249results about How to "Reduced Stiffness Requirements" patented technology

The invention relates to an atmospheric plasma chemical processing method of WC and SiC optical molding molds, which belongs to the atmospheric plasma chemical processing methods of the optical molding molds. The atmospheric plasma chemical processing method can solve the problems that the grinding and polishing technology which is used for processing after processing and forming of the optical molding molds made of SiC and WC materials has the disadvantages of low processing efficiency, poor surface quality, damage of a sub-surface layer and short service life of the molds. The method comprises the steps of: introducing a mixture of plasma gas, reaction gas and oxygen into space between a cathode and an anode of a plasma generator, imposing radio frequency power signals on the cathode andthe anode, producing the plasma discharge between the two electrodes, then placing the surface to be processed of the WC or SiC optical molding mold in a plasma jet region for carrying out chemical reaction and realizing the optical surface processing of the optical molding molds made of the SiC and WC materials. The method is used for carrying out the optical processing on the surfaces of the WCand SiC optical molding molds.

The invention provides an installation process of an upper module on an offshore oil platform. The installation process comprises the following steps: (1) arranging a slipping track device in a platform lifting operation area; (2) transporting the upper module to a platform construction area and putting the upper module on the slipping track device; (3) arranging a hydraulic lifting and slipping device at one side of the slipping track device; (4) starting lifting operation; (5) after a slipping track to be lifted is parallel and level with a slipping track on the platform, stopping the lifting operation and connecting the two slipping tracks into a whole; (6) slipping the upper module to a set position; and (7) stopping slipping and putting the upper module on lower support structures tocomplete connection between the upper module and the lower support structures. The installation process has the following beneficial effects: accurate positioning of the upper module and installationoperation of the upper module in any position on the offshore oil platform can be achieved; at the same time, the installation process has no special requirements for the arrangement position of the site for offshore oil platform construction and is slightly affected by external factors; and the installation process is convenient for site operation and has the effects of lowering the operation cost and improving the operation safety.

The invention discloses a method for testing the fracture energy of concrete by a three-point bending beam without self-gravity doing work, and belongs to the technical field of civil engineering. The method is characterized by manufacturing a concrete beam of which the total length is 1.912 times of clear span. A test device comprises a sensor, an angle steel connecting rod, a clip-on extensometer, a sheet bar and the like. Through a tested load-deflection curve, the fracture energy of the concrete is calculated directly without fitting a curve. The fracture energy of the concrete is the ratio of an area enclosed by the load-deflection (the work done by a load) to the area of a beam ligament. The device for testing the fracture energy of the concrete by the three-point bending beam without self-gravity doing work has the advantages that: the self-gravity of a concrete test piece is counteracted without adding any connecting rod or weight to counteract the work done by the self-gravity; requirements on the rigidity of a test machine are low; the fracture energy is calculated without fitting the curve or calculating the work done by the gravity; calculation processes are simplified; and a test device is simple and easy to operate, so the device is suitable for small and medium laboratories with small test machine rigidity.

The invention provides a numerical-control machine tool for processing spiral bevel gear, which comprises a machine tool body, a workpiece box, a turn table of the workpiece box, a tool box and the supporting post of the tool box, wherein, the machine tool body is T-shaped, and two groups of rails X and Z which are perpendicular to each other are formed on the machine tool body; the turn table of the workpiece box is mounted on the rail X; the supporting post of the tool box is mounted on the rail Z; the workpiece box is mounted on the turn table thereof via turntable bearings; the supporting post of the tool box has a gantry structure, the sliding rail Y of the tool box is formed on one side of the gantry, and two traction screw rods are arranged in the gantry; and screw holes are formed on the tool box, the tool box is rotationally mounted on the traction screw rods via the screw holes, and one end of the tool box is stuck to the rail Y via slideway. The invention has the following advantages: the structure is reasonable, the operation and the application are convenient, the workpiece box has a small turning radius and large turning angle, the machine tool has small volume and stable operation, and the tool has high positioning accuracy, so that the invention is applicable to industrialized production, in particular to the numerical-control processing of large-size spiral bevel gear.

