30results about How to "Take off fast" patented technology

The invention relates to an electromagnetic runway. Both sides of a runway are provided with two rows of electromagnetic tracks with the same size; each electromagnetic track is provided with an electromagnetic sensor and a controller, and a landing gear of an airplane is provided with a magnetic disc; the electromagnetic sensor senses take-off or loading information on the airplane and transmitsthe information to the controller; and the controller controls the polarity and magnetic force of the electromagnetic tracks. Compared with the prior art, the electromagnetic runway has the characteristics of enabling the airplane to take off or land quickly, shortening runway sliding and the like.

The invention discloses a surface treatment process method before the wiredrawing of a welding wire. The method comprises the following process steps of: physically removing mill scale of a welding wire to be drawn in a husking machine; and performing an electrolytic pickling process under the condition that the movement speed of the welding wire to be drawn is 0.3 to 0.5 meter / second, the surface current density of the welding wire to be drawn is 150 to 350A / dm<2> and the temperature of an electrolyte solution is controlled to 15-60 DEG C, wherein the electrolyte solution consists of sulfuric acid, hydrochloric acid, sodium sulfate and an additive, and the additive consists of sodium dodecyl benzene sulfonate and alkylphenol polyoxyethylene ether. By the method, the problems of long pickling time, low production efficiency, non-ideal mill scale removing effect, environmental pollution and the like existing in the surface treatment process before the wiredrawing of the welding wire are solved.

The invention provides a modularized meteorology detection system based on an unmanned plane, comprising a modularized airborne meteorology detection device, a multi-rotor industrial grade unmanned plane platform, a mooring ground tracking vehicle and a vehicle-mounted unmanned plane support device. The modularized airborne meteorology detection device is assembled to the unmanned plane, and can conduct sensor customization based on scene requirement, and comprises an aerosol detector, a wind direction and wind speed device, a vehicle-mounted radar mapping system, and other meteorological parameter sensors. The unmanned plane platform conducts data transmission with the ground terminal in a wireless and wired manner. The ground vehicle is equipped with a data processing distribution earthstation, a power supply supporting device of the unmanned plane, and a flying control device, and with the data processed through the data processing distribution station, the information obtained caneffectively cooperate related departments to conduct work.

The present invention provides a vertical / short-range take-off and landing airplane flight control method. A transition process controller, a routine flight mode controller and a flight mode determiner are provided. Through adoption of a prediction control method, the transient process flight mode controller is configured to observe the state and the disturbance of a system by employing an extended Kalman filter based on the expansion system formed by a vertical / short-range take-off and landing airplane partial linear model and a propulsion system linear model and design a prediction controller weight matrix changed with flight dynamic pressure and a manipulator desired value. The flight mode determiner takes a propulsion system state as a basis for determination, and when the determination basis is satisfied, the transition process controller is switched to the flight mode controller. The vertical / short-range take-off and landing airplane flight control method considers the propulsion system dynamic characteristic and the dynamics modeling uncertainty, is able to realize the manipulator coordination control and flight mode stable switching, is applicable to the vertical / short-range take-off and landing airplane, and is fast in taking-off speed and small in attitude disturbance, etc.

The invention discloses an early-warning system and method for water pollution. The early-warning system comprises a water early-warning unmanned aerial vehicle and a bank-based server, and the waterearly-warning unmanned aerial vehicle is used for flying according to a preset optimal path and completing water quality testing and sampling; the bank-based server is used for receiving and analyzingdata transmitted back by the water early-warning unmanned aerial vehicle, predicating the position of a pollution source according to multi-point data, and meanwhile monitoring the position of the water early-warning unmanned aerial vehicle in real time and planning the flying path of the water early-warning unmanned aerial vehicle. Through combination of the water early-warning unmanned aerial vehicle and the bank-based server, the water early-warning unmanned aerial vehicle can fly to a designated area according to the optimal path set by the bank-based server so as to complete collection of water quality information, the collected information is quickly sent to the bank-based server to be analyzed and presented, and the early-warning system has the advantages of high safety, high efficiency, and low cost.

