Integrated propulsion device and aerostat
By integrating the propulsion components and rudder into one unit, the problem of low disassembly efficiency of the airship was solved, achieving efficient disassembly and directional control.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIHANG UNIV
- Filing Date
- 2026-02-02
- Publication Date
- 2026-05-08
AI Technical Summary
When existing airships require maintenance or repair of the capsule, the disassembly efficiency of the propulsion components and rudder is relatively low.
Design an integrated propulsion device that integrates the propulsion component and the rudder into a single structure. The propulsion component includes a mounting component, a drive component, and a propeller. The rudder is connected to the mounting component, and directional control is achieved by the airflow generated by the propeller acting on the rudder surface.
It improves the disassembly efficiency of the airship, so that only the propulsion component needs to be disassembled during maintenance, repair or storage, and it can still work normally to achieve directional control of the airship.
Smart Images
Figure CN121990149A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft technology, and more particularly to an integrated propulsion device and airship. Background Technology
[0002] This section provides only background information relevant to this disclosure and is not necessarily prior art.
[0003] The airship includes a capsule, a propulsion assembly, and a rudder. The propulsion assembly and the rudder are fixedly connected to the capsule. When the capsule needs to be repaired, maintained, transported, or stored, the propulsion assembly and the rudder need to be removed from the capsule, which is inefficient. Summary of the Invention
[0004] The purpose of this invention is to at least solve the problem in the prior art where, when repairing or maintaining an airship, the propulsion assembly and rudder need to be removed from the airship separately, resulting in low disassembly efficiency. This objective is achieved through the following technical solution: A first aspect of the present invention provides an integrated propulsion device for use in an airship, the airship including a capsule, the integrated propulsion device comprising: A propulsion assembly connected to the capsule, the propulsion assembly including a mounting component, a drive component, and a propeller, the drive component being disposed on the mounting component and connected to the propeller to drive the propeller to rotate; and The rudder includes a control surface, the propeller faces the control surface, and the rudder is connected to the mounting component, so that the propulsion assembly and the rudder are integrated into a single structure.
[0005] According to an embodiment of the present invention, an integrated propulsion device is provided with a propulsion assembly and a rudder. The propulsion assembly includes a mounting component, a drive component, and a propeller. The drive component is mounted on the mounting component and connected to the propeller to drive the propeller to rotate. The rudder includes a control surface, the propeller faces the control surface, and the rudder is connected to the mounting component. Because the propulsion assembly and the rudder are integrated into one unit, the propulsion assembly can be removed from the airship body only when it is being repaired, maintained, transported, or stored, thus improving the disassembly efficiency of the airship. Furthermore, since the propulsion assembly includes a mounting component, a drive component, and a propeller, the airflow generated by the propeller can act on the control surface to control the direction of the airship, enabling the airship to operate normally.
[0006] In addition, the integrated propulsion device according to the present invention may also have the following additional technical features: In some embodiments of the invention, the propulsion assembly is detachably connected to the capsule.
[0007] In some embodiments of the present invention, the propulsion component is connected to the bladder by means of adhesion, hinge connection or snap-fit connection. A second aspect of the present invention provides an airship, which further includes a counterweight assembly connected to the capsule, and the counterweight assembly and the integrated propulsion device are respectively disposed on opposite sides of the capsule. The direction control of the airship can be achieved by controlling the torque generated by the interaction between the deflection of the rudder and the airflow of the propeller to achieve pitch and yaw motion.
[0008] In addition, the airship according to the present invention may also have the following additional technical features: In some embodiments of the present invention, the integrated propulsion device is located at the rear end of the capsule, and the counterweight assembly is located at the front end of the capsule. In some embodiments of the present invention, the propulsion assembly further includes: The power supply unit and the electronic speed controller are provided. The electronic speed controller is mounted on the mounting component. The power supply unit is electrically connected to the electronic speed controller, and the electronic speed controller is electrically connected to the drive unit.
[0009] In some embodiments of the present invention, the propulsion assembly further includes: The load-bearing component is disposed on the mounting component or on the counterweight assembly.
[0010] In some embodiments of the present invention, the power supply component is disposed on the mounting component or on the counterweight assembly.
