142 results about "Aerostat" patented technology

The invention discloses an anchoring device and an aerostat anchoring and releasing method. The anchoring device comprises an anchoring tower body, a nose cone, a guide assembly and a winding assembly. The nose cone is arranged at the top of the anchoring tower body through the mounting frame, is located on the mounting frame and can be opened and closed relative to the mounting frame so as to be switched between a release state and a locking state; the guide assembly comprises a rail and a sliding block arranged on the rail in a sliding mode, and the rail inclines downwards from the end, provided with the nose cone, of the installation frame and extends to the bottom of the anchoring tower body to form a triangular structure with the anchoring tower body. The winding assembly comprises a pull rope and a locking block fixed to the pull rope, and the pull rope is connected to the two ends of the sliding block so as to drive the sliding block to reciprocate along the track. A driving channel is formed in the center of the nose cone, the pull rope penetrates through the driving channel, and the locking block can move along the track along with movement of the pull rope and gradually enter the driving channel to push the nose cone to enable the nose cone to be converted into a locking state from a releasing state so as to lock the aerostat.

The invention relates to the technical field of aerostats, solves the technical problem that a traditional CD-ROM device control design method is large in application range limitation, and particularly relates to a control method of a floating device and an autonomously-moving floating device.The control method comprises the steps that an independent air chamber is filled with low-density air, and the floating device autonomously floats in air; and establishing a control equation for controlling the autonomous movement of the floating device by controlling the illumination intensity, placing the floating device floating in the air in the illumination area, and autonomously controlling the floating device to advance according to the preset direction based on the control equation. The optical drive control system is simplified by utilizing the deformation characteristic of the liquid crystal elastomer, so that the light weight of the floating device is realized, fuel and a controller do not need to be carried, and long-time autonomous flight can be realized by utilizing photo-thermal energy so as to adapt to complex and changeable application scenes.

The invention relates to the technical field of aerostat control, and discloses an aerostat control method and system, and the method comprises the steps: S1, collecting the internal state data, external environment data and environment parameters of an aerostat through a multi-source sensor; s2, processing the data acquired in the S1, and constructing a state and disturbance observer to obtain an aerostat state estimation value and an environmental wind disturbance estimation value; s3, based on the state estimation value and the wind disturbance estimation value of the aerostat, a self-adaptive control algorithm is adopted, a control instruction used for controlling the height and the horizontal position of the aerostat is generated, and the control instruction comprises a feedforward component used for actively compensating wind disturbance; and S4, distributing the control instruction to a channel power system of the aerostat and executing the control instruction. An integrated control architecture with state estimation, disturbance observation and adaptive control capabilities is constructed, three technical bottlenecks of weak control robustness, poor anti-interference capability and low intelligent level of a traditional aerostat in outdoor application are effectively solved, and the positioning precision and stability are improved.

The invention relates to the technical field of aerostat transportation, and provides container type aerostat capsule loading and transporting equipment and a loading and transporting method.The container type aerostat capsule loading and transporting equipment comprises a box used for being arranged on transportation equipment, and a containing space with an opening formed in one side is formed in the box; the folding guide rail comprises a first guide rail and a second guide rail, the first guide rail is rotatably connected with the second guide rail, and the first guide rail is arranged in the accommodating space; and the lifting mechanism is used for lifting the aerostat capsule body. The container type aerostat capsule loading and transporting equipment provided by the invention has the advantage of large volume of a conventional loading and transporting container, can meet the loading and transporting and storage requirements at the same time, and does not need additional storage facilities. And through cooperation of the lifting mechanism and the folding guide rail, collision, friction and the like of the bag body in the carrying process are reduced, the bag body is effectively protected, and the damage possibility of the bag body is reduced. Meanwhile, the equipment further has a semi-automatic loading and transporting function, manual operation links are reduced, and labor cost input is reduced.

According to one aspect, an aerostat may include an inflatable structure including a balloon and a neck collectively defining a volume, a valve including a funnel supportable in the neck and defining a first opening, a second opening, and a cavity therebetween, the cavity in fluid communication with the volume via the second opening, a stem defining a channel at least partially outside of the inflatable structure, a stopper disposed in the cavity, a rod coupled to the stopper and at least partially disposed in the channel, and an actuator electrically actuatable to move the rod relative to the channel such that the stopper moves relative to the first opening of the cavity to control fluid communication between the volume and the channel via the cavity.

