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50-573: The name of the system is Russian in origin, and is an acronym, АПАС , in the Cyrillic alphabet, from the Russian Андрогинно-периферийный агрегат стыковки ( Androginno-periferiynyy agregat stykovki ). The English acronym was designed to be just the same letters but in the Latin alphabet, for which the first two words are direct counterparts of those in the original. The third word in Russian comes from

100-662: A $ 18 million contract signed in June 1993. Rockwell International, prime contractor for the Shuttle, accepted delivery of hardware from Energiya in September 1994 and integrated it onto Space Shuttles' Orbiter Docking System, an add-on that was installed in the payload bay and was originally meant for use with Space Station Freedom . Although Energia's code for the Shuttle APAS is APAS-95, it has been described as being basically

150-517: A 1-meter double ring and cone docking system that had four guide fingers and attenuators on both rings, so either half could be active or passive during docking. The Structures and Mechanics Laboratory at MSC made 16-millimeter movies demonstrating this system in action, which Johnson took to Moscow in November, along with a booklet describing the system and a model of the capture latches. To Johnson's surprise, Vladimir Syromyatnikov had been working on

200-689: A Salyut space station for cost and technical reasons. Final official approval of a joint docking mission came in Moscow on 24 May 1972. U.S. President Nixon and U.S.S.R. Premier Aleksey N. Kosygin signed the Agreement Concerning Cooperation in the Exploration and Use of Outer Space for Peaceful Purposes, including development of compatible spacecraft docking systems to improve safety of manned space flight and to make joint scientific experiments possible. The first flight to test

250-542: A leak that would cause one shock absorber to collapse on impact. A study of various combinations had led the MSC specialists to conclude that four guides and eight shock absorbers was the optimum design. Creasy pointed out too that the most likely trouble with an electromechanical system would be a freeze-up or binding of one of the pairs of attenuators. Thus, the Soviets had sought to minimize the number of pairs in their system for

300-490: A new shroud, they would have to test out the launch aerodynamics of the altered hardware. The Americans had hoped to argue for a larger tunnel, but such a change appeared to be too great for their counterparts. After the June meetings, Johnson had put Bill Creasy and his mechanical designers to work on the preliminary design of a docking mechanism. By the time the NASA delegation left for Moscow, Creasy's crew had designed and built

350-439: A number of connectors, providing for transfer of power, data, and fuel between two docked vehicles. A "hybrid" version, combining the design of SSVP and APAS-95 , is also available, used for permanent docking of space station modules. This version uses the probe-and-drogue design of the standard SSVP, but with a hard-dock collar from APAS-95. The APAS-95 collar has twelve latches instead of the eight of standard SSVP. This variant

400-573: A passive drogue. The probe enters the drogue, and its tip is grasped by soft-capture latches which are then retracted using electrically driven motors to provide close alignment. Eight hard-capture locks then firmly attach the two spacecraft. After hard docking, the pressure between spacecraft is equalized using the Interface Leak Check System. The port contains a transfer tunnel, with an internal diameter of 800 mm (31.5 in). The ring surrounding this tunnel also includes

450-418: A similar drawing for the structural latches. T.O. Ross then took these drawings and conducted a dimensional analysis to be sure that all items were compatible. Agreement on technical specifications for the docking system cleared the way for NASA to begin discussions with Rockwell about building the docking system. In April 1972, the Soviets informed NASA that they had chosen to use a Soyuz spacecraft in place of

500-530: A variation of NASA's ring and cone concept since the previous October. Instead of the four guide fingers in the American proposal, Syromyatnikov suggested three, and in lieu of hydraulic shock-absorbers, he proposed electromechanical attenuators. In essence, the Soviets had accepted the idea of using a set of intermeshing fingers to guide the two halves of the docking gear from the point of initial contact to capture. The concept of using shock absorbing attenuators on

550-574: Is a docking standard used by Soviet and Russian spacecraft, sometimes called RDS for Russian Docking System . It has been used on all variants of Soyuz other than the Soyuz 7K-L3 and early flights of the Soyuz 7K-OK , as well as Progress , TKS , ATV , and on all Soviet and Russian space stations . SSVP was initially conceived in 1967 by the TsKBEM design bureau for use on the then-planned OIS military space station. Though OIS never flew, in 1970

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600-511: Is a unique hybrid derivative of the Russian APAS-89/APAS-95 system, as it has 4 petals instead of 3 along with 12 structural hooks and is a combination of an active "probe and drogue" soft-dock mechanism on port and passive target on airlock. Probe-and-drogue docking system Sistema Stykovki i Vnutrennego Perekhoda, SSVP ( Russian : Система стыковки и внутреннего перехода , System for docking and internal transfer )

