CN216660317U - Aircraft packing box throwing device and aircraft - Google Patents

Abstract

The utility model provides an aircraft container throwing device and an aircraft, wherein the aircraft container throwing device comprises two brackets and a driving mechanism; the two brackets are respectively arranged at the throwing-in opening of the aircraft cabin, the brackets extend along a first direction, the two brackets are arranged at intervals along a second direction perpendicular to the first direction, and the brackets can move along the second direction; the driving mechanism is respectively connected with the two brackets and is used for driving the two brackets to move towards or away from each other in the second direction; the aircraft container throwing device is configured to adjust the two brackets to be switched between a bearing state and a throwing state through the driving mechanism, in the bearing state, the distance between the two brackets in the second direction is smaller than the width of a container, and in the throwing state, the distance between the two brackets in the second direction is larger than or equal to the width of the container.

Description

Aircraft packing box throwing device and aircraft

Technical Field

The utility model relates to the technical field of airplanes, in particular to an airplane container throwing device and an airplane.

Background

Air supply is one of the main ways of supplying supplies. In military applications, military transport planes mostly have air drop capability, and can complete material supply in a state that the plane is not on land. Military transport aircraft mostly adopt a fixed wing form, and due to the limitation of factors such as layout characteristics, high flying speed and the like, the aircraft usually adopts a tail cabin door form for air drop. In the unmanned aerial vehicle field, the main material supply mode at present is the external-hanging of many gyroplanes and puts in, also has the form such as little small-size fixed wing unmanned aerial vehicle's external-open hatch door is put in.

In the field of military transport aircraft, the air-drop form of the tail cabin door is characterized in that goods need to move in a large range in an aircraft cargo cabin, so that aircraft control and air-drop systems are complex, and flight safety is seriously influenced. In the unmanned aerial vehicle field, external air-drop is applicable to unmanned aerial vehicle and carries out the input of little load goods. The outward-opening cabin door airdrop is suitable for small aircrafts flying at low speed so as to avoid the influence of the outward-opening cabin door on the flight safety.

SUMMERY OF THE UTILITY MODEL

It is a primary object of the present invention to overcome at least one of the above-mentioned deficiencies of the prior art and to provide an aircraft cargo box drop device that does not require extensive movement of cargo within the aircraft cabin and that has little impact on the flight safety of the aircraft.

Another main object of the present invention is to overcome at least one of the above drawbacks of the prior art and to provide an aircraft comprising such an aircraft container release device.

In order to achieve the purpose, the utility model adopts the following technical scheme:

according to one aspect of the utility model, an aircraft cargo box throwing device is provided, wherein the aircraft cargo box throwing device comprises two brackets and a driving mechanism; the two brackets are respectively arranged at a throwing opening of an aircraft cabin, the brackets extend along a first direction, the two brackets are arranged at intervals along a second direction perpendicular to the first direction, and the brackets can move along the second direction; the driving mechanisms are respectively connected to the two brackets and used for driving the two brackets to move towards or away from each other in the second direction; wherein the aircraft cargo box dropping device is configured to adjust the two brackets to switch between a supporting state and a dropping state through the driving mechanism, wherein in the supporting state, the distance between the two brackets in the second direction is smaller than the width of a cargo box, and in the dropping state, the distance between the two brackets in the second direction is larger than or equal to the width of the cargo box.

According to one embodiment of the present invention, the driving mechanism comprises two pairs of ball screws and two motors; the two pairs of ball screws are respectively arranged in a cabin of an airplane through a support, the ball screws extend along the second direction, the two pairs of ball screws are arranged at intervals along the first direction, the two ball screws of the same pair are arranged at intervals along the second direction, the thread directions of the screw rods are opposite, and the screw rods of the two ball screws of the same pair are connected through a torsion tube; the two motors are respectively connected with one of the two pairs of ball screws in a transmission way; one end of one of the brackets is connected to the slider of one of the ball screws, the other end of the one of the brackets is connected to the slider of the other of the ball screws located on the same side in the second direction, one end of the other of the brackets is connected to the slider of the other of the ball screws, and the other end of the other of the brackets is connected to the slider of the other of the ball screws located on the same side in the second direction.

According to one embodiment of the utility model, the end of the bracket is connected to the slider by a connecting plate, and the end of the bracket is hinged to the connecting plate.

According to one embodiment of the present invention, a cross beam is connected between two of the supports located on the same side along the second direction.