The invention discloses body armor capable of being taken off rapidly. Two shoulder straps are integrally formed at the top of a front piece, and the suspended ends of the two shoulder straps stretch into an interlayer of a rear piece from top to bottom; a left inner waist piece and a right inner waist piece are arranged at the lower end of the front piece, and an outer waist piece is arranged on the outer side of each inner waist piece; the front ends of the inner waist pieces and the front ends of the outer waist pieces are fixedly glued onto the front piece, and the rear ends of the inner waist pieces and the rear ends of the outer waist pieces stretch into the interlayer of the rear piece; buckles arranged on the rear piece penetrate through via holes in the suspended ends of the two shoulder straps, via holes in the rear ends of the two inner waist pieces and via holes in the rear ends of the two outer waist pieces from front to back; the suspended ends of the shoulder straps, the rear ends of the inner waist pieces and the rear ends of the outer waist pieces are fixed together through steel wire ropes. The body armor capable of being taken off rapidly is simple in structure, low in production cost and capable of being taken on conveniently; the body armor can be rapidly disassembled by pulling out the steel wire ropes, and operation is easy and convenient; the armor can be untied and taken off rapidly, and thus the wounded can be rescued conveniently in time.

Packing material roll sterilizing apparatus and method is provided. The apparatus includes one bath for the rolled material to pass through and one sterilizing fluid conveying system from the source to the bath. The apparatus features that the conveying system includes one movable volume regulating element for regulating the sterilizing fluid from the source to the buffering tank and the sterilizing fluid from the buffering tank to the bath. The volume regulating element has at least one part set inside the buffering tank and acting on the sterilizing fluid inside the buffering tank, so that the volume of the sterilizing fluid inside the bath is the function of the position of the volume regulating element inside the buffering tank.

The invention provides a multistage cascaded self-balancing mooring unmanned aerial vehicle system. The whole system is composed of a plurality of mooring unmanned aerial vehicles; each unmanned aerial vehicle is provided with an upper interface module and a lower standard cable module; a serially configured mooring unmanned aerial vehicle set is formed by connecting the lower standard cable module of one of the plurality of mooring unmanned aerial vehicles with the upper interface module of another adjacent unmanned aerial vehicle; so the unmanned aerial vehicles are greatly improved in core technical indexes like load, stability, reliability and lift-off height.

The invention discloses a dragonfly-imitating ornithopter, and belongs to the technical field of ornithopters. The dragonfly-imitating ornithopter comprises a flight control system, a flapping wing device and two pairs of flexible flapping wings, wherein the flapping wing device comprises a front double-wing driving mechanism, a rear double-wing driving mechanism and a driving mechanism connecting frame; the front double-wing driving mechanism and the rear double-wing driving mechanism have the same structure and comprise double-wing active energy piezoelectric actuators and a pair of side wing driving mechanisms with the same structure; the pair of side wing driving mechanisms with the same structure comprises a side wing auxiliary kinetic energy piezoelectric actuator and a side wing flapping mechanism; the side wing flapping mechanism comprises a side wing flapping structure and a side wing rocker arm; the side wing flapping structure comprises a main kinetic energy driving connecting arm and an auxiliary kinetic energy driving connecting arm; the flexible flapping wings are connected with the side wing rocker arms through the flapping wing connecting structures; and the front double-wing driving mechanism and the rear double-wing driving mechanism are respectively arranged in front of and behind the driving mechanism connecting frame. The dragonfly-imitating ornithopter has the characteristics of light weight, compact structure, independent control of four-wing amplitude and vibration frequency and the like.

The wearable unmanned aerial vehicle comprises an unmanned aerial vehicle body, a base and a wrist strap, an electromagnet assembly capable of switching magnetic poles is embedded in the base, a groove for containing the unmanned aerial vehicle body is formed in the upper end face of the base, and the two ends of the wrist strap are fixedly connected with the two opposite side walls of the base; the unmanned aerial vehicle body is provided with a camera device, a magnet which attracts or repels the electromagnet assembly, a GPS positioner, a touch display screen, an antenna, a loudspeaker, a microphone, a laser radar, an illumination light source, a processor and a first built-in power supply, and the camera device, the GPS positioner, the touch display screen, the antenna, the loudspeaker, the microphone, the laser radar and the illumination light source are electrically connected with the processor. The output end of the first built-in power supply is electrically connected with the power input end of the processor, and the electromagnet assembly and the processor are electrically connected with the control terminal in a wireless mode. The multifunctional pen container has the advantages of integrating multiple functions and being wide in application range.

