Airship capsule surface resistance reduction configuration design method and system, scaling prototype and equipment

Abstract

The invention provides an airship capsule surface resistance reduction configuration design method and system, a scaling prototype and equipment, and relates to the technical field of aerostats, the method comprises the following steps: determining a preset microstructure shape of a capsule surface of an airship to be designed, the preset microstructure shape is a periodic structure formed by arranging a plurality of continuous semi-arc bulges at equal intervals; based on preset dimensionless microstructure parameters, groove spacing and groove height corresponding to the preset microstructure shape are obtained; and according to the groove spacing, the groove height and the preset microstructure shape, constructing a design parameter combination of the surface microstructure drag reduction configuration of the airship to be designed. According to the invention, resistance reduction of the stratospheric airship is effectively realized.

Description

Technical Field

[0001] This invention relates to the field of airship technology, and in particular to a method, system, scaled-down prototype and equipment for designing drag-reducing configurations on the surface of an airship hull. Background Technology

[0002] As a core flight platform in near space (20-50km altitude), stratospheric airships have become specialized equipment for fields such as Earth observation, navigation enhancement, and emergency communication due to their regional loitering capabilities, ultra-long endurance (up to several months), high flight altitude (covering ground areas above 200km), and strong information transmission efficiency.

[0003] Airships are primarily powered by solar cells; however, the excessive aerodynamic drag of the airship envelope results in a significant portion of energy being consumed in wind resistance, making it difficult for airships to maintain prolonged regional hovering or high-speed wind-resistant flight. Existing technologies for reducing drag in aerodynamics mainly employ methods such as shape optimization and flow control to lower aerodynamic drag. However, these methods still fall short in addressing the problems of high energy consumption and limited flight performance caused by excessive aerodynamic drag in stratospheric airships.

[0004] Therefore, there is an urgent need for a design method, system, scaled-down prototype, and equipment for reducing drag on the surface of an airship to solve the above problems. Summary of the Invention

[0005] To address the problems existing in the prior art, this invention provides a method, system, scaled-down prototype, and equipment for designing drag-reducing configurations on the surface of an airship capsule.

[0006] This invention provides a method for designing a drag-reducing configuration for the surface of an airship's airfoil, comprising: The preset microstructure shape of the surface of the airship to be designed is determined, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular arc protrusions. Based on preset dimensionless microstructure parameters, the groove spacing and groove height corresponding to the preset microstructure shape are obtained. The preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. The groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape. Based on the groove spacing, the groove height, and the preset microstructure shape, a combination of design parameters is constructed for the drag reduction configuration of the surface microstructure of the airship to be designed.

[0007] According to the present invention, the airship to be designed has a streamlined hull shape and the tail fin of the airship to be designed adopts an X-shaped cross-layout of the wing surfaces; the airship to be designed is made of one or more of nylon fiber, aramid fiber and polyaramid fiber.

[0008] According to the present invention, a method for designing a drag-reducing configuration for the surface of an airship capsule is provided, wherein the preset dimensionless microstructure parameters include dimensionless groove spacing and dimensionless groove height, wherein the dimensionless groove spacing is less than or equal to 30, and the dimensionless groove height is less than or equal to 15.

[0009] According to the present invention, a method for designing a drag-reducing configuration for an airship capsule surface includes obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, comprising: Based on the distance between the current position and the preset position of the surface of the airship to be designed, the local Reynolds number corresponding to the current position of the surface of the airship to be designed is determined. Based on the preset operating conditions of the airship to be designed, the kinematic viscosity and free-flow velocity of the airship to be designed are obtained; The groove spacing is calculated based on the dimensionless groove spacing, the local Reynolds number, the kinematic viscosity, and the free-flow velocity. The groove height is calculated based on the dimensionless groove height, the local Reynolds number, the kinematic viscosity, and the free-flow velocity.

[0010] According to the drag reduction configuration design method for the surface of an airship capsule provided by the present invention, the groove spacing and the groove height are calculated using a dimensionless microstructure size formula, which is specifically as follows: ; ; in, This indicates the dimensionless groove height. This indicates the dimensionless groove spacing. Indicates the height of the trench. Indicates the trench spacing, This indicates the free flow velocity. This indicates the kinematic viscosity; The distance between the current position and the preset position of the surface of the airship to be designed is... The local Reynolds number at that time.

[0011] According to the drag reduction configuration design method for an airship capsule surface provided by the present invention, after obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, the method further includes: Based on the numerical simulation results of the aerodynamic characteristics of the airship to be designed, the groove spacing and the groove height are optimized and adjusted respectively to obtain the optimized groove spacing and the optimized groove height.

