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36results about How to "Long sailing time" patented technology
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Aircraft, preferably unmanned
InactiveCN104364154AExtension of timeExpand the scope ofUnmanned aerial vehiclesEfficient propulsion technologiesFlight vehicleUncrewed vehicle
The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or unmanned aerial system (UAS), comprising a rigid wing (2), which enables aerodynamic horizontal flight, and at least four rotors (4, 4'), which are driven by means of controllable electric motors (5) and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism (7), wherein all electric motors (5) and rotors (4) are arranged on the wing (2).
Owner:QUANTUM SYST GMBH
Buoyancy compensation control method for AUV (autonomous underwater vehicle) in deep submergence motion
ActiveCN107776859AEliminate pitch deviationImprove maneuverabilityUnderwater vesselsUnderwater equipmentMarine engineeringRunning time
The invention provides a buoyancy compensation control method for an AUV (autonomous underwater vehicle) in deep submergence motion. The method comprises steps as follows: depth of the AUV during depth-fixed navigation in a deep sea area is detected; residual buoyancy to the AUV during depth-fixed navigation in the current deep sea area is identified with an AUV residual buoyancy identification algorithm; when the identification result is stable, the AUV is subjected to buoyancy compensation by an oil sac type buoyancy balancing system, otherwise, the residual buoyancy to the AUV during depth-fixed navigation in the deep sea area is identified continuously; when a buoyancy identification value of the AUV is equal to a residual buoyancy value identified with the AUV residual buoyancy identification algorithm, buoyancy compensation for the AUV is finished; otherwise, buoyancy compensation for the AUV is continued. According to the buoyancy compensation control method for the AUV in deepsubmergence motion, influence of the residual buoyancy can be effectively balanced, trim angle deviation of the AUV is eliminated, controllabitity and control precision of the AUV are improved, resistance to the AUV during depth-fixed navigation is reduced, and the running time of the AUV is prolonged under the condition of carrying the same energy.
Owner:HARBIN ENG UNIV
Wave glider with evaporative waveguide monitoring system
ActiveCN111717359ARealize accumulationLarge monitoring areaPropulsion power plantsIndication of weather conditions using multiple variablesFrequency spectrumData information
The invention relates to a wave glider with an evaporative waveguide monitoring system. Through an evaporation waveguide electromagnetic channel monitoring system carried on a wave glider, a near seasurface channel monitoring link is established; according to application requirements, a motion path of the wave glider is planned; channel monitoring data and marine meteorological data of a specified sea area and a specified frequency are obtained; through a beidou communication technology, data information monitored in real time is transmitted to a shore-based service platform; and algorithms such as evaporation waveguide inversion, interpolation and the like are utilized to acquire large-area region evaporation waveguide distribution characteristics. The wave glider is wide in monitoring area, long in endurance time, real-time, accurate and the like, mass basic data accumulation, marine environment real-time monitoring and marine monitoring data sharing can be finally achieved, and data support and technical support are provided for marine and electromagnetic environment detection, spectrum management, electronic system aided decision making and the like.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Stern shaft sealing device
ActiveCN106321855ALong sailing timeGuaranteed normal navigationEngine sealsTransmission with propulsive element synchronisationEngineeringMechanical engineering
The invention belongs to the technical field of ships and relates to a stern shaft sealing device. The stern shaft sealing device comprises an installation base; an air bag is fixed into an inner hole of the installation base; the installation base is provided with a first sealing ring bracket which is connected with a second sealing ring bracket through a connecting piece; the outer end of the second sealing ring bracket is fixedly connected with a sealing ring; the end surface of the sealing ring is provided with a supporting ring in an attached mode; the supporting ring is connected with a transmission ring; an emergency sealing body is installed between the installation base and the first sealing ring bracket and is a whole circle defined by a plurality of equational circular-arc structures; and each circular-arc structure can move in the radial direction. The stern shaft sealing device has an adjustable emergency sealing function, and an emergency mechanism can be repeatedly used; adjusting is convenient, and the service life is long; and thus, the emergency capacity of a ship during sailing is greatly improved, and the effect that the ship can continue to keep sailing for a long time after a main stern shaft sealing body breaks down during distant sailing is ensured.
