Low-altitude distribution aircraft

Abstract

The embodiment of the invention provides a low-altitude distribution aircraft, and relates to the technical field of aircrafts. A low-altitude distribution aircraft comprises an aircraft body, two supporting frames, a warehouse, a retracting and releasing mechanism and a lifting rope. The aircraft body is fixedly connected with the two supporting frames, the warehouse is arranged between the two supporting frames, the winding and unwinding mechanism is arranged in the warehouse, the lifting rope is connected with the winding and unwinding mechanism and used for winding and unwinding the lifting rope, and the end, away from the winding and unwinding mechanism, of the lifting rope is used for binding goods. By arranging the retracting and releasing mechanism and the lifting rope, the aircraft body does not need to land on the ground in the cargo loading and taking process, and the problem that landing is limited due to the complex ground environment is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a low-altitude delivery aircraft. Background Art

[0002] In recent years, with the continuous advancement of aviation technology, the application of aircraft in cargo delivery has become increasingly widespread. Unmanned aerial vehicles (UAVs), such as drones, have become widely used in logistics transportation, emergency supplies delivery, and cargo delivery to remote areas due to their efficiency, flexibility, and ability to reach areas inaccessible to traditional vehicles. Aircraft, using pre-set routes or real-time navigation, can quickly transport cargo from a starting point to a destination, providing a novel solution for modern logistics systems. However, with the increasing demand for delivery, optimizing the cargo delivery process using aircraft has become a pressing issue.

[0003] In the existing aircraft cargo delivery process, the aircraft usually needs to land on the ground so that the operator or recipient can take out the cargo. However, due to the complexity of the ground environment at the delivery location, such as rugged terrain, the presence of obstacles or the lack of a flat landing area, it is sometimes difficult for the aircraft to land safely. In this case, if the aircraft is allowed to float in the air to avoid landing, it faces the dilemma of lacking an effective means of releasing the cargo. In existing technologies, some aircraft rely on a simple delivery mechanism, but this method often cannot guarantee the accurate delivery or safety of the cargo, especially when the cargo needs to be delivered to a specific location or to avoid damage to the cargo. Therefore, there is an urgent need for a technical solution that can achieve efficient and safe cargo delivery in complex environments. Summary of the Invention

[0004] According to an embodiment of the present invention, a low-altitude delivery aircraft is provided to solve the problems raised by the above-mentioned background technology.

[0005] In a first aspect of the present invention, a low-altitude delivery aircraft is provided, comprising: an aircraft body, two support frames, a cargo hold, a retractable mechanism, and a sling; the aircraft body is fixedly connected to the two support frames, the cargo hold is arranged between the two support frames, the retractable mechanism is arranged inside the cargo hold, the sling is connected to the retractable mechanism for winding and releasing the sling, and the end of the sling away from the retractable mechanism is used for binding cargo.

[0006] Preferably, the bottom wall of the cargo warehouse is provided with two openable warehouse doors, and the interior of the cargo warehouse is provided with a second driving component for driving the two warehouse doors to open or close.

[0007] Preferably, the second drive assembly includes an electric push rod and a drive member; a first transmission arm is provided on the warehouse door, the electric push rod is installed inside the cargo warehouse, the output end of the electric push rod is connected to the drive member, a first drive groove is provided on the drive member, and the ends of the two first transmission arms away from the warehouse door are slidably connected to the first drive groove through a shaft.

[0008] Preferably, the second drive assembly also includes a synchronizing member, a synchronizing groove is provided on the synchronizing member, a second transmission arm identical to the first transmission arm is provided on the side of the warehouse door away from the driving member, and the end of the second transmission arm away from the warehouse door is slidably connected to the synchronizing groove through an axis, and two limit plates are provided inside the cargo warehouse, and an installation space for the synchronizing member is formed between the two limit plates, and the synchronizing member is slidably installed between the two limit plates.

[0009] Preferably, the retracting and extending mechanism includes a damping assembly, a rotating body and a first driving assembly; the rotating body is rotatably mounted on the top wall of the cargo hold, the damping assembly is connected to the rotating body to provide resistance to the rotating body, the first driving assembly is connected to the rotating body to drive the rotating body to rotate, and one end of the lifting rope is fixedly connected to the rotating body.

[0010] Preferably, the damping assembly includes a sleeve, a first friction plate, a connecting rod, a fixed rod, a sliding sleeve and a second friction plate; the sleeve is fixedly connected to the rotating body, the first friction plate is installed in the sleeve, the fixed rod is fixedly installed inside the cargo hold, the sliding sleeve is slidably installed on the fixed rod, the second friction plate is fixedly connected to the sliding sleeve, one end of the connecting rod is rotatably connected to the sliding sleeve, the other end of the connecting rod is rotatably connected to the driving member, and the connecting rod is in an inclined state.

[0011] Preferably, the first driving assembly includes a motor, a driving disk, an elastic structure, a limiting structure, a guide disk, a lever, a driving block and a connecting piece; the motor is fixedly mounted on the top wall of the cargo warehouse, the output end of the motor passes through the driving disk and is fixedly connected to the driving disk, the output end of the motor is rotatably connected to the guide disk, a second driving groove is provided on the driving disk, an arc-shaped guide groove is provided on the guide disk, the number of the driving blocks is multiple, the driving block is rotatably connected to the guide disk, the driving block is connected to the lever, the lever passes through the guide groove and the second driving groove, a card slot is provided inside the connecting piece, the driving block extends into the connecting piece and can extend into the card slot, the limiting structure is provided inside the cargo warehouse, the limiting structure is used to provide friction for the guide disk, and the elastic structure is provided between the driving disk and the guide disk.