The invention discloses a linkage hollowed-out wing unit suitable for a flapping-wing air vehicle. The linkage hollowed-out wing unit suitable for the flapping-wing air vehicle comprises a rack, a driving device, a linkage device and a plurality of rotary wings which are sequentially arranged at intervals. The linkage device comprises a rocker, a reversing gear component, a gear connecting rod, a transmission gear and a vertically-mounted transmission rod. The designed wing unit is formed by arranging the multiple rotary wings at intervals, and the assembled wing unit is of a hollowed-out structure, so that when the air vehicle takes off, the contact area between the wing unit and air is small, the rising resistance borne by the air vehicle is small, the air vehicle can take off rapidly, and the flight efficiency is high; in addition, the wing unit is folded or unfolded through linkage control so that the flapping-wing air vehicle can obtain the optimal performance in different flight states; furthermore, the linkage device is adopted for synchronous deformation of the wing unit, the synchronization rate of deformation is high, and linkage control is stable and accurate; and the linkage hollowed-out wing unit is extremely suitable for the flapping-wing air vehicle of a small structure.

The invention discloses an unmanned aerial vehicle undercarriage for forestry fire prevention. The unmanned aerial vehicle undercarriage comprises a base and a lifting base, a first screw rod is rotationally mounted in the middle of the base and is in threaded connection with a first screw sleeve, and a plurality of sliding grooves are evenly formed on the base and at the periphery of the first screw. The sliding blocks are mounted in the sliding grooves in a sliding manner, the lifting seat is arranged above the base, and a plurality of push-pull rods are hinged to the periphery of the lifting base and are in a one-to-one correspondence with the sliding blocks. The lower ends of the push-pull rods are hinged to the sliding blocks at the same side, a plurality of first connecting rods arehinged to the outer sides of the first threaded sleeve, the first connecting rods are in one-to-one correspondence with the push-pull rods, and the other ends of the first connecting rods are hinged to the inner sides of the push-pull rods. When an unmanned aerial vehicle lands, the lifting base moves upwards, the resistance between the undercarriage and the air is increased, so that the stable landing of the unmanned aerial vehicle is guaranteed. When the unmanned aerial vehicle takes off, the resistance between the undercarriage and air is reduced, so that the unmanned aerial vehicle takes off quickly.

The invention discloses a takeoff method and device for a fixed wing unmanned aerial vehicle and belongs to the field of aircrafts. The takeoff device comprises the fixed wing unmanned aerial vehicle,a launching platform, a launching device and a blocking device. The launching platform comprises a fixing table and a guiding column, the fixing table is mounted at the tail end of the guiding column, and the inclined angle between the guiding column and the ground horizontal line is 10-45 degrees. The blocking device is composed of a left telescopic device and a right telescopic device. The launching device comprises two vertical rods symmetrically distributed on the left side and the right side of the guiding column. A circular hole penetrating through a fuselage is formed in the middle ofthe fixed wing unmanned aerial vehicle, and the size of the circular hole is set to enable the guiding column to penetrate through the fixed wing unmanned aerial vehicle through the circular hole. A buckle device is arranged on the upper portion of the middle of the fixed wing unmanned aerial vehicle, is of a reverse 7-shaped structure and is used for clamping rubber ropes. According to the fixedwing unmanned aerial vehicle takeoff mode, compared with the traditional mode that the fixed wing unmanned aerial vehicle takes off in an accelerated mode through a runway, the fixed wing unmanned aerial vehicle can take off more rapidly, the occupied place is small, and the cost is relatively low.

