228 results about "Ogive" patented technology

A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with the addition of a weld filler material. Each frame includes a frame root portion and a frame profile portion connected to each other. The frame root portion has cut-out notches receiving the stringers passing therethrough. The frame root portion is welded to the skin panel at the areas between the cut-out notches, and may be welded to the respective stringer in each cut-out notch. The stringers and frames are fabricated from webs and flanges, whereby a premanufactured grid of flanges may be used. The result is a very strong, yet simple shell component structure, that may be manufactured with a simple welding process, at a low cost and with low effort.

A countermeasure system which is capable of defusing rocket propelled grenades (RPG) is provided by spacing an array of explosive charges or primacord from the protected structure to allow and sense an ogive of the fused RPG to enter into a functional plane of the array initiating one or more of the charges to collapse to ogive. The array is supported flexibly or rigidly and further ballistic protection is incorporated behind the array in fixed or inflatable forms to provide protection of the structure from the explosive products from the array and the ballistic impact of the defused RPG.

A subfloor structure of an aircraft airframe, particularly of a helicopter, includes longitudinal beams and crossbeams that intersect each other and are interconnected to form a grid that is fixedly attached to the floor and the bottom skin of the aircraft fuselage. Structural elements such as pyramid frustums and reinforcements are arranged on the beams. The longitudinal beam and the crossbeam have a trapezoidal cross-section that is preferably open on the wider base side, closed by a spine web along the narrow side, and bounded laterally by inclined leg webs that extend downwardly from the spine web at an angle outwardly relative to each other. The subfloor structure grid effectively absorbs the energy of a crash impact having both axial or vertical as well as non-axial or lateral impact force components.

A training cartridge projectile for use in either a plastic cartridge case or a conventional metal cartridge case is disclosed that contains no explosive material. The projectile has an insert having a body portion and a front end, a container overmolded onto the body portion of the insert, a frangible ogive fastened to the front end of the tubular insert; and a payload module within the ogive in front of the container carrying a non-explosive signature material for providing a visual indication of projectile impact to an observer upon projectile impact with an object. The module includes a hollow frangible ampoule containing the signature material, and a generally disc shaped base member engaging the insert and closing the ampoule. The base member preferably has a set of axially extending vanes engaging the signature material during spin-up as the projectile is accelerated through the bore of the weapon firing the projectile.

A projectile, particularly a practice round, has a projectile body that includes a hollow ogive that bursts upon striking the target into which marking material is inserted. The marking material is released when the projectile strikes the target and the ogive bursts. The marking material is covered by a protective cap that breaks when the projectile bursts on the target.

The invention relates to a thrust inverter with grids (5) for a turbojet, that defines at least a portion of the downstream section (103) of a nacelle (100) housing the turbojet, comprising a front frame (105) to be secured to a fixed portion (102) of the nacelle and bearing, on the one side, cylinders (6) for the translational actuation of at least one mobile cowling (2) and, on the other side, grids for inverting the peripheral thrusts, characterised in that the front frame includes a fixed portion for securing the front frame to the fixed portion of the nacelle and bearing the diversion grids, and a portion mounted so as to be capable of translation movement along the longitudinal axis of the nacelle and on which one end of the cowling actuation cylinders is attached, wherein the fixed and mobile portions of the front frame can be removably connected to each other by locking means.

Closely spaced conventional optical fibers are arranged in a grid placed between a first surface and a second surface. A penetrating impact onto the first surface results in a hole of a size proportional to the diameter and velocity of the impacting object. The size and shape of the debris plume that travels between the first and second surfaces is also proportional to the diameter and velocity of the impacting object. If the debris plume is sufficiently energetic, a number of the fibers in the grid are broken. The size and shape of the area defined by the broken fibers can be determined simply by determining which fibers are no longer transmitting light. Analytical methods are then used to relate the extent of the damaged area to the location of an MOD impact, the direction from which the impact occurred, and the size of the impacting object.

A contact is provided for use in a land grid array (LGA) socket. The contact includes a support body defining a support body plane. The support body is configured to be held in a hole in an LGA socket and has opposed side edges. The contact also includes a contact beam having a base portion projecting from one of the side edges. The base portion extends along a base axis and has an upper end joined at a deflectable bend with an outer portion of the contact beam. The outer portion is configured to have surface mounted thereon an adjoining contact, and the outer portion projects from the bend at a first angle with respect to the base axis and at a second angle with respect to the support body plane.

