Umbrella cabin support and unmanned aerial vehicle

Abstract

The utility model discloses a kind of umbrella cabin support and unmanned aerial vehicle, umbrella cabin support includes: top plate, first side frame, second side frame and bottom plate, top plate is provided with a plurality of first mounting hole for assembling umbrella cabin;First side frame and second side frame are respectively detachably connected to the opposite sides of the bottom surface of top plate, and first side frame and second side frame are all provided with second mounting hole for assembling unmanned aerial vehicle fuselage;The opposite sides of the top surface of bottom plate are respectively detachably connected to first side frame and second side frame;Among them, top plate and bottom plate are carbon fiber material, first side frame and second side frame are aluminum alloy material.The umbrella cabin support of the utility model, by selecting carbon fiber material for the top plate and bottom plate of umbrella cabin support, to realize light weight and keep high strength;First side frame and second side frame are made of aluminum alloy material, to ensure the firmness and durability of structure;Both realize the light weight of umbrella cabin support, and ensure the strength and stability connected with unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a parachute cabin support and an UAV. Background Technology

[0002] With the rapid development of drone technology, the application fields of drones are constantly expanding, covering multiple industries such as aerial photography, agricultural plant protection, resource exploration, surveying and mapping, power line inspection, and emergency rescue, and their operating environments are becoming increasingly complex and diverse. As drones fly at higher altitudes and the mission environments become more complex, higher demands are placed on their safety performance. Drone parachute technology has emerged to address this need. In emergencies, it can provide a final safety barrier for drones, reducing damage to ground personnel and equipment upon crash, while simultaneously protecting the drone itself from destruction and minimizing economic losses.

[0003] The parachute compartment support is a key component connecting the parachute compartment and the drone. Currently, most of them adopt an integrated molding structure and are manufactured as a whole using a single material. The drawback of this is that a single material cannot meet the dual requirements of lightweight and high strength, which limits the overall flight performance of the drone. Utility Model Content

[0004] The main purpose of this utility model is to overcome the shortcomings and deficiencies of the prior art and provide a parachute cabin support and a drone, aiming to solve the problems in the prior art.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] In a first aspect, this utility model provides a parachute compartment support, comprising: a top plate, a first side frame, a second side frame, and a bottom plate. The top plate is provided with a plurality of first mounting holes for assembling the parachute compartment. The first side frame and the second side frame are detachably connected to opposite sides of the bottom surface of the top plate, and both the first side frame and the second side frame are provided with second mounting holes for assembling the fuselage of a drone. The opposite sides of the top surface of the bottom plate are detachably connected to the first side frame and the second side frame. The top plate, the first side frame, the second side frame, and the bottom plate form a fuselage space for enclosing the fuselage. The top plate and the bottom plate are made of carbon fiber, and the first side frame and the second side frame are made of aluminum alloy.

[0007] Furthermore, multiple first mounting holes are provided, and the multiple first mounting holes are evenly distributed in a circle around the central axis of the top plate.

[0008] Furthermore, the top plate is also provided with multiple hollow holes, which are evenly distributed around the central axis of the top plate.

[0009] Furthermore, the first side frame includes an outer frame, an oblique reinforcing beam, and a transverse reinforcing beam. The upper side of the outer frame is connected to the top plate. The oblique reinforcing beam is provided between the upper side and the left side and between the upper side and the right side of the outer frame. The transverse reinforcing beam is provided between the left side and the right side of the outer frame.

[0010] The second side frame has the same structure as the first side frame, and the second side frame and the first side frame are arranged symmetrically.

[0011] Furthermore, a heat dissipation area for the UAV is formed between the outer frame and the transverse reinforcing beam.

[0012] Furthermore, both the first side frame and the second side frame are provided with at least two second mounting holes, which are equally spaced along the direction from the top plate to the bottom plate on the first side frame and the second side frame.

[0013] Secondly, this utility model provides a drone, including a fuselage, a parachute compartment, and the parachute compartment support described in the first aspect. The parachute compartment is connected to a first mounting hole via a connector, and the fuselage is located in the fuselage space and connected to a second mounting hole via a connector.

[0014] Furthermore, the drone is a multi-rotor drone.

