11 results about "Transverse stiffness" patented technology

A medical probe is presented including an expandable basket assembly coupled to a distal end of a tubular shaft. The basket assembly includes a cloverleaf cutout structure at its distal end and spines extending proximally from the cloverleaf structure and coupling to the tubular shaft. The cloverleaf structure includes a sinusoidal-like member extending from one spine to an adjacent spine in a direction around the longitudinal axis. Dimensions of the sinusoidal-like member can be configured to provide a lateral stiffness of the expandable basket assembly within a predetermined range and a maximum peak stress during retraction of the expandable basket assembly into an intermediate catheter such that the maximum peak stress is less than a predetermined threshold.

The invention discloses a compact transverse stable vertical ultralow frequency three-way limiting marine airbag vibration isolator which comprises an upper cover plate, a lower cover plate, a middle limiting ring, an elastic limiting layer and rubber bag bodies, and a multi-closed cavity structure is formed among the rubber bag bodies through the upper cover plate, the lower cover plate and the middle limiting ring; the upper cover plate and the lower cover plate are respectively provided with an elastic limiting layer, the elastic limiting layers and the middle limiting ring form a three-way limiting structure, vertical stretching, compression and transverse displacement of the rubber air bag are limited, and therefore three-way limiting of the rubber air bag body is achieved. The air bag vibration isolator for the ship can be applied to various mechanical equipment with vibration reduction requirements, and has the advantages of being small in structural size, low in vertical frequency, large in transverse rigidity, capable of achieving three-direction limiting, safe, reliable, good in system stability and the like.

A medical probe is presented including an expandable basket assembly coupled to a distal end of a tubular shaft. The basket assembly includes a cloverleaf cutout structure at its distal end and spines extending proximally from the cloverleaf structure and coupling to the tubular shaft. The cloverleaf structure includes a sinusoidal-like member extending from one spine to an adjacent spine in a direction around the longitudinal axis. Dimensions of the sinusoidal-like member can be configured to provide a lateral stiffness of the expandable basket assembly within a predetermined range and a maximum peak stress during retraction of the expandable basket assembly into an intermediate catheter such that the maximum peak stress is less than a predetermined threshold.

The invention relates to a mechanism (1) with variable stiffness. It comprises a plurality of solid, discrete elements (2) arranged at least in series and at least one connector (3) interconnecting elements. The at least one connector is configured to apply a tensional force (F) of variable size between the series of elements, so that by varying the size of the tensional force, at least the transversal stiffness of the mechanism is varied accordingly. The mechanism constitutes a pivoting system with equilibrium defined by the shape of the elements. The mechanism is configured to adapt to externally applied interaction forces during use by adjusting the tensional form force applied by the connector in response to the applied interaction forces.

The invention discloses a sandwich composite material light high-strength wing rib and an integral forming method. The wing rib comprises an annular web plate, a peripheral surface layer, a web plate edge strip, a connecting area turned-over edge, a connecting area surface layer and a plurality of wing rib supporting rods. The annular web is of a sandwich structure and is matched with the surface layer composite materials on the two sides, the transverse rigidity is improved, the problems of loading instability and S-shaped bending of an existing wing rib are solved, the characteristics of light weight and high strength are achieved, and the strict requirements of solar airplanes and the like are met. The flanging edge strip, the web edge strip and the connecting area flanging are integrally formed by a surface layer composite material, so that the structural integrity and the damage resistance are enhanced; the surface layer of the connecting area is fixed to the spar, and the connecting area turnup improves the fitting degree and the bonding strength. The two ends of the wing rib supporting rod are clamped between the surface layers on the two sides of the web edge strip, the risk of secondary bonding and splitting is avoided, and the bearing capacity is further enhanced.

The utility model discloses an air spring with the ratio of transverse rigidity to vertical rigidity larger than 1, which comprises a bag skin, an upper cover and a piston which form a closed cavity, the closed cavity is filled with gas with set pressure so as to enable the bag skin to expand, the periphery of the upper cover is connected with an outer sleeve part, and the outer sleeve part extends vertically and wraps the outer side wall part of the bag skin. The air spring is provided with the outer sleeve piece, the air spring generates transverse rigidity through the interaction force between the outer sleeve piece and the expansion bag skin, the transverse rigidity of the air spring can be adjusted by adjusting the vertical height of the outer sleeve piece, and then the ratio of the transverse rigidity to the vertical rigidity of the air spring is larger than 1. The transverse stroke and the vertical stroke of the air spring are both large, rigidity sudden change does not exist in the operation process, and the overall stability is good. The air spring is simple in overall structure and low in production cost, the fatigue life of the bag skin of the air spring can be prolonged through shape optimization of the outer sleeve piece, and reliability is improved.

