High-altitude wind power generation platform

Abstract

The application discloses a high-altitude wind power generation platform, which comprises a main air bag, two compensation components, wind power blades and aerodynamic components. The main air bag is arranged along the front-back direction and has a rotary outer circumferential surface. The diameter of the main air bag gradually increases from the front to the rear and then gradually decreases. The two compensation components are symmetrically arranged on the two sides of the main air bag and are connected with the main air bag. The compensation component has an annular structure and comprises an air inlet channel. The compensation component is hollow to inject gas. The wind power blades are arranged in the air inlet channel and each air inlet channel comprises at least one group of wind power blades. The aerodynamic components are symmetrically arranged on the outer circumferential surface of the main air bag and are located on the side of the compensation component and outside the disturbed airflow area generated by the wind power blades. The mooring point is arranged on the front side of the main air bag and is located between the compensation components in the extension direction of the main air bag. The high-altitude wind power generation platform can guarantee the stable operation of the platform and simultaneously improve the light weight and the power generation efficiency.

Description

Technical Field

[0001] This invention relates to the field of wind power generation technology. More specifically, it relates to a high-altitude wind power generation platform. Background Technology

[0002] High-altitude wind energy, with its high energy density and low turbulence, has become a high-quality wind resource with significant development potential. Currently, achieving efficient and reliable capture of high-altitude wind energy has become a crucial research topic of continuous concern in the wind energy industry. This is not only related to energy utilization efficiency but also closely linked to the continuous and stable operation of platforms in complex high-altitude airflow environments.

[0003] From an economic perspective, helium costs constitute a significant proportion of the overall cost of high-altitude wind power platforms, making it one of the main factors affecting their economic viability. Therefore, reducing reliance on helium and achieving lightweight design are key design directions for improving the economics of high-altitude wind power platforms. However, during the lightweight design process, ensuring the platform's force balance and stability in the airflow requires precise optimization of its aerodynamic performance. Summary of the Invention

[0004] In view of the above problems, one object of the present invention is to provide a high-altitude wind power generation platform.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A high-altitude wind power generation platform, comprising:

[0007] The main airbag extends along the front-to-back direction, and its outer circumferential surface is a rotating surface. The diameter of the main airbag gradually increases and then gradually decreases from front to back.

[0008] Two compensation components are symmetrically arranged on both sides of the main airbag and connected to the main airbag;

[0009] The compensation component is a ring structure, including an air inlet duct, and the interior of the compensation component is hollow to allow for gas injection;

[0010] Wind turbine blades are installed inside air intake ducts, and each air intake duct contains at least one set of wind turbine blades.

[0011] Aerodynamic components: Multiple aerodynamic components are centrally symmetrically distributed on the outer periphery of the main airbag, located beside the compensation components, outside the area of ​​turbulent airflow generated by the wind turbine blades;

[0012] A tether point is located between the front sides of the main airbag and is disposed at a distance from the compensation component in the direction of extension of the main airbag.

[0013] Alternatively, the main airbag can be divided into a first airbag and a second airbag along the front-to-back direction, with the junction of the first airbag and the second airbag being the point where the main airbag has the largest diameter.

[0014] The mooring point is located in the first capsule, and the compensation component, wind turbine blade, and dynamic component are all located in the second capsule.

[0015] The aerodynamic component extends along the front-to-back direction, and its outer peripheral surface is a rotating surface with its diameter gradually increasing and then decreasing from front to back.

[0016] Alternatively, the buoyancy center, center of gravity, and center of lift of the high-altitude wind power generation platform are all located in the region near the central axis of the main airbag.

[0017] The center of gravity and the center of lift are located behind the center of buoyancy, and the mooring point is located in front of the center of buoyancy.

[0018] Alternatively, at least one of the center of gravity and the center of lift is located within the range where the compensation component and the main airbag coincide in the axial direction.

[0019] Alternatively, the inner diameter of the compensation component can be gradually reduced from front to back and then gradually increased.

[0020] The air intake duct is divided into a tapering section, a throat section, and a widening section from the front edge to the rear edge of the compensation component according to the inner diameter of the compensation component. The inner diameter of the front edge of the compensation component is smaller than the inner diameter of the rear edge of the compensation component.

[0021] The throat is located at the point where the inner diameter of the compensation component is at its minimum, and the wind turbine blade is located at the throat.

[0022] In addition, an alternative option is that the high-altitude wind power generation platform also includes a blade cascade located at the rear edge of the compensation component and fitted on the radial outside of the compensation component, with the blade cascade partially overlapping the compensation component in the radial direction;

[0023] The inner diameter of the leading edge of the blade cascade is larger than the outer diameter of the trailing edge of the compensation assembly.

[0024] Alternatively, the blade cascade may include a first cascade ring and a second cascade ring, both of which have an airfoil profile.

[0025] The inner diameter of the first gate ring gradually decreases and then gradually increases from front to back, and the inner diameter of the front edge of the first gate ring is smaller than the inner diameter of the rear edge of the first gate ring.

[0026] The inner diameter of the second gate ring gradually decreases and then gradually increases from front to back, and the inner diameter of the front edge of the second gate ring is smaller than the inner diameter of the rear edge of the second gate ring.

[0027] The first grid ring is located at the rear edge of the compensation component and is fitted on the radial outer side of the compensation component. The smallest inner diameter of the first grid ring is located at the rear edge of the compensation component. There is a gap between the inner surface of the front edge of the first grid ring and the outer surface of the rear edge of the compensation component.

[0028] The second grid ring is located at the rear edge of the first grid ring and is fitted radially outside the first grid ring. The smallest inner diameter of the second grid ring is located at the rear edge of the first grid ring. There is a gap between the inner surface of the front edge of the second grid ring and the outer surface of the rear edge of the first grid ring.