Owner:WUXI HONGYUAN DEVFLEX
Self-propelled dropsonde system
ActiveCN105000183AGood value for moneyCost-effectiveEfficient propulsion technologiesPower plant typeWork PerformancesHydrogen storage system
A self-propelled dropsonde system comprises an unmanned aerial vehicle on which a propeller motor, an airborne flight control system and a sonde. A hydrogen storage system is arranged at the interior front part of an unmanned aerial vehicle body; an environment control cabin with a fuel cell is mounted at the middle part of the unmanned aerial vehicle body; and the airborne flight control system is arranged at the rear part of the unmanned aerial vehicle body. The self-propelled dropsonde system provided by the invention is advantaged in that an optimal weight ratio of about 1 / 10 between a dropsonde and an aircraft and the ceiling is high. As the fuel cell is used as unmanned aerial vehicle energy, the flight time is long. Through an air collecting chamber and a supercharger, the air is heated and pressurized by the unmanned aerial vehicle; and the air inlet temperature and the air density of the environment control cabin are adjusted; therefore, the working performance of the fuel cell at high altitude is improved and enough power for guaranteeing cruising duration is provided to the unmanned aerial vehicle. As a plurality of sondes are mounted on the self-propelled dropsonde system, meteorological data of the atmosphere vertical section can be accurately detected from the plurality of dropsondes at altitudes of 12-20 km in once launching. The self-propelled dropsonde system provided by the invention is advantaged in that the system is economic and environment-friendly and the cost performance of the system is higher.
Owner:CMA METEOROLOGICAL OBSERVATION CENT
A three-purpose vertical take-off and landing aircraft
InactiveCN109263967ALong sailing timeStable flightSteering ruddersAircraft controlLeading edgePost disaster
The invention relates to a three-purpose vertical take-off and landing aircraft, belonging to the technical field of aircraft, comprising a fuselage, a wing, a reversing lifting device, a vertical lifting device and a rudder. The fuselage has a flat rhombus structure, and a main controller is arranged in the fuselage, and the main controller is connected with a reversing lifting device, a verticallifting device and a rudder. The wing adopts forward swept wing. The reversing lifting device is located at the leading edge of the wing and can be steered 90 degrees under the control of the mastercontroller to provide vertical lift or forward pull for the aircraft. The vertical lifting device is arranged at the rear end of the fuselage, and the vertical lifting device provides the upward lifting force for the aircraft in the form of rotating the paddle blades driven by an electric motor. The rudders are arranged at the tips of both sides of the wing. The invention can carry out vertical take-off and landing, has long sailing time, stable flight process, has two lifting modes, has high safety coefficient, and is suitable for logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Cage type foldable multi-rotor heavy-duty large unmanned aerial vehicle
The invention relates to a cage type foldable multi-rotor heavy-duty large unmanned aerial vehicle, and belongs to the technical field of aviation. The cage type foldable multi-rotor heavy-duty largeunmanned aerial vehicle includes a cage airframe, a flight control device, a lift device and an attitude control device, four folding frames are unfolded, and a front left movable arm, a front right movable arm, a rear left movable arm and a rear right movable arm are unfolded; an engine is started, the engine drives left and right rotating shafts to rotate through a synchronous belt, and the leftrotating shaft and the right rotating shaft drive a large left propeller and a large right propeller to rotate crosswise; by increasing the rotating speed of the engine, the large left propeller andthe large right propeller speed up to produce larger lift, the unmanned aerial vehicle takes off vertically, and the flying attitude of the unmanned aerial vehicle is adjusted by adjusting the attitude control device; and during landing, the rotating speed of the engine is lowered, the unmanned aerial vehicle slowly lands vertically, and balance of the unmanned aerial vehicle is adjusted by adjusting the attitude control device. According to the cage type foldable multi-rotor heavy-duty large unmanned aerial vehicle, the airframe is made of an aluminum alloy or a titanium alloy by welding, andcan be folded to facilitate parking and transportation of the unmanned aerial vehicle; and the lift is large, stability is good, and the cage type foldable multi-rotor heavy-duty large unmanned aerial vehicle is suitable for lifting and hanging operation.
