CN111332455A - Cargo loading method and system for ultra-narrow cabin of branch cargo aircraft - Google Patents
Cargo loading method and system for ultra-narrow cabin of branch cargo aircraft Download PDFInfo
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
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Abstract
The invention relates to a cargo loading method for a branch cargo aircraft ultra-narrow cabin, which comprises a branch cargo aircraft, wherein the front end of the branch cargo aircraft is provided with a cockpit, the rear part of the branch cargo aircraft is provided with an empennage, the outside of the branch cargo aircraft is provided with wings, the body of the branch cargo aircraft is provided with a cabin door, and the inside of the branch cargo aircraft is provided with the ultra-narrow cabin and is characterized in that a front loading area and a rear loading area are arranged in the cabin, and the gravity center of the branch cargo aircraft in a horizontal state is positioned in the rear loading area; the cabin door comprises a front cabin door and a rear cabin door, wherein the front cabin door is arranged at the front half part of the front loading area, and the rear cabin door is arranged at the rear half part of the rear loading area; the front part of the front loading area is provided with a front frame plate, the rear part of the rear loading area is provided with a rear frame plate, and a preset distance is arranged between the gravity center of the branch cargo aircraft and the front frame plate. By using the method and the system provided by the invention to load the goods, the goods can be efficiently loaded in the state of the balance of the gravity center in the whole process, so that the method and the system can be widely applied to the technical field of branch line air cargo transportation.
Description
Technical Field
The invention relates to the technical field of cargo transportation, in particular to a cargo loading method and a cargo loading system for a branch cargo aircraft ultra-narrow cabin, and more particularly relates to a loading technology for a branch cargo aircraft for efficient logistics transportation.
Background
With the rapid development of electronic commerce and logistics industry worldwide, the size of the logistics service has been gradually increased, and meanwhile, the logistics service has been developed from the demand of single goods delivery to the demand of diversified classified delivery, timely delivery and quality delivery, which puts requirements on multi-level air transportation on the aspect of air logistics. In 2018, the first global annual report focusing on the development of the unmanned aerial vehicle industry in the logistics field, namely the annual report of the development of the world logistics unmanned aerial vehicle industry, was published in Jingdong. The reporting system combs the technical level, policy environment, market demand and other core elements of the world logistics unmanned aerial vehicle industry development, particularly performs key analysis on the latest development strategy of major world logistics unmanned aerial vehicle enterprises such as amazon, UPS and Google, and simultaneously combines the development demand of the national logistics industry to firstly provide a future 'trunk-branch-tail end' three-level intelligent aviation logistics system.
Because the concept of the multi-stage air transportation logistics system is just proposed, the standard definition of the multi-stage air transportation logistics system of the trunk line, the branch line and the tail end is not provided at present. According to the existing civil aviation system standard, the trunk-level cargo aircraft are wide-body cargo aircraft and narrow-body cargo aircraft of the current civil aviation transportation system, the range of the aircraft is generally hundreds of kilometers to thousands of kilometers, and the single cargo capacity is dozens of tons to hundreds of tons. The tail-end freight aircraft is the multi-rotor unmanned aerial vehicle for current cargo carrying, the range of the multi-rotor unmanned aerial vehicle is generally within 30 kilometers, and the single cargo carrying capacity is within 30 kilograms. The transport distance and the cargo capacity of the branch-level freight aircraft are between a 'trunk line' and a 'tail end' aviation logistics system, different models of aircraft can be researched and developed according to specific freight requirements, the branch-level freight aircraft is suitable for aviation logistics transportation from a logistics hub node to a logistics center node in a provincial region, the voyage of the branch-level freight aircraft is generally 500 kilometers, and the single cargo capacity is about 1-5 tons.
At present, a branch-level cargo plane belongs to a blank interval in a three-level aviation logistics system, is still in a starting stage in a global scope, and with the vigorous demand of the aviation logistics market in China and the gradual refinement of the industry, the research and development of China in the field are faster. In 10 months in 2017, a branch-level freight unmanned aerial vehicle AT200 developed by the department of engineering thermophysics research of Chinese academy of sciences and the Langxing unmanned aerial vehicle company as a general unit and the units of aviation industry 618, China Electricity 54, aerospace 773, West industry and the like is combined to complete first flight. The effective load of the machine reaches 1.5 tons, the total length is 11.84 meters, the wingspan is 12.80 meters, the height is 4.04 meters, and the volume of the cargo hold is 10 cubic meters. The unmanned aerial vehicle can efficiently finish point-to-point freight branch line transportation service, and is a first-money tonnage level branch line level freight unmanned aerial vehicle in the world.