[0029] Alternatively, the chord length of the first gate ring is greater than or equal to the chord length of the second gate ring;

[0030] The distance between the minimum inner diameter of the first gate ring and the leading edge of the first gate ring is less than the distance between the minimum inner diameter of the first gate ring and the trailing edge of the first gate ring.

[0031] The distance between the minimum inner diameter of the second gate ring and the leading edge of the second gate ring is less than the distance between the minimum inner diameter of the second gate ring and the trailing edge of the second gate ring.

[0032] Alternatively, the central axes of both compensation components are parallel to the central axis of the main airbag, and the central axis of the main airbag and the central axes of the two compensation components are in the same plane.

[0033] Alternatively, the central axis of the aerodynamic component is parallel to the central axis of the main airbag, and is either tangential to or separate from the main airbag, and is fixed to the outer circumference of the main airbag by a bracket and ropes.

[0034] In the longitudinal direction, the leading edge of the aerodynamic component is positioned close to the leading edge of the compensation component, and the trailing edge of the compensation component is located behind the point where the diameter of the aerodynamic component is at its maximum.

[0035] Alternatively, the high-altitude wind power generation platform may include four aerodynamic components, which are distributed in an X-shaped structure on the outer periphery of the main airbag.

[0036] Two aerodynamic components are located above the two compensation components, and the other two aerodynamic components are located below the two compensation components.

[0037] The trailing edge of the aerodynamic components protrudes beyond the trailing edge of the main airbag, and an X-shaped tail sail is formed between the trailing edges of the four aerodynamic components.

[0038] Alternatively, the surface at the connection between the aerodynamic component and the main airbag can be covered with a smoothing skin to achieve a natural transition between the main airbag and the aerodynamic component.

[0039] Alternatively, a tail fin may be provided on the surface of the aerodynamic component away from the main airbag, and the tail fin may be arranged perpendicular to the plane formed by the central axis of the compensation component and the central axis of the main airbag.

[0040] Alternatively, the inner diameter of the throat is 0.5-1 times the maximum diameter of the main airbag;

[0041] The inner diameter of the rear edge of the compensation component is 1.05-1.6 times the inner diameter of the throat.

[0042] The beneficial effects of this invention are as follows:

[0043] To address the technical problems existing in the prior art, this invention provides a high-altitude wind power generation platform. Through the coordinated design of various components such as the main airbag, compensation components, and aerodynamic components, the platform ensures stable operation from multiple dimensions, including mechanical balance, airflow stability, and structural reliability, while also achieving lightweight design and improved power generation efficiency. The main airbag and four aerodynamic components adopt the rotating shape of a traditional airship, resulting in a higher volume-to-surface ratio for the same capacity. This significantly reduces the amount of skin used and helium consumption, achieving overall lightweight design to reduce structural load and smoother airflow, reducing local aerodynamic fluctuations and laying the foundation for stable operation. The compensation components on both sides form a graded aerodynamic layout with the aerodynamic components located near the platform's center of buoyancy and the maximum diameter of the main airbag, primarily providing stable aerodynamic lift to supplement the buoyancy of the center of buoyancy. The four aerodynamic components, relying on their relatively long lever arms, provide the main restoring torque, effectively balancing the impact of high-altitude airflow and the counter-torque of the wind turbine blades, maintaining attitude stability. With no obstructions in front of the compensation components and wind turbine blades, the incoming airflow is clean and turbulent-free, improving aerodynamic efficiency and avoiding lift fluctuations caused by turbulence. The aerodynamic components have large cross-sections and excellent rigidity, making them resistant to deformation under aerodynamic forces and enabling them to continuously and stably output restoring torque, solving the failure problem caused by the easy bending of traditional tail fins. The X-shaped tail sail at the very end further enhances the effect, not only supplementing the restoring torque in the yaw and pitch directions, but also increasing the airflow velocity on the sides of the main capsule by improving the tail flow field, helping the wind inlet duct to obtain higher wind speeds, ultimately achieving the dual benefits of stable operation and increased power generation. Attached Figure Description

[0044] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0045] Figure 1 This is an isometric view of the high-altitude wind power generation platform provided in an embodiment of the present invention.

[0046] Figure 2 This is a side view of the high-altitude wind power generation platform provided in an embodiment of the present invention.

[0047] Figure 3This is a front view of the high-altitude wind power generation platform provided in an embodiment of the present invention.

[0048] Figure 4 The diagram shows the tail section of the high-altitude wind power generation platform provided in an embodiment of the present invention.

[0049] Figure 5 The diagram shows the rotational profile of the compensation component and blade cascade provided in an embodiment of the present invention.

[0050] Figure 6 The simulation velocity cloud map of the compensation component and the blade cascade provided in the embodiment of the present invention is shown.

[0051] Figure 7 This is a top-view cross-sectional view of the high-altitude wind power generation platform provided in an embodiment of the present invention.

[0052] Figure 8 This is a sectional view of the high-altitude wind power generation platform provided in an embodiment of the present invention from a side view perspective.

[0053] Figure 9 The image shows a front view of a high-altitude wind power generation platform with four compensation components provided in an embodiment of the present invention. Detailed Implementation

[0054] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0055] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or a connection through an intermediate medium or gap; they can refer to the internal communication of two elements or the interaction between two elements. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0056] In this invention, unless otherwise expressly specified and limited, the first feature "above" or "below" the second feature may include direct contact between the first and second features, or contact between the first and second features not in direct contact but through another feature between them.

