CN114229010B - Low-cost simple unmanned aerial vehicle nacelle structure - Google Patents
Low-cost simple unmanned aerial vehicle nacelle structure Download PDFInfo
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- CN114229010B CN114229010B CN202210165209.8A CN202210165209A CN114229010B CN 114229010 B CN114229010 B CN 114229010B CN 202210165209 A CN202210165209 A CN 202210165209A CN 114229010 B CN114229010 B CN 114229010B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
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Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to a low-cost simple unmanned aerial vehicle pod structure, which comprises a cabin body, wherein lifting lugs are arranged at the upper part of the cabin body, and the surface of the cabin body is wrapped by a waterproof layer; the tail part of the cabin body is provided with an opening, and the waterproof layer forms a plurality of turnover structures at the opening; the cabin body includes cabin portion and lower cabin portion, and cabin portion and lower cabin portion set up relatively and connect fixedly through fastening structure, go up and form accommodation space between cabin portion and the lower cabin portion, and accommodation space's front end sets up the bolster, and the top sets up the main tributary supporting beam in the accommodation space, and the both ends of main tributary supporting beam are provided with front end support piece and rear end support piece respectively. The invention can improve the cargo volume carried by the unmanned aerial vehicle; after the nacelle is thrown in, the flexible buffer part is used for damping and buffering, so that the impact on the nacelle body is minimized, the nacelle is prevented from being damaged, and the protection on internal goods is also improved; the pod is high in machining and assembling efficiency, the use cost is reduced, and the unmanned aerial vehicle freight transportation has high economical efficiency.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle pod, in particular to a low-cost simple unmanned aerial vehicle pod structure.
Background
The unmanned aerial vehicle nacelle is a task load installed on an unmanned aerial vehicle, and is mainly used for the unmanned aerial vehicle to transport and release materials. The traditional unmanned aerial vehicle pod is complex in structural design, large in number of parts, high in processing difficulty and high in subsequent assembly difficulty; when the device is used specifically, goods loading is complex, efficiency is low, and use cost is increased. Because traditional unmanned aerial vehicle nacelle structure contains too much spare part, and overall structure is very complicated, and the nacelle causes the damage easily after carrying out the task of puting in, because the cost of itself nacelle is higher, need carry out a large amount of repairs and put into secondary operation, then has further improved use cost.
The nacelle that uses is carried to unmanned aerial vehicle, still exists at present and waits for the space of improving urgently, should satisfy the nacelle and carry load when, the structure is as simple as possible, and the part is few, and the dead weight is little, and convenient assembling reduces manufacturing cost and whole use cost, satisfies the economic nature of unmanned aerial vehicle freight. Therefore, a more reasonable technical scheme is provided for optimizing and improving the unmanned aerial vehicle pod, and the technical problem existing in the prior art is solved.
Disclosure of Invention
In order to solve the defects of the prior art mentioned in the content, the invention provides a low-cost simple pod structure of the unmanned aerial vehicle, the integrated structure is formed by simple and easy components, the internal load can be conveniently contained, the unmanned aerial vehicle can be conveniently carried and thrown in, the pod is more convenient to process, produce and use, and compared with the traditional pod, the use cost is reduced.
In order to achieve the purpose, the invention specifically adopts the technical scheme that:
a low-cost simple unmanned aerial vehicle nacelle structure comprises a nacelle body, wherein lifting lugs are arranged at the upper part of the nacelle body, and the surface of the nacelle body is wrapped by a waterproof layer; the tail part of the cabin body is provided with an opening, the waterproof layer forms a plurality of turnover structures at the opening, the opening is closed when the turnover structures are turned inwards, and the opening is opened when the turnover structures are turned outwards; the cabin body includes cabin portion and lower cabin portion, and cabin portion and lower cabin portion set up relatively and connect fixedly through fastening structure, go up and form accommodation space between cabin portion and the lower cabin portion, and accommodation space's front end sets up the bolster, and the top sets up the main tributary supporting beam in the accommodation space, and the both ends of main tributary supporting beam are provided with front end support piece and rear end support piece respectively.
