A space capsule is a spacecraft designed to transport cargo, scientific experiments, and/or astronauts to and from space.[1] Capsules are distinguished from other spacecraft by the ability to survive reentry and return a payload to the Earth's surface from orbit or sub-orbit, and are distinguished from other types of recoverable spacecraft by their blunt shape, not having wings and often containing little fuel other than what is necessary for a safe return. Capsule-based crewed spacecraft such as Soyuz or Orion are often supported by a service or adapter module, and sometimes augmented with an extra module for extended space operations. Capsules make up the majority of crewed spacecraft designs, although one crewed spaceplane, the Space Shuttle, has flown in orbit.
Current examples of crewed space capsules include Soyuz, Shenzhou, and Dragon 2. Examples of new crew capsules currently in development include NASA's Orion, Boeing's Starliner, Russia's Orel, India's Gaganyaan, and China's Mengzhou. Historic examples of crewed capsules include Vostok, Mercury, Voskhod, Gemini, and Apollo, and active programs include the New Shepard launches. A crewed space capsule must be able to sustain life in an often demanding thermal and radiation environment in the vacuum of space. It may be expendable (used once, like Soyuz) or reusable (like Crew Dragon).
The capsule was originally designed for use both as a camera platform for the Soviet Union's first spy satellite program, Zenit and as a crewed spacecraft. This dual-use design was crucial in gaining Communist Party support for the program. The design used a spherical reentry module, with a biconic descent module containing attitude control thrusters, on-orbit consumables, and the retro rocket for orbit termination. The basic design has remained in use for some 40 years, gradually adapted for a range of other uncrewed satellites.
It was a single-seat capsule that was 4.4 meters long and 2.4 meters in diameter, weighing 4.73 tonnes at launch.[2] The reentry module was completely covered in ablative heat shield material, 2.3 meters (7.5ft) in diameter, weighing 2,460 kilograms (5,420lb). The capsule was covered with a nose cone to maintain a low-drag profile for launch, with a cylindrical interior cabin approximately 1 meter (3.3ft) in diameter nearly perpendicular to the capsule's longitudinal axis. The cosmonaut sat in an ejection seat with a separate parachute for escape during a launch emergency and landing during a normal flight. The capsule had its own parachute for landing on the ground. Although official sources stated that Gagarin had landed inside his capsule, a requirement for qualifying as a first crewed spaceflight under International Aeronautical Federation (IAF) rules, it was later revealed that all Vostok cosmonauts ejected and landed separately from the capsule. The capsule was serviced by an aft-facing conical equipment module 2.25 meters (7.4ft) long by 2.43 meters (8.0ft), weighing 2,270 kilograms (5,000lb) containing nitrogen and oxygen breathing gasses, batteries, fuel, attitude control thrusters, and the retrorocket. It could support flights as long as ten days.[3] Six Vostok launches were successfully conducted, the last two pairs in concurrent flights. The longest flight was just short of five days, on Vostok 5 on June 14–19, 1963.[4]
Since the attitude control thrusters were located in the instrument module which was discarded immediately prior to reentry, the reentry module's path and orientation could not be actively controlled. This meant that the capsule had to be protected from reentry heat on all sides, determining the spherical design (as opposed to Project Mercury's conical design, which allowed for maximum volume while minimizing the heat shield diameter).[citation needed] During reentry, the heat of atmospheric friction is so great that air molecules around the capsule are ionized, creating a layer of plasma around the capsule which blocks radio communication with the ground. However, ionized gases in the plasma layer can also be used to create an artificial radio window, allowing communication signals to be transmitted and received despite the interference.[5] Some control of the capsule's reentry orientation was possible by offsetting its center of gravity. Proper orientation with the cosmonaut's back to the direction of flight was necessary in order to best sustain the which also maximized the 8 to 9 g-force.
