CN213008694U - Light conveyor body - Google Patents
Light conveyor body Download PDFInfo
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- CN213008694U CN213008694U CN202021317470.8U CN202021317470U CN213008694U CN 213008694 U CN213008694 U CN 213008694U CN 202021317470 U CN202021317470 U CN 202021317470U CN 213008694 U CN213008694 U CN 213008694U
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- fuselage
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- 238000000034 method Methods 0.000 claims abstract description 5
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims 1
- 240000000731 Fagus sylvatica Species 0.000 description 1
- 235000010099 Fagus sylvatica Nutrition 0.000 description 1
- 241001233242 Lontra Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
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- 230000009467 reduction Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1415—Cargo doors, e.g. incorporating ramps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0045—Fuselages characterised by special shapes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The utility model provides a fuselage of light-duty cargo airplane: the method comprises the following steps: a nose and a rear portion; a central portion whose cross-sectional profile is constituted by combined arcs of different radii; a frame; a door; wherein a cross-sectional profile of a central portion of the fuselage is formed by combining eight circular arcs of five radii; the radius of the combined circular arc of the upper side and the side portion of the cross-sectional profile is greater than the radius of the combined circular arc of the lower side and the side portion, and the centers of the radii of the combined circular arc of the upper side and the side portion are positioned so as to be horizontally spaced from each other by a distance less than the horizontal distance between the centers of the combined circular arc of the lower side and the side portion corresponding to the upper side and the side portion. The utility model discloses a cross sectional shape has optimally satisfied the requirement that cross sectional area minimizing and good aerodynamics flow, guarantees to arrange and transport great size self-propelled wheeled vehicle by this light aircraft simultaneously. The shape of the fuselage cross-section expands the functionality of the fuselage in transporting various cargo of the largest possible overall size by maintaining the rigidity and strength of the fuselage.
Description
Technical Field
The utility model relates to an aircraft structure field relates to the fuselage structure of cargo airplane promptly.
Background
Currently, aircraft fuselages come in a variety of cross-sectional shapes. In each particular case, the size and shape of the fuselage cross-section is determined by the use of the aircraft. Generally, the cross-sectional shape of an aircraft fuselage varies from circular to rectangular and medium elliptical, with different overall dimensional ratios of width and height. The cross-sectional shape of the fuselage of a transport aircraft is determined by the maximum overall dimensions of the entire class of transported cargo. The overall size of the transported cargo is a determining factor in the transport process and is of particular relevance for small aircraft.
An aircraft (a.i. kovalev "L-410 UVP aircraft," the "transport" press, 1988) is known, which comprises a fuselage comprising reinforcing frames and normal bulkheads, stringers forming a truss, and a smooth stressed skin connected to the truss. The cross-sectional shape of the fuselage is rectangular with rounded corners, and the width-to-height aspect ratio of the nacelle is 1.15. In an aircraft of the cargo aircraft type, there is a relatively large cargo door which is designed for loading the transported cargo in the rear part of the fuselage on the port side. The aircraft has no cargo rotating ramp or cargo half door (halfdoor).
A disadvantage of the known solutions is that vehicles and air cargo containers cannot be loaded due to the cross-sectional shape and size of the cargo hold and the absence of cargo ramps.
There is known a light multifunction short sc.7 "Skyvan" aircraft (www.airwar.ru) designed for operation on local airlines. The aircraft fuselage is short, having a rectangular cross-sectional shape with rounded corners. This cross-sectional shape of the fuselage enables the arrangement of self-propelled vehicles of larger dimensions (for example "jeep" vehicles) on small aircraft, but the flat bottom and the lower steep slope of the rear portion of the fuselage make the fuselage highly resistant, which generates additional aerodynamic drag. The aircraft is equipped with a foldable flat ramp, which enables motor vehicles of larger size to be loaded in a self-propelled manner.
