CN115107988B - Cargo handling device and unmanned freight aircraft - Google Patents
Cargo handling device and unmanned freight aircraft Download PDFInfo
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- CN115107988B CN115107988B CN202210854979.3A CN202210854979A CN115107988B CN 115107988 B CN115107988 B CN 115107988B CN 202210854979 A CN202210854979 A CN 202210854979A CN 115107988 B CN115107988 B CN 115107988B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/22—Other structures integral with fuselages to facilitate loading, e.g. cargo bays, cranes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a cargo handling device and an unmanned cargo aircraft, wherein the device comprises a guide rail unit, the guide rail unit is arranged on the floor of a cargo compartment of the aircraft, and the guide rail unit comprises a first guide rail, a second guide rail and a plurality of third guide rails positioned between the first guide rail and the second guide rail. The device can be modified on the basis of the cargo hold structure of the original aircraft, so that the original aircraft structure is not damaged, and the structural safety of the original aircraft is ensured; the structural design characteristics of the original machine are fully utilized, the cargo handling device is convenient to install and disassemble, the modification process of the prototype machine is convenient to simplify, and the maintenance, the inspection and the replacement of each part of the cargo handling device are convenient; the cargo handling process is simple and convenient, the handling and the fixing of the cargo fully consider the operation space of personnel, and the fixing operation of the cargo transportation box is convenient; the movement of the cargo transportation box is carried out on the universal balls, so that the manual operation burden is fully lightened.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a cargo handling device and an unmanned freight aircraft.
Background
With the rapid development of the economic society in China, the logistics industry development presents a vigorous machine, enters a high-speed growth period, reduces logistics cost, shortens logistics time, and becomes a target pursued by various large logistics enterprises.
Initially, mainstream logistics enterprises are used for shortening logistics time and improving transportation frequency, and on the basis of land transportation, goods with urgent needs and high added value are transported in a civil aviation manned transportation mode. Although the logistics time can be shortened by the civil aviation personnel freight transportation, and the purpose of improving the efficiency is achieved, the mode has the following defects: firstly, people in civil aviation drive and transport, including participation of people (pilots), inevitably generate labor cost; secondly, considering the limitation of large manned freight aircraft on airport runways, most of civil aviation manned aircraft are matched with large civil aviation airports, so that airport load is necessarily brought; finally, large and medium airports in China are mostly distributed in provincial and isocentric cities, and cannot be effectively covered in remote areas, so that insufficient logistics capacity of civil aviation branches is caused.
Along with the development of science and technology, the application of unmanned aerial vehicle under commodity circulation scene will open up the new passageway of aviation commodity circulation of domestic trunk line and branch line, effectively solves the problem such as inconvenient, the transportation efficiency low of remote area commodity circulation transportation. The unmanned aerial vehicle freight transportation mode has obvious advantages. Firstly, unmanned, the manpower cost is reduced; secondly, unmanned aerial vehicle goods fortune aircraft mass is little, and is low to the airport runway requirement, can adapt to civil aviation airport, also can operate at remote navigation airport, realizes shipping trunk line, branch line seamless connection, great improvement operating efficiency.
Cargo handling devices are an important component of cargo-transporting aircraft that are used to assist a user in loading or unloading cargo into or from an aircraft cargo hold. Most of the current airplanes with the capability of transporting goods in the tonnage level are piloted airplanes, and the design scheme of the goods handling device cannot be directly transplanted to unmanned goods transport airplanes. The cargo handling device is used as a device for realizing cargo carrying function of the unmanned aerial vehicle, and the functionality of the cargo handling device directly influences the safety of the unmanned aerial vehicle and the experience of users.
Therefore, how to provide a cargo handling device suitable for unmanned transportation aircraft, which is capable of guaranteeing the balance and safety of the aircraft load, ensuring other structures of the aircraft body, facilitating the user to realize rapid loading and unloading and exerting the requirements of the aircraft load capacity as much as possible, is a technical problem which needs to be solved by the technicians in the field.
Disclosure of Invention
The invention provides a cargo handling device and an unmanned cargo plane.
The invention provides the following scheme:
A cargo handling device comprising:
the guide rail unit is arranged on the aircraft cargo compartment floor and comprises a first guide rail, a second guide rail and a plurality of third guide rails positioned between the first guide rail and the second guide rail; the respective axial directions of the first guide rail, the second guide rail and the third guide rail extend along the course of the aircraft;
A plurality of side edge guide roller mechanisms are respectively arranged on the first guide rail and the second guide rail, each side edge guide roller mechanism comprises a guide roller, and the rotation direction of each guide roller is the same as the axial direction of each of the first guide rail and the second guide rail;
the third guide rail is provided with a plurality of universal ball mechanisms; the universal ball mechanism comprises universal balls;
The side guide roller mechanism is connected with the first guide rail and the second guide rail through the fixed clamping seat assembly, and the universal ball mechanism is connected with the third guide rail through the fixed clamping seat assembly; the surface of the guide roller is used for being abutted against the side face of the cargo transportation box so as to limit the transverse displacement of the cargo transportation box, and the universal balls contained in the universal ball mechanisms are all used for being abutted against the bottom face of the cargo transportation box so as to form a supporting plane of the cargo transportation box.
