Loading assembly and load-bearing light-weight annular airship

Abstract

The utility model relates to a carrying assembly and a load-bearing light-weight annular airship, and relates to the technical field of carrying and airships. The object carrying assembly comprises an airship shell, an airship body, an airship body and an airship body, the cavity side wall (3) penetrates through the airship shell; a top bearing platform (2) for bearing a first heavy object is arranged on the airship shell on one side of the cavity side wall (3); and the other side of the cavity side wall (3) is provided with at least one side wall loading ring (14) for hanging a second heavy object. According to the embodiment of the invention, loading optimization and bearing light weight of the annular airship can be realized.

Description

Technical Field

[0001] This disclosure relates to the field of cargo and airship technology, and in particular to a cargo component and a lightweight, load-bearing ring-shaped airship. Background Technology

[0002] With the rapid development of the low-altitude economy and air logistics, the demand for airships as green heavy-duty transport vehicles is becoming increasingly urgent. However, currently available traditional airships employ spherical or elliptical hull designs. While these meet basic flight stability requirements, the traditional symmetrical hull design imposes stringent requirements on payload trimming, resulting in low tolerance for center of gravity adjustment errors. Even slight shifts in the center of gravity can trigger pitch imbalance. Furthermore, the curved base design of traditional airships significantly reduces the effective payload area and can lead to stress concentration and excessively high impact transmission rates, threatening heavy-load transport safety and failing to simultaneously meet the demands for high load capacity and high safety. Therefore, a new airship design is urgently needed that optimizes payload functionality and safety while ensuring flight stability.

[0003] Currently, existing airship technologies typically employ a distributed pod layout design to increase the load-bearing capacity, or use a rigid support structure to concentrate the load below the geometric center of the gasbag in an attempt to meet load requirements, as seen in patents CN119611839A and CN117262192A. Simultaneously, to strengthen the curved base of the airship, designs often involve embedding titanium alloy mesh at the bottom of the gasbag, or using an integrated inflatable honeycomb structure at the bottom to enhance the strength of the airship base, as seen in patents CN116729618A and CN219821746U.

[0004] The existing technology has at least the following technical defects:

[0005] Firstly, regarding the design of the airship's mounting system, although a distributed pod layout can be adopted, with multiple small pods symmetrically distributed at the bottom of the gasbag, this layout occupies a considerable portion of the gasbag's surface area, and the single-point load-bearing capacity is low due to limitations in the tensile strength of the skin. On the other hand, a rigid support connection method can lead to a mismatch in vibration frequencies due to the difference in stiffness between the rigid support and the flexible skin of the gasbag, easily causing low-frequency resonance and compromising stability.

[0006] Secondly, regarding the reinforcement technology of the airship's bottom, although embedding a titanium alloy reinforcing mesh at the bottom of the airbag can improve local compressive strength, the reinforcing ribs significantly increase the density of the skin in the bottom structure, leading to a decrease in effective load. Furthermore, peak stress is generated at the junction of the reinforcing ribs and the curved surface, increasing the probability of crack formation. Integrating an inflatable honeycomb structure at the bottom also results in a significant decrease in the elastic modulus at low temperatures, leading to a sharp reduction in cushioning effectiveness and insufficient reliability. Summary of the Invention

[0007] This disclosure proposes a technical solution for a cargo-carrying component and a lightweight, load-bearing ring-shaped airship.

[0008] According to one aspect of this disclosure, a cargo-carrying assembly is provided, comprising: an airship hull; and a hollow sidewall penetrating the airship hull;

[0009] The airship hull on one side of the cavity sidewall is provided with a top load-bearing platform for supporting the first weight; the other side of the cavity sidewall is provided with at least one sidewall load-bearing ring for hanging the second weight.

[0010] Preferably, the sidewall load-bearing ring is configured as a ring structure, and the ring structure is connected to the other side of the cavity sidewall.

[0011] Preferably, the top load-bearing platform and the side wall load-bearing ring are respectively provided with a plurality of limiting holes for fixing the first weight and the second weight; wherein, the plurality of limiting holes are used to detachably wrap and fasten to the first weight and / or the second weight by means of rope.

[0012] Preferably, the plurality of limiting holes are evenly distributed on the top load-bearing platform and the side wall load-bearing ring.

[0013] Preferably, the first number corresponding to the plurality of limiting holes is configured to be 6.

[0014] Preferably, the top load-bearing platform is provided with an airflow channel for airflow to pass through the cavity sidewall from the upper side to the lower side or from the lower side to the upper side of the top load-bearing platform.

