Ken,yes you are right.Schorsch,sorry if you feel ofended,your post is little confusing.
Also,despite the fact that F-22 is very capable plane,i think that it will be not be an easy task to beat P-42.Just look how drastic were the measures taken to provide this extreme 2:1 thrust-to-weight ratio.

5th generation fighter engine test?

Yes.
Translation from babel fish:
“Sukhoi completed the tests of engine for the aircraft of the fifth generation The prototype of engine for the Russian fifth generation fighter underwent tests, ITAR- TASS reports. “in OKB of Sukhoi are executed tens of flights, engine completely confirms design characteristics and already today it can be used as the intermediate power plant on the aircraft of the fifth generation”, stated by the central board VVS of Russia Vladimir Mikhaylov. The design Of engine AL -41 achieves NPO “Saturn”. In the work participate the specialists of the Machine Building Plant “Salyut”, plant the name of Klimov and other leading engine-building enterprises. The precise characteristics of new engine are still secret, however, on the statement of glavkoma VVS, it exceeds on the absolute and specific thrust the existing engines AL -31 used on the Su-27, and it is also characterized by the large resource between repairs. Fifth generation fighter or project PACK FA (promising aviakompleks of front aviation) is developed BY OKB of Sukhoi from the end of the 90th it is annual past century. Promising aircraft is known also under the index I -21. The flight tests of new machine, according to the information from different sources, can begin as long ago as 2007, series production – in the beginning of the following decade.”

He doesn’t deserve to live and everyone here knows it!

PhantomII
No offence,but who are you to decide who deserve to live?Certanly you are not God…..

Also recently i read book about Suez crisis,and i was wondering 20 years from now,how will the whole Iraq invasion will look like.Given the fact that the whole war is based on a lies,like Anthony Eden used Israel to give his “right” to send troops.

Actually you may have more luck with the name “Skif”.I hope you like this pictures.The link is in bulgarian,so say if you need translation.
http://airgroup2000.com/forum/viewtopic.php?p=84191&highlight=1987#84191
And here is translation from russian site.I use online translator,so there are plenty of mistakes and i don’t have the time to make correction.Tomorrow i will try to correct some.

“History of the creation

The development of the combat laser station “Scythian”, intended for the defeat of low-orbital space ob”ktov by onboard laser complex, began in NPO” energy “, but in connection with large zagruzzhennost’yu NPO since 1981 theme” Scythian “on the creation of laser combat station they transmitted in OKB -23 (KB”Salyut”) (the Director-General OF D.A. Of polukhin). This KA with the laser onboard complex, which was created in NPO “astrophysics”, had a length ok. 40 m and weights 95 T. for the starting KA “Scythian” proposed to use RN “energy”. On 18 August, 1983, the General Secretary of the CC of the CPSU YU.V. Andropov made statement, that THE USSR in the one-sided order ceases the tests of complex PKO – after which all tests were ended. However, programs SDI of work on the space defense were continued with the arrival M.S. of Gorbachev and the declaration in THE USA. For the tests of laser combat station was designed dynamic analog “Scythian- D”, by the length of ok. 25 m and with the diameter of 4 m, on the external overall sizes it was the analog of future combat station. “Scythian- D” was made from heavy-gauge steel, internal sortings supplemented and was collected weight. Inside the mock-up – void. According to the flight program it had to be brought together with the second step of “energy” in the water area of Pacific Ocean. Subsequently for conducting the test launch RN “energy” quickly was created the model model subsequently for conducting the test launch RN “energy” quickly was created the model model station “Scythian- dm Automatic spacecraft “pole” thought during July y98shchg. precisely as size-weight the mock-up (GVM), with which it was in prospect to produce the first launching “energy”. This concept arose after it became clear that the basic load of rocket – orbiting craft “snow-storm” – not will be ready to this period. At first task was not especially complex – indeed to make 100- ton “ingot” is not difficult. But suddenly KB “Salyut” obtained the wish- order of the minister of general machine building: to convert “ingot” into the automatic spacecraft for conducting the geophysical experiments in the near-earth space and to combine thus of testing “energy” and of 100- ton automatic spacecraft. On prevailing in our space branch practitioner new KA usually it were developed, tested and were made at least five years. But now it was in prospect to find completely new approach. Decided to maximally actively use finished sections, instruments, equipment, already tested mechanisms and knots, drawings from other “articles”. The Machine Building Plant im. Khrunicheva, to which was charged assembling “pole”, immediately began the preparation for production. But these efforts clearly would not be sufficient, they do not fortify themselves by the energetic actions of management – each Thursday at the plant was conducted the operational conferences, conducted by minister o.D.Baklanov or his deputy As o.N.Shishkinym. At these strategy meetings “rammed” sluggish or in by something the discordant leaders of subcontracting enterprises it were discussed, if it was required, the necessary aid. No reasons, and even that that by almost the same composition of executors was simultaneously conducted the immense work on the creation of “snow-storm”, as a rule, into the calculation did not enter. Everything was subordinated to maintaining the given ones is on top timetable – the clear example of the administrative- command methods of the management: “volitional” idea, the “volitional” performance of this idea, “volitional” periods and – “money not to stint on!” During July 1986 all sections, including anew designed and prepared, has already been find in Baikonur. On 15 May, 1987, from the spaceport Baikonur for the first time started the superheavy carrier rocket of yyK2shch “energy” OF?’SL (stendovo- flying). Starting became sensation for world cosmonautics. The appearance of a carrier of this class opened before our country the gripping prospects. In its first flight the carrier rocket “energy” bore as the payload experimental apparatus “Scythian- dm”, in the open press the named “pole”.

