170 results about "Aerostat" patented technology

The invention relates to a water-drop-shaped captive balloon high-altitude wind power generation system. The water-drop-shaped captive balloon and kite cloth carried by the water-drop-shaped captive balloon are used for generating lift force to drive a ground power generator to generate power. The lift force generation mechanism is that the windward side and the wind resistance are increased by adjusting the pitch angles of the aerostat and the bearing kite cloth, and the wind resistance is converted into cable tension to drive power generation. A V-shaped pulley expansion mode is adopted to uniformly distribute tension of main and auxiliary cables, so that bag damage caused by non-uniform stress in a posture adjusting process is avoided; the captive balloon is provided with an attitude controller, communicates with a ground control system through wireless data transmission, adjusts the take-up and pay-off speed of a main cable and an auxiliary cable to control the pitching angle to achieve lift force control, and greatly improves the power generation efficiency. The main cable power output winch drives a generator to generate electricity through a one-way bearing, and the input end is connected with a motor through a clutch to achieve cable recovery. The backpack kite cloth can be controlled to open and close through a small winch to increase and decrease wind resistance; lift force and wind resistance control is optimized, the power generation efficiency is improved, safety is enhanced, operation is simplified, and maintenance is convenient.

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 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 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 discloses a mooring type floating wind power generation device, and belongs to the technical field of wind power generation. The device comprises a first bag body, the peripheral surface of the first bag body is a rotary surface, and the diameter of the first bag body is gradually increased from front to back; the peripheral surface of the second capsule body is a rotary surface, the diameter of the second capsule body is gradually reduced from front to back, the second capsule body is arranged on the rear side of the first capsule body at intervals, and a crack is formed between the second capsule body and the first capsule body; the first ring wing sleeves the radial outer side of the crack; the radial outer side of the second bag body is sleeved with the second ring wing; and the contra-rotating fan blades comprise two fan blades with opposite rotating directions, each fan blade comprises a hub and a blade body connected to the hub, the hubs are located in the cracks, and at least part of the fan blades are located outside the cracks in the radial direction and located in the area defined by the first ring wings. According to the mooring type floating wind power generation device, the aerial high-density wind energy capturing capacity is considered, and meanwhile the aerodynamics and the aerial floating capacity of the aerostat are enhanced.

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 utility model relates to an impact-resistant low-altitude unmanned aerial vehicle interceptor and interception equipment, the interceptor comprises an interception net which can be unfolded to be in a vertical plane state perpendicular to the ground or approximately perpendicular to the ground, the interception net is formed by weaving ropes or flexible fabric, the interception net comprises at least two pull-up nodes and at least two lower nodes, the pull-up nodes are connected with an aerostat for providing buoyancy, the lower nodes are connected with an anchoring structure, and the low-altitude unmanned aerial vehicle interceptor is configured as follows: the number of the pull-up nodes is at least three, and the number of the lower nodes is also at least three; and / or the low-altitude unmanned aerial vehicle interceptor further comprises a protective net and / or a restraint rope matched with the intercepting net. The number of the pull-up nodes and the pull-down nodes is increased, or deformation of the interception net is limited through the protective net and the restraint ropes, the stability of the interception net can be improved, the deformation amplitude of the interception net when the interception net is collided by the low-altitude unmanned aerial vehicle is reduced, and therefore the continuously-attacked low-altitude unmanned aerial vehicle can be smoothly dealt with.

According to one aspect, a reactor for generating lifting gas may include a first port, a second port, a coupling releasably securable in fluid communication with an aerostat, and a tank including a base and a crown defining at least a portion of a chamber therebetween, the first port and the coupling each supported on the crown, the second port supported on the tank away from the crown, the chamber in fluid communication with each one of the first port, the second port, and the coupling, the chamber expandable between the crown and the base from an uninflated state to an inflated state and, with the tank in the inflated state, a maximum height of the chamber less than a maximum dimension of the base.

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 invention belongs to the technical field of aviation equipment, and discloses a clean energy silent cruise aerostat which comprises an aerostat body, a rectangular groove is formed in the bottom of the aerostat body, a rectangular frame is fixedly installed at the bottom of the aerostat body, a lifting mechanism is arranged in the rectangular frame, and the lifting mechanism is connected with the aerostat body. A buffer mechanism is arranged on the outer wall of the rectangular frame; through the design of a double-end motor and threaded connection, movement of the moving block and the supporting plate can be accurately controlled, it is ensured that the supporting plate stably and slowly stretches out in the descending process, particularly, the moving wheel assembly at the bottom of the supporting plate makes contact with the ground firstly, hard landing can be effectively avoided, impact force on the aerostat body is reduced, and the service life of the aerostat is prolonged. By means of the design of the multiple air bag rings, impact force in the descending process is effectively absorbed, and particularly when a person lands on the uneven terrain or the hard ground, the air bag rings provide a soft landing platform, and damage to equipment caused by hard landing is reduced.

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 invention relates to the technical field of winding devices, in particular to a dual-drive winding device for collecting and releasing a lashing rope of an aerostat, which comprises a rack, a driving module and a winding module, and the driving module and the winding module are both arranged on the rack; the driving module comprises a shell, a first driving motor, a second driving motor, a first clutch, a second clutch, a first rotating shaft and a second rotating shaft, an output shaft of the first driving motor, the first clutch and the first rotating shaft are sequentially connected, and an output shaft of the second driving motor, the second clutch and the second rotating shaft are sequentially connected; the first rotating shaft and the second rotating shaft are rotationally connected with the shell and are in transmission connection, so that the first rotating shaft is driven to rotate through the second driving motor, and the first rotating shaft is in transmission connection with the winding module. The invention provides a dual-drive winding device for collecting and releasing a lashing rope of an aerostat, which is used for overcoming the defect of poor reliability of a winch due to the fact that the winch of the aerostat in the prior art is usually provided with a single-group driving mechanism.

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 present invention relates to an aerostat (1) for carrying out transport and / or observation missions on a planet with an atmosphere, the aerostat comprising: an inflatable body (2) designed to be pressurised by a gas lighter than the atmosphere, a payload (3) configured to have at least one scientific instrument installed on-board, and a solar energy generator (7) arranged between the inflatable body (2) and the payload (3).

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.