93results about How to "Realize replacement and maintenance" patented technology

The invention relates to a pebble-bed module type high-temperature gas cooled reactor fuel loading and unloading system which comprises a reactor (10), a reactor core fuel circulating system (20), a new fuel loading system (300) and a spent fuel unloading system (400). The reactor (10) comprises a reactor pressure container (11), a graphite coating reactor internal component (12), a central reactor core cylinder (13), a metal reactor internal component (15) and an unloading pipe (14), the reactor core fuel circulating system (20) comprises a reactor core unloading system (100) and a reactor core loading system (200) and further comprises a helium pneumatic conveying system (500), a compressed air pneumatic conveying system (600), a vacuum pumping system (700) and a helium supplying and recycling system (800), and the compressed air pneumatic conveying system (600), the vacuum pumping system (700) and the helium supplying and recycling system (800) are all connected with the helium pneumatic conveying system (500). The helium pneumatic conveying system (500) is further respectively connected with the reactor (10), the reactor core fuel circulating system (20), the new fuel loading system (300) and the spent fuel unloading system (400).

The invention belongs to a railway ballast bed and relates to a track structure of the railway. The railway ballast bed comprises a floating slab and an elastic vibration isolator, wherein the elastic vibration isolator is arranged in a reserved through hole of the floating slab; a support stop block is arranged on the inner wall of the through hole; the floating slab is supported on the elastic vibration isolator through the support stop block; a blind hole or a groove is reserved on a concrete structure of the inner wall of the through hole of the floating slab; and the support stop block is inserted in the blind hole or the groove. In the invention, the support stop block is separated from the floating slab, the support stop block can be maintained and replaced at any time under the condition of unchanged original vibration isolation performance of the floating ballast bed, the structure is more reasonable, and the service life of the floating ballast bed is beneficially prolonged.

The invention belongs to the field of vibration and noise control of rail transportation and particularly relates to a plate-type rail ballast bed structure adopting a damping cushion layer for elastic supporting. The maintenance-liable elastic cushion damping ballast bed comprises an elastic cushion and a rail plate. The elastic cushion is placed onto a foundation, and the rail plate is placed onto the elastic cushion. A steel rail and a fastener system are arranged on the rail plate. The elastic cushion and at least part of a rail plate body are embedded into the foundation. The cross section of the rail plate is in a basin shape or an inverted-trapezoidal shape and corresponds to the outline of the foundation matched with the cross section of the rail plate. An isolating layer is arranged between the rail plate and the elastic cushion. The rail plate is further provided with a plate body lifting structure. According to the maintenance-liable elastic cushion damping ballast bed, maintenance and replacement of the elastic cushion can be conveniently achieved, and the problem existing in the ballast bed technical scheme adopting the elastic cushion to conduct damping at present is solved, the structure of the maintenance-liable elastic cushion damping ballast bed is simple, the practicable property is high, the safe and reliable effects are achieved, the ratio of performance to price is higher, and the market application prospects are pretty wide.

The invention provides a bracket type gas distribution pipe lifting device and an aerator pipe maintenance and replacement method. The bracket type gas distribution pipe lifting device comprises a plurality of sets of gas distribution pipes, wherein the gas distribution pipes are arranged in an aeration tank and bear aerator pipes. Gas inlet pipes are arranged corresponding to the gas distribution pipes, the gas distribution pipes are arranged on a bracket arranged at the bottom of the aeration tank, vertical lifting rods are arranged on the four corners of the bracket, and lifting mechanisms are arranged on the portions, corresponding to the lifting rods, of the tank wall top of the aeration tank. Each lifting mechanism comprises a chain block, wherein each chain block is installed on a corresponding lifting support and located exactly above the corresponding lifting rod. A hanging ring is arranged on each lifting rod, and hooks of the chain blocks are hung on the hanging rings in a hooked mode. The gas inlet pipes are arranged beside one side of the tank wall. Each gas inlet pipe comprises a vertical section and a horizontal section. Each vertical section is communicated with the corresponding gas distribution pipe, each horizontal section is led to the aeration tank from the top of the corresponding tank wall, and the vertical section and the horizontal section of each gas inlet pipe are connected through a flange or are detached. According to the bracket type gas distribution pipe lifting device and the aerator pipe maintenance and replacement method, maintenance and replacement of the aerator pipes can be achieved under the condition that water drainage and sewage removal are not conducted, unimpeded maintenance and replacement of the aerator pipes are achieved, and the aeration effect of the sewage treatment technology is guaranteed.