The Voskhod space capsule, as flown in two variants
The Vostok design was modified to permit carrying multi-cosmonaut crews, and flown as two flights of the Voskhod programme. The cylindrical interior cabin was replaced with a wider, rectangular cabin which could hold either three cosmonauts seated abreast (Voskhod 1), or two cosmonauts with an inflatable airlock in between them, to permit extravehicular activity (Voskhod 2). A backup solid-fuel retro rocket was added to the top of the descent module. Vostok's ejection seat was removed to save space (thus there was no provision for crew escape in the event of a launch or landing emergency). The complete Voskhod spacecraft weighed 5,682 kilograms (12,527lb).
Lack of space meant that the crew members of Voskhod 1 did not wear space suits.[6] Both Voskhod 2 crew members wore spacesuits, as it involved an EVA by cosmonaut Alexei Leonov. An airlock was needed because the vehicle's electrical and environmental systems were air-cooled, and complete capsule depressurization would lead to overheating. The airlock weighed 250kg (551lb 2oz), was 700mm (28in) in diameter, 770mm (30in) high when collapsed for launch. When extended in orbit, it was 2.5m (8ft 2in) long, had an internal diameter of 1m (3ft 3in) and an external diameter of 1.2m (3ft 11in). The second crew member wore a spacesuit as a precaution against accidental descent module depressurization. The airlock was jettisoned after use.
The lack of ejection seats meant that the Voskhod crew would return to Earth inside their spacecraft unlike the Vostok cosmonauts who ejected and parachuted down separately. Because of this, a new landing system was developed, which added a small solid-fuel rocket to the parachute lines. It fired as the descent module neared touchdown, providing a softer landing.
The Mercury program was the United States' first crewed space program. It ran from 1958 through 1963, with the goal of putting a human in orbit around the Earth and returning him safely. The program used a small capsule attached to a booster rocket to achieve orbit. The development of the Mercury capsule began in earnest after NASA selected the McDonnell Aircraft Corporation as its contractor in 1959.[7] The Mercury spacecraft's principal designer was Maxime Faget, who started research for human spaceflight during the time of the NACA.[8] It was 10.8 feet (3.3m) long and 6.0 feet (1.8m) wide; with the launch escape system added, the overall length was 25.9 feet (7.9m).[9] With 100 cubic feet (2.8m3) of habitable volume, the capsule was just large enough for a single crew member.[10] Inside were 120 controls: 55 electrical switches, 30 fuses and 35 mechanical levers.[11] The heaviest spacecraft, Mercury-Atlas 9, weighed 3,000 pounds (1,400kg) fully loaded.[12] Its outer skin was made of René 41, a nickel alloy able to withstand high temperatures.[13]
The spacecraft was cone shaped, with a neck at the narrow end.[9] It had a convex base, which carried a heat shield (Item 2 in the diagram below)[14] consisting of an aluminum honeycomb covered with multiple layers of fiberglass.[15] Strapped to it was a retropack (1)[16] consisting of three rockets deployed to brake the spacecraft during reentry.[17] Between these were three minor rockets for separating the spacecraft from the launch vehicle at orbital insertion.[18] The straps that held the package could be severed when it was no longer needed.[19] Next to the heat shield was the pressurized crew compartment (3).[20] Inside, an astronaut would be strapped to a form-fitting seat with instruments in front of him and with his back to the heat shield.[21] Underneath the seat was the environmental control system supplying oxygen and heat,[22] scrubbing the air of CO2, vapor and odors, and (on orbital flights) collecting urine.[23][n 1] The recovery compartment (4)[25] at the narrow end of the spacecraft contained three parachutes: a drogue to stabilize free fall and two main chutes, a primary and reserve.[26] Between the heat shield and inner wall of the crew compartment was a landing skirt, deployed by letting down the heat shield before landing.[27] On top of the recovery compartment was the antenna section (5)[28] containing both antennas for communication and scanners for guiding spacecraft orientation.[29] Attached was a flap used to ensure the spacecraft was faced heat shield first during reentry.[30] A launch escape system (6) was mounted to the narrow end of the spacecraft[31] containing three small solid-fueled rockets which could be fired briefly in a launch failure to separate the capsule safely from its booster. It would deploy the capsule's parachute for a landing nearby at sea.[32] (See also Mission profile for details.)