The invention belongs to the technical field of agricultural engineering and intellectualization, and particularly relates to a buoyancy air bag rapid adjusting device and a wind resistance cooperative control method thereof.The buoyancy air bag rapid adjusting device comprises a buoyancy providing original module and a flight control module, the buoyancy providing original module comprises an inner balloon, an outer balloon and a hot-air balloon, and the inner cambered surface of the inner balloon and the inner cambered surface of the outer balloon are provided with inflation cavities; a rope is connected to the bottoms of the outer cambered surfaces of the inner and outer balloons and the hot-air balloon, one end of the rope is connected with a frame in a penetrating manner, and a burner assembly is fixedly mounted on the upper surface of the frame; wind power is sensed in real time through an anemograph and a monitoring sensor, in combination with cooperative response of a flight control module, a buoyancy module and a connection adjusting module, measures of posture fine adjustment, height avoidance and safe landing are adopted in the gentle breeze, stroke and strong wind environments, so that the device keeps precision operation below multiple wind levels, safe risk avoiding is achieved in the strong wind, and the safety and reliability of the device are improved. The problems that a traditional aerostat is poor in wind resistance and prone to being out of control are solved.

The invention discloses an inflatable aerial carrying platform and a flying method, and relates to the field of aerostats, and the key point of the technical scheme is that the inflatable aerial carrying platform comprises a platform main body cabin with an annular structure, a spherical auxiliary balance cabin arranged above the platform main body cabin and connected through a cable, and a balance control system. A plurality of groups of partition sheets are arranged in the platform main body cabin, the platform main body cabin is uniformly divided into a plurality of independent air chambers which are symmetrically arranged, and each air chamber is provided with an independent inflation and deflation hole, so that fine air pressure regulation and control and high-altitude attitude stability are realized. The auxiliary balance cabins form a composite buoyancy system through upper and lower layered layout, and the gravity center control and anti-instability capacity of the whole platform under load fluctuation or airflow disturbance is improved. According to the invention, the fault resistance, the safety and the pneumatic stability of the aerial platform are obviously improved.

The present invention relates to the field of aerostat technology, resolving the technical issues of traditional optical drive control design methods, which have significant limitations on their scope of application. In particular, the invention relates to a control method for an aerostat and an autonomously moving aerostat. The control method includes filling an independent air chamber with a low-density gas, causing the aerostat to float autonomously in the air; establishing a control equation for controlling the autonomous motion of the aerostat by controlling light intensity; placing the aerostat floating in the air within an illuminated area; and autonomously controlling the aerostat to advance in a predetermined direction based on the control equation. The present invention utilizes the deformation properties of liquid crystal elastomers to simplify the optical drive control system, thereby achieving a lightweight aerostat without the need for fuel or a controller. The aerostat can utilize photothermal energy to achieve long-term autonomous flight, adapting to complex and diverse application scenarios.

The invention discloses an energy cabin frame, an energy cabin system and a near space aerostat with the energy cabin frame, the energy cabin frame is used for the near space aerostat and comprises a transition frame, the transition frame is arranged on a sphere of the near space aerostat, the transition frame is located on the side, in the first direction, of the sphere, and the transition frame comprises a plurality of first pipes; and the main body is arranged on the side, away from the sphere, of the transition frame, the main body comprises a plurality of second pipes, the first pipes and the second pipes are three-dimensional multidirectional braided pipes, and the three-dimensional multidirectional braided pipes are formed by braiding and curing carbon fiber composite materials. According to the energy cabin frame, the mechanical performance and functional performance of the transition frame and the main body can be optimized, the structural efficiency of the transition frame and the main body is improved, the stress level of the transition frame and the main body is improved, the reliability and safety of the energy cabin frame are improved, and the weight of the transition frame and the main body can be reduced; and the lightweight design of the energy cabin frame is facilitated.

The invention discloses an aerostat with a built-in pressure adjusting structure, a wind power generation system and a control method, the aerostat of one embodiment comprises an auxiliary air bag, the pressure adjusting structure arranged in the auxiliary air bag and a pressure control structure arranged outside the auxiliary air bag, the pressure adjusting structure comprises an air duct pipe, a first valve arranged at one end of the air duct pipe, a second valve arranged at the other end of the air duct pipe and a fan arranged in the air duct pipe and located between the first valve and the second valve. The pressure control structure comprises a controller and a differential pressure sensor, and the controller is used for controlling the fan, the first valve and the second valve to exhaust or inflate the auxiliary air bag according to the air pressure, sensed by the differential pressure sensor, of the bag body. According to the embodiment, the pressure adjusting structure of the aerostat is integrally arranged in the auxiliary air bag, the beneficial effects of being compact in structure, good in air tightness and the like are achieved, the stability and reliability of the aerostat are remarkably improved, and the practical application value is achieved.

