Abstract:Recent advances in the development of interlayer toughening for CFEPs are presented in this review
paper. Especially, the influences of the toughening methodology on the properties of CFEPs are discussed.

Abstract:Recent research and development of matrix resins for high temperature polymer composites has been
summarized in the present paper. The current status of several characteristic high temperature matrix resins, including
polyimide (PI), bismaleimide (BMI), cyanate ester (CE), benzoxazine (BX), and phthalonitrile polymers is emphatically
presented.

Abstract:Recent advances on high temperature polyimide thermoset resins and the fiber reinforced composites
especially their applications in aerospace industry are reviewed. The rheological mechanical and physical properties of
several domestic novel high temperature polyimide matrix composites are summarized. The polyimide matrix honeycomb
sandwich structural composites and quartz fiber reinforced composites are discussed. The development trends of PMR
polyimide matrix composites are proposed.

Abstract:Carbon fiber reinforced silicon carbide ceramic matrix composites (C/ SiC) is a material that possess
high specific stiffness, low sensitivity of thermal distortion and the adaptability in high and cryogenic temperatures,
which make it a most promising space optical application material. The article summarizes the fabrication processes of
C/ SiC and the practical application of C/ SiC to space technologies abroad.

Abstract:Non-powered solar sails are arousing more and more research interest all over the world in recent
years, which have significant potential applications in deep-space exploration due to their unique advantages. The
structures and materials are critical factors for solar sails. According to the flight environment of solar sails,this paper
introduced their basic structures and mechanisms,and reviewed the deployable boom materials and sail membrane materials
for some typical solar sail designs. The features of different materials and designs were also discussed.

Abstract:Multi-layer insulation structures(MLI) are a kind of composite mostly used as thermal insulation of
the aerocraft and propellant tank in the space. In this paper,heat insulating principle,composition,processing technology
and the application of MLI are reviewed. The recent the progress and tendency of MLI is introduced briefly. With
the purpose of landing on moon and deep space exploration,the property of MLI must be improved.

Abstract:A novel modified polybenzoxazine resin was prepared. The final product was characterized with Fourier
transform infrared spectrometry (FT-IR) and gel permeation chromatography (GPC). Processing capability and
cure behavior of the modified resin was investigated by rotary viscometer and differential scanning calorimetry (DSC),
respectively. The resin shows a low viscosity of 180 mPa·s at 60℃ for above 6 hours, indicating that the resin is suitable
for resin transfer molding (RTM) process to fabricate composites. DSC results show the modified resin can be
cured at about 200℃ without adding any other curing additives. Dynamic mechanical analysis (DMA) shows the inflection
point of tanδ is 353. 4℃. Thermogravimetric analysis (TGA) showed 5% weight loss temperature of the final
cured products in nitrogen is 437. 9℃, and char yield is 73. 71% at 900℃.

Abstract:Soluble preceramic polymer to BN ceramic, polyborazine, was synthesized via condensation of boron
trichloride and hexamethydisilazane followed by a polymerization process. The average molecular weight and structure
of the prepolymer during polymerization, mechanism of polymerization, pyrolysis process, and chemical composition of
the obtained ceramic were investigated using gel permeation chromatography, 1H NMR, infrared spectra, thermogravimetric
analysis and element analysis. The results indicate that hexamethydisilazane and NH3 were released during the
polymerization process. The average weight molecular and ceramic yield (1 000℃ in N2 ) of the polyborazine are 7
582 and 41． 6 wt%, respectively. The ceramic mainly formed at the temperature range of 400 to 600℃ and white BN
ceramic with low carbon content was obtained after pyrolyzed in NH3 at 800℃.

Abstract:In this paper, the temperature dependence of stacking of graphite layer during the heat treatment
process for carbon fiber was investigated by the method of 2-dimensional wide angle X-ray diffraction (WAXD). The
results indicated that with the increas of the treatment temperature, the number of the stacked graphite layer was increased.
When the temperature was higher than 1900℃, the increasing of the stacked layer number was accelerated
due to the improving of defect resulted from the removing of non-carbon elements and the transition to sp2 hybridization,
which was supported by the evidence of Raman spectroscopy and elemental analysis experiments data.

