Abstract: Provided is a locking plate system for treatment of a distal radius fracture including a locking plate (4) that is a flat laminate of intermediate molding materials that includes carbon fibers as a reinforcing material and thermoplastic resin as a matrix; a screw anchor (5) having a shaft portion (10) which has a principal thread (13) achieving a self-tapping action formed thereon and an outer circumference of a head portion of the screw anchor (5) which has an auxiliary thread (13) achieving a self-tapping action tapped thereon; and a through-hole (6) in the radius locking plate (4), which allows the radius main body (3) and the fractured bone piece (2) to be threadably fixed to the radius locking plate (4) and having a diameter that is oversized relative to the principal thread (11), and that is undersized relative to the auxiliary thread (13).

Abstract: Provided is a locking plate system for treatment of a distal radius fracture, including a locking plate (4) that is a flat laminate of intermediate molding materials that includes carbon fibers as a reinforcing material and thermoplastic resin as a matrix; a screw anchor (5) having a shaft portion (10) which has a principal thread (13) achieving a self-tapping action formed thereon and an outer circumference of a head portion of the screw anchor (5) which has an auxiliary thread (13) achieving a self-tapping action tapped thereon; and a through-hole (6) in the radius locking plate (4), which allows the radius main body (3) and the fractured bone piece (2) to be threadably fixed to the radius locking plate (4) and having a diameter that is oversized relative to the principal thread (11), and that is undersized relative to the auxiliary thread (13).

Abstract: A stem 8 has the following elements made from FRP: an upper outer shell 4U, a main structure upper half 3U, a main structure lower half 3L, and a lower outer shell 4L when the stem is placed in a flat state. The elements are integrated into one piece by stacking the elements and applying heat and pressure to melt resins impregnated in the FRP structural elements. Each outer shell is a curved prepreg sheet formed by impregnating carbon fibers arranged at angle of ±45 degrees with a thermoplastic resin, and each upper and lower halve is an evenly stacked part in which prepreg sheets are stacked. Overlapping section 5 of the upper and lower outer shells are formed such that the left and right portions of a main structure 3 formed by integrating the upper and lower halves 3U, 3L does not have a stepped outer surface.

Abstract: A stem 8 has the following elements made from FRP: an upper outer shell 4U, a main structure upper half 3U, a main structure lower half 3L, and a lower outer shell 4L when the stem is placed in a flat state. The elements are integrated into one piece by stacking the elements and applying heat and pressure to melt resins impregnated in the FRP structural elements. Each outer shell is a curved prepreg sheet formed by impregnating carbon fibers arranged at angle of ±45 degrees with a thermoplastic resin, and each upper and lower halve is an evenly stacked part in which prepreg sheets are stacked. Overlapping section 5 of the upper and lower outer shells are formed such that the left and right portions of a main structure 3 formed by integrating the upper and lower halves 3U, 3L does not have a stepped outer surface.

Abstract: The purpose of the invention is to eliminate not only the shearing stress concentration occurring at a distal end of a stem but also that at a proximal end thereof so that a load acted on a hip joint can be distributed collectively on the proximal portion of the stem corresponding to transmission route in a normal state and the range of variation of the stress distribution on the proximal portion comes to be as narrow as possible on the whole. An artificial cement-less hip prosthesis stem which comprises an inner construct 7 reacted with the load acted on the hip joint and an outer construct 8 transmitting the load acted on the inner construct to a femur 1. The former construct has an inner body 7B reacted with the load transmitted from a neck 7A. The latter construct has both an outer body 8A which is bell mouth-shaped toward epiphysis so as to surround the inner body 7B and a leg 8B extending toward medullary cavity.

Abstract: The method of designing and manufacturing the artificial joint stem, comprising steps of performing analysis of the internal stress of the artificial joint stem and bone and the adhesive stress of the artificial stem and bone, using the computer, based on the three dimension data indicating the structure of the bone formed by using plural tomographic images of the bone, the design condition involving the form and stiffness of the artificial joint stem configured by using at least one of the tomographic images and the three dimension data, wherein if the result of the analysis does not satisfy the design condition, the condition is changed to have the computer reanalyze and if the result of the analysis satisfies the design condition, the artificial joint stem is designed and manufactured with the stem data based on the result of analysis and the design condition.