[0015] Preferably, the airflow channel includes: a peripheral airflow channel corresponding to a first size and a second-sized inner airflow channel smaller than the first size inside the peripheral airflow channel.

[0016] Preferably, the second number corresponding to the peripheral airflow channels is configured to be 6.

[0017] Preferably, the number of the third type of the inner airflow channels is configured to be three.

[0018] Preferably, the multiple limiting holes corresponding to the top load-bearing platform are arranged between the outer airflow channel and the inner airflow channel.

[0019] Preferably, the airship hull includes: an outer shell and a horizontal base connected to the lower side of the outer shell; wherein the outer shell and the horizontal base are provided with a first through hole and a second through hole communicating with the first through hole; the cavity sidewall penetrates the first through hole and the second through hole.

[0020] Preferably, the lower side of the horizontal base is provided with an anti-slip texture; and / or, the texture shape corresponding to the anti-slip texture is configured as a snowflake.

[0021] Preferably, a rope is also provided on the lower side of the top load-bearing platform, passing through the side wall of the cavity.

[0022] According to one aspect of this disclosure, a lightweight, load-bearing annular airship is provided, comprising: the cargo-carrying assembly as described above; wherein the outer shell corresponding to the airship hull is configured as a centrally symmetrical annular aerodynamic outer shell.

[0023] Preferably, the shape of the centrally symmetrical annular pneumatic housing is configured as an inverted bowl shape; wherein, the top dimension of the centrally symmetrical annular pneumatic housing corresponding to the inverted bowl shape is smaller than the bottom dimension.

[0024] Preferably, a drive mechanism for driving the flight direction of the lightweight, load-bearing annular airship is provided inside the cavity sidewall.

[0025] Preferably, the drive mechanism includes: an arc-shaped rotor compartment and a propeller disposed within the rotor compartment; wherein the rotor compartment is connected to a retractable rotating shaft, and the rotating shaft is connected to the propeller.

[0026] Preferably, the rotating shaft passes through a propeller receiving slot provided in the rotor compartment; the propeller is connected via the outside of the rotating shaft exposed within the propeller receiving slot.

[0027] Preferably, the drive mechanism further includes a retractable support rod for connecting the lower side of the top load-bearing platform to the rotor compartment.

[0028] Preferably, the lightweight ring-shaped airship further includes an arc-shaped central control plate for controlling the drive mechanism to drive the lightweight ring-shaped airship to fly.

[0029] Preferably, the cavity sidewall, the centrally symmetrical annular aerodynamic shell, and the horizontal base connected to the lower side of the centrally symmetrical annular aerodynamic shell form a sealed hollow structure;

[0030] The cavity sidewall, the centrally symmetrical annular pneumatic shell, or the horizontal base is provided with a gas valve; the gas valve is used to fill the sealed hollow structure with helium or to release helium from the sealed hollow structure.

[0031] Preferably, the geometry of the top load-bearing platform is similar to the geometry of the centrally symmetrical annular pneumatic shell or the horizontal base connected to the lower side of the centrally symmetrical annular pneumatic shell.

[0032] In the embodiments of this disclosure, a technical solution for a cargo-carrying component and a lightweight ring-shaped airship is proposed to solve at least one technical problem of existing airships, namely poor balance, insufficient loading flexibility, and high landing risk.

[0033] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure.

[0034] Other features and aspects of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0035] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the specification, serve to illustrate the technical solutions of this disclosure.

[0036] Figure 1 The diagram shows the external overall structure of the cargo-carrying components and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a first-view perspective.

[0037] Figure 2 The diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a first-view perspective.

[0038] Figure 3 The diagram shows the external overall structure of the cargo-carrying components and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a second perspective.

[0039] Figure 4 This diagram shows the external overall structure of the cargo-carrying components and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a third-person perspective.

[0040] Figure 5 This diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight circular airship according to an embodiment of the present disclosure from a third-person perspective.

[0041] Figure 6 This diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a fourth perspective.

[0042] Figure 7 This diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight ring-shaped airship according to an embodiment of the present disclosure, viewed from a fifth perspective opposite to the fourth perspective.

[0043] Figure 8 A schematic diagram of the airflow direction during the ascent phase of the cargo-carrying component and the lightweight circular airship according to an embodiment of the present disclosure is shown in a second view.

[0044] Figure 9A schematic diagram of the airflow direction during the level flight phase of the cargo-carrying components and the lightweight ring airship according to an embodiment of the present disclosure is shown in a second view.