The embodiment of the application provides a ballast valve performance testing device and system to improve the accuracy of ballast valve performance testing, and relates to the technical field of aerostat. The ballast valve performance testing device provided by the embodiment of the application comprises a storage box, a receiving box and a driving assembly. The storage box forms a first accommodating cavity, the first accommodating cavity is used for accommodating materials, the first accommodating cavity has a feeding port and a discharging port, the discharging port is located below the feeding port, and the discharging port is used for arranging the ballast valve. The receiving box forms a second accommodating cavity, the second accommodating cavity has an opening, the opening is located on the lower side of the discharging port, so that the materials can enter the second accommodating cavity through the discharging port and the opening. The driving assembly is used for driving the receiving box to move, so that the opening can move to the upper side of the feeding port, and then the materials in the second accommodating cavity can enter the first accommodating cavity through the feeding port and the opening. The ballast valve performance testing device provided by the embodiment of the application is used for testing the performance of the ballast valve.

The application provides a floating transportation device, which comprises a capsule, a gas filled in the capsule, and the density of the gas is less than the density of air; a bearing structure connected with the capsule and capable of moving synchronously with the capsule to form a moving body; and at least one guide connected with the capsule and / or the bearing structure, which drives the capsule and / or the bearing structure to move. The application solves the problem that the prior art air transportation device cannot determine a flight route and has few applicable scenarios.

The embodiment of the invention provides an aerostat capsule and a capsule splicing method. The aerostat capsule body is formed by splicing a plurality of cutting pieces, the plurality of cutting pieces comprise a first cutting piece and a second cutting piece which are adjacent to each other, the first cutting piece comprises a first body part and a first bending part which is bent towards a first side, and the second cutting piece comprises a second body part and a second bending part which is bent towards a second side. The first bending part is located between the second bending part and the first body part, the second bending part is located between the first bending part and the second body part, and an orthographic projection overlapping area of each body part and each bending part forms a splicing area; a first adhesive layer is arranged between the second bending part and the first body part; a second adhesive layer is arranged between the first bending part and the second body part; the splicing area is provided with fixing pieces penetrating through the body parts and the bent parts, and through holes formed in the body parts and the bent parts of the fixing pieces are filled with the first adhesive layer and the second adhesive layer. According to the invention, the joint tensile strength and the sealing reliability are improved, and high-efficiency and low-cost processing is also realized.

The invention discloses a falling collision protection device, a task equipment module and an aerostat, and relates to the technical field of aerostats, the falling collision protection device comprises a mounting part, an air bag and a control unit, and the mounting part is provided with a containing cavity; the air bag can be contained in the containing cavity, and a gas generating agent is loaded in the air bag; the control unit is used for judging whether falling and collision protection is implemented or not, and when falling and collision protection is implemented, the gas generating agent is excited to generate protective gas, so that the air bag is unfolded under the action of pressure. According to the falling collision protection device, the solid sodium azide is instantaneously decomposed to generate nitrogen, so that the air bag is quickly unfolded before touching the ground, and the buffer failure caused by inflation delay of the compressed air cylinder is eliminated.

The invention provides an aerostat anti-drag capsule material aerodynamic characteristic test model and test method, and belongs to the technical field of aerostats, the aerostat anti-drag capsule material aerodynamic characteristic test model comprises a main body, a capsule material sleeve body and a tail boom connecting piece; the main body is streamline-shaped, and the tail section of the main body is provided with a tail wing; the bag material sleeve body is of a sleeve type structure and is attached to the outer surface of the main body in a covering mode through a detachable bonding layer. The capsule material sleeve body is formed by welding one or more capsule material sheets with different surface appearances; the bag body material sleeve body is composed of segmented structures in the axial direction of the main body, the segmented structures are welded and connected into a whole in the circumferential direction of the main body, and a connecting seam is formed in the circumferential direction so that the bag body material sleeve body can be opened and closed in the axial direction during assembly; the tail boom connecting piece is fixed to the tail section of the main body and used for supporting and installing a test model in a wind tunnel. According to the invention, the sleeve type wind tunnel test model which can be attached and can replace different capsule materials is constructed, so that the aerodynamic characteristics of the aerostat anti-drag capsule material under the wind tunnel condition can be truly and effectively tested.