[0012] Preferably, the limiting structure includes a limiting ring, two guide wheels and a brake wire; a cavity connected to the cargo warehouse is provided on the top of the cargo warehouse, the limiting ring is slidably connected to the inner wall of the cavity, the brake wire is fixedly connected to the limiting ring, the two guide wheels are rotatably installed in the cavity, the brake wire passes around the two guide wheels, and the end of the brake wire away from the limiting ring is fixedly connected to the synchronization component.

[0013] Preferably, the elastic structure includes a spring and two connecting wires, the two connecting wires are U-shaped and have bent portions at their ends; the two connecting wires pass through the spring, and the bent portions are connected to the ends of the spring, one of the connecting wires is connected to the driving disk, and the other connecting wire is connected to the guide disk.

[0014] Preferably, a hook is provided at one end of the sling away from the retractable mechanism.

[0015] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0016] The present invention provides a low-altitude delivery aircraft. By providing the retractable mechanism and the sling, the aircraft body does not need to descend to the ground during cargo loading and retrieval, thus avoiding the problem of landing restrictions caused by the complex ground environment. Furthermore, the sling can flexibly adjust the height of the cargo, facilitating the user to bind and remove the cargo on the ground, thereby improving delivery efficiency and applicability. Furthermore, the cargo hold provides temporary storage space for the cargo, ensuring its stability during transportation and avoiding damage or inaccurate positioning that may result from direct delivery.

[0017] The damping assembly provides rotational resistance to the rotator, slowing its rotational speed, allowing the sling and cargo to descend at a smooth, controllable speed. This design makes it easier for users to remove cargo from the ground or attach it to the sling, while also preventing damage or misalignment caused by a rapid drop.

[0018] It should be understood that the contents described in the summary of the invention are not intended to limit the key or important features of the embodiments of the present invention, nor are they intended to limit the scope of the present invention. Other features of the present invention will become readily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and other features, advantages and aspects of the embodiments of the present invention will become more apparent with reference to the following detailed description in conjunction with the accompanying drawings. In the accompanying drawings, the same or similar reference numerals represent the same or similar elements, wherein:

[0020] Figure 1A schematic diagram of a three-dimensional structure of a low-altitude delivery aircraft from a first perspective according to an embodiment of the present invention is shown;

[0021] Figure 2 A schematic diagram of the three-dimensional structure of a low-altitude delivery aircraft from a second perspective according to an embodiment of the present invention is shown;

[0022] Figure 3 A schematic cross-sectional view of a cargo hold of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0023] Figure 4 A perspective view showing the internal structure of a cargo hold of a low-altitude delivery aircraft according to an embodiment of the present invention;

[0024] Figure 5 A schematic diagram of the three-dimensional structure of a second drive assembly of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0025] Figure 6 A schematic cross-sectional view of a damping assembly of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0026] Figure 7 A schematic diagram of the exploded structure of a damping assembly of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0027] Figure 8 A schematic diagram of the three-dimensional structure of a restriction structure of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0028] Figure 9 A schematic diagram of an exploded structure of a first drive assembly of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0029] Figure 10 A schematic diagram of the main structure of a drive disc of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0030] Figure 11 A schematic diagram of the three-dimensional structure of a drive disc of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0031] Figure 12 A schematic diagram of the main structure of a guide plate of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0032] Figure 13 A schematic diagram of the three-dimensional structure of a guide plate of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0033] Figure 14 A schematic diagram of the main structure of a connecting member of a low-altitude delivery aircraft according to an embodiment of the present invention is shown;

[0034] Figure 15 A schematic diagram of the exploded structure of the elastic structure of a low-altitude delivery aircraft according to an embodiment of the present invention is shown.

[0035] Description of Reference Numerals

[0036] 1-aircraft body, 2-support frame, 3-cargo compartment, 31-door, 32-first transmission arm, 33-second transmission arm, 34-limiting plate, 35-cavity, 4-retracting mechanism, 41-damping assembly, 411-sleeve, 412-first friction plate, 413-connecting rod, 414-fixed rod, 415-sliding sleeve, 416-second friction plate, 42-rotating body, 43-first drive assembly, 431-motor, 432-drive disc, 4321-second drive slot, 43 3-elastic structure, 4331-spring, 4332-connecting wire, 434-limiting structure, 4341-limiting ring, 4342-guide wheel, 4343-brake line, 435-guide plate, 4351-guide groove, 436-dial rod, 437-drive block, 438-connecting piece, 4381-slot, 5-hanging rope, 51-hook, 6-second drive assembly, 61-electric push rod, 62-drive piece, 621-first drive groove, 63-synchronizing piece, 631-synchronizing groove. DETAILED DESCRIPTION

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0038] In this document, the term "and / or" simply describes a relationship between related objects, indicating that three possible relationships exist. For example, "A and / or B" can represent: A exists alone, A and B exist simultaneously, or B exists alone. Furthermore, the character " / " in this document generally indicates that the related objects are in an "or" relationship.

