161 results about "Aeroshell" patented technology

The invention discloses an ore fine crushing and grinding device which comprises a machine shell, a hot oil cavity, a cylinder block, a grinding roller and a collecting groove. The hot oil cavity is formed in the upper end of the outer side of the machine shell in a sleeved manner, a sleeve is rotationally connected to the upper end of the inner side of the machine shell, and a first rotating rodis arranged in the sleeve; the first rotating rod penetrates and is hinged to a base plate of the inner side of the shell to be fixedly connected with the grinding roller, and a taper bottom is correspondingly arranged at the lower end of the grinding roller; and the collecting groove is arranged in the bottom of the inner side of the machine shell in a sliding manner, and the right end of the collecting groove penetrates the machine shell and is fixedly connected with a pull handle. By means of the ore fine crushing and grinding device, the hot oil cavity is arranged so that ore can be heated, ore crushing and grinding are facilitated, and the working efficiency is improved; when the arranged first rotating rod downwards moves, four fan-shaped plates are driven by a pull rod to downwardsrotate, cur ore intermittently falls downwards, the intermittent discharging effect is achieved, falling and stacking of too much ore are prevented, the follow-up grinding effect is influenced, and the practicability is high.

The invention discloses a turbine motor of gas turbine; the turbine motor comprises a casing, a turbine motor entrance, a turbine motor exit, a turbine rotor, four-level fixed blades, and four-level movable blades. The turbine rotor comprises four impeller disks and three intermediate disks; the four impeller disks and the three intermediate disks are alternately arranged along an axial direction, and are connected together via a group of pull rods. The fixed blades are mounted on the fixed casing, and an impingement cooling sleeve is arranged therein, film holes are arranged on the surface thereof, and a convection cooling channel is arranged on the trailing edge thereof. The movable blades are mounted on one side of the rotor and revolve together with the rotor, wherein three levels are hollow structures, a double-snakelike cooling channel and multiple groups of herringbone fins are arranged therein. The fixed blades and the movable blades are alternately arranged in the axial direction of the rotor, and form a gas combustion channel therein. When the gas turbine is running, the turbine motor is able to effectively change the thermal energy of the high-temperature gas into the mechanical energy for rotating the rotor, and ensure the safety of the mechanical movement by sufficient and reasonable cooling.

A direct-drive servo electric cylinder comprises a screw, a nut, a casing, an end cover and a driving system. The driving system drives the nut to rotate on the screw, therefore, the screw moves linearly along the axial direction. Outside of the electric cylinder is closed by the casing and the end cover. The driving system consists of a motor stator and a motor rotor, wherein, the motor stator is fixed on the casing and the motor rotor is fixed on the nut. The nut and an inner circle of a bearing are connected with each other directly or are in integrated design. An outer circle of the bearing is fixed on the casing. A guide sleeve arranged on the end cover is used for guiding the linear motion of the screw. A dust cover is arranged at the tail of the end cover. A cooling groove is arranged in the casing. The cooling liquid circulates in the cooling groove by a pipe joint. The direct-drive electric cylinder of the invention has simple structure and good performance. As a standardization and serialization device, the direct-drive electric cylinder provides different specifications and types for choosing, which can meet different driving requirements.

The invention discloses a two-stage turbocharger for an aviation piston engine. The two-stage turbocharger comprises a rotor assembly, a front support assembly, a rear support assembly, a turbine volute, a high-pressure compressor casing, a low-pressure compressor casing and the like, wherein each part in the rotor assembly is locked through a compression nut, and respectively connected with the turbine volute and the compressor casings through bolts; the rear support assembly is of a thin-walled stainless steel soldering structure, and bearings are distributed in a back to back mode; and the compressor casings are of a combined mode, the low-pressure compressor casing is connected with the high-pressure compressor casing through a bolt, and is connected with a regulator assembly through a bolt. The two-stage turbocharger has the advantages that: the turbocharger has simple structure and light weight, and a structure that one turbine drives two compressors is adopted, so that the requirement of an aircraft for high-altitude flight is fulfilled, and the weight of the engine is effectively reduced. The two-stage turbocharger has the characteristics of high reliability and good sealing property, and fulfills the requirement of high-altitude sealing.