The unmanned aerial vehicle pod structure disclosed above has the advantages that the structure of the pod body is simple, and the composition is reliable; when the unmanned aerial vehicle is used specifically, the cabin body is connected with a hanging frame on the unmanned aerial vehicle through a lifting lug; the main supporting beam plays a main supporting role, the accommodating space is used for placing goods, and the front end supporting piece, the main supporting beam and the rear end supporting piece ensure that the structure of the whole cabin body is not changed; after the parachute is thrown, the parachute is popped out from the rear end of the accommodating space, the cabin body is kept vertically downward after the parachute is unfolded, the buffer parts land firstly when the cabin body lands on the ground, and the effect of shock absorption and protection on the cabin body can be achieved. In order to facilitate the parachute to pop up when the parachute is opened, an elastic traction structure is arranged at the turnover structure, and the elastic traction structure applies traction force to the turnover structure and enables the turnover structure to have a movement trend of being turned outwards.
Further, in the present invention, the upper cabin and the lower cabin constitute a main body part of the nacelle, and the upper cabin and the lower cabin are detachably mounted, and a specific mounting structure thereof is not limited uniquely, and is optimized and set forth as one of the following feasible options: the upper cabin part and the lower cabin part form a hexagonal columnar accommodating space, and the inner top of the accommodating space is horizontal; the fastening structure comprises a plurality of binding pieces, and the upper cabin part and the lower cabin part are bound into a fixed whole by the binding pieces. When the scheme is adopted, the upper cabin part and the lower cabin part can adopt the same structure, namely, the upper cabin part and the lower cabin part respectively comprise three surfaces, and cylindrical containing spaces with six surfaces are formed after the upper cabin part and the lower cabin part are oppositely covered, binding pieces can adopt binding bands, anchor ears and the like, and the binding pieces are wound on the outer surfaces of the upper cabin part and the lower cabin part to realize fixation; in the specific use process, goods are stored in the accommodating space, but when the goods are irregular in size, the lower cabin part can be detached to guarantee the mounting of the goods.
Further, in the present invention, the main supporting beam is used as a main load-bearing member, and the structure thereof may take many different forms, which are not limited only, and is optimized and one of the possible options is: the main supporting beam extends from the front end to the rear end of the accommodating space, a plurality of connecting holes are formed in the main supporting beam, and connecting pieces are arranged at the connecting holes to fix the main supporting beam to the upper cabin part; the main supporting beam is also provided with a weight reduction structure and a packing and fixing structure. When the scheme is adopted, the weight reduction structure is used for reducing the whole weight, so that the load of the unmanned aerial vehicle is reduced, and more loads can be distributed to goods; the packing fixed knot constructs can be used to fixed goods, ensures that the goods remains stable in the delivery process, avoids dropping and collision damage.
Still further, the weight reduction structure on the main supporting beam is generally a hollow structure, which is not limited in particular, and is optimized here and one of the feasible options is shown: the weight reducing structure comprises a plurality of weight reducing holes, the two sides of the main support beam in the extending direction are connected with extending wing plates, and the packaging fixing structure comprises a plurality of fixing holes formed in the extending wing plates. When the scheme is adopted, the extension wing plates can be integrally formed with the main bearing beam, and then the main bearing beam and the extension wing plates are combined to form a U-shaped structure.
Further, in the present invention, the front end support is used for maintaining the structure of the front end of the accommodating space, and the specific structure is not limited only, and is optimized and a feasible choice is shown as follows: the front end support piece include the front end backup pad, the preceding surface laminating bolster of front end backup pad, and the upside edge and the both sides edge of front end backup pad all laminate the internal surface of upper deck portion, the upside edge of front end backup pad is provided with the preceding buckle that is used for connecting the main tributary supporting beam, is provided with a plurality of enhancement nests that are used for strengthening the plate body structure in the front end backup pad. When the scheme is adopted, the front supporting plate is vertically arranged, and the upper side edge and the two side edges of the front supporting plate are connected with the inner surface of the bent edge which is better attached to the upper cabin part.