[0011] In some embodiments of the present invention, the number of integrated propulsion devices is at least two, and at least two rudders are arranged at circumferential intervals along the capsule, with each integrated propulsion device connected to the capsule.
[0012] In some embodiments of the present invention, at least two of the integrated propulsion devices are arranged at uniform intervals along the circumference of the capsule. Attached Figure Description
[0013] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 A schematic diagram of the structure of an airship according to an embodiment of the present invention is shown. Figure 2 for Figure 1 Another structural schematic diagram of the airship shown; Figure 3 for Figure 2 The diagram shown is a structural schematic of the airship from a second-person perspective; Figure 4 for Figure 1 A schematic diagram of the propulsion components and rudder of the airship shown in the figure; Figure 5 for Figure 4 The diagram shown illustrates the working principle of the airship. Figure 6 for Figure 1 The diagram shows a cross-sectional view of the airship's capsule.
[0014] The attached figures are labeled as follows: 100. Airship; 10. Encapsulation; 11. Substrate layer; 12. First intermediate layer; 13. Second intermediate layer; 14. Protective layer; 20. Propulsion assembly; 21. Mounting component; 22. Drive component; 23. Propeller; 24. Power supply component; 25. Electronic speed controller; 27. Load cell component; 28. Circuit board; 30. Rudder; 31. Control surface; 40. Counterweight components; 200. The direction of airflow; 300. The direction of the airflow reaction force; α, the angle between the airflow direction and the control surface. Detailed Implementation
[0015] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
[0016] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.
[0017] Although terms such as first, second, third, etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the first element, component, region, layer, or segment discussed below may be referred to as the second element, component, region, layer, or segment without departing from the teachings of the exemplary embodiments.
[0018] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "middle," "outer," "below," "below," "above," "over," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure is flipped, an element described as "below other elements or features" or "below other elements or features" would subsequently be oriented "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both upper and lower orientations.
[0019] Existing airships typically include a capsule, a propulsion assembly, and a rudder. The propulsion assembly and the rudder are fixedly connected to the capsule. When the capsule needs to be repaired or maintained, the propulsion assembly and the rudder need to be removed from the capsule, which is inefficient.
[0020] To address this technical problem, the embodiments of this application propose an integrated propulsion device that allows for easy removal of the propulsion assembly from the airship during maintenance, repair, transportation, or storage, thereby improving the disassembly efficiency of the airship. Furthermore, since the propulsion assembly includes mounting components, a drive unit, and a propeller, the airflow generated by the propeller can act on the control surfaces to control the direction of the airship, ensuring its normal operation.
[0021] The specific structure of the airship of this application will be described in detail below.
[0022] like Figures 1 to 6 As shown, Figure 1 A schematic diagram of the structure of an airship 100 according to an embodiment of the present invention is shown. Figure 2 for Figure 1 Another structural schematic diagram of the airship 100 shown. Figure 3 for Figure 2 The diagram shown is a structural schematic of the airship 100 from a second perspective. An embodiment of the present invention proposes an airship 100, which includes a capsule 10, a propulsion assembly 20, and a rudder 30. The capsule 10 is filled with gas. The propulsion assembly 20 and the rudder 30 form an integrated propulsion device.
[0023] The propulsion assembly 20 is directly connected to the capsule 10. The propulsion assembly 20 includes a mounting component 21, a drive component 22, and a propeller 23. The drive component 22 is mounted on the mounting component 21 and connected to the propeller 23 to drive the propeller 23 to rotate. The rudder 30 includes a rudder surface 31. The propeller 23 is positioned facing the rudder surface 31, and the rudder 30 is connected to the mounting component 21.
[0024] It should be noted that the propulsion assembly 20 mainly provides the thrust required by the airship 100 during its forward movement and assists in achieving attitude control and maneuverability. The propulsion assembly 20 includes a mounting component 21, a drive component 22, and a propeller 23. The drive component 22 can be a power component such as a motor, and the propeller 23 can rotate under the action of the drive component 22, thereby generating airflow.