The invention discloses an evaporative cooling system of a hybrid motor stator. A stator sealing space comprises a stator housing (1), an insulated sleeve (3) and an end cover (2), wherein a hollow pipeline (7), an end part spraying system, a stator evaporation space and a condenser (16) which are arranged in a stator core (6) or the straight line section of a stator winding (8), and an external forced circulation system form an evaporative cooling loop. Heat produced by the straight line section of the stator winding (8) is transferred to an evaporative cooling medium inside the hollow pipeline (7). A plurality of nozzles (10) are arranged around the end part of the stator winding (8), and the evaporative cooling medium is directly sprayed on the end part of the stator winding (8) after atomized by the nozzles (10) for absorbing the heat produced on the end part. A liquid part subjected to heat exchange in the evaporative cooling medium on two parts flows into the stator sealing space, the vaporized evaporative cooling medium raises to enter the condenser (16), and is condensed by the condenser (16) to become liquid, and the liquid flows back to the stator sealing space.

The invention discloses a positioning fixture for drum-like part turning. The positioning fixture comprises a support bar, wherein the front end of the support bar is coaxially provided with a support device which is inserted in the inner hole of a drum-like part when in use; the supporting device comprises a support wheel coaxially wound at the outer side of the support bar; a spoke structure used for supporting and fixing the support wheel is fixedly arranged between the support wheel and the support bar; spiral mounting holes, which extend along the radial direction of the support wheel, are uniformly and circumferentially distributed in the external ring surface of the support wheel; support studs are spirally assembled in the spiral mounting holes; and one end, away from the support bar, of each support stud is provided with a propping end which is used for propping against the inner hole wall of the drum-like part when in use. Holes are not required to be formed in the support bar, so that the strength of the support bar is not influenced, multiple spiral mounting holes can be formed in the support wheel, so that more support stud can be inserted so as to improve the supporting effect of the support device.

The invention relates to an iron bird bench test system, in particular to a performance testing device of an airplane steering surface drive actuator. The device comprises a bracket, the steering surface drive actuator (5), a steering surface imitation part (6) and a loading actuator (7); the steering surface imitation part (6) comprises rocker arms (6-1 and 6-3), mass plates (6-2) and a rotary shaft (6-4); the rocker arms (6-1 and 6-3) are fixedly connected with the rotary shaft (6-4); the mass plates (6-2) are symmetrically fixed to the two ends of the rotary shaft (6-4); one end of the steering surface drive actuator (5) is fixed through the bracket; the other end of the steering surface drive actuator (5) is connected with the steering surface imitation part (6) through the rocker arm (6-1); one end of the loading actuator (7) is fixed through the bracket; and the other end of the loading actuator (7) is connected with the steering surface imitation part (6) through the rocker arm (6-3). By means of the performance testing device of the airplane steering surface drive actuator, the problems that in traditional design, a loading system is not convenient to install, output force of an airborne actuator is difficult to measure, the stiffness analog is dispersed and accuracy is low are solved, and optimal design of the iron bird bench actuator and a back end system is achieved.

The invention provides a device used for aircraft skin drilling. The device comprises a large arm part with multiple degrees of freedom, a supporting connecting base, a small arm part with multiple degrees of freedom and a sucking disc part, wherein the large arm part can slide along a guide rail; the tail end of the large arm part is fixedly arranged on the first side surface of the supporting connecting base; the small arm part and the sucking disc part are independently mounted on the second side surface of the supporting connecting base; the large arm part can drive the supporting connecting base to move to a working region of aircraft skin; the supporting connecting base is fixed relative to the skin by virtue of a sucking disc of the sucking disc part; and the small arm part drills on a plurality of positions of the working region. Compared with existing skin drilling equipment, the device provided by the invention is more suitable for a complex surface of aircraft skin, has greater drilling space and greater flexibility.