Preferably: the cross sections of the first guide rail, the second guide rail and the third guide rail are all of the same U-shaped structure; the fixed clamping seat assembly comprises a fixed seat supporting rod, a cargo hold guide rail fixed buckle and a spring; the bottom of fixing base bracing piece is provided with T type portion, T type portion be used for with U type structure joint links to each other.
Preferably: the side guide roller mechanism comprises guide roller supports and connecting bolts, wherein two guide rollers are hinged with the guide roller supports; the connecting bolts sequentially penetrate through the guide roller support, the springs and the cargo compartment guide rails to be fixedly and in snap fit with the threaded holes of the fixing seat support rods.
Preferably: the universal ball mechanism comprises a ball seat, the universal balls are connected with the ball seat in a matched mode, the ball seat comprises a connecting screw rod, and the connecting screw rod sequentially penetrates through the spring and the cargo hold guide rail to be fixedly and in a matched mode to be connected to the threaded hole of the fixing seat support rod.
Preferably: the locking unit at least comprises a first locking mechanism, and the first locking mechanism is arranged on the third guide rail through the fixed clamping seat assembly; the first locking mechanism includes a bullet type male abutment for connection with a bullet type female abutment on the cargo transportation box.
Preferably: the first locking mechanism comprises a first bullet head supporting seat, and the first bullet head supporting seat is connected with two groups of fixed clamping seat components.
Preferably: the second locking mechanism is arranged on the third guide rail through the fixed clamping seat assembly; the first locking mechanism is positioned in front of the second locking mechanism in the course direction of the aircraft;
The second locking mechanism comprises a second bullet head supporting seat and two bullet type male butt joints, wherein the two bullet type male butt joints are connected with the second bullet head supporting seat and symmetrically distributed on the front side and the rear side of the second bullet head supporting seat.
Preferably: the third locking mechanism is arranged on the third guide rail through the fixed clamping seat assembly; the second locking mechanism is positioned in front of the third locking mechanism in the course direction of the aircraft;
The third locking mechanism comprises a third bullet head supporting seat, two bullet type male butt joints and thin universal balls, wherein the two bullet type male butt joints are connected with the second bullet head supporting seat and symmetrically distributed on the front side and the rear side of the second bullet head supporting seat, and the thin universal balls are connected with the third bullet head supporting seat and located behind the third bullet head supporting seat.
Preferably: the four guide rails are arranged behind the third guide rail and opposite to the cabin door of the aircraft, and the four guide rails are connected with the universal ball mechanism and/or the fourth locking mechanism through the fixing clamping seat assembly; the third locking mechanism is positioned in front of the fourth locking mechanism in the course direction of the aircraft;
The fourth locking mechanism comprises a supporting bottom plate, a fourth bullet head supporting seat, a bullet type male-to-joint and a thin type universal ball, wherein the bullet type male-to-joint and the thin type universal ball are connected with the fourth bullet head supporting seat and are positioned in front of the fourth bullet head supporting seat.
An unmanned cargo aircraft comprising a cargo hold, the cargo hold floor being provided with a cargo handling device as described above.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
According to the cargo handling device and the unmanned cargo plane provided by the embodiment of the application, the cargo handling device can be modified on the basis of the cargo space structure of the original plane, the original plane structure is not damaged, and the structural safety of the original plane is ensured; the structural design characteristics of the original machine are fully utilized, the cargo handling device is convenient to install and disassemble, the modification process of the prototype machine is convenient to simplify, and the maintenance, the inspection and the replacement of each part of the cargo handling device are convenient; the cargo handling process is simple and convenient, the handling and the fixing of the cargo fully consider the operation space of personnel, and the fixing operation of the cargo transportation box is convenient; the movement of the cargo transportation box is carried out on the universal balls, so that the manual operation burden is fully lightened.
In addition, under a preferred implementation mode, the cargo transportation box is fixed through the locking units designed at the front part and the rear part of the cargo transportation box, so that the manual operation links are greatly simplified; the connecting structure appearance that contains locking mechanism is designed into bullet head shape for possess certain ability of rectifying to locking unit, reduced the requirement to the cooperation precision, combined the combined action of the lateral displacement of the guide roller limit cargo transportation case of distributing in cargo transportation case both sides, make the cargo transportation case can be easily realized with the butt joint cooperation to locking unit.
Of course, it is not necessary for any one product to practice the invention to achieve all of the advantages set forth above at the same time.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings by those of ordinary skill in the art without inventive effort.