Abstract: This invention provides cement-less type artificial joint stems with the use of complex material which can be connected to bone without using cement, does not get loose over a long period of time, has excellent durability, and has appropriate external form and stiffness to meet the condition of each patient. Stem 1 with the use of composite material inserted in the insertion hole 8 which is penetrated into the bone 7 and fixed to the bone 7 without using cement, has the external form of the epiphysis which fits the internal form of the insertion hole 8, has the main part 3 with changing stiffness so that in the neighborhood of the boundary between the epiphysis and diaphysis, stiffness becomes lower as approaching toward the diaphysis, and possesses a neck part 2 to place a spherical head in an artificial joint provided at the proximal end of the main part.

Abstract: A first parting film is held on a first flat laminating table in close contact with the first flat laminating table, and then wide prepregs are laid for plane lamination on the first parting film to form a large prepreg-laminate having a large area. A second parting film is held on a second flat laminating table in close contact with the second flat laminating table by suction, and then narrow prepregs to form a gridlike prepreg-laminate. The large prepreg-laminate is floated up by jetting air from the first flat laminating table is cut on a cutting table to obtain a prepreg-laminate skin. The gridlike prepreg-laminate is processed similarly to obtain a prepreg-laminate doubler. The prepreg-laminate skin and the prepreg-laminate doubler are carried from the cutting table to a laminating mold having a single-contour laminating surface so as to be superposed and are laminated to form a composite panel.

Abstract: A first parting film is held on a first flat laminating table in close contact with the first flat laminating table, and then wide prepregs are laid for plane lamination on the first parting film to form a large prepreg-laminate having a large area. A second parting film is held on a second flat laminating table in close contact with the second flat laminating table by suction, and then narrow prepregs to form a gridlike prepreg-laminate. The large prepreg-laminate is floated up by jetting air from the first flat laminating table is cut on a cutting table to obtain a prepreg-laminate skin. The gridlike prepreg-laminate is processed similarly to obtain a prepreg-laminate doubler. The prepreg-laminate skin and the prepreg-laminate doubler are carried from the cutting table to a laminating mold having a single-contour laminating surface so as to be superposed and are laminated to form a composite panel.

Abstract: A first parting film is held on a first flat laminating table in close contact with the first flat laminating table, and then wide prepregs are laid for plane lamination on the first parting film to form a large prepreg-laminate having a large area. A second parting film is held on a second flat laminating table in close contact with the second flat laminating table by suction, and then narrow prepregs to form a gridlike prepreg-laminate. The large prepreg-laminate is floated up by jetting air from the first flat laminating table is cut on a cutting table to obtain a prepreg-laminate skin. The gridlike prepreg-laminate is processed similarly to obtain a prepreg-laminate doubler. The prepreg-laminate skin and the prepreg-laminate doubler are carried from the cutting table to a laminating mold having a single-contour laminating surface so as to be superposed and are laminated to form a composite panel.

Abstract: A sandwich structure does not permit the permeation of water and a sandwich structure repairing method is capable of easily repairing the sandwich structure. A sandwich structure (1) includes a core (4) formed of a closed-cell foam plastic material, and surface plates (2, 3) formed of a fiber-reinforced composite material containing hydrophobic inorganic fibers as reinforcing fibers and bonded to the opposite surfaces of the core (4). Water is unable to permeate the sandwich structure.

Abstract: A first parting film is held on a first flat laminating table in close contact with the first flat laminating table, and then wide prepregs are laid for plane lamination on the first parting film to form a large prepreg-laminate having a large area. A second parting film is held on a second flat laminating table in close contact with the second flat laminating table by suction, and then narrow prepregs to form a gridlike prepreg-laminate. The large prepreg-laminate is floated up by jetting air from the first flat laminating table is cut on a cutting table to obtain a prepreg-laminate skin. The gridlike prepreg-laminate is processed similarly to obtain a prepreg-laminate doubler. The prepreg-laminate skin and the prepreg-laminate doubler are carried from the cutting table to a laminating mold having a single-contour laminating surface so as to be superposed and are laminated to form a composite panel.

