According to the resolution of the Council of Ministers Soviet Union dated May 17, 1979, the scientific and production association of mechanical engineering begins development SCRC, which is a further development of the P-500 Basalt complex. New complex retained the launch equipment from the previous complex and received a greater range of destruction thanks to the use of an improved launch engine in the rocket, the addition of fuel to the sustainer stage, a reduction in the armor protection of the hull and a number of other improvements.
Testing of the new complex began on December 3, 1982 at 10.55 Moscow time at a test site near the village of Nenoksa Arkhangelsk region. The first launch of the rocket was unsuccessful: the launch unit did not separate from the rocket after testing, as a result of which the rocket began to fall apart in flight and fell after 8 seconds after launch. The next launch, carried out on April 9, 1983, also turns out to be unsuccessful; the rocket falls 9 seconds into the flight. As the investigation into the unsuccessful launches progressed, it was determined that the cause of the problems in the rocket lay in the control system. Therefore, by the third launch, which took place in June 1983, the control system was being finalized, and the rocket successfully operated along the entire flight path.
Basic tests SCRC Anti-ship missile system "Vulcan" begins on December 22, 1983 from the SSGN project P-500 Basalt upgraded to project 675MKV. The modernization consisted of installing a new SCRC Anti-ship missile system. Joint testing of modernized SSGN Nuclear Submarine with cruise missiles and new installed P-1000 complexes begin in 1985. A salvo of two missiles was fired, which successfully destroyed the designated target, and this despite the fact that there was a malfunction in the pressure support system in the instrumentation compartment and an error in the launch of the operator's missile. The next launch within the framework of the joint testing program was carried out on November 8, 1985 - a salvo of three missiles was fired, which, in general, was considered successful - two missiles successfully destroyed the designated target, the third missile failed in flight Radar Radar station sight In total, 18 missile test launches were carried out and 11 of them were considered successful.
By the end of 1985, improvements to the control system were completed, upon completion of which a Certificate of Completion of Joint Tests was signed, in which it is recommended to adopt SCRC Anti-ship missile system"Vulcan" into service Navy Navy taking into account control tests carried out in 1986. 8 missiles were allocated for testing - a salvo launch of 4 missiles and a single launch of the rest as part of various test programs:
The launch of the first missile was carried out on May 24, 1986, as part of the test program for the missile control system of the Basalt complex. The launch was considered successful;
The launch of the 2nd rocket was carried out on June 18, 1986, as part of a noise immunity test. The launch was considered successful;
The launch of the 3rd rocket was carried out on June 19, 1986, as part of a noise immunity test. The launch was considered successful;
The salvo launch of 4 missiles took place on July 4, 1986, the salvo was considered successful. Three of the four missiles were equipped with telemetry, since the ground equipment at the test site could not receive data from four missiles at once. The fourth missile, without telemetry, for an unknown reason strayed from its flight path and did not hit the target.
SCRC Anti-ship missile system“Vulcan” was put into service on December 18, 1987. The production of missiles for the complex was carried out by the Orenburg association "Strela" from 1985 to 1992. The complex could be supplied in three versions - ground (shore) with PU Launcher type SM-49 (used during the first tests in 1982), surface and underwater (analogue of the P-500 Basalt complex).
In design RCC Anti-ship missiles Titanium alloys were used, thereby reducing the armor protection of the hull. The complex's missile used an inertial control system with the ability to make adjustments from a radar homing head developed at the Granit Central Research Institute. The developer of the control system is designer A. Chizhov, the on-board RTA designer is B. Godlinik. The autopilot was developed by designer A. Kuchin, and the digital computer was designed by V. Nikoltsev. Target selection by the missile was carried out either automatically, or using telemetry, or with the possibility of combining modes. The autopilot and control system were assembled on the latest element base at that time, and were seriously different from similar solutions of the P-500 Basalt complex. The designers were able to improve the noise immunity characteristics of the radar homing head by creating an improved on-board computer.
When aiming the missile, an algorithm was used to select the main target in a group of ships. At launch, the missile received the coordinates of the target and passed the main part of the trajectory with the radar sight turned off. At the final section of the trajectory, the missile descended towards the target, and the sighting device was automatically turned on, with the help of which the coordinates were clarified and the target was captured. At the same time, the on-board equipment analyzed the size of the targets and their position relative to the given coordinates of the target. This algorithm ensured that the missile could capture the largest target in a group of ships.
