11 results about "Composite propeller" patented technology

The rigid-flexible composite propeller hub connecting device for the variable pitch propeller comprises a propeller hub and a propeller root assembly, and is characterized in that a flexible connecting assembly is arranged at the connecting interface of the propeller hub and the propeller root assembly. The assembly is composed of rigid inner and outer ring bushings and a rubber elastomer embedded between the rigid inner and outer ring bushings. The inner ring lining is in close contact with the propeller root, and the outer ring lining is in interference fit with the propeller hub. By means of the rigid-flexible composite structure, reliable and accurate transmission of torque and centrifugal force is ensured, meanwhile, vibration energy generated by working of the propeller is effectively absorbed and dissipated through the high-damping rubber material, and therefore a vibration transmission path is remarkably blocked, the excellent vibration and noise reduction effect is achieved, and the working stability and reliability of a system are improved; and the service life of the propeller is prolonged. The variable-pitch propeller is compact in structure, convenient to assemble and maintain and easy to integrate into an existing variable-pitch propeller structure.

The application provides a device and method for fine measurement of a composite propeller blade deformation field. The device comprises an adjustable height horizontal control console, a horizontal plate, a blade loading point fixing device, a plurality of adjustable length displacement calibration probes, an electronic vernier caliper and a base device, and the like. The measurement method provided by the application realizes fine measurement of the blade deformation field of a composite propeller, can accurately, stably, efficiently and at low cost measure the small deformation amplitude of the composite propeller, thereby providing accurate test data support for simulation calculation, and can be applied to deformation measurement of composite propellers of different types and different scales.

The application discloses a self-calibration strain testing system and method for propeller composite materials, and solves the problems of high-precision measurement and real-time calibration of dynamic strain under a complex flow field environment. The system core comprises a linear fiber grating sensor array attached to the surface of the propeller blade and a fiber demodulator integrated in the propeller hub. The sensors are arranged symmetrically along the span, and two infrared transmitting / receiving devices in each pair intersect at the center O of the hub to form a global reference when positioned accurately. A single sensor is installed through a double-shaft flexible hinge and integrated with a shape memory alloy (SMA) wire driving mechanism, which can realize independent micro-motion calibration in the span direction and the chord direction according to the offset of the infrared intersection. The sensor is provided with an internal failure alarm, which is filled with gallium-indium-tin alloy through hollow glass microbeads. The alarm is triggered only when >= 3 microbeads are broken to form a conductive path, thereby avoiding false alarms. The anti-electromagnetic interference module solves the problem of dynamic strain monitoring of the large-deformation composite propeller under high pressure, low temperature and strong electromagnetic environment.

This invention relates to the field of composite material propeller blade molding technology, and discloses a large-size composite material propeller blade molding mold, comprising: a blade, a base mold, and a connecting section assembly mold. The base mold is located below the blade, and one side of the base mold has a product film-coating surface. The connecting section assembly mold is located above the base mold, and includes a top mold, a side wall mold below the top mold, and a fastening mold on the side of the side wall mold away from the top mold. This invention, through the combination of a base mold, a connecting section assembly mold, and a prepreg vacuum bag compression molding process, produces large-size composite material propeller blades with low cost, high quality, and high performance. The product has a compact structure, low porosity, high fiber straightness, and excellent performance. It also has the advantages of a clear and simple production process, low equipment requirements, convenient and quick mold operation, and strong feasibility.

The application belongs to the technical field of composite propeller analysis, and particularly relates to a composite propeller excitation characteristic test method based on finite element optimization. The method comprises the following steps: based on the propeller type value, completing the parametric expression of the propeller and the finite element grid processing; simulating and calculating the propeller excitation characteristic to generate the excitation configuration parameters required for actual measurement; selecting the propeller simulation excitation point according to the propeller simulation mode and the excitation characteristic obtained in steps A and B; establishing a data acquisition system for measuring the excitation response signal; based on the data acquisition system and the excitation configuration parameters, performing the excitation test to obtain the excitation response signal of all the excitation points; the application is convenient for quickly generating and optimizing the test configuration scheme, and then the inherent vibration characteristic of the propeller is measured by using the excitation device, so that the excitation characteristic is determined, thereby laying a foundation for the production and development of a low-noise pre-deformation composite propeller.

The invention discloses an integral type composite material propeller torque testing device which comprises a bottom plate, a first side plate and a second side plate are fixedly connected to the two sides of the bottom plate respectively, a rotating torque shaft is installed between the first side plate and the second side plate, a plurality of check blocks are fixedly connected to the inner side of the second side plate, and the check blocks are matched with blades of a propeller; the force arm connecting rod is provided with a force loading rod, the force loading rod is axially perpendicular to the force arm connecting rod, the two ends of the force arm connecting rod are both connected with torque loading arms, and the ends, away from the force arm connecting rod, of the two torque loading arms are assembled with the two ends, extending out of the first side plate and the second side plate, of the rotating torque shaft correspondingly. And the two torque loading arms are respectively positioned on the outer sides of the two side plates. The integral type composite material propeller torque testing device is simple in structure, greatly saves equipment, labor and time cost, and solves the problem that a loading device cannot simulate stress of blades in water due to mutual shielding of the blades of an integral type propeller.

