284results about "Gas-bag arrangements" patented technology

The invention provides a new class of transportation with a partially aerostatically supported ram air cushion ship (PASRACS) that can provide safe, fast, efficient global transport services with extraordinary comfort, luxury and amenities. The PASRACS employs inventive synergistic combinations of lift from aerostatic, aerodynamic, hydrostatic and hydrodynamic forces for different modes of operation ranging from a stationary floating configuration on a water surface, to flight in ground effect at high speed. A propulsion system can utilize hydrogen as an energy source driving fluid-dynamic thrusters, to enable zero carbon emissions operations. A transition method is provided for a PASRACS to transition from a floating mode to a takeoff mode to a flight in ground-effect mode in an inventive optimized manner. A transport method for multimodally transporting payload is provided with PASRACS vehicles and systems, with quick turn time operations enabled by the use of payload transfer transport modules and transfer vehicles.

The invention comprises an apparatus, method for using the apparatus and system for balloon altitude control by in-situ characterization and active energy management. The invention presented enables transportation, autonomous operation and use of a balloon beyond the limits of conventional high-altitude ballooning to the edge of the atmosphere, or about 100 km above the surface of the Earth. The apparatus comprises at least: an envelope containing lift-gas; an envelope and lift-gas characterizer; an altitude control system operated using active energy addition and lift-gas transfer or ambient air introduction into the system; and an external payload component. The invention is capable of operating in ascent, descent, or stationary mode; the altitudinal movement of the balloon is caused by measuring in-situ envelope and lift-gas characteristics, identifying the change in the lift-gas energy needed, and facilitating the required energy change for altitude control.

The invention discloses a fan blade transportation and installation system and method and a flight device, and belongs to the technical field of intelligent transportation of fan blades. The system comprises a flight transportation module, an intelligent navigation control module, an installation auxiliary module and a scheduling module; the flight transportation module is used for suspending and loading the fan blades, and suspending, flying and transporting the fan blades according to a preset flight route; the intelligent navigation control module is used for monitoring a flight path, collecting flight data and environment data in a flight process, predicting potential obstacles according to the flight data and the environment data, and optimizing a flight strategy; the mounting auxiliary module is used for aligning and fastening the blades and the fan hub; the scheduling module is used for determining a flight plan according to the meteorological data, the performance of the flight transportation module and the priority of the transportation installation task. By combining a plurality of transportation, installation and dispatching modules, efficient and safe transportation and installation of the fan blades are achieved, and the transportation and installation difficulty and cost are reduced.

Described herein are features for a high altitude lighter-than-air (LTA) system and associated methods. A zero-pressure balloon (ZPB) is attached in tandem with one or more air super-pressure balloons (SPB). The ZPB provides lift for the system while the SPB may provide a variable amount of ballast air by pumping in or expelling out ambient air. Various advanced performance targets relating to ascent rate, descent rate, range and maximum altitude are achievable with various scaled versions of the basic design of the LTA system. Advanced navigation and control techniques, such as more efficient high altitude station-keeping approaches, made possible with the LTA system are also described.

According to the deformable multi-rotor airship, an air bag filled with light gas is mounted in a rack, and the air bag can be inflated and deflated with the light gas from a gas tank at any time through an airborne gas pump. The multi-rotor aircraft is high in maneuverability and stable in attitude control, and the air bag can provide extra buoyancy, so that loads of the rotors are reduced, the overall flight efficiency is improved, and the endurance time is prolonged. Air in the air bag can be compressed into the air tank through the air pump, and the size of the air bag is reduced to reduce wind resistance and enhance control capacity. Firstly, additional lift force is provided by adding the air bag, the power consumption of the aircraft is greatly reduced, and the aircraft is suitable for long-time hovering and low-speed cruising. And secondly, the design reserves the flexibility and controllability of the multi-rotor unmanned aerial vehicle, more complex and efficient control can be carried out, and the dynamic response speed of the aircraft is effectively improved. And finally, the air bag capable of inflating and deflating air in real time greatly enhances the environmental adaptability of the aircraft, and can effectively cope with various complex environments in low-altitude scenes.