[0015] Compared with the prior art, this utility model has the following advantages and beneficial effects: the parachute cabin support of this utility model uses carbon fiber material for the top and bottom plates of the parachute cabin support to achieve lightweight while maintaining high strength; the first and second side frames are made of aluminum alloy material to ensure the structural strength and durability; it achieves both lightweighting of the parachute cabin support and ensures the strength and stability of the connection with the drone. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the embodiments of this utility model will be briefly introduced below.

[0017] Figure 1 This is a first structural schematic diagram of the unmanned aerial vehicle according to an embodiment of the present invention;

[0018] Figure 2 This is a schematic diagram of the structure of the umbrella compartment bracket connecting the umbrella compartment according to an embodiment of the present invention;

[0019] Figure 3 This is a schematic diagram of the structure of the parachute compartment support according to an embodiment of the present invention;

[0020] Figure 4 This is an exploded view of the parachute compartment support according to an embodiment of this utility model;

[0021] Figure 5 This is a top view of the parachute compartment support according to an embodiment of the present invention;

[0022] Figure 6 This is a schematic diagram of the second structure of the UAV according to an embodiment of the present invention;

[0023] Figure 7 This is a schematic diagram of the third structure of the UAV according to an embodiment of the present utility model;

[0024] Figure 8 This is a schematic diagram of the internal structure of the liquid spraying warning component of the drone according to an embodiment of the present invention.

[0025] Explanation of reference numerals in the attached figures:

[0026] 10. Drone; 11. Airframe;

[0027] 20. Parachute compartment;

[0028] 30. Parachute compartment support; 31. Top plate; 311. First mounting hole; 312. Hole opening; 32. First side frame; 321. Outer frame; 322. Diagonal reinforcing beam; 323. Transverse reinforcing beam; 324. Second mounting hole; 325. Heat dissipation area; 33. Second side frame; 34. Base plate;

[0029] 40. Spray indicator component; 41. Liquid tank; 411. Liquid outlet; 42. Easy-tear film; 43. Gas generator; 44. Airbag; 45. Fluorescent liquid. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0032] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0033] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0034] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0035] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0036] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. The illustrative expressions of the above terms in this specification should not be construed as necessarily referring to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0037] Please see Figure 1 This utility model provides a drone 10, including a fuselage 11, a parachute compartment 20, and a parachute compartment support 30. The parachute compartment 20 is connected to a first mounting hole 311 via a connector. The fuselage 11 is located in the space of the fuselage 11 and is connected to a second mounting hole 324 via a connector. Specifically, the parachute compartment 20 is bolted to the first mounting hole 311. The parachute compartment 20 is provided with a first connecting hole corresponding to the first mounting hole 311. The first connecting hole and / or the second mounting hole 324 are provided with an internal thread structure. The bolts securely connect the parachute compartment 20 and the top plate 31 through threaded engagement. The fuselage 11 is bolted to the second mounting hole 324. The fuselage 11 is provided with a second connecting hole corresponding to the second mounting hole 324. The second connecting hole and / or the second mounting hole 324 are provided with an internal thread structure. The bolts securely connect the first side frame 32 and the second side frame 33 to the fuselage 11 through threaded engagement. Furthermore, the drone 10 is a multi-rotor drone 10.

[0038] It should be noted that the screws used to connect the top plate 31 to the first side frame 32 and the second side frame 33 should avoid the area where the parachute compartment 20 is installed on the top plate 31, so as to prevent the recoil force generated when the parachute compartment 20 is activated from hitting the screws and damaging the shell of the parachute compartment 20.

[0039] Please see Figures 2 to 5 The parachute compartment support 30 includes a top plate 31, a first side frame 32, a second side frame 33, and a bottom plate 34. The top plate 31 is provided with a plurality of first mounting holes 311 for assembling the parachute compartment 20. The first side frame 32 and the second side frame 33 are detachably connected to opposite sides of the bottom surface of the top plate 31, and both the first side frame 32 and the second side frame 33 are provided with second mounting holes 324 for assembling the fuselage 11 of the UAV 10. The opposite sides of the top surface of the bottom plate 34 are detachably connected to the first side frame 32 and the second side frame 33. The top plate 31, the first side frame 32, the second side frame 33, and the bottom plate 34 form a fuselage 11 space for enclosing the fuselage 11. The top plate 31 and the bottom plate 34 are made of carbon fiber, and the first side frame 32 and the second side frame 33 are made of aluminum alloy.