Still further, in the present invention, the rear end support is used for maintaining the structure of the rear end of the accommodating space, and the specific structure is not limited uniquely, and the arrangement is optimized and one of the feasible options is shown: rear end support piece include the rear end backup pad, the internal surface of cabin portion in all laminating is gone up to the upside edge and the both sides edge of rear end backup pad, and the upside edge of rear end backup pad is provided with the back buckle that is used for connecting the main tributary fagging, is provided with a plurality of enhancement nests that are used for the reinforcing plate body structure in the rear end backup pad. In this way, the rear end support plate is vertically arranged, the height of the rear end support plate is smaller than the inner height of the accommodating space, and a certain gap is reserved between the accommodating space and the tail opening of the nacelle.
Furthermore, in order to conveniently set the parachute, the pod is hung through the parachute after the parachute is put in, so that slow landing is realized, connection of the parachute can be realized through various modes, the connection is not limited uniquely, and the parachute is optimized and one feasible option is selected: the main supporting beam is provided with a connector for connecting a parachute, the connector comprises a connecting part, the upper surface of the connecting part is attached to the main supporting beam, and the connecting part and the main supporting beam are correspondingly provided with a plurality of through holes and are fixedly connected; the lower surface of the connecting part is provided with a hanging part and a hanging hole for connecting the parachute is arranged on the hanging part. When adopting such scheme, can be fixed through welded fastening's mode with connecting portion and articulate portion mutually perpendicular.
Further, in order to achieve better cushioning and shock absorption and protect the cargo in the nacelle from damage, the cushioning member is provided as an elastic member, and the cushioning structure thereof may be constructed in various forms, but is not limited thereto, and the following possible options are provided by way of optimization and improvement: the buffer piece is made of light elastic material, and the front end face of the buffer piece is a conical surface, a spherical surface or an ellipsoidal surface. When the scheme is adopted, materials such as foam and silica gel can be adopted to manufacture the buffer piece, so that the weight can be reduced, and the shock absorption can be realized through the elastic structure.
Further, in the present invention, in order to facilitate reliable connection of the pod, a connection detection structure is provided, and the specific structure is not limited uniquely, and is optimized and set forth as one of the feasible options: the top of the nacelle is provided with a push rod structure, and the push rod structure is used for being matched with a hanging rack on the unmanned aerial vehicle and ensuring that the nacelle is hung in place. When adopting such scheme, the ejector pin cooperates with the detection structure on the unmanned aerial vehicle stores pylon, sets up the signal pole on the stores pylon for example, and after the nacelle cooperation targets in place, the ejector pin supported the signal pole to produce the signal and show that the nacelle has installed to the target in place, otherwise can not produce this signal.
Further, for better stable mounting of the nacelle, auxiliary structures may be provided to help stabilize the nacelle, such as alignment structures and stops to prevent the nacelle from shifting, which are optimized and one of the possible options is: the top of the nacelle is provided with a plurality of stop blocks, and the stop blocks are used for matching with a hanging rack on the unmanned aerial vehicle and keeping the nacelle from shaking in the installation process. When the scheme is adopted, the front and the rear of the lifting lug can be respectively provided with the stop block, and the stability of the nacelle can be kept after the stop block is aligned and matched with the hanging rack.
Compared with the prior art, the invention has the beneficial effects that:
the unmanned aerial vehicle has the advantages that the structure is simple, the overall weight is light, the overall structure is stable and reliable after combination, and the cargo quantity carried by the unmanned aerial vehicle can be increased; after the nacelle is thrown in, the flexible buffer part is used for damping and buffering, so that the impact on the nacelle body can be minimized, the nacelle is prevented from being damaged, and the protection on internal goods is further improved; the nacelle structure is convenient to process and produce, convenient to use and beneficial to reducing use cost.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required in the embodiments will be briefly described below, it should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be considered as limiting the scope, and those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
Fig. 1 is a schematic view of the process after the nacelle is mated with the pylon.
Fig. 2 is a schematic overall structure and a schematic partial enlarged structure of the nacelle.
Fig. 3 is an exploded view of the upper and lower deck portions.
Fig. 4 is a schematic view of the internal structure of the upper chamber portion.
Fig. 5 is a schematic view and a partial structure enlarged schematic view of the upper cabin part with the rear end support part removed.
Fig. 6 is a schematic structural diagram of the connecting head.
Fig. 7 is a schematic view of the overall structure of the front end support.
Fig. 8 is a schematic view of the overall structure of the rear end support.
