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11.02.2012 17:09
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The Giant Kalinin
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Buran a spaceship
Buran a spaceship
Work on the Energy—Buran program began in 1976.
86 ministries and departments and 1286 enterprises of the entire USSR (about 2.5 million people in total) participated in the creation of this system.
The main developer of the ship was a specially created NGO "Molniya".
Production was carried out at the Tushinsky Machine building Plant since 1980; by 1984, the first full scale copy was ready.
From the factory, the ships were delivered by water transport to the city of Zhukovsky, and from there (from the Ramenskoye airfield) - by air transport (on a special VM T transporter aircraft) - to the Baikonur cosmodrome.
Buran made its first and only space flight on November 15, 1988.
The spacecraft was launched from the Baikonur Cosmodrome using an Energia launch vehicle and after circling the Earth landed at the specially equipped Yubileyny airfield on Baikonur.
The flight took place without a crew, completely in automatic mode, unlike the "shuttle", which can land only on manual control.
In 1990, work on the Energia Buran program was suspended, and in 1993 the program was finally closed.
The only Buran that flew into space (1988) was destroyed in 2002 by the collapsed roof of the hangar of the assembly and test building at Baikonur.
During the work on the Buran project, several mock up samples were produced for dynamic, electrical, airfield and other tests.
After the closure of the program, these products remained on the balance of various banks?�
? and production associations. �
?it is known, for example, that the Rocket and Space Corporation Energia and the NGO Molniya have mock up samples.
The length of the "Buran" is 36.4 m, the wingspan is about 24 m, the height of the ship when it stands on the chassis is more than 16 m, the starting mass is more than 100 tons.
The cargo compartment accommodates a payload weighing up to 30 tons.
A sealed all welded cabin for the crew and people for work in orbit (up to 10 people) and most of the equipment for flight support as part of the rocket and space complex, autonomous flight in orbit, descent and landing is inserted into the nose compartment.
The volume of the cabin is over seventy cubic meters.
it has a triangular wing with a variable sweep, as well as aerodynamic controls that work during landing after returning to the dense layers of the atmosphere — a rudder, elevators and an aerodynamic shield.
"Baikal" is the name of a Soviet reusable transport spacecraft created within the framework of the Energia Buran program.
The launch took place on February 4, 1992.
The flight program included a seven day stay in space and docking with the Mir station.
Unfortunately, at the very beginning of the flight, an emergency situation occurred and the Baikal made an emergency landing.
This was the basis for the curtailment of the Russian program for the creation of reusable ships.
In fact, the inscription " Baikal "(in red in a straight font like" Arial") decorated the side of the first flight copy of the MTCC" Buran " almost during the entire time of ground tests.
However, shortly before the launch, the name "Buran" was put on board the MTCC in black oblique font, under which he went on a flight and became known to the whole world.
The name of the ship and the entire program - "Buran" - was known to everyone who had anything to do with them (including outside the USSR) from the very beginning of the development of the program.
However, due to the all encompassing secrecy, this word was not recommended to be used openly, in connection with which "Baikal" was born (and later the open name of the Energia launch vehicle, known to specialists as product 11K25, was put into circulation).
A total of 6 people were enrolled in the first group on July 12, 1977:
Wolf,�?
gor Petrovich
Kononenko, Oleg Grigoryevich
Levchenko, Anatoly Semyonovich
Sadovnikov, Nikolai Fedorovich
Stankevicius, Rimantas Antanas
Shchukin, Alexander Vladimirovich
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12.02.2012 03:19
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A brief history of the creation of the Buran reusable orbiter (products 11F35)
The work on the creation of reusable spacecraft in the Soviet Union has its own history.
The idea of using wings on a returnable spacecraft arose immediately with the start of flights into space.
This was explained by the desire to use the potential capabilities of the Earth's atmosphere (first of all, controlled braking and precise maneuvering) and the aviation reserve with which the first rocket scientists came to cosmonautics.
Therefore, the presence of wings on the descent vehicle moving in the atmosphere looked simple and logical.
The first projects of cruise spacecraft
In the second half of the 50s, TsAGI began to study hypersonic manned and unmanned aerial vehicles.
The first official mention of " spaceships "("cosmoplanes") - aircraft type devices capable of flying at extremely high altitudes and in near Earth space appeared in 1958 in the plans of the Ministry of Defense of the USSR, outlining the main activities of the Soviet Air Force for the next 25 years.
It was assumed that the developed devices would be able to reach speeds over M=10 and flight altitudes of more than 60 km.
Soon, the OKB 23 and OKB 256 of the State Committee for Aviation Technology began developing projects for manned "spaceplanes" launched into orbit by a three stage modification of the R 7 ICBM.
word designations: 1 cosmonauts ' cabin; 2 portholes; 3 entrance hatch; 4 instrument compartment; 5 wing consoles at the entrance to the dense layers of the atmosphere; 6 tail unit
In the OKB 256 of Pavel Tsybin, by order of the OKB 1 of Sergei Korolev, in parallel with the Gagarin Vostok, a winged spacecraft (CC) of the" classical "aerodynamic scheme was designed, the preliminary design of which was approved on May 17, 1957.
The gliding spacecraft (PKA) had a trapezoidal wing and a normal tail with a launch mass of 4.7 tons, a landing mass of 2.6 tons and a crew of 1 person.
The estimated duration of the flight reached 27 hours.
The CC had a length of 9.4 m, a wingspan of 5.5 m, a tail height of 4 m and a fuselage width of 3 m.
A special feature of the project was the folding of the wing into an aerodynamic "shadow" of the fuselage in the area of intensive braking in the atmosphere.
The descent scheme assumed intensive braking in the atmosphere using the lifting force of the main body to a speed of 500-600 km / h at an altitude of about 20 km, then planning was provided with the help of a folding wing.
The cosmonaut had to eject before landing on the runway (runway).
After connecting to the work of the CAG�?
it turned out that the problems facing the developers of cruise spacecraft are much more serious than was commonly believed.
So, after purging in wind tunnels, it turned out that the thermal loads on the heat shield significantly exceed the calculated ones, and the hinge joint of the wing consoles on the most heat stressed section of the descent is located in a" stagnant " zone with almost complete absence of a heat sink.