The invention relates to a jet-flow-guided laser-spark-electrolysis combined machining device, and belongs to the field of non-traditional machining. The jet-flow-guided laser-spark-electrolysis combined machining device adopts the structure integrating three non-traditional machining methods, and is composed of a laser generator, a machining module, a working solution circulation system and a power supply module, wherein the laser generator is placed above the machining module, and laser beam machining and spark machining are ensured to be coaxial; an electrode in the machining module for sparking machining can be stationary or rotary; the working solutions for jet-flow-guided laser machining and spark machining employ deionized water, and form a set of working solution circulation system with the working solution for electrolytic machining. When the device is used for machining, the jet-flow-guided laser machining and spark machining are employed as the main means for removing material, being accompanied by electrolytic machining; speed, accuracy and surface quality of part manufacturing are all taken into consideration; thereby, rapid machining of various micro holes with abnormal countersunk heads, and various defects caused by using single non-traditional machining method are overcome.

The invention discloses a bamboo-shaped buckling-restrained brace, comprising a core component, an external restrained component and reinforced connecting components, wherein the core component is formed by alternately arranging a plurality of circular energy dissipation sections and a plurality of circular elastic sections along a longitudinal coaxial line; each circular elastic section comprises a plurality of middle elastic sections and two end elastic sections; the cross sectional area of each circular energy dissipation section is smaller than that of the corresponding circular elastic section; the core component is positioned in the external restrained component; each reinforced connecting component is composed of a node section, a connecting section and a reinforcing barrel. The bamboo-shaped buckling-restrained brace disclosed by the invention has the advantages that all the circular energy dissipation sections are shorter, and only yield without buckling under the action of an axial force, so that mortar is unnecessarily added or additional parts are unnecessarily arranged for restraining the circular energy dissipation sections, the cross sectional area of each circular energy dissipation section is smaller than that of each circular elastic section, the yielding force is less, and the rigidity requirement on the external restrained component is lower, therefore the external restrained component can be a simple circular casing, and the effects of simple structure, convenience in processing and lighter dead-weight are achieved.

A ''short-range overloading vacuum prepressing---dynamic discharging consolidation combination method'' to dealing with the soft soil ground foundation, its features are : overloading prepressing the vacuum membranes of conventional vacuum prepressing method with covering water; proceeding the settlement observation to each settlement observation points according the vacuum prepressing operating rules, continuing prepressing 5~10 days after the prepressing settlement above 80% of calculate settlement, then stopping the water overloading vacuum prepressing after ensuring stable completely; removing the vacuum membrane and sun-curing 1~2 days, then proceeding the dynamic dewatering consolidation to eliminating the stored water in sand cushions which is leaved when overloading vacuum prepressing rapidly, then dynamic consolidation or roller compaction after the water level below 1.5m. Its beneficial effects are: it can eliminate the water in muck soil during a short time and enhance the consolidation degree; it makes the skin soil layer get the greatest density, meets the requirements of load bearing capacity and rigidity rapidly and prevents rebound phenomenon; it shortens the construction period and lowers the costs and applies to large area project filling soil recently which has large thickness saturated soft soil particularly.

The invention discloses a supporting structure of a low-pressure cylinder module of a high-power nuclear steam turbine. The low-pressure cylinder module is positioned on a base platform and comprises an outer cylinder, an inner cylinder and a rotor, wherein the inner cylinder is positioned in the outer cylinder; a low-pressure end part steam seal is arranged on the end part of the rotor; the outer cylinder is supported on the base platform; a plurality of inner cylinder cat foot supports are arranged on the inner cylinder, are extended out of the outer cylinder and are supported on a supporting component of the base platform; and the rotor is supported on the base platform through a rotor bearing support base. Due to the adoption of the supporting structure, the design difficulty of the outer cylinder and the base platform can be reduced, the production cost can be reduced, and the economy and the safety of the turbine are effectively improved.