The invention discloses a reboiler. The reboiler comprises a reboiler casing and a heat exchanger, wherein a material inlet and a gaseous phase outlet are formed in the reboiler casing; the heat exchanger comprises an end head with a heat oil guide inlet / outlet, and a heat exchanger tube array communicated with an end head pipeline, one end of the heat exchanger tube array is inserted into the reboiler, and the other end of the heat exchanger tube array penetrates through the reboiler casing and then is connected onto the end head, the outer part of the heat exchanger tube array extending out of the reboiler casing is covered with a heat exchanger casing, and the heat exchanger casing is detachably connected with the end head. The reboiler is simple in structure and convenient to reconstruct; through changing the assembly structure of the reboiler casing and the heat exchanger, the maintenance and exchange of the heater can be easily implemented, the service life of the reboiler is prolonged, and the production cost is lowered.

The invention relates to the field of nuclear reactor engineering and safety, and provides an absorption ball reactor shutdown device for a high-temperature gas-cooled reactor. The absorption ball reactor shutdown device for the high-temperature gas-cooled reactor comprises a ball storage tank, a supporting tube, a driving piece and a transmission rod, wherein a ball falling opening is formed in the bottom of the ball storage tank; the bottom of the supporting tube is connected with a top opening of the ball storage tank; the driving piece is fixed on the top of the supporting tube; the transmission rod penetrates in the supporting tube, a first end is connected to an output component of the driving piece, and a second end extends to the bottom of the ball storage tank; the output component drives the transmission rod to lift so as to open and close the ball falling opening; and the driving piece rises and can drive the transmission rod to move to the outside of the ball storage tank.According to the device, the transmission rod controls opening and closing of the ball falling opening of the bottom of the ball storage tank. The driving piece rises and can drive the transmission rod to move to the outside of the ball storage tank, then the transmission rod can be disassembled integrally along with the driving piece for overhauling, and the adaptability of the device to harsh environments is expanded. In addition, according to the device, a single bearing surface mounting mode from bottom to top is adopted, and the whole device has good adaptability to thermal expansion displacement.

The invention discloses an installation device for an osmometer of a hydraulic pressure monitoring system for a tunnel lining. The installation device comprises a pipeline pre-buried in tunnel concrete, the two ends of the pipeline are higher than the middle part of the pipeline, one end of the pipeline is communicated with a longitudinal blind pipe located at the back of the lining, the other endof the pipeline extends out from a tunnel inverted arch to a tunnel space, the middle part of the pipeline is located below a gutter, the end, extending out to the tunnel space, of the pipeline is used for installing the osmometer, and the osmometer is enabled to be communicated with the back of the tunnel lining. The invention further provides an installation method based on the installation device. The installation device for the osmometer of the hydraulic pressure monitoring system for the tunnel lining and the installation method aim to solve problem that in the prior art, in the aspect of the installation of an osmometer, the hydraulic pressure monitoring precision cannot meet the requirements. According to the installation device and the installation method, seepage water is alwaysleft in the adopted pipeline, so that the working environment of the osmometer can meet the requirements, and therefore the detection precision of the osmometer is guaranteed; and meanwhile, the device bypasses an inverted arch side wall formwork, the phenomenon that the device penetrates through a steel formwork in the installation process can be avoided, and the construction is convenient.

The invention provides a zero backward thrust composite wing aircraft with ducted fan composite ailerons. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons comprises an aircraft body and composite lift wings which are fixedly mounted on the two sides of the aircraft body, wherein the aircraft body is arranged as a deck platform; self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; ducted fan propellers are arranged at the front ends of ducted fan thrust self-energizedcomposite ailerons; the self-sealing ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electricity, liquid and gas ports and the wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wings through thewing hinges. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons has the characteristics that the taking-off and landing distance is short, the flying speed is high, the structural strength of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; and the ailerons adopt compositelift forces to guarantee appropriate power.