A display device includes a display panel; a middle cabinet including a first support surrounding sides of the display panel and a second support extending inward from inner surfaces of the first support with the display panel seated on the second support; and a sealing-bonding member disposed on the second support abutting the first support to couple the display panel with the middle cabinet and to seal the display panel and the middle cabinet together.

The invention discloses a vortex tube motor. The vortex tube motor comprises a vortex tube rotor, a stator, thrust bearings, end covers and a case, wherein the vortex tube rotor comprises a tube, a vortex plate in spiral structure in the tube, and tubular magnetic material casted at the periphery of the tube, the thrust bearings are sleeved at the two ends of a vortex tube, the stator is surrounded at the periphery of the rotor, a certain gap is reserved between the stator and the rotor, a cylindrical magnetic slot is fixedly sheathed inside the case and a coil is embedded in the slot, the end covers are sealed at the two ends of the vortex tube rotor and the case, and the case is sheathed at the periphery of the stator. According to the vortex tube motor in the invention, electromechanical integrated design is adopted, the structure is simple, a transmission device is not needed, the motor is directly connected with a liquid or gas pipeline in series for work, so that the input cost of a transmission system is saved, the field installation space is saved, the energy consumption generated by mechanical transmission is saved, in addition, a turbine motor utilizes the vortex tube motor to discharge water for secondary power generation as the turbine motor is connected with the vortex tube motor in series, and the vortex tube motor is also installed at the bottom of a ship so as to drive the ship to run or steer.

Mounting apparatus includes an enclosure, a tray, and a securing member. The enclosure includes a side plate, and a fixing portion is defined in the enclosure. The tray secures a first storage device and is slidable in a first direction that is substantially parallel to the side plate to engage with the side plate. The securing member includes a first limiting portion and a securing portion. The first limiting portion is engaged with the tray, and the securing portion is engaged with the fixing portion to prevent the first limiting portion from disengaging from the tray.

The invention relates to a three-phase asynchronous motor for an explosion-proof fan, and relates to the technical filed of motors. The three-phase asynchronous motor comprises a motor body, a case sleeving the motor body, fan blades coaxially fixed to an output shaft of the motor body, and a dehumidification mechanism arranged on the motor body and used for dehumidification; and the dehumidification mechanism comprises a plurality of heating sheets arranged on the inner wall of the case and distributed around the circumferential side of the motor body at equal angles, a plurality of gas holesare formed in the motor body in the two axial ends of the motor body, a heat conducting layer is arranged between the heating sheets and the motor body, the gas holes are opposite to the fan blades,and a plurality of convection holes are formed in the circumferential surface of the motor body. The three-phase asynchronous motor has the effect that the motor burnout accident caused by the fact that the motor is affected by the damp is avoided, so that the service life of the motor is prolonged.

The invention discloses a fully-protected flexible unfolding re-entry aeroshell comprising a load capsule main body. A rigid thermal protection blunt nose is connected to the lower end of the load capsule main body. A sliding connecting frame is installed at the upper end of the load capsule main body. A head cover is arranged at the top of the sliding connecting frame. Hinged seats and threaded hole bearings are arranged at the connection between the load capsule main body and the rigid thermal protection blunt nose. The hinged seats are connected with the lower parts of lower support bars. The upper parts of the lower support bars are connected with the lower parts of upper support bars. The upper parts of the upper support bars is connected with the sliding connecting frame. A leeward side flexible thermal protection structure and a windward side flexible thermal protection structure are respectively connected to the upper support bars and the lower support bars. The fully-protected flexible unfolding reentry aeroshell uses a connecting-bar unfolding mechanism and adds the leeward side flexible thermal protection structure, thereby not only reducing the requirement of the fairing envelope of a launch vehicle and avoiding the impact of the inflow/shock wave on the rear-end of the aeroshell, but also improving the flight environment and increasing the loading volume to provide a technological path for the entrance, deceleration and landing of future load extraterrestrial asters.