At present, a branch-line-level cargo unmanned aerial vehicle in research and development mainly performs flight performance test flight of an air vehicle, and does not perform flight tests under cargo loading conditions, and the series of unmanned aerial vehicles still need to perform a series of flight tests of different cargo loading capacity, multiple complex flight environments, different take-off and landing conditions and the like to reach a test flight certification standard, so that the unmanned aerial vehicle can be really served in the aviation logistics industry of China. For the existing branch-line-level manned machine, the unmanned aerial vehicle is mainly used in the fields of manned, surveying, aerial photography, agriculture and forestry plant protection and the like, rarely relates to a cargo loading process, and adopts a manual loading mode due to the fact that the cargo loading capacity is small even if the cargo loading process exists. Therefore, no matter whether the branch-level freight unmanned aerial vehicle is under development or the mature branch-level unmanned aerial vehicle is adopted, the efficient cargo loading scheme applied to the logistics industry is not available at present.
With the diversified development of the aviation logistics demand, the gradual improvement of a three-level intelligent aviation logistics system of 'trunk-branch-tail' gradually makes the 'branch' aviation logistics transportation relatively blank become a hot spot of technical and market research. The problem of cargo loading efficiency inevitably becomes one of core technical indexes influencing the development of the branch cargo aircraft, and the improvement of the indexes can not only improve the operation efficiency of the branch cargo aircraft in an airport working interval in an aviation logistics system, but also improve the cargo transport professional capacity of the airport. At present, the technology of an industrial grade branch line freight airplane applied to the logistics industry in the civil field is still in the research and development starting stage, the matched efficient cargo loading technology is in the germination stage, and the rapid research and development of the innovative technology is urgently needed.
For the existing trunk-level cargo aircraft, the cabin structures are both wide and narrow, and an aviation container (ULD for short) is adopted to complete efficient loading of cargoes in the cargo loading process, so that the technology is mature. However, the cabin structure of the branch-line cargo plane is much smaller, and belongs to an ultra-narrow cabin structure, and the change rule of the gravity center of the cabin structure in the loading process is obviously different from that of the trunk-line cargo plane. In order to ensure the high efficiency, the safety and the operability of the branch cargo aircraft in the cargo loading process, the cargo loading unit device suitable for the ultra-narrow cabin of the branch cargo aircraft and the corresponding cargo high-efficiency loading method are provided by combining the fuselage structure of the branch cargo aircraft and considering the actual weight loading and the dynamic change of the gravity center of the aircraft in the cargo loading process.
However, no technical report for solving the above problems has been found in the prior art.
Disclosure of Invention
In order to solve the technical problems, the technical scheme provided by the invention is as follows:
a cargo loading method for a branch cargo aircraft ultra-narrow cabin divides cargo to be loaded into four container units with standard weight, and then sequentially places each container unit at a designated position of the cabin, so that the branch cargo aircraft can always keep a balanced state without gravity center movement during and after loading the cargo,
s1, dividing the goods to be loaded into four container units, namely a container unit I, a container unit II, a container unit III and a container unit IV, wherein the four container units are in a fixed counterweight relationship;
s2, dividing a cabin of the branch cargo aircraft into four loading areas, namely a front loading area I, a front loading area II, a rear loading area I and a rear loading area II, wherein the four loading areas are sequentially arranged from front to back, and the gravity center balance range of the branch cargo aircraft is located between the front loading area II and the rear loading area I;
s3, firstly, placing the second assembly unit at the position of the front loading area, then placing the first assembly unit at the position of the front loading area, then placing the third assembly unit at the position of the rear loading area, and finally placing the fourth assembly unit at the position of the rear loading area, thus completing the whole loading process.
Further, in step S2, the first front loading area and the second front loading area are equal in size, and the first rear loading area and the second rear loading area are equal in size.
Furthermore, the first preposed loading area and the second preposed loading area are both positioned on one side of the gravity center position of the branch cargo aircraft in an unloaded state, the first postposed loading area and the second postposed loading area are positioned on the other side of the gravity center position of the branch cargo aircraft in the unloaded state, and the first postposed loading area penetrates through the gravity center.