Initially the start of system “3nergi4”-“Skif- dm” was planned on September 1986. However, because of the delay the productions of apparatus, preparation of the launcher and other systems of the spaceport of work were detained almost on half a year – on 15 May, 1987. Only at the end of January of 1987 apparatus was transported from the assembly and testing housing on the 92nd area of the spaceport, where it passed preparation, into the building of the assembly- servicing complex of yyPshch9e on the area of yyА. There on 3 February, 1987, “Scythian- dm” it was butted with the carrier rocket of yyK2shch “energy” OF ‘SL. Next day complex they exported to the universal complex stand- start (UKSS) of y”Pey on 250 areas. Prelaunch joint testing there began. Continued finishing operation UKSS. Actually complex “Energy-Scythian- dm” was ready to starting only at the end of April. Rocket with the apparatus stood all this time since the beginning of February on the starter. “Scythian- dm” was completely charged by fuel, inflated by compressed gases and equipped with the onboard sources of power supply. For these three and one-half of month for it it was necessary to transfer the most extreme climatic conditions: temperature from -27 to +30 degrees, blizzard, wet snow, rain, fog and dust storms. However, apparatus withstood. After comprehensive preparation the start was assigned on 12 May. The first launching of new system with the promising automatic spacecraft seemed Soviet management of such important that it intended to honor by his presence very General Secretary of the CC of the CPSU Mikhail Sergeyevich Gorbachev. By the fact the more new leader OF THE USSR, who engaged the first post in the state year ago, had long ago been intended to visit main spaceport. However, even to the arrival of Gorbachev management of the preparation for launching decided not to experience fate and to insure against the “general effect” (there is this property in any technology to break in the presence of “high” guests). Therefore on 8 May at the session of state commission the start of complex “Energy-Scythian- dm” they transferred on 15 May. It was decided to say to Gorbachev about the emergent technical problems. However, to await already three days at the spaceport Secretary General not could: on 15 May in it was already planned the trip to New York for the appearance in THE UNITED NATIONS. On 11 May, 1987, Gorbachev arrived flying to the spaceport Baikonur. On 12 May he became acquainted with the models of space technology. The gist of the trip of Gorbachev on the spaceport was the inspection of “energy” with “Scythian- dm”. Then Mikhail Sergeyevich appeared before participants in the forthcoming starting. On 13 May Gorbachev flew away from Baikonur, and preparation for the starting entered the completing stage. Flight program “Scythian- dm” included 10 experiments: four applied and 6 geophysical. Experiment VPY was dedicated to finalizing the diagram of removal large-dimension KA according to bezkonteynernoy diagram. In the experiment VP2 were conducted studies of injection condition large-dimension KA, elements of its construction and systems. To the experimental check of the principles of construction large-dimension and superheavy KA (standardized module, control system, thermal control, electric power supply, questions of electromagnetic compatability) is dedicated experiment VPE. In the experiment VPYY it was planned to work out diagram and the technology of flight. The program of geophysical experiments “mirage” was dedicated to a study of the influence of combustion products on the upper air and ionosphere. Experiment “mirage -1” (Ay) had to be carried out to the height of 120 km in the stage of removal, experiment “mirage -2” (A2) – at the heights from 120 to 280 km with the preacceleration, experiment “mirage -3” (AE) – at the heights from 280 to 0 km with the braking. Geophysical experiments GF-Y/Y, GF-Y/2 and GF-Y/E it was planned to carry out with the work of engine installation “Scythian- dm”. Experiment GF-Y/Y was dedicated to the generation of the artificial internal gravity waves of the upper atmosphere. The purpose of experiment GF-Y/2 was the creation of artificial “dynamo effect” in the terrestrial ionosphere. Finally, experiment GF-Y/E was planned for creating the large-scale formation of ions in the ion and the plasmaspheres (holes and ducts). “pole” was equipped with a large quantity (420 kg) of gas mixture of xenon with krypton (42 balloons, each with a capacity of 36 l) and with exhaust system its into the ionosphere. Furthermore on KA it was planned to conduct 5 applied military experiments, including shooting of targets, but before the starting took place the appearance of the General Secretary of the CC of the CPSU M.S. Gorbachev, where he stated about the impossibility of the transfer of an arms race in space, after which the solution was accepted – military experiments on KA “Scythian- dm” not to carry out. The schematic of the removal of the apparatus “Scythian- dm” on 15 May, 1987, was following. The nose fairing was discarded 212 s after the contact of climb of 90 km. This occurred as follows: in T+2y2 s was produced the undermining of the drives of the longitudinal joint of fairing, the undermining of the locks of the first group of transverse joint GO occurred after 0.3 s, the locks of the second group were undermined after 0.3 more s. Finally into T+2yya.y s was produced the breaking of the mechanical bonds of nose fairing and it was separated.

