Dropping cabin door assembly and dropping cabin door control method

Abstract

The invention relates to a throwing cabin door assembly and a throwing cabin door control method. The throwing cabin door assembly comprises a first throwing cabin door, the first throwing cabin door comprises a first throwing cabin door pivot part at a first side edge, the first throwing cabin door is pivotally connected to a fuselage of the fire extinguishing aircraft through the first throwing cabin door pivot part, the first throwing cabin door blocks a fire extinguishing medium outlet of the fuselage, and the first throwing cabin door comprises a first cabin door locking hook part; the first lifting actuator is connected to the fuselage and the first throwing cabin door from the outside of the aircraft and actuates the first throwing cabin door to pivot around the first throwing cabin door pivot part; the first latch shaft is rotatably arranged on the machine body, the rotation center of the first latch shaft is coaxial with the first cabin door locking hook part, the first latch shaft comprises a first latch part matched with the first cabin door locking hook part, and the first latch part and the first cabin door locking hook part are connected and disconnected through rotation of the first latch shaft; and a first latch actuator that actuates rotation of the first latch shaft.

Description

Technical Field

[0001] The present invention relates to a delivery hatch assembly, and in particular to a delivery hatch assembly for a fire-fighting aircraft, which can be configured to deliver a delivery hatch from the air to the ground to perform a fire-fighting task. The present invention relates to a delivery hatch control method, which can realize the opening and closing of a delivery hatch for a fire-fighting aircraft to deliver a fire-fighting task to the ground. The present invention belongs to the field of fire-fighting aircraft delivery control design. Background Art

[0002] The research and application of existing fire-fighting aircraft in forest aerial firefighting are relatively mature. Helicopters and seaplanes are mainly used as fire-fighting aircraft. The main fire-fighting plan is to drop water bombs, water bags and other methods into the forest to extinguish the fire.

[0003] In recent years, more types of firefighting aircraft have been developed and deployed, such as light multi-purpose fixed-wing aircraft, large strategic transport aircraft, etc. At present, attempts are being made to convert regional passenger aircraft into firefighting aircraft.

[0004] The release door actuation control system is the most important part of the firefighting aircraft's mission, and its reliability directly affects the success or failure of the aircraft's firefighting mission. Fixed-wing aircraft fly at a faster speed, so the release door needs to be opened in a faster time to meet the needs of fire extinguishing medium delivery. Summary of the invention

[0005] The purpose of the present invention is to provide a launch hatch device which can quickly open the launch hatch, has a simple structure, is easy to modify, has a small space requirement and avoids the risk of interference with the launched fire extinguishing medium as much as possible.

[0006] In view of the above problems in the prior art, the inventor provides a delivery hatch assembly, which can quickly open the delivery hatch to deliver the fire extinguishing medium and avoid interference with the release of the fire extinguishing medium.

[0007] In a first example of the delivery door assembly, the delivery door assembly includes: a first delivery door, the first delivery door includes a first delivery door pivot at a first side, and is pivotally connected to the fuselage of the fire-fighting aircraft through the first delivery door pivot, the first delivery door blocks the fire-extinguishing medium outlet of the fuselage, and the first delivery door includes a first door locking hook; a first lifting actuator, the first lifting actuator is respectively connected to the fuselage and the first delivery door from the outside of the aircraft, and actuates the first delivery door to pivot around the first delivery door pivot; a first latch shaft, the first latch shaft is rotatably arranged on the fuselage and the rotation center is coaxial with the first door locking hook, the first latch shaft includes a first latch portion that cooperates with the first door locking hook, the first latch portion and the first door locking hook are engaged and disengaged by the rotation of the first latch shaft; and a first latch actuator, the first latch actuator actuates the first latch shaft to rotate.

[0008] In a second example of the launch door assembly, optionally including the first example, a first end of a first lift actuator is connected to the fuselage from outside the aircraft near the first side edge, and a second end of the first lift actuator is connected to a middle section of the first launch door from outside the aircraft.

[0009] In a third example of the delivery door assembly, optionally including one or more of the first example and the second example, the delivery door assembly further includes: a second delivery door, the first delivery door and the second delivery door are arranged in a mirror-symmetrical manner with respect to the center line of the fuselage in the span direction of the aircraft, and together block the fire extinguishing medium outlet, the second delivery door includes a second door locking hook; a second lifting actuator, the second lifting actuator is respectively connected to the fuselage and the second delivery door at both ends, and actuates the second delivery door to pivot between an open position and a closed position; a second latch shaft, the second latch shaft is rotatably provided on the fuselage and the rotation center is coaxial with the second door locking hook, the second latch shaft includes a second latch portion cooperating with the second door locking hook, the second latch portion and the second door locking hook are engaged and disengaged by the rotation of the second latch shaft; and a second latch actuator, the second latch actuator actuates the second latch shaft to rotate.