Technical problems associated with accurate orientation during descent, difficulties with thermal protection and successful tests of the Vostok CC determined the termination of work on the PKA.
VKA 23 V. M. Myasishcheva, the third variant ("49", 1960): the starting mass is 4.5 tons when launched into orbit at a height of 400 km, the payload is 700 kg; the crew is 1 person; the length is 9.0 m, the wingspan is 6.5 m, the height is 2 m.
In 1957-60, air and space vehicles (VKA) The M 40, M 46 and others were developed at Vladimir Myasishchev's OKB 23 as part of the"Theme 48".
The latest version of the VKA 23 for the first time provided for the use of tiled ceramic thermal protection, was intended for one cosmonaut and when launched into orbit at a height of 400 km had a mass of 4.5 tons, a length of 9 m, a wingspan of 6.5 m, a height of 2 m along the keels and was capable of carrying a payload of 700 kg.
Rocket plane R 2 developed by Vladimir Chelomey
In 1960, OKB 23 and OKB 256 became branches of Vladimir Chelomey's OKB 52, which continued working on rocket planes.
The result was a preliminary design of an unmanned rocket plane P 1 weighing 6.3 tons, equipped with an M shaped folding wing of variable sweep, and its manned version P 2.
The unmanned version of the P 1 was intended for testing and testing all units and systems of the rocket plane in orbit, including orientation and stabilization systems, thermal protection, activation of separation means with the study of the dynamics of the uncoupling process, clarification of the ballistic and aerodynamic parameters of the rocket plane with an assessment of the reliability of all onboard systems.
On the R 2 rocket plane, the cosmonaut was supposed to work out control, verification, communication and observation functions from space.
The total mass of the R 1 and R 2 rocket planes was 6,300 kg each, the standard flight path was to include an elliptical orbit with a perigee of 160 km and an apogee of 290 km, the total flight time was 24 hours.
The overload on the descent was supposed to be only 3.5-4 g, unlike 9-11 g on the descent vehicle of the Vostok spacecraft.
For the launch of rocket planes, the development of its own two stage A 150 rocket launcher with a starting weight of about 200 tons was carried out.
According to the program for the development of a rocket plane and maneuvering warheads in 1961-63, 12 suborbital launches of large scale models MP 1 and M 12 on the RN R 12 developed by Mikhail Yangel (the first launch on 21.02.1963) were carried out, but after Nikita Khrushchev, who favored Chelomey (his son Sergei worked at OKB 52), on October 19, 1964, all work was stopped with the transfer of materials on rocket planes to Artyom Mikoyan's OKB 155.
The MP 1 was a prototype of a maneuvering warhead in the form of a 1.8 meter cone weighing 1.75 tons, controlled at hypersonic speeds by eight aerodynamic shields.
The ballistic missile lifted the sample at 405 km, it entered the atmosphere at 1760 km from the launch site at a speed of 3.8 km / s.
M 12 - the same cone, but with four stabilizers.
If the work on rocket planes did not save the independence of the Myasishchev OKB 23, then the patriarch of Russian aviation Andrey Tupolev acted wiser, having created the "K" department inside his OKB 156 in 1956-57 under the leadership of his son Alexey, entrusting him with work in the field of unmanned aircraft and missile systems.
In 1958, the "K" department began work on the "DP" (long range planning) unmanned strike complex, consisting of a launch vehicle (it was supposed to use modifications of the combat P 5, -12, -14 or P 16) and the last stage in the form of a gliding rocket plane with a thermonuclear warhead.
It was also envisaged that OKB 156 would develop its own carrier.
The PH was supposed to throw the gliding device to a height of 50-100 km and give it a horizontal speed of up to 20,000 km / h.
After separation, the rocket plane performed a correction and flew to the target along the planning trajectory with a decrease in speed and altitude.
The device was supposed to reach the target at a distance of up to 4000 km from the launch point, developing a speed of up to M=10 (~7000 km/h) above the target at an altitude of 30 km.
In 1959, the Tupolev team began working on the design of an experimental prototype of the DP combat complex the 130 aircraft (Tu 130).
In its final form, it became a "tailless" weighing 2050 kg and relatively small in size: length 8.8 m, wingspan 2.8 m and height 2.2 m.
In the pilot production, a series of five experimental "130" was laid, and in 1960 the first glider was ready to be equipped with equipment and to dock with the PH - modified P 12.
However, according to the decree of February 5, 1960, work on the "130" was stopped - its fate was decided by the success in creating Soviet ICBMs.
By this time, the final version of the DP complex consisted of a three stage launch vehicle of its own design with a starting weight of 240 tons, and a winged vehicle capable of delivering a thermonuclear warhead weighing 3-5 tons at a range of 9000-12000 km.
The reserve on the topics "DP" and " 130 "was used in the projects of the rocket plane" 136 "(Tu 136," Zvezda"," Red Star") and its orbital version"Sputnik".
The manned " 136 "was intended for a single turn flight around the Earth with a subsequent landing, and the" Sputnik "("137", Tu 137) for several turns with a subsequent planned landing on the airfield runway.
The work on the topics" Star "and" Sputnik " continued until 1963, without going beyond the preliminary design. �
?another interesting thing is that within the framework of Zvezda, a variant of putting a rocket plane into orbit was being worked out with the help of an aerospace system, the first stage of which was a strategic supersonic aircraft ("135" or "139"), and the second stage was an air - based ballistic missile with a rocket plane instead of a head warhead.
this variant can be considered the forerunner of the Spiral air orbiting aircraft (VOS), the brilliant project of which was proposed by Mikoyan's OKB 155 on June 29, 1966.
We will not dwell here in detail on the Spiral project - a separate section of the site is dedicated to it, including its continuation in the form of unmanned orbital rocket planes ("HOG").
But you can learn much more about the "Spiral" and about the above mentioned projects of winged spacecraft in our book " Space Wings"
---------- Post added at 01:32 ---------- Previous post was at 00:55 ----------
The path to the " Buran"
The next milestone work for the Soviet cosmonautics was the development of a reusable space system (ISS) "Energia Buran", which ended with a triumphant unmanned flight and an automatic landing of "Buran" on the runway of the Baikonur cosmodrome on November 15, 1988.