Owner:广东电网能源发展有限公司
A four-axle vertical take-off and landing fixed-wing aircraft
InactiveCN109250101ALong sailing timeSmooth flightAircraft stabilisationRotocraftPost disasterFlight vehicle
A fort-axle vertical take-off and landing (VTOL) fixed-wing aircraft belongs to that technical field of aircraft, and comprises a fuselage, a wing, a tail wing, a left rotor thrust device, a right rotor thrust device, a tilting mechanism, a flight control device and a movable pin, wherein the four-axis vertical take-off and landing fixed-wing aircraft comprises a right rotor thrust device, a tilting mechanism, a flight control device and a movable pin. In VTOL and hover flight, left rotor thrust unit, the right rotor thrust unit is locked in the horizontal position, From hovering to fixed-wingflight, Unlock the left rotor thrust first, Horizontal position of the right rotor thrust device; the left rotor thrust device and the right rotor thrust device are locked after the left rotor thrustdevice and the right rotor thrust device are erected, and the flight attitude of the aircraft is controlled by controlling the aileron and the tail wing. The left rotor thrust device and the right rotor thrust device are locked after the left rotor thrust device and the right rotor thrust device are erected. The invention can perform vertical take-off and landing, the flight process is stable, the safety factor is high, and the invention is suitable for the work of logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
A tilt vertical take-off and landing fixed-wing aircraft
InactiveCN109250100ALong sailing timeStable flightAircraft stabilisationRotocraftJet aeroplanePost disaster
A tilt vertical take-off and landing fixed-wing aircraft belongs to the technical field of aircraft, and comprises a fuselage, a wing, a tail wing, a left rotor thrust device, a right rotor thrust device, a driving motor, a rotating shaft, and a flight control device, wherein, the tilt vertical take-off and landing fixed-wing aircraft comprises a fuselage, a wing, a tail wing, a left rotor thrustdevice and a right rotor thrust device. The inner wing is fixed on the fuselage, and the inner wing and the outer wing are fixed by fixing rods. The outer wing is fixed on the fuselage by fixing rods.The outer wing is provided with an aileron; Left rotor thrust device and right rotor thrust device are provided with connecting rods; a left rotor thrust device and a right rotor thrust device are movably connected between an inner wing and an out wing of that wing through a bearing structure; Both the left rotor thrust device and the right rotor thrust device provide thrust force in the form that the motor drives the propeller to rotate. The driving device drives the rotating shaft. The rotating shaft tilts both the left rotor thrust device and the right rotor thrust device via a synchronousbelt. The invention can perform vertical take-off and landing, the flight process is stable, the safety factor is high, and the invention is suitable for the work of logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Energy system control device for continuously sailing unmanned boat
PendingCN109391019AExtend sea area operation timeAchieve year-round continuous sailingBatteries circuit arrangementsPropulsion power plantsCapacitanceEngineering
The application discloses an energy system control device for a continuously sailing unmanned boat. The energy system control device comprises a solar panel component, a solar panel controller matrix,an inverter power supply, a switchboard system, a boat power supply system, a combined control unit, a coupler, a super capacitor component and a lithium battery component; wherein the control end ofthe coupler is connected to the output end of the combined control unit; the power input end of the coupler is connected to the solar panel component through a DC bus; the first energy storage end ofthe coupler is connected to the super capacitor component; the second energy storage end of the coupler is connected to the lithium battery component; and the power output end of the coupler is connected to the inverter power supply. Through a technical solution implemented by the combined control unit in the present application, the solar energy utilization ratio of the unmanned boat is improved, and the offshore working time of the unmanned boat is prolonged, thereby realizing the continuous sailing of the unmanned boat throughout the year.
