AIRCRAFT FOR TRANSPORTING CARGO AND PASSENGERS, CARGO CONTAINER, METHOD FOR LOADING AN AIRCRAFT AND METHOD FOR RECONFIGURING AN AIRCRAFT

Abstract

An aircraft for the transport of cargo and/or passengers, comprising a fuselage extending in longitudinal direction and having an upper deck, in particular main deck, and a lower deck separated from each other by a floor, wherein the fuselage comprises a barrel section with a cross-sectional profile for accommodating cargo and/or passengers, wherein the cross-sectional profile is essentially formed by several, in particular four, circular arc sections, which have radii (R1, R2, R3) with centers (M1, M2, M3′, M3″) differing from one another, so that the cross-sectional profile is designed in such a way that cargo items with different size dimensions, in particular cargo containers with different height and width dimensions, can be accommodated in the upper deck and the lower deck.

Claims

1. An aircraft for transporting cargo and/or passengers, comprising a fuselage which extends in the longitudinal direction and has an upper deck, in particular main deck, and a lower deck, which are separated from each other by a floor, wherein the fuselage has a barrel section with a cross-sectional profile for accommodating cargo items and/or passengers, wherein the cross-sectional profile is essentially formed by a plurality of, in particular four, circular arc sections, which have radii (R1, R2, R3) with centers (M1, M2, M3′, M3″) differing from one another, so that the cross-sectional profile is designed in such a way that cargo items with different sizes, in particular cargo containers with different height and width dimensions, can be accommodated in the upper deck and the lower deck.

2. The aircraft according to claim 1, wherein the cross-sectional profile of the fuselage is oval in shape, wherein the fuselage has an outer maximum width of 490 cm to 510 cm in the y-direction and an outer maximum height of 480 cm to 500 cm in the z-direction and/or an outer maximum height of 440 cm to 450 cm in the z-direction.

3. The aircraft according to claim 1, wherein the fuselage has a first clear width of 460 cm to 480 cm in the y-direction and a second clear width of 450 cm to 480 cm in the z-direction.

4. The aircraft according to claim 1, wherein the lower deck is formed continuously in the longitudinal direction of the fuselage, wherein the lower deck has a forward cargo space, an aft cargo space and, in the region of a wing box, a through-loading space which connects the forward cargo space and the aft cargo space.

5. The aircraft according to claim 4, wherein the through-loading space in the region of the wing box or the landing gear is designed in such a way that, when the lower deck is loaded, cargo containers can be loaded through from the aircraft nose and/or from the aircraft tail.

6. The aircraft according to claim 4, wherein the through-loading space has a minimum width in the y-direction of the aircraft of 240 cm to 270 cm and/or of 150 cm to 180 cm.

7. The aircraft according to claim 1, wherein at least one first loading door for loading and unloading the upper deck and/or at least one second loading door for loading and unloading the lower deck are arranged in the barrel section, wherein preferably the first loading door is arranged in a nose region and the second loading door is arranged in a tail region or the second loading door is arranged in the nose region and the first loading door is arranged in the tail region on opposite sides of the aircraft.

8. The aircraft according to claim 4, wherein: a plurality of plates and/or C-shaped beams extending transversely to the longitudinal direction of the aircraft, in particular as part of the wing box, which are spaced apart from one another in the longitudinal direction of the aircraft and are connected to a fuselage structure, in particular frames, of the aircraft.

9. The aircraft according to claim 8, wherein the plates each have at least one passage opening formed in the longitudinal direction of the aircraft, through which the through-loading space extends.

10. The aircraft according to claim 8, wherein the wing box has a plurality of crossbeams (extending in the y-direction), which are arranged above the plates in the z-direction and interact with the plates to stiffen the fuselage structure.

11. The aircraft according to claim 10, wherein wing box comprises a plurality of longitudinal beams extending in the longitudinal direction of the aircraft and connecting the crossbeams to each other.

12. The aircraft according to claim 1, wherein the wings of the aircraft are designed to be angled in the z-direction, wherein the wings have a larger angle of inclination (SW1) relative to a reference axis (RA1) extending in the y-direction in each case starting from the fuselage then towards a free wing tip.

13. The aircraft according to claim 1, wherein the fuselage has a fuselage structure extension on both sides in the y-direction to accommodate the landing gear, which forms a free space into which the respective landing gear can be folded at least in sections.

14. The aircraft according to claim 4, wherein the landing gears each have at least one axis of rotation about which the landing gears can be pivoted for retraction and extension, wherein the two axes of rotation have a distance between 930 cm and 970 cm in the y-direction and the through-loading space has a clear width between 240 cm and 270 cm or the two axes of rotation have a distance between 750 cm and 800 cm in the y-direction and the through-loading space has a clear width between 300 cm and 340 cm.

15. A cargo container for transporting cargo items in an aircraft, comprising a trapezoidal base body having a base area and a ceiling area arranged opposite each other, wherein the base area comprises at least one fastening element, which can be connected to a fastening device of the aircraft, and wherein the base area has at least one first longitudinal side of at least 240 cm, in particular 244 cm, and the ceiling area has at least one second longitudinal side of at least 315 cm, in particular 317 cm, wherein the cargo container has an overall height of at least 99 cm to a maximum of 130 cm, in particular 114.5 cm.

16. A method, in particular for loading an aircraft in accordance with claim 1, wherein the lower deck of the aircraft has a forward cargo space, an aft cargo space and, in the region of a wing box, a through-loading space which connects the forward cargo space and the aft cargo space, and the lower deck has a forward loading opening which can be closed by a loading door, wherein during a loading operation at least one cargo item, in particular a cargo container, is introduced through the forward loading opening into the forward cargo space and is then loaded through the through-loading space into the aft cargo space.

17. A method for reconfiguring an aircraft, in particular an aircraft according to claim 1, in which a preferably foldable module having a floor and at least two side walls preferably hinged to the floor is introduced into the aircraft via a loading door and mounted on the lower deck, preferably in the front area of the aircraft, in order to provide passenger seats in the lower deck, wherein the module has pre-assembled seats and/or holding devices for mounting seats preferably during the introduction.

18. An aircraft for transporting cargo and/or passengers, having a fuselage which extends in a longitudinal direction and has an upper deck, in particular main deck, and a lower deck, which are separated from one another by a floor, wherein the fuselage has a barrel section with a cross-sectional profile for accommodating cargo items and/or passengers, wherein the aircraft is designed as a low-wing or mid-wing configuration, wherein the lower deck has a forward cargo space, an aft cargo space and, in the region of a wing box, a through-loading space which connects the forward cargo space and the aft cargo space, wherein the through-loading space is designed in the region of the wing box or of the landing gear in such a way that, when the lower deck is loaded, cargo containers can be loaded through from the aircraft nose and/or from the aircraft tail.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0156] The invention is explained in more detail below with reference to the attached drawings. The embodiments shown are examples of how the aircraft and cargo container according to the invention can be designed. They show as follows:

[0157] FIG. 1 shows a cross-section of a barrel section of the fuselage of an aircraft according to a preferred exemplary embodiment according to the invention in a cargo configuration with a first loading variant;

[0158] FIG. 2 shows a cross-section of the barrel section of the fuselage as shown in FIG. 1 in the cargo configuration with a second loading variant;

[0159] FIG. 3 shows a cross-section of the barrel section of the fuselage as shown in FIG. 1 in a cargo configuration with a third loading variant;

[0160] FIG. 4 shows a cross-section of the barrel section of the fuselage as shown in FIG. 1 in a passenger configuration with a first transport variant;

[0161] FIG. 5 shows a cross-section of the barrel section of the fuselage as shown in FIG. 1 in a passenger configuration with a second transport variant;

[0162] FIG. 6 shows a cross-section through the aircraft according to FIG. 1 in the area of the wing box;

[0163] FIG. 7 shows a cross-section through the aircraft according to FIG. 1 in the area of the landing gear;

[0164] FIG. 8 shows a perspective bottom view of the aircraft according to FIG. 1;

[0165] FIG. 9 shows a perspective top view of the aircraft according to FIG. 1;

[0166] FIG. 10 shows a longitudinal section through the aircraft according to FIG. 1, with the lower deck loaded with cargo items;

[0167] FIG. 11 shows a longitudinal section through the aircraft according to FIG. 1, wherein several mobile additional tanks are arranged in the lower deck in the area of the wing box;

[0168] FIG. 12 shows a perspective view of a cargo container according to an exemplary embodiment according to the invention;

[0169] FIG. 13 shows a front view of the cargo container according to FIG. 12;

[0170] FIG. 14 shows a cross-section of a barrel section of the fuselage of an aircraft according to another exemplary embodiment according to the invention;

[0171] FIG. 15 shows a cross-section of a barrel section of the fuselage of an aircraft according to another exemplary embodiment according to the invention;

[0172] FIG. 16 shows several different loading/equipment configurations of the upper deck of the aircraft as shown in FIG. 1, FIG. 14 and FIG. 15;

[0173] FIG. 17 shows several different loading configurations of the lower deck of the aircraft according to FIG. 1 and FIG. 14;

[0174] FIG. 18 shows a section of a side view of an aircraft according to another exemplary embodiment according to the invention;

[0175] FIG. 19a-d show cross-sections through the aircraft as shown in FIG. 18 at different positions along the longitudinal direction of the aircraft;

[0176] FIG. 20 shows a perspective view of a longitudinal section through the aircraft according to FIG. 18 in the area of the wing box;