The creation of the Energia Buran ISS (fig. on the right) was the most ambitious and time consuming program in the history of Soviet cosmonautics.
Suffice it to say that for 18 years more than a million people worked directly on the ISS in 1286 enterprises and organizations of 86 ministries and departments, the largest scientific and industrial centers of the country were involved.
The total cost of the program as of the beginning of 1992 amounted to 16.4 billion rubles.
soviet rubles.
"Buran" was conceived as a military system.
This is how the director of the Central Research Institute of the Rocket and Space Industry recalled this in 1994?машиностро?
mechanical engineering Yu.
A. Mozzhorin:
"The program has its own background.
In 1972, Nixon announced that the "Space Shuttle"program was being developed in the United States.
It was announced as a national one, designed for 60 shuttle launches per year, it was supposed to create 4 such ships; the cost of the program was planned at 5 billion 150 million dollars in 1971 prices.
In the future, they certainly grew up, as it happens with everyone, they reached 13 billion 400 million dollars.
The program was serious, since 4 launch complexes were being created, at the Vandenberg base and at Cape Kennedy, special production facilities were being created.
The shuttle put 29.5 tons into low Earth orbit, and could lower cargo up to 14.5 tons from orbit.
This is very serious, and we have begun to study for what purposes it is being created?
After all, it was very unusual: weight into orbit with the disposable media in America, not even up to 150 t/year, and there are thought to 12 times more; nothing of its orbit did not go down, and there was supposed to return 820 MT/year...
It was not merely a programme of creating some space system under the motto reduce the cost of transportation costs (our, our Institute study showed that no reduction will not actually be observed), it had a clear target military purposes.
indeed, at that time they began to talk about the creation of powerful lasers, beam weapons, weapons based on new physical principles, which theoretically allows you to destroy enemy missiles at a distance of several thousand kilometers.
It was precisely the creation of such a system that was supposed to test this new weapon in space conditions."
The words of Yuri Alexandrovich are confirmed by the Deputy Chief Designer of the ISS "Buran" V. M. Filin: "The need to create a domestic reusable space system as a means of deterring a potential enemy was revealed during the analytical studies conducted by?the Institute of Applied Mathematics of the USSR Academy of Sciences and NPO Energia in the period 1971-75.
It was shown that the United States, by putting into operation its reusable Space Shuttle system, will be able to gain a decisive military advantage in terms of launching a preventive nuclear missile strike on vital objects on the territory of our country."
In the decisions of the NTS of the Ministry of General Engineering and the Ministry of Defense, the task was set: "to exclude possible technical and military surprise associated with the appearance of a potential enemy of a reusable space Shuttle transport system - a fundamentally new technical means of delivering significant masses of payloads to near Earth orbits and returning to Earth."
in principle, to exclude fuel consumption during flight in the atmosphere and the corresponding emissions of combustion products into the atmosphere.
The final version of the device, which received the designation MG 19 (Myasishchev Gurko, M 19, "gurkolet"), was made according to the load bearing body scheme, which ensures high weight perfection of the device, and was equipped with a combined propulsion system consisting of a nuclear reactor and a combined direct flow hydrogen LRE.
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In the first half of the 1970s, MG 19 was considered as a serious competitor to the Energia Buran ISS, but due to the lower degree of elaboration and a greater degree of technical risk during implementation, as well as due to the lack of a foreign analogue, the MG 19 project did not receive further development.
Nevertheless, this project has not yet been declassified, and information about it is still extremely scarce.
---------- Post added at 02:08 ---------- Previous post was at 01:53 ----------
"Spiral"
Step by step plan of work on the VOS "Spiral".
stage 1.
Creation of a manned analog aircraft (product index "50-11") weighing about 11.85 tons, including a fuel reserve of 7.45 tons, with two rocket engines, starting from the Tu 95 carrier aircraft.
The analog aircraft does not have a mass dimensional and instrument similarity with the OS.
The purpose of the tests is to work out the aerodynamics of the vehicle, the gas dynamic control organs, the operating modes of the fuel system on the AT+NDMG components, the assessment of thermal modes in conditions close to space flight (the maximum flight altitude is 120 km, the maximum flight speed corresponds to M=6-8) and entry into the atmosphere.
On an analog aircraft, the drive to the airfield and landing were to be worked out.
It was planned to manufacture and test 3 analog aircraft.
According to the plan, the flight at subsonic speed and landing - 1967, the flight at supersonic and hypersonic 1968.
The cost of the work is 18 million rubles.
This stage was essentially an analogue of the American X 15 project and was not implemented in metal.
stage 2.
Creation of a single seat experimental manned orbital aircraft (EPOS, product index "50") - a prototype of a combat variant weighing 6800 kg for full scale testing of the design and flight confirmation of the characteristics of the main onboard systems.
The launch is carried out using a carrier rocket 11A511 (Soyuz) with an orbit with a height of 150-160 km and an inclination of 510, where the device makes 2-3 turns with a gas dynamic maneuver (AT+NDMG fuel) in orbit to change the orbit plane to 80, and then performs descent and landing as a full size OS .
It provided for a complete external, systemic and structural (in terms of structural and thermal insulation materials) similarity with the combat OS.
It was planned to manufacture and launch 4 aircraft in unmanned (1969) and manned (1970) versions.
The cost of the work is 65 million rubles.
stage 3.
Creation of a hypersonic booster aircraft (GSR).
To speed up the work, it was planned to create and test first a full size GSR with engines running on kerosene (flight tests of 4 aircraft, with the achievement of M=4 - in 1970, the cost of the work is 140 million rubles).
After the accumulation of data on the aerodynamics and operation of the aircraft at hypersonic speed, it was planned to switch the GSR to hydrogen fuel, for which it was necessary to manufacture and test 4 aircraft.
Flight tests of the GSR on hydrogen - 1972, the cost of work - 230 million rubles.
stage 4.
testing of a fully equipped system consisting of GSR and OS with a rocket accelerator (GSR engines run on kerosene) - 1972 Since the capabilities of such a system are limited, it seems that the OS of this option is unmanned.
