160results 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 relates to the technical field of aerostat control, and discloses an aerostat control method and system, and the method comprises the steps: S1, collecting the internal state data, external environment data and environment parameters of an aerostat through a multi-source sensor; s2, processing the data acquired in the S1, and constructing a state and disturbance observer to obtain an aerostat state estimation value and an environmental wind disturbance estimation value; s3, based on the state estimation value and the wind disturbance estimation value of the aerostat, a self-adaptive control algorithm is adopted, a control instruction used for controlling the height and the horizontal position of the aerostat is generated, and the control instruction comprises a feedforward component used for actively compensating wind disturbance; and S4, distributing the control instruction to a channel power system of the aerostat and executing the control instruction. An integrated control architecture with state estimation, disturbance observation and adaptive control capabilities is constructed, three technical bottlenecks of weak control robustness, poor anti-interference capability and low intelligent level of a traditional aerostat in outdoor application are effectively solved, and the positioning precision and stability are improved.

The invention 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.

The invention discloses an inflatable aerial carrying platform and a flying method, and relates to the field of aerostats, and the key point of the technical scheme is that the inflatable aerial carrying platform comprises a platform main body cabin with an annular structure, a spherical auxiliary balance cabin arranged above the platform main body cabin and connected through a cable, and a balance control system. A plurality of groups of partition sheets are arranged in the platform main body cabin, the platform main body cabin is uniformly divided into a plurality of independent air chambers which are symmetrically arranged, and each air chamber is provided with an independent inflation and deflation hole, so that fine air pressure regulation and control and high-altitude attitude stability are realized. The auxiliary balance cabins form a composite buoyancy system through upper and lower layered layout, and the gravity center control and anti-instability capacity of the whole platform under load fluctuation or airflow disturbance is improved. According to the invention, the fault resistance, the safety and the pneumatic stability of the aerial platform are obviously improved.

The invention discloses a novel solar cell system and method suitable for an airship. The system comprises an electrochromic layer used for changing light transmittance, a solar cell array integrated on the airship and a voltage control module. Wherein the electrochromic layer is physically connected with the solar cell array, the electrochromic layer covers the surface of the solar cell array, and the voltage control module is electrically connected with the electrochromic layer. Therefore, by adopting the embodiment of the invention, the problems of overheat and overpressure of the capsule body can be reduced, meanwhile, the power generation efficiency of the solar cell is improved, damage to a skin material of the capsule body of the airship is avoided, and the service life of the airship is prolonged.

The invention provides a deck type helium airship unmanned aerial vehicle platform which comprises an unmanned aerial vehicle platform body and further comprises two air bags arranged in parallel left and right, at least two sets of distributed propelling units and an energy module. The unmanned aerial vehicle platform is fixed between the two air bags, the two air bags are connected with each other through a rigid connecting structure and keep relative positions fixed, a balance weight storage part is arranged at the bottom of the unmanned aerial vehicle platform, and the unmanned aerial vehicle platform is provided with a bin door communicating with the balance weight storage part and a berth used for taking off and landing of an unmanned aerial vehicle. The system can be used as aerial mother port cluster operation and maintenance, and full-process automatic management of receiving, launching, charging and data interaction of the unmanned aerial vehicle is realized.

Modular flying platform including an airship body defining an internal space and configured to achieve buoyancy, an internal structure supporting a transfer channel, an attachment mechanism positioned on the transfer channel to detachably connect with a second platform. The transfer channel is configured to permit transfer therethrough of a payload between the flying platforms when securely connected. A chain of modular flying platforms with one or more motors mounted to the airship body to control motion thereof. A method for managing a chain of modular flying platforms includes deploying a plurality of platforms, connecting the platforms to form the chain, transferring a payload through channels of the connected platforms and distributing at least one of propulsion, electrical power and computing across the chain.

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 present invention relates to the field of aerostat technology, resolving the technical issues of traditional optical drive control design methods, which have significant limitations on their scope of application. In particular, the invention relates to a control method for an aerostat and an autonomously moving aerostat. The control method includes filling an independent air chamber with a low-density gas, causing the aerostat to float autonomously in the air; establishing a control equation for controlling the autonomous motion of the aerostat by controlling light intensity; placing the aerostat floating in the air within an illuminated area; and autonomously controlling the aerostat to advance in a predetermined direction based on the control equation. The present invention utilizes the deformation properties of liquid crystal elastomers to simplify the optical drive control system, thereby achieving a lightweight aerostat without the need for fuel or a controller. The aerostat can utilize photothermal energy to achieve long-term autonomous flight, adapting to complex and diverse application scenarios.

The 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 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.

This invention relates to a spherical airship with adjustable vector propulsion. The spherical airship mainly consists of a vector propulsion device, an airship body, an airship frame, a flight control module, an attitude detection module, an environmental monitoring module, and a battery. By adjusting the thrust direction of the vector propulsion device and the angle between the airship frame and the body, precise control of the airship's attitude and flight path can be effectively achieved. This design features small size and compact structure. The propulsion device is mounted on a frame with an adjustable angle, making the control process more flexible. Simultaneously, the propulsion device's position is dynamically adjusted through the frame structure, preventing it from being positioned in the direction of the airship's movement and overcoming the safety hazards of traditional external propellers. Despite having only two propulsion devices, the system still provides precise control capabilities through seven controllable degrees of freedom, significantly enhancing the accuracy and flexibility of flight control.

