Abstract: According to one aspect, a system for launching an aerostat may include an inflatable structure defining a volume having a neck, a reactor defining a chamber, a coupling releasably secured in fluid communication between the chamber and the neck, and a drain valve within the volume, the drain valve in a first position away from the neck to receive a lifting gas from the chamber into the volume via the coupling, the drain valve movable from the first position to a second position when the coupling is released from fluid communication between the chamber and the neck, and the drain valve in the second position in sealed engagement with the inflatable structure along the neck to control accumulation of condensate from the lifting gas within the volume.

Abstract: When lighter-than-air gas compressed and filled in a pressure-resistant container is injected into an envelope, buoyancy created in the envelope causes an aircraft to ascend. When the aircraft finishes its flight role, a lid of an opening/closing mechanism is opened to exhaust from a port lighter-than-air gas from the envelope. When the buoyancy of the envelope is insufficient to counter the weight of the aircraft, the aircraft begins to descend. The lid of the opening/closing mechanism is closed on the port, and exhaust of lighter-than-air gas from the envelope stops. After the aircraft reaches a surface of land or water, an operator connects a duct to a gas suction device. The gas suction device collects the lighter-than-air gas remaining in the air sac into a container. The lighter-than-air gas collected into the container is transported to a gas collection facility, compressed by a compressor, and filled into a pressure-resistant container.

Abstract: Horizontal translation, pendular motion, and or yaw control of a load suspended from a carrier with a suspended load control system, wherein control input to the suspended load control system may be provided through the use of more than one remote pendant.

Abstract: Aspects of the technology relate to propulsion systems for high altitude, long duration balloons, such as balloons that operate in the stratosphere for weeks, months or longer. A propeller assembly is used to provide lateral directional adjustments, which allows the balloon to spend more time over a desired region, reduce the return time to the desired region, reduce fleet overprovisioning, and increases the safety case by additional controls and avoidance abilities. A control assembly manages operation of the propeller assembly, including setting the pointing direction, speed of rotation and determining when to turn on the propeller and for how long. The propulsion system including the control and propeller assemblies is rotatable around a connection member of the balloon. Such rotation is independently adjustable from any rotation of the balloon's payload. The propeller blades may be made of plastic, which reduces weight and cost while providing sufficient speed at stratospheric altitudes.

Abstract: The disclosed invention describes a method for determining a current state of a gas cell in an airship, particularly the lift. A computing device receives depth measurements of the interior of the gas cell using a lidar sensor positioned outside the cell and uses these depth measurements to create a mesh, segment a space within the mesh into geometric shapes, calculate the volume of the shapes, and use the calculated volume to estimate the total volume of the space within the mesh, representing the volume of gas within the gas cell. The computing device then uses the estimated volume to calculate the lift of the gas cell and sends the calculated lift to a control module of the airship.

Abstract: A remote controlled lighter-than-air drone assembly that is capable of prolonged flight. The drone assembly utilizes a balloon structure. Separately, a reservoir is provided for holding a smaller second volume of gas. A propulsion system and a control unit are carried by the balloon structure. The control unit selectively transfers the gas from the reservoir to the balloon structure, and selectively vents the gas as needed. A receiver is used to receive command signals from an external source. The command signals are utilized to operate the propulsion system. An electronics suite is provided that can be altered depending upon duties. The electronics suite is used to scan or otherwise monitor an area below the drone assembly. In flight, the balloon structure is translucent and internally illuminated. A projector can be provided for projecting images onto the interior of the balloon structure.

Abstract: Disclosed are systems, apparatuses, and methods to enhance control of a drone-load system, including through drone thrusters or load thrusters.

Abstract: A stability control method and device based on particle active disturbance rejection are provided. The method includes: establishing an active disturbance rejection controller model based on a dynamic model and a speed loop control model of a tethered balloon system, where the speed loop control model is established through theoretical modeling of executive components of a control system of the tethered balloon system; and optimizing to-be-optimized parameters of the active disturbance rejection controller model using a particle swarm optimization algorithm, determining an optimal active disturbance rejection controller model, and using the optimal active disturbance rejection controller model to implement stability control of a photoelectric pod. An active disturbance rejection controller is optimized by using a particle swarm optimization algorithm, which can effectively isolate the internal and external disturbances of the photoelectric pod and improve the imaging stability of the photoelectric pod.