[0010] In a fourth example of the launch door assembly, which optionally includes one or more of the first to third examples, the first latch actuator and the second latch actuator are arranged on the same side of the fuselage in the span direction of the aircraft.

[0011] In the fifth example of the delivery door assembly, one or more of the first to fourth examples may be optionally included, and the delivery door assembly further includes: a door target, the door target being disposed on a fourth side of the first delivery door adjacent to the first side; and a door-closed position proximity switch, the door-closed position proximity switch being disposed on the fuselage and disposed close to the fourth side, and being configured so that when the first delivery door is in the closed preparation position, the door-closed position proximity switch can sense the door target.

[0012] In a sixth example of the launch door assembly, one or more of the first to fifth examples are optionally included, and the launch door assembly further includes: a latch shaft target, the latch shaft target is arranged at a predetermined position on the outer peripheral surface of the first latch shaft; a latch in place proximity switch, the latch in place proximity switch is arranged on the fuselage, is arranged close to the outer peripheral surface of the first latch shaft, and is arranged so that when the first latch shaft is in the latched position, the latch in place proximity switch can sense the latch shaft target; and an unlatched in place proximity switch, the unlatched in place proximity switch is arranged on the fuselage, is arranged close to the outer peripheral surface of the first latch shaft, and is arranged so that when the first latch shaft is in the unlatched position, the unlatched in place proximity switch can sense the latch shaft target.

[0013] In a seventh example of the launch hatch assembly, optionally including one or more of the first to sixth examples, the first lift actuator and the first latch actuator are electric actuation mechanisms that do not include a hydraulic system.

[0014] The present invention provides a delivery door control method for a fire-fighting aircraft, wherein the delivery door control method comprises the following steps when opening the delivery door: a first latch actuator actuates a first latch shaft to an unlatched position; the first delivery door opens and delivers the fire-extinguishing medium under the action of the gravity of the fire-extinguishing medium; wherein, when the delivery rate of the fire-extinguishing medium under the action of gravity alone meets the preset delivery requirement, the first lifting actuator follows, and wherein, when the delivery rate of the fire-extinguishing medium under the action of gravity alone does not meet the preset delivery requirement, the first lifting actuator actuates the first delivery door to move toward an open position; when the first delivery door reaches the open position, the first lifting actuator actuates and resists the movement trend of the first delivery door; and when the first delivery door is opened to a preset maximum opening angle, the first lifting actuator locks and maintains the current position of the first delivery door.

[0015] The present invention provides a method for controlling a delivery hatch door, which is used for a fire-fighting aircraft, wherein the method comprises the following steps when closing the delivery hatch door: a first lifting actuator unlocks and actuates the first delivery hatch door to a closing preparation position; the first lifting actuator locks and maintains the current position of the first delivery hatch door; a first latch actuator actuates a first latch shaft to an upper latch position, and when the first latch shaft reaches the upper latch position, the first latch actuator stops actuating; the first lifting actuator is unlocked and the structural deformation stress is released.

[0016] In another aspect of the launch hatch control method, in the step of the first latch actuator actuating the first latch shaft to the latched position, the launch hatch control method also includes: the first latch shaft rotates from the unlatched position toward the latched position, the first latch portion of the first latch shaft contacts the first door locking hook portion of the first launch hatch, the first latch shaft continues to rotate so that the first launch hatch pivots from the closed preparation position toward the closed position, and the first latch actuator actuates the first latch shaft to rotate to the latched position.

[0017] This patent provides a control system and method for the launch door of a fire-fighting aircraft. By externalizing the actuator, the resistance to the launch of the fire-extinguishing medium is reduced; the launch door opening method that combines gravity launch with active control improves the door opening efficiency; and the door closing control method that improves the linkage between the actuator and the latch actuator reduces the structural design cost.

[0018] The actuator is externally mounted to reduce system complexity, increase the storage capacity of the fire extinguishing medium, and effectively improve the efficiency of the fire extinguishing medium delivery without affecting the fire extinguishing medium delivery.

[0019] A door delivery method combining gravity delivery and active control is adopted to ensure the door opening time requirements of fire extinguishing efficiency, while making full use of gravity impact to improve door opening efficiency.