According to one embodiment of the utility model, the end of the bracket is connected to the slide block through a connecting plate, and in a throwing state, the bracket is positioned below the cross beam on the same side; and the two end parts of the cross beam are respectively provided with an avoiding groove for avoiding the connecting plate when the bracket is in a throwing state.

According to one embodiment of the utility model, the aircraft container throwing device further comprises two folio doors, two energy storage mechanisms, a locking mechanism and an unlocking mechanism; the two cabin doors are respectively hinged to the two cross beams, and the door opening direction faces to the inside of the cabin; the two energy storage mechanisms are respectively connected between the two cabin doors and the two cross beams and are used for driving the cabin doors to close; the locking mechanism is arranged at the hinged position of the cabin door and the cross beam and used for locking the cabin door in an open state; the unlocking mechanism is connected to the locking mechanism and matched with the bracket, and is used for unlocking the locking mechanism to the cabin door when the bracket moves to the releasing state, so that the cabin door is driven to be closed by the energy storage mechanism.

According to one embodiment of the utility model, the cross beam is provided with a hinged support which is provided with an upper ear plate and a lower ear plate, the cabin door is provided with a hinge which is hinged to the upper ear plate through a cabin door shaft, and the hinge is provided with a positioning bulge; the locking mechanism comprises a locking rod which is hinged to the upper lug plate through a locking pin shaft, the other end of the locking rod extends to the unlocking mechanism, and a locking torsion spring is arranged between the locking pin shaft and the upper lug plate; the unlocking mechanism comprises an unlocking trigger rod, the unlocking trigger rod is hinged to the lower lug plate through an unlocking pin shaft, one end of the unlocking trigger rod extends to the other end of the locking rod and is matched with the locking rod, the other end of the unlocking trigger rod extends to the bracket and is matched with the bracket, and an unlocking torsion spring is arranged between the unlocking pin shaft and the lower lug plate; when the cabin door is in an open state, the positioning protrusion is clamped with the locking rod, and the other end of the locking rod is pressed against one end of the unlocking trigger rod; when the bracket moves to a throwing state, the bracket triggers the other end of the unlocking trigger rod, one end of the unlocking trigger rod pushes the other end of the locking rod to unlock the locking rod, and therefore the cabin door is driven to be closed by the energy storage mechanism.

According to one embodiment of the utility model, the door in the open state is perpendicular to the first direction and the second direction; and/or a door handle is arranged on the inner side surface of the cabin door facing the cabin; and/or the energy storage mechanism is a gas spring, a cylinder body of the gas spring is hinged to the cross beam, and a telescopic rod of the gas spring is hinged to the cabin door.

According to one embodiment of the utility model, the upper surface of the bracket is provided with a ball, and the bracket is used for supporting a cargo box through the ball.

According to another aspect of the present invention, there is provided an aircraft, wherein the aircraft comprises the aircraft cargo box dropping device as set forth in the utility model and described in the above embodiments.

According to the technical scheme, the aircraft container throwing device and the aircraft provided by the utility model have the advantages and positive effects that:

the utility model provides an aircraft container throwing device, which comprises two brackets and a driving mechanism; the two brackets are movably arranged at the throwing-in opening of the aircraft cabin respectively, and the driving mechanisms are used for driving the two brackets to move oppositely or back to back respectively. Therefore, the two brackets can be adjusted to be switched between a bearing state and a throwing state through the driving mechanism, the distance between the two brackets in the second direction is smaller than the width of the container in the bearing state, and the distance between the two brackets in the second direction is larger than or equal to the width of the container in the throwing state. Through the structural design, the movable bracket can be driven to support and release the container, so that the released container can be thrown in from the throwing opening of the cabin, the container does not need to move in the cabin in a large range, the device is simple in structure and convenient to arrange, and the influence on the flight safety of an airplane is small.