The invention relates to a cross rod end socket for a railway wagon x-bracing bogie. The cross rod end socket for the railway wagon x-bracing bogie comprises an end socket body, an inner thread bushing, multiple threaded pins and two sealing locks, wherein a blind hole is formed in the large end of the end socket body and multiple through holes are formed in the side wall of the end socket body; the inner thread bushing is of a cylindrical structure and is embedded in the blind hole and multiple threaded holes corresponding to the through holes one to one are formed in the outer wall of the inner thread bushing in the circumferential direction; the threaded pins are respectively of a square-head cylindrical structure, cylinders with threads of the threaded pins penetrate through the through holes in the end socket body and then are screwed in the threaded holes in the inner thread bushing, and a square head of each threaded pin is provided with two locking holes; the two sealing locks respectively penetrate through the locking holes in the same side of the square heads of the threaded pins and lock the threaded pins. The threads of the cross rod end socket are easy to overhaul, part replacement and overhauls can be achieved as well, and the overhaul efficiency is high; in addition, the whole threads can be replaced, the problem that once the threads are damaged, a whole cross rod is scraped is solved, and economic benefits are improved.

The invention provides a mine car pull rod seat welding maintenance method. A pull rod seat is prevented from being integrally cut, only parts, provided with holes, on old side plates (a first side plate and a second side plate) are cut off, and repair welding of new side plates (a third side plate and a fourth side plate) are carried out at the cutting positions; and specifically, the old first side plate is firstly cut off, spot welding is carried out on the new third side plate with the old second side plate as a standard, then the old second side plate is cut off, the new fourth side plateis arranged with the new third side plate as a standard, and the third side plate and the fourth side plate are welded to the original cut-off positions, so that the consistency of the positions of pin holes in the new side plates and pin holes in the old side plates is effectively guaranteed, and maintenance and replacement of the pull rod seat can be achieved under the condition that an original pull rod seat is not disassembled.

The invention discloses a three-phase asynchronous electric motor variable-frequency speed modulation device, which comprises a position limiting clamp groove, a variable frequency speed modulator, awood pin and a position limiting clamp block, wherein the variable frequency speed modulator consists of a host box and an overhaul door; the overhaul door is arranged at the back part of the host box; through the connection between the position limiting clamp groove and the position limiting clamp block, the variable frequency speed modulator can be fast installed into a connecting block arrangedon the top of a three-phase asynchronous electric motor; the fixation can be completed through the wood pin, so that the mounting and the dismounting of the variable-frequency speed modulator becomesimple and convenient; the whole structure is very simple; the production cost is very low; the production speed of enterprises is greatly improved; through the arrangement of the overhaul door, the overhaul door is used as a medium for connecting the three-phase asynchronous electric motor; the repair and replacement on the electric element inside the host box can be realized through host box turning under the condition of not taking down a speed modulator; the repair and the use of the whole equipment become convenient and fast.

The invention provides a foldable composite wing aircraft with twin-propeller thrust composite ailerons. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons comprises an aircraft body and composite lift wings, wherein the composite lift wings are mounted on the two sides of the aircraft body in a foldable manner; the aircraft body is arranged as a deck platform;self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; propellers are arranged at the front ends of propeller thrust self-energized composite ailerons; self-sealing ducted fans are arranged in the propeller thrust self-energized composite ailerons; electricity, liquid and gas ports and wing hinges are arrangedon one side or two sides of the propeller thrust self-energized composite ailerons; and the propeller thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons has the advantages that the take-off and landing distance is short, the flying speed is high,the structural intensity of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; the ailerons adopt composite lifts so that the adaption range of the power is guaranteed.

The invention relates to a ship rudder bearing wharf maintenance and replacement method. According to the method, after a rudder system is lifted through a jacking device, a connecting plate is installed, the weight of the rudder system is supported and transferred to the connecting plate, after a tiller is detached, a worn part is maintained and replaced, and the tiller is reinstalled. By means of the maintenance and replacement method, maintenance and replacement of the ship rudder bearing can be achieved under the condition that a ship does not enter a dock, a large amount of cost is saved,the method is simple and convenient, and the problem that the ship cannot normally operate due to rudder bearing abrasion can be rapidly solved.