[0045] Figure 10 A schematic diagram of the airflow direction during the descent phase of the cargo-carrying component and the lightweight ring airship according to an embodiment of the present disclosure is shown in a second-view perspective. Detailed Implementation

[0046] Various exemplary embodiments, features, and aspects of this disclosure will now be described in detail with reference to the accompanying drawings. The same reference numerals in the drawings denote elements that have the same or similar functions. Although various aspects of the embodiments are shown in the drawings, they are not necessarily drawn to scale unless specifically indicated otherwise.

[0047] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0048] In this document, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent three cases: A alone, A and B simultaneously, and B alone. Furthermore, the term "at least one" in this document means any combination of at least two of any one or more elements. For example, including at least one of A, B, and C can mean including any one or more elements selected from the set consisting of A, B, and C.

[0049] Furthermore, to better illustrate this disclosure, numerous specific details are set forth in the following detailed description. Those skilled in the art will understand that this disclosure can be practiced without certain specific details. In some instances, methods, means, components, and circuits well known to those skilled in the art have not been described in detail in order to highlight the main points of this disclosure.

[0050] Figure 1 The diagram shows the external overall structure of the cargo-carrying components and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a first-view perspective. Figure 2 The diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a first-view perspective. Figure 3 The diagram shows the external overall structure of the cargo-carrying components and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a second perspective. Figure 4 This diagram shows the external overall structure of the cargo-carrying components and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a third-person perspective. Figure 5 This diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight circular airship according to an embodiment of the present disclosure from a third-person perspective. Figure 6This diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight ring-shaped airship according to an embodiment of the present disclosure from a fourth perspective. Figure 7 This diagram shows a partial external structural view of the cargo-carrying assembly and the lightweight ring-shaped airship according to an embodiment of the present disclosure, viewed from a fifth perspective opposite to the fourth perspective. Figure 8 A schematic diagram of the airflow direction during the ascent phase of the cargo-carrying component and the lightweight circular airship according to an embodiment of the present disclosure is shown in a second view. Figure 9 A schematic diagram of the airflow direction during the level flight phase of the cargo-carrying components and the lightweight ring airship according to an embodiment of the present disclosure is shown in a second view. Figure 10 A schematic diagram of the airflow direction during the descent phase of the cargo-carrying component and the lightweight ring airship according to an embodiment of the present disclosure is shown in a second-view perspective.

[0051] This disclosure discloses a cargo-carrying assembly comprising: an airship hull; and a hollow sidewall 3 penetrating the airship hull; a top load-bearing platform 2 for supporting a first weight is provided on one side of the hollow sidewall 3; and at least one sidewall load-bearing ring 14 for attaching a second weight is provided on the other side of the hollow sidewall 3. This addresses the technical problem of insufficient flexibility in cargo-carrying capabilities of existing airships.

[0052] In embodiments of this disclosure and other possible embodiments, the sidewall load-bearing ring 14 is configured as a ring structure, which is connected to the other side of the cavity sidewall 3.

[0053] In the embodiments of this disclosure, the top load-bearing platform 2 and the side wall load-bearing ring 14 are respectively provided with a plurality of limiting holes 15 for fixing the first weight and the second weight; wherein, the plurality of limiting holes 15 are used to detachably wrap and fasten to the first weight and / or the second weight by means of ropes 4. By using the plurality of limiting holes 15 provided on the top load-bearing platform 2 and the side wall load-bearing ring 14 for fixing the first weight and the second weight, the technical problem of insufficient flexibility in the mounting of existing airships is further solved.

[0054] In the embodiments of this disclosure and other possible embodiments, the sidewall load-bearing ring 14 is configured as a ring structure, and a plurality of limiting holes 15 provided in the sidewall load-bearing ring 14 are disposed on the ring structure corresponding to the sidewall load-bearing ring 14.

[0055] In the embodiments of this disclosure, the plurality of limiting holes 15 are evenly distributed on the top load-bearing platform 2 and the side wall load-bearing ring 14; the first number of the plurality of limiting holes 15 is configured to be 6.

[0056] In the embodiments of this disclosure, the top load-bearing platform 2 is provided with an airflow channel 8 for airflow to pass through the hollow sidewall 3 from the upper side to the lower side or from the lower side to the upper side of the top load-bearing platform 2. The interaction between the airflow within the airflow channel 8 and the airflow within the airship hull increases the balance of the lightweight, load-bearing annular airship.

[0057] In the embodiments of this disclosure, the airflow channel 8 includes: a peripheral airflow channel 8-1 corresponding to a first size and a second-sized inner airflow channel 8-2 smaller than the first size inside the peripheral airflow channel 8-1.