The Mercury spacecraft did not have an on-board computer, instead relying on all computation for reentry to be calculated by computers on the ground, with their results (retrofire times and firing attitude) then transmitted to the spacecraft by radio while in flight.[33][34] All computer systems used in the Mercury space program were housed in NASA facilities on Earth.[33] The computer systems were IBM 701 computers.[35][36]
The US launched its first Mercury astronaut Alan Shepard on a suborbital flight almost a month after the first crewed orbital spaceflight. The Soviets were able to launch a second Vostok on a one-day flight on August 6, before the US finally orbited the first American, John Glenn, on February 20, 1962. The United States launched a total of two crewed suborbital Mercury capsules and four crewed orbital capsules, with the longest flight, Mercury-Atlas 9, making 22 orbits and lasting 32 and one-half hours.
Gemini capsule internal diagram, with equipment adapter
Many components in the capsule itself were reachable through their own small access doors. Unlike Mercury, Gemini used completely solid-state electronics, and its modular design made it easy to repair.[37] The Gemini spacecraft was the precursor to the Apollo program which aimed to land humans on the Moon. It was designed to test new techniques for orbital rendezvous and docking, but it also featured improvements in life support systems, spacecraft reentry, and other critical areas.[7]
Gemini's emergency launch escape system did not use an escape tower powered by a solid-fuel rocket, but instead used aircraft-style ejection seats. The tower was heavy and complicated, and NASA engineers reasoned that they could do away with it as the Titan II's hypergolic propellants would burn immediately on contact. A Titan II booster explosion had a smaller blast effect and flame than on the cryogenically fueled Atlas and Saturn. Ejection seats were sufficient to separate the astronauts from a malfunctioning launch vehicle. At higher altitudes, where the ejection seats could not be used, the astronauts would return to Earth inside the spacecraft, which would separate from the launch vehicle.[38]
The main proponent of using ejection seats was Chamberlin, who had never liked the Mercury escape tower and wished to use a simpler alternative that would also reduce weight. He reviewed several films of Atlas and Titan II ICBM failures, which he used to estimate the approximate size of a fireball produced by an exploding launch vehicle and from this he gauged that the Titan II would produce a much smaller explosion, thus the spacecraft could get away with ejection seats.
Maxime Faget, the designer of the Mercury LES, was on the other hand less-than-enthusiastic about this setup. Aside from the possibility of the ejection seats seriously injuring the astronauts, they would also only be usable for about 40 seconds after liftoff, by which point the booster would be attaining Mach 1 speed and ejection would no longer be possible. He was also concerned about the astronauts being launched through the Titan's exhaust plume if they ejected in-flight and later added, "The best thing about Gemini was that they never had to make an escape."[39]
The Gemini ejection system was never tested with the Gemini cabin pressurized with pure oxygen, as it was prior to launch. In January 1967, the fatal Apollo 1 fire demonstrated that pressurizing a spacecraft with pure oxygen created an extremely dangerous fire hazard.[40] In a 1997 oral history, astronaut Thomas P. Stafford commented on the Gemini 6 launch abort in December 1965, when he and command pilot Wally Schirra nearly ejected from the spacecraft:
So it turns out what we would have seen, had we had to do that, would have been two Roman candles going out, because we were 15 or 16 psi, pure oxygen, soaking in that for an hour and a half. You remember the tragic fire we had at the Cape. (...) Jesus, with that fire going off and that, it would have burned the suits. Everything was soaked in oxygen. So thank God. That was another thing: NASA never tested it under the conditions that they would have had if they would have had to eject. They did have some tests at China Lake where they had a simulated mock-up of Gemini capsule, but what they did is fill it full of nitrogen. They didn't have it filled full of oxygen in the sled test they had.[41]
