255 results about "Stratosphere" patented technology

A light weight photovoltaic device for use in stratospheric and outer space applications. The device includes a protective surface coating on the light incident side thereof. The protective coating does not deleteriously affect the photovoltaic properties of the solar cell, is formed of a material which protects said solar cell from the harsh conditions in the stratospheric or outer space environment in which the photovoltaic device is adapted to be used; and remains substantially unchanged when exposed to the harsh conditions in the stratosphere or outer space. The protective coating is preferably made of a spray coated silicone based material and is between 0.01 and 2 mil thick.

The invention discloses a control method for the flight path of an airship on the stratosphere. The control method comprises the following steps: firstly, giving out an instruction flight path of the airship; secondly, calculating an error margin e between the induction flight path of the airship and the actual flight path; thirdly, selecting a sliding mode surface s and a reaching law, designing a sliding mode control law and calculating the system control amount tau; and fourthly, designing a fuzzy controller with the sliding mode surface s as an input of the fuzzy controller and with a control parameter as an output of the fuzzy controller and adjusting the control parameter according to a fuzzy rule. According to the control method, the induction flight path can be stably tracked, the problem of buffeting caused by sliding mode control is solved, favorable robustness and dynamic performance are realized and an effective scheme is provided for designing a flight path control system of the airship on the stratosphere.

The invention discloses a medium-range forecast system and method for cold, rainy and snowy weather based on atmospheric variable physical decomposition. By utilizing the atmospheric space three-dimensional multivariable and time continuous grid data outputted in the past observed, the current observed and the medium-range numerical weather prediction modes, and the physical decomposition of the climate and the weather disturbance quantity, a causality between the regional sustained low temperature, rain and snow and freezing extreme weather events and the weather disturbance prior to and during the events is established in the method. According to the invention, a physical decomposition of the climate seasonal variation field and the day-to-day weather disturbance field is carried out according to the data of day-to-day three-dimensional space grid point temperature, altitude and wind and the like of the atmosphere from the troposphere to the stratosphere in the northern hemisphere for nearly 30 years, and a database for the atmospheric climate field and the weather disturbance field can be established; and a historical database of the low temperature, rain and snow and freezing weather in south China is established according to the data of day-to-day temperature and precipitation from the national meteorological station for nearly 50 years. The invention provides not only an inquiring system for historical low temperature, rain and snow and freezing weather events, but also a forecasting system for medium-range low temperature, rain and snow and freezing weather events.

Unmanned aircraft for telecommunicative or other scientific purposes, which is stationed at a determined height, in particular in the stratosphere. The aircraft includes a gas-filled balloon carrying a platform and equipment that maintains the platform in a position relative to the ground. The balloon carrying the platform is disposed in the interior of an external balloon of aerodynamical shape, particularly in the stratosphere. At least one low or high pressure insulation chamber filled with a medium is arranged between them and encircles the inner balloon. The medium used in the insulation chamber is a gas having a low thermal conductivity. The negative effects of the temperature differences are largely compensated so that the inner balloon can be produced from a lighter and cheaper material, thereby increasing durably its longevity.

A dropsonde system adopting a stratospheric balloon adopts the zero-pressure high altitude balloon to fly horizontally in the stratosphere according to the preset height, can adopt the actual situation of different wind directions in different height and adopt the means such as slinging, exhausting and the like to control the balloon to float to the target zone, and then throws the dropsonde down to detect the vertical profiles of the basic parameters such as atmospheric temperature, humidity, pressure, wind direction and speed and the like in the zone. In addition, the system also adopts the satellite relay communication technology and can detect the atmospheric condition over the sea or the uninhabited zones in deep desert.

The invention provides an ultra-light, weather-resistant and high-strength stratosphere skin material which has high strength and weatherability, relating to skin materials. The ultra-light stratosphere skin material consists of a weather-resistant layer, a force bearing layer, a block layer and a heat sealing layer from outside to inside. Vectran fiber 200 Daniel plain woven fabric with ultra-high strength is selected and used as the force bearing layer, the Vectran fiber 200 Daniel plain woven fabric has the strength about 6 times as high as that of common polyesters, and the light weight of 54 g / m<2> and the thickness of 0.16 mm. The produced stratosphere skin material has ultra-light mass.