Fig. 1 is a schematic structural view of a cargo handling device according to an embodiment of the present invention;
FIG. 2 is another schematic view of a cargo handling device (prior to loading a cargo conveyance) according to an embodiment of the present invention;
FIG. 3 is an exploded view of a side guide roller mechanism provided in an embodiment of the present invention;
FIG. 4 is a schematic view of a side guide roller mechanism according to an embodiment of the present invention;
FIG. 5 is an exploded view of a universal ball mechanism provided in accordance with an embodiment of the present invention;
FIG. 6 is a schematic view of a ball and socket assembly according to an embodiment of the present invention;
FIG. 7 is an exploded view of a first locking mechanism provided in an embodiment of the present invention;
FIG. 8 is a schematic structural view of a first locking mechanism according to an embodiment of the present invention;
FIG. 9 is an exploded view of a second locking mechanism provided in an embodiment of the present invention;
FIG. 10 is a schematic diagram of a second locking mechanism according to an embodiment of the present invention;
FIG. 11 is an exploded view of a third locking mechanism provided in an embodiment of the present invention;
FIG. 12 is a schematic view of a third locking mechanism according to an embodiment of the present invention;
FIG. 13 is an exploded view of a fourth locking mechanism provided by an embodiment of the present invention;
FIG. 14 is a schematic view of a fourth locking mechanism according to an embodiment of the present invention;
FIG. 15 is an isometric view of a first cargo conveyance case according to an embodiment of the invention secured thereto;
FIG. 16 is an isometric view of a second cargo conveyance case according to an embodiment of the invention secured thereto;
FIG. 17 is an isometric view of a third cargo conveyance box according to an embodiment of the invention secured thereto;
fig. 18 is a schematic structural view of an unmanned cargo aircraft according to an embodiment of the present invention.
In the figure: the cargo handling device 1, the first rail 11, the second rail 12, the third rail 13, the side guide roller mechanism 14, the guide roller 141, the guide roller support 142, the connecting bolt 143, the universal ball mechanism 15, the universal ball 151, the ball seat 152, the fixing holder assembly 16, the fixing holder support bar 161, the cargo compartment rail fixing buckle 162, the spring 163, the first locking mechanism 17, the first bullet support 171, the second locking mechanism 18, the second bullet support 181, the third locking mechanism 19, the third bullet support 191, the fourth locking mechanism 110, the support bottom plate 1101, the fourth bullet support 1102, the bullet male-female joint 111, the thin universal ball 112, the fourth rail 113, the unmanned cargo aircraft 2, the cargo compartment 3, the cargo compartment door 4, the first cargo transportation box 5, the second cargo transportation box 6, and the third cargo transportation box 7.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which are derived by a person skilled in the art based on the embodiments of the invention, fall within the scope of protection of the invention.
Referring to fig. 1,2,3 and 4, a cargo handling device 1 according to an embodiment of the present invention, as shown in fig. 1,2,3 and 4, may include:
The guide rail unit is arranged on the floor of the aircraft cargo compartment 3 and comprises a first guide rail 11, a second guide rail 12 and a plurality of third guide rails 13 positioned between the first guide rail 11 and the second guide rail 12; the axial directions of the first guide rail 11, the second guide rail 12 and the third guide rail 13 all extend along the course of the aircraft;
a plurality of side edge guide roller mechanisms 14 are respectively arranged on the first guide rail 11 and the second guide rail 12, the side edge guide roller mechanisms 14 comprise guide rollers 141, and the rotation direction of the guide rollers 141 is the same as the respective axial directions of the first guide rail 11 and the second guide rail 12;
The third guide rail 13 is provided with a plurality of universal ball mechanisms 15; the universal ball mechanism 15 includes a universal ball 151;
The side guide roller mechanism 14 is connected with the first guide rail 11 and the second guide rail 12 through a fixed clamping seat assembly 16, and the universal ball mechanism 15 is connected with the third guide rail 13 through the fixed clamping seat assembly 16; the surface of the guiding roller 141 is used for abutting against the side surface of the cargo transportation box so as to limit the lateral displacement of the cargo transportation box, and the universal balls contained in the universal ball mechanisms 15 are all used for abutting against the bottom surface of the cargo transportation box so as to form a supporting plane of the cargo transportation box.
The cargo handling device provided by the embodiment of the application can be installed in the cargo hold 3 of the unmanned cargo aircraft 2, wherein the rail units can be various rails existing in the prior art. The first guide rail 11 and the second guide rail 12 which are positioned at two sides are respectively provided with the side guide roller mechanisms 14, the side guide roller mechanisms 14 can limit the lateral displacement of the cargo transportation box in the process that the cargo transportation box is pushed forward by a user, meanwhile, rolling friction with the cargo transportation box can be realized through the rollers, friction force between the two is reduced, and the requirement on the thrust of the user is reduced. The plurality of universal ball mechanisms 15 arranged on the third guide rail 13 can be abutted with the bottom surface of the cargo transportation box so as to form a supporting plane of the cargo transportation box, and meanwhile, rolling friction is formed with the bottom surface of the cargo transportation box, so that the purpose of further reducing the requirement on the thrust of a user is achieved.
In addition, the side guiding roller mechanism 14 and the universal ball mechanism 15 provided by the embodiment of the application are connected with the opposite guide rails by adopting the fixing clamping seat assembly 16 with the same structure, so that the universality of parts with all mechanisms is strong, all the mechanisms can be quickly installed and disassembled, and the positions of all the mechanisms can be flexibly adjusted to adapt to different cargo transportation box arrangement schemes.
It can be understood that each guide rail provided by the embodiment of the application can be an original guide rail of an airplane, all parts are directly connected with the original guide rail, and the original structure is not required to be damaged in the installation process of the whole cargo handling device, so that any adverse effect is not caused to the original structure. Of course, in an aircraft without a guide rail, the corresponding guide rail may be provided at a corresponding position by providing the corresponding guide rail.