[0040] It should be explained that the top plate 31 and bottom plate 34 are made of carbon fiber, utilizing its lightweight and high-strength properties to achieve weight reduction while ensuring structural strength. The first side frame 32 and the second side frame 33 are made of aluminum alloy. Aluminum alloy has high strength, good toughness, and relatively light weight, which can meet the stress requirements at the connection with the UAV 10. Specifically, the top plate 31 and bottom plate 34 mainly bear the weight from the parachute compartment 20 and the airflow impact force during flight. Because they are made of carbon fiber, they effectively reduce their own weight while ensuring load-bearing capacity, reducing the burden on the UAV 10 during flight. The first side frame 32 and the second side frame 33 mainly bear the weight of the UAV 10 fuselage 11, various complex loads during flight, and the force transmitted at the connection with the top plate 31 and bottom plate 34. The aluminum alloy material gives it sufficient strength and toughness to resist these forces, ensuring the stability and reliability of the connection and ensuring the safety of the UAV 10 during flight.

[0041] Optionally, the first side frame 32, the second side frame 33 and the top plate 31 are detachably connected by screws, and the first side frame 32, the second side frame 33 and the bottom plate 34 are detachably connected by screws.

[0042] Optionally, the first side frame 32 and the second side frame 33 are perpendicular to the top plate 31, the first side frame 32 and the second side frame 33 are perpendicular to the bottom plate 34, the top plate 31 and the bottom plate 34 are parallel, and the first side frame 32 and the second side frame 33 are parallel.

[0043] Optionally, a first magnet is provided at the connection point of the first side frame 32 and the second side frame 33 corresponding to the top plate 31, and a second magnet is provided at the connection point of the top plate 31 corresponding to the first side frame 32 and the second side frame 33. The first magnet and the second magnet are magnetically attracted to each other, so that the first side frame 32, the second side frame 33 and the top plate 31 can be quickly aligned during the assembly stage, making it convenient for workers to insert screws and facilitating the connection and assembly of the first side frame 32, the second side frame 33 and the top plate 31. Optionally, a third magnet is provided at the connection point of the first side frame 32 and the second side frame 33 corresponding to the bottom plate 34, and a fourth magnet is provided at the connection point of the bottom plate 34 corresponding to the first side frame 32 and the second side frame 33. The third magnet and the fourth magnet are magnetically attracted to each other, so that the first side frame 32, the second side frame 33 and the bottom plate 34 can be quickly aligned during the assembly stage, making it convenient for workers to insert screws and facilitating the connection and assembly of the first side frame 32, the second side frame 33 and the bottom plate 34.

[0044] Understandably, the top plate 31 is provided with a first mounting hole 311 for mounting and fixing the parachute compartment 20; the first side frame 32 and the second side frame 33 are provided with a second mounting hole 324 for connecting the entire parachute compartment bracket 30 to the fuselage 11 of the UAV 10. Through the parachute compartment bracket 30 of this embodiment, the weight and force of the parachute compartment 20 can be distributed to multiple parts of the fuselage 11 of the UAV 10, avoiding uneven force and loosening risk caused by single-point connection, and enhancing the stability of the parachute compartment 20 during flight.

[0045] In some embodiments, multiple first mounting holes 311 are provided, and the multiple first mounting holes 311 are evenly distributed circumferentially around the central axis of the top plate 31. Specifically, in this embodiment, four first mounting holes 311 are provided. When the parachute compartment 20 is subjected to forces from various directions, the multiple evenly distributed first mounting holes 311 can transmit these forces to the top plate 31 more evenly, thereby reducing stress concentration at the connection points of the top plate 31.

[0046] In some embodiments, the top plate 31 is further provided with a plurality of perforated holes 312, which are evenly distributed circumferentially around the central axis of the top plate 31. Optionally, the perforated holes 312 have an arcuate shape, and the plurality of perforated holes 312 are distributed circumferentially to form a discontinuous annular perforated structure coaxial with the central axis of the top plate 31. Optionally, the top plate 31 is provided with a plurality of annular perforated structures with different radii.

