CN114750926A - Long-endurance unmanned aerial vehicle body structure - Google Patents
Long-endurance unmanned aerial vehicle body structure Download PDFInfo
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- CN114750926A CN114750926A CN202210476159.5A CN202210476159A CN114750926A CN 114750926 A CN114750926 A CN 114750926A CN 202210476159 A CN202210476159 A CN 202210476159A CN 114750926 A CN114750926 A CN 114750926A
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- frame
- steel cable
- unmanned aerial
- aerial vehicle
- tail
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- 238000012423 maintenance Methods 0.000 claims abstract description 10
- 229910000831 Steel Inorganic materials 0.000 claims description 32
- 239000010959 steel Substances 0.000 claims description 32
- 230000003014 reinforcing effect Effects 0.000 claims description 6
- 210000001015 abdomen Anatomy 0.000 claims description 4
- 239000006260 foam Substances 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 3
- 230000017525 heat dissipation Effects 0.000 claims description 2
- 239000000295 fuel oil Substances 0.000 claims 2
- 239000003921 oil Substances 0.000 claims 2
- 238000005192 partition Methods 0.000 claims 2
- 238000000926 separation method Methods 0.000 claims 2
- 230000000694 effects Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
Images
Classifications
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention provides a fuselage structure suitable for an unmanned aerial vehicle during long endurance. On the premise of satisfying equipment loading and load transfer, the bearing capacity of the structure is fully exerted, stringers or trusses in the traditional fuselage structure are not required to be arranged, the structural arrangement is simple, the number of structural members is small, the structural weight is small, meanwhile, a large number of lightening designs are carried out on the structural members, and the structural weight can be further lightened. Combine the use needs of other systems of unmanned aerial vehicle in structural detail, structural functionality is strong. A certain amount of opening covers are arranged on the machine body, so that the use and maintenance are good. The unmanned aerial vehicle body structure has the characteristics of light weight and convenience in use and maintenance, and the cruising ability of the unmanned aerial vehicle in long voyage can be improved.
Description
Technical Field
The invention relates to an unmanned aerial vehicle body structure suitable for an unmanned aerial vehicle during long-endurance.
Background
The long-endurance unmanned aerial vehicle is mainly characterized by long endurance, and is specially designed around the long-endurance target in the aspects of overall design, pneumatic design, structural design, a power system, a take-off and landing system and the like. For structural design, the size of unmanned aerial vehicle weight is directly influenced by the quality of design, and weight is big more, and required power is big more during the flight, therefore the oil consumption is high, and the time of endurance shortens. The conventional unmanned aerial vehicle is firm and safe in structure, but is heavy, and is not suitable for the model with high requirement on time of flight. The invention designs a fuselage structure with simple structure and light weight for the long-endurance unmanned aerial vehicle, which is beneficial to improving the endurance performance of the unmanned aerial vehicle.
Disclosure of Invention
As the unmanned aerial vehicle fuselage, its main function is the loading of all kinds of equipment on realizing unmanned aerial vehicle to need set up corresponding flap so that install the maintenance to equipment. Meanwhile, the fuselage needs to bear aerodynamic loads, landing impact loads and the like on wings and empennages. How to achieve a small structural weight while achieving a loading function and bearing load is a major difficulty, and needs to be considered in terms of structural form, arrangement of structural elements, connection form and the like.
Drawings
Fig. 1 is an overall outline view of a drone according to one embodiment of the invention.
FIG. 2 is a schematic illustration of a wing root interface according to an embodiment of the present invention.
FIG. 3 is a bottom schematic view of a fuselage according to one embodiment of the invention.
FIG. 4 is a schematic illustration of fuselage capsule division according to an embodiment of the present invention.
Fig. 5 is a schematic view of the fuselage structural arrangement according to one embodiment of the invention.
FIG. 6 is a schematic view of an equipment bay bulkhead according to an embodiment of the invention.
FIG. 7 is a front view of an equipment bay bulkhead according to an embodiment of the invention.
Fig. 8 is a diagram of the effect of equipment bay loading according to one embodiment of the present invention.
Figure 9 is a detailed design schematic of a fuselage bulkhead according to one embodiment of the invention.
FIG. 10 is an enlarged schematic view of a wire rope segment according to one embodiment of the present invention.
FIG. 11 is a schematic view of a power pod configuration according to one embodiment of the present invention.
Figure 12 is an enlarged schematic view of a takeoff pin socket according to one embodiment of the present invention.
Fig. 13 is a diagram of the fuel tank and power tank loading effect according to one embodiment of the invention.