An aircraft fuselage (RU2481236) is also known, which comprises a front section, a central section and a rear section. The cross-sectional shape of the central portion of the fuselage is flattened and is formed by four circular arc segments connected in series with one another. Meanwhile, the radius of curvature of the circular arcs corresponding to the upper and lower sides of the body is greater than that of the circular arcs corresponding to the side portions of the body. The flat shape of the fuselage contributes to saving space and to obtaining additional space for passengers and cargo in the aircraft cabin. Moreover, this fuselage shape enables higher aerodynamic performance to be obtained than with conventional cylindrical cross-sectional shapes. However, the elliptical cross-sectional shape of the fuselage, formed by only two radii, is not optimized for a particular pre-set payload, which is particularly relevant for light-duty transport aircraft on local airlines.
The aircraft according to patent RU2148534 is closest to the present invention, in which the fuselage has a non-circular cross-sectional shape, which is formed by four circular arc segments in the upper, lower and side parts, which consist of three radii. The loading ramp is located in the rear portion of the fuselage. The proposed structure is able to provide a relatively simple transition of the aircraft from passenger transport to freight transport (and vice versa), and is also able to load containers of larger size through the cargo door in the rear portion.
This solution has the disadvantage that an optimum fuselage cross section cannot be obtained by constructing a circular arc of four segments consisting of three radii.
The purpose of the invention is to expand the functionality of a light conveyor designed for a local route by selecting the optimal fuselage shape for a specific pre-set payload.
SUMMERY OF THE UTILITY MODEL
The utility model provides a fuselage of light-duty cargo airplane: the method comprises the following steps: a nose and a rear portion that taper in a direction along a longitudinal axis of the light conveyor; a central portion in the form of an elliptical cylinder having a width exceeding its height, wherein the cross-sectional profile of the central portion is constituted by combined arcs of different radii, the centers of the radii of the upper and lower arcs forming the cross-sectional profile being located on the same vertical axis, the centers of the radii of the side arcs being offset with respect to the vertical axis of the cross-section of the central portion of the fuselage; a truss including a reinforcing frame and normal bulkheads, stringers and stringers, a panel, and a smooth stressed skin; a door installed in a loading opening made of a bottom of a rear portion of the body and including a ramp folded downward, wherein a sectional profile of a central portion of the body is formed by combining eight circular arcs of five radii; the radius of the combined circular arc of the upper side and the side portion of the cross-sectional profile is greater than the radius of the combined circular arc of the lower side and the side portion, and the centers of the radii of the combined circular arc of the upper side and the side portion are positioned so as to be horizontally spaced from each other by a distance less than the horizontal distance between the centers of the combined circular arc of the lower side and the side portion corresponding to the upper side and the side portion.
Preferably, the vertical distance between the center of radius of the combined arc of the upper side and the lateral part and the center of radius of the combined arc of the lower side and the lateral part of the cross-sectional profile is 0.32 of the height of the cross-sectional profile.
Preferably, the ratio of the width of the cross-sectional profile of the central portion of the fuselage to its height is 1.33.
Preferably, the cross-sectional profile of the central portion of the fuselage consists of a circular arc with the following radii: an upper arc of 1.07H; 3.11H lower arc; a side arc of 0.91H; 0.38 and 0.24, where H is the height of the cross-sectional profile of the central portion of the fuselage.
Preferably, the centre of each side arc is positioned on the opposite side of the vertical axis of the section of the central portion of the fuselage.
Preferably, the door further comprises deflectable side half doors and an upwardly deflectable central half door, wherein in the closed position of the door the side half doors, the central half door and the ramp form part of a structural arrangement that takes up all loads acting on the fuselage.
The technical result obtained by using the invention is to extend the functionality of an aircraft to transport various goods having the maximum possible overall dimensions allowed by this type of aircraft, while maintaining the required rigidity and strength of the fuselage and the aerodynamic properties of the aircraft.