650-481: Is an active and a passive side, but both sides can fulfill either role. There are three basic variations of the APAS. Co-developed by American and Soviet engineers through a series of in-person meetings, letters and teleconferences, APAS-75 was initially planned to be used on an American mission to a Salyut space station which instead became Apollo–Soyuz . There were differences between the American and Soviet version of

700-516: Is known as SSVP-M8000 . These hybrid SSVP ports are used to permanently connect Pirs, Nauka, Poisk and Zarya to Zvezda and Prichal to Nauka. Modified Passive hybrids of SSVP-M8000 are used on lateral ports of Prichal and are known as SSPA-GB 1/2 . It converts passive Hybrid SSVP-M8000 Docking System to passive SSVP-G4000. The docking ring initially used for Soyuz MS-18 and Progress MS-17 docking on Nauka until detached by Progress MS-17 inflight for Prichal module arrived on ISS. This adapter

750-576: Is termed as SSPA-GM . It was made for the Nauka nadir and Prichal nadir ports of the International Space Station, where Soyuz and Progress spacecraft had to dock to a port designated for modules. Before removal of SSPA-GM, the docking ring is 80 cm (31 in) in diameter; that becomes 120 cm (47 in) after removal. Vladimir Syromyatnikov Vladimir Sergeevich Syromyatnikov (January 7, 1933 - September 19, 2006)

800-539: The Manned Spacecraft Center (MSC) draw up a "design specifically adequate to requirements of a particular CSM/Salyut mission, the design being representative only of the fundamental form and function of docking gear satisfying the requirements for compatible docking system for future spacecraft." During a meeting in Houston during June 1971, Soviet docking specialist Valentin N. Bobkov indicated that

850-778: The Mir , and for most spacecraft dockings (with the exception of the Space Shuttle flights, and Soyuz TM-16 , which used the APAS-89 docking mechanisms located on Kristall and the Mir Docking Module . ) The modern version of SSVP is SSVP-G4000 . The Russian segment of the International Space Station features eight available passive SSVP-G4000 ports, located on Zvezda -aft, Rassvet , Poisk , and Prichal . An additional port, on Zarya -nadir,

900-535: The 1990s, following the fall of the Soviet Union, he updated the design of his docking mechanism for the meeting of the Mir space station and the Atlantis Space Shuttle . Syromyatnikov's designs are still used by spacecraft visiting the International Space Station . Having failed to get support for a solar sail program in the mid-1980's, Syromyatnikov pivoted to use the technology as

950-460: The Americans observed that while the U.S.S.R. mechanism was more complex mechanically than the American one, it was suitable for the mission and "sophisticated" in its execution. The two sides reviewed and signed the two-fifths-model test plan and scheduled the test for December in Moscow. The Preliminary Systems Review (PSR) was planned to be a "formal configuration review ... initiated near

1000-610: The Apollo probe. This proposal also called for developing docking gear that could be used in either an active or passive mode; when one ship's system was active, the other would be passive. Looking into the detailed design of the mechanism, the two sides had further agreed that the capture latches would follow the design developed at MSC and the structural latches and ring would follow the Soviet pattern. These paired sets of hooks had been successfully used on both Soyuz and Salyut. In addition,

1050-532: The German Aggregat , meaning "complicated mechanism", and the last means "docking". The last two words in the English name were picked to begin with the same equivalent letters as in the Russian name. The idea behind the design is that unlike with the probe-and-drogue docking system , any APAS docking ring can mate with any other APAS docking ring; both sides are androgynous . In each docking there

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1100-414: The Soviets also favored some version of the double ring and cone. Bobkov illustrated through sketches that the overall diameter of the docking system could not exceed 1.3 meters, because any larger system would require a change in the launch shroud. When Johnson raised the question of altering the shroud, the Soviets stressed the major impact that such a modification would have. In addition to having to design

1150-404: The active or passive role as required. For docking, the spade-shaped guides of the extended active unit (right) and the retracted passive unit (left) interacted for gross alignment. The ring holding the guides shifted to align the active unit latches with the passive unit catches. After these caught, shock absorbers dissipated residual impact energy in the American unit; mechanical attenuators served

1200-407: The active spacecraft's capture ring to buffer the impact of two spacecraft coming together was also acceptable. Both groups of engineers planned to retract the active half of the docking gear using an electrically powered winch to reel in a cable. Once retracted, structural or body latches would be engaged to lock the two ships together. Three basic issues had to be resolved — the number of guides,

1250-507: The area of hatch diameter, he noted that "it became apparent from the beginning ... that a hatch diameter greater than about 800 mm could not be incorporated into the Salyut spacecraft without great difficulty," but MSC had "long since reconciled itself" to a test hatch diameter of less than 1 meter. Johnson went on to comment that "the capture ring assembly had variously been called ring and cone, double ring and cone, and ring and fingers. It