The invention also provides a technical scheme that:
a loading system using the cargo loading method of the branch cargo aircraft ultra-narrow cabin comprises a branch cargo aircraft, wherein a cockpit is arranged at the front end of the branch cargo aircraft, an empennage is arranged at the rear part of the branch cargo aircraft, wings are arranged outside the branch cargo aircraft, a cabin door is arranged on the body of the branch cargo aircraft, the ultra-narrow cabin is arranged inside the branch cargo aircraft, a front loading area and a rear loading area are arranged in the cabin, and the center of gravity of the branch cargo aircraft in a horizontal state is positioned in the rear loading area;
the cabin door comprises a front cabin door and a rear cabin door, wherein the front cabin door is arranged at the front half part of the front loading area, and the rear cabin door is arranged at the rear half part of the rear loading area;
the front part of the front loading area is provided with a front frame plate, the rear part of the rear loading area is provided with a rear frame plate, and a preset distance is reserved between the gravity center of the branch cargo aircraft and the front frame plate.
Further, the heights of the front cabin door and the rear cabin door are equal to the cabin height of the branch cargo aircraft, the width of the front cabin door is 1/2 of the width of the front loading area, and the width of the rear cabin door is 1/2 of the width of the rear loading area.
Further, the front loading area comprises a first front loading area and a second front loading area which are equal in size, and the rear loading area comprises a first rear loading area and a second rear loading area which are equal in size; and the front loading area I, the front loading area II, the rear loading area I and the rear loading area II are sequentially arranged from front to back.
Furthermore, the front cabin door is positioned on the corresponding fuselage of the front loading area I, and the rear cabin door is positioned on the corresponding fuselage of the rear loading area II.
Further, the cabin outer part extends to a top plate of the body of the branch cargo aircraft in the upward direction, and the cabin outer part extends to a bottom plate of the body of the branch cargo aircraft in the downward direction; and a cabin top plate is arranged in the cabin and at the top, and a cabin bottom plate is arranged in the cabin and at the bottom.
Furthermore, a cargo transmission system and a ground locking system are arranged on the bottom plate of the engine room and are used for the transmission transportation and the fixed locking of the container unit II and the container unit III on the bottom plate of the engine room, and the fixed locking of the container unit I and the container unit IV.
Further, the transmission system comprises a plurality of rollers fixedly arranged on a bottom plate of the cabin, the rollers are connected through a belt, and the belt is driven by a motor; the locking system comprises a plurality of clamping hooks for clamping the four packaging units; the container unit is provided with a groove clamped with the clamping hook.
After the structure and the loading method are adopted, the invention has the following advantages:
(1) the loading method provided by the invention is particularly suitable for a branch line logistics transportation system in a three-level aviation logistics system of trunk line-branch line-tail end, can greatly improve the loading efficiency of the branch line cargo aircraft, and improves the freight professional ability of an airport;
(2) the technical method carries out the grouping type standardized design of the cargo loading units according to the integral structure of the ultra-narrow cabin of the branch cargo aircraft, thereby not only ensuring the maximum utilization of the loading space of the ultra-narrow cabin, but also realizing the intensive standardized loading of various random bulk cargos;
(3) according to the technical scheme, the cargo loading unit is designed in a 'pair mode' with completely matched size according to the structural size and the opening mode of the cabin door of the ultra-narrow cabin and the internal structural size of the cabin, so that the loading unit can be loaded quickly and efficiently, and meanwhile, the internal loading space of the ultra-narrow cabin can be utilized to the maximum extent;
(4) according to the technical method, the cargo loading area in the ultra-narrow cabin is designed into a front loading area and a rear loading area according to the wing arrangement mode and the gravity center balance range of the branch cargo aircraft, the structure and the counterweight requirements of each loading unit are matched and designed at the same time, each loading unit strictly carries out counterweight and sequential loading, the aircraft gravity centers of the whole process of the branch cargo aircraft before, during and after the loading can be ensured to be in the balance range, and the safety and reliability of the whole process of the cargo loading of the branch cargo aircraft are ensured.
Drawings
FIG. 1 is a schematic illustration of a load compartment section within a cabin of a branch cargo aircraft according to an embodiment of the present invention;
fig. 2 is a schematic illustration of the relationship of the counterweight according to the embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
With reference to the attached drawings 1-2, the invention divides the cargo loading area of the branch cargo aircraft into a front loading area and a rear loading area, simultaneously further allocates each loading area into two loading units, and gradually loads the cargo by 4 different loading units in the whole loading process, thereby ensuring the fast and efficient loading of the branch cargo aircraft, and simultaneously ensuring the balance of the gravity centers of the aircrafts in the whole process before, during and after the loading of the branch cargo aircraft, and ensuring the safe loading.