[0057] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0058] To achieve synergistic optimization of lightweighting and operational performance, the platform's structural and aerodynamic design needs to be improved from multiple dimensions. On the one hand, the high-altitude wind power platform needs to have good aerodynamic lift. This not only reduces the demand for helium buoyancy by supplementing lift and lowers helium usage, but also balances the force distribution of the platform in the high-altitude airflow, avoiding attitude tilting or fluctuations caused by insufficient or unstable lift. On the other hand, unnecessary aerodynamic drag needs to be minimized to reduce the impact and interference of unstable airflow on the platform, avoiding operational instability caused by abrupt changes in aerodynamic forces. At the same time, the effective convergence of wind energy reduces the blade diameter and weight, achieving both lightweighting and operational stability while optimizing lift and reducing drag.

[0059] To address the shortcomings of existing technologies, this invention provides a high-altitude wind power generation platform. Through a rational aerodynamic layout, it provides core support for the platform's continuous and stable operation in complex high-altitude airflow environments. Combined with... Figure 1-9 As shown, the high-altitude wind power generation platform includes a main airbag 1, a compensation component 2, wind turbine blades 3, a dynamic component 4, and a mooring point 5.

[0060] The main airbag 1 extends along the front-to-back direction. The outer circumferential surface of the main airbag 1 is a rotating surface. The diameter of the main airbag 1 gradually increases and then gradually decreases from front to back.

[0061] There are two compensation components 2, symmetrically arranged on both sides of the main airbag 1 along its extension direction and connected to the outer surface of the main airbag 1. Each compensation component 2 has a ring-shaped structure, including an air inlet duct 20, and is hollow inside to allow for gas injection. Specifically, the gas injected into the compensation component 2 can be air or a floating gas, such as hydrogen or helium, depending on the requirements.

[0062] The wind turbine blades 3 are installed inside the air intake duct 20, and each air intake duct 20 includes at least one set of wind turbine blades 3.

[0063] The high-altitude wind power generation platform includes multiple aerodynamic components 4, which are centrally symmetrically distributed on the outer periphery of the main airbag 1, located beside the compensation component 2, and outside the area of ​​the turbulent airflow generated by the wind turbine blades 3. That is, the airflow passing through the air intake duct 20 will not interfere with the aerodynamic components 4. In this way, when the high-altitude wind power generation platform and the free airflow in front have a relative angle of attack, significant aerodynamic lift can be generated.

[0064] The aerodynamic component 4 is specifically an airbag structure that extends along the front-to-back direction. The outer circumferential surface of the aerodynamic component 4 is a rotating surface, and its diameter gradually increases and then gradually decreases from front to back.

[0065] The mooring point 5 is the connection point between the high-altitude wind power generation platform and the mooring rope. The mooring rope is sleeved on the radial outside of the main airbag 1 and connected to the ground equipment. The mooring point 5 is located on the front side of the main airbag 1 and is spaced apart from the compensation component 2 in the extension direction of the main airbag 1.

[0066] In this embodiment, as Figure 1-4 As shown, the main airbag 1 is the primary component generating buoyancy for the high-altitude wind power platform. It is filled with sufficient helium and has space to accommodate auxiliary airbags and other control components. It has the largest volume among all components and plays a dominant role in the design and adjustment of the buoyancy center. By adjusting the layout of the high-altitude wind power platform and the arrangement of the auxiliary airbags within the main airbag 1, the buoyancy center A of the high-altitude wind power platform can be moved forward appropriately compared to traditional aerostats. This satisfies the platform's requirement for the relative position of buoyancy center A between the center of gravity B and the center of lift C. This precisely matches the core balance requirements of the high-altitude wind power platform, avoiding the uneven force on the mooring ropes and attitude tilting problems caused by the misalignment of the three centers (buoyancy center, center of gravity, and center of lift) when combined with a wind power device, thus laying the foundation for the platform's stable operation at high altitudes.

[0067] In a specific embodiment, such as Figure 2 As shown, the main airbag 1 is divided into a first airbag 11 and a second airbag 12 along the front-to-back direction. The junction of the first airbag 11 and the second airbag 12 is at the point where the diameter of the main airbag 1 is the largest. The tethering point 5 is located in the first airbag 11, while the compensation component 2, wind turbine blades 3, and aerodynamic components 4 are all located in the second airbag 12. This arrangement causes the aerodynamic component 4 to be positioned rearward relative to the high-altitude wind power platform, shifting the lift center C of the high-altitude wind power platform backward. Therefore, an attitude-restoring torque will be generated relative to the buoyancy center A of the high-altitude wind power platform, enabling the high-altitude wind power platform to operate stably at high altitudes.

[0068] In this embodiment, the orderly arrangement of the mooring point, buoyancy center, center of gravity, and lift center is achieved through the partitioned layout of components such as compensation component 2, wind turbine blade 3, and aerodynamic component 4. The restoring torque generated by the rearward shift of the lift center can cope with the impact of high-altitude gusts of airflow, preventing the platform from rotating irregularly around the mooring point when operating at high altitudes, and significantly improving the stability of the high-altitude wind power generation platform. Moreover, since the aerodynamic component 4 is concentrated in the second bladder 12, it can use the main airbag 1 as an end plate to enhance its own aerodynamic lift, while avoiding airflow interference with the mooring point and wind turbine blade 3, maximizing the functional efficiency of each component.

[0069] In a specific embodiment, such as Figure 2 As shown, the center of buoyancy A, center of gravity B, and center of lift C of the high-altitude wind power generation platform are all located in the region near the central axis of the main airbag 1. Among them, the center of buoyancy A is usually slightly higher than the central axis of the main airbag 1 due to the influence of the auxiliary airbag, while the center of gravity B is often lower than the central axis of the main airbag 1.

[0070] In a preferred example, the center of buoyancy A is located at the maximum diameter of the main airbag 1, the center of gravity B and the center of lift C are located behind the center of buoyancy A, and the mooring point 5 is located in front of the center of buoyancy A.

