93 results about "Aerostat" patented technology

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 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 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.

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.

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.

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.

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.

The invention relates to the technical field of aircraft design and control, in particular to an aerostat, a floating operation platform and floating operation equipment. The aerostat comprises a flight platform main body and a flight control system, wherein the platform main body is provided with a main lift force and attitude adjusting system and a jet flow micro-control system; the flight control system is configured to obtain state information of the aerostat; judging the motion state of the aerostat based on the state information; when it is judged that the system is in the state needing large-amplitude posture correction, the main lift force and posture adjusting system is controlled to work so as to conduct posture recovery; and controlling the jet flow micro-control system to work so as to accurately control the attitude and the position when the jet flow micro-control system is judged to be in a steady state needing precise displacement or attitude adjustment. According to the invention, decoupling of attitude and displacement of the unmanned aerial vehicle is realized, and high-precision and high-stability omnidirectional displacement control is realized on the premise of strictly maintaining a horizontal operation attitude.

The application relates to the technical field of aerostats, and provides a shape design method, device and equipment of an overpressure balloon and a storage medium. The method comprises the following steps: obtaining external parameters of a bidirectional tension overpressure balloon; the external parameters comprise a load and an overpressure amount; constructing a generatrix-stress equation group of the overpressure balloon according to the external parameters; performing stress balance analysis on the overpressure balloon according to the generatrix-stress equation group, and determining shape parameters of the overpressure balloon; the shape parameters comprise a generatrix shape; and designing the shape of the overpressure balloon according to the shape parameters. By constructing the generatrix-stress equation, when the shape of the overpressure balloon is designed, the load and the boundary condition of the overpressure balloon under the condition of bidirectional tension are considered, the problem that the overpressure balloon in the form of a regular sphere needs to be deformed to adapt to the load and the boundary condition under the condition of bidirectional tension, stress concentration and a weak area of the balloon membrane are prone to occurring is solved, and the stress distribution is more reasonable.

The present application relates to the field of tethered aerostat power generation technology, and provides a ground platform and a tethered aerostat power generation system. The ground platform comprises a platform body, an energy storage unit, an electric drive assembly and an energy management module; the energy storage unit is used for storing electric energy; the electric drive assembly is electrically connected with the energy storage unit and is used for driving the platform body to move; the energy management module is electrically connected with an air platform through a power cable and is used for receiving and distributing the electric energy generated by the air platform. The energy management module, the energy storage unit and the electric drive assembly constitute an internal power supply loop, the energy management module delivers the received electric energy to the energy storage unit, and the energy storage unit supplies power to the electric drive assembly through the internal power supply loop. The present application can make the ground platform realize energy self-sufficiency and autonomous movement and deployment, efficiently receive and distribute the electric energy of the air platform, construct a stable internal power supply loop, take into account its own power supply and energy storage, and independently complete the work in a complex work environment without external supporting facilities.

A pod performance test system for a near space aerostat includes: a HCI test control device, a motion simulation control device, a suspension device, and a motion simulation anti-twisting mechanism. The HCI test control device is electronically connected to the motion simulation control device, the motion simulation anti-twisting mechanism and a pod of the near space aerostat separately. The motion simulation control device is electronically connected to the motion simulation anti-twisting mechanism. The motion simulation anti-twisting mechanism is connected to the pod by a connector. The motion simulation control device controls the motion simulation anti-twisting mechanism to simulate various complex motion states according to a motion control parameter from the HCI test control device, and thus the pod is in the various complex motion states. When the pod is in the various complex motion states, performance test results of the pod under the various complex motion states can be obtained.

This invention discloses a tethered aerostat, comprising: a tethered aerostat body, a wind power generation component, and a connecting component; the connecting component connects the capsule of the tethered aerostat body and the wind power generation component, with the wind power generation component located below the capsule. In this invention, wind energy can be converted into stable and continuous electrical energy through the cable adjustment device of the wind power generation component and the tethered aerostat body for use by various devices of the tethered aerostat; simultaneously, by placing the wind power generation component below the capsule, the connecting component adjusts the wind-driven directional balance of the tethered aerostat.

The invention relates to a hydrogen supply device comprising a low-pressure hydrogen tank (3), a water tank (5), a fuel cell (2), and an electrolyzer (6), characterized in that the device includes a switch (10) for switching an electrical circuit (200) of the aircraft either to the power output (24) of the fuel cell (2) in a first switching position, or to the power input (69) of the electrolyzer (6) in a second switching position. Figure 1

The invention belongs to the technical field of floating aircrafts, and discloses a multi-safety margin pressure control system architecture for a manned airship, which comprises a manual control system provided with an integrated switch board and a mechanical pressure gauge, the integrated switch board is connected with an exhaust valve and a fan, and the mechanical pressure gauge measures and displays the pressure value of an air bag; the automatic control system is provided with a pressure sensor, a main pressure control computer and a standby pressure control computer, the pressure sensor is connected with the main pressure control computer and the standby pressure control computer, and the main pressure control computer and the standby pressure control computer are both connected with the exhaust valve and the fan. The problem that a conventional unmanned aerostat air bag pressure control system excessively depends on a power supply and distribution system and a control device is solved, and major safety accidents caused by system function loss are avoided.

