Lift structure for aerostat and buoyancy adjusting method

Abstract

The invention relates to a lift structure for an aerostat and a buoyancy adjusting method, and the structure realizes dynamic adjustment of lift and optimization of flight performance by combining a light gas storage chamber, a middle buffer chamber and an annular wing. The lift force structure comprises a floating main body, an annular wing, an air storage chamber, a middle buffer chamber and a control system, and further comprises an air filling unit and a pressure adjusting unit. The inner surface of the floating body defines a first air duct, and the annular wing and the floating body are spaced to form a second air duct. And the gas storage chamber and the middle buffer chamber are inflated and subjected to pressure regulation through the gas filling unit and the pressure regulation unit. The control system monitors the state of the aerostat in real time through the sensor array and adjusts the pressure of the air storage chamber and the middle buffer chamber and the absolute angle of attack of the annular wing through feedback control logic, so that dynamic adjustment of lift force and optimization of flight performance are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerostats, and in particular to a lift structure and a buoyancy adjustment method for an aerostat. Background Art

[0002] Aerostats are aircraft that use the principle of gas buoyancy to hover or move in the air. They are widely used in meteorological monitoring, environmental monitoring, communications, reconnaissance, and high-altitude wind power generation. Compared with traditional fixed-wing aircraft and helicopters, aerostats have higher durability and lower energy consumption, can stay at high altitudes for a long time, and maintain stability at lower flight speeds.

[0003] The lift structure of an aerostat is one of its core components and mainly relies on the buoyancy provided by lightweight gases such as helium or hydrogen. The lift structure is usually composed of multiple air bags or bubbles, which are made of special materials to ensure good pressure resistance and durability in high-altitude environments. The injection and discharge of gas are regulated by a control system to achieve precise control of lift. The regulation of lift can be achieved by changing the volume and density of the gas, such as by adding gas, exhausting gas or adjusting the gas temperature. In addition, the lift structure of the aerostat may also be equipped with an airflow guide device to optimize the distribution of airflow and increase the efficiency of lift.

[0004] In high-altitude wind power generation systems, the lift structure design of the aerostat is particularly important because it needs to hover stably in strong wind conditions and effectively collect wind energy. Through reasonable lift structure design, the aerostat can resist the influence of wind, improve power generation efficiency, and achieve stable flight for a longer period of time. At the same time, the lightweight design of the lift structure also helps to improve the maneuverability of the aerostat, reduce energy consumption, and thus extend its operation time in the air.

[0005] In recent years, with the progress of material science and control technology, the lift structure of aerostats has been significantly improved, especially in terms of material strength and airtightness, making aerostats perform better in various application scenarios. As a kind of aircraft that can hover in the air for a long time or move slowly, aerostats are widely used in aerial wind power generation, weather monitoring, communication relay, advertising display and other fields.

[0006] CN116773077A discloses a system and method for calculating the buoyancy of an aerostat by infrared thermal imaging. The system includes a pressure sensor, a first temperature sensor, a first infrared imaging sensor and a calculation terminal. The pressure sensor is arranged at the mouth of the gas-filled bottle to measure the pressure in the gas-filled bottle. The first temperature sensor is arranged on the gas-filled bottle, the first infrared imaging sensor is arranged on one side of the gas-filled bottle, the first temperature sensor is used to measure the temperature on the gas-filled bottle, and the first infrared imaging sensor is used to measure the temperature field of the gas-filled bottle. The system for calculating the buoyancy of an aerostat by infrared thermal imaging provided by the invention uses a pressure sensor to measure the pressure in the bottle before and after inflation, and uses a first temperature sensor and a first infrared imaging sensor to measure the temperature in the bottle before and after inflation, so as to determine the inflation amount of the aerostat, which greatly improves the measurement accuracy of the inflation amount of the aerostat.

[0007] CN205971786U discloses a buoyancy regulating device of an aerostat, an aerostat and an aerostat system, wherein the buoyancy regulating device of the aerostat comprises: a temperature detection unit, an air pressure detection unit, a control unit, an air valve unit and a heating unit. The temperature information and air pressure information of the internal filling gas are respectively measured by the temperature detection unit and the air pressure detection unit, the control unit compares the temperature information and the air pressure information with the preset temperature threshold and the preset air pressure threshold, and outputs the air pressure control information and the temperature control information to the air valve unit and the heating unit respectively, and then when the light is sufficient during the day and the temperature of the internal filling gas rises and the air pressure increases, the air valve unit deflates the internal filling gas according to the air pressure control information, and the heating unit heats the internal filling gas according to the temperature control information at night, thereby avoiding the phenomenon that the aerostat has insufficient buoyancy after deflation and the aerostat drops at night as the temperature drops sharply.

[0008] Traditional aerostat lift structures usually rely on a single lightweight gas filling, lack flexibility and adaptability, and have difficulty maintaining stable flight performance under different wind speed and wind direction conditions.

[0009] In addition, on the one hand, there are differences in understanding among those skilled in the art; on the other hand, the applicant studied a large number of documents and patents when making the present invention, but due to space limitations, not all details and contents are listed in detail. However, this does not mean that the present invention does not have the characteristics of these prior arts. On the contrary, the present invention already has all the characteristics of the prior art, and the applicant reserves the right to add relevant prior art to the background technology. Summary of the invention

[0010] In view of the deficiencies of the prior art, the present invention provides a lift structure and a buoyancy adjustment method for an aerostat to solve at least part of the above-mentioned technical problems.