Owner:SHANGHAI JIAO TONG UNIV
Self-propelled drop sounding system
ActiveCN105000183BGood value for moneyCost-effectiveEfficient propulsion technologiesPower plant typeHydrogen storage systemFlight time
Owner:CMA METEOROLOGICAL OBSERVATION CENT
Eight-rotor manned vehicle
InactiveCN109263878AImprove stabilityReliable powerFreight handlingPower plant typeJoystickInformation capture
The invention discloses an eight-rotor manned aircraft comprising the aircraft body and flight control system, a main body of that aircraft include a manned cabin, a landing gear, a support arm fixedly connected to the manned cabin and a rotor fixed to the support arm, the manned cabin comprises a seat, a left control lever and a right control lever for controlling flight, and a display system forobserving the position information of the aircraft, and the environment state of the aircraft during flight can be observed through image information captured by a rocking camera installed at the front end of the aircraft; the manned cabin comprises a left control lever and a right control lever for controlling flight. The flight control system is divided into two parts to control the setting ofthe rotor, so that the aircraft has more power and more flexibility; Hybrid power supply ensures the power source. Hybrid power supply converts the excess energy of light load into electric energy when the aircraft is decelerated or descended, thus achieving the purpose of saving fuel and fast starting, and prolonging the sailing time.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
A vertical take-off and landing aircraft
InactiveCN109263896ALong sailing timeStable flightFloatsVertical landing/take-off aircraftsJet aeroplanePost disaster
The invention relates to a vertical take-off and landing aircraft, belonging to the technical field of aircraft, comprising a fuselage, a wing, a tail wing, a movable blade, a telescopic rod, a buoy,a multi-rotor device, a driving device and a transmission rod. The root of the wing is movably connected to the left and right sides of the fuselage through the movable blades. There are two telescopic rods, which are symmetrically arranged on the left and right sides, and the upper and lower angles of the wing are adjusted by adjusting the length of the two telescopic rods simultaneously. There are two buoys which are symmetrically arranged at the wing tips of the wing. The fuselage is provided with a groove. The driving device is connected with one end of the driving rod through a gear structure, so that the driving device drives the driving rod to rotate in the groove of the fuselage. The other end of the drive lever is secured to the frame at the center of gravity of the multi-rotor device, and the multi-rotor device rotates with the drive lever as it rotates. The invention can be used for vertical take-off and landing, long sailing time, stable flight process and high safety factor, and is suitable for logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
A loop-wing vertical take-off and landing aircraft
InactiveCN109263955ASimple structureLong sailing timeAircraft controlWing shapesLeading edgePull force
A loop-wing vertical take-off and landing aircraft belongs to that technical field of aircraft and comprises a loop-wing, a thrust device and a flight control device. The annular wing is annular. Thethrust devices provide thrust in the form of propeller rotating driven by the engine, and the engine is distributed on the leading edge of the annular wing. The flight control device is connected withthe engine on the thrust device through an electric signal, and the rotational speed of the engine on the thrust device is controlled by the flight control device, so that the annular wing is tilted;Providing vertical lift to the aircraft when the thrust device is in the horizontal position. The thrust device provides the aircraft with a forward pull when it is in a vertical position. The invention can be used for vertical take-off and landing, air hovering, long sailing time, stable flight process, high safety factor, air reconnaissance and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
An aircraft capable of taking off and landing vertically
InactiveCN109263915ALong sailing timeStable flightVertical landing/take-off aircraftsRotocraftAirplaneTailplane
