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

The invention belongs to the technical field of rolling bearing measurement, and relates to a bearing static stiffness test device and a test method thereof. The rolling bearing static stiffness testdevice provided by the invention is correct in principle, simple in structure and convenient to assemble and disassemble; the device can accurately load the rolling bearing in the radial direction andaccurately position the circumferential angle of the rolling body, the method for testing the static stiffness of the bearing is simple and easy to implement, and the measured static stiffness parameter of the rolling bearing is accurate and reliable.

The invention discloses a supporting mechanism for a main mirror of a telescope with an anti-rotation design. The outer spherical surface of the mandrel of the main mirror of the main mirror cooperates with the cylindrical surface of the middle hole of the main mirror of the telescope to limit the two-dimensional translation in the horizontal direction of the main mirror; three groups of bottom supports The component adopts a flexible structure to limit the vertical translation of the primary mirror and the two-dimensional tilt in the horizontal direction; an anti-rotation component is added to the support mechanism to limit the vertical rotation of the primary mirror, and the two sides of the anti-rotation flexible rod are fixed on the primary mirror support The base plate is flat, and the middle is bonded to the lower plane of the bottom support bonding seat through optical structural glue. The anti-rotation component has no direct contact with the primary mirror, which can reduce the influence of installation stress and adhesive stress on the surface shape of the primary mirror; the flexibility of the support mechanism Links can avoid mutual stress interference of each link. The supporting mechanism of the invention has correct principle, easy processing of mechanical parts and easy assembly, and is suitable for the main mirror supporting field of the reflective tracking and capturing telescope. The invention also discloses a telescope using the support mechanism and its main mirror assembly.

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 wavesin 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, andcalculating 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 joint bearing rigidity test device and a test method. The joint bearing rigidity test device comprises a test box body, a joint bearing seat, a main shaft, a locking nut, a loading device and a sensor, other parts are arranged in the test box body, an outer ring of a tested joint bearing is arranged in the joint bearing seat, the main shaft is sleeved with an inner ring,and a shaft shoulder axially depending on the main shaft is fixed with the locking nut; at a left end of the main shaft, a flange plate is externally arranged at a left end surface of the test box body, the right end of the main shaft is fixed with the right end surface of the test box body through a bolt; the loading device is used for applying axial and radial load on the tested joint bearing, the sensor is used for testing the displacement and load of the tested joint bearing. The joint bearing rigidity test device provided by the invention has the advantages of being simple in structure and convenient to assemble and disassemble, and can be used for performing accurate radial loading and accurate axial loading of the joint bearing, the tested joint bearing rigidity parameter is accurate and reliable, and the device is suitable for the performance measurement of the joint bearing development organization and using organization.

The present invention provides a distributed power generation traction network train operating state identification method, comprising: obtaining the voltage and current phasors of the head end of the traction network segment; power flow) to obtain the train power of this segment, based on the different determination conditions of the active power of the segment, identify the running state of the train in the segment of the traction network, and by calculating the active power of the entire line, identify the combined operation of the trains in the traction network of the entire line state. The train running state identification method of a distributed power generation traction network provided by the present invention is to identify the train running state through its power flow distribution. The principle is correct, the algorithm is simple and reliable, and it can be directly applied to the traction network system of distributed power generation. Energy intelligence management of power generation system provides the basis.

The invention relates to the technical field of heat distribution pipeline leakage detection, in particular to a method for detecting leakage from a heat distribution pipeline with a heat preservation structure. The method comprises the following steps: step 1, after the heat distribution pipeline with the heat preservation structure is subjected to leakage, initiating a heat conduction and heat exchange process composed of pipeline wall slit jet impact heat exchange as well as heat conduction and heat exchange on a heat preservation layer; step 2, analyzing the distribution of flow fields formed by the impact jet from a pipeline wall slit nozzle on an impact surface; and step 3, measuring the distribution of temperature fields on the heat distribution pipeline through infrared heat radiance, and acquiring a changing process of temperature fields in the axial direction of the heat distribution pipeline. The method provided by the invention is free of contact, high in detection sensitivity and accuracy, and definite in principle, and has the advantages that whether the heat distribution pipeline is subjected to leakage or the temperature change is caused by damage of a heat preservation structure can be visually and accurately determined, and both safety dangers and running risks caused by the leakage from the heat distribution pipeline can be effectively reduced.