The invention discloses an energy supply system for a stratosphere electricity-electricity hybrid solar airship. The system is an electricity-electricity hybrid energy supply system which takes a solar battery array as a main power supply, takes a regenerative hydrogen-oxygen fuel cell and a high-energy power storage battery pack as auxiliary power supplies, takes a direct-current brushless motor and driving controller as drive devices, takes an energy monitor as an energy distribution system, and takes a one-way DC / CD converter and a two-way DC / CD converter as voltage regulating devices. The solar battery array is connected with the one-way high-voltage DC / CD converter with maximum power point tracking through a cable; the one-way high-voltage DC / CD converter is connected with the driving controller of the direct current brushless motor through the cable; the controller controls the direct current brushless motor to drive a high altitude propeller; the one-way high-voltage DC / CD converter is connected with the two-way high-voltage DC / CD converter through the cable; and the one-way high-voltage DC / DC converter is connected with a charging regulator of the high-energy power storage battery pack. The energy supply system realizes reasonable distribution of power based on the energy monitor, and ensures the maneuvering safety and long service life of the stratosphere electricity-electricity hybrid solar airship.

A stratospheric airship plane path tracking control method based on model predictive control comprises a step of desired tracking value giving; a step of guidance error calculation in which the distance error and angle error between a desired position and an actual position are calculated; a step of vertical and horizontal dynamic equation decomposition in which only the horizontal state quantity is adopted in controller design; a step of discrete system equation solving in which a stratospheric airship lateral continuous system obtained by the steps above is linearly processed, error derivatives are linearly processed, then, the airship lateral state quantity and error are taken as an extended quantity, and an extended continuous state space equation is discretized; a step of system future prediction in which the state or output quantity of a future period of time is predicted according to the current state quantity obtained by a combined inertial navigation sensor and the like; and a step of model predictive control objective function construction in which an objective function is constructed with a predicted state quantity, and the function is solved by a standard QP algorithm to obtain the system input quantity.

The invention discloses a ground testing system suitable for a power source controller of a stratospheric airship. The ground testing system is applied to the development and test processes of the power source controller of the stratospheric airship. The ground testing system is composed of an industrial personal computer, a CAN bus, a data collecting unit, a solar battery array simulator, a storage battery simulator, a load simulator and an environment control simulation box. The CAN bus is adopted for communicating with the power source controller of the stratospheric airship, and combined with the industrial control computer and the data collecting unit, and testing on the function and the performance of the power source controller is finished under signals issued by the industrial control computer. The designed ground testing system reduces the testing cost and improves the testing efficiency.

The present invention relates to an aircraft and to a method of getting the aircraft onto station. According to the invention, said aircraft (1) includes propulsion means (2) capable only of enabling said aircraft (1) to move and to orient itself at high altitude, and said aircraft (1) is taken to its station in the high atmosphere, in particular in the stratosphere, by means of an independent transporter (3).

A rocket launch system (1) includes a tubular rocket launcher carriage (2) with electromotive cableway traction drives (26) conveyed beneath a two axis pivot (63) anchored to the earth, elevated into a co-axial transfer tube (124, 143) leading to three primary tether cables (27) whose weight is offset by balloons (164). The carriage is conveyed to a docking station (166) supported into the stratosphere by a pair of secondary cables (184) suspended under an attachment frame (162) for tensioning balloons. The carriage is engaged by a carriage end gripper (196) guided by two secondary and two tertiary cables (186) and lifted by a lower hoist (198) guided by the secondary cables. This lower hoist is supported by an upper hoist (168) suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring (183) guided by two secondary cables, is elevated further, rotated as desired, with rocket release and nearly recoilless ejection during freefall of the carriage, with engine ignition occurring at a safe distance.