Drawings

Various objects, features and advantages of the present invention will become more apparent from the following detailed description of preferred embodiments of the utility model, when considered in conjunction with the accompanying drawings. The drawings are merely exemplary of the utility model and are not necessarily drawn to scale. In the drawings, like reference characters designate the same or similar parts throughout the different views. Wherein:

FIG. 1 is a perspective view of an aircraft cargo box drop arrangement in one state, according to an exemplary embodiment;

FIG. 2 is a perspective view of a portion of the structure shown in FIG. 1;

FIG. 3 is an enlarged schematic view of portion A of FIG. 2;

FIG. 4 is a schematic view of a portion of the structure shown in FIG. 2 in one state;

fig. 5 is a schematic view of the portion of the structure shown in fig. 4 supporting a cargo container;

FIG. 6 is a schematic structural view of a portion of the structure shown in FIG. 2 in another state;

fig. 7 is a schematic view of the structure of fig. 6 showing a part of the structure for dropping a container;

fig. 8 is a perspective view of the aircraft cargo box dropping device shown in fig. 1 in another state;

FIG. 9 is an enlarged schematic view of a portion of the structure shown in FIG. 8;

figure 10 is a schematic perspective view of the hinge base shown in figure 9;

FIG. 11 is a perspective view of a portion of the structure shown in FIG. 9;

FIG. 12 is a schematic view of the partial structure shown in FIG. 8 with the hatch door closed;

FIG. 13 is a schematic view of the door shown in FIG. 8 with the door open;

fig. 14 is a schematic perspective view of the aircraft cargo box dropping apparatus shown in fig. 1 supporting a cargo box;

fig. 15 is a perspective view of the aircraft cargo box dropping device shown in fig. 1 when dropping a cargo box.

The reference numerals are explained below:

100. a bracket; a door shaft;

110. a connecting plate; a door handle 330;

120. a ball bearing; 400, an energy storage mechanism;

210. a ball screw; a hinged support 500;

211. a screw; 510, an upper ear plate;

212. a slider; a lower ear plate;

220. a support; locking bar 610;

230. a torsion tube; locking the pin shaft 620;

240. an electric motor; 630. locking torsion spring;

250. a cross beam; unlocking a trigger lever 710;

251. an avoidance groove; 720, unlocking the pin shaft;

300. a cabin door; 730, unlocking the torsion spring;

310. a hinge; 800. a cargo box;

311. positioning a projection; x. a first direction;

y. a second direction.

Detailed Description

Exemplary embodiments that embody features and advantages of the utility model are described in detail below. It is to be understood that the utility model is capable of other and different embodiments and its several details are capable of modification without departing from the scope of the utility model, and that the description and drawings are accordingly to be regarded as illustrative in nature and not as restrictive.

In the following description of various exemplary embodiments of the utility model, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of illustration various exemplary structures, systems, and steps in which aspects of the utility model may be practiced. It is to be understood that other specific arrangements of parts, structures, example devices, systems, and steps may be utilized and structural and functional modifications may be made without departing from the scope of the present invention. Moreover, although the terms "over," "between," "within," and the like may be used in this specification to describe various example features and elements of the utility model, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples described in the figures. Nothing in this specification should be construed as requiring a specific three dimensional orientation of structures in order to fall within the scope of the utility model.

Referring to fig. 1, a perspective view of an aircraft cargo box dropping device according to the present invention in one state is representatively shown. In this exemplary embodiment, the aircraft cargo box releasing device proposed by the present invention is described by taking the application to military aircraft or unmanned aerial vehicles as an example. Those skilled in the art will readily appreciate that numerous modifications, additions, substitutions, deletions, or other changes may be made to the embodiments described below in order to utilize the concepts of the present invention in other types of aircraft, and still be within the scope of the principles of the aircraft cargo box drop arrangement set forth herein.

As shown in fig. 1, in the present embodiment, the device for dropping an aircraft cargo box according to the present invention includes two brackets 100 and a driving mechanism. Referring to fig. 2 to 15, fig. 2 representatively illustrates a perspective view of a portion of the structure shown in fig. 1; fig. 3 representatively illustrates an enlarged schematic structural view of a portion a in fig. 2; fig. 4 representatively illustrates a schematic structural view of a portion of the structure illustrated in fig. 2 in a state; fig. 5 representatively illustrates a schematic view of a portion of the structure shown in fig. 4 supporting a cargo box 800; fig. 6 representatively illustrates a schematic structural view of a portion of the structure illustrated in fig. 2 in another state; fig. 7 representatively illustrates a schematic view of a portion of the structure shown in fig. 6 when the cargo box 800 is dropped; fig. 8 representatively shows a perspective view of the aircraft cargo box dropping device in another condition; fig. 9 is an enlarged schematic view representatively illustrating a part of the structure shown in fig. 8; a perspective view of the hinge base 500 is representatively illustrated in fig. 10; fig. 11 is a perspective view typically illustrating a part of the structure shown in fig. 9; fig. 12 representatively illustrates an action schematic diagram of the partial structure illustrated in fig. 8 when the hatch door 300 is closed; fig. 13 representatively illustrates an action schematic diagram of the partial structure illustrated in fig. 8 when the hatch door 300 is opened; fig. 14 representatively illustrates a perspective view of an aircraft cargo box drop device holding a cargo box 800; fig. 15 representatively illustrates a perspective view of the aircraft cargo box dropping device dropping a cargo box 800. The structure, connection mode and functional relationship of the main components of the aircraft cargo box throwing device provided by the utility model will be described in detail below with reference to the attached drawings.

