210 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 a ducted layout rigid-flexible mixed structure mooring aerostat type high-altitude wind power generation system which comprises an air aerostat wind power generation system, an air-ground electric energy transmission and mooring cable and a ground anchoring system, and the air aerostat wind power generation system is connected with the ground anchoring system through the air-ground electric energy transmission and mooring cable. The air aerostat wind power generation system comprises a ducted thin-wall truss bearing structure, an annular air bag, an empennage, a skin component and a wind power generator set, and the ducted thin-wall truss bearing structure is provided with a plurality of constraint spaces distributed in the longitudinal direction; the plurality of annular air bags are respectively arranged in the plurality of constraint spaces; a plurality of empennages are arranged at the rear part of the ducted thin-wall truss bearing structure; the ducted thin-wall truss force bearing structure and the multiple empennages are sleeved with the skin component. The wind generating set is installed in the ducted thin-wall truss force bearing structure through the supporting structure. The device is stable in structure, can stably generate power in a long-time air-staying mode, is low in cost, and is autonomous and controllable.

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.

Disclosed herein are systems and methods for passive sensing of unmanned aircrafts (UAs) using radio frequency (RF) signals transmitted by satellites and / or aerostats. One or more passive RF sensor units are employed, and each of the sensor units is configured to: produce one or more concurrent reception beams; receive RTSA resultant signals originating from one or more RTSAs, an RTSA being one of a satellite and an aerostat, which transmits RF signals, and an RTSA resultant signal is a signal transmitted by an RTSA after traversing a medium between the RTSA and the passive RF sensor unit; and process the received RTSA resultant signals to perform target detection based on the forward scatter effect. The systems and methods may also provide additional UA situational surveillance capabilities, e.g., target detection, target tracking, target classification, target identification, and prediction and / or detection of events associated with UA safety and / or security.

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.

The invention relates to the technical field of aerostats, and provides a high-altitude balloon self-destruction device and a high-altitude balloon system.The high-altitude balloon self-destruction device comprises a mounting frame, the mounting frame is provided with a first mounting part, and the first mounting part is used for being fixedly connected with a dome flange of a high-altitude balloon; the hob is provided with a first end and a second end on the axis of the hob, the first end is connected to the mounting frame through a safety piece, the second end is used for being connected with a traction rope, and the hob can be separated from the mounting frame under the action of the traction rope and cut the balloon film of the high-altitude balloon. After a flight task is finished and the balloon-parachute cabin is separated, the parachute can pull the traction rope to trigger the hob of the high-altitude balloon self-destruction device to destroy the balloon membrane, so that the balloon safely lands back to a preset area, and the safety problem that the balloon body of the high-altitude balloon uncontrollably flies at high altitude for a long time is avoided; in addition, the high-altitude balloon can be prevented from being in direct contact with the balloon film soft structure in the releasing process, and the safety of the balloon releasing process is guaranteed.

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 invention discloses a flying wing and buoyancy lift integrated layout mooring aerostat type high-altitude wind power generation system which comprises an air aerostat wind power generation system, an air-ground electric energy transmission and mooring cable and a ground anchoring system. The air aerostat wind power generation system comprises a flying wing configuration thin-wall truss force bearing structure, a plurality of buoyancy air bags, two empennages, a skin component and three wind power generator sets, and the flying wing configuration thin-wall truss force bearing structure is provided with a plurality of constraint spaces distributed in the wingspan direction; the plurality of buoyancy airbags are respectively arranged in the plurality of constraint spaces; the two empennages are arranged at the two ends of the rear portion of the flying wing type thin-wall truss force bearing structure respectively. The skin component is arranged on the flying wing configuration thin-wall truss force bearing structure and the two empennages in a sleeving manner; the three wind generating sets are installed at the bottom of the flying wing type thin-wall truss force bearing structure through a supporting structure. The device is stable in structure, can stably generate power in a long-time air-staying mode, is low in cost, and is autonomous and controllable.

The invention relates to a large-wingspan curled wing unmanned aerial vehicle aerial delivery system which comprises an unmanned aerial vehicle, a delivery carrier and a delivery control system. The unmanned aerial vehicle is hung on the throwing carrier in a wing curled state; the unmanned aerial vehicle automatically flies after the constraint of the release carrier is released; the delivery carrier carries the unmanned aerial vehicle in a wing curled state to reach a specified delivery height; and after the unmanned aerial vehicle reaches the specified delivery height, the delivery control system controls the unmanned aerial vehicle to realize wing unfolding in a curled state, adjusts the attitude of the unmanned aerial vehicle to be stable, and then relieves the constraint of the unmanned aerial vehicle and the delivery carrier. According to the large-wingspan light low-wing-load unmanned aerial vehicle, efficient storage is achieved after the wings are curled, the scheme that a carrier is put in the air is utilized, the defect that traditional ground take-off and landing have high requirements for airspace, runways and weather is overcome, and air deployment can be rapidly achieved. The unmanned aerial vehicle is suitable for various carriers such as aerostats, airplanes and rockets, cluster launching can be achieved, and the use flexibility of the large-wingspan light low-wing-load unmanned aerial vehicle is greatly 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 present invention relates to the technical field of aerostats, and provides a floating flight system. The floating flight system comprises: a superpressure balloon sphere, an aerodynamic sail, a wind speed sensor and a controller; the wind speed sensor is arranged on the aerodynamic sail, and the wind speed sensor is used to measure wind field data, and the wind field data includes wind speed and wind force; the controller is communicatively connected with the wind speed sensor, and the controller is communicatively connected with the aerodynamic sail, and the controller is used to receive the wind field data of the wind speed sensor, and control the aerodynamic sail based on the wind field data. The floating flight system provided by the present invention has a controller receiving the wind field data of the wind speed sensor, so that the controller controls the aerodynamic sail based on the wind field data, so that the aerodynamic sail can be adjusted in real time according to the wind field conditions, and can adapt to different wind field conditions at a relatively low energy cost, thereby ensuring that the floating flight system can fly for a long time, and the aerodynamic sail is controlled to adapt to different wind field conditions, so that the floating flight system can achieve regional residence.

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.

1. Name of the product of this design: mooring components for aerostats. 2. Purpose of the product with this design: The product with this design is used as a component of an aerostat mooring system to connect an aerostat in the air to the ground. 3. The design key point of this appearance design product lies in the overall shape of the product. 4. The picture or photo that best illustrates the design points: three-dimensional picture. 5. Description of other situations that need to be explained: Reference Figure 1, Reference Figure 2, Reference Figure 3, Reference Figure 4, Reference Figure 5, Reference Figure 6 and Reference Figure 7 are reference diagrams of the use status of the mooring components of the airship provided by this design.