The invention provides a solar module which is composed of a surface sealing film, a transparent adhesive film, a solar cell, a lightweight adhesive film A and an isolated substrate which are stacked from the top to the bottom in order; and the isolated substrate is composed of an isolated film, a carbon-fiber sheet, a lightweight adhesive film B, a honeycomb core, a lightweight adhesive film C and the carbon-fiber sheet which are stacked from the top to the bottom in order, wherein the honeycomb core inside also needs to be appropriately added embedded parts according to concrete operating requirements. The technical scheme of a preparation method of the solar module comprises following steps: (1) making use of an oven to match with a vacuum air pump to process a pre-compacting treatment for a carbon-fiber prepreg; (2) meanwhile, processing a welding sequence of the solar cell; (3) processing a cutting sequence; (4) processing a laminating technology treatment; (5) processing post treatment procedures which in order are: removing raw edges, embedding strakes, arranging a junction box, measuring high voltage, cleaning the surface, measuring photo-electrical output characteristics, classifying components, and examining the appearance. The solar module has the advantages of lightweight, high efficiency and good low-temperature characteristics, and being very suitable to being applied in the stratosphere.

A novel high resolution large visual field optical imaging system is composed of a share primary mirror, a microlens array and a detector array. The share primary mirror is in a holocentric spherical mirror structure, and the center of the share primary mirror is a spherical mirror. Two meniscus lenses are wrapped on two sides of the share primary mirror, and incident rays respectively pass through the share primary mirror and the microlens array, and finally reach the detector array for imaging. Through the computed imaging technology, image restoration is carried out on every sub-image (eliminating impact of spherical difference on image quality), and all sub-images are subjected to registration recombination to obtain a complete clear image. The novel high resolution large visual field optical imaging system is simple in structural type, and the visual field can reach 180 degrees in theory. The full visual field has a uniform resolution ratio, and combines with the computed image post processing technology, the systematic resolution ratio can be close to a diffraction limit in theory. The novel high resolution large visual field optical imaging system has the advantages of having an extra large visual field, a high resolution ratio, and the like, and particularly suitable for researching and finding of space targets in a wide range, air monitoring for a stratosphere, and the like.

The invention relates to a stratospheric airship with a hydrogen adjusting device, and belongs to the technical field of buoyancy adjusting of stratospheric airships. A hydrogen bag and air bags are included in an airship body in the stratospheric airship, a hood is included in the hydrogen bag, and a pressure sensor is included in the hood. A buoyancy lift adjusting system and a hydrogen storage ballast are included in a pod in the stratospheric airship. A buoyancy adjusting system comprises a hydrogen treatment system, a fuel storage box, an air storer, a fuel battery, an energy management system, a lithium battery, a water electrolyzer, a hydrogen purifier and a water storer. A hydrogen generation device is a container, and the middle of the container is divided by separation plates into four cavities. The hydrogen generation device is fixedly connected to the outside of the pod through a separating and unlocking device, and the hydrogen generation device is thrown out from the pod when the separating and unlocking device is opened.

The invention discloses a high-efficient heat exchange tube with a fine channel structure, which consists of an outer tube and a non-conducted inner tube that are sleeved with each other. The heat exchange tube is characterized in that a regular or irregular fine channel with the hydraulic diameter less than 3mm is formed between the outer tube and the inner tube; and the fine channel assumes a helical shape, a helical-like shape or a flat shape along the axial direction of the inner tube. The invention has the advantages of realizing the technology that an air-conditioning heat exchanger transfer heat through fine channel, eradicating the defects of the difficulty of dewatering and defrosting, heating impossibility, and the like, in the existing parallel follow art, realizing helixication of the fine channel, breaking through the problem that the common heat exchange tube can carries out high-efficient heat exchange on only one side, weakening or eliminating the stratosphere hindering heat exchange, which realize comprehensive high-efficient heat exchange of the whole heat exchange tube, maintaining the prior production equipment and the prior production process of a factory, maintaining the prior integral structure mode of the heat exchanger, and avoiding the problem that the prior production equipment and prior production process have to be replaced by adopting the prior parallel flow art, which greatly reduce cost.

The invention discloses a bag body telescopic stratospheric airship. In order to enable an airship to lift up into a stratosphere, a telescopic inner air bag, a telescopic outer air bag, and a principle that the pressure between the inner air bag and the outer air bag is balanced are adopted; when the airship flies into the stratosphere from the ground, the telescopic inner air bag and the telescopic outer air bag can be expanded to required volumes along with the continuous reduction of external ambient pressure; when the airship returns to the ground from the stratosphere, the telescopic inner air bag and the telescopic outer air bag can be reduced to the original volumes along with the continuous increase of the external ambient pressure, so that the appearance and the safety of the airship can be guaranteed; meanwhile, the hang time of the airship is prolonged by times.