Fig. 14 is a schematic view of a fuselage cover according to an embodiment of the present invention.
Detailed Description
1) Original conditions
The overall appearance of the unmanned aerial vehicle according to one embodiment of the invention is shown in fig. 1, wherein wings (4) are installed on the upper part of a fuselage (7), a steel cable (5) is installed in the middle section of the wings (4), and the other end of the steel cable (5) is connected with the bottom of the fuselage (7). The vertical tail wing (1) and the horizontal tail wing (2) are installed on the tail boom (3), the tail boom (3) is installed on the upper portion of the machine body (7), and the propeller (6) is located at the tail portion of the machine body (7).
The connection form of the root of the wing (4) and the fuselage (7) is shown in figure 2, the wings (4) on two sides transmit main load through a main pin (9) inserted into the fuselage (7), a cylindrical pin (10) plays a role in positioning and transmitting partial load, and a pin hole (8) needs to be formed in the corresponding position of the fuselage (7).
The unmanned aerial vehicle adopts a take-off and landing mode of vehicle-mounted take-off and abdomen ground rubbing. As shown in figure 3, during take-off, the unmanned aerial vehicle is pushed to accelerate through a take-off pin hole (11), and during landing, the landing impact is borne through the wiping foam (12) of the belly. Meanwhile, air inlets (13) are arranged on two sides of the engine body (7) according to the air inlet and heat dissipation requirements of the engine.
2) Fuselage structural arrangement
As shown in fig. 4, the fuselage (7) is divided into an equipment compartment (14), a front fuel compartment (15), a rear fuel compartment (17), a power compartment (18), and a roof compartment (16), and structural arrangement is performed according to the compartment division.
In order to achieve the effect of reducing weight, a skin skeleton type structural form is selected, and the skin skeleton type structural form is composed of a bulkhead formed by plate-shaped structural parts and a skin (27), as shown in figure 5. No. 1 frame (26), No. 2 frame (23), No. 3 frame (22), No. 4 frame (19) and reinforcing ribs (28) are arranged at the position of the cabin section boundary. A kingpin sleeve (29) is arranged at the interface of the No. 3 frame (22) and the reinforcing rib (28). A half frame (20) is arranged between the No. 3 frame (22) and the No. 4 frame (19), and the lower half part of the half frame (20) is in a thin rib shape, so that the partial skin (27) can be reinforced to a certain extent, and meanwhile, the weight is kept light. Tail boom sleeve pipes (30) are arranged at the tops of the No. 3 frame (22), the half frame (20) and the No. 4 frame (19), and after the tail boom (3) is inserted into the tail boom sleeve pipes (30), loads can be transmitted to the No. 3 frame (22), the half frame (20) and the No. 4 frame (19). The tail boom sleeve (30) is divided into three sections by removing unnecessary parts on the basis of a whole pipe, so that the structural weight can be reduced.
Two floor mopping foams (12) are arranged below the No. 1 frame (26) and the No. 3 frame (22), and the No. 1 frame (26) and the No. 3 frame (22) bear the concentrated load of landing impact. A steel cable piece (21) is arranged at the bottom of the No. 3 frame (22) and is used for connecting the steel cable (5) and transmitting the concentrated tension of the steel cable (5) to the No. 3 frame (22). A flat plate (24) and a vertical plate (25) are arranged beside the No. 1 frame (26), so that various devices can be conveniently installed.
3) Design of construction details
The structure composed of the frame No. 1 (26), the vertical plate (25) and the flat plate (24) is shown in fig. 6, and an equipment mounting hole (32) with a smaller aperture, a wire passing hole (31) with a larger aperture and a maintenance hole (35) for maintenance personnel to stretch into the arm for maintenance are arranged on the structure. In one embodiment, a separate compartment (34) is provided on the side of the riser (25) for mounting a particular piece of equipment.
As shown in fig. 7, the flat plate (24) and the vertical plate (25) are both offset by a center line, and the pitot seat (33) is opposite to the center line. With such a configuration, certain flight control equipment can be installed, and the airspeed head (36) is centrally installed and aesthetically pleasing, as shown in fig. 8.
As shown in fig. 9, the bulkhead is provided with a plurality of lightening holes (38) to lighten the weight of the structure. And a wire passing hole (37) is formed for the cable and the oil pipe to pass through.
As shown in fig. 10, the steel cable sheet (21) is installed at the bottom of the No. 3 frame (22) through two bolts (40), and the angle of the two ends of the steel cable sheet (21) is the same as that of the steel cable (5), so that the steel cable sheet is subjected to pure tension and is not easy to break, and thus, the steel cable sheet can be thinner and lighter. The tail end of the steel cable sheet (21) is provided with a steel cable mounting hole (39) which is convenient for mounting the steel cable (5).
