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(19) TZZ Z _T

(11) EP 2 404 826 B1

(12) EUROPEAN PATENT SPECIFICATION

(45) Date of publication and mention (51) Int Cl.: of the grant of the patent: B64C 39/00 (2006.01) B64C 25/10 (2006.01) 04.05.2016 Bulletin 2016/18 B64C 11/00 (2006.01) B64C 1/00 (2006.01) B63H 5/125 (2006.01) B64C 35/00 (2006.01) (21) Application number: 10748320.8 (86) International application number: (22) Date of filing: 01.03.2010 PCT/CN2010/070806

(87) International publication number: WO 2010/099730 (10.09.2010 Gazette 2010/36)

(54) AMPHIBIOUS LARGE WITHOUT GROSSES AMPHIBISCHES FLUGZEUG OHNE GANGWAY GRAND AVION AMPHIBIE SANS ESCALIER

(84) Designated Contracting States: (74) Representative: Stuttard, Garry Philip AT BE BG CH CY CZ DE DK EE ES FI FR GB GR Urquhart-Dykes & Lord LLP HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL Tower North Central PT RO SE SI SK SM TR Merrion Way Leeds LS2 8PA (GB) (30) Priority: 04.03.2009 CN 200910060955 (56) References cited: (43) Date of publication of application: CN-A- 1 351 944 CN-A- 1 351 944 11.01.2012 Bulletin 2012/02 CN-A- 1 439 573 CN-A- 1 439 573 CN-Y- 2 504 194 CN-Y- 2 504 194 (73) Proprietor: Liu, Shiying DE-C1- 10 043 863 FR-A1- 2 575 723 Wuhan, Hubei 430072 (CN) GB-A- 506 719 GB-A- 506 719 US-A- 2 989 269 US-A- 3 010 424 (72) Inventor: Liu, Shiying US-A- 4 579 300 US-A- 4 579 300 Wuhan, Hubei 430072 (CN) US-A- 5 086 992 US-A- 5 086 992 US-A- 5 893 535 US-A- 5 893 535

Note: Within nine months of the publication of the mention of the grant of the European patent in the European Patent Bulletin, any person may give notice to the European Patent Office of opposition to that patent, in accordance with the Implementing Regulations. Notice of opposition shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention). EP 2 404 826 B1

Printed by Jouve, 75001 (FR) 1 EP 2 404 826 B1 2

Description thus the is long in distance. Besides, due to the cylindrical , landing on water is generally unsafe; [0001] The aircraft of this invention involves an am- only takeoff and landing on the runway are reliable; and phibious large aircraft without the traditional airstairs. Es- a forced landing on water in en emergency may cost tre- pecially with its flat and oblong fuselage, said amphibious 5 mendous loss. For instance, both engines of one A-320 large aircraft has wing-in-ground effect in addition to gen- airliner of American were broken down by bird erating elevating force in flight. Thus, said amphibious strike shortly after taking off on Jan 15, 2009; fortunately, large aircraft has smooth takeoff and touchdown on the it was forced landed on Hudson River at last by the de- runway as well as on broad water area. cisive and experienced pilot, preventing a grievous air [0002] At present, it is known to all that the 10 crash and casualty. The event is recognized as a miracle of the large aircrafts with more than 150 are in the world; although there is no casualty with the 155 always in narrow cylindrical shape. Aerodynamically, this passengers, 87 of them were injured, and the aircraft was type of fuselage does not generate elevating force in damaged seriously, with both engines falling into water flight; it only serves as a vessel for the and pas- in addition to the soaked fuselage. sengers. With the aircraft load beared by the elevating 15 [0003] CN 1351944 A discloses an aircraft with a flat force generated by the airfoils on both sides, these leads and oblong shaped fuselage, which comprises a passen- to large airfoil area, long overhanging length and low flight ger cabin and a cargo hold on the same floor. The pilot efficiency. Furthermore, because the cross-section of the compartment protrudes from the fuselage. This aircraft fuselage is round, and the cabin is over the also comprises airfoils, empennages, undercarriages re- cargo hold; the cargo hold is inconvenient for use due to 20 tracting into bays in the passenger cabin, and engines. its wide top and narrow bottom; the cabin floor has raised [0004] To overcome the foregoing disadvantages of ground clearance due to the cargo hold and the under- the existing jumbo aircraft, the aircraft of this invention carriage underneath; taken together, an is the makesit possible tomanufacture atype of improved over- only choice for passenger and landing, and an sized aircraft; said aircraft generates elevating force for inflatable slide is the only resort for passenger evacuation 25 the improved flight efficiency, is free from passenger air- in an emergency. For the oversized passenger aircraft stairs, and makes safe and smooth takeoff and touch- such as A-380, the fuselage section consists of three down on an existing runway as well as broad sea, lake floors; the lower floor is the cargo hold; above which is and river surfaces,leading to a widescope of applications the passenger cabin with ground clearance of 6.2meter and enhanced flight safety. and9.0meter respectively; thepassengers are ata height 30 [0005] These disadvantages are overcome by the air- equivalent to the 3rd and 4th floors, where boarding and craft defined in independent claim 1, with preferred em- landing are inconvenient, and where it is hard to evacuate bodiments of the invention being defined in the depend- by inflatable slide in an emergency. Due to the narrow ent claims. fuselage of the existing aircraft, the passenger cabin is [0006] The technical design for the technical solution like a corridor, which is inconvenient for use due to the 35 of the aircraft of this invention is described as follows. long walking distance for the stewardess; in addition, the [0007] Divide the narrow fuselage of the existing air- main undercarriage is also unable to mount on the airfoil craft into two sections from the center, then assemble base. In this case, the full load of the aircraft is applied the said two sections in parallel, and eliminate the cargo on the airfoil base before being transferred to the land hold under the cabin of the existing aircraft section; then via the main undercarriage when landing. The compli- 40 reshape the fuselage so that its cross-sectional shape cated path for the force transfer leads to the high bending resembles that of the airfoil section, and as such the pre- moment on the airfoil base; the underside of the airfoil vious narrow fuselage is transformed into the flat and base must also projects outwards for encasing the col- oblong shaped fuselage; the pilot compartment pro- umn of the main undercarriage, and as a result the airfoil trudes out from the fuselage to obtain a better view on lift is reduced. In addition, since the airfoil and the fuse- 45 the front and the two sides; the airfoil is mounted on the lage form a cross in narrow shape, the aircraft has a long fuselage of the aerofoil section, both sides of central air- fuselage and a wide wingspan, and also a high fuselage foil assembly which is higher above the useable space and a large landing area (e.g. passenger aircraft A-380 in the cabin; and the twin-finned supporting empennage has a fuselage length of 72.7m, a wingspan of 98.8m and is mounted behind the wide fuselage. Therefore, the pas- an empennage height of 24.3m), resulting in a tremen- 50 senger cabin is no longer like a corridor, rather it resem- dous investment in construction from the aircraft manu- bles an auditorium; and the fuselage generates elevating factory, the service workshop, garage and land acquisi- force in flight for increased flight efficiency and shorter tion. Due to the complicated structure of the undercar- walking distance for the stewardess. For the existing air- riage bay of the existing aircraft, the overhanging fuse- craft, the passenger cabin and the cargo hold are at dif- lage section has a large bulge undercarriage bay, leading 55 ferent floors and the area ratio of the two is fixed. In con- to the increased atmospheric drag in flight. For the ex- trast, the passenger cabin and the cargo hold are at the isting aircraft, wing-in-ground effect in takeoff and touch- same floor in the aircraft of this invention. Even the equiv- down is relatively low, and the approaching speed is high, alent of the largest oversized A380 airliner in the world