Disclosed is a high altitude space launcher system for transferring payloads from surface to orbit at a significantly lower cost than conventional rockets. It comprises a aerostat lifted one stage light gas gun operating in stratosphere that shoots rocket assisted projectiles containing payload at near orbital velocities to a low angle trajectory. Alternatively, to launch acceleration sensitive payloads such as astronauts the light gas gun is replaced with a muzzle loaded conventional gun that shoots a single stage rocket at a much lower velocity. The system is mostly static structure, attached to a tether-elevator that moors it to land or a ship and provided it with electricity and lifts the projectiles to the gun.

The invention discloses a horizontal position control system for a stratospheric airship as well as an implementing method. The horizontal position control system comprises a horizontal position control module, a gravity / buoyancy difference selection module, a pitching control module, a pitching control distribution module, a thrust velocity control module and a state measurement module, wherein the pitching control module obtains pitching moment and outputs the pitching moment to the pitching control distribution module with a pitching angle control algorithm according to the instruction tracing speed, so that the pitching moment can be distributed between a front / rear balloonet and an elevator and output to an aircraft. Rise and fall schemes for the stratospheric airship are established on the basis of a thermal model, and a method for controlling the forward velocity of the airship through a pitching angle is provided; an elevator and balloonet variable-weight optimal control strategy is adopted in pitching angle control to realize pitching control, a switch distribution method is adopted in velocity control to combine the pitching angle with vectored thrust, the capacity of the existing actuator of the airship is used effectively, and forward velocity control of the airship in a strong-wind field is realized. The horizontal position control system is applied to horizontal position control of the stratospheric airship in the rise and fall processes.

The invention discloses a wingspan-changeable inflatable floating and rising integrated stratospheric airship. The wingspan-changeable inflatable floating and rising integrated stratospheric airship comprises a central cabin and two wingtip cabins. Four propeller propelling devices are mounted on the central cabin, and two propeller propelling devices are mounted on each wingtip cabin. Double-row wings are adopted, and the interior of a front wing body and the interior of a rear wing body of each wing are both provided with three air chambers distributed in the extension direction. All the air chambers are separated from one another through supporting ribs. The inner surfaces of all the wing bodies adhere to the outer profiles of the supporting ribs. Telescopic rod sets are arranged in the air chambers respectively, the diameters of telescopic rods of the telescopic rod sets in the air chambers are different, and thus the telescopic rods in the air chambers can stretch and retract in a nested mode. The wingspan-changeable inflatable floating and rising integrated stratospheric airship has the advantages that the aerodynamic efficiency is high, and generated dynamic lifting force is large; both control and manipulation are quite convenient, and adjustment of different air-staying heights is achieved by adjusting the extension lengths of the wings.

The invention discloses a convection heat-radiation system for temperature control of electronic equipment close to space vehicle, comprising an electronic equipment pressure maintaining cabin, a liquid storage tank, a pump, an in-cabin finned-pipe heat exchanger, a fan for an in-cabin radiator, an extravehicular finned-pipe heat exchanger, a fan for an extravehicular radiator, a pipeline and circulating fluid, the inlet of the pump is connected with the outlet of the liquid storage tank, the inlet of the liquid storage tank is connected with the outlet of the in-cabin finned-pipe heat exchanger, the inlet of the in-cabin finned-pipe heat exchanger is connected with the outlet of the extravehicular finned-pipe heat exchanger, the inlet of the extravehicular finned-pipe heat exchanger is connected with the outlet of the pump, and the circulating fluid working medium is filled in the pipeline; in the invention, a fluid loop coupling type convection radiator is arranged, waste heat in the electronic equipment is transmitted to the finned-pipe heat exchanger through the fluid loop and is discharged to the ambient atmosphere through the convection radiator driven by the motor; the convection radiator is used in special working environment at bottom part of a stratosphere to carry out heat radiation of high-power electronic equipment, and the structure is compact.