The invention discloses a vane wheel built-in submersible electric pump with a stator coil protection sleeve. The vane wheel built-in submersible electric pump comprises a vane guide body, an integrated rotor, a protection sleeve positioning seat, a motor stator and a ring-shaped stator shell, wherein two axial ends of the stator shell are correspondingly connected with the periphery of the protection sleeve positioning seat and the periphery of a guide shell; a protection sleeve is mounted on the vane guide body via the protection sleeve positioning seat; the guide shell is mounted on the protection sleeve via a sealing ring; the vane guide body, the guide shell, the sealing ring, the protection sleeve, the stator shell and the protection sleeve positioning seat form a sealed space; the space is filled with clean soft water; a winding coil of the motor stator is a water-resistant winding coil. According to the vane wheel built-in submersible electric pump, a winding is placed in the sealed space filled with the clean soft water; cooling of a stator winding during normal operation of a water filling type submersible motor is facilitated; meanwhile, adverse effects caused by contact between the stator winding of the ordinary vane wheel built-in submersible electric pump and environment water can be avoided; the safe reliability of the winding and even the whole unit is improved.

The invention discloses an inner stator permanent-magnet moving iron core-type linear oscillation motor which comprises an inner stator iron core, an outer stator iron core, a rotor iron core, a cage-type rotor iron core bracket, permanent magnets, an armature winding and a resonant spring, wherein multiple permanent magnets are uniformly embedded into a yoke of each annular stator iron core of the inner stator iron core along the peripheral direction; multiple coils for forming the armature winding are wound on outer stator iron core teeth; the rotor iron core comprises multiple segments of arc-shaped iron cores; various segments of arc-shaped iron cores are fixedly connected into a whole by using the cage-type rotor iron core bracket; the whole is arranged in an air gap between the inner stator iron core and the outer stator iron core; and the resonant spring sleeves the part between the cage-type rotor iron core bracket and an end cover. The permanent magnets do not participate in reciprocating vibration, so that the security, the reliability and the robustness of the motor can be greatly improved; the permanent magnets and the armature winding are put on different stators, so that high-temperature magnetic losses of the permanent magnets can be avoided; the mass of a rotor is reduced; the requirements of a system on the rigidity of the resonant spring can be reduced; and improvement of the resonant frequency is facilitated.

The invention discloses a flexible direct-current transmission wind and wave hybrid power generation system. The flexible direct-current transmission wind and wave hybrid power generation system comprises a mouse cage type tower frame platform, a wind energy subsystem, a wave energy subsystem, a power regulation unit and a flexible direct-current power transmission station; wind power generation and wave energy power generation are combined, the characteristic that dynamic response of the wave energy subsystem is rapid is fully exerted, wind power generation fluctuation power restraining and tower frame platform inclination active regulation can be achieved, the mouse cage type tower frame platform supports the wind and wave hybrid power generation system, a rigid oval floating body passively regulates the inclination angle of a tower frame, the wave energy subsystem is inversely hung on a round platform, power generation and electric modes can be rapidly switched according to the station, and power grid scheduling power and tower frame inclination angle stability can be ensured; the power regulation unit achieves wind and wave maximum power capturing and power dual-way flowing; the flexible direct-current power transmission station finishes converging and feed of wind wave capturing power. Wind and power output power and tower frame inclination angle stability can be improved,the mounting and maintaining cost can be greatly reduced, and development of the wind and wave hybrid power generation system can be promoted.

The invention discloses a shaft system structure of a five-gear rear drive transmission with small gear-shifting synchronous inertia. A spindle reverse gear assembly (4) is mounted on the left side of a spindle front bearing (5), a spindle first-gear gear assembly (6), a low-speed synchronizer component (7), a spindle second-gear gear assembly (8), a spindle third-gear gear (9) and a spindle fourth-gear gear (10) are sequentially mounted on a spindle (12) from left to right and positioned between the spindle front bearing and a spindle rear bearing (11), the low-speed synchronizer component, the spindle third-gear gear and the spindle fourth-gear gear are fixedly connected with the spindle, the spindle first-gear gear assembly and the spindle second-gear gear assembly rotatably sleeves the spindle, and a middle shaft fourth-gear gear assembly (14), a third-gear and fourth-gear synchronizer component (15) and a third-gear gear assembly (16) are sequentially mounted on a middle shaft (17) from right to left and positioned on the left side of a middle shaft rear bearing (13).