In order to realize the smooth loading of the goods in the cabin of the ultra-narrow branch goods machine, the invention provides a loading method, thereby utilizing the internal space of the cabin to the maximum extent and realizing the purpose that the branch goods machine is not unbalanced before loading, during loading and after loading. The specific loading steps are as follows:
s1, dividing the goods to be loaded into four container units, namely a container unit I, a container unit II, a container unit III and a container unit IV, wherein the four container units are in a fixed counterweight relationship;
s2, dividing a cabin of the branch cargo aircraft into four loading areas, namely a front loading area I, a front loading area II, a rear loading area I and a rear loading area II, wherein the four loading areas are sequentially arranged from front to back, and the gravity center balance range of the branch cargo aircraft is located between the front loading area II and the rear loading area I;
s3, first placing the second assembly unit at the two positions of the front loading area, then placing the first assembly unit at the one position of the front loading area, then placing the third assembly unit at the one position of the rear loading area, and finally placing the fourth assembly unit at the two positions of the rear loading area, thereby completing the whole loading process.
Wherein:
in step S2, the first front loading area and the second front loading area are equal in size, and the first rear loading area and the second rear loading area are equal in size.
The front loading area I and the front loading area II are both positioned on one side of the gravity center position of the branch cargo machine in an unloaded state, the rear loading area I and the rear loading area II are positioned on the other side of the gravity center position of the branch cargo machine in the unloaded state, and the rear loading area I penetrates through the gravity center.
In the invention, in order to achieve the purpose that the airplane cannot be unbalanced, the cargo is divided into a first container unit, a second container unit, a third container unit and a fourth container unit according to the relationship of a fixed counterweight, and the method specifically comprises the following steps:
with reference to fig. 2, according to the cargo loading balance principle, assuming that the distances from the first container unit to the fourth container unit to the original gravity centers of the branch cargo aircraft are S1, S2, S3 and S4, respectively, the weights of the four container units are M1, M2, M3 and M4, respectively, the self weight of the branch cargo aircraft is N, when the four container units are installed in different loading areas, the gravity centers of the branch cargo aircraft will be shifted, and assuming that the gravity centers of the branch cargo aircraft after shifting are L1 ', L2', L3 'and L4', respectively, it can be concluded that the counterweight relationship is:
m1 (S1-L1 ') + M2 (S2-L1 ') -M3 (S3+ L1 ') + M4 (S4+ L1 ') + N × L1 ', or M1 (S1+ L2 ') + M2 (S2+ L2 ') + N2 ' + M3 (S3-L2 ') + M4 (S4-L2 '), and L1 ' ≦ L1, L2 '. L2-L, where L is the position of the aircraft ' S own center of gravity point.
On the basis, in order to solve the problem of instability in the process of loading goods onto the branch cargo aircraft in the prior art, the invention provides a fixed loading sequence, namely the branch cargo aircraft is arranged according to the sequence of a front loading area II, a front loading area I, a rear loading area I and a rear loading area II, so that the problem of unbalance of the branch cargo aircraft in the loading process can be solved.
The invention also provides a system for efficiently loading cargoes, which is realized by the method, and the system is an improvement on the conventional branch cargo aircraft, so that the loading process is completed by matching with the method provided by the invention, and the cargoes are finally and smoothly transported.
The system provided by the invention comprises a branch cargo aircraft, wherein a cockpit is arranged at the front end of the branch cargo aircraft, a tail wing is arranged at the rear part of the branch cargo aircraft, wings 1 are arranged outside the branch cargo aircraft, a cabin door is arranged on the body of the branch cargo aircraft, a super-narrow cabin 2 is arranged inside the branch cargo aircraft, a front loading area 3 and a rear loading area 4 are arranged in the cabin 2, and the center of gravity of the branch cargo aircraft in a horizontal state is positioned in the rear loading area 4;
the cabin door comprises a front cabin door 5 and a rear cabin door 6, wherein the front cabin door 5 is arranged on the front half part of the front loading area 3, and the rear cabin door 6 is arranged on the rear half part of the rear loading area 4;
the front part of the front loading area 3 is provided with a front frame plate 7, the rear part of the rear loading area 4 is provided with a rear frame plate 8, and a preset distance L is arranged between the gravity center 11 of the branch cargo aircraft and the front frame plate 7.