[0012] According to the present invention, a method for designing drag-reducing configurations of an airship's capsule surface, after constructing a combination of surface microstructure drag-reducing configuration design parameters corresponding to the capsule surface of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape, the method further includes: Based on the design parameter combination of the surface microstructure drag reduction configuration, the surface microstructure drag reduction configuration is deployed at different positions on the surface of the airship to be designed, resulting in airships with multiple deployment methods. Aerodynamic simulation analysis was performed on the airships to be designed for various deployment methods. Based on the aerodynamic simulation analysis results, a first deployment area and a second deployment area were determined in the airships to be designed. The first deployment area was used to deploy the capsule material without the surface microstructure drag reduction configuration, and the second deployment area was used to deploy the capsule material with the surface microstructure drag reduction configuration. The first deployment area extended from the bow area of ​​the airship to the tail fin, and the second deployment area extended from the tail fin to the bow area. The second deployment area was smaller than the first deployment area.

[0013] The present invention also provides a drag reduction configuration design system for the surface of an airship capsule, comprising: The first processing module is used to determine the preset microstructure shape of the surface of the airship to be designed, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular protrusions. The second processing module is used to obtain the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters. The preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. The groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape. The design parameter generation module is used to construct a combination of design parameters for the drag reduction configuration of the surface microstructure of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape.

[0014] The present invention also provides a scaled-down prototype, wherein the surface of the capsule of the scaled-down prototype is provided with a surface microstructure drag reduction configuration, which is constructed based on the above-mentioned airship capsule surface drag reduction configuration design method.

[0015] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the airship hull surface drag reduction configuration design method as described above.

[0016] The present invention provides a method, system, scaled-down prototype, and equipment for designing drag-reducing configurations on the surface of an airship capsule. By determining the periodic, pre-set microstructure shape of the airship capsule surface, which is composed of multiple continuous, equally spaced semi-circular protrusions, and then obtaining the corresponding groove spacing and height based on the pre-set dimensionless microstructure parameters, the design parameter set for the drag-reducing configuration of the airship surface microstructure is constructed by combining the groove spacing, height, and pre-set microstructure shape, thereby effectively achieving drag reduction for stratospheric airships. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 A schematic flowchart illustrating the drag reduction configuration design method for the airship body surface provided by the present invention; Figure 2 A schematic diagram of the semi-circular arc-shaped microstructure provided by the present invention; Figure 3 A schematic diagram of the layout of the surface microstructure drag reduction configuration provided by the present invention; Figure 4 This is a schematic diagram of the drag reduction configuration design system for the airship body surface provided by the present invention; Figure 5 This is a schematic diagram of the scaled-down prototype provided by the present invention; Figure 6 This is a schematic diagram of the structure of the electronic device provided by the present invention. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0020] Stratospheric airships are ideal flight platforms in the near-space zone, possessing advantages such as regional loitering capability, long loiter time, high flight altitude, wide coverage area, and strong information acquisition and transmission capabilities. When equipped with payloads for Earth observation, navigation, and communication, they can realize the unique application effectiveness of near-space platforms.

[0021] Stratospheric airships are primarily powered by solar cells, but due to the excessive aerodynamic drag of the airship's envelope, most of the energy is consumed in wind resistance, making it difficult for the airship to maintain long-term regional hovering or high-speed wind-resistant flight.

[0022] Currently, most methods for reducing drag on the aerodynamic characteristics of airships are based on methods such as shape optimization and flow control. However, these methods are still insufficient, making it difficult for airships to maintain long-term regional hovering or high-speed wind-resistant flight. Furthermore, there are few existing technologies for achieving drag reduction through the surface of the airship material.

[0023] To address the problems existing in the prior art, this invention proposes a microstructure drag-reducing configuration design method for the surface of the capsule material of a stratospheric airship. By combining the characteristics of flexible capsule materials, a microstructure with appropriate roughness and arrangement is designed on the surface of the capsule material, and drag-reducing materials are arranged at appropriate positions on the airship. Based on the designed airship capsule material layout, a ground-based scaled-down prototype is developed to verify the post-processing performance of the corresponding materials, thereby improving the aerodynamic performance of the airship.

[0024] Figure 1 This is a flowchart illustrating the drag reduction configuration design method for the airship body surface provided by the present invention, as shown below. Figure 1 As shown, the present invention provides a method for designing a drag-reducing configuration for the surface of an airship capsule, comprising: Step 101: Determine the preset microstructure shape of the surface of the airship to be designed, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular arc protrusions.

[0025] In this invention, the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular protrusions. Figure 2 The schematic diagram of the semi-circular arc-shaped microstructure provided by the present invention can be referred to. Figure 2As shown, on the surface of the airship's capsule, semi-circular protrusions will appear repeatedly according to a certain pattern, and the spacing between these protrusions is equal, thus presenting a series of semi-circular protrusions arranged in sequence, forming a regular periodic structure.

[0026] In this invention, the pre-defined microstructure shape is determined based on the interaction between the microstructure and the fluid. This requires consideration of the flexible characteristics of the stratospheric airship's capsule material, as well as the high-frequency rubbing and friction encountered during the material's processing and use. The semi-circular protrusions can influence the fluid's flow state, thereby reducing drag. By employing this periodic structure, the interaction between the fluid and the microstructure can be better controlled and predicted, providing a foundation for subsequent drag-reduction design.

[0027] Step 102: Based on preset dimensionless microstructure parameters, obtain the groove spacing and groove height corresponding to the preset microstructure shape. The preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. The groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape.