The invention discloses a modular decorative wall surface structure convenient to install, and relates to the technical field of decorative wall surface installation. The modular decorative wall surface structure convenient to install comprises an inner wall, a mounting plate and a decorative wallboard; a sliding rod is arranged on the inner side wall of the inner wall, a mounting column is slidably connected to the side wall of the inner wall, one end of the mounting column penetrates through the inner wall and is fixedly connected with a pressing block, a pressing spring is arranged on the inner side wall of the inner wall, and the other end of the mounting column extends into a mounting plate; an inner groove is formed in the portion, extending into the mounting plate, of the mounting column, a sliding groove is formed in the mounting plate, a clamping block is slidably connected into the inner groove, the clamping block extends into the sliding groove, an ejection block is slidablyconnected into the sliding groove, a telescopic spring is arranged on the inner wall of the inner groove, a wedge-shaped block is slidably connected to the outer surface of the sliding rod, and a sliding column is slidably connected to the side wall of the inner wall; one end of the sliding column penetrates through the inner wall and is fixedly connected with an extrusion block, and outer surface of the part, extending into the inner wall, of the sliding column is sleeved with an extrusion spring. According to the modular decorative wall surface structure convenient to install, and the problem that an existing decorative wall surface is difficult to disassemble and assemble is solved.

The invention provides a thrust compound auxiliary wing with double ducts and a rear single-propeller type compound wing man carrying aircraft with the auxiliary wings. The rear single-propeller typecompound wing man carrying aircraft is composed of a rear single-propeller type compound wing aircraft and the ducted fan thrust self-energy-supply compound auxiliary wings arranged on the two sides of wings of the rear single-propeller type compound wing aircraft. The rear single-propeller type compound wing aircraft comprises an aircraft body, the compound lift force wings fixedly installed on the two sides of the aircraft body and a thruster. The aircraft body is arranged as a deck platform; self-sealed ducted fans are arranged in the compound lift force wings, and wing hinges are arrangedon the outer sides of the compound lift force wings; and the thruster is a propeller thruster. The rear single-propeller type compound wing man carrying aircraft has the beneficial effects that the take-off and landing distance is short, the flight speed is high, the wing structural strength is high, the wings can store energy, flight energy consumption is low, and the hang time is long, the auxiliary wings adopt compound lift force, the adaption range of power is guaranteed, meanwhile, the large-area compound lift force wings can achieve the effect of a glider under an emergency, the safety of the aircraft is greatly improved, and safety of personnel, goods and materials is guaranteed.

The invention discloses a spent fuel storage pool system which comprises a spent fuel storage pool and a purification unit, the purification unit is arranged in the spent fuel storage pool and comprises a pump and a purification section, the pump is communicated with the input end of the purification section, the pump is used for conveying pool water in the spent fuel storage pool to the purification section, and the purification section is communicated with the pump. The purification section is used for purifying the pool water conveyed by the pump, and the output end of the purification section is communicated with the spent fuel storage water pool so as to discharge the purified pool water and return the purified pool water to the spent fuel storage water pool. The invention further discloses an installation / replacement method of the filter element of the spent fuel storage pool system. The system provided by the invention can realize in-pool purification, and compared with the prior art, the system provided by the invention can solve the problems of insufficient treatment capacity and the like of out-pool purification, and can meet the operation requirements of large spent fuel storage pools. The method can realize remote maintenance and replacement.

The invention discloses an eccentric grinding roller integrated efficient grinding machine. A main grinding machine comprises a base, a grinding ring, a main shaft, a grinding roller frame, an eccentric grinding roller imposed power assembly and a cover cylinder. The main shaft is arranged on the base center; the grinding roller frame is installed on the main shaft; a plurality of grinding roller assemblies are arranged on the grinding roller frame and in uniform circular distribution; the grinding ring is coaxially arranged in the base; the grinding roller frame is coaxially provided with a material distribution disc enabling the material to fall on a grinding zone uniformly; the main shaft is coaxially provide with a material fling platform, which is provided with a material fling device for flinging the material to the grinding zone; the base is coaxially equipped with the cover cylinder and an air return box; a classifier is installed on the cover cylinder; and the cover cylinder is provided with a feed chute for introducing the material into the material distribution disc. The invention adopts a zero suspension and eccentric thrust augmentation structure of the grinding roller assembly to reduce the height of the main machine, vibration, noise, and power consumption; at the same time, repair and replacement of the grinding roller and grinding ring do not need to remove the classifier, and are very convenient and time-saving.