[0058] In the embodiments of this disclosure, the second number of the peripheral airflow channels 8-1 is configured to be 6; and the third number of the inner airflow channels 8-2 is configured to be 3.

[0059] In the embodiments of this disclosure, a plurality of limiting holes 15 corresponding to the top load-bearing platform 2 are disposed between the outer airflow channel 8-1 and the inner airflow channel 8-2.

[0060] In an embodiment of this disclosure, the airship hull includes: an outer shell and a horizontal base 6 connected to the lower side of the outer shell; wherein the outer shell and the horizontal base 6 are provided with a first through hole and a second through hole communicating with the first through hole; the cavity sidewall 3 penetrates the first through hole and the second through hole.

[0061] In embodiments of this disclosure and other possible embodiments, the outer shell corresponding to the airship hull is configured as a centrally symmetrical annular aerodynamic outer shell 1.

[0062] In embodiments of this disclosure and other possible embodiments, the centrally symmetrical annular aerodynamic shell 1 is configured in the shape of an inverted bowl; wherein the top dimension of the centrally symmetrical annular aerodynamic shell 1 corresponding to the inverted bowl shape is smaller than the bottom dimension. The centrally symmetrical annular aerodynamic shell 1 corresponding to the inverted bowl shape is used to solve the technical problem of poor balance in existing airships.

[0063] In the embodiments of this disclosure and other possible embodiments, the cavity sidewall 3, the centrally symmetrical annular aerodynamic shell 1, and the horizontal base 6 connected to the lower side of the centrally symmetrical annular aerodynamic shell 1 form a sealed hollow structure; wherein, the cavity sidewall 3, the centrally symmetrical annular aerodynamic shell 1, or the horizontal base 6 is provided with an air valve 5; the air valve 5 is used to fill the sealed hollow structure with helium or to release helium from the sealed hollow structure. Using the air valve 5 to fill the sealed hollow structure with helium or to release helium from the sealed hollow structure solves the technical problem of high landing risk in existing airships.

[0064] In the embodiments of this disclosure and other possible embodiments, the geometry corresponding to the top load-bearing platform 2 is similar to the geometry corresponding to the centrally symmetrical annular pneumatic housing 1 or the horizontal base 6 connected to the lower side of the centrally symmetrical annular pneumatic housing 1.

[0065] In the embodiments of this disclosure, the lower side of the horizontal base 6 is provided with an anti-slip texture 7; the texture shape corresponding to the anti-slip texture 7 is configured as a snowflake; and the lower side of the top load-bearing platform 2 is also provided with a rope 4 passing through the hollow sidewall 3.

[0066] This disclosure also proposes a lightweight, load-bearing annular airship, comprising: the cargo-carrying components as described above; wherein the outer shell corresponding to the airship hull is configured as a centrally symmetrical annular aerodynamic outer shell 1.

[0067] This disclosure also proposes a lightweight, load-bearing annular airship, comprising: an airship hull; the outer shell corresponding to the airship hull is configured as a centrally symmetrical annular aerodynamic outer shell 1.

[0068] In the embodiments of this disclosure, the shape of the centrally symmetrical annular pneumatic housing 1 is configured as an inverted bowl shape; wherein, the top dimension of the centrally symmetrical annular pneumatic housing 1 corresponding to the inverted bowl shape is smaller than the bottom dimension.

[0069] In the embodiments of this disclosure, a drive mechanism for driving the flight direction of the lightweight load-bearing annular airship is provided inside the cavity sidewall 3.

[0070] In an embodiment of this disclosure, the drive mechanism includes: an arc-shaped rotor compartment 12 and a propeller 11 disposed within the rotor compartment 12; wherein the rotor compartment 12 is connected to a retractable rotating shaft 13, and the rotating shaft 13 is connected to the propeller 11.

[0071] In embodiments of this disclosure and other possible embodiments, the rotating shaft 13 passes through a propeller receiving slot provided in the rotor compartment 12; the propeller 11 is connected via the outside of the rotating shaft 13 exposed in the propeller receiving slot.

[0072] In embodiments of this disclosure, the drive mechanism further includes a retractable support rod 10 for connecting the lower side of the top load-bearing platform 2 to the rotor compartment 12.

[0073] In embodiments of this disclosure, the lightweight ring-shaped airship further includes an arc-shaped central control plate 9 for controlling the drive mechanism to drive the lightweight ring-shaped airship to fly.

[0074] In the embodiments of this disclosure and other possible embodiments, the central control board 9 is used to control the gas valve 5 to control the filling of helium into the sealed hollow structure or the release of helium from the sealed hollow structure, so as to realize the airship take-off and / or landing.