The invention discloses a combined type agricultural unmanned aerial vehicle. The combined type agricultural unmanned aerial vehicle structurally comprises spray nozzles, a spray bar, buckles, an aircraft nose, cables, arm levers, paddles, a bearing seat, connecting rods, a medicine box, a medicine box cover, a battery and a landing gear. The four spray nozzles are installed on the spray bar, andthe buckles are fixed to the spray bar in a snap-fit mode. The aircraft nose is horizontally fixed to the top portions of the connecting rods, and the arm levers are welded on both sides of the paddles. The bearing seat is mounted on the aircraft nose, and the landing gear is mechanically connected to the bottom of the aircraft nose. The battery is mounted at the top end of the landing gear. According to the combined type agricultural unmanned aerial vehicle, pin rollers are rotated on guide rails with good stability through check rings, and no offset or shaking occurs; inner rings are drivento rotate by the rolling of the pin rollers, so that the friction between a rotating shaft and the bearing seat is greatly reduced; and the rotation speed of the unmanned aerial vehicle is greatly accelerated, and when the arm levers and the paddles are operated, the friction is reduced and the rotation efficiency is improved to enable the take-off speed of the unmanned aerial vehicle to be higher.

The invention belongs to the technical field of traffic management, and particularly relates to an intelligent traffic management system based on big data, which comprises a server and mobile terminals. The server runs on a cloud server, and the mobile terminals can be installed in a mobile phone, a tablet personal computer, a vehicle-mounted navigator and other intelligent devices. When an intersection is in a congestion state, the mobile terminals on vehicles 200-300m away from a current intersection stop line receive a lane-borrowing driving signal and a prompt control signal sent by the server; after receiving the lane-borrowing driving signal, the mobile terminals guide the vehicles to advance, drive into a left-turn lane or a right-turn lane, cross the congestion area, return to thestraight lane and continue to advance; and if the mobile terminals do not receive the lane-borrowing driving signal, the corresponding vehicles are not allowed to run on another lane. According to the invention, when the road intersection is jammed, the traffic can be rapidly dredged, the jam is relieved, the road smoothness is ensured, and meanwhile, the road traffic video is recorded, thereby facilitating responsibility determination when an accident occurs, and increasing the accident handling speed.

The invention provides a flying automobile comprising a machine body and wheels. First wing cabins and a second wing cabin are arranged on the machine body. Folding wings are arranged in the first wing cabins and the second wing cabin correspondingly. Each folding wing comprises a first folding shaft, a second folding shaft and a third folding shaft which are arranged in a sleeved connection manner. A motor box is connected to each third folding shaft and is arranged in a rotating manner relative to the third folding shaft. A propeller is installed on the upper portion of each motor box. A propeller drive motor is arranged in each motor box. The propellers are arranged in a folding manner relative to propeller grooves. Therefore, when the flying automobile runs on the ground, the folding wings can be rapidly unfolded into the first wing cabins and the second wing cabin, the first folding shafts, the second folding shafts, the third folding shafts, the propellers and the motor boxes canbe tightly put away, it is ensured that there will be no parts of the folding wings extending to the outer portion when the flying automobile runs on the ground, and safety and service life of the folding wings are ensured.

The invention discloses a tubular vertical ejection type ejection unmanned aerial vehicle, an ejection system and a realization method thereof. The present invention is mounted on a carrier platform and includes an ejection drone and an ejection system. Before ejection, the ejection drone is folded and slid into the ejection system. After ejection, the ejection drone realizes autonomous flight and completes the designated task; the present invention The excellent functions and structural layout of the catapult UAV can obviously overcome the problems that conventional UAVs have strict requirements for take-off and landing conditions, as well as poor endurance. Quick take-off, safe landing, and fast deployment in various environments; the catapult system for the catapult drone can store the drone, and by using the explosive gas of the projectile, push the push plate, and indirectly eject the drone. The man-machine is ejected in a stable ballistic manner without damaging the drone, and it can be made into the form of multiple ejection tubes, so the ejection efficiency of the drone is higher.