The technical result is achieved in an aircraft fuselage having a nose, a central and a rear section. The nose portion of the fuselage has a streamlined shape tapering towards the nose, the central portion is made in the form of an elliptical cylinder with a constant cross-section along the longitudinal axis, and the rear portion has a tapered aerodynamic shape. The elliptical profile of the cross-section of the central portion of the fuselage is made up of at least five circular arcs of radius. The centres of the radii of the arcs forming the upper and lower sides of the profile are located on the same vertical axis, and the centres of the radii of the side arcs are offset with respect to the axis of symmetry of the aircraft. The radii of the combined arcs of the upper and side portions of the profile are larger than the respective combined radii of the lower and side portions, and the centers of the radii of the combined arcs of the upper and side portions are arranged at a smaller horizontal distance from each other than the horizontal distance between the centers of the combined arcs of the lower and side portions corresponding thereto. The vertical distance between the radius centers of the joining arcs of the upper and lower sides of the profile and the radius centers of the joining arcs of the sides is proportional to the profile height. Furthermore, a cargo half-door system is installed in the loading opening of the cargo door, which system is part of the structural layout of the fuselage.
Drawings
The attached drawings show the utility model.
Figure 1 shows an overall view of a light conveyor according to the invention;
FIG. 2 illustrates a cross-section of the fuselage of the aircraft shown in FIG. 1;
figure 3 shows a comparison of a circular cross section of a fuselage with a fuselage according to the invention;
FIG. 4 illustrates a comparison of the overall size and shape of the fuselage cross-section of the present invention with that of a similar aircraft;
FIG. 5 shows a cross-section of a passenger cabin;
FIG. 6 shows a schematic view of the rear cargo half-door with the center half-door open;
figure 7 shows a schematic view of the rear cargo half-door with all sets of half-doors open.
Detailed Description
As shown in fig. 1, the aircraft fuselage according to the invention has a head section 1, a central section 2 and a rear section 3. The nose portion 1 of the fuselage has a streamlined shape tapering towards the nose, the central portion being a non-circular cylinder with a constant cross-section along the longitudinal axis, while the rear portion has a tapered aerodynamic shape.
The central part of the fuselage, made in the form of a non-circular cylinder, has a complex cross-sectional shape with a horizontally oriented main axis. In one embodiment, the fuselage cross-section is made such that the ratio of the overall dimension of the width to the height is 1.33, wherein the shape of the fuselage cross-section is made by the geometry of circular arcs with different radii. Such a cross-sectional shape optimally meets the requirements of minimized cross-sectional area and good aerodynamic flow while ensuring the deployment and transportation of larger size cargo, including self-propelled wheeled vehicles, by the light aircraft.
The optimized shape of the fuselage cross-section (fig. 2) is formed by constructing a plurality of circular arcs of radius, including: an upper arc of radius R1, a lower arc of radius R5, a side arc of radius R3, an upper joining arc of radius R2, and a lower joining arc of radius R4.
The ratio values (as a fraction of the overall section height) of the relative sizes of the radii of the circular arcs in one fuselage embodiment are given in table 1.
TABLE 1
| Coordinates of the center of the arc | Х(Н) | Y(H) | R(H) |
| O1 | 0 | –0.07H | 1.07H |
| O2 | 0.20H | 0.59H | 0.38H |
| O3 | –0.26H | 0.34H | 0.91H |
| O4 | 0.40H | 0.27H | 0.24H |
| O5 | 0 | 3.11H | 3.11H |
This cross-sectional shape of the fuselage enables the following advantages to be obtained compared with a circular shape with equal area: the width increased by 9% and the height decreased by 16%.
Fig. 3 shows the ratio of the proposed fuselage shape to the circular fuselage shape for equal cross-sectional areas, where it can be seen that the proposed cross-section fills the lower half of the cross-section. The increased width of the fuselage section in the lower part enables free arrangement of air freight containers (e.g. 2AK-0.7 and LD3-45) or self-propelled motor vehicles (e.g. UAZ "Patriot" etc.).