After comprehensive testing and testing of all systems, in 1973 it was planned to conduct flight tests of a fully equipped system with hydrogen powered engines and a manned OS.
Further work was to be associated with the transition to liquid fluorine (!), used as an oxidizer on a rocket accelerator and OS, and the deployment of work to create an effective reusable second stage equipped with a hypersonic ramjet engine instead of a rocket accelerator.
Suborbital manned aircraft analog " 50-11"
To practice landing, on board systems, aerodynamics, gas dynamic control and all aircraft control systems, as well as to train the flight crew, it was supposed to develop an analog of an orbital aircraft that exactly repeats its shape.
Such an analog, dropped from the Tu 95KM carrier aircraft, with the help of its own engines, was supposed to continue the flight and allow working out the landing and flight conditions up to M=6-8 and H=50-120 km.
Since the flight speed in the upper atmosphere of the analog was several times less than the orbital one, taking into account the gentle temperature conditions, it was planned to build it from ordinary structural materials (steel, titanium and aluminum alloys).
According to the project, the analog was equipped with a power plant consisting of two serial rocket engines developed by OKB 117 with a thrust of 11.75 ts each (fuel consumption 81.8 kg/sec, specific impulse 319 sec) and one turbojet "36-35" OKB 36 with a bench thrust of 2500 kg and already existing equipment (on the first copies).
The rocket engines were located with a half collapse angle of 11 ° 40" in the horizontal plane so that their thrust vectors passed through the center of mass of the device.
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the use of the units mastered in production should have significantly reduced the cost and time of testing the experimental orbital aircraft.
In the future, it was planned to install accelerators developed in the OKB 2 MAP on an analog, allowing to bring its speed to M=12-13, and a number of standard EPOS systems.
The suspension scheme of the analog under the carrier aircraft corresponded to the suspension of the X 20 cruise missile adopted for service, so the revision of the Tu 95KM was also not required.
The planned flight profile looked as follows.
After a joint takeoff, the Tu 95 carrier aircraft lifts the analog to an altitude of 11-12 km within an hour, where it is reset at a speed of 830 km / h.
The angle of installation V of the movable wing consoles at the beginning of the flight is ψ=20º...35 ° (respectively 70°...55 ° from the horizontal plane).
Having turned on its own marching rocket engines (all the free internal volumes of the airframe are used for a fuel reserve of 7.15 tons), the analog aircraft accelerates to a speed of 8000 km/h in 81 seconds.
The active acceleration section ends at an altitude of 48-50 km.
By this time, two LRE engines have time to burn 6625 kg of fuel.
During the further flight, passing by inertia, the analog reaches a maximum altitude of 120 km, having at this moment a speed of 6800 km / h (M=7.5).
At the ascending point of its trajectory, the device can perform maneuvers with the help of two rocket engines with a total thrust of 1.5 tons and orientation engines (gas dynamic control systems).
Re entry into the atmosphere occurs at a speed of 7250 km / h, the maximum overload at the descent stage reaches 5.3 g.
The maximum quality of the device at hypersonic speeds is 1.4, balancing is 1.0.
In the most heat stressed places, the skin has time to heat up to 890 ° C.
After returning to the dense layers of the atmosphere, with a decrease in flight speed to M=2.5, the wing consoles are laid out in the position ψ=60°, and in the altitude range of 5-10 km, a 2.5 ton turbofan engine is activated, which with a fuel reserve of 300 kg can provide a flight range of up to 90 km at a cruising speed of 400 km/h at an altitude of 500-2000 m .я?meya maximum subsonic quality of 4.5, the analog switches to a cruising flight mode with a planning trajectory angle of 12 ° and a vertical speed of about 18 m/sec.
The landing glide path has an inclination of 18°, (since the quality due to the released landing gear is reduced to 4), the landing speed is 250 km/h.
With a landing weight of 4.4 t, the run length is about 1000-1100 m.
The program for creating a suborbital manned analog " 50-11 "was never implemented in the intended volumes, but the developed design solutions for dropping the Tu 95KM carrier from the aircraft were in demand during the construction and testing of the subsonic analog"105.11".
---------- Post added at 02:14 ---------- Previous post was at 02:08 ----------
The first flights into space of the epic (products "50")
The docking of the EPIC with the 11A511 rocket was worked out jointly with OKB 1 and its Kuibyshev branch.
The dynamics of putting the aircraft into orbit was calculated and the output weight of the aircraft (6800 kg) and the possible height of the orbit (up to 150 km) were determined.
At the same time, in order to reduce the disturbing aerodynamic moments acting on the rocket, the aircraft must be equipped with a conical fairing, which is dropped after the separation of the first stage of the rocket.
In this case, no significant improvements in the strength and control system of the rocket were required.
Only the launch and lifting devices were subject to revision, with the creation of ground based control and verification devices servicing the orbital aircraft.
In the first flights, the EPIC had to test the fundamental feasibility of a gas dynamic maneuver to change the plane of the orbit.
This maneuver was to become a regular element of the flight program of combat orbital aircraft in strike and reconnaissance versions to ensure the possibility of re passing over the target.
The available amount of fuel for performing the maneuver was 2000 kg due to the weight limit of the aircraft, conclusion and it was launched into orbit with the help of the 11A511 rocket.
It was enough for 7 minutes of operation of the main rocket engine and the rotation of the orbit plane only by 8°.
Nevertheless, the success of this operation on the EPIC would give confidence in the rotation of the orbit plane on the combat WASPS at large (required) angles.
The first test orbital flight was supposed to look like this.
First, after checking Board systems of the EPIC in the Assembly and testing facility at the site of Baikonur N2 refuel EPIC high boiling components of the fuel are then docking with the Soyuz (11А511).
To do this, fold the wing in the starting position ("the tent on the back"), and after rolling the head fairing of the rocket with the spacecraft with a total height of about 37 m (10 m of which is accounted for under the fairing, and power farm fastening to PH) is transported to the start where the last operations (comprehensive inspection, refueling PH, landing a pilot astronaut in the apparatus, a set of pre launch readiness, etc.), the familiar triggers other "Unions".