In T+ya’0 s at the height of 117 km was produced the separation of apparatus and RN “energy”. In this case preliminarily into T+yashch’.ya s was given the command to the passage of four sustainer engines RN to the intermediate level of thrust. Passage occupied 0.15 s. In T+yashch9.ya s revealed basic command to turning off of sustainer engines. Then this command was duplicated after 0.4 s. Finally into T+ya’0 s revealed command to the department “Scythian- dm”. 0.2 s after this they were included by 16 RDTT – SOLID-PROPELLANT ROCKET ENGINE of withdrawal. Then into T+ya’y.2 s was produced the first switching on RDTT – SOLID-PROPELLANT ROCKET ENGINE of the system of the compensation for angular velocities SKUS (along the channels of pitch, hunting and bank). The second start RDTT – SOLID-PROPELLANT ROCKET ENGINE SKUS, if such was required, was produced into T+ya’e.ya s (channel of bank), the third – into T+ya’ya.0 s (along the channels of pitch and hunting). 51 s after department (T+shchyy s), when “Scythian- dm” and “energy” already divided 120 m, began the turn of apparatus for delivering the first pulse. Since “Scythian- dm” started by engines forward, then its one-hundred-and-eighty-degree turn degrees around transverse axis Z was required, in order to fly by engines back. To this one-hundred-and-eighty-degree turn degrees because of the special features of the system of controlling a vehicle was required still the “corrective turn” around the longitudinal axis X to 90 degrees. Only after this maneuver, called by specialists “perevertonom”, it was possible to dorazgonyat’ “Scythian- dm” for its output in orbit. To “pereverton” it was removed by 200 s. During this turn into T+shch’shch s was given the command to the department of ground fairing “Scythian- dm” (speed of department 1.5 m/s). After 3.0 s (T+shch’8 s) revealed the commands to the department of the covers of lateral blocks (speed of department 2 m/s) and cover of the system of zero spin exhaust (1.3 m/s). At the end of the maneuver of turn occurred sealing the antennas of onboard radar complex, opening the covers of the sensors of the local infrared vertical. In T+92shch s at the height of 155 km was produced the first firing of four engines of correction and stabilization DKS by thrust 417 kg. the time of the work of engines it was planned with 384 s, the value of the first pulse 87 m/s. Then into T+2220 s began the disclosure of solar batteries on the functional- official block “Scythian- dm”. Maximum opening time SB was 60 s. Removal “Scythian- dm” completed at the height of 280 km by the second start four DKS. It was produced into T+e’0shch s (3145 s after separation from RN). The duration of the work of engines was 172 s, the value of pulse – 40 m/s. The calculated orbit of apparatus was planned with the circular height of 280 km and with the inclination of 64.6 degrees. On 15 May start was outlined for 15 it was hour 00 minutes OF MOSCOW STANDARD TIME (16:00 summer Moscow time). During this day already into 00:10 (here and throughout MOSCOW STANDARD TIME) began and into 01:40 was completed the checking of initial state “Scythian- dm”. The preliminarily