The invention belongs to the field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle take-off power assisting device arranged on the water surface. The unmanned aerial vehicle take-off power assisting device comprises a cylinder body, an annular floating plate is fixedly connected to the top end of the side wall of the cylinder body, a plurality of buoyancy bags are fixedly connected to the bottom end of the annular floating plate, a plurality of driving mechanisms are fixedly connected to the side wall of the cylinder body, a power assisting cavity is formed in the cylinder body, and a plurality of air pressure pieces are fixedly connected to the inner bottom wall of the power assisting cavity. In the stage that the unmanned aerial vehicle needs to take off, the air pressure pieces can be rapidly stretched by utilizing the tension effect of the bag body and the water pressure effect, then a supporting block can be rapidly bounced upwards, first-stage acceleration of the supporting block and a supporting plate is achieved, meanwhile, the supporting plate can move upwards more quickly relative to the supporting block through a transmission mechanism, so that second-stage acceleration of the supporting plate is achieved, and it is ensured that the unmanned aerial vehicle located on the supporting plate can have good ejection and flying assisting effects through the second-stage acceleration.

The invention discloses a suspension uni-directional / bi-directional steam catapult which comprises a cylinder, a left cylinder cover, a right cylinder cover, a piston, a steam guide pipe system, a left steel cable and a right steel cable; the cylinder consists of an outer cylinder and an inner cylinder; the left cylinder cover and the right cylinder cover are fixedly connected with the left and right ends of the outer cylinder respectively; multiple rows of annularly arranged steam ports are formed on the outer wall of the outer cylinder; through micro-steam holes are formed on the wall of the inner cylinder; the steam guide pipe system is composed of four groups of pipe collection; the first and second groups of pipe collections are arranged on the outer parts of the left and right cylinder covers respectively; the third and fourth groups of pipe collections are arranged on the outer wall of the outer cylinder; the piston is arranged in the inner cylinder; multiple suspension levers are arranged in the inner cylinder; the piston and the suspension levers are in sliding fit; a left tunnel pipe and a right tunnel pipe are mounted on the axle centre of the piston; the right side of the piston is fixedly connected with a signal shaft; and a left buffer and a right buffer are arranged on the inner sides of the left and right cylinder covers respectively. In the catapult, totally-closed cylinders are adopted; and the catapult has the advantages of compact structure, high airtight performance and heat energy utilization rate, large catapult force and high speed and can enable a heavy airplane to take off immediately.

The invention discloses a disc-shaped aircraft driven by high-pressure gas, which comprises a cylinder block, a rotating baffle is arranged above the inside of the cylinder block, a piston and a piston cover are arranged at the bottom of the inside of the cylinder block, and a There are air bags. It is characterized in that a notch is provided on the rotating baffle and is connected with a rotating motor, a number of air injection ports are provided on the cylinder body, an L-shaped support rod is provided on the piston cover, and the air bag is sleeved on the cylinder The outer surface of the middle part of the body, the piston is connected with the linear motor. The invention realizes the flight of the aircraft in different attitudes in the air by controlling the discharge of high-pressure air from the jet port per unit time, and changes the direction of the aircraft by coordinating the rotating baffle with the jet port on the cylinder block. The invention can realize rapid take-off, improves the safety of outdoor use, has the advantages of longer battery life, and is especially suitable for flying in jungles.

The invention provides a silicon carbide pipeline product forming machine. The silicon carbide pipeline product forming machine comprises a machine base and a mixed feeding device. A rotary table, a cantilever installation mechanism and a rotary table power driving mechanism are arranged on the machine base. A pneumatic tamping machine is arranged on the cantilever installation mechanism. The rotary table is rotatably connected to the upper surface of the machine base. A silicon carbide pipeline forming mold located under the pneumatic tamping machine is arranged on the rotary table. The rotary table power driving mechanism is in transmission connection with the rotary table. A material outlet of the mixed feeding device is connected with a material inlet of the silicon carbide pipeline forming mold. The silicon carbide pipeline product forming machine is convenient to operate, high in mechanization degree and capable of relieving the labor intensity of workers and improving the production efficiency.