The invention discloses an easily dismountable vehicle-mounted lithium battery. The lithium battery comprises a connecting block, a groove is formed at the bottom of the inner wall of the connecting block, a fixing device is fixedly connected to the top of the connecting block, the inner wall of the groove is slidingly connected to a fixing leg, the top of the fixing leg is fixedly connected to a stabilizing block, the interior of the stabilizing block is fixedly connected to a lithium battery, the front surface of the stabilizing block is fixedly connected to a handle, a fixing device comprises a casing, the bottom of the casing is fixedly connected to the top of the connecting block, one side of the inner wall of the casing is fixedly connected to a sliding block, and the front surface of the sliding block is provided with a sliding slot. The lithium battery relates to the technical field of lithium batteries. The easily dismountable vehicle-mounted lithium battery solves the problem that an automobile battery usually needs to be dismantled trough complex processes in automobile repair and maintenance, saves a plenty of time of the staff, reduces workload of the staff, improves work efficiency and reduces an enterprise cost.

The invention discloses a lamination device for laminated glass. A case is fixedly mounted on a worktable, a plurality of uniformly arranged brackets are fixedly mounted on the worktable, carrier rollers rotationally connected through hinge pins are arranged on the brackets, slide bars fixedly mounted on the worktable are arranged between the carrier rollers, a rubber blanket is mounted in a glassfixing plate arranged on the carrier rollers, the other end of a rotary disc is fixedly mounted on a lamination cylinder, a vacuum suction cup is fixedly mounted at the tail end of a push rod of thelamination cylinder, uniformly distributed nozzles are arranged on the vacuum suction cup, a microswitch is fixedly mounted at the left side end of the vacuum suction cup which is connected with a vacuum pump through an air pipe, and output ends of a position sensor and the microswitch are electrically connected with an input end of a data processing module. The lamination device adopts simple andreasonable structural design, is novel in modeling and has practical functions, automatic material taking, mounting and lamination are realized, so that the lamination precision is improved well, andquality of the laminated glass product is guaranteed effectively.

A wall-mounted type microwave oven includes a cabinet and a hood having a guide duct. The guide duct is movably arranged in the hood, and automatically slides in and out the hood by an actuating unit of the microwave oven. A movable filter is set in the guide duct so as to be spaced apart from an inner surface of the guide duct by a predetermined interval. Where the guide duct is moved forward, exhaust gases generated therebelow pass through the movable filter, and the filtered gases are guided into the cabinet by the guide duct. The actuating unit includes a rotary member and a drive motor mounted on the hood. The rotary member is rotated by the drive motor to move the guide duct forward. The actuating unit further includes an elastic member which is connected, at an end thereof, to the hood and, at the other end thereof, to an inside end of the guide duct. The elastic member provides an elastic force to move the guide duct rearward.

The invention discloses a foldable wing of an unmanned aerial vehicle. The foldable wing comprises a wing fixing device and a driven gear part. A rotary motor main body is fixed in the wing fixing device through a bolt. A rotary driving motor is installed on the rotary motor main body. A rotary motor driving wheel is fixed to the output end of the rotary motor main body. The driven gear part is installed on the wing fixing device through a rotary gear main body. A main swing body is installed on one side of the wing fixing device. A swing folding motor is installed on a center rotary shaft in the main swing body. An auxiliary swing body is installed on one side of the main swing body. A folding motor shell is installed at the top of the swing folding motor. A folding motor stator winding is installed in the folding motor shell through a fixing device. According to the foldable wing of the unmanned aerial vehicle, the swing bodies of the unmanned aerial vehicle can be folded at two degrees, can be turned over and can be folded rotationally at the same time.

The invention relates to a semi-open compact integral torque motor, comprising a housing assembly, a magnetic steel, a shaft sleeve, an armature winding, a brush holder, a brush, a bearing, an inner lock mother, an outer lock mother and a lead wire, wherein the housing assembly comprises a housing outer ring, a housing shaft and a housing flange. As that bear of the invention is directly installedin the inn cavity of the shaft sleeve, the function of the general fully closed integral structure is completed by the semi-open mode, and the mechanical performance of the motor is greatly improvedin the limited space and the weight range. The invention has the advantage of less parts, high reliability, compact structure and wide application range.