218 results about "Aircraft manufacturing" patented technology

The invention discloses a laminated plate aircraft skin with lift augmentation, resistance reduction, flow control and deicing prevention functions. The laminated plate aircraft skin comprises a glass fiber layer (2) and an aluminum alloy (1), wherein the glass fiber layer (2) and the aluminum alloy (1) are alternative; the surface of the skin is provided with an insulating material layer (4) and an electrode layer; the electrode layer is divided into an upper layer and a lower layer; the upper layer and the lower layer are respectively positioned on two sides of the insulating material layer (4) and are asymmetrically distributed; the upper electrode layer (3) is exposed in air and is connected with an alternating current power supply; and the lower electrode layer (5) is positioned below the insulating material layer (4) and is grounded. The laminated plate aircraft skin can be directly applied to aircraft manufacturing engineering, cannot be damaged by high-speed airflow and cannot bring parasite drag due to the damage of the original pneumatic shape. The deicing prevention function is realized by utilizing plasma heating on air and the pulse expansion wave function, the flow separation can be effectively controlled, the stall is delayed, the highest lift coefficient is increased, and the pressure difference resistance is reduced.

The invention provides a method for controlling warping of a web of a large frame type sheet metal part, and belongs to the technical field of aircraft manufacturing. For a large frame type sheet metal part of which the variable curvature, the variable section and the length are more than 1m, the method is that a technological rib groove structure is added to the outer flank of bent edge of the outer side of frame type rib part, so as to enable uniform distribution of the stress on the bent edge of the outer side of such parts after forming. The method is applicable to further control of the warping of the web of the large frame type part of which the bent edge section is complex and the curvature and the sectional linear dimension are changed constantly according to the bent edge line after forming and unloading, on the basis of springback compensation. With the adoption of the method, the springback of the part can be controlled, and the warping of the web of the part can be effectively controlled; after being formed, the part can simply meet the requirement on accurate formation without or with little manual repair by tapping, so that the forming quality and the production efficiency of the large frame type part can be obviously improved.

The invention discloses a conformal compressing tool of a wing wallboard, and belongs to the technical field of digital aircraft assembly. The conformal compressing tool comprises a conformal frame, the conformal frame comprises a supporting frame, wallboard connecting parts and a wallboard compressing part, wherein the wallboard connecting part and the wallboard compressing part are installed onthe supporting frame, the face, where the wallboard compressing part exerts pressure, of a wallboard is a curved face adaptive to the face of a pressure bearing plate of the wallboard; the two or morewallboard connecting parts are arrayed in the wallboard heading at intervals; a pushing and pressing mechanism is arranged between the wallboard compressing part and the supporting frame and used forforcing the wallboard compressing part to move relative to the supporting frame and compressing the wallboard. The conformal tool is connected with the wallboard, not only wallboard rigidity can be improved, the wallboard and a wing rib skeleton can be compressed to improve the wallboard installing efficiency and quality, and the conformal compressing tool can be widely applied to the aircraft manufacturing field.

The invention relates to a conduction and insulation test system and method of a large aircraft automatic system. The test system comprises an upper computer, a test host and distribution type test terminals; the test host is integrated with a distribution type aviation cable automatic detection system and an electric bridge measurement circuit and is in communication connection with the upper computer; the distribution type test terminals are a plurality of test terminals which are divided and distributed according to aircraft systems and are in conduction connection with the test host after being connected in series with a bus; and each test terminal is provided with a transfer cable used for being connected with a test point. According to the conduction and insulation test system, one point to multi-points simultaneous operation can be automatically realized, rapid measurement for many times is realized, test command and speed are increased, and the cost is also considered; the distribution type test terminals are distributed at a part, needing test, of an aircraft, so that the length of the transfer cable can be shortened, the cost of the transfer cable is lowered, huge economic benefit of million level is brought to an aircraft manufacturing plant, and wide popularization and spreading use are facilitated.

The invention relates to the aviation aircraft manufacturing field and relates to a longitudinal tensile loading trajectory design method based on mold surface extension. The method includes the following steps: 1, extending the mold surface, the wollens covers the mold surface via the action of the clamp during the forming process, and the material has the shape having the part curved surface; 2, calculating the jaw position and space posture, obtaining the final covering condition of the wollens during the forming process in the mold surface extending process, respectively processing the curves at two ends of the extending curved surface; (1) jaw curve scattering, (2) calculating clamp plane, (3) calculating curved clamp angle; 3, solving the movement of pulling device, designing loading trajectory of the pulling middle step, calculating according to the final device parameter; (1) calculating the pitching angle of clamp, (2) calculating the extending part of the pulling action cylinder. The longitudinal tensile loading trajectory design method based on mold surface extension can offer the guiding function for the skin longitudinal shape trajectory design and trajectory optimization.

The invention belongs to the technical field of aircraft manufacturing, particularly relates to an installing method of an airplane component based on laser positioning, and relates to an airplane system guide pipe support frame installing and detection method. An airplane coordinate system is built by mainly using an airplane entity and a laser tracking instrument; the projection equipment coordinate system building is completed by using measuring points on the entity; then, the guide pipe support frame shape and position under the airplane coordinate system are projected out by using a projection instrument; finally, a guide pipe is installed according to the projection shape and position. The method mainly solves the technical problem that the installing position of an airplane system guide pipe support frame is frequently changed, and cannot be fixed. The method is mainly used for the quality control of the airplane system guide pipe support frame installation.

Reactive hotmelt adhesives based on copolyamide can be used in hybrid components. These hybrid components find application in, for example, vehicle construction and aircraft construction.