[0020] The door closing control method of the lifting actuator and the latch actuator linkage is adopted. For the external actuator, the lifting actuator is used to close the door. Because the compression of the seal must be overcome, the actuator output force is huge, which poses challenges to the device space requirements, device structure and actuator design. After the lifting actuator and the latch actuator linkage mode are adopted, the lifting actuator output requirements are greatly reduced, and the door closing efficiency is optimized. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to describe the implementation of the above and other features of the present invention, a more particular description of the invention briefly described above will be presented with reference to the exemplary embodiments of the invention shown in the accompanying drawings. It will be understood that these drawings only depict exemplary embodiments of the invention and should not be considered as limiting the scope thereof. The invention will be described and explained through the use of the accompanying drawings and with additional features and details. In the drawings:

[0022] Figure 1 is a bottom view of an aircraft with a launch door assembly according to an embodiment of the present invention;

[0023] Figure 2 yes Figure 1 A bottom view of an optional first set of door targets and door-closed proximity sensors of the launch door assembly;

[0024] Figure 3 yes Figure 1 A bottom view of the optional second set of door targets and door-closed proximity sensors of the launch door assembly;

[0025] Figure 4 yes Figure 1 A bottom view of a connecting rod of a lift actuator of a launch hatch assembly;

[0026] Figure 5 is a simplified diagram of the mechanism movement of the launch hatch assembly according to an embodiment of the present invention, wherein the launch hatch is in a closed preparatory position and the latch shaft is in an unlatched position;

[0027] Figure 6 is a simplified diagram of the mechanism movement of the launch hatch assembly according to an embodiment of the present invention, wherein the launch hatch is in a closed preparatory position and the latch shaft is in an upper latch position;

[0028] Figure 7 is a graph showing the relationship between the speed of the lifting actuator and the angle of the delivery hatch when the delivery hatch is opened according to the delivery hatch control method of an embodiment of the present invention;

[0029] Figure 84 is a graph showing the relationship between the speed of the lifting actuator and the angle of the delivery hatch when closing the delivery hatch according to the delivery hatch control method of an embodiment of the present invention.

[0030] The drawings are roughly drawn to scale, however, the dimensions in the drawings are only schematic and do not need to be strictly drawn to scale, but are intended to be more clearly illustrated. In other embodiments, other relative dimensions may be used. Here and in all of the following, the same features appearing in different drawings are represented by the same or similar reference numerals.

[0031] List of reference numerals:

[0032] 1 Drop door assembly

[0033] 110 First drop hatch

[0034] 110a First side

[0035] 110b Second side

[0036] 110c Third side

[0037] 110d Fourth side

[0038] 111 First launch hatch pivot

[0039] 112 Door locking hook

[0040] 120 First lifting actuator

[0041] 121 Connecting rod

[0042] 130 First Latch Axle

[0043] 131 first latch portion

[0044] 140 First latch actuator

[0045] 150 Hatch Target

[0046] 151 Door closing position proximity switch

[0047] 160 Latch Target

[0048] 161 Bolt in place proximity switch

[0049] 162 Unlatch position proximity switch

[0050] 210 Second launch hatch

[0051] 220 Second lifting actuator

[0052] 230 Second Latch Axle

[0053] 240 Second latch actuator DETAILED DESCRIPTION

[0054] First, the present invention mainly relates to a delivery hatch assembly of a fire-fighting aircraft, in particular, the present invention relates to a delivery hatch assembly of a branch airliner converted into a fire-fighting aircraft, but is not limited to the delivery hatch assembly of this type of fire-fighting aircraft.

[0055] "Fit" in the context of the present invention is intended to describe that the shape of at least a portion of one component and the shape of at least a portion of another component can fit with each other. The "fit" does not require complete shape matching, but can be partial shape matching, for example, one component is convex and can be received in a curved recess of another component, or the key of one component can be partially received in the groove of another component. As long as there are force transmission paths, no matter how many, they are within the scope of the present invention.

[0056] As used herein, the terms "comprising," "having," "including," and variations thereof are intended to serve as open-ended transitional phrases, terms or words requiring the presence of specified elements / steps and also allowing for the presence of other elements / steps.

[0057] In the present invention, unless explicitly stated to the contrary, the terms "first", "second", etc. are not intended to indicate any difference in order, position, quantity or importance, but are merely used as labels to distinguish different positions and components, to distinguish one element, component, region and / or position from another element, component, region and / or position.

[0058] The numerical value used herein should be understood to include the same numerical value when reduced to the same significant digits, and the numerical value that differs from the numerical value less than the experimental error of the conventional measurement technology of the type described in the application to determine the numerical value. The numerical value provided in each embodiment is only used as an example, and is not intended to limit the scope of the invention.

[0059] In a non-limiting example, the fire-fighting aircraft of the present invention includes a fire-extinguishing medium opening at the belly below the fuselage, and at least one delivery door for sealingly blocking the fire-extinguishing medium opening.

[0060] In a non-limiting example, the launch door assembly 1 of the present invention includes at least one launch door 110, 210, and the outer contour shape of at least one launch door can be a rectangle with rounded corners but is not limited to this, and can also be other shapes based on actual needs, such as having a notch in the outer contour shape to avoid the frame of the fuselage.