The invention relates to an aircraft capable of taking off and landing vertically, belonging to the technical field of aircraft, comprising a fuselage, a left wing, a right wing, a tail wing, a multi-rotor device, a front telescopic rod, a rear telescopic rod, a left telescopic rod and a right telescopic rod. The fuselage is provided with a fixed rod, and the left wing and the right wing are movably connected to the fixed rod through a bearing structure. The front telescopic bar and the rear telescopic bar are symmetrically arranged forward and backward, one end of which is respectively connected above the fuselage at the position of the center of gravity of the aircraft, and the other end of which is correspondingly connected to the front and rear frames of the multi-rotor device; changing the lift direction of the multi-rotor device through the front telescopic rod and the rear telescopic rod; a left telescopic rod and a right telescopic rod are symmetrically arrange left and right,one end of which is respectively connected with a left and a right frame of that multi-rotor device, and the other end of which is correspondingly connected with an upper wing surface of the left wingand a right wing and is close to a leading edge; change the angle of attack of the left and right wings by means of the left and right telescopic rods. The invention can carry out vertical take-off and landing, has long sailing time, stable flight process and high safety factor.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
A multi-axis fixed-wing aircraft
InactiveCN109263921ALong sailing timeStable flightAircraft power plantsRotocraftJoystickPost disaster
A multi-axis fixed-wing aircraft belongs to the technical field of aircraft, and comprises a fuselage, a left wing, a right wing, a tail wing, a thrust device, a joystick, a rotating shaft and a flight control device. The left and right flanks have a certain angle of attack. The joystick is connected to a rotating shaft which is movably connected to the fuselage and wing and is arranged laterallywithin the fuselage and wing. The thrust devices provide thrust force in the form that the engine drives the propeller to rotate, the engine is connected with the rotating shaft through a support frame, and a plurality of engines mounted on the support frame are uniformly arranged on the leading edge, the trailing edge and the wing tip of the wing; and the thrust devices provide thrust force in the form that the engine drives the propeller to rotate. The flight control device is connected with the engine on the thrust device through an electric signal. The rotating shaft is rotated by the push-pull lever, and the rotating shaft drives the engine to tilt under the action of the support frame, thereby changing the direction of the pulling force generated by the engine. The invention can carry out vertical take-off and landing, the flight process is stable, and is suitable for logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Fuel cell hybrid power system for small inland river boat
InactiveCN109649624ALong sailing timeGuaranteed safety and reliabilityPower plants using propulsion unit combinationsPropulsive elementsSpecific gravityCapacitance
The invention discloses a fuel cell hybrid power system for a small inland river boat. By parallel output of a fuel cell and a supercapacitor, when one power source is in performance decline, the other one can provide energy required by the small inland river boat. The output voltage of a fuel cell stack passing through a single-way DC / DC converter is higher than the full voltage of the supercapacitor. When the small inland river boat requires low output power, the fuel cell provides energy and charges the supercapacitor until the supercapacitor is fully charged, and then charging is stopped.When the output power required by the small inland river boat exceeds capacity of the fuel cell, the fuel cell and the supercapacitor operate simultaneously to provide power for the small inland riverboat. Once fuel cell faults or fuel exhausting occur in a navigation process of the small inland river boat, a diesel generating set starts to provide electric energy for the small inland river boatto return. Therefore, navigation time of the small inland river boat can be prolonged to the greatest extent, an air power system is simplified, a proportion of a power system is decreased, and systemenergy consumption is reduced.