[0028] In this invention, the preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The use of dimensionless parameters eliminates the influence of dimensions on the parameters, allowing for comparison and analysis of microstructure designs under different sizes and conditions. In this invention, the optimal combination of dimensionless parameters that achieves the best drag reduction effect under specific fluid flow conditions can be determined through experiments or theoretical analysis.

[0029] In this invention, the groove spacing s represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. Different groove spacings may lead to different fluid flow states, thereby affecting the drag reduction effect.

[0030] The groove height h refers to the vertical distance between the top and bottom of the semi-circular arc-shaped protrusion in the preset microstructure shape. The groove height also affects the interaction between the fluid and the microstructure, such as the flow separation and reattachment of the fluid around the protrusion.

[0031] By obtaining these two key parameters, the geometric characteristics of the preset microstructure shape can be described more accurately, providing specific data support for the design parameter combination of the subsequent drag-reducing configuration.

[0032] Step 103: Based on the groove spacing, the groove height, and the preset microstructure shape, construct the design parameter combination for the drag reduction configuration of the surface microstructure of the airship to be designed.

[0033] In this invention, the preset microstructure shape, groove spacing, and groove height determined in the above embodiments are combined to form a complete set of design parameters. This set of parameters comprehensively describes the geometric characteristics and related parameters of the drag-reducing configuration of the microstructure on the airship body surface. For example, it explicitly specifies that the microstructure is a periodic structure of semi-circular protrusions, and provides the horizontal distance between adjacent protrusions (groove spacing) and the height of the protrusions (groove height), providing clear guidance for subsequent manufacturing and performance evaluation of the airship body surface microstructure. Using this set of parameters, microstructures that meet design requirements can be accurately manufactured, and their drag-reduction performance can be tested and optimized through experimental or simulation methods.

[0034] The drag reduction configuration design method for the airship capsule surface provided by this invention determines the periodic preset microstructure shape of the airship capsule surface, which is composed of multiple continuous and equally spaced semi-circular arc protrusions. Then, based on the preset dimensionless microstructure parameters, the corresponding groove spacing and height are obtained. Finally, by combining the groove spacing, height and preset microstructure shape, a set of design parameters for the drag reduction configuration of the airship surface microstructure is constructed, thereby effectively achieving drag reduction of the stratospheric airship.

[0035] Based on the above embodiments, the hull shape of the airship to be designed is streamlined, and the tail fin of the airship to be designed adopts an X-shaped cross layout of the wing surfaces; the shell material of the airship to be designed is one or more of nylon fiber, aramid fiber and polyaramid fiber.

[0036] In this invention, the airship to be designed has a streamlined shape, with a rounded front that gradually narrows towards the rear, allowing air to flow more smoothly across the hull surface. This streamlined design significantly reduces air resistance during flight. When an airship flies in the stratosphere, air resistance is a crucial factor affecting its flight efficiency and energy consumption. The streamlined hull reduces air collisions and friction with the hull surface, allowing the airship to traverse the air more easily, thereby increasing flight speed, extending endurance, and reducing energy consumption.

[0037] The tail fins of the airship are arranged in an X-shape, with the four tail fins positioned at the four vertices of a square, facing each other in an X-shape. This arrangement creates a symmetrical and stable structure at the tail of the airship, providing better stability and maneuverability. During flight, the tail fins effectively control the airship's attitude, including pitch, yaw, and roll. For example, when the airship is affected by crosswinds, the X-shaped tail fins can coordinate the angle changes of the various fins to maintain a stable flight attitude, preventing excessive tilting or turning. Simultaneously, this arrangement also enhances the airship's maneuverability, allowing for more flexible adjustments to its flight direction.

[0038] In this invention, selecting one or more fiber materials allows for the full utilization of their advantages. For example, the abrasion resistance and elasticity of nylon fibers, the high strength of aramid fibers, and the fatigue resistance of polyarylate fibers enable the capsule material to meet the requirements of airships under complex operating conditions, ensuring the safety and reliability of the airship. Furthermore, depending on specific performance requirements and cost factors, a single material or a combination of multiple materials can be selected for use.

[0039] Based on the above embodiments, the preset dimensionless microstructure parameters include dimensionless groove spacing and dimensionless groove height, wherein the dimensionless groove spacing is less than or equal to 30, and the dimensionless groove height is less than or equal to 15.

[0040] In this invention, the preset dimensionless microstructure parameters are a set of dimensionless values ​​set to describe the microstructural characteristics of the airship's surface. Dimensionless means that these parameters do not depend on specific physical units (such as length units like meters or millimeters), making the study and comparison of microstructures universal across different scales or conditions. The preset dimensionless microstructure parameters mainly include two key parameters: dimensionless groove spacing and dimensionless groove height, which are used to accurately characterize the geometric features of the microstructure surface.

[0041] In this invention, when the trench height and trench spacing meet certain conditions, the microstructure surface exhibits drag-reducing characteristics. Specifically, when the dimensionless trench spacing s... + When the value is less than or equal to 30, the microstructured surface can exhibit drag reduction. Similarly, when the dimensionless trench height h... + When the value is less than or equal to 15, the microstructure surface can play a drag-reducing role.