[0061] The at least one delivery door may include two or more delivery doors, and the arrangement of these delivery doors may be adaptively changed based on the arrangement of the fire extinguishing medium storage container and the fire extinguishing medium opening inside the fuselage.

[0062] For example, the at least one delivery door may include two delivery doors 110, 210, and the first delivery door 110 and the second delivery door 210 are arranged in a mirror-symmetrical manner relative to the center line of the fuselage in the span direction of the aircraft, and together block the fire extinguishing medium outlet.

[0063] For example, the at least one delivery hatch may include two or more delivery hatches, and the delivery hatches are arranged in a row in the heading direction of the flight and block the fire extinguishing medium outlet together.

[0064] The delivery hatch 110 includes at least a closed position and an open position. In the closed position, the fire extinguishing medium opening can be sealed and blocked, and in the open position, the delivery of the fire extinguishing medium is not interfered with. Preferably, a sealing member is arranged in a circle along the periphery of the delivery hatch, and the sealing member can be, for example, a rubber sealing ring, which is compressed and deformed to provide dense contact between the delivery hatch 110 and the fire extinguishing medium opening.

[0065] The delivery hatch 110 may also include a closed preparation position, which is a delivery hatch position where the seal of the delivery hatch 110 is substantially in contact with the fire extinguishing medium opening. Since the seal needs to be squeezed and deformed to provide sealing, the compression force may be large. The present invention actuates the lifting actuator 120 and / or the latch actuator 140 to compress the seal so that the delivery hatch 110 moves from the closed preparation position to the closed position, which will be described in detail below.

[0066] The delivery hatch 110 may also include a maximum angle position, which is a delivery hatch position at which the delivery hatch 110 has a preset maximum opening angle that does not cause damage to the electric actuator, and will be described in detail below.

[0067] The delivery door 110 may include a door pivot 111 at its first side 110a, and may be pivotally connected to the fuselage of the fire-fighting aircraft through the door pivot 111. Preferably, the first side 110a is designed so that the door opening direction of the delivery door 110 is the span direction. Considering that the present invention can be used for fire-fighting aircraft modified from fixed-wing aircraft, the flight speed is much higher than that of helicopters and seaplanes, and the aerodynamic force of the air in the heading direction is relatively large, and the door opening direction is the span direction to avoid the additional resistance of opening and closing the door due to aerodynamic resistance.

[0068] The launch door 110 may include a door locking hook 112 on its side, which cooperates with a latch portion 131 of a latch shaft 130 provided on the fuselage to compress the seal of the launch door 110 and lock the launch door 110, which will be described in detail below.

[0069] The door locking hook 112 is preferably arranged on the third side 110c opposite to the first side 110a, or may also be arranged on the second side 110b or the fourth side 110d adjacent to the first side 110a, but close to the third side 110c. Therefore, compared with the position far away from the third side 110c, the force arm of the force for closing the launch door (i.e., the distance between the door locking hook 112 and the pivot axis of the door pivot portion 111 of the first side 110a) can be longer, wherein at least a part of the force for closing the launch door is provided by the latch shaft 130 and the latch actuator 140, which will be described in detail below.

[0070] In a non-limiting example, the launch door assembly 1 of the present invention includes a lifting actuator 120. The lifting actuator 120 is respectively connected to the fuselage and the door 110 from the outside of the aircraft, and actuates the door 110 to pivot around the door pivot 111.

[0071] For example, a first end of the lift actuator 120 is connected to the fuselage from outside the aircraft near the first side edge 110 a , and a second end is connected to the middle section of the launch door 110 from outside the aircraft.

[0072] In the present invention, the lifting actuator 120 is arranged outside the aircraft to avoid occupying the space inside the fuselage, to avoid blocking and jamming of non-fluid fire extinguishing media, such as colloidal fire extinguishing bombs, when the fire extinguishing media is released, and to avoid additional requirements such as waterproof design of the built-in lifting actuator.

[0073] Considering that the present invention can be used for firefighting aircraft modified from fixed-wing aircraft, which have high flight speed and high ground clearance, it is necessary to quickly open the delivery door to deliver the fire extinguishing medium in a short period of time. Preferably, the lifting actuator 120 is an electric actuator that does not include a hydraulic system, and for example includes a motor, a gear, and a connecting rod 121 to perform high-precision and high-speed control on the lifting actuator 120.

[0074] In a non-limiting example, the launch door assembly 1 of the present invention includes a latch shaft 130. The latch shaft 130 is rotatably disposed on the fuselage, and preferably at the third side 110c of the launch door 110, so as to obtain a larger moment arm of the compression force as described above.