[0025] The propeller 23 here includes multiple blades, which are arranged in a vertical plane and can rotate in the vertical plane. The propeller 23 can rotate around the rotation axis of the drive member 22, which is arranged in a horizontal direction. Each blade can rotate counterclockwise or clockwise under the drive of the rotation axis.
[0026] The mounting component 21 mentioned here can be a mounting plate or mounting base structure, which enables the installation of the drive component 22.
[0027] The shape of the capsule 10 here can be an ellipsoidal structure, a spherical structure, or a pumpkin-shaped or teardrop-shaped axially symmetric body with an arc generatrix, and is not limited to this embodiment.
[0028] In addition, it is important to note that the connection between the rudder 30 and the mounting component 21 allows the rudder 30 and the propulsion component 20 to form an integrated module. It is not necessary to connect the rudder 30 to the capsule 10; only the propulsion component 20 needs to be connected to the capsule 10. Therefore, when maintaining the capsule 10, it is only necessary to remove the propulsion component 20 from the capsule 10, thereby speeding up the disassembly efficiency of the airship 100.
[0029] According to an embodiment of the present invention, the airship 100, by providing a propulsion assembly 20 and a rudder 30, wherein the propulsion assembly 20 includes a mounting member 21, a drive member 22, and a propeller 23, the drive member 22 is disposed on the mounting member 21 and connected to the propeller 23 to drive the propeller 23 to rotate, and the rudder 30 includes a control surface 31, the propeller 23 is disposed facing the control surface 31, and the rudder 30 is connected to the mounting member 21, can be easily removed from the airship 10 during maintenance or repair, thus improving the disassembly efficiency of the airship 100. Furthermore, since the propulsion assembly 20 is provided with the mounting member 21, the drive member 22, and the propeller 23, the airflow generated by the propeller 23 can act on the control surface 31 to control the direction of the airship 100, enabling the airship 100 to operate normally.
[0030] In some embodiments of the present invention, the propulsion component 20 is detachably connected to the capsule 10. That is, after the propulsion component 20 is connected to the capsule 10, the propulsion component 20 can be detached from the capsule 10 when needed. Therefore, the detachable connection can be made in a common manner, so as to facilitate the removal of the propulsion component 20 from the capsule 10.
[0031] Specifically, the propulsion component 20 is connected to the bladder body 10 by means of adhesive bonding, hinge connection or snap-fit connection. The connection method between the propulsion component 20 and the capsule 10 will be described in detail below.
[0032] The first connection method is bonding, which is a technology that achieves connection by generating adhesive force on the material surface with an adhesive. For example, the propulsion component 20 and the capsule 10 are connected by bonding. In this embodiment, the propulsion component 20 and the capsule 10 can be bonded together with glue or double-sided tape. When it is necessary to disassemble the propulsion component 20, it is only necessary to remove the propulsion component 20 from the capsule 10.
[0033] The second connection method is a hinge connection. That is, the hinge includes a first part and a second part, which are hinged together. The first part is connected to the propulsion assembly 20, and the second part is connected to the capsule 10, thus achieving a hinged connection between the propulsion assembly 20 and the capsule 10. Alternatively, the hinge includes a first part and a second part, which are hinged together. The second part is connected to the propulsion assembly 20, and the first part is connected to the capsule 10, thus achieving a hinged connection between the propulsion assembly 20 and the capsule 10.
[0034] The second connection method is a snap-fit connection. In this embodiment, the snap-fit includes a first snap-fit and a first slot, wherein the first snap-fit and the first slot are plugged into each other. The first snap-fit is connected to the propulsion component 20, and the first slot is connected to the bladder body 10, thereby realizing the connection between the bladder body 10 and the propulsion component 20. Alternatively, the first snap-fit is connected to the bladder body 10, and the first slot is connected to the propulsion component 20, thereby realizing the connection between the bladder body 10 and the propulsion component 20.
[0035] In some embodiments of the present invention, reference continues to be made to... Figure 1 As shown, the airship 100 also includes a counterweight assembly 40, which is connected to the capsule 10, and the counterweight assembly 40 and the integrated propulsion device are respectively disposed on opposite sides of the capsule 10.
