Nanjing University of Aeronautics and Astronautics

Congze Fan

Kai Liu

Zhongde Shan

Wenzhe Song

Jinghua Zheng

Yiwei Chen

Yaxing Song

Jingxuan Wang

Hao Zhang

Linlin Luo

Yufeng Jin

Jiaxun Xu

Zhibo Li

A continuous fiber curing extrusion device based on additive manufacturing ceramic composites includes a main support frame. A top inner wall of the main support frame is simultaneously mounted with a first guide rail, a second guide rail, and a third guide rail. The first guide rail is parallel to the second guide rail, the second guide rail is perpendicular to the third guide rail, a ceramic flux extrusion gun is movably connected to the first guide rail, and a bottom end of the ceramic flux extrusion gun is provided with a segmentation mechanism. One end of the ceramic flux extrusion gun is connected to a ceramic flux storage bin through a first connecting pipe, and a first fiber flux extrusion gun and a second fiber flux extrusion gun are movably connected to the second guide rail and the third guide rail respectively.

Continuous fiber curing extrusion device based on additive manufacturing ceramic composites

A continuous carbon fiber composite filament impregnation pretreatment device includes a conveying assembly. The conveying assembly is arranged on a pretreatment device frame. Adhesive layer spray assemblies are provided on left and right sides of the conveying assembly. A plurality of multi-angle cleaning assemblies is sequentially arranged at a front end of the pretreatment device frame. The device overcomes the defects in the impregnation of a continuous fiber reinforced composite filament by pre-treating the surface of the filament and then spraying a thermoplastic adhesive layer onto the fiber surface during the fiber spreading process before impregnation treatment.

Continuous carbon fiber composite filament impregnation pretreatment device

A high-temperature vibration modal testing device for variable cross-section carbon fiber resin-based composites includes triangular serrated sliding rails, high-temperature steel sliding bayonets, sliding furnace door, water-cooled conduits, dual-axis sliding rail, insulation box, infrared radiation heating array, thin armored thermocouples, observation port, tapping threaded rod, tapping threaded fixture, ceramic force transmission rod, excitation source, laser vibration measurer, vibration measuring port, mechanical pump, and exhaust valve. A variable cross-section carbon fiber resin-based composite test piece is fixed to the high-temperature steel sliding bayonets and fixed to the tapping threaded fixture by the dual-axis sliding rail. During high-temperature vibration modal testing, the infrared radiation heating array provides a high-temperature thermal environment, the excitation source connected to the tapping threaded fixture provides random vibration, and thermal model measurement is performed through the laser vibration measurer. The device can perform high-temperature vibration modal testing on variable cross-section carbon fiber resin-based composites in aerospace flight environments.

High-temperature vibration modal testing device for variable cross-section carbon fiber resin-based composites

A multi-arm forming device for space on-orbit composite braiding is provided. Through the rotary movement of a combination of circularly arranged mechanical arm-type laying apparatuses relative to a mold, a plurality of hot press laying heads are controlled together to implement high-efficiency and high-freedom winding and braiding formation of a composite member. The retraction and expansion deformation of the gasbag mold is achieved by inflating and deflating based on design, and the overall device is lightened by switching its structural volume in an operating/non-operating state, thereby achieving the purpose of facilitating the lift-off of rockets and the demolding, repair and weight reduction of winding and braiding structural members for operation in space. Additionally, gas in a gasbag can be used as emergency kinetic energy for the movement and attitude adjustment of the overall device in space. High-quality and efficient winding and braiding formation of composites in space are achieved ultimately.

Multi-arm forming device for space on-orbit composite braiding

An on-orbit composite filament forming device for space 3D printing includes a constant tension unwinding module, a replaceable resin filament rotary wrapping module, a melt preheating chamber, a curved channel impregnation chamber, a variable aperture resin recovery device, a heat protective housing, a convective cooling device, a traction device, and a winding device. The replaceable resin filament rotary wrapping module wraps a resin filament on a surface of a carbon fiber by circumferential rotation and is provided with an active unwinding reel placed on a circular rail centered on the carbon fiber; the melt preheating chamber is used for melting resin to wrap the surface of the fiber, and is equipped with a lifting device for automatic opening and closing; the curved channel impregnation chamber is formed with a wedge-shaped high-pressure impregnation zone by mutual extrusion of upper and lower pressure blocks, thereby improving the quality of fiber impregnation.

On-orbit composite filament forming device for space 3D printing

A path planning method based on dynamic contour offset discretization and for spatial curved-surface printing is provided. Firstly, transversal equal slicing is carried out on a target model, and single/double contours are labeled; secondly, central slicing is carried out on the model, curvature contours are discretized, feature values of contour offsets of slice layers are calculated on the basis of a surface contour curvature of the model, and dynamic offset filling for inner contours of horizontal slices is realized; then longitudinal equal slicing is carried out on the slices, and spatial discrete points of the target model are obtained; and finally, virtual double contours are constructed for the single contours, and labeling processing for the discrete points is carried out, so that a discretized three-dimensional spatial equidistant lattice of the target model is obtained.

Path planning method based on dynamic contour offset discretization and for spatial curved-surface printing

A hot bed deformation tolerance structure for a large-sized continuous fiber high-temperature 3D printer is provided. Size changes caused by thermal expansion of a hot bed are compensated through motion coordination of a secured hot bed support assembly and a motion device, especially for an aluminum alloy material. A Z-direction motion structure of this structure is fixedly mounted with a frame and works at room temperature. A compensation motion module is fixedly mounted with a Z axis and incompletely secured with the hot bed support assembly, and works at room temperature with the Z axis. The hot bed support assembly is incompletely secured and partially in a high-temperature chamber, with a maximum working temperature of 300° C. The hot bed support assembly retains motion redundancy in a direction of thermal expansion deformation, tolerates thermal deformation through a linear motion module, and compensates for metal deformation through horizontal motion coordination.

Hot bed deformation tolerance structure for large-sized continuous fiber high-temperature 3D printer

A wire feeding mechanism suitable for fused deposition Additive Manufacturing (AM) of a flexible wire is provided, which includes a support housing. A melting nozzle is arranged at the lower end of the support housing, a hook is connected to the inner wall of the top end of the support housing, a connecting rod is connected to the inner wall of one side of the support housing, a wire drawing mechanism is connected to one end of the connecting rod, the wire drawing mechanism is located at the lower end of the hook, a limiting mechanism and a wire guide mechanism are connected to the inner wall of one side of the support housing, the limiting mechanism is located at the lower end of the wire drawing mechanism, the wire guide mechanism is located at the lower end of the limiting mechanism.

Wire feeding mechanism suitable for fused deposition Additive Manufacturing (AM) of flexible wire

An additive manufacturing device for an aerospace truss includes a raw material input unit, a longitudinal beam forming unit, a longitudinal beam traction unit, a cross beam forming unit and a truss support unit. The raw material input unit stores pre-impregnated wires and pre-impregnated tapes, and a motor drives rollers to convey the pre-impregnated wires and the pre-impregnated tapes forward; the longitudinal beam forming unit is composed of three sets of forming molds, and the pre-impregnated tapes form V-shaped longitudinal beams through heating molds; a stepper motor used in the longitudinal beam traction unit drives three sets of roller traction devices through steering gears to pull formed longitudinal beams; the cross beam forming unit is composed of a motion module and a printing module, and a truss cross beam is printed through aD printing method of molten deposition.

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Nanjing, China

Congze Fan