Abstract:The brief historical retrospect on exploring Mars and successfully landing on Mars were carried out.
The basic status and entry conditions of Mars were introduced. The Mars Science Laboratory (MSL) program, MSL
flying to Mars and the aeroheating conditions endured when entering the Mars atmosphere were described. The thermal
protective materials development and correlative aeroheating tests for MSL entry capsule were introduced in details.

Abstract:The definition of near space and the types of vehicles in near space were simply described . The developmental
course of hypersonic vehicles in near space in America was reviewed. The research objects and the military
application of Falcon program were mainly introduced. The development of thermal protective materials for hypersonic
vehicles in Falcon program was emphasized.

Abstract:The compositions, microstructures, synthsis techniques, mechanical properties as well as impact behaviors
of fluoropolymer-matrix reactive energetic materials were sumarized in this paper. Finaly, the applications and
prospectives of such kind of materials were discussed as well.

Abstract:The analysis models of carbon fiber reinforced epoxy laminates with cylindrical and step shape preembedded
metal part are built based on the application of embedded metal part in composite laminates. The single
layer in the laminates is assumed as three dimensional orthotropic material. The stress analysis of the laminates with
embedded metal part is carried out by finite element method. The distributions of material principal direction stress of
the single layers and the von mises stress of metal part are given. The ultimate loads of the composite laminates are
determined based on the strength criterion of maximum stress. It is shown that the initial damages of the two models
both occur in the 90°layer, and the damage mode is matrix cracking under tension. The initial damage of the laminates
with cylindrical embedded metal part occurs at the twelve o’clock location of the central hole border, and the
initial damage of the laminates with step shape embedded metal part occurs at the six o’clock location of the border
between the No. 7th layer and the pre-embedded metal part. Owing to the more discontinuous carbon fibers, the ultimate
load of the laminates with step shape metal part is smaller than that of the laminates with cylindrical metal part
by 18． 03%.

Abstract:Using carbonzed needled PAN-based pre-oxidized fiber felts as preform,the porous C/ C frameworks
with different densities were fabricated by chemical vapor infiltration method ( CVI) and resin impregnation ( IR)
methods, and then C/ C-Cu composites were manufactured by gas pressure infiltration technique. In the present
work, the ablative properties of C/ C-Cu composites were tested by H2 -O2 ablation method. The experimental results
indicate that the linear ablation rate and the mass ablation rate of C/ C-Cu composite with the C/ C perform at 0. 99 g/
cm3 are lower than C/ C composite (ρ =1. 9 g/ cm3 ), exhibiting excellent ablation-resistant performance. During the
ablation test, melting copper matrix depleted a large amount of heat,droped the surface temperature and improved the
anti-ablation performance of C/ C-Cu. For C/ C-Cu composites,the ablation mechanisms are thermal-oxidation and
mechanical erosion.

Abstract:Two Al-Mg alloys plate with 0. 10wt% Sc and 0. 25wt% Er are prepared by casting-rolling-annealing
technology. The variation of tensile properties, corrosion properties and microstructure of the two alloys at different
treated condition was studied. The results show that the first, during annealing two alloys have same variation rule of
microstructure and properties, i. e. with the increase of annealing temperature, the strength decrease but the ductility
increase. At 350℃ /1 h annealing the alloy with 0. 10wt% Sc shows strong annealing softing-resistent ability, but the
alloy with Er become soft when the annealing temperature is higher than 280℃; at 300℃ /1 h annealing condition,
the tensile strength,yield strength and elongation of the alloy with 0. 10wt% Sc and 0. 25wt% Er are 424 MPa,314
MPa,18. 3% and 350 MPa,177 MPa,29. 1%, respectively. Meanwhile, the exfoliation corrosion resistance of the
two alloys show the same variation rule, i. e. at 200℃ /1 h annealing the exfoliation corrosion resistance of the two alloys
is the lest, then with increase of annealing temperature, the resistance increase. After 280℃ annealing for an
hour,two alloys can get excellent exfoliation corrosion resistance. Compared with 5B70 alloy, tensile properties, corrosion
properties and annealing softing-resistent ability of the alloy with 0. 25wt% Sc is similar to 5B70 alloy, but its
manufacture cost decreased, which shows good developing foresight on space vehicle.