Gemini was the first astronaut-carrying spacecraft to include an onboard computer, the Gemini Guidance Computer, to facilitate management and control of mission maneuvers. This computer, sometimes called the Gemini Spacecraft On-Board Computer (OBC), was very similar to the Saturn Launch Vehicle Digital Computer. The Gemini Guidance Computer weighed 58.98 pounds (26.75kg). Its core memory had 4096 addresses, each containing a 39-bit word composed of three 13-bit "syllables". All numeric data was 26-bittwo's-complement integers (sometimes used as fixed-point numbers), either stored in the first two syllables of a word or in the accumulator. Instructions (always with a 4-bit opcode and 9 bits of operand) could go in any syllable.[42][43][44][45]
The Apollo spacecraft was first conceived in 1960 as a three-man craft to follow Project Mercury, to accomplish several types of mission: ferrying astronauts to an Earth-orbiting space station, circumlunar flight, or a Moon landing. NASA solicited feasibility study designs from several companies in 1960 and 1961, while Faget and the Space Task Group worked on their own design using a conical/blunt-body capsule (Command Module) supported by a cylindrical Service Module providing electrical power and propulsion. NASA reviewed the entrants' designs in May 1961, but when President John F. Kennedy proposed a national effort to land a man on the Moon during the 1960s, NASA decided to reject the feasibility studies and proceed with Faget's design, focused on the lunar landing mission. The contract to build Apollo was awarded to North American Aviation.
The main Apollo spacecraft was built in two segments: a Command Module (CM) and a Service Module (SM). The CM was 154 inches (3.91m) in diameter and 137 inches (3.48m) high, with a mass of 5,560 kilograms (12,260lb) at launch.[46] The Service Module was 13 feet (4.0m) long, with a total Command/Service Module (CSM) vehicle length of 36feet 2.5inches (11.04m) including the engine bell. The hypergolic propellant service propulsion engine was sized at 20,500 pounds-force (91,000N) to lift the CSM off the lunar surface and send it back to Earth using a direct ascent mission profile. This required a single-launch vehicle much larger than the Saturn V, or else multiple Saturn V launches to assemble it in Earth orbit before sending it to the Moon.
Early on, the direct ascent mission profile was replaced with lunar orbit rendezvous, augmenting the CSM with the Lunar Excursion Module (LM) to ferry two astronauts to the lunar surface. This reduced the net spacecraft mass, allowing the mission to be launched with a single Saturn V. Since significant development work had started on the design, it was decided to continue with the existing design as Block I, while a Block II version capable of rendezvous with the LEM would be developed in parallel. Besides addition of a docking tunnel and probe, Block II would employ equipment improvements based on lessons learned from the Block I design. Block I would be used for uncrewed test flights and a limited number of Earth orbit crewed flights. Though the service propulsion engine was now bigger than required, its design was not changed since significant development was already in progress; however, the propellant tanks were downsized slightly to reflect the modified fuel requirement. Based on astronaut preference, the Block II CM would replace the two-piece plug door hatch cover, chosen to avoid an accidental hatch opening such as had happened on Gus Grissom's Mercury-Redstone 4 flight, with a one-piece, outward-opening hatch to make egress easier at the end of the mission.
The Mercury-Gemini practice of using a prelaunch atmosphere of 16.7 pounds per square inch (1,150mbar) pure oxygen proved to be disastrous in combination with the plug-door hatch design. While participating in a pre-launch test on the pad on January 27, 1967, in preparation for the first crewed launch in February, the entire crew of Apollo 1—Grissom, Edward H. White, and Roger Chaffee—were killed in a fire that swept through the cabin. The plug door made it impossible for the astronauts to escape or be removed before their deaths. An investigation revealed the fire was probably started by a spark from a frayed wire, and fed by combustible materials that should not have been in the cabin. The crewed flight program was delayed while design changes were made to the Block II spacecraft to replace the pure oxygen pre-launch atmosphere with an air-like nitrogen/oxygen mixture, eliminate combustible materials from the cabin and the astronauts' space suits, and seal all electrical wiring and corrosive coolant lines.