Abstract: A sandwich structure does not permit the permeation of water and a sandwich structure repairing method is capable of easily repairing the sandwich structure. A sandwich structure (1) includes a core (4) formed of a closed-cell foam plastic material, and surface plates (2, 3) formed of a fiber-reinforced composite material containing hydrophobic inorganic fibers as reinforcing fibers and bonded to the opposite surfaces of the core (4). Water is unable to permeate the sandwich structure.

Abstract: A method for absorbing the moisture of a composite material, which can absorb the moisture of the composite material in a short period of time and which can provide a moisture absorption distribution which is equal to that of a composite material placed under actual environment. At time table, having a plurality of different environment conditions for pressure, temperature and humidity, and periods of time corresponding to the environment conditions, is previously prepared. Then, a composite material is put in a pressure vessel, and the environmental conditions in the pressure vessel are changed on the basis of the time table. Thus, the moisture absorption state of the composite material can be equal to that after the elapse of predetermined years under actual environment. In addition, it is possible to absorb the moisture of the composite material in a short period of time by absorbing the moisture of the composite material under an environment condition of high pressure.

Abstract: A three-dimensional digital map prepared by an satellite or the like is stored in a first memory as a wide-area information. Narrow-area information obtained by a laser radar is stored in a second memory. Obstacle information on obstacles, such as high-voltage power lines, high buildings and cranes, is stored in a third memory. These three information are read out to generate virtual images on a see-through type display mounted on a helmet of a pilot so that the virtual images is superimposed on the actual field of vision.

Abstract: A pitch link for a rotary wing aircraft includes first and second shaft members threadingly engaged with each other. A first rod end is fixedly secured to the first shaft member and a second rod end is rotatably coupled to the second shaft member. First and second spherical bearings are mounted on the first and second rod ends, respectively. A guide member guides the first shaft member for movement in an axial direction of the first shaft with respect to the second shaft while preventing rotation of the first shaft.

Abstract: A pitch link having an adjustable length is constructed as a diamond-shaped frame by coupling and fixing four flexible beams at end portions thereof. Spherical bearings are provided on opposite ends of the structure. A turnbuckle shaft is screwed into vertices of the structure and turned to the length of the pitch link. The turnbuckle shaft can be rotated by a detachable motor.

Abstract: A pitch link having an adjustable length is constructed as a diamond-shaped frame by coupling and fixing four flexible beams same in length and rigidity each at end portions thereof. Spherical bearings are provided on opposite ends with the longer diagonal line as an axis of the pitch link. A turnbuckle shaft is screwed into vertex portions on the shorter diagonal line, which is turned so as to adjust a length of the shorter diagonal line, thereby adjusting a length of the pitch link. The turnbuckle shaft is rotated by a detachable motor. Vibrations of a body and the rotational position of a rotor are detected by a vibrosensor and a phase detector respectively while an aircraft equipped with the pitch link is flying, an amount for adjusting the pitch link is calculated by a vibration analyzer from the electrical signals, and the motor is driven through a FM data transmitter/receiver to adjust the pitch link.

Abstract: A manufacturing method of composite articles is provided by which it is possible to constantly mold thick composite articles as primary structure component parts for aircraft, such as rotor hubs of helicopters, which are highly accurate in dimensions and have a favorable internal quality with no internal defects such as molding cracks, voids and so forth. Therefore, this manufacturing method of composite articles includes the steps of laying up resin-impregnated reinforcing fiber materials in a molding cavity within a molding jig of a matched die type, evacuating the interior of the molding jig so that the resin-impregnated reinforcing fiber materials are under reduced pressure and thereafter closing and heating the dies of the molding cavity, causing the resin to overflow from the laid up materials into a trap located remote from the molding cavity, and molding the laid up materials inside of the molding jig.

Abstract: A ducted fan-type tail rotor of a rotor craft in which the tail rotor is surrounded by a tubular duct is provided which includes at least six rotor blades, and pitch horns, each mounted to the respective rotor blades. Each pitch horn is swingable to change a pitch angle of the rotor blade. Some of the pitch horns, the number of which is about a half of the total number of the pitch horns, are mounted to a first type of the rotor blades at a mounting angle larger than a reference mounting angle required to obtain a predetermined thrust, and the remainder of the pitch horns are mounted to a second type of the rotor blades at a mounting angle smaller than the reference mounting angle.