[0071] In this embodiment, as Figure 2 As shown, the layout design of the center of buoyancy A, center of gravity B, and center of lift C near the central axis of the main airbag 1 concentrates their lines of action on the same axis, avoiding platform tilting caused by lateral moments, simplifying the structural force transmission path, meeting the platform's own torque resistance design requirements, and reducing the overall structural weight of the platform. Since the center of buoyancy A is located at the maximum diameter of the main airbag 1, it forms a reasonable lever arm with the mooring point 5, center of gravity B, and center of lift C. This not only satisfies static balance in windless conditions but also spontaneously generates restoring moments when airflow changes, preventing large attitude fluctuations. Furthermore, because the adjustment logic of the three centers (center of buoyancy A, center of gravity B, and center of lift C) is relatively clear (e.g., the main airbag body mainly affects the center of buoyancy, aerodynamic components mainly regulate the aerodynamic lift center, and the wind power system mainly affects the center of gravity), it is convenient to optimize position parameters through simulation in the early stages, reducing later debugging costs, and also providing a standardized design basis for mass production.

[0072] In this embodiment, as Figure 2As shown, at least the center of gravity B is located within the range where the compensating component 2 and the main airbag 1 coincide in the axial direction. The coincidence of the center of gravity B with the compensating component 2 shortens the distance between the center of lift C and the center of gravity B, reducing the additional torque generated by lift, lowering the bending moment load on the platform, and extending the platform's service life. The position of the center of gravity B can be adjusted by moving the compensating component 2 without the need for additional counterweights, reducing ineffective weight and conforming to lightweight design principles. The proximity of the center of gravity B to the center of lift of the compensating component 2 avoids platform pitch attitude deviation caused by changes in the aerodynamic lift of the compensating component, ensuring that the wind turbine blades 3 remain in a stable airflow zone and maintain stable power generation efficiency.

[0073] In a specific embodiment, such as Figure 7 As shown, the inner diameter of the compensation component 2 gradually decreases and then gradually increases from front to back. The air inlet duct 20 is divided into a tapering section 21, a throat 22 and a widening section 23 from the front edge to the rear edge of the compensation component 2 according to the inner diameter of the compensation component 2. This forms a convergent-expanding duct section channel for the wind turbine blade 3, so that the wind speed and wind energy density at the throat 22 are much higher than those of the free flow.

[0074] In this embodiment, the inner diameter of the leading edge of the compensation component 2 is smaller than the inner diameter of the trailing edge of the compensation component 2. The throat 22 is located at the point where the inner diameter of the compensation component 2 is the smallest, and the wind turbine blade 3 is disposed at the throat 22.

[0075] The wind speed and wind energy density at throat 22 are much higher than those of the free flow. The wind turbine blade 3 is located at throat 22, which can significantly improve its wind energy capture efficiency and directly improve the power generation efficiency of the platform.

[0076] In a preferred example, the compensation component 2 can specifically be a ring wing, located at 60%-62% of the axial direction of the main airbag 1. The ring wing itself serves as an excellent aerodynamic lift component, providing aerodynamic lift to the high-altitude wind power platform, supplementing the buoyancy of the main airbag 1 to maintain the stability of the platform's altitude. Furthermore, the convergent-expansion type inlet duct 20 formed by its annular structure ensures that the throat 22 has a higher wind speed and wind energy density than the free flow. The wind turbine blades 3 are positioned at the throat 22, which helps improve wind energy utilization efficiency. Moreover, there are no other components obstructing the airflow in front of the compensation component 2 and the wind turbine blades 3, resulting in a stable inflow, high aerodynamic efficiency, and avoiding turbulence that easily induces efficiency reduction and lifespan decrease. The installation position of the compensation component 2 ensures that the distance between its lift center and the platform's buoyancy center A is moderate, allowing the dynamic lift of the compensation component 2 to supplement the buoyancy while preventing deformation of the main airbag 1 due to excessive lift torque. Moreover, the installation position of the compensation component 2 is offset from the maximum diameter of the main airbag 1, which can avoid interference between the airflow of the compensation component 2 and the main airbag 1, maximize the aerodynamic performance between the two, and achieve synergistic optimization of buoyancy and aerodynamic lift.

[0077] In a specific embodiment, such as Figure 4-6 As shown, the high-altitude wind power generation platform also includes a blade cascade 6 located at the rear edge of the compensation component 2 and fitted radially outside the compensation component 2. The blade cascade 6 and the compensation component 2 partially overlap in the radial direction. The inner diameter of the leading edge of the blade cascade 6 is smaller than the inner diameter of the trailing edge of the blade cascade 6, while the inner diameter of the leading edge of the blade cascade 6 is larger than the outer diameter of the trailing edge of the compensation component 2. This allows the airflow within the compensation component 2 to be induced towards the larger inner diameter (i.e., inside the blade cascade 6), thereby improving the airflow expansion capability of the inlet duct 20 and further increasing wind energy utilization. This eliminates the need for a compensation component 2 with a larger inner diameter, better meeting the requirements of lightweight and economical design.

[0078] In a specific embodiment, such as Figure 5-6 As shown, the blade cascade 6 includes a first cascade ring 61 and a second cascade ring 62. Both the first cascade ring 61 and the second cascade ring 62 have airfoil sections, both formed by rotating a high-camber airfoil section. Specifically, the inner diameter of the first cascade ring 61 gradually decreases and then gradually increases from front to back, with the inner diameter of the leading edge of the first cascade ring 61 being smaller than the inner diameter of the trailing edge. Similarly, the inner diameter of the second cascade ring 62 gradually decreases and then gradually increases from front to back, with the inner diameter of the leading edge of the second cascade ring 62 being smaller than the inner diameter of the trailing edge.

