Parachute bay support, parachute bay assembly and unmanned aerial vehicle

Abstract

The utility model discloses a parachute bay support, a parachute bay assembly and an unmanned aerial vehicle, the parachute bay support comprises a top mounting plate and side mounting plates connected to the two sides of the top mounting plate, the top mounting plate is provided with a parachute bay mounting part used for mounting a parachute bay, and the side mounting plates are provided with fuselage mounting parts used for mounting a fuselage. According to the parachute bay support, the fuselage is installed through the side installation plates, after the parachute bay support is connected with the top installation plate, stress of a parachute bay can be dispersed to multiple positions of the fuselage of the unmanned aerial vehicle, and the risks of uneven stress and looseness caused by single-point or local connection are avoided; the problem that in the prior art, a parachute bay is not reliably fixed due to bolt looseness is solved, and the safety of the unmanned aerial vehicle in the flight process is effectively improved.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a parachute compartment bracket, a parachute compartment assembly, 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] For example, the patent document with patent authorization announcement number CN204415737U describes a structure that includes a parachute compartment, a compartment cover, and a parachute, a parachute opening controller for calculating the drone's flight attitude, and a compartment cover switch; the parachute compartment has two cross-shaped ejection elastic bands in the middle, and the parachute is placed between the ejection elastic bands and the compartment cover; the parachute opening controller calculates the drone's attitude in real time, and issues an opening command when the drone becomes out of control or its attitude becomes abnormal, thus opening the parachute for protection.

[0004] Based on the search of the aforementioned patent grant announcement numbers, and considering their shortcomings, the following was found:

[0005] In existing drones, the parachute compartment is integrated into the drone during the design phase. However, for some drones that are not equipped with a parachute compartment, the parachute compartment is usually directly connected to the drone using bolts. In drones where the parachute compartment is directly connected by bolts, the bolts may loosen during flight due to factors such as vibration, affecting the stability of the parachute compartment. This may even cause the parachute to fail to activate properly in an emergency, posing a safety hazard. Utility Model Content

[0006] The main purpose of this utility model is to overcome the shortcomings and deficiencies of the prior art and provide a parachute cabin support, a parachute cabin assembly, and a drone, aiming to solve the problems in the prior art.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] In a first aspect, the present invention provides a parachute compartment bracket, comprising: a top mounting plate and side mounting plates connected to both sides of the top mounting plate, wherein the top mounting plate is provided with a parachute compartment mounting part for mounting the parachute compartment, and the side mounting plates are provided with a fuselage mounting part for mounting the fuselage.

[0009] Furthermore, the parachute compartment mounting section includes a plurality of first mounting holes for bolts to pass through, and the plurality of first mounting holes are circumferentially distributed.

[0010] Furthermore, the top mounting plate is also provided with multiple perforated holes, which are distributed circumferentially.

[0011] Furthermore, the side mounting plate includes an outer frame, diagonal reinforcing beams, and transverse reinforcing beams. The outer frame includes an upper frame, a left frame, and a right frame. The upper frame is connected to the top mounting plate. The diagonal reinforcing beams are provided between the upper frame and the left frame, and between the upper frame and the right frame. The transverse reinforcing beams are provided between the left frame and the right frame.

[0012] Furthermore, a heat dissipation area for the UAV is formed between the outer frame and the diagonal reinforcing beam and / or between the outer frame and the transverse reinforcing beam and / or between the diagonal reinforcing beam and the transverse reinforcing beam.

[0013] Furthermore, the fuselage mounting section includes a plurality of second mounting holes for bolts to pass through.

[0014] Furthermore, the parachute compartment support also includes a bottom mounting plate, the upper side of the side mounting plate is connected to the top mounting plate, and the lower side of the side mounting plate is connected to the bottom mounting plate.

[0015] Furthermore, the bottom mounting plate is an X-shaped structure with four ends, and the connection points between the bottom mounting plate and the side mounting plate are located at the four ends of the bottom mounting plate, respectively.

[0016] Secondly, this utility model provides a parachute compartment assembly, including a parachute compartment, a controller, and the parachute compartment bracket described in the first aspect. The parachute compartment is installed in the parachute compartment mounting part, and the controller is electrically connected to the parachute compartment.

[0017] Thirdly, this utility model provides a drone, including a drone body and the parachute assembly described in the second aspect, wherein the drone body is connected to the inner side of the parachute support of the parachute assembly.

[0018] Compared with the prior art, this utility model has the following advantages and beneficial effects: The parachute compartment bracket of this utility model installs the parachute compartment through the top mounting plate, ensuring the stability of the parachute compartment during flight; the fuselage is installed through the side mounting plate, and after it is connected with the top mounting plate, the force of the parachute compartment can be distributed to multiple positions of the UAV fuselage, avoiding the risk of uneven force and loosening caused by single point or local connection, solving the problem of unreliable parachute compartment fixation caused by loose bolts in the prior art, and effectively improving the safety of UAV during flight. Attached Figure Description

[0019] 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.