The Block II spacecraft weighed 63,500 pounds (28,800kg) fully fueled, and was used in four crewed Earth and lunar orbital test flights, and seven crewed lunar landing missions. A modified version of the spacecraft was also used to ferry three crews to the Skylab space station, and the Apollo-Soyuz Test Project mission which docked with a Soviet Soyuz spacecraft. The Apollo spacecraft was retired after 1974.
The Soyuz spacecraft, with reentry capsule (Descent Module) highlighted
In 1963, Korolev first proposed the three-man Soyuz spacecraft for use in Earth orbit assembly of a lunar exploration mission. He was pressured by Soviet premier Nikita Khrushchev to postpone development of Soyuz to work on Voskhod, and later allowed to develop Soyuz for space station and lunar exploration missions. He employed a small, lightweight bell-shaped reentry capsule, with an orbital crew module attached to its nose, containing the bulk of the mission living space. The service module would use two panels of electric solar cells for power generation, and contained a propulsion system engine. The 7K-OK model designed for Earth orbit used a 2,810-kilogram (6,190lb) reentry module measuring 2.17 meters (7.1ft) in diameter by 2.24 meters (7.3ft) long, with an interior volume of 4.00 cubic meters (141cuft). The 1,100-kilogram (2,400lb) spheroidal orbital module measured 2.25 meters (7.4ft) in diameter by 3.45 meters (11.3ft) long with a docking probe, with an interior volume of 5.00 cubic meters (177cuft). The total spacecraft mass was 6,560 kilograms (14,460lb).
Ten of these craft flew crewed after Korolev's death, from 1967 to 1971. The first (Soyuz 1) and last (Soyuz 11) resulted in the first in-space fatalities. Korolev had developed a 9,850-kilogram (21,720lb)7K-LOK variant for use in the lunar mission, but this was never flown crewed.
The Russians continued to develop and fly the Soyuz to this day.
Space capsules have also been used for scientific research and experimentation in space. For example, the Chinese Shenzhou spacecraft has carried out experiments in life sciences, material sciences, fluid dynamics, and space environment monitoring.[47] The PRC developed its Shenzhou spacecraft in the 1990s based on the same concept (orbital, reentry and service modules) as Soyuz. Its first uncrewed test flight was in 1999, and the first crewed flight in October 2003 carried Yang Liwei for 14 Earth orbits.
The SpaceX Dragon 2 capsule first launched crew to the International Space Station on 30 May 2020 on the Demo-2 mission for NASA. Although originally envisaged as a development of SpaceX's uncrewed Dragon capsule which was used for the NASA Commercial Resupply Services contract, the demands of crewed spaceflight resulted in a significantly redesigned vehicle with limited commonality. The Dragon capsule was designed to be reusable. In fact, SpaceX has flown the same Dragon capsule to the International Space Station multiple times, with the first successful reuse occurring in June 2017.
The six-seat Blue Origin developed New Shepard crew capsule is a suborbital crewed spacecraft designed for human tended research and space tourism. The capsule can also fly uncrewed, carrying payloads and experiments.
↑ On the first suborbital flight there was no urine collection whereas on the other, the astronaut had a reservoir added to the space suit[24]
Related Research Articles
Human spaceflight is spaceflight with a crew or passengers aboard a spacecraft, often with the spacecraft being operated directly by the onboard human crew. Spacecraft can also be remotely operated from ground stations on Earth, or autonomously, without any direct human involvement. People trained for spaceflight are called astronauts, cosmonauts (Russian), or taikonauts (Chinese); and non-professionals are referred to as spaceflight participants or spacefarers.