Abstract: Systems are described for transporting organic material, such as trees and logs, by flight. Such a transportation system may include a remotely-piloted air vehicle, a frame coupled thereto, multiple air vehicles, one or more propellers, a harness, and/or other components. The frame is coupled to both the remotely-piloted air vehicle and to the multiple other air vehicles.

Abstract: An integrated solar hydrogen production module includes a plurality of PV cells supported on a housing of the module. The module has an energy storage system which includes a rechargeable metal ion battery and a flow battery. The metal ion battery is charged by the PV cells. An electrolyser for converting water to gaseous hydrogen and oxygen can be powered directly by the PV cells or by either of the rechargeable metal ion battery and a flow battery. The PV cells, the metal-ion battery, the flow battery membrane and the electrolyser are electrically coupled together and integrated into or carried by the module housing. Electrically powered and solar thermal heaters can be incorporated into or with the module to heat the water in the electrolysers. A pump pressurises the water to facilitate the pressurisation of hydrogen and oxygen produced by the electrolysis.

Abstract: The present invention concerns hybrid airship comprising at least one buoyancy enclosure containing a gas lighter than air, a gondola attached below the buoyancy enclosure, the gondola extending along a longitudinal axis, at least one propeller configured to propel the hybrid airship, the at least one propeller being attached to the buoyancy enclosure, at least one generator, configured to provide power to the propeller, the generator being connected to the gondola. The hybrid airship comprises an arm protruding from the gondola and connecting the generator to the gondola.

Abstract: An aerial detection system includes an aerial vehicle unit and a hanging platform mechanically connected to an aerial vehicle by at least one flexible link. An EM sensor and hanging platform circuitry are mounted on the hanging platform. The hanging platform circuitry processes the EM sensor output signals. The aerial vehicle unit is attached the aerial vehicle and includes AVU circuitry which processes signals output by the hanging platform circuitry. The hanging platform circuitry and AVU circuitry are connected by one or more wired and/or wireless signal connections.

Abstract: An airship utilizing an innovative lift mechanism featuring dynamic and static vacuum chambers. The lift created by the vacuums created in the chambers elevates the ship into the atmosphere, thereby eliminating the need for lighter than air gases.

Abstract: A structural system for lifting cells, constructed of modular, lightweight framing supporting thin, lightweight, single-ply or laminated, air-impermeable membranes, that maintain near constant-volume under low pressure for aerostatic lift in lighter-than-air aircraft; a system for controlling that aerostatic lift in a single or a plurality of such lifting cells, using electrically-powered vacuum pumps and valves; and a system for recovering electrical energy expended during ascent by using the inflow of air into the lifting cells during descent to generate electricity.

Abstract: A method, computer system, and a computer program product for payload stabilization is provided. The present invention may include, in response to receiving at least one sensor data associated with a suspended payload, detecting an unstable movement in the suspended payload during a transport of the suspended payload. The present invention may also include implementing at least one sail coupled to the suspended payload to stabilize the detected unstable movement of the suspended payload.

Abstract: An inflatable kite includes a main tube and a sub tube. The inflatable kite includes: a first air chamber, which constitutes the sub tube; a second air chamber, which constitutes the sub tube and which is disposed at a position that is farther from the main tube than from the first air chamber in the sub tube; and a pressure regulator configured to adjust a pressure of the first air chamber and a pressure of the second air chamber. The sub tube cut by one plane that crosses in the direction of extension of the sub tube has a maximal cross-sectional area on a cross section of the first air chamber. The pressure regulator regulates the pressure of the first air chamber to be lower than the pressure of the second air chamber in a steady flight of the inflatable kite.

Abstract: A variable lift device includes a pressurized airtight enclosure accommodating air, a first airtight ballonet disposed inside the airtight enclosure accommodating a pressurized gas with a density lower than the density of air, the first airtight ballonet comprising a perforation means for perforating the first airtight ballonet.

Abstract: Disclosed is a take-off and landing station (1) for a flying vehicle (2) for transporting people and/or loads, which flying vehicle takes off and lands vertically and comprises a flight module (3), having a plurality of drive units (17) arranged on a supporting framework structure (16) of the flight module (3), and a transportation module (4), which can be coupled to the flight module (3). The take-off and landing station (1) comprises a holding apparatus (21) having a plurality of gripper elements and support elements (11) for supporting, fixing and/or orienting the supporting framework structure (16) during take-off and landing of the flying vehicle (2) or the flight module (3).

