Salutary Address Keldysh Research Center - Federal State Unitary Enterprise "Keldysh Research Center" [earlier Rocket Scientific-Research Institute (RNII), Scientific-Research Institute -1 (NII-1), Scientific-Research Institute of Thermal Processes (NIITP)] - in Russia this is the leading organization in the field of rocket engine manufacturing and space power. The Keldysh Research Center is included in the structure of Russian Aviation and Space Agency * and takes an active part in formation and realization of the Federal Space Program. It develops, manufactures and tests promising prototypes of various types of rocket engines, space power systems, high-energy beam generators and particle accelerators.

October,2008
The monographies on liquid, electric and hybrid rocket engines were published by an anniversary of Keldysh Research Center.
"The microfiltration unit of the UMF type" was specially appraised among other exhibits and rewarded with a diploma and a gold medal at the Second International Exhibition that took place from September 30 till October 03, 2008 and also at the Congress "Advanced technologies of XXI century" (Moscow, the All-Russia Exhibition Centre, pavilion 55 "Electrification").
The small-scale unit for utilization of dissolved oil gases, developed by Keldysh Research Center in collaboration with Scientific-production association "Power technology" and Moscow Physics and Technology Institute, was rewarded with a diploma and medal at the Second International Exhibition and at the Congress "Advanced technologies of XXI century".

June,2008
Successful operation of the KM-5 Hall thruster aboard the geostationary communication satellite "Express-A4" put into orbit in June 2002 is going on. As of May 2008, the fire running time per thruster made up 1550 hours at 900 burns.
This is the maximum service life of the Hall thruster in full-scale conditions, that was ever attained when solving the problem of orbital correction of geostationary communication satellites.
Works on creation of the KM-88 Hall thruster with the specific impulse as much as 2200s have been completed.

March,2008
At the VIII Moscow International Salon of Innovations and Investments, FSUE "KeRC"-developed products have aroused considerable interest of both participants and visitors of the Salon. KeRC has been awarded with a Diploma of the Salon for development of filter elements.

Oktober,2007
Bench experimental researches of an updated laser-ignition system for an igniter of rocket engine propelled by gaseous hydrogen and oxygen with using a small-size laser were conducted. The maximum total flow rate of propellants did not exceed 9 g/s, and the mixture ratio Km varied from 1.2 to 2.2. The solid-state laser of 40 g mass was joined directly to the igniter. The laser power source of 360 g mass is powered with a 12 V constant-voltage source at power consumption of ~ 1 W on the average. At a single ignition of propellants, power consumption of the power source with the laser amounts to ~ 4 J. A reliable ignition of propellants after repeated firings occurs on retention of operability of the laser and igniter. Works are fulfilled in the context of ISTC Project No. 3236 in co-operation with CADB (Voronezh).

September,2007
After the acceptance of the federal program "Development of nanoindustry infrastructure in Russian Federation for the period from 2008 to 2010 years." Keldysh Research Center has been appointed the head organization in the direction "Functional nanomaterials for space technique".

June,2007
In the context of the XI Petersburg International Economic Forum in St. Petersburg (June 8-10, 2007), the exhibition of high technologies took place.
KeRC developments demonstrated there were awarded an Exhibition diploma. A government congratulation telegram has been received by KeRC (s. Section “Conferences”).

May,2007
Bench experimental investigations of laser ignition of low-thrust rocket engine (LTRE) of 50N thrust, propelled by gaseous oxygen and ethanol, were performed. The experiments were conducted in atmospheric conditions, the oxidizer-to-fuel ratio was varied from 0.29 to 0.34. Optical fiber ytterbium laser operating in pulse-periodic regime at the laser-pulse energy of 0.5 mJ at the average radiation power of 10W was used for the laser ignition. Laser radiation was transferred to LTRE through optical fiber and special laser plug screwed in to the LTRE injector assembly. Regimes of short-time pulse firings of LTRE were optimized, LTRE reliable ignition thereat takes place on retention of operability of laser plug, injector assembly, combustion chamber and nozzle after repeated firings.

April,2007
Scientific and engineering work has been done in anticipation.
This work covers field-conversion technologies on a basis of a small-scale unit for conversion of associated petroleum gases to chemical raw material (methanol). It consists of a tricomponent synthesis-gas generator based on up-to-date high-power rating aggregates, and a methanol synthesizer fulfilled to the recyclingfree scheme.
Main components of the small-scale unit were put through bench tests and revealed results warranting going to complex tests of a unit demonstrator. Scientific and technological developments, brought up to making of a demonstration bench operating specimen give promise that in the not distant future small-scale units would be used at sites of oil deposits for the purpose of utilization of associated gases and production of liquid energycarrier (methanol) suitable for transportation for any distances.
As potential consumers may be oil fields, oilfield clusters with the oil gas output of 1000 nm³ per hour and over.

January,2007
Bench experimental tests of laser ignition on methane + oxygen fuel in rocket engine igniter were conducted. In the course of experiments, operation of the device was simulated both in atmospheric, and vacuum conditions. The maximum total flow rate of propellants did not exceed 8 g/s, the mixture ratios were changed within the range from 0.4 to 1.6. For laser ignition, the fiber-ytterbium laser operating in the pulsed-periodic regime at laser pulses energy at the level of 0.4 mJ was used. A reliable ignition of propellants takes place on retention of operability of the igniter construction upon multiple firings.

December,2006
Prize-giving ceremony was held on December 21^st, 2006 in the Saint Catherine's Hall in the Great Kremlin Palace for awards and decorations presentation to outstanding scientists and public figures, educators, workers of culture, medicine, sportsmen and production men.
Anatoly S. Koroteev, Director of the Keldysh Research Center, Academician of the Russian Academy of Sciences, President of the Russian Academy of Cosmonautics, was awarded an Order of Merit for Fatherland, III degree.

A method of heat supply and the device for its implementation have been developed. They are protected by RF Patent #2260157 (2003137068 dated 25.12.2003). The patent was published in the bulletin "Inventions. Useful models" # 25, 2005.

A radiometric complex for contactless thermal diagnostics of high-temperature media and objects has been developed.
The radiometric complex performs contactless temperature measurement simultaneously in every point on the whole surface of the measured object with the help of optical-electronic system in wavelength range from 0.4 microns up to 1.1 microns. Sizes of the measured object may vary from several square centimeters up to the meter. Measured temperature fields are registered on PC with frequency up to 25 frames in a second that allows one to reproduce temperature on any generatrix and in any time moment within the range from 600°C up to 3000°C with a measurement error plus/minus 3 degrees.
Developed complex is used at testing LRE with uncooled nozzles and nozzle extension.

Hall-effect thruster KM-60 successfully passed a complex of tests on external effects. Including those to the effect of random vibration at mean effective value 25.5 g and impact loads at the value of shock spectrum up to 2500 g. Development of the engine is made on the order of Scientific and Production Association of Applied Mechanics named after M.F. Reshetnev for use in the structure of correction and orientation block in the advanced satellite platform "Express-1000". Features of the engine are high specific impulse at relatively low level of energy consumption and peak limiting of the discharge voltage value, record number of operating cycles and high level of external mechanical effects.
Started in June 2002 flight tests of Hall-effect thruster KM-5 continue at nominal power 2 kW in the structure of serial geostationary communication satellite "Express-A" #4 of development of Scientific and Production Association of Applied Mechanics named after M.F. Reshetnev. The thurster is used for orbit correction in directions "North-South" and "West-East". Thruster has been operating about 1000 hours in the orbit.

Jointly with Saint-Petersburg State University, Scientific Research Center "Planeta" and Space Research Institute of the Russian Academy of Sciences it has been developed a technology of distant probing the temperature fields, humidity and concentrations of main small gas components in the atmosphere at using infra-red Fourier-spectrometer of the increased informativity as applied to advanced space means for atmospheric monitoring.
The technology provides recovery of vertical temperature-humidity field of the atmosphere an data on concentrations of the main "greenhouse" gases in the atmosphere with accuracies exceeding accuracies provided by existing analogs: vertical resolution - 1 km; error in temperature recovery lesser or equal to 1K; humidity lesser or equal to 10%; concentrations of "greenhouse" gases: O₃ lesser or equal to 10%; H₂O lesser or equal to 10%; small gas components lesser or equal to 20%.