[0047] Specifically, the perforated holes 312 are designed to further reduce weight while ensuring the structural strength of the top plate 31 meets requirements, thereby reducing the overall weight of the UAV 10 and improving its flight efficiency and endurance. Furthermore, the perforated holes 312 can also improve the heat dissipation performance of the top plate 31 to some extent, preventing localized overheating from affecting component lifespan and flight safety.

[0048] In some embodiments, the first side frame 32 includes an outer frame 321, an oblique reinforcing beam 322, and a transverse reinforcing beam 323. The upper side of the outer frame 321 is connected to the top plate 31. An oblique reinforcing beam 322 is provided between the upper side and the left side and between the upper side and the right side of the outer frame 321. A transverse reinforcing beam 323 is provided between the left side and the right side of the outer frame 321. The second side frame 33 has the same structure as the first side frame 32, and the second side frame 33 and the first side frame 32 are symmetrically arranged.

[0049] It is understood that by setting the oblique reinforcing beam 322 and the transverse reinforcing beam 323 in this embodiment, the structural strength and stability of the first side frame 32 and the second side frame 33 are significantly enhanced, enabling the first side frame 32 and the second side frame 33 to effectively bear and transmit various complex loads during flight, reducing the risk of deformation and damage to the first side frame 32 and the second side frame 33 during use, and ensuring the safety and reliability of the UAV 10 flight.

[0050] Furthermore, a heat dissipation area 325 is formed between the outer frame 321 and the transverse reinforcing beam 323 for dissipating heat from the UAV 10. This heat dissipation area 325 provides excellent heat dissipation conditions for the UAV 10. During flight, the heat generated by the UAV 10 can be quickly dissipated through the heat dissipation area 325, reducing the risk of component overheating, extending its service life, and improving the reliability and safety of the UAV 10.

[0051] In some embodiments, the first side frame 32 and the second side frame 33 are each provided with four second mounting holes 324, which are arranged in a matrix in the first side frame 32 and the second side frame 33.

[0052] In some embodiments, the top plate 31 is a one-piece molded structure, the first side frame 32 is a one-piece molded structure, the second side frame 33 is a one-piece molded structure, and the bottom plate 34 is a one-piece molded structure. In some embodiments, the top plate 31, the bottom plate 34, and the parachute cabin support 30 are all axisymmetric structures, and the axis of symmetry of the top plate 31 and the axis of symmetry of the bottom plate 34 are located on the plane of symmetry of the parachute cabin support 30.

[0053] Please see Figures 6 to 8 Optionally, considering that in densely populated urban areas, simply using the parachute compartment 20 to launch a parachute to reduce the damage to ground units caused by the fall of the drone 10 may not be effective, as some people may not be able to see the landing drone 10 in time. In this embodiment, the drone 10 has a liquid spraying indicator component 40 installed on the underside of the base plate 34. When the parachute compartment 20 is triggered to launch the parachute, the liquid spraying indicator component 40 sprays the liquid stored within it downwards. It can be understood that by installing the liquid spraying indicator component 40 on the underside of the base plate 34, this embodiment can spray liquid downwards at the same time as the parachute compartment 20 launches the parachute, allowing ground personnel to see the landing drone 10 in time after contacting the liquid, thus avoiding accidents caused by ignoring the abnormality of the drone 10.

[0054] Furthermore, the liquid spray indicator component 40 includes a liquid container 41, an easy-tear film 42, a gas generator 43, and an airbag 44. The liquid container 41 is installed on the bottom side of the base plate 34, and has a liquid storage chamber for storing liquid. The gas generator 43 is installed on the top of the liquid storage chamber, and the air inlet of the airbag 44 is connected to the gas generator 43. The bottom side of the liquid container 41 is provided with several liquid outlet holes 411 connected to the liquid storage chamber, and the easy-tear film 42 is attached to the liquid outlet holes 411. Optionally, the liquid stored in the liquid container 41 is fluorescent liquid 45.