The invention discloses a laser scanning method for laser melting in a selected area. The laser scanning method comprises the following steps: dividing a workpiece area into a plurality of latticed regular triangles with side length being 1mm-10mm and a plurality of irregular figures at borders according to the cross section information of a workpiece, taking a gap G between the adjacent figures from -1mm to 1mm; scanning the irregular figures at the borders as the zoning regular triangles and adopting an equidistant scanning line for successively finishing the zoning figure scanning; according to the zoning direction, adopting the equidistant scanning line for successively finishing the gap scanning; scanning along a practical outline of the workpiece or the outline deviating within 1mm inward or outward to the practical outline of the workpiece according to the requirement, or repeatedly scanning along a plurality of outlines deviating from the practical outline of the workpiece within 1mm, thereby finishing the cross section canning for the workpiece. According to the scanning method provided by the invention, the scattering effect of residual stress in the workpiece during a laser scanning process is improved, the laser scanning direction during the scanning process does not need to be repeatedly changed, the scanning efficiency is high, the technique control is simple, and the compactness and the precision of the workpiece are ensured.

In one aspect, an artillery projectile apparatus is provided that includes a carrier projectile containing a payload, and a fuze disposed at an ogive of the projectile and which is configured to eject the payload when the fuze is detonated. The fuze includes a receiver configured to receive location information from a radionavigation source and a processor configured to acquire position data from the receiver. The processor is also configured to estimate a projectile flight path using the position data, to determine intercept parameters of the artillery projectile relative to an ejection plane of its payload cargo, and to adjust an ejection event initiation command time of the payload in accordance with the determined intercept parameters. In some configurations, the present invention dramatically decreases range errors typically associated with delivering artillery payloads to specific targets.

An electromagnetic shielding film comprises a conductive portion and an opening portion, and a moire preventing part is formed in the opening portion. The moire preventing part may be formed approximately at the center of the opening portion, and may be formed on a line connecting intersections facing each other in the conductive portion in the mesh pattern. The moire preventing part may have a substantially circular planar shape or a polygonal planar shape (such as a quadrangular, pentagonal, hexagonal, or octagonal shape). Of course the moire preventing part may have an at least partially curved planar shape. The electromagnetic shielding film preferably satisfies the inequality 0.1Sa≦Sb≦5.0Sa, in which Sa is the area of the intersection of the conductive portion and Sb is the area of the moire preventing part.

The invention relates to a helical weld pipe line outer diameter measuring device and a helical weld pipe line outer diameter measuring method based on view detection. The helical weld pipe line outer diameter measuring device comprises an industrial camera 1, an industrial camera 2, a grid calibration target, a linear laser generator, a cantilever, a guide track, a lifting mechanism and a measuring platform, wherein the plane of laser generated from the linear laser generator is perpendicular to the horizontal plane; the industrial camera is fixed on the guide track through the lifting mechanism; a central light axis is perpendicular to the plane of the laser; the industrial camera 2 is used for vertically taking images of the edge of a steel pipe and the laser light from top to bottom through the cantilever; the grid calibration target is arranged inside the plane of the laser and perpendicular to the central optical axis of the industrial camera 1; the calibration of the industrial camera is firstly completed; when a helical weld pipe is produced, laser light images are simultaneously taken by the industrial camera 1 and the industrial camera 2, and the outer diameter and the ellipticity of the helical weld pipe can be calculated by processing the images. Due to the cooperation of the double industrial cameras, the guide track and the lifting mechanism, dynamic measurement on the outer diameter and the ellipticity of helical weld pipes of different diameters can be achieved.

The present invention provides a multi-stage tilting and multi-rotor flying car including: a main frame externally shaped like a rectangle and internally partitioned to have a grid structure; a body mounted at a center of the main frame in consideration of balance; a plurality of rotors mounted to the main frame to face upward; a plurality of wheels mounted to the main frame to face downward; body wings provided at opposite sides of the body; and an automatic driving controller provided in the body and controlling the rotors and the wheels, thereby having effects on spending only the minimum necessary flying time for taking off and landing in a narrow area, and improving flight performance three times higher in flight time and flight speed and five times higher in fight distance than a rotary-wing aircraft such as a helicopter while flying in the fixed-wing mode.