[0042] This invention limits the dimensionless groove spacing to less than or equal to 30 and the dimensionless groove height to less than or equal to 15. This is to allow for informed selection of parameters in the design of the microstructure on the airship's surface, ensuring that the designed microstructure surface has good drag-reduction characteristics, thereby improving the airship's flight efficiency and reducing energy consumption. Preferably, in this invention, when the dimensionless groove spacing and dimensionless groove height meet the above conditions and are the same, for example, s + =h + When the value is 15, the groove height and groove spacing are calculated based on the preset dimensionless microstructure parameters, which can achieve the optimal drag reduction rate of the airship body surface.

[0043] Based on the above embodiments, obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters includes: Based on the distance between the current position and the preset position of the surface of the airship to be designed, the local Reynolds number corresponding to the current position of the surface of the airship to be designed is determined. Based on the preset operating conditions of the airship to be designed, the kinematic viscosity and free-flow velocity of the airship to be designed are obtained; The groove spacing is calculated based on the dimensionless groove spacing, the local Reynolds number, the kinematic viscosity, and the free-flow velocity. The groove height is calculated based on the dimensionless groove height, the local Reynolds number, the kinematic viscosity, and the free-flow velocity.

[0044] In this invention, the Reynolds number is a dimensionless number used to characterize the state of fluid flow, and it is related to factors such as the fluid's flow characteristics and geometry. In this invention, the fluid flow varies at different locations on the surface of the airship capsule, and the local Reynolds number reflects the flow characteristics at a specific location. By determining the distance between the current location on the capsule surface and a preset location (usually a reference point, such as the airship's bow), and combining this distance with the laws of fluid flow and relevant formulas, the local Reynolds number corresponding to that current location can be calculated. For example, in fluid mechanics, the calculation of the Reynolds number is related to the fluid's velocity, characteristic length, and kinematic viscosity; distance information can help determine relevant parameters such as the characteristic length, thereby calculating the local Reynolds number.

[0045] In this invention, the local Reynolds number varies at different locations, which affects the drag reduction effect of the microstructure at those locations. Accurately determining the local Reynolds number is crucial for subsequently designing the groove spacing and height rationally based on different flow states, enabling the microstructure to better adapt to fluid flow at different locations and achieve more effective drag reduction.

[0046] In this invention, the preset operating conditions include various environmental parameters and operational status information for airship flight. Kinematic viscosity is an intrinsic property of the fluid, related to factors such as fluid type and temperature. Based on the given fluid (usually air) temperature and other conditions in the preset operating conditions, the kinematic viscosity can be obtained by consulting relevant fluid property parameter tables or calculating using specific formulas. For example, the kinematic viscosity of air changes with temperature; given the temperature, the corresponding kinematic viscosity value can be determined. Kinematic viscosity reflects the viscous characteristics of a fluid and has a significant impact on fluid flow and drag reduction on microstructure surfaces.

[0047] The preset operating conditions also specify the airship's speed information under specific flight states. Free-flow velocity refers to the velocity of the fluid around the airship that is not disturbed by the airship itself, and this velocity value can be directly obtained from the flight parameters of the preset operating conditions. Free-flow velocity is an important indicator describing the speed of fluid flow, and it directly affects the interaction between the fluid and microstructures.

[0048] In this invention, based on preset dimensionless microstructure parameters, local Reynolds number, kinematic viscosity, and free-flow velocity, the trench spacing and trench height are calculated using a dimensionless microstructure size formula. Building upon the above embodiment, the trench spacing and trench height are calculated using a dimensionless microstructure size formula, which is specifically: ; ; in, This indicates the dimensionless groove height. This indicates the dimensionless groove spacing. Indicates the height of the trench. Indicates the trench spacing, This indicates the free flow velocity. This indicates the kinematic viscosity; The distance between the current position and the preset position of the surface of the airship to be designed is... The local Reynolds number at that time.

[0049] In this invention, the dimensionless groove spacing is known. s + Local Reynolds number Re x kinematic viscosity ν and free flow velocity U When the value is 0, the actual trench spacing can be calculated by modifying the formula. s For example, by transforming and deriving the formula, we can... s Represented as about s + Re x , ν and U The function is 0, and then the values ​​of these known parameters are substituted for calculation. The groove spacing or groove height calculated in this way is determined by combining multiple factors such as the flow characteristics (local Reynolds number), fluid properties (kinematic viscosity), and flight state (free flow velocity) at a specific location on the airship surface. This allows the microstructure to better play its drag-reducing role at that location and adapt to actual fluid flow conditions.

[0050] Based on the specific conditions and fluid characteristics of the airship, this invention accurately calculates the groove spacing and height suitable for different locations, providing accurate data support for the design of microstructures on the surface of the airship body.

[0051] Based on the above embodiments, after obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, the method further includes: Based on the numerical simulation results of the aerodynamic characteristics of the airship to be designed, the groove spacing and the groove height are optimized and adjusted respectively to obtain the optimized groove spacing and the optimized groove height.