[0075] For example, when the air valve 5 is used to control the filling of helium into the sealed hollow structure, the air volume of the corresponding sealed hollow structure inside the airship meets the buoyancy required for its ascent, thus enabling the airship to take off; in the airship's take-off state, the set destination navigation information is obtained; based on the set destination navigation information, the airship's drive mechanism is used to drive the lightweight ring airship in the direction of flight.

[0076] For example, during the process of controlling the release of helium from the sealed hollow structure at a first rate using the gas valve 5, the hovering state of the airship is determined; in the hovering state, it is determined whether the position of the airship is at the set landing position corresponding to the set destination navigation information; if it is at the set landing position, the gas valve 5 is used to control the release of helium from the sealed hollow structure at a second rate less than the first rate to achieve airship landing; otherwise, the position of the airship is obtained; using the position of the airship and the landing position navigation information corresponding to the set landing position, the airship's drive mechanism is used to drive the lightweight ring airship in the direction of flight; until the position of the airship is at the set landing position, the gas valve 5 is used to control the release of helium from the sealed hollow structure at a second rate less than the first rate to achieve airship landing.

[0077] In embodiments of this disclosure and other possible embodiments, the central control board 9 includes: a processor; and a memory connected to the processor for storing processor-executable instructions.

[0078] In embodiments of this disclosure and other possible embodiments, the memory is used to store the set destination navigation information. The processor is used to drive the lightweight ring-shaped airship in the direction of flight using the airship's drive mechanism based on the set destination navigation information; the processor is also used to determine whether the airship's position is at the set landing position corresponding to the set destination navigation information; if it is at the set landing position, the processor uses the gas valve 5 to control the release of helium gas from the sealed hollow structure at a second rate less than the first rate to achieve airship landing; otherwise, the processor obtains the position corresponding to the airship; using the airship's position and the landing position navigation information corresponding to the set landing position, the processor uses the airship's drive mechanism to drive the lightweight ring-shaped airship in the direction of flight; until the airship's position is at the set landing position, the processor uses the gas valve 5 to control the release of helium gas from the sealed hollow structure at a second rate less than the first rate to achieve airship landing.

[0079] In embodiments of this disclosure and other possible embodiments, the processor includes: a calculator and a subprocessor; the calculator is used to determine whether the airship's position is at a set landing position corresponding to the set destination navigation information; if it is at the set landing position, the subprocessor is used to control the release of helium gas from the sealed hollow structure at a second rate less than a first rate using the gas valve 5 to achieve airship landing; otherwise, the subprocessor obtains the position corresponding to the airship, and uses the airship's position and the landing position navigation information corresponding to the set landing position to drive the lightweight ring airship in the direction of flight using the airship's drive mechanism; until the airship's position is at the set landing position, the subprocessor controls the gas valve 5 to control the release of helium gas from the sealed hollow structure at a second rate less than a first rate to achieve airship landing. The subprocessor is also used to drive the lightweight ring airship in the direction of flight using the airship's drive mechanism based on the set destination navigation information.

[0080] In embodiments of this disclosure and other possible embodiments, the processor may be configured to be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), controllers, microcontrollers, microcontrollers, or microprocessors.

[0081] In embodiments of this disclosure and other possible embodiments, the memory may be implemented by any type of volatile or non-volatile storage device or a combination thereof, such as static random access memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic storage, flash memory, magnetic disk or optical disk.

[0082] In the embodiments of this disclosure, the cavity sidewall 3, the centrally symmetrical annular pneumatic shell 1, and the horizontal base 6 connected to the lower side of the centrally symmetrical annular pneumatic shell 1 form a sealed hollow structure; wherein, the cavity sidewall 3, the centrally symmetrical annular pneumatic shell 1, or the horizontal base 6 is provided with an air valve 5; the air valve 5 is used to fill the sealed hollow structure with helium or to release helium from the sealed hollow structure.

[0083] In the embodiments of this disclosure, the geometry of the top load-bearing platform 2 is similar to the geometry of the centrally symmetrical annular pneumatic housing 1 or the horizontal base 6 connected to the lower side of the centrally symmetrical annular pneumatic housing 1.

[0084] In embodiments of this disclosure and other possible embodiments, such as Figures 1 to 10 As shown, the structure includes an annular pneumatic housing 1, a horizontal base 6 fixedly connected to the annular pneumatic housing 1, a hollow sidewall 3, and a top load-bearing platform 2 fixedly connected to the hollow sidewall 3 and the annular pneumatic housing 1; wherein the fixed connection is a detachable fixed connection.

