96results about "Rigid airships" patented technology

The invention relates to a remote-control system of a stratospheric airship and a control method thereof. The control system is divided to four levels: a decision-making level for executing the selection and switch of a remote-control flight mode according to the actual working state data, and sending a corresponding mode command; a planning level for dynamically planning and generating an airship motor drive command according to the mode command sent by the decision-making level; an executing level for realizing the drive control to an airship motor according to the motor drive command of the planning level; and a perceiving level for finishing the real-time monitoring and data collection of the airship working state, and providing the original data of the airship working state to the decision-making level. The four-level control system architecture design of the control system is capable of simplifying the control device, improving the control efficiency, and fundamentally solving the problems of the function, efficiency and reliability of the near space airship ground and airborne control system.

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.

Unmanned and remotely controlled airship constituted from system of multirotor combined with inflatable envelope. The airship may be lifted / powered by a power system comprising three or more rotors. In some embodiments, 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.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

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 application discloses a small airship device and a control method for automatic modeling of indoor three-dimensional objects, and belongs to the field of indoor aircraft intelligent inspection and three-dimensional perception systems. The airship adopts a four-rotor design arranged in layers. The upper vertical rotors control horizontal forward and backward movement and turning, and the lower horizontal rotors adjust the lifting force to realize lifting and hovering, thereby realizing multi-degree-of-freedom decoupling control. Attitude data are collected through an attitude sensor, and a PID algorithm is combined to realize automatic height maintenance. A communication module is used to build a WiFi local area network and run a Web control page, thereby realizing remote flight control of an intelligent terminal. On this basis, a preset flying-around program is executed to control the airship to automatically cruise at a constant radius and height around a target object, the rudders are synchronously adjusted to drive the camera to take multi-angle photographs, and image acquisition required for three-dimensional modeling is completed. The method combines manual and automatic control modes, and improves flight stability and modeling efficiency.

The invention discloses a falling collision protection device, a task equipment module and an aerostat, and relates to the technical field of aerostats, the falling collision protection device comprises a mounting part, an air bag and a control unit, and the mounting part is provided with a containing cavity; the air bag can be contained in the containing cavity, and a gas generating agent is loaded in the air bag; the control unit is used for judging whether falling and collision protection is implemented or not, and when falling and collision protection is implemented, the gas generating agent is excited to generate protective gas, so that the air bag is unfolded under the action of pressure. According to the falling collision protection device, the solid sodium azide is instantaneously decomposed to generate nitrogen, so that the air bag is quickly unfolded before touching the ground, and the buffer failure caused by inflation delay of the compressed air cylinder is eliminated.

The invention provides 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.

A system for the thermal management of an external electric-power-generating nacelle equipping an electrically powered airship, the nacelle comprising electrical generation means implementing at least one turbogenerator contained in a fire containment vessel and provided with an inlet duct for turbine feed air and a flue gas exhaust duct, the system comprising ventilation means for injecting external air into the fire containment vessel, and means for discharging the ventilation air from the fire containment vessel, the means surrounding the flue gas exhaust duct so as to provide a Venturi effect for the outflow energized by the turbine flue gases.

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 relates to the technical field of aerospace energy systems, in particular to a tethered airship system. The tethered airship system comprises an airship body and an anchoring platform and further comprises a solar cell array, and the solar cell array is arranged on the airship body and / or the anchoring platform. An ocean energy generator; the first power supply is electrically connected with the ocean energy generator; the input end of the energy manager is electrically connected with the solar cell array and the first power supply; the input end of the power distributor is electrically connected with the output end of the energy manager; the ocean energy generator, the first power supply, the energy manager and the distributor form a first power supply subsystem; and the solar cell array, the energy manager and the distributor form a second power supply subsystem. The first power supply subsystem and the second power supply subsystem can enable the tethered airship system to be used at the position without the external power supply capacity all the time, the applicability of the tethered airship system is improved, and the application range of the tethered airship system is widened.