A DC air plasmatron, designed for power up to 30 kW, has been developed. Uninterrupted operation (without replacement of electrodes) as high as 102 hours 40 minutes has been achieved.
A laser ignition system for multiple ignitions of oxygen/kerosene, oxygen/alcohol, oxygen/hydrogen, and oxygen/methane LRE propellants has been developed. A laser oxygen/kerosene igniter's 120 firings of specified off-duty ratio and frequency have been demonstrated.
Processes for an application of multilayer coatings and implanted nanostructures to flat surfaces have been developed. The processes can be used in LRE with the aim of gain in its operability and reliability.

October,2006
Keldysh Research Center in co-operation with leader Russian Space Industry enterprises is developing, manufacturing and testing ammonia heat pipes with long time life period. The profiles with capillary structure formed by various form axial canales are used in heat pipes.

Cryo-heat exchanger working on Neon was developed.
An experimental prototype of the lithium-ion accumulator storage battery at capacity of 50 A*hour and voltage 30 V was made.
An experimental prototype of the multifunctional engine for SPPS was developed and manufactured.
A system of laser ignition of oxygen-hydrocarbon and oxygen-kerosene LRE was developed.

September,2006
The book came off the press:
"Manned Mars Expedition" edited by Academician A.S. Koroteev, Moscow, Russian Academy of Cosmonautics named after K.E. Tsiolkovsky, 2006.- 320 pp with illustrations.
The book contains the first systematized presentation of the history of Mars manned expedition concepts and projects. The modern Russian project of manned Mars Expedition - MME - is stated. Main problems including the medical ones are discussed, ways to solve them are proposed on the basis of Soviet, Russian and International cosmonautics heritage. It has been shown the influence of technologies including the nuclear ones that have been developed for Mars expedition to the program of lunar outpost arrangement and effective space transportation system. Authors are involved into the tasks of the human flight to Mars within almost fifty years and share their experience in developments.
The book can be interested to specialists in rocketry and space engineering, students of corresponding specialities in higher education as well as all interested in history and outlook in space research and exploration.

A complex of experimental and calculation works was performed on investigation of the ice formation process on the oxygen tank cryogenic surface in LV "Soyuz-2" for Kourou launching site and estimation of ice formation velocity and antiicing measures efficiency.
Results of calculation investigations have shown that the surface of oxygen-filled cryogenic tank is iced with the velocity conditioned by the rain intensity and angle of raindrops fall. Calculated value of ice thickness per one hour can exceed 60 mm.
According to the experimental data, fluoroplastic-4-type hydrophobic coating of 0.6mm-thickness does not protect against rain formation because of high velocity of the first water layers freezing on the cryogenic surface coated by fluoroplastic-4 film.
Required efficiency of antiicing thermal protective coatings on the basis of tubular and laminar thermal protective material from synthetic rubber K-FLEX-ST of 6...20mm-thickness with small coefficients of thermal conductivity 0.038 W/(m*K) was experimentally determined.

Prime multi-chamber propulsion system with nozzle extension (variants) protected by the RF Patent № 2267026 (application № 2005104257 dated 17.02.2005). The patent is published in the bulletin "Inventions. Utility models" №36, 2005.

July,2006
Mr. V. V. Putin, President of the Russian Federation, issued a decree. By this decree Mr. A. S. Koroteev, director of Keldysh Research Center, is awarded the Order of Service to Fatherland in the 3rd degree for having contributed heavily to the development of rocket and space technology and for the honest labor in the course of many years.

May,2006
On the 15^th of May, 2006, 80 years have passed since an outstanding scientist in the field of rocket engine manufacturing and space power, the ex-head of power department of Keldysh Research Center, Chief Designer, Associate Member of the Academy of Sciences of the USSR, Vitaly Mikhaylovich Iyevlev was born.
After laying flowers to the V. M. Iyevlev's memorial plaque, a joint sitting of the Bureau of the RAS Section of Power, Machine building, Mechanics and Control processes and KeRC Research council's presidium has taken place. The sitting has been opened by the director of KeRC, Academician of RAS, President of the Academy of Cosmonautics, A. S. Koroteev.
At the sitting have spoken:
Academician-Secretary of the Section V. Ye. Fortov,
Academician B. I. Katorgin
Academician N. N. Ponomarev-Stepnoy
Pro-rector of MPTI E. Ye. Son
The first deputy of Chief Designer of NPO "Mash" V. P. Tsarev
Cand. Sc. (tech). A. B. Prishletsov.
The speakers emphasized on a valuable contribution to the Russian science, made
by V. M. Iyevlev, the great number of his disciples and his high humane characteristics.

February,2006
To support the issue of the Federal Space Agency Standard on fire safety of space stations inhabited modules, experiments using a mock-up of the installation "Skorost-M" were conducted to determine burning and extinction conditions for materials capable of smouldering and for those leaving coke when burning.
Proposals on a structure of the normative document on flameproof arrangement and flameproof operating conditions of inhabited modules of space transporters and orbital stations have been stated.

January,2006
Principal propositions on development of reusable oxygen-methane engine have been worked out. Piloted rockets' recoverable stages are proposed to be provided with engines fulfilled to the expander cycle where a turbopump unit is driven by a turbine running on methane heated in a chamber cooling passage. For the methane heating required by the balanced coordination of the cycle, a new configuration of a chamber, protected by RU patent No. 2254490, the priority of invention - September 25, 2003, has been proposed.
A tentative program of preparing and performing tests of the oxygen-methane demonstrator-chamber (of new configuration with an enlarged heat-exchange surface and at 10 tf of thrust) is presented.

Firing tests to investigate into hydraulic characteristics of a gas passage of a subscale oxygen-methane gas generator were conducted. The gas generator involved a turbine-nozzle simulator and cooled nozzle simulating a chamber injector assembly.
The firing tests were conducted on the gas generator for determination of a condensed phase in the form of solid carbon (soot) with using optical method and filtration of generator gas sampled out of the gas generator. An amount of soot deposited onto the turbine-nozzle non-cooled simulator was determined through weighing of simulator bushes before and after test. In the operating temperature range of generator gas from 600 to 1200 K the content of soot, obtained with optical method, comprised approximately 0.02 to 0.08 %.

December,2005
Optimisation of the main directions in development of the advanced algorithms, sensors and autonomous control systems equipment for LRE & LPS performing the functions of the Diagnostics & Emergency Protection System was made. The program for identification of the oxygen-kerosene engine quasi-stationary mathematical model on the firing test results was developed (2^nd edition). A procedure of the engine spectrometric diagnostics in the course of the firing tests was developed. "Spectral portraits" of the engines as well as for express-assessment of the firing test results were prepared. A procedure of EP spectro-photometric diagnostics was developed. Experimental equipment for EP spectro-photometric diagnostics was manufactured and tested.

Stand experimental investigations of oxygen-methane fuel multiple ignition in the prechamber were performed.
It has been experimentally shown that the mixture of methane with oxygen stably ignites by high-voltage plug mounted in the injector head of the prechamber within the wide range of average-mass mixture ratio Km=30...80, Km=0.6...1.2.
It has been obtained that reliable ignition of oxygen-methane mixture occurs with keeping the serviceability of the hardware after multiple operating cycles.

Calculation-project studies of the tanks and ball-vessels from structural composites were made. Project-technological methods to form load-carrying shells of the tanks and ball-vessels on the basis of structural composites were investigated. Comparative analysis of the mass characteristics of the tanks and ball-vessels on the basis of structural composites and metals were presented. Combined as well as toroidal design schemes of the tanks were considered.

The analysis of domestic and foreign materials on research of power-propulsion systems for Mars complex on the foundation of nuclear energetics was performed. Comparative analysis of the various systems of Mars complex power-propulsion support on the foundation of the nuclear power sources was made.