To overcome missile defense and air defense enemy, the missile was provided with anti-aircraft maneuvering algorithms at low altitudes. When launching missiles in salvo, when there was a threat, they dispersed along the front and reassembled into a group at the final section of the trajectory (before the sight was turned on). For electronic warfare an installation station was installed in the rocket active interference 4B-89 “Bumblebee”, it was developed by department No. 25 of the Granit Institute, designers R. Tkachev and Yu. Romanov. The instrument compartment is completely sealed and is equipped with a special system to maintain the required pressure inside the compartment.
During the work on creating rockets for SCRC Anti-ship missile system"Vulcan" carried out a research work called "Radiation", the tasks of which included analyzing the impact damaging factors Nuclear weapons on missiles heading towards the target. For this analysis, an explosion was carried out in a special adit on Novaya Zemlya. nuclear charge. The analysis revealed that most elements of on-board equipment were damaged by neutron radiation at a distance of 500 meters from the epicenter of the explosion, while some parts received irreversible damage. As a result of the analysis, some parts of the on-board equipment were replaced with ones more resistant to the damaging factors of nuclear weapons.
At the end of 1987, according to a resolution of the Council of Ministers of the Soviet Union, work began on the creation of Vulcan missiles OK Battleship » using a laser high-precision guidance channel. This should have led to increased accuracy of missile hits. The onboard equipment for the new rocket was developed under the leadership of chief designer V. Senkov. The laser guidance channel was created at the Granit Central Research Institute, project manager S. Sharov. The laser guidance system could recognize surface ships by geometric parameters, after which it issued correction commands along the flight path to hit surface ships in the most vulnerable place. The first tests of the newest system took place in the hero city of Sevastopol, the system was tested on passing surface ships and from the flying laboratory of the Il-18 aircraft.
Test launches of missiles with a laser channel homing head, as part of the creation of the Vulcan missiles OK Battleship"should have taken place approximately in 1989. The onboard equipment of the laser guidance channel was located in the air intake channel. The prototype rocket successfully passed ground bench tests. The launches were to take place at the same test site near the village of Nenoksa. It was planned to carry out from 5 to 9 launches. However, the development of a new rocket and new system laser guidance was discontinued approximately in 1988-89. The known data of the new guidance system is that the beam had an approximate diameter of 10 meters, the detection and recognition range was approximately 15 kilometers.
P-1000 "Vulcan" (3M70) - anti-ship missile system. Tactical and technical characteristics of the P-1000 "Vulcan" Length 11.7 m Diameter 0.88 m Wingspan 2.6 m Launch weight 7000-8000 kg Speed Mach number (km/h) at altitude: 2.5 (3077) y surfaces: 2 (2460) Maximum firing range up to 1000 km Inertial + radar control system High-explosive-cumulative warhead: 500 kg (explosive mass) nuclear: 350 kt Development of the P-1000 “Vulcan” (3M70) complex was started by NPO Mashinostroeniya ( previously - OKB-52) V.N. Chelomey (since 1984, general designer - G.A. Efremov) according to the Resolution of the USSR Council of Ministers of May 17, 1979. The rocket is a further development of the P-500 complex rocket with the preservation of launch equipment and a noticeable increase in range due to the use of a new starting engine, an increase in fuel volumes for the sustainer stage, a reduction in armor weight and other improvements. The first test launch from the SM-49 ground stand in Nenoksa - December 3, 1982 (10 hours 55 minutes) - the launch was unsuccessful - the launch block did not separate from the rocket, the rocket fell apart and fell after 8 flights. The second launch - April 9, 1983 - a similar result at 9 seconds of flight. As a result of the analysis of unsuccessful tests, it was established that the failures occurred due to the fault of the rocket control system. The third launch was successful (probably June 1983). Tests with SSGN pr.675MKV began on December 22, 1983. Conducting joint tests of the P-1000 complex and SSGN pr.675MKV - 1985, first launch within the framework of joint tests - 2 rocket salvo(both missiles hit the target despite the failure of the pressure maintenance system in the instrument compartment and operator error). The second launch as part of the joint tests - November 8, 