[0085] In embodiments of this disclosure and other possible embodiments, such as Figures 1 to 10 As shown, the annular pneumatic housing 1 is fixedly connected to the horizontal base 6; wherein, the bottom of the horizontal base 6 is provided with a centrally symmetrical anti-slip texture 7, and the anti-slip texture 7 is designed to be arranged in six groups of rings in a snowflake-like outward array.

[0086] In embodiments of this disclosure and other possible embodiments, such as Figures 1 to 10 As shown, the hollow sidewall 3 vertically penetrates the annular aerodynamic shell 1 and the horizontal base 6; an air valve 5 is provided on the hollow sidewall 3, the air valve 5 penetrates the hollow sidewall 3, one end of the air valve 5 is connected to the external environment, and the other end of the air valve 5 is connected to the internal environment of the airship.

[0087] In embodiments of this disclosure and other possible embodiments, such as Figures 1 to 10 As shown, the cavity sidewall 3 is provided with multiple sidewall load rings 14, and the sidewall load rings 14 are provided with multiple symmetrical and evenly distributed limiting holes 15; the top of the cavity sidewall 3 and the top of the annular pneumatic shell 1 are fixedly connected to the top load-bearing platform 2.

[0088] In the embodiments of this disclosure and other possible embodiments, the top load-bearing platform 2 is provided with a plurality of symmetrical and evenly distributed limiting holes 15, a hanging cable 4 is provided at the bottom center of the top load-bearing platform 2, and two parallel and symmetrical support rods 10 are provided at the bottom edge of the top load-bearing platform 2.

[0089] In embodiments of this disclosure and other possible embodiments, such as Figures 1 to 10 As shown, the upper end of the support rod 10 is fixedly connected to the top load-bearing platform 2, the middle position is fixedly connected to the central control plate 9, and the lower end is fixedly connected to the rotor compartment 12; the rotor compartment 12 is fixedly connected to the rotating shaft 13; the rotating shaft 13 is parallel to the two support rods 10, the rotating shaft 13 vertically penetrates the rotor compartment 12, the upper end of the rotating shaft 13 is fixedly connected to the central control plate 9, and the lower end is fixedly connected to the propeller 11; the center of the propeller 11 is flush with the center of the rotor compartment 12.

[0090] In the embodiments of this disclosure and other possible embodiments, the airship is released as follows: the annular airship is placed horizontally upward on a parallel ground with the horizontal base 6 as its base, and the rotor compartment 12 is built into the cavity sidewall 3;

[0091] Helium is introduced into the airship by opening the air valve 5. When the amount of air inside the airship (airship) (the sealed hollow structure composed of the annular aerodynamic shell 1, the horizontal base 6, and the hollow sidewall 3) meets the buoyancy required for its ascent, the airship takes off. After rising to a certain height, the rotor compartment 12 extends downward from the hollow sidewall 3 through the support rod 10 under the drive of the rotating shaft 13, and the propeller 11 begins to rotate.

[0092] In the embodiments disclosed herein and other possible embodiments, the airship operates as follows: the amount of air injected into the airship's interior (a sealed hollow structure composed of the annular aerodynamic shell 1, the horizontal base 6, and the hollow sidewalls 3) is controlled by switching the air valve 5 on and off, thereby changing the buoyancy of the airship and its downward movement; the rotation of the rotating shaft 13 is controlled by the central control plate 9 to change the propulsion direction of the propeller 11, thereby achieving the airship's turning; when the rotating shaft 13 drives the propeller 11 toward the right front, the airship moves to the left front; when the rotating shaft 13 drives the propeller 11 toward the left front, the airship moves to the right front; when the airship rotates to a 180-degree angle in either direction, it achieves a turnaround.

[0093] In the embodiments of this disclosure and other possible embodiments, the airship operates as follows: Cargo (carried heavy objects) or work units are fixed through the limiting holes of the top load-bearing platform 2 located in the central area of ​​the top of the annular aerodynamic shell 1, thereby enabling equipment mounting and cargo (carried heavy objects) transportation during airship operation; Multiple sidewall load-bearing rings 14 with evenly distributed and symmetrical limiting holes 15 are provided inside the hollow sidewall 3, allowing the ropes binding the loads to be detachably wound and tightened onto the limiting holes 15, with the hanging ends of the ropes binding and fixing the loads to be carried, thus achieving the fixation of cargo (carried heavy objects) through the limiting holes 15.