The application relates to the technical field of aerostats, and provides a high-altitude balloon system which comprises a rising balloon, a cutting mechanism, a recovery balloon and a gondola, the bottom of the rising balloon is connected with the bottom of the recovery balloon, the recovery balloon is arranged in the rising balloon, the gondola is fixedly connected with the recovery balloon, and a task execution device is arranged in the gondola; the cutting mechanism is arranged on the outer wall of the rising balloon and is used for cutting the rising balloon when the task execution device is recovered; wherein the buoyancy of the recovery balloon is less than the total gravity of the load of the gondola. The application has the advantages of simple structure, low cost and convenient operation, compared with the traditional mode of recovering the gondola load by using a parachute, the application has fewer interference factors when the gondola load is recovered, and the recovery efficiency of the task execution device is improved.

The invention relates to the technical field of low-altitude unmanned aerial vehicles, in particular to a new energy saucer-shaped aerostat which comprises a saucer-shaped shell, air bags and ducted fans, the saucer-shaped shell is of a flat disc-shaped structure, the air bags are filled in the saucer-shaped shell, and the air bags comprise at least two independent air bags; at least one air bag is filled with helium, and the helium in the air bag provides lift force for the aerostat; at least one air bag is filled with air, the volume of the air bag can be adjusted by inflating and deflating the air, and then the aerostat is controlled to ascend and descend through the volume change of the air bag; eight ducts are arranged in the air bag and evenly distributed in the front direction, the rear direction, the left direction and the right direction, the inner ends of the eight ducts are communicated, the outer ends of the eight ducts are led to the outside of the air bag, a ducted fan is installed in each duct, and the eight ducted fans cooperatively control the aerostat to move front, back, left and right in the horizontal direction. The invention provides the new energy unmanned aerial vehicle which is high in maneuverability, long in endurance, large in load and low in noise.

The invention discloses a nose-cone-free modular anchoring device, a high-altitude wind power generation system and an anchoring method of the high-altitude wind power generation system. The anchoring device comprises a frame, supporting legs, a rotary platform, a front arm frame, two rear arm frames and corresponding executing mechanisms. A nose-cone-free double-ring aerostat connector and a three-point distributed rigid bearing structure are adopted, a traditional single-point nose cone bearing mode is replaced, drawing, horizontal and torsion combined loads in a high-altitude wind field are effectively decomposed and resisted, and the anchoring stability and safety are remarkably improved. Meanwhile, the anchoring device adopts a modular design, has the capabilities of rapid assembly, maneuvering transition, automatic leveling and rotation adaptation, can be flexibly matched with aerostats with different sizes and loads, and achieves the technical effects of efficient deployment, reliable bearing and wide adaptation.

1. The name of the design product: floating wind turbine (double ring wing). 2. The use of the design product: for wind power generation in high altitude. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

An aerostat having an elongate hollow body having a length defining a local axis of the body, the hollow body adapted to receive sufficient lighter than air gas such that the aerostat can become buoyant in air, the aerostat body comprising a series of a plurality of joined body portions, the present invention relates to an elongate hollow body comprising a plurality of body portions, each body portion comprising an outer skin and a hollow interior space wherein a joint is substantially perpendicular to a local axis of the body, the joined body portions comprising two end body portions and a plurality of interior body portions such that the joined body portions together form the elongate hollow body; and a method of manufacturing an aerostat according to any of the preceding claims, the method comprising the steps of: supporting a first body portion to form a first mounted hollow body portion; supporting the second body portion to form a second mounted hollow body portion; contacting the first mounted body portion and the second mounted body portion such that the outer skins of the first body portion and the second body portion are aligned; the outer skin of the first body part and the outer skin of the second body part are jointed together; the process is then repeated with a further body portion, thereby creating an aerostat having an elongate hollow body.

The application discloses a space false target system based on an inflatable structure and a deployment method thereof, and relates to the technical field of spacecraft protection.The system comprises a load cabin and a storage cabin, a camouflage module is arranged in the storage cabin, an inflation module for inflating the camouflage module, a power supply module for power supply and an attitude control module for controlling attitude are arranged in the load cabin, the storage cabin is composed of multiple folding plates, the folding plates can be automatically unfolded to release the camouflage module in the storage cabin, the deployment method is realized through satellite release, and subsequent attitude adjustment and inflation are performed, the folding storage cabin and a torsional spring hinge are combined to realize quick unfolding, the inflation module and the attitude control module are combined to realize quick deployment and stable control, the problems of complex deployment, low unfolding efficiency and insufficient attitude adjustment of a traditional system are solved, and the system has the advantages of quick deployment, compact structure, stable and reliable attitude and suitability for a dynamic space environment.