[0075] The latch shaft 130 includes a latch portion 131 that cooperates with the launch hatch locking hook portion 112, and the latch portion 131 and the launch hatch locking hook portion 112 are engaged and disengaged by the rotation of the latch shaft 130. Therefore, the latch shaft 130 is designed to be coaxial with the hatch locking hook portion 112.

[0076] In a non-limiting example, the launch hatch assembly 1 of the present invention includes a latch actuator 140 for actuating the rotation of the latch shaft 130. Preferably, it is an electric actuator, and for example includes a motor, a gear, and a connecting rod 121 to control the latch shaft 130 with high precision and high speed.

[0077] The present invention will be further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0078] A coordinate system is provided in the figures for reference, the z-axis may be the vertical axis (e.g., parallel to the direction of gravity), the x-axis may be the longitudinal axis (e.g., parallel to the heading direction of the aircraft), and the y-axis may be the horizontal axis (e.g., parallel to the span direction of the aircraft).

[0079] When referring to directions, a positive direction may refer to the direction of the arrows for the y-axis, x-axis, and z-axis, while a negative direction may refer to the opposite direction of the arrows for the y-axis, x-axis, and z-axis. A filled circle may represent arrows and axes facing toward or positive to the view. An unfilled circle may represent arrows and axes facing away from or negative to the view.

[0080] Figure 1 A bottom view of an aircraft with a launch door assembly according to an embodiment of the present invention is schematically shown.

[0081] In this example, the at least one delivery door may include two delivery doors 110, 210, and the first delivery door 110 and the second delivery door 210 are arranged in a mirror-symmetrical manner relative to the center line of the fuselage in the span direction of the aircraft, and together block the fire extinguishing medium outlet.

[0082] Preferably, the second lifting actuator 220, the second latch shaft 230, and the second latch actuator 240 corresponding to the second delivery door 210 may be arranged in a mirror-symmetrical manner with the first lifting actuator 120, the first latch shaft 130, and the first latch actuator 140. It can be understood that the specific arrangement positions of the second lifting actuator 220, the second latch shaft 230, and the second latch actuator 240 may not be limited to the mirror-symmetrical arrangement. For example, in this embodiment, based on the actual space limitation of the fuselage of the aircraft, the first latch actuator 140 and the second latch actuator 240 may also be arranged on the same side of the fuselage in the span direction of the aircraft.

[0083] Figure 2 yes Figure 1A bottom view of the optional first set of door targets 150 and the door-closed proximity sensor 151 of the launch door assembly, Figure 3 yes Figure 1 A bottom view of the launch door assembly's optional second set of door targets and door-closed proximity sensors.

[0084] The delivery door assembly 1 according to the embodiment of the present invention further comprises a door target 150, which is arranged on a fourth side 110d of the first delivery door 110 adjacent to the first side 110a; and a door-closed-position proximity switch 151, which is arranged on the fuselage and is arranged close to the fourth side 110d, and is arranged so that when the first delivery door 110 is in the closed preparation position, the door-closed-position proximity switch 151 can sense the door target 150.

[0085] Figure 4 A bottom view of the connecting rod 121 of the first lifting actuator 120 is schematically shown.

[0086] The first end of the first lifting actuator 120 is mounted on the lower wall of the aircraft, whereby the actuating torque of the first lifting actuator 120 gradually decreases during the closing of the first delivery door 110 , and thus a very large output of the first lifting actuator 120 is required to completely close the first delivery door 110 .

[0087] Therefore, a connecting rod 121 can be used to connect the second end of the first lifting actuator 120 to the first delivery hatch 110. The force transmission direction can be changed by the connecting rod 121, so that the torque acting on the first delivery hatch 110 is increased, and thus the required output of the first lifting actuator 120 can be reduced.

[0088] The form of the connecting rod 121 is not limited thereto, and may be any form suitable for increasing the moment acting on the first launching hatch 110 .

[0089] Figure 5 A simplified diagram of the mechanism movement of the launch hatch assembly 1 according to an embodiment of the present invention is schematically shown, wherein the first launch hatch 110 is shown in a closed preparation position with a solid line, and its desired closed position is shown with a dotted line, and at this time, the first latch shaft 130 and the first latch portion 131 thereon rotate to the unlatched position.

[0090] The launch hatch assembly 1 according to the embodiment of the present invention further includes a latch shaft target 160, which is disposed on the outer peripheral surface of the first latch shaft 130. In this example, the first latch portion 131 is in a crescent shape, and a latch shaft target 160 is disposed at one end, specifically, on a radially extending protrusion of the first latch shaft 130.

[0091] The delivery door assembly 1 according to the embodiment of the present invention further comprises an unlatching position proximity switch 162 (for example, a proximity sensor), which is disposed on the fuselage and is disposed close to the outer peripheral surface of the first latch shaft 130, and is disposed so that when the first latch shaft 130 is in the unlatching position, for example, Figure 5 As shown, the unlatch position proximity switch 162 is capable of sensing the latch shaft target 160 .