Firing tests of the laboratory model of multi-mode Hall-effect thruster of the nominal power 5 kW were performed. Characteristics of the thruster within wide ranges on thrust (240...360 mN) and specific impulse (1400...2700 s) were studied. The given thruster can be a prototype while developing propulsion systems for interorbital tugs as well as for the tasks of the heavy geostationary vehicles correction.

Experimental determination of the HF oscillations occurrence mechanism in the LRE combustion chamber was made and the recommendations on their elimination were issued.

Earlier made demonstration installation for production of technical hydrogen as well as synthesis gas continues.
Complex tests of three main aggregates were fulfilled: generator of gas mixture (H₂, CO, residual CH₄, CO₂), shift reactor for vapor conversion CO into CO2, scrubber for purification of gas mixture from CO₂.
Stable efficiency of 75% in hydrogen production has been confirmed (regarding combined hydrogen incorporating into fuel - methane, water, oxygen). Installation output on hydrogen is 14 nm³/hour, on synthesis gas - 24.6 nm³/hour.

A procedure of the accelerated life tests for Hall-effect thrusters with ceramic discharge chamber has been developed. It provides reduction of the thruster life testing reduction in 5 times. The experimental check of the given procedure on an example of 500-hour life tests has shown that the difference of the output engine characteristics got in direct and accelerated life tests is within the measurement error.

October,2005
Calculation-theoretical and experimental investigations of the possibility to use super-cavitating blade pre-cascades have been performed.
Experimental investigations of the pump model stage with super-cavitating impeller in assembly with axial-radial type impeller confirmed the possibility to use super-cavitating impeller in LRE pump as pre-impeller instead of usual inducer. In so doing, traces of cavitation erosion on the blades were absent, the stage had high hydraulic efficiency (>0.85), the value of cavitation specific speed was C_cr=2600. Numerical simulation of the working process in a flow core element of the combustion chamber in the oxygen-kerosene engine with coaxial jet-centrifugal and centrifugal-centrifugal injectors at staged combustion cycle with oxidizer generator gas has been performed.
In the work course the peculiarities of the working process detailed picture at using the injectors with swirling of both kerosene and generator gas were investigated by calculations. The assessment of the combustion efficiency in a flow core element was conducted. The given results are compared with the calculation results of the working process for injector initial variant where only kerosene swirling occurs.

On October 14^th, 2005 the Conference held to hear reports and elect new officials of the Russian Academy of Cosmonautics named after K/E/ Tsiolkovskiy. Academician A.S. Koroteev, Director of the Keldysh Research Center, has been elected President of the Russian Academy of Cosmonautics.

September,2005
The design of the liquid rocket engine combustion chamber injector head has been developed. It is protected by the RF Patent № 2225947 (application № 2002116120 dated 21.06.2002). The Patent is published in the bulletin "Inventions and the useful models" № 8, 2004.

A full-scale functional article of the high-resolution IR-spectrometer onboard calibration module has been manufactured (as applied to the developed Fourier spectrometer IKFS-2 for temperature-humidity probing of the atmosphere). The functional article consists of radiator-black body model with aperture 78 mm, two temperature sensors of TM 344 type, heat receiver, film heater, thermo-regulation system. Measurements of radiator brightness spatial distribution on the aperture have been performed.

Tasks statement on calculation -theoretical investigations of the structural materials ignition process in LRE heat-stressed aggregates.
Directions of the investigations are formed on the basis of the experience available at Keldysh Research Center, analysis of the operational data and review of the designs ignition cases with the purpose to search the effective measures for fire hazard localization.

Firing experiments on studying the regenerative cooling by fuel of the cylinder section in the 2kN-thrust model oxygen-methane combustion chamber at lifetime higher 1000 s have been realized. Hydraulic characteristic of the cylinder cooling passage did not changed for the total operation time of the model combustion chamber.

The first stage of experimental investigations is completed. It was to justify longevity of rolling bearings in the high-pressure liquid oxygen flow at calibrated axial and radial forces. The purpose of the investigation was determination of bearing lifelength when operating in liquid oxygen to correlate the experimental lifelength and designed longevity. The lifelength of tested bearings amounts to 600...1000 seconds. By the test results the standard longevity was determined to be 3-4 times more.
Based on results of narrow-band frequency analysis of vibrations in the "Treniye" (Friction) facility, the investigations performed confirmed that to predict the early stage of fatigue life of races, two values could be used: the number of main and intermodulation discrete components which are related to the rate of balls passing over the defect race, also the total amplitude of the above-mentioned peaks.

Using the developed procedure the stage of experimental investigations was completed to confirm the predicted small-cycle strength of structural materials under thermal and power loadings .The materials are intended for structural elements of reusable LRE turbopump units. Fifty tests were carried out by a special run sequence. Based on test results the stressed-and-strained state of sample material was determined. Recommendations were worked out for improvement of the "Procedure for predicting life of low-cycle strength of structural materials".

August,2005
A new bench test bed is developed. It facilitates experimental investigations with coaxial methane ( hydrogen ) jets, 3 mm and 5 mm in diameter, and air at Reynolds numbers ranging from 200 to 7000.
A series of adjustment experiments has been carried out using methane and air.The photographs of plume which are obtained in the course of adjustment experiments have been processed. The processing has shown the validity of the method chosen to register the flame jets(by the digital photo camera and the digital video camera).
Results have been obtained which attest the impact of cocurrent air flow on the plume length , on the completeness of combustion process with an increase in the cocurrent flow Re number. Parameters of the combustion stall in experimental conditions have been determined. Results of the experiment are interesting for specialists in fundamental research of combustion in jets.

The subject of integrated physicochemical investigations was properties of materials and samples than had been exposed on the "Kromka 1-2" tray in the zone of the ISS service module pitch thruster impact (the stage of space experiment "Kromka 1-2").
The comparative analysis of dynamics of contamination of the trays "Kromka 1-1" (~ 3-month exposure) and "Kromka 1-2" (23-month exposure) with products of incomplete combustion revealed identical character of contamination that verifies effectiveness of gasdynamic devices which reduce the contaminating effect of LT LRE. It also revealed that protective devices retained their lifetime from the moment of their installation (2.5.01.02). Using the results of the "Kromka 1" space experiment and results of ground tests predictive-theoretical models were refined. These models are purposed to predict the contaminating impact of impulse LT LRE on space stations and spacecraft.
Test calculations of parameter distribution in the jet of the 13 N-thrust LT LRE were performed. This LRE is widely used on various spacecraft, orbital transfer vehicles and the ISS.

July,2005
A special method of space experiments on processes of material combustion in microgravity on board the ISS has been developed. The method offers capability of investigations into combustion of flash-resistant materials. The method involves a list and the order of operations for preparation of equipment, performance of space experiments and completion of work.
The laboratory mockup of the experimental facility "Skorost-M" was used to optimize the main stages of the method including ignition of material samples with a descending current in the combustion chamber at velocities up to 60 cm/s.

June,2005
The first version of the draft program on research and development "Complex target program on research and development in space energetics for 2006...2015" (solar and chemical energetics) has been developed. This program includes complex investigations on onboard energetics and works on updating and manufacturing of the new types of high-performance elements in the power supply systems for articles of rocketry and space engineering. The works point towards solving the problems of Federal Space Program of the Russian Federation for a period up to 2015.

The program for flight tests of the KeRC-developed T-120 thruster aboard the geostationary communication spacecraft "Express A4" developed by the M. F. Reshetnev NPO for Applied Mechanics has been successfully completed. The spacecraft was put into orbit on June 10, 2002. At present the thruster is used for corrections of satellite orbital inclination.

Requirements to operating modes of Hall-type thrusters of increased power (~10 kW and more) on the advanced geostationary heavy-class space vehicles at the high level of power to weight ratio were analyzed. It has been demonstrated that use of electric thrusters of power ~6.4...10 kW at available lifetime 7000...5000 hour and optimal specific impulse 2400...3000 s in the operating mode for keeping the 10...14t spacecraft aiming point within 15 years provides minimum costs of mass on electric thruster at the level of 9...10% of spacecraft mass. Use of electric thruster of power ~10...11 kW at specific impulse 1500...2000s for orbit raising of spacecraft at power to weight ratio ~ 5 kW/t within 150...360 days from the intermediate orbit into GSO that allows one to increase the payload mass determining in the work as spacecraft mass into GSO at subtracting electric thruster mass in 1.5...1.7 times as compared to the variant of standard insertion of LV "Proton-M" with booster "Briz-M" into GSO.