Described herein are features for a high altitude lighter-than-air (LTA) system and associated methods. The LTA may include one or more super-pressure balloons (SPB). One or more of the SPB's may include one or more interior volumes. One or more of the interior volumes may be configured to receive an LTA gas therein to supplement the free lift of the LTA system. There may be an adjustable valve or vent to release the LTA gas. One or more of the interior volumes may be configured to receive ambient air to provide a variable downward force. The SPB may use a compressor to pump in ambient air. The compressor or another valve may release ambient air to decrease the downward force. A zero-pressure balloon (ZPB) may be attached with the one or more SPB's. The ZPB may supplement lift for the system.

The invention belongs to the technical field of aviation mechanical equipment, and provides aviation monitoring flight equipment and an implementation method thereof. The device comprises a framework, a floating ball arranged in the framework and restrained by the framework, spiral wings symmetrically arranged on the two sides of the framework, a control host arranged at the bottom of the lower end of the framework and a monitoring camera carried at the bottom of the control host, and a mounting table is arranged in the middle of the upper end of the framework; a wind speed and direction sensor and an adjustable mounting frame mechanism are arranged on the mounting table, and a flexible solar cell panel is mounted on the adjustable mounting frame mechanism. According to the unmanned aerial vehicle, the floating balls and the spiral wings adopted by the unmanned aerial vehicle are creatively combined, the floating balls are filled with helium, on one hand, the operation energy consumption of equipment can be reduced through buoyancy of the floating balls, the cruising ability of equipment operation is improved, on the other hand, based on the arrangement of the floating balls, the spiral wings can adopt small wing equipment, and the operation noise is lower.

The invention comprises an apparatus, method for using the apparatus and system for balloon altitude control by in-situ characterization and active energy management. The invention presented enables transportation, autonomous operation and use of a balloon beyond the limits of conventional high-altitude ballooning to the edge of the atmosphere, or about 100 km above the surface of the Earth. The apparatus comprises at least: an envelope containing lift-gas; an envelope and lift-gas characterizer; an altitude control system operated using active energy addition and lift-gas transfer or ambient air introduction into the system; and an external payload component. The invention is capable of operating in ascent, descent, or stationary mode; the altitudinal movement of the balloon is caused by measuring in-situ envelope and lift-gas characteristics, identifying the change in the lift-gas energy needed, and facilitating the required energy change for altitude control.

The invention discloses a wing-shaped sail split floating aircraft and a flight control method thereof. The problems that an existing floating aircraft is large in energy consumption and complex in control mode are solved. The airfoil-shaped sail split floating aircraft comprises a ship-shaped main body, a plurality of sails are arranged on the upper portion of the ship-shaped main body, and a manned cabin is arranged on the lower portion of the ship-shaped main body; a power strip type air bag mechanism, a fixed type air bag mechanism and a lifting control air bag mechanism are arranged in the ship-shaped main body, a wind power propeller is arranged on the ship-shaped main body and provides thrust for steering and horizontal movement, and the wing-shaped sails provide assistance for horizontal flight. According to the ship-shaped aircraft, a large number of independent split helium-filled air bags are integrated into the ship-shaped aircraft body, and the flight safety coefficient is increased; the suspension of the aircraft in the air is realized through the balance weight of the power strip type variable air bag at a balance state critical value; the expansion volume change of the air bag is changed by pressing and releasing the air bag to control the lifting of the aircraft; through coupling of the control systems, the aircraft can fly safely, stably and flexibly with low energy consumption.

A flight craft comprises: an intermediate member, which has an annular shape in a plan view and has a flat cross-sectional shape when cut along a plane that includes a straight line in a direction of the plan view; a plurality of gores, each of which extends from an outer side to an inner side of the intermediate member in the plan view, passes through an inner opening of the intermediate member, is folded back, and then extends from the inner side to the outer side of the intermediate member in the plan view; a front side member, which is positioned on a front side of the intermediate member, where the front side is defined as a side facing outward in the plan view, and a rear side is defined as a side opposite to the front side; a rear side member that is positioned on a rear side of the intermediate member; and a tightening mechanism that tightens the front side member and the rear side member in a direction that brings them closer to each other.