[0092] Figure 6 A simplified diagram of the mechanism movement of the delivery hatch assembly 1 according to an embodiment of the present invention is schematically shown, wherein the first delivery hatch 110 is shown in a closed position by a solid line, and at this time the first latch shaft 130 and the first latch portion 131 thereon rotate to the upper latch position.

[0093] The delivery hatch assembly 1 according to the embodiment of the present invention further comprises a latching position proximity switch 161 (for example, a proximity sensor), which is disposed on the fuselage and is disposed close to the outer peripheral surface of the first latch shaft 130, and is configured so that when the first latch shaft 130 is in the latching position, for example, Figure 6 As shown, the latch-in-place proximity switch 161 is capable of sensing the latch shaft target 160 .

[0094] Here, the latch position proximity switch 161 and the unlatched position proximity switch 162 are set to correspond to different angular positions of the outer circumferential surface of the first latch shaft 130, such as the angular position of the latch shaft target 160 when the first latch shaft 130 is in a predetermined latch position and unlatched position.

[0095] Figure 7 The diagram schematically shows the relationship between the speed of the lifting actuator 120 and the angle of the delivery door 110 when the delivery door 110 is opened according to the delivery door control method of an embodiment of the present invention. It can be understood that the specific value of the angle is not limited thereto, but is specifically set based on actual aircraft conditions such as aircraft type, airspeed, altitude, load, environmental conditions, etc. In this example, the door angle of the delivery door 110 in the closed position is, for example, about 20°.

[0096] When preparing for delivery, the aircraft control needs to be powered on first, then the delivery pre-position switch is pressed, and the delivery button is pressed at a suitable time. At this time, the delivery door assembly 1 according to the present invention will go through the following steps.

[0097] First, the latch actuator 140 actuates the latch shaft 130 to rotate, the latch shaft 130 rotates to an unlatched position to allow the drop bay door 110 to open, and the first latch actuator 140 stops.

[0098] Subsequently, the delivery door 110 is delivered by gravity, specifically, the door is opened and the fire extinguishing medium is released under the effect of the gravity of the fire extinguishing medium. In actual implementation, for example, on a fixed-wing firefighting aircraft, the opening and delivery of the delivery door 110 will be completed in less than 1 second. Figure 7 The figure also shows an exemplary curve of the relationship between the speed of the follow-up lifting actuator 120 and the angle of the launch door 110 when the door is opened only under the action of gravity. It can be understood that the specific value of the angle is not limited to this.

[0099] When the release rate of the fire extinguishing medium under the action of gravity alone meets the preset release requirements, the lifting actuator 120 follows, for example, during the period from t40 to t41, so that the opening speed v of the lifting actuator 120 (for example, the opening speed v1 at t41) is greater than or equal to the expected speed.

[0100] Among them, when the delivery rate of the fire extinguishing medium under the action of gravity alone does not meet the preset delivery requirements, the lifting actuator 120 actively actuates the delivery hatch 110 to move toward the open position, for example, during the period from t41 to t42 to t43, so that the opening speed v of the lifting actuator 120 (for example, the opening speed v2 at t42, the opening speed v3 at t43) meets the expected speed until the opening position of the delivery hatch 110 as described below is reached, so as to meet the goal of opening the delivery hatch 110 to the open position within 0.8s or 0.6s.

[0101] Subsequently, when the launch hatch 110 reaches the open position, for example at t43, the lift actuator 120 is actuated and resists the movement tendency of the hatch 110. Figure 7 In the example shown, the launch door angle is 98° when the door 110 is in the open position, which is referred to as the clear opening.

[0102] When the launch hatch 110 is opened to the preset maximum opening angle, for example, at t44, the lifting actuator 120 is locked and maintains the current position of the launch hatch 110. Figure 7 In the example shown, the maximum opening angle of the launch hatch 110 is 110°.

[0103] After exceeding the open position, i.e., the net opening, the actuator 120 is lifted for buffering. Under the action of gravity, spring force, negative pressure, etc., the speed of the launch door 110 drops to zero, and part of the energy is converted into elastic energy and gravitational potential energy, and part is consumed by friction; finally, the launch door 110 is fixed at the maximum opening angle.

[0104] Figure 8The diagram schematically shows the relationship between the speed of the lifting actuator 120 and the angle of the delivery door 110 when closing the delivery door 110 according to the delivery door control method of an embodiment of the present invention. It can be understood that the specific value of the angle is not limited to this, but is specifically set based on the actual aircraft situation.