Optimization of the main directions in development of the promising algorithms for autonomous control systems in LRE and LPPS for the purposes of diagnostics and emergency protection was performed. Recommendations and proposals on introduction of LRE spectrophotometric diagnostics while the firing tests of the engine. Some typical measurement results of LRE exhaust plume signature spectra are given. Experimental functional article of the equipment for LRE spectrophotometric diagnostics was manufactured and tested.

Expert-analytical,calculation-theoretical and research works on solid membranes of the new class have been performed. In their course the target points as well as new progress directions are determined for development of the main principles in technology providing the capability of producing the electrochemical generator at power up to 50 kW and the cost meeting the commercial use requirements.
Investigations on comparison of main parameters of the new-type membranes with presently used membranes of "Nafion" and MF-4SK type are fulfilled.
Technologies of producing the membrane of specified properties are considered.

A small-scale installation for production of hydrogen due to thermochemical transformations of methane with the design output of 3 kg per hour has been developed. The hydrogen production efficiency of the installation was verified by testing and comprised 82%.

April,2005
A power module has been designed and manufactured which is made of four prismatic lithium-ion accumulators of rated capacity Crated = 50 A*hr.
A voltage control and grading device has been developed and manufactured which provides voltage control and grading in accumulators which are part of the power module.
The accumulators and the voltage control and grading device are arranged on the cold plate which maintains the prescribed temperature level in charge and discharge modes.
The accumulators which are part of the power module underwent calorimetric studies. Investigations of electric characteristics of accumulator assembly were performed at various charge and discharge currents.

At present, the tendency to use plasmatrons for processing of industrial, domestic and medical wastes has gained strength.. Owing to the high temperature provided by plasmatrons the degree of waste processing can be significantly improved and the quantity of detrimental emissions can be reduced . The use of "Zvezda" plasmatrons, which are under development at KeRC, for these purposes seems very promising. A prototype of respective plant for waste processing is developed, also new highly-effective technologies are developed:
- plasma-cluster technology for applying heat-resisting coatings and those resistant to chemicals on the basis of refractory materials;
- technology for producing basalt staple to manufacture high-quality basalt wool.

March,2005
The firing of a 20 N-thrust rocket engine operating GO₂-GH₂ and GO₂-GCH₄ was studied experimentally. Multistep firings were realized by means of a glow plug.
The work performed resulted in obtaining a complex of experimental data on characteristics of firing in atmospheric conditions and in vacuum at nominal and low (less than 0.2 MPa) delivery pressures, also with propellant supply electric valves opening not coincident in time. Optimum conditions were found for realization of a reliable multistep firing of the thruster using a glow plug of 4.0...6.0 W power.
Results of studies can be used in development of thrusters operating on oxygen-hydrogen (methane and other hydrocarbons) which are designed to control orbital transfer stages and other orbital facilities.

December,2004
Main principles of LRE "hot" assemblies simulation by means of firing tests of subscale chambers and gas generators are proposed. Substantially lower mass flow rates of oxygen-methane propellants are needed as compared to full-size engines. A two-stage concept for development of an oxygen-methane demonstrator of 7 tf thrust is detailed.

Experiments were conducted on investigation into regenerative cooling of subscale oxygen-methane chamber cylindrical part with fuel. The combustion chamber features 2 kN thrust and lifetime of more than 150 seconds. It was traced that the methane temperature at the end of model cylinder cooling passage being 593 K, the temperatures of cold and hot walls were 930 K and 885 K, respectively. Within the subscale chamber running time of 133 seconds the hydraulic characteristic of cylinder cooling passage did not change.

"Program work progress on development and manufacturing the advanced information-diagnostic systems with emergency protection functions in liquid rocket propulsion systems (LRPS) up to 2013" was developed.
Optimisation of the main directions in development of perspective sensors for autonomous control systems in LRE and LRPS for fulfilment of the functions of diagnostic emergency protection system was realized. Comparison of the results obtained at mathematical simulation with the results of LRE firing tests was made. Their convergence was estimated.
Testing the procedure on determination of the structural material traces on spectra of LRE flame radiation was continued for express-estimate of the stand firing tests.
Experimental prototype of equipment for spectrophotometric diagnostics of electric propulsion was developed.

"Studying the combustion chamber of oxygen-hydrogen low-thrust rocket engine RDMT-M with axial feed of heated hydrogen. Investigations of life and thermal characteristics of pulse plasma engines"
Cooperation KeRC-NIIPME fulfilled the stage of investigations on making the pulse plasma engines (PPE) on solid propellant. Ratios of PPE elements temperature from duration of operation and the total number of operating cycles were determined at work with repetition frequency of the operating cycles 0.5...2Hz and power 20...80W as a result of the first stage in PPE tests on conventional propellant (PTFE). It was shown that while working at repetition frequency of operating cycles 0.5 and 1 Hz, the PPE elements temperature had been at a permissible level. Influence of degree of rarefaction in vacuum chamber to PPE characteristics was investigated with the purpose to test the procedure of thermal and life tests of PPE on alternative propellant. Ratio of thrust efficiency from the degree of rarefaction in the vacuum chamber was experimentally determined. It allowed one to uniquely interpret the results of thermal tests. Preliminary assessment of influence of heating the alternative propellant to PPE characteristics was performed. An order and procedure for life and thermal testing were developed.
The results of these investigations can be used for studying the characteristics and at design testing of PPE.

The variants of ceramic compositions being the candidates for accelerated life tests as well as for increasing the life characteristics of discharge chamber in stationary plasma thrusters were chosen.
A procedure was developed and the experimental installation for research of coefficients of the materials spraying in plasma jet of Hall-effect thrusters was made.
Experimental investigations of spraying coefficients of traditional and newly proposed ceramic compositions were conducted.

The investigations on possibilities to increase the efficiency of auxiliary propulsion systems (APS) of space boost unit were conducted. Assessment of various variants of propulsion systems at autonomous feed of APS engines and at cyclic refuelling of APS tanks by oxygen from the systems of prime engine was fulfilled for the specified energy requirements with due regard to high requirements to economical characteristics and realizability of the project. The advantage of partial integration of the feed systems of APS as well as prime engine; efficiency in using gas tanks from composites and bi-component low-thrust rocket engines on fuel "oxygen-methane", "oxygen-naphthyl (ethanol)" were shown.
The investigation results can be used at development of propulsion system for the systems of orientation and stabilization in space boost units at increased requirements to energy-mass and ecological characteristics.

October,2004
A Session of Scientific and Technical Board of the Federal Space Agency on liquid and electric propulsion was held at Keldysh Research Center under the chairmanship of Academician A.S. Koroteev on October 14^th, 2004. The session was devoted to the analysis of using the accelerated tests at different stages of electric rocket engines experimental development. Participants of the session, the respresentatives of the leading Russian organizations-developers of electric propulsion noted the topicality of development and introduction of the methods of EP accelerated tests for reduction of terms and cost in making the new models of the engines.

The features of heat transfer in the combustion chamber and nozzle of the advanced LRE working on cryogenic propellant components "oxygen + hydrogen, oxygen + methane (liquefied natural gas)" were analysed. It was shown that with due regard to the necessary operating life, the combustion chamber must have film cooling in the area of throat. Preliminary estimate of the required flow rate for film cooling was performed. The recommendations on possible increase in cooling efficiency of the initial part of the combustion chamber and the initial part of the nozzle extension were developed.