1985 - a three-missile salvo, one missile had a radar sighting failure, the other two missiles hit their targets. As a result of flight design and joint tests, 18 missile launches were carried out, of which 11 launches were considered successful. Launcher: - ground launcher SM-49 - for missile testing at the Nenoksa test site; - missile cruisers pr.1164 - probably a single-container launcher SM-248, similar to the P-500 complex - SSGN pr.675MKV - probably a single-container launcher similar to the P-500 complex Control system and guidance - inertial missile control system with correction according to radar seeker data - developed by the Central Research Institute "Granit", chief designer control system by A.V. Chizhov, on-board radio equipment - B.L. Godlinik, autopilot - A.N. Kuchin, digital computer - V.A. Nikoltsev and E.A. Gorbachev. Target selection is probably either automatic or based on remote control (by the ship operator based on data Missile radar) or combined. The rocket uses an A21 autopilot with a B9 on-board computer (different from the P-500 missiles) made on a new element base, which, coupled with a new launch engine and a different (probably) control algorithm for the launch section of the trajectory, made it possible to increase the range. The noise immunity of the seeker radar has been significantly improved by improving the on-board computer. Shipborne and onboard (placed on the rocket) instruments automated system controls, as well as control and testing equipment of the complex, were created anew. As part of the "Vulcan" research and development project, the "Radiation" research project was carried out, during which the task was set to analyze the impact of damaging factors nuclear explosion (anti-aircraft missile) on attacking anti-ship missiles. During the research work, a real nuclear explosion was carried out in a specially equipped adit at the test site New land. Tests showed that most elements of the onboard missile control systems were affected by neutron radiation within the distance of mechanical damage from a nuclear explosion. Some of the microcircuits received irreversible changes at a greater distance, which necessitated their modification for use in the onboard missile systems of the Vulcan complex. 3M70 rocket: Design - new materials were used in the design - incl. titanium alloys. Armor protection has been reduced. Engines: - launch-acceleration stage - solid propellant rocket engine with controlled nozzles, more powerful than the P-500. Can be used with the launch solid propellant rocket motor of the P-500 "Basalt" missiles. There is a possibility that there are no published photographs of the original Vulcan solid propellant rocket engine yet. The operating time of the launch-acceleration stage is 12 s - the sustainer - short-life turbojet engine KR-17V, similar to the rocket engine of the P-500 complex. Developed by OKB-300 GKAT. Carriers: - missile cruiser Project 1164 "Varyag" (entered service on October 16, 1989 under the name "Chervona Ukraine") was initially armed with the P-1000 complex. It is also likely that by 2006, the P-1000 complex was installed at the Moscow RK instead of the P-500 during modernization. It was also planned to install it on the unfinished missile cruiser "Ukraine" (formerly "Admiral Lobov", located at the Shipyard in Nikolaev). The ship has 16 non-rechargeable launchers (reloading is carried out in the port). - SSGN Project 675MKV - re-equipment of 5 SSGN Project 675MK (K-1, K-22, K-34, K-35 and K-10) on Project 675MKV was carried out by the Zvezdochka Shipyard. The re-equipment of the K-1 SSGN began on December 15, 1981 and was completed in 1983. The modernization of the K-10 SSGN has not been completed; a total of 4 SSGNs have been converted. On SSGNs, the launchers of the P-500 complex are replaced by launchers of the Vulcan complex (8 units per submarine). Launchers with surface launch. The firing control system on the submarine is Argon-675MKV. For target designation based on satellite data, the Kasatka system was used. SSGNs were withdrawn from the Navy from July 1992 to July 1994 (all 4 units).
DATA FOR 2015 (standard update)
P-1000 "Vulcan" complex, 3M70 missile - SS-N-12 mod.2 SANDBOX
Anti-ship cruise missile. The development of the complex was started by NPO Mashinostroeniya (formerly OKB-52) by V.N. Chelomey (since 1984, general designer - G.A. Efremov) according to the Resolution of the Council of Ministers of the USSR dated May 17, 1979. The rocket is a further development of the complex's rocket with the preservation of the launch equipment and a noticeable increase in the range due to the use of a new launch engine, an increase in the volume of fuel for the sustainer stage, a reduction in the weight of the armor and other improvements.