[0020] Figure 1 This is a schematic diagram of the structure of the drone according to an embodiment of the present invention;

[0021] Figure 2 This is a structural schematic diagram of the parachute compartment assembly according to an embodiment of the present utility model;

[0022] Figure 3 This is an exploded view of the parachute assembly according to an embodiment of this utility model;

[0023] Figure 4 This is a three-dimensional structural schematic diagram of the parachute compartment support according to an embodiment of the present utility model;

[0024] Figure 5 This is an exploded view of the parachute compartment support according to an embodiment of this utility model;

[0025] Figure 6 This is a top view of the parachute cabin support according to an embodiment of this utility model.

[0026] Explanation of reference numerals in the attached figures:

[0027] 10. Drone; 11. Drone body;

[0028] 20. Parachute compartment assembly; 21. Parachute compartment; 22. Controller;

[0029] 30. Parachute compartment support; 31. Top mounting plate; 311. Parachute compartment mounting section; 312. Hole opening; 32. Side mounting plate; 321. Outer frame; 322. Diagonal reinforcing beam; 323. Lateral reinforcing beam; 324. Fuselage mounting section; 325. Heat dissipation area; 33. Bottom mounting plate. 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 drone body 11 and a parachute compartment assembly 20. The drone body 11 is connected to the inner side of the parachute compartment support 30 of the parachute compartment assembly 20. Specifically, the drone body 11 and the parachute compartment support 30 are connected by bolts or screws.

[0038] Understandably, compared to directly connecting the parachute compartment 21 to the drone body 11 with bolts, this embodiment distributes the stress points through the parachute compartment bracket 30, reducing the risk of the parachute compartment 21 falling off due to a single loose bolt, improving the reliability of the parachute's activation in emergency situations, and ensuring the safety of the drone 10's flight. Specifically, this embodiment uses bolts or screws as fasteners, and by designing corresponding connection holes on the drone body 11 and the parachute compartment bracket 30, the drone body 11 and the parachute compartment bracket 30 are tightly connected together. At the same time, the parachute compartment bracket 30 evenly distributes the weight and stress of the parachute compartment 21 onto the drone body 11, effectively ensuring that the parachute compartment 21 can be activated normally in emergency situations.

[0039] like Figure 2 and Figure 3 As shown, the parachute assembly 20 includes a parachute compartment 21, a controller 22, and a parachute compartment support 30. The parachute compartment 21 is mounted on the parachute compartment mounting part 311, and the controller 22 is electrically connected to the parachute compartment 21. The controller 22 can be an ECU (Electronic Control Unit) specifically configured in the parachute compartment 21, or it can be a control system configured in the UAV body 11. It should be explained that the controller 22 is used to monitor the flight status of the UAV 10 and activate the parachute compartment 21 according to the flight status of the UAV 10 or according to the control commands of the UAV 10, thereby activating the activation device installed in the parachute compartment 21 and launching the parachute installed in the parachute compartment 21.

[0040] like Figures 4 to 6As shown, the parachute compartment support 30 includes a top mounting plate 31 and side mounting plates 32 connected to both sides of the top mounting plate 31. The top mounting plate 31 is provided with a parachute compartment mounting part 311 for mounting the parachute compartment 21, and the side mounting plates 32 are provided with a fuselage mounting part 324 for mounting the fuselage. Specifically, there is one top mounting plate 31 and two side mounting plates 32, with the upper ends of the two side mounting plates 32 respectively connected to both sides of the top mounting plate 31. Optionally, the side mounting plates 32 are perpendicular to the top mounting plate 31.

[0041] Understandably, the top mounting plate 31 is provided with a parachute compartment mounting part 311 for mounting and fixing the parachute compartment 21; the side mounting plate 32 is provided with a fuselage mounting part 324 for connecting the entire bracket to the fuselage of the UAV 10. Through the parachute compartment bracket 30 of this embodiment, the weight and force of the parachute compartment 21 can be distributed to multiple parts of the fuselage of the UAV 10, avoiding uneven force and loosening risk caused by single-point connection, and enhancing the stability of the parachute compartment 21 during flight.

[0042] In some embodiments, the parachute compartment mounting portion 311 includes a plurality of first mounting holes for bolts to pass through, the plurality of first mounting holes being circumferentially distributed. Preferably, the plurality of first mounting holes are evenly distributed circumferentially around the central axis of the top mounting plate 31. Specifically, in this embodiment, four first mounting holes are provided.