In practical applications, the fixing cassette assembly 16 provided in the embodiment of the present application is used for connecting with a guide rail, and the structure of the fixing cassette assembly 16 can provide a structure capable of being quickly connected with the guide rail according to the style of the guide rail. For example, in one implementation, the embodiment of the present application may provide that the cross sections of the first rail 11, the second rail 12, and the third rail 13 all have the same U-shaped structure; the fixing holder assembly 16 comprises a fixing holder support bar 161, a cargo compartment guide rail fixing buckle 162 and a spring 163; the bottom of fixing base bracing piece 161 is provided with T type portion, T type portion be used for with U type structure joint links to each other. The fixing base support bar 161 may be provided with a positioning protrusion, the cargo compartment guide rail fixing buckle 162 is provided with a positioning slot, and the fixing base support bar 161 and the cargo compartment guide rail fixing buckle 162 implement positioning through the positioning protrusion and the positioning slot.
The main design of the existing cargo hold 3 floor of a cargo aircraft is preset with several rows of floor-mounted mounting rails. The guide rails with the U-shaped cross sections are most commonly used, and the fixing clip seat assembly 16 according to the embodiment of the present application provides the T-shaped portion of the fixing seat support rod 161 according to the commonly used U-shaped guide rails, and the T-shaped portion can be inserted into the guide rails by inserting the open ends of the guide rails and can be used to connect with the corresponding connecting members after moving to the corresponding positions along the guide rails.
The principle that each mechanism can be flexibly disassembled, assembled and moved in the original machine guide rail is realized through the cooperation of the guide rail fixing buckle, the fixing seat supporting rod 161 and the spring 163 is as follows: when the lugs on two sides of the guide rail fixing buckle are used for lifting the guide rail fixing buckle by the compression spring 163, the fixing seat supporting rod 161 can move back and forth in the original machine guide rail; when the fixing seat supporting rod 161 moves to any narrow slit position of the original machine guide rail, the guide rail fixing buckle is put down, and at the moment, the fixing seat supporting rod 161 is locked at the position of the guide rail, cannot move back and forth, and cannot be lifted from the original machine guide rail.
Specifically, as shown in fig. 3 and 4, the side guiding roller mechanism 14 includes two guiding roller supports 142 and a connecting bolt 143, and the two guiding rollers are hinged to the guiding roller supports 142; the connecting bolt 143 is connected to the threaded hole of the fixing base support bar 161 through the guide roller support 142, the spring 163 and the cargo compartment rail fixing buckle 162 in sequence. The side edge guiding roller mechanisms 14 of the side edges of the cargo transportation box are arranged on two guide rails positioned on two sides of the cargo transportation box, the displacement of the cargo transportation box in the directions of two sides of an airplane is firmly limited through the guiding rollers, the cargo transportation box is ensured to slide along a given track only, and the cargo transportation box and the locking device are matched.
The matched key slot is designed between the guide roller support 142 and the guide rail fixing component, which can prevent the guide roller from blocking the moving channel of the cargo transportation box due to rotating around the fixed seat supporting rod 161; the guide roller adopts a standard component with the standard number of PU 8 x 40 x 30, has very high dimensional accuracy and very low rolling friction resistance, and the roller is made of polyurethane soft rubber material and can be well attached to the surface of the cargo transportation box. The side guiding roller devices are distributed on the guide rails on two sides of the cargo transportation box, and the guiding roller is contacted with the left side and the right side of the cargo transportation box by designing the size of the cargo transportation box, so that the effect of limiting the lateral displacement of the cargo transportation box is achieved.
As shown in fig. 5 and 6, the universal ball mechanism 15 includes a ball seat 152, the universal balls are cooperatively connected with the ball seat 152, the ball seat 152 includes a connecting screw, and the connecting screw sequentially passes through the spring 163 and the cargo compartment rail fixing buckle 162 and is cooperatively connected to the threaded hole of the fixing seat support bar 161. The universal ball mechanism 15 located at the bottom of the cargo transportation box contacts with the bottom of the cargo transportation box through the universal balls, and enough universal balls contact with the cargo transportation box to ensure that the cargo transportation box can stably and smoothly slide in the cargo hold 3 of the aircraft.
The universal ball provided by the embodiment of the application is a standard component with the standard number of SP15-FL, and is directly screwed with the fixing seat supporting rod 161 through a threaded rod at the bottom end of the universal ball. The supporting plane of the cargo transportation box is formed by a plurality of universal balls arranged along the original machine guide rail, so that the cargo transportation box can slide smoothly on the plane constructed by the universal balls.
In order to realize positioning and fixing of the cargo transportation box after the cargo transportation box runs in place, as shown in fig. 7 and 8, the embodiment of the application may further provide a locking unit, where the locking unit includes at least a first locking mechanism 17, and the first locking mechanism 17 is disposed on the third rail 13 through the fixing clamping seat assembly 16; the first locking mechanism 17 comprises a bullet-shaped male abutment 111, the bullet-shaped male abutment 111 being adapted to be connected to a bullet-shaped female abutment on the cargo transportation box.