Abstract:The properties of moulded quartz phenolic composites are studied by the methods of mechanical and
physical tests,comparing with moulded high silica phenolic composites. The result shows that moulded quartz phenolic
composite not only has good mechanical property,but also has much more lower thermal deformation in the environment
of low enthalpy,low heat flux and long-time ablation as the property of half linear expansion coefficient comparing
with moulded high silica phenolic composite.

Abstract:In this paper, moisture absorption, outgas capacity in vacuum and deformation after moisture absorption
of carbon fiber reinforced cyanate ester composite were studied, and were compared with corresponding capacity
of epoxy resin composites. Result show that the moisture absorption of cyanate ester composite is lower than epoxy resin
composites, and capacity in simulated space environment is compatible with epoxy resin composites.

Abstract:The technology difficulties of the manufacturing of complex composite component which use metal
mould unable demoulded were introduced. We emphatically studied,the forming processes and properties of water soluble
core. The water soluble core was successfully used to manufacture a composite structure with typical features.
The results show that,the properties of water soluble core appeased the need of fabrication of composite.

Abstract:The integral forming technique of cap-shaped frame, the structure of mould in process design,and the
form of spread out the prepreg,the effect of the honeycomb sandwich construction are introduced. The stren of capshaped
frame was analysed. These results indicated that the forming technique had large potentialities of the integral
forming technology of cap-shaped frame

Abstract:Based on the development of composite vessel used in space propulsion system, the applied research
of PBO filament was developed. By the mechanical property tests of PBO/ D-3 and PBO/ D-8, the optimum composite
system was obtained. Furthermore, the design, process and test of PBO filament wound thin wall high pressure
vessel with aluminum liner were also studied. The results showed that, the optimum composite was PBO HM(high
modulus) / D-8. The tensile strength and NOL ring interfacial shear strength can reach 1397 MPa and 20. 2 MPa respectively.
The maximum vessel performance factor with PBO HM/ D-8 is 64. 5 km

Abstract:The experiments are studied in epoxy resin cast mechanical property, NOL hoop mechanical property,
surface property of metallic inner wall, vacuum outgassing of composite and composite pressure vessel, aimed to
the manufacturing of composite overwrapped pressure vessels(COPV) on the propulsion system of satellites. The result
shows that the burst pressure of the COPV is 86 MPa after 150 times fatigue experiments, the vessel characteristic
factor is 57. 7 km,and the COPV is suitable for the application needing in vacuum .

Abstract:This paper was aimed at the investigation of effect of the aluminum liner vices to the fatigue and burst
characteristics of the filament winding composite pressure vessels. These vices included hollowness, corrosion and
cracks on the metal liner. The results shown that the vices exited on the metal liner could lead to stress concentration,
which brought on cracks spreading along these vices. So the invalidation of the metal liner was advance of the composite.
All of those could stimulate more damages to the vessels, which lead to degrade final burst pressure and fatigue
cycling. These vices hereby gave rise to a great effect on final properties of the composite pressure vessels.

Abstract:The forming process of carbon fiber MT300/648 epoxy panel honeycomb sandwich structure cylindrical
with a large size is investigated in the paper. The forming process of internal and external panel, the plug-in
process of aluminum honeycomb with “F” shape metal frames and the assembly co-curing technology of panels-aluminum
honeycomb-metal frames are introduced. The size of honeycomb sandwich structure cylindrical achieve the requirements
by the mold design optimization,and the difficulty of panel-honeycomb-frames assembly technology is resolved

Abstract:The residual stress caused by machining directly related to machining deformation and machining
damage. Being limited to measuring technique of machining residual stress and characteristics of composite, there are
seldom paper about machining residual stress on composites. In this paper, hole-drilling method that is suitable for
measuring the machining residual stress of composites has been adopted. C/ C composites are machined by means of
milling-grinding. The cutting tool is grinding head that is electroplating emery on, by means of quadratic general rotary
unitized design. Four factors including cutting speed, cutting width, cutting depth and feed are selected for this experiment.
The regression mathematical model based on quadratic polynomial is obtained through the analysis of experimental
results. The variation of machining residual stress along with the change of processing parameters is analyzed.
The extreme value is obtained by searching optimization. It shows that machining residual stress is all compressive
stress. Along with the increase of the cutting speed, residual stress tends to an asymptotic values that is -16MPa in
this experiment. Along with the increase of the cutting width, cutting depth and feed, residual stress first increased
and then decreased. The demarcation of parameters are cutting width: aw =6 mm; cutting depth: ap =0． 5 mm; feed:
f =200 mm/ min.