In the above drawings, the meaning of each symbol is: 1. a nacelle; 2. a waterproof layer; 3. a buffer member; 4. a folding structure; 5. a hanger; 6. lifting lugs; 7. a stopper block; 8. a top rod; 9. an upper cabin part; 10. a lower cabin part; 11. a fastening structure; 12. a front end support; 1201. a front end support plate; 13. a main support beam; 14. lightening holes; 15. an extension wing plate; 16. a fixing hole; 17. a rear end support; 1701. a rear end support plate; 18. a connecting portion; 19. a hanging part; 20. hanging holes; 21. the reinforcing nest.
Detailed Description
The invention is further explained below with reference to the drawings and the specific embodiments.
It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. This invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.
Examples
To the situation that the pod structure in the prior art is complicated, the processing difficulty is large, the use is inconvenient, goods damage is easy to occur after the pod is put in, and the overall use cost is high, the pod structure is optimized and improved by the embodiment so as to solve the problem existing in the prior art.
In this embodiment, the structure of the pod 1 itself is mainly described, and as for the releasing and parachute-opening structure for releasing and assisting the parachute opening in cooperation with the pod 1, many schemes in the prior art can be adopted, and a person skilled in the art can select a scheme to be used in cooperation with this embodiment as needed, and this embodiment is not described again.
Specifically, as shown in fig. 1 to 5, the embodiment discloses a low-cost simple unmanned aerial vehicle nacelle 1 structure, which comprises a cabin body, wherein a lifting lug 6 is arranged at the upper part of the cabin body, and the surface of the cabin body is wrapped by a waterproof layer 2; the tail part of the cabin body is provided with an opening, the waterproof layer 2 forms a plurality of turnover structures 4 at the opening, the opening is closed when the turnover structures 4 are turned inwards, and the opening is opened when the turnover structures 4 are turned outwards; the cabin body includes last cabin portion 9 and lower cabin portion 10, goes up cabin portion 9 and sets up relatively and connect fixedly through fastening structure 11 with lower cabin portion 10, goes up and forms accommodation space between cabin portion 9 and the lower cabin portion 10, and accommodation space's front end sets up bolster 3, and the top sets up main supporting beam 13 in the accommodation space, and main supporting beam 13's both ends are provided with front end support piece 12 and rear end support piece 17 respectively.
The unmanned aerial vehicle pod 1 structure disclosed above has the advantages that the structure of the pod body is simple and the composition is reliable; when the unmanned aerial vehicle is used specifically, the cabin body is connected with a hanging rack 5 on the unmanned aerial vehicle through a lifting lug 6; the main supporting beam 13 plays a main role in supporting and bearing, the accommodating space is used for placing goods, and the front end supporting piece 12, the main supporting beam 13 and the rear end supporting piece 17 ensure that the structure of the whole cabin body is not changed; after the parachute is thrown, the parachute is popped out from the rear end of the accommodating space, the cabin body is kept vertically downward after the parachute is unfolded, the buffer member 3 lands firstly when the cabin body lands on the ground, and the effect of shock absorption and protection on the cabin body can be achieved. In order to facilitate the parachute to pop out when the parachute is opened, an elastic traction structure is arranged at the turnover structure 4, and the elastic traction structure applies traction force to the turnover structure 4 and enables the turnover structure 4 to have a movement trend of turning outwards.
Preferably, in this embodiment, the waterproof layer 2 is made of waterproof cloth, the turning plate is arranged at the turning structure, and the elastic traction structure is an elastic rope.
In the present embodiment, the upper cabin part 9 and the lower cabin part 10 constitute a main body part of the nacelle 1, and the upper cabin part 9 and the lower cabin part 10 are detachably mounted, and the specific mounting structure is not limited uniquely, and is optimized and adopts one of the following feasible options: as shown in fig. 3, the upper cabin part 9 and the lower cabin part 10 form a hexagonal cylindrical accommodating space, and the inner top of the accommodating space is horizontal; the fastening structure 11 comprises a plurality of binding pieces, and the upper cabin part 9 and the lower cabin part 10 are bound into a fixed whole by the binding pieces. When the scheme is adopted, the upper cabin part 9 and the lower cabin part 10 can adopt the same structure, namely, the upper cabin part and the lower cabin part both comprise three surfaces, and form a cylindrical accommodating space with six surfaces after being oppositely covered, binding pieces can adopt binding bands, hoop hoops and the like, and the outer surfaces of the upper cabin part 9 and the lower cabin part 10 are wound to realize fixation; in a specific use process, goods are stored in the accommodating space, but when the goods are irregular in size, the lower cabin part 10 can be detached to ensure the mounting of the goods.