[0177] FIG. 21 shows a front view of the aircraft according to FIG. 18;

[0178] FIG. 22 shows a cross-section through the aircraft according to FIG. 18 in the area of the landing gears, wherein these are shown in the folded-out state;

[0179] FIG. 23 shows a cross-section through the aircraft according to FIG. 18 in the area of the landing gears, wherein these are shown in the folded-in state;

[0180] FIG. 24 shows a perspective view of an aircraft according to another exemplary embodiment of an invention;

[0181] FIG. 25 shows a cross-section through the aircraft according to FIG. 24 in the area of the landing gears, wherein these are shown in the folded-in and folded-out state;

[0182] FIG. 26 shows a schematic top view of a barrel section of the aircraft according to FIG. 24 in the area of the wing box and landing gear;

[0183] FIG. 27 shows a side view of the aircraft according to FIG. 24 in a first deck configuration;

[0184] FIG. 28 shows a side view of the aircraft according to FIG. 24 in a second deck configuration;

[0185] FIG. 29 shows a side view of the aircraft according to FIG. 24 in a third deck configuration;

[0186] FIG. 30 shows a side view of the aircraft according to FIG. 24 in the first deck configuration as shown in FIG. 27, wherein at least the outer fuselage skin and the configuration of the upper deck are hidden;

[0187] FIG. 31 shows a side view of the aircraft according to FIG. 24 in the second deck configuration according to FIG. 28 and in the third deck configuration according to FIG. 29, wherein at least the outer fuselage skin and the upper deck configuration are hidden; and

[0188] FIG. 32 shows a cross-section of a barrel section of the fuselage of an aircraft according to another exemplary embodiment according to the invention.

DETAILED DESCRIPTION

[0189] In the following description, the same reference numerals are used for identical and similarly acting parts.

[0190] Usually, a Cartesian coordinate system is used to provide individual directional information within an aircraft. The x-axis extends from the tail to the nose of the aircraft, the y-axis is transverse to the x-axis and lies essentially in the plane defined by the wings. The z-axis is perpendicular to the x- and y-axis (see FIG. 1 and FIG. 9). The longitudinal direction corresponds to the x-direction of the aircraft and is parallel to the x-axis. The y-direction of the aircraft is parallel to the y-axis and the z-direction is parallel to the z-axis.

[0191] FIGS. 1 to 5 show a cross-section of an aircraft 10 according to an exemplary embodiment according to the invention. The aircraft 10 is designed as a low-wing aircraft. Specifically, FIGS. 1 to 5 show a cross-section through a barrel section 15 of a fuselage 11 of aircraft 10, wherein the barrel section 15 extends longitudinally and comprises a part of the upper deck 12 and a part of the lower deck 13. The upper deck 12 may also be referred to as the main deck and the lower deck 13 as the cargo deck. The two decks 12, 13 are separated by a floor 14.

[0192] The floor 14 has an upper edge 41 and a lower edge 42, with the upper edge 41 facing the upper deck 12 and the lower edge 42 facing the lower deck 13. The following height measurements concerning the upper deck 12 are measured from the upper edge 41 of the floor 14 in z-direction upwards. Furthermore, the following height measurements concerning the lower deck 13 are measured from the lower edge 42 of the floor 14 in z-direction downwards. The upper edge 41 and the lower edge 42 each form the maximum extension of the floor 14 in z-direction.

[0193] Floor 14 is spaced from the y-axis of aircraft 10 in negative z-direction. Preferably, the upper edge 41 of floor 14 has a distance A1′ of at least 40 cm to a maximum of 55 cm (16 inches to 22 inches). As shown in FIG. 1, the distance A1′ of the upper edge 41 of floor 14 from the y-axis of the aircraft 10 is approximately 47 cm (approx. 18.5 inches).

[0194] The barrel section 15 has a cross-sectional profile 16, which is formed by several circular arc sections 17, which have radii R1, R2, R3 with centers M1, M2, M3′, M3″ that differ from each other. The circular arc sections 17 each comprise an inner radius R1′, R2′, R3′ and an outer radius R1″, R2″, R3″, which will be discussed in more detail later. The cross-sectional profile 16 is designed in such a way that cargo items 18 with different size dimensions, in particular cargo containers 18 with different height and width dimensions, can be accommodated in the upper deck 12 and the lower deck 13.

[0195] According to FIGS. 1 to 5, the cross-sectional profile 16 is designed oval in shape. The barrel section 15 has an outer maximum width 19 of 497 cm (196 inches) in the y-direction and an outer maximum height 21 of 485 cm (191 inches) in the z-direction. In addition, barrel section 15 has a first clear width 22, especially an inner maximum width, of 472.5 cm (186 inches) in the y-direction and a second clear width 23, especially an inner maximum height, of 460 cm (181 inches) in the z-direction.

[0196] In other words, the barrel section 15 in the z-direction has an outer maximum height of 485 cm (191 inches) and an inner maximum height, especially second clear width 23, of 460 cm (181 inches). In addition, barrel section 15 in the y-direction has an outer maximum width of 497 cm (196 inches) and an inner maximum width, especially first clear width 22, of 472.5 cm (186 inches).

[0197] Preferably, the fuselage 11 or the barrel section 15 has a wall thickness of the fuselage outer skin 43 of approx. 13 cm (5 inches). The outer maximum width 19 and the outer maximum height 21 may have a dimensional tolerance of +/−5%, in particular a dimensional tolerance of less than 2%, in particular a dimensional tolerance of +/−0.5%. The two clear widths 22, 23 can have a dimensional tolerance of +/−5%, in particular a dimensional tolerance of less than +2%, in particular a dimensional tolerance of +/−1% or +/−0.7%. In other words, the outer maximum width 19 and the outer maximum height 21 can vary in the range of +/−5%, preferably in the range of +/−0.5%. The two clear widths 22, 23 can vary in the range of +/−5%, preferably in the range of +/−1% or +/−0.7%. This dimensional tolerance also applies to the wall thickness of the fuselage outer skin 43.

[0198] The upper deck 12 may have a clear width 49, in particular clear height, in the barrel section 15 starting from the upper edge 41 of floor 14, in the z-direction of aircraft 10 of at least 254 cm to a maximum of 287 cm (100 inches to 113 inches), in particular of at least 264 cm to 273 cm (104 inches to 107 inches). Specifically, the upper deck 12 in the barrel section 15 in the z-direction has a clear width 49 of 268.6 cm (105.75 inches). Alternatively, it is conceivable that the upper deck 12 in barrel section 15 has a clear width 49 of 284.75 cm (112.5 inches) in the z-direction.

[0199] The cross-sectional profile 16 of barrel section 15 may be designed in such a way that the upper deck 12 has a clear width 49, in particular height, in the z-direction of at least 280 cm to a maximum of 300 cm (approx. 110 inches to approx. 118 inches), in particular of at least 285 cm to 290 cm (approx. 112 inches to approx. 114 inches). Preferably, the upper deck 12 in the barrel section 15 in z-direction may have a clear width 49 of 288 cm (approx. 113.5 inches).

[0200] The lower deck 13 may have a clear width 51, in particular clear height, in the barrel section 15 in the z-direction of at least 140 cm (55 inches), in particular at least 127 cm (50 inches). Specifically, lower deck 13 in barrel section 15 has a clear width 51 of at least 124.5 cm (49 inches) in the z-direction. The clear width 51 of the lower deck 13 is essentially measured from a floor structure 47, which has a roller conveyor system 48 for loading the lower deck 13 and securing the cargo items, to the lower edge 42 of the floor 14. The floor structure 47 will be discussed in more detail later. The clear widths 49, 51 of the two decks 12, 13 can be essentially constant throughout the barrel section 15.

[0201] The lower deck 13 can have a minimum usable width in the barrel section 15 in y-direction of approx. 317.5 cm (approx. 125 inches). Preferably, the lower deck 13 in barrel section 15 has a width in y-direction of approx. 328 cm (approx. 129 inches).

[0202] As described above, the cross-sectional profile 16 has several circular arc sections 17, wherein the cross-sectional profile 16 is formed by a total of four circular arc sections 17′, 17″, 17′″. A first circular arc section 17′ partially spans the upper deck 12, a second circular arc section 17″ delimits the lower deck 13 and two third circular arc sections 17′″ are arranged between the first and the second circular arc section 17′, 17″. The third circular arc sections 17′″ are arranged opposite each other with respect to the z-axis of the aircraft 10. The two third circular arc sections 17′″ are adjacent in each case to the first circular arc section 17′ and the second circular arc section 17″. In other words, the third circular arc section 17′″ connects the first circular arc section 17′ and the second circular arc section 17″ to each other. The four circular arc sections 17 are arranged in such a way that the cross-sectional profile 16 is formed symmetrically. Specifically, the cross-sectional profile 16 is mirror-symmetrical in relation to the z-axis.

[0203] As can be seen in FIG. 1, the first circular arc section 17′ has an inner radius R1′ and an outer radius R1″. The inner radius R1′ is 239 cm (94 inches) and the outer radius R1″ is 252 cm (99 inches). The center M1 of the two radii R1 is located on the z-axis of the aircraft 10 and is spaced from the floor 14 in a positive z-direction, especially upward. The center M1 of the two radii R1 is formed by the intersection of the z- and y-axis of aircraft 10. In other words, the center M1 is exactly at the intersection of the z- and y-axis of the aircraft 10. Preferably, the center M1 of the two radii R1 has a distance A1″ of at least 40 cm to a maximum of 55 cm (16 inches to 22 inches) from the upper edge 41 of the floor 14. According to FIG. 1, the distance A1″ of the center M1 of the two radii R1 from the upper edge 41 of the floor 14 is approximately 47 cm (approx. 18.5 inches).