Abstract:As a important form of connector and load-bearing structure, the connection property of composite
bolted joint directly affect the structure reliability. Against the anisotropism and progressive damage character, the
composite bolt and plate is modeled by finite element method. According to the written U-mat code, the progressive
damage process of composite bolted joint is simulated by numerical method, the load-displacement curves of bolted
joint are obtained, and the failure mode is studied in this paper.

Abstract:Based on the characteristics of the laminated materials and structure of the cone-shaped part,we discussed
its processing principle and developed hole drilling techniques. Rotate speed of spindle and feed speed were
optimized by designing “pre-load” equipment and breadboard experiment. Qualifed products were successfuly manufactured
through the application of these techniques.

Abstract:Cutting tool plays an significant role in composite machining. In this paper the special property of
composite and its machining mechanism is analyzed, the requirement of cutting tool materials, structure and geometrical
parameters for composite machining is discussed. Several kinds of drilling and milling tools which are fit for carbon
fiber reinforced plastic(CFRP) and aramid fiber reinforced plastic (AFRP) are introduced.

Abstract:The two cf-zerodur composites mirrors with and without pre-embedded parts are polished by continuous
polishing method, and they are under stability experiment after polishing. The surface figures of the cf-zerodur
composites mirrors are measured by a Zygo interferometer. The surface errors of the mirror without pre-embedded parts
after the stability experiment are as follows:the P-V error is 2. 313λ,the RMS error is 0. 669λ. The surface errors of
the mirror with pre-embedded parts after the stability experiment are as follows: the P-V error is 3. 013λ,the RMS error
is 0. 276λ(λ =632. 8 nm). The experimental results show that the structure of cf-zerodur composites mirror with
pre-embedded parts is better than that of without pre-embedded parts. The paper presents some references for the application
of cf-zerodur composites mirrors.

Abstract:This paper describes the supporting conditions, technology and quality control, etc, in the process of
cementing and assembling truss of a certain model satellite which is made of carbon fiber composite. The research
shows that the truss has higher bonding strength when fitting clearance of rods and joints is between 0. 1 and 0. 3 mm.
The precision of truss is entirely depend on high-precision tooling, and ultimately precision can reach the accuracy of
0. 2 mm. Appropriate technological process and quality control method can satisfy the high precision of the carbon fiber
truss structure and cementing quality, and this method is also suitable for other products.

Abstract:A large thin-wall casting part for aeroplane cracked many times when it was riveted with the skin and
resulted in serious security risk. The cause of the riveting crack was analyzed synthetically by macro and micro observation
of fracture surface, metallographic microstructure analysis and other relative tests. The result shows that the insufficient
modification, the low plasticity which reduces the ability of bearing concussion when riveting of this casting
part are the main causes of cracking. Meanwhile, the pressure produced after the assembling is also the important
cause of riveting crack.

Abstract:The dispersion property of Si3N4 was studied when ammonium polyacrylate was used as dispersant. And
the influences of acid leaching and thermal oxidation on aqueous dispersibility were investigated. The results indicated
that the best dispersing effect could be obtained when the ratio of ammonium polyacrylate was 0.2 wt% and pH=9. After
acid leaching, both the width and the value of particle diameter became smaller. The contamination of metal can be
eliminated efficiently by acid leaching. After themal oxidation, the viscosity of Si3N4 suspension dropped significantly.

Abstract:The flexible aerogel monoliths were prepared by the hydrolysis and condensation of methyltriethoxysilane
(MTES),followed by supercritical drying. The influence of concentration of precursor on the chemical composition,
microstructure,flexibility and thermal stability of aerogel were investigated. It is shown that the degree of cross
linking of aerogel molecule, which was prepared by the precursor of MTES and showed excellent flexibility was declined
because of the existence of methyl groups. With the reduction of concentration of precursor, the degree of compactness
of aerogel particles declined, which is responsible for the enhancement in the flexibility of the aerogels, the
number of Si-OH increased and the thermal stability of aerogel exhibited the same tendency.