[0011] The present invention discloses a lift structure for an airship, the airship comprises: an airship body made of a light and flexible material, the inner surface of which defines a first air duct, the first air duct is in the form of a reduced air inlet and an enlarged air outlet in an axial cross-sectional view, a trumpet shape from large to small, or a roughly hollow cylindrical shape. The lift structure is composed of the airship body located on the radial inner side and an annular wing fixed thereon at intervals, wherein the annular wing is located on the radial outer side of the airship body and is spaced from the airship body, and in the interval area, the radial inner wall of the annular wing and the radial outer wall of the airship body opposite thereto jointly form a second air duct, wherein the area of ​​the second air duct is larger than the area occupied by the first air duct, and the second air duct is arranged in an induced diffusion manner to provide a lift force far greater than the resistance brought by it.

[0012] The lift structure of the present invention realizes the reasonable configuration of the first air duct and the second air duct through the carefully designed layout of the floating body and the annular wing. The trumpet-shaped design of the first air duct improves the air intake efficiency, while the area of ​​the second air duct is larger than the first air duct, and the induced diffusion method is adopted, which not only reduces the airflow resistance, but also significantly increases the lift. The lift structure forms a low-pressure area through the acceleration and diffusion of the airflow, thereby generating lift. In addition, this structural design also allows the airship to optimize the aerodynamic performance by adjusting the air duct area at different wind speeds, achieving the dual effects of efficient energy utilization and flight stability.

[0013] According to a preferred embodiment, the annular wing adopts a multi-stage structure, and the absolute angle of attack of the annular wing is adjustable, and the adjustment method includes adjusting the posture of the floating body, wherein the posture of the floating body can be passively adjusted by an external angle of attack adjustment mechanism, and / or autonomously adjusted by using the aerodynamic lift generated by the pressure difference formed by the airflow flowing through the annular wing on the upper and lower sides of the annular wing. According to a preferred embodiment, the areas occupied by the first air duct and the second air duct can be adjusted independently of each other, wherein the lift structure can adapt to different wind speeds and wind directions, so as to optimize the flow characteristics of the airflow by dynamically adjusting the geometric shapes of the first air duct and the second air duct.

[0014] The independent adjustment capability of the first and second duct areas enables the lift structure to flexibly adapt to changing wind speeds and directions. By dynamically adjusting the geometry of the ducts, the flow characteristics of the airflow can be optimized and the efficiency of lift generation can be improved.

[0015] According to a preferred embodiment, a plurality of mutually independently sealed air storage chambers for carrying lighter-than-air gas are provided in the floating body, and these air storage chambers are inflated in a controlled pressure manner by special inflation equipment to achieve buoyancy adjustment of the floating body.

[0016] The design of the independently sealed air storage chamber inside the aerostat body is inflated with controlled pressure through a dedicated inflation device, providing a precise means of buoyancy adjustment. This design allows the aerostat to adjust its buoyancy as needed to adapt to different flight altitudes and load conditions. The independence of the air storage chamber also ensures that in the event of a light gas leak, it can be replenished quickly and effectively to maintain the stability and safety of the aerostat.

[0017] According to a preferred embodiment, an intermediate buffer chamber is provided in the airship body, and the intermediate buffer chamber is filled with a first gas. The first gas and the light gas in the gas storage chamber are different gases from each other. The intermediate buffer chamber is used to form multiple pressure gradients in the light gas leakage path in the direction from the inside to the outside of the airship.

[0018] The design of the intermediate buffer chamber forms multiple pressure gradients inside the aerostat, which not only helps to reduce the leakage of light gas, but also can accurately control the outer diameter of the aerostat by adjusting the pressure and volume of the first gas. This design controls buoyancy by adjusting the internal pressure. At the same time, the formation of this pressure gradient also helps to optimize the airflow state of the second air duct and further improve the lift efficiency.

[0019] According to a preferred embodiment, the light gas in the floating body and the first gas in the intermediate buffer chamber are filled and pressure-regulated by different gas filling units and pressure regulating units, and then the outer diameter size in the floating body area is adjusted jointly or independently to achieve control of the relative position and shape of the annular wing, thereby changing the structure, size and shape of the first air duct and / or the second air duct.

[0020] By charging and regulating the pressure of the light gas and the first gas through different gas filling units and pressure regulating units, the outer diameter of the floating body can be precisely controlled. The present invention changes the lift by adjusting the shape and angle of the wing, thereby controlling the flight state of the aircraft. In addition, this independent adjustment capability also allows the aerostat to optimize the aerodynamic performance by changing the structure and shape of the air duct under different flight conditions.

[0021] According to a preferred embodiment, the lift structure includes a control system that not only controls the attitude, altitude and position of the aerostat, but is also capable of controlling the pressure of the air storage chamber and the intermediate buffer chamber, thereby dynamically changing the angle and speed of the airflow entering the first air duct and / or the second air duct to achieve lift regulation, so as to achieve efficient and adaptable flight performance.

[0022] The integration of the control system not only realizes the control of the attitude, height and position of the aerostat, but also can dynamically adjust the pressure of the air storage chamber and the intermediate buffer chamber, thereby changing the airflow angle and speed to achieve precise adjustment of lift. The present invention realizes real-time monitoring and adjustment of the flight status through the coordinated work of sensors and control logic, ensuring the efficiency and adaptability of the flight.

[0023] According to a preferred embodiment, the control system includes a sensor array and feedback control logic for real-time monitoring and adjusting the internal air pressure of the aerostat and the airflow conditions of the first air duct and / or the second air duct to ensure the stability and efficient energy utilization of the aerostat in complex environments.