Abstract:The NOL rings, laminates and Ф150mm standard pressure vessels of F-12 aramid fiber/ cyanate resin
matrix composites were manufactured by pre-impregnated wind process. The mechanical properties and fracture morphology
of F-12 aramid fiber/ cyanate composites were also studied. The results show that the interlaminar shear
strength(ILSS) was less than 35 MPa,and vessel performance factor (PV / Wc) of Ф150 mm standard pressure vessels
were 34. 22 km. The strength transfer rate of F-12 fiber in Ф150 mm pressure vessels was 70. 22%. The form of fracture
surface mainly reveals tearing and fibrillation of F-12 fiber.

Abstract:The curing reaction kinetics of an eutectic aromatic amine/ epoxy resin E44 system is investigated by
nonisothermal DSC method. The kinetic parameters of this system are calculated by Kissinger, Ozawa and Crane equations:
the apparent activation energy E =49. 2 kJ/ mol(by Kissinger and Ozawa methods), the reaction order n =
0． 95(by Crane equation), the frequent factor A =2. 60×105 s-1(by Kissinger method). The kinetic model of the curing
process based on n order reaction equation is established, which is used for modeling the curing reaction characteristics.
The curing conditions are defined as follow: 50℃ /2 h, 140℃ /2 h, post-curing 200℃ /2 h. The curing behavior
of the system is hardly affected by the change in the amount of the filler boron carbide (B4C) added into the
eutectic aromatic amine/ epoxy resin E44 system.

Abstract:Poly(o-ethoxyaniline) / Fe3O4 nano-multilayer films were prepared by layer-by-layer electrostatic selfassembly.
Poly(o-ethoxyaniline) was synthesized by chemical oxidation and Fe3O4 fluid was obtained by hydrothermal
method. The morphologies, electromagnetic parameters and microwave absorbing properties of the film were characterized
by means of scanning electron microscope (SEM) and vector network analyzer. The SEM picture indicated that
the film was sheeted. The film had both magnetic loss and dielectric loss, but had magnetic loss predominantly. Besides,
in the lower frequency range (8-10 GHz), when the thickness of the film was 3. 5 mm, microwave absorbing
effect is better and the minimal reflection loss is -11. 5 dB. In the lower frequency range (10-12. 5 GHz), the minimal
reflection loss is -10. 4 dB when the thickness of the film was 2. 5 mm.

Abstract:Carbon fiber needling preform reinforced C/ C-SiC composites and C/ C-SiC-ZrB2 composites were
prepared by liquor dipping process. The mechanical, thermal and ablation properties of the composites were investigated
and compared. The results show that the flexural strength,compress strength and shear strength of the C/ C-SiCZrB2
composite are 199 MPa, 274 MPa and 19. 3 MPa respectively. These mechanical properties of the C/ C-SiCZrB2
composite are all lower than the counterpart properties of C/ C-SiC composite. Compared with C/ C-SiC composite,
thermal conductivity of the C/ C-SiC-ZrB2 is greatly higher and the linear expansion coefficient of the C/ C-SiCZrB2
composite is slightly lower. The ablation behavior of them is studied by arc wind tunnel test at a temperature of 2
500 K for 600 s. The C/ C-SiC-ZrB2 composite has an average mass ablation rate of 0. 4×10-4 g/ s and has excellent
properties of oxidation resistance and ablation resistance.

Abstract:The Ni-Fe-P alloy catalysts were deposited on the graphite matrix using electroless plating method,
the catalysts were also characterized and analyzed by scanning electron microscopy, X-ray diffraction, energy dispersive
X-ray. Using the heat treated Ni-Fe-P alloy as catalyst, thiophene as impurity, acetylene as the carbon source,
the carbon micro-coils were successfully prepared by chemical vapor deposition method under the reaction temperature
at 650℃. The study found that the resulting products are almost a regular dimension, morphology of the double helix
carbon fibers, the length of the fiber is millimeter, the helix diameter and the single fiber diameter are 2 to 3 μm,0． 5
to 0. 8 μm.

