35results about How to "The principle is correct" patented technology

The invention provides a novel adsorption and desorption experiment device and a novel adsorption and desorption experiment method. The device mainly consists of a reference cylinder, a sample cylinder, a confining pressure pump, a booster pump, an air compressor, an intermediate container, a constant temperature system, a pressure sensor and a computer, wherein the sample cylinder mainly consists of a sample chamber, a confining pressure chamber, a left adjustable plug, a right adjustable plug, a barrel, a sealing ring, a screen mesh and a leather sheath; the confining pressure chamber is defined by the barrel and the leather sheath; the sample chamber is defined by the leather sheath and the adjustable plugs; the sample chamber is connected with the reference cylinder; the reference cylinder, the sample cylinder and the pressure sensor are arranged in the constant temperature system; the confining pressure chamber is connected with the confining pressure pump, and the confining pressure pump is used for increasing the confining pressure of the confining pressure chamber, so that the real stratum conditions can be simulated; the sample cylinder is provided with the two adjustable plugs, one adjustable plug is provided with the screen mesh on the top, and the other adjustable plug is not provided with the screen mesh, so that two rock samples including standard rock samples (having length of 5cm and diameter of 2.5cm) or rock sample powder (with 60-80 meshes) can be arranged in the sample cylinder. The device and the method have the advantages that the principle is reliable, and the device is simple in structure and simple and safe to operate; the real stratum environment can be simulated, and temperature and pressure conditions of different reservoir stratums as well as the methane adsorption and desorption law of the rock samples can be determined, so that reasonable experimental data can be provided for shale gas occurrence form research and reserve calculation.

The invention discloses a low impact unlocking device based on a shape memory alloy spring and mainly applied to spacecraft. A main structure of the low impact unlocking device can be mounted an effective load to be unlocked and can be used with bolts to connect a spacecraft body with the load. When on-orbit unlocking is needed, the mechanism can be unlocked by heating the shape memory alloy spring of the low impact unlocking device, restraint between the bolts and nuts is unlocked by moving the mechanism, the bolts are separated from the nuts under the action of force, and accordingly two parts are unlocked. The low impact unlocking device has the advantages that such problems that an initiating explosive device widely on spacecraft models is high in impact and nonuniform in launching state and test state are solved; the device is reusable, lightweight, small and the like; and reliability, applicability and economy of the device are guaranteed.

The invention discloses a synchronal rotary multi-phase oil-gas mixed delivery pump, comprising a shell; an oil cylinder synchronal rotary sleeve and a main shaft are arranged in the shell; the main shaft is connected with the oil cylinder synchronal rotary sleeve by a sliding plate; the shell is penetrated by the main shaft; synchronal rotary sleeve end covers and an eccentric bearing seat are arranged at the two sides of the oil cylinder synchronal rotary sleeve; conical roller bearings are arranged between the synchronal rotary sleeve end covers and the eccentric bearing seat; the conical roller bearings are arranged in an outer sleeve and are fixed by round nuts; flat keys are arranged between the outer sleeve and the eccentric bearing seat; main shaft bearing seats are respectively arranged on the two sides of the eccentric bearing seat; an elastic shaft coupler is arranged on one side of the main shaft bearing seat, and an outlet flange is arranged on the other side of the main shaft bearing seat; a pair of conical roller bearings is arranged between the main shaft bearing seats and the main shaft; a sealing cover is arranged on the main shaft positioned at one side of the conical roller bearing; the sealing cover is fastened by a first round nut. By use of the synchronal rotary multi-phase oil-gas mixed delivery pump, no emission and no pollution of an oil well can be realized. The synchronal rotary multi-phase oil-gas mixed delivery pump is simple in structure, easy to be manufacture and maintain.

The invention discloses a method for the non-destructive measurement and calculation of the casting length of an anchor bolt, and particularly provides a method for achieving the non-destructive measurement and calculation of the casting length of an anchor bolt by calculating the functional relation between amplitudes and attenuation coefficients during the propagation of ultrasonic guided waves in the anchor bolt in order to overcome the defects that the method for the non-destructive testing method based on the ultrasonic guided wave in the prior art is incapable of acquiring reliable results and the method itself is of no repeatability. The method comprises the following steps: using an anchor bolt which is completely identical with the anchor bolt to be measured and calculated as a reference basis; acquiring the characteristic indexes of the propagation of the guided waves in the casting part of the anchor bolt through the frequency scanning test and wave packet analysis of the ultrasonic guided waves under the preset testing conditions; and further carrying out the frequency scanning test on the anchor bolt to be measured and calculated under the same testing conditions, and calculating according to the result of the wave packet analysis and the acquired characteristic index values to acquire the casting length of the anchor bolt. The invention further provides a method for the non-destructive measurement and calculation of the total length of an anchor bolt on the basis of the method. The method of the invention has the advantages of reliable principle, scientific and convenient calculation, simple implementing instruments, convenient installation and high accuracy of the measurement and calculation result. Therefore, the invention is particularly applicable in the field of engineering.