[0094] In the embodiments disclosed herein and other possible embodiments, the airship is recovered as follows: the gas valve 5 begins to discharge helium to move the airship to hover above the horizontal ground, the propeller 11 is controlled to stop rotating, and the rotor compartment 12, driven by the rotating shaft 13, retracts upward into the cavity sidewall 3 through the support rod 10. Then, the corresponding gas valve 5 begins to discharge helium, causing the airship to fall smoothly and slowly to the ground.

[0095] In the embodiments of this disclosure and other possible embodiments, a centrally symmetrical, lightweight, ring-shaped airship main structure is designed in the shape of an "inverted bowl". It adopts a vertically hollow ring-shaped aerodynamic shell 1 with a narrow top and a wide bottom. The horizontal base 6 is flat. The cross-sections of the ring-shaped aerodynamic shell 1 and the horizontal base 6 present a semi-elliptical geometry that is narrow at the top and wide at the bottom, thereby improving aerodynamic stability.

[0096] In the embodiments of this disclosure and other possible embodiments, the upper structure of the annular pneumatic shell 1 is reinforced to become the main load-bearing component, and a disc-shaped top load-bearing platform 2 is provided in the top center area of ​​the main structure of the annular pneumatic shell 1 for bearing heavy objects. At the same time, multiple evenly distributed and symmetrical limiting holes 15 are provided on this top load-bearing platform 2. By placing the load inside the protective container, the load is securely installed on the top load-bearing platform 2 using the limiting holes 15, thereby achieving safe transportation of the load.

[0097] In the embodiments of this disclosure and other possible embodiments, the hollow sidewall 3 is provided with one or more sidewall load-bearing rings 14, and a plurality of evenly distributed and symmetrical limiting holes 15 are provided on the structure of the sidewall load-bearing rings 14. The limiting holes 15 are embedded with wear-resistant rings to provide places for the rope 4 to be wound and tightened. The hanging end of the rope is used to tie and fix the load. By adjusting the relative position of the load on the limiting holes 15 provided on the sidewall load-bearing rings 14 (changing the distance between the loads corresponding to the lever arm length in the lever principle) or adjusting the weight distribution of the load (changing the magnitude of the force corresponding to the lever arm length and the weight of the load in the lever principle), the load balance of the entire airship is achieved, and the load balance is achieved by using the lever principle to realize the safe transportation of the load.

[0098] In the embodiments of this disclosure and other possible embodiments, the disclosed embodiments provide a lightweight ring-shaped airship with central symmetry and load-bearing capacity.

[0099] 1. Dynamic balance optimization: The annular central symmetry structure design of the annular aerodynamic shell 1 and the vertical arrangement of the center of gravity of the top load-bearing platform 2 ensure that the load torque is minimized to almost zero, enabling the airship to maintain excellent stability during flight. It is not easy to tilt when the load changes and can still maintain a stable attitude. For example, based on the "inverted bowl" shape design, during the airship's ascent phase, the airflow will be guided by the "inverted bowl" structure to form meridional streamlines, reducing some of the dynamic aerodynamic drag; during the airship's level flight phase, the airflow will be guided by the side arc structure of the "inverted bowl" structure to form meridional streamlines, reducing some of the dynamic aerodynamic drag.

[0100] 2. Impact-resistant safety design: The horizontal base 6 is designed to provide an additional buffer layer in the event of abnormal landing or crash, helping to absorb and disperse impact energy, thereby significantly reducing damage to the airship structure and improving overall safety. For example, during the vertical descent phase of the airship, the lower side of the base plane 6 forms a vertical windward surface with the airflow direction, inducing the airflow to form a pressure stagnation zone below the base plane 6, generating dynamic aerodynamic drag, thereby reducing the overall speed of the airship.

[0101] 3. Multifunctional mounting design: Multiple evenly distributed and symmetrical limiting holes 15 are provided on the top load-bearing platform 2 and the hollow sidewall 3 in the top central area. The sidewall load-bearing rings 14 corresponding to the multiple evenly distributed and symmetrical limiting holes 15 on the hollow sidewall 3 adopt a segmented modular design, which can flexibly adjust the number and position of the sidewall load-bearing rings 14 fixed on the hollow sidewall 3 according to the actual needs of the user. Each sidewall load-bearing ring 14 is provided with multiple evenly distributed and symmetrical limiting holes 15. The limiting holes 15 can provide places for the rope 4 to be wound and tightened. The hanging end of the rope is used to tie and fix the load-bearing weight, thereby realizing the fixation and transportation of the load-bearing weight. In addition, the reinforced hollow sidewall 3 and top load-bearing platform 2 achieve lightweight design while ensuring excellent load-bearing capacity, improving the efficiency and performance of the airship.

