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102results about How to "Easy to derive" patented technology

Quick simulation analysis method for radar antenna servo system

The invention discloses a quick simulation analysis method for a radar antenna servo system. The quick simulation analysis method includes the steps that (1) parametric modeling of a bond graph is carried out, components in the system are simplified according to the modeling sequence of a drive motor, a transmission mechanism and a reflecting surface body and accordingly a bond graph model of the antenna servo system is built; (2) virtual prototype multi-rigid-body modeling is carried out, part rigid-body models in all links are sequentially built on the basis of the modeling theory that each solid body in the system corresponds to one rigid body in a multi-rigid-body model, the corresponding rigid bodies are combined according to a parametric model of the bond graph and accordingly a system design model is obtained; (3) a parameter synchronization mechanism is introduced, and design model parameters are transferred to the bond graph model synchronously by means of a design model information file; (4) a system mathematic model is deducted according to the system bond graph model. Mathematical modeling simulation, multi-rigid-body modeling simulation and bond graph modeling simulation methods are well combined, advantages are made use of and defects are avoided.
Owner:XIDIAN UNIV

Diplopore nanoscale poly(glycidyl methacrylate)-ethylene glycol dimethacrylate (PGMA-EDMA) cross-linked microballoons and preparation method thereof

The invention discloses diplopore nanoscale poly(glycidyl methacrylate)-ethylene glycol dimethacrylate (PGMA-EDMA) cross-linked microballoons and a preparation method thereof. The diplopore nanoscale PGMA-EDMA cross-linked microballoons have ultra-macroporous and mesoporous double structures uniformly arranged in the interiors and the exteriors of the diplopore nanoscale PGMA-EDMA cross-linked microballoons, diameters of 3 to 20 micrometers, dispersion coefficients of 2.5 to 5%, ultra-macroporous diameters of 200 to 600 nanometers and mesoporous diameters of 30 to 60 nanometers. The preparation method has the advantages that linear PGMA seeds obtained by dispersion polymerization and having uniform aperture sizes are utilized as templates and undergo a one-step swelling polymerization reaction, wherein formation and distribution of diameters are adjusted by a binary pore-foaming system and a phase-separation technology, and thus the diplopore nanoscale PGMA-EDMA cross-linked microballoons which are all-poly(glycidyl methacrylate) (PGMA-EDMA) microballoons having ultra-macroporous and mesoporous double structures, uniform aperture sizes and good biocompatibility are obtained. Therefore, the preparation method realizes high-efficiency, rapid and high-flux biochemical separation analysis.
Owner:INST OF CHEM CHINESE ACAD OF SCI

Determination method for interference film hole machining angle

The invention relates to a determination method for an interference film hole machining angle, and belongs to the technical field of aero-engine turbine blade machining. The determination method comprises the following steps that, a machine tool coordinate system (x, y, z) is established according to a position axis of a machine tool, a horizontal rotation axis of the machine tool serves as a B axis, and a vertical rotation axis of the machine tool serves as a C axis; according to the machine tool coordinate system (x, y, z), an initial coordinate of the interference air film hole and an initial coordinate of a bending guider are determined; and according to the initial coordinate of the interference film hole and the initial coordinate of the bending guider, when the B axis and the C axis are rotated to drive the interference film hole to rotate towards the bending guider, the rotation angle of the B axis and the rotation angle of the C axis are the machining angle of the interference film hole. According to the determination method, on the premise that the design performance of a turbine blade air cooling system is not reduced, shielding of a blade structure is effectively avoided, electric spark machining of the interference film hole is achieved, and therefore the design performance of an advanced aero-engine is met.
Owner:GUIYANG AVIC POWER PRECISION CASTING
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