The first test launch from the SM-49 ground stand in Nenoksa - December 3, 1982 (10 hours 55 minutes) - the launch was unsuccessful - the launch block did not separate from the rocket, the rocket fell apart and fell after 8 flights. The second launch - April 9, 1983 - a similar result at 9 seconds of flight. As a result of the analysis of unsuccessful tests, it was established that the failures occurred due to the fault of the rocket control system. The third launch was successful (probably June 1983). Tests with SSGN pr.675MKV began on December 22, 1983. Conducting joint tests of the P-1000 complex and SSGN pr.675MKV - 1985, the first launch within the framework of joint tests - 2-missile salvo (both missiles hit the target despite the failure of the system maintaining pressure in the instrument compartment and operator error). The second launch as part of the joint tests - November 8, 1985 - a three-missile salvo, one missile had a radar sighting failure, the other two missiles hit their targets. As a result of flight design and joint tests, 18 missile launches were carried out, of which 11 launches were considered successful. Tests of the control system and test equipment were completed in 1985. In December 1985, an Act on the completion of joint tests was signed with a recommendation for the P-1000 Vulcan complex to be put into service with control tests carried out in 1986. Allocated for control tests 8 missiles and it was planned to carry out a 4-missile salvo and 4 single missile launches with different programs. One of the single launches (April 24, 1986) took place with the launch engine of the complex’s rocket under the program of the P-500 complex’s rocket control system. The launch was successful. On June 18 and 19, 1986, two successful launches took place to test the missiles' noise immunity. A four-missile salvo took place on July 4, 1986 (three missiles were equipped with telemetry equipment due to the fact that the equipment at the test site could not receive information from 4 missiles). The missile, not equipped with a telemetry system, lost control while approaching the target; the reason has not been established.
In 1986, the creators of the complex were awarded the Lenin Prize of the USSR (). The Vulcan complex was put into service on December 18, 1987. Serial production of missiles of the Vulcan complex was carried out by Strela Production Association in Orenburg. The missile was produced from 1985 to 1992.
Launcher:
- ground launcher SM-49 - for missile testing at the Nenoksa test site;
- missile cruisers Project 1164 - probably a single-container SM-248 launcher, similar to the complex
- SSGN pr.675MKV - probably a single-container launcher similar to the complex
Control system and guidance- inertial missile control system with correction according to radar seeker data - developed by the Granit Central Research Institute, chief designer of the control system A.V. Chizhov, on-board radio equipment - B.L. Godlinik, autopilot - A.N. Kuchin, on-board computer - V.A. Nikoltsev and E.A. Gorbachev. Target selection is probably either automatic or based on the principle of telecontrol (by the ship operator based on missile radar data) or combined. The rocket uses an A21 autopilot with a B9 on-board computer (different from the P-500 missiles) made on a new element base, which, coupled with a new launch engine and a different (probably) control algorithm for the launch section of the trajectory, made it possible to increase the range. The noise immunity of the seeker radar has been significantly improved by improving the on-board computer. The shipborne and onboard (placed on the rocket) instruments of the automated control system, as well as the control and testing equipment of the complex, were created anew.
The missile control system, depending on the configuration of the launch engine, can operate according to the launch and flight program of the P-500 "Basalt" anti-ship missiles or according to the "Vulcan" program.
The missile guidance algorithms use selection logic main goal in the ships order. After receiving the coordinates of the target, the missile with the radar (radar sight) turned off descended to a low altitude and flew to the target coordinate point. At the target coordinate point, the radar (radar sighting device) was turned on and the target was selected and captured. The size of the targets and the distance of the targets from the target coordinate point were analyzed. The free agglorhythm made it possible to select the largest target in the order of ships.
In order to overcome missile defense and air defense, the missile is provided with anti-aircraft maneuvering at low altitude and dispersing missiles in a salvo along the front (with preliminary assembly of missiles into a group) before turning on the radar at the final stage. The rocket is equipped with an active jamming station for the 4B-89 "Shmel" defense system, developed since 1965 in the laboratory of department No. 25 of the Granit Central Research Institute under the leadership of R.T. Tkachev and Yu.A. Romanov.
The instrument compartment on the rocket is hermetically sealed and equipped with a pressure maintenance system (tested by launches from a coastal stand in Nenoksa starting from March 25, 1984.