The first locking mechanism 17 provided in the embodiment of the present application is connected to the corresponding guide rail by using the same fixing socket assembly 16 as the side guide roller mechanism 14 and the universal ball mechanism 15. And the bullet-shaped butt joint is in butt joint with the bullet-shaped female butt joint corresponding to the cargo transportation box. By adopting the locking mode, the manual operation link of locking the front part of the cargo transportation box is eliminated, and the problem that the front part of the cargo transportation box is difficult to lock because of insufficient operation space is solved; the bullet is designed to have certain deviation rectifying capacity, so that the matching precision requirement of the cargo transportation box and the locking mechanism is reduced, and the cargo transportation box can be easily abutted with the locking mechanism.
Further, the first locking mechanism 17 includes a first bullet head supporting seat 171, and two groups of fixing clamping seat assemblies 16 are connected to the first bullet head supporting seat 171. The first bullet head supporting seat 171 is connected with the original machine guide rail through two groups of fixed seat supporting rods 161, so that the original machine guide rail is not damaged due to the tendency of torque generated by a single fixed seat supporting rod 161 when bearing the axial force transmitted by the goods transport box through a bullet butt joint; the butt joint adopts the shape of a bullet, so that the accuracy requirement of the butt joint of the bullet and the cargo transport box is reduced; the first locking mechanism 17 mainly serves to restrict the up-down, left-right and forward movement of the cargo conveyance case.
It will be appreciated that the first locking mechanism 17 provided in the present embodiment is primarily used to secure the front end of the cargo box, although it may be used to secure the rear end of the cargo box. Since a plurality of containers may be arranged in the same cabin, in order to fix a plurality of containers at the same time, as shown in fig. 9 and 10, the embodiment of the present application may further include a second locking mechanism 18, where the second locking mechanism 18 is disposed on the third guide rail 13 through the fixing card seat assembly 16; the first locking mechanism 17 is located in front of the second locking mechanism 18 in the direction of the heading of the aircraft; the second locking mechanism 18 includes a second bullet supporting seat 181 and two bullet type male-to-connector 111, and the two bullet type male-to-connector 111 are connected to the second bullet supporting seat 181 and symmetrically distributed on the front and rear sides of the second bullet supporting seat.
The left side and the right side of the second bullet head supporting seat 181 are fixedly connected with bullet type male butt joints 111 which are respectively used for butt joint with the rear part of the first cargo transportation box 5 and the front part of the second cargo transportation box 6; when the first cargo transportation box 5 has a tendency to retreat and transmit axial force to the left bullet-shaped male butt joint 111, the rear locking device of the second cargo transportation box 6 has a tendency to topple backwards, and at this time, the right bullet-shaped male butt joint 111 abutting against the second cargo transportation box 6 provides a reverse moment to balance the rolling moment due to displacement limitation, so that only one set of fixing seat support rods 161 is needed for the second locking mechanism 18 at the rear of the first cargo transportation box 5 to be connected with the original machine guide rail.
Further, as shown in fig. 11 and 12, the locking device further includes a third locking mechanism 19, where the third locking mechanism 19 is disposed on the third rail 13 through the fixing socket assembly 16; the second locking mechanism 18 is located in front of the third locking mechanism 19 in the direction of the heading of the aircraft;
The third locking mechanism 19 includes a third bullet-shaped supporting seat 191, two bullet-shaped male-to-connector 111 and a thin universal ball 112, the two bullet-shaped male-to-connector 111 are connected with the second bullet-shaped supporting seat 181 and symmetrically distributed on the front and rear sides of the second bullet-shaped supporting seat, and the thin universal ball 112 is connected with the third bullet-shaped supporting seat 191 and is located behind the third bullet-shaped supporting seat 191.
The difference from the second bullet supporting seat 181 is that a thin universal ball 112 is added to the rear part of the third bullet supporting seat 191 for supporting the third cargo transportation box 7; after the bullet type male butt joint 111 at the left side of the third bullet supporting seat 191 is engaged with the second cargo-transporting box 6, the combined supporting action of the second cargo-transporting box 6 and the original machine guide rail already enables the third cargo-transporting box 7 to be supported, and the thin universal ball 112 is fixed at this point to solve the problem that the front side of the third cargo-transporting box 7 lacks the universal ball support.
Further, as shown in fig. 13 and 14, the device further includes a plurality of fourth guide rails 113, where the fourth guide rails 113 are disposed behind the third guide rails 13 and opposite to the cabin door of the aircraft, and the fourth guide rails 113 are connected to the universal ball mechanism 15 and/or the fourth locking mechanism 110 through the fixing clamping seat assembly 16; the third locking mechanism is positioned in front of the fourth locking mechanism in the course direction of the aircraft;
The fourth locking mechanism 110 includes a fourth bullet supporting seat 1102, the bullet-shaped male-to-connector 111 and a thin-type universal ball 112, where the bullet-shaped male-to-connector 111 and the thin-type universal ball 112 are connected to the fourth bullet supporting seat 1102 and located in front of the fourth bullet supporting seat 1102.