2 3 EP 2 404 826 B1 4

(five-hierarchy structure of 555 seats, one- hierarchy at small landing angle near the surface for a safe and structure of 840 seats) can have its seats smooth touchdown; in this way, all the passengers and all arranged to be within one floor; and the area ratio of crew would be free from injury, and the aircraft as a whole the passenger cabin and the cargo hold is adjustable would be safe. The existing floatplane has the cylindrical based upon the market demand of the client. As for the 5 fuselage, while the aircraft of this invention has the flat low atmospheric pressure in the aircraft above 10,000 fuselage with better wing-in-ground effect, thus the in- meters in the sky, the cabin needs to be pressurized to vention will perform better than the existing floatplane. 0.8 atmospheric pressure to ensure easy breath by the [0011] From the perspective of manufacture and as- passengers and the crew; and the strength and rigidity sembly, the A380 oversized airliner needs simultaneous of the aircraft structure is achievable by the additional 10 vertical manufacture and assembly at three floors. How- columns and oblique struts in the flat fuselage, for the ever, the passenger cabin and the cargo hold of the air- loading structure of a octagonal framework is similar to craft of this invention are on the same floor, and the air- that of the round framework of the traditional aircrafts. craft section has only one floor where the manufacture [0008] As the fuselage of the aircraft of this invention and assembly takes place; together with the vertical re- is flat, and the fuselage width approximately doubles that 15 tractable undercarriage, the final assembly is done on of the existing aircraft of equal numbers of seats, and the the ground floor, which is much more convenient for as- aircraft of this invention has higher space on top within sembly and adjustment, leading to a remarkably less the cabin, thus it is not necessary to mount the main manufacturing cost and shorter manufacturing cycle. (MLG) on the airfoil base; rather, the MLG [0012] To conclude, under conditions of equivalent bay and the front undercarriage bay are mounted directly 20 load (equal passengers or cargo) and mileage, in the fuselage, so that the full load of the aircraft is trans- the aircraft of this invention is more advantageously ef- ferred on the ground via the undercarriage; the path for fectiveand its flightefficiency is estimatedto be increased the force transfer is simple, which is helpful for not only by 30~40% in comparison with other existing aircrafts; reducing the weight of the aircraft structure, but also when the aircraft of this invention flies 4~12 meters above avoiding disruption of the normal form of the fuselage 25 water, the flight efficiency may be improved by 40~45%; and the airfoil base sections, thereby leading to improved the aircraft of this invention has remarkably reduced man- aircraft lift and lift-drag ratio. ufacturing cost and shortened manufacturing cycle; its [0009] The engines are mounted either on the rear top fuselage land close to ground for convenient passage of of the flat and oblong shaped fuselage or suspended in the passengers and cargo, faster and safer emergency the lower part of the flat empennage. As the flat fuselage 30 evacuation, wide scope of applications in terms of safe has no cargo hold underneath and the undercarriage is and smooth takeoff and touchdown on the runway and inside, if the current rotary undercarriage control is re- water as well, allowing the future construction of an air- placed by the vertical retractable control, and the under- port in a coastal city for less land acquisition. carriage door of the traditional up-and-down turnover [0013] The aircraft of this invention is further illustrated type is replaced by the sliding doors, the fuselage base- 35 by the attached illustrations and embodiments. plate of the aircraft of this invention can be landed firmly close to ground; therefore, passengers can get on and Figure 1 is the layout plan of the passenger cabin off the aircraft of this invention in the same convenient (two-compartment cabin). way as that of a , and no inflatable slide is necessary in enemergency evacuation. 40 Figure 2 is the B-B longitudinal sectional view of Fig- [0010] Its flat fuselage of the aircraft of this invention ure 1. instead of the cylindrical shape of the existing aircraft makes the aircraft of this invention have better gliding Figure 3 is the A-A longitudinal sectional view of Fig- performance than the existing aircraft, which is helpful ure 1. for reducing the approach speed, for safe takeoff and 45 touchdown on the runway, and for shortening the re- Figure 4 is the C-C enlarged transverse sectional quired runway distance in comparison to the existing air- view of Figure 1. craft. Likewise, the invention has better wing-in-ground effect than the existing floatplane when flying close to Figure 5 is the top view of the exterior of the passen- water surface; hence it is comparable to the floatplane 50 ger cabin (two-compartment cabin). in terms of convenient, safe and smooth takeoff and touchdown on broad water. Assuming that the aircraft of Figure 6 is the side view of the exterior of the pas- the aircraft of this invention would suffer a bird strike sim- senger cabin (two-compartment cabin). ilar to that of the American Airlines airliner, the inertia velocity of the aircraft of this invention would generate 55 Figure 7 is the front view of the exterior of the pas- enough elevating force and airfoil lift to support the gliding senger cabin (two-compartment cabin). of the idle aircraft, providing the time needed for seeking broad surface of sea, river or lake for landing the aircraft Figure 8 is the D-D transverse sectional view of Fig-

3 5 EP 2 404 826 B1 6 ure 1. Figure 38.

Figure 9 is the D-D transverse sectional view of the Figure 42 is the M-M sectional view of Figure 43. passenger cabin (three-compartment cabin). 5 Figure 43 is the layout plan of the compartment floor Figure 10 is the D-D transverse sectional view of the of an embodiment of the aircraft of this invention passenger cabin (four-compartment cabin, equiva- (equivalent to A-380 , open-V empennage, lent to A-380 airbus). half-and-half areas of passenger cabin and cargo hold, amphibious aircraft). Figure 11 is the enlarged sectional view of the trans- 10 verse framework of the passenger cabin (three-com- Figure 44 is the N-N sectional view of Figure 43. partment cabin). Figure 45 is the transverse sectional view of a four- Figure 12 is the layout plan of an embodiment of the compartment passenger cabin which is not in ac- aircraft of this invention (four-compartment cabin, 15 cordance with the invention (equivalent to A-380 air- equivalent to A-380 airbus). bus, for land use only).

Figure 13 is the side view of an embodiment of the Figures 46 to 48 are the dimensional comparison of aircraft of this invention (four-compartment cabin, the four-compartment passenger cabin of the inven- equivalent to A-380 airbus). 20 tion (equivalent to A-380 airbus, amphibious aircraft) and the existing A380 airliner. Figures 14 to 17 are an embodiment of the aircraft of this invention in the process of from ground landing Figures 49 to 50 are the enlarged comparison of the to takeoff. front view windward area of the fuselages of the four- 25 compartment passenger cabin of the invention Figures 18 to 21 are the structure drawing of the (equivalent to A-380 airbus, amphibious aircraft) and vertical lift propeller of the aircraft of this invention the existing A380 airliner. for functioning as a floatplane. Figure 51 is the enlarged sectional view of the trans- Figures 22 to 26 are the aircraft of this invention in 30 verse framework of the passenger cabin with the U- the process of from water landing to surface cruise. groove of the aircraft of this invention (three-com- partment cabin). Figures 27 to 34 are the aircraft of this invention (two- compartment passenger cabin) in the process of Figure 52 is the enlarged structure drawing of the U- from landing in the harbor to departure. 35 groove.

Figures 35 is the layout plan of the compartments of Figure 53 is the transverse sectional view of the an embodiment of the aircraft of this invention (am- of the aircraft of this invention phibious aircraft) as a . (three-compartment cabin). 40 Figure 36 is the G-G longitudinal sectional view of Figure 54 is the side view of the emergency landing Figure 35. of the aircraft of this invention (three-compartment cabin). Figure 37 is the H-H longitudinal sectional view of Figure 35. 45 [0014] Inthe drawings, 1-; 2-Electronic console chamber; 3-front undercarriage bay; 4- front undercar- Figure 38 is the layout plan of the compartment floor riage; 5-passenger cabin door; 6-passenger cabin; 7-fu- of an embodiment of the aircraft of this invention selage; 8-airfoil; 9-MLG; 10-MLG bay; 11-rest room; 12- (open-V empennage, land use only) as a cargo air- food serving compartment; 13-cargo hold door; 14-fuel- craft. 50 oil engine; 15-propellers; 16-fuselage empennage; 17- steering sleeve; 18-rotating shaft; 19-propeller chamber; Figure 39 is the K-K longitudinal sectional view of 20-fixedgearbox; 21-cargo hold;22-seat; 23-column; 24- Figure 38. oblique strut; 25-airstairs; 26-engine room; 27-instru- ment panel; 28-pilot radar compartment; 29-luggage Figure 40 is the K’-K’ longitudinal sectional view of 55 compartment; 30-; 31-vertical empennage; 32- Figure 38. horizontal empennage; 33-front and rear sliding doors; 34-airfoil assembling center; 35-open-V empennage; 36- Figure 41 is the K"-K" longitudinal sectional view of passenger cabin window; 37-aircraft top passenger cab-