[0039] like Figures 1 to 15 As shown, the present invention provides a low-altitude delivery aircraft, which aims to solve the problems of difficult landing caused by the complex ground environment and the lack of efficient cargo release methods in existing aircraft cargo delivery. The low-altitude delivery aircraft includes an aircraft body 1, two support frames 2, a cargo compartment 3, a retractable mechanism 4, and a sling 5.

[0040] The aircraft body 1 is the flight structure of the entire delivery aircraft and includes a fuselage 11 and rotors 12. The rotors 12 are fixedly connected to the fuselage 11. An electric motor is internally disposed within the fuselage 11 and is in transmission connection with the rotors 12 for driving the rotors 12 to rotate. The high-speed rotation of the rotors 12 provides lift for the aircraft body 1, enabling the aircraft body 1 to fly or hover. The fuselage 11 may also be equipped with a control module and a power supply module for controlling the flight path and power supply. The specific circuit structure and control method can be based on existing technologies and will not be further described here.

[0041] The two support frames 2 are respectively fixedly connected to the body 11 of the aircraft body 1, and the two support frames 2 are symmetrically arranged below or on both sides of the body 11 to support the cargo hold 3. The cargo hold 3 is arranged between the two support frames 2, which is a storage space for accommodating cargo. The cargo hold 3 can be a box structure with an opening, and the opening is arranged downward to facilitate the loading and unloading of cargo. The retracting and releasing mechanism 4 is installed inside the cargo hold 3. Specifically, the retracting and releasing mechanism 4 can be a device with winding and releasing functions such as a winch or an electric winch, which is driven by a motor to realize the retraction and release control of the sling 5. One end of the sling 5 is connected to the retracting and releasing mechanism 4, and the other end is a free end for binding cargo. The material of the sling 5 can be a high-strength fiber rope or a steel wire rope to ensure reliability when towing cargo.

[0042] The method of using the low-altitude delivery aircraft is as follows: during the cargo loading stage, first control the aircraft body 1 to lift to a certain height through the rotor 12, such as a low-altitude area 1-2 meters above the ground, to avoid the impact of ground debris or uneven terrain on the aircraft. Subsequently, operate the retracting and releasing mechanism 4 to release the sling 5, so that the free end of the sling 5 droops to a position close to the ground, and the user firmly binds the cargo to be delivered to the free end of the sling 5. After the cargo is bound, control the retracting and releasing mechanism 4 to reel in the sling 5, and the sling 5 drives the cargo upward during the reeling process until the cargo is pulled into the cargo hold 3 and securely stored. Subsequently, control the aircraft body 1 to fly along the preset route to the designated delivery location.

[0043] When the aircraft 1 reaches the location of the user, it remains in a low-altitude hover, eliminating the need to land. The retractable mechanism 4 releases the sling 5 again, which then lowers the cargo down to near-ground level, allowing the user to conveniently remove it from the sling 5. After the cargo is removed, the sling 5 can be retracted back into the cargo hold 3 via the retractable mechanism 4, completing the delivery. The cargo can include, but is not limited to, food, daily necessities, electronic products, or pharmaceuticals, and can be selected based on actual needs.

[0044] By providing the retractable mechanism 4 and the sling 5, the present invention eliminates the need for the aircraft body 1 to land on the ground during cargo loading and retrieval, thus avoiding the problem of restricted landing due to a complex ground environment (such as the presence of debris, uneven terrain, or a lack of flat areas). Furthermore, the sling 5 can flexibly adjust the height of the cargo, making it easier for users to tie and remove cargo on the ground, thereby improving delivery efficiency and applicability. Furthermore, the cargo hold 3 provides temporary storage space for cargo, ensuring its stability during transportation and avoiding damage or inaccurate positioning that may result from direct delivery.

[0045] In this embodiment, to further optimize the convenience of loading and unloading cargo, the bottom wall of the cargo hold 3 is provided with two openable doors 31. A second drive assembly 6 is provided inside the cargo hold 3 to drive the two doors 31 to open or close. The second drive assembly 6 is configured to drive the doors 31 downward to form an opening for cargo to enter and exit the cargo hold 3.

[0046] Specifically, the second drive assembly 6 includes an electric push rod 61 and a drive member 62. The electric push rod 61 is fixedly installed inside the cargo warehouse 3, and its output end is connected to the drive member 62, which is used to drive the drive member 62 to move in the up and down directions. A first drive slot 621 is provided on the drive member 62, and a first transmission arm 32 is fixedly provided on each of the warehouse doors 31. The end of the first transmission arm 32 away from the warehouse door 31 is slidably connected to the first drive slot 621 through a shaft. The two warehouse doors 31 are hingedly connected to the bottom wall of the cargo warehouse 3 through an existing hinge structure (such as a hinge or a rotating shaft), and the two first transmission arms 32 are preferably located between two hinge shafts to ensure transmission stability.

[0047] The operating principle of the second drive assembly 6 is as follows: when the output end of the electric push rod 61 extends, pushing the drive member 62 downward, the first drive slot 621 subsequently causes the two first transmission arms 32 to slide and flip. Because the first transmission arms 32 are fixedly connected to the compartment doors 31, the flipping action of the first transmission arms 32 drives the two compartment doors 31 to flip downward about the hinge axis, thereby opening the compartment doors 31. Conversely, when the output end of the electric push rod 61 retracts, driving the drive member 62 upward, the first drive slot 621 drives the two first transmission arms 32 to flip in the opposite direction, causing the two compartment doors 31 to flip upward and close, returning to the closed state.