hydrogen tank of the central block (tank G of block Q) of carrier was blown through by gaseous nitrogen. In 04:00 was carry ouied the scavenging by nitrogen of remaining sections RN, and through half-hour passed the control of initial concentration in the hydrogen tank of block Q from 06:10 to 07:30 it were carried out the introduction of settings and the measurement of the frequency of the telemetric system “cube” of apparatus. The nitric preparation of the fuel tanks of lateral blocks was included in 07:00. Servicing rocket “energy” began into 08:30 (on the mark T -06 it was hour 30 min) from servicing of the oxidizer tanks (liquid oxygen) of lateral and central blocks. Regular cyclogram provided for: – to begin on the mark endeavor hour 10 min servicing with hydrogen of the tank G of central block (duration of servicing 2 hours of 10 min); – on the mark the t-th of the hour of 40 min to begin the charging of the submerged buffer batteries (BB) in the oxygen tanks of lateral blocks (block A); – to begin on the mark the t-th of the hour of 2 min charging submerged BB in the hydrogen tank of block Q; – on the mark the t-th of hour to begin servicing the fuel tanks of lateral blocks; – to finish in T -3 of the hour of 05 min loxing of the tanks of block A also to include their makeup; – in T -3 of the hour of 02 min to complete servicing with liquid hydrogen of central block; – in T -3 of the hour of 01 min to complete refueling of lateral blocks and to include the drainage of servicing mains; – to complete in T -2 of the hour of 57 min servicing with the oxidizer of central block [ 45,46 ]. However, in the course of servicing carrier arose technical troubles, because of which the preparation for the start was delayed as a whole to five and one-half it was hour. The total delay time being about eight it was hour. However, the graph of prelaunch operations had the built-in delays, due to what it was possible to two and one-half of hour to reduce delay. Delays happened for two reasons. First was revealed the nonhermetic state of the sectional joint of conduits along the line of the manager of pressure on disconnecting of the plug connector of thermostating and shooting of electro-pay on the block of e0A because of the nonstandard installation of the sealing gasket. The correction of this contingency situation engaged five it was hour. Then it was discovered, that one of two onboard valves in the main of thermostating, after the delivery of automatic command to their closing, did not operate liquid hydrogen. This it was possible to judge by the position of the end contacts of valve. All attempts to shut valve to nothing did not lead. Both these valves are fixed on the carrier rocket on one base. Therefore was accepted the solution to open the proper closed valve “by hand”, podav command from the control panel, and then to give out command “closing” “immediately to two valves simultaneously. In this case mechanical action from the normally working valve through the general base to the second valve would be provide ford. After the fulfillment of this operation from the “overhanging” valve entered the information about its closing.