[0024] The sensor array and feedback control logic in the control system provide the aerostat with real-time monitoring and adjustment capabilities. By monitoring the internal air pressure and airflow conditions in the air duct, the control system can make timely adjustments to ensure the stability and efficient energy utilization of the aerostat in complex environments. The present invention collects data through sensors and analyzes and adjusts it through control logic to achieve the optimal operating state.

[0025] The present invention also discloses a buoyancy adjustment method, which is applicable to a high-altitude wind power generation system, wherein the high-altitude wind power generation system includes a floating body made of a lightweight flexible material and a lift structure jointly constituted by an annular wing, wherein the floating body is located radially inside the annular wing and there is a gap between the floating body and the annular wing, thereby when the floating body forms an aerodynamic hollow cylindrical body, the annular wing surrounds the aerodynamic hollow cylindrical body from its radial outside, and the lift of the floating body is adjusted by adjusting the absolute angle of attack of the annular wing in the lift structure jointly formed by the annular wing and the floating body, thereby adjusting the buoyancy of the high-altitude wind power generation system.

[0026] According to a preferred embodiment, the radial inner wall of the annular wing and the radial outer wall of the floating body jointly form a second wind duct in the interval area. The area of ​​the second wind duct is larger than that of the first wind duct, and the second wind duct is arranged in an induced diffusion manner so that the lift provided is much greater than the resistance it brings, thereby changing the buoyancy.

[0027] The design of the second air duct not only provides a larger area to increase lift, but also reduces drag by means of induced diffusion. This design generates thrust by accelerating and diffusing airflow. In addition, this design allows the system to optimize aerodynamic performance and achieve a higher lift-to-drag ratio by adjusting the geometry of the air duct under different wind speed conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a three-dimensional schematic diagram of a lift structure of a preferred embodiment provided by the present invention;

[0029] Figure 2It is a front view of a lifting structure of a preferred embodiment provided by the present invention;

[0030] Figure 3 It is a schematic diagram of the configuration of a floating body and annular wings according to a preferred embodiment of the present invention;

[0031] Figure 4 It is a principle diagram of the injection diffusion effect of the annular wing of a preferred embodiment provided by the present invention;

[0032] Figure 5 It is a schematic diagram of realizing the return of the floating body to the normal position by the sealing effect produced by the annular wing in a preferred embodiment provided by the present invention;

[0033] Figure 6 It is a layout diagram of the air storage chamber and the intermediate buffer chamber inside the floating body of a preferred embodiment provided by the present invention;

[0034] Figure 7 It is a control logic diagram of a control system of a preferred embodiment provided by the present invention.

[0035] Reference numerals list

[0036] 100: airship; 200: airborne body; 210: gas storage chamber; 211: light gas; 220: intermediate buffer chamber; 221: first gas; 230: first air duct; 300: annular wing; 310: second air duct; 400: ducted generator; 500: mooring; 600: control system; 610: gas filling unit; 620: pressure regulating unit; 630: sensor array; 640: feedback control logic; 650: angle of attack adjustment mechanism; 660: outlet cross-sectional area adjustment unit. DETAILED DESCRIPTION

[0037] The following is a detailed description with reference to the accompanying drawings.

[0038] Example 1

[0039] The present invention discloses a lifting structure for an aerostat 100, which includes: a floating body 200, an annular wing 300, an air storage chamber 210 and a control system 600. Further, the lifting structure may also include an air filling unit 610 and a pressure regulating unit 620.

[0040] like Figure 1 and Figure 2As shown, the floating body 200 of the airship 100 and the annular wing 300 fixed to the floating body 200 at intervals therefrom together constitute the lift structure of the present invention. Preferably, the inner surface of the floating body 200 defines a first air duct 230, and the first air duct 230 is in the form of a reduced air inlet and an enlarged air outlet in the axial cross-sectional view, a trumpet shape from large to small, or a generally hollow cylindrical shape. Preferably, the annular wing 300 is located radially outside the floating body 200 and is spaced from the floating body 200, wherein, in the spacing area, the radial inner wall of the annular wing 300 and the radial outer wall of the floating body 200 opposite thereto jointly form a second air duct 310. Preferably, the annular wing 300 and the floating body 200 can be connected by a fixing member, wherein a plurality of fixing members can be symmetrically arranged on the radial outer wall of the floating body 200 so that the axis of the annular wing 300 and the floating body 200 are roughly coincident. Further preferably, three fixing members can be arranged.

[0041] Preferably, if Figure 1 and Figure 2 As shown, the area of ​​the second air duct 310 is larger than that of the first air duct 230, and it is arranged in an ejection-diffusion manner to provide a lift force that is much greater than the resistance it brings. Figure 3 As shown, the outlet radius R of the first air duct 230 is taken as a reference, and the minimum curved surface distance between the airborne body 200 and the annular wing 300 is set as d, and it is usually set in a manner of d<R, so that the annular wing 300 can produce an induced diffusion effect on the first air duct 230. This design can reduce resistance while increasing lift, so that the airship 100 can work stably at a higher wind speed, and at the same time, the induced diffusion effect produced on the first air duct 230 can be used to increase the airflow speed of the first air duct 230.