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 a low-altitude heavy-load transportation airship and a buoyancy control method in the loading and unloading process, and belongs to the technical field of heavy-load transportation aircrafts. Comprising a bag body filled with buoyancy gas, a high-pressure air bag and an air bag which are located in the bag body, a pressure control system used for controlling the high-pressure air bag and the air bag to be inflated and deflated and a flight control system used for controlling the pressure control system to act, the density of the buoyancy gas is smaller than that of air, and the pressure control system comprises a first pressure control system and a second pressure control system; the first pressure control system controls buoyancy gas to flow into or out of the high-pressure air bag. The second pressure control system controls external air to flow into or out of the air bag. The flight control system is in signal connection with the first pressure control system and the second pressure control system. The buoyancy and gravity of the airship are adjusted by inflating and deflating the high-pressure air bag and / or the air bag, so that the problem that the airship rises rapidly due to the fact that the net buoyancy of the airship is increased sharply during cargo unloading is solved, and flight safety is guaranteed.

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 comprises an apparatus, method for using the apparatus and system for balloon altitude control by in-situ characterization and active energy management. The invention presented enables transportation, autonomous operation and use of a balloon beyond the limits of conventional high-altitude ballooning to the edge of the atmosphere, or about 100 km above the surface of the Earth. The apparatus comprises at least: an envelope containing lift-gas; an envelope and lift-gas characterizer; an altitude control system operated using active energy addition and lift-gas transfer or ambient air introduction into the system; and an external payload component. The invention is capable of operating in ascent, descent, or stationary mode; the altitudinal movement of the balloon is caused by measuring in-situ envelope and lift-gas characteristics, identifying the change in the lift-gas energy needed, and facilitating the required energy change for altitude control.

An airship may include a plurality of struts and a plurality of hubs joined to form a geodesic frame. A material may at least substantially enclose the frame. The material may be configured to contain a gas within a volume enclosed by the material, and may also be configured to absorb solar radiation for heating the gas. The airship may include a vent configured to selectively open and close to regulate one or more of a temperature and a pressure of the gas. When the vent is open, the volume enclosed by the material may be in fluid communication with an exterior of the material. When the vent is closed, the volume enclosed by the material may be at least substantially hermetically sealed from the exterior of the material. Also disclosed are methods of carrying a payload with the airship.

The invention relates to the technical field of airship control, in particular to a floating aircraft control method and system oriented to an extreme environment. The control method comprises the following steps that environment parameters and running state data of the floating aircraft are collected in real time through a multi-mode sensor, and the environment parameters comprise the air speed of the stratosphere or under the stratosphere, the ultraviolet radiation intensity, the external temperature gradient and the air pressure fluctuation value; the operation state data comprises an air bag sealing index, propeller output power, a counterweight slide rail position and the residual capacity of the energy storage unit. Through the dynamic pressure compensation and self-repairing technology, the problem of sealing failure of the floating aircraft in an extreme environment is solved; and multi-mode wind resistance control and hybrid energy optimization are combined, so that the flight path precision and the cruising ability are remarkably improved.

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 invention belongs to the technical field of floating equipment, and particularly relates to a tethered airship with a propelling device and a conveying system for the tethered airship. A connecting part is arranged on the outer surface of a boat body, a propelling device comprises a horizontal propelling part and a vertical propelling part, the horizontal propelling part is arranged on the peripheral surface of the boat body and used for moving the boat body in the horizontal direction, and the vertical propelling part is arranged on the peripheral surface of the boat body and used for moving the boat body in the vertical direction. The horizontal direction is perpendicular to the vertical direction, and the mooring rope is detachably connected with the connecting part. According to the tethered airship with the propelling device in the technical scheme, the horizontal propelling part is used for providing propelling force in the horizontal direction to achieve the functions of headwind adjustment, yaw control and the like of the airship body, and the vertical propelling part is used for providing pulling force in the vertical direction to achieve height adjustment and pitching control of the airship body. The propulsion device improves the propulsion efficiency of the boat body, and further enhances the wind measurement resistance and attitude stability of the boat body.