The invention discloses a straight acting device for a spacecraft based on an SMA (Shape Memory Alloy) spring and a use method thereof. The straight acting device for the spacecraft based on the SMA spring comprises a piston jacking rod, an upper end cover, a limiting spring, a sleeve, the SMA spring, a heater resistance wire, an electric heater, a soft outgoing line and an electric connector, wherein the sleeve is a piston cavity; a piston acting rod, the limiting spring, the SMA spring, the electric heater and the soft outgoing line are arranged in the sleeve from top to bottom; when the straight acting device does not work, the piston jacking rod is restrained in an initial position by the limiting spring, and the limiting spring and the SMA spring are balanced; when the straight acting device acts in orbit, any one of two heating wires in the heater is electrified through instruction, the SMA spring is heated, after the temperature reaches a phase-transition temperature, memory alloy is subjected to phase-transition, and the heat expanding type SMA spring stretches out and drives the piston jacking rod. The straight acting device for the spacecraft based on the SMA spring utilizes the advantage of easiness in controlling the action of the SMA spring and ensures the high reliability of a spacecraft mechanism.

The invention belongs to the technical field of die cutting forming equipment, and relates to a high precision ferrule punching positioning forming die cutting device which comprises two function parts which refer to a ferrule punching counterpart circular motion device and a die plate and die positioning device. A height adjusting nut which can be vertically adjusted in position is inserted in a fixed nut support which is fixedly arranged at the center of an upper die plate of a die cutting machine, the tip of the height adjusting nut aims at a pulley connected at the front end of a lever tripod, the tail end of the lever tripod connected to a fixing shaft of a lower bottom plate of the die cutting machine is connected with a fixed stress bearing, a punching material dragging circular roller is placed on the fixed stress bearing, and punching materials are laid between the fixed stress bearing and the lower bottom plate of the die cutting machine. A die with a positioning needle is arranged on an upper die plate of the die cutting machine, a die bottom plate with a positioning hole is arranged on the lower die plate of the die cutting machine, and the positioning needle corresponds to the positioning hole. The high precision ferrule punching positioning forming die cutting device is simple in structure, reliable in principle, scientific in design, simple and convenient to assemble, easy to operate, accurate in positioning, low in production cost, high in production efficiency, and environmentally friendly.

The invention discloses a method and a device for computing stiffness of an aviation orthogonal stiffened plate, which comprises the following steps of: receiving the data of the aviation orthogonal stiffened plate, constructing a theoretical mechanical model of the orthotropic plate of the single-stirrup, and calculating the bending rigidity value of the orthotropic plate of the single-stirrup; applying a finite element model by statics bending moment to calculate the bending deformation curve of the orthotropic plate of the single-stirrup distribution structure; Comparing the data results calculated by the two models to obtain a finite element model correction parameter, constructing a complex aviation multi-stirrup orthogonal plate numerical model, and calculating the rigidity value ofthe aviation orthogonal stiffened plate. The method and the device is characterized by taking the characteristics of wallboard parts as starting points, avoiding estimating the rigidity according to experience, calculating the rigidity of the aviation positive crossing reinforcement plate rapidly, and providing the theoretical basis for the clamping scheme and the quality control of the frame parts in the processing process, thereby improving the processing quality and the efficiency.

The invention provides a preparation method for a quickly quenched Fe-based metal grain with an excellent wave absorbing property. The preparation method comprises the following steps: weighting corresponding metals according to the mass percent of each metal element in an alloy; preparing the metals into a magnetic metal alloy; and after melting, melt-spinning and ball-milling the metal alloy, performing ultrasonic dispersing treatment, thereby obtaining a material of the Fe-based metal grain with the excellent wave absorbing property, wherein the material is capable of improving an interface property and is uniformly distributed. According to the preparation method, the cavitation principle and the mechanical effect of ultrasonic wave in liquid are utilized to obtain the uniformly distributed quickly quenched Fe-based metal grain material; and when the ultrasonic wave is transmitted in a piezoelectric material and a magnetostriction material, the wave absorbing property of the material of the Fe-based metal grain is increased due to the induced polarization and the induced magnetization caused by the mechanical effect of the ultrasonic wave. The preparation method provided by the invention is correct in principle and is scientific in measures. The material of the quickly quenched Fe-based metal grain with the excellent wave absorbing property prepared according to the preparation method is high in practical value and wide in application prospect.

