305results about "Rigid airships" patented technology

An aircraft thermal management system comprising a high temperature loop and a low temperature loop. The high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. The low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.

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 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 relates to a vector propulsion spherical airship with an adjustable structure. The spherical airship is mainly composed of a vector propelling device, an airship capsule, an airship framework, a flight control module, a posture detection module, an environment monitoring module, a battery and the like. By adjusting the thrust direction of the vector propulsion device and the included angle between the airship framework and the capsule body, accurate control over the attitude and the flight path of the airship is effectively achieved. The design has the advantages of being small in size and compact in structure, and the propelling device is installed on the framework with the adjustable included angle, so that the control process is more flexible. Meanwhile, the propelling device achieves dynamic position adjustment through a framework structure and is prevented from being located in the airship movement direction, and potential safety hazards of a traditional external propeller are overcome. Although only two propelling devices are configured, the system can still provide fine control capability through seven controllable degrees of freedom, and the precision and flexibility of flight control are remarkably enhanced.

The invention relates to the technical field of aerostats, solves the technical problem that a traditional CD-ROM device control design method is large in application range limitation, and particularly relates to a control method of a floating device and an autonomously-moving floating device.The control method comprises the steps that an independent air chamber is filled with low-density air, and the floating device autonomously floats in air; and establishing a control equation for controlling the autonomous movement of the floating device by controlling the illumination intensity, placing the floating device floating in the air in the illumination area, and autonomously controlling the floating device to advance according to the preset direction based on the control equation. The optical drive control system is simplified by utilizing the deformation characteristic of the liquid crystal elastomer, so that the light weight of the floating device is realized, fuel and a controller do not need to be carried, and long-time autonomous flight can be realized by utilizing photo-thermal energy so as to adapt to complex and changeable application scenes.

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.

The invention provides an innovative vector propulsion system of a low-altitude airship, aims to provide accurate attitude adjustment and path planning capabilities for the low-altitude airship in a complex space environment, and consists of a plurality of key components, comprising an executing mechanism, a power driving module, a vector rotating mechanism, a propeller connecting mechanism, a detecting module and a propeller control system. The core characteristic of the airship is that adjusted vector thrust can be applied to any direction in a three-dimensional space so as to respond to real-time attitude adjustment and control requirements, so that accurate vertical rising, lateral flying and rotating operation of the airship in a limited space are realized; due to the unique design, the influence of the thrust direction change on the gravity center of the airship is reduced to the maximum extent, and therefore it is ensured that the low-altitude airship keeps the stable posture, and meanwhile fine control is achieved; the system is further integrated with a set of independent control system so as to guarantee accurate output of thrust angles, meanwhile, the overall structure is light and handy, the system particularly meets the requirements of low-altitude small airships, and the maneuverability and adaptability of the system in a narrow space are enhanced.

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.

An aircraft thermal management system includes a high temperature circuit and a low temperature circuit. The high temperature loop is configured to manage a temperature of a fuel cell stack in the engine compartment using the engine compartment heat exchanger. The cryogenic circuit is configured to cool a plurality of thermal loads in the engine compartment using the thermal capacity of the liquid hydrogen.

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.

An Internet-of-Things-based management system and method for transmission of airship data. In the method, a state prediction module performs comprehensive calculation on multi-source data on the basis of the positive and negative correlation of the multi-source data, and then generates an airship index, and predicts the flight state of an airship by means of a comparison result between the airship index and an anomaly threshold value; when it is predicted that the flight state of the airship is poor, a remote control platform automatically takes over a flight control module, and an airship base station operator controls the use of the flight control module by means of the remote control platform; when it is predicted that the flight state of the airship is poor, the remote control platform first searches for the nearest airship base station to the airship; and if the airship base station meets an airship landing condition, the airship base station operator can control the airship to land at the nearest base station. When an airship flies, multi-source data is effectively analyzed to predict the flight state of the airship, so that the airship can be controlled and managed in a timely manner before the airship is abnormal, thereby ensuring the safe use of the airship.

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 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 provides a conformal structure suitable for a large-wingspan flexible wing and a design method, and relates to the technical field of aircraft mechanical structure design. The unmanned aerial vehicle is provided with a fuselage and inflatable wings; fuselage fixing pieces are installed on the surface of the fuselage, at least one pulling point is arranged on the surface of each inflatable wing in the wingspan direction of the surface of the inflatable wing, at least one pulling point is located at the wingtip of the inflatable wing, wing fixing pieces are installed at the pulling points, and the wing fixing pieces are connected with the fuselage fixing pieces through traction pieces. According to the large-wingspan flexible inflatable wing, the wing can be prevented from generating large structural deformation in the lift force direction under the gravity and pneumatic action, and the engineering application problem that an existing large-wingspan flexible inflatable wing is large in deformation under the gravity and pneumatic load can be solved; the pulling point arrangement along the spanwise direction and the chordwise direction can be flexibly determined according to flight conditions; a certain dihedral angle or dihedral angle is pre-set for the inflatable wing by adjusting the length of the pull rope, so that the transverse stability of the aircraft is improved.