The present invention discloses a nose cone mooring structure for an airship without a rigid frame, comprising a base, a bottom ring, straight beams, and arc beams. The base is provided with several straight beams, and the ends of the straight beams away from the base are connected to the arc beams via a four-way structural member. The arc beams are provided with through slots that cooperate with fixing loops on the airship capsule. The bottom ring is provided between the four-way structural members. The nose cone mooring structure for an airship without a rigid frame of the present invention provides a simple nose cone fixing and mooring method for mooring an airship without a rigid frame. This solution can evenly distribute the tension during the mooring of the airship, does not require special reinforcement of the airship capsule material, and does not significantly increase the amount of capsule material used. At the same time, the nose cone can also ensure that the head portion, which is subject to greater air resistance, does not deform during the flight of the airship, thereby increasing the flight resistance.

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 present invention provides a flying object. In a flying object having an airbag, the risk of damage to the airbag skin is reduced by fastening components arranged on the inner and outer sides of the airbag skin. The component (14) has an annular middle component (141), and the portion around the opening of the airbag in the skin (111) is folded back after passing through the inner opening of the middle component from the back side to the front side. A front component (142) having an annular front sealing component (143) mounted on the back side is arranged in a manner that contacts the front side of the middle component covered by the folded back skin. In addition, a back component (144) having an annular back sealing component (145) mounted on the front side is arranged in a manner that contacts the back side of the middle component covered by the folded back skin. The front side component and the back side component are fastened in a direction toward each other by means of bolts (1461) and nuts (1462), thereby mounting the assembly on the airbag.

The application discloses a three-body type helium-hydrogen hybrid power airship, and belongs to the technical field of airships. The three-body type helium-hydrogen hybrid power airship comprises an airship frame, an electric power channel fan propulsion system, a main gas bag area, an auxiliary gas bag area, a battery cabin and a hanging cabin. The electric power channel fan propulsion system is arranged at the top of the airship frame on both sides and is used for assisting the airship in flight. The electric power channel fan propulsion system is electrically connected with the battery cabin. The main gas bag area is arranged at the middle of the airship frame and comprises a closed helium cabin, which is used for providing main lifting force for the airship. The closed helium cabin is arranged at the two sides of the airship frame. The auxiliary gas bag area is arranged at the upper part of the airship frame and is used for providing gas fuel for the battery cabin and also providing lifting force for the airship. The battery cabin is slidingly arranged at the middle of the airship frame and is used for providing electric power for the airship and realizing gravity center distribution adjustment in a sliding mode. The hanging cabin is arranged at the lower part of the airship frame. The application has the advantages of high safety, reliability and economy.

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 provides a fixed-point overwater recovery method, system and device for an aircraft. The fixed-point overwater recovery method for the aircraft comprises the steps that a target landing area is determined according to initial position information, water surface information and wind field information of the aircraft; the aircraft is controlled to move to a first position in the target landing area, the first position refers to the position of the target height right above the central point in the target landing area, and a plurality of simulated landing points are calculated based on a landing point prediction algorithm and the wind field information; taking the simulated landing point closest to the central point in the plurality of simulated landing points as a second position, and controlling the aircraft to move from the first position to the second position; and in the process of controlling the aircraft to descend from the second position to the target water surface, the water surface control system adjusts the position of the floating platform according to the horizontal position difference between the aircraft and the floating platform, so that the aircraft lands on the floating platform. According to the embodiment of the invention, accurate aircraft water recovery can be realized.