To provide an equipment mounting tool for a flying object, a flying object and an equipment mounting method for the flying object capable of easily mounting equipment for the flying object inside the flying object and regulating the movement of the equipment for the flying object in spite of a compact and lightweight structure.SOLUTION: The jig 1 comprises a base member 2 fixed inside the flying object and provided with an opening 21, a ring-shaped bracket 3 mounted on the outer peripheral surface of the flying object device 11 and attachable to the opening 21, and a first direction regulating means 4 regulating the movement of the ring-shaped bracket 3 in a first direction along the circumferential direction of the opening 21 and a second direction regulating means 5 regulating the movement of the ring-shaped bracket 3 in a second direction orthogonal to the opening surface of the opening 21.SELECTED DRAWING: Figure 1

This application discloses an inflatable tail fin for an airship made of polyethylene film, characterized by comprising: a spherical membrane made of polyethylene film; reinforcing ribs for securing the spherical membrane; and longitudinally extending partitions welded into the cavity of the spherical membrane, wherein the longitudinal direction refers to the direction from the root of the tail fin to the tip of the tail fin; and multiple partitions arranged laterally within the cavity of the spherical membrane. This application also discloses a method for manufacturing an inflatable tail fin for an airship made of polyethylene film. This solves the problem that polyethylene film cannot withstand high pressure.

The invention discloses a small airship device for indoor three-dimensional object automatic modeling and a control method, and belongs to the field of indoor aircraft intelligent inspection and three-dimensional sensing systems. The airship adopts a layered four-rotor design, an upper-layer vertical rotor controls horizontal advancing, retreating and steering, a lower-layer horizontal rotor adjusts lift force to realize lifting and hovering, and multi-degree-of-freedom decoupling control is realized. Attitude data are collected through an attitude sensor, and height automatic holding is achieved in combination with a PID algorithm. And a WiFi local area network is constructed by using the communication module, and a Web control page is operated, so that remote control of the intelligent terminal on flight is realized. On the basis, a preset flying-around program is executed, the airship is controlled to conduct fixed-radius and fixed-height automatic cruise around the target object, a steering engine is synchronously adjusted to drive a camera to conduct multi-angle shooting, and image collection needed by three-dimensional modeling is completed. According to the method, manual and automatic control modes are fused, and the flight stability and the modeling efficiency are improved.

A spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. According to one example, a spacecraft docking station may include a frame enclosing an area, and a net-like mesh coupled to the frame and filling the area enclosed by the frame. An autonomous robot may be coupled to the net-like mesh. One or more vessels may be coupled to the frame and / or the net-like mesh, where the one or more vessels include a propulsion mechanism. Other aspects, embodiments, and features are also included.

A Fluid traversing system disclosed herein. The fluid traversing system, or FTS (116), comprising primarily at least one self-vectoring craft, or SVC (111), wherein each SVC has one or more detachable coupling means, or DC (114). Further, each SVC has a plethora of components in order to, sustain independent stable motion through a fluidic medium, establish wired / wireless communications, generate power and has a plurality of DC that are selectively controlled, in order to couple with another SVC and / or any other type of crafts and / or various payloads. Furthermore, each SVC has a plurality of pivotable / displaceable rotors / stators coupled within the fuselage / hull of the SVC. Further, each rotor / stator has a plurality of blades (112), wherein each blade is selectively pivoted / articulated with respect to the said rotor / stator or other blades.

A connection interface made of composite or possibly metal material for connecting at least one chord with at least two diagonals, wherein the sleeve has at least one sleeve provided to surround the chord about a longitudinal direction and at least two radially projecting sockets. Each of the sockets is designed to receive one end of one of the diagonals. The interface further includes a first reinforcing part extending between the two sockets, the reinforcing part having a bore forming an attachment point, and a second reinforcing part opposite the first reinforcing part with respect to the longitudinal direction, the second reinforcing part having a second bore forming an attachment point.

An aerostat having an elongate hollow body having a length defining a local axis of the body, the hollow body being suitable for receiving sufficient lighter-than-air gas, such that the aerostat can become buoyant in air, the aerostat body comprising a sequence of a plurality of joined body portions, each body portion comprising an outer skin and a hollow internal space, wherein the joins are substantially perpendicular to the local axis of the body, the joined body portions comprising two end body portions, and a plurality of internal body portions, so that the joined body portions together form the elongate hollow body; and a method of manufacturing an aerostat according to any one of the preceding claims, comprising the steps of supporting a first body portion to form a first mounted hollow body portion, supporting a second body portion to form a second mounted hollow body portion, bringing the first and second mounted body portions to come into contact such that the outer skins of the first and second body portions come into alignment, followed by joining together the outer skins of the first and second body portions, followed by repeating the process with further body portions, thereby to produce the aerostat having an elongate hollow body.