Abstract:High density Polymethacrylimide ( PMI) foam was prepared by using methacrylic acid( MAA) and
acrylonitrile(AN) as the main monomers. The influence of the flowing agent dosage, foaming temperature and foaming
time on the density of PMI foam was discussed. The microstructure, mechanical performance and dielectric electrical
properties at 10 GHz of the high-density PMI foam were studied. The results indicate that high-density PMI foam
with the density of 150 to 450 kg/ m3 can be obtained by foaming 40 min at 170 to 180℃ with 1 to 5 phr flowing agent.
The bubble edges and bubble walls of the high-density PMI foam gradually thickened with the increase of the
foam density, following the decrease of the average cellular diameter. Meanwhile, the mechanical properties including
compression strength, tensile strength was improved gradually, which was closen to the theoretically calculated values,
and the dielectric constant and dielectric loss increased linearly at the same time.

Abstract:After purification,sensitization, activation of multi-wall carbon nanotubes( CNTs),Ni-coated CNTs
were produced by electroless plating. By DSC analysis,suitable heat treatment temperature is excavated,then Ni-coated
CNTs were annealed under inert gas atmosphere. The products were characterized by transmission electron microscopy
(TEM),energy chromatog raphy (EDS),X-ray diffraction (XRD). The results show that CNTs surface is successfully
coated with a layer of nickel-phosphorus alloys,and Ni-coated CNTs after heat treatment is smoother and
crystallization reaction is occurred, thereby electromagnetic performance is greatly enhanced. The test of electrical
properties show that the conductivity of Ni-coated CNTs is 450 S/ m, and is improved to 1 400 S/ m after the heat
treatment. The test of magnetic properties show Ni-coated CNTs before and after the heat treatment are soft magnetic
material, the saturation magnetization is 2. 753 emu/ g before the heat treatment,and is improved to 11. 254 emu/ g after
the heat treatment.

Abstract:An extensive investigation was carried out on the SR-FSW of 2219aluminium alloy with the thickness
of 6 mm, and the weld appearances, microstructure and mechanical properties of the SR-FSW joint has been analyzed.
The results indicated that the SR-FSW joint had excellent top and underside appearances without inner defects,
distortion and seam thinning if the parameters were carefully chosen. Typical macrosections of the joint were slightly
hourglass shpaed,and the width of the top and underside surface was slightly greater than the mid-thickness of the
joint. As analyzed, the macrosection of the joint was related with the change of the SRPT, heat production and heat
trasfer. The microstructure of the joint also consisted of nugget zone, thermal-mechanically affected zone, heat affected
zone, and within each zone, the microstructure was the same as C-FSW joint. The SR-FSW joint and C-FSW joint
had the similar hardness distribution with the typical “W” type, but the former had no anisotropic. The mechanical
property shown that the tensile strength of the joint can reach 318. 3 MPa, and the ductility can get to 5. 5%. The
fracture mechanisium of the joint was ductile fracture.

Abstract:Composite chamber case of Φ200 mm solid-rocket motor was made by using the two kinds of epoxy
resins E-51 and TDE-85, as well as molding process of hermetic and heat-resistance material and molding process of
filament winding composites were adopted. The PV / W values of the finished Φ200 mm case are 32. 3 km. The hydrostatic
burst test of 36 MPa show that the performances of the filament winding case of solid-rocket motor meet the design
requirements.

Abstract:In this paper, some experiments were carried out by using PCD tool to bore carbon fiber reinforced
plastics (CFRP) and the influence of cutting parameters on cutting force and hole exit tear factor(the ratio of tear size
and hole diameter) was analyzed. The testing results showed that 3-D components of cutting forces increase along
with the increasing of the cutting depth, feed rate and cutting speed. It is indicated that the raise of cutting speed results
in the increasing of yield-stress of the material. Large corner radius causes the highest radial force, followed by
the main cutting force and axial force;Tear factor is almost independent of cutting depth, but there is a linear positive
correlation between the factor and feed rate. When increasing the cutting speed the value of tear factor shows a tendency
to decrease and then kept essentially constant. Boring CFRP using PCD tool can effectively reduce tear degree of
hole exit.

