SiCf/SiC ceramic matrix composite is the key material of thermal structural component of turbine. Highly dense KD-II SiC fiber reinforced SiCf/SiC composite was fabricated by melt infiltration of silicon. The microstructure, mechanical properties, thermal properties and oxidation resistance under 1200℃ or above were studied. The porosity of meltinfiltrated SiCf/SiC is only 1.6%. The flexural strength of SiCf/SiC composite at room temperature and 1200℃ are (521±89) and (576±22)MPa, respectively. SiCf/SiC composite shows non-brittle failure characteristic. The thermal conductivities of thickness direction at room temperature and 1300℃ are 41.7W/(m · K) and 18.9W/(m · K). The flexural strength of meltinfiltrated SiCf/SiC composite oxidized for 1000h at 1200℃ is (360±54)MPa, which is only decreased by 19%. The meltinfiltrated SiCf/SiC composite possess excellent oxidation stability, which is promised to be used as thermal structural material in turbine energy.

      Due to the high specific strength and modulus, as well as excellent anti-fatigue and creep resistance properties in the high temperature, continuous SiC fibers reinforced titanium matrix composite (SiCf/Ti) has attracted extensive attention. In the paper, we overviewed the manufacture techniques in the fabrication processing of SiCf/Ti composites, including the SiC fiber and coating deposition technique, hot isostatic press (HIP) consolidation technique and component manufacturing. Besides, our study and progress carried out in this area in recent years were summarized. We successfully can make a small bath trial for SiC fiber and also prepare SiCf/Ti composite with brilliant property. In addition, the interfacial reaction investigation in different matrix system consists of Ti alloy, Ti-Al, Al alloy have been performed. The experiments showed that the interface of SiCf/Ti composites can be retained intact with the help of protective coating (C coating) under heat treatment at 1100 ℃ /10h. Moreover, SiC fiber precursor wires of titanium alloy, aluminum alloy, and nickel-based super alloy have been explored through physical vapor deposition technique (PVD), respectively. The most important is that we had a successful tempt to fabricate ring-like component with the size of Ф600mm×160mm at 1∶1 ratio and roll shaft with the size of Ф50mm×300mm were fabricated successfully.

      The curing reaction kinetic parameters of CF832/T700 ultra-thin carbon fiber prepreg/epoxy resin systems were studied through DSC tests. The influence laws of pre-absorbing process parameters and curing process parameters on the mechanical properties of ultra-thin carbon fiber composite laminates were investigated by orthogonal tests. The most suitable adhesive film was determined by using three different adhesive films of EA9696NW, LWF–2B and FM73M to co-cure the ultra-thin prepreg laminates and Nomex honeycomb. The results show that the curing reaction activation energy of CF832/T700 prepregs is 85.98kJ/mol, the curing reaction is a slow first-order reaction. The pre-curing temperature, curing temperature and post-curing temperature are 115℃ , 135℃ and 171℃ , respectively. The bending and stretching experiments were carried out with the orthogonal analysis, the best pre-absorbing and curing process parameters are obtained, including pre-absorbing temperature 60℃ , pre-absorbing pressure magnitude 0.3MPa and pre-absorbing time 10min. The best curing parameters of curing temperature, curing pressure and curing time are 130℃, 0.4MPa and 2.5h. The EA9696NW adhesive film presents the best co-curing performance.

      Porosity is one of the most unavoidable defects in composite part which has significant impact on structural strength. The sandwich structural composite parts were manufactured by vacuum bag-autoclave co-curing method. Porosity of sandwich composite part laminated area with variable thickness was studied by adjusting compaction parameters including compaction vacuum, compaction time and ancillary material types. Results show that improving compaction vacuum, extending compaction time appropriately and using perforated release film A4000RP3 and breather Style PC3 can reduce the porosity of composite part variable thickness area.

      Aiming to resolve the technical matters such as uneven pressure on products, pits on the panel, improvement of the inner quality, based on the analysis of co-curing method, the T shape stiffened panels were researched in this paper. The match condition, process parameters and orientation of the stringer are analyzed and optimized. The fabrication process of T shape stiffened panels and technical details are improved. The results show that the test product quality is excellent, the product inner is compact, the surface is smooth and the stringer axis is accurate.

      The carbon fiber laminates are fabricated by wet compression molding method. We have designed two molding parameters of infiltration time and curing pressure to fabricate the laminates. The micro appearance of the laminates’ section was observed by metalloscope. The molding qualities of laminates were represented, which include the thickness, fiber volume content, ILSS, compression and tensile strength. Results show that the laminates have good quality with the infiltration time being 4 minutes and the curing pressure being 1MPa, there are few defects in the section, and the mechanical properties have relatively improved by 5%–11.45% compared with others; with the increase of infiltration time, the mechanical properties showed a rapid and then slow trend; with the increase of curing pressure, the fiber volume content and tensile modulus of laminates showed an increasing trend. The fiber volume content and tensile modulus have the largest value 66.12% and 86.50GPa respectively, when the infiltration time is 10 minutes and the curing pressure is 1.5MPa.