In order to be insured, commands to opening and closing of valves repeated two additional times by hand. Each time valves were shut normally. In the course of further preparation for the starting the “overhanging” valve worked normally. However, this contingency situation “pulled out” from the graph already one hour. The already two hours of delays ran across because of the troubles in the work of some systems of the ground equipment of universal complex stand- start. As a result three-hour readiness for the start into 17:25 was only declared, the input of operational data to the launching began. Hour readiness was declared in 19:30. On the mark T -47 min began the refueling with liquid oxygen of central block RN, which was completed after 12 minutes. The collection of the starting readiness of apparatus began in 19:55. Then in T -21 min passed command “drawing 1”. After 40 seconds on the “energy” were included the radio facilities, and in T -20 min the prelaunch servicing procedure of carrier began and the correction of the level of kerosene in the fuel tanks of lateral blocks and their supercharging was included. 15 minutes prior to start (20:15) was included the regime of the preparation of the system of control “Scythian- dm”. Command “launching”, that initiates the automatic cyclogram of the starting of carrier rocket, was given out 10 minutes prior to start (20:20). Simultaneously was included the correction of the level of liquid hydrogen in the fuel tank of central block, which continued 3 minutes. 8 min 50 s prior to start began the supercharging and refueling with liquid oxygen of the oxidizer tanks of block A, which were completed also in 3 minutes. In T -8 min the automation of engine installation and pyro-means was mounted. In T -3 min was executed the command “drawing 2”. The conclusion about the readiness of apparatus for the starting was obtained 2 min prior to launching. In T-1 min of 55 s had to begin to be given the water for cooling the gas-bleeding chute. However, problems arose with this, water in a necessary quantity did not enter. 1 min 40 s prior to the contact of lift the engines of central block were transferred into the “starting position”. The pre-operational supercharging of lateral blocks passed. In T -50 s occurred the outlet of maintenance platform 2 ZDM. The system of the afterburning of launching system was included 45 s prior to start. In T -14.4 s firing the engines of central block occurred, in T -3.2 s starting of the engines of lateral blocks passed. 20 hours 30 minutes (21:30 MOSCOW STANDARD TIME, 17:30 gmt) passed the signal the “contact of lift”, went away area 3 ZDM, from “Scythian- dm” was separated transitional butt block. Enormous rocket is shrewd into the night velvety- black sky of Baikonur. In first seconds of flight in the bunker of control light panic arose. After detachment from the butt- supporting platform (block 4) the carrier made strong kachok in the pitching plane. In principle, this “nod” it was previously forecast by systems specialists of control. It was obtained because of control of “energy” of algorithm placed into the system. The flight was stabilized through the pair of seconds and rocket exactly went upward. Subsequently this algorithm was corrected, and with launching of “energy” with the “snow-storm” of this “nod” it was no longer. Two steps of “energy” worked out successfully. 460 seconds after start “Scythian DM” it were separated from RN at the height of 110 km in this case orbit, to be more precise, ballistic trajectory had the following parameters: the maximum altitude of 155 km, minimum height is minus 15 km (i.e., the pericenter of orbit it lay under the earth’s surface), the inclination of trajectory plane to the terrestrial equator 64.61 deg. In the process of separation without the observations the system of the withdrawal of apparatus with the aid of 16 RDTT – SOLID-PROPELLANT ROCKET ENGINE operated. Disturbances in this case were minimum. Therefore according to the data of telemetry data operated only one RDTT – SOLID-PROPELLANT ROCKET ENGINE of the system of the compensation for angular