[0048] In order to further ensure the synchronization of the two warehouse doors 31 during the opening and closing process, in this embodiment, the second drive assembly 6 also includes a synchronizer 63. A synchronizer groove 631 is provided on the synchronizer 63, and a second transmission arm 33 is fixedly provided on the side of each warehouse door 31 away from the drive member 62. The structure of the second transmission arm 33 is the same as that of the first transmission arm 32, and the end away from the warehouse door 31 is slidably connected to the synchronizer groove 631 through an axis. Two limit plates 34 are also provided inside the cargo warehouse 3. The two limit plates 34 are arranged in parallel and form an installation space for the synchronizer 63. The synchronizer 63 is slidably installed between the two limit plates 34. Preferably, a guide structure (such as a slide rail or a slide groove) can be provided between the limit plate 34 and the synchronizer 63 to limit the synchronizer 63 to only be able to slide and move in the up and down directions.

[0049] The operating principle of the synchronizer 63 is as follows: when the door 31 is opened by the second drive assembly 6, the two second transmission arms 33 rotate with the door 31 and drive the synchronizer 63 downward through the synchronization slot 631. When the door 31 is closed, the two second transmission arms 33 reverse and drive the synchronizer 63 upward. Because the synchronizer 63 is linked to the two second transmission arms 33 through the synchronization slot 631, its sliding motion effectively coordinates the movement of the two doors 31, ensuring synchronization during the opening and closing process, and avoiding problems such as jamming or deviation caused by uneven force on one side.

[0050] In this embodiment, the provision of the door 31, combined with the use of the retractable mechanism 4 and the sling 5, further enhances the flexibility of cargo delivery. Specifically, when loading or releasing cargo, the second drive assembly 6 drives the door 31 to open, and the retractable mechanism 4 releases the sling 5 to pull the cargo in and out of the cargo hold 3. After loading or unloading, the retractable mechanism 4 retracts the sling 5, and the second drive assembly 6 drives the door 31 to close, thereby ensuring the safety of the cargo during transportation. The coordinated operation of the door 31 and the second drive assembly 6 enables the aircraft body 1 to complete cargo transfers while hovering at low altitude, avoiding delivery interruptions caused by ground conditions.

[0051] It should be noted that the electric push rod 61 in the above embodiment can be replaced with other linear drive devices (such as a cylinder or a screw mechanism), and the shapes of the first drive slot 621 and the synchronization slot 631 can be designed to be linear or curved according to actual transmission requirements to optimize transmission efficiency. The above improvements are all routine replacements made by those skilled in the art and should be considered to fall within the scope of protection of the present invention.

[0052] In this embodiment, in order to achieve smooth release and reliable reeling of the sling 5, the retracting and releasing mechanism 4 includes a damping assembly 41, a rotating body 42 and a first driving assembly 43. The rotating body 42 is rotatably mounted on the top wall of the cargo hold 3. The rotating body 42 can be a structure such as a drum, a turntable or a roller, which is rotatably connected to the top wall of the cargo hold 3 through a bearing or a rotating shaft to reduce rotational friction. The damping assembly 41 is connected to the rotating body 42 to provide resistance to the rotation of the rotating body 42 to control its rotation speed. The first driving assembly 43 is connected to the rotating body 42 to drive the rotating body 42 to rotate. One end of the sling 5 is fixedly connected to the rotating body 42, and the other end is a free end, which is used to bind the cargo. The reeling or release of the sling 5 is achieved by the rotation of the rotating body 42.

[0053] The working process of the retracting and releasing mechanism 4 is as follows: when the door 31 of the cargo warehouse 3 is opened, the first driving component 43 is disconnected from the rotating body 42, and the rotating body 42 is in a free rotation state. Under the action of the gravity of the goods themselves, the free end of the sling 5 drives the goods to move downward, while pulling the rotating body 42 to rotate, and the sling 5 is gradually released. During this process, the damping component 41 provides rotational resistance to the rotating body 42, slowing down the rotation speed of the rotating body 42, so that the sling 5 and the goods slowly descend at a steady and controllable speed. This design makes it easy for users to take goods off the ground or mount goods on the sling 5, while avoiding damage or position deviation of the goods due to rapid falling.

[0054] When the cargo is removed or loaded, the first drive assembly 43 is started. The first drive assembly 43 establishes a connection with the rotating body 42 through a clutch structure and drives the rotating body 42 to rotate in the winding direction. The rotation of the rotating body 42 gradually reels the sling 5, driving the cargo or the unloaded sling 5 upward until the sling 5 and the cargo are completely retracted into the interior of the cargo hold 3. Subsequently, the second drive assembly 6 drives the warehouse door 31 to close, completing the cargo loading or releasing operation. The motor of the first drive assembly 43 can be equipped with an encoder or a limit switch to accurately control the retraction and extension length of the sling 5 to ensure the accuracy of cargo positioning.

[0055] In this embodiment, the retractable mechanism 4, in conjunction with the cargo hold 3 and door 31, further enhances the functionality of the low-altitude delivery aircraft. Specifically, the damping assembly 41 ensures smooth cargo release, preventing the potential for loss of control associated with traditional direct delivery methods. The first drive assembly 43 provides active retraction, enabling the aircraft 1 to complete cargo loading and unloading operations while hovering at low altitude, eliminating the need for landing. This design not only improves delivery efficiency but also enhances the aircraft's adaptability in complex environments.