Abstract:For the purpose of welding lead-free BGA devices, among three main welding processes, lead-free
BGA reflow with Sn-Pb solder paste is chosen as process method. By adjusting the temperature zone reflow oven parameters
in order to get the approach of the temperature curve, and by looking at the appearance, X-ray, dye penetrant,
shear stress,metallographic, the conclusion can be made that lead-free BGA soldering technology with SnPb
solder paste passes through test. The result shows that the process method of lead-free BGA reflow with SnPb solder
paste can manage to weld lead-free BGA devices. The result shows that the method is reasonable an feasible.

Abstract:In this paper,the principle and the method for the measurement of Poisson ratio of C/ C composite
material by laser holographic interterometry are described. The result shows that this method is especially suitable for
the measurement of C/ C composite Poisson’ s ratio. The mean value of Poisson’ s ratio of braided C/ C, needled
punching C/ C, felted C/ C were 0. 196, 0. 183, 0. 040.

Abstract:The thermal vacuum of space condition is an important factor to cause properties degradation and outgassing
contamination of adhesive bonding materials used in optic-electrical components. The thermal vacuum aging
and volatile characteristic of several typical adhesive bonding materials were investigated. The change of mechanical
properties and the source of volatile after thermal vacuum test were analyzed and discussed, and the pretreatment
method under thermal vacuum condition were validated and analyzed. The results indicate that the soft silicone rubber
adhesive display greater mass loss than that of harder epoxy resin and acrylic resin adhesives, and the condensation
type silicone rubber and epoxy resin adhesives appear greater changes of modulus because of end hydroxyl group exist
in their molecular structures. The pretreatment method under thermal vacuum condition could be used as an effective
measure to reduce the outgassing contamination of adhesive bonding materials. The results are important for the design
and screening of nonmetallic materials used in optic-electrical components.

Abstract:In this paper, a method is provide to determine the tolerances of the components based on computation
of digital model and data fitting, tolerances chain analysis on the aerodynamics edges, combining with equalized
tool design and process control of model based design (MBD) model. Varity of digital methods, such as laser tracker
and data fitting between MBD model and the product, is adopt to equalize the tolerances during assembling. The
structural interference can be avoided with this technique, making the product meet the demand of the delivery specifications.
Besides, it decreases the rates of tolerance exceeding and the cost of manufacturing. The accumulated tolerance
of aerodynamics can be reduced to 10% of designed demands during assembling with the method.

Abstract:The material flow stress model for 300M ultra high strength steel has been established by hot compression
tests on the Gleeble-1500 thermal simulation testing machine. The hammer forging forming for 300M ultra high
strength steel die forging of landing gear cylinder has been investigated by DEFORM 3D FEM software, the influence
of hammer forging under different process parameters has been researched in this paper. The results show that: the die
forging filled completely at 1 100℃ initial forging temperature after the three fires;the average stress of the forging is
228 MPa and the average strain is 1. 51, which provides technical reference for hammer forging process.

Abstract:Through the milling test of titanium alloy TC21, the surface roughness is measured with different cutting
parameters. Orthogonal experimental design method is used to arrange the test and range analysis to process experimental
data,and the effection to surface roughness caused by different cutting parameters, is analyzed. The most
significant effect on the TC21 titanium alloy surface roughness of the factors is the feed per tooth, followed by the cutting
depth and cutting speed,and the least important comes to cutting width. Based on the analysis of the mechanism of
effect on surface roughness, smaller amount of feed and cutting depth ,larger cutting speed and cutting width should
be used in processing

Abstract:In order to maintain the temperature of the reentry capsule, the S781 thermal coating is painted on
outside wall of the reentry capsule of manned spacecraft. In the painting process, the color difference appears between
the partition and adjacent partition. In this paper, the composition of color difference area of S781 coating is analyzed,
and several experiments are designed with different painting temperatures, interval time and materials. The result
reveals that the color difference is due to that the interval time of partition painting is longer than the surface drying
time of the coating. The color difference becomes obviously with the interval time, which is more than 1 minute.
And there are granules when the temperature is high, because the surface dries much more quickly. At last, an improved
painting method of S781 thermal coat is proposed to control the joint color difference. The result will be helpful
to the implement of thermal control of manned spacecraft.