The invention discloses a VOCS online monitoring terminal based on a could terminal and a using method thereof. The VOCS online monitoring terminal comprises a base, an angle adjusting device is arranged at the upper end of the base, an installing disc is arranged at the top end of a rotary shaft in the angle adjusting device, and six sets of threaded holes evenly distributed in the upper end of the installing disc are in threaded connection with a threaded hole at the center of the bottom face of a supporting plate through bolts. The VOCS online monitoring terminal based on the Cloud is simple in structure, rapid and stable to install and convenient to operate, can detect data accurately, can completely protect a monitoring device, and brings great convenience to a user. Meanwhile, detection data can be timely transmitted to and stored in a Cloud server memory through a GPRS data transmission module according to demands, a supervising department can monitor the relevant data in real time through a network software, supervision of pollution emission and control effects is enhanced, some pollution equipment processing terminal data fraud is prevented, the environment is protected, and the using efficiency of the VOCS online monitoring terminal is improved.

The invention discloses a rear single-paddle type compound wing airplane with twin-duct thrust compound auxiliary wings and additional wings. The rear single-paddle type compound wing airplane comprises an airplane body, compound lift force wings fixedly mounted on two sides of the airplane body and ducted fan propellers, wherein self-enclosed ducted fans are arranged in the compound lift force wings; wing hinges are designed on the outer sides of the compound lift force wings; the ducted fan propellers are arranged at the front ends of propeller thrust self-powered compound auxiliary wings; self-enclosed ducted fans are arranged in the propeller thrust self-powered compound auxiliary wings; electricity liquid gas connection ports and the wing hinges are arranged on both sides of the propeller thrust self-powered compound auxiliary wings which are movably connected with the compound lift force wings through the wing hinges on one sides. The rear single-paddle type compound wing airplane has the characteristics of short take-off and landing distance, high flying speed, high wing structure strength, capability of energy storage in the wings, low flying energy consumption, long hang time, high safety and the like; the auxiliary wings adopt compound lift force to guarantee an application range of power.

The invention provides a rear single-duct fan type combined wing manned aircraft which is composed of a rear single-duct fan type combined wing aircraft and a manned cabin. The rear single-duct fan type combined wing aircraft comprises an aircraft body, combined lift force wings fixedly installed on the two sides of the aircraft body and a ducted fan propeller. The aircraft body is arranged to bea deck platform. Self-closed ducted fans are arranged in the combined lift force wings, and wing hinges are designed on the outer sides of the combined lift force wings. The manned cabin is installedbelow the aircraft body. The rear single-duct fan type combined wing manned aircraft has the beneficial effects of being short in take-off and landing distance, high in flight speed, high in wing structural strength, capable of storing energy through the wings, low in flight energy consumption, long in hang time, high in safety and the like.

A split type mechanical sealing part of an elastic sealing ring with a rectangular cross section comprises a static ring base flange, a static ring installed on the upper middle portion of the static ring base flange, a static ring sealing ring arranged on the outer side of the static ring, a movable ring arranged above the static ring, a movable ring sealing ring arranged in the movable ring, a movable ring base arranged on the upper portion of the movable ring and the like. The static ring and the movable ring are both members opened side by side from the center, the static ring sealing ring and the movable ring sealing ring are formed by overlapping elastic sealing strips with rectangular cross sections through two end portions. The split type mechanical sealing part changes integral mechanical sealing into split type mechanical sealing, the static sealing ring and the movable sealing ring which are formed by overlapping the elastic sealing strips with the cross sections through the end portions allow small amount of expansion and contraction, consistency in continuity and radial deformation amount cannot be influenced, and the overlapping surfaces are naturally bonded together by means of pressure of a container to be sealed, so that sealing effect is ensured, and maintenance and replacement of damageable parts in mechanical sealing can be finished under the condition that parts on a shaft do not need to be detached.

