49results about How to "Reduce the number of tools" patented technology

The invention relates to an incremental sheet metal stirring composite forming device and method. The forming device comprises an incremental stirring forming tool head, a reverse roof pressure head, a spindle motor, a main drive unit, an auxiliary drive unit and a sheet metal fixture. The forming method includes: generating an incremental forming track according to a three-dimensional model of a machining part to be machined to serve as a synchronous movement track of the main drive unit and the auxiliary drive unit; controlling the spindle motor to rotate, allowing the incremental stirring forming tool head to be driven to rotate by the spindle motor to be inserted in the interior of a sheet metal to be machined, and the reverse roof pressure head and the incremental stirring forming tool head pressing the sheet metal; respectively controlling the incremental stirring forming tool head and the reverse roof pressure head to move synchronously according to the synchronous movement track to complete incremental sheet metal stirring composite forming. Compared with the prior art, the incremental sheet metal stirring composite forming device and method has the advantages that functionally graded materials can be integrated in welding and forming, the manufacturing process is shortened, the number of tools is reduced, and the problem that traditional functionally graded materials are poor in extension and cannot be formed can be avoided as well.

The invention discloses a floating and overturning type motor pressing assembling trolley which comprises an overturning mechanism and a trolley body. The overturning mechanism is fixedly arranged onthe trolley body and is used for assembling a gearbox body to the trolley body so that the pressing assembling action of a motor in the gearbox body can be conducted conveniently. The overturning mechanism comprises a positioning plate and a fixing plate, the fixing plate and the trolley body are fixedly connected, the positioning plate and the fixing plate are connected in a floating manner, andthe positioning plate can overturn at will in six freedom degrees relative to the fixing plate.

The invention discloses a flexible fixture with self-adaptive support and multi-point pressing, which comprises a fixture base and a first self-adaptive clamping device, a second self-adaptive clamping device, an self-adaptive support device and a fixture arranged on the fixture base. Supporting boss; the first self-adaptive clamping device and the second self-adaptive clamping device are respectively slidably connected to the clamp base, and the two ends of the first self-adaptive clamping device and the second self-adaptive clamping device are respectively connected to the The part A surface and the part B surface are pressed tightly; the self-adaptive support device is attached to the part C surface; the opening slot of the part is inserted into the fixture support boss, and the main positioning sleeve of the part is inserted into the part positioning hole, the fixture support boss and is connected with the press Tighten bolted connections. The invention designs multiple clamping points, and the clamping force can be evenly distributed on the parts, so that the rigidity of the parts during processing is well guaranteed, the machining accuracy and surface quality of the parts are guaranteed, the process flow and production preparation time are shortened, and the Improve processing quality and production efficiency.

An integral co-curing molding method for an unmanned aerial vehicle wing belongs to the field of aviation composite material molding. The method steps are: step 1: assembling the wing frame; step 2: assembling the lower mold; step 3: making the lower wing surface skin of the wing in the assembled lower mold mold, and reserving the upper wing surface skin when paving step 4: positioning the wing frame; step 5: making the upper wing surface skin; step 6: assembling the upper mold; step 7: curing and demoulding. The wing prepared by the method of the present invention can be molded at one time, which improves the strength, saves the cost, and improves the manufacturing speed.

The invention discloses a tenon root and front and rear edge machining clamp of a precisely-forged blade. The tenon root and front and rear edge machining clamp is composed of a pouring box, a supporting arm, a pressing plate and a rotary table. The blade is located in a cavity of the pouring box through assembly of the pouring box and the blade. The molded surface of a blade body is clamped through low-melting-point alloy solidification, and the clamp is prevented from generating clamping injuries to the molded surface of the blade body. The pouring box is pressed and fixed through the pressing plate, pressing force is evenly transmitted to the pouring box through the pressing plate, the pouring box is pressed, and clamping deformation of the blade cannot be caused. To-be-machined parts of a tenon root and front and rear edges of the blade are located outside the pouring box, and numerical control machining of the tenon root and the front and rear edges of the blade is completed through one-time clamping. According to the clamp, clamping errors and the number of tools are reduced, meanwhile, the machining technological process of the precisely-forged blade is optimized, and the machining precision and machining efficiency of the precisely-forged blade are improved. The clamp is suitable for efficient and batched numerical control machining of aero-engine precisely-forged blades and can also be used for machining of tenon roots and front and rear edges of rolled blades and other precisely-formed blades.