The invention discloses an aerostat launching tower system used for integrated final assembly and flying of aerostats, the aerostat launching tower system comprises a tower body, a final assembly space is arranged in the tower body, a flying opening communicated with the final assembly space is formed in the top of the tower body, the aerostats are suitable for being assembled and inflated in the final assembly space, and the flying opening is communicated with the final assembly space. The air is released through the releasing opening; the position adjusting mechanism is arranged in the tower body and is configured to be used for adjusting the relative position of the aerostat and the tower body in the vertical direction and the relative rotation angle of the aerostat around the vertical axis; and the fixing device is configured to fix the aerostat in the general assembly space. According to the aerostat launching tower system, the influence of wind field changes on aerostat launching can be effectively reduced, and therefore the aerostat launching efficiency is effectively improved.

This invention proposes a method and apparatus for calibrating the volume of auxiliary airbags of an airship under different attitudes, comprising: an airbag body, an attitude adjustment mechanism, a ranging instrument, a pressure acquisition instrument, an attitude measurement instrument, a flow meter, and a data recording instrument. The airbag body includes a main airbag and several auxiliary airbags; the attitude adjustment mechanism is used to adjust the pitch and roll angles of the main airbag; the ranging instrument measures the distance from its location to the top of the corresponding auxiliary airbag; the pressure acquisition instrument measures the pressure difference between the inside of the main airbag and the outside atmosphere; the attitude measurement instrument measures the pitch and roll angles of the main airbag; the flow meter records the inflation volume of the main airbag in real time; and the data recording instrument records and stores the pitch and roll angles of the main airbag, as well as the distance values ​​measured by the ranging instrument, in real time. This invention can accurately measure the effective volume of each auxiliary airbag under actual working conditions and quickly calibrate the relationship between the volume of each auxiliary airbag and the pitch, roll, and ranging distances.

The embodiment of the invention provides an aerostat, an aerostat air operation control system and a wind power generation device, and the aerostat comprises an aerostat body which is in a streamline design, and the two ends of the aerostat body form a large head end and a small head end respectively; the steering part is arranged below the floating body, and the floating body can rotate around the steering part along with the change of the wind direction; the lifting force adjusting part is arranged above the floating body, the position of the lifting force adjusting part changes along with the change of the wind direction, and the lifting force adjusting part always has upward pulling force on the floating body. The lifting force adjusting part can adjust the pulling force on the floating body in real time according to the change of the wind force and direction, so that the floating body is always kept at a stable height and posture, meanwhile, the steering part enables the floating body to flexibly cope with the change of the wind direction, and the floating body is prevented from shaking or inclining due to the sudden change of the wind direction.

This application provides an airborne wind power generation system and its assembly method, relating to the field of airship assembly technology. The assembly method for the airborne wind power generation system includes the following steps: S1, at the assembly site, assembling system components into an intermediate body with the main airbag in a vertical orientation; S2, during or after the assembly of the intermediate body, filling at least one airbag component with buoyancy gas to generate net buoyancy in the intermediate body to assist subsequent assembly operations; S3, with the assistance of net buoyancy, completing the installation of the remaining system components to assemble the power generation system; S4, adjusting the attitude of the power generation system from a vertical orientation to a horizontal operating orientation. This application solves the problems of low efficiency and high risk in assembling ultra-large airborne wind power generation systems in field environments using traditional flat-lying assembly methods, achieving a more efficient, safer, and adaptable airborne wind power generation system assembly method for complex field environments.

The application discloses a kind of built-in pressure regulating structure's aerostat, wind power generation system and control method, wherein the aerostat of an embodiment includes auxiliary air bag, pressure regulating structure arranged inside auxiliary air bag, and pressure control structure arranged outside auxiliary air bag, wherein, pressure regulating structure includes air duct pipe, first valve arranged at one end of air duct pipe, second valve arranged at the other end of air duct pipe, and fan arranged in air duct pipe between first valve and second valve;Pressure control structure includes controller and differential pressure sensor, and controller is used to control fan, first valve and second valve to exhaust or inflate auxiliary air bag according to the air pressure sensed by differential pressure sensor.The embodiment provided by the application has the characteristics of compact structure and good air tightness by integrating the pressure regulating structure of the aerostat inside the auxiliary air bag, significantly improves the stability and reliability of the aerostat, and has practical application value.