The invention provides a bionic stratospheric airship, and belongs to the technical field of aircraft design. The shape of a hull of the stratospheric airship is obtained according to the shape setting out of a portuguese man-of-war. The hull is internally provided with more than one main airbag, more than one auxiliary airbag and a heat-regulating airbag. The main airbags are filled with gas withthe density lower than air, the main airbags are disposed on an upper layer in the hull, and first gas valves are arranged on the upper parts of the main airbags. The auxiliary airbags are filled with the air, the auxiliary airbags are disposed on a lower layer in the hull, and second gas valves and blowers are arranged at the bottoms of the auxiliary airbags. The heat-adjusting airbag is arranged in a middle layer in the hull, and the heat-regulating airbag is internally provided with a thermal cycle device. The heat-regulating airbag is filled with a gas-liquid reversible control working medium. Under the working conditions of super-thermal and over-pressure, the working medium is converted from a gaseous state to a liquid state by the thermal cycle device, and the working medium is converted from the liquid state to the gaseous state by the thermal cycle device under the ultra-cold working condition.

The invention relates to a stratospheric airship flight performance parameter estimation method and system. The stratospheric airship flight performance parameter estimation method comprises the steps: enabling an airship in a steady circling flight state; acquiring ground velocity, attitude angle information and position information of the airship; estimating flight performance parameters of the airship according to the ground velocity, attitude angle information and position information of the airship. According to the stratospheric airship flight performance parameter estimation method and system, which are provided by the invention, the accurate flight performance parameters, such as horizontal wind velocity, wind direction, airspeed, steady circling radius, circling period, circling angular speed, sideslip angle, attack angle and the like, can be computed by utilizing the ground velocity, position information and attitude angle information given out by a navigation system of the airship under an upper thin atmosphere environment; furthermore, the process is simple and is easy to implement; as long as main propeller rotation speed and yaw controlled quantity are constant, the airship can start the circling flight state; due to the circling flight, the airship has a constant altitude, and the wind speed and the wind direction are also constant, so that the airship is located under a constant wind field, and airship flight performance parameter estimation errors are reduced.

The invention provides a method for bringing a mobile base station into the stratosphere by using a hot-air balloon to restore communication. After an earthquake, communication services in a disaster area will be inevitably interrupted; and however, disaster relief allows of no delay and the interruption of the communication is not favorable for earthquake relief works. Therefore, it is necessary to invent a technology for restoring communication services in the area within a short time. As a large-sized hot-air balloon is made to bring the mobile base station into the stratosphere (the weather in the stratosphere is stable, the coverage of the stratosphere is wide and the stratosphere is not affected by weathers) and electric energy is required by the mobile base station to transmit a signal, a solar power generating material covers the surface of the hot-air balloon. Once the earthquake occurs, the hot-air balloon is released to restore the communication services and the rescue department can send self-saving methods and other information to people in the disaster area through the communication services. According to the large-sized hot-air balloon manufacturing technology, the mobile base station, the stratosphere solar power generating technology and so on in the invention, the communication services in the disaster area are rapidly restored after the earthquake to organize the disaster relief works and save people lives.

The present invention discloses a stratosphere meteorological parameter fixed high detection device. The device comprises a sounding balloon, a fixed high balloon and a meteorology sonde. The sounding balloon is located above the fixed high balloon; the meteorology sonde is located below the fixed high balloon; the sounding balloon and the fixed high balloon are connected through a sounding plumb rope; the fixed high balloon and the meteorology sonde are connected through a fixed high plumb rope; the sounding plumb rope is provided with a cutting device for cutting the sounding plumb rope after the sounding balloon and the fixed high balloon reach the object height. The stratosphere meteorological parameter fixed high detection device is simple in structure, easy to operate, low in cost, adjustable in flight height, short in preparation time and easy to flexibly enforce and is able to effectively improve the reliability of the stratosphere meteorological parameter fixed high detection.

The invention relates to an autonomous celestial navigation method for a deep space probe on a near-earth parking orbit. The method comprises the following steps: performing continuous height (20-50km) modeling and fitting in the stratosphere on density scale height H according to data given by United States atmosphere standard in 1976, establishing a stellar atmospheric refraction model, establishing a novel measurement model by taking height difference at adjacent moments as observed quantity, and estimating the navigation parameters by adopting a method for correspondingly improving extended Kalman filter parameters. The autonomous celestial navigation method is applied to navigational positioning of the deep space probe on the near-earth parking orbit, errors caused by the environment can be eliminated on the basis that extra observed quantity is not increased, and the navigation accuracy is guaranteed.