Owner:WUHAN UNIV OF TECH
An aircraft
InactiveCN109263916ALong sailing timeStable flightAircraft stabilisationRotocraftGravity centerRotary wing
The invention relates to an aircraft, belonging to the technical field of aircraft, comprising a fuselage, a left wing, a right wing, a tail wing, a multi-rotor device, a support bar, an upper telescopic bar, a left telescopic bar and a right telescopic bar. The fuselage is provided with a fixed rod, and the left wing and the right wing are movably connected to the fixed rod through a bearing structure. The lower end of the support rod is fixed above the fuselage of the aircraft at the center of gravity position, and the upper end of the support rod is connected to the frame at the center of gravity position of the multi-rotor device through a bearing structure; the multi-rotor devices provide upward lift or forward pull to the aircraft; one end of the telescopic rod is connected to the support rod and the other end is connected to the multi-rotor device; a left telescopic rod and a right telescopic rod are symmetrically arranged, one end of which is connected with a support rod, and the other end of which is correspondingly connected with an upper wing surface of the airfoil and is close to a leading edge. The angle of attack of the left wing and the right wing is changed by the telescopic movement of the left and right telescopic rods. The invention can carry out vertical take-off and landing, has long sailing time, stable flight process and high safety factor.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
A vertical take-off and landing aircraft with multiple axes combined with fixed wings
InactiveCN109250102AEasy to observe headingEasy to observe heightPower plant typeRotocraftPost disasterGear wheel
The invention relates to a vertical take-off and landing aircraft with multiple axes combined fixed wings, belonging to the technical field of aircraft, comprising a fuselage, a wing, a tail wing, a transmission rod, an operation rod, a cross beam, a multi-rotor device and a landing gear. The wing is provided with an aileron, the left section and the right section of the wing are symmetrically provided with notches, and the notches are parallel to the central axis of the fuselage. The tail includes a horizontal tail and a vertical tail, which are located at the end of the fuselage. The transmission rod is located at the position of the lift point of the wing, and is arranged on the left and right sections of the wing through bearings. The operating lever is arranged in the fuselage, and isconnected with the transmission lever through a gear set for controlling the rotation angle of the transmission lever. The invention relates to a multi-axis vertical take-off and landing fixed-wing aircraft, which combines the advantages of a multi-rotor device and a fixed-wing aircraft, can carry out vertical take-off and landing, hovering in the air, long sailing time, stable flight process, high safety factor, and is suitable for logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
A vertical take-off and landing aircraft
InactiveCN109263950AImprove lifting efficiencyIncrease air velocityVertical landing/take-off aircraftsSkis/runnersLeading edgeFlight vehicle
The invention relates to a vertical take-off and landing aircraft, belonging to the technical field of aircraft, comprising a wing, a flight control device, a tail wing, a rotor device, a rotary arm mechanism, a traction device and a controller. Having a cockpit on the wing; a controller is arranged in the cockpit. The motors on the rotor device are arranged in a distributed manner. The motor located at the leading edge and the trailing edge of the wing is respectively connected with the leading edge and the trailing edge of the wing through two rotating arm mechanisms. The motor located at the wing tip is fixed on the outside of the wing tip through a connecting rod structure. The two ends of the traction device are respectively connected with two turning arm mechanisms; when the propeller on the motor is in the horizontal position by swinging the two rotating arm mechanisms, the traction device is in the longest state. The wing is also provided with a locking mechanism which locks the traction device to the wing and prevents the traction device from being pulled forward or backward. The invention can carry out vertical take-off and landing, has long sailing time, stable flight process and high safety factor.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Aerial monitoring type unmanned aerial vehicle
ActiveCN111806675AIncrease buoyancyLong sailing timeAircraft controlWithdrawing sample devicesHydrogen compressionElectrical battery
The invention relates to the technical field of unmanned aerial vehicles, and discloses an aerial monitoring type unmanned aerial vehicle which comprises a fixed circular plate, a remote controller and an air sampling bag, wherein an external solar flexible charging panel is fixedly mounted on the upper surface of the fixed circular plate. The hydrogen compression tank and the folding bag are arranged, when the unmanned aerial vehicle rises to a preset height, the hydrogen compression tank is used for filling hydrogen into the folding bag through the hydrogen filling electromagnetic valve, thebuoyancy of the unmanned aerial vehicle is increased, the rotating speed of the fan blades can be reduced, low energy mode operation is entered, the power consumption in the battery is reduced, therefore, the navigation time of the unmanned aerial vehicle is prolonged, the monitoring range and the monitoring time of the unmanned aerial vehicle are expanded, collision between airflow and the fan blades is reduced, the stability of the unmanned aerial vehicle is improved, meanwhile, through arrangement of the first servo motor and the second servo motor, the rotating posture of the fan blades can be changed, balance can be formed between the fan blades and the airflow, and the stability between the unmanned aerial vehicles is further improved.