[0056] In addition, the surface of the rotating body 42 may be provided with a guide groove or a fixing clip to prevent the rope 5 from deflecting during the winding process. These improvements are conventional design choices made by those skilled in the art and should be considered to fall within the scope of protection of the present invention.

[0057] In this embodiment, to achieve a damping effect when the rotating body 42 releases the suspension rope 5, the damping assembly 41 includes a sleeve 411, a first friction plate 412, a connecting rod 413, a fixed rod 414, a sliding sleeve 415, and a second friction plate 416. The sleeve 411 is fixedly connected to the rotating body 42. Preferably, the sleeve 411 is a cylindrical structure that is sleeved outside the rotating shaft of the rotating body 42 and rotates synchronously with the rotating body 42 via a key connection or bolt fixation. The first friction plate 412 is mounted on the inner wall of the sleeve 411 and is made of a wear-resistant, high-friction material (such as rubber or a ceramic composite material) to provide frictional resistance.

[0058] The fixed rod 414 is fixedly mounted within the cargo compartment 3. The fixed rod 414 is a rod-shaped structure, one end of which is fixed to the top or side wall of the cargo compartment 3. The sliding sleeve 415 is slidably mounted on the fixed rod 414. The sliding sleeve 415 is a cylindrical member that fits over the fixed rod 414 and is capable of sliding axially on the fixed rod 414. The second friction plate 416 is fixedly connected to the sliding sleeve 415 and is positioned on the side of the sliding sleeve 415 near the sleeve 411. Its material matches that of the first friction plate 412 to ensure stable friction when the two contact. One end of the connecting rod 413 is rotatably connected to the sliding sleeve 415 via a hinged structure (e.g., a pin), and the other end is rotatably connected to the driving member 62 via a similar hinged structure. In its initial state, the connecting rod 413 is tilted to form an effective transmission angle.

[0059] Furthermore, the outer surface of the fixed rod 414 is provided with a strip-shaped protrusion along the axial direction, and the inner wall of the sliding sleeve 415 is provided with a corresponding groove that matches the strip-shaped protrusion. The strip-shaped protrusion slidably engages with the groove, thereby restricting the sliding sleeve 415 to sliding only along the axial direction of the fixed rod 414 and preventing it from rotating relative to the fixed rod 414. This design ensures the stability of the sliding sleeve 415 during movement and avoids damping failure caused by rotational offset.

[0060] The damping assembly 41 operates as follows: When the electric push rod 61 drives the driving member 62 downward, the driving member 62 opens the compartment door 31 via the first driving slot 621 (see the description of the second driving assembly 6 above). Simultaneously, the downward movement of the driving member 62 causes the connecting rod 413 to rotate and displace. Due to the inclined configuration of the connecting rod 413, the downward thrust is converted into a sliding force along the fixed rod 414, driving the sliding sleeve 415 to slide downward along the fixed rod 414. When the compartment door 31 is fully opened, the sliding sleeve 415 slides to a predetermined position, causing the second friction plate 416 to closely contact the first friction plate 412, generating friction.

[0061] In this state, the cargo moves downward under the action of gravity via the free end of the sling 5, driving the rotation of the rotating body 42. The rotation of the rotating body 42 further drives the sleeve 411 to rotate synchronously, which in turn drives the first friction plate 412 to rotate. Because the second friction plate 416 is fixed to the sliding sleeve 415, which is held stationary by the fixing rod 414, relative sliding friction is generated between the first friction plate 412 and the second friction plate 416. This frictional force dampens the rotation of the rotating body 42, slowing the release of the sling 5 and allowing the cargo to descend slowly and controllably, making it easier for users to remove or load cargo from the ground.

[0062] When cargo is removed or loaded, the electric push rod 61 drives the driving member 62 upward. The driving member 62, via the connecting rod 413, drives the sliding sleeve 415 upward along the fixed rod 414, causing the second friction plate 416 to separate from the first friction plate 412. At this point, the damping effect of the damping assembly 41 on the rotating body 42 is released, and the first driving assembly 43 activates and drives the rotating body 42 to rotate, retracting the sling 5 into the interior of the cargo hold 3 (see the description of the retracting mechanism 4 above). Subsequently, the warehouse door 31 closes under the drive of the second driving assembly 6, completing the delivery operation.

[0063] In this embodiment, the damping assembly 41, through its linkage with the second drive assembly 6, synchronizes the opening of the door 31 with the activation of the damping mechanism. Specifically, the downward movement of the drive member 62 not only drives the door 31 open but also triggers the damping assembly 41 via the connecting rod 413, ensuring a smoother and more controllable cargo release process. This structure improves the operational efficiency and safety of low-altitude delivery aircraft, making it particularly suitable for cargo delivery in complex environments.

[0064] It should be noted that the material and contact area of ​​the first friction plate 412 and the second friction plate 416 in the above embodiment can be adjusted according to actual damping requirements. The bar-shaped protrusions on the fixing rod 414 can also be replaced with other guiding structures (such as a polygonal cross-section or a keyway fit). In addition, the length and inclination angle of the connecting rod 413 can be optimized based on the internal space of the cargo hold 3. These modifications are routine modifications that can be made by those skilled in the art and should be considered within the scope of protection of the present invention.