A resolution of the Council of Ministers of the USSR in October 1987 ordered work to improve the accuracy of the Vulcan missiles with the development of a high-precision laser guidance channel and the creation of the Vulcan LK missile. Work on the pulsed laser guidance channel was carried out by the Granit Central Research Institute under the leadership of S.A. Sharov. The system recognized geometric parameters the target ship and issued commands to correct the missile’s flight path to hit the most vulnerable areas of the target ship. Tests of the system were carried out in Sevastopol on passing ships and from an Il-18 flying laboratory aircraft. The development of a laser guidance channel as a missile guidance system began before 1987. The chief designer of the onboard missile equipment was V.G. Senkov, the chief designer of the laser channel was S.N. Sharov. It was planned to launch serial missiles equipped with a laser channel seeker in 1987-1989. The laser channel equipment was placed in the air intake diffuser. The technological rocket for ground testing of the system has passed bench tests. At the Northern test site in Nenoksa, it was planned to carry out 5 missile launches from a ground stand (according to other data, 9 missiles were allocated for testing). But probably in 1988-1989. The development of the "Vulcan LC" theme was discontinued.
Beam diameter - approx. 10 m
Recognition range - 12-15 km
Experimental laser channel of the missile control system complex P-1000 "Vulcan", 1988 (photo - showroom of NPO "Mashinostroenie", Reutov, 08/15/2006, http://www.novosti-kosmonavtiki.ru)
As part of the "Vulcan" research and development project, the "Radiation" research project was carried out, during which the task was set to analyze the impact of the damaging factors of a nuclear explosion (anti-aircraft missile) on attacking anti-ship missiles. During the research, a real nuclear explosion was carried out in a specially equipped adit at the Novaya Zemlya test site. Tests showed that most elements of the onboard missile control systems were affected by neutron radiation within the distance of mechanical damage from a nuclear explosion. Some of the microcircuits received irreversible changes at a greater distance, which necessitated their modification for use in the onboard missile systems of the Vulcan complex.
Rocket 3M70:
Design- new materials were used in the design - incl. titanium alloys. Armor protection has been reduced.
Model of the 3M70 rocket of the Vulcan complex with an increased SRS, MAKS-2009 air show (photo - A.V. Karpenko, http://bastion-karpenko.narod.ru/).
Engines:
- launch-acceleration stage - solid propellant rocket engine with controlled nozzles, more powerful than that of . Can be used with the launch solid propellant rocket motor of the P-500 "Basalt" missiles. There is a possibility that there are no published photographs of the original Vulcan solid propellant rocket engine yet.
Operating time of the start-acceleration stage - 12 s
Sustainer - short-life turbojet engine KR-17V, similar to the rocket engine of the complex. Developed by OKB-300 GKAT.
Tail parts of missiles of the P-1000 and P-500 complexes with nozzles of propulsion engines and antennas (photo from the Skeptic-2 archive, http://forums.airbase.ru).
Rocket of the "Vulcan" complex with the original enlarged SRS, model, MAKS-2009 exhibition (http://maks.sukhoi.ru)
Performance characteristics of the missile:
Length - 11.7 m
Case diameter - 0.88 m
Wingspan - 2.6 m
Starting weight - 9300 kg (?)
Weight without starting engine - 5070 kg (4800 kg according to other data)
Range - 550-700 km (depending on the flight profile), some sources indicate 1000 km
Speed - 2 / 2.5 M (at low altitude / at high altitude)
Flight altitude - minimum - 15-20 m
Warhead types:
- high-explosive-cumulative; armor penetration tests of warheads were carried out by launches on a ground stand (“jet track”). According to calculations, 3 missiles are required to destroy an aircraft carrier.
Explosive mass - 500 kg
Armor penetration - up to 400 mm
Nuclear power 350 kt
Modifications:
- P-1000 "Vulcan" - anti-ship missile.
- "Vulcan LK" - modification of the missile of the "Vulcan" complex with a laser guidance channel ( see "Control and Guidance System", above)
Carriers:
- missile cruiser Project 1164 "Varyag" (entered service on October 16, 1989 under the name "Chervona Ukraine") was initially armed with the P-1000 complex. It is also likely that by 2006, the P-1000 complex was installed at the Moscow RK instead of the P-500 during modernization. It was also planned to install it on the unfinished missile cruiser "Ukraine" (formerly "Admiral Lobov", located at the Shipyard in Nikolaev). The ship has 16 non-rechargeable launchers (reloading is carried out in the port).