[0052] In this invention, aerodynamic characteristic numerical simulation is used to simulate the aerodynamic behavior of an airship under specific conditions using computer software. For the airship to be designed, numerical simulation can be used to simulate the flow of fluid (such as air) around the microstructures on the surface of the airship body under different groove spacing and groove height, including key parameters such as velocity distribution, pressure distribution, and drag coefficient. These simulation results (i.e., aerodynamic characteristic numerical simulation results) can intuitively reflect the influence of different microstructure parameters on the aerodynamic performance of the airship.

[0053] Specifically, in the numerical simulation of aerodynamic characteristics, different groove spacing values ​​are set for simulation. By comparing the aerodynamic parameters of the airship, such as the drag coefficient and lift coefficient, under different groove spacings, the influence of groove spacing on the airship's aerodynamic performance is analyzed. For example, it is found that as the groove spacing increases, the drag coefficient may first decrease and then increase, and there exists an optimal groove spacing value that minimizes drag. Based on the changing trends of these parameters in the simulation results, the groove spacing is repeatedly adjusted and optimized to find the groove spacing value that achieves the optimal aerodynamic performance of the airship.

[0054] During the optimization and adjustment process, other factors also need to be considered, such as the manufacturing difficulty and cost of the microstructure. If a groove spacing that improves aerodynamic performance is too complex or too costly to manufacture, it may need to be adjusted appropriately to strike a balance between aerodynamic performance, manufacturability, and cost. The final optimized groove spacing is then obtained.

[0055] Similarly, in numerical simulations, the effect of varying groove height on the aerodynamic characteristics of the airship can be observed. For example, the flow separation and frictional drag on the airship surface can be analyzed at different groove heights. By comparing simulation results for different groove heights, the optimal groove height range and specific values ​​for reducing drag and improving aerodynamic performance can be identified. For instance, it might be observed that as the groove height increases within a certain range, frictional drag gradually decreases, but beyond a certain value, the drag begins to rise again, thus determining the optimal direction for adjusting the groove height.

[0056] Similar to optimizing trench spacing, optimizing trench height also requires comprehensive consideration of factors such as manufacturing and cost. After in-depth analysis and comprehensive weighing of simulation results, the final optimized trench height was determined.

[0057] After optimizing the groove spacing and height based on aerodynamic characteristic numerical simulation results, the optimized groove spacing and height are obtained. These optimized parameters enable the microstructures on the airship's surface to better reduce drag, improving the overall aerodynamic performance of the airship while considering manufacturing feasibility and cost. For example, in one embodiment, when both the dimensionless groove spacing and dimensionless groove height are 15, the groove spacing and height are calculated to be 0.3 mm based on the microstructure dimension formula. After aerodynamic characteristic numerical simulation comparison and comprehensive consideration, the optimized groove spacing and height are obtained as 0.15 mm, thus providing a more reliable parameter basis for the actual design and manufacturing of the airship.

[0058] Based on the above embodiments, after constructing the surface microstructure drag reduction configuration design parameter combination corresponding to the surface of the airship to be designed according to the groove spacing, the groove height, and the preset microstructure shape, the method further includes: Based on the design parameter combination of the surface microstructure drag reduction configuration, the surface microstructure drag reduction configuration is deployed at different positions on the surface of the airship to be designed, resulting in airships with multiple deployment methods. Aerodynamic simulation analysis was performed on the airships to be designed for various deployment methods. Based on the aerodynamic simulation analysis results, a first deployment area and a second deployment area were determined in the airships to be designed. The first deployment area was used to deploy the capsule material without the surface microstructure drag reduction configuration, and the second deployment area was used to deploy the capsule material with the surface microstructure drag reduction configuration. The first deployment area extended from the bow area of ​​the airship to the tail fin, and the second deployment area extended from the tail fin to the bow area. The second deployment area was smaller than the first deployment area.

[0059] In this invention, the design parameter combination for the drag-reducing configuration of the surface microstructure includes key information such as trench spacing, trench height, and microstructure shape (hemispherical). Based on these parameters, the specific form of the microstructure is determined, for example, a hemispherical microstructure with a height and spacing of approximately 0.15 mm.

[0060] Furthermore, the effects of deploying the surface microstructures at different locations on the surface of the airship under design are analyzed. Since there are numerous locations on the airship surface, there are many possible deployment methods. For example, a small number can be deployed near the bow, followed by a large number in the middle of the hull; or the microstructures can be evenly deployed across the entire airship surface. Each different combination of deployment location and range forms a deployment method, resulting in airships with multiple deployment options under design.

[0061] This invention uses computer software to simulate the flight state of an airship under different deployment methods, analyzing the interaction between the fluid (air) and the airship surface, including key aerodynamic parameters such as airflow state (laminar, turbulent, etc.), pressure distribution, and drag coefficient. For each airship under design with different deployment methods, corresponding boundary conditions and initial parameters are set, and numerical calculations are performed. The influence of microstructures on airflow under different deployment methods is observed, such as whether they can effectively delay airflow separation and reduce drag. By comparing the aerodynamic simulation results of different deployment methods, the drag reduction effect of microstructures at different locations is understood.