4 7 EP 2 404 826 B1 8 in window; 38-aircraft top exit; 39-transverse framework passenger cabin (6) does not have the cargo hold un- of the passenger cabin; 40- aileron; 41-fuselage frame- derneath; and the jet engine (30) is not suspended be- work; 42- hexagonal shaft; 43-pore; 44-hydraulic cylin- neath the airfoil, instead, it is mounted on the top of the der; 45-bevel gear; 46-locking bolt; 47-loose bevel gear; fuselage (7) ; for the above reasons taken together, 48-shaft; 49-movable gearbox; 50-piston; 51-waterproof 5 therefore, the fuselage (7) can be landed with its bottom shaft gland; 52-harbor airport; 53-dome bracing; 54- close to the ground. To realize this landing, the vertical wharf; 55-rain shed; 56-surface; 57-mounting base; 58- turnover undercarriage door for the existing aircraft is no vertical lift propeller device; 59-lifting hole; 60-open-V longer used; rather, a front and rear sliding door (33) is empennage; 61-cargo hold open close slot; 62-coupling; adopted. On each end of the fuselage empennage (16) 63-U-groove; 64-underplate; 65-snap slot; 66-strip air 10 in the cargo hold (21), one vertical lift propeller device cushion. (58) is incorporated. As shown in the figure, all the front [0015] The present invention will further be described and rear sliding doors (33) of all the undercarriage bays in detail in accordance with the Figures. are opened, and the undercarriages are adjusted to the [0016] As illustrated in the embodiment in figure 1 height with the fuselage landed on the ground, and the (equivalent to A-32 airliner series), the linear length-to- 15 passenger cabin (6) is ready for passenger boarding. width ratio of the fuselage (7) is preferred to be in the [0018] It is obvious from figure 3 that the longitudinal range of 2.0~4.5:1; the pilot compartment (1) protrudes section at the longitudinal centerline of the fuselage (7) out from the fuselage (7) for better pilot view; the engine of the aircraft of this invention also matches the section room (26), the electronic console chamber (2) and the form of the airfoil. In the front of the fuselage (7) is the front undercarriage bay (3) are configured in the front 20 pilot compartment (1), where the instrument panel (27) section of the fuselage (7); in the middle of the fuselage and the pilot radar chamber (28) are located. Against the (7) is the passenger cabin (6), within the aisle and the pilot compartment (1) is the engine room (26). On both seats are arranged (22); behind the passenger cabin (6) sidesof theengine roomare theelectronic consolecham- is the section for the rest room (11) and the food serving bers (2). The airstairs (25) are for passenger passage to compartment (12). The MLG bay (10) is arranged at the 25 and from the passenger cabin (6) when the aircraft of this two sides at the rear of the aircraft center of gravity in the invention serves as a floatplane when landing in airport passenger cabin (6), and within the MLG bay is the MLG (52). In this case, on both sides of the passenger cabin (9); the cabin doors (5) are arranged on both sides of the (6) outside the cabin doors (5), the water is approximately passenger cabin (6). The cargo hold (21) and the fuse- 0.4~1.0 meter deep, and the cabin doors (5) can not be lage empennage (16) that can rotate around the rotating 30 opened for the purpose of safety; because the cabin shaft (18) is arranged at the rear of the fuselage (7); the doors (5) are designed and manufactured for structure vertical lift propeller device (58) is arranged at both ends strength and rigidity to withstand 0.5~0.6 atmospheric of the cargo hold (21), and the device is mainly for ma- pressure from boththe inside andthe outside of thecabin, nipulating in-shore, off-shore and steering of the aircraft both the cabin doors (5) and the cabin windows (36) are when the aircraft is landed on water (with more details 35 watertight. Above the seat (22) is the luggage compart- found in Figures 27 to 34). Because the longitudinal sec- ment (29). At the very end of the passenger cabin (6) is tion of the fuselage (7) matches the section shape of the the food serving compartment (12) and the rest room airfoil, and the fuselage (7) is wider and larger than the (11), and their locations and the circular corridor in the airfoil, when the aircraft of this invention flies forward as passenger cabin (6) are designed in favor of the conven- propelled by the engine (30), the fuselage (7) may gen- 40 ience of the service by the stewardess as well as the use erate elevating force greater than that generated by the by the passengers. The arc external wall in front of the airfoil. In contrast, the existing aircraft is unable to gen- fuselage (7) is the outcome of the front shape of the airfoil, erate elevating force due to its cylindrical shaped fuse- and the rear arc wall of the food serving compartment lage. To analyze comprehensively, the aircraft of this in- (12) and the rest room (11) is designed for meeting the vention may improve the flight efficiency by about45 special requirement of bearing the swelling effect under 30~40% than the existing civil airliner with the same 0.5~0.6 atmospheric pressure. As the aircraft of this in- number of seats and flight mileage, which is equivalent vention is designed for landing close to the ground of the to reducing the fuel consumption as well as air pollution airport, no airstairs is necessary and the passengers can by 30~40%. board with the convenience and swiftness as boarding a [0017] It is obvious from figure 2 that the fuselage of 50 bus; furthermore, because the aircraft of this invention the aircraft of this invention (7) has longitudinal section intends to function as a floatplane that can land on water, as that of the airfoil section; the control mode of the front the engine (30) can not be suspended beneath the airfoil undercarriage (4) and the MLG (9) is different from that as in the existing aircraft; instead, it is mounted above of the existing aircraft in that the existing aircraft uses the rear fuselage (7). Still, the fuselage empennage (16) rotational mechanism; however, the fuselage (7) of the 55 can be rotated around the rotating shaft (18) behind the aircraft of this invention has the space that is large cargo hold (21); when the aircraft of this invention takes enough for accommodating the vertical retractable un- off and lands on the runway, the fuselage empennage dercarriage; in addition, the fuselage (7) is flat; and the can bend upward to function as the flat empennage while

5 9 EP 2 404 826 B1 10 reducing the risk of the fuselage empennage (16) being invention. The upper surface of the fuselage (7) has two rubbed against the ground, which is helpful for increasing top cabin doors (37) in the front, which serves for board- the angle of attack during the take off; when the aircraft ing passengers into the passenger cabin (6) as this air- of this inventiontakes off and lands on water,the fuselage craft lands as a floatplane in the harbor airport (52); and empennage can bend upward, for downward pressing of 5 two top exits (38) are arranged next to the engine (30) the rear fuselage (7) under the effect of the water current, for an emergency evacuation when this aircraft functions while the front side develops the angle of attack for taking as a floatplane. off upward. In this figure, the passengers are coming into [0021] Figure 6 is the side view of the aircraft of this the passenger cabin (6) in succession. invention during parking and preparing to takeoff from [0019] As illustrated in figure 4, when the aircraft of this 10 the airport, when the front undercarriage (4) and MLG invention stays close to the ground, the ground clearance (9) extend to the technical height for the ground clearance of the bottom of the passenger cabin (6) is about 0.2 of the fuselage (7). The airfoil (8) is mounted on the airfoil meter, and the ground clearance of the floor of THE pas- assembly center (34) on the top central part of the fuse- senger cabin (6) is about 0.32~0.36 meter; hence the lage (7). The figure also illustrates the locations of the passengers may board the aircraft without the airstairs 15 cabin door (5), the cabin window (36) and the cargo hold with the convenience and swiftness as boarding the bus. door (13), which are the traffic doors for the passengers The flat shaped passenger cabin (6) is separated by the entering the cabin (6) and the cargo hold (21). columns (23) into two symmetric and matching left and [0022] Figure 7 is the front view of the exterior of the right compartments, wherein the seats (22), the luggage aircraft of this invention. Due to the width of the fuselage compartment (29) and the aisle are arranged exactly the 20 (7), the front undercarriage (4) and the MLG (9) are not same. Because the passenger cabin (6) needs to stand required to be mounted on the base of the airfoil (8). the swelling force under 0.5~0.6 atmospheric pressure, [0023] Figures 8, 9 and 10 represent longitudinal view the transverse framework (39) on both sides of passen- of the aircraft of this invention respectively of second- ger cabin is in the form of the arc wall, and one row of compartment, third-compartment and fourth-compart- columns (23) are set along the longitudinal center line of 25 ment passenger cabins (6) at the location of the MLG the flat shaped passenger cabin (6), so as to reduce the (9). Because the fuselage (7) is flat shaped, wide and structure span of the transverse framework (39) of the tall, the MLG bay (10) can be directly placed in the pas- passenger cabin. In addition, for further reduction of the senger cabin (6), and at the same time the aircraft is structure span and improvement of the structure stress, stably supported by the main undercarriage (9) and the and for reduction of the structure bending moment for 30 front undercarriage (4). The main undercarriage (9) is reducing the structure weight of the fuselage (7), and for mounted in the MLG bay (10), and the top of the main making use of the upper space within the luggage com- undercarriage is connected with the airfoil assembly partment (29) and the space beneath the seats (22), the center (34); and the fuselage (7) is also tightly connected oblique struts (24) are added on the upper and the lower with the airfoil assembly center (34); hence, the airfoil ends of the arc walls on both sides of the columns (23) 35 assembly center (34) serves the dual functions of rein- and both sides of the transverse framework (39) of the forcing the strength and rigidity of the overall structure of passenger cabin. As illustrated in figure 1, if the design the fuselage (7). The airfoils (8) are mounted on both adopts equal spacing of the longitudinal arrangement of sides of the airfoil assembly center (34). The large space the transverse framework (39) of the passenger cabin on top of the passenger cabin (6) makes it impossible for (6) and of the seats (22), and the seats (22) are arranged 40 the MLG bay (10) not bulging from the fuselage (7), hence along both sides of the center line of the transverse it will not interfere with the normal form of the fuselage framework (39) of the passenger cabin, the seats (22) (7) as a lifting body, i.e. it will not reduce the elevating installed in this manner do not impact the comfort of the force of the fuselage (7) in flight. In this figure, the main passengers; and those in the passengers cabin (6) can undercarriage (9) is at its maximal vertical extension, and not view the oblique trusts (24) hidden underneath the 45 the status of the aircraft of this invention is at parking or seats (22) and in the luggage compartment (29); hence ready for takeoff. The figure shows that the full load of the inner view in the passenger cabin is as aesthetic as the aircraft is transferred to the ground directly via the that of the civil airliner. Furthermore, with protection of main undercarriage (9); the path for the force transfer is the inward oblique arc wall, the passengers in the far- simple, and is advantageous for reducing the aircraft thermost seats on both sides of the passenger cabin (6) 50 structure weight while maintaining the structure strength are prevented from the head collisions like that of the civil and rigidity of fuselage (7). airliner. Besides, the inward oblique arc wall within the [0024] In figure 11, the third-compartment passenger existing aircraft limits the luggage compartment (29) to cabin (6) is used as an example to illustrate the structure be just enough for the small trunks; in contrast, the lug- characteristics of the transverse framework (39) of the gage compartment (29) of the aircraft of this invention is 55 passenger cabin of the aircraft of this invention (second- spacious and allows for storage of luggage of sufficient compartment and forth-compartment are mainly the size. same as the third-compartment passenger cabins). The [0020] Figure 5 is the top view of the aircraft of this third-compartment passenger cabin is equivalent to the