[0204] Furthermore FIG. 1 shows that the second circular arc section 17″ also has an inner radius R2′ and an outer radius R2″. The inner radius R2′ is 236 cm (93 inches) and the outer radius R2″ is 249 cm (98 inches). The center M2 of the two radii R2 is on the z-axis of the aircraft 10. The center M2 of the second circular arc section 17″ is spaced from the center M1 of the first circular arc section 17′ in the positive z-direction. In other words, the center M2 of the second circular arc section 17″ is offset upward in the z-direction away from the center M1 of the first circular arc section 17′. The center M2 of the second circular arc section 17″ is thus spaced from the y-axis in positive z-direction, in particular upwards. Preferably, the center M2 of the second circular arc section 17″ is at a distance A2 of at least 5 cm to a maximum of 25 cm (2 inches to 10 inches) from the center M1 of the first circular arc section 17′. According to FIG. 1, the distance A2 of the center M2 of the second circular arc section 17″ from the center M1 of the first circular arc section 17′ is approximately 15 cm (6 inches).

[0205] Furthermore, the center M2 of the second circular arc section 17″ is spaced from the upper edge 41 of the floor 14 in positive z-direction. Preferably, the center M2 of the second circular arc section 17″ from the upper edge 41 of the base 14 is at a distance A3 of at least 50 cm to a maximum of 70 cm (20 inches to 28 inches). According to FIG. 1, the distance A3 of the center M2 of the second circular arc section 17″ from the upper edge 41 of the base 14 is approx. 62 cm (24.5 inches).

[0206] The centers M3′, M3″ of the third circular arc sections 17′″ can be at the same height in z-direction as the center M2 of the second circular arc section 17″. The centers M3′, M3″ of the third circular arc sections 17′″ have a distance of approx. 58.5 cm (23 inches) in z-direction from the upper edge 41 of the floor 14. The centers M3′, M3″ of the third circular arc sections 17′″ are offset from the z-axis in the opposite y-direction. The centers M3′, M3″ are arranged opposite each other on the z-axis, with the centers M3′, M3″ having the same distance to the z-axis. It is also conceivable that the centers M3′, M3″ are at different distances from the z-axis. For the sake of clarity, only the two radii R3 and the center M3′ of one of the two third circular arc sections 17′″ are shown in FIG. 1. However, the following description applies to both third circular arc sections 17′″ and their radii R3 and centers M3′, M3″. The center M3 has a distance A4 to the z-axis in the y-direction, which is preferably at least 15 cm to a maximum of 35 cm (6 inches to 14 inches). According to FIG. 1, the distance A4 of the center M3′ to the z-axis is approx. 22.5 cm (approx. 9 inches).

[0207] Furthermore, FIG. 1 shows that the third arc section 17′″ also has an inner radius R3′ and an outer radius R3″. The two third circular arc sections 17′″ are identical or identical in design. The inner radius R3′ is 213 cm (84 inches) and the outer radius R3″ is 226 cm (89 inches).

[0208] The inner radius R1′ of the first circular arc section 17′ is smaller than the inner radius R2′ of the second circular arc section 17″. Furthermore, the outer radius R1″ of the first circular arc section 17′ is smaller than the outer radius R2″ of the second circular arc section 17″. The inner radii R3′ of the two third circular arc sections 17′″ are smaller than the inner radii R1′, R2′ of the first and second circular arc sections 17′, 17″. Furthermore, the outer radii R3″ of the two third circular arc sections 17′″ are smaller than the outer radii R1″, R2″ of the first and second circular arc sections 17′, 17″.

[0209] In general, the dimensions of the radii R1, R2, R3 are not limited to the aforementioned dimensions. Other dimensions of radii R1, R2, R3 not mentioned above are also possible.

[0210] According to FIGS. 1 to 5, the third circular arc sections 17′″ are designed in such a way that they have a height of 80 cm to 120 cm (32 inches to 47 inches) in the z-direction, in particular a height of approx. 104 cm to approx. 109 cm (40 inches to 443 inches). The third circular arc sections 17′″ have a concrete height of approx. 104 cm (41 inches). The height is measured starting from a height position of the centers M3′, M3″ of the third circular arc sections 17′″ in z-direction. In the third circular arc sections 17′″ at least one row of windows of aircraft 10 can be provided. Starting from the upper edge 41 of the floor 14, the third circular arc sections 17′″ in z-direction can have a height of approx. 140 cm to approx. 170 cm (approx. 55 inches to approx. 67 inches). Specifically, the third circular arc sections 17′″ in the z-direction, starting from the upper edge 41 of the floor 14, have a height of approx. 162 cm (approx. 64 inches). This enables the arrangement of the window row in the third circular arc sections 17′″, since conventional windows have a height of approx. 45 cm to approx. 48 cm (18 inches to 19 inches).

[0211] As shown in FIG. 1, aircraft 10 is configured for cargo transport, wherein a first loading variant of the upper and lower decks 12, 13 is shown. With the first loading variant, an aircraft engine 44, especially of the own aircraft type, can be introduced into the upper deck 12. Furthermore, two first cargo containers 18′, especially AAJ containers, having the basic dimensions 223.5 cm by 317.5 cm (88 inches×125 inches) and a height H1 of 243.8 cm (96 inches), can be arranged next to each other in the y-direction on upper deck 12. Alternatively or additionally, at least one second cargo container 18″, in particular an AMA container, having the basic dimensions 243.8 cm by 317.5 cm (96 inches×125 inches) and a height H1 of 243.8 cm (96 inches), can be introduced into the upper deck 12.

[0212] In addition, trapezoidal cargo containers 45 having the basic dimensions of 153.4 cm×156.2 cm (60.4 inches×61.5 inches) and/or 153.4 cm×243.8 cm (60.4 inches×96 inches) and each with a height H2 of approx. 114 cm to approx. 127 cm (approx. 45 inches to approx. 50 inches) can be introduced into the lower deck 13 for the first loading variant. Furthermore, at least one pallet 46, in particular PMC, having the dimensions 243.8 cm×317.5 cm (96 inches×125 inches) and a height H2 of approx. 114 cm to approx. 127 cm (approx. 45 inches to approx. 50 inches), can be introduced lengthwise into the lower deck 13.

[0213] The lower deck 13 has a floor structure 47 with a roller conveyor system 48 to accommodate and secure the cargo items 18 or cargo containers 18′, 18″, 45 and/or pallets 46.

[0214] According to FIG. 2, aircraft 10 is configured for cargo transport, wherein a second loading variant of upper deck 12 is shown. The loading of the lower deck 13 corresponds to that of the first loading variant as shown in FIG. 1, whereas the second loading variant is equipped with a receiving device 52 for cargo, especially luggage, in the ceiling area 53 of the upper deck 12. The shortest distance A5 between the receiving device 52 and the upper edge 41 of deck 14 can be between 160 cm and 180 cm (63 inches and 71 inches).

[0215] Specifically, the shortest distance A5 between the receiving device 52 and the upper edge 41 of the base 14 is approximately 175 cm (approx. 69 inches). Therefore, cargo containers and/or pallets with a height of 163 cm (64 inches) can be arranged in the upper deck 12 below the receiving device 52. Specifically, two third cargo containers 18′″, in particular LAJ containers, having the basic dimensions 223.5 cm by 317.5 cm (88 inches×125 inches) and a height of 163 cm (64 inches), and/or two pallets, in particular PAG pallets, having the basic dimensions 223.5 cm by 317.5 cm (88 inches×125 inches) and a height of 163 cm (64 inches), and/or two pallets, especially HCU-6E pallets, having the basic dimensions 223.5 cm by 274.3 cm (88 inches×108 inches) and a height of 163 cm (64 inches), can be arranged next to each other in the y-direction.

[0216] According to FIG. 3, aircraft 10 is shown with a third loading variant of the upper deck 12. The loading of the lower deck 13 corresponds again to the first loading variant as shown in FIG. 1. In the upper deck 12, the receiving device 52 for cargo items, as described in FIG. 2, is provided in the ceiling area 53, wherein the receiving device 52 has a central area 54, especially in the area of the z-axis of the aircraft 10. Between the central area 54 and the upper edge 41 of the floor 14, there is a distance A6, which can be between 203 cm and 229 cm (80 inches and 90 inches). According to FIG. 3, the distance A6 is approximately 217 cm (approx. 86 inches).

[0217] According to FIG. 4, aircraft 10 is configured for passenger transport. A first transport variant of upper deck 12 is shown. The loading of the lower deck 13 again corresponds to the first loading variant as shown in FIG. 1. In the upper deck 12, the receiving device 52 for cargo items is provided in the ceiling area 53 as described in FIG. 2. The upper deck 12 has seven rows of seats 34. The rows of seats 34 extend in the x-direction of the aircraft 10. The rows of seats 34 are provided as 2-3-2 configuration. Specifically, two rows of seats 34 are arranged laterally outside in opposite y-direction. These form the window rows. The three remaining seat rows 34 are arranged between the lateral seat rows 34. These form the center seat rows. An aisle 35 is provided between each of the side rows 34 and the center rows 34, extending in the x-direction of the aircraft 10. The aisles 35 can each have a width in the y-direction between the adjacent rows of seats of 38 cm to 65 cm (15 inches to 25.6 inches). Specifically, the aisles 35 have a width in the y-direction between the adjacent rows of seats 34 of approximately 52 cm (20.5 inches).