The invention relates to a built-in pump LNG (liquefied natural gas) storage tank, belongs to the field of LNG storage devices, and discloses the built-in pump LNG storage tank. The built-in pump LNG storage tank comprises an LNG storage tank body and a pump well, wherein the pump well is connected on the LNG storage tank body, and stretches into the LNG storage tank body; an LNG immersed pump is arranged in the pump well; one end of a liquid outlet hose is connected on the LNG immersed pump, and the other end of the liquid outlet hose is communicated to the outer part of the pump well; a hoisting mechanism used for hoisting and lifting the LNG immersed pump and a pump well blind flange used for sealing the pump well are arranged at the opening part of the pump well; a pump well bottom valve is arranged at the bottom of the pump well; the pump well bottom valve comprises a valve seat, a valve core and a spring seat; the spring seat is fixedly connected with the valve seat through a valve core guide pillar; the valve core is arranged on the valve core guide pillar in a sleeving manner, and is propped against the spring seat through a spring; the valve seat and the valve core are sealed through a valve seat sealing element; and the valve core of the pump well bottom valve is pushed open under the gravity action of the LNG immersed pump, or is closed under the elastic action of the spring.

The invention discloses a herringbone-tooth planetary transmission device, which comprises a sun wheel, a planet wheel and an inner tooth ring, and is characterized in that herringbone teeth are respectively adopted by the sun wheel, the planet wheel and the inner tooth ring; a planet carrier is fixed, and the planet wheel only rotates without revolution; the inner tooth ring and the sun wheel respectively rotate around own axes; the inner tooth ring is a combined-type segmented herringbone inner tooth ring and is formed by combining and connecting two or more than two single-segment herringbone tooth rings through hinge-hole bolts which are forwards and backwards arranged; the left and right turning wheel teeth of the single-segment herringbone tooth rings are respectively formed through integral machining, and a direct horizontal-cutting segmenting mode is adopted. The herringbone-tooth planetary transmission device has the beneficial effects that the assembly of herringbone-tooth planetary transmission is realized, the reliability of a transmissions system is improved, the assembling precision is guaranteed, the inner tooth ring with a large diameter can be obtained on a smaller machine tool through segmented machining, the machining process and the assembling process are mature, simple and feasible, the transporting, packaging, assembling and disassembling processes are quite convenient, the maintenance and the replacement of the single-segment tooth rings can be realized, and therefore a large number of materials and machining expenses are saved.

The invention discloses a rear single-vortex type composite wing manned aircraft. The rear single-vortex type composite wing manned aircraft comprises a rear single-vortex type composite wing aircraftand a manned bin, wherein the rear single-vortex type composite wing aircraft comprises a machine body, composite lifting wings fixedly mounted at the two sides of the machine body, and a propeller;the machine body is a deck platform; vertical tail wings are further arranged above or below the machine body; the vertical tail wings are arranged at the two sides of the wings; the vertical tail wings can realize folding; the rear surfaces of the vertical tail wings are equipped with movable vertical rudder wings; self-sealed duct fans are arranged in the composite lifting wings; wing hinges andelectrical gas interfaces are designed at the outer sides of the composite lifting wings; the propeller is a turbine jet engine; and the manned bin is mounted below the machine body. The rear single-vortex type composite wing manned aircraft integrates characteristics of the turbine jet engine, and has the characteristics of being short in lifting distance, rapid in flight speed, high in wing structural strength, capable of storing energy through the wings, low in flight energy consumption, long in hang time, high in safety and the like.

The invention provides a foldable composite-wing cargo aircraft provided with single rear propeller. The foldable composite-wing cargo aircraft comprises a single rear propeller type composite-wing aircraft and a cargo bin, wherein the single rear propeller type composite-wing aircraft comprises an aircraft body, composite lift wings mounted on two sides of the aircraft body in a foldable manner and a thruster; the aircraft body is set as a deck platform; a self-sealing ducted fan is arranged in each composite lift wing, and a wing hinge (1028) is designed on the outer side of the composite lift wing; a magnetic type automatic interlocking port male head and a magnetic type automatic interlocking port female head are arranged on the front and rear sides of each composite lift wing respectively and are of the same size; the thruster is the propeller; the cargo bin is mounted at the lower part of the aircraft body. The foldable composite-wing cargo aircraft has the characteristics of short taking-off and landing distance, high flying speed, high wing structural strength, low flying energy consumption, long hang time and high safety, and the wings can store energy.