Launch of the P-1000 "Vulcan" missile from missile cruiser"Varyag" pr.1164, probably 1994 (photo from the Skeptic-2 archive, http://forums.airbase.ru)
Missile cruiser "Moskva" pr.1164, early 2000s (http://militaryphotos.net)
Loading ammunition onto the missile cruiser "Moskva" pr.1164, Sevastopol, August 14, 2004 (photo - USSRNAVY, http://forums.airbase.ru)
Loading 3M70 missiles of the P-1000 "Vulcan" complex onto the missile cruiser "Moscow", Black Sea Fleet, 2006 (photo - Dmitry Stogniy, http://militaryphotos.net)
- SSGN Project 675MKV - re-equipment of 5 SSGN Project 675MK (K-1, K-22, K-34, K-35 and K-10) on Project 675MKV was carried out by the Zvezdochka Shipyard. The re-equipment of the K-1 SSGN began on December 15, 1981 and was completed in 1983. The modernization of the K-10 SSGN has not been completed; a total of 4 SSGNs have been converted. On SSGNs, the launchers of the complex are replaced by launchers of the Vulcan complex (8 pcs per submarine). Surface launched launchers. The firing control system on the submarine is Argon-675MKV. For target designation based on satellite data, the Kasatka system was used. SSGNs were withdrawn from the Navy from July 1992 to July 1994 (all 4 units).
Status- USSR and Russia
- 2003 May 16 - the missile cruiser "Moscow" pr.1164 carried out training launches of missiles of the P-1000 "Vulcan" complex in the northeastern part of the Arabian Sea.
2008 January 22 - missile cruiser of the Russian Black Sea Fleet "Moscow" pr.1164 as part of the active phase of joint naval exercises strike force Northern and Black Sea Fleet Russia in the Atlantic used the unique Basalt anti-ship missile system with the Vulcan anti-ship missile system to fire at a sea target, successfully hitting the target (
ULA Corporation (United Launch Alliance) (USA), one of the most famous developers and manufacturers of space technology in the World, a joint venture between Boeing and Lockheed Martin, has been creating a new generation Vulcan launch system for about 2 years, which will allow make satellite decommissioning cheaper and more accessible. It is expected that the Vulcan system will be a serious competitor to the reusable Falcon rocket 9v1.1R (R from the English Reusable, reusable) by Elon Musk.
Instead of returning the entire first stage, ULA engineers propose returning only its engines. Reusing rocket parts is a key component of Vulcan. ULA believes that reuse is NOT about soft landing the ENTIRE first stage. Instead, it is proposed to return only a small, but the most expensive part of the stage - the engines; this is simpler and cheaper. One of the ULA leaders said the following about this: “ The heaviest thing in a rocket is not always the most expensive.».
Before Elon Musk entered the launch market, ULA was a monopolist and charged launch prices at full program, without hesitation. With the arrival of Musk, prices for launches dropped significantly (from $110 million to $60 million) and some of the launches from ULA went to Musk, and a significant part. For fun, we can say that the development of the Vulcan rocket is carried out under the motto of Star Wars: "The Empire Strikes Back." I read that work on creating reusable rockets began at ULA a long time ago, almost in the early 2000s, but then stopped. They were a monopoly back then and it didn’t make any sense for them to reduce the cost of launching. We must give Musk his due - he attracted the attention of the whole world to reusable rockets, and how!
Before continuing the story about the Vulcan rocket, I would like to remind, for those who are not in the know, the characteristics of the first (returnable) stage of the Falcon 9v1.1R rocket and the return technology. The first stage is equipped with 9 Merlin 1D engines, with increased thrust and specific impulse. New type engine received the ability to throttle from 100% to 70% and possibly even lower. The layout of the engines has been changed: instead of three rows of three engines, a layout with a central engine and the others arranged in a circle is used. The central engine is also mounted slightly lower than the others. The scheme is called Octaweb, it simplifies general device and the first stage engine compartment assembly process.