As shown in fig. 1 to 7, in the present embodiment, two carriages 100 are respectively provided at a delivery opening of an aircraft cabin, the carriages 100 extend in a first direction X, the two carriages 100 are arranged at intervals in a second direction Y perpendicular to the first direction X, and the carriages 100 are movable in the second direction Y. The driving mechanisms are respectively connected to the two brackets 100, and the driving mechanisms can drive the two brackets 100 to move toward or away from each other in the second direction Y. On this basis, the aircraft packing box throwing device can adjust two brackets 100 through actuating mechanism and change between bearing state and throwing state, and under the bearing state, the interval of two brackets 100 on second direction Y is less than the width of packing box 800 to make two brackets 100 can bear packing box 800, under the throwing state, the interval of two brackets 100 on second direction Y is greater than or equal to the width of packing box 800, thereby make packing box 800 can fall by the space between two brackets 100, and throw out the cabin of aircraft via throwing the mouth. Through the structural design, the movable bracket 100 is driven to support and release the container 800, so that the released container 800 can be put in from the putting-in opening of the cabin, the container 800 does not need to move in a large range in the cabin, and the device is simple in structure, convenient to arrange and small in influence on the flight safety of an airplane. The utility model is suitable for aircrafts flying at low speed and high speed, and realizes high-efficiency, high-safety and low-cost aerial material supply

Specifically, as shown in fig. 1 to 3, in the present embodiment, the driving mechanism includes two pairs of ball screws 210 and two motors 240. Specifically, two pairs of ball screws 210 are respectively disposed on the cabin of the aircraft through a support 220, the ball screws 210 extend along the second direction Y, the two pairs of ball screws 210 are arranged at intervals along the first direction X, the two ball screws 210 of the same pair are arranged at intervals along the second direction Y, the thread directions of the screw rods 211 are opposite, and the screw rods 211 of the two ball screws 210 of the same pair are connected through a torsion tube 230. The two motors 240 are respectively connected to one of the two pairs of ball screws 210 in a driving manner. In addition, one end of the one bracket 100 is connected to the slider 212 of one of the pair of ball screws 210, the other end is connected to the slider 212 of the other ball screw 210 located on the same side in the second direction Y, one end of the other bracket 100 is connected to the slider 212 of the other ball screw 210 of the pair, and the other end is connected to the slider 212 of the other ball screw 210 located on the same side in the second direction Y. Through the above structural design, the two pairs of ball screws 210 can be driven to rotate in opposite directions or opposite directions (for example, one of the two ball screws rotates clockwise and the other rotates counterclockwise and the other rotates clockwise and the other rotates opposite directions), so that the two sliders 212 spaced along the first direction X can move along the second direction Y at the same time, and the other two sliders 212 spaced along the first direction X can move along the second direction Y at the same time, thereby realizing the opposite or opposite movement of the two brackets 100 along the second direction Y, and further realizing the adjustment and conversion of the two brackets 100 between the supporting state and the releasing state. Accordingly, the driving mechanism of the present invention can realize the synchronous driving of the four ball screws 210, i.e., the four ends of the two brackets 100, by only arranging the two motors 240, and has the advantages of simple structure, convenient arrangement and accurate adjustment.

Further, as shown in fig. 3, in the present embodiment, the end of the bracket 100 may be connected to the slider 212 through the connection plate 110, and the end of the bracket 100 and the connection plate 110 may be connected in a hinged manner. Through the structural design, the structural design that the bracket 100 is hinged with the connecting plate 110 can meet the working requirement when two end parts of the bracket 100 are not flat, and the adaptability of the device is enhanced.

Further, as shown in fig. 3, in the present embodiment, the connecting plate 110 may have a substantially "L" shape, wherein one end of the connecting plate 110 may be fixedly connected to the slider 212 by a connecting member such as a bolt, and the other end of the connecting plate 110 may be hinged to the end of the bracket 100 by a pin.