[0062] In this invention, the first deployment area extends from the bow region of the airship to the tail. According to aerodynamic simulation analysis, when the airship's level flight speed is low and the angle of attack is less than 10°, the airflow typically remains laminar in the bow and forward half of the airship. A transition begins between 35% and 60% of the bow angle, and the airflow enters an unstable region. However, in this forward half region, the drag reduction effect of the microstructure is not significant or critical. Therefore, this invention defines the area where microstructures are not required as the first deployment area. This area occupies the range from the bow to a certain position on the airship. The first deployment area is used to deploy conventional capsule materials with drag-reducing configurations without surface microstructures. This is because in this area, conventional capsule materials can meet aerodynamic performance requirements without the need for drag reduction through microstructures.

[0063] The second deployment area extends from the tail fin towards the bow region and is smaller than the first deployment area. Aerodynamic simulation analysis shows that airflow separation or lateral flow easily occurs in the mid-to-rear part of the airship hull and the tail fin area. Placing the microstructure 60% of the way from the bow can effectively reduce aerodynamic drag. Therefore, in this invention, the second deployment area is mainly concentrated in the mid-to-rear part of the airship, extending a certain distance from the tail fin towards the bow. This area is the key region where the microstructure exerts its drag-reducing effect. In this invention, the second deployment area is used to deploy capsule materials with surface microstructure drag-reducing configurations. By deploying the microstructures, the airflow state in this area can be improved, reducing airflow separation and lateral flow, thereby reducing drag and improving the aerodynamic performance of the airship.

[0064] By following the above steps, the material arrangement in different areas of the airship's body can be determined in a reasonable manner, giving full play to the drag reduction effect of the microstructure and optimizing the airship's aerodynamic performance. Figure 3 The schematic diagram of the surface microstructure drag reduction configuration provided by the present invention can be referred to. Figure 3 As shown, in one embodiment, for a streamlined airship, conventional capsule material (i.e., capsule material without surface microstructure drag-reducing configuration) is laid in the area extending from the bow region to the tail (i.e., the first 60% of the airship capsule body), while drag-reducing capsule material (i.e., capsule material with surface microstructure drag-reducing configuration) is laid in the remaining area of ​​the airship capsule body (i.e., the last 40% of the airship capsule body, extending from the tail to the bow region).

[0065] The drag reduction configuration design system for the airship capsule surface provided by the present invention is described below. The drag reduction configuration design system for the airship capsule surface described below can be referred to in correspondence with the drag reduction configuration design method for the airship capsule surface described above.

[0066] Figure 4 This is a schematic diagram of the drag reduction configuration design system for the airship body surface provided by the present invention, as shown below. Figure 4As shown, this invention provides a drag-reduction configuration design system for the surface of an airship, including a first processing module 401, a second processing module 402, and a design parameter generation module 403. The first processing module 401 determines a preset microstructure shape for the surface of the airship to be designed. The preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular arc-shaped protrusions. The second processing module 402 obtains the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters. The preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. The groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape. The design parameter generation module 403 constructs a combination of design parameters for the drag-reduction configuration of the surface microstructure of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape.

[0067] The drag reduction configuration design system for the airship capsule surface provided by this invention determines the periodic preset microstructure shape of the airship capsule surface, which is composed of multiple continuous and equally spaced semi-circular arc protrusions. Then, based on the preset dimensionless microstructure parameters, the corresponding groove spacing and height are obtained. Finally, by combining the groove spacing, height and preset microstructure shape, a set of design parameters for the drag reduction configuration of the airship surface microstructure is constructed, thereby effectively achieving drag reduction of stratospheric airships.

[0068] The system provided in this embodiment of the invention is used to execute the above-described method embodiments. For specific processes and details, please refer to the above embodiments, which will not be repeated here.

[0069] Figure 5 This is a schematic diagram of the scaled-down prototype provided by the present invention, as shown below. Figure 5 As shown, the present invention provides a scaled-down prototype 501, wherein the surface of the capsule of the scaled-down prototype 501 is provided with a surface microstructure drag reduction configuration 502, which is constructed based on the airship capsule surface drag reduction configuration design method described in the above embodiments.

[0070] In this invention, the scaled-down prototype 501 is a ground-based scaled-down prototype model of the airship's capsule material, designed based on the airship's drag-reduction configuration. This scaled-down prototype has specific structural features: the main capsule is streamlined, with a conical nose and tail, and an X-shaped tail fin that is rotationally symmetrical along its central axis. This structural design corresponds to the structural characteristics of actual airships, simulating relevant airship properties on the ground for experimental and research purposes. The invention is developed according to the airship's composition, consisting of a main capsule made of conventional materials, a drag-reduction microstructure material, and a tail fin. These sections are welded together in a circumferential direction to form a single unit, ensuring the integrity and stability of the prototype structure.