The invention belongs to the technical field of motor block-type stator manufacturing technology, and discloses a block-shaped stator forming method under full-size control, a block stator and a motor. The inner circle, outer circle and groove shape of the sheet iron core are positioned, and then the punching sheet is pressed and compacted by tightening the screws on the tool, and then the V-shaped buckle is used to crimp the iron core into a whole; then install the stator iron core After the skeleton is completed, the winding is carried out. After the winding is completed, the tooling is used again for full positioning, and then laser welding is used to weld into a full-circle stator. According to the invention, the four parts of the mandrel and the inner circle of the stator iron core, the slot positioning rod and the stator slot, the toothed positioning rod and the outer circle fixing hoop cooperate with each other and the stator iron core. size control. The invention saves the number of tooling, facilitates switching of the tooling, enables reliable forming of the stator iron core and can maintain the size of each part of the stator iron core.

The application belongs to the field of aircraft structure design, and in particular relates to an integral frame structure of an aircraft front fuselage. To solve the negative impact of the traditional aircraft front fuselage structure, multiple longitudinal girders, transverse reinforcement frames, and longitudinal plates of the overall frame structure of the aircraft front fuselage in the present application are integrally formed, and the surface of the longitudinal girder facing the outside of the aircraft Conformal with the surface of the transverse reinforcement frame facing the outside of the aircraft, the surface of the longitudinal plate and the surface of the longitudinal girder facing the outside of the aircraft, the surface of the longitudinal plate and the surface of the transverse reinforcement frame facing the outside of the aircraft are in the same shape; Significantly reduce structural weight, reduce fatigue weak links, reduce the number of structural parts, standard parts, and tooling, and shorten the manufacturing cycle.

The invention discloses a bidirectional location thin-walled workpiece welding clamp. The bidirectional location thin-walled workpiece welding clamp comprises a body base, a clamping plate, overturnable locating blocks, small shafts, gaskets, push pins, expansion blocks, guide plates, stop pins, a conical body, a cover plate, a mandrel, a nut, a ventilation pipe, a locating plug, springs I, split pins, bolts I, springs II, screws I, screws II, bolts II and screws III. By means of the bidirectional location thin-walled workpiece welding clamp, location clearance can be effectively eliminated, welding deformation can be resisted, and a welding seam zone is prevented from metal oxidation; and due to the fact that a locating face can be overturned, a support ring can be welded to a tool, and the number of tools and tool replacement time are reduced. When the bidirectional location thin-walled workpiece welding clamp is used practically, the problems that welding deformation of the support ring is large, and dimensions and angles are out of tolerance are solved; tool cost is saved; labor intensity is lowered; the qualification rate of products is increased; and production efficiency is improved.

The invention relates to a rear anti-collision beam assembly suitable for multiple automobiles. The rear anti-collision beam assembly comprises an exterior board and installation supports. A square auxiliary hole is formed in one end of the exterior board, a first lap joint surface is arranged close to the edge of the square auxiliary hole, and the structure of the other end of the exterior board is the same as that of one end of the exterior board. Each installation support is of an open square box shape, and folded edges are arranged on the four sides of each opening portion and distributed symmetrical about the center of the opening portion, wherein the two laterally-symmetrical folded edges are spaced into three second lap joint surfaces through two reinforcing ribs, the two sides of the two vertically-symmetrical folded edges are provided with small planes connected with the left side wall and the right side wall of the square box shape, multiple installation holes are formed in the bottom of the square box shape, and the installation supports are correspondingly connected with the first lap joint surface at the edge of the square auxiliary hole in the exterior board. The left installation support and the right installation support can be interchanged and used, the positions of the installation supports can be adjusted, the installation supports are matched with different automobile types by changing the distance between installation points, and universality is high.

The invention discloses a rectifying blade body end face position measuring device and method, and the device comprises a first positioning V-shaped block and a second positioning V-shaped block whichare respectively used for positioning an upper shaft neck and a lower shaft neck of a rectifying blade, and also comprises a positioning unit; an upper shaft neck side blade body end face limiting block and a lower shaft neck side blade body end face limiting block are arranged on the outer side of the first positioning V-shaped block and the outer side of the second positioning V-shaped block respectively and connected with a first gauge stand and a second gauge stand respectively in a matched mode; the upper sides of the first gauge stand and the second gauge stand are respectively connected with dial gauges used for measuring an upper shaft neck side blade body end face and a lower shaft neck side blade body end face, an upper shaft neck side blade body end face gauge checking member and a lower shaft neck side blade body end face gauge checking member are arranged between the upper shaft neck side blade body end face limiting block and the lower shaft neck side blade body end facelimiting block.