[0042] The principle of the induced diffusion effect of the annular wing is as follows Figure 4 shown. Figure 4 (a) shows the air static pressure field distribution of the outlet area of ​​the first air duct 230 obtained entirely by the floating body 200 under the condition of 20m / s axial incoming flow; Figure 4 (b) shows the Figure 4 Based on the floating body 200 of (a), the static pressure field of air is formed by the structure composed of a ring wing 300 arranged in a manner of d=0.33R and the floating body 200. Figure 4It can be seen that the second air duct 310 is a convergent-expansion channel formed by the floating body 200 and the annular wing 300, and according to the Bernoulli principle, when the airflow passes through the convergent section, the area of ​​the channel is reduced, the flow rate will be accelerated, and the static pressure will be reduced. Therefore, the airflow of the second air duct 310 will be accelerated and the static pressure will be reduced in the convergent section, forming an ejection flow, and generating a local air static pressure negative pressure area, wherein the ejection flow refers to the fluid being discharged from a container or nozzle at a high speed to form a stream of flow, which is characterized in that the fluid is ejected from a narrow outlet, and after rapid expansion and mixing, a low pressure area (i.e., negative pressure area) is usually formed in this process. Further, since the negative pressure area is just configured near the outlet of the first air duct 230, the airflow is subjected to a stronger suction effect when passing through the area, and the annular wing 300 is similar to the role of a diffuser, which enhances the airflow velocity in the first air duct 230. In addition, the design of the annular wing 300 not only increases the airflow velocity, but also reduces the generation of vortices, maintaining the smoothness of the airflow. The annular wing 300 configured in this way can have a maximum specific lift, wherein the maximum specific lift means that the lift is the largest under the conditions of the same speed and the same gravity.

[0043] Preferably, the induced diffusion effect of the second air duct 310 can also be achieved or further enhanced by a guide plate arranged inside or near the second air duct 310. Preferably, the arrangement of the guide plate can be a plurality of slats arranged side by side, or evenly distributed on the inner wall of the second air duct 310 in an annular structure, wherein, when a plurality of guide plates are arranged side by side, they can be connected by a support rod or a frame to keep their relative positions unchanged, thereby forming an integral guide system. Preferably, the guide plate can be designed as a structure with adjustable angles so as to make real-time adjustments according to airflow changes, thereby optimizing aerodynamic performance. Preferably, the guide plate can be made of lightweight and high-strength materials, such as composite materials or aluminum alloys, to ensure its stability and durability in high-altitude environments. Preferably, the guide plate can be designed as a gradient shape, with a wider front and a gradually narrower rear to form a better airflow guiding effect, or an airfoil structure can be used to improve aerodynamic efficiency and reduce airflow resistance. The guide plate changes the airflow path to form an ejection effect, so that the air flowing through the second air duct 310 is accelerated and a low pressure area is formed at the air outlet of the second air duct 310, thereby increasing the lift. By optimizing the shape and angle of the guide plate, the resistance of the airflow passing through the guide plate can be reduced, and the lift effect can be enhanced. The design of the guide plate directly affects the distribution and speed of the airflow.

[0044] Preferably, the aerostat 100 further includes a mooring portion 500 for towing the aerostat 200 and providing a force opposite to the lift and wind resistance. The mooring portion 500 can be connected to the aerostat 200 via a mooring cable, so that the aerostat 200 can be relatively stably maintained in a predetermined area under complex wind conditions.

[0045] Preferably, the lift structure for the aerostat 100 of the present invention may further include an angle of attack adjustment mechanism 650 of the annular wing 300 , which is used to adjust the absolute angle of attack of the annular wing 300 according to the command of the control system 600 .

[0046] Preferably, the absolute angle of attack of the annular wing 300 is adjustable, and the adjustment method includes adjusting the posture of the floating body 200. Preferably, the posture of the floating body 200 can be regulated by the angle of attack adjustment mechanism 650, wherein the angle of attack adjustment mechanism 650 can be connected to different positions of the floating body by means of a connecting rope, etc., so that the posture of the floating body 200 is deflected by retracting and releasing the corresponding connecting rope, thereby adjusting the absolute angle of attack of the annular wing 300.

[0047] Preferably, the attitude of the floating body 200 can be adjusted by real-time monitoring of wind speed changes and the current attitude of the floating body 200 to calculate an attitude control scheme, and then the angle of attack adjustment mechanism 650 can be used to adjust the connecting rope based on the attitude control scheme. Further, the angle of attack adjustment mechanism 650 can be arranged at the end of the mooring cable of the mooring part 500.

[0048] Preferably, if Figure 5As shown, the annular wing 300 is usually located in the rear half of the floating body 200, which is determined based on the incoming flow direction. Usually, the part closer to the incoming flow direction is the front half (i.e., the windward side), and the part farther away from the incoming flow direction is the rear half (i.e., the leeward side). On this basis, since the design of the annular wing 300 is derived from a three-dimensional structure formed by rotating a two-dimensional airfoil along an axis, this structure has the following unique performance in aerodynamics: when the incoming flow direction is at an angle with the axis of the annular wing (i.e., there is an absolute angle of attack of a certain angle), the annular wing 300 can effectively capture the airflow and generate significant aerodynamic lift. This is because when the airflow flows through the annular wing 300, the shape of the annular wing 300 causes the airflow to accelerate above the annular wing 300, while it is relatively slow below. According to the Bernoulli principle, the change in airflow speed will cause a pressure difference, thereby forming a low-pressure area above the annular wing 300 to generate aerodynamic lift. Furthermore, the lift center of the annular wing 300 is usually located at a position biased toward the rear half of the reference point of the airborne body 200, which means that the relative positional relationship between the lift action point and the center of gravity will affect the attitude and stability of the airborne body 200. Specifically, under the action of aerodynamic lift, the attitude of the airborne body 200 will tend to deviate from its initial equilibrium state, and based on the relatively rearward lift center, a restoring moment that always tends to push the airborne body 200 back to the right position is formed, prompting the airborne body 200 to return to the upright state. At this time, the aerodynamic lift and the restoring moment disappear, and the airborne body 200 can maintain the righting state facing the wind, so as to form a "sealing effect" that can effectively maintain the stability of the airship. Preferably, the attitude of the airborne body 200 can also be adjusted based on the "sealing effect", thereby adjusting the absolute angle of attack of the annular wing 300. Further preferably, since the structure of the combination of the floating body 200 and the annular wing 300 of the present invention is a rotating body, it can achieve omnidirectional stability based on the "sealing effect" for any deviation from the incoming flow direction (ie, pitch, yaw).