1300-547: The design was selected for use on the Salyut and Almaz space stations. During its first attempted use on the Soyuz 10 mission, docking was unsuccessful due to a faulty hatch, and a failure in the automatic docking system. This led to a number of redesigns to reduce damage from accidental loads. In the 1980s, SSVP was further upgraded to support docking of large modules, such as the ones that would be used to construct Mir . They were used to attach all pressurized modules of

1350-654: The docking mechanism, but they were still mechanically compatible. Early on, the Americans called the device both the International Rendezvous and Docking Mission (IRDM) Docking Mechanism and the International Docking System. The device is called the Androgynous Peripheral Docking System (APDS) in the NASA press packet for ASTP. Unlike previous docking systems, either APAS-75 unit could assume

1400-688: The end of the conceptual phase, but prior to the start of detail design" work on the docking mechanism. As part of their presentation to the Preliminary Systems Review Board (the Board being the Technical Directors), Don Wade and Syromyatnikov included all the test data, specifications, and drawings for the docking system, as well as a design evaluation for the mechanism. After hearing their report, Lunney and Bushuyev felt three problem areas needed further study. First,

1450-608: The full-scale Soviet and American docking systems began in Houston during October 1973. When the USSR started working on Mir , they were also working on the Buran shuttle program. APAS-89 was envisioned to be the docking system for Buran with the Mir space station. The APAS-75 design was heavily modified. The outer diameter was reduced from 2030 mm to 1550 mm and the alignment petals were pointed inward instead of outward. This limited

1500-404: The group concurred on details regarding the alignment pins, spring thrusters (to assist in the separation of the spacecraft at undocking), and electrical connector locations. To evaluate the docking system concept and to ensure the establishment of compatibility at an early point in the development, the men planned to build a two-fifths-scale test model, the exact details of which would be decided at

1550-619: The group to present their specific recommendations to them in December and January. The group tests of the two-fifths-scale model and the second part of the Preliminary Systems Review for the docking system was the last joint activity scheduled for 1972. The Americans arrived in Moscow on December 6 and worked through December 15. Testing the scale models occurred at the Institute of Space Research in Moscow. Tests of

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1600-522: The guides were also included in the minutes. They were to be solid and not rodlike; as first proposed by the Soviets, and three in number. As long as the requirement for absorbing docking forces was met, each side was free to execute the actual attenuator design as it best saw fit. The Soviets planned to use an electromechanical approach designed for the Soyuz docking probe, and the Americans proposed to stick with hydraulic shock absorbers similar to those used on

1650-437: The interface seals were compressed, while the Soviet system gave data on compression of the seals but none for the latches. To assure the structural integrity of the transfer tunnel, it was important to know that all eight latches were closed. The third problem area was whether it was possible for the structural latches be inadvertently released. Bushuyev and Lunney called for a thorough re-evaluation of all these issues and advised

1700-523: The internal passage diameter of the docking port to about 800 mm. The Buran shuttle was finally canceled in 1994 and never flew to the Mir space station, but Mir's Kristall module was outfitted with two APAS-89 docking mechanisms. The Mir Docking Module , basically a spacer module between Kristall and the Shuttle, also used APAS-89 on both sides. APAS was selected for the Shuttle-Mir program and manufactured by Russian company RKK Energiya under

1750-486: The next joint meeting. Upon his return to Houston, Caldwell Johnson prepared a memorandum to document some of the informal understandings reached in Moscow. He indicated that this reflected "upon the manner in which the two countries will conduct and coordinate the next phase of the engineering studies of those systems ... The understandings ... were reached more often than not outside of formal meetings, and so are not likely otherwise to be reported." For example, in

1800-415: The other. The Soviets said they would draft the "Test Plan for Scale Models of Apollo/Soyuz Docking System" (IED 50003), while the Americans drew up the dimensions of the model and the test fixtures. Under the direction of Syromyatnikov, the Soviet team had readied their documentation in both English and Russian and had prepared their two-fifths-scale model of the docking system for the joint meeting. Some of

1850-443: The requirement for a spring thruster designed to help separate the two spacecraft had caught their attention, since the failure of this thruster to compress properly could prevent completion of docking. Second, Lunney and Bushuyev emphasized the importance of an indicator that would verify that the structural latches were properly in place. The American system provided information on the functioning of each latch but did not indicate that

1900-541: The same as APAS-89. It had a mass of 286 kg. APAS-95 was selected to join the American and Russian modules on the International Space Station (ISS) and to allow the Space Shuttle to dock. The Shuttle's Orbiter Docking System remained unchanged from when it was used for the Shuttle–Mir Program in 1995. The active capture ring that extends outward from the spacecraft captured the passive mating ring on