[0071] The surface microstructure drag reduction configuration 502 is placed on the surface of the capsule of the scaled-down prototype 501. The surface microstructure drag reduction configuration 502 is determined based on the airship capsule surface drag reduction configuration design method described in the above embodiments. The airship capsule surface drag reduction configuration design method encompasses several key steps and considerations. For example, the aerodynamic characteristics of the airship must be considered, including the airflow state at different locations. For instance, during level flight, the airflow maintains laminar flow in the bow and forward half, begins to transition at 35% to 60%, and separates or lateral flows occur in the mid-rear and tail sections. The design parameters of the microstructure, such as groove spacing and groove height, must also be considered, and the optimal placement position and parameter combination are determined through aerodynamic simulation analysis.

[0072] In this invention, the preparation process of the scaled-down prototype mainly consists of diaphragm cutting, main capsule assembly, tail fin processing, and main capsule-tail fin assembly, as detailed below: First, using a hyperboloid flattening method, the capsule membrane is mapped from a three-dimensional structure to a two-dimensional planar structure. The main capsule membrane is continuously laid out from beginning to end to form a spindle-shaped planar membrane. The number of membrane segments can be set appropriately according to the size of the ground prototype and the size of the cut membrane segments to ensure that the membrane size is suitable for heat sealing and to meet the fit requirements of the three-dimensional model as much as possible.

[0073] Then, using an automatic cutting machine, the two-dimensional membrane of the capsule material is cut according to the membrane segmentation. Afterwards, the first segment membrane is welded together using a continuous heat sealing machine, and then the membrane is assembled along the weld seam starting from the head. Specifically, the two materials of the main capsule are welded together axially to form segmented main capsules, and then the two capsule materials are circumferentially welded together. The beginning and end of the main capsule membrane are cut with a head and tail circle to avoid the membrane assembly concentrating at a singular point. Finally, a circular membrane is used to seal the beginning and end weld points of the main capsule. In addition to installing the head and tail reinforcing circles during the main capsule membrane welding process, auxiliary processes such as installing the inflation nozzle and excavating the bottom membrane are also required.

[0074] Furthermore, during the welding of the main capsule, the tail fin can be fabricated simultaneously. An internal partition is added to the tail fin to connect the left and right side membranes, ensuring it maintains its designed shape during inflation. The process includes cutting the side membranes and partitions, assembling the side membrane partitions, joining the connecting strips on the side membranes, and welding the upper and lower membranes. The completed tail fin is then welded to the main capsule, completing the preparation of the scaled-down prototype. Finally, the scaled-down prototype undergoes an inflation check to ensure there are no leaks and is stored properly.

[0075] In this invention, the scaled-down prototype, because it incorporates a surface microstructure drag-reducing configuration, can be used to simulate and study the performance of an actual airship after applying this drag-reducing configuration. It can observe and analyze the drag-reducing effect of the microstructure in practical applications, its influence on the capsule structure, etc., providing important experimental basis and data support for the design and optimization of actual airships.

[0076] The scaled-down prototype provided by this invention, based on the design of drag-reducing configuration and layout of the airship's capsule material surface, is divided into a main capsule conventional material part, a drag-reducing microstructure material part, and a tail fin part according to the airship's composition and layout. Furthermore, it proposes targeted processing procedures for components such as the head and tail fin, which is conducive to improving the processing accuracy and flatness of the drag-reducing capsule material. Through the scaled-down prototype, the post-processing performance of the corresponding materials can be verified, thereby improving the aerodynamic performance of the airship.

[0077] Figure 6 This is a schematic diagram of the structure of the electronic device provided by the present invention, such as... Figure 6 As shown, the electronic device may include: a processor 601, a communications interface 602, a memory 603, and a communication bus 604, wherein the processor 601, the communications interface 602, and the memory 603 communicate with each other through the communication bus 604. Processor 601 can call logic instructions in memory 603 to execute a method for designing a drag-reducing configuration for the surface of an airship. This method includes: determining a preset microstructure shape for the surface of the airship to be designed, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular arc-shaped protrusions; obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, wherein the preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid; the groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape; the groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape; and constructing a combination of design parameters for the drag-reducing configuration of the surface microstructure of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape.

[0078] Furthermore, the logical instructions in the aforementioned memory 603 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, essentially, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0079] On the other hand, the present invention also provides a computer program product, the computer program product comprising a computer program stored on a non-transitory computer-readable storage medium, the computer program comprising program instructions, wherein when the program instructions are executed by a computer, the computer is able to execute the airship body surface drag reduction configuration design method provided by the above methods, the method comprising: determining a preset microstructure shape of the airship body surface to be designed, wherein the preset microstructure shape is a periodic structure composed of a plurality of continuous and equally spaced semi-circular arc protrusions; obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, wherein the preset dimensionless microstructure parameters are determined according to the interaction between the preset microstructure shape and the fluid; the groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc protrusions in the preset microstructure shape; the groove height represents the vertical distance between the top and bottom of the semi-circular arc protrusions in the preset microstructure shape; and constructing a design parameter combination for the surface microstructure drag reduction configuration of the airship to be designed according to the groove spacing, the groove height and the preset microstructure shape.