[0049] Preferably, the fixing parts of the floating body 200 and the annular wing 300 can be configured in the form of a fixing bracket, which is connected to the outer wall of the floating body 200 by bolts, and the clamps and connecting rods ensure that the annular wing 300 does not move or deform during the force application process.

[0050] Preferably, the areas occupied by the first air duct 230 and the second air duct 310 are adjustable, especially dynamically adjustable. This adjustability can dynamically adjust the air duct area according to changes in the external environment and optimize the flow characteristics of the airflow.

[0051] Preferably, a ducted generator 400 is disposed radially inwardly in the floating body 200, and the ducted generator 400 is surrounded by the floating body 200. In other words, the first wind duct 230 can be defined by the ducted generator 400. This design allows wind energy to be effectively utilized, thereby improving energy utilization efficiency.

[0052] Preferably, the opening area of ​​the air inlet of the first air duct 230 in the form of a reduced air inlet and an enlarged air outlet, a trumpet shape from large to small, or a roughly hollow cylindrical shape is smaller than the opening area of ​​the air outlet, so that a throat with a minimum radial dimension can be formed in the first air duct 230, wherein the generator assembly of the ducted generator 400 can be arranged in the throat or in the vicinity thereof, so that wind energy can be captured and converted in the area with the highest wind speed in the first air duct 230. Preferably, when observed along the airflow flow direction of the first air duct 230, an outlet cross-sectional area adjustment unit 660 for adjusting the outlet area of ​​the first air duct 230 can be arranged downstream of the generator assembly to control the strength of the axial airflow passing through the first air duct 230. Preferably, the outlet cross-sectional area adjustment unit 660 can be configured as any mechanism capable of adjusting the outlet area of ​​the first air duct 230.

[0053] Preferably, the second air duct 310 is formed between the annular wing 300 and the airborne body 200, and the arrangement of the second air duct 310 can enhance the diffusion effect of the airflow and improve the lift efficiency. This design can reduce wind resistance while increasing lift, so that the airship 100 can work stably at higher wind speeds.

[0054] Preferably, if Figure 6 As shown, a middle buffer chamber 220 is provided inside the floating body 200, and the middle buffer chamber 220 is filled with a first gas 221. The first gas 221 is of a different type from the light gas 211 in the gas storage chamber 210 in the floating body 200, and the pressure is also different; and the filling methods of the two may also be different in time and / or position.

[0055] Preferably, since the light gas 211 may leak slightly during the long-term flight of the aerostat 100, the aerostat 200 of the present invention is filled with a first gas 221 of a predetermined pressure in the intermediate buffer chamber 220 to form a pressure different from the atmospheric pressure, thereby forming a pressure gradient on the path from the inside of the aerostat 200 to the atmosphere. Furthermore, by dynamically adjusting the shape of the outer wall of the aerostat 200, the shape of the outer wall of the aerostat 200 facing the annular wing 300 can be changed, especially by adjusting the degree of bulge to narrow or widen the second air duct 310, thereby changing the flow rate of the second air duct 310, thereby changing the lift. It can be seen that the design of the intermediate buffer chamber 220 can adjust the shape and structure of the second air duct 310.

[0056] In addition, the leaked light gas 211 will be mixed into the first gas 221 in the intermediate buffer chamber 220. Other equipment of the aerostat 100 can separate the mixed gas mixed with the light gas 211 and the first gas 221 by using the principle of phase change, so that the collected light gas 211 can be recovered, retained or sent back, which not only helps to optimize the airflow state in the second air duct 310, but also maintains or improves the lift of the aerostat 100.

[0057] Preferably, the gas storage chamber 210 and the intermediate buffer chamber 220 are inflated and pressure-regulated by different gas-filling units 610 and pressure-regulating units 620. Further, the gas-filling unit 610 is used to fill the gas storage chamber 210 and the intermediate buffer chamber 220 with gas, and the pressure-regulating unit 620 is used to regulate the gas pressure in the gas storage chamber 210 and the intermediate buffer chamber 220, wherein the gas-filling unit 610 and the pressure-regulating unit 620 can be communicatively connected to the control system 600.

[0058] Preferably, based on the inflation and pressure regulation of the air filling unit 610 and the pressure regulating unit 620, the outer diameter size in the area of ​​the floating body 200 can be adjusted jointly or independently to achieve control of the relative position and shape of the annular wing 300, thereby changing the structure, size and shape of the first air duct 230 and / or the second air duct 310.

[0059] In order to achieve effective regulation of the second air duct 310, dynamic adjustment can be performed based on a variety of monitoring data, including airflow velocity and pressure sensors to monitor the flow velocity and pressure changes of the gas in the second air duct 310 and provide real-time feedback on the airflow status; temperature sensors to monitor the temperature of the gas in the intermediate buffer chamber 220 and the air storage chamber 210 to determine the gas status and efficiency; lift sensors to detect the actual lift of the airship 100 and provide timely feedback on lift changes; tilt sensors to monitor the posture of the airship 100 to ensure stability during flight; and environmental parameter sensors to monitor the external environment (such as wind speed, air pressure, temperature, etc.) so as to adjust the internal airflow status in a timely manner.