The fourth guide rail 113 provided by the embodiment of the application can be in the form of a section guide rail, is arranged at the position of the cabin door, and the universal balls are arranged on part of the fourth guide rail 113, so that the starting position can be supported after equipment such as a crane is used for placing a cargo transportation box in a cabin, and the bottom rolling support mode is adopted in the whole pushing process of the cargo transportation box.
The fourth locking mechanism 110 at the rear of the third cargo transportation box 7 is divided into two parts, namely a bullet supporting bottom plate 1101 and a fourth bullet supporting seat 1102; the parts of the guide rail fixing buckle, the fixing seat supporting rod 161, the spring 163, the inner hexagonal cylindrical head screw, the thin universal ball 112 and the supporting bottom plate 1101 are connected to the original machine guide rail before the loading of the goods transportation boxes, after the third goods transportation boxes 7 are loaded in place, the bullet butt joint fixed on the fourth bullet supporting seat 1102 is inserted into the butt joint hole at the rear part of the third goods transportation boxes 7, and then the fourth bullet supporting seat 1102 is screwed on the bullet supporting bottom plate 1101 through bolts, so that the fixing of the third goods transportation boxes 7 can be completed.
The second locking mechanism 18 fixes the first cargo transportation box 5 at the corresponding position of the guide rail after the first cargo transportation box 5 is pushed to the position matched with the first locking mechanism 17. The first cargo transportation box 5 is engaged with the bullet connector of the first locking mechanism 17 through the bullet butt hole at the front part thereof, the bullet butt hole at the rear part thereof is engaged with the bullet of the rear second locking mechanism 18, and the first cargo transportation box 5 is fixed on the floor of the cargo compartment 3 of the aircraft through the coaction of the guiding roller devices on the guide rails at both sides. The second cargo conveyance case 6 and the third cargo conveyance case 7 are fixed in a similar manner to the first cargo conveyance case 5.
The following describes in detail the use of the device according to the embodiment of the application, taking three cargo transportation boxes as examples.
The first, second and third cargo transportation boxes are positioned on the parking apron lifter at the lower position outside the door of the cargo hold 3, and the loading process of the cargo transportation boxes is as follows:
Firstly, lifting the first cargo transportation box 5 to the floor height in the cabin door of the airplane by a lifter, pushing the first cargo transportation box 5 into the cargo cabin 3 from the cabin door of the cargo cabin 3 by a person, placing the first cargo transportation box 5 on a universal ball contained in a fourth guide rail 113, pushing the first cargo transportation box 5 until the first cargo transportation box contacts a guide roller positioned in front of cargo transportation by a user, wherein the first cargo transportation box 5 cannot be pushed continuously along the direction of the cabin door; and then the first cargo transportation box 5 is pushed to a position matched with the first locking mechanism 17 at the front part of the first cargo transportation box 5 in the course direction of the cargo hold 3. In the process, the guide rollers positioned at the two sides of the cargo transportation limit the displacement of the guide rollers in the left-right direction, and the moving track of the cargo transportation box is L-shaped;
As shown in fig. 15, fixing the second locking mechanism 18 at the rear of the first cargo transportation box 5 to the guide rail by the guide rail fixing assembly enables the bullet-shaped male butt joint 111 at the left side of the second locking mechanism 18 at the rear of the first cargo transportation box 5 to be mated with the bullet-shaped female butt joint at the rear of the first cargo transportation box 5 in a tight position. So far, the loading and fixing of the first cargo transportation box 5 are finished;
As shown in fig. 16, the second cargo conveyance case 6 is pushed to a position where the bullet-shaped female abutment fitting hole at the front thereof is tightly fitted with the bullet-shaped male abutment 111 at the right side of the second locking mechanism 18 in the same manner, and then the third locking mechanism 19 at the rear of the second cargo conveyance case 6 is fixed to the guide rail in the same manner so that the bullet-shaped male abutment 111 at the left side thereof can be tightly fitted with the bullet-shaped female abutment at the rear of the second cargo conveyance case 6.
As shown in fig. 17, the third cargo conveyance case 7 is pushed to a position where the bullet-shaped female butt joint engagement hole at the front portion thereof is tightly engaged with the bullet-shaped male butt joint 111 at the right side of the third locking mechanism 19 in the same manner, the fourth locking mechanism 110 is installed in a manner different from that of the third locking mechanism 19, and the supporting base 1101 is partially connected to the original machine rail in advance, where the fourth bullet supporting base 1102 is simply screwed to the supporting base 1101. So far, the loading and fixing of the 3 cargo transportation boxes are finished, and the cargo loading process is finished.
In some embodiments of the present disclosure, the unloading process of the cargo conveyance case is: the cargo transportation boxes are unloaded in sequence according to the third, second and first sequences, when the third cargo transportation box 7 is unloaded, the locking bolt of the fourth locking mechanism 110 at the rear part of the third cargo transportation box 7 is firstly loosened, the third cargo transportation box 7 is pulled backwards to the position of the cabin door of the cargo hold 3, and then the cargo container is pulled from the cabin door to the lifting platform. And then the third locking mechanism 19 is removed in sequence, the second cargo transportation box 6 is pulled backwards, and the second locking mechanism 18 is removed after the second cargo transportation box 6 is unloaded, so that the first cargo transportation box 5 can be moved out of the cargo hold 3.
