Abstract:The development of foreign metallic thermal protection system ( TPS) is briefly reviewed. And the
up to the minute study and test of the metallic TPS in China is introduced emphatically. It is indicated that the metal lic TPS is the one of top priority blue prints of the acreage TPS for the next generation reusable launch vehicle.

Abstract:The compositions, processing technologies and performances of the command module of Shenzhou
manned spacecraft are introduced in this article and compared with the related ablation materials in other countries.
Furthermore, the development of ablation materials of command module is summarized and prospected.

Abstract:The present status of research and application of ultra high temperature materials such as refractory
metal diboride/ carbide ceramic composites is summarized. The existing problems were analyzed, and the research tendency in the future is put forward.

Abstract:The latest progress in PMI foam cored sandwich structure application is reviewed in this paper. There
are still some problems in the application of domestic PMI foam cored sandwich composites. It is necessary to establish
the manufacturing standard system for PMI foam cored sandwich composites.

Abstract:The importance of sound absorbing polyurethane foam is reviewed in this paper, and the research development of sound absorbing polyurethane foam is described in detail. The manufacture processes, raw materials and their properties, and sound absorbing performance of sound absorbing polyurethane foam are introduced in detail as well.

Abstract:The traits and classification of metal seals and how to select seals at elevated temperature are intro
duced. By taking the elevated temperature metal seals used by shuttle orbiters and X-38 as an example,selection of
materials,structure design and test to fabricate elevated temperature metal seals,in NASA are introduced as well.

Abstract:The recent developments of repair techniques of the structural composites are reviewed and the influencing
factors of the composite repairs are analyzed. Furthermore the application of the composite repair techniques of Aerospace
Research Institute of Materials & Processing Technology in aerospace industry is introduced.

Abstract:Study significance and relative basic concept and testing method of evaluation and characterization of
high temperature dielectric properties of microwave transmitting materials is summarized,development is introduced,
and also the common key technology in high temperature testing of high Q cavity method is expatiated,future develop ment and applications are put forward.

Abstract:The types of operational aerospace arc heater facility is performed. These facility include multiseg
ment, huels or vortex stabilized, magnetically stabilized, induction coupled and magnetplasmdynamic heaters. The
main facility is described. The trend of arc heater facility is also introduced in this paper.

Abstract:Recent research findings and applications of static test and model test for wind turbine blade as well
as test standards and test institutions at home and abroad are introduced in this paper.

Abstract:The isothermal forging process of MB26 magnesium alloy was studied by one type of DEFORM-3D elerent analytical software. The results show visually the distribution of the stress,the trend of metal flow and the forming
effect. The cause of typical forming defects, such as folding was found out. According to numerical analysis,the proper
blank dimensions, die structure and process parameters were achieved. The forming defects were eliminated.

Abstract:In the base of progressive damage method and bilinear cohesive model, destruction mode and limit
load of C/ C composite made by axial rod method under axial tension load were forecast by using user defined program
USDFLD of ABAQUS 6. 8. The experiment result and forecast result were compared. As a result, fracture mode of axial rod carbon/ carbon composite can be accurately forecast by using the method put forward in the paper.

Abstract:In order to develop a smart variable emittance thermal control coating, we here report on a flexible
solidstate electrochromic device(ECD) based on soluble polyaniline by simple fabrication process. Devices were assembled in sandwich configuration of electrochromic materials on flexible PET substrate and a Li+ doped polyacrylonitrile as a solid polymer electrolyte. The initial surface emissivity characteristics related to oxidation states, doping concentration, doping agent and thickness were discussed. The smart thermal management of this ECD was characterized
by its emittance in view of the thickness of active layer and the applied voltage. The emittance of our ECD can be
tuned from 0. 46 to 0. 75 without any fine optimization, which is similar to that of other solidstate ECDs. The major
advantage of this work is that the electrochromic variable emittance coating can be preparedby using simple process,
such as spin coating and spray coatings. These methods do not require any special equipments and vacuum working
conditions, and are easily applied for large area process as well. This study may open new avenues in the development
of flexible electrochromic devices for spacecraft thermal control.

Abstract:In this paper, the performances of 803 resin and its composites were studied. Dynamic DSC indicated 803
resin has high reactivity;rheological analysis proved 803 resin has excellent processing property; research of thermal behavior expressed that MT300/803 has high heatdurability, the glass transition temperture tested by DMA was 300益,Td
5 was
396益; mechanical properties showed that MT300/803 is excellent and 803 resin matches MT300 well. Therefore the
MT300/803 composite has good heatdurability and can meet the needs of highproperties in the aerospace field.

Abstract:The 603 is a heatresistant epoxy resin. Its glass transition temperature and heat decomposition temperature are 225益and 387益respectively. The solidifying characteristics are studied by geltime,DSC and rheology,
and then its curing technique is confirmed. Draping prepregs can be made through solvent and melting. The composites
of T700/603 and T800/603 can be used as structural components with high performance.