Further, in the present embodiment, the output shaft of the motor 240 may be coupled to the screw 211 of the ball screw 210 by a coupling. Further, the torsion tube 230 may be coupled to the screw 211 of the ball screw 210 by a coupling. For example, in the case of one ball screw 210, one end of the screw 211 is coupled to one end of the torsion tube 230 via a coupling, and the other end of the screw 211 is coupled to the output shaft of the motor 240 via a coupling.

Specifically, as shown in fig. 1 and 2, in the present embodiment, a cross beam 250 may be connected between two mounts 220 located on the same side (i.e., two mounts 220 of two ball screws 210 of the same pair) along the second direction Y, the cross beam 250 extends along the first direction X, and the two cross beams 250 are spaced along the second direction Y. Through the structural design, the cross beam 250, the two pairs of ball screws 210 and the two torsion tubes 230 can form a frame structure in a shape of a Chinese character 'kou', so that the throwing opening of an airplane cabin is better matched, and the structural integrity and the structural strength of the device are optimized.

Further, as shown in fig. 3, based on the structural design that the beam 250 is connected between the two supports 220, and the end of the bracket 100 is connected to the slider 212 through the connecting plate 110, in the present embodiment, the bracket 100 may be located below the beam 250 on the same side in the thrown state. In addition, avoidance grooves 251 may be respectively provided at both end portions of the beam 250, and the avoidance grooves 251 may avoid the connection plate 110 when the bracket 100 is in the thrown state.

Specifically, as shown in fig. 8, 14 and 15, in this embodiment, the aircraft cargo box dropping device provided by the present invention may further include a two-piece door 300, two energy storage mechanisms 400, a locking mechanism, and an unlocking mechanism. Specifically, the two doors 300 are respectively hinged to the two cross beams 250, and the opening direction of the doors faces the cabin. The two energy storage mechanisms 400 are respectively connected between the two doors 300 and the two cross beams 250, and the energy storage mechanisms 400 can drive the doors 300 to close. The locking mechanism is disposed at the hinge joint of the door 300 and the cross member 250, and can lock the door 300 in an open state. The unlocking mechanism is connected to the locking mechanism and is matched with the bracket 100, and when the bracket 100 moves to the release state, the unlocking mechanism can unlock the cabin door 300 by the locking mechanism, so that the cabin door 300 is driven to close by the energy storage mechanism 400. Accordingly, when the door 300 is opened and the bracket 100 is in the support state, the locking mechanism locks the door 300 so that it cannot be driven to close by the energy storage mechanism 400, and at this time, the unlocking mechanism is not triggered, and the door 300 remains in the open state. When the bracket 100 moves and is switched from the supporting state to the dropping state, the cargo box 800 is dropped, and the bracket 100 triggers the unlocking mechanism, the unlocking mechanism contacts the locking mechanism to lock the cabin door 300, and the cabin door 300 is closed under the driving of the energy storage mechanism 400. When the door 300 needs to be opened again, the door 300 can be opened manually or through an automatic door opening mechanism, the bracket 100 moves and is converted from the release state to the support state, and the unlocking mechanism is not triggered by the bracket 100, so that the locking mechanism locks the opened door 300. Through the structural design, the inward opening type cabin door 300 is adopted, and air resistance caused by outward opening is avoided. Therefore, before the cargo box 800 is thrown, the cargo box 800 shields the throwing opening to keep the pneumatic appearance of the airplane, and after the cargo box 800 is thrown, the utility model can shield the throwing opening through the closed cabin door 300 and still keep the pneumatic appearance of the airplane, thereby further reducing the influence of throwing the cargo box 800 on the flight safety of the airplane. In addition, the energy storage mechanism 400, the locking mechanism and the unlocking mechanism are adopted in the utility model, so that the hatch 300 can be automatically switched from the open state to the closed state, and the hatch 300 in the open state can be locked and maintained.