[0218] According to FIG. 5, aircraft 10 is configured for passenger transport, wherein a second transport variant of lower deck 13 is shown. The seating on the upper deck 12 corresponds to the first transport variant as shown in FIG. 4. According to FIG. 5, a common area 55 for the aircraft personnel is provided on lower deck 13. The common area 55 has two first areas 56 for sitting and two second areas 57 for sleeping or reclining for the flight crew. Between the two areas 56 for sitting a walking area 58 is provided. The first area 56, the second area 57 and the walking area 58 are essentially the same width in y-direction. The width of each of the areas 56, 57, 58 in y-direction can vary from a minimum of 56 cm to a maximum of 81 cm (22 inches to 32 inches). Specifically, the areas 56, 57, 58 in y-direction each have a width of approx. 68.4 cm (approx. 26.9 inches). With respect to the first areas 56, the second areas 57 are raised. The lower deck 13 preferably has a first clear width 59 in z-direction between the first areas 56 and the lower edge 42 of the floor 14 of at least 125 cm to a maximum of 150 cm (49 inches to 59 inches), in particular of at least 140 cm to a maximum of 145 cm (55 inches to 57 inches). According to FIG. 5, the first clear width 59 is approx. 143 cm (approx. 56 inches).

[0219] In addition, the lower deck 13 preferably has a second clear width 61 in the z-direction of at least 75 cm to a maximum of 90 cm (29.5 inches to 35.5 inches), in particular from at least 81 cm to a maximum of 85 cm (32 inches to 34 inches), preferably between the second area 57 and the lower edge 42 of the floor 14. According to FIG. 5, the second clear width 61 is approximately 83 cm (33 inches).

[0220] The lower deck 13 preferably has a third clear width 62, preferably in the z-direction between walking area 58 and the lower edge 42 of floor 14, of at least 145 cm to a maximum of 165 cm (57 inches to 65 inches), in particular of at least 150 cm to 160 cm (59 inches to 63 inches). According to FIG. 5, the third clear width 62 is approximately 156 cm (approx. 61.5 inches).

[0221] The aircraft 10 according to FIGS. 6 to 11 has a forward cargo space 24 in the lower deck 13, an aft cargo space 25 and a through-loading space 26 in the area of a wing box 27 and a landing gear 28. The through-loading space 26 connects the forward cargo space 24 and the aft cargo space 25 to each other. In other words, the lower deck 13 is designed to be continuous in the x-direction so that in the area of a wing box 27 and/or in the area of a landing gear 28 at least one mobile additional tank 63 and/or at least one cargo container 18 can be accommodated. The lower deck 13 is loaded with cargo containers 18 and/or mobile additional tanks 63 as shown in FIGS. 6, 7, 10 and 11.

[0222] FIG. 6 shows a cross-section through the aircraft 10 in the area of landing gear 28, with landing gear 28 in a retracted state. In the area of the landing gear 28, the through-loading space 26 can have a minimum width 32 in the y-direction of the aircraft 10 of at least 240 cm to a maximum of 270 cm (94.5 inches to 106.5 inches), in particular of at least 250 cm to a maximum of 260 cm (98.5 inches to 102.5 inches). Specifically, the through-loading space 26 has a minimum usable width of 32′ in the y-direction of 244 cm (96 inches). In the y-direction, landing gear 28 has a distance A7 between the two axes of rotation of approximately 956.6 cm (approx. 376 inches).

[0223] According to FIG. 7, a cross-section through the aircraft 10 is shown in the area of the wing box 27. There are no permanently installed central tanks for fuel in wing box 27. The permanently embedded fuel tanks 64 of the aircraft 10 are located laterally next to the through-loading space 26. In the area of the wing box 27, the through-loading space 26 has a width which corresponds to the width of the forward and/or aft cargo space 24, 25. The width of the through-loading space 26 in the area of the wing box 27 is larger than the width of the through-loading space 26 in the area of the landing gear 28. The through-loading space 26 can have a minimum usable width in y-direction of approximately 317.5 cm (approx. 125 inches) in the area of the wing box 27. Preferably, the through-loading space 26 in the area of the wing box 27 has a width in y-direction of approximately 328 cm (approx. 129 inches).

[0224] Cargo containers 18 and/or mobile additional tanks 63 with a width of approximately 244 cm (96 inches) can be arranged in the through-loading space 26 as shown in FIGS. 6 and 7 or moved through the through-loading space 26. Preferably, only cuboidal cargo containers with a width of approximately 244 cm (96 inches) and a height of approximately 114.5 cm (45 inches) can be placed and/or moved through the through-loading space 26 in the area of the landing gear 28.

[0225] The through-loading space 26 has a through-loading height 33 of at least 140 cm (55 inches), in particular of at least 130 cm (51 inches). Preferably, the through-loading space 26 has a through-loading height 33 of at least 124.5 cm (49 inches). The through-loading height 26 corresponds to the clear width 51, in particular height, in z-direction of the lower deck 13. The through-loading height 33 can be essentially constant.

[0226] As shown in FIGS. 8 and 9, aircraft 10 has one loading door 36 for loading and unloading the upper deck 12 and two loading doors 37′, 37″ for loading and unloading the lower deck 13. As shown in FIG. 8, one of the two loading doors 37″ is located forward and one of the two loading doors 37″ is located aft. The forward loading door 37″ closes a loading opening 39, especially the front one, through which the forward loading space 24 is accessible for loading and unloading. The aft loading door 37′ closes an aft loading opening 67, especially at the rear, through which the aft loading space 25 is accessible for loading and unloading. The forward loading opening 39 is larger than the aft loading opening 67, while the forward loading opening 39 has a passage size with a minimum width of approximately 332.5 cm (131 inches) and a minimum height of 124.5 cm (49 inches) or 137 cm (54 inches). The aft loading opening 67 has a passage size with a minimum width of 168 cm (66 inches) and a minimum height of 124.5 cm (49 inches) or 137 cm (54 inches).

[0227] The loading door 36 as shown in FIG. 9 is located at the rear and closes an aft loading opening 67′ for loading and unloading the upper deck 12. The loading opening of the upper deck 12 can have a passage size with a minimum clear width of 370 cm to 380 cm (approx. 145.5 inches to approx. 149.5 inches). More specifically, the loading opening of the upper deck 12 can have a passage size with a minimum clear width of 373 cm to 376 cm (approx. 147 inches to approx. 148 inches). The loading doors 36, 37′, 37″ are each located in a barrel section 15.

[0228] When loading the lower deck 13, the cargo items 18 and/or cargo containers 45 can be introduced through the forward loading opening 39 into the forward cargo space 24 and then loaded through the through-loading space 26 into the aft cargo space 25. It is also possible that when loading the lower deck 13, the cargo items 18 and/or cargo containers 45 are loaded through the aft loading opening 67 into the aft cargo space 25 and then through the through-loading space 26 into the forward cargo space 24.

[0229] As can be seen in FIG. 9, the aircraft 10 also has four doors 65 for passengers on each of the long sides. The doors are located outside the wings in the longitudinal direction of the aircraft 10. This enables a safe evacuation in case of an emergency.

[0230] FIGS. 10 and 11 show two different loading variants for the lower deck 13, wherein in FIG. 10 only cargo items 18 or cargo containers 18 are arranged in the forward and aft cargo spaces 24, 25 and in the through-loading space 26 and in FIG. 11 three mobile additional tanks 63 are arranged in the through-loading space 26. According to FIG. 10, a cargo item 18 is arranged in the area of the landing gear 28 of aircraft 10, which has a maximum width in y-direction of 244 cm (96 inches). In the two other cargo spaces 24, 25, cargo containers 45 are arranged, which are wider in y-direction than the cargo items 18.

[0231] Furthermore, FIGS. 10 and 11 show in the area of the aircraft nose 29 and the aircraft tail 31 a further receiving device 66, especially a galley ring, to accommodate cargo items, especially kitchen utensils and/or luggage. The further receiving device 66 is ring-shaped in fuselage 11 and extends through the two decks 12, 13.

[0232] According to FIGS. 12 and 13, a cargo container 70 according to the invention is shown, which can be placed in the lower deck 13 of the aircraft 10 according to the invention. The cargo container 70 has a trapezoidal base body 71 with a base area 72 and a ceiling area 73, which are arranged opposite each other. The base area 72 comprises a fastening element 74, which can be connected to a fastening device of the aircraft 10.

[0233] The base area 72 forms a bottom end in the z-direction and the ceiling area 73 forms a top end in the z-direction of the cargo container 70. The base area 72 and the ceiling area 73 each comprise two longitudinal sides 75, 76, wherein the base area 72 has two first longitudinal sides 75 of at least 240 cm (95 inches), in particular 243.8 cm (96 inches). The ceiling area 73 has two second longitudinal sides 76 of at least 315 cm (approx. 124 inches), in particular 317.5 cm (125 inches). The cargo container 70 has a total height 77 of at least 99 cm to a maximum of 130 cm (39.5 inches to 51 inches). The cargo container 70 can have a total height 77 of at least 102 cm to a maximum of 127 cm (40 inches to 50 inches). According to FIGS. 12 and 13, the cargo container 70 has a total height 77 of 114.5 cm (45 inches). Alternatively, the cargo container 70 can also have a maximum overall height 77 of 127 cm (50 inches). In addition, the cargo container 70 preferably has a depth of at least 119 cm to a maximum of 317.5 cm (approx. 47 inches to 125 inches). As shown in FIGS. 12 and 13, the cargo container 70 has a preferred depth of 153.5 cm (60.4 inches).