The application discloses a small composite propeller and a preparation method thereof. The small composite propeller comprises a metal part and a composite part. The metal part is an inner ring part of a hub. The composite part is an integral structure, comprising an outer ring part of the hub and all blades. The outer wall of the metal part is provided with a plurality of protrusions or grooves for forming an interlocking connection with the composite part. The composite part is integrally injection molded by embedding the metal part into an injection mold. Based on the interface characteristics of the composite part and the metal part, the connection structure is innovatively designed. The integral design of the circumferential structure of the composite part ensures the strength reliability of the connection between the metal part and the composite part. The manufacturing is completed by integral injection molding, which is high in manufacturing efficiency, low in manufacturing cost, and short in single-piece manufacturing period (within 8 minutes). The manufacturing cost advantage is more obvious in the case of large batch molding demand.

The application belongs to the technical field of robots, and discloses an amphibious robot propulsion device and method based on a wheel-propeller composite structure. The device is integrated with a reduction motor driving system of a wheel mechanism and a composite propeller system of a propeller mechanism, and outputs propulsion power in the same coaxial direction. The reduction motor driving system takes a waterproof reduction motor as a driver to provide power for the amphibious robot when walking on the ground. The composite propeller system takes a propeller as a driving component to provide power for the amphibious robot when floating in water. The application can interact with other structures to form vector propulsion, increase controllability and stability of the robot, and quickly switch between water and land modes. The switching structure is simple. Most amphibious robot water-land switching structures are too complex, which causes great pressure on the body space and reduces the practicability of the product.

The invention relates to a design method of a blade middle surface layer-propeller hub integrated metal embedded composite material propeller, which comprises the following steps: constructing a blade middle surface layer-propeller hub integrated metal embedded composite material propeller integral structure, the structure comprises an integrated high-rigidity area made of metal and a carbon fiber composite material layer wrapping the integrated high-rigidity area. The propeller is divided into a limited number of areas with similar shapes in the radial direction, and the areas are segmented and discretized into fiber metal laminated variable cross-section beams with similar limited section widths; based on a classic laminated plate theory and metal plastic mechanics, acquiring a stiffness parameter of the fiber metal laminated variable cross-section beam through a multi-scale hybrid analysis method; a series spring model is adopted, the variable cross-section beams in the similar areas of the same shape are connected in series and stacked, and then stacking results of all the areas are combined to obtain the overall effective rigidity of the propeller; and according to the overall effective rigidity result, the laying sequence and interlayer ratio of the metal layers and the composite material layers are designed.

The invention discloses a composite material propeller blade structure and a manufacturing method thereof. The composite material propeller blade structure comprises a supporting pipe; the girder layer comprises a middle girder, a front edge girder and a rear edge girder; the skin layer comprises a first skin, a second skin and a third skin; the threaded sleeve is arranged on the outer side of the first skin, and external threads are arranged on the outer side of the threaded sleeve; the cloth liner layer is arranged on the outer side of the first skin; and the metal pipe fitting is used for being connected with a propeller hub and is in threaded connection with the threaded sleeve. According to the invention, the blades made of the composite material are arranged and are cured to form a whole body, so that firm interface bonding is formed, loads are effectively transmitted, stress concentration is avoided, the propeller can be suitable for low-rotating-speed and large-load electric vertical take-off and landing aircrafts, and the structural weight is reduced and the reliability is improved while the connection reliability is ensured.

This application relates to an RTM mold structure for composite material propeller blades, including an upper mold, a lower mold, and a sealing strip. The upper mold has a protrusion protruding from the parting surface, and a first mold cavity matching the upper contour of the blade is formed on the inner side of the protrusion. The lower mold has a recessed portion recessed into the parting surface, and a second mold cavity matching the lower contour of the blade is formed on the inner side of the recess. After the lower mold and the upper mold are engaged along the parting surface, the first mold cavity and the second mold cavity are joined to form a complete mold cavity for molding the propeller blade. The sealing strip is disposed on the contact side of the recessed portion and the protrusion. The upper mold is a protrusion protruding from the parting surface, and the lower mold is a recessed portion recessed into the parting surface. The lower mold aligns with the upper mold to form a circumferential limit. Compared with the traditional guide post and guide sleeve positioning method, the positioning accuracy is greatly improved, effectively preventing the relative displacement of the upper and lower molds during pressurization and heating, and ensuring the accuracy of the blade shape. At the same time, the sealing strip is disposed on the contact side of the recessed portion and the protrusion, replacing the traditional parting surface sealing structure, resulting in a more stable sealing effect.