The invention discloses a stratospheric aerostat pressure difference control method, which belongs to the field of flight control, is used for aerostat pressure difference control, and comprises the following steps: starting an aerostat pressure difference control program, detecting the internal temperature condition of an aerostat caused by external environment change, judging whether the aerostat is in a normal environment or not, if so, changing the volume of an internal phase change air bag, and if not, judging that the aerostat is in the normal environment. If yes, the internal pressure of the aerostat changes, then whether the pressure difference is within the safety range or not is judged, if not, the volumes of the internal and external phase change air bags cooperatively change, the internal pressure change and the height change of the aerostat enable the external atmospheric pressure of the aerostat to change, and then whether the pressure difference is within the safety range or not is judged; and judging whether the pressure difference is within a safe range, if not, returning to detect the internal temperature condition of the aerostat caused by the change of the external environment, and if so, ending the pressure difference control method. Under the normal day and night alternation condition, the volume of the internal phase change air bag is adjusted, the internal pressure of the aerostat is adjusted, and the internal and external pressure difference of the stratospheric aerostat is always kept within a safe range.

The invention relates to the technical field of space communication, in particular to an implementation method for constructing a high-altitude free space communication link system based on a mooring floating platform, and the method specifically comprises the steps: setting a ground base station on the ground, and carrying out the height hierarchical division of the working height of the mooring floating platform; deploying a plurality of groups of mooring floating platforms on different height levels; constructing an optical fiber link between the mooring floating platform and the ground base station; according to the height level sequence, multi-level free space communication links of multiple sets of mooring floating platforms are established in sequence; a high-rise mooring floating platform is connected with a space-based laser communication node, and a multi-level ground-air-space integrated high-altitude free space communication path is formed. The problems that in the prior art, transmission loss of free space communication laser in the low-layer atmosphere is large, the influence of airflow and weather is large, and stability is poor are solved.

The utility model discloses an aerostat nose cone lock strength test device, which comprises a vertical loading device and a guiding device which are fixed on a heavy frame, a transverse loading device is arranged on the vertical loading device, the transverse loading device can move along the vertical direction under the driving of the vertical loading device, and the guiding device is arranged on the vertical loading device. The actuating cylinder in the transverse loading device can also move along a horizontal plane perpendicular to the axis direction of the nose cone lock test piece, the nose cone lock test piece is fixed on the heavy frame, the guide device is located below the nose cone lock test piece, and a pulley adapter plate in the guide device can move along a horizontal plane parallel to the axis of the nose cone lock test piece. And a guide pulley is arranged on the pulley adapter plate. The test device is convenient to install, can realize rapid and quantitative tensioning and fixing, and better simulates the boundary condition of the installation state of the test piece.

This invention discloses a lightweight monopole transmitting antenna for an aerostat. From the inside out, it comprises a central reinforcing filler made of multi-strand twisted lightweight reinforcing fibers, a binding layer made of polytetrafluoroethylene film, a non-metallic reinforcing layer woven from non-metallic reinforcing fibers, an inner sheath made of extruded polyethylene, a radiator layer woven from metal wires, and an outer sheath comprising a semi-conductive outer sheath and a metal-woven outer sheath. The semi-conductive and metal-woven outer sheaths have the same outer diameter and alternately cover the outside of the radiator layer. This invention offers advantages such as miniaturization, lightweight, corona resistance, high current resistance, and fatigue resistance, resulting in high reliability and practicality, meeting the requirements for rapid deployment of long-range very low frequency (VLF) communication systems using aerostats.

According to one aspect, a system for midair deployment of an aerostat may include an inflatable structure including a balloon at least partially defining a volume, a reaction vessel defining a chamber in fluid communication with the volume, a fuel package disposed in the chamber, the fuel package including a container and water-reactive aluminum, the container fluidically isolating the water-reactive aluminum from an environment of the chamber, and an actuator actuatable to release the water-reactive aluminum from the container into the environment of the chamber.