[0065] In this embodiment, to achieve drive control of the rotating body 42 when reeling in the sling 5, the first drive assembly 43 includes a motor 431, a drive disc 432, an elastic structure 433, a limiting structure 434, a guide disc 435, a lever 436, a drive block 437, and a connector 438. The motor 431 is fixedly mounted on the top wall of the cargo hold 3, with its output end (i.e., the motor shaft) extending vertically to provide rotational power. The drive disc 432 is a disc-shaped structure. The output end of the motor 431 passes through the center of the drive disc 432 and is fixedly connected thereto, for example, by a key connection or bolts, so that the drive disc 432 rotates synchronously with the output end of the motor 431. The guide disc 435 is also a disc-shaped structure. The output end of the motor 431 is rotatably connected to the guide disc 435. The guide disc 435 cooperates with the output end of the motor 431 via a bearing to ensure relative rotation between the two.

[0066] The drive disk 432 is provided with a second drive slot 4321; the guide disk 435 is provided with an arcuate guide slot 4351, the arcuate trajectory of which matches the rotation direction of the drive disk 432. There are multiple drive blocks 437, each rotatably connected to the guide disk 435 via a rotating shaft, enabling rotation about its own axis. The number of deflector levers 436 corresponds to the number of drive blocks 437. Each deflector lever 436 has one end fixedly connected to a drive block 437, and the other end passes through the guide slot 4351 on the guide disk 435 and the second drive slot 4321 on the drive disk 432, respectively. The connecting member 438 is a component fixedly connected to the rotating body 42, and is provided with a plurality of slots 4381 inside. The openings of the slots 4381 face the driving block 437. The driving block 437 can extend into or out of the slots 4381 by rotating to achieve connection or disconnection with the connecting member 438.

[0067] The elastic structure 433 is disposed between the drive plate 432 and the guide plate 435. The elastic structure 433 is a torsion spring or tension spring, one end of which is fixed to the drive plate 432 and the other end to the guide plate 435, and is used to provide elastic restoring force when the two rotate relative to each other. The limiting structure 434 is disposed within the cargo hold 3 and is used to provide friction for the guide plate 435 to temporarily limit its rotation.

[0068] The first drive assembly 43 operates as follows: In the initial state, the drive block 437 does not extend into the slot 4381, and the connector 438 is disconnected from the drive block 437. At this point, if the sling 5 needs to be released, the door 31 is opened directly via the second drive assembly 6 (see the previous description). The cargo moves downward under gravity, driving the rotating body 42 to rotate, and the sling 5 is gradually released (see the damping effect of the damping assembly 41). During this process, the motor 431 is not activated, the guide plate 435 is restrained by the friction of the restraining structure 434 and does not rotate, and the drive plate 432 and guide plate 435 remain relatively stationary.

[0069] When the sling rope 5 needs to be reeled in, the motor 431 is activated, and the output of the motor 431 drives the drive disc 432 to rotate. Because the guide disc 435 is initially restrained by the limiting structure 434 and cannot rotate, the drive disc 432 rotates relative to the guide disc 435, causing the elastic structure 433 to be stretched or compressed, storing elastic potential energy. Simultaneously, the second drive slot 4321 pushes the lever 436 along the arcuate trajectory of the guide slot 4351. The lever 436 drives the drive block 437 to rotate about its axis until the drive block 437 enters the engaging slot 4381 of the connecting member 438, thereby connecting the drive block 437 to the connecting member 438. As the output end of the motor 431 continues to rotate, the driving disk 432 drives the guide disk 435 through the lever 436 to overcome the friction of the limiting structure 434 and start to rotate. The guide disk 435 further drives the connecting member 438 to rotate through the driving block 437. The connecting member 438 drives the rotating body 42 to rotate synchronously, thereby realizing the winding action of the lifting rope 5 and retracting the cargo or empty lifting rope 5 into the cargo warehouse 3.

[0070] In this embodiment, the restraining structure 434 comprises a restraining ring 4341, two guide wheels 4342, and a brake wire 4343. The top wall of the cargo hold 3 is provided with a cavity 35 connected to the interior of the cargo hold 3. The cavity 35 serves as a working space for the restraining structure 434. The restraining ring 4341 is an annular structure, positioned outside the guide plate 435. Its inner diameter is slightly larger than the outer diameter of the guide plate 435. The restraining ring 4341 is slidably connected to the inner wall of the cavity 35, preferably by means of a slide rail or guide groove, restricting its movement to a vertical direction. The two guide wheels 4342 are rotatably mounted within the cavity 35 via a rotating shaft. One end of the brake wire 4343 is fixedly connected to the restraining ring 4341, while the other end passes around the two guide wheels 4342 and is fixedly connected to the synchronizer 63 (see the description of the second drive assembly 6 above). The guide wheels 4342 are used to adjust the transmission direction of the brake wire 4343 and reduce frictional resistance.

[0071] The limiting structure 434 operates as follows: when the synchronizer 63 moves downward under the drive of the second drive assembly 6 (i.e., when the door 31 is opened), the synchronizer 63 pulls the brake wire 4343 to move. The brake wire 4343, guided by the two guide wheels 4342, drives the limiting ring 4341 to slide downward until the limiting ring 4341 contacts the outer edge of the guide plate 435 and generates friction, thereby limiting the rotation of the guide plate 435. At this point, the door 31 is fully open, the lifting rope 5 is released under the weight of the cargo, the rotating body 42 rotates, and the first drive assembly 43 has not yet been activated, and the driving block 437 is not connected to the slot 4381.