[0234] The cargo container 70 has two broad sides 78, which include an inclined section 79 towards the base area 72. The inclined section 79 has a height H3 in z-direction from 43 cm to 56 cm (17 inches to 22 inches), in particular from 47 cm to 51 cm (18.5 inches to 20 inches). Specifically, the inclined section 79 has a height H3 in the z-direction of approximately 50 cm (approx. 19.6 inches).

[0235] FIG. 14 shows a cross-sectional profile 16 of an aircraft 10 according to another exemplary embodiment according to the invention. Here the aircraft 10 is designed as a low-wing aircraft. In contrast to the cross-sectional profile 16 in FIG. 1, the cross-sectional profile 16 in FIG. 14 is designed circularly. In other words, the cross-sectional profile 16 according to FIG. 14 is formed by a single circle 91, 91′. The circle 91, 91′ has a center M4 from which the radius R4, R4′ of the circle extends. The barrel section 15, which includes the above-mentioned cross-sectional profile 16, has a wall thickness as described in FIG. 1. The barrel section 15, as shown in FIG. 14, has an outer maximum width of 497 cm (196 inches) in the y-direction and an outer maximum height 21 of 497 cm (196 inches) in the z-direction. Further dimensions of the cross-sectional profile 16 as well as loading configurations of the upper deck 12 and the lower deck 13 are shown in FIG. 14. The dimensions shown above the dimensions in the square brackets are given in millimeters. The dimensions shown in the square brackets below correspond to the inch value of the dimensions above in millimeters.

[0236] FIG. 15 shows a cross-sectional profile 16 of an aircraft 10 according to another exemplary embodiment according to the invention. Here the aircraft 10 is designed as a low-wing aircraft. The cross-sectional profile 16 according to FIG. 15 is designed oval in shape. The barrel section 15, which includes the cross-sectional profile 16 as mentioned above, has a wall thickness as described in FIG. 1. In contrast to the cross-sectional profile 16 according to FIG. 1, the first and the second circular arc sections 17′, 17″ of the cross-sectional profile 16 according to FIG. 15 can each have a straight section in the area of the z-axis of the aircraft 10.

[0237] The barrel section 15 as shown in FIG. 15 has an outer maximum width of 501.5 cm (approx. 197.5 inches) in the y-direction and an outer maximum height 21 of 447.9 cm (approx. 176.5 inches) in the z-direction. Further dimensions of the cross-sectional profile 16 and loading configurations of the upper deck 12 and the lower deck 13 are shown in FIG. 15. The dimensions shown above the dimensions in the square brackets are given in millimeters. The dimensions shown in the square brackets below correspond to the inch value of the dimensions above in millimeters.

[0238] FIGS. 16 and 17 show several different loading/equipment configurations of the upper and lower decks 12, 13 of the aircraft according to FIG. 1, FIG. 14 and FIG. 15. Specifically, FIG. 16 shows several loading variants for aircraft 10 according to FIG. 1, FIG. 14 and FIG. 15, which are described below starting from the left. For a first loading variant V1, the aircraft 10 can accommodate six PGA pallets 81 with the basic dimensions 243.8×605.7 cm (96×238.5 inches) or six PRA pallets 81′ with the basic dimensions 243.8×497.8 cm (96×196 inches) one behind the other on the upper deck 12 in longitudinal direction of the aircraft.

[0239] With a second loading variant V2, the aircraft 10 can each accommodate, for example, twenty-five HCU-6E pallets 82 with the basic dimensions 223.5×274.3 cm (88×108 inches) and two HCU-12E pallets 82′ with the basic dimensions of 137.1×223.5 cm (54×88 inches) on the upper deck 12.

[0240] With a third loading variant V3, the aircraft 10 can each accommodate, for example, twenty-three AAC containers 83 with the dimensions 223.5×317.5×208.2 cm (88×125×82 inches) on the upper deck 12. The AAC containers 83 have a double contour. In this loading arrangement, the last AAC container 83 is loaded lengthwise in the longitudinal direction of the aircraft.

[0241] With a fourth loading variant V4, the aircraft 10 can each accommodate, for example, twelve AMA containers 84 with the basic dimensions 243.8×317.5×243.8 cm (96×125×96 inches) on the upper deck 12. It is conceivable that the aircraft 10 can each accommodate, for example, eleven AMA containers 84 with the dimensions 243.8×317.5×243.8 cm (96×125×96 inches) and one AAJ container 85 with the dimensions 223.5×317.5×243.8 cm (88×125×96 inches) or one PAG pallet 86 with the basic dimensions 223.5×317.5 cm (88×125 inches) on the upper deck 12. Alternatively, it is conceivable that the aircraft 10 can each accommodate, for example, twelve PMC pallets 88 with the basic dimensions 243.8×317.5 cm (96×125 inches) on the upper deck 12.

[0242] With a fifth loading variant V5, the aircraft 10 can each accommodate, for example, twenty-three AAJ containers 85 with the dimensions 223.5×317.5×243.8 cm (88×125×96 inches) or twenty-three PAG pallets 86 with the basic dimensions 223.5×317.5 cm (88×125 inches) on the upper deck 12. In addition, the aircraft 10 can each accommodate, for example, at least one aircraft engine 44 or at least one vehicle 87 on at least one PRA pallet 81′ or at least one PGA pallet 81 on the upper deck 12.

[0243] In a first configuration variant AV1, the aircraft 10 can have, for example, seven rows of seats, several sanitary areas and two receiving devices 66, especially galley rings, on the upper deck 12. The receiving devices 66 are described in FIGS. 10 and 11. In addition, the aircraft 10 may have a receiving device 52 for cargo items, especially baggage, in the ceiling area of the upper deck 12.

[0244] With a second configuration variant AV2, the aircraft 10 can accommodate, for example, seven PAG pallets 86 with basic dimensions of 223.5×317.5 (88×125) and a height of 243.8 cm (96 inches) on the upper deck 12 in addition to passenger seating. This configuration variant corresponds to a combination configuration of aircraft 10, which combines a cargo configuration and a passenger configuration of aircraft 10.

[0245] FIG. 17 shows several loading variants for the aircraft 10 according to FIG. 1 and FIG. 14, which are described in the following starting from the left. For a first loading variant B1, the aircraft 10 can accommodate, for example, several PMC pallets 88 with the basic dimensions 243.8×317.5 cm (96×125 inches) loaded one behind the other in the longitudinal direction of the aircraft or several PAG pallets 86 with the basic dimensions 223.5×317.5 cm (88×125 inches) loaded one behind the other in the longitudinal direction of the aircraft on the lower deck 12. A PMC pallet can be arranged in the through-loading space. With this loading arrangement, the last cargo item in the longitudinal direction of the aircraft may be a cargo container 70, as described in FIGS. 12 and 13, in the aft cargo space.

[0246] With a second loading variant B2, the aircraft 10 can alternatively accommodate, for example, several cargo containers 70 loaded one behind the other in the longitudinal direction of the aircraft on the lower deck 12 as shown in FIGS. 12 and 13, wherein a PMC pallet 88 or at least one mobile additional tank 63 with the basic dimensions of a PMC pallet 88 is arranged in the through-loading space.

[0247] With a third loading variant B3, the aircraft 10 can each accommodate several containers 89, in particular AKH containers, having the basic dimensions of 153.4 cm×156.2 (60.4×61.5 inches) loaded one behind the other in the longitudinal direction of the aircraft, for example, on the lower deck 12, wherein a PMC pallet 88 or at least one mobile additional tank 63 with the basic dimensions of a PMC pallet 88 is arranged in the through-loading space 26.

[0248] With a fourth loading variant B4, the aircraft 10 can each accommodate, for example, several cargo containers 70 loaded one behind the other in the longitudinal direction of the aircraft as shown in FIGS. 12 and 13 in the aft cargo space, as well as several PMC pallets 88 loaded one behind the other in the forward cargo space and several three mobile auxiliary tanks 63 in the area of the through-loading space 26 on the lower deck 12. The mobile additional tanks 63 can have the basic dimensions of a PMC pallet 88. With a fifth loading variant B5, the aircraft 10 can accommodate several cargo containers 70 loaded one behind the other in the longitudinal direction of the aircraft as shown in FIGS. 12 and 13 in the forward cargo space, and several PMC pallets 88 loaded one behind the other in the aft cargo space and two mobile additional tanks 63 in the area of the through-loading space on the lower deck 12. The mobile additional tank 63 can have the basic dimensions of a PMC pallet 88. With this loading variant, the last cargo item in the longitudinal direction of the aircraft can be a cargo container 70, as described in FIGS. 12 and 13, in the aft cargo space. Further arrangements of the containers and pallets in the area of the forward and aft cargo space are directly recognizable in FIG. 17 with regard to the aforementioned loading variants.

[0249] FIG. 18 shows a section of a side view of an aircraft 10 according to another exemplary embodiment according to the invention, wherein the section represents the aircraft 10 in a wing area. FIG. 18 shows a sequential numbering “23” to “61”, wherein one number is assigned to each frame 93 of the fuselage structure 38. In the wing area, additional lines of intersection are shown between frames 93, which can be recognized by the arrows shown on the lines at the top and bottom. The intersections along the lines of intersection will be discussed in detail later.