[0079] In this embodiment, as Figure 5As shown, the first grid ring 61 is located at the rear edge of the compensation component 2 and fits radially outside the compensation component 2. The smallest inner diameter of the first grid ring 61 corresponds to the rear edge of the compensation component 2, and there is a gap between the inner surface of the leading edge of the first grid ring 61 and the outer surface of the rear edge of the compensation component 2. The second grid ring 62 is located at the rear edge of the first grid ring 61 and fits radially outside the first grid ring 61. The smallest inner diameter of the second grid ring 62 corresponds to the rear edge of the first grid ring 61, and there is a gap between the inner surface of the leading edge of the second grid ring 62 and the outer surface of the rear edge of the first grid ring 61. The partial axial overlap between the first grid ring 61 and the compensation component 2, as well as the partial axial overlap between the first grid ring 61 and the second grid ring 62, can better induce the aerodynamic effect of the airflow turning towards the larger inner diameter.

[0080] In one specific embodiment, the chord length of the first gate ring 61 is greater than the chord length of the second gate ring 62. The distance between the minimum inner diameter of the first gate ring 61 and its leading edge is less than the distance between the minimum inner diameter of the first gate ring 61 and its trailing edge; the distance between the minimum inner diameter of the second gate ring 62 and its leading edge is less than the distance between the minimum inner diameter of the second gate ring 62 and its trailing edge.

[0081] like Figure 6 As shown, the blade cascade 6 can induce airflow to expand towards the larger inner diameter, improving wind energy utilization efficiency without increasing the inner diameter of the compensation component 2. Compared to a bladeless design, the radial expansion of airflow after the throat 22 is increased by approximately 12%, indirectly increasing power generation by approximately 25%. The axial overlap of the double-layer cascade rings optimizes the airflow turning path and reduces airflow separation losses. The inner diameter of the leading edge of the blade cascade 6 is larger than the inner diameter of the trailing edge of the compensation component 2, and a radial gap forms a local low-pressure acceleration zone for the airflow, inducing the airflow in the duct to move towards the larger radius while ensuring smooth airflow without flow separation resistance, reducing local aerodynamic drag, and minimizing structural interference between the blade cascade 6 and the compensation component 2, facilitating future maintenance and replacement.

[0082] In a specific embodiment, such as Figure 7 As shown, the central axes of both compensation components 2 are parallel to the central axis of the main airbag 1, and the central axes of the main airbag 1 and the two compensation components 2 are in the same plane. The parallel arrangement of the two compensation components 2 makes the platform aerodynamically symmetrical from left to right, avoiding lateral tilting caused by excessive lift on one side. At the same time, the arrangement of wind turbine blades on both sides can increase the total power generation compared to a single wind turbine blade.

[0083] In another embodiment, such as Figure 9As shown, the number of compensation components 2 can also be four, arranged in a cross structure at the four positions of the main airbag 1 (top, bottom, left, and right). Each compensation component 2 has at least one set of wind turbine blades 3 arranged in its air intake duct 20. The cross arrangement of the four compensation components 2 can adapt to the lift requirements of different wind directions (such as crosswinds and headwinds). When the airflow in one direction is weak, the compensation components 2 in other directions can still provide stable lift, improving the platform's adaptability to complex wind fields.

[0084] It should be noted that this embodiment does not impose a specific limit on the number of compensation components 2, and the above two embodiments are only illustrative examples. The arrangement of multiple compensation components 2 can distribute the total weight of the wind turbine blade 3, avoid the center of gravity shift caused by single-point weight concentration, and at the same time reduce the volume and weight of a single compensation component 2, reduce the difficulty of transportation and assembly, and meet the needs of engineering applications.

[0085] In one specific embodiment, the central axis of the aerodynamic component 4 is parallel to the central axis of the main airbag 1, and is arranged tangentially to or separate from the main airbag 1, and is fixed to the outer peripheral surface of the main airbag 1 by a bracket and ropes. Figure 7-8 As shown, in the front-rear direction, the leading edge of the aerodynamic component 4 is located before the leading edge of the compensation component 2, and the trailing edge of the compensation component 2 is located after the maximum diameter of the aerodynamic component 4. Since the aerodynamic component 4 is located beside the compensation component 2, the aerodynamic component 4 is outside the area of ​​the turbulent airflow generated by the wind turbine blade 3. That is, the airflow passing through the air intake duct 20 will not interfere with the aerodynamic component 4, thus reducing the interference of the wake airflow of the high-altitude wind power generation platform on the aerodynamic characteristics of the tail of the main airbag 1.

[0086] In this embodiment, the leading edge of the aerodynamic component 4 is located near the leading edge of the compensation component 2. The leading edge of the aerodynamic component 4 is generally located in front of or flush with the leading edge of the compensation component 2. The trailing edge of the compensation component 2 is located behind the point of maximum diameter of the aerodynamic component 4, which shifts the lift center of the platform to the rear and significantly enhances the attitude recovery torque, effectively resisting the impact of high-altitude airflow.

[0087] In a specific embodiment, such as Figure 1-4 As shown, the high-altitude wind power platform includes four aerodynamic components 4, which are distributed in an X-shape on the outer periphery of the main airbag 1. Two aerodynamic components 4 are located above the two compensation components 2, and the other two are located below the two compensation components 2. The aerodynamic value of the four aerodynamic components 4 lies in their use of the main airbag 1 as a side endplate, which enhances their lift. Simultaneously, their rearward positioning shifts the center of lift backward, generating a restoring torque and enhancing the stability of the high-altitude wind power platform.