[0105] After a preset fixed delay time, the lifting actuator 120 is unlocked and starts to actuate and retract, actuating the opening angle of the delivery hatch 110 from the maximum opening angle to the closed preparation position, for example, the opening angle of the delivery hatch 110 is from 110° to 17.2°. As described above, the hatch angle in the closed position is, for example, about 20°, but a seal is arranged around the delivery hatch 110, and during the rotation of the latch shaft 130 to the unlatched position, the compressed seal restores its original volume, so the hatch angle in the closed preparation position is, for example, about 17.2°.

[0106] The lift actuator 120 then locks and maintains the current position of the launch door 110 .

[0107] Then, the latch actuator 140 actuates the latch shaft 130 to rotate, and the latch shaft 130 rotates to the latch position. Figure 5 , Figure 6 The latch shaft 130 rotates from the unlatched position toward the latched position. After a certain idle stroke, the latch portion 131 contacts the door locking hook portion 112 of the launch door 110. The latch actuator 140 actuates the latch shaft 130 to rotate to the latched position, so that the launch door 110 enters the closed position.

[0108] In the embodiment shown in the drawings, the lifting arm of the lifting actuator 120 for lifting the delivery door 110 is relatively long, so the lifting actuator 120 locks and maintains the current position of the delivery door 110, that is, the closed preparatory position, and the latch shaft 130 is rotated to further compress the seals arranged around the delivery door 110 as described above, so that when the delivery door 110 moves to the closed position, the seals can seal the fire extinguishing medium opening of the fuselage.

[0109] When the first latch shaft 130 reaches the latching position, the first latch actuator 140 stops actuating. At this time, the lifting actuator 120 is unlocked and the structural deformation stress is released.

[0110] By releasing the compression amount and the rigidity characteristics of the lifting actuator 120, the connecting rod 121, the delivery door 110 and the fuselage structure, the travel requirement of the lifting actuator 120 caused by the latch shaft 130 actuating the delivery door 110 is compensated. Specifically, the travel from the aforementioned door closing preparation position to the final closing position is about 1.5 to 2 mm in this example. Figure 8 The thick solid line in shows that the compression amount of the lifting actuator 120 is released, and for example, the opening angle of the launch hatch 110 is from 17.2° to 20°.

[0111] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution of the present invention is clearly and completely described above in combination with the specific embodiments of the present invention and the accompanying drawings.

[0112] It should be understood that the steps shown above in conjunction with the specific embodiments are illustrative, and those skilled in the art may add or delete corresponding steps, and may adjust the execution order of one or some of the steps, or replace one or more of the steps with similar steps.

[0113] Although various embodiments have been described above, it should be understood that the embodiments described are part of the embodiments of the present invention, rather than all embodiments, and they are presented in an exemplary rather than limiting manner. It is obvious to those skilled in the relevant art that the disclosed subject matter can be implemented in other specific forms without departing from its spirit and essential features.

[0114] In the process, various elements that are important to the present invention or are conducive to further developing the present invention will be mentioned in the content of the specific examples, but some of these elements can also be used to further develop the present invention when they are separated from the content of the corresponding examples and other features of the corresponding examples. Therefore, the embodiments described above are considered to be illustrative and non-restrictive in all aspects and are not used as a basis for any limitation of the present invention.

[0115] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention. The present disclosure also includes various modifications and modifications within the equivalent scope. In addition, various combinations and methods, further including only one element, more than one or less than one other combinations and methods also belong to the scope and scope of thought of the present disclosure.

Claims

1. A launch door assembly for a fire-fighting aircraft, characterized in that: The delivery hatch assembly (1) comprises: A first delivery hatch (110), the first delivery hatch (110) comprising a first delivery hatch pivot portion (111) at a first side edge (110a), and being pivotally connected to a fuselage of the fire-fighting aircraft via the first delivery hatch pivot portion (111), the first delivery hatch (110) blocking a fire-extinguishing medium outlet of the fuselage, and the first delivery hatch (110) comprising a first hatch locking hook portion (112); a first lifting actuator (120), the first lifting actuator (120) being connected to the fuselage and the first delivery door (110) from the outside of the aircraft, respectively, and actuating the first delivery door (110) to pivot around the first delivery door pivoting portion (111); a first latch shaft (130), the first latch shaft (130) being rotatably disposed on the fuselage and having a rotation center coaxial with the first door locking hook portion (112), the first latch shaft (130) comprising a first latch portion (131) cooperating with the first door locking hook portion (112), the first latch portion (131) and the first door locking hook portion (112) being engaged and disengaged by the rotation of the first latch shaft (130); and A first latch actuator (140), the first latch actuator (140) actuates the first latch shaft (130) to rotate.

2. The launch hatch assembly according to claim 1, characterized in that: The first end of the first lifting actuator (120) is connected to the fuselage from outside the aircraft near the first side (110a), and A second end of the first lifting actuator (120) is connected to a middle section of the first launch door (110) from outside the aircraft.