[0043] Understandably, the multiple first mounting holes increase the number of connection points between the parachute compartment 21 and the parachute compartment bracket 30, distributing the force on the parachute compartment 21, making it more stable during flight, reducing the risk of bolt loosening due to vibration, improving the fixation effect of the parachute compartment 21, ensuring the parachute can be activated normally in an emergency, and enhancing the safety of the UAV 10. When installing the parachute compartment 21, align the multiple first connection holes at the bottom of the parachute compartment 21 with the multiple first mounting holes on the top mounting plate 31, then pass the bolts through these holes sequentially and tighten them to ensure a tight connection between the parachute compartment 21 and the top mounting plate 31. When it is necessary to disassemble the parachute compartment 21, simply loosen the bolts to easily separate the parachute compartment 21 from the top mounting plate 31.

[0044] In some embodiments, the top mounting plate 31 is further provided with a plurality of perforated holes 312, which are distributed circumferentially.

[0045] In some embodiments, a plurality of perforated holes 312 are evenly distributed circumferentially around the central axis of the top mounting 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 mounting plate 31. Optionally, the top mounting plate 31 is provided with a plurality of annular perforated structures with different radii.

[0046] Specifically, in this embodiment, by providing perforations 312 in the top mounting plate 31, some material is removed, thereby reducing the weight of the parachute compartment support 30 and consequently lowering the overall weight of the UAV 10. This helps improve the flight performance of the UAV 10, such as increasing payload capacity, extending endurance, and improving climb rate and flight speed. It should be noted that although the perforation design removes some material, this embodiment designs the perforations 312 in a circumferentially evenly distributed manner around the central axis. This effectively disperses stress while maintaining overall structural stability, preventing structural damage caused by stress concentration.

[0047] In some embodiments, the top mounting plate 31 has an axisymmetric structure, which reduces the unbalanced moment caused by the shift in the center of gravity during flight of the parachute compartment support 30 after it is installed on the UAV 10, thereby improving flight stability. Optionally, the two side mounting plates 32 are symmetrical about the axis of symmetry of the top mounting plate 31, ensuring that the force on both sides of the parachute compartment support 30 can be evenly distributed when it is installed on the UAV 10, avoiding local stress concentration or uneven force due to structural asymmetry. Optionally, the center of mass of the top mounting plate 31 is located on its central axis, and the center of mass of the top mounting plate 31 coincides with its outer center.

[0048] In some embodiments, the side mounting plate 32 includes an outer frame 321, a diagonal reinforcing beam 322, and a transverse reinforcing beam 323. The outer frame 321 includes an upper frame, a left frame, and a right frame. The upper frame is connected to the top mounting plate 31. Diagonal reinforcing beams 322 are provided between the upper frame and the left frame, and between the upper frame and the right frame. A transverse reinforcing beam 323 is provided between the left frame and the right frame.

[0049] Specifically, the upper, left, and right frames of the outer frame 321, together with the diagonal reinforcing beams 322 and lateral reinforcing beams 323, constitute a stable frame structure. When the parachute compartment 21 is subjected to external forces, this frame structure can distribute the force in various directions, avoiding local stress concentration and thus improving the overall load-bearing capacity of the structure. The diagonal reinforcing beams 322 and lateral reinforcing beams 323 increase the bending and torsional stiffness of the side mounting plate 32, making it less prone to deformation under lateral forces or torques, thus ensuring the accuracy and stability of the parachute compartment 21's installation position.

[0050] Furthermore, a heat dissipation area 325 is formed between the outer frame 321 and the diagonal reinforcing beam 322, and / or between the outer frame 321 and the transverse reinforcing beam 323, and / or between the diagonal reinforcing beam 322 and the transverse reinforcing beam 323, for dissipating heat from the drone 10. Specifically, the heat dissipation area 325 formed between the outer frame 321 and the diagonal reinforcing beam 322, between the outer frame 321 and the transverse reinforcing beam 323, and between the diagonal reinforcing beam 322 and the transverse reinforcing beam 323 provides a channel for heat exchange between the drone 10 and the outside environment, thereby enhancing the heat dissipation effect.

[0051] In some embodiments, the fuselage mounting portion 324 includes a plurality of second mounting holes for bolts to pass through. Optionally, a total of four second mounting holes are provided, two on the left frame and two on the right frame. When installing the parachute bracket 30, the left and right frames of the side mounting plate 32 are aligned with the left and right sides of the drone 10 fuselage, respectively. Then, the bolts are passed sequentially through the second mounting holes on the left and right frames and the corresponding connecting holes on the fuselage, and finally the bolts are tightened to securely connect the parachute bracket 30 to the drone 10 fuselage. When it is necessary to disassemble the parachute bracket 30, simply follow the reverse order of installation, loosen and remove the bolts, and the parachute bracket 30 can be easily separated from the drone 10 fuselage.