The invention is designed aiming at the improved ultra-narrow cabin 2 of the branch cargo machine, and the invention adopts a mode of dividing the cabin 2 and forming a plurality of loading areas, in particular a front loading area 3 and a rear loading area 4, wherein the gravity center balance range of the branch cargo machine is positioned between the front loading area 3 and the rear loading area 4. Furthermore, the invention adds a front door 5 and a rear door 6 on the basis of the prior art, wherein the front door 5 is positioned in the front half part of the front loading area 3, and the rear door 6 is positioned in the rear half part of the rear loading area 4. On the basis of achieving the design, the system can achieve balanced loading by matching with the method provided by the invention, and the balance of the branch cargo aircraft is ensured.
The height of the front cabin door 5 and the rear cabin door 6 is equal to the height of the cabin 2 of the branch cargo aircraft, the width of the front cabin door 5 is 1/2 of the width of the front loading area 3, and the width of the rear cabin door 6 is 1/2 of the width of the rear loading area 4.
The front loading area 3 comprises a front loading area I3-1 and a front loading area II 3-2 which are equal in size, and the rear loading area 4 comprises a rear loading area I4-1 and a rear loading area II 4-2 which are equal in size.
The front loading area I3-1 and the front loading area II 3-2 are arranged in parallel in the horizontal direction, the rear loading area I4-1 and the rear loading area II 4-2 are arranged in parallel in the horizontal direction, and the front loading area I3-1, the front loading area II 3-2, the rear loading area I4-1 and the rear loading area II 4-2 are sequentially arranged from front to back.
The front hatch 5 is positioned on the fuselage corresponding to the front loading area I3-1, and the rear hatch 6 is positioned on the fuselage corresponding to the rear loading area II 4-2.
The outside of the cabin 2 extends in an upward direction to a fuselage roof 9 of the branch cargo aircraft, and the outside of the cabin 2 extends in a downward direction to a fuselage floor 10 of the branch cargo aircraft; a cabin top plate 2-1 is arranged at the top position in the cabin 2, and a cabin bottom plate 2-2 is arranged at the bottom of the loading space of the cabin 2.
The cabin bottom plate 2-2 is provided with a cargo transmission system and a ground locking system which are used for the transmission transportation and the fixed locking of the container unit II and the container unit III on the cabin bottom plate 2-2 and the fixed locking of the container unit I and the container unit IV.
The transmission system comprises a plurality of rollers fixedly arranged at the bottom of the bottom plate 2-2 of the engine room, the rollers are connected through a belt, and the belt is driven by a motor; the locking system comprises a plurality of clamping hooks for clamping the four container units, and grooves clamped with the clamping hooks are formed in the container units.
By applying the cargo transmission system in the cabin and the ground locking system which are widely used on the existing cargo aircraft to the ultra-narrow body branch cargo aircraft provided by the invention, the cargo transportation system is used for transporting the four container units to the specified positions after the four container units are transported into the cabin 2, and then the ground locking system is used for fixing the container units, thereby completing the whole transportation process. The specific operation process is as follows: inside 2 with freight to cabin through machines such as fork truck earlier, then, start 2 inside motors in cabin, drive the belt and rotate to the collection dress unit motion that the drive is located the belt, and remove appointed loading area, will collect the dress unit through the pothook at last and fix respectively, prevent to take place the displacement of great degree in the transportation. The roller and the hook are common technologies in the existing cargo plane, and are not described in detail herein.
In summary, the invention improves the structure of the branch cargo aircraft with the ultra-narrow cabin in the emerging technology, particularly, the cargo accommodating space inside the cabin is divided, the cabin and the main body structure of the aircraft body are changed, and the corresponding loading method is used for loading the cargo with fixed counterweight relationship according to a certain sequence, so that the balance of the branch cargo aircraft before, during and after loading is ensured.