The invention provides an aerial unmanned charging and battery replacing method which comprises the following steps: during battery replacing, a pesticide applying unmanned aerial vehicle flies to a battery replacing platform of an operation and maintenance platform which is driven by a helium balloon to rise to a certain height, and a mechanical arm module takes out a first unmanned aerial vehicle battery on the pesticide applying unmanned aerial vehicle and places the first unmanned aerial vehicle battery in an empty slot position of a battery storage cabinet; taking out the fully charged unmanned aerial vehicle battery I pushed out by the automatic push-out mechanism from the battery storage cabinet, and putting the unmanned aerial vehicle battery I into a battery jar on the pesticide applying unmanned aerial vehicle; during charging, the charging unmanned aerial vehicle flies to the position above the pesticide applying unmanned aerial vehicle, and a charging connector II at the bottom of the charging unmanned aerial vehicle is in magnetic attraction butt joint with a power supply connector at the top of the pesticide applying unmanned aerial vehicle, so that a charging contact II of the charging unmanned aerial vehicle is connected with a power supply contact of the pesticide applying unmanned aerial vehicle; a second unmanned aerial vehicle battery on the charging unmanned aerial vehicle supplies power to all electric devices in the pesticide applying unmanned aerial vehicle. The working efficiency of forest pesticide application work is improved, the cost of building a fixed unmanned aerial vehicle base station is reduced, and the problem that the endurance of an unmanned aerial vehicle in forestry pest control is short is solved.

The invention relates to a load transportation airship and a loading and unloading control method thereof, the airship comprises a main bag body, at least one auxiliary bag body is arranged in the main bag body, one of the main bag body and the auxiliary bag body is a buoyancy air bag, and the other one is an air bag; the light skeleton structure is arranged around the main capsule body; the vector electric propellers are mounted on the periphery of the main bag body and fixed to the light skeleton structure; the empennage is provided with a movable control surface and is positioned at the rear part of the main capsule body in the advancing direction; the temperature adjusting system is connected with the buoyancy air bag and is used for adjusting the temperature of the buoyancy gas filled in the buoyancy air bag so as to adjust the static lift force of the whole boat; the hybrid energy system is fixed to the light skeleton structure and used for providing power for the vector electric propeller and the temperature adjusting system. Compared with the prior art, the unmanned aerial vehicle has the advantages of structural safety, bearing capacity, accurate and flexible flight control, stable and reliable energy supply, wide application range and the like.

The invention discloses a high-altitude airship net buoyancy adjusting device and method, and relates to the technical field of high-altitude airship net buoyancy adjustment. The high-altitude airship net buoyancy adjusting device comprises a hanging frame, a sand bag, a slinging mechanism and an inhaul cable; the hanging frame is connected with the air bag and used for bearing and dispersing loads; the sand bag is connected to the lower portion of the hanging frame, balance weight particles are contained in the sand bag, and an outlet is formed in the bottom of the sand bag. The slinging mechanism is connected below an outlet of the sand bag and comprises a control mechanism, and the control mechanism is used for controlling opening and closing of the outlet and the outflow time of the counterweight particles; the weight of the airship is directly reduced by throwing the counterweight particles, so that the net buoyancy is increased, the principle is simple, and the response is quick. The concentrated load of the sand bag is dispersed and transmitted to the air bag by adopting the hanger structure, so that stress concentration is avoided, and the air bag material is protected. The slinging mechanism achieves accurate control over the slinging amount and the slinging speed by controlling the opening and closing time and the caliber of the sand outlet, and the adjusting precision is high.

The invention provides a new class of transportation with a partially aerostatically supported ram air cushion ship (PASRACS) that can provide safe, fast, efficient global transport services with extraordinary comfort, luxury and amenities. The PASRACS employs inventive synergistic combinations of lift from aerostatic, aerodynamic, hydrostatic and hydrodynamic forces for different modes of operation ranging from a stationary floating configuration on a water surface, to flight in ground effect at high speed. A propulsion system can utilize hydrogen as an energy source driving fluid-dynamic thrusters, to enable zero carbon emissions operations. A transition method is provided for a PASRACS to transition from a floating mode to a takeoff mode to a flight in ground-effect mode in an inventive optimized manner. A transport method for multimodally transporting payload is provided with PASRACS vehicles and systems, with quick turn time operations enabled by the use of payload transfer transport modules and transfer vehicles.