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 floating air bag and a floating power generation platform. The floating air bag comprises an air bag main body; the at least two air bag straight wings are arranged at intervals in the circumferential direction of the air bag main body; each air bag straight wing is provided with at least one auxiliary rotor wing assembly, each auxiliary rotor wing assembly at least has a first state, and when the auxiliary rotor wing assemblies are in the first state, the auxiliary rotor wing assemblies are used for adjusting the position of the floating air bag in the first direction. The floating air bag solves the problem that in the prior art, interference is likely to be generated between the floating air bag and the adjacent floating air bag.

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.

The invention relates to the technical field of aircrafts, and discloses a cargo-carrying airship and an airship transportation method.The cargo-carrying airship comprises a main bag body containing working gas used for providing net buoyancy; the cabin body is used for bearing goods; the horizontal driving device is used for providing thrust in the horizontal direction, and the vertical driving device is used for providing vertically downward adjustable downward thrust; the net buoyancy of the cargo airship in the transportation process is larger than the sum of the weight of the cargo airship and the weight of cargoes borne by the cabin body; the cargo carrying airship can meet the requirement that net buoyancy is equal to the sum of downward thrust, the weight of the cargo carrying airship and the weight of cargoes borne by the cabin body in the transportation process. According to the cargo carrying airship, high-altitude transportation can be achieved, due to the fact that the net buoyancy borne by the whole cargo carrying airship in the transportation process is larger than the sum of the weight of the cargo carrying airship and the weight of cargos borne by the cabin body, the cargo carrying airship cannot fall down but floats upwards even under the extreme conditions such as insufficient energy, and therefore the safety of ground facilities and personnel is guaranteed.

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.

An aircraft thermal management system comprising a high temperature loop and a low temperature loop. The high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. The low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.

To provide a life support method, a life support device, a life support program, and a balloon cabin that can not only maintain the lives of passengers inside the cabin of a balloon used for manned flight at high altitudes by a balloon, but also safely and comfortably adjust the internal pressure and gas concentration. [Solution] A life support method within a balloon cabin 100 that is sealed during flight and can only be vented, which executes an internal pressure adjustment mode reading step for reading an internal pressure adjustment mode, a gas concentration adjustment mode reading step for reading a gas concentration adjustment mode, an internal pressure adjustment step for adjusting the internal pressure according to the internal pressure adjustment mode, and a gas concentration adjustment step for adjusting the gas concentration according to the gas concentration adjustment mode.

The utility model relates to an impact-resistant low-altitude unmanned aerial vehicle interceptor and interception equipment, the interceptor comprises an interception net which can be unfolded to be in a vertical plane state perpendicular to the ground or approximately perpendicular to the ground, the interception net is formed by weaving ropes or flexible fabric, the interception net comprises at least two pull-up nodes and at least two lower nodes, the pull-up nodes are connected with an aerostat for providing buoyancy, the lower nodes are connected with an anchoring structure, and the low-altitude unmanned aerial vehicle interceptor is configured as follows: the number of the pull-up nodes is at least three, and the number of the lower nodes is also at least three; and / or the low-altitude unmanned aerial vehicle interceptor further comprises a protective net and / or a restraint rope matched with the intercepting net. The number of the pull-up nodes and the pull-down nodes is increased, or deformation of the interception net is limited through the protective net and the restraint ropes, the stability of the interception net can be improved, the deformation amplitude of the interception net when the interception net is collided by the low-altitude unmanned aerial vehicle is reduced, and therefore the continuously-attacked low-altitude unmanned aerial vehicle can be smoothly dealt with.

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.

A system, method and apparatus are proposed to assist in assembling the frame, attaching the skin, and performing other tasks in manufacturing an airship and constructing other structures that are otherwise challenging, inefficient, or unsuitable for humans to perform, and / or that traditionally require significant investments in capital intensive manufacturing facilities. Several embodiments are proposed in which these and other recurring manufacturing tasks can be performed safely and efficiently with the assistance of autonomous, semi-autonomous, and / or human-directed robots, acting independently and in robot swarms.

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.

The invention relates to the technical field of the large aviation equipment design precision manufacturing industry, in particular to a modular design structure of a large load-carrying airship. The engineering manufacturing problem that a single-hull load-carrying airship is too large in load (huge in geometric dimension) is solved. According to the invention, two or more buoyancy modules are integrated on one load-carrying airship; the structure of the load-carrying airship comprises an airship control module unit, a buoyancy module unit, a skeleton structure module unit, a load structure module unit, a power module unit, an unloading balance control module unit and an auxiliary function module unit which cooperate with one another to complete an airship flight task.

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.