A series of approximate methodical approaches to solving the tasks of technical-economical analysis at determination of the rational areas of the engine use was developed. A standard breakdown of expenditure for launch vehicle start-up and for the cost of life cycle of the launch vehicle or propulsion system was laid into the foundation of the developed approaches. It reflects the modern level and standard relative enlarged expenditure distribution for manufacturing of launch vehicle stage, design of stage and propulsion system. The used efficiency criteria are presented in dimensionless relative kind (with regard to the similar index of the basic reference variant of the launch vehicle, propulsion system or engine).
In the general case the goal of the developed methods is to define the boundaries of the equal efficiency and the areas of preferableness depending on the parameters characterising the basic variants of the launch vehicle, propulsion system, engine. Usability of every among the developed approaches is illustrated on the definite examples at analysis of the obtained results.

A method of simulation of solar arrays radiation at interorbital transport modules was developed on the basis of reproduction of spectrum characteristics of energy transfer from the radiating particles to the atoms of semi-conductor. The essence of the method is in proposition that if spectra of energy transfer from radiating particles to the atoms of semi-conductor in all areas of semi-conductor structure in two cases at different radiation effect to the identical photo-converters, then electric characteristics of photo-converters after radiation will be equal. Calculation of energy transfer spectra with due regard to the design of solar array is made by Monte Carlo method at using the classical models of ionisation deceleration and shape-elastic scattering of the charged particles.

September,2004
The calculations of the liquid hydrogen tanks strength in booster of "Yastreb" type were fulfilled for different cases of destruction. The analysis of the project schemes to reinforce the power shells, the materials of thermal protection and liner was performed.

A stage of predictive studies for development of methodology for testing on KeRC test facilities has been completed. The purpose of tests is prediction of low-cycle strength of LRE design stressed elements . Test regimes are determined including conditions of startup (heating of structure) and shutdown (cooling) which determine the rate of heating and cooling of the tested assembly made from a nickel alloy with specific physicochemical and thermophysical properties. Results of analysis of the tested assembly heat and stress state are used to balance parameters of test facility operation with variation of heat carrier flow rate against duration of tests and the number of cycles ( startings), which determine symptoms of defects.

Within the limits of work on introduction of the filter in the structure of engines of 11D511 and 11D512 types the scope of work on confirmation of filter serviceability is determined. The filter is mounted at the hydrogen peroxide pump inlet in bench tests of engines of 11D512 and 11D511 types. Results of filter development were analyzed and compared, they are presented in the final report on development. Proposals are worked out on introduction of the filter in the structure of series-produced engines.

A stage of adjustment tests was completed on the Treniye (Friction) test facility for the on-going studies of durability of radial thrust bearings in liquid oxygen under calibrated axial and radial loads. Experimental data are obtained on serviceability of ball bearings in prolonged tests with total bench hours exceeding the standard durability of a ball bearing.
A stage of tests of gasdynamic ignition devices for non-hypergolic propellants (gaseous oxygen-hydrocarbon fuel) is completed. Results are presented on reliable ignition over the range of mixture ratio which is smaller and higher than the stoichiometric value.
The delay in propellant components ignition does not exceed 0,2 -0,4 s. The time of warming up is not over 1-2 s.

August,2004
On July 31, 2004 major executives of the Federal Space Agency (FSA) of Russia visited Keldysh Research Center (KeRC). Among them were A. N. Perminov - head of FSA, N. F. Moiseyev, V. P. Remishevsky, G. M. Polishchuk - deputy heads, Yu. G. Gusev - head of department, Yu. Ye. Levitski - deputy head of department, A. Ye. Shilov and A. V. Golyanovskii - assistants to the head.
Academician A. S. Koroteev, director of KeRC, told them the history of the Institute and showed exhibits of the KeRC's exhibition.
The detailed report treated of main advances of KeRC in recent years, set forth plans up to 2015 and emphasized the most important lines of work.
They are
- maintaince of reliability of engines for launch vehicles (LV) and the boosters Proton, Soyuz, Zenit, Briz, Fregat, DM;
- assurance of quality and reliability of engines for newly developed and updated LV and boosters Angara, Soyuz, Proton-M, Onega, KVD 1M3;
- participation in promising development projects such as reusable engines, oxygen/hydrogen LRE, electric rocket thrusters, a solar power-propulsion system, solid-propellant motors operating on new propellants, new materials for engines and power systems.

Attention was also centered on interesting prospects of advancement of activities related to production, storage and the use of hydrogen in propulsion and power systems, motor transport, also works attending the problems of ecology, development of systems and plants for production of drinking water.
The economic situation of KeRC was analysed, main sources of financing were stated (contracts with the FSA and Ministry of Defense, international contracts and contracts on development of technical consumer goods).
The FSA management familiarized themselves with the experimental test facilities of KeRC where some experiments were demonstrated.
When summarizing the meeting, the FSA management approved of the main lines of KeRC's work, noted the high level of research projects and competence of the personnel, the stable economic status of KeRC and charged the KeRC's management to prepare proposals on updating its infrastructure.

To fit the geostationary spacecraft of heavy-weight class, the analysis of requirements to operating characteristics and to life of multimode average-power Hall thrusters, as well evaluation of the effective application thereof as part of EPS providing the SC orbit-raising from intermediate orbit to GEO and correction of GEO parameters in the course of 15 years active life were conducted. The optimum value of specific impulse of cruise electric thrusters by insertion was equal to 1500 s, the optimum value of specific impulse in working orbit correction - to ~ 3000 s. A decrease in specific impulse in the correction mode down to 2400 s results in an insignificant increase in EPS mass at the level of 1.5 % of its minimum value.

Experimental data on the allowed quantity of metal particles with size less than 1.5 mm in the oxidizer pump passage were obtained from results when using the test facility "Friction" at KeRC.
The particle warming up due to friction heat, governed by experimental conditions, is calculated with solving nonstationary heat-conduction problem on motion of the point heat source with a constant velocity over surface of semi-infinite body.

On the firing vibration-combustion facility, the experiments were carried out. It is revealed that under the subscale conditions of vibration combustion, mounting of special fuel-metering jets of Laval-nozzle type with high pressure losses and subcritical gas flow, being installed at the inlet of combustion chamber injector in oxidizing gas line, can liquidate high-frequency transverse oscillations.

Design studying and experimental investigation of rocket engine on gaseous oxygen and hydrogen at ~ 20 N of thrust were carried out. The engine can be repeatedly started with the aid of surface ignition.
The work fulfilled resulted in obtaining experimental data on characteristics of a low-thrust rocket engine (LTRE) starting in atmospheric and vacuum conditions with changing pressures and mixture ratios within broad ranges, as well with a time difference in opening of propellants feed valves. A power consumption of the spark plug comprised 3 to 4 W at a voltage 1.0 to 1.2 V. The filament temperature at which propellant ignition took place made up 1100 to 1250 K. The operating scheme of LTRE where the conditions required for propellant ignition are produced at the instant of engine starting was realized. If operation of the engine is proceeding in steady-state mode, the spark plug is under the atmosphere of one of propellants, outside of the combustion zone. The investigation results may be used in development of LTRE for control of oxygen-hydrogen orbital vehicles.

The analysis of ground test results and sufficiency of measures applied for removal of defects of upper stage "Fregat" engines was carried out.
Estimated life characteristics and reliability of engines were obtained.

July,2004
The meeting of the Moscow administration's commission on scientific-technical policy under the chairmanship of Academician O.M.Nefedov took place on July 15 at KeRC.
Reports on the outlooks for advancement of hydrogen energetics and its application in Moscow urban economy were made by:
- Minister of Moscow Administration, Bochin L. A.;
- Director of KeRC, Academician Koroteev A. S.;
- Deputy Chairman of Executive Committee for International Partnership on Hydrogen Energetics, Head of Laboratory at the Institute of High Temperatures of RAS, Malyshenko S.P, Cand. Sc. (Tech.);
- Deputy Director of the Institute for Hydrogen Energetics and Plasma Technologies, Korobtsev S.V.;
- Head of NAMI Division of spark-ignition engines and hydrogen power systems, Professor Kamenev V. F.;
- Director of Blagonravov Institute of Science of Machines of RAS, Academician Frolov K. V.;
- Director of Institute for Chemical Physics problems of RAS, Academician Aldoshin S. M.;
- Director of Frumkin Electrochemistry Institute, Professor Grafov B. M.;
- Director General of Joint Stock Company of the safeguard-systems firm, Ishutin V. P, Cand. Sc. (Tech.).
The conference was summarized by the Moscow Administration Minister Panteleev Ye. A.
Academician Nefedov O. M. the Chairman of Commission, addressed the meeting with concluding remarks.
From the work results the Commission has drawn the conclusion of exceptional promising prospects in the near future of production methods, storage and use of hydrogen for the energetics branch of Moscow urban economy.
It has been proposed to organize the commission to elaborate the complex, long-term program of application of hydrogen technology in the energetics complex of the city and its transport.