A method and system for protection against natural temperature-dependent dangerous phenomena connected with huge streams mainly water, mud, locust. The method allows weakening these streams and allows protecting against these dangers at least at of the first two stages of development of said phenomena: forming these masses and their moving, as far as possible. The method allows protecting ecology and increasing CO2 absorption. The system allows also transporting the electrical energy that is received from solar radiation with help of solar cells flying in stratosphere to ground-based reception stations.

The invention provides a steady taking-off and landing method for a stratospheric airship provided with a taking-off assisting balloon, a wide airship body and variable wings. A solar power generation device is laid on the upper portion of the wide airship body of the airship. The folding airship wings are mounted on the two sides of the wide airship body and are each of a framework structure, and solar cells of the solar power generation device are fixedly mounted on the upper portions of the folding airship wings. The folding airship wings can be folded to retract or unfolded flatly. Vector propellers are symmetrically mounted on the two sides and the rear portion of the wide airship body. Inflation or deflation of the wide airship body is completed through a pressure system. The solar power generation device is used for supplying power to the vector propellers, the pressure system, the folding airship wings and a flight control system. The flight control system is electrically connected with the solar power generation device, the vector propellers, the folding airship wings and the pressure system. The solar cells are laid on the airship wings, the laying area is enlarged, light energy is converted into sufficient electric energy to drive the vector propellers, and thus sufficient power is provided for the airship; and meanwhile, the pitching angle of the airship can be controlled, the airship is kept cruising at a certain altitude, and both the controllability and the power are remarkably improved.

The invention provides a stratospheric airship buoyancy and pressure cooperative control method and belongs to the technical field of aircraft flight control. The method includes setting an upper limit value Pu and a lower limit value P1 of the pressure difference between the inside and the outside of a stratospheric airship body, measuring the air pressure P and P' inside and outside the stratospheric airship body respectively, calculating the pressure difference between the inside and the outside of the stratospheric airship body that Pe=P-P', comparing the pressure difference Pe and the upper limit Pu and the lower limit value Pl of the stratospheric airship body and adjusting the buoyancy and the pressure cooperatively by adopting a buoyancy lift airbag, an air bag and an adjusting airbag according to the relation. The thermodynamic parameters of a working medium are adjusted by a thermodynamic cycle device, so that the volume and the pressure of the adjusting airbag are changed, and the pressure and the buoyancy of the stratospheric airship are adjusted accordingly.

The invention relates to backbone network networking transmission technology in the spatial communication field, and discloses a microwave-assisted spatial information network backbone networking transmission method. The method comprises steps: (1) spatial information network backbone nodes comprise a large-capacity communication satellite located in a synchronous orbit and a high-altitude communication platform in the stratosphere, and each backbone node has microwave and laser transmission means; (2) a backbone node accessed to the network newly uses the microwave means to send an access network application in a public control channel, access network approval is completed by an operational control central station, and node routing information is updated in a special control channel; and (3) a user initiates an access application, a backbone node in charge of access judges service requirements, transmission of low-speed service is completed in the microwave means, and as for high-speed service, the microwave means first assists to build a laser link, and signal transmission is then completed in the laser link. The broadcasting ability of the microwave and the high-speed ability of the laser are combined, and a flexible and high-speed transmission ability is provided for the satellite backbone network.

The present invention discloses an energy supply system of a stratosphere solar energy airship and a control method thereof. The system comprises an energy monitoring unit and a solar generation unitand an energy storage unit which are connected with the energy monitoring unit. The solar generation unit is connected with a power supply bus in an airship through the energy storage unit, the energymonitoring unit comprises multiple generation paths, each generation path comprises one solar cell array, one MPPT module and one control switch module which are connected in order, and the energy monitoring unit controls output of each MPPT module and charge and discharge of the energy storage unit according to the power required by a load, and controls on-off of each control switch module according to the residual energy of the energy storage unit. The control method is configured to control the system mentioned above. The energy supply system of the stratosphere solar energy airship and the control method thereof are simple in structure, low in cost and high in energy supply efficiency and utilization rate, can meet the long-term continuous power supply demand of the stratosphere airship, and are stable and reliable, etc.