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.

The application discloses a kind of double hulls lift-float integrated aircraft roll adjusting method, it is related to aircraft design technical field, using the form of auxiliary air bag control, main air bag control and full-motion horizontal tail control combination to carry out double hulls lift-float integrated aircraft roll adjusting, using the mode that auxiliary air bag is connected with atmosphere environment and air is pumped out, main air bag is connected and helium is pumped out, full-motion horizontal tail deflection, changes the lift distribution of aircraft, buoyancy distribution, so that aircraft generates roll torque, adjusts aircraft roll angle.The double hulls lift-float integrated aircraft roll adjusting method that the application adopts has significantly improved the aircraft roll adjusting efficiency, is conducive to improving the maneuverability and safety of aircraft, compared with the existing aircraft attitude adjusting mode, combines the characteristics of double hulls lift-float integrated aircraft, aircraft roll adjusting mechanism work can generate greater moment change, aircraft has very high adjusting capacity to attitude.

The invention discloses a posture-controllable suspension mounting device for power station line inspection, and the device comprises a bag body which is used for providing buoyancy; the multiple driving rotor wings are arranged, and the driving rotor wings are evenly distributed in the circumferential direction of the capsule body; and the multi-sensing comprehensive detector is hung below the bag body through a connecting piece. The six-degree-of-freedom maneuvering ability is achieved through the buoyancy characteristic of the helium bag body carrier platform and the eight-rotor-wing propelling system with the eight driving rotor wings, the device can easily reach the position near overhead lines in complex terrain areas such as mountainous areas and river-crossing sections, and the constraint of the terrain on routing inspection work is eliminated; meanwhile, the flight height can be flexibly adjusted, lines with different erection heights can be close to each other in a short distance, a detection blind area formed due to the fact that traditional manual inspection cannot reach is effectively eliminated, and the space coverage rate of line inspection is greatly increased.

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

The invention relates to the technical field of high-altitude wind power generation, in particular to a variable-wing floating device suitable for high-altitude wind power generation, a working method and an umbrella ladder. The wing type bags capable of being opened and closed are symmetrically arranged on the two sides of the floating body, so that in the initial rising process of the floating body, due to the fact that air is gradually rarefied, the internal and external pressure difference between the floating body and the wing type bags is gradually increased, and the size of the floating body and the size of the wing type bags are gradually increased; the wing type bag body is still kept in a closed state and is attached to the outer surface of the floating main body; when the floating main body ascends to the preset height, the volume of the floating main body and the volume of the wing type bag body both reach the maximum, at the moment, the wing type bag body can be switched from the closed state to the open state, in this way, the wing type bag body can generate upward lifting force under the action of wind power, and therefore the floating main body continues to ascend. Therefore, according to the technical scheme, the acting interval of the umbrella ladder can be widened, and the acting capacity of the umbrella ladder is improved.

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 multi-air-chamber high-overpressure low-resistance soft stratospheric airship comprises a front wrapping piece, a middle wrapping piece, a rear wrapping piece and a flexible diaphragm, the front wrapping piece, the middle wrapping piece and the rear wrapping piece are sequentially connected and surround to form an airship body structure, and the connecting position between the front wrapping piece and the middle wrapping piece is connected with the flexible diaphragm. Flexible diaphragms are arranged at the connecting position between the front wrapping piece and the rear wrapping piece and the connecting position between the middle wrapping piece and the rear wrapping piece, a front rectification helium cabin is formed in the front wrapping piece through separation of the flexible diaphragms, a middle gas cabin is formed in the middle wrapping piece, a tail edge high-pressure helium cabin is formed in the rear wrapping piece, and a helium bag is arranged in the front rectification helium cabin. A helium air bag is arranged in the trailing edge high-pressure helium cabin, an air bag and electric control pressure adjusting equipment are arranged in the middle air cabin, and the electric control pressure adjusting equipment is connected with the air bag. The multi-air-chamber high-overvoltage low-resistance soft stratospheric airship has the advantages of being excellent in stability and low in release difficulty.

The application provides a kind of aerostat system, comprising: capsule, first gondola, second gondola and external equipment;External equipment is installed on the outer surface of the capsule;First gondola and second gondola are respectively hoisted on the lower surface of the capsule;External equipment is connected with first gondola and / or second gondola through shielded wire and external equipment, and magnetic ring is arranged at the connection of shielded wire and external equipment;First gondola and second gondola are both closed structure with metal shell;Grounded metal mesh is used to connect between first gondola and second gondola;Power supply equipment is installed in first gondola;Flight control equipment is installed in second gondola;Equipment cabinet in first gondola and second gondola is connected with gondola rack on gondola structure.The aerostat system provided by the application is designed from the whole, divides the aerostat system into multiple areas, different areas use targeted protection measures, and electromagnetic interference is avoided in all directions, which improves the reliability of the aerostat system.

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.