Abstract:In order to meet the requirement for wave transparent materials, the porous Si3N4 materials with high
strength and low dielectric constant were fabricated by gel casting method. The microstructure, dielectric properties,
wave transmittance and flexural strength were investigated. The results show that the flexural strength of porous Si3N4 is up to 50 MPa with dielectric constant of 2. 3 to 2. 8. At the same time, the materials have steady high temperature
dielectric properties and good wave transparent properties.

Abstract:A novel epoxy based coating designated as TR-48 is developed in house at Aerospace Research Insti
tute of Materials & Processing Technology. This material is composed of toughened epoxy binder for durable performance and is filled with special carbonate agent for improvement of ablation resistance. The TR-48 coating is evaluated
by mechanical property testing,thermal physics property testing,ablation testing,as well as batch stable testing. The
tensile strength is 8. 7 to 11. 2 MPa,elongation rate is 6. 8% to 12. 2%,mass retained in TG analysis at 800益is
51%,mass retained after 800益,5 min static ablation is 38% to 47%. It is also found that sinter reaction during 600
to 800益is the main reason which makes ablation resistance improved. Then the TR-48 is qualified by thermal testing
in a wind tunnel or under an oxygen kerosene engine to simulate the hypersonic aerodynamic heating and exhaust erosion. This material is characterized by excellent thermal protection performance and good ablation resistance.

Abstract:Pouring experiments were conducted by adjusting the dosage of TEDA solution and DBTL in the rigid
polyurethane plastic foam pouring formulation. The properties of two kinds of plastic foams manufactured at the material temperature of room temperature and 5 were compared. The mechanical properties, closed cell proportion, liner
expansion coefficient and thermal conductivity have the equal values at room temperature and 5. So the pouring
process at the material temperature of RT is feasible.

Abstract:Electric conducting silicon rubber was prepared by filling acetylene carbon black into the rubber. The
structures of the conducting rubbers were characterized by SEM and TGA. Then their conducting mechanism was investigated in detail. The results show that the content of carbon black obviously affects mechanical properties of the
conducting silicon rubber. But the change of volume resistivity is not obvious when the carbon black content is beyond
45 phr. The structure of “grain/ cluster冶and “chain/ cluster冶formed in the conducting rubber. Therefore, the “electric channels and tunnels冶increased and the volume resistivity decreased. The content of 50 phr is the optimal quantity of thermal resistance for the silicon rubber. With the increase of temperature, the tensile strength of conducting
rubbers with 50 phr carbon black decreased gradually. After aging at the temperature of 100益, the conducting property of silicon rubber reduced.

Abstract:The properties and microstructure of P/ M  TiAl based alloy obtained from pre alloyed spherical pow
ders by HIP process were tested and analyzed. As the applications of P/ M TiAl based alloy, brazing technologies
and some typical components were introduced at the end of the article. The results show that P/ M TiAl based alloy
can be an attractive candidate material for some aerospace vehicles due to its good mechanical properties, fine microstructures and excellent oxidation resistance.

Abstract:The corrosion properties of a new high strength Al Li alloy is characterized as a functions of the solu
tion treatment and the different aging time after the solution treatment. Results show that the corrosion properties of the
new Al Li alloy solution treated is the best, but its intercrystalline corrosion and spalling corrosion become worse with
increase of the aging time.

Abstract:The prealloyed powder metallurgy (PM) process and HIP technology and PREP powders are used to
prepare full density PM TC11 (Ti-6. 5Al-3. 5Mo-1. 5Zr-0. 3Si) alloy, a kind of heat resistant titanium alloy. Heat
treatment is studied to optimize the microstructures and properties of the PM TC11 alloy. The microstructures are examined by optical microscope, and the morphologies of PREP powders are observed by SEM. Room temperature and
high temperature (550) tensile properties and elastic modulus of PM TC11 alloy are tested and discussed. The mi
crostructures and properties of the PM TC11 alloy are compared with those of the same batch forged rod. Nearnetshape processes are studied to fabricate PM TC11 parts. By using of special dies, a big dimension thin wall integrated
PM TC11 alloy spacecraft cabin with inner gridding stiffening ribs is nearnetshaped and no inner defect is detected.
The results show that the PM TC11 alloy has the same good tensile properties as forged material and plus perfect elas tic modulus. The microstructures of the PM TC11 alloy are fine and uniform and the typical ones are basketweave
structures surrounded by equiaxed  The PM TC11 alloy and suitable nearnetshape process can be used in the field of fabricating high performancetocost, high reliability, lightweight and heat resistant parts for spacecrafts.

Abstract:This work introduces impregnation process of difference and influence between Fanglun and F-12
fiber. Under the consideration of unique surface performance and yarn of Fanglun fiber, Fanglun yarn parameter and impregnation processing technique are optimized. Due to the easy processing and stable prepreg tape, prepreg
tape is suitable as a reinforcing material for winding manufacture.