Typically, existing branch-line aircraft have a relative mid-fuselage cross-section, i.e., the ratio of the maximum cross-sectional area of the fuselage to the wing area, of about 10%. The fuselage of a branch-line aircraft is compact in size, since it is desirable to obtain a reasonable compromise between aerodynamic drag, weight and capacity of the aircraft fuselage.
The comparative dimensions of the fuselage section of the same type of aircraft with the section of the proposed utility model are shown in fig. 4. All existing branch aircraft (An-28, An-38, L-410, Short Skyvan, Do-228, TwinOtter, Y-12F (China)) having a takeoff weight of 8600 kg are manufactured according to a classical aerodynamic design, the fuselage of these aircraft being rectangular with rounded corners. All the above listed aircraft can be operated in passenger transport and freight transport types with corresponding changes to the cabin. In passenger transport type, the cabins of a branch aircraft accommodate 2 to 3 passenger seats in one row according to the scheme "1 + 1" or "1 + 2". The distinguishing feature of the fuselage according to the invention is the particular shape of its cross-section, the dimensions of which greatly exceed all known similar aircraft. When compared to the actual dimensions of the passenger cabin (cargo hold) of all known operational branch-line aircraft, the cabin width according to the invention exceeds the maximum cabin width (1.92m) of the L-410 aircraft by 36% and the height exceeds the maximum cabin height (1.84m) of the Y-12F aircraft by 10%. This makes it possible to place five seats in a row according to scheme "2 + 3" in a passenger type of aircraft according to the invention (figure 5).
In FIG. 4, A, B, C, D, E and F respectively show the fuselage sections of a Beech-1900D aircraft (manufactured by Beech corporation), a Dornier-228 aircraft (manufactured by Dornier corporation), a Cessna-208 aircraft (manufactured by Cessna corporation), a DHC-6Twin Otter aircraft (manufactured by De Havilland-DHC, Canada, which is used in China, such as civil aviation, China), an L-410 aircraft, and the aircraft of the present invention.
In order to perform loading and unloading operations, a cargo half-door system is provided in the tapered rear portion of the fuselage (fig. 6 and 7), which system comprises: a lowerable ramp 4; a side-lobe half-door 5, the side-lobe half-door 5 being laterally openable similarly to the half-door of the Mi-8 helicopter; and a final narrow central half-door 6, which central half-door 6 can be raised. The side-lobe half-doors 5 are only open on the ground during loading and unloading operations and they are integrated in the structural layout of the rear part of the fuselage during flight by means of power locks. The central half-door 6 is designed to perform a landing in flight, with the opening being open for free disengagement from the aircraft when it is raised. Only on the ground during the loading/unloading operation are the half-doors of all groups open simultaneously.
With the cargo door closed, the cargo ramp is a continuation of the cargo compartment floor, on which the payload can be placed. The half-door systems of the cargo hold provide a variety of options for their use in different settings. When loading a motor vehicle on the ground, all half doors are open and the cargo ramp is lowered; when an airborne landing is performed, only the central half-door 6 is opened.
The utility model discloses when the very big size of the single piece goods that transport occupies the aircraft cargo hold, the utility model discloses there is the biggest positive effect to light-duty cargo airplane.
The above-described cross-sectional shape of the fuselage enables a significant increase in the width of the cargo compartment floor, which in turn enables a reduction in the overall length of the aircraft by maintaining a permissible change in the center of gravity.
Cargo half-door systems and methods of opening them can provide the operations of loading and unloading large equipment into a tapered aft section of a fuselage.