The launch takes place in the early morning (from 6.00 to 9.00 DMV - decree Moscow time) during a two to three hour launch window to ensure landing at selected airfields on the territory of the USSR during daylight hours.
In the active section of the PH flight, the fairing is affected by a maximum velocity pressure of 3600 kg/m2, the cosmonaut pilot experiences a maximum overload of 4.4 g.
The rocket puts the EPIC weighing 7 tons into a low working orbit with a height of 130 km, an inclination of 51 ° and a rotation period of about an hour and a half.
Then the device drops a 200 kilogram connecting truss and begins half hour checks of on board systems, during which the ground control center analyzes the telemetry information coming from the board, after which the preparation of the maneuver for turning the orbit plane begins - the orientation engines are checked, the EPOS is stabilized to issue a pulse.
At the beginning of the second orbit, in the tracking zone of ground command posts, the main rocket engine turns on, and after 7 minutes, having "lightened" by almost 2 tons, the device enters a new orbit with an inclination of 58 ° 45'.
On the second round, tests of on board systems continue, i.e. the implementation of the flight program for "peaceful space exploration", then preparations for landing begin.
The wing consoles occupy the position for entering the atmosphere (V=60°), the EPIC is guided by the engines forward, and over �?the Ndian Ocean (approximately at the point with coordinates 20 ° S, 50 ° VD, at a distance of about 14,000 km to the landing airfield), by turning on emergency rocket engines (for the purpose of checking them), a braking impulse is issued for de orbiting.
The cosmonaut pilot drains the remaining fuel overboard and orients the device at the required angle of attack to enter the atmosphere at a speed of M=25.
Hypersonic maneuvering in the atmosphere with an average aerodynamic quality of 0.9 (at an angle of attack of 45°) can provide a landing zone of plus/minus 1100 km in any direction from the orbital plane by performing a lateral maneuver and up to 4000 km in the orbital plane.
The passage of the maximum heat flow section is carried out using a change in the roll angle in the range from 0 ° to 60°, which provides the necessary longitudinal and lateral range and output to a given landing area.
Roll maneuvering significantly simplifies the control scheme and minimizes fuel costs for gas dynamic control during descent.
The maximum overloads experienced by the pilot on the descent section do not exceed -1.4 g on the X axis (in the direction of "chest back") and +1.4 g on the Y axis ("head of the leg").
After reducing the speed to M=10, the consoles are programmatically unfolded to 45°.
The next final layout of the consoles to the maximum position (V=30°) occurs at a speed of M=2.5.
At a distance of 60 km to the airfield, a turbojet engine is launched, developing a thrust of 1000 kgf at a speed of M=0.35, and a planning section begins from a height of 2000 m, where the aircraft performs pre landing maneuvering (with a maximum overload on the turn ny=1.5 g) at a speed of about 400 km/h, descending at a vertical speed of 18 m / sec along a trajectory with an angle of inclination of 12°.
A landing approach is made from a height of 500 m.
The manufactured landing gear reduces the aerodynamic quality from 4.5 to 4, with a landing weight of 4.5 tons, the aircraft can withstand a landing angle of 14°, touching the runway at a speed of 225-250 km/h.
The length of the run of the still hot device along the dirt strip is 1000-1700 m.
At the end of the runway, the plane is already waiting at a respectful distance (after all, the remnants of toxic fuel!) greeters, and the plane has just returned from the plasma furnace, you need to give it time to cool down...
Or maybe the landing team, dressed in chemical protection suits, is quickly deploying ground based means of cooling the hull and ventilating the internal compartments?
In any case it ends with the exit tired of smiling pilot cosmonaut, greetings and hugs N ish airfield in the Western part of the USSR... �?Menno the country's first real pilot astronaut looks both terms in the same flight... (not belittling the accomplishments of our astronauts skazem that the few lucky ones, ketabchi into space on the U.S. space Shuttle, there was only passengers)
It wasnot ... but it could have been!
Such a flight could really take place in the early 70s!
After all, much later, already in our days, when all the emotions about the closure of the Spiral program were noisy, one of the designers said in an interview with the web master: "With the GSR, of course, it was still a question, but with the EPIC orbiter, there are no questions, it could really be built, and it would fly now..."
We will add from ourselves - only probably, after all, with quartz tile thermal protection.
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In the drawing of the orbital aircraft on the Soyuz launch vehicle (11A511), taken from the Spiral advance project and shown above on the left, any specialist will see a fundamental error a two stage rocket is depicted, which is fundamentally unable to put a cargo weighing 6.8 tons into orbit.
To put an orbiting aircraft into orbit, a three stage modification of the rocket is required, which we have depicted in our reconstruction
The third stage is the most mysterious, and information on it is extremely scarce.
But in the end, at the next, fourth stage, we had to get a unique aerospace system, getting acquainted with which even today, forty years (!) later, you feel legitimate pride and admiration for the engineering talent and the power of foresight of its authors.
---------- Post added at 02:19 ---------- Previous post was at 02:14 ----------
The combat manned single seat reusable OS provided for the use of a daytime photo reconnaissance, radar reconnaissance, a space target interceptor or a strike aircraft with a space to Earth missile and could be used for the inspection of space objects.
The weight of the aircraft in all variants was 8800 kg, including 500 kg of combat load in the scout and interceptor variants and 2000 kg in the strike aircraft.
The range of reference orbits was 130 ... 150 km in height and 450...1350 in inclination in the northern and southern directions when starting from the territory of the USSR, and the flight task was to be performed during 2-3 turns (the third round is landing).
The maneuvering capabilities of the OS using an onboard rocket propulsion system running on high energy fuel components fluorine F2 + amidol (50% N2H4 + 50% BH3N2H4), were supposed to provide a change in the inclination of the orbit for the scout and interceptor by 170, for an attack aircraft with a rocket on board (and a reduced fuel reserve) - 70...80.
The interceptor was also able to perform a combined maneuver a simultaneous change in the inclination of the orbit by 120 with an ascent to an altitude of up to 1000 km.