[0052] In some embodiments, the umbrella cabin support 30 further includes a bottom mounting plate 33, with the upper side of the side mounting plate 32 connected to the top mounting plate 31 and the lower side of the side mounting plate 32 connected to the bottom mounting plate 33.

[0053] It is understood that in this embodiment, the side mounting plate 32 is connected to the left and right sides of the fuselage of the UAV 10, the top mounting plate 31 is connected to the side mounting plate 32 on the upper side of the fuselage of the UAV 10 and is used to install the parachute 21, and the bottom mounting plate 33 is connected to the side mounting plate 32 on the lower side of the fuselage of the UAV 10. The top mounting plate 31, the side mounting plate 32 and the bottom mounting plate 33 together form a spatial frame structure. The fuselage of the UAV 10 is set in the space enclosed by the top mounting plate 31, the side mounting plate 32 and the bottom mounting plate 33, which effectively improves the stability of the parachute support 30 under various flight conditions and reduces the risk of structural deformation caused by external forces.

[0054] Furthermore, the bottom mounting plate 33 is an X-shaped structure with four ends, and the connection points between the bottom mounting plate 33 and the side mounting plate 32 are located at the four ends of the bottom mounting plate 33. It should be explained that the X-shaped structure has high spatial geometry stability, and the connection points at the four ends can form a stable quadrilateral frame, enabling the bottom mounting plate 33 to maintain its shape under load and not easily deform, thereby improving the flight stability and safety of the UAV 10.

[0055] In some embodiments, the top mounting plate 31 is a one-piece molded structure, the side mounting plate 32 is a one-piece molded structure, and the bottom mounting plate 33 is a one-piece molded structure. In some embodiments, the top mounting plate 31, the bottom mounting plate 33, and the parachute compartment bracket 30 are all axisymmetric structures, and the axis of symmetry of the top mounting plate 31 and the axis of symmetry of the bottom mounting plate 33 are located on the plane of symmetry of the parachute compartment bracket 30.

[0056] In some embodiments, the top mounting plate 31 and the side mounting plate 32 are connected by screws, and the side mounting plate 32 and the bottom mounting plate 33 are connected by screws. It should be noted that the screws used to connect the top mounting plate 31 and the side mounting plate 32 should avoid the area where the parachute compartment 21 is mounted on the top mounting plate 31, to prevent the recoil force generated when the parachute compartment 21 is activated from impacting the screws and damaging the shell of the parachute compartment 21.

[0057] 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, The parachute compartment support includes a top mounting plate and side mounting plates connected to both sides of the top mounting plate. The top mounting plate is provided with a parachute compartment mounting part for mounting the parachute compartment, and the side mounting plates are provided with a fuselage mounting part for mounting the fuselage.

2. The parachute compartment support according to claim 1, characterized in that, The parachute compartment mounting section includes a plurality of first mounting holes for bolts to pass through, and the plurality of first mounting holes are distributed circumferentially.

3. The parachute compartment support according to claim 1, characterized in that, The top mounting plate is also provided with multiple perforated holes, which are distributed in a circular pattern.

4. The parachute compartment support according to claim 1, characterized in that, The side mounting plate includes an outer frame, diagonal reinforcing beams, and transverse reinforcing beams. The outer frame includes an upper frame, a left frame, and a right frame. The upper frame is connected to the top mounting plate. The diagonal reinforcing beams are provided between the upper frame and the left frame, and between the upper frame and the right frame. The transverse reinforcing beams are provided between the left frame and the right frame.

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

6. The parachute compartment support according to claim 1 or 4, characterized in that, The fuselage mounting section includes multiple second mounting holes for bolts to pass through.

7. The parachute compartment support according to claim 1, characterized in that, The parachute support also includes a bottom mounting plate, the upper side of the side mounting plate is connected to the top mounting plate, and the lower side of the side mounting plate is connected to the bottom mounting plate.

8. The parachute compartment support according to claim 7, characterized in that, The bottom mounting plate is an X-shaped structure with four ends, and the connection points between the bottom mounting plate and the side mounting plate are located at the four ends of the bottom mounting plate.

9. A parachute compartment assembly, characterized in that, It includes a parachute compartment, a controller, and a parachute compartment support as described in any one of claims 1-8, wherein the parachute compartment is installed in the parachute compartment mounting part, and the controller is electrically connected to the parachute compartment.

10. A drone, characterized in that, It includes a drone body and the parachute assembly as described in claim 9, wherein the drone body is connected to the inner side of the parachute support of the parachute assembly.

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