Activities on the manned Mars mission over a period 2001 to 2003 were generalized and analysed. The works were performed in co-operation with RSC "Energia" and TsNIIMash. The orbital-landing scenario of the mission was justified, single- and two vehicle missions with the date of realization in 2018 - 2020 were considered. Schemes of the mission on the basis of LRE, NRE and Solar PS were studied. All the required characteristics of propulsion and power systems were determined.

Shaping of radiation-cooled nozzle extension of engine was conducted. Power characteristics of engine chamber were determined to the procedure updated by results of the comparison between designed and experimental data. Temperature conditions of radiation-cooled nozzle extension were determined, the recommendations on choosing structural material issued. It has been revealed the introduction of radiation-cooled nozzle extension in the sustainer design may allow increasing payload mass to be injected by the "Fregat" booster.
A generalized curve of specific impulse raising was derived which would allow evaluating a possibility of a further rise in specific impulse with consideration for nozzle mass at different lengths of the nozzle extension.

Researches in optimization of electric propulsion system performance for the electric-propulsion transport-and-power module providing GEO insertion of spacecraft and subsequent correction of working orbit were conducted.
The calculation of efficiency values for the combined scheme of GEO insertion of spacecraft with using chemical orbit transfer stage and orbit-raising EPS to fit variants of application of launchers of medium-weight ("Sojuz-2") and heavy-weight class ("Proton-M") was conducted.

The variant of solar thermal propulsion system (STPS) with using pneumatic pump units for liquid propellants supply instead of electric pumps used in the basic variant was proposed. In the upper stage of the "Onega" launcher replacement of electric pumps in STPS by pneumatic pump units allows GEO-inserted SC mass to be increased by ~90 kg. It was also established that a possible significant rise in thrust of STPS equipped with pneumatic pumps may essentially expand the field of its application. It was demonstrated that the STPS-based upper stage in the "Sojuz-2-1B" launcher makes it possible to put the SC of 600...610 kg mass with a great hyperbolic excessive velocity of 10 km/s in interplanetary trajectory.

The investigations were fulfilled on analysis of the contamination effects of the orientation engines (using fuel components NTO+UDMH) to the external surfaces of ISS.
1. Using the results of time analysis of video-images of the plotting card "Kromka 1-2" photographed through the port-hole of module "Pirs" onboard ISS it was analysed the dynamics of its contamination by the incomplete combustion products of ISS engines for pitching. On the foundation of the obtained results it was analysed the functioning of gasdynamic protective devices mounted on the engines of the service module onboard ISS.
2. The model of evaporation of contamination products of propellant components incomplete combustion from the surface of the service module onboard ISS with due regard to the change of its fractional composition including the toxic constituents was refined on the basis of the chemical analysis results of the properties of the samples delivered to the Earth in the course of the stage of space experiment "Kromka 1-2" as well as earlier received results.
3. Experimental investigations on determination of the modes of film separation of incomplete combustion propellant products from the edges of low-thrust liquid rocket engine nozzles under the conditions simulating the low-thrust liquid rocket engines operation in space at using the model liquids were performed at the cryogenic-vacuum test facility 246 in Department 3. As a result, the minimum Weber numbers were determined at which there is film separation from the edges of various configurations. Also the data were received on the angles of scattering the drops separating from the edge.

Research and comparative analysis of radiation degradation of solar arrays with silicon photo-converters on multi-pass trajectories of interorbital transfer with multiple passing the Earth radiation belts were fulfilled as applied to the task of spacecraft insertion into GEO from the cosmodromes Plesetsk and Baykonur by launch vehicle "Onega" at using transport modules (TM) on the basis o solar electric rocket engines and thermal propulsion systems.
The capability to reduce radiation loads at the section of insertion by choice of rational intermediate orbits was shown for TM with electric propulsion system. In particular, as applied to case of launch from cosmodrome Plesetsk for a variant of TM with electric propulsion system in the area of characteristic velocity reached by electric propulsion system 2...2.7 km/s (characteristic velocity of the chemical boost block 3...3.5 km/s) it is possible to decrease in 1.5...4 times the magnitude of solar array power fall at the insertion trajectory by choice of intermediate orbit differing from optimal in energy. In so doing, the losses of the SC inserted mass to GEO will not exceed 1%.

A mathematical model to assess the thermal state of basic energy module 4LIA-50 on the basis of lithium-ion accumulators LIA-50 of prism form at cyclic charge-discharge operating mode has been developed. The calculation results have shown that for accepted construction of energy module and its cooling from one lateral side (K_TO~1000 W/m²*K), maximum heating of the accumulators will not exceed 30° at discharge current up to 0.8C.

June, 2004
The report prepared at Keldysh Research Center contains the results of development of schemes and conceptual documentation for the device of power supply. Prototype of the device of power supply on the basis of chemical current sources (lithium elements of ER20S type) was manufactured according to the developed documentation. The test program was developed and on its basis the tests were fulfilled. They have shown that the prototype provides power consumption in conformity with work cyclogram.
Full-scale functional article of the combined device of power supply on the basis of functional article RITEG-238-FT with electric simulator of radioisotope current source and storage battery on the basis of nickel-metal-hydride accumulators of AAHC-UC2 type was developed and manufactured. The tests of power supply functional article were fulfilled. They have shown that the functional article of the device provides the specified work cyclogram at necessary voltages and current consumption of the load.

A procedure of thermal state of the film cooling supply unit with due regard to fuel decomposition on the cooled surfaces of the combustion chamber and availability of radiation flow has been developed.
The results of testing engine RD0124A №5APR were analyzed and the probable causes led to emergency stop were determined.
Computation of the thermal state of the firing wall in the combustion chamber in the areas of the first jet screen zone and throat was made and analysis of efficiency of the already introduced measures and measures under introduction was fulfilled. The recommendations on further updating of the combustion chamber cooling in engine RD0124A within the guaranteed lifetime were developed on the given computation.

Classification of pressurized compartments in manned transport space vehicles and orbital stations on their purposes and working conditions determining their fire hazard were performed.
Experimental and theoretical investigation results of the main factors determining the processes of ignition, combustion, thermal destruction and fire suppression of the materials were analyzed and generalized. On that foundation, the main criteria of fire safety for pressurized compartments in manned transport space vehicles and orbital stations of various types were established.
The results of experimental investigation of the fire safety support system for habitat pressurized compartments in manned transport space vehicles and orbital stations were generalized on full-scale models including the conditions of the orbital flight.
Autonomous tests of laboratory functional article of small-sized laser interferometer were performed.

May, 2004
Calculation-theoretical and experimental studies of mixed-flow impellers for high-rotation pumps in LRE have been conducted.
The recommendations were developed on calculation and designing the mixed-flow impellers where it is possible to provide the required length and form of blade at great ratio of impeller diameter in the inlet to the diameter of impeller in the outlet (D₁/D₂> or = 0.7) on the foundation of the experience in making the pump axis-radial impellers providing combination of high economical efficiency at high anti-cavitation properties and low level of pressure pulsation in the outlet from the pump.
The tests have shown that the pump with mixed-flow impeller without preinducer has economical efficiency at the level 0.75-0.8, high anti-cavitation properties (cavitation coefficient of specific speed 2000-3000) and low level of pressure pulsation in the outlet from the pump - no higher 0.7%from the head of stage.
The results of studies can be used at development of high-efficiency pumps for advanced LRE.