According to the embodiment of the application, universal balls at the bottom of the cargo transportation box, guide rollers at two sides of the cargo transportation box and a cargo transportation box locking device are fixed on guide rails of the cargo hold 3 through the design of the universal fixing clamping seat assembly 16; the whole cargo handling device takes the 3 guide rails of the cargo hold of the unmanned aerial vehicle as a carrying platform, so that the cargo handling device has the characteristics of easy disassembly and assembly and easy maintenance, and zero damage to the unmanned aerial vehicle structure is realized.
The device provided by the embodiment of the application can be suitable for various unmanned freight aircrafts 2, is not limited to the application of a certain aircraft, and can be used for all unmanned aircrafts with four guide rails in a cargo hold 3 or similar structural characteristics.
The device enables a common cargo transportation box to easily slide in the cargo hold 3 by arranging a plurality of rows of universal balls on the guide rail of the cargo hold 3, thereby reducing the requirement on the cargo transportation box; the guide rollers are arranged on the two sides of the moving track of the cargo transport box, so that the moving track of the cargo transport box in the cargo hold 3 is controlled, the cargo transport box can be accurately pushed to the preset position, and the loading and unloading operation process of cargoes is facilitated; the bullet butt joint devices designed at the front part and the rear part of the cargo transport box are used for fixing the cargo transport box, so that the manual operation links are greatly simplified; the locking mechanism is designed into a bullet shape in appearance, so that the docking device has certain deviation rectifying capability, the requirement on the matching precision is reduced, and the docking matching with the docking device can be easily realized by combining the combined action of the lateral displacement of the cargo transportation box limited by the guide rollers distributed on the two sides of the cargo transportation box.
In a word, the cargo handling device provided by the application can be designed on the basis of the cargo hold structure of the original machine, so that the original machine structure is not damaged, and the structural safety of the original machine is ensured; the structural design characteristics of the original machine are fully utilized, the cargo handling device is convenient to install and disassemble, the modification process of the prototype machine is convenient to simplify, and the maintenance, the inspection and the replacement of each part of the cargo handling device are convenient; the cargo handling process is simple and convenient, the handling and the fixing of the cargo fully consider the operation space of personnel, and the fixing operation of the cargo transportation box is convenient; the movement of the cargo transportation box is carried out on the universal balls, so that the manual operation burden is fully lightened.
The embodiment of the present application may further provide an unmanned cargo aircraft, as shown in fig. 18, where the unmanned cargo aircraft 2 includes a cargo hold 3, and a cargo handling device 1 described above is disposed on a bottom plate of the cargo hold 3.
The unmanned cargo aircraft 2 may be an unmanned aircraft provided with various guide rails in advance, or may be provided with corresponding guide rails in the cargo hold 3 of an unmanned aircraft without guide rails according to needs, and then the unmanned cargo aircraft 2 may be built by connecting various mechanisms to the corresponding guide rails.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
From the above description of embodiments, it will be apparent to those skilled in the art that the present application may be implemented in software plus a necessary general hardware platform. Based on such understanding, the technical solution of the present application may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a storage medium, such as a ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method described in the embodiments or some parts of the embodiments of the present application.
In this specification, each embodiment is described in a progressive manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment mainly describes differences from other embodiments. In particular, for a system or system embodiment, since it is substantially similar to a method embodiment, the description is relatively simple, with reference to the description of the method embodiment being made in part. The systems and system embodiments described above are merely illustrative, wherein the elements illustrated as separate elements may or may not be physically separate, and the elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
The foregoing description is only of the preferred embodiments of the present invention and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.