After performing an orbital flight and turning on the braking engines, the OS should enter the atmosphere with a large angle of attack, control at the descent stage was provided for by changing the roll at a constant angle of attack.
On the trajectory of the planning descent in the atmosphere, the ability to perform an aerodynamic maneuver at a range of 4000 was set...6000 km with a lateral deviation of plus/minus 1100...1500 km.
The OS was to be output to the landing area with a choice of the speed vector along the runway axis, which was achieved by choosing a roll change program.
The maneuverability of the aircraft made it possible to land at night and in difficult weather conditions at one of the reserve airfields of the territory of the Soviet Union from any of the 3 turns.
The landing was made using a turbojet engine ("36-35" developed by OKB 36), on a class II unpaved airfield at a speed of no more than 250 km / h.
According to the Spiral advance project approved by G. E. Lozino Lozinsky on June 29, 1966, the VOS with an estimated mass of 115 tons was a combined winged wide body reusable horizontal takeoff and landing vehicles - a 52 ton hypersonic booster aircraft (which received the index "50-50"), and a manned OS (index "50") located on it with a two - stage rocket accelerator a launch unit.
In the main version, four air jet engines (VRD) running on liquid hydrogen are installed on the GSR.
The GSR was used to accelerate the VOS to a hypersonic speed corresponding to M=6 (about 1800 m / s), then at an altitude of 28...30 km there was a separation of the stages, after which the GSR returned to the airfield, and the OS with the help of the LRE of the output unit I was entering a working orbit.
To speed up the flight testing of the carrier aircraft, the installation of four VRD (P 39-300), running on kerosene and having approximately the same air flow, is provided.
The VOS made it possible to put a payload weighing up to 10.3 tons into a polar orbit with a height of 130-150 km at a starting parallax of up to 750 km when using a liquid hydrogen power plant on the GSR and a cargo of 5.0 tons with a kerosene power plant on the GSR.
due to the lack of development of liquid fluorine as an oxidizer to accelerate the work on VOS as a whole, an alternative development of a two - stage rocket accelerator on oxygen hydrogen fuel and the gradual development of fluorine fuel on OS was proposed as an intermediate step first, the use of high boiling fuel on nitrogen tetraxide and asymmetric dimethylhydrazine (AT+NDMG), then fluoro ammonia fuel (F2+NH3), and only after accumulating experience, it was planned to replace ammonia on amidol.
Thus, the team of OKB 155 A.�?.In the summer of 1966, Mikoyan began to develop an air orbiting aircraft, which, thanks to the features of the design solutions laid down and the chosen scheme of the aircraft launch, made it possible to implement fundamentally new properties for the means of launching military loads into space:
- putting into orbit a payload that makes up 9% or more of the take off weight of the system by weight;
- reducing the cost of putting one kilogram of payload into orbit by 3-3.
5 times compared to rocket complexes with the same fuel components;
- the launch of spacecraft in a wide range of directions and the possibility of rapid re targeting of the launch with a change of the necessary parallax due to the aircraft range;
- self relocation of the booster aircraft;
- minimizing the required number of airfields;
- quick launch of a combat orbital aircraft to any point of the globe;
- effective maneuvering of an orbital aircraft not only in space, but also at the stage of descent and landing;
- aircraft landing at night and in difficult weather conditions at an airfield specified or selected by the crew from any of the three turns.
At the same time, the designers already at the stage of the preliminary project saw ways to further improve the system.
First of all, it was planned to achieve a significant increase in the efficiency of the VOS by developing a reusable accelerator with a RAMJET with supersonic combustion, which made it possible to create a completely reusable complex in the future.
Gorenje
The designers hoped that these features of the VOS would ensure its economic feasibility, prompt solution of military tasks and effective use of near Earth outer space for military purposes.
For the full scale processing of the design and the main systems that should be used on combat aircraft in the future, an experimental manned single seat reusable orbital aircraft was worked out in detail in the advance project, which, in order to accelerate the work, without waiting for the development of the GSR, was to be put into orbit using a Soyuz launch vehicle (product 11A511 developed by the Design Bureau 1 S. P. Korolev); and an analogue of an orbital aircraft launched from a Tu 95 carrier aircraft similar to the X 20 rocket.
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13.02.2012 15:51
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Let's go back to the " Buran"
Application of " Buran"
The goals of creating the Buran orbiter were first clearly formulated in the tactical and technical task for the development of a reusable space system, issued by the Main Directorate of Space Assets of the Ministry of Defense of the USSR and approved by D. F. Ustinov in a festive atmosphere on November 7 (according to other sources, 8), 1976. �
?so, "Buran" was intended for: - comprehensive counteraction to the activities of a potential enemy to expand the use of outer space for military purposes; - solving target tasks in the interests of defense, national economy and science; - conducting military applied research and experiments to ensure the creation of large space systems using weapons on known and new physical principles; - launching into orbit, servicing them and returning spacecraft, astronauts and cargo to Earth.
The initial plans assumed the construction of five orbiters to achieve a frequency of 30 flights per year.
Combat space complexes
In the late 60s - early 70s, work began in the United States to explore the possibility of using outer space for conducting combat operations in space and from space.
The Government of the USSR by a number of special resolutions (the first Resolution of the Central Committee of the CPSU and the Council of Ministers of the USSR "On the study of the possibility of creating weapons for conducting combat operations in space and from space" was issued in 1976) entrusted the work in the country in this area to the cooperation of developer organizations headed by NPO Energia.
In the 70s and 80s, a complex of studies was conducted to determine possible ways to create space assets capable of solving the tasks of destroying military spacecraft, ballistic missiles in flight, as well as especially important air, sea and ground targets.
At the same time, the task was set to achieve the necessary characteristics of these funds on the basis of using the scientific and technical reserve that was available at that time with the prospect of developing these funds with limited production capacity and financing.
To defeat the military space objects has been developed for two combat spacecraft on a single constructive basis, equipped with various types of on Board armament systems - laser (combat system "SKIF") and rocket (military complex "Cascade").
The basis of both devices were unified service unit, based on the design of service systems and units of space station series 17K DOS.
Unlike the station, the service unit had to have significantly larger fuel tanks of the propulsion system to ensure maneuvering in orbit.