Claims (6)
1. A light conveyor body: the method comprises the following steps:
a nose and a rear portion that taper in a direction along a longitudinal axis of the light conveyor;
a central portion in the form of an elliptical cylinder having a width exceeding its height, wherein the cross-sectional profile of the central portion is constituted by combined arcs of different radii, the centers of the radii of the upper and lower arcs forming the cross-sectional profile being located on the same vertical axis, the centers of the radii of the side arcs being offset with respect to the vertical axis of the cross-section of the central portion of the fuselage;
a truss including a reinforcing frame and normal bulkheads, stringers and stringers, a panel, and a smooth stressed skin;
a door mounted in a loading opening made by a bottom of a rear portion of the fuselage and including a downwardly folded ramp,
it is characterized in that the preparation method is characterized in that,
the cross-sectional profile of the central portion of the fuselage is formed by combining eight circular arcs of five radii;
the radius of the combined circular arc of the upper side and the side portion of the cross-sectional profile is greater than the radius of the combined circular arc of the lower side and the side portion, and the centers of the radii of the combined circular arc of the upper side and the side portion are positioned so as to be horizontally spaced from each other by a distance less than the horizontal distance between the centers of the combined circular arc of the lower side and the side portion corresponding to the upper side and the side portion.
2. The body of a light weight conveyor as claimed in claim 1, wherein: the vertical distance between the center of radius of the combined arc of the upper side and the side of the cross-sectional profile and the center of radius of the combined arc of the lower side and the side is 0.32 of the height of the cross-sectional profile.
3. The body of a light weight conveyor as claimed in claim 1, wherein: the ratio of the width of the cross-sectional profile of the central portion of the fuselage to its height is 1.33.
4. The body of a light weight conveyor as claimed in claim 1, wherein: the cross-sectional profile of the central portion of the fuselage consists of a circular arc with the following radii: an upper arc of 1.07H; 3.11H lower arc; a side arc of 0.91H; 0.38 and 0.24, where H is the height of the cross-sectional profile of the central portion of the fuselage.
5. The body of a light weight conveyor as claimed in claim 1, wherein: the center of each side arc is positioned on the opposite side of the cross-sectional vertical axis of the central portion of the fuselage.
6. The body of a light weight conveyor as claimed in claim 1, wherein: the door further includes deflectable side half doors and an upwardly deflectable center half door, wherein in the closed position of the door, the side half doors, the center half door and the ramp form part of a structural arrangement that takes all loads acting on the fuselage.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2019124498 | 2019-08-01 | ||
| RU2019124498 | 2019-08-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213008694U true CN213008694U (en) | 2021-04-20 |
Family
ID=72178841
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021317470.8U Active CN213008694U (en) | 2019-08-01 | 2020-07-07 | Light conveyor body |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP3924249A1 (en) |
| CN (1) | CN213008694U (en) |
| WO (1) | WO2021019487A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113139235A (en) * | 2021-04-22 | 2021-07-20 | 贵州天义电器有限责任公司 | Design method of airplane curved surface power distribution device |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB560580A (en) * | 1942-11-13 | 1944-04-11 | Laurence Rachard Morphew | Improvements in or relating to the construction of streamlined panel structures |
| DE1217213B (en) * | 1964-05-08 | 1966-05-18 | Dornier Werke Gmbh | Rear loading gate for transport aircraft |
| RU2148534C1 (en) | 1996-05-14 | 2000-05-10 | АО Авиационный научно-технический комплекс им.А.Н.Туполева | Aircraft (versions) |
| US6616100B2 (en) * | 2001-10-02 | 2003-09-09 | The Boeing Company | Cargo loading means for short body airplanes |
| FR2910434B1 (en) | 2006-12-26 | 2009-12-04 | Airbus | AIRCRAFT FUSELAGE |
| DE102010045588B4 (en) * | 2010-09-16 | 2017-04-06 | Airbus Operations Gmbh | Fuselage segment for an aircraft |
-
2020
- 2020-07-07 CN CN202021317470.8U patent/CN213008694U/en active Active
- 2020-07-30 WO PCT/IB2020/057200 patent/WO2021019487A1/en active Search and Examination
- 2020-07-30 EP EP20760542.9A patent/EP3924249A1/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113139235A (en) * | 2021-04-22 | 2021-07-20 | 贵州天义电器有限责任公司 | Design method of airplane curved surface power distribution device |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2021019487A1 (en) | 2021-02-04 |
| EP3924249A1 (en) | 2021-12-22 |
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