In the present embodiment, the main supporting beam 13 is used as a main load-bearing member, and the structure thereof can take many different forms, which are not limited only, and is optimized and adopts one of the feasible options: as shown in fig. 4 and 5, the main supporting beam 13 extends from the front end to the rear end of the accommodating space, the main supporting beam 13 is provided with a plurality of connecting holes, and the connecting holes are provided with connecting pieces for fixing the main supporting beam 13 to the upper cabin part 9; the main supporting beam 13 is also provided with a weight reduction structure and a packing and fixing structure. When the scheme is adopted, the weight reducing structure is used for reducing the whole weight, so that the load of the unmanned aerial vehicle is reduced, and more loads can be distributed to goods; the packing fixed knot constructs can be used to fixed goods, ensures that the goods remains stable in the delivery process, avoids dropping and collision damage.
The weight reduction structure on the main support beam 13 is generally a hollow structure, and is not limited to the above, and is optimized and adopts one of the feasible options: as shown in fig. 4 and 5, the weight reducing structure includes a plurality of weight reducing holes 14, and two sides of the main support beam 13 in the extending direction are connected with extending wing plates 15, and the packing and fixing structure includes a plurality of fixing holes 16 disposed on the extending wing plates 15. When such a scheme is adopted, the extension wing plate 15 can be integrally formed with the main carrier beam, and then the main carrier beam and the extension wing plate 15 are combined to form a U-shaped structure.
Further, in the present embodiment, the front end support 12 is used for maintaining the structure of the front end of the accommodating space, and the specific structure is not limited only, and is optimized and adopts one of the following feasible options: as shown in fig. 7, the front end supporting member 12 includes a front end supporting plate 1201, the front surface of the front end supporting plate 1201 is attached to the buffer member 3, the upper side edge and the two side edges of the front end supporting plate 1201 are both attached to the inner surface of the upper cabin 9, the upper side edge of the front end supporting plate 1201 is provided with a front buckle plate for connecting the main supporting beam 13, and the front end supporting plate 1201 is provided with a plurality of reinforcing sockets 21 for reinforcing the plate body structure. When the scheme is adopted, the front supporting plate is vertically arranged, and the upper side edge and the two side edges of the front supporting plate are connected with the inner surface of the bent edge which is better attached to the upper cabin part 9.
Preferably, since the accommodating space in this embodiment is a cylindrical hexagon, the edge of the front support plate fits the inner shape of the accommodating space, but the height of the front support plate is half of the accommodating space, and thus the surface of the front support plate is an isosceles trapezoid. In other embodiments, the height of the front support plate may be set to coincide with the height of the accommodation space, and the shape of the front support plate is hexagonal.
In the present embodiment, the rear end support 17 is used for maintaining the structure of the rear end of the accommodating space, and the specific structure is not limited, and the arrangement is optimized and one of the feasible options is adopted: as shown in fig. 8, the rear end support 17 includes a rear end support plate 1701, an upper side edge and two side edges of the rear end support plate 1701 are attached to an inner surface of the upper cabin 9, a rear buckle plate for connecting the main support plate is disposed on the upper side edge of the rear end support plate 1701, and a plurality of reinforcing sockets 21 for reinforcing the plate body structure are disposed on the rear end support plate 1701. With such a configuration, the rear end support plate 1701 is vertically arranged, and the height of the rear end support plate 1701 is smaller than the internal height of the accommodation space, so that a certain clearance is maintained between the accommodation space and the rear opening of the nacelle 1.
Preferably, the height of the rear supporting plate in this embodiment is half of the height of the accommodating space, and the surface is also an isosceles trapezoid.