The invention discloses an on-track monitoring device for tension of a spacecraft rope. The device comprises an angular position sensor, a gear rack transmission assembly, a microswitch, an installation sleeve, a compression spring, a push rod and a roller assembly, wherein the rope rotates around the roller assembly; the roller assembly is tightly pressed by the compression spring through the push rod; the compression spring is mounted in the installation sleeve; a first end of the push rod slides inside the installation sleeve; an end part of a second end of the push rod is connected with the roller assembly; the roller assembly performs translational motion due to the change of the tension on the rope; the gear rack transmission assembly changes the translational motion of the roller assembly into rotation; the angular position sensor measures the rotation angle of the gear rack transmission assembly; and the microswitch triggers limit signals. According to the device, the problem that the tension of a rope part on the spacecraft requires to be monitored accurately is solved. At the same time, the device has the advantages of light mass, simple adjustment, small size, high security, low power consumption and the like, and the reliability and the applicability of on-track monitoring of rope tension are effectively guaranteed.

The invention provides a compartment separation device for a space vehicle, comprising a base, a sleeve, a push rod assembly, a push spring and an adjusting gasket, the bottom of the push spring is in conflict with the base, and the top of the push spring is in contact with the push rod In contrast, there is a groove on the base, and the adjusting gasket is located in the groove to adjust the push force of the push rod by adjusting the push spring. The sleeve is installed on the docking ring of the first cabin of the space vehicle, and the push rod is arranged on The end face of the docking ring of the second cabin of the space vehicle, when there is no external force constraint, the piston is placed on the top of the sleeve; when the space vehicle is launched, the ejector rod is pressed into the sleeve; Promote the reverse movement of the first compartment and the second compartment to complete the separation. The invention can ensure the consistency of the thrust when a plurality of separation devices work together, can effectively improve the smoothness of the cabin section separation process of the aircraft, and reduce the attitude disturbance caused by the cabin section separation.

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 method and device for calculating the stiffness of an aeronautical orthogonally stiffened plate. The method includes: receiving the data of an aeronautical orthogonally stiffened plate, constructing a theoretical mechanical model of a single-rib orthotropic plate, and calculating the single-rib orthotropic Bending stiffness value of the plate; apply the finite element model through the static bending moment, calculate the bending deformation curve of the orthotropic plate of the single-rib distribution structure under the bending moment; compare the data results calculated by the above two models, and obtain the correction parameters of the finite element model , construct the numerical model of the complex aeronautical multi-reinforced orthogonal plate, and calculate the stiffness value of the aeronautical orthogonally stiffened plate. The present invention starts from the characteristics of wall plate parts, avoids the previous method of estimating the stiffness based on experience, quickly calculates the stiffness of the aviation orthogonally stiffened plate, and can provide a theory for the clamping scheme and quality control of the frame parts in the processing process basis, improve processing quality and efficiency.

The invention discloses an on-orbit frequency increasing mechanism for a spacecraft flexible appendage. The on-orbit frequency increasing mechanism comprises a driving element, a speed reducing device, a support frame, a woven stay cord belt, a joint support, a transitional shaft section, a unidirectional bearing and a winding reel, wherein the driving element, the speed reducing device, the joint support, the transitional shaft section, the unidirectional bearing and the winding reel are respectively mounted on the support frame, the woven stay cord belt is wound on the winding reel, driving power of the driving element is transmitted to the winding reel via the speed reducing device, the transitional shaft section and the unidirectional bearing, the winding reel rotates to drive the woven stay cord belt to be tensioned and loosened, and an end portion of the woven stay cord belt is connected with the flexible appendage. By the on-orbit frequency increasing mechanism for the spacecraft flexible appendage, the problem that the spacecraft flexible appendage is too low in fundamental frequency or frequency is required to be improved for coupling of lower-order frequency and on-satellite disturbance source. Meanwhile, the on-orbit frequency increasing mechanism for the spacecraft flexible appendage has the advantages of light weight, simplicity in control, small size, capability of being unfolded along movement, low consumption and the like, and can effectively guarantee reliability and applicability of the spacecraft flexible appendage in the on-orbit frequency increasing mechanism.