6 11 EP 2 404 826 B1 12 horizontal assembly of the transverse section of the fu- gitudinal section of the fuselage (7) matches the foilage selage of an existing A320 airliner (single aisle with three section, and its front is in arc shape; as the common rear seats installed on both sides, which is the most economic wall of the cargo hold (21) and the passenger cabin (6) and practical layout) with the elimination of the cargo hold is constructed as an arc wall, the passenger cabin (6) previously underneath the passenger cabin. When the 5 composed of longitudinal members of transverse frame- existing civil airliner cruises at more than 10,000 meters workof thepassenger cabin (39) and fuselage framework in the sky, where the air is thin at only 0.2~0.3 atmos- (41) can withstand 5 ∼6 ton/square meters outward force. phericpressure (namely, 0.2~0.3atm), ifthe atmospheric [0026] Figures 12 and 13 are the layout plan and the pressure in the cabin is the same, the passengers will side view of an embodiment of the fuselage (7) for the feel hard to breathe and their lives are at danger. For 10 aircraft of this invention (four-compartment, equivalent easy breath, at least 0.8 atm is required for the passenger to an A-380 airbus). In the figure, the passenger cabin cabin (6); and the passenger cabin (6) is inflated by a (6) is arranged as four compartments, and more than 800 mechanical equipment. To this end, the structure of the seats (22) can be arranged within one floor. Four longi- passenger cabin (6) must withstand the swelling force of tudinal aisles of the four-compartment and several trans- 0.5∼0.6 differential atmospheric pressure between the 15 verse aisles directly connecting to the cabin door (5) form inside and the outside of the cabin; namely, the passen- the convenient, circular and safe passages. Due to the ger cabin (6) casing is subject to 5∼6 ton/square meter heavy weight of the aircraft, four main undercarriages (9) pressure; this is the principal reason for which the fuse- are set; as the fuselage (7) is flat shaped and wide, the lagesection of theexisting aircraftis designedto be round four main undercarriages (9) can be arranged in a line; shaped. Still, round fuselage section of the existing air- 20 this way, the four main undercarriages (9) are subject to craft brings about many unavoidable disadvantages. loading or unloading concurrently during takeoff and Thus remarkably improved performance of the existing touchdown for uniform loading; the four MLGs (9) are of civil airliner relies upon the radical breakthrough and im- identical type (the A-380 airbus MLGs mounted under- provement in its structure configurations. neath the fuselage or the airfoil base are of different [0025] The success of the aircraft of this invention de- 25 heights, thus MLGs of two types are needed). Due to the pends ultimately upon its ability of bearing 5 ∼6ton/square single floor arrangement of the passenger cabin (6) with meters outward force on its casing structure of the flat the cargo hold (21), the undercarriages can be retracted shaped passenger cabin (6). To this end, first, both sides before landing on the ground; this is much more conven- of transverse framework of the passenger cabin (39) ient for the final assembly and the adjusting of the various must not be manufactured as flat planes, but rather as 30 systems, and it shortens the manufacturing cycle and bulging arc surfaces instead, which is similar to the ex- reduces the manufacturing cost. isting airliner; because the linear size on both sides of [0027] Figures 14 to 17 are the the aircraft of this in- passenger cabin is identical (6), the practice of opening vention in the process of from landing on the ground of cabin door (5) and cabin window (36) on the arc wall on the airport to takeoff. both sides of the passenger cabin (6) is completely iden- 35 [0028] In figure 14, MLGs (9) are compressed until the tical as the existing aircraft. Then, columns (23) are add- ground clearance of the fuselage underplate is of approx- ed in the transverse framework (39) of the passenger imately 0.2 meter; the fuselage (7) is landed close to cabin to reduce the transverse span of the flat cabin (6); ground; no traditional airstairs are necessary; and the it is not enough by merely adding columns (23), and the passengers can board on and off the aircraft like a bus. oblique trusts (24) should be added on the upper and 40 This figure shows the passengers boarding on the air- lower sides of columns (23). The length projection of the craft. oblique trusts (24) is approximately 1/3 (approximately [0029] In figure15, all passengers are on board, and 1.2∼1.3 meter) of each span of the transverse framework the aircraft can take off; both the front undercarriages (4) of the passenger cabin (39); and the height of the oblique and the MLGs (9) vertically extend simultaneously until trusts (24) under the columns (23) is approximately the 45 the fuselage (7) rise to a given height, indicating readi- space (approximately 0.3~0.35meter) underneath the ness for takeoff. seat (22); and the height of the oblique trusts (24) above [0030] In figure 16, jet engine (30) starts to jet; together the columns (23) is not more than the upper space on with the action of the flat empennage (32), the front un- top of the luggage compartment (29). So each span of dercarriage(4) is cleared fromthe ground; and the aircraft the passenger cabin (6) can be considered as an octag- 50 of this invention glides on the runway and is at takeoff onal structure, which is much better than a rectangular mode. structure in withstanding stress; though it is slightly less [0031] In figure 17, jet engine (30) continues jetting; optimal than an oblong structure, it approximates an ob- and the angle of attack increases with the action of the long structure; as the three compartments are tightly cou- flat empennage (32); both the front undercarriages (4) pled through the airfoil assembly center (34) above the 55 and the MLGs (9) are cleared from the ground, and the passenger cabin (6), the structure strength and rigidity aircraft of this invention is at flight mode. of the transverse framework of the passenger cabin (39) [0032] After several minutes, the front undercarriages as an integral whole are reinforced substantially. The lon- (4) retract into the front undercarriage bay (3), and the

