Abstract:High-performance thermosetting resins are the important material for aerospace,traffic and microelectronic
field etc. The research on high-performance thermosetting resins,such as bismaleimide resin,polyimide resin,
cyanate ester resin,phthalonitrile resin,polytriazole resin and organic/ inorganic hybrid resins,and their applications
are discussed in terms of their advantages and features,difficulties and key technologies to be solved,and future development
trends and directions.

Abstract:In this paper, firstly, a brief introduction of UHTCs is made and then progresses of several preparation
processes such as PIP, RMI, CVI, and SI are discussed.

Abstract:The significance of electromagnetic interference (EMI) shielding material was explained. The properties
and characters of the electromagnetic interference shielding material such as the style of surface layer,filling, intrinsic
conductive polymer, conductive fabric and transparent conductive film were reviewed. The trend of research
and development of the EMI shielding material is introduced.

Abstract:The effect of autofrattage on stress distribution and fatigue life of composite overwrapped pressure vessels(COPV) was studied by using the numerical simulation. The finite element model of COPV was established based on the commercial software ANSYS. The variations of the thickness and winding angles of the composites along the meridian in the domes section are considered during the modeling. The influence of autofrettage pressure of 54 MPa on the stress of metallic liner and composite layers is analyzed. The fatigue life of the COPV is predicated by using Coffin-Manson formula. The results demonstrated that the diversity between the result of finite element analysis and the experiments
is within 8%,which indicated the finite element model and the analysis is reasonable

Abstract:The finite element software was used to get the X-Cor sandwich’ s stress fields and its compressive
strength was also analysed. During the compressive strength analysis, the failure criterion and materials stiffness degradation
rules fitting for the analysis of the X-Cor sandwich’s failure mechanism were proposed and the X-Cor sandwich’s
failure process and modes were also clarified. According to the failure criterion we used the elements with stiffness
degradation and their distributions in the finite element model to simulate the types and propagation path of the
failure and the failure mechanisms of the X-Cor sandwich under compression were explained. The finite element analysis
indicates that during the compression firstly the resin regions fail and secondly the Z-pins fail. The main failure
mode is the Z-pin’s elastic buckling failure and the propagation paths of the failure elements are dispersive. By contrasting
the finite element results and experiments the values are consistent well and the error range is -7． 6% to
9． 5%

Abstract:Based on the viscosity study of resin for VARTM,the manufacturing of testing laminates,and the resin
flow simulation of composite container with PAM-RTM,the optimized injection pattern and process parameters were
determined. The composite container was manufactured to verify the validity and feasibility of the VARTM technique
for the composite container.

Abstract:As the head of an aircraft, the blunted cone-flare undergoes thermal load, external pressure in supersonic
flow, and the stability are most important issues in the structural design. In the paper, the stability of thinwalled
structure is researched. First, the correction factor of FEM simulation is 0. 8, which is obtained by comparing
the FEM critical load and the test-corrected theoretical solutions. Then, the thermo-stability of composite blunted
cone-flare under thermal load and external pressure is analyzed by combining FEM and test, and considering the material
mechanical characters under different temperatures.

Abstract:The micro-damage evolution of TiC particle reinforced titanium matrix composites was analyzed, and
a dynamic constitutive model with damage evolution was established. When TiC particle reinforced titanium matrix
composites withstands tensile loads, micro-cracks expand in form of wing cracks through the matrix. Based on the
wing crack growth model, a biaxial damage evolution constitutive was set up. And by degenerating, the uniaxial tension
damage evolution constitutive was gotten. It is assumed that microcrack nucleation law accords with Weibull distribution,
then a macroscopic and microscopic combined dynamic constitutive model in a one-dimensional stress state
was established, which can reflect the damage evolution of TiC particle reinforced titanium matrix composites. Model
simulation results agree well with the experimental curves.

Abstract:Digital technologies,including 3D processing model design,stacking simulation,prepreg NC cutting,
laser projection locating,were applied to large composite structure,which played on important role in solving processing
difficulties,decreasing the manufacture circle and cost,and improved the products quality.