[0060] Preferably, if Figure 7 As shown, the control system 600 can adjust the output of the air filling unit 610 and the pressure regulating unit 620 based on at least part of the above-mentioned monitoring data to maintain the target lift and airflow state, or use a model predictive control method to use an airflow dynamics model to predict the impact of different adjustment methods on lift, thereby selecting the best adjustment strategy.

[0061] Through the optimization of the above-mentioned adjustment method, the control system 600 can adjust the lift in real time according to the flight state and environmental changes to improve the flight efficiency; it also enhances the navigation stability. Through the precise adjustment of the second air duct 310, it can effectively reduce the vibration of the airship 100 during the flight and maintain a stable navigation posture; and realize the recycling of the light gas 211. Through the treatment of the mixed gas, the recycling of the light gas 211 is completed, thereby continuously optimizing the performance of the airship 100, reducing energy consumption, and extending the life of the airship 100. In summary, the optimization of this adjustment method can not only improve the lift and navigation stability of the airship 100, but also effectively solve the leakage problem of the light gas 211 and realize the recycling of resources. In other words, by monitoring and adjusting the airflow state, it is possible to improve the lift while ensuring the collection and reuse of the light gas 211, achieving the dual effects of maximizing resource utilization and improving performance.

[0062] According to this embodiment of the present invention, by setting the intermediate buffer chamber 220 inside the floating body 200, a certain pressure gradient is formed to dynamically adjust the lift and effectively solve the leakage problem of the light gas 211, thereby providing better lift adjustment performance and navigation stability.

[0063] Preferably, the control system 600 is used to control the attitude, height and position of the aerostat 100, as well as the pressure of the air storage chamber 210 and the intermediate buffer chamber 220, so as to dynamically change the angle and speed of the airflow entering the first air duct 230 and / or the second air duct 310 to achieve lift adjustment, thereby achieving efficient and adaptable flight performance. Further, the control system 600 may include a sensor array 630 and a feedback control logic 640, and the state of the aerostat 100 may be monitored in real time through the sensor array 630, and the pressure of the air storage chamber 210 and the intermediate buffer chamber 220, as well as the absolute angle of attack of the annular wing 300 may be adjusted through the feedback control logic 640 to achieve dynamic adjustment of lift and optimization of flight performance.

[0064] Preferably, the lift structure core formed by the airborne body 200 and the annular wing 300 can adapt to different wind speeds and wind directions, and optimize the flow characteristics of the airflow by dynamically adjusting the geometric shapes of the first air duct 230 and the second air duct 310. This design can ensure the stable operation of the airship 100 under complex wind conditions and effectively improve the utilization rate of wind energy.

[0065] Preferably, the design of the airship body 200 and the annular wing 300 can work together, and through dynamic adjustment and optimization, maintain efficient operation under different wind conditions, and contribute to the performance improvement of the wind power generation system. This design optimizes the performance of the wind power generation system to the extreme, so that the airship 100 can operate efficiently under various wind conditions.

[0066] The aerostat 100 of the present invention realizes efficient generation and precise regulation of lift through a unique structure of the aerostat body 200 and the annular wing 300 , as well as a complex pressure gradient regulation mechanism, thereby greatly improving the flight performance of the aerostat 100 .

[0067] Example 2

[0068] This embodiment is a further improvement on Embodiment 1, and some repeated contents will not be repeated here.

[0069] The present invention also discloses a buoyancy adjustment method, in particular, a buoyancy adjustment method for a high-altitude wind power generation system, wherein the high-altitude wind power generation system includes a floating body 200 made of a lightweight flexible material and a lift structure jointly constituted by an annular wing 300, wherein the floating body 200 is located radially inside the annular wing 300 and there is a gap between the annular wing 300, thereby when the floating body 200 forms an aerodynamic hollow cylindrical body, the annular wing 300 surrounds the aerodynamic hollow cylindrical body from its radial outside, and the lift of the floating body 200 is adjusted by adjusting the absolute angle of attack of the annular wing 300 in the lift structure jointly formed by the annular wing 300 and the floating body 200, thereby adjusting the buoyancy of the high-altitude wind power generation system.

[0070] Preferably, the radial inner wall of the annular wing 300 and the radial outer wall of the floating body 200 jointly form a second air duct 310 in the interval area, the area of ​​the second air duct 310 is larger than the area of ​​the first air duct 230, and the second air duct 310 is arranged in an ejection diffusion manner so that the lift provided is much greater than the resistance it brings, thereby changing the buoyancy. Preferably, the ejection diffusion effect of the second air duct 310 can be achieved or further enhanced by a guide plate arranged inside or near the second air duct 310. Preferably, the arrangement of the guide plate can be a plurality of slats arranged side by side, or evenly distributed on the inner wall of the second air duct 310 in an annular structure, wherein, in the case of a plurality of guide plates arranged side by side, they can be connected by a support rod or a frame to keep their relative positions unchanged, thereby forming an integral guide system. Preferably, the guide plate can be designed as an adjustable angle structure so that it can be adjusted in real time according to the change of airflow, thereby optimizing the aerodynamic performance. Preferably, the guide plate can be made of a lightweight and high-strength material, such as a composite material or an aluminum alloy, to ensure its stability and durability in a high-altitude environment. Preferably, the guide plate can be designed to be a gradient shape, with a wider front portion and a gradually narrower rear portion, to form a better airflow guiding effect, or an airfoil structure can be used to improve aerodynamic efficiency and reduce airflow resistance. The guide plate forms an ejection effect by changing the airflow path, so that the air flowing through the second air duct 310 is accelerated, and a low-pressure area is formed at the air outlet of the second air duct 310, thereby increasing lift. By optimizing the shape and angle of the guide plate, the resistance of the airflow passing through the guide plate can be reduced, and the lift effect can be enhanced. The design of the guide plate directly affects the distribution and speed of the airflow.