Abstract: A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

Abstract: A method for determining a flight path of an unmanned aerial vehicle (UAV) includes: acquiring an initial flight path configured by a management platform; determining, based on the initial flight path, a first group of accessible base stations of the UAV on the initial flight path capable to be accessed when the UAV flies based on the initial flight path; if the first group cannot provide continuous cellular network services for the UAV, acquiring a second group of accessible base stations capable of providing continuous cellular network services for the UAV; and determining the flight path corresponding to the second group as a target flight path. As such, the initial flight path of the UAV can be reasonably adjusted upon that the core network device cannot provide satisfactory network services for the UAV flying according to the initial flight path, to enable the cellular network to provide satisfactory network services for the UAV.

Abstract: A fan includes a fan hub and a plurality of blades. At least one of the blades includes an axial blade portion and a centrifugal blade portion. The axial blade portion has an axial arc surface. The axial arc surface extends between opposite two edges of the at least one blade, and connects with one of the two edges. The centrifugal blade portion has a guide trench. The guide trench extends away from the centrifugal blade portion. A width of the guide trench increases as it extends away from the centrifugal blade portion.

Abstract: Disclosed is a digital twin tethered balloon system; key running state data of a tethered balloon is collected through an Internet of Things of a tethered balloon system; the key running state data of the tethered balloon is transmitted to a twin data service center; the twin data service center receives, analyzes and stores the data and forwards the data to a tethered balloon digital twin system; the tethered balloon digital twin system simulates a pose of a tethered balloon body and the movement of a ground tethering facility; and the tethered balloon monitoring service provides running state monitoring, quality problem tracking, fault prediction and early warning, automatic control and other services.

Abstract: Disclosed are an unmanned aerial vehicle (UAV) having a buoyancy apparatus and an attitude control method thereof, in which the buoyancy apparatus is coupled to the UAV to reduce the energy consumption of rotors such that the time of staying in the air is extended, enabling a long flight, and in which the buoyancy apparatus absorbs the impact energy and reduces the falling speed to thereby ensure sufficient safety for the UAV.

Abstract: An aircraft includes: a plurality of rotor units each including a propeller and a motor that drives the propeller; a balloon that laterally covers the plurality of rotor units, across the height of the plurality of rotor units in the up-and-down direction; a camera that protrudes, along a predetermined axis, beyond the balloon; and a holding component that holds the camera and whose overall length can be shortened along the predetermined axis.

Abstract: An industrial activity drone comprising an aerial vehicle having at least one rotor, an activity system, and a fastener device for fastening the activity system to the aerial vehicle. The activity system includes a structure, a computer, a work camera that is stationary relative to the aerial vehicle and that provides a view of a work zone, a distribution device having a plurality of compartments, and a turning motor enabling the distribution device to turn relative to the aerial vehicle. The industrial activity drone performs hovering flight so that the work camera faces a work zone and the distribution device is turned so that the compartment that is to be used faces the work zone, thereby performing one or more tasks.

Abstract: An aircraft control system has a flight specification acquisition sensor for acquiring flight specifications of an aircraft and outputting the respective numerical values, and a plurality of flight computers, each having the same control software and performing airframe control based on the flight specification numerical values, thereby constituting a redundant system of flight control functions. Further, the control system includes a noise generator for the plurality of flight computers, which generates a plurality of noises different from each other, and the plurality of noises are individually superimposed on the numerical value of one flight specification output from the flight specification acquisition sensor to generate a plurality of new flight specification numerical values different from each other which are then output to the plurality of flight computers. This configuration ensures redundancy of the aircraft control software against potential bugs using the same control software.

Abstract: A system may include an inflatable assembly having a plurality of members. The system may also include a plurality of sensors disposed at a plurality of positions inside or around the inflatable assembly, such that the plurality of sensors may acquire data related to a shape of the inflatable assembly. The system also includes one or more valves, each configured to direct a fluid into a corresponding member of the plurality of members of the inflatable assembly. The system also includes a processor that adjusts positions of the one or more valves to cause the fluid to be directed into the corresponding member of the plurality of members of the inflatable assembly based on the data and a desired shape of the inflatable assembly.