7 13 EP 2 404 826 B1 14

MGLs (9) retract into the MLG bay (10); then the front gear (45) driven by the shaft (48) of the fuel-oil engine and the rear sliding doors (33) start to slide simultane- (14), the propeller (15) rotates reversely to drive water ously to close the front undercarriage bay (3) and the flow reversely, so as to generate the reverse force for MLG bay (10); and the aircraft of this invention is at the the aircraft on water. When the propeller (15) rotates in cruise mode. 5 water, the pilot may control the two vertical lift propeller [0033] Figures 18 to 21 are the structure and the op- devices (58) mounted at both rear corners of the cargo erational mechanisms of the vertical lift propeller device hold (21); only by controlling the orderly up-and-down (58). When the aircraft of this invention functions as a movement of the piston (50) in the small hydraulic cylin- floatplane by landing on water, it needs to control the der (44) in the two stationary gearboxes (20) can the pilot landing, steering and departure with the vertical lift pro- 10 control the advance, backward and left-right steering of peller device (58) in a harbor airport. the aircraft of this invention on water in the harbor airport. [0034] In Figure 18, the propeller (15) retracts into the [0038] Figures 22 to 26 are the aircraft of this invention propeller chamber (19); the front and rear sliding doors in the process of from landing on water to cruise flight (33)close thepropeller chamber (19)in the samemanner above water; during the process both the front and the as closing the front undercarriage bay (3) and the MLG 15 rear sliding doors (33) of the front undercarriages bay (3) bay (10), so as to decrease the atmospheric drag in flight. and the MLG bay (10) are closed. The fuel-oil engine (14) on the mounting base (57) in the [0039] In Figure 22, all passengers within the airport cargo hold (21) drive the bevel gear (45) and the loose walk into the cabin (6) in order. bevel gear (47) through the coupling (62) and the shaft [0040] In Figure 23, all passengers are boarded in the (48); at the center of the loose bevel gear (47) are the 20 cabin (6); the top cabin door (37) is closed; the pilot con- hexagonal holes with the hexagonal shaft (42) fitting in; trols the two vertical lift propeller devices (58) mounted a small hydraulic cylinder (44) mounted on the stationary in the cargo hold (21) according to the sequence require- gearbox (20) pushes and pulls the steering sleeve (17) ment; the aircraft departs and steers, and is ready for via the piston (50), so that both the loose bevel gear (47) takeoff. simultaneously move up and down with the hexagonal 25 [0041] In figure 24, the jet engine (30) starts to jet; the shaft (42); but only one loose bevel gear (47) (the lower pilot controls the fuselage empennage (16) for the up- loose bevel gear as shown in the figure) drives the hex- wardmovement; when theaircraft of thisinvention moves agonal shaft (42) and drives the two bevel gears (45) forward, the fuselage (7) front-side faces upward for tak- mounted in the moveable gearbox; then the bevel gear ing off from water. (45) drives the propeller (15) to rotate via the shaft (48). 30 [0042] In figure 25, the aircraft of this invention takes In contrary, the large hydraulic cylinder (44) mounted in off from water and flies forward by the driving force of the the stationary gearbox (20) is coupled to the casing of jet engine (30) and the ground effect. the moveable gearbox (49) via the piston (50), and the [0043] In figure 26, the aircraft of this invention makes moveable gearbox (49) moves up and down against the cruise flight 4~12 meter above water by the driving force stationary gearbox (20) fixed on the fuselage framework 35 of the jet engine (30) and the ground effect; due to the (41) with the locking bolts (46). ground effect, 5~10% less aviation oil is consumed than [0035] Figure 19 is the E-E sectional view of the move- flying at 10,000 meter in the sky. Again, as the floatplane able gearbox (49), illustrating that the bevel gears (45) always flies 4-12 meter above water, the passengers drives the propeller (15) to rotate via the shaft (48). tend to feel safer than during a flight at 10,000 meter in [0036] Figure 20 is F-F sectional view of the stationary 40 the sky. However, calm weather is the precondition, to- gearbox (20), illustrating that the shaft (48) of the fuel-oil gether with a visibility of more than several kilometers engine (14) drives the bevel gear (45) and the loose bevel and few vessels in the sea, thus it is particularly suitable gear (47) to rotate; at the center of the loose bevel gear for airliner flying across oceans (pacific ocean, Atlantic (47) are the hexagonal holes with the hexagonal shaft and etc). In the case of a sudden foul weather during the (42) fitting in; the piston (50) is in the hydraulic cylinder 45 flighton the sea, theaircraft ofthis invention may increase (44). the driving force of the jet engine (30) and ascend the [0037] In figure 21, the front and the rear sliding doors flat empennage (32), so that the aircraft can ascend to (33) slide forward to open the lower opening of the pro- 10,000 meter in the sky for the cruise flight as the existing peller chamber (19); the large hydraulic cylinder (44) ex- civil airliner. tends downward via the piston (50), so as to extend the 50 [0044] Figures 27 to 34 are the aircraft of this invention moveable gearbox (49), the hexagonal shaft (42) and the (two-compartment passenger cabin) in the process of propeller (15) into water out of the propeller chamber from landing in airport to departure. (19); if the fuel-oil engine (14) is started at this moment, [0045] In figure 27, the aircraft of this invention lands the propeller (15) rotates and drives water flow, so as to in the wharf (54) of the airport (52); the passengers within drive the aircraft on water. When the small hydraulic cyl- 55 the airport walk into the passenger cabin (6) through the inder (44) drives the steering sleeve (17) to move down- top cabin door (37); as the opening of top cabin door (37) ward through the downward extension of the piston (50), is toward the sky, and to avoid rainwater from entering so that the loose bevel gear (47) above contacts the bevel into the passenger cabin (6), the rain shed (55) of the

8 15 EP 2 404 826 B1 16 airport (52) needs a large cantilever span; hence the outside of the cargo hold (21), cargo hold doors (13) are wharf (54) needs to set the roof strut (53) for the rain not to be opened on both sides of the cargo hold (21) ; shed (55). the aircraft of this invention loads and unloads cargo on [0046] Figure 28 is the top view of the aircraft of this water by the overhead crane in the airport (52), simply invention slowly approaching the airport driven by the 5 by opening the lifting hole (59) on the top of the cargo two vertical lift propeller devices (58). hold (21). [0047] Figure 29 is the top view of the aircraft of this [0058] In figure 36, the aircraft of this invention loads invention landing in the wharf (54) of the airport (52) after and unloads cargo on water by overhead crane in the the two vertical lift propeller devices (58) are closed. airport (52), simply by opening the lifting hole (59) on the [0048] Figure 30 is the top view of the aircraft of this 10 top of cargo hold (21). And the crew can access from the invention departing from the airport for a given distance top passenger cabin door (37) on the upper door of the after starting the two vertical lift propeller devices (58). fuselage (7). [0049] Figures 31 to 32 are the top views of the two [0059] Figure 38 to 41 are an embodiment of the air- vertical lift propeller devices (58) of the aircraft of this craft of this invention functioning as a land cargo aircraft. invention steering above water after departing from the 15 [0060] In figure 38, due to the heavy load of the cargo, airport for a given distance, with the right vertical lift pro- four MLGs (9) are required to be assembled. To obtain peller device driving forward and the left one dragging a spacious interior of the cargo hold (21) for easier load- backward. ing and unloading cargo, two MLGs (9) are mounted on [0050] Figure 33 is the top view of the aircraft of this both sides respectively, and the longitudinal arrange- invention steering away from the airport (52) on water 20 ment of the MLGs is against both sides of the cargo hold and ready for departure. (21). To achieve convenient handling of bulky cargo, both [0051] Figure 34 is the top view of the aircraft of this the front and the rear ends of the cargo hold (21) can invention departing from the water driven with the started ascend to divide the cargo hold (21) into three sections, jet engine (30) jetting; and the aircraft takes off from water and two cargo hold opening/closing slots are set on the as being propelled by the jet engine (30). 25 floor of the cargo hold (61). [0052] Figures 35 and 37 are the embodiments of the [0061] In figure 39, in order to load the container into aircraft of this invention (amphibious aircraft) functioning the cargo hold (21), first prop up the rear side of the cargo as the amphibious cargo aircraft; the three drawings il- hold (21) with the hydraulic cylinder (44); then adjust the lustrate the states of the aircraft in use when landed in height of the front undercarriage (4) and the MLG (9) until the airport. 30 the floor of the cargo hold (21) is as high as the cargo [0053] In figure 35, most of the configuration layout is floor of the container car, so that the container is easily identical with the current amphibious aircraft; as the car- moved into the cargo hold. go aircraft does not carry passengers, the cargo hold (21) [0062] In figure 40, in order to allow the convenient needs no inflation; thus the fuselage framework (41) of movement of the moveable equipments such as the load- the cargo hold (21) does not need to withstand the out- 35 ing trucks to and from the cargo hold (21), the aircraft of ward force, leading to the low load of the fuselage frame- this invention can land closely to the ground; then prop work (41); no additional column (23) is necessary for re- up the front and the rear of the cargo hold (21) to ascend inforcing the cargo hold (21). However, for the pilot to around the rotating shaft (18) with the hydraulic cylinder obtain the easy breath in the pilot compartment (1), con- (44); then retract the hydraulic cylinder (44) after access sideration should be given to the structure against out- 40 of the loading truck, close the cargo hold opening/closing ward force in the pilot compartment (1). While in service slot (61), and cargo hold (21) returns to its previous state. at the airport, loading and unloading cargo can begin with [0063] In figure 41, the cargo is loaded, with the hy- opening the cargo hold doors (13) on both sides. draulic cylinder (44) retracted; the cargo hold open- [0054] In figure 36, when the MLGs (9) and the front ing/closing slot (61) is closed and the cargo hold (21) is undercarriages(4) arecompressed to theidentical height 45 returned to its previous state; the front undercarriage (4) of a cargo floor of a truck, cargo can be handled to and and MLG (9) retract simultaneously; and the aircraft of from the cargo hold door (13). The lifting hole (59) on the this invention as a land cargo aircraft is ready for depar- top of the cargo hold (21) is applicable when the aircraft ture. of this invention functions as a floatplane; when in use, [0064] Figures 42 to 44 are another embodiment of the it needs to open the front and rear sliding doors (33). 50 aircraft of this invention (equivalent to a A380 airliner, [0055] Figure 37 shows the retracted undercarriages open-V empennage, amphibious aircraft) functioning as of the aircraft at the airport ready for departure. an amphibious aircraft and passenger-cargo plane, with [0056] When the aircraft of this invention serves as a the characteristics that the custom-made adjustable area cargo aircraft for loading cargo on water, the above three ratio of the passenger cabin and the cargo hold during drawings should have the following variations. 55 the ordering and manufacturing is requested by the client, [0057] In figure 35, both the MLG bay (10) and the front so that flexible business operation is available for the undercarriage bay (3) are closed by the front and rear airlines; the airlines may load more cargo during reces- sliding doors (33) ; as water of certain depth is at the sion of passengers and vice versa; in either