The total thrust of the engines is 5885 kN at sea level and increases to 6672 kN in vacuum, specific impulse at sea level is 282 s, in vacuum - 311 s. The nominal operating time of the first stage is 180 s. The height of the first stage is 45.7 m, the dry weight of the v1.1 stage is about 23 tons and about 26 tons for the (R) modification. The mass of the placed fuel is 395,700 kg, of which 276,600 kg is liquid oxygen and 119,100 kg is kerosene. Weight of one Merlin 1D engine: 450-490 kg. The mass of 9 engines is approximately 4.5 tons, which is 17.3% of the DRY mass of the first stage. Technology and return trajectory of Falcon 9v1.1R shown in Fig. 1.
Rice. 1. Flight path.
From the diagram it can be seen that in order to land the first stage on the folding supports, it is necessary to turn it with the engines forward, i.e. rotate around its axis, and for this Falcon 9 v1.1 needs to be supplemented with equipment for turn and landing systems, which is what was done:
1. The first stage is equipped with four folding landing struts used for soft landing. The total mass of the struts reaches 2100 kg (this is almost half the weight of all 9 engines for which all this was started).
2. Navigation equipment has been installed for the stage to exit to the landing point (you need to get exactly to the site in the OCEAN);
3. Three of the nine engines are designed for braking and have an ignition system for restarting;
4. Folding lattice titanium rudders are installed on the top of the first stage to stabilize rotation and improve controllability during the descent phase, especially while the engines are switched off. Titanium handlebars are slightly longer and heavier than their aluminum predecessors, they increase stage control capabilities, withstand high temperature without the need for an ablative coating and can be used an unlimited number of times without inter-flight maintenance.
5. An orientation system is installed at the top of the stage - a set of gas nozzles that use the energy of compressed nitrogen to control the position of the stage in space before releasing the lattice rudders. On both sides of the stage there is a block, each with 4 nozzles directed forward, backward, to the side and down. The downward-facing nozzles are used before firing the three Merlin engines during stage braking maneuvers in space, the pulse produced lowering the fuel to the bottom of the tanks, where it is captured by the engine pumps. Titanium lattice rudders and a block of gas nozzles of the attitude control system (under the flag) before and after landing are shown in photo 2. The paint under the nozzles has not peeled off because the energy of compressed nitrogen is used.
Rice. 2. Titanium lattice rudders and a block of gas nozzles for the attitude control system
For landing, SpaceX rents TWO spaceports - Cape Canaveral Air Force Station (LC-13) on the East (Atlantic) coast and Vandenberg Air Force Base (SLC-4-West) on the West (Pacific) coast. Accordingly, TWO offshore platforms are used, each of which is a converted barge. The engines and GPS equipment installed on them allow them to be delivered to the desired point and held there, creating a stable landing site, but the possibility of an accident-free landing is affected by the weather. SpaceX has two such platforms, because... the width of the platforms does not allow them to pass the Panama Canal from Vandenberg Air Force Base to Cape Canaveral.
Propulsion descent of the entire first stage reduces the MAXIMUM payload of the launch vehicle by 30-40%. This is due to the need for redundancy significant amount fuel for braking and landing, as well as additional mass of landing equipment (landing legs, lattice rudders, jet control system, etc.). Let me remind you that rockets do not always launch with a 100% load; there is almost always an incomplete load and averages from 10 to 17%.
Let's return to the story about Vulcan rocket engine reentry technology. The planting technology is shown in Figure 3.
Rice. 3.
The technology is called Sensible, Modular, Autonomous Return Technology (SMART - translated from English as smart, smart). The propulsion and steering engines will be caught in the air; this is the most expensive part of the first stage. ULA's plan is for the bottom of the rocket to detach after the first stage completes its operation. Then, using an inflatable thermal shield, it reenters the atmosphere. The parachutes will open, the helicopter will pick up the engine block and land with it in any place convenient for this - no landing spaceports or floating barges are needed.
In technology SMART additional The landing equipment, which reduces the payload mass, consists only of a parachute and inflatable thermal protection. Helicopter pickup of cargo dropped by parachute is a common technology in aviation and astronautics. About 2 million such operations have been performed worldwide, and they continue to be performed.
Fig.4
Rice. 5
ULA's Delta 4 and Atlas 5 (Atlas 5 still flies on our RD-180s and will continue to do so until at least 2019) are modular, and the Vulcan will also be modular with different head fairing sizes or additional boosters to allow increase productivity. Modularity distinguishes ULA from other players in the American market (our Hangar is also modular): SpaceX has a regular Falcon 9 and a planned heavy version, Arianespace can only offer Vega and Soyuz, but there are no gradations. “Vulcan” will be available in 12 variants from medium to heavy class. The missile will be available with nose fairings with a diameter of either four or five meters. The first option can accommodate up to four solid fuel boosters, the second - up to six. In the latter case, the rocket will become an analogue of the heavy modification Delta 4.