[0088] The X-shaped symmetrical layout of the aerodynamic components 4 eliminates unilateral aerodynamic load differences, prevents platform tilting, and adapts to complex wind fields such as crosswinds and oblique winds. The four aerodynamic components 4 are divided into two groups, located between the two compensation components 2, forming an alternating force-bearing structure between the compensation components 2 and the aerodynamic components 4. This effectively disperses the load on the outer periphery of the main airbag 1, reduces local stress concentration, and extends the service life of the main airbag 1. Simultaneously, the X-shaped layout of the aerodynamic components 4 provides a natural framework for the construction of the tail sail 7, eliminating the need for additional support structures, reducing weight, and ensuring even stress distribution on the tail sail 7, preventing localized tearing.

[0089] In this embodiment, the aerodynamic component 4 is located at 60% of the axial length of the main airbag 1. The axial length of the aerodynamic component 4 is approximately 45% of the chord length of the main airbag 1. Therefore, the trailing edge of the aerodynamic component 4 slightly extends beyond the trailing edge of the main airbag 1.

[0090] The axial mounting position of aerodynamic component 4 is basically coincident with that of compensation component 2, making their lift centers close together. This avoids torque conflicts caused by the dispersion of lift sources and reduces the bending moment load on the main airbag 1. The appropriate chord length of aerodynamic component 4 can control the weight of the component while ensuring lift output, and its trailing edge extending beyond the main airbag 1 can utilize the wake of the main airbag 1 to generate secondary lift, effectively improving the overall lift of the platform. Compensation component 2 and aerodynamic component 4 are concentrated in the second airbag 12, which can effectively shorten the force transmission path, accelerate the structural response speed, and improve the timeliness of attitude adjustment.

[0091] In this embodiment, as Figure 8 As shown, the trailing edge of the aerodynamic component 4 protrudes beyond the trailing edge of the main airbag 1, and an X-shaped tail sail 7 is formed between the trailing edges of the four aerodynamic components 4. The tail sail 7 is an X-shaped tail sail formed by using canvas to construct a structure based on the relative positional relationship between the four aerodynamic components 4 and the main airbag 1. The tail sail 7 is located at the rearmost end of the main airbag 1 and can generate attitude-restoring torque to improve the stability of the high-altitude wind power generation platform. In addition to improving the attitude stability of the high-altitude wind power generation platform, the tail sail 7 also, compared to the central axis of the compensation component 2, geometrically expands further, thereby further enhancing the effective airflow expansion ratio of the exit section of the trailing edge of the compensation component 2 compared to the section at the throat 22, which can increase the wind speed at the throat 22 and improve the power generation capacity.

[0092] The X-shaped tail sail 7, located at the end of the main airbag 1, can generate a bidirectional restoring torque for pitch and yaw. The attitude response speed is significantly improved compared to traditional tail fins, enabling the platform to quickly return to normal when tilting.

[0093] In a specific embodiment, such as Figure 1 As shown, the surface of the connection between the aerodynamic component 4 and the main airbag 1 is covered with a rectifier skin 8. The rectifier skin 8 can improve the aerodynamic shape of the high-altitude wind power generation platform, realize the natural transition between the main airbag 1 and the aerodynamic component 4, and shield the connection structure between the aerodynamic component 4 and the main airbag 1. It reserves design space for the support and ropes. Since there is no airflow blowing in this space, it can avoid the support and ropes at the connection point from disturbing the airflow and causing the airflow to separate, thereby avoiding weakening the aerodynamic effect of the tail sail 7 and not having an adverse effect on the aerodynamic characteristics of the high-altitude wind power generation platform.

[0094] The smoothing skin 8 achieves a natural transition at the connection between the main airbag 1 and the aerodynamic component 4, which can shield the connection structure of the two to form a closed space, including the brackets and ropes, from the scouring of high-speed airflow, reduce the corrosion rate of the components, and extend the maintenance cycle.

[0095] Because both the main airbag 1 and the four aerodynamic components 4 are of a rotating shape, they have a relatively high profile for the same volume, requiring less fairing skin and better meeting lightweight design requirements. The four aerodynamic components 4 have large cross-sections and excellent rigidity. Compared to traditional tail fin structures, the aerodynamic components 4 are more likely to maintain their shape under aerodynamic forces, and are less prone to significant deformation or even bending. The large-section rotating structure of the aerodynamic components 4 significantly improves their resistance to deformation compared to traditional tail fins, resulting in smaller deformation in strong winds and ensuring stable lift output.

[0096] In a specific embodiment, such as Figure 1-4 As shown, a tail fin 9 is provided on the surface of the aerodynamic component 4 away from the main airbag 1. The tail fin 9 is arranged perpendicular to the plane formed by the central axis of the compensation component 2 and the central axis of the main airbag 1. The tail fin 9 is a small tail fin used to additionally assist the high-altitude wind power generation platform in compensating for the restoring moment in the yaw direction. In the yaw direction, after the compensation component 2 captures the wind energy of the incoming airflow, the air velocity behind the compensation component 2 is low and spreads to the four aerodynamic components 4 in the yaw attitude, which weakens the ability of the aerodynamic components 4 to adjust the yaw attitude to a certain extent. Therefore, a small tail fin 9 protruding from the height of the compensation component 2 is provided on the aerodynamic component 4 to supplement the yaw restoring moment, thereby ensuring the stability of the high-altitude wind power generation platform in the high altitude. In addition, the tail fin 9 can also grow further out of the disturbance airflow area generated by the wind turbine blade 3 based on the aerodynamic component 4, which enhances the aerodynamic efficiency of the tail fin 9 and reduces the size requirements of the tail fin 9.