A sonotrode and anvil are adapted for ultrasonic welding of work pieces, to produce a narrower weld region that exhibits greater durability, permitting use of less material per package. The horn-to-anvil contact is through a plurality of energy directors arranged into a three-dimensional grid pattern to be capable of distributed vibration-transmissive contact. The energy directors include a series of plateau surfaces regularly spaced apart in a first direction, and in a second direction that is orthogonal to the first direction, to form the grid pattern. The energy directors of the horn are configured to interlock with the energy directors of the anvil. The rectangular-shaped plateaus are spaced apart by angled side-surfaces that form valleys. A stepped transition to a corresponding region of reduced height for the energy directors of the sonotrode and anvil may form a cosmetic seal region with a lesser integrity, in addition to the main barrier seal.

The invention discloses a conformal cutting layer and path planning method for curved surface 3D printing. The conformal cutting layer comprises a conformal curved surface cutting layer method and a three-dimensional space path planning method, the conformal curved surface cutting method comprises the following steps that defect inspection and repairing are carried out on a grid model, it is ensured that the outer surface of the model is a two-dimensional flow shape, if the grid surface is not an all-triangular unit, triangular formation is carried out on the grid surface; then regional segmentation is carried out, the printing sequence of each sub-portion and the approximate direction of the sub-layer are determined; the outer surface is converted into point cloud data, and the point cloud is biased inwards; the offset point cloud data is fit to form a triangular mesh surface; and the model is correspondingly divided into a plurality of curved surface layers to obtain a curved surfaceset; and the three-dimensional space path planning method comprises the following steps of checking whether the curved surface in the curved surface set is the two-dimensional flow shape or not, homogenizing the triangular unit, calculating the geodesic distance of each vertex of the grid relative to the designated reference point, extracting equivalent points, fitting to be a contour line, and converting into a G-code to obtain a printing path. According to the conformal cutting layer and path planning method, the special requirements of curved surface printing can be met.

The invention discloses a cutter wheel for cutting a brittle material and a processing method thereof. The cutter wheel is provided with a V-shaped cutting blade part (1), a disc surface (2) and an axle hole (3), wherein the periphery of the chine line l at the external edge of the V-shaped cutting blade part (1) is provided with cutting blades (4) and recess structures (5), which are alternately-distributed; each cutting blade (4) comprises curved surfaces (Part a1 and Part a2), four side surfaces (a3, a4, a5 and a6) and V-shaped cutting edges (V-shaped cutting edge 1, V-shaped cutting edge 2 and V-shaped cutting edge 3)of which the included angles are respectively psi1, psi2 and psi3; and the disc surface (2) and the axle hole are provided with grid-line grooves (6), and the cutting blades (4), the recess structures (5) and the grid-line grooves (6) are obtained by the processing in a laser scanning mode. The cutter wheel with the new structure can avoid or reduce the condition that the cutter wheel is blocked when the cutter wheel with other structures cuts the material, and can prevent the material from producing radial cracks, thereby prolonging the service life of the cutter wheel and simultaneously obtaining the high-grade cutting sections. Besides, the inner walls of the grid-line grooves (6) are coated with solid lubricant, thereby well solving the lubrication problem.

A Reconfigurable Nose Control System (RNCS) is designed to adjust the flight path of spin-stabilized artillery projectiles. The RNCS uses the surface of a projectile nose cone as a trim tab. The nose cone may be despun by the action of aerodynamic surfaces, to zero spin relative to earth fixed coordinates using local air flow, and deflected by a simple rotary motion of a Divert Motor about the longitudinal axis of the projectile. A forward section of the nose cone having an ogive is mounted at an angle to the longitudinal axis of the projectile, forming an axial offset of an axis of the forward section with respect to the longitudinal axis of the projectile. Another section of the nose cone includes another motor, the Roll Generator Motor, that is rotationally decoupled from the forward section and rotates the deflected forward section so that its axis may be pointed in any direction within its range of motion. Accordingly, deflection and direction of the forward section may be modulated by combined action of the motors during flight of the projectile.

The invention relates to a wing, a wing, a tail unit or grid fins for a flying object moving with supersonic speeds. The wing comprises leading edges and tailing edges.

According to the invention, the contour of at least one of the leading contour and the tailing contour has a meandered shape.

By means of the inventive meandered contours the wave drag of the flying object may be decreased. The inventive design of the leading or tailing edges of a wing can be used for aircrafts, spacecrafts, missiles, projectiles and the like.