[0072] When the sling rope 5 needs to be reeled in, the motor 431 is activated, and the output end of the motor 431 drives the drive disc 432 to rotate, preferentially establishing a connection with the connecting member 438 through the movement of the shifting rod 436 and the driving block 437. Subsequently, the friction of the restriction ring 4341 is overcome, driving the guide disc 435 and the rotating body 42 to rotate, completing the reeling of the sling rope 5. When the sling rope 5 is reeled in place (i.e., the cargo enters the cargo hold 3), the second drive assembly 6 drives the door 31 to close, the synchronizer 63 moves upward, the brake wire 4343 relaxes, and the restriction ring 4341 disengages from the guide disc 435 under the action of gravity, thereby releasing the restriction on the guide disc 435. At this point, the elastic structure 433 releases its elastic potential energy, driving the guide plate 435 to rotate in the opposite direction relative to the drive plate 432. Under the combined action of the guide slot 4351 and the second drive slot 4321, the lever 436 drives the drive block 437 to rotate out of the engaging slot 4381, and the connector 438 and the drive block 437 are disconnected. The cargo falls onto the closed door 31 and is supported by it. The friction between the cargo and the door 31 enhances its stability within the cargo hold 3.

[0073] In this embodiment, the first drive assembly 43, through linkage with the second drive assembly 6, achieves coordinated control of the opening / closing of the door 31 and the release / retraction of the sling 5. The restraining structure 434 ensures the stability of the guide plate 435 during the release phase, while the clutch design of the elastic structure 433 and the drive block 437 optimizes power transmission efficiency during the retraction phase. This structure not only enhances the automation level of cargo delivery but also strengthens the reliability of the aircraft during low-altitude operations.

[0074] In this embodiment, to achieve the elastic connection and return function between the drive disk 432 and the guide disk 435, the elastic structure 433 includes a spring 4331 and two connecting wires 4332. The spring 4331 is preferably a compression spring having a certain initial length and elastic coefficient for providing elastic force. The two connecting wires 4332 are both U-shaped, and each of the two ends of the connecting wire 4332 is provided with a curved portion, which is preferably a hook-shaped or ring-shaped structure to enhance the connection stability. The two connecting wires 4332 are inserted into the interior of the spring 4331, and each curved portion is connected to the two ends of the spring 4331, for example, by hooking or welding. The U-shaped bottom of one of the connecting wires 4332 is fixedly connected to the driving disk 432 and is fixed to the edge of the driving disk 432 by bolts or clips; the U-shaped bottom of the other connecting wire 4332 is fixedly connected to the guide disk 435 in a similar fixing manner to ensure that both can be subjected to force as the driving disk 432 and the guide disk 435 move relative to each other.

[0075] The elastic structure 433 operates as follows: When the motor 431 starts and drives the drive disk 432 to rotate, if the guide disk 435 is temporarily unable to rotate due to the restriction of the restriction structure 434 (see the above description), the drive disk 432 rotates relative to the guide disk 435. At this point, the connecting wires 4332 fixed to the drive disk 432 move with the drive disk 432, while the connecting wires 4332 fixed to the guide disk 435 remain stationary, causing the distance between the two connecting wires 4332 to increase, moving them away from each other. Because the curved portions of the two connecting wires 4332 are connected to the ends of the spring 4331, the spring 4331 is compressed by the tension of the two connecting wires 4332, storing elastic potential energy. When the restriction on the guide disk 435 is released and it begins to rotate, the spring 4331 releases the elastic potential energy, driving the two connecting wires 4332 to return to their initial positions, thereby assisting in resetting the relative positions of the guide disk 435 and the drive disk 432. This design ensures a smooth transition of the first drive assembly 43 during the winding and disconnecting process.

[0076] In this embodiment, to enhance the convenience of attaching cargo to the sling 5 and the reliability of its release, a hook 51 is provided at the end of the sling 5 away from the retractable mechanism 4. The hook 51 is preferably a hook-shaped structure made of metal or high-strength plastic, with a closable snap or spring at its open end to prevent cargo from accidentally falling off. The hook 51 facilitates quick attachment of cargo to the sling 5. Furthermore, the hook 51 itself possesses a certain weight, for example, achieved by adding a counterweight or using a heavier material. The gravity-activated design of the hook 51 offers the following advantages: when there is no cargo in the cargo hold 3, when the door 31 is open and the first drive assembly 43 is not connected to the rotator 42, the hook 51, under its own weight, can pull the sling 5 downward and release it, driving the rotator 42 to rotate (controlled by the damping action of the damping assembly 41), thereby allowing the sling 5 to smoothly extend out of the cargo hold 3, facilitating cargo attachment.

[0077] The above specific embodiments do not limit the scope of protection of the present invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions may be made based on design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention are intended to be included within the scope of protection of the present invention.

Claims

1. A low-altitude delivery aircraft, characterized in that: include: An aircraft body (1), two support frames (2), a cargo compartment (3), a retractable mechanism (4), and a sling (5); the aircraft body (1) is fixedly connected to the two support frames (2), the cargo compartment (3) is arranged between the two support frames (2), the retractable mechanism (4) is arranged inside the cargo compartment (3), the sling (5) is connected to the retractable mechanism (4) and is used to reel in and release the sling (5), and the end of the sling (5) away from the retractable mechanism (4) is used to bind cargo.