Claims (6)
1. A cargo handling device, comprising:
the guide rail unit is arranged on the aircraft cargo compartment floor and comprises a first guide rail, a second guide rail and a plurality of third guide rails positioned between the first guide rail and the second guide rail; the respective axial directions of the first guide rail, the second guide rail and the third guide rail extend along the course of the aircraft;
A plurality of side edge guide roller mechanisms are respectively arranged on the first guide rail and the second guide rail, each side edge guide roller mechanism comprises a guide roller, and the rotation direction of each guide roller is the same as the axial direction of each of the first guide rail and the second guide rail;
the third guide rail is provided with a plurality of universal ball mechanisms; the universal ball mechanism comprises universal balls;
The side guide roller mechanism is connected with the first guide rail and the second guide rail through the fixed clamping seat assembly, and the universal ball mechanism is connected with the third guide rail through the fixed clamping seat assembly; the surface of the guide roller is used for abutting against the side surface of the cargo transportation box so as to limit the transverse displacement of the cargo transportation box, and the universal balls contained in the universal ball mechanisms are all used for abutting against the bottom surface of the cargo transportation box so as to form a supporting plane of the cargo transportation box;
The locking unit at least comprises a first locking mechanism, and the first locking mechanism is arranged on the third guide rail through the fixed clamping seat assembly; the first locking mechanism comprises a bullet type male butt joint which is used for being connected with a bullet type female butt joint on the cargo transportation box;
The second locking mechanism is arranged on the third guide rail through the fixed clamping seat assembly; the first locking mechanism is positioned in front of the second locking mechanism in the course direction of the aircraft;
The second locking mechanism comprises a second bullet head supporting seat and two bullet type male butt joints, wherein the two bullet type male butt joints are connected with the second bullet head supporting seat and are symmetrically distributed on the front side and the rear side of the second bullet head supporting seat;
The third locking mechanism is arranged on the third guide rail through the fixed clamping seat assembly; the second locking mechanism is positioned in front of the third locking mechanism in the course direction of the aircraft;
the third locking mechanism comprises a third bullet head supporting seat, two bullet type male butt joints and thin universal balls, wherein the two bullet type male butt joints are connected with the second bullet head supporting seat and are symmetrically distributed on the front side and the rear side of the second bullet head supporting seat, and the thin universal balls are connected with the third bullet head supporting seat and are positioned behind the third bullet head supporting seat;
the fourth guide rails are arranged behind the third guide rails and opposite to the cabin door of the aircraft, and the fourth guide rails are connected with the universal ball mechanism and/or the fourth locking mechanism through the fixing clamping seat assembly; the third locking mechanism is positioned in front of the fourth locking mechanism in the course direction of the aircraft;
The fourth locking mechanism comprises a supporting bottom plate, a fourth bullet head supporting seat, a bullet type male-to-joint and a thin type universal ball, wherein the bullet type male-to-joint and the thin type universal ball are connected with the fourth bullet head supporting seat and are positioned in front of the fourth bullet head supporting seat.
2. The cargo handling device of claim 1, wherein the first rail, the second rail, and the third rail each have the same U-shaped structure in cross section; the fixed clamping seat assembly comprises a fixed seat supporting rod, a cargo hold guide rail fixed buckle and a spring; the bottom of fixing base bracing piece is provided with T type portion, T type portion be used for with U type structure joint links to each other.
3. The cargo handling device of claim 2 wherein the side guide roller mechanism includes a guide roller support and a connecting bolt, the guide rollers including two, both of the guide rollers being hinged to the guide roller support; the connecting bolts sequentially penetrate through the guide roller support, the springs and the cargo compartment guide rails to be fixedly and in snap fit with the threaded holes of the fixing seat support rods.
4. The cargo handling device of claim 2, wherein the universal ball mechanism comprises a ball seat, the universal ball is cooperatively connected with the ball seat, the ball seat comprises a connecting screw, and the connecting screw sequentially penetrates through the spring and the cargo compartment guide rail to be fixedly and in a snap fit manner connected to the threaded hole of the fixing seat support bar.
5. The cargo handling device of claim 1, wherein the first locking mechanism comprises a first bullet head support base to which two sets of the fixed cartridge assemblies are connected.
6. An unmanned cargo aircraft, characterized in that it comprises a cargo hold, the cargo hold floor being provided with a cargo handling device according to any one of claims 1 to 5.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210854979.3A CN115107988B (en) | 2022-07-19 | 2022-07-19 | Cargo handling device and unmanned freight aircraft |
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| CN202210854979.3A CN115107988B (en) | 2022-07-19 | 2022-07-19 | Cargo handling device and unmanned freight aircraft |
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| CN103803311A (en) * | 2014-01-23 | 2014-05-21 | 燕山大学 | Rapid cargo loading and unloading track device and loading and unloading method |
| CN109941421A (en) * | 2019-03-20 | 2019-06-28 | 庆安集团有限公司 | A kind of side rails system applied in aircraft hold |
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| GB8508840D0 (en) * | 1985-04-04 | 1985-05-09 | Short Brothers Ltd | Cargo handling system for aircraft |
| RU2248308C2 (en) * | 2002-07-08 | 2005-03-20 | Государственный научно-производственный ракетно-космический центр "ЦСКБ-Прогресс" (ГНПРКЦ "ЦСКБ-Прогресс") | Method of transportation and loading of large-sized cargoes into aircraft cabin and unloading from cabin and system for realization of this method |
| EP2815969B1 (en) * | 2013-06-17 | 2018-08-08 | Airbus Operations GmbH | Cargo handling system |
| DE102018108803B4 (en) * | 2018-03-07 | 2022-04-07 | Telair International Gmbh | Lateral guide, lateral guide group, cargo deck, airplane |
| US11167848B2 (en) * | 2018-03-23 | 2021-11-09 | The Boeing Company | Unmanned aerial vehicle with enhanced cargo storage |
| DE102020118478B4 (en) * | 2020-07-14 | 2024-02-08 | Lufthansa Technik Aktiengesellschaft | Cargo bridge for airliner and airliner |
| CN212981825U (en) * | 2020-08-12 | 2021-04-16 | 百利威仓储服务（北京）有限公司 | Automatic loading and unloading platform |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103803311A (en) * | 2014-01-23 | 2014-05-21 | 燕山大学 | Rapid cargo loading and unloading track device and loading and unloading method |
| CN109941421A (en) * | 2019-03-20 | 2019-06-28 | 庆安集团有限公司 | A kind of side rails system applied in aircraft hold |
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