[0055] Specifically, in standby mode, the liquid is stored in the reservoir of liquid box 41, and the easy-tear film 42 keeps the liquid outlet 411 closed to prevent liquid leakage. The gas generator 43 is inactive. When the UAV 10 makes an emergency landing and triggers the parachute compartment 20, the liquid spraying warning component 40 is triggered simultaneously. The gas generator 43 starts and quickly generates a large amount of gas. The gas generated by the gas generator 43 enters the airbag 44, causing the airbag 44 to inflate and squeeze the liquid in the reservoir towards the liquid outlet 411. The easy-tear film 42 ruptures due to the pressure exceeding its limit. The liquid, pushed by the airbag 44 in the reservoir, is sprayed out from the liquid outlet 411, alerting ground personnel to the abnormal status and location of the UAV 10 until the UAV 10 lands safely or the liquid spraying is completed.

[0056] Furthermore, the outlet holes 411 are arranged in a matrix on the bottom side of the liquid box 41, and the tilt angle of the outlet holes 411 gradually increases from the center of the liquid box 41 outwards. The central axis of the outlet hole 411 located at the center of the liquid box 41 coincides with the central axis of the liquid box 41. Optionally, the angle between the outlet hole 411 furthest from the center of the liquid box 41 and the vertical direction is 30°. Specifically, in this embodiment, the tilt angle refers to the angle between the central axis of the outlet hole 411 and the vertical direction. In this embodiment, outlet holes 411 with a tilt angle greater than 0° are all tilted with their upper ends close to the central axis of the liquid box 41 and their lower ends far away from the central axis of the liquid box 41.

[0057] Specifically, this embodiment adjusts the angle of the liquid outlet 411 to make the liquid form a uniform fan-shaped distribution during spraying, ensuring that the liquid can cover a larger area, while avoiding mutual interference or overlap of liquids during spraying, improving spraying efficiency, and further enhancing the awareness of surrounding personnel regarding abnormal states of the drone 10, ensuring timely avoidance and preventing potential dangers.

[0058] The above embodiments are preferred embodiments of the present utility model, but the embodiments of the present utility model are not limited to the above embodiments. Any changes, modifications, substitutions, combinations, or simplifications made without departing from the spirit and principle of the present utility model shall be regarded as equivalent substitutions and shall be included within the protection scope of the present utility model.

Claims

1. A parachute compartment support, characterized in that, include: The device comprises a top plate, a first side frame, a second side frame, and a bottom plate. The top plate has multiple first mounting holes for assembling the parachute compartment. The first and second side frames are detachably connected to opposite sides of the bottom surface of the top plate, and both the first and second side frames have second mounting holes for assembling the drone fuselage. The opposite sides of the top surface of the bottom plate are detachably connected to the first and second side frames. The top plate, the first side frame, the second side frame, and the bottom plate form a fuselage space for enclosing the drone fuselage. The top plate and the bottom plate are made of carbon fiber, and the first and second side frames are made of aluminum alloy.

2. The parachute compartment support according to claim 1, characterized in that, The first mounting hole is provided in multiple ways, and the multiple first mounting holes are evenly distributed in a circle around the central axis of the top plate.

3. The parachute compartment support according to claim 1, characterized in that, The top plate is also provided with multiple hollow holes, which are evenly distributed around the central axis of the top plate.

4. The parachute compartment support according to claim 1, characterized in that, The first side frame includes an outer frame, diagonal reinforcing beams, and transverse reinforcing beams. The upper side of the outer frame is connected to the top plate. The diagonal reinforcing beams are provided between the upper side and the left side and between the upper side and the right side of the outer frame. The transverse reinforcing beams are provided between the left side and the right side of the outer frame. The second side frame has the same structure as the first side frame, and the second side frame and the first side frame are arranged symmetrically.

5. The parachute compartment support according to claim 4, characterized in that, A heat dissipation area is formed between the outer frame and the transverse reinforcing beam for the drone to dissipate heat.

6. The parachute compartment support according to claim 1, characterized in that, Both the first side frame and the second side frame are provided with four second mounting holes, which are arranged in a matrix on the first side frame and the second side frame.

7. A drone, characterized in that, The device includes a fuselage, a parachute compartment, and a parachute compartment support as described in any one of claims 1-6. The parachute compartment is connected to a first mounting hole via a connector, and the fuselage is located in the fuselage space and connected to a second mounting hole via a connector.

8. The UAV according to claim 7, characterized in that, The drone in question is a multi-rotor drone.

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