9 17 EP 2 404 826 B1 18 case it is helpful for reducing the no-load ratio. plane crash and casualty. However, if U-groove (63) is [0065] In figure 42, due to the wide fuselage (7), an added at the structure intersection of the transverse open-V empennage like that of a fighter plane can be framework of the passenger cabin( 39), with strip air incorporated. cushion (66) filled in, the undercarriages is not required [0066] In figure 43, with regards to the general plan of 5 to be released in the event of emergency; the strip air the fuselage (7), the area distribution of the passenger cushion (66) is inflated by opening the valve of the com- cabin and the cargo hold is approximately half and half; pressed air tank in the aircraft; the strip air cushion (66) for the cargo hold (21) is large in area, four cargo hold immediately swell and automatically blow out the under- doors (13) are opened for improving the loading and un- plate (64) in the snap slot (65) of the U-groove (63); and loading rate of the cargo. The arc wall between the pas- 10 many strip air cushions are developed underneath the senger cabin (6) and the cargo hold (21) also moves for- aircraft external panels (67); the length of the strip air ward to the location of the MLG bay (10). There is no cushions (66) can span from the front undercarriage bay bulging stress inside the cargo hold (21) as that in the (3) to the fuselage empennage (16). In this way, forced passenger cabin, so only a few columns (23) are set for landing in an emergency is available on a flat field; due reducing the structure weight; or no column (23) is set 15 to the flat shaped fuselage and the protection of the strip for the purpose of convenient loading and unloading of air cushions (66), the impact of the ground against the the cargo; the option is up to the discretion of the client. aircraft can be buffered substantially, so as to minimize [0067] In figure 44, the arc wall between the passenger the tragedy of the passengers and crew. cabin (6) and the cargo hold (21) is at the location of the [0072] Figure 52 is the enlarged structure drawing of MLG bay (10); the area distribution of passenger cabin 20 the U-groove. Usually, the underplate (64) in the snap (6) and cargo hold (21) is approximately half and half; slot (65) of the U-groove (63) supports the strip air cush- and other aspects are identical to those of figure 12 to 13. ions (66) to prevent the cushions from falling. Although [0068] Figure 45 is an embodiment of an aircraft not in the aircraft weight is increased with the strip air cushions accordance with the invention (equivalent to A380 airlin- (66), the aircraft of this invention, however, has no inflat- er, for land use only) and only functioning as a land air- 25 able slide as that of the existing aircraft; it is estimated craft, which is used as a large passenger aircraft as the that the weight of the strip air cushions (66) may not ex- existing civil airliner; the jet engine (30) is suspended ceed that of the common inflatable slide; thus it is worth- underneath the airfoil (8) like that of the existing civil air- while to have the cushions that provide safe protection liner; because the jet engine (30) lower edge is lower for the passengers and crew during a forced landing on than the underplate of the fuselage (7), the aircraft can 30 the ground. not be landed on the ground; instead, it can only be land- [0073] Figure 53 is the transverse sectional view of the ed with the overhead undercarries similar as the existing aircraft of this invention (three-compartment passenger civil airliner, and the airstairs are necessary for boarding cabin) in the case of a forced landing in an emergency; and landing. when the strip air cushions (66) are opened to buffer the [0069] Figures 46 to 48 are dimensional comparison 35 impact of the ground against the aircraft, injury of pas- drawings of the aircraft of this invention (equivalent to sengers and crew in the case of accident is minimized. A380 airliner, amphibious aircraft) and the updated A- [0074] Figure 54 is the side view of the aircraft of this 380 airbus. It is obvious from the figure that the fuselage invention (three-compartment passenger cabin) in the length, wingspan and height of the large aircraft of this case of forced landing in an emergency; some strip air invention are approximately 25~30% less than those of 40 cushions (66) may fail due to the piercing by the sharp the A-380 airbus. edges on the ground during landing; to keep as many [0070] Figures 49 to 50 are the comparison drawings strip air cushions (66) from piercing as possible, strip air of the enlarged front view of the windward area of the cushions (66) are preferred to be at shortened length and large aircraft of this invention (equivalent to A380 airliner, to be provided in greater quantity. If the traditional para- amphibious aircraft) and the updated A-380 airbus. It is 45 chutes are placed near the rear cargo hold (21), and the obvious from the figure that the front view of windward parachutes are simultaneously released with the strip air area of is approximately 10~13% less than that of the A- cushions (66) in the case of the forced landing in an emer- 380 airbus; hence, the atmospheric drag of the aircraft gency, the aircraft may be further slowed down by the of this invention is 10~13% less than that of the A-380 inflated parachutes; with the combined action of the strip airbus. 50 air cushions (66) and the parachutes, impact of the [0071] Figure 51 is the enlarged sectional view of the ground against the aircraft is buffered further for mini- transverse framework of the passenger cabin (39) with mized tragedy of the passengers and crew in the acci- the U-groove of the aircraft of this invention (three-com- dent. partment passenger cabin). In an case of the breakdown of the jet engine (30) during a flight resulting in lack of 55 dynamics, or in the case of the failure of releasing un- Claims dercarriages, if there is no broad water area for forced landing in an emergency, distress landing may cause 1. An amphibious aircraft without airstairs which com-

10 19 EP 2 404 826 B1 20 prises: ing of the propeller chamber (19) into the water. a fuselage (7), one or more airfoils (8), one or more empennages (16), a plurality of engines 2. An amphibious aircraft as claimed in claim 1, wherein (14, 30), a plurality of undercarriages (4, 9) and 5 the fuselage (7) is flat and oblong shaped in the lon- a plurality of propeller devices (58), wherein: gitudinal plane; the pilot compartment (1) protrudes from a middle section of the fuselage (7); a lower the fuselage (7) is flat and oblong shaped part of the fuselage (7) serves as the passenger cab- and comprises a passenger cabin (6), a pilot in (6) with upper space for the comfort of the pas- compartment (1) and a cargo hold (21); 10 sengers; a middle top section above the passenger thepilot compartment (1) protrudes from the cabin (6) comprises an assembly center (34) for the fuselage (7) and the passenger cabin (6) one or more airfoils (8) on the top central part of the and cargo hold (21) are located at the same fuselage (7); a gradually lower space in a rear part floor in the aircraft; of the fuselage (7) serves as the cargo hold (21) and a cross-sectional shape of the fuselage (7) 15 the fuselage empennage (16); the fuselage empen- resembles a cross-sectional shape of the nage (16) can up and down around a rotating one or more airfoils (8); shaft (18) behind the cargo hold (21); both sides of the one or more airfoils (8) extend to two the fuselage (7) are arc planes; the passenger cabin sides from a top central part of the fuselage (6) is divided by flat transverse frameworks (39) into (7); 20 several passenger compartments with columns (23); a jet engine (30) of the one or more engines upper and lower parts and both sides of columns (14, 30) is mounted on the rear of the fuse- (23) are reinforced by oblique struts (24) in a luggage lage (7) near an empennage (16) of the one compartment (29) and space underneath the seats or more empennages (16); (22); arc frameworks in the transverse framework all of the undercarriages (4) are mounted in 25 (39) of the passenger cabin (6) are reinforced with the fuselage (7); the oblique struts (24) at the identical position of the two front undercarriage bays (3) and sever- arc wall on both sides of the fuselage (7); the average al main landing gear bays (10) are mounted projection length of the oblique struts (24) in the var- in the passenger cabin (6) of the fuselage ious compartments of a passenger cabin cell is 1/3 (7); 30 the span of said passenger cabin cell; the longitudi- front undercarriages (4) of the one or more nal framework of the front and rear passenger cabin undercarriages (4) are mounted within the (6) is a protruding arc shape; the interspacing of the front undercarriage bays (3); transverse frameworks (39) of the passenger cabin main landing gears (9) are mounted within (6) is arranged to be the same as that of the seats the main landing gear bays (10); 35 (22) along the longitudinal direction of the passenger all of the front undercarriages (4) and the cabin (6); and all rows of seats (22) in the passenger main landing gears (9) are vertically retract- cabin (6) are aligned with the transverse frameworks able; (39) of the passenger cabin (6), and mounted longi- all of the front undercarriage bays (3) and tudinally in the center by passing across the corre- the main landing gear bays (10) are mount- 40 sponding oblique struts (24). ed with front and rear sliding doors (33); each of the propeller devices (58) compris- 3. An amphibious aircraft as claimed in the claim 1, es a fuel-oil engine (14) of the plurality of wherein the propeller device (58) further comprises engines (14, 30), a stationary gearbox (20), a first and a second hydraulic cylinder (44) fixed on a moveable gearbox (49), and a propeller 45 a top casing of the stationary gearbox (20), wherein (15); the first hydraulic cylinder (44) is larger than the sec- the propeller devices (58) are located in a ond hydraulic cylinder (44); a piston (50) of the first propeller chamber (19) at each of the two hydraulic cylinder (44) is connected to the top of the rear corners of the fuselage (7) inside the moveable gearbox (49); the piston (50) of the second cargo hold (21); 50 hydraulic cylinder (44) is connected to the top of a each propeller chamber (19) is mounted steering sleeve (17); double slots of the steering with front and rear sliding doors (33) which sleeve (17) are encased in one upper loose bevel in use, when the aircraft functions as a float- gear (47) and one lower loose bevel gear (47), of plane on water, slide forward to open a low- which one of the upper and lower loose bevel gears er opening of the propeller chamber (19); 55 (47) meshes with a respective bevel gear (45) at all and times; a shaft of the bevel gear (45) runs across the each moveable gearbox (49) and propeller stationary gearbox (20) and the fuselage framework (15) are extendable through the lower open- (41) and is connected with the fuel-oil engine (14)