velocities along the channel of bank, which ensured the compensation for the angular velocity of 0.1 deg/s along the bank. 52 seconds after separation began the maneuver “perevertona” of apparatus. Then into T+shch’shch s occurred the shooting of ground fairing. After 568 s was given out the command to the shooting of the covers of lateral blocks and shielding cover SBV. There and happened irreparable: the engines for stabilization and orientation DSO did not stop the rotation of apparatus after its regular one-hundred-and-eighty-degree turn degrees. Despite the fact that “pereverton” continued, accordingly the logic of the work of program timing device passed the department of the covers of lateral blocks and system of zero spin exhaust, the disclosure of the antennas of system “cube”, the shooting of the covers of the sensors of the local infrared vertical. Then, on revolving “Scythian- dm” were included engines DKS. Without having collected necessary orbital speed automatic spacecraft it went along the ballistic trajectory it fell there, where central block RN “energy” – into the waters of Pacific Ocean. Solar panels were opened – it is not known, but this operation had to pass to the moment of the entrance “Scythian- dm” into the earth’s atmosphere. The program timing device of apparatus worked with the removal properly, and therefore, most likely, the batteries of raskrylis’.Prichiny of failure were revealed in Baikonur practically immediately. In the conclusion according to the results of launching the complex “energy Scythian- dm” it was said: “… the functioning of all aggregates and systems KA… in the sections of launch preparation, the joint flight with the carrier rocket of yyK2shch ‘SL, department from RN and autonomous flight in the first section to the orbital injection passed without the observations. Subsequently by 568 second from the wear and tear OF KP (contact of lift) because of the passage of the not provided by cyclogram command of control system to turning off of the nourishment of the driver amplifiers of the engines for stabilization and orientation (DSO), the article lost orientation. Thus, the first pulse of the preacceleration of the regular duration of 384 seconds revealed with not quench angular velocity (article it completed approximately two complete revolutions on the pitch) and after 3127 seconds of flight, as a result of the nonreceipt of the required speed of preacceleration, it completed descent into the water area of Pacific Ocean, in the region of the zone of a drop in the block “Q” of carrier rocket. Ocean depths in the place of the fall of article… are 2.5-6 km. Turning off of driver amplifiers occurred upon command of the block of the logic OF YYM8EY-22M on obtaining of marker from onboard program timing device (PVU)”spectrum 2SK” to the discharge of the covers of lateral blocks and shielding covers of the system of the zero spin exhaust of article… Earlier on the articles of yyF”2 this marker was used for disclosing the solar panels with the simultaneous blocking DSO. With re-addressing of marker PVU -2SK to the delivery of commands to the discharge of covers BB and SBV of article… NPO “electric appliance” did not consider string on the electrical circuits of the instrument OF YYM8EY-22M, which blocks work DSO in entire section of the delivery of the first corrective pulse. KB “Salyut” with the analysis of the functional diagrams SU of development NPO “electric appliance” also did not reveal this string The reasons for nevyvedeniya of article… in orbit are: a) the passage of the not provided by cyclogram command SU to turning offs of the nourishment of the driver amplifiers of the engines for stabilization and orientation in the course of programmed rotation up to the delivery of the first pulse of preacceleration. This contingency situation not was revealed in the course of of ground-based finalizing because of neprovedeniya the head developer of the system of administration NPO “electric appliance” on the complex stand (Kharkov) of performance checkout of systems and aggregates of article… for flight cyclogram in real time.