Experimental studying of interaction between stationary pyrographite ring and rotating disk from nickel alloy ЭП202 in liquid oxygen at loading by contact force up to 450 kg was made.
Calculations of non-stationary heating of the tested construction elements at using software complex COSMOS 2.8 in wide range of determining parameters were performed: intensity of heat source, thermophysical properties and cooling conditions of rotating disk.
It was shown that state of contact surfaces of ЭП202 and pyrographite ring correspond to heating because of friction not exceeding 500°C at loading by force up to 450 kg within 11s.
Serviceability of the contacting couple of materials in LOX is provided at calculated power of friction up to 1000 W/m² and time of the contact up to 11 s. The research results are used for characterization of closed shaft seal reliability in oxygen engines RD191, RD180 and RD520.

March, 2004
Joint session of Scientific and Technical Board of Keldysh Research Center and Interdepartmental Scientific Board of the Russian Academy of Sciences and Federal Space Agency on the problems of space energetics was held on March 17, 2004 at FSUE "Keldysh Research Center" chaired by Academician A.S. Koroteev. The proposals presented by PhTI named after A.F. Ioffe on the work program "Soal arrays on the basis of cascade photo-converters of efficiency up to 30% and life 10-15 years were discussed on the session. The participants of the session: the members of Scientific Boards, representatives of PhTI named after A.F. Ioffe, SPA "Kvant", OAO "Saturn" and organizations-developers of space vehicles. In its decision, the Board has noted importance of making the domestic arrays with cascade photo-converters and has recommended to developing a special objective program.

March, 2004
In March 2004, at FSUE "Keldysh Research Center" the results of the works performed within 2001-2003 on the complex research work "Experimental and calculation-theoretical studies on updating the energy-mass and life characteristics of solar arrays and chemical current sources of solar power stations onboard space vehicles of scientific, socioeconomic and double-purpose" were summarized. The final scientific and technical report was issued where there were the investigation results performed within the indicated period by Keldysh Research Center in cooperation with RSC "Energiya", NPO of Applied Mechanics of MKB, NPP "Kvant", OAO "AVEKS", IPN RAN, and other organization. The main directions of the performed studies were: complex investigations of power supply systems of space vehicles, experimental and calculation-theoretical studies on updating of characteristics of solar arrays, nickel-hydrogen and lithium-ion accumulators, elements of equipment of electric power conversion, regulation and control, project investigations of advanced electric power sources, investigation of principally new installations for hydrogen production, etc. The main directions in continuation of the studies on the subject were envisaged.

March, 2004
Electric propulsion systems (EPS) on the basis of pulse plasma engine working on the traditional propellant (Teflon) have the least mass in comparison with the other types of EPS in the area of total impulses up to 60 - 70 kNs.
Use of alternative propellant proposed by Keldysh Research Center will allow one to expand this area in 2 - 3 times.

February, 2004
The tests of the model LRE working of oxygen and hydrogen with the nozzles of great nozzle expansion area ratio which are made from carbon-carbon composite and siliconized composite at simulation of the high-altitude conditions are fulfilled. The tests have shown that the siliconized nozzles are the most stable to ablation. High efficiency of using the nozzles made from carbon-carbon composites is confirmed by successful launch of the booster unit under the program "Sea launch" by RSC "Energiya".
Comparative tests of the stand patterns of the models of impulse plasma thrusters of erosion type on the traditional (teflon) and alternative propellants that had been fulfilled within the range of power capacities of the accumulator 35-100 J were finished. It has been shown that use of alternative propellant allows one to increase thrust efficiency in 1.5-2 times. At power capacity 40 J, thrust efficiency was 21.6%.
The work on technique and a complex of the programs on calculation of the parameters of reaching the mode by oxygen-hydrogen expander-cycle LRE was completed. The complex includes the modules of the parameters calculation: a) fuel components feed system, b) flux and thermal state of hydrogen in the cooling jacket channels of the combustion chamber and nozzle, c) heat exchange and warmed-up state of the walls in the cooling jacket, d) flux of the combustion products in the combustion chamber and nozzle. The technique assumes that hydrogen after heating in the cooling jacket is used as a propellant for rotation of the TPU turbines and than as fuel it enters to the combustion chamber that causes the interdependence of the considered processes.
On November 18-21, 2003 at the Second International Scientific Conference "Rocket-space engineering: fundamental and applied problems" the specialists of Keldysh Research Center made the paper: "Methods of calculation of the heat protection of the nozzle blocks in SRM" where the development of a complex of mathematical models, adjoint numerical techniques and automatic program package for analysis of heat transfer, thermal state and thermochemical destruction of ablating heat protection of the nozzle blocks in SRM within the framework of the common methodical approach was presented.

January, 2004
1. Mechanism of interaction of structural metal alloys (steel, bronze,aluminum) with chemically active gas medium (oxidizer-rich or fuel-rich combustion products) at various levels of temperatures and pressure excess is determined. Recommendations on choice of alloy mark and methods of their effective protection are issued. 2. Analytical (by method of photocolorimetry and gas chromatography) control of the chemical substances used and formed at manufacturing processes is carried out.
3. The methods of design-theoretical optimization of the channels in blade pumps are developed.

January, 2004
Investigations on laser ignition of the various mixtures in the combustion chambers of rocket engines were made. Prospects in using impulse lasers for reusable engines were shown.
The measurements of K-phase content in fuel-rich oxygen-methane generator gas in different operating modes in the range of measurement of mixture ratio coefficient Km=0.2...0.42 were conducted. Relative in mass soot content in generator gas was ~(8...10)*10^-4 in the fulfilled experiments series, at measurements in the nozzle exit it had been ~(13,4...27)*10^-4 that substantially lesser than the calculations for the conditions of thermochemical equilibrium gave.

January, 2004
Block "Dynamics" intended for calculation of the transitional processes in LRE at engine transfer from one mode to another one was developed, tested and integrated into the LRE multifunctional computer simulation program system "AnaSyn 2.0 for Windows".

October, 2003
A membrane installation is developed which is protected by RF patent № 2198018(application № 2001125975 dated 24.09.2001).The patent is published in the bulletin "Inventions. Utility models'",№ 4, 2003

October, 2003
On October 30 and 31, 2003 Keldysh Research Center held festive functions dedicated to the 70th anniversary of establishment of Keldysh Research Center.
At the scientific and technical conference at KeRC, which took place on October 30,2003, after the opening address of B.V. Bodin, who is Head of Department of the Russian Aviation and Space Agency, director of KeRC A. S. Koroteev, Full Member of RAS, delivered the lecture "Seventy years in the forefront of rocket and space technology".
The paper stated the glorious creative way of KeRC since the day of its establishement and up to now and showed the main achievements of KeRC in training scientific specialists, support and development of main rocket and space systems, participation in tackling scientific and economic problems.
Lectures were also given by the following persons:
- Yuri P. Semyonov, Full Member of RAS, President of Korolev Rocket and Space Corporation "Energia";
- Boris I. Katorgin , Full Member of RAS, Director General and General Designer of Glushko Energomash Research and Production Association;
- Alexander N. Kirilin, D. Sc. (Tech.), Director General of Progress State Research and Production Rocket and Space Center;
- Igor V. Barmin, D. Sc. (Tech.), Head and General Designer of Barmin General Engineering Design Bureau;
- Vladimir G. Degtyar, D. Sc. (Tech.), Head and General Designer of Makeyev Design Burea, State Rocket Center;
- Nikolai A. Anfimov, Full Member of RAS, Director of Central Research Institute for Machine-Building;
- Vladimir S. Rachuk, D. Sc. (Tech.), Director General and General Designer of Chemical Automation Design Bureau;
- Vladimir K. Karrask, D. Sc. (Tech.), Deputy Director General of Khrunichev State Research and Production Center;
- Anatoly V. Romashko, Chief Designer of Reshetnev Applied Mechanics Research and Production Association;
- Alexander A. Makarov, D. Sc. (Tech.), Director of Chemical Engineering Design Bureau.