The invention provides an analysis method of handover conditions of a hypersonic-velocity target interception missile based on interception geometry and belongs to the field of aircraft manufacturing technology. The method is technically characterized in that by considering all possible velocity direction of a target and according to the relative motion relation between the interception missile and the target, positions of all possible impact points are obtained through derivation, and the interception geometry is built; according to a research result of the interception geometry and the positional relation among the interception missile at the midcourse and terminal guidance handover moment, the target and the interception geometry, interception conditions required to be met for intercepting the hypersonic-velocity target are given; on the basis that the interception conditions are met, a calculation method of the positional condition and the solving process of the angle condition of the interception missile at the midcourse and terminal guidance handover moment are given, and the influence of maneuvering of the target on solving the angle condition of the interception missile is analyzed. Through the method, the problem that the hypersonic-velocity target cannot be intercepted through an existing interception method is solved.

The invention relates to an aluminum alloy skin digital assembly method, and belongs to the field of aircraft manufacturing. In the prior art, when skin is assembled, the position is adjusted by workers according to experience, so that assembly accuracy is low; when the position of skin is not accurate, the skin and a framework will be staggered in shape, moreover, because of the shape error of the skin, riveting deformation is big, and the appearance of an aircraft body is poor; the quality of butt joints of the skin is poor; manual lineation is big in error and low in repeat accuracy and efficiency; when no tools are provided, allowance is polished manually on the site of riveting, the efficiency is low, the quality is poor, and the noise is high. According to the aluminum alloy skin digital assembly method, the digital technological lug positioning technology is adopted, skin can be clamped in place at a time, and repeated adjustment is not needed; besides technological lugs, the edges of the skin are net edges, and on-site allowance polishing is not needed; the assembly efficiency and the assembly quality can be greatly improved.

The invention relates to the field of metal molding, in particular to a high rib aluminum alloy wallboard manufacturing method. Firstly, upper and lower multipoint molds are adopted to oppositely press an aluminum alloy plane thick plate to mold a needed curved surface shape; and then, a high-speed milling method is used for milling a needed rib structure on the curved surface thick plate in a processing path parallel to the curved surface, so that a designed high rib aluminum alloy wallboard is obtained. The method applies the characteristic of quick and adjustable reconstruction of profile surfaces of the multipoint molds, uses one set of multipoint molds for molding double-curvature aluminum alloy thick plate parts with different geometric shapes, different thicknesses and different materials, and can control the rebound in molding of the aluminum alloy thick plate through multiple times of correction so as to improve the molding precision; and the high rib aluminum alloy wallboard manufacturing method can obtain high-precision high rib aluminum alloy wallboard parts without damaging fiber structures of the aluminum alloy plate materials, guarantees the strength requirements of the wallboard parts, solves the technical difficulties in large aircraft manufacturing, and can be popularized and applied to manufacturing of such other parts as spacecrafts and rockets.

The embodiment of the invention discloses a vortex generator for reducing resistance of a fuselage and delaying airflow separation, and relate to the technical field of rotor aircraft manufacturing. According to the vortex generator, the passive control for the flowing of a flow field near the fuselage can be realized when a rotor aircraft encounters strong cross-wind or carries out side flight, so that the resistance of the rotor aircraft is reduced, and meanwhile, the implementation cost and the failure rate are reduced. The vortex generator provided by the invention comprises an installation angle (2) of the vortex generator, a first corner (9) of a single-chip vortex generator and a second corner (20) of the single-chip vortex generator, wherein a value of the installation angle (2) ofthe vortex generator is larger than or equal to 10 degrees and less than or equal to 45 degrees; the second corner (20) of the single-chip vortex generator is an included angle between an upper surface (7) of the second section and a connecting section (19) of the vortex generator and the object surface; a value of the first corner (9) of the single-chip vortex generator is less than 30 degrees;and a value of the second corner (20) is larger than or equal to 40 degrees and less than or equal to 60 degrees. The vortex generator is suitable for the passive control for the flow of the flow field near the fuselage when the rotor aircraft encounters the strong cross-wind or carries out side flight.

The invention relates to the technical field of aviation aircraft manufacturing, in particular to a skin roll-bending part sectional curvature analysis method. The method includes: treating digital-analog discrete grids of a skin roll-bending part, and rapidly obtaining a part datum plane by a part grid surface segmentation method; then, generating and automatically connecting part section segments so as to obtain a part section characteristic curve; finally, subjecting the section characteristic curve to curvature analysis so as to obtain curvature information of the roll-bending part. The skin roll-bending part sectional curvature analysis method has the advantages that the method is a rapid part curvature analysis method, can be convenient for development of independent programs and can achieve automatic computational analysis of part section information; workload of workers can be reduced, technology analysis efficiency can be improved greatly and errors caused by man-made faults can be decreased.

The invention belongs to the technical field of aircraft manufacturing, and relates to an inflation airship. The inflatable airship is characterized in that a plurality of buoyancy lift air bags are sequentially connected with an inflation and deflation control device and an air storage cabin through pipelines; and the inflation and deflation control device comprises a sealing valve and an air compression pump or a vacuum-pumping pump or a combination thereof. The inflation airship has the advantages that: the structure of the airship is simple, the flow direction of helium gas can be controlled by hands or electronic switching programs with convenient operation, the expansive helium gas transfers between the air storage cabin and the buoyancy lift air bags without external leakage, and the running cost is low. When the helium gas in the air storage cabin transfers to the buoyancy lift air bags through the sealing valve and the inflation and deflation control device, the volume of the air bags is increased, the buoyancy is increased, and the airship ascends; and otherwise, the helium gas in the buoyancy lift air bags transfers to the air storage cabin, the volume of the buoyancy lift air bags is reduced, the buoyancy is reduced, and the airship descends. The inflation airship also can be used in rural areas with poor road conditions, and when meeting barriers or swamps in the direction of forward motion, the inflation airship can bypass roadblocks through levitation and continue to land and go forward.