[0036] It should be noted that the counterweight assembly 40 is an additional device used to balance the weight of mechanical components or equipment. By adjusting the mass distribution, it counteracts unbalanced torques, ensuring the stable operation of the aerostat 100. The counterweight assembly 40 can be made from a variety of materials. Traditional metals such as cast iron and lead are suitable for general loads, while tungsten alloys, due to their high density, corrosion resistance, and machinability, are often used in space-constrained or high-precision applications. The design trend of the counterweight assembly 40 emphasizes modularity and adjustability, such as magnetic connections or quick-change mechanisms, to adapt to different working conditions and facilitate weight adjustment.
[0037] The counterweight assembly 40 here can be a single counterweight or multiple counterweights. Adjacent counterweights can be connected using a magnetic attraction structure, facilitating weight adjustment of the counterweight assembly 40. It is understood that in a structure with multiple counterweights, each counterweight can have the same or different weights, thus allowing for convenient adjustment of the total weight of the counterweight assembly 40.
[0038] Specifically, each counterweight has a different weight; for example, some counterweights weigh 10 kilograms, while others weigh 5 kilograms or 2 kilograms, allowing for more accurate adjustment of the weight of the counterweight assembly 40.
[0039] To maintain the balance of the capsule 10, the counterweight assembly 40 and the integrated propulsion device are respectively located on opposite sides of the capsule 10. That is, the counterweight assembly 40 and the integrated propulsion device are located on opposite sides of the capsule 10, and the counterweight assembly 40 and the integrated propulsion device are symmetrically arranged with respect to the capsule 10. If the capsule 10 has an elliptical sphere structure, the counterweight assembly 40 and the integrated propulsion device can be located at both ends of the elliptical sphere along the major axis. Alternatively, the counterweight assembly 40 and the integrated propulsion device can also be located at both ends along the minor axis.
[0040] In some embodiments of the present invention, such as Figure 1 As shown, the integrated propulsion device is located at the rear end of the capsule 10, and the counterweight assembly 40 is located at the front end of the capsule 10. The levitation device 100 can move forward in the front-back direction, generating forward and upward motion under the propulsion of the propulsion assembly 20. Furthermore, the location of the counterweight assembly 40 at the front end of the capsule 10 and the integrated propulsion device at the rear end of the capsule 10 ensures that the levitation device 100 maintains its balance in the front-back direction, keeping it balanced during movement. The counterweight assembly 40 also counteracts any unbalanced torque of the levitation device 100.
[0041] In some embodiments of the present invention, such as Figures 4 to 5 As shown, Figure 4 for Figure 1 The schematic diagram of the propulsion assembly 20 and rudder 30 of the airship 100 shown is as follows. Figure 5 for Figure 4 The schematic diagram of the working principle of the airship 100 shown shows that the propulsion assembly 20 also includes a power supply unit 24 and an electronic speed controller 25. The electronic speed controller 25 is disposed on the mounting component 21. The power supply unit 24 is electrically connected to the electronic speed controller 25, and the electronic speed controller 25 is electrically connected to the drive component 22.
[0042] The power supply unit 24 here can supply power to components such as the electronic speed controller 25 and the drive unit 22 through wires. When the distance between the power supply unit 24 and the drive unit 22 is far, the power supply unit 24 and the drive unit 22 can be electrically connected through wires. The power transmission method can be AC power transmission or DC power transmission, or wireless power transmission, such as magnetic coupling wireless power transmission. Magnetic coupling wireless power transmission loads a high-frequency power supply onto the transmitting coil, so that the transmitting coil generates a high-frequency magnetic field under the excitation of the power supply. Under the action of this high-frequency magnetic field, the receiving coil couples to generate current, thereby realizing wireless power transmission.
[0043] It is important to note that when the power supply unit 24 supplies power to components such as the electronic speed controller 25 and the drive unit 22 via wires, it can fix the wires to the outer surface of the housing 10 to secure the wires and reduce the chance of the wires swaying in the air.
[0044] Specifically, the wires can be fixed to the outer surface of the bladder 10 by adhesive bonding. The wires can be completely bonded to the surface of the bladder 10, or the wires can be spaced out on the outer surface of the bladder 10.