Abstract: An environment improvement system includes: a sensor configured to detect a state of pollution by an environmental pollutant; a plurality of vehicles; and a server configured to communicate with the plurality of vehicles. The plurality of vehicles include vehicles including environment improvement devices configured to remove the environmental pollutant. When a pollution level by the environmental pollutant exceeds a threshold value in an area where the sensor is located, the server is configured to select at least a part of the vehicles including the environment improvement devices and cause the selected vehicles to move to the area, and to output a command to execute an environment improvement operation using the environment improvement devices.

Abstract: An air vehicle comprises a payload vessel, a propulsion system, and a buoyancy lifting unit anchored on said payload vessel. The buoyancy lifting unit comprises a plurality of balloons and a plurality of buoyancy gas reservoirs arranged in horizontal rows and vertical columns, a protractible rod, and a control system. Each of the balloons and buoyancy gas reservoirs is tethered to a lifting-joint on the protractible rod through a cable. The control system controls vertical move of the air vehicle to ascend through directing buoyancy gas flow from the buoyancy gas reservoirs into the balloons, and to descend through directing buoyancy gas flow from the balloons into the buoyancy gas reservoirs. The propulsion system controls horizontal move of the air vehicle to go forward and make turns.

Abstract: Devices, systems, and methods are directed to controlling lifting gas in a volume defined by an inflatable structure of an aircraft. For example, controlling lifting gas in the volume of the inflatable structure may account for variations in ambient and tactical conditions experienced by the aircraft over the course of flight, as may be useful for lifting the aircraft to a target altitude and/or carrying out a particular mission. Additionally, or alternatively, controlling lifting gas in the volume of the inflatable structure may facilitate lifting the aircraft using lifting gas generated by reacting stable materials with one another at a launch site in the field. As an example, aluminum may react with water to form a lifting gas including hydrogen and steam. As the steam condenses to water in the inflatable structure, a valve may expel water from the inflatable structure to assist in maintaining buoyancy of the aircraft.

Abstract: An aircraft includes; a plurality of rotor units each of which includes a propeller and a motor which drives the propeller, and generates thrust for flight of the aircraft; a controller which controls rotation of the propellers included in the plurality of rotor units; a balloon which laterally covers the plurality of rotor units; and a detector which detects a state of the aircraft, wherein the controller decreases a rotational speed of the propeller included in at least one rotor unit among the plurality of rotor units, according to a result of detection by the detector.

Abstract: An airborne device for surveillance of an enclosed area, comprising a platform having illuminating imaging devices, and an attached lighter than air balloon. A vertically aligned rotor provides additional lift, a rotor directed along the length of the platform provides forward and backward motion, and additional rotors aligned sideways steer and rotate the device. The rotors are driven by electric motors powered by an on-board battery. A vertically directed distance sensor measures and controls the hovering distance of the device from the roof. A reel of optical fiber is installed at the rear end of the platform, and the optical fiber unwinds from the reel and deploys behind the device as it moves forward. This optical fiber carries image data back to a monitor. The length of fiber deployed, combined with directional and accelerometer readings can be used to determine the absolute position of the device.

Abstract: A lighter-than-air (LTA) vehicle navigation system and vehicle. The navigation system includes a first wind probing device disposed at a first probe position, wherein the first wind probing device is in communication, via a first probe communications link, with a body communication system. The navigation system also includes a second wind probing device disposed at a second probe position, wherein the second wind probing device is in communication, via a second probe communications link, with the body communication system. The navigation system also includes a wind variation detection system configured to determine wind information, including at least a wind direction, for the first wind probing device and the second wind probing device.

Abstract: An airborne computational facility uses an energy collection system to provide energy for operation. An airborne balloon is provided with a photovoltaic collector array, and uses energy generated by the photovoltaic collector array to power an on-board computational facility. Data for computation is received by a communication module and computational results are transmitted by the communication module.

Abstract: An unmanned and remotely controlled airship has a multirotor system combined with an inflatable envelope. The airship may be lifted/powered by a power system that has three or more rotors. The airship may be constructed using rods, connectors, the main system/control box and the rotors. The airship system may have a systemic symmetry for weight distribution and flight control and may be, for example, a symmetric ellipsoid envelope/blimp.