The invention discloses a push rod limiting circuit, a push rod limiting method, a push rod device and an aerostat, and relates to the technical field of push rod limiting. A first solid-state relay and a second solid-state relay of a solid-state relay control module are each provided with a control end and a controlled access; a first limit switch of the limit switch module is connected in series in a loop between the rectification power supply module and the control end of the first solid-state relay, and a second limit switch is connected in series in a loop between the rectification power supply module and the control end of the second solid-state relay; the PWM driving module is used for receiving PWM power supply and selectively supplying power to the push rod motor through a controlled access of the first solid-state relay and the second solid-state relay so as to control forward and reverse rotation and speed regulation of the push rod motor; according to the push rod limiting circuit, contactless switching of the solid-state relay is combined with PWM speed regulation, power supply of the motor is cut off instantaneously at the limiting position, meanwhile, mechanical abrasion, contact oxidation and electromagnetic interference are avoided, and long-service-life and high-reliability limiting under the high-altitude severe environment is achieved.

The application provides a kind of aerostat system, comprising: capsule, first gondola, second gondola and external equipment;External equipment is installed on the outer surface of the capsule;First gondola and second gondola are respectively hoisted on the lower surface of the capsule;External equipment is connected with first gondola and / or second gondola through shielded wire and external equipment, and magnetic ring is arranged at the connection of shielded wire and external equipment;First gondola and second gondola are both closed structure with metal shell;Grounded metal mesh is used to connect between first gondola and second gondola;Power supply equipment is installed in first gondola;Flight control equipment is installed in second gondola;Equipment cabinet in first gondola and second gondola is connected with gondola rack on gondola structure.The aerostat system provided by the application is designed from the whole, divides the aerostat system into multiple areas, different areas use targeted protection measures, and electromagnetic interference is avoided in all directions, which improves the reliability of the aerostat system.

This invention discloses a low-altitude unmanned aerial vehicle (UAV) all-domain monitoring and targeted jamming defense system. This invention relates to the field of UAV defense technology and includes an airship platform, a detection module, a jamming module, a decoy module, a control module, a power module, and a ground command center. The airship platform is a tethered balloon, and its pod integrates the core working units of the detection module, jamming module, decoy module, control module, and power module. The power module receives AC power from the ground via a tethered cable. This low-altitude UAV all-domain monitoring and targeted jamming defense system overcomes the inherent limitations of traditional ground-deployed defenses, effectively avoids communication blind spots caused by terrain and features, and upgrades from single-area protection to wide-range coverage. It can capture UAV signals at greater distances, allowing sufficient time for countermeasures, accurately distinguishing between compliant UAVs and illegal intrusion targets, avoiding misjudgments and accidental damage, and ensuring the normal operation of legitimate operations.

The invention relates to the technical field of aerostat ground support equipment, and discloses a jacking type short-distance transfer system and method for a mooring aerostat. The system comprises a ground anchoring device and a self-propelled ground flat car, the bottom of the ground anchoring device is provided with a standard connector and a lifting supporting mechanism with high-strength lifting supporting capacity, and the self-propelled ground flat car is provided with a butt joint locking mechanism and a universal driving wheel set which are matched. The ground anchoring device and the self-propelled ground flat car are rigidly fixed through a standardized connector and a butt joint locking mechanism, and integrated short-distance transfer of the mooring aerostat in the mooring keeping state is achieved. The semi-hanging type mooring device solves the technical problems that a traditional semi-hanging type mooring device is low in transfer efficiency, poor in maneuverability, high in safety risk and the like, has the advantages of being short in preparation time, flexible, safe, reliable, high in universality and the like, and is suitable for short-distance transfer scenes of large captive balloons between different stations and boats in a field.

The invention discloses an offshore wind power plant communication relay and edge calculation method, which comprises a plurality of aerostats deployed in an offshore wind power plant, each aerostat is provided with an edge calculation module, and the method comprises the following steps: sending preset configuration parameters to the plurality of aerostats, the preset configuration parameters comprising flight paths, flight heights and target task areas of the aerostats; and when the aerostat flies to the target task area according to the preset configuration parameters, a communication link establishment instruction is sent to the aerostat residing in the target task area, and communication links of the offshore wind turbine generator, the aerostat, the shore-based control center and the booster station control center are established. And the offshore wind turbine generator uploads the real-time operation data to the aerostat, and the aerostat outputs a processing result based on the real-time operation data and sends the processing result to the shore-based control center or the booster station control center. The timeliness and accuracy of operation monitoring and fault early warning are improved, the centralized monitoring capability and operation and maintenance efficiency of the offshore wind power plant are effectively improved, and good adaptability and expansibility are achieved.