[0045] In some embodiments of the present invention, such as Figure 5 As shown, the propulsion assembly 20 also includes a load member 27, which is disposed on the mounting member 21 or on the counterweight assembly 40.
[0046] The payload 27 of the airship 100 mentioned here refers to the various instruments, equipment, personnel, or experimental items carried by the airship 100, which are essential components for achieving specific missions. Specifically, the payload 27 may include radar antennas, telescopes, electronic warfare equipment, communication devices, synthetic aperture radar, optical sensors, etc., for performing tasks such as observation, communication, mapping, or scientific research.
[0047] The load element 27 can be mounted on the mounting component 21, meaning it can be integrated into the propulsion assembly 20. Alternatively, the load element 27 can be mounted on the counterweight assembly 40, in which case it can function as a counterweight. When there are multiple load elements 27, some can be integrated into the propulsion assembly 20, while others can be mounted in the counterweight assembly 40.
[0048] In some embodiments of the present invention, such as Figure 5 As shown, the power supply component 24 is mounted on the mounting component 21 or on the counterweight assembly 40.
[0049] The power supply component 24 here is a basic unit in the power supply equipment used to realize the functions of power conversion, distribution, control and protection. These components work together to ensure that the power supply can stably and efficiently supply power to the load.
[0050] Specifically, when the power supply component 24 is installed on the mounting component 21, the power supply component 24 is installed on the propulsion assembly 20. At this time, the distance between the power supply component 24 and the electronic speed controller 25, the circuit board 28 and the drive component 22 is relatively close, and it can provide power to the electronic speed controller 25, the circuit board 28 and the drive component 22.
[0051] Alternatively, the power supply unit 24 can also be located on the counterweight assembly 40. In this case, the distance between the power supply unit 24 and the electronic speed controller 25, the circuit board 28 and the drive unit 22 is relatively far, but it can still provide power to the electronic speed controller 25, the circuit board 28 and the drive unit 22. In this case, the electrical connection between the power supply unit 24 and the electronic speed controller 25, the circuit board 28 and the drive unit 22 can be achieved by wires, wherein the wires are fixed on the outer surface of the bladder body 10.
[0052] It is important to add that if the load-bearing component 27 does not require a power supply or has its own power supply, then simply installing the load-bearing component 27 at the front of the bladder body 10 can serve as a counterweight.
[0053] exist Figure 1 and Figure 2 In this system, there is one rudder 30 and one propulsion assembly 20. The propulsion method of the airship 100 is to control the interaction between the thrust of the propeller 23 and the buoyancy of the capsule 10 to achieve forward or upward movement of the airship 100. The directional control of the airship 100 can be achieved by controlling the torque generated by the interaction between the deflection of the rudder 30 and the airflow of the propeller 23 to achieve pitch and yaw movements.
[0054] Specifically, such as Figure 4 As shown, when the propeller 23 rotates in the vertical plane, it will generate a horizontal airflow. The direction of the airflow 200 is set horizontally. During the horizontal flow, the airflow will be deflected by the deflecting control surface 31. At this time, the airflow will exert a reverse force on the control surface 31, causing the airship 100 to move upward. The angle between the direction of the airflow 200 and the control surface 31 is represented by α. α can be adjusted by the degree of deflection of the control surface 31, thereby controlling the yaw angle of the airship 100.
[0055] It should be noted that when the rudder surface 31 of the rudder 30 does not deflect, the angle between the direction 200 of the airflow generated by the propeller 23 and the rudder surface 31 is 0 degrees. At this time, the power of the airflow generated by the propeller 23 cannot act on the rudder surface 31. When the rudder surface 31 of the rudder 30 deflects, the angle between the direction 200 of the airflow and the rudder surface 31 is α. The angle α is usually within 45 degrees, such as 30 degrees or 20 degrees, which allows at least part of the airflow generated by the propeller 23 to act on the rudder surface 31. The reaction force causes the aerostat 100 to deflect, changing its direction of motion. Under the combined action of the buoyancy of the capsule 10 and the reaction force of the airflow, it generates upward momentum. The direction 300 of the airflow reaction force is used to... Figure 5 The direction of the wide arrow in the image indicates that the direction of the airflow reaction force 300 is vertically upward, which allows the airship 100 to float in the air through the action of the airflow.