2. The low-altitude delivery aircraft according to claim 1, characterized in that: The bottom wall of the cargo warehouse (3) is provided with two openable warehouse doors (31), and the interior of the cargo warehouse (3) is provided with a second driving component (6) for driving the two warehouse doors (31) to open or close.

3. The low-altitude delivery aircraft according to claim 2, characterized in that: The second driving assembly (6) includes an electric push rod (61) and a driving member (62); a first transmission arm (32) is provided on the warehouse door (31), the electric push rod (61) is installed inside the cargo warehouse (3), the output end of the electric push rod (61) is connected to the driving member (62), and a first driving groove (621) is provided on the driving member (62), and the ends of the two first transmission arms (32) away from the warehouse door (31) are slidably connected to the first driving groove (621) through a shaft.

4. The low-altitude delivery aircraft according to claim 3, characterized in that: The second driving assembly (6) further comprises a synchronous member (63), a synchronous groove (631) being provided on the synchronous member (63), a second transmission arm (33) identical to the first transmission arm (32) being provided on the side of the warehouse door (31) away from the driving member (62), an end of the second transmission arm (33) away from the warehouse door (31) being slidably connected to the synchronous groove (631) via an axis, two limiting plates (34) being provided inside the cargo warehouse (3), an installation space for the synchronous member (63) being formed between the two limiting plates (34), and the synchronous member (63) being slidably installed between the two limiting plates (34).

5. The low-altitude delivery aircraft according to claim 4, characterized in that: The retracting and unfolding mechanism (4) includes a damping assembly (41), a rotating body (42) and a first driving assembly (43); the rotating body (42) is rotatably mounted on the top wall of the cargo hold (3); the damping assembly (41) is connected to the rotating body (42) to provide resistance for the rotating body (42); the first driving assembly (43) is connected to the rotating body (42) to drive the rotating body (42) to rotate; and one end of the lifting rope (5) is fixedly connected to the rotating body (42).

6. The low-altitude delivery aircraft according to claim 5, characterized in that: The damping assembly (41) includes a sleeve (411), a first friction plate (412), a connecting rod (413), a fixed rod (414), a sliding sleeve (415) and a second friction plate (416); the sleeve (411) is fixedly connected to the rotating body (42), the first friction plate (412) is installed in the sleeve (411), the fixed rod (414) is fixedly installed inside the cargo hold (3), the sliding sleeve (415) is slidably installed on the fixed rod (414), the second friction plate (416) is fixedly connected to the sliding sleeve (415), one end of the connecting rod (413) is rotatably connected to the sliding sleeve (415), the other end of the connecting rod (413) is rotatably connected to the driving member (62), and the connecting rod (413) is in an inclined state.

7. The low-altitude delivery aircraft according to claim 5, characterized in that: The first driving assembly (43) includes a motor (431), a driving disk (432), an elastic structure (433), a limiting structure (434), a guide disk (435), a shifting rod (436), a driving block (437) and a connecting piece (438); the motor (431) is fixedly mounted on the top wall of the cargo bin (3); the output end of the motor (431) passes through the driving disk (432) and is fixedly connected to the driving disk (432); the output end of the motor (431) is rotatably connected to the guide disk (435); a second driving groove (4321) is provided on the driving disk (432); an arc-shaped guide groove (4351) is provided on the guide disk (435); the number of the driving blocks (437) is There are multiple drive blocks (437) rotatably connected to the guide plate (435), the drive block (437) is connected to the shift rod (436), the shift rod (436) passes through the guide groove (4351) and the second drive groove (4321), the interior of the connecting member (438) is provided with a card slot (4381), the drive block (437) extends into the connecting member (438) and can extend into the card slot (4381), the limiting structure (434) is provided inside the cargo hold (3), the limiting structure (434) is used to provide friction for the guide plate (435), and the elastic structure (433) is provided between the drive plate (432) and the guide plate (435).

8. The low-altitude delivery aircraft according to claim 7, characterized in that: The limiting structure (434) includes a limiting ring (4341), two guide wheels (4342) and a brake wire (4343); a cavity (35) connected to the cargo bin (3) is provided on the top of the cargo bin (3); the limiting ring (4341) is slidably connected to the inner wall of the cavity (35); the brake wire (4343) is fixedly connected to the limiting ring (4341); the two guide wheels (4342) are rotatably installed in the cavity (35); the brake wire (4343) passes around the two guide wheels (4342); and the end of the brake wire (4343) away from the limiting ring (4341) is fixedly connected to the synchronizer (63).

9. The low-altitude delivery aircraft according to claim 8, characterized in that: The elastic structure (433) includes a spring (4331) and two connecting wires (4332), the two connecting wires (4332) are U-shaped, and a bent portion is provided at the end; the two connecting wires (4332) pass through the spring (4331), and the bent portion is connected to the end of the spring (4331), one of the connecting wires (4332) is connected to the driving disk (432), and the other connecting wire (4332) is connected to the guide disk (435).

10. The low-altitude delivery aircraft according to claim 1, characterized in that: A hook (51) is provided at one end of the lifting rope (5) away from the retracting and releasing mechanism (4).

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