The specific details of the No. 4 frame (19) are shown in FIG. 11, and the frame is provided with a vent hole (44), a power system mounting hole (43), and an anti-bubble oil tank bracket (42). As shown in figure 12, the takeoff pin hole seat (41) is connected with the No. 4 frame (19) and the skin (27), and the thickness of the front half part of the takeoff pin hole seat (41) is smaller due to the support of the No. 4 frame (19), so that the weight is reduced. The loading effect by the frame No. 2 (23), the frame No. 3 (22) and the frame No. 4 (19) is shown in fig. 13.
As shown in fig. 14, in consideration of the use and maintenance, the fuselage (7) is further provided with a nose cover (47), a side cover (46), a tail cover (45) and a roof cover (48), which can be quickly detached and facilitate the installation and maintenance of the equipment inside the fuselage (7).
Advantageous effects
The invention has the following advantages:
1) can satisfy unmanned aerial vehicle's equipment loading requirement to bear the load that comes from other parts of unmanned aerial vehicle, and structural arrangement is simple, and the structure quantity is less, and structure weight is little.
2) Because the load on the tail boom is small, an additional reinforcing structure is not needed to be arranged in the top cabin, and the appearance of the top cabin is maintained only by the skin, so that the weight of the structure can be reduced.
3) The skin between the frame No. 1 and the frame No. 2 forms a large closed cylinder, the bending resistance is strong, the gravity of the machine head equipment can be borne only through the skin, and the load is transmitted to the rear part of the machine body, so that a stringer or a truss beam in the traditional structure is not required to be arranged, the bearing effect of the skin can be fully exerted, and the weight of the structure is reduced.
4) The structural member is designed to be greatly lightened, so that the structural weight can be further lightened.
5) A certain amount of cover covers are arranged on the fuselage skin, so that the use and maintenance are good.
6) Combine the use needs of other systems of unmanned aerial vehicle in structural detail, carried out the setting of crossing line hole, airspeed tube seat etc. and the functional strong of structure.
Claims (10)
1. An unmanned aerial vehicle, its characterized in that includes:
a machine body (7),
a wing (4) arranged on the upper part of the fuselage (7),
one end of the steel cable (5) is arranged at the middle section of the wing (4), the other end of the steel cable (5) is connected with the bottom of the fuselage (7),
a tail support (3) arranged at the upper part of the machine body (7),
a vertical tail wing (1) and a horizontal tail wing (2) which are arranged on a tail boom (3),
a propeller (6) arranged at the tail part of the machine body (7),
a main pin (9) inserted into the fuselage (7), the wings (4) on both sides transmit the main load through the main pin (9),
wherein:
the fuselage (7) comprises an equipment cabin (14), a front fuel oil cabin (15), a rear fuel oil cabin (17), a power cabin (18) and a roof cabin (16),
the fuselage (7) adopts a skin skeleton type structure form and comprises a skin (27) and a bulkhead,
no. 1 frame (26), No. 2 frame (23), No. 3 frame (22), No. 4 frame (19) and reinforcing ribs (28) are arranged at the position of the cabin section boundary,
a main pin sleeve (29) is arranged at the junction of the No. 3 frame (22) and the reinforcing rib (28),
a half frame (20) is arranged between the No. 3 frame (22) and the No. 4 frame (19), the lower half part of the half frame (20) is in a thin rib shape and is used for reinforcing the local skin (27) and keeping light weight,
the tail-boom sleeve (30) is arranged on the top of the No. 3 frame (22), the half frame (20) and the No. 4 frame (19),
The tail boom (3) is inserted into the tail boom sleeve (30) to transfer load to the No. 3 frame (22), the half frame (20), and the No. 4 frame (19).
2. A drone according to claim 1, characterized in that:
the unmanned aerial vehicle adopts the take-off and landing form of vehicle-mounted take-off and abdomen ground wiping landing,
during takeoff, the unmanned aerial vehicle is pushed to accelerate through the takeoff pin hole (11), and during landing, the landing impact is borne through the ground wiping foam (12) of the belly,
two floor mopping foams (12) are arranged below the No. 1 frame (26) and the No. 3 frame (22), and the No. 1 frame (26) and the No. 3 frame (22) bear the concentrated load of landing impact.
3. A drone according to claim 2, characterized in that:
a flat plate (24) and a vertical plate (25) are arranged beside the No. 1 frame (26), so that various devices can be conveniently installed.