The invention discloses a tooling for hole depth measurement and processing assurance using a vertical drilling machine, comprising a base (1), a support rod (2) fixedly connected with the base (1), and a bracket fixed above the support rod (2) (3), a through groove for accommodating and fixing the gauge (4) is arranged on the bracket (3); the through groove includes a circular groove (32) for accommodating the meter body (42), which is arranged below the circular groove (32) 1. The adjustment groove (33) for placing the adjustment end (43) and facilitating adjustment is arranged on the top of the circular groove (32) for the measurement groove (31) protruding from the measurement end (41); it is also provided with a horizontally placed position transmission Block (5), one end of it remains fixed with a certain plane that is lifted and lowered synchronously with the drill bit on the vertical drilling machine, and the lower surface of the other end is in contact with the upper surface of the measuring end (41) of the measuring table (4). The invention has the advantages of simple structure, precise control, hole depth measurement and hole depth processing guarantee functions and the like.

The invention provides a dual-redundancy aircraft fuel remaining amount measuring system. The dual-redundancy aircraft fuel remaining amount measuring system comprises an electromechanical managementcomputer (1), a fuel computer (2), a left oil way flow sensor (3), a right oil way flow sensor (4), a comprehensive display (5), a left engine fuel flow meter (6), a right engine fuel flow meter (7) and an electronic control device (8), the fuel computer (2) collects and calculates the numerical values of the left oil path flow sensor (3) and the right oil path flow sensor (4), and obtains the aircraft fuel remaining amount value through comprehensive calculation; when the loop breaks down, subsequent airplane fuel remaining amount values are obtained through comprehensive calculation of the electromechanical management computer (1) after the numerical values measured by the left engine fuel flow meter (6) and the right engine fuel flow meter (7) are subjected to signal conversion of the electronic control device (8). The system is correct in principle and simple in composition, and the safety redundancy of the system is effectively improved.

The invention provides an airplane negative overload auxiliary oil supply device. The airplane negative overload auxiliary oil supply device mainly comprises an oil supply pump (1), an oil supply pipeline (2) and an auxiliary oil supply device body (3). The oil supply pump (1) is connected with an oil outlet of an airplane oil tank; the oil supply pump (1) is connected with the aircraft engine through an oil supply pipeline (2), an opening of the oil supply pipeline (2) between the oil supply pump (1) and the aircraft engine is connected with the auxiliary oil supply device (3) in parallel, and the auxiliary oil supply device (3) comprises a piston (31), a spring (32), an auxiliary oil tank (33) and a limiter (34). When a certain negative overload occurs to the aircraft, the oil supply pump (1) cannot suck fuel from an aircraft fuel tank, and the auxiliary fuel supply device (3) works to supply fuel to an aircraft engine, so that the continuous flight requirement of the aircraft is met. The device is simple in structure and can meet the use requirements of the aircraft in a flight overload state.

The invention discloses a quick detection device for skid resistance of a port rail-mounted loading and unloading machine. The detection device comprises a frame, wherein a pre-tightening mechanism, aclamping mechanism, a main hydraulic cylinder and a connecting assembly are arranged in the frame. The detection device has novel structure, and skillfully converts the reaction force of the main hydraulic cylinder into the clamping force and the friction force of the detection device on a track guide rail, so that the track guide rail enters a self-locking state during working. During detection,one hydraulic station is used for controlling two sets of detection devices to simultaneously load the stress surfaces of the port rail-mounted loading and unloading machine on two guide rails. The quick detection device for skid resistance of the port rail-mounted loading and unloading machine adopts a modular design, thereby being convenient for quick assembly, disassembly and transportation indetection fields of different environments and conditions; and the detection device has strong applicability, and can meet the requirement of the skid resistance detection of the port rail-mounted loading and unloading machines used on guide rails with different types and specifications only by replacing the clamping blocks on the pre-tightening mechanism and the clamp mechanism. The quick detection device for skid resistance of the port rail-mounted loading and unloading machine can also be used as a rail locking device of the port rail-mounted loading and unloading machine.

The invention belongs to the technical field of inner cavity volume measurement and relates to a solid rocket engine inner cavity volume measurement method based on laser point cloud. The method comprises the following steps of: (1) acquiring a displacement value of the inner surface of the inner cavity of a solid rocket engine by using a line laser displacement sensor, and converting data acquired by the line laser displacement sensor into three-dimensional point cloud data of the inner cavity of the solid rocket engine by using a D-H matrix; (2) setting the design radius of the inner cavity of the solid rocket engine to be detected as R, and simplifying the three-dimensional point cloud data of the inner cavity of the solid rocket engine by adopting a radius R-based mean filtering method; and (3) calculating the volume of the inner cavity of the solid rocket engine by using a volume measurement method based on point cloud slices according to the simplified three-dimensional point cloud data of the inner cavity of the solid rocket engine.