1950-516: The same function on the Soviet side. The active unit then retracted to bring the docking collars together. Guides and sockets in the docking collars completed alignment. Four spring push rods drove the spacecraft apart at undocking. The Americans selected North American Rockwell to construct seven docking mechanisms (two flight, four test, and one spare). The Soviet Union built five Soyuz spacecraft that used APAS-75. The first three flew as test systems ( Cosmos 638 , Cosmos 672 and Soyuz 16 ). One

2000-526: The same reason that the Americans had preferred a larger number to limit the probability of something going wrong. Since the United States had no significant engineering or hardware equity in its proposed design, and since the USSR had considerable equity in its proposed design, the Soviet design was selected as a baseline for the next phase of study. By the end of the November–December meeting,

2050-656: The space station's APAS-95 connection on the Pressurized Mating Adapter . The capture ring aligned them, pulled them together and deployed 12 structural hooks, latching the two systems with an airtight seal. The Pressurized Mating Adapters are permanently passive. The ASA-G is used only by the Nauka Science (or Experiment) Airlock to berth to the Nauka forward port on 4 May 2023, 01:00 UTC during VKD-57 spacewalk. The non-androgynous berthing mechanism

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2100-406: The systems was to be in 1975, with modified Apollo and Soyuz spacecraft. Beyond this mission, future crewed spacecraft of the two nations were hoped to be able to dock with each other. In July 1972, the group concentrated on spelling out more fully specifications for the docking system. Some refinements were made in the guides and other parts of the mechanism; as with the other groups, a schedule for

2150-444: The two nations cooperate on astronaut safety, including compatible docking equipment on space stations and spacecraft to permit rescue operations in space emergencies. Engineer Caldwell Johnson proposed a ring and cone system during a meeting in Moscow during October 1970. Boris N. Petrov rejected the simple adaptation of Apollo and Soyuz as a "space stunt" and had proposed developing a universal docking mechanism, Johnson suggested that

2200-446: The two teams had signed a set of minutes outlining the basic concept for a universal androgynous docking system. The formal statement read, "The design concept includes a ring equipped with guides and capture latches that were located on movable rods which serve as attenuators and retracting actuators, and a docking ring on which are located peripheral mating capture latches with a docking seal." Basic information on shapes and dimensions of

2250-514: The type of attenuators, and the type of structural latches — before the design of a universal system could proceed. Johnson, Creasy, and the other engineers in the Spacecraft Design Division had wanted to use four guides because they believed that it provided the best geometry when using hydraulic attenuators. As Bill Creasy subsequently explained it, the most probable failure situation using hydraulic attenuators would be

2300-437: The upcoming months was written, indicating documents to be prepared and tests to be conducted. After the team had a thorough look at the American two-fifths-scale docking system, which helped the designers discuss the operation of the mechanism and decide on refinements, they scheduled joint model tests for December. Then the engineers would be able to see just how the interfacing elements of one country's system mated with those of

2350-516: Was a Russian engineer and designer in the former Soviet space program . His notable designs including the docking mechanisms for crewed spacecraft ; it was his Androgynous Peripheral Attach System which, in the 1970s, linked the Soviet and American space capsules in the Apollo-Soyuz test flight. Syromyatnikov also helped design and develop Vostok , the world's first crewed spacecraft, which launched Yuri Gagarin into space in 1961. In

2400-411: Was agreed henceforth to call the capture ring 'ring' and the fingers 'guides.'" Bill Creasy and several of his colleagues worked with Yevgeniy Gennadiyevich Bobrov at the drafting table to lay out these first Soviet-American engineering drawings. Larry Ratcliff drew the capture ring and guides on drafting paper, and Robert McElya supplied the details of the structural interface ring, while Bobrov prepared

2450-618: Was used for the Apollo-Soyuz Test Project, Soyuz 19 the only Soyuz to actually use the docking system, and the last one flew as Soyuz 22 . On the American side the Apollo–Soyuz Docking Module carried one APAS-75 docking collar and one Apollo docking collar. In April 1970 NASA Administrator Thomas O. Paine suggested, in an informal meeting with Russian academician Anatoli Blagonravov in New York, that

2500-757: Was used to dock Rassvet. In addition to Russian spacecraft, the SSVP was also used on the European Automated Transfer Vehicle , which docked to the aft port of Zvezda. These ports were provided by Russia in exchange for the Data Management System, supplied by ESA for use in Zvezda. An upgraded version, designed for reusability and to provide a wider tunnel, is planned for use on the next-generation Orel spacecraft . SSVP consists of two components; an active probe, and

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