[0250] The aircraft 10 according to FIG. 18 has a fuselage 11 with a barrel section 15 connected to two wings 98. In general, the aircraft 10 comprises an upper deck 12 and a lower deck 13, separated by a floor 14. The aircraft 10 is designed as a low-wing aircraft and has two aircraft engines 44, with one of the aircraft engines 44 located below on each of the wings 98. This is clearly visible in FIG. 21, for example.

[0251] The barrel section 15 comprises a wing box 27, which is located in the lower deck 13 between the wings 98 in y-direction. The wing box 27 is fixed to the wings 98 and forms a stiffening structure to transfer forces from the wings 98 to the fuselage structure 38 of the aircraft 10. For the connection with the wings 98, the wing box 27 has a wing connection area 106 on both sides, which will be discussed in detail later.

[0252] The wing box 27 has several plates 92 extending transversely to the longitudinal direction of the aircraft. The plates 92 are spaced from each other in the longitudinal direction of the aircraft. Specifically, one plate 92 is arranged at each frame 93 of the fuselage structure 38 of the barrel section 15. In other words, the distances between the plates 92 in the longitudinal direction of the aircraft correspond to the distances between the frames 93. The plates 92 are firmly attached to the frames 93. It is possible that the plates 92 are integrally formed with the frames 93. In other words, the plates 92 can be integral with the frames 93.

[0253] Plates 92 are made in one piece, i.e. integrally. It is possible that at least one of the plates 92 is formed from several individual plate parts.

[0254] The plates 92 can have different cross-sectional shapes depending on their position in wing box 27. FIGS. 19a to 19d show exemplary cross-sections through barrel section 15 to illustrate the arrangement or the cross-sectional shape of the plates 92 (cross-hatching) which changes in the longitudinal direction.

[0255] FIG. 19a shows a section between two frames 93 with the numbering “32” and “33”, looking towards the tail 31 of the aircraft. FIG. 19a shows a first plate 92′, which is arranged in the area of the wing root in longitudinal direction of the aircraft. The plate 92′ is essentially U-shaped. The plate 92′ fills a space which is limited by a through-loading space 26, a fuselage skin 43 and a crossbeam 95 of the floor 14.

[0256] FIG. 19b shows a section between two frames 93 with the numbering “34” and “35” looking towards the tail 31 of the aircraft. FIG. 19b shows a second plate 92″, which is also located in the area of the wing root in longitudinal direction of the aircraft.

[0257] In contrast to the first plate 92′, the second plate 92″ has two plate ends 107, each of which extends into one of the wings 98. The plate ends 107 are directly adjacent to an inner contour 108 of the wings 98.

[0258] As shown in FIG. 19c, a further section is shown, which extends between the two frames 93, numbered “35” and “36”. The figure shows a third plate 92′″ which, in contrast to the second plate 92″, has plate ends 107 which are longer in the y-direction than the plate ends 107 of the second plate 92″. In other words, the plate ends 107 of the third plate 92′″ extend further into the wings 98 than the plate ends 107 of the second plate 92″. The plate ends 107 of the third plate 92′″ are also directly adjacent to the inner contour 108 of the wings 98.

[0259] FIG. 19d shows a fourth plate 92″, which can be seen by a section between two frames 93 with the numbering “39” and “40”. The fourth plate 92″ is located in the area of landing gears 28, which can be clearly seen in FIG. 21. The fourth plate 92″ has 107 downwardly open recesses 108 at the panel ends to accommodate the landing gears 28. The axes of rotation of the landing gears 28 are embedded in the ends of the plates 107 in order to achieve direct force transmission into the wing box 27. In other words, the plate ends 107 of the fourth plate 92″ protrude above the axes of rotation of the landing gears 28 in the y-direction of the aircraft 10.

[0260] The four plates 92′, 92″, 92″, 92″ are only examples of the structure of the plurality of plates 92 at certain positions in the wing box 27. The wing box 27 contains more than four plates 92, as shown in FIGS. 18 and 20. The respective cross-sectional shape of the plates 92 depends on the position of the plates 92 in the longitudinal direction of the aircraft, the inner contour 108 of the wings 98 and the cargo space cross-section of the through-loading space 26 at the corresponding position.

[0261] The wing box 27 according to FIG. 18 has a total of thirteen plates 92. Alternatively, wing box 27 can have more or less than thirteen plates 92. Some of the plates 92 have, as described above, plate ends 107 extending on both sides in the y-direction and projecting into the two wings 98. The plate ends 107 form a wing connection area 106 at the barrel section 15 to which the wings 98 are attached. As shown in FIGS. 19b-d, the wings 98 are pushed or plugged onto the plate ends 107 of the plates 92. The plate ends 107 of the plates 92 form a common mounting stub 97 on each transverse side of the barrel section 15, onto which the wings 98 are plugged. The respective mounting stub 97 engages in the corresponding wing 98 in a fan shape. The wings 98 are positively connected to the respective mounting stub 97. In addition, the wings 98 can be connected to the respective mounting stub 97 in a force-locking and/or materially bonded manner. Preferably, the wings 98 are additionally flanged to the wing connection area 106.

[0262] As can be seen in FIGS. 19a-d, the plates 92 each have a passage opening 94. Plates 92, which are located in the longitudinal direction of the aircraft outside a side landing gear compartment 109, have first openings 94′, which are the same.

[0263] This is clearly visible in FIGS. 19a-c. The plates 92 with the first passage openings 94′ are arranged in the longitudinal direction of the aircraft in such a way that the first passage openings 94′ are aligned.

[0264] The plates 92, which are located in the longitudinal direction of the aircraft within a lateral receiving space 109 for the landing gear 28, have second passage openings 94″, which are the same. The plates 92 with the second passage openings 94″ are arranged in the longitudinal direction of the aircraft so that the second passage openings 94″ are aligned. The shape and width of the first openings 94″ differ from the shape and width of the second passage openings 94″. The second passage openings 94″ of the plates 92 are smaller in y-direction than the first openings 94″ of the corresponding plates 92.

[0265] The width of the second passage openings 94″ is limited laterally by the receiving space 109 for the landing gears. The through-loading space 26, which extends through the passage openings 94′, 94″, is narrowed in the area of the lateral receiving space 109. This can be seen in the longitudinal sectional view of the aircraft 10 according to FIG. 20.

[0266] FIG. 20 also shows that a ramp 110 is arranged at the nose and tail towards the through-loading space 26, which leads to a raised level 111 of the wing box 27. Below level 111, the plates 92 extend transversely through the barrel section 15. The ramps 110 are preferably used to stabilize the transition between the wing box 27 and the fuselage structure 38 which is connected in longitudinal direction.

[0267] The wing box 27 also has several crossbeams 95 extending in the y-direction, which are arranged above the plates 92 in the z-direction and interact with the plates 92 to reinforce the fuselage structure 38 (see FIGS. 19-20). The crossbeams 95 form the part of the cross-bracing structure of the wing box 27 that is located at the top in z-direction. Compared to crossbeams of the fuselage structure 38 of the adjacent barrel sections, which are located outside the wing box 27 in the longitudinal direction of the aircraft, the crossbeams 95 are reinforced to absorb increased forces.

[0268] The crossbeams 95 of the wing box 27 are connected to the plates 92 in a force-transmitting manner. Together with the plates 92, the crossbeams 95 form a particularly stable stiffening unit. The crossbeams 95 stiffen the fuselage structure 38 of the barrel section 15 in y-direction. The crossbeams 95 support the frames 93 in y-direction in the wing area.

[0269] The wing box 27 also has several longitudinal beams 96 extending in the longitudinal direction of the aircraft, which connect the crossbeams 95 to each other. The longitudinal beams 96 connect the crossbeams 95 to each other in the longitudinal direction of the aircraft. Together with the crossbeams 95, the longitudinal beams 96 form a grid structure which is arranged above the plates 92 in the z-direction. The longitudinal beams 96 are arranged over the length of the wing box 27. All in all, the wing box 27 with the plates 92 and the crossbeams and longitudinal beams 95, 96 form a very stable structure which is the stiffest part of the fuselage structure 38 of the entire aircraft 10.

[0270] Seat rails 112 are arranged horizontally on the longitudinal beams 96 in order to provide appropriate seating on the upper deck 12 or to secure cargo items. The seat rails 112 are hinged to the seat rails of the adjacent barrel sections 15 in the two transition areas in the longitudinal direction of the aircraft where the wing box 27 merges with the adjacent barrel sections 15. The articulated connection enables a pivoting movement of the seat rails of the adjacent barrel sections in z-direction. This can be the case especially during flight operations.

[0271] FIG. 21 shows a front view of aircraft 10 according to FIG. 18, with the wings 98 showing an angled wing shape. Starting from the wing connection area 106, the wings 98 extend outwards transversely to the longitudinal direction of the aircraft to a free wing tip 101. The wings 98 have an area 113 close to the fuselage and a an area 114 remote from the fuselage. In the area 113 close to the fuselage the wings 98 extend in a first angle of inclination SW1, which is larger than a second angle of inclination SW2, in which the wings 98 extend in the area 114 remote from the fuselage towards the free wing tip 101. The angles of inclination SW1, SW2 refer to a reference axis RA1, which extends in the y-direction of the aircraft 10.