Claims (10)
1. A cargo loading method of a branch cargo aircraft ultra-narrow cabin divides cargo to be loaded into four container units with standard weight, and then sequentially places each container unit at a designated position of the cabin, thereby enabling the branch cargo aircraft to keep a balanced state without gravity center shift during and after loading the cargo,
s1, dividing the goods to be loaded into four container units, namely a container unit I, a container unit II, a container unit III and a container unit IV, wherein the four container units are in a fixed counterweight relationship;
s2, dividing a cabin of the branch cargo aircraft into four loading areas, namely a front loading area I, a front loading area II, a rear loading area I and a rear loading area II, wherein the four loading areas are sequentially arranged from front to back, and the gravity center balance range of the branch cargo aircraft is located between the front loading area II and the rear loading area I;
s3, firstly, placing the second assembly unit at the position of the front loading area, then placing the first assembly unit at the position of the front loading area, then placing the third assembly unit at the position of the rear loading area, and finally placing the fourth assembly unit at the position of the rear loading area, thus completing the whole loading process.
2. The method as claimed in claim 1, wherein in step S2, the first front loading area and the second front loading area are equal in size, and the first rear loading area and the second rear loading area are equal in size.
3. The method as claimed in claim 2, wherein the first forward loading area and the second forward loading area are located on one side of the center of gravity of the branch cargo aircraft in the unloaded state, the first rear loading area and the second rear loading area are located on the other side of the center of gravity of the branch cargo aircraft in the unloaded state, and the first rear loading area passes through the center of gravity.
4. The loading system for the cargo loading method by using the ultra-narrow cabin of the branch cargo aircraft according to claim 1, comprising the branch cargo aircraft, wherein the front end of the branch cargo aircraft is provided with a cockpit, the rear part of the branch cargo aircraft is provided with a tail wing, the outside of the branch cargo aircraft is provided with a wing, the body of the branch cargo aircraft is provided with a cabin door, and the inside of the branch cargo aircraft is provided with the ultra-narrow cabin, and the loading system is characterized in that a front loading area and a rear loading area are arranged in the cabin, and the center of gravity of the branch cargo aircraft in a horizontal state is positioned in the rear loading area;
the cabin door comprises a front cabin door and a rear cabin door, wherein the front cabin door is arranged at the front half part of the front loading area, and the rear cabin door is arranged at the rear half part of the rear loading area;
the front part of the front loading area is provided with a front frame plate, the rear part of the rear loading area is provided with a rear frame plate, and a preset distance is reserved between the gravity center of the branch cargo aircraft and the front frame plate.
5. The cargo loading system of ultra-narrow cabin of branch cargo aircraft according to claim 4, wherein the height of the front and rear doors is equal to the cabin height of the branch cargo aircraft, the width of the front door is 1/2 of the width of the front loading area, and the width of the rear door is 1/2 of the width of the rear loading area.
6. The cargo loading system of the ultra-narrow cabin of the branch cargo aircraft according to claim 5, wherein the front loading area comprises a first front loading area and a second front loading area which are equal in size, the rear loading area comprises a first rear loading area and a second rear loading area which are equal in size, and the first front loading area, the second front loading area, the first rear loading area and the second rear loading area are sequentially arranged from front to rear.
7. The cargo loading system of a spur cargo aircraft ultra-narrow body cabin according to claim 6, wherein the front hatch door is located on the fuselage corresponding to the first forward loading area and the rear hatch door is located on the fuselage corresponding to the second rearward loading area.
8. The cargo loading system of a spur cargo aircraft ultra-narrow hull cabin according to claim 4, wherein the cabin extends outwardly in an upward direction to a fuselage roof of the spur cargo aircraft, the cabin extends outwardly in a downward direction to a fuselage floor of the spur cargo aircraft; and a cabin top plate is arranged in the cabin and at the top, and a cabin bottom plate is arranged in the cabin and at the bottom.
9. The cargo loading system of the ultra-narrow cabin of the branch cargo aircraft as claimed in claim 8, wherein the cargo conveying system and the ground locking system are arranged on the bottom plate of the cabin, and are used for the transmission transportation and the fixed locking of the second container unit and the third container unit on the bottom plate of the cabin, and the fixed locking of the first container unit and the fourth container unit.
10. The cargo loading system of the ultra-narrow cabin of the branch cargo aircraft as claimed in claim 9, wherein the transmission system comprises a plurality of rollers fixed on the bottom plate of the cabin, the rollers are connected through a belt, and the belt is driven by a motor; the locking system comprises a plurality of clamping hooks for clamping the four packaging units; the container unit is provided with a groove clamped with the clamping hook.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113492982A (en) * | 2021-09-07 | 2021-10-12 | 中国民航大学 | Method and device for trim loading of passenger aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113492982A (en) * | 2021-09-07 | 2021-10-12 | 中国民航大学 | Method and device for trim loading of passenger aircraft |
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