Performing analogous work on KISe of manufacturing plant, in KB “Salyut” or on the technical complex it was impossible since: – plant complex tests are combined with the preparation of article on the technical complex; – complex stand and electrical analog of article… in KB “Salyut” were dismantled, and equipment is transmitted for completing of regular article and complex stand (Kharkov); – technical complex not was equipped by the enterprise OF NPO “electric appliance” by mathematical programmed software. b) the absence in the equipment SU for development NPO the “electric appliance” of telemetry data about presence or absence of nourishment on the driver amplifiers of the engines for stabilization and orientation “. In the test recordings, which made the chart recorders with conducting of complex tests, the fact of turning off of driver amplifiers DSO was accurately fixed. Here only time to the interpretation of these records it did not remain – all greatly hurried to neglect “energy” with “Scythian- dm”. The curious case occurred with the starting of complex. Yenisey separate control-measuring complex 4 as it was planned it approached on the second turn conducting of the radio control of orbit neglected “Scythian- dm”. Signal on the system “Kama” was steady. There was how the surprise of specialists OKIK-YA, when by them it was declared, that “Scythian- dm”, without having completed the first turn along the orbit, disappeared into the waters of Pacific Ocean. Proved to be because of the unavailable previously error OKIK assumed information from completely different automatic spacecraft. Similar occurs sometimes with the equipment “Kama”, that has the very wide antenna radiation pattern. However, unsuccessful flight “Scythian- dm” gave many results. First of all was obtained entire necessary material on the refinement of loads aboard the orbiting craft OF YYFESHCHOK “snow-storm” into the guarantee of flight tests of the complex of yyFe’ (index of the complex, which consists of the carrier rocket of yyK2shch and orbiting craft OF YYFESHCHOK “snow-storm”). With the starting and the autonomous flight of apparatus were executed all four applied experiments (VP-Y, VP-2, VP-E and VP-YY), and also parts of the geophysical experiments (“mirage -1” and partially GF-Y/Y and GF-Y/E). In the conclusion on the sums of launching it was said: “… thus, the general tasks of launching the article…, determined by the tasks of launching, affirmed TO M and UNKS, taking into account” the solution “of 13 May, 1987, by the limitation of the volume of purposeful experiments, were you polneny according to the number of solved tasks more than to 80%. The solved tasks cover practically entire volume of the new and problematic solutions, whose checking was planned with the first launching of complex… The flight tests of complex in the composition RN of yyK2shch ‘SL and KA “Scythian- dm” they were for the first time: – is confirmed the fitness for work RN of superheavy class with the asymmetric lateral arrangement of the concluded object; – is obtained the wide experience of ground-based operation in all preparation stages for the start of superheavy rocket-space complex; – is obtained on the basis of telemetry data KA… the extensive and reliable experimental material on injection condition, which will be used for the creation KA of different designation and S “snow-storm”; – are begun the tests of the space platform of 100- ton class for solving the wide circle of tasks, for the creation by which was used a number of new progressive assembly, constructive and technological solutions “. They passed with launching of the complex of testing and many elements of construction, which were used then and for other KA and RN. Thus, the carbon plastic nose fairing, for the first time tested in full-scale 15 May of 1987, was used then with the starting of modules “quantum -2”, “crystal”, “spectrum” and “nature”, and also it is already prepared for the starting of the first element of international space station – power unit FGB. In the communication TO TASS of 15 May, to this dedicated starting, it was said: “in the Soviet Union are begun the flight design tests by new powerful universal RN” energy “, intended for the removal to the near earth orbits of both the reusable orbiting crafts and the large-dimension automatic spacecraft of scientific and national-economic designation. Two-step universal carrier rocket… is capable of placing in orbit more than 100 tons of the useful load… on 15 May, 1987, 21 hours 30 minutes of Moscow time from the spaceport Baikonur it is realized the first launching of this rocket… The second step of carrier rocket… derived into the calculation point of size-weight the mock-up of satellite. Size-weight mock-up after separation with the second step had to with the aid of its own engine be brought out to the circular near earth orbit. However, because of the nonstandard work of its onboard systems mock-up to the designated orbit did not leave and was given in the water area of Pacific Ocean… “. Source: site “troops of rocket-space defense”, site “spacecraft” snow-storm “”