Abstract: Methods, systems, and computer program products for providing automatic responsive actions to biometrically detected events are provided. Aspects include receiving, from a biometric sensing device associated with an animal, biometric data associated with the animal and animal location data associated with the animal. Aspects also include determining an intensity level of an event associated with the animal based on the biometric data and approximating a location of the event based on the animal location data and the biometric data. In response to determining that the intensity level of the event exceeds a predetermined intensity threshold, aspects include initiating a responsive action proximate to the location of the event.

Abstract: A movement analyzer includes a position information acquiring device, a memory, and a processor. The processor executes a program to perform operations including acquiring position information of the movement analyzer with the position information acquiring device, determining whether or not a moving state of the movement analyzer is a specific moving state, and recording the position information corresponding to the specific moving state in the memory as a path of the specific moving state when a determination result indicates that the moving state of the movement analyzer is the specific moving state.

Abstract: An air vehicle (10) comprising a main body (12) and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12) having a principal axis orthogonal to the longitudinal axis (20) of said wing members, at least a first propulsion device (16a) associated with a first of said wing members arranged and configured to generate a linear thrust relative to the main body in a first direction, and a second propulsion device (16b) associated with a second of said wing members arranged and configured to generate linear thrust relative to said main body in a second, substantially opposite, direction such that said wing members and said main body are caused to rotate about said principal axis, in use, the air vehicle further comprising an imaging system (100) configured to cover a substantially 360° imaging area about said principal axis and comprising at least one electro-optic sensor (102) mounted on a support member (104) and having a field of view (102a) covering a portion of said

Abstract: In some embodiments, apparatuses and methods are provided herein useful to transport unmanned aircraft systems to delivery products. In some embodiments, gas-filled aerial transport and launch system, comprises: a transport aircraft comprising: a gas chamber; and a carrier compartment where the gas chamber induces a lifting force on the carrier compartment; at least one propulsion system; and a navigation control system that controls the direction of travel of the transport aircraft; wherein the carrier compartment comprises: an unmanned aircraft system (UAS) storage area configured to receive multiple UASs; and an UAS launching bay that enables the UAS to be launched while the transport aircraft is in flight and while the UAS is carrying a package to be delivered.

Abstract: A system for treating ambient air is provided. The system includes a flow control structure disposed on a vehicle. The flow control structure is adapted to control flow of ambient air received during movement of the vehicle. The system further includes an actuator operatively coupled to the flow control structure. The actuator is adapted to movably adjust the flow control structure. The system further includes a controller disposed on the vehicle and communicably coupled to the actuator. The controller is configured to control the actuator based on at least a quality of ambient air. The system further includes an air treatment component for selectively receiving ambient air from the flow control structure. The air treatment component is adapted to treat at least one pollutant present in ambient air.

Abstract: Apparatuses for providing a portable display, such as temporary signage or telepresence communication capabilities, as well as methods for providing a portable display are described. A portable display apparatus includes a base, a collapsible component extending from the base and a plurality of light emitting devices coupled to the collapsible component. The collapsible component is configured to transition from a collapsed position to an extended position. The plurality of light emitting devices are arranged in a movable configuration such that, when the collapsible component is in the extended position, the plurality of light emitting devices rotate around the collapsible component and selectively illuminate to provide a display.

Abstract: A secondary UAV flies over the solar-powered UAV at night and illuminates the solar-powered UAV's solar panels to help supplement the solar-powered UAV's battery charge mid-flight. The secondary UAV could be equipped with a directional light source for providing light of a color and intensity selected for optimal absorption by the solar cells of the solar-powered UAV. As the secondary UAV flies over the solar-powered UAV, the secondary UAV could thus direct its light source at the solar-powered UAV for absorption by the solar cells, to help supplement the solar-powered UAV's battery charge. Further, the secondary UAV could potentially recharge multiple solar-powered UAVs during a single nighttime mission.

Abstract: An energy collection system uses one or more airborne energy collection vehicles having a lighter-than-air balloon structure. The balloon structure has an outer gas envelope formed of a substantially inelastic material and an inner gas envelope at least partially separate from the outer gas envelope, contained within the outer gas envelope and separated from the outer gas envelope by a flexible diaphragm. The space between the outer and inner gas envelopes is filled with air. An air chamber pressurization mechanism maintains the outer gas envelope gas pressure at a target value. An energy storage facility receives energy from a photovoltaic collector array and converts the received energy to stored energy. Storage of the received energy can be accomplished by conversion of a precursor to a high energy fuel as the stored energy, by use of storage batteries or by storage in an inertial mass.