Further, as shown in fig. 9 to 13, in the present embodiment, the cross beam 250 may be provided with a hinge seat 500, and the hinge seat 500 may be provided with an upper ear plate 510 and a lower ear plate 520. Also, the hatch 300 may be provided with a hinge 310, the hinge 310 being hinged to the upper ear plate 510 by a hatch shaft 320, and the hinge 310 being provided with a positioning protrusion 311. On this basis, the locking mechanism may include a locking rod 610, the locking rod 610 is hinged to the upper ear plate 510 through a locking pin 620, the other end extends to the unlocking mechanism, a locking torsion spring 630 is disposed between the locking pin 620 and the upper ear plate 510, and the locking torsion spring 630 may be mounted on the locking pin 620 and apply a certain torque to the locking rod 610. The unlocking mechanism may include an unlocking trigger lever 710, the unlocking trigger lever 710 is hinged to the lower ear plate 520 through an unlocking pin 720, one end of the unlocking trigger lever 710 extends to the other end of the locking lever 610 and is matched, the other end extends to the bracket 100 and is matched with the bracket 100, an unlocking torsion spring 730 is disposed between the unlocking pin 720 and the lower ear plate 520, the unlocking torsion spring 730 may be installed on the unlocking pin 720, and a certain torque may be applied to the unlocking trigger lever 710 to keep the unlocking trigger lever 710 in contact with the bottom of the locking lever 610. Accordingly, when the door 300 is in the open state, the positioning protrusion 311 is engaged with the locking rod 610, and the other end of the locking rod 610 presses against one end of the unlocking trigger rod 710. When the bracket 100 moves to the release state, the bracket 100 triggers the other end of the unlocking trigger rod 710, and one end of the unlocking trigger rod 710 pushes the other end of the locking rod 610 to unlock the locking rod 610, so that the hatch door 300 is driven to close by the energy storage mechanism 400. In some embodiments, the present invention may also adopt other specific structural designs to achieve the above-mentioned locking and unlocking functions of the door 300, and is not limited thereto.

Further, as shown in fig. 14, in the present embodiment, the hatch 300 in the open state may be perpendicular to the first direction X and the second direction Y, that is, the hatch 300 is perpendicular to a plane defined by the first direction X and the second direction Y. Through the structural design, the cabin door 300 can not interfere with the vertical side wall of the cargo box 800 in the opening state, the structural matching degree of the aircraft cargo box throwing device and the cargo box 800 is further optimized, and the space occupation of the device is favorably reduced.

Further, as shown in fig. 8, in the present embodiment, the inner side surface of the hatch 300 facing the cabin may be provided with a door handle 330. Through the structural design, the hatch door 300 can be manually opened by an operator through the door handle 330, so that the opening operation of the hatch door 300 is more convenient and labor-saving.

Further, in the present embodiment, the energy storage mechanism 400 may be a gas spring. Wherein the cylinder body of the gas spring may be hinged to the cross beam 250, and the telescopic rod of the gas spring extends from the cylinder body and may be hinged to the hatch 300. In some embodiments, the energy storage mechanism 400 may also be other devices, such as a hydraulic spring, and the like, but not limited thereto.

Alternatively, as shown in fig. 3, in the present embodiment, the upper surface of the bracket 100, i.e., the surface for supporting the cargo box 800, may be provided with the rolling balls 120. Accordingly, the carrier 100 can support the cargo box 800 by the balls 120. Through the structural design, the utility model can reduce the friction force between the bracket 100 and the container 800 when the bracket 100 supports the container 800 or when the container 800 moves out of or into the bracket 100.

Based on the above description of the structure of the main components of the device for releasing the aircraft cargo box according to the present invention, the working principle and the working process of the device for releasing the aircraft cargo box will be briefly described below.

As shown in fig. 4 and 5, when loading the cargo box 800, the motor 240 operates to move the carriage 100 of the cargo box 800 to the innermost side. The cargo box 800 is placed on the cargo box 800 bracket 100

As shown in fig. 6 and 7, when the dropping operation is performed, the motor 240 is operated to move the carriage 100 of the container 800 to the outermost side, the dropping passage of the container 800 is opened, and the container 800 is dropped out of the compartment by gravity.

As shown in fig. 12, when the cargo box 800 is loaded, the door 300 is manually opened, the door 300 is opened by 90 degrees, the locking rod 610 tends to move counterclockwise under the action of the locking torsion spring 630, the hinge 310 of the door 300 tends to move clockwise under the action of the gas spring, the bulge of the hinge 310 of the door 300 is locked by the locking rod 610, and the cargo door 300 is locked at the open position.

As shown in fig. 13, when the dropping operation is performed, the motor 240 operates to move the carriage 100 of the cargo box 800 to the outermost side, and simultaneously, the carriage 100 moves to contact with the unlocking trigger rod 710, the trigger rod rotates to drive the locking rod 610 to rotate reversely, and the contact locks the protruding structure of the hinge 310 of the hatch 300. The door 300 is closed at this time by the gas spring force and maintained in the closed position.