Owner:重庆唯客科技有限公司
A special-shaped aircraft
InactiveCN109263920ALong sailing timeStable flightWing shapesPower plant typeJet aeroplaneMotor drive
A special-shaped aircraft belongs to the technical field of aircraft, which comprises a fuselage, a wing, a tail wing, a left thrust device, a right thrust device, a front spar, a rear spar, a transmission rod and a landing gear. The wing has a definite angle of attack. The two wings on both sides of the fuselage are divided into an inner wing and an outer wing. The inner wing is connected to thefuselage, the outer wing is connected to the inner wing through a front spar and a rear spar, and there is a certain gap between the inner wing and the outer wing. The front and rear spar penetrate the wings on either side of the fuselage. The transverse arrangement of the transmission rods is at the center of gravity of the aircraft. The left thrust device and the right thrust device have the same structure, and both the left thrust device and the right thrust device provide thrust force in the form that the motor drives the propeller to rotate; a left thrust device and a right thrust deviceare symmetrically arrange on both sides of that fuselage and are connected to drive rods positioned between the inner wing and the out wing through a support frame. The invention combines the advantages of a multi-rotor device and a fixed-wing aircraft, and can carry out vertical take-off and landing, hover in the air, have long flight time, stable flight process and high safety factor.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Method and system for reducing vessel fuel consumption
PendingCN113365909ALow costReduce consumptionNavigational calculation instrumentsAuxillariesIndustrial engineeringShip master
Owner:SHELL INT RES MAATSCHAPPIJ BV
A water-landing drone
Owner:大强信息技术(深圳)有限公司
Vertical take-off and landing seaplane
The invention relates to a vertical take-off and landing seaplane, belonging to the technical field of aircraft, comprising a fuselage, a wing, a reversing lifting device, a vertical lifting device, atail rotor and a buoy. A main control is arranged in that fuselage, and the main control is connected with a reversing lifting device, a vertical lifting device and a tail rotor. The wing adopts forward swept wing. The reversing lifting device is located at the leading edge of the wing and can be steered 90 degrees under the control of the master controller to provide vertical lift or forward pull for the aircraft. The vertical lifting device is arranged at the rear end of the fuselage, and the vertical lifting device provides the upward lifting force for the aircraft in the form of rotatingthe paddle blades driven by an electric motor. The tail rotor is located below the vertical lift. The invention can carry out vertical take-off and landing, has long sailing time, stable flight process, has two lifting modes, has high safety coefficient, and is suitable for logistics transportation, air fire extinguishing, post-disaster rescue and the like.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Seawater desalting device
InactiveCN108862434ASimple structureEasy to operateGeneral water supply conservationSeawater treatmentFresh water organismDesalination
The invention discloses a seawater desalting device. The seawater desalting device comprises a device main body and a distillation device arranged in the device main body, wherein the distillation device comprises a first cavity arranged in the device main body; a second cavity is formed in a lower-side inner wall of the first cavity in a communication manner; the second cavity and the first cavity are isolated through an isolation plate; a first through hole is formed in the isolation plate in an up-down penetrating manner; an exhausting and stirring device is arranged in the first through hole; a first fixed block is fixedly connected with a left-side inner wall of the second cavity; a second fixed block, which is fixedly connected between front-side and rear-side inner walls of the second cavity, is arranged at the upper side of the first fixed bloc; the sailing distance of a ship is limited along the consumption of freshwater; although a lot of seawater desalting machines exist atpresent, the seawater desalting cost is relatively high; the invention aims at providing the device which can be conveniently carried and also can be used for carrying out seawater desalting by utilizing relatively low cost.