In order to facilitate the setting of the parachute, the nacelle 1 is hooked by the parachute after the nacelle is dropped to achieve slow descent, and the connection of the parachute can be achieved in various ways, which are not limited uniquely, and is optimized and adopts one of the feasible options: the main supporting beam 13 is provided with a connector for connecting a parachute, the connector comprises a connecting part 18, the upper surface of the connecting part 18 is attached to the main supporting beam 13, and the connecting part 18 and the main supporting beam are correspondingly provided with a plurality of through holes and are fixedly connected; the lower surface of the connecting part 18 is provided with a hanging part 19, and the hanging part 19 is provided with a hanging hole 20 for connecting a parachute. When the scheme is adopted, the connecting part 18 and the hanging part 19 can be perpendicular to each other and fixed in a welding and fixing mode.
Preferably, as shown in fig. 6, in this embodiment, the connector is formed by two L-shaped angle steels, and the angle steels are spliced together to form the connector with a T-shaped structure.
Preferably, in order to achieve better damping and shock absorption and protect the goods in the nacelle 1 from damage, the damping element 3 is provided as an elastic element, and the embodiment is optimized and modified and adopts one of the following feasible options: the buffer member 3 is made of a light elastic material, and the front end surface of the buffer member 3 is a conical surface, a spherical surface or an ellipsoidal surface. When adopting such scheme, can adopt materials such as foam, silica gel to make bolster 3, can enough lighten weight, also can realize the shock attenuation through elastic construction.
In the present embodiment, in order to facilitate reliable connection of the pod 1, a connection detection structure is provided, and the specific structure is not limited, and is optimized and adopts one of the feasible options: the top of the nacelle 1 is provided with a mandril 8 structure, and the mandril 8 structure is used for matching with a hanging rack 5 on the unmanned aerial vehicle and ensuring that the nacelle 1 is hung in place. When the scheme is adopted, the ejector rod 8 is matched with a detection structure on the unmanned aerial vehicle hanging rack 5, for example, a signal rod is arranged on the hanging rack 5, and after the nacelle 1 is matched in place, the ejector rod 8 pushes against the signal rod, so that a signal is generated to indicate that the nacelle 1 is installed in place, otherwise, the signal cannot be generated.
For better stable mounting of the nacelle 1, auxiliary structures may be provided to help stabilize the nacelle 1, such as alignment structures and limit structures to prevent the nacelle 1 from shifting, where optimization and use one of the possible options: the top of the nacelle 1 is provided with a plurality of stop blocks 7, and the stop blocks 7 are used for matching with a hanging rack 5 on the unmanned aerial vehicle and keeping the nacelle 1 free of shaking in the installation process. When the scheme is adopted, the front part and the rear part of the lifting lug 6 are respectively provided with the stop blocks 7, and the stability of the nacelle 1 can be kept after the stop blocks are aligned and matched with the hanging rack 5.
Preferably, the stop block in this embodiment may be, but not limited to, a polygonal or circular structural member, which is fixedly disposed on the surface of the nacelle, and is provided with a directional rod or a limiting rod protruding from the surface of the nacelle, so as to be conveniently butted against the pylon and kept relatively still.
The above embodiments are just exemplified in the present embodiment, but the present embodiment is not limited to the above alternative embodiments, and those skilled in the art can obtain other various embodiments by arbitrarily combining with each other according to the above embodiments, and any other various embodiments can be obtained by anyone in light of the present embodiment. The above detailed description should not be construed as limiting the scope of the present embodiments, which should be defined in the claims, and the description should be used for interpreting the claims.
Claims (10)
1. The utility model provides a simple and easy unmanned aerial vehicle nacelle structure of low cost which characterized in that: the device comprises a cabin body, wherein the upper part of the cabin body is provided with a lifting lug (6), and the surface of the cabin body is wrapped by a waterproof layer (2); the tail part of the cabin body is provided with an opening, the waterproof layer (2) forms a plurality of turnover structures (4) at the opening, the opening is closed when the turnover structures (4) are turned inwards, and the opening is opened when the turnover structures (4) are turned outwards; the cabin body comprises an upper cabin part (9) and a lower cabin part (10), the upper cabin part (9) and the lower cabin part (10) are installed in a separable mode and are fixedly connected through a fastening structure (11), and when the size of goods is irregular, the lower cabin part (10) is detached to guarantee the hanging of the goods; fastening structure (11) are a plurality of ligatures, and the ligature is with last cabin portion (9) and lower cabin portion (10) ligature for fixed whole, forms accommodation space between last cabin portion (9) and lower cabin portion (10), and accommodation space's front end sets up bolster (3), and the top sets up main tributary supporting beam (13) in the accommodation space, and the both ends of main tributary supporting beam (13) are provided with front end support piece (12) and rear end support piece (17) respectively.