Example implementations provide fluid-borne vehicles comprising a body and a plurality of thrust vectoring modules, each thrust vectoring module comprising a set of thrust producing means, wherein a first thrust producing means, mounted on a first mounting bar having a first mounting bar axis, is rotatable about the mounting bar axis and the mounting bar axis is rotatable about an arm having an arm axis that is nonparallel to the mounting bar axis; and a second thrust producing means, mounted on a second mounting bar having a second mounting bar axis, is rotatable about the second mounting bar axis and the second mounting bar axis is rotatable about the arm axis that is nonparallel to the second mounting bar axis.

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 utility model provides a helium balloon hanging basket with a multi-pipe folding spray pipe, which comprises a working hanging basket, side spray pipe components are respectively arranged on two sides of the working hanging basket, a bottom spray pipe is arranged at the bottom of the working hanging basket, and each side spray pipe component comprises a mounting bracket, a folding spray pipe and a telescopic driving device. The side spraying pipe assemblies are arranged on the two sides of the working hanging basket respectively, the foldable spraying pipes in the side spraying pipe assemblies are arranged on one side of the working hanging basket through the installation supports, the telescopic driving devices drive the foldable spraying pipes to be folded and unfolded so as to adjust the length of the foldable spraying pipes, and the spraying device is suitable for different spraying operation ranges. The bottom spraying pipe is arranged at the bottom of the working hanging basket, and the spraying range can be fully covered; a plurality of sets of cross spray pipes are arranged, the cross spray pipes are simple in structure and can provide large telescopic stroke and large deformability, meanwhile, the foldable spray pipes can be completely contracted, and therefore the size of the whole equipment is reduced, and the equipment is convenient to store.

The invention relates to an aircraft comprising a load-bearing structure (1) and at least three propellers (21, 22, 23) fixed to the load-bearing structure (1), each propeller (21, 22, 23) being configured to generate a vectored thrust in at least one direction, said aircraft being characterized in that each propeller (21, 22, 23) can be oriented independently of the other propellers (21, 22, 23) so as to form a combination of vectored thrust, the support structure (1) can be held stationary at any attitude angle theta defined between a yaw axis (z) relative to a reference frame (O, x, y, z) of the support structure (1) and a reference axis (Z) of an absolute reference frame (O, X, Y, Z). The invention also relates to a method for controlling the flight of such an aircraft.

An air conditioning controller (150) acquires in-cabin environment information, outside environment information, and flight information in steps S101 to S103. The air conditioning controller determines whether a window fogging condition is satisfied in a window fogging determination process. The air conditioning controller uses in-cabin environment information, outside environment information, and flight information, for a determination of whether the window fogging condition is satisfied. When the window fogging condition is not satisfied, the air conditioning controller performs an inside air mode process in step S107. In the inside air mode process, an operation mode of an air conditioner system (110) is set to an inside air mode. When the window fogging condition is satisfied, the air conditioning controller performs an outside air mode process in step S108. In the outside air mode process, the operation mode of the air conditioner system (110) is set to an outside air mode. In the outside air mode, taken-in outside air (Air2) is introduced into a cabin (15).

A lighter than air platform an unfinned envelope having two or more propulsion elements coupled with the unfinned envelope proximate to the center of gravity. At least one navigation sensor is configured to monitor an actual flight path of the unfinned envelope, and at least one perturbation sensor is configured to monitor one or more perturbations of the unfinned envelope. A navigation controller is configured to guide the unfinned envelope with coordinated propulsion of the two or more propulsion elements. The navigation controller includes a navigation comparator that compares the actual flight path with a specified flight path of the unfinned envelope and determine a navigation instruction. A perturbation comparator compares the navigation instruction with the monitored one or more perturbations to determine a perturbation compensation. A propulsion coordinator controls propulsion values of each of the propulsion elements based on the navigation instruction and the perturbation compensation.

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 invention provides an airship capable of modularly installing a rescue patrolling device launching cabin. Comprising an airship capsule body (1), a main airship cabin and power cabin (3), a vector propulsion device (4), an undercarriage (5) and a rescue patrolling device launching airship cabin (6), the airship capsule body (1) is filled with helium serving as light gas to provide buoyancy; the main airship cabin and power cabin (3) is connected to the lower end of the airship capsule body (1) in a suspended mode, the vector propulsion devices (4) are symmetrically installed on the side faces of the power cabin in the main airship cabin and power cabin (3), motor cabins of the vector propulsion devices (4) are connected with a main airship cabin of the main airship cabin and power cabin (3) through linkage wing sections, and propellers of the vector propulsion devices (4) are arranged behind the motor cabins. And the rescue patrolling device launching boat cabin (6) is arranged at a reserved position of the main boat cabin and the power cabin (3). The task execution efficiency of an emergency rescue unit is improved.