Project Mercury was the first human spaceflight program of the United States, running from 1958 through 1963. An early highlight of the Space Race, its goal was to put a man into Earth orbit and return him safely, ideally before the Soviet Union. Taken over from the US Air Force by the newly created civilian space agency NASA, it conducted 20 uncrewed developmental flights, and six successful flights by astronauts. The program, which took its name from Roman mythology, cost $2.68 billion. The astronauts were collectively known as the "Mercury Seven", and each spacecraft was given a name ending with a "7" by its pilot.
The Soyuz programme is a human spaceflight programme initiated by the Soviet Union in the early 1960s. The Soyuz spacecraft was originally part of a Moon landing project intended to put a Soviet cosmonaut on the Moon. It was the third Soviet human spaceflight programme after the Vostok (1961–1963) and Voskhod (1964–1965) programmes.
The Space Race was a 20th-century competition between the Cold War rivals, the United States and the Soviet Union, to achieve superior spaceflight capability. It had its origins in the ballistic missile-based nuclear arms race between the two nations following World War II, and had its peak with the more particular Moon Race to land a man on the Moon between the US moonshot and Soviet moonshot programs. The technological advantage demonstrated by spaceflight achievement was seen as necessary for national security, particularly in regard to intercontinental ballistic missile and satellite reconnaissance capability, but also became part of the cultural symbolism and ideology of the time. The Space Race brought pioneering launches of artificial satellites, robotic landers to the Moon, Venus, and Mars, and human spaceflight in low Earth orbit and ultimately to the Moon.
Soyuz is a series of spacecraft which has been in service since the 1960s, having made more than 140 flights. It was designed for the Soviet space program by the Korolev Design Bureau. The Soyuz succeeded the Voskhod spacecraft and was originally built as part of the Soviet crewed lunar programs. It is launched atop the similarly named Soyuz rocket from the Baikonur Cosmodrome in Kazakhstan.
Vostok 2 was a Soviet space mission which carried cosmonaut Gherman Titov into orbit for a full day on August 6, 1961, to study the effects of a more prolonged period of weightlessness on the human body. Titov orbited the Earth over 17 times, exceeding the single orbit of Yuri Gagarin on Vostok 1 − as well as the suborbital spaceflights of American astronauts Alan Shepard and Gus Grissom aboard their respective Mercury-Redstone 3 and 4 missions. Titov's number of orbits and flight time would not be surpassed by an American astronaut until Gordon Cooper's Mercury-Atlas 9 spaceflight in May 1963.
Voskhod 1 was the seventh crewed Soviet space flight. Flown by cosmonauts Vladimir Komarov, Konstantin Feoktistov, and Boris Yegorov, it launched 12 October 1964, and returned on the 13th. Voskhod 1 was the first human spaceflight to carry more than one crewman into orbit, the first flight without the use of spacesuits, and the first to carry either an engineer or a physician into outer space. It also set a crewed spacecraft altitude record of 336 km (209 mi).
Human spaceflight programs have been conducted, started, or planned by multiple countries and companies. Until the 21st century, human spaceflight programs were sponsored exclusively by governments, through either the military or civilian space agencies. With the launch of the privately funded SpaceShipOne in 2004, a new category of human spaceflight programs – commercial human spaceflight – arrived. By the end of 2022, three countries and one private company (SpaceX) had successfully launched humans to Earth orbit, and two private companies had launched humans on a suborbital trajectory.
Apollo–Soyuz was the first crewed international space mission, carried out jointly by the United States and the Soviet Union in July 1975. Millions of people around the world watched on television as an American Apollo spacecraft docked with a Soviet Soyuz capsule. The project, and its handshake in space, was a symbol of détente between the two superpowers amid the Cold War.
Vostok was a class of single-pilot crewed spacecraft built by the Soviet Union. The first human spaceflight was accomplished with Vostok 1 on April 12, 1961, by Soviet cosmonaut Yuri Gagarin.