[0080] In another aspect, the present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the airship capsule surface drag reduction configuration design method provided in the above embodiments. The method includes: determining a preset microstructure shape of the capsule surface of the airship to be designed, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular arc-shaped protrusions; obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, wherein the preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid; the groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape; the groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape; and constructing a design parameter combination for the surface microstructure drag reduction configuration of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape.

[0081] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0082] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0083] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for designing a drag-reducing configuration for the surface of an airship's airfoil, characterized in that, include: The preset microstructure shape of the surface of the airship to be designed is determined, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular arc protrusions. Based on preset dimensionless microstructure parameters, the groove spacing and groove height corresponding to the preset microstructure shape are obtained. The preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. The groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape. Based on the groove spacing, the groove height, and the preset microstructure shape, a combination of design parameters is constructed for the drag reduction configuration of the surface microstructure of the airship to be designed.

2. The airship body surface drag reduction configuration design method according to claim 1, characterized in that, The airship to be designed has a streamlined hull shape, and its tail fin adopts an X-shaped cross-layout. The airship's body material is one or more of nylon fiber, aramid fiber, and polyaramid fiber.

3. The airship body surface drag reduction configuration design method according to claim 1 or 2, characterized in that, The preset dimensionless microstructure parameters include dimensionless groove spacing and dimensionless groove height, wherein the dimensionless groove spacing is less than or equal to 30, and the dimensionless groove height is less than or equal to 15.

4. The airship hull surface drag reduction configuration design method according to claim 3, characterized in that, The step of obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters includes: Based on the distance between the current position and the preset position of the surface of the airship to be designed, the local Reynolds number corresponding to the current position of the surface of the airship to be designed is determined. Based on the preset operating conditions of the airship to be designed, the kinematic viscosity and free-flow velocity of the airship to be designed are obtained; The groove spacing is calculated based on the dimensionless groove spacing, the local Reynolds number, the kinematic viscosity, and the free-flow velocity. The groove height is calculated based on the dimensionless groove height, the local Reynolds number, the kinematic viscosity, and the free-flow velocity.

5. The airship body surface drag reduction configuration design method according to claim 4, characterized in that, The trench spacing and the trench height are calculated using a dimensionless microstructure size formula, which is as follows: ； ； in, This indicates the dimensionless groove height. This indicates the dimensionless groove spacing. Indicates the height of the trench. Indicates the trench spacing, This indicates the free flow velocity. This indicates the kinematic viscosity; The distance between the current position and the preset position of the surface of the airship to be designed is... The local Reynolds number at that time.

6. The airship body surface drag reduction configuration design method according to claim 3, characterized in that, After obtaining the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters, the method further includes: Based on the numerical simulation results of the aerodynamic characteristics of the airship to be designed, the groove spacing and the groove height are optimized and adjusted respectively to obtain the optimized groove spacing and the optimized groove height.

7. The airship body surface drag reduction configuration design method according to claim 2, characterized in that, After constructing the combination of surface microstructure drag-reduction configuration design parameters corresponding to the surface of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape, the method further includes: Based on the design parameter combination of the surface microstructure drag reduction configuration, the surface microstructure drag reduction configuration is deployed at different positions on the surface of the airship to be designed, resulting in airships with multiple deployment methods. Aerodynamic simulation analysis was performed on the airships to be designed for various deployment methods. Based on the aerodynamic simulation analysis results, a first deployment area and a second deployment area were determined in the airships to be designed. The first deployment area was used to deploy the capsule material without the surface microstructure drag reduction configuration, and the second deployment area was used to deploy the capsule material with the surface microstructure drag reduction configuration. The first deployment area extended from the bow area of ​​the airship to the tail fin, and the second deployment area extended from the tail fin to the bow area. The second deployment area was smaller than the first deployment area.

8. A drag-reduction configuration design system for the surface of an airship hull, characterized in that, include: The first processing module is used to determine the preset microstructure shape of the surface of the airship to be designed, wherein the preset microstructure shape is a periodic structure composed of multiple continuous and equally spaced semi-circular protrusions. The second processing module is used to obtain the groove spacing and groove height corresponding to the preset microstructure shape based on preset dimensionless microstructure parameters. The preset dimensionless microstructure parameters are determined based on the interaction between the preset microstructure shape and the fluid. The groove spacing represents the horizontal distance between the centers of two adjacent semi-circular arc-shaped protrusions in the preset microstructure shape. The groove height represents the vertical distance between the top and bottom of the semi-circular arc-shaped protrusions in the preset microstructure shape. The design parameter generation module is used to construct a combination of design parameters for the drag reduction configuration of the surface microstructure of the airship to be designed based on the groove spacing, the groove height, and the preset microstructure shape.

9. A scaled-down prototype, characterized in that, The scaled-down prototype has a surface microstructure drag-reducing configuration on its capsule surface, which is constructed based on the airship capsule surface drag-reducing configuration design method according to any one of claims 1 to 7.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and running on the processor, characterized in that, When the processor executes the computer program, it implements the airship hull surface drag reduction configuration design method as described in any one of claims 1 to 7.

Images