[0071] Preferably, the floating body 200 is connected to the ground facilities through a mooring part 500, and the mooring part 500 is used to tow the floating body 200 and provide a force opposite to its lift and wind resistance, thereby changing the aerial position of the floating body 200 by changing the force that has a mutual relationship with the buoyancy.

[0072] Preferably, the floating body 200 is provided with an internal chamber for adjusting the buoyancy of the high-altitude wind power generation system, wherein the buoyancy of the high-altitude wind power generation system is dynamically adjusted according to the lift, drag and / or the force provided accordingly by the mooring part 500.

[0073] Preferably, the high-altitude wind power generation system further includes a lift monitoring device for the floating body 200, wherein the lift monitoring device is capable of monitoring the change of lift in real time, and automatically adjusting the absolute angle of attack of the annular wing 300 and / or the amount of gas in the internal chamber of the floating body 200 according to the monitoring results to maintain the required buoyancy.

[0074] Preferably, an intermediate buffer chamber 220 filled with a first gas 221 is provided in the floating body 200, and the intermediate buffer chamber 220 serves as an internal chamber for adjusting buoyancy. Preferably, the charging of the first gas 221 and the charging of the light gas 211 are different in time and / or position, wherein the design of the intermediate buffer chamber 220 allows the outer diameter of the floating body 200 to be precisely controlled by adjusting the pressure and volume of the first gas 221, thereby optimizing the airflow state of the second air duct 310. Further preferably, the injection and discharge of the first gas 221 are dynamically adjusted as needed to adjust the outermost wall thickness of the floating body 200, thereby changing the outer diameter.

[0075] Preferably, the selection and filling pressure of the first gas 221 are optimized according to the lift requirements of the floating body 200 under different altitudes and wind speed conditions, so as to adjust the lift according to environmental parameters.

[0076] Preferably, a plurality of independently sealed air storage chambers 210 are provided inside the floating body 200, and these air storage chambers 210 are designed to carry gases lighter than air, wherein the intermediate buffer chamber 220 is independently sealed from other air storage chambers 210 of the floating body 200 to prevent gas mixing and ensure the accuracy and safety of buoyancy adjustment.

[0077] Preferably, when the light gas 211 in the gas storage chamber 210 inside the floating body 200 leaks, the light gas 211 will be mixed into the first gas 221 in the intermediate buffer chamber 220, and the collected light gas 211 can be recovered, retained or returned by other equipment of the high-altitude wind power generation system.

[0078] Preferably, the air filling unit 610 and the pressure regulating unit 620 connected to the intermediate buffer chamber 220 can be designed to quickly respond to the control signal sent by the control system 600, so as to quickly adjust the outer diameter of the floating body 200 when necessary to adapt to the changes in wind speed and wind direction. Preferably, the control system 600 equipped with the high-altitude wind power generation system can be used to control the attitude, height and position of the floating body 200, and can also be used to control the pressure of the air storage chamber 210 and the intermediate buffer chamber 220 in the floating body 200.

[0079] Preferably, the control system 600 is capable of dynamically changing the angle and speed of the airflow entering the second air duct 310 , which is achieved by jointly or independently adjusting the pressures of the air storage chamber 210 and the intermediate buffer chamber 220 in the area of ​​the floating body 200 .

[0080] Preferably, the control system 600 further includes a fault detection unit and a fault-tolerant unit, so that when the control system 600 detects or an abnormality occurs, the floating body 200 of the high-altitude wind power generation system can safely perform an emergency landing or implement other safety measures.

[0081] Preferably, a fault detection unit and a fault-tolerant unit are provided in the control system 600 to enhance the safety and reliability of the system. The fault detection unit adopts a variety of sensor data fusion technologies, and through real-time monitoring of various key parameters of the aerostat 100, such as airflow velocity, pressure, temperature, lift and power supply status, etc., uses advanced data analysis algorithms, such as Kalman filtering or neural networks, to quickly identify and judge abnormal conditions. When any abnormal situation is detected, the fault detection unit will immediately generate an alarm. The fault-tolerant unit is responsible for taking countermeasures immediately when a fault occurs to ensure the stability and safety of the aerostat 100. Specifically, the fault-tolerant unit can ensure that the system can still operate effectively when key components fail through redundant system design, such as backup sensors or actuators. In addition, the fault-tolerant unit can also dynamically adjust the flight mode of the aerostat 100, control the distribution of airflow and lift, and even start the emergency landing procedure to ensure that the aerostat 100 can land safely or perform other safety measures. By combining fault detection with fault tolerance technology, the control system 600 is able to quickly respond and execute appropriate safety strategies when faced with potential faults, thereby significantly improving the survivability and reliability of the aerostat 100 in complex and uncertain environments.