[0056] It is understandable that the control surface 31 of the rudder 30 can deflect in two directions during the deflection process, and the control surface 31 of the rudder 30 can deflect along the width direction of the airship 100, wherein the width direction is parallel to the horizontal axis of the airship 100. Figure 1 The front-to-back direction is perpendicular to and is in line with Figure 1 The height direction is vertical.
[0057] Continue to refer to Figure 2 and Figure 3 As shown, in some embodiments of the present invention, the number of integrated propulsion devices is at least two, and the at least two integrated propulsion devices are arranged at circumferential intervals along the capsule 10, and each integrated propulsion device is provided with a propulsion component 20.
[0058] It is important to note that if more precise and wider-range control is required for the airship 100, at least two integrated propulsion devices can be installed at appropriate locations within the capsule 10 to achieve torque balance. Furthermore, the combined use of at least two integrated propulsion devices allows for more precise and accurate motion control of the airship 100. Figure 3 The number of integrated propulsion devices is three, and the three integrated propulsion devices are arranged at intervals along the circumference of the capsule 10. Each integrated propulsion device is provided with a propulsion component 20. The movement direction of the airship 100 can be accurately controlled by selectively using a certain integrated propulsion device and the propulsion component 20 of that integrated propulsion device, making the movement process of the airship 100 more flexible.
[0059] It is understandable that the number of integrated propulsion devices can also be four, five or more. Among them, four integrated propulsion devices are arranged at intervals along the circumference of the capsule 10, and each integrated propulsion device is provided with a propulsion component 20. Five integrated propulsion devices are arranged at intervals along the circumference of the capsule 10, and each integrated propulsion device is provided with a propulsion component 20. A greater number of integrated propulsion devices are arranged at intervals along the circumference of the capsule 10, and each integrated propulsion device is provided with a propulsion component 20.
[0060] In the actual selection process, the number of integrated propulsion devices can be selected as needed, and the number of propulsion components 20 can be determined based on the number of integrated propulsion devices. In actual use, the movement direction of the airship 100 can be accurately controlled by activating one of the integrated propulsion devices.
[0061] The propulsion component 20 here can operate independently, and the direction of movement of the airship 100 can be controlled according to the operation of the selected propulsion component 20.
[0062] In some embodiments of the present invention, such as Figure 3 As shown, at least two integrated propulsion devices are evenly spaced along the circumference of the capsule 10. Figure 3 In this embodiment, the number of integrated propulsion devices is three. The three integrated propulsion devices are evenly spaced along the circumference of the capsule 10. In this embodiment, the capsule 10 can be a spherical structure, so that the rudder 30 can be evenly arranged along the circumference of the capsule 10.
[0063] The structure of capsule 10 will be described in detail below.
[0064] like Figure 6 As shown, where, Figure 6 for Figure 1 The diagram shows a cross-sectional view of the capsule 10 of the airship 100.
[0065] The material of the capsule 10, as the main structural material of the airship 100, is usually composed of multiple layers of composite materials. The main performance indicators of the capsule 10 material include strength, barrier properties, weather resistance, and processability. The materials of the capsule 10 are mainly divided into the following categories: The first category is airtight membrane materials, such as polyester film, polyethylene film, and nylon cloth, commonly used in inflatable airships 100 (such as hot air balloons and airships), characterized by their lightweight, flexibility, and ease of processing. The second category is composite materials, including high-molecular composites reinforced with carbon fiber, glass fiber, and Kevlar, achieving high strength, lightweight, and excellent flexibility through multi-layer design. The third category is rubber materials, such as styrene-butadiene rubber and nitrile rubber, mainly used for airtight membranes, possessing good wear resistance and environmental adaptability.