2. The low cost improvised drone pod structure of claim 1, characterized by: the upper cabin part (9) and the lower cabin part (10) form a hexagonal columnar accommodating space, and the top of the accommodating space is horizontal.
3. The low cost improvised drone pod structure of claim 2, characterized by: the main supporting beam (13) extends from the front end to the rear end of the accommodating space, a plurality of connecting holes are formed in the main supporting beam (13), and connecting pieces are arranged at the connecting holes to fix the main supporting beam (13) on the upper cabin part (9); the main supporting beam (13) is also provided with a weight reduction structure and a packing and fixing structure.
4. The low cost improvised drone pod structure of claim 3, characterized by: the weight reducing structure comprises a plurality of weight reducing holes (14), extending wing plates (15) are connected to two sides of the extending direction of the main supporting beam (13), and the packaging fixing structure comprises a plurality of fixing holes (16) formed in the extending wing plates (15).
5. The low cost simple unmanned aerial vehicle pod structure of claim 1, wherein: the front end supporting piece (12) comprises a front end supporting plate (1201), a front surface of the front end supporting plate (1201) is attached to a buffer piece (3), the upper side edge and the two side edges of the front end supporting plate (1201) are attached to the inner surface of the upper cabin part (9), a front buckle plate used for being connected with a main supporting beam (13) is arranged on the upper side edge of the front end supporting plate (1201), and a plurality of reinforcing pits (21) used for reinforcing a plate body structure are arranged on the front end supporting plate (1201).
6. The low cost improvised drone pod structure of claim 1, characterized by: rear end support piece (17) include rear end backup pad (1701), the internal surface of upper deck portion (9) is all laminated to the upside edge and the both sides edge of rear end backup pad (1701), and the upside edge of rear end backup pad (1701) is provided with the back buckle that is used for connecting the main tributary fagging, is provided with a plurality of enhancement nests (21) that are used for strengthening the plate body structure on rear end backup pad (1701).
7. The low cost improvised drone pod structure of claim 1, characterized by: the main supporting beam (13) is provided with a connector for connecting a parachute, the connector comprises a connecting part (18), the upper surface of the connecting part (18) is attached to the main supporting beam (13), and the connecting part (18) and the main supporting beam are correspondingly provided with a plurality of through holes and are fixedly connected; the lower surface of the connecting part (18) is provided with a hanging part (19), and the hanging part (19) is provided with a hanging hole (20) for connecting a parachute.
8. The low cost improvised drone pod structure of claim 1, characterized by: the buffer piece (3) is made of light elastic material, and the front end surface of the buffer piece (3) is a conical surface, a spherical surface or an ellipsoidal surface.
9. The low cost improvised drone pod structure of claim 1, characterized by: the top of nacelle (1) be provided with ejector pin (8) structure, ejector pin (8) structure is used for coordinating stores pylon (5) on the unmanned aerial vehicle and ensures that nacelle (1) articulates and targets in place.
10. The low cost improvised drone pod structure of claim 1, characterized by: the top of the nacelle (1) is provided with a plurality of stop blocks (7), and the stop blocks (7) are used for matching with a hanging rack (5) on the unmanned aerial vehicle and keeping the nacelle (1) free of shaking in the installation process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210165209.8A CN114229010B (en) | 2022-02-23 | 2022-02-23 | Low-cost simple unmanned aerial vehicle nacelle structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210165209.8A CN114229010B (en) | 2022-02-23 | 2022-02-23 | Low-cost simple unmanned aerial vehicle nacelle structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114229010A CN114229010A (en) | 2022-03-25 |
| CN114229010B true CN114229010B (en) | 2022-07-01 |
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| CN116534266B (en) * | 2023-07-06 | 2024-01-05 | 中国电子科技集团公司第二十九研究所 | Airborne high-rigidity and lightweight electronic nacelle body and assembly method |
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| CN114229010A (en) | 2022-03-25 |
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