The invention discloses a suspension uni-directional / bi-directional steam catapult which comprises a cylinder, a left cylinder cover, a right cylinder cover, a piston, a steam guide pipe system, a left steel cable and a right steel cable; the cylinder consists of an outer cylinder and an inner cylinder; the left cylinder cover and the right cylinder cover are fixedly connected with the left and right ends of the outer cylinder respectively; multiple rows of annularly arranged steam ports are formed on the outer wall of the outer cylinder; through micro-steam holes are formed on the wall of the inner cylinder; the steam guide pipe system is composed of four groups of pipe collection; the first and second groups of pipe collections are arranged on the outer parts of the left and right cylinder covers respectively; the third and fourth groups of pipe collections are arranged on the outer wall of the outer cylinder; the piston is arranged in the inner cylinder; multiple suspension levers are arranged in the inner cylinder; the piston and the suspension levers are in sliding fit; a left tunnel pipe and a right tunnel pipe are mounted on the axle centre of the piston; the right side of the piston is fixedly connected with a signal shaft; and a left buffer and a right buffer are arranged on the inner sides of the left and right cylinder covers respectively. In the catapult, totally-closed cylinders are adopted; and the catapult has the advantages of compact structure, high airtight performance and heat energy utilization rate, large catapult force and high speed and can enable a heavy airplane to take off immediately.

The invention discloses an active shaft type combined air bearing which comprises an outer bearing seat, an inner bearing seat, a rolling shaft and a plurality of balls. The inner bearing seat comprises an outer ball shaft seat, an inner air shaft seat and an extension coaxial seat, and one end of the extension coaxial seat is connected with a driving motor. When the rolling shaft starts to rotate, the driving motor starts to rotate, but the rotating direction of the driving motor is opposite to the rotating direction of the rolling shaft, so that the relative rotating speed of takeoff of the rolling shaft is increased, and the rolling shaft in a foil ring takes off faster at a lower rotating speed. When the rotating speed is gradually increased after the rolling shaft takes off, the driving motor gradually decelerates and reversely rotates, and the relative rotating speed between the rolling shaft and the inner bearing seat is reduced. The actual relative rotating speed of a rotating shaft relative to the inner bearing seat is obtained by subtracting the same-direction rotating speed of the inner bearing seat from the original highest rotating speed of the rotating shaft. Relative friction and heating between the rotating shaft and the inner bearing seat are reduced, the abrasion loss is reduced, the service life of the whole product is prolonged, and the quality of the whole product is improved.

The invention discloses a disc type aircraft taking high pressure gas as power. The disc type aircraft comprises a cylinder body, a rotating baffle plate is arranged in the upper side of the cylinderbody, a piston and a piston cover plate are arranged in the lower side of the cylinder body, and an air bag is arranged in a center region of the cylinder body. The disc type aircraft is characterizedin that a notch is formed in the rotating baffle plate to be connected to a rotating motor, a plurality of air injection ports are formed in the cylinder body, the piston cover plate is provided withan L-shaped supporting rod, the air bag is connected to the outer surface of the middle part of the cylinder body in a sleeving manner, and the piston is connected to a linear motor. The aircraft flies in the air with different gestures by controlling the discharge rate of high pressure air from the air injection ports within a unit time, and the direction of the aircraft is changed by matching the rotating baffle plate with the air injection ports in the cylinder body. The aircraft can take off quickly, so that the outdoor using safety is improved. The disc type aircraft has the advantages of being longer in time of endurance and the like, and is in particular suitable for flying in a jungle.

The invention discloses a high-speed long-endurance aircraft, which comprises a fuselage, a wing, a lifting rotor, a vertical tail, a horizontal tail, a propulsion paddle, a rotating rotor system anda power system; the power system provides power for the propulsion rotor, rotating rotor system and lifting rotor. The wings are symmetrically arranged on both sides of the fuselage; a lifting rotor is positioned above that fuselage head; two or more propulsion paddles are arranged on the trailing edge of the wing, and symmetrically arranged with respect to the fuselage. The vertical tail and thehorizontal tail are arranged at the tail of the fuselage, and the vertical tail is perpendicular to the horizontal tail. There are two horizontal tail fins, symmetrically arranged on both sides of thevertical tail fins. The aircraft provided by the invention integrates the characteristics of the vertical take-off and landing aircraft and the advantages of the long endurance aircraft, has simple control system, and realizes the horizontal taxiing function of the long endurance manned aircraft.