Again sorry for the bad translation.

More about PRS-1.Sorry for any mistakes,because i used online translator and right now i don’t have the time to check all.

“The design of new high-speed antimissile was executed in two organizations: OKB -2 (the chief designer OF P.D. Of grushin) and KB “innovator”. Was selected the version, proposed BY KB “innovator”. This PR obtained designation PRS -1. Rocket was cone without aerodynamic carriers and managers of elements. In the engine was used the quick-burning powder in 4 seconds of the work of engine rocket it were accelerated to the maximum speed. In this case axial overloads reached 300 g., and the temperature of skin rose to 2000 degrees. All this required the new technical solutions with the creation of onboard equipment, which must be small and high-strength. Onboard equipment was developed in KB -1: autopilot – by association P.M. Kirilov, radio equipment – by association V.I.Tolstikov and V.I. Dlugnii. Everything else, except warhead and engine, in KB Novator under the management L.V. lyul’eva. Engine installation was created in KB of Perm’ plant under Kozlov’s management.”

“Its development conducted Sverdlovsk KB Novator with the chief designer L. lyul’ev. This KB approached the works in 1967. Task stood extremely complex. It was necessary to drive away rocket for several seconds to speed on the order of 4 km/s. This could make an engine on the rapidly burning powders only. This engine undertook to develop chief designer Kozlov from Permian KB. In view of the fact that in flight in the atmosphere at a high speed the surface of rocket nagrevayetsya from the friction against air to the temperature above 2000 degrees, was required the adoption of special measures for the protection of constructions and equipment. Housing PRS -1 was executed in the form of cone with the special heat-shielding coating without any coming out elements. Gas current engines with the thrust vector, directed perpendicularly to the axis of rocket were used as the control elements and stabilization. PRS -1 had single-stage diagram from the separable head part. Creation for this rocket of onboard equipment for stabilization and control was complex problem. It must be small with the light weight and operational with the overloads to 300 g. Furthermore, already to e-ya-oy second of flight on the surface of rocket was formed the high-temperature plasma, which is screen for the radiowave propagation. The development of onboard equipment was produced in KB -1: autopilot – in the subdivisions P.M. Of kirillova, and equipment for radio control and sighting – by subdivisions xV.I. Tolstikova.kh and xV.I. Dolgikh.kh.”

“As a result of design and designing were developed avan- and preliminary designs, while in 1973 experimental model PRS, was created and set for the tests. The first launchings were carry ouied from the launching ramp at angle of 20° to the horizon. To the second launching the rocket was not equipped with onboard equipment and, as a rule, it broke. From the third – the rocket had regular assembly. Stage separation was not produced. Beginning from 1978, from 7 through 11 launchings they were carried out with the draft on funds of the first prototype of system. Beginning from 12 launchings in 1979, the means of the second prototype were used. Tests were passed with the great difficulties, connected with the special features of rocket. Of 15 that following it is starting into 6 rocket it broke also to 17 launchings it was impossible to ensure reliable radio communication with the board. The fact is that the designers of rocket, worrying about strength and aerodynamics, led for the installation of onboard antennas the ground part of the second stage of rocket. As tests showed, in flight these antennas completely screen by plasma. After detailed analysis of the insistence of specialists KB -1 for the designers of rocket it was necessary to establish antennas on the housing of the conical forming the rockets in front of the nozzles gas current system for control. Moreover the duplexing system depending on the position of the axis of rocket relative to radio equipment of complex was developed. The developers did not meet with such difficulties. Beginning from 17 launchings, it was possible to obtain stable communications along the control channel, and with 20 – and along the channel of sighting. In the course of these tests it was necessary to finish equipment SPK and to introduce into its composition of the device of initial tracking with the appropriate changes in the programs of control.”

It’s funny how if somebody want to project USSR as the Evil Empire,they all use the crimes in Stalin era.Yet up to 60’s there was segregation in USA.Maybe you are not “collored” and is easy to forget.Yeah,millions killed in USSR is no way equal to segregation in USA,but that don’t justify the racism at all.
And Meat if i use your tactic to pick up a shamefull period of one country’s history to make it something like portrait,then USA is sooooo evil because of all that slavery.

Schorsch thanks for clear up.

“Those who promote this nonsense usually never lived a day under the USSR and often as not lived under military protection provided by others.”
Well i’m not from USSR,but i lived more than a day under communist regime.Also i was in the military(Bulgaria).The scenarios that we learned in military school was primary defencive/counter offence after first strike from NATO.For example in one exercise with Soviet soldiers we “played” a scenario in which Soviet para-troopers come to aid after massive strike from Greece and Turkey.Nevertheless Bulgaria lacked any weapon in the class of Pershing so we were even unable to deliver proper first strike.Sure our MiG’s were capable of using nukes,but i don’t know a single case when there was such bombs in Bulgaria.But i can be wrong….