36results about How to "Long sailing time" patented technology

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).

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.