The papers outlined main tendencies of advancement of space and rocket technology for the next years and pointed to the tremendous role of KeRC in solving practically all scientific problems in development of space and rocket hardware in these organizations as well as the assistance of KeRC in training highly-skilled specialists for these organizations.
In the concluding remarks academician A. S. Koroteev, Director of KeRC thanked the speakers for the warmy words about the Center, for the presented souvenirs and wished further success to the allied organizations.
On October 31, 2003 the festive actions dedicated to the KeRC jubilee continued in the "Akademichesky" concert hall.
The ceremonial party was opened by A. N. Kuznetsov, Deputy Director General who acted on behalf on Yu. N. Koptev, Director General of the Russian Aviation and Space Agency, Ye. I. Shaposhnikov, Assistant of President, Marshal of aviation read the salutary telegram from Vladimir V. Putin, President of Russia.
Then A. S. Koroteev, Full Member of RAS, Director of KeRC delivered a lecture.
Salutary speeches were made by
- V. P. Sherstyuk, First Deputy Secretary of Security Counsil;
- Lientenant-General A. A. Rakhmanov, Deputy Head of Agency, Chief of Arms of Armed Forces;
- V. Ye. Fortov, Full Member of RAS, Academician-Secretary of the Department of power engineering, machine-building, mechanics and processes of control of RAS;
- A. A. Fursenko, Acting Minister of the Ministry of industry and science.

Telegrams of greetings were received from the Government of Russia, the State Duma of Russian Federation, Moscow State Duma, Moscow Government, and Command of space armies. Cosmonauts Michael Foale and A. Yu. Kaleri greeted KeRC from space .
Finally , a film about KeRC was shown and a festive concert was given.

September, 2003
On September 29, 2003 the book "70 years in the foreground of rocket and space technology" came out.
It is devoted to the 70th anniversary of foundation of Keldysh Research Center.
The 6th Seminar of the International Science and Technology Center named "Science and Computing" was closed in Moscow.
At this Seminar Keldysh Research Center presented the paper "Multifunctional mathematical simulation of thermodynamic cycles" by Ye. V. Lebedinsky, S. V. Mosolov, V. A. Fedotchev, V. I. Tararyshkin
The week of Air Salon MAKS-2003 passed. One more interesting page in the history of aviation and space engineering was turned.
An exposition of SPPS model and key elements of SPPS that had been developed and experimentally tested at Keldysh Research Center was jointly presented with RSC "Energiya" and NPO Energomash.
The work on SPPS project came to the stage of development activity.
Conceptual design of multi-functional engine for LV "ONEGA" was jointly made with NPO Energomash.
The Second International Symposium "Safety and economics of hydrogen transport" was successfully over in Sarov-town where Director of the Keldysh Research Center, Academician A.S. Koroteev presented the paper "Prospects of hydrogen use in transportation means".
The results of work fulfilled at KeRC were reflected in the paper and the recommendations were given on outlook in progress of hydrogen energetics.
Our preparations to hold an anniversary are framing well, lesser than two months remain.
The program of jubilee includes Scientific Conference on October 29th and 30th at KeRC and festive evening.
The program of the Conference includes addresse4s and reports of the management and specialists from the leading enterprises in the industry branch where today's problems of rocketry and space engineering will be reflected, the ways in their solving and prospects in progress will be discussed.
Festive evening will take place on October 31st, 2003 in the Conference Hall of the Russian Academy of Sciences.
On the threshold of jubilee the specialists of KeRC will actively participate in several Conferences:
In connection with the jubilee a series of publications are under preparation:
F.S. Sklyar "Why the Germans could not reproduce "Katyusha" made by Moscow RNII?".
A.A. Gafarov "Nuclear energetics - future of cosmonautics".
V.F. Semyonov "Manned Mars Expedition - dreams or conscious necessity?"

June, 2003
On the 25th of June, 2003 the Interagency Research Council of the Academy of Sciences, RF, and the Russian Aviation and Space Agency on problems of space energetics was held under the chairmanship of A. S. Koroteev, Academician of RAS, director of the FCUE "Keldysh Research Center".
The use of hydrogen in power engineering and transport was under consideration.
It was noted that a high level of designing and technology had been attained in the field of development of power plants based on electrochemical generators with fuel elements.
The efforts of the R&SC "Energia" and the Ural Electrochemical Integrated Works resulted in development of an electrochemical generator for space application.
Jointly with "Alt-En" these organizations designed and manufactured electrochemical generators operating on air.

June, 2003
On June 10, 2003 the Zenit-SL rocket was successfully launched with the 11Д58M engine built up with a radiation-cooled nozzle extension made from the Grauris carbon-carbon composite material.

June, 2003
Specialists of the FSUE "Keldysh Research Center" took an active part to provide the successful launch of the AMC-9 spacecraft by the Proton launch vehicle with the "Briz-M" booster with regard to:
- analysis of results of ground development of the cruise engine and the booster in complex ground tests, adequacy of introduced precautions for elimination of causes of detected malfunctions;
- assessment of stability of cooling properties of the cooler after long-term storage and their effect on the cooling of chambers at a long life time (3600 seconds);
- determination of the influence of vibratory and pulsation state of engine on the strength of structural members;
- development, experimental verification and introduction of provisions for increasing stability margins of the gas generator;
Judging by the results of the work done, the FSUE "Keldysh Research Center" made a positive expert opinion to clear the cruise engine for normal work as part of the "Briz-M" booster.

March,2003
The International Jury of the VI Moscow International Salon of Industrial Property "Archimedes" awarded a silver medal to Keldysh Research Center for the development of
"Compact Heat Exchanger".
Authors: G. V. Konyukhov, A. I. Petrov.
The compact stationary semi-demountable plate-type heat exchanger features a relatively simple production technology and operation when made with a core from stainless plates of extruded-profile which are welded together in pairs over the perimeter and stacked into a core with elastic sealing rings between pairs of welded plates (compactness of the heat-exchanging surface is about 300 m²/m³).
The heat exchanger is designed to be used in power engineering, chemical and food industry, district heating systems of public services, etc.

A quarter of a century has passed since the day of the first firing test of the prototype of ЯРД11Б91 reactor (article 11Б91-ИР100) which occurred on March 27, 1978.
In accordance with the test programme in the run of startings the hydrogen temperature of 2600 K at the reactor outlet was reached with 42 MW power.
The analysis of test results and the complex of post-start investigations showed that main units of the reactor, including fuel assemblies, had underwent the tests successfully. The good agreement of design (predicted) and experimentally obtained thermal-physical and neutron-physical characteristics verified correctness of the calculative procedures adopted in designing of the reactor, correctness of design, technological solutions and solutions with respect to the choice of materials.
The work was done in cooperation by the following organizations: NII-1 (NIITP, KeRC), CADB, Research Institute for Physics and Power Engineering (GNTsRF-FEI), PNITI (NPO "Luch"), Instrument Making Research Institute.

March,2003
The problems of ecology and limited reserves of hydrocarbon material will require searching for new ways towards development of conventional power. One of the ways may consist in a wide application of hydrogen as ecologically friendly fuel and power accumulator.
The hopes of XXI century as to that problem are associated with the potentially to producer hydrogen at a cost less than that of organic fuel production.
Searching for thermochemical methods of water decomposition, started in the middle 70 s, are based for the most part on the use of cheaper thermal power and, partially, of the electric one.
At KeRC are also started the research into technical possibility to develop the power installation on the basis of thermochemical cycle of production of oxygen and hydrogen out of water, that can be used in electrochemical generator for power generation.
The objective of works is a follows:
- Continuation of searching for the most advanced effective thermochemical cycles;
- The evaluation of the prospects of methane-methanol cycle;
- The choice and justification of main parameters of the cycle;
- The analysis of the feasibility of available materials for main aggregates;
- Development of proposals on using a high-temperature water electrolyzer consuming 40 % of thermal and 60 % of electric power.

January, 2003
Combustion chamber of liquid rocket engine has been developed, it is protected by RF Patent № 2196917 (2002102796 dated 06.02.2002). The Patent is published in bulletin "Inventions. Utility models", № 2, 2003.

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