[0097] In this embodiment, the main airbag 1 provides the main buoyancy force of the high-altitude wind power generation platform, the compensation component 2 provides the compensation aerodynamic lift, and is relatively close to the buoyancy center A, which can avoid excessive torque caused by the lift of the compensation component 2; the aerodynamic component 4, tail fin 9 and tail sail 7 provide relatively small aerodynamic force, and use a long lever arm to provide a suitable restoring torque to maintain the stability of the attitude of the high-altitude wind power generation platform.

[0098] In one specific embodiment, the inner diameter at the throat 22 is 0.5-1 times the maximum diameter of the main airbag 1, and the inner diameter of the trailing edge of the compensation component 2 is 1.05-1.6 times the inner diameter at the throat 22. The design of the inner diameter at the throat 22 being 0.5-1 times the maximum diameter of the main airbag 1 achieves a good engineering balance between power generation requirements and airship capacity. The design of the inner diameter of the trailing edge of the compensation component 2 being 1.05-1.6 times the inner diameter at the throat 22 achieves a balance between airflow resistance and wind energy convergence. By matching the proportional parameters with the compensation component 2, the pressure distribution within the air intake duct 20 is made uniform, the stress fluctuation amplitude of the wind turbine blade 3 is reduced, and fatigue damage to the wind turbine blade 3 is decreased.

[0099] In one embodiment, each compensation component 2 has a set of wind turbine blades 3 installed in its air inlet duct 20. The wind turbine blades 3 located in the air inlet ducts 20 of the two compensation components 2 rotate in opposite directions to counteract the horizontal torque generated by each blade, thereby maintaining the attitude stability of the high-altitude wind power generation platform at high altitude. In another embodiment, each compensation component 2 has two sets of wind turbine blades 3 installed in its air inlet duct 20. The two sets of wind turbine blades 3 located in the same air inlet duct 20 rotate in opposite directions, enabling torque self-balancing within the same air inlet duct 20, maintaining the attitude stability of the high-altitude wind power generation platform at high altitude, and allowing the downstream blades to restore the vortex formed during the operation of the upstream blades, thereby improving wind energy utilization efficiency.

[0100] In one embodiment, the tail fin 9 on the aerodynamic component 4 can be arranged at an angle.

[0101] In one embodiment, the tail fin 9 on the aerodynamic component 4 can be a rigid tail fin or a thicker inflatable tail fin.

[0102] In one embodiment, a large X-tail can be used to replace the four aerodynamic components 4, but the effects of lightweighting, aerodynamic lift, and economy will be reduced.

[0103] The following is a design example of a high-altitude wind power generation platform provided in an embodiment of the present invention.

[0104] The high-altitude wind power generation platform mainly includes: main airbag 1, compensation component 2, wind turbine blade 3, dynamic component 4, blade cascade 6, tail sail 7, fairing skin 8, and tail fin 9.

[0105] For ease of description, the diameter at the maximum diameter of the main airbag 1 is used as the reference datum D, and this design example is described in detail.

[0106] The main airbag 1 has a chord length of 3.2D and its maximum diameter is located at 40% of the axial direction.

[0107] The leading edge of the compensation component 2 is located at 62% of the axial direction of the main airbag 1. The compensation component 2 is a ring wing, generated by rotating a two-dimensional airfoil profile. The airfoil chord length is 0.5D, the thickest part of the airfoil is 0.15D, and the angle between the airfoil chord and the rotation axis is 5deg. The inner diameter of the ring wing throat 22 generated by the rotation is 0.76D, and the inner diameter at the trailing edge exit is 0.96D.

[0108] Wind turbine blades 3 are arranged at the throat of the compensation component 2. To prevent the blade tip of the wind turbine blade 3 from rubbing against the inner surface of the compensation component 2, the diameter of the wind turbine blade 3 is slightly smaller than the inner diameter at the throat 11, which is 0.74D.

[0109] The blade cascade 6 is located at the trailing edge of the compensation component 2 and includes a first cascade ring 61 and a second cascade ring 62. The first cascade ring 61 and the second cascade ring 62 are each generated by rotating a two-dimensional airfoil profile, which can be obtained by the Naca four-digit airfoil generation algorithm. The airfoil chord length of the first cascade ring 61 is 0.03D, and the point of maximum camber (i.e., the thickest part of the airfoil) is approximately located at the trailing edge of the compensation component 2; the airfoil chord length of the second cascade ring 62 is 0.024D, and the point of maximum camber (i.e., the thickest part of the airfoil) is approximately located at the trailing edge of the first cascade ring 61.

[0110] Between the four aerodynamic components 4 and the main airbag 1, a 0.09D wide skin is used to form a fairing skin 8.

[0111] An X-shaped tail sail 7 is stretched out using skin between the four aerodynamic components 4 and the main airbag 1.

[0112] A rigid tail fin 9 is arranged on the surface of the four aerodynamic components 4 on the side opposite to the main airbag 1. The tail fin 9 has a thickness of 0.03D and a height of 0.23D.

[0113] The above completes the layout design of the high-altitude wind power generation platform.

[0114] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. For those skilled in the art, other variations or modifications can be made based on the above description. It is impossible to exhaustively list all the implementation methods here. All obvious variations or modifications derived from the technical solutions of the present invention are still within the protection scope of the present invention.