Abstract:The processing,heat-resistance and mechanical properties of novel modified cyanate ester ware evaluated
in this article. The dielectric property and mechanical properties of cyanate ester matrix composite materials were
also studied. The results showed that the cyanate ester adapted to madding prepreg by hot-melt methods because of its
good process. All of the cyanate ester and composite materials had nice mechanical properties and could be used under
180℃. The composite materials are suitable for use as for high performance microwave-transparence materials and high
frequency circuit boards.

Abstract:A new type of glass fibers reinforced expoy prepreg was successfully prepared by heat-melt impregnation
method. The reactive and rheological properties were studied by the differential scanning calorimetry(DSC),visocity-
temperature curve,and the flame retardant mechanics was approached through thermo-gravimetry analysis technology.
The results shows that the reaction start at 129℃ and the storage at room temperature is more than 30 days.
The composite laminates made from the observed prepregs by autoclave process were further tested and the result show
that the composite has excellent mechanical and flame retardant properties.

Abstract:In this paper, multi-walled carbon nanotubes (MWNTs) were functionalized with PVP, and then the
PVP functionalized MWNTs ( PVP-MWNTs) / epoxy composites were prepared by the electron beam in-situ curing.
The PVP-MWNTs were characterized by IR spectroscopy and TGA. The results showed that the MWNTs were sucessfully
coated with PVP, and the PVP-MWNTs showed improved dispersion stablity in the epoxy resin. The tensile
modulus of the 0. 1 wt% PVP-MWNTs/ epoxy composites was enhanced by 25%. Dynamic mechanical analysis studies
also revealed that the addtion of PVP-MWNTs can improve the storage modulus of epoxy matrix.

Abstract:Composite panel/ aluminium sandwich structure was fabricated by the co-curing process. The effect of
processing pressure on the properties of composite panel was investigated to determine the co-curing pressure. The
properties of aluminium honeycomb with different dimension parameter and their sandwich structures were also tested
and analyzed. The results show that the processing pressure has little effect on the properties of thin composite panel.
The sandwich structure fabricated by the aluminium honeycomb of 0. 04 mm×4 mm has high specific strength and
modulus, and is easier to fabricate. Therefore, it has more widely potential applications.

Abstract:The processing technology of Von Karman Fairing Fabricated by PMI Foam Sandwich Structure was
investigated. The processing method was determined by the investigation on the properties of glass fiber reinforced
composite and foam structure, the thermoforming and splicing of foam, the processing of composite and sandwich
structure, and the nondestructive testing technology. The results show that the lognitudinal and transverse strength of
glass reinforced composite panel are respectively 602 MPa and 593 MPa. The lognitudinal and transverse modulus of
panel are respectively 26. 0 GPa and 27. 2 GPa. The lognitudinal and transverse edgewise compression strength of
foam sandwich structure with density of (110±10) kg/ m3 and thickness of 8mm are respectively 32. 9 MPa and 30. 5
MPa. The lognitudinal and transverse edgewise compression modulus of foam sandwich structure are respectively 2. 31
GPa and 2. 38 GPa. The mechanical properties of panel and foam sandwich can meet the design requirements. In addition,
the lest Von Karman Fairing fabricated with the PMI foam sandwich structure with glass fiber reinforced composite
panel by the step-cured processing can also meet the design requirement.

Abstract:The forming process and properties of carbon fiber reinforced composite pipe with the diameter of
10mm were investigated. The results show that the carbon fiber reinforced composite pipe fabricated by the thermal
shrinkage process has the advantages of simple forming process and better quality reliability. Compared to the stainless
steel pipe with the diamemer of 10 mm, the carbon fiber reinforced composite pipe with the same diameter has the equivalent
flexural stiffness. While the flexural strength of composite pipe is more than three times of the stainless steel
with the same diameter, and its weight is only half of the stainless steel pipe. In addition, the composite has good dimension
precision which can meet the design requirements.