Owner:福州安辛达环保科技有限公司
Sea energy driven power generation piling semi-submerged ship
PendingCN113548156AReduce the impactNot easy to shakeHydro energy generationSteering by jetsMarine engineeringWater energy
The invention discloses a sea energy driven power generation piling semi-submerged ship. The ship comprises a ship body and further comprises a water energy power generation system, wherein the ship is provided with an ocean current and ocean wave energy collector and a water pumping and pressurizing device which are linked in sequence, and is also provided with a main water suction port; an input end of the water pumping and pressurizing device is connected with the main water suction opening, and an output end of the water pumping and pressurizing device is connected with a second high-pressure pipe which is connected with the water energy power generation system; the ship is provided with a pipe pile sinking machine and a pile sinking stabilizing clamp which are arranged up and down; and the water energy power generation system is electrically connected with the pipe pile sinking machine. According to the sea energy driven power generation piling semi-submerged ship, power generation and piling on the sea can be achieved through the energy of ocean currents and waves, environmental protection is achieved, the duration time of single-time piling operation can be greatly prolonged, and long-term offshore operation of the piling semi-submerged ship is facilitated.
Owner:曾昭达
A rescue transport aircraft
InactiveCN109263907AEasy to treatIncrease chances of survivalWing shapesPower plant typeFlight vehicleAirplane
The invention relates to a rescue transport aircraft, belonging to the technical field of aircraft, comprising a fuselage, a wing, a lifting device and a tail fin. The fuselage has a flat structure with thicker front end than rear end. The wing adopts delta wing, and the wing extends from the front end to the rear end of the fuselage; a mast controller is arranged in that fuselage. The lifting device comprises two large motors with large blades and two small motors with small blades. The lifting device provides vertical lift and horizontal forward pull for the aircraft. The pitch and yaw of the aircraft are adjusted by the tail fins. During take-off, the inclination caused by the side wind is adjusted by controlling the speed difference between the two small motors through the vertical lift of the large motor and the tension of the small motor. The wings are lifted to the wounded position quickly, and the wounded are landed vertically by a large electric motor. Finally, the plane takesoff vertically with the wounded and transports them to the treatment point for treatment. The invention can carry out vertical take-off and landing, has long sailing time, stable flight process and high safety factor.
Owner:FOSHAN SHENFENG AVIATION SCI & TECH
Stern shaft seal
ActiveCN106321855BLong sailing timeGuaranteed normal navigationEngine sealsTransmission with propulsive element synchronisationEngineeringMechanical engineering
Owner:WUXI HONGYUAN DEVFLEX
Telescopic airfoil solar variant floating aircraft
PendingCN111422341ALong sailing timeIncrease loadBatteries circuit arrangementsElectric powerFlight vehicleDrive shaft
The invention discloses a telescopic airfoil type solar variant floating aircraft. The aircraft comprises an airship body, two air inflation and suction devices, a carrying platform, two propelling devices and a landing gear. The two air inflation and suction devices are symmetrically installed on the two sides of the airship body. The carrying platform is installed on the lower portion of the airship body. The two propelling devices are symmetrically installed on the side portions of the airship body. The landing gear is mounted at the lower part of the airship body; the airship body comprises a fixed airfoil type airship body and two telescopic airfoil type variant assemblies; the carrying platform comprises two connecting rods and a placing plate; each propelling device comprises a propelling motor, a driving shaft and blades, and the landing gear comprises two first supporting frames, a second supporting frame, two first rolling wheels and two second rolling wheels. According to the invention, the navigation time is effectively prolonged, the load capacity is increased, the high-altitude residence time is prolonged, and the application range is enlarged.
Owner:江苏航空职业技术学院
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