Abstract:Based on the analysis of ATP ( automated tape placement) technology, the virtue of the ultrasonic
cutting technology is presented. According to the working status of ATP machine, the experiment is designed for the
ultrasonic cutting system, and the stability of the system is analyzed and studied. The control scheme is achieved via
the ultrasonic cutting system reliability experiment, which is suitable for the limit need of the ATP working status.

Abstract:The paper summarizes the measure methods of permeability, and some test conditions are unified
based on tests. Test methods of permeability of stitching fabric for wind turbine blade are established based on its
process and parts in order to attempt to give some references to evaluate the permeability of the blade material and
control blade quality.

Abstract:Different dimensional specimens of 3D carbon/ carbon composites were made. The microstructure of
the 3D carbon/ carbon composites was investigated with microCT. The correction of projective images rotational center, denoising, and ring artifacts correction were performed. Results show that the microCT images of 3D carbon/ carbon composites are improved through data processing. And the microstructures are accurately displayed.

Abstract:The ultrasonic resonant NDT technique was analytically discussed and the inspection technology of
composite bond structures was studied with the developed ultrasonic resonant equipment,the result suggests that the
debond defects more than 10 mm in the bond structures for the composite layer of 7 mm thick, and the debond defects more than 15 mm in the bond structures for the composite layer of 9 mm thick can be found out.

Abstract:By taking axial carbon rods 4D preform woven with two kinds of T300 grade PAN based carbon fiber
made in China as reinforcement and high temperature coaltar pitch as matrix precursor, the C/ C composites with a
density up to 1. 95 g/ cm3 were prepared by using combined impregnationcarbonization and graphitization techniques.
Thermal conductivity of the C/ C composites from RT to 800益and the influencing factors were discussed. The results
show that thermal conductance of the C/ C composites is decreased with increasing of the temperature under the experimental condition. Because of the own features of raw materials and the directivity of preform, the thermal conductivity
of the C/ C composites along radial direction is higher than that of axial direction. C/ C composites with higher density, lower porosity and higher graphitization degree have higher thermal conductivity due to their excellent connectivity
between crystal particles and gradually perfected crystal microstructure. The thermal conductivity of the C/ C composites with low pressure heat treatment as its final process is higher than that after high pressure carbonization. The thermal conductivity of C/ C composites prepared by T300 carbon fibers made in China is similar to that of the C/ C composites prepared by Toray T300 carbon fibers.

Abstract:With respect to the noise interference in rear surface temperature curves with laser pulse method,
frequency range of noisy signal was ascertained through frequency analysis method, a corresponding FIR filter is designed to reduce the noise interference in rear surface temperature curves, and a recursive smoothing filter was used to
reduce residual noise. The compared results before and after filtering show the method is effective to reduce the noise
interference in rear surface temperature curves with laser pulse method.

Abstract:Ten C/ E composite pressure vessels were testing by acoustic emission technique to research the Feasibility of
evaluating the craft quality and damage seriousness by t-location and the Felicity ration.In addition,the fatigue test of the C/
E compostie pressure vessels were examined by the acoustic emission technique. The results show that the acoustic emisson
technique is feasible to evaluating the composite pressure vessel and t-location and fatigue test are the assistant function for evaluation.Damage of the vessel is more serious as the Felicity ratio is bigger.

Abstract:This paper reports the results of ablation tests conducted in FD04 arc tunnel of China Academy of
Aerospace Aerodynamics (CAAA) for the development of wing leading edge thermal protection materials. The models
were made of high temperature ceramic(HTC), with swept angle 53, height 75 mm, long 55 mm, leading edge radius 2 mm and symmetric cross section made up of a 5wedge on each side. The test facility included 20 MW arc heat
er, mixing chamber, rectangular supersonic nozzle, test box, trajectory simulation and vacuum system etc. The rectangular supersonic nozzle with Mach number 3. 6 was used in tests. The aero heating conditions of the wing leading
edge were simulated by a test trajectory with flow field parameters of three steps. The test duration was 77. 0 s. The
results show that HTC has well ablation performance, and two models had no breakage during the tests. The inner
temperature responses are attained in tests.

Abstract:The aeroheating impact experiment on three kinds of thermal protection materials of missile launch
canister was conducted. The turbulent duct connected to arc heater was used to simulate the thermal conditions during
launching, both high pressure and high temperature. Thermal protection performances of three kinds of materials were
obtained at the same conditions. The results indicated that thermal protection performance of rubber is better than that
of ceramic matrix braided composite and glass fibre braided composite. Rubber is more suitable for using on the innersurface of launch conister.

Abstract:This paper reports the development and application of radiation heating facility in China Academy of
Aerospace Aerodynamics (CAAA). The facility includes 0 to 150 kW quartz lamps heater,test chamber,vacuum system
and control system. The performances of low density thermal insulation materials in deferent low pressures have been
studied on the radiation heating facility. The model cross size is 100 mm 伊100 mm. The maximum running time is 2 000
s. The surface temperature of low density thermal insulation materials is up to 1 000 K. The minimum pressure in the test
chamber is 10 Pa.