The invention discloses a soft sealing gate valve. The soft sealing gate valve comprises a valve shell, wherein a valve plate is arranged inside the valve shell, a sealing plug is connected to the topof the valve plate, and third rubber pads and second rubber pads are sequentially arranged on the outer wall of the sealing plug from bottom to top in an embedded mode; and sealing rings are arrangedon the inner side of the valve shell, and first rubber pads are arranged on the outer walls of the sealing rings in a wrapping mode. According to the soft sealing gate valve, the sealing plug is arranged on the top of the valve plate, a valve rod is arranged on the top of the sealing plug, and during downward movement of the valve plate, the sealing rings abut against the third rubber pads on theouter wall of the sealing plug and are clamped in grooves of the third rubber pads; and when the third rubber pads are damaged, the valve plate can continue to slide down, and the sealing rings abutagainst the second rubber pads and are clamped in grooves of the second rubber pads, so that the sealing stability of the soft sealing gate valve is achieved, and the service life of the soft sealinggate valve is prolonged..

The invention relates to a rear single ducted fan type composite wing aircraft with double ducted fan composite ailerons. The rear single ducted fan type composite wing aircraft with the double ductedfan composite ailerons comprises a rear single ducted fan type composite wing aircraft and ducted fan thrust self-energized composite ailerons which are assembled on the two sides of the rear singleducted fan type composite wing aircraft, wherein the rear single ducted fan type composite wing aircraft comprises an aircraft body, composite lift wings and a propeller, wherein the composite lift wings are fixedly mounted on the two sides of the aircraft body; the aircraft body is a deck platform; self-sealed ducted fans are placed in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; self-sealed ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electric, liquid and gas interfaces and wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wingsthrough the wing hinges. The rear single ducted fan type composite wing aircraft with the double ducted fan composite ailerons has the advantages of short takeoff and landing distance, high flying speed, high wing structural strength, energy storage ability of the wing, low flying energy consumption, long hang time and so on; and the large-area composite lift wings can have effects of gliders inan emergency case, the safety of the aircraft is greatly enhanced, and safeties of personnel and materials are guaranteed.

The invention discloses a propeller-thrusted composite wing manned aircraft with additional wings. A composite wing aircraft with a rear single-propeller comprises an airframe, additional wings assembled on two sides of a wing, and a manned cabin; a self-enclosed ducted fan is arranged in the composite lift wing, and wing hinges are designed on the outside of the composite lift wing; the wing hinge and an electro-hydraulic gas interface are arranged on one side, towards the airframe, of each additional wing, and the additional wing is arranged on the outside of the composite lift wing in a folding way through the hinge wing; the electro-hydraulic gas interface is provided with a cover, and battery and fuel are built in the additional wing; and the manned cabin is arranged below the airframe. The composite wing manned aircraft disclosed by the invention is not only short in take off and land distance, fast in flight speed, high in wing structure intensity, low in flight energy consumption, long in hang time and high in security, and the wing can store energy; the electro-hydraulic gas interface is arranged on one side or two sides of the additional wing, the energy intercommunication between the additional wing and the composite lift aircraft airfoil is realized, and the flexibility of the whole aircraft is improved since the action is controlled by the composite lift aircraft.

The invention provides a rear single ducted fan type composite-wing aircraft with zero thrust composite ailerons and additional wings. The rear single ducted fan type composite-wing aircraft with thezero thrust composite ailerons and the additional wings comprises a rear single ducted fan type composite-wing aircraft, zero thrust self-energized ailerons and additional wings, wherein the zero thrust self-energized ailerons and the additional wings are assembled on the two sides of wings; the additional wings are mounted on the external sides of the zero thrust self-energized ailerons through wing hinges in a foldable manner. The rear single ducted fan type composite-wing aircraft with the zero thrust composite ailerons and the additional wings has the advantages that the taking-off and landing distance is short, the flying speed is high, the structural strength of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, large-compositelift wings can have effects of gliders in the case of emergency, the safety of the aircraft is greatly enhanced, and safeties of personnel and materials are guaranteed.