3. The launch hatch assembly according to claim 1, characterized in that: The delivery hatch assembly (1) further comprises: a second delivery hatch (210), wherein the first delivery hatch (110) and the second delivery hatch (210) are arranged in a mirror-symmetrical manner relative to a center line of the fuselage in a span direction of the aircraft and together block the fire extinguishing medium outlet, and the second delivery hatch (210) comprises a second hatch locking hook; a second lifting actuator (220), which is connected to the fuselage and the second delivery door (210) at both ends, respectively, and actuates the second delivery door (210) to pivot between an open position and a closed position; a second latch shaft (230), the second latch shaft (230) being rotatably disposed on the fuselage and having a rotation center coaxial with the second door locking hook portion, the second latch shaft (230) comprising a second latch portion cooperating with the second door locking hook portion, the second latch portion and the second door locking hook portion being engaged and disengaged by the rotation of the second latch shaft (230); and A second latch actuator (240), the second latch actuator (240) actuates the second latch shaft (230) to rotate.

4. The launch hatch assembly according to claim 3, characterized in that: The first latch actuator (140) and the second latch actuator (240) are arranged on the same side of the fuselage in the span direction of the aircraft.

5. The launch hatch assembly according to claim 1, characterized in that: The delivery hatch assembly (1) further comprises: a hatch target (150), the hatch target (150) being arranged on a fourth side (110d) of the first delivery hatch (110) adjacent to the first side (110a); and A door-closed position proximity switch (151) is disposed on the fuselage, close to the fourth side edge (110d), and configured so that when the first launch door (110) is in a closed preparation position, the door-closed position proximity switch (151) can sense the door target (150).

6. The launch hatch assembly according to claim 1, characterized in that: The delivery hatch assembly (1) further comprises: a latch shaft target (160), the latch shaft target (160) being disposed at a predetermined position on the outer peripheral surface of the first latch shaft (130); a latching position proximity switch (161), the latching position proximity switch (161) being disposed on the fuselage and being disposed close to the outer peripheral surface of the first latch shaft (130), and being disposed so that when the first latch shaft (130) is in the latching position, the latching position proximity switch (161) can sense the latch shaft target (160); and An unlatching position proximity switch (162) is disposed on the fuselage and is disposed close to the outer peripheral surface of the first latch shaft (130). The unlatching position proximity switch (162) is configured so that when the first latch shaft (130) is in the unlatching position, the unlatching position proximity switch (162) can sense the latch shaft target (160).

7. The launch hatch assembly according to claim 1, characterized in that: The first lift actuator (120) and the first latch actuator (140) are electrically actuated mechanisms that do not include a hydraulic system.

8. A method for controlling a launch door for a fire-fighting aircraft, characterized in that: The delivery hatch control method comprises the following steps when opening the delivery hatch: The first latch actuator (140) actuates the first latch shaft (130) to an unlatched position; The first delivery hatch (110) opens under the action of the gravity of the fire extinguishing medium and delivers the fire extinguishing medium; When the delivery rate of the fire extinguishing medium under the action of gravity alone meets the preset delivery requirement, the first lifting actuator (120) moves with it, and When the delivery rate of the fire extinguishing medium under the action of gravity alone does not meet the preset delivery requirement, the first lifting actuator (120) actuates the first delivery hatch (110) to move toward the open position; When the first delivery hatch (110) reaches the open position, the first lifting actuator (120) is actuated to resist the movement tendency of the first delivery hatch (110); and When the first delivery hatch (110) is opened to a preset maximum opening angle, the first lifting actuator (120) is locked and maintains the current position of the first delivery hatch (110).

9. A method for controlling a launch door for a fire-fighting aircraft, characterized in that: The delivery hatch control method comprises the following steps when closing the delivery hatch: The first lifting actuator (120) unlocks and actuates the first delivery hatch (110) to a closed ready position; The first lifting actuator (120) locks and maintains the current position of the first launch hatch (110); The first latch actuator (140) actuates the first latch shaft (130) to the upper latch position, and when the first latch shaft (130) reaches the upper latch position, the first latch actuator (140) stops actuating; The first lifting actuator (120) is unlocked and releases structural deformation stress.

10. The method for controlling a launch hatch according to claim 9, characterized in that: In the step of the first latch actuator (140) actuating the first latch shaft (130) to the latched position, the launch hatch control method further comprises: The first latch shaft (130) rotates from an unlatched position toward a latched position, The first latch portion (131) of the first latch shaft (130) contacts the first door locking hook portion (112) of the first launch door (110), The first latch shaft (130) continues to rotate so that the first launch hatch (110) pivots from the closed preparation position toward the closed position. The first latch actuator (140) drives the first latch shaft (130) to rotate to an upper latch position.

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