a signal to the aircraft central control (23), and the aircraft central control (23) displays that the external hanging port (3) is in an open state; when the synchronous pin shaft (9) on the corresponding double-link structure is at the outer end of the slot (11), the travel switch (21) is in an open state, the travel switch (21) transmits a signal to the aircraft central control (23), and the aircraft central control (23) displays that the external hanging port (3) is in a closed state.

5. The aircraft external attachment port sealing device according to claim 4, characterized in that: The electric push rod (15) is connected to the aircraft central control (23) for control. The electric push rod (15) can be controlled by the aircraft central control (23) to realize three gear switching: the telescopic rod (20) of the electric push rod (15) is in a semi-extended state, an extended state and a retracted state; when the aircraft central control (23) is operated to separate the external attachment connector (2) from the aircraft, the aircraft central control (23) does not receive the start signal of the travel switch (21) within a set time, the aircraft central control (23) controls the electric push rod (15) to run to the extended state, and the long limit frame (17) pushes the synchronous pin (9) to the outer end of the slot (11), so that the two opening and closing plates (6) are completely closed, thereby linking the two sealing cover plates (13) to seal the external attachment opening (3).

6. The aircraft external attachment port sealing device according to claim 5, characterized in that: The butt joint surfaces of the two opening and closing plates (6) are butt joint surfaces, and at the same time, the butt joint surfaces of the two sealing cover plates (13) are also butt joint surfaces. When the sealing cover plates (13) and the opening and closing plates (6) are in a fitted state, a gap is left between the sealing cover plates (13) and the aircraft skin (1). The outer surface of the sealing cover plates (13) is coated with a stealth coating that can absorb radar waves.

7. The aircraft external attachment port sealing device according to claim 6, characterized in that: The invention also includes an opening and closing plate locking structure, which includes a lock hook (24), a lock block (25), a guide rod (26) and a return spring (27). The lock hook (24) is a T-shaped structure. The bottom end of the longitudinal lock rod (28) of the lock hook (24) is installed on the upper side of an opening and closing plate (6) through a rotating shaft. The upper end of the longitudinal lock rod (28) is provided with a lock hook head (29). The transverse lock rod (30) of the lock hook (24) is movably connected to the guide rod (26) vertically arranged on the opening and closing plate (6). The guide rod (26) is inserted into a guide cylinder (31) arranged on the opening and closing plate (6), and a return spring (27) is sleeved on the guide rod (26); the lock block (25) and the lock hook head (29) are correspondingly arranged on the upper side of the other opening and closing plate (6).

8. The aircraft external attachment port sealing device according to claim 7, characterized in that: The bottom end of the guide rod (26) is connected to the maintenance interface (33) via a pull rope (32).

9. A method for sealing an aircraft external attachment port, using the aircraft external attachment port sealing device according to claim 8, characterized in that: The following steps are involved: Step 1: Open the opening and closing plate (6) and the sealing cover (13) by controlling the electric push rod (15) or tightening the pull rope (32), and the tension spring (8) is in a stretched state, and the external attachment is installed on the aircraft through the external attachment connector (2); Step 2: Control the electric push rod (15) to make the telescopic rod (20) in a semi-extended state, align the long limit frame (17) with the slot (11) up and down, and adjust the maintenance interface (33) to make the pull rope (32) in a relaxed state; the butt joint surfaces of the two sealing cover plates (13) are against the external attachment joint (2); Step 3: Separate the external attachment connector (2) from the aircraft by operating the aircraft central control (23), and after the external attachment connector (2) falls off the external attachment opening (3); Step 4, the two opening and closing plates (6) are closed under the action of the tension spring (8); in the process of closing the opening and closing plates (6), the two sealing cover plates (13) are first docked and closed under the action of the return torsion spring (14), and the two sealing cover plates (13) are aligned with the external hanging opening (3) up and down. When the two opening and closing plates (6) are gradually closed, the connecting rod (12) suspending the sealing cover plates (13) gradually extends vertically. When the two opening and closing plates (6) are completely closed, the two sealing cover plates (13) are also sealed in the external hanging opening (3); Step 5: When the two opening and closing plates (6) are completely closed, the locking hook (24) is locked on the locking block (25), and the two opening and closing plates (6) are closed and locked.

10. The method for sealing an aircraft external attachment port according to claim 9, characterized in that: When the external attachment connector (2) falls off from the external attachment opening (3) in step 3, the aircraft central control (23) does not receive the on signal of the travel switch (21); the aircraft central control (23) is automatically triggered to control the telescopic rod (20) of the electric push rod (15) to run to the extended state, and the long limit frame (17) pushes the synchronous pin (9) to the outer end of the slot (11), so that the two opening and closing plates (6) are completely closed, and the two sealing cover plates (13) are also sealed in the external attachment opening (3).

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