The Voskhod was a spacecraft built by the Soviet Union's space program for human spaceflight as part of the Voskhod programme. It was a development of and a follow-on to the Vostok spacecraft. Voskhod 1 was used for a three-man flight whereas Voskhod 2 had a crew of two. They consisted of a spherical descent module, which housed the cosmonauts, and instruments, and a conical equipment module, which contained propellant and the engine system. Voskhod was superseded by the Soyuz spacecraft in 1967.
A service module is a component of a crewed space capsule containing a variety of support systems used for spacecraft operations. Usually located in the uninhabited area of the spacecraft, the service module serves a storehouse of critical subsystems and supplies for the mission such as electrical systems, environmental control, and propellant tanks. The service module is jettisoned upon the completion of the mission, and usually burns up during atmospheric reentry.
Project Gemini was the second United States human spaceflight program to fly. Conducted after the first American crewed space program, Project Mercury, while the Apollo program was still in early development, Gemini was conceived in 1961 and concluded in 1966. The Gemini spacecraft carried a two-astronaut crew. Ten Gemini crews and 16 individual astronauts flew low Earth orbit (LEO) missions during 1965 and 1966.
Spacecraft call signs are radio call signs used for communication in crewed spaceflight. These are not formalized or regulated to the same degree as other equivalent forms of transportation, like aircraft. The three nations currently launching crewed space missions use different methods to identify the ground and space radio stations; the United States uses either the names given to the space vehicles or else the project name and mission number. Russia traditionally assigns code names as call signs to individual cosmonauts, more in the manner of aviator call signs, rather than to the spacecraft.
A reentry capsule is the portion of a space capsule which returns to Earth following a spaceflight. The shape is determined partly by aerodynamics; a capsule is aerodynamically stable falling blunt end first, which allows only the blunt end to require a heat shield for atmospheric entry. A crewed capsule contains the spacecraft's instrument panel, limited storage space, and seats for crew members. Because a capsule shape has little aerodynamic lift, the final descent is via parachute, either coming to rest on land, at sea, or by active capture by an aircraft. In contrast, the development of spaceplane reentry vehicles attempts to provide a more flexible reentry profile.
Spaceflight began in the 20th century following theoretical and practical breakthroughs by Konstantin Tsiolkovsky, Robert H. Goddard, and Hermann Oberth, each of whom published works proposing rockets as the means for spaceflight. The first successful large-scale rocket programs were initiated in Nazi Germany by Wernher von Braun. The Soviet Union took the lead in the post-war Space Race, launching the first satellite, the first animal, the first human and the first woman into orbit. The United States landed the first men on the Moon in 1969. Through the late 20th century, France, the United Kingdom, Japan, and China were also working on projects to reach space.
Advanced Gemini was a series of proposals that would have extended the Gemini program by the addition of various missions, including crewed low Earth orbit, circumlunar and lunar landing missions. Gemini was the second crewed spaceflight program operated by NASA, and consisted of a two-seat spacecraft capable of maneuvering in orbit, docking with uncrewed spacecraft such as Agena Target Vehicles, and allowing the crew to perform tethered extra-vehicular activities.
Globus IMP instruments were spacecraft navigation instruments used in Soviet and Russian crewed spacecraft. The IMP acronym stems from the Russian expression Indicator of position in flight, but the instrument is informally referred to as the Globus. It displays the nadir of the spacecraft on a rotating terrestrial globe. It functions as an onboard, autonomous indicator of the spacecraft's location relative to Earth coordinates. An electro-mechanical device in the tradition of complex post-World War II clocks such as master clocks, the Globus IMP instrument incorporates hundreds of mechanical components common to horology. This instrument is a mechanical computer for navigation akin to the Norden bombsight. It mechanically computes complex functions and displays its output through mechanical displacements of the globe and other indicator components. It also modulates electric signals from other instruments.
↑ Tomayko, James E. (1988). "The Gemini Digital Computer: First Machine in Orbit". Computers in Spaceflight: The NASA Experience. Washington, D.C.: National Aeronautics and Space Administration. pp.10–19. Retrieved 2015-01-04.
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