4. A drone according to claim 2, characterized in that:
the steel cable piece (21) is arranged at the bottom of the No. 3 frame (22) through two bolts (40), the angle of the two ends of the steel cable piece (21) is the same as that of the steel cable (5), so that the steel cable piece is subjected to pure tension,
the tail end of the steel cable sheet (21) is provided with a steel cable mounting hole (39) to facilitate the installation of the steel cable (5).
5. The drone of claim 1, wherein:
air inlets (13) are arranged on both sides of the machine body (7) and are used for air inlet and heat dissipation of the engine,
A steel cable piece (21) is installed at the bottom of the No. 3 frame (22) and is used for connecting the steel cable (5) and transmitting the concentrated pulling force of the steel cable (5) to the No. 3 frame (22).
6. A drone according to one of claims 1 to 5, characterized in that:
the No. 4 frame (19) is provided with a vent hole (44) and a power system mounting hole (43), and is also provided with an anti-bubble oil tank bracket (42),
the takeoff pin hole seat (41) is connected with the No. 4 frame (19) and the skin (27), so that the thickness of the front half part of the takeoff pin hole seat (41) is reduced through the support of the No. 4 frame (19).
7. A drone according to one of claims 1 to 5, characterized in that:
the machine body (7) is provided with a detachable machine head cover (47), a side cabin cover (46), a machine tail cover (45) and a machine top cover (48).
8. A drone according to one of claims 1 to 5, characterised in that:
the separation frame of the equipment cabin (14) comprises a No. 1 frame (26), a vertical plate (25) and a flat plate (24), an equipment mounting hole (32), a wire passing hole (31) and a maintenance hole (35) are arranged on the separation frame,
an independent cabin (34) is arranged on the side of the vertical plate (25) and is used for installing specific equipment,
the flat plate (24) and the vertical plate (25) are both offset by a center line, and the airspeed head (33) is opposite to the center line.
9. A drone according to one of claims 1 to 5, characterised in that:
Lightening holes (38) are arranged on the partition frame to lighten the weight of the structure,
the partition frame is provided with a wire passing hole (37) for the cable and the oil pipe to pass through.
10. A drone according to one of claims 1 to 5, characterised in that:
the steel cable piece (21) is arranged at the bottom of the No. 3 frame (22) through two bolts (40), the angle of the two ends of the steel cable piece (21) is the same as that of the steel cable (5), so that the steel cable piece is subjected to pure tension,
the tail end of the steel cable sheet (21) is provided with a steel cable mounting hole (39) to facilitate the installation of the steel cable (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210476159.5A CN114750926A (en) | 2022-04-29 | 2022-04-29 | Long-endurance unmanned aerial vehicle body structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210476159.5A CN114750926A (en) | 2022-04-29 | 2022-04-29 | Long-endurance unmanned aerial vehicle body structure |
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| Publication Number | Publication Date |
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| CN114750926A true CN114750926A (en) | 2022-07-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210476159.5A Pending CN114750926A (en) | 2022-04-29 | 2022-04-29 | Long-endurance unmanned aerial vehicle body structure |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| RU2380286C1 (en) * | 2008-06-24 | 2010-01-27 | Закрытое Акционерное Общество "Транзас" | Pilotless aircraft |
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN108116692A (en) * | 2016-11-30 | 2018-06-05 | 波音公司 | For automating the compound-contoured vacuum track of fuselage interior general assembly |
| CN109823514A (en) * | 2019-02-02 | 2019-05-31 | 北京航空航天大学 | A kind of quick detachable tail structure of adjustable established angle |
| CN113682469A (en) * | 2021-09-30 | 2021-11-23 | 北京航空航天大学 | Overall layout of small long-endurance unmanned aerial vehicle |
-
2022
- 2022-04-29 CN CN202210476159.5A patent/CN114750926A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| RU2380286C1 (en) * | 2008-06-24 | 2010-01-27 | Закрытое Акционерное Общество "Транзас" | Pilotless aircraft |
| CN108116692A (en) * | 2016-11-30 | 2018-06-05 | 波音公司 | For automating the compound-contoured vacuum track of fuselage interior general assembly |
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN109823514A (en) * | 2019-02-02 | 2019-05-31 | 北京航空航天大学 | A kind of quick detachable tail structure of adjustable established angle |
| CN113682469A (en) * | 2021-09-30 | 2021-11-23 | 北京航空航天大学 | Overall layout of small long-endurance unmanned aerial vehicle |
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