Combat space complexes the payload of the OK " Buran"
The Skif system"
Designations: 1 instrument fuel compartment; 2 aggregate compartment; 3 on board complex of special weapons
The Cascade system"
Designations: 1 - the basic unit, which includes the aggregate and instrument fuel compartments; 2 on board weapons system; 3 - homing missile
Combat Space Homing Interceptor Missile
The launch of spacecraft into orbit was supposed to be carried out in the cargo compartment of the ISS Buran orbiter (by the Proton carrier rocket at the experimental stage).
It was planned to refuel the tanks in orbit with the help of means also delivered to the vehicles in the ISS Buran OK.
To ensure a long period of combat duty in orbit and maintain high readiness of space complexes, it was provided for the possibility of visiting objects by the crew (two people up to 7 days), including using the Soyuz SPACECRAFT.
The smaller mass of the on board weapons complex "Cascade" with rocket weapons, compared with the complex" Skif " with laser weapons, allowed to have a larger fuel supply on board the spacecraft, so it seemed advisable to create a system with an orbital grouping consisting of combat spacecraft, one part of which is equipped with laser, and the other with rocket weapons.
At the same time, the first type of spacecraft was to be used for low - orbit objects, and the second for objects located in medium altitude and geostationary orbits.
To defeat the launching ballistic missiles and their head blocks on the passive flight section, a project of a space based interceptor missile was developed for the Cascade complex at NPO Energia.
In the practice of NPO Energia, it was the smallest, but the most energy armed rocket.
Suffice it to say that with a launch mass measured in only tens of kilograms, the interceptor rocket had a reserve of characteristic speed commensurate with the characteristic speed of rockets that put modern payloads into orbit?NW.
High performance was achieved through the use of technical solutions based on the latest achievements of domestic science and technology in the field of instrument miniaturization.
The author's development of NPO Energia was a unique propulsion system using unconventional non cryogenic fuels and heavy duty composite materials.
In the early 90s, due to the change in the military political situation, work on combat space complexes at NPO Energia was stopped.
All thematic divisions of the Head Design Bureau and a wide cooperation of specialized organizations of developers of the country's military industrial complex, as well as leading research organizations of the Ministry of Defense and the Academy of Sciences were involved in the work on combat space complexes.
According to other sources, the missile system for the Cascade was developed by order of NPO Energia in the firm of A. E. Nudelman, a well known designer of cannon weapons for aircraft and spacecraft.
For the orbital tests of the rockets, it was decided to install them on the Progress cargo transport ships.
At the first stage, in 1986-88, five flights of such ships were planned as part of the Cascade program.
The production of these ships under the side numbers 129, 130, 131, 132 and 133 began at the production base of NPO Energia - the Experimental Mechanical Engineering Plant (ZEM).
However, it never came to flight tests.
The ships were converted and put into orbit (already under new numbers) for their original purpose - to deliver cargo to the manned orbital station.
In the early 1990s, work on the program for creating the Cascade apparatus was discontinued.
The main company for the laser complex for the "Skif" was the NGO "Astrophysics" - the leading Soviet laser company.
After the transfer of the groundwork for the "Skif" from NPO Energia to the Salyut Design Bureau in the early 1980s, a new team developed a project for a space based heavy combat laser station "Skif".
On August 18, 1983, the General Secretary of the CPSU Central Committee, Yuri Vladimirovich Andropov, made a statement that the USSR unilaterally stops testing the anti space defense complex.
However, with the announcement of the Strategic Defense Initiative (SO�?)program in the United States work on the Skiff was continued, and on May 15, 1987, a dynamic mock up of the Skif DM laser station weighing about 80 tons was tested in space during the first test launch of the Energia launch vehicle.
To defeat particularly important ground targets, a space station was developed, the basis of which was the station of the 17K DOS series and on which autonomous modules with ballistic or gliding type combat units were to be based.
By a special command, the modules were separated from the station, by maneuvering they had to occupy the necessary position in outer space, followed by the separation of the blocks on command for combat use.
The design and main systems of the autonomous modules were borrowed from the Buran orbiter.
As a variant of the combat unit, a device based on the experimental model of the OK "Buran" (devices of the "BOR"family) was considered.
The military target load for Buran was developed on the basis of a special secret resolution of the Central Committee of the CPSU and the Council of Ministers of the USSR "On the study of the possibility of creating weapons for conducting combat operations in space and from space" (1976)
---------- Post added at 14:51 ---------- Previous post was at 13:57 ----------
Combat space station with shock blocks based on the OK " Buran"
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Most likely (for obvious reasons, we are forced to use this phrase - "most likely"), the combat units, which were essentially planning nuclear bombs, should have been compactly placed in the payload compartment of the combat strike module with the wing consoles folded in three...four sequentially mounted revolver catapult launchers.
The figure on the left shows a cross section of the payload compartment with the warheads installed on one of the revolver launchers.
The dimensions of the Buran payload compartment make it possible to place up to five combat units on each rotating ejection unit, as shown in the figure.
Taking into account the possible lateral maneuver of each combat unit during descent in the atmosphere of at least plus/minus 1100...1500 km one strike module could in a short time with its twenty maneuvering combat units wipe out all life from the face of the Earth in a strip up to 3000 km wide.
This is how S. Alexandrov describes the use of the combat space station in his article "The Sword that became a shield" ("Youth Technology", N4 ' 98):
"...The same basic module as on the Mir orbital station, the same side ones (it's no secret that, for example, tests of an optical system for detecting rocket launches were supposed to be carried out on the Spectrum...
And a stabilized platform with TV and photo cameras on the "Crystal" - what is not a sight?), but instead of an astrophysical "Quantum" - a module with a combat control complex.
Under the" ball " of the transition compartment is another adapter, on which four modules (based on the "Buranovsky" fuselage) with combat blocks hang.
This is ,so to speak, the"starting position".
On alarm, they separate and diverge into working orbits, chosen from the following consideration: that each block will reach its target at the moment when the control center will fly over it.