Claims

1. A high-altitude wind power generation platform, characterized in that, include: The main airbag extends along the front-to-back direction, and its outer circumferential surface is a rotating surface. The diameter of the main airbag gradually increases and then gradually decreases from front to back. Two compensation components are symmetrically arranged on both sides of the main airbag and connected to the main airbag; The compensation component is a ring structure, including an air inlet duct, and the interior of the compensation component is hollow to allow gas to be injected. Wind turbine blades are installed inside air intake ducts, and each air intake duct contains at least one set of wind turbine blades. Aerodynamic components: Multiple aerodynamic components are centrally symmetrically distributed on the outer periphery of the main airbag, located beside the compensation components, outside the area of ​​turbulent airflow generated by the wind turbine blades; A tether point is located between the front sides of the main airbag and is disposed at a distance from the compensation component in the direction of extension of the main airbag; The aerodynamic component extends along the front-to-back direction. The outer circumferential surface of the aerodynamic component is a rotating surface, and its diameter gradually increases and then gradually decreases from front to back. In the front-to-back direction, the leading edge of the aerodynamic component is located near the leading edge of the compensation component, and the trailing edge of the compensation component is located behind the point where the diameter of the aerodynamic component is at its maximum.

2. The high-altitude wind power generation platform according to claim 1, characterized in that, The main airbag is divided into a first airbag and a second airbag along the front-to-back direction, and the junction of the first airbag and the second airbag is the part with the largest diameter of the main airbag. The mooring point is located in the first capsule, and the compensation component, wind turbine blade, and aerodynamic component are all located in the second capsule.

3. The high-altitude wind power generation platform according to claim 1, characterized in that, The center of buoyancy, center of gravity, and center of lift of the high-altitude wind power generation platform are all located in the region near the central axis of the main airbag; The center of gravity and the center of lift are located behind the center of buoyancy, and the mooring point is located in front of the center of buoyancy.

4. The high-altitude wind power generation platform according to claim 3, characterized in that, At least one of the center of gravity and the center of lift is located within the range where the compensation component and the main airbag coincide in the axial direction.

5. The high-altitude wind power generation platform according to claim 1, characterized in that, The inner diameter of the compensation component gradually decreases from front to back and then gradually increases. The air intake duct is divided into a tapering section, a throat section, and a widening section from the front edge to the rear edge of the compensation component according to the inner diameter of the compensation component. The inner diameter of the front edge of the compensation component is smaller than the inner diameter of the rear edge of the compensation component. The throat is located at the point where the inner diameter of the compensation component is at its minimum, and the wind turbine blade is located at the throat.

6. The high-altitude wind power generation platform according to claim 1, characterized in that, The high-altitude wind power generation platform also includes blade cascades located at the rear edge of the compensation component and fitted on the radial outer side of the compensation component, with the blade cascades partially overlapping the compensation component in the radial direction; The inner diameter of the leading edge of the blade cascade is larger than the outer diameter of the trailing edge of the compensation assembly.

7. The high-altitude wind power generation platform according to claim 6, characterized in that, The blade cascade includes a first cascade ring and a second cascade ring, both of which have an airfoil profile. The inner diameter of the first gate ring gradually decreases and then gradually increases from front to back, and the inner diameter of the front edge of the first gate ring is smaller than the inner diameter of the rear edge of the first gate ring. The inner diameter of the second gate ring gradually decreases and then gradually increases from front to back, and the inner diameter of the front edge of the second gate ring is smaller than the inner diameter of the rear edge of the second gate ring. The first grid ring is located at the rear edge of the compensation component and is fitted on the radial outer side of the compensation component. The smallest inner diameter of the first grid ring is located at the rear edge of the compensation component. There is a gap between the inner surface of the front edge of the first grid ring and the outer surface of the rear edge of the compensation component. The second grid ring is located at the rear edge of the first grid ring and is fitted radially outside the first grid ring. The smallest inner diameter of the second grid ring is located at the rear edge of the first grid ring. There is a gap between the inner surface of the front edge of the second grid ring and the outer surface of the rear edge of the first grid ring.

8. The high-altitude wind power generation platform according to claim 7, characterized in that, The chord length of the first gate ring is greater than or equal to the chord length of the second gate ring; The distance between the minimum inner diameter of the first gate ring and the leading edge of the first gate ring is less than the distance between the minimum inner diameter of the first gate ring and the trailing edge of the first gate ring. The distance between the minimum inner diameter of the second gate ring and the leading edge of the second gate ring is less than the distance between the minimum inner diameter of the second gate ring and the trailing edge of the second gate ring.

9. The high-altitude wind power generation platform according to claim 1, characterized in that, The central axes of the two compensation components are parallel to the central axis of the main airbag, and the central axis of the main airbag and the central axes of the two compensation components are in the same plane.

10. The high-altitude wind power generation platform according to claim 1, characterized in that, The central axis of the aerodynamic component is parallel to the central axis of the main airbag, and is either tangential to or separate from the main airbag. It is fixed to the outer circumference of the main airbag by a bracket and ropes.

11. The high-altitude wind power generation platform according to claim 10, characterized in that, The high-altitude wind power generation platform includes four aerodynamic components, which are distributed in an X-shaped structure on the outer periphery of the main airbag. Two aerodynamic components are located above the two compensation components, and the other two aerodynamic components are located below the two compensation components. The trailing edge of the aerodynamic components protrudes beyond the trailing edge of the main airbag, and an X-shaped tail sail is formed between the trailing edges of the four aerodynamic components.

12. The high-altitude wind power generation platform according to claim 10, characterized in that, The surface at the connection between the aerodynamic component and the main airbag is covered with a smoothing skin to achieve a natural transition between the main airbag and the aerodynamic component.

13. The high-altitude wind power generation platform according to claim 10, characterized in that, The aerodynamic component has a tail fin on the side of its surface away from the main airbag. The tail fin is perpendicular to the plane formed by the central axis of the compensation component and the central axis of the main airbag.

14. The high-altitude wind power generation platform according to claim 5, characterized in that, The inner diameter of the throat is 0.5-1 times the maximum diameter of the main airbag; The inner diameter of the rear edge of the compensation component is 1.05-1.6 times the inner diameter of the throat.

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