As mentioned above, the process of releasing the cargo box 800 by using the device for releasing the cargo box of the aircraft according to the present invention is as follows:

before loading, as shown in fig. 14, when the container 800 is loaded, the motor 240 is operated to move the bracket 100 to the innermost side, i.e., the supported state. When the two doors 300 are opened, the locking mechanism is matched with the unlocking mechanism to lock the doors 300 in the opening state.

In the case of dropping, as shown in fig. 15, when a dropping operation is performed, the motor 240 is operated to drive the carriage 100 to move to the outermost side, i.e., a dropping state, and the container 800 is dropped out of the cabin through the dropping opening by gravity. Meanwhile, the bracket 100 moved to the release state triggers the unlocking mechanism, the unlocking mechanism unlocks the locking mechanism to lock the door 300, and the door 300 is closed under the driving of the energy storage mechanism 400.

After deployment, as shown in fig. 8, the hatch 300 is maintained in a closed state by the energy storage mechanism 400.

It should be noted here that the aircraft cargo box drop arrangement shown in the drawings and described in this specification is only a few examples of the many types of aircraft cargo box drop arrangements that can employ the principles of the present invention. It should be clearly understood that the principles of the present invention are in no way limited to any details or any components of the aircraft cargo box drop arrangement shown in the drawings or described in this specification.

Based on the above detailed description of several exemplary embodiments of the cargo box dropping device for an aircraft according to the present invention, an exemplary embodiment of the aircraft according to the present invention will be described below.

In this embodiment, the aircraft proposed by the present invention includes the aircraft cargo box dropping device proposed by the present invention and described in detail in the above-described embodiment.

It should be noted herein that the aircraft illustrated in the accompanying drawings and described in the present specification are but a few examples of the wide variety of aircraft in which the principles of the present invention can be employed. It should be clearly understood that the principles of this invention are in no way limited to any of the details or any of the components of the aircraft shown in the drawings or described in this specification.

In summary, the device for releasing the cargo box of the aircraft according to the present invention includes two brackets 100 and a driving mechanism; the two brackets 100 are respectively movably arranged at the throwing opening of the aircraft cabin, and the driving mechanisms are respectively used for driving the two brackets 100 to move towards or away from each other. Accordingly, the present invention can adjust the two brackets 100 by the driving mechanism to switch between the supporting state in which the distance between the two brackets 100 in the second direction Y is smaller than the width of the cargo box 800 and the loading state in which the distance between the two brackets 100 in the second direction Y is greater than or equal to the width of the cargo box 800. Through the structural design, the movable bracket 100 can be driven to support and release the container 800, so that the released container 800 can be thrown in from the throwing opening of the cabin, the container 800 does not need to move in the cabin in a large range, and the device is simple in structure, convenient to arrange and small in influence on the flight safety of an airplane.

Exemplary embodiments of an aircraft cargo box drop arrangement and an aircraft according to the present invention are described and/or illustrated in detail above. Embodiments of the utility model are not limited to the specific embodiments described herein, but rather, components and/or steps of each embodiment may be utilized independently and separately from other components and/or steps described herein. Each component and/or step of one embodiment can also be used in combination with other components and/or steps of other embodiments. When introducing elements/components/etc. described and/or illustrated herein, the articles "a," "an," and "the" are intended to mean that there are one or more of the elements/components/etc. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc. Furthermore, the terms "first" and "second" and the like in the claims and the description are used merely as labels, and are not numerical limitations of their objects.

While the utility model has been described in terms of various specific embodiments, those skilled in the art will recognize that the utility model can be practiced with modification within the spirit and scope of the claims.

Claims (10)

1. An aircraft cargo box drop device, comprising:

the device comprises two brackets, a first fixing device and a second fixing device, wherein the two brackets are respectively arranged at a throwing opening of an aircraft cabin, the brackets extend along a first direction, the two brackets are arranged at intervals along a second direction perpendicular to the first direction, and the brackets can move along the second direction; and

the driving mechanisms are respectively connected to the two brackets and used for driving the two brackets to move towards or away from each other in the second direction;

wherein the aircraft cargo box dropping device is configured to adjust the two brackets to switch between a supporting state and a dropping state through the driving mechanism, wherein in the supporting state, the distance between the two brackets in the second direction is smaller than the width of a cargo box, and in the dropping state, the distance between the two brackets in the second direction is larger than or equal to the width of the cargo box.