Abstract:Structural damping of carbon fiber reinforced laminate composite is experimentally determined using a
cantilever beam test with an impulse excitation. Continuous carbon fiber reinforced laminates with different lamia orientation
were fabricated from MT300/603 and MT300/603A to investigate the effect of matrix properties and fiber orientation
on the damping of composite. The results show that the MT300/603A composite has a higher loss factor than
MT300/603. Fiber orientation has an important effect on the modal frequency and modal damping and the effect is
characteristic as changing structural flexibility. The 0° material exhibits a lighter damping loss factor than the other fiber
orientation.

Abstract:In order to solve the inherent defect of dry grinding in CFRP, a new adding liquid coolant in processing
CFRP was proposed. Dry grinding and liquid coolant grinding has been studied by means of experiment. The
results show that processing method of adding water solubility cooling fluid has no-effect on mechanical property of
CFRP, this method can not only improve machining efficiency but also reduce cut-tool wear, and is more suitable for
processing CFRP.

Abstract:To understand the properties of the fiber reinforced polyimide composite based on 2, 3, 3′, 4′-biphenyl-
tetracarboxcylic anhydride ( a-BPDA) at high temperature,composite samples were preparel using carbon fiber
and quartz fiber as reinforcement. The T5
d decomposition temperature and Tg of composites were 565℃ and 471℃.
The experimental results show that the retention of flexural strength,moduli and interlaminate strength of composites
are 42%,55%,44% at 450℃,respectively;after treated 50 hours at 400℃ in air the retention of flexural strength and
moduli of carbon fiber reinforced composites are 66% and 95%;and the coefficient transmit heat of quartz fiber reinforced
composites at 300℃,500℃ are 0. 503 and 0. 657W/ (m·K)

Abstract:The effect of mild-carbon steel and high-temperature alloy GH1131 on the microstructure of HIPed TC4
alloy was studied. The results show that mild-carbon steel die prevents the transfer of the stress for densification of TC4
during the process of HIP, different from the GH1131 die. When the die is designed,the deep cavity structure should
be avoided for the mild-carbon steel. Due to the interdiffusion of elements,the alloy surface is contaminated by both of
the die materials. Although the thickness of the boundary between TC4 and mild-carbon steel is slim,the alloy surface
is coarse with the wave-like morphology. And the thickness of the boundary between TC4 and GH1131 is raised to
more than 100 μm. In order to gain the clean and smooth material surface,the die cavity surface must be treated to
form a protect layer compatible with TC4.

Abstract:Curing behavior and processing of a novel BMI resin ( R801) for RTM were investigated. The mechanical
properties. Carbon fiber reinforced BMI composites were also studied. DSC results indicated that the curing
temperature of this resin ranged from 170℃ to 220℃. There is a low viscosity platform longer than 7 hours due to the
soft rise of the resin’s viscosity from 70 to 120℃ the viscosity-to-temperature curves. Sufficient processing time longer
than 10 hours is possible with the initial viscosity below 100 mPa·s at the temperature about 90℃. According to the
testing mechanical properties,excellent heat-resistant property could also be obtained for the composites using it as the
matrix,and mechanical properties retention is above 63% when tested at 300℃.

Abstract:A high-temperature resistant phthalonitrile resin R802 for RTM process was introduced in this paper. Its
viscosity dependence on temperatures and time, DSC data under different heating rates, flexural strength, shearing
strength and interface between the fiber and resin are investigated. According to the viscosity-to-times results,sufficient
processing time is possible become there is a low viscosity platform longer than 180 minutes at 140℃. DSC results indicated
the resin began to gel at 180℃,to cure at 203℃ and to handle for better properties at 256℃. From the mechanical
properties results, there was an obvious advancement of about 3.8% higher of R802/ MT300 flexural strength tested at
200℃ and 18% higher of shearing properties tested at 300℃ compared to the results at room temperature. The flexural
properties could maintain 41.1% and strength retention of shearing properties is up to 44% at 500℃. There is an excellent
interface between fiber and resin of R802/ MT300 composites.