[0066] In the embodiments of this application, a second type of material is used to fabricate the capsule 10. Specifically, the capsule 10 is generally made of a multi-layered composite material, which includes a substrate layer 11, a first intermediate layer 12, a second intermediate layer 13, a protective layer 14, and an adhesive layer for bonding the multi-layered structure. The strength of the capsule 10 is mainly provided by the substrate layer 11. However, the substrate layer 11 in the prior art mostly adopts a single fiber structure, which makes it impossible for the airship 100 to maintain high strength for a long time in the relatively extreme natural environment of the stratosphere, thereby reducing the lifespan of the airship 100.
[0067] In the embodiments of this application, the substrate layer 11 is located inside the capsule 10, and the protective layer 14 is located outside the capsule 10. The substrate layer 11 can be made of composite materials, such as high-density polyethylene and aluminum alloy, which enables the substrate layer 11 to have tear resistance and bending resistance.
[0068] Furthermore, the substrate layer 11 here is typically in direct contact with the gas; therefore, the substrate layer 11 usually needs to be non-flammable to reduce the risk of explosion. Additionally, the substrate layer 11 of the capsule 10 must also possess high barrier properties to minimize the leakage rate of the booster gas (such as helium). For example, the substrate layer 11 of the capsule 10 of the airship 100 achieves low gas permeability through airtight fabric or polymer coating, ensuring an annual gas leakage rate of less than 1%.
[0069] Considering the specific requirements of the substrate layer 11 mentioned above, in the embodiments of this application, the substrate layer 11 is made of high-performance fiber fabrics such as aramid fiber cloth, polyester fiber cloth and ultra-high molecular weight polyethylene fiber cloth, which has high working strength and light weight, and helps to improve the load capacity and flight technology efficiency of the airship 100.
[0070] In addition, the main function of the first intermediate layer 12 is to prevent the leakage of gases lighter than air, such as helium, thereby maintaining the lift of the airship 100. The gas barrier performance of the first intermediate layer 12 directly determines the dwell time and operating cost of the airship 100. High-barrier polymer films, such as ethylene-vinyl alcohol copolymer, polyvinyl alcohol, and polyester films, are commonly used barrier materials. After the substrate layer 11 achieves the gas barrier function, it can further improve the gas barrier performance of the capsule 10, thereby reducing the gas leakage rate of the capsule 10 and achieving low gas permeability.
[0071] Optionally, the second intermediate layer 13 can be made of the same material as the first intermediate layer 12, or it can be made of a different material. In addition to its gas barrier function, the second intermediate layer 13 also needs to have corrosion resistance to supplement the function of the protective layer 14. Specifically, the second intermediate layer 13 can be made of materials such as polyester fiber or polypropylene.
[0072] Optionally, a protective layer 14 is disposed on the outer layer of the capsule 10 to protect against ultraviolet radiation. This protective layer 14 can be a polyvinyl fluoride film or a thermoplastic polyurethane containing zinc oxide, capable of preventing ultraviolet radiation. The protective layer 14 is mainly responsible for protecting the inner layer from environmental factors such as ultraviolet radiation and ozone. It needs excellent weather resistance and anti-aging properties to ensure that the airship 100 can remain stable after prolonged exposure to harsh environments.
[0073] Optionally, the layers of materials are connected by an adhesive layer, which is a medium for bonding the layers of materials in the capsule 10. The adhesive layer can firmly bond the substrate layer 11, the first intermediate layer 12, the second intermediate layer 13 and the protective layer 14 into a whole. Generally, the adhesive layer used is a polyester, polyether or polyurethane adhesive.
[0074] The manufacturing process of the integrated propulsion device formed by the propulsion component 20 and the rudder 30 of the airship 100 will be briefly described below.
[0075] First, based on the type parameters of the capsule 10 and the requirements of the load member 27, select a suitable drive member 22 and propeller 23; Secondly, after connecting the drive unit 22 to the propeller 23, the rudder 30 is connected at a certain distance behind the propeller 23. The connection between the rudder 30 and the propulsion assembly 20 can be achieved through the mounting part 21. Finally, the electronic speed controller 25 and the circuit board 28 are connected to the drive unit 22 by wires. The power supply unit 24 can be integrated inside the propulsion assembly 20 or on the counterweight assembly 40.