Vulcan's first launch is scheduled for 2019. It will be carried out either using two Blue Origin BE-4 engines at liquefied gas, or with a pair of more traditional kerosene Aerojet Rocketdyne AR-1. The creation process is quite expensive, so the rocket will be developed in several stages. We are talking about billions: specific numbers are not mentioned, but historically it is known that the development of a new rocket engine costs $1 billion, and the start of work on new rocket- approximately 2 billion dollars.
(missiles): 3M70) - Soviet/Russian anti-ship missile system (ASM). Is a development of the system P-500 Basalt
History of creation
The P-1000 Vulcan missile was developed as a development of the successful anti-ship missile P-500 “Basalt”, in turn, is a development of the old P-35 missile. The goal of the designers was to create a longer-range missile, while maintaining the same dimensions and weight and the ability to use existing ones without major modernization launch complexes and infrastructure for the P-500. A government decree of May 15, 1979 marked the beginning of the development of a new P-1000 Vulcan anti-ship missile system.
The first test launch from a ground stand as part of flight design tests was carried out at the Nenoksa test site in July 1982.
The development of the control system and a number of other equipment was completed in 1985.
The complex was put into service on December 18, 1987.
Design
In the main design elements, the P-1000 missile repeats the previous P-500 “Basalt”. It is cigar-shaped with a delta folding wing and an engine air intake under the fuselage. The main differences between the P-1000 and its predecessor are related to the reduction in the mass of the rocket structure in order to increase the fuel supply.
The body of the P-1000 was made using titanium alloys, which made it possible to reduce the weight of the structure without reducing its strength. The propulsion system is identical to the P-500 (short-life turbojet engine KR-17V). New starting accelerator increased power, with a deflectable thrust vector, allows you to optimize the rocket trajectory at launch and ensure take-off with a large launch weight. The mass of the high-explosive fragmentation warhead was reduced to 500 kilograms. Reservations have been reduced. All these measures made it possible to increase the fuel supply without changing the dimensions of the rocket, and to increase its range to 700-1000 km.
The P-1000 "Vulcan" missile uses a combined flight pattern similar to the P-500 "Basalt". Most The missile covers the trajectory at a high altitude, and near the target it decreases and the remaining distance travels at an ultra-low altitude (about 15-20 meters), hiding from detection by radars over the horizon. Due to the larger fuel reserve on the P-1000, the duration of its low-altitude section can be increased, which makes the missile less vulnerable to long-range enemy air defense systems.
The missile seeker uses target identification and distribution algorithms created based on work on the P-700 Granit. The rocket can identify individual ships, analyze their position in the order and select the most valuable ones. Target selection is probably either automatic or based on the principle of telecontrol (by the ship operator based on missile radar data) or combined. Like the P-700, P-1000 missiles exchange data during an attack and form a common strategy of action, distributing targets and performing simultaneous approaches from different directions.
In order to overcome missile defense and air defense, the missile is equipped with anti-aircraft maneuvering at low altitude and the dispersal of missiles in a salvo along the front (with preliminary collection of missiles into a group) before turning on the radar at the final stage. The missile is equipped with an active jamming station for the 4B-89 Shmel defense system ", developed starting this year in the laboratory of department No. 25 of the Central Research Institute "Granit" under the leadership of R. T. Tkachev and Yu. A. Romanov.
A resolution of the USSR Council of Ministers in October 1987 ordered work to improve the accuracy of the Vulcan missiles with the development of a high-precision laser guidance channel and the creation of the Vulcan LK missile. The laser channel equipment (beam diameter - about 10 m, recognition range - 12-15 km) was placed in the air intake diffuser and recognized the geometric parameters of the target ship, generating commands to correct the trajectory to hit the most vulnerabilities. The system was tested in Sevastopol on passing ships from the Il-18 flying laboratory. The launches of serial missiles equipped with a laser channel seeker were planned to be carried out in - years. But, probably, in -1989 the development of the “Vulcan LC” theme was stopped.
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