The present application relates to the technical field of flexible strain measurement, and discloses a flexible sensing module for measuring the spatial curvature of a continuum mechanism and a manufacturing method thereof, which comprises a flexible substrate and a sensing array module arranged in the flexible substrate in a determined direction; after the flexible sensing module is wrapped on the surface of the continuum mechanism, the axial tensile strain or the axial 45-degree angle shear strain at different positions on the surface of the continuum mechanism is measured by each strain sensing unit, then the bending deformation and the torsional deformation of the measurement interval covered by the flexible sensing module are calculated by combining the deformation continuity of the continuum mechanism, and the spatial curvature distribution of the continuum mechanism is fitted and reconstructed. Based on the capacitive in-plane strain sensing element of the flexible substrate and combined with the design of the lateral stiffness enhancement structure, the one-directional large tensile strain measurement with low cross-interference of the sensing site is realized, thereby increasing the accuracy and the range of the curvature measurement of the continuum mechanism.

The invention relates to the technical field of framework assembling and machining, in particular to a marine composite material laminated structure which comprises an outer skin, and an inner skin is attached to the surface of one side of a damping layer. The composite material laminated structure for the ship is composed of the outer skin, the anti-stripping reinforcing layer, the sandwich layer, the damping layer and the inner skin, longitudinal bending, shearing and transverse rigidity improvement are achieved through the multi-direction reinforced outer skin, and the anti-stripping reinforcing layer forms resin anchoring points through a thermoplastic fiber thin net; the sandwich layer is designed through gradient partitions with different densities and thicknesses, so that a high-load area has higher compression resistance and bending resistance, a low-load area realizes light weight, the stress of the sandwich structure is effectively optimized, the longitudinal overall rigidity is improved, local crushing is prevented, and meanwhile, the strength of the sandwich structure is improved. A longitudinal drainage channel is arranged in the sandwich layer and corresponds to the inspection hole, so that drainage, ventilation and internal damage detection can be realized.

The invention discloses a method for controlling the critical rotating speed of a rotor by adjusting the rigidity of a bearing supporting system, and relates to the field of heavy rotating equipment with a bearing support. The method for controlling the critical rotating speed of the rotor by adjusting the rigidity of the bearing supporting system comprises the following steps that a rigidity model of the bearing supporting system is built, a rigidity calculation point is marked as O1, and supporting points at the two ends are marked as O2 and O3; collecting the distance a between the O1 and the O2, and collecting the distance b between the O1 and the O3; the bearing rigidity K2 at the O2 position is collected, and the bearing rigidity K3 at the O3 position is collected; according to a, b, K2 and K3, the bearing supporting rigidity K0 at the position of O1 is obtained; the rigidity KM1 borne by the mass M1 at the position O1 is obtained according to the bearing supporting rigidity K0 at the position O1 and the transverse rigidity K1 of the shaft at the position O1; and obtaining the critical rotating speed of the rotor according to the M1 and the KM1. According to the method, the rigidity borne by the mass of the point is calculated, the critical rotating speed of the rotor is obtained, the critical rotating speed of the rotor can be controlled by adjusting the rigidity of a bearing supporting system, and resonance is avoided.

The utility model belongs to the field of rail transit vibration damping fasteners, and discloses a rigidity-adjustable vibration damping fastener, which sequentially comprises an upper iron plate, upper iron plate retaining shoulders arranged at two ends of the upper iron plate, an under-plate elastic base plate and a lower iron plate along a rail falling direction, and lower iron plate retaining shoulders arranged at two ends of the lower iron plate. According to the utility model, the under-plate elastic base plate, the upper iron plate, the lower iron plate and the transverse stop block are arranged, so that the fastener has large vertical displacement and low rigidity, the transverse extrusion rigidity and the shearing performance are ensured, and the combined damping effect of a compression type structure and a shearing type structure is achieved; the upper iron plate shoulder retaining part, the transverse stop block and the lower iron plate shoulder retaining part are sequentially matched, and it is guaranteed that the fastener has high transverse rigidity under low-vertical-rigidity movement.