[0076] The airship 100 of this invention integrates the propulsion component 20 and the rudder surface 31 of the rudder 30 into one unit, combined with a modular counterweight component 40, to achieve efficient and convenient propulsion control for small and medium-sized airships 100 suitable for indoor or outdoor windless or weak wind scenarios. The integrated propulsion device (the integrated propulsion device is an integrated module of the propulsion component 20 and the rudder 30) significantly reduces the difficulty and cost of replacing the capsule 10 of small and medium-sized airships 100. The overall structure is simple and highly modular, with good environmental adaptability and maintenance convenience. It is suitable for various emergency application scenarios and commercial scenarios, and has broad promotion value and application prospects.
[0077] Furthermore, the airship 100 here has the following advantages: It integrates the propulsion assembly 20 and the rudder 30's control surfaces 31 into one unit, improving overall integrity, facilitating maintenance and expansion, and making installation and disassembly convenient. Additionally, because the propulsion assembly 20 and the rudder 30's control surfaces 31 are modularly designed, the rudder 30 can be directly connected to the capsule 10 for immediate operation, and the propulsion assembly 20 and rudder 30 can be easily removed from the capsule 10 when replacing it. Moreover, the airship 100 is also reusable; the disassembled propulsion assembly 20 and rudder 30 can be directly installed on a new capsule 10 for continued use, offering convenience and efficiency. The control process of the airship 100 is more flexible. The horizontal thrust generated by the propeller 23 and the horizontal torque are jointly controlled to achieve attitude adjustment of the airship 100. It can also be remotely controlled across multiple platforms with software development. The structure is lightweight and the small integrated design eliminates redundancy, making the airship 100 efficient and lightweight, and suitable for a variety of application scenarios: The airship 100 has high integration performance, is lightweight and easy to install, and is suitable for a variety of occasions such as commercial, military and emergency.
[0078] For the structure of other parts of this application, please refer to the prior art; further details will not be provided here.
[0079] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. An integrated propulsion device applied to an airship, the airship comprising a capsule, characterized in that, The integrated propulsion device includes: A propulsion assembly connected to the capsule, the propulsion assembly including a mounting component, a drive component, and a propeller, the drive component being disposed on the mounting component and connected to the propeller to drive the propeller to rotate; and The rudder includes a control surface, the propeller faces the control surface, and the rudder is connected to the mounting component, so that the propulsion assembly and the rudder are integrated into a single structure.
2. The integrated propulsion device according to claim 1, characterized in that, The propulsion component is detachably connected to the capsule.
3. The integrated propulsion device according to claim 2, characterized in that, The propulsion component is connected to the capsule by means of adhesive bonding, hinge connection, or snap-fit connection.
4. An airship, said airship comprising a capsule, characterized in that, The airship also includes: The integrated propulsion device as described in any one of claims 1 to 3; The counterweight assembly is connected to the capsule, and the counterweight assembly and the integrated propulsion device are respectively disposed on opposite sides of the capsule. The direction control of the airship can be achieved by controlling the torque generated by the interaction between the deflection of the rudder and the airflow of the propeller to achieve pitch and yaw motion.
5. The airship according to claim 4, characterized in that, The integrated propulsion device is located at the rear end of the capsule, and the counterweight assembly is located at the front end of the capsule.
6. The airship according to claim 4, characterized in that, The propulsion assembly also includes: The load-bearing component is disposed on the mounting component or on the counterweight assembly.
7. The airship according to claim 4, characterized in that, The propulsion assembly also includes: The power supply unit and the electronic speed controller are provided. The electronic speed controller is mounted on the mounting component. The power supply unit is electrically connected to the electronic speed controller, and the electronic speed controller is electrically connected to the drive unit.
8. The airship according to claim 7, characterized in that, The power supply component is disposed on the mounting component or on the counterweight assembly.
9. The airship according to any one of claims 4 to 8, characterized in that, The number of integrated propulsion devices is at least two, and the at least two integrated propulsion devices are arranged at circumferential intervals along the capsule, with each integrated propulsion device connected to the capsule.
10. The airship according to claim 9, characterized in that, At least two of the integrated propulsion devices are evenly spaced along the circumference of the capsule.