2. An aircraft cargo box drop arrangement as defined in claim 1, wherein the drive mechanism comprises:

the two pairs of ball screws are respectively arranged in a cabin of an airplane through a support, the ball screws extend along the second direction, the two pairs of ball screws are arranged at intervals along the first direction, the two ball screws of the same pair are arranged at intervals along the second direction, the thread directions of the screw rods are opposite, and the screw rods of the two ball screws of the same pair are connected through a torsion tube;

the two motors are respectively connected with one of the two pairs of ball screws in a transmission way;

one end of one of the brackets is connected to the slider of one of the ball screws, the other end of the one of the brackets is connected to the slider of the other of the ball screws located on the same side in the second direction, one end of the other of the brackets is connected to the slider of the other of the ball screws, and the other end of the other of the brackets is connected to the slider of the other of the ball screws located on the same side in the second direction.

3. An aircraft cargo box drop arrangement as claimed in claim 2, wherein the ends of the brackets are connected to the slide by connection plates and the ends of the brackets are hinged to the connection plates.

4. An aircraft cargo box drop arrangement as claimed in claim 2, wherein a cross-beam is connected between the two supports on the same side in the second direction.

5. An aircraft cargo box drop arrangement as claimed in claim 4, wherein the ends of the brackets are connected to the skid by connection plates, the brackets being located beneath the cross beams on the same side in a dropped condition; and the two end parts of the cross beam are respectively provided with an avoiding groove for avoiding the connecting plate when the bracket is in a throwing state.

6. An aircraft cargo box drop apparatus as claimed in claim 4, further comprising:

the two opposite-opening cabin doors are respectively hinged to the two cross beams, and the door opening direction faces to the inside of the cabin;

the two energy storage mechanisms are respectively connected between the two cabin doors and the two cross beams and are used for driving the cabin doors to close;

the locking mechanism is arranged at the hinged position of the cabin door and the cross beam and used for locking the cabin door in an open state; and

and the unlocking mechanism is connected with the locking mechanism, is matched with the bracket and is used for unlocking the cabin door by the locking mechanism when the bracket moves to a throwing state so as to enable the cabin door to be driven by the energy storage mechanism to be closed.

7. An aircraft cargo box drop arrangement as claimed in claim 6, wherein:

the cross beam is provided with a hinged support, the hinged support is provided with an upper ear plate and a lower ear plate, the cabin door is provided with a hinge, the hinge is hinged to the upper ear plate through a cabin door shaft, and the hinge is provided with a positioning bulge;

the locking mechanism comprises a locking rod which is hinged to the upper lug plate through a locking pin shaft, the other end of the locking rod extends to the unlocking mechanism, and a locking torsion spring is arranged between the locking pin shaft and the upper lug plate;

the unlocking mechanism comprises an unlocking trigger rod, the unlocking trigger rod is hinged to the lower lug plate through an unlocking pin shaft, one end of the unlocking trigger rod extends to the other end of the locking rod and is matched with the locking rod, the other end of the unlocking trigger rod extends to the bracket and is matched with the bracket, and an unlocking torsion spring is arranged between the unlocking pin shaft and the lower lug plate;

when the cabin door is in an open state, the positioning protrusion is clamped with the locking rod, and the other end of the locking rod is pressed against one end of the unlocking trigger rod; when the bracket moves to a throwing state, the bracket triggers the other end of the unlocking trigger rod, one end of the unlocking trigger rod pushes the other end of the locking rod to unlock the locking rod, and therefore the cabin door is driven to be closed by the energy storage mechanism.

8. An aircraft cargo box drop arrangement according to claim 6 wherein the hatch in the open condition is perpendicular to the first and second directions; and/or a door handle is arranged on the inner side surface of the cabin door facing the cabin; and/or the energy storage mechanism is a gas spring, a cylinder body of the gas spring is hinged to the cross beam, and a telescopic rod of the gas spring is hinged to the cabin door.

9. An aircraft cargo box drop arrangement as claimed in claim 1, wherein the upper surface of the carrier is provided with a roller ball by which the carrier carries a cargo box.

10. An aircraft, characterized in that the aircraft comprises the aircraft container throwing device as claimed in any one of claims 1 to 9.

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