Abstract:In this paper, the SiO2 -TiO2 / polyimide hybrid materials were prepared by using silicon and aluminum
sols obtained by sol-gel method. The mechanical properties,structure,and thermal properties of hybrid materials
were studied by means of SEM, DMTA, and TGA. The results show that the impact strength and flexural strength of
hybrid materials are all improved by adding inorganic particles, when the content of inorganic particles is 3%,the mechanical
properties are the best. The impact strength and flexural strength are 177% and 54. 6% higher than those of
pure resin, respectively. The thermal stability of hybrid materials is better than that of pure resin.

Abstract:Countering the flight character of astronautical flight vehicle, two experimental methods of load bearing
capacity were summarized, in order to obtain the structural load bearing capacity under different flight temperature
and different flight duration. It was able to express the high temperature load bearing capacity of the material in the
process of heat transfer, reducing the weight of structural heat resistance.

Abstract:Based on a typical multilayer insulating materials in vacuum environment of series experiment and anlytical
heat insulation performance,trend of multilayer insulation material layer temperature difference (Δt ) distribution
was anlytical and the multilayer insulation materials in different interlayer insulation performance characteristics
and their variation regularities was disdesed. The test results proved that multilayer insulation performance is superier
to the intermediate layer heat insulation performance. Inside 4 layers and outside 18 layers air flow approach the molecular
flow with better thermal insulating performance and big temperature difference(Δt ). The middle layer air flow
is unsteady,and the insulation performance slightly differenct,temperature difference(Δt ) near the heating plate side
is smaller, interpass temperature is less than the low temperature side.

Abstract:To meet the need of thermal protection ( ~1 500℃) for novel aerospace vehicles, ultra-high temperature
rigid thermal insulation materials had been fabricated and investigated. Using a high-resisting fiber and inorganic
binder,the insulation was produced through the process of vacuum-molding and firing the dried billet. The microstructure,
thermophysical and mechanical properties of the materials were characterized and measured. The results
showed that the fibers were bonded effectively;the properties could be tailored by adjusting the ratio of fiber to binder;
the thermal conductivity at room temperature and mechanical properties varied linearly with density. The insulation materials
had a shrinkage of less than 2% after heating at 1 500℃ for 1 h,a low density in the range of 0. 3 to 0. 5 g/
cm3, thermal conductivity of 0. 06 to 0. 09 W/ (m·K), and compressive strength of 0. 6 to 1. 2 MPa.

Abstract:A engineering method is used to simulate low oxygen and high temperature environment during altitude
flight of aerocraft by inert gases all around, in which the propellant-thruster sleeve made of composite material
actually works. Concretely, there are two experiment methods, loading the force and heat orderly, and loading the
force and heat at the same time. The analysis result of experiment data indicates these experiments are able to examine
mechanics capacity and high temperate performance of the propellant-thruster sleeve, not by actually starting up of the
engine in altitude flight simulation.

Abstract:The cure reaction behavior of 6421 BMI resin was investigated by the DSC method. The relationship
between the curing degree and temperature as well as curing rate and time were obtained. Based on Melak method,
the curing reaction behavior was analyzed. The corresponding parameters of the n-order curing model, the autocatalytic
model and the Kamal model were determined by fitting the experimental data, respectively. According to the coefficient
values of R2, a suitable curing reaction kinetic model was determined. It was found that the curves of curing degree
vs temperature presented a “S” shape and the curing rate increased with the rising heating rate. The apparent activation
energy Ea of curing reactions is 105. 611 kJ/ mol, while the curing reaction conformed to the Kamal reaction
kinetic model. The Kamal model is in a good agreement with the experimental data.

Abstract:The basic theory of ultrasonic squirter transmission method and the four-axes automatic ultrasonic
squirter transmission C-scan system were introduced. Several advanced composite materials including the flat plate
sample, the heavy section forming and the cylinder structure were studied by the system and method. The results show
that the defects such as pore, crack, sticky point and lamination in the advanced composite materials can be effectively
detected by this method.