[0102] In summary, the embodiments of this disclosure provide a lightweight, centrally symmetrical, load-bearing ring-shaped airship (lightweight ring-shaped airship), solving the technical problems of poor balance, insufficient payload flexibility, and high landing risk of existing airships. The preferred technical solution provided by the embodiments of this disclosure is a helium airship with a centrally symmetrical load-bearing layout, multi-functional payload capacity, and fall buffer function.

[0103] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A carrier assembly comprising: The airship hull is characterized by a hollow sidewall (3) that penetrates the airship hull. The airship hull on one side of the cavity sidewall (3) is provided with a top load-bearing platform (2) for bearing the first weight; the other side of the cavity sidewall (3) is provided with at least one sidewall load-bearing ring (14) for hanging the second weight. The top load-bearing platform (2) is provided with an airflow channel (8) for airflow to flow through the cavity sidewall (3) from the top load-bearing platform (2) to the bottom or from the bottom to the top.

2. The carrier assembly of claim 1, wherein, The top load-bearing platform (2) and the side wall load-bearing ring (14) are respectively provided with multiple limiting holes (15) for fixing the first weight and the second weight.

3. The carrier assembly of claim 1, wherein, The airflow channel (8) includes: a peripheral airflow channel (8-1) corresponding to a first size and a second-sized inner airflow channel (8-2) smaller than the first size inside the peripheral airflow channel (8-1); and / or, The multiple limiting holes (15) corresponding to the top load-bearing platform (2) are arranged between the outer airflow channel (8-1) and the inner airflow channel (8-2).

4. The cargo-carrying assembly according to any one of claims 1-3, characterized in that, The airship hull includes: an outer shell and a horizontal base (6) connected to the lower side of the outer shell; wherein the outer shell and the horizontal base (6) are provided with a first through hole and a second through hole communicating with the first through hole; the cavity sidewall (3) penetrates the first through hole and the second through hole; and / or, The lower side of the top load-bearing platform (2) is also provided with a rope (4) that passes through the side wall (3) of the cavity.

5. A lightweight, load-bearing ring-shaped airship, characterized in that, include: The cargo-carrying assembly as described in any one of claims 1-4; wherein the outer shell corresponding to the airship hull is configured as a centrally symmetrical annular aerodynamic shell (1); the hollow sidewall (3), the centrally symmetrical annular aerodynamic shell (1) and the horizontal base (6) connected to the lower side of the centrally symmetrical annular aerodynamic shell (1) form a sealed hollow structure; The cavity sidewall (3), the centrally symmetrical annular pneumatic shell (1), or the horizontal base (6) is provided with a gas valve (5); the gas valve (5) is used to fill the sealed hollow structure with helium or to release helium from the sealed hollow structure.

6. The lightweight, load-bearing ring-shaped airship according to claim 5, characterized in that, The centrally symmetrical annular pneumatic housing (1) is configured in the shape of an inverted bowl; wherein the top dimension of the centrally symmetrical annular pneumatic housing (1) corresponding to the inverted bowl shape is smaller than the bottom dimension.

7. The lightweight, load-bearing ring-shaped airship according to any one of claims 5 or 6, characterized in that, The cavity sidewall (3) is provided with a drive mechanism for driving the flight direction of the lightweight ring airship.

8. The lightweight, load-bearing ring-shaped airship according to claim 7, characterized in that, The drive mechanism includes: a rotor compartment (12) and a propeller (11) disposed inside the rotor compartment (12); wherein the rotor compartment (12) is connected to a retractable rotating shaft (13), and the rotating shaft (13) is connected to the propeller (11).

9. The lightweight, load-bearing ring-shaped airship according to claim 8, characterized in that, The drive mechanism further includes a support rod (10) for connecting the lower side of the top load-bearing platform (2) to the rotor compartment (12).

10. The lightweight, load-bearing ring-shaped airship according to any one of claims 5, 6, 8, and 9, characterized in that, The geometry of the top load-bearing platform (2) is similar to that of the centrally symmetrical annular pneumatic shell (1) or the horizontal base (6) connected to the lower side of the centrally symmetrical annular pneumatic shell (1).

11. The lightweight, load-bearing ring-shaped airship according to claim 7, characterized in that, The geometry of the top load-bearing platform (2) is similar to that of the centrally symmetrical annular pneumatic shell (1) or the horizontal base (6) connected to the lower side of the centrally symmetrical annular pneumatic shell (1).

Images