Abstract: A method for launch of an airship includes connecting a cargo airship to a second airship that is not positively buoyant at the launch site, launching the cargo airship, transferring lifting gas from the cargo airship to the second airship where said lifting gas is carded by the cargo airship while aloft; and releasing the second airship from the cargo airship. A high-altitude airship launch system is also provided.

Abstract: An aircraft comprising a hydrogen-containing envelope, a water-collection system for collecting water from the envelope, an electrolyser to convert the water collected using the water-collection system into hydrogen, and a hydrogen-replenishment system for replenishing the envelope with hydrogen generated using the electrolyser. In one embodiment, generated hydrogen is also supplied to a hydrogen-fueled propulsion system for propulsion of the aircraft.

Abstract: The system to be installed on a vehicle to purify air using kinetic energy generated by movement of the vehicle is presented. The system comprises at least one kinetic air purifier structure which is an air conduit having a first particle collection chamber and a second particle separation chamber. Each chamber comprises at least one convex element that provides obstacle to the air flow to separate large particles from the air flow, at least one trapping element, such as cotton fabric, to trap smaller dirt particles, and at least one chamber orifice that allows access to the chambers for cleaning purpose. The system further comprises a micro-porous trapping element to trap micro particles. Due to separated and trapped particles at various chambers, the air is purified. The air purification is achieved by capturing the dirt particles instead of diminishing those.

Abstract: The device for generating an electrical current, intended for a pipeline, includes a pipe element (1), a rotor (2) suitable for being set in motion by the fluid and a stator (3a, 3b) arranged to cooperate with an end of the rotor (2) opposite to an axis of rotation (4) of said rotor (2) in order to generate the electrical current. The axis of rotation (4) is mounted at its opposing longitudinal ends (4a, 4b) on first and second supports (5a, 5b) arranged on either side of the plane of rotation (P1) of the rotor (2) and each linked to the pipe element (1). The stator has at least one ring (3a) arranged on one side of the rotor (2), and each ring (3a, 3b) includes a circuit suitable for generating all or part of the electrical current when excited by a magnetic element of the rotor (2).

Abstract: An unmanned lighter-than-air aircraft includes an outer membrane, a flexible bladder within the outer membrane and containing a lighter-than-air gas, a region disposed between the outer membrane and flexible bladder, a volume detection device configured to measure the volume of the flexible bladder, a pressure adjustment device to adjust the pressure within the region, and pressure control circuitry to control the region pressure adjustment device based on measurements from the volume detection device. The aircraft is maintained at a desired altitude, and the volume of the flexible bladder is measured. The pressure within the region is then adjusted by the pressure control circuitry to maintain the volume of the flexible bladder at a desired volume less than its maximum volume, equalizing its pressure with that of the region to reduce lighter-than-air gas leakage from the flexible bladder.

Abstract: A system may include an inflatable assembly having a plurality of members. The system may also include a plurality of sensors disposed at a plurality of positions inside or around the inflatable assembly, such that the plurality of sensors may acquire data related to a shape of the inflatable assembly. The system also includes one or more valves, each configured to direct a fluid into a corresponding member of the plurality of members of the inflatable assembly. The system also includes a processor that adjusts positions of the one or more valves to cause the fluid to be directed into the corresponding member of the plurality of members of the inflatable assembly based on the data and a desired shape of the inflatable assembly.

Abstract: A hybrid airship has both aerostatic and aerodynamic lift comprising: an engine, a flexible external envelope (2) and at least one primary enclosure Ep filled with lifting gas (G). The primary enclosure Ep having an elastic wall P1 separating this enclosure from compartment C1, the latter having an elastic wall Pi separating compartment C1 from compartment Ci, the latter having an elastic wall Pi+1 separating the compartment Ci from compartment Ci+1, and so on up until elastic wall PJ+1 separating compartment CJ from compartment CJ+1 where J corresponds to a whole number greater than or equal to 1, each compartment Ci being equally delimited by the flexible exterior envelope. The hybrid airship includes a) a valve Vi between each compartment Ci and its adjacent compartment Ci+1, and b) a controller (22) for the valve Vi.