[0272] On aircraft 10 as shown in FIG. 21, the first angle of inclination SW1 is between 16 degrees and 18 degrees. The second angle of inclination SW2 is between 7 degrees and 10 degrees.

[0273] As can be seen in FIGS. 21 to 23, the landing gears 28 are located in the area near the fuselage 113 and the aircraft engines 44 in the area remote from the fuselage 114. The aircraft 10 according to FIG. 18 has an outer maximum height of the fuselage 11 or barrel section 15 of approximately 485 cm (191 inches) and an outer maximum width of approximately 498 cm (196 inches). The landing gears 28 of aircraft 10 have axes of rotation 104 in y-direction with a distance Arot of approximately 955 cm (376 inches). With a length LF of the landing gears 28 of approximately 335 cm (132 inches), the through-loading space 26 in the area of the receiving space 109 of the landing gears 28 has a clear width in y-direction of 254 cm (100 inches). The clear height of the through-loading space 26 in the area of the landing gears 28 is approximately 128 cm (approx. 50.5 inches). The landing gear length LF is measured from the axes of rotation 104 to the lower edge of the landing gear wheels.

[0274] Due to the two protruding angles of inclination SW1, SW2 of the wings 98, the aircraft 10 has a first ground clearance BF1 in z-direction from a lower edge of the fuselage 11 to a lower edge of the landing gears 28 in the folded-out condition of approximately 186 cm (approx. 173 inches) according to FIG. 18. When using aircraft engines 44 with a rotor diameter of approximately 265 cm (approx. 104.5 inches) with corresponding arrangement at the wings 98, a second ground clearance BF2 in z-direction from a lower edge of the engines 44 to a lower edge of the landing gears 28 of between 69 cm and 72 cm (approx. 27 inches and approx. 28 inches), preferably approximately 700 cm (approx. 27.5 inches), can be achieved.

[0275] According to FIG. 24, an aircraft 10 is shown according to another exemplary embodiment according to the invention, which has a fuselage 11 with a barrel section 15 connected to two wings 98. In general, the aircraft 10 has an upper deck 12 and a lower deck 13 separated by a floor 14. The aircraft 10 is designed as a low-wing aircraft and has two aircraft engines 44. In contrast to the aircraft shown in FIG. 18, however, the aircraft engines 44 are not located on the wings 98, but on the tail 31. Furthermore, there is no bend in the curves of the wings 98, which have a constant shape as shown in FIG. 25.

[0276] The aircraft 10 according to FIG. 24 has a wing box 27 with plates 92, which corresponds to the wing box 27 as described in FIGS. 18 and 19a-d. By contrast, however, the plates 92 of the wing box 27 as shown in FIG. 24 (not visible) have a passage opening 94 for the through-loading space 26, which are identical. The through-loading space 26 of the aircraft 10 according to FIG. 24 has a through-loading cross-section which is identical to the cross-sections of the cargo space adjoining the forward and aft cargo space. In other words, the forward and aft cargo spaces together with the through-loading space 26 form a common cargo space 105, which has a constant continuous cross-section between the nose and the tail of the aircraft 10.

[0277] According to FIG. 25, the landing gears 28 are shown in folded-in and folded-out condition for the sake of simplicity. As can be seen in FIG. 25, the landing gears 28 are arranged close to the fuselage.

[0278] The aircraft 10 as shown in FIG. 24 has an outer diameter of the fuselage 11 or barrel section 15 of approximately 477 cm (188 inches). The landing gears 28 of aircraft 10 have axes of rotation 104, which have a distance Arot of 775 cm (approx. 305 inches) in y-direction. With a length LF of the landing gears 28 of approximately 212 cm (83.7 inches), the through-loading space 26 in the area of the receiving space 109 of the landing gears 28 has a clear width in y-direction of 328 cm (approx. 129 inches). The landing gear length LF is measured from the axes of rotation 104 to the lower edge of the landing gear wheels. The distance X from the axes of rotation 104 to the rotation axis of the landing gear wheels is approximately 161 cm (63.3 inches).

[0279] The aircraft 10 according to FIG. 24 has a ground clearance BF1 in z-direction from a lower edge of the fuselage 11 to a lower edge of the landing gears 28 in the folded-out position of approximately 125.5 cm (approx. 49.5 inches). Furthermore, the landing gears 28 together have an outer track width ASB of approximately 914 cm (360 inches). The outer track width ASB corresponds to the maximum track width when the landing gears 28 are folded out.

[0280] FIG. 26 shows a top view of the aircraft 10 according to FIG. 24, wherein the outer fuselage skin 43 is not shown. The fuselage 11 has a fuselage structure extension 102 on both sides in y-direction to accommodate the landing gears 28. In other words, the barrel section 15 has a bulge on both sides in the longitudinal direction of the aircraft in the area of the landing gears 28 at the outer contour in y-direction. Due to the fuselage structure extension 102, the cross-sectional profile of barrel section 15 is wider in the area of the landing gears 28 than outside the area of the landing gears 28. Due to the fuselage structure extension 102, a free space 103 is formed on one wing side in the lower deck 13 to accommodate the landing gears 28. In other words, the free space 103 is used to stow the landing gears 28. The fuselage structure extension 102 is formed in the area of the wing box 27. The free space 103 is embedded in the wing box 27. This means that the plates 92 of the wing box 27 are exposed in the area of free space 103 in the y-direction from the outside to the inside, in particular cut out to allow the landing gears 28 to be folded in.

[0281] As shown in FIG. 25, in cross-section the fuselage structure extension 102 in the area of the landing gears 28 is formed by a straight extension 115 of an upper, circular-segment-shaped fuselage segment 116 of the barrel section 15 towards the wing connection area 106. The straight extension 115 is formed as a tangent of the circular-segment-shaped fuselage segment 116 towards the wing 98. The straight extension 115 extends diagonally outwards in the y-direction and thus widens the cross-section of the barrel section 15 in the lower deck 13, so that the free space 103 is formed.

[0282] In FIG. 26 the drawing clearly shows that the fuselage structure extension 102 in longitudinal direction of the aircraft is formed in a tail area of the wings 98. The straight extension 115 of the upper fuselage segment 116 leads diagonally outwards from upper deck 12 to lower deck 13. The free space 103 is formed between the outer fuselage skin 43 and the through-loading space 26 in such a way that the cargo space cross-section of the through-loading space 26 is the same as the forward and aft cargo spaces. In other words, the free space 103 is such that the through-loading space 26 does not have a cross-section narrowing in the y-direction with respect to the forward and aft cargo spaces. This can be seen, for example, in FIG. 25, wherein a cargo item is arranged in the through-loading space 26 for illustration purposes only.

[0283] FIGS. 27 to 29 each show a variant with a deck configuration of aircraft 10 according to FIG. 24. FIG. 27 shows a first deck configuration of aircraft 10. In concrete terms the aircraft is shown in a configuration in which a passenger seating, e.g. for approximately 200 passengers, is arranged in the entire upper deck 12 and passenger seating, e.g. for approximately 60 to 70 passengers, is arranged in the lower deck 13 in a forward fuselage area 117, i.e. in the longitudinal direction of the aircraft in front of the through-loading space 26, especially the wing box 27. The through-loading space 26 and the aft cargo space 25 are equipped for the transport of cargo and therefore do not have any passenger seating. In the passenger areas of the upper and lower decks 12, 13 there are rows of windows on both sides. To connect the two decks 12, 13 a staircase 118 is arranged in the area of the forward wing attachment. Sanitary facilities may also be provided in this area. In this case, it is advantageous to divide the passengers between the upper and lower decks 12, 13 to shorten the length of the aircraft 10. The passenger seating on the lower deck 13 and staircase 118 is clearly visible in FIG. 30, wherein FIG. 30 does not show the aircraft structure, i.e. outer skin, frames, wing box, etc., or the passenger seating on the upper deck 12 for better illustration.

[0284] In addition, as shown in FIG. 24, the aircraft 10 has an aft loading door 119 through which the aft cargo space 25 is accessible for loading and unloading the lower deck 13. There is no forward loading door provided for loading the lower deck 13. Compared to a forward loading door, the aft loading door 119 has the advantage that in the first deck configuration of the aircraft 10 it prevents an undesired draft in the cabin, thus increasing the comfort for the passengers during flight.

[0285] Furthermore, the aft loading door 119 is located on one side of the aircraft, which is on the left side when looking from the tail 31 to the nose 29 of the aircraft. This has the advantage that the loading or unloading process is simplified by means of a ramp vehicle.

[0286] As the aircraft 10 according to FIG. 24 has a cargo space with a constant cross-section over the entire length of the fuselage 11, i.e. from the tail 31 of the aircraft to the nose 29 of the aircraft, reconfiguration of the lower deck 13 is considerably simplified.

[0287] For example, FIG. 28 shows a second deck configuration which differs from the first deck configuration shown in FIG. 27 only in that the forward fuselage area 117 is converted to a forward cargo space 24. In other words, the forward fuselage area 117 is set up as a cargo space to transport cargo items. In the second deck configuration, the aircraft 10 thus has a seated upper deck 12 for passenger transport and a lower deck 13 for cargo transport.

[0288] In a third deck configuration, shown in FIG. 29, aircraft 10 is designed for pure cargo transport. For this purpose, the upper deck 12 and the lower deck 13 are each set up as cargo spaces for transporting cargo items. In addition, the aircraft 10 in the cargo configuration has a forward loading door 121 through which the cargo space of the upper deck 12 is accessible for loading and unloading. Seating on the upper and lower decks 12, 13 is missing in the third deck configuration.