11 21 EP 2 404 826 B1 22

by coupling; the upper and lower loose bevel gears mehreren Motoren (14, 30) auf der Rück- (47) and four plates of the steering sleeve (17) are seite des Rumpfes (7) in der Nähe eines passed through by the center hexagonal shaft (42) Leitwerks (16) des einen oder der mehreren of the moveable gearbox (49); and the hexagonal Leitwerke (16) montiert ist; shaft (42) runs across an upper and a lower casing 5 all die Fahrgestelle (4) bei dem Rumpf (7) of the stationary gearbox (20) straight through a hole montiert sind; on the top surface of the fuselage (7). zwei vordere Fahrgestellräume (3) und mehrere Hauptfahrwerkräume (10) in der 4. An amphibious aircraft as claimed in claim 3, wherein Passagierkabine (6) des Rumpfes (7) mon- the two bevel gears (45) in the moveable gearbox 10 tiert sind; (49) are vertically connected; wherein the shaft (48) vordere Fahrgestelle (4) des einen oder der of the vertically mounted bevel gear (45) extrudes mehreren Fahrgestelle (4) in den vorderen from the moveable gearbox (49) and connects with Fahrgestellräumen (3) montiert sind; the propeller (15); the hexagonal shaft (42) above Hauptfahrwerke (9) in den Hauptfahrwer- the horizontal bevel gear (45) runs across the casing 15 kräumen (10) montiert sind; of the stationary gearbox (20) and the hexagonal alle der vorderen Fahrgestelle (4) und der holes at the center of the upper and lower loose bevel Hauptfahrwerke (9) vertikal zurückziehbar gears (47); and the top surface of the moveable gear- sind; box (49) is connected with the piston (50) of the first alle der vorderen Fahrgestellräume (3) und hydraulic cylinder (44). 20 der Hauptfahrwerkräume (10) mit vorderen und hinteren Gleittüren (33) montiert sind; 5. An amphibious aircraft as claimed in claim 2, wherein jede der Propellervorrichtungen (58) einen one or more U-grooves (63) with snap slots (65) are Schwerölmotor (14) der mehreren Motoren set at the intersection of a bottom frame of the trans- (14, 30), ein stationäres Getriebegehäuse verse framework (39) of the passenger cabin (6) with 25 (20), ein bewegbares Getriebegehäuse the columns (23) and the frameworks along the arc (49) und einen Propeller (15) umfasst; sections on both sides; underplates (64) are mount- diePropellervorrichtungen (58) in einerPro- ed in the snap slots (65); and air cushions (66) are pellerkammer (19) an jeder der zwei rück- mounted within the U-grooves (63) and are support- seitigen Ecken des Rumpfes (7) in dem ed by the underplates (64). 30 Frachtraum (21) angeordnet sind; jede Propellerkammer (19) mit vorderen und hinteren Gleittüren (33) montiert ist, Patentansprüche welche im Betrieb, wenn das Flugzeug als ein Schwimmerflugzeug auf Wasser fun- 1. Amphibienflugzeug ohne Passagiertreppe, welches 35 giert, nach vorn gleiten, um eine untere Öff- umfasst: nung der Propellerkammer (19) zu öffnen; und einen Rumpf (7), eine oder mehrere Tragflächen jedes Getriebegehäuse (49) und jeder Pro- (8), ein oder mehrere Leitwerke (16), mehrere peller(15) durch dieuntere Öffnung der Pro- Motoren (14, 30), mehrere Fahrgestelle (4, 9) 40 pellerkammer (19) in das Wasser ausfahr- und mehrere Propellervorrichtungen (58), wo- bar ist. bei: 2. Amphibienflugzeug nach Anspruch 1, wobei der der Rumpf (7) flach und länglich geformt ist Rumpf (7) flach und länglich in der Längsebene ge- und eine Passagierkabine (6), eine Piloten- 45 formt ist; wobei die Pilotenkabine (1) von einem Mit- kabine (1) und einen Frachtraum (21) um- telabschnitt des Rumpfes (7) hervorragt; wobei ein fasst; unterer Teil des Rumpfes als die Passagierkabine die Pilotenkabine (1) von dem Rumpf (7) (6) mit einem oberen Raum für den Komfort der Pas- hervorragt, und die Passagierkabine (6) sagiere dient; wobei ein mittlerer oberer Abschnitt und der Frachtraum (21) auf derselben Eta- 50 oberhalb der Passagierkabine (6) eine Anordnungs- ge in dem Flugzeug angeordnet sind; mitte (34) für die eine oder die mehreren Tragflächen eine Querschnittsform des Rumpfes (7) ei- (8) auf dem oberen Mittelteil des Rumpfes (7) um- ner Querschnittsform der einen oder der fasst; wobei ein graduell unterer Raum in einem hin- mehreren Tragflächen (8) ähnelt; teren Teil des Rumpfes (7) als der Frachtraum (21) sich dieeine oder diemehreren Tragflächen 55 und das Rumpfleitwerk (16) dient; wobei das (8) von einem oberen mittigen Teil des Rumpfleitwerk (16) um eine Drehwelle (18) hinter Rumpfes (7) zu zwei Seiten erstrecken; dem Frachtraum (21) herum nach oben und nach ein Strahlmotor (30) des einen oder der unten klappen kann; wobei beide Seiten des Rump-

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fes (7) gebogene Ebenen sind; wobei die Passagier- Kegelgetriebe (45) in dem bewegbaren Getriebege- kabine (6) durch flache Querrahmen (39) in mehrere häuse (49) vertikal verbunden sind; wobei die Welle Passagierabteilungen mit Gestellen (23) geteilt ist; (48) des vertikal montierten Kegelgetriebes (45) von wobei obere und untere Teile und beide Seiten der dem bewegbaren Getriebegehäuse (49) hervorragt Gestelle (23) durch schräge Streben (24) bei einem 5 und mit dem Propeller (15) verbunden ist; wobei die Gepäckabteil (29) und einem Raum unterhalb der hexagonale Welle (42) oberhalb des horizontalen Sitze (22) verstärkt sind; wobei gebogene Rahmen Kegelgetriebes (45) über die Ummantelung des sta- in dem Querrahmen (39) der Passagierkabine (6) tionären Getriebegehäuses (20) und die hexagona- mit schrägen Streben (24) an der identischen Posi- len Löcher an der Mitte des oberen und des unteren tion der gebogenen Wand auf beiden Seiten des10 freien Kegelgetriebes (47) verläuft; und wobei die Rumpfes (7) verstärkt sind; wobei die mittlere Pro- obere Oberfläche des bewegbaren Getriebegehäu- jektionslänge der schrägen Streben (24) in den ver- se (49) mit dem Kolben (50) des ersten Hydraulik- schiedenen Abteilen einer Passagierkabinenzelle zylinders (44) verbunden ist. 1/3 der Spannweite der Passagierkabinenzelle ent- spricht; wobei der längste Rahmen der vorderen und 15 5. Amphibienflugzeug nach Anspruch 2, wobei eine hinteren Passagierkabine (6) eine hervorragende oder mehrere U-Vertiefungen (63) mit Rastschlitzen Bogenform aufweist; wobei der Abstand der Quer- (65) an der Schnittstelle eines Bodenrahmens des rahmen (39) der Passagierkabine (6) derselbe ist, Querrahmens (39) der Passagierkabine (6) mit den wie derjenige der Sitze (22) entlang der Längsrich- Gestellen (23) und den Rahmen entlang der Bogen- tung der Passagierkabine (6); und wobei alle Reihen 20 abschnitte auf beiden Seiten montiert sind; wobei von Sitzen (22) in der Passagierkabine (6) mit den Unterplatten (64) in den Rastschlitzen (65) montiert Querrahmen (39) der Passagierkabine (6) ausge- sind; und wobei Luftkissen (66) in den U-Vertiefun- richtet und in Längsrichtung in der Mitte montiert gen (63) montiert sind und durch die Unterplatten sind, indem sie über die entsprechenden schrägen (64) gehalten werden. Streben (24) verlaufen. 25