The invention relates to a method for the purification and rejuvenation of an edible fungus strain. According to the method, a first culture medium and a second culture medium are adopted, wherein the first culture medium is obtained by mixing 95 to 97 weight percent of sawdust and 3 to 5 weight percent of river silt and regulating the moisture content of the mixture with a 1 percent potassium permanganate aqueous solution, and the second culture medium is obtained by mixing 95 to 97 weight percent of sawdust and 3 to 5 weight percent of river silt and regulating the moisture content with a 0.5 percent topsin aqueous solution. The method comprises the following steps: pushing 80 grams of the first culture medium and 80 grams of the second culture medium into the centers of bottomless test tubes respectively, and plugging cotton plugs into the two ends of the bottomless test tubes for sterilization; selecting fungus blocks sized as green beans in an aseptic technique manner, inoculating the fungus blocks into the first culture medium, performing culturing for 4 to 6 days at 25 DEG C, selecting mycelium at the uninoculated end to be inoculated to one end of the second culture medium when the mycelium in the first culture medium reaches the other end, performing culturing for 4 to 6 days at 25 DEG C, selecting the mycelium at the uninoculated end to be inoculated to a PDA culture medium when the mycelium penetrates through the second culture medium, and performing culturing for 4 days at 25 DEG C to obtain sterile mother strain. The method is short in cycle and high in accuracy, the sources are simple, the virus, bacterium and fungus pollution of the strain can be rapidly removed, and meanwhile, rejuvenation and strain purification functions are realized.

The invention belongs to the technical field of amphibious flying vehicles, and in particular relates to a hollow-wheel multi-rotor flying vehicle. The present invention includes a body with a rotor as the structural main body, and is characterized in that: the flying vehicle also includes a ground walking assembly, and the ground walking assembly includes a hollow wheel driven by a power source to drive the body to travel along the ground, and the shape of the hollow wheel is circular. Ring wheel shape, the ring cavity of the hollow wheel constitutes a placement cavity for the placement of the rotor, and the rotation axis of the rotor and the rotation axis of the hollow wheel intersect each other. The present invention can not only realize the ground driving function in relatively complex terrain, but also can fly off the ground with the power provided by the rotor to climb over obstacles or fly in the air quickly; in addition, the present invention does not need to change the amphibious mechanism when walking on the ground and flying in the air , the flight and ground driving state transition is convenient and reasonable, and the environmental adaptability is extremely strong.

The invention discloses a double-wing driving mechanism for a dragonfly-imitating ornithopter, and belongs to the technical field of ornithopters. The mechanism comprises a double-wing active energy piezoelectric actuator and a pair of side wing driving mechanisms with the same structure; the lower end of the double-wing active energy piezoelectric actuator is fixedly connected with a driving mechanism connecting frame; the pair of side wing driving mechanisms of the same structure comprises a side wing auxiliary kinetic energy piezoelectric actuator and side wing flapping mechanisms, and the two side wing flapping mechanisms are symmetrically arranged on the left side and the right side of the double-wing active energy piezoelectric actuator. The lower end of the side wing auxiliary kinetic energy piezoelectric actuator is fixedly connected with the driving mechanism connecting frame; each side wing flapping mechanism comprises a side wing flapping structure and a side wing rocker arm; the side wing flapping structure comprises a main kinetic energy driving connecting arm and an auxiliary kinetic energy driving connecting arm; the whole side wing rocker arm comprises a flapping wing connecting part and a flapping wing driving part. The mechanism has the characteristics of light weight, compact structure, independent control of four-wing amplitude and vibration frequency and the like.

An apparatus (10) and method for sterilizing rolls (12) of packaging material are provided. The apparatus includes a bath (20) through which the roll passes and a transfer system for transferring a germicidal fluid from a germicidal fluid supply (30) to the bath. The device is characterized in that the transfer system comprises a buffer tank (18) to which the sterilizing fluid is transferred from the supply source and a movable volume adjustment element (34) for transferring the sterilizing fluid from the buffer tank to the bath. At least a portion (36) of the volume adjustment element is arranged to be received in the surge tank and to act on the sterilizing fluid in the surge tank, whereby the volume of the sterilizing fluid in the bath is a function of the position of the volume adjustment element in the surge tank .