[0289] In the second and third deck configuration, the lower deck 13 is formed as shown in FIG. 31. In other words, the lower deck 13 is intended for cargo transport only.

[0290] In the lower deck 13, the passenger seating and staircase 18 are missing here. Furthermore, the aircraft structure, i.e. outer skin, frames, wing box, etc., is not shown in FIG. 31 for better illustration. In FIG. 31 it is also evident that unfolded cargo space modules 122 are introduced to form the cargo space, which will be discussed in more detail below.

[0291] A great advantage of the aircraft 10 according to FIG. 24 results from the fact that the lower deck 13 has a cargo space that is continuous from tail to nose with a constant cargo space cross-section, especially cargo space profile. This allows a reconfiguration of the lower deck 13 by means of foldable cargo space modules quickly and easily. The cargo space modules can be designed in such a way that they replace vertical frames of the fuselage structure 38 of the aircraft 10. When reconfiguring the lower deck 13, for example to a cargo space for cargo items or to a passenger cabin, the foldable cargo space modules can be brought into the lower deck 13 via the aft loading door 119 and arranged in a row one behind the other. The cargo space modules can be combined in any desired way, for example to create a lower deck 13 according to the first deck configuration, second or third deck configuration.

[0292] The foldable cargo space modules can, for example, be fitted with pre-assembled seat rails for the subsequent attachment of a passenger seat, or with a pre-assembled passenger seat in the lower deck 13. For the configuration of the lower deck 13 as a cargo-only area, the cargo space modules may have pre-assembled devices for securing and guiding cargo items.

[0293] With regard to the foldable cargo space module, reference is made to application DE 10 2019 132 292.8, which is already mentioned in the introduction to the description.

[0294] FIG. 32 shows a cross-sectional profile 16 of an aircraft 10 according to another exemplary embodiment according to the invention. In this example, the aircraft 10 is designed as a low-wing aircraft. The cross-sectional profile 16 according to FIG. 32 is oval. The barrel section 15, which includes the cross-sectional profile 16 as mentioned, has a wall thickness as described in FIG. 1.

[0295] The barrel section 15 as shown in FIG. 32 has an outer maximum width of 497 cm (approx. 196 inches) in the y-direction and an outer maximum height 21 of 461 cm (approx. 181 inches) in the z-direction. Further dimensions of the cross-sectional profile 16 as well as loading configurations of the upper deck 12 and the lower deck 13 are shown in FIG. 32. The dimensions shown above the dimensions in the square brackets are given in millimeters. The dimensions shown in the square brackets below correspond to the inch value of the dimensions above in millimeters.

[0296] The aircraft 10 as shown in FIG. 32 may be configured in several different loading/equipment configurations of the upper and lower decks 12, 13 as shown and described in FIGS. 16 and 17, like the aircrafts shown in FIG. 1, FIG. 14 and FIG. 15. Reference is hereby made to the loading variants V1 to V5 and the equipment variants AV1 and AV2 as described above.

[0297] At this point, it should be noted that all parts described above, in particular also the embodiments and/or exemplary embodiments themselves, each for itself—even without features additionally described in the respective context, even if these are not explicitly identified individually as optional features in the respective context, e.g. by using: in particular, preferably, for example, e.g., if necessary, round brackets, etc.—and in combination or any sub-combination are to be regarded as independent designs or further developments of the invention, as defined in particular in the introduction to the description and the claims. Deviations from this are possible. Specifically, it should be noted that the word in particular or round brackets do not indicate any features that are mandatory in the respective context.

[0298] Furthermore, it should be noted that the term ‘wing box’ in this application is by no means to be understood as meaning a conventional wing box as it has been used in aircraft construction for more than 50 years. Rather, the wing box of the present application is a functional unit that serves to absorb the forces acting on the wings.

[0299] In the embodiments and exemplary embodiments, reference is mainly made to the plates. The individual explanations and/or advantages are also applicable to the C-shaped beams. With regard to the additional or alternative design of the plates, reference is made to the embodiments of the plates mentioned in the introduction to the description.

LIST OF REFERENCE NUMERALS

[0300] 10 Aircraft [0301] 11 Fuselage [0302] 12 Upper deck [0303] 13 Lower deck [0304] 14 Floor [0305] 15 Barrel section [0306] 16 Cross-sectional profile [0307] 17 Circular arc sections [0308] 17′ First circular arc section [0309] 17″ Second circular arc section [0310] 17′″ Third circular arc sections [0311] 18 Cargo item/container [0312] 18′ First cargo container [0313] 18″ Second cargo container [0314] 18′″ Third cargo container [0315] 19 Outer maximum width [0316] 21 Outer maximum height [0317] 22 First clear width [0318] 23 Second clear width [0319] 24 Forward cargo space [0320] 25 Aft cargo space [0321] 26 Through-loading space [0322] 27 Wing box [0323] 28 Landing gear [0324] 29 Aircraft nose [0325] 31 Aircraft tail [0326] 32 Minimum width of the through-loading space [0327] 32′ Minimum usable width of the through-loading space [0328] 33 Through-loading height [0329] 34 Seating rows [0330] 35 Corridors [0331] 36 First loading door [0332] 37 Second loading door [0333] 38 Fuselage structure [0334] 39 Forward loading opening [0335] 41 Upper edge of the floor [0336] 42 Lower edge of the floor [0337] 73 Outer fuselage skin [0338] 44 Aircraft engine [0339] 45 Trapezoidal cargo containers [0340] 46 Pallet [0341] 47 Floor structure [0342] 48 Roller conveyor system [0343] 49 Clear width of the upper deck [0344] 51 Clear width of the lower deck [0345] 52 Receiving device [0346] 53 Ceiling area [0347] 54 Central area [0348] 55 Common area [0349] 56 First area [0350] 57 Second area [0351] 58 Walking Area [0352] 59 First clear width [0353] 61 Second clear width [0354] 62 Third clear width [0355] 63 Mobile additional tank [0356] 64 Fuel tank [0357] 65 Doors [0358] 66 Additional receiving device [0359] 67 Tail loading opening of the lower deck [0360] 67′ Tail loading opening of the upper deck [0361] 70 Cargo container [0362] 71 Trapezoidal base body [0363] 72 Base area [0364] 73 Ceiling area [0365] 74 Fastening element [0366] 75 First longitudinal side [0367] 76 Second longitudinal side [0368] 77 Total height [0369] 78 Broad sides [0370] 79 Inclined section [0371] 81 PGA pallets [0372] 81′ PRA pallets [0373] 82 HCU-6E pallets [0374] 82′ HCU-12E pallets [0375] 83 AAC container [0376] 84 AMA container [0377] 85 AAJ container [0378] 86 PAG pallets [0379] 87 Vehicle [0380] 88 PMC pallet [0381] 89 AKH container [0382] 91 Circle [0383] 92 Plate [0384] 92′ First plate [0385] 92″ Second plate [0386] 92′″ Third plate [0387] 92″ Fourth plate [0388] 93 Frames [0389] 94 Passage opening [0390] 94′ First passage opening [0391] 94″ Second passage opening [0392] 95 Crossbeam [0393] 96 Longitudinal beam [0394] 97 Mounting stubs for wings [0395] 98 Wing [0396] 99 - [0397] 101 Free wingtip [0398] 102 Fuselage structure extension [0399] 103 Free space [0400] 104 Axes of rotation [0401] 105 Common cargo space [0402] 106 Wing connection area [0403] 107 Plate ends [0404] 108 Inner contour of the wings [0405] 109 Lateral receiving space [0406] 110 Ramp [0407] 111 Raised level [0408] 112 Seat rails [0409] 113 Area close to the fuselage [0410] 114 Area remote from the fuselage [0411] 115 Extension [0412] 116 Fuselage segment [0413] 117 Forward fuselage area [0414] 118 Staircase [0415] 119 Aft loading door [0416] 121 Forward loading door [0417] 122 Foldable cargo space modules [0418] A1′ Distance of the floor to the y-axis [0419] A1″ Distance of the center of the first circular arc section [0420] A2 Distance of the center of the second circular arc section from the center of the first circular arc section [0421] A3 Distance of the center of the second circular arc section from the upper edge of the floor [0422] A4 Distance between the centers of the third circular arc sections [0423] A5 Minimum distance [0424] A6 Distance between the central area and the upper edge [0425] A7 Distance between the axes of rotation [0426] R1′, R2′, [0427] R3′, R4′ Outer radii [0428] R1, R2, [0429] R3, R4 Radii [0430] M1, M2, [0431] M3, M4 Centers [0432] H1 Height of the first and second cargo container [0433] H2 Height of the trapezoidal cargo container and pallet [0434] H3 Height of the inclined section [0435] V1, V2, V3, [0436] V4, V5 Loading variants of the upper deck [0437] AV1, AV2 Equipment variants of the upper deck [0438] B1, B2, B3, [0439] B4, B5 Loading variants of the lower deck [0440] Arot Distance between the axes of rotation [0441] ASB Outer track width [0442] BF1 First ground clearance [0443] BF2 Second ground clearance [0444] LF Length of landing gear [0445] RA1 Reference axis [0446] SW1, SW2 Angle of inclination [0447] X Distance of the axes of rotation from the rotation axis of the landing gear wheels