3. Amphibienflugzeug nach Anspruch 1, wobei die Pro- Revendications pellervorrichtung (58) darüber hinaus einen ersten und einen zweiten Hydraulikzylinder (44) umfasst, 1. Aéronef amphibie sans escaliers escamotables, qui welcher auf einer oberen Ummantelung des statio- 30 comprend : nären Getriebegehäuses (20) befestigt ist, wobei der erste Hydraulikzylinder (44) größer als der zweite un fuselage (7), une ou plusieurs voilures (8), Hydraulikzylinder (44) ist; wobei ein Kolben (50) des un ou plusieurs empennages (16), une pluralité ersten Hydraulikzylinders (44) mit der Oberseite des de moteurs (14, 30), une pluralité de trains d’at- bewegbaren Getriebegehäuses (49) verbunden ist; 35 terrissage (4, 9) et une pluralité de dispositifs wobei der Kolben (50) des zweiten Hydraulikzylin- d’hélice (58), dans lequel : ders (44) mit der Oberseite einer Steuerungsabde- ckung (17) verbunden ist; wobei Doppelschlitze der le fuselage (7) est de forme plate et oblon- Steuerungsabdeckung (17) bei einem oberen freien gue, et comprend une cabine de passagers Kegelradgetriebe (47) und bei einem unteren freien 40 (6), un compartiment de pilotage (1) et une Kegelradgetriebe (47) eingeschlossen sind, wobei soute à cargaison (21) ; sich das obere oder das untere freie Kegelradgetrie- le compartiment de pilotage (1) fait saillie à be (47) mit einem entsprechenden Kegelradgetriebe partir du fuselage (7), et la cabine de pas- (45) zu jeder Zeit in Eingriff befindet; wobei eine Wel- sagers (6) et la soute à cargaison (21) sont le des Kegelradgetriebes (45) über das stationäre 45 situées au même étage dans l’aéronef ; Getriebegehäuse (20) und den Rumpfrahmen (41) une forme de section transversale du fuse- verläuft und durch Kopplung mit dem Schwerölmotor lage (7) ressemble à une forme de section (14) verbunden ist; wobei die mittlere hexagonale transversale des voilures au nombre d’une Welle (42) des bewegbaren Getriebegehäuses (49) ou de plusieurs (8) ; durch das obere und das untere freie Kegelradge- 50 les voilures au nombre d’une ou de plu- triebe (47) und vier Platten der Führungsabdeckung sieurs (8) s’étendent des deux côtés à partir (17) verläuft; und wobei die hexagonale Welle (42) d’une partie centrale supérieure du fusela- über ein oberes und ein unteres Gehäuse des stati- ge (7) ; onären Getriebegehäuses (20) gerade durch ein un moteur à réaction (30) parmi les moteurs Loch auf der oberen Oberfläche des Rumpfes (7) 55 au nombre d’un ou de plusieurs (14, 30) est verläuft. monté sur l’arrière du fuselage (7) au voisi- nage d’un empennage (16) des empenna- 4. Amphibienflugzeug nachAnspruch 3, wobeidie zwei ges au nombre d’un ou de plusieurs (16) ;

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tous les trains d’atterrissage (4, 9) sont (7) sont des plans en arc ; la cabine de passagers montés dans le fuselage (7) ; (6) est divisée par des ossatures transversales pla- deux baies de trains d’atterrissage avant (3) tes (39) en plusieurs compartiments passagers avec et plusieurs baies de trains d’atterrissage des colonnes (23) ; des parties supérieures et infé- principaux (10) sont montées dans la cabi- 5 rieures des deux côtés des colonnes (23) sont ren- ne de passagers (6) du fuselage (7) ; forcées par des entretoises obliques (24) dans un des trains d’atterrissage avant (4) parmi les compartiment à bagages (29) et un espace en des- trains d’atterrissage au nombre d’un ou de sous des sièges (22) ; des ossatures en arc dans plusieurs (4) sont montés à l’intérieur des l’ossature transversale (39) de la cabine de passa- baies de trains d’atterrissage avant (3) ; 10 gers (6) sont renforcées avec les entretoises obli- des trains d’atterrissage principaux (9) sont ques (24) dans une position identique à celle de la montés à l’intérieur des baies de trains d’at- paroi en arc des deux côtés du fuselage (7) ; la lon- terrissage principaux (10) ; gueur de projection moyenne des entretoises obli- tous les trains d’atterrissage avant (4) et les ques (24) dans les différents compartiments d’une trains d’atterrissage principaux (9) sont ré- 15 cellule de cabine de passagers est de 1/3 de l’éten- tractables verticalement ; due de ladite cellule de cabine de passagers ; l’os- toutes les baies de trains d’atterrissage sature longitudinale de la cabine de passagers avant avant (3) et les baies de trains d’atterrissage et arrière (6) est une forme en arc saillante ; l’espa- principaux (10) sont équipées de portes cement intermédiaire des ossatures transversales coulissantes avant et arrière (33) ; 20 (39) de la cabine de passagers (6) est configuré de chacun des dispositifs d’hélice (58) com- façon à être identique à celui des sièges (22) le long prend un moteur à fioul (14) de la pluralité de la direction longitudinale de la cabine de passa- de moteurs (14, 30), une boîte d’engrena- gers (6) ; et toutes les rangées de sièges (22) dans ges fixe (20), une boîte d’engrenages mo- la cabine de passagers (6) sont alignées avec les bile (49) et une hélice (15) ; 25 ossatures transversales (39) de la cabine de passa- les dispositifs d’hélice (58) sont disposés gers (6), et montées longitudinalement dans le cen- dans une chambre d’hélice (19) à chacun tre par passage sur les entretoises obliques corres- des deux coins arrière du fuselage (7) à l’in- pondantes (24). térieur de la soute à cargaison (21) ; chaque chambre d’hélice (19) est équipée 30 3. Aéronef amphibie selon la revendication 1, dans le- de portes coulissantes avant et arrière (33), quel le dispositif d’hélice (58) comprend de plus un qui, lors de l’utilisation, lorsque l’aéronef premier et un deuxième cylindres hydrauliques (44) fonctionne en hydravion sur l’eau, coulis- fixés sur un carter supérieur de la boîte d’engrena- sent vers l’avant de façon à ouvrir une ges fixe (20), le premier cylindre hydraulique (44) ouverture inférieure de la chambre d’hélice 35 étant plus grand que le deuxième cylindre hydrauli- (19) ; et que (44) ; un piston (50) du premier cylindre hydrau- chaque boîte d’engrenages mobile (49) et lique (44) étant relié au sommet de la boîte d’engre- chaque hélice (15) peuvent être étendues nages mobile (49) ; le piston (50) du deuxième cy- dans l’eau à travers l’ouverture inférieure lindre hydraulique (44) étant relié au sommet d’un de la chambre d’hélice (19). 40 manchon de direction (17) ; des doubles fentes du manchon de direction (17) étant renfermées dans 2. Aéronef amphibie selon la revendication 1, dans le- un engrenage conique lâche supérieur (47) et un quel le fuselage (7) est de forme plate et oblongue engrenage conique lâche inférieur (47), l’un des en- dans le plan longitudinal ; le compartiment de pilo- grenages coniques lâches supérieur et inférieur (47) tage (1) fait saillie à partir d’une section médiane du 45 s’engrenant à tout moment avec un engrenage co- fuselage (7) ; une partie inférieure du fuselage (7) nique respectif (45) ; un arbre de l’engrenage coni- joue le rôle de cabine de passagers (6) avec un es- que (45) s’étendant à travers la boîte d’engrenages pace supérieur pour le confort des passagers ; une fixe (20) et l’ossature de fuselage (41) et étant relié section supérieure médiane au-dessus de la cabine au moteur à fioul (14) par couplage ; les engrenages de passagers (6) comprend un centre d’assemblage 50 coniques lâches supérieur et inférieur (47) et quatre (34) pour les voilures au nombre d’une ou de plu- plaques du manchon de direction (17) étant traver- sieurs (8) sur la partie centrale supérieure du fuse- sés par l’arbre hexagonal central (42) de la boîte lage (7) ; un espace graduellement plus bas dans d’engrenages mobile (49) ; et l’arbre hexagonal (42) une partie arrière du fuselage (7) joue le rôle de soute s’étendant à travers un carter supérieur et un carter à cargaison (21) et d’empennage de fuselage (16) ; 55 inférieur de la boîte d’engrenages fixe (20), en ligne l’empennage de fuselage (16) peut se soulever et droite à travers un trou sur la surface supérieure du se rabattre autour d’un arbre rotatif (18) derrière la fuselage (7). soute à cargaison (21) ; les deux côtés du fuselage

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4. Aéronef amphibie selon la revendication 3, dans le- quel les deux engrenages coniques (45) dans la boî- te d’engrenages mobile (49) sont reliés verticalement ; dans lequel l’arbre (48) de l’engre- nage conique monté verticalement (45) sort de la 5 boîte d’engrenages mobile (49) et est relié à l’hélice (15) ; l’arbre hexagonal (42) au-dessus de l’engre- nage conique horizontal (45) s’étendant à travers le carter de la boîte d’engrenages fixe (20) et les trous hexagonaux au centre des engrenages coniques lâ- 10 ches supérieur et inférieur (47) ; et la surface supé- rieure de la boîte d’engrenages mobile (49) étant reliée au piston (50) du premier cylindre hydraulique (44). 15 5. Aéronef amphibie selon la revendication 2, dans le- quel une ou plusieurs rainures en U (63) avec des fentes d’encliquetage (65) sont situées à l’intersec- tion d’un bâti inférieur de l’ossature transversale (39) de la cabine de passagers (6) avec les colonnes (23) 20 et les ossatures le long des sections en arc des deux côtés ; des plaques inférieures (64) sont montées dans les fentes d’encliquetage (65) ; et des coussins d’air (66) sont montés à l’intérieur des rainures en U (63), et sont supportés par les plaques inférieures 25 (64).

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REFERENCES CITED IN THE DESCRIPTION

This list of references cited by the applicant is for the reader’s convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

Patent documents cited in the description

• CN 1351944 A [0003]

33