      In order to improve the fitting accuracy of the stiffened skin profile, an adaptive fitting method based on the self-adaptive mould was proposed. The rubber was treated as the fitting surface. It was vulcanized and its surface was formed with that of the cured composite skin. Then, the rubber was attached to the steel mould to form an adaptive mould. The results showed that the cooperated clearance and interference were eliminated by the adaptive fitting of the unvulcanized rubber. There were no negative effects on the mechanical properties of composites, and the mechanical properties of the rubber could satisfy the requirement of adaptive fitting. What’s more, the effect of the method on the properties of composites was evaluated.

      PAN-based carbon fibers and composites have become the ideal materials for aviation application, and structure dosage and application locations are the important symbols of aircraft. Development status of domestic PANbased carbon fiber was summarized. Main problems of domestic PAN-based carbon fiber were pointed out from eight aspects, including industry distribution, product quality, supporting equipment, industry chain, etc. Then, the key problems during aviation evaluation and application were discussed. At last, development suggestion was presented in order to promote sustainable development of domestic PAN-based carbon fiber.

      The excellent mechanical properties, wide usage temperature range and secondary processing possibility make continuous fiber reinforced thermoplastic prepreg develop rapidly. The hot-melt method is an accurate and efficient thermoplastic prepreg molding method. It is an engineering problem that needs to be solved that how to achieve the uniform and full impregnation of continuous fiber bundles with high viscous resin melts, such as PPS, PEEK and so on. Firstly, based on Darcy’s law, four impregnation theoretical models were proposed, which fully consider the effects of process temperature, pressure, processing stage and shape of fiber bundles on impregnation, and they can provide theoretical guidance for the establishment of continuous fiber reinforced thermoplastic prepreg production lines and the determination of process parameters. Then the research and industrialization status of domestic and foreign continuous fiber reinforced thermoplastic prepreg are compared: foreign related industries have a wide range of prepregs, which have been widely used in military aircraft, civil aircraft and other fields, but foreign company have a strict purchase policy for China. Domestic demand for continuous fiber reinforced high performance thermoplastic prepreg is in short supply. Beihang thermoplastics group has independently developed a continuous fiber reinforced high performance thermoplastic prepreg production line via hot melting method, which has eased domestic urgency to some extent.

      The chopped fiber reinforced thermosetting polyimide composites (C–T700/HT–350RTM) were produced through molding process, and the chopped T700 carbon fiber (C–T700) were chosen as reinforcing material, the HT–350RTM polyimide were chosen as resin matrix. The influences of changing carbon fiber volume fraction on the coefficient of linear expansion and mechanical properties of C–T700/HT–350RTM composites were investigated. The experimental results showed that the coefficient of linear expansion of C–T700/HT–350RTM composites decreased with the chopped fiber volume fraction increased, and the tensile modulus, compression modulus, flexural modulus increased with increasing chopped fiber volume fraction, while the tensile strength and flexural strength first increased and then decreased, the compressive strength has slowly increased with the increasing of chopped fiber volume fraction.

      As its high quality, high efficiency, high molding adaptability and low scrap rate, automatic fiber placement process is especially suitable for the automatic manufacture of large complex composite components, such as fuselage, inlet, bearing cone, blended wing body. In this paper, the developments of automated fiber placement equipment were reviewed, from the perspective of lathe bed, tow storage box, placement head. Moreover, research and application status of automated fiber placement equipment in China was analyzed. Finally, the future of placement equipment was predicted.

      Advanced composite material has been widely used in aviation industry because of good performances. As manual forming prevails in China’s composite manufacturing, study of automatic manufacturing on large-sized stiffened panel has significant importance in promoting China’s composite manufacturing industry. This paper focuses on the study of manufacturing of center-wing-box lower panel of an aircraft, verifies automatic manufacturing flow with combination of automated tape layup, hot drape forming, automatic turn-over, which provides a foundation for establishment of future composite automatic manufacturing line.

      The bearing-less composite tail rotor is one of the most important components of helicopters, and their manufacturing quality directly affects their service life, but the traditional handmade manufacturing technology is far from meeting the current requirements. This paper studies the exiting automatic manufacturing technology of composite tail rotors, and in the forming process of the flexible beam of the tail rotor, the self heating and self pressurization molding system is used to determine the time of the pressure according to the viscosity of the resin, and the perfect manufacturing of the flexible beam of tail rotor blade is realized. The stability of the tail rotor blade manufacturing is ensuring by using automatic heating and boring process in assembling, and the qualification rate of the product is greatly improved. At the same time, combined with the current situation, the development direction of tail rotor blade manufacturing technology is briefly described.