[0082] It should be noted that the above-mentioned specific embodiments are exemplary, and those skilled in the art can come up with various solutions inspired by the disclosure of the present invention, and these solutions also belong to the disclosure scope of the present invention and fall within the protection scope of the present invention. Those skilled in the art should understand that the present invention specification and its drawings are illustrative and do not constitute a limitation of the claims. The scope of protection of the present invention is defined by the claims and their equivalents. The present invention specification contains multiple inventive concepts, such as "preferably" or "according to a preferred embodiment", which means that the corresponding paragraph discloses an independent concept, and the applicant reserves the right to file a divisional application based on each inventive concept. Throughout the text, the features guided by "preferably" are only an optional method and should not be understood as a must-have setting. Therefore, the applicant reserves the right to abandon or delete the relevant preferred features at any time.

Claims

1. A lifting structure for an aerostat (100), the aerostat (100) comprising: A floating body (200) made of a light and flexible material, the inner surface of which defines a first air duct (230), wherein the first air duct (230) is in the form of a reduced air inlet and an enlarged air outlet in an axial cross-sectional view, a trumpet shape from large to small, or a generally hollow cylindrical shape; It is characterized in that The lift structure is composed of a floating body (200) located radially inside and an annular wing (300) fixed thereon at a distance therefrom, wherein the annular wing (300) is located radially outside the floating body (200) and is spaced apart from the floating body (200), and in the spaced apart area, a second air duct (310) is formed by the radial inner wall of the annular wing (300) and the radial outer wall of the floating body (200) opposite thereto, wherein the area of ​​the second air duct (310) is larger than the area occupied by the first air duct (230), and the second air duct (310) is arranged in an induced diffusion manner to provide a lift force that is much larger than the resistance caused by it.

2. The lifting structure according to claim 1, characterized in that: The annular wing (300) adopts a multi-stage structure, and the absolute angle of attack of the annular wing (300) is adjustable, and the adjustment method includes adjusting the posture of the floating body (200), wherein the posture of the floating body (200) can be passively adjusted by an external angle of attack adjustment mechanism (650), and / or autonomously adjusted by using the aerodynamic lift generated by the pressure difference formed on the upper and lower sides of the annular wing (300) by the airflow flowing through the annular wing (300).

3. The lifting structure according to claim 1 or 2, characterized in that: The areas occupied by the first air duct (230) and the second air duct (310) can be adjusted independently of each other, wherein the lift structure can adapt to different wind speeds and wind directions to optimize the flow characteristics of the airflow by dynamically adjusting the geometric shapes of the first air duct (230) and the second air duct (310).

4. The lift structure according to any one of claims 1 to 3, characterized in that: A plurality of mutually independently sealed gas storage chambers (210) for storing gas lighter than air are arranged in the floating body (200). The gas storage chambers (210) are inflated in a controlled pressure manner through a dedicated inflation device to achieve buoyancy adjustment of the floating body (200).

5. The lift structure according to any one of claims 1 to 4, characterized in that: An intermediate buffer chamber (220) is provided in the airship body (200), and the intermediate buffer chamber (220) is filled with a first gas (221). The first gas (221) and the light gas (211) in the gas storage chamber (210) are different gases from each other. The intermediate buffer chamber (220) is used to form multiple pressure gradients in the light gas (211) leakage path in the direction from the inside to the outside of the airship (100).

6. The lift structure according to any one of claims 1 to 5, characterized in that: The light gas (211) in the floating body (200) and the first gas (221) in the intermediate buffer chamber (220) are charged and pressure-regulated by different gas filling units (610) and pressure regulating units (620), thereby jointly or independently adjusting the outer diameter size in the area of ​​the floating body (200) to achieve control of the relative position and shape of the annular wing (300), thereby changing the structure, size and shape of the first air duct (230) and / or the second air duct (310).

7. The lift structure according to any one of claims 1 to 6, characterized in that: The lift structure includes a control system (600) that not only controls the attitude, altitude and position of the aerostat (100), but is also capable of controlling the pressure of the air storage chamber (210) and the intermediate buffer chamber (220), thereby dynamically changing the angle and speed of the airflow entering the first air duct (230) and / or the second air duct (310) to achieve lift regulation, thereby achieving efficient and adaptable flight performance.

8. The lift structure according to any one of claims 1 to 7, characterized in that: The control system (600) comprises a sensor array (630) and feedback control logic (640) for real-time monitoring and adjusting the internal air pressure of the aerostat (100) and the airflow conditions of the first air duct (230) and / or the second air duct (310), thereby ensuring the stability and efficient energy utilization of the aerostat (100) in a complex environment.

9. A buoyancy adjustment method, applicable to a high-altitude wind power generation system, the high-altitude wind power generation system comprising a lift structure composed of a floating body (200) made of a light and flexible material and an annular wing (300), wherein: The floating body (200) is located radially inside the annular wing (300) and there is a gap between the floating body (200) and the annular wing (300), so that when the floating body (200) forms an aerodynamic hollow cylindrical body, the annular wing (300) surrounds the aerodynamic hollow cylindrical body from its radial outside. It is characterized in that the lift of the floating body (200) is adjusted by adjusting the absolute angle of attack of the annular wing (300) in the lift structure formed by the annular wing (300) and the floating body (200), thereby adjusting the buoyancy of the high-altitude wind power generation system.

10. The buoyancy adjustment method according to claim 9, characterized in that: The radial inner wall of the annular wing (300) and the radial outer wall of the floating body (200) together form a second air duct (310) in the interval area. The area of ​​the second air duct (310) is larger than that of the first air duct (230), and the second air duct (310) is arranged in an induced diffusion manner so that the lift provided is much greater than the resistance it brings, thereby changing the buoyancy.

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