The fuselage of the Buran is used in this project on the principle of "do not waste the good": large fuel reserves in the combined propulsion system and a very good control system allow you to actively maneuver in orbit, while the payload combat units are in a container, hidden from prying eyes, as well as unfavorable factors of space flight.
What is essential in the context of strategic deterrence is that this weapon system will deliver a targeted, "surgical" strike even if everything else is destroyed.
Like nuclear submarines, it is able to wait out the first salvo!"
When creating the Buran ,it was also assumed that maneuvering combat units could be placed not only on the attack modules, but also on the orbiters themselves, being located on revolver launchers inside the cargo compartment.
It is possible that if necessary (for example, the cancellation of the order for combat use) the ship's onboard manipulator could be used to return the shock modules to the cargo compartment on the turret launchers for their maintenance and reuse, as shown in the figure below on the left.
Another option for using Buran as a carrier of space to Earth class attack weapons provided for the placement on board of the orbital head parts 8F021 of the orbital ("global") R 36orb rocket (R 36 O, OR 36, 8K69orb), each of which consisted of a body, an instrument compartment with a control system, a brake propulsion system and a combat unit with a monoblock thermonuclear charge with a capacity of 5 MT in TNT equivalent.
The blocks were to be placed in low waiting orbits with a height of 150-180 km, at the descent from which an autonomous inertial control system with a gyrostabilized platform ensured the accuracy of hitting a ground target (circular probable deviation - CVO) of 1100 meters.
With the weight of one complete block of 1700 kg, Buran could launch up to 15 blocks into space in one launch, replacing a similar number of R 36orb missiles (for comparison: in the USSR, as part of the only regiment on combat duty from 25.08.1969 until its liquidation under the OSV 2 agreement, 18 mine launchers were deployed).
In addition to the head parts of the R 36orb rocket, special Bolide missiles of the cosmos Earth class in nuclear execution were developed for the Buran.
Presumably, the Bolid missile was created at NPO Mashinostroeniya either as a further development of the 3M 45 (P 700) Granit anti ship missile (photo on the left) with a 3M15 nuclear warhead (with a capacity of 500 kt), or on the basis of the 3M 25 Meteor cruise strategic missile (fig. on the right).
The Bolid rocket was supposed to have an atmospheric flight range of up to 800 km at an altitude of more than 21 km.
"Bolides" were created for high precision destruction of protected targets (underground command posts of ICBM mines, etc.), so their concrete piercing warhead could be buried to a depth of up to 30 meters before the explosion.
In parallel, technical measures were being worked out that did not allow the enemy's spacecraft inspectors to detect (for example, by X ray or registration of radioactive/ionizing radiation, etc.) nuclear or conventional weapons on board the Buran.
There is fragmentary information about other military aspects of the use of orbiters.
In particular, as part of the "asymmetric response" to the American "Star Wars" program (SO�? - the Strategic Defense Initiative) the issues of mining near Earth space with the help of a "Buran" with the creation of an insurmountable veil for the space segment of the SO?
were considered.
The active means acting on enemy spacecraft were called " Fireplaces "(from" space mines"). "
Fireplaces " could be used both in conventional and nuclear equipment.
In addition, a third, special version of equipment was also provided for them: in the USSR (under the leadership of Nikolai Vetchinkin, the son of the famous aerodynamicist prof. V. P. Vetchinkin), research work was carried out with ground based experimental testing to create orbital high explosive clouds (based on high explosive sols), quickly and completely "cleaning" the entire near Earth space from spacecraft to altitudes of 3000 km.
Of course, after the operation of this original means, near Earth space became completely inaccessible for several months, but these measures were supposed to be used only during (or immediately before) a full scale military conflict between the USSR and the United States.
And as you know, "they cut down the forest - chips fly"...
All possible scenarios of combat operations in outer space with the participation of 11F35 orbiters were worked out, modeled (i.e. played), analyzed and evaluated at the head institute for military Space of the TSN????
-50 of the Ministry of Defense of the USSR.
By the time of the launch of the Buran on 15.11.1988, the military scientific justification for its use was completely completed, and some technical samples of its weapons were undergoing ground testing.
But there were also less "radical" military plans for the use of orbiters.
For example, for breeding exclusively on the "Buran" in the Kuibyshev (now Samara) TsSKB under the leadership of D.??.Kozlov created a heavy (mass in orbit 24 t) orbital complex of multispectral optical and electronic reconnaissance "Sapphire", periodically serviced by astronauts during visiting expeditions.
The basis of the Saphir complex was to be an optical telescope with a diameter of the main mirror of 3 meters.
The development of the telescope managed to advance before the production of the first flight sample.
According to the technology of manufacturing the main mirror, the glass billet was supposed to cool down slowly in the furnace for several years, but already in the process of its cooling, the USSR collapsed, work on the Buran was frozen, and the Sapphire was no longer needed, since with uncertain prospects for orbital spacecraft, the Proton payload was clearly not enough.
Be that as it may, by accident or not, but after the collapse of the USSR, after a year and a half of cooling the workpiece, the technological process was disrupted and it cracked.
A domestic optical telescope with a 3 meter mirror in space has not appeared until now.
One of the possible images of the Saphir optical electronic reconnaissance orbital complex when it is placed in the Buran cargo compartment is presented on the right.
About the "Sapphire" complex, see also the article "Top secret space" in the newspaper "Volzhskaya Kommuna" from 26.04.2007.
There were also completely exotic projects for the military use of 11F35 orbiters, about which very little is known.
For example, in the case of a full scale deployment of the Soviet Star Wars program in outer space, the Skif combat orbital laser stations were to operate, the demonstration model of which (the Polyus spacecraft) the USSR tried to put into orbit on May 15, 1987.
The initial plans assumed that at first the combat stations would be equipped with excimer lasers, but in the future it was planned to use liquid fluorine as a working medium for pumping the laser.
As the working fluid was consumed during the firing process, the combat stations had to be refueled - for this purpose, it was supposed to develop a modification of a reusable space tanker equipped with a self defense complex based on Orbita Orbita class missiles on the basis of 11F35 reusable orbiters.
Below we present a freeze frame (screenshot) of our screensaver, illustrating both the moment of refueling of the combat laser, and all the stages of the operation of the combat laser station:
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