The Gemini program was designed as a bridge between the Mercury and Apollo programs, primarily to test equipment and mission procedures in Earth orbit and to train astronauts and ground crews for future Apollo missions. The general objectives of the program included: long duration flights in excess of of the requirements of a lunar landing mission; rendezvous and docking of two vehicles in Earth orbit; the development of operational proficiency of both flight and ground crews; the conduct of experiments in space; extravehicular operations; active control of reentry flight path to achieve a precise landing point; and onboard orbital navigation. Each Gemini mission carried two astronauts into Earth orbit for periods ranging from 5 hours to 14 days. The program consisted of 10 crewed launches, 2 uncrewed launches, and 7 target vehicles, at a total cost of approximately 1,280 million dollars.
After the prototype Gemini 1, which lacked most of the systems of the Gemini spacecraft, beginning with Gemini 2 the complete Gemini capsule was flown.
Capsule
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The Gemini spacecraft was a cone-shaped capsule consisting of two components, a reentry module and an adaptor module. The adaptor module made up the base of the spacecraft. It was a truncated cone 228.6 cm high, 304.8 cm in diameter at the base and 228.6 cm at the upper end where it attached to the base of the reentry module. The re-entry module consisted of a truncated cone which decreased in diameter from 228.6 cm at the base to 98.2 cm, topped by a short cylinder of the same diameter and then another truncated cone decreasing to a diameter of 74.6 cm at the flat top. The reentry module was 345.0 cm high, giving a total height of 573.6 cm for the Gemini spacecraft.
The adaptor module was an externally skinned, stringer framed structure, with magnesium stringers and an aluminum alloy frame. The adaptor was composed of two parts, an equipment section at the base and a retrorocket section at the top. The equipment section held fuel and propulsion systems and was isolated from the retrorocket section by a fiber-glass sandwich honeycomb blast shield. The retrorocket section held the re-entry rockets for the capsule.
The reentry module consisted mainly of the pressurized cabin which held the two Gemini astronauts. Separating the reentry module from the retrorocket section of the adaptor at its base was a curved silicone elastomer ablative heat shield. The module was composed predominantly of titanium and nickle-alloy with beryllium shingles. At the narrow top of the module was the cylindrical reentry control system section and above this the rendezvous and recovery section which holds the reentry parachutes. The cabin held two seats equipped with emergency ejection devices, instrument panels, life support equipment, and equipment stowage compartments in a total pressurized volume of about 2.25 cubic meters. Two large hatches with small windows could be opened outward, one positioned above each seat.
Control, Propulsion, and Power
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Attitude control was effected by two translation-maneuver hand controllers, an attitude controller, redundant horizon sensor sytems, and reentry control electronics, with guidance provided via an inertial measuring unit and radar system. Big flash casino. The orbital attitude and maneuver system used a hypergolic propellant combination of monomethylhydrazine and nitrogen tetroxide supplied to the engines by a helium system pressurized at 2800 psi. Two 95 lb translation thrusters and eight 23 lb attitude thrusters were mounted along the bottom rim of the adaptor, and two 79 lb and 4 95 lb thrusters were mounted at the front of the adaptor. Power was supplied by 3 silver-zinc batteries to a 22- to 30-volt DC two-wire system. During reentry and post-landing power was supplied by four 45 amp-hr silver-zinc batteries.
Communications
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Voice communications were performed at 296.9 MHz with an output power of 3 W. A backup transmitter-receiver at 15.016 MHz with an output power of 5 W was also available. Two antenna systems consisting of quarter-wave monopoles were used. Telemetry was transmitted via three systems, one for real time telemetry, one for recorder playback, and a spare. Each system was frequency-modulated with a minimum power of 2 W. Spacecraft tracking consisted of two C-band radar transponders and an acquisition-aid beacon. One transponder is mounted in the adaptor with a peak power output of 600 W to a slot antenna on the bottom of the adaptor. The other is in the reentry section, delivering 1000 W to three helical antennas mounted at 120 degree intervals just forward of the hatches. The acquisition-aid beacon was mounted on the adaptor and had a power of 250 mW.
Reentry
At the time of reentry, the spacecraft would be maneuvered to the appropriate orientation and equipment adaptor section would be detached and jettisoned, exposing the retro rocket module. The retro rockets consisted of four spherical-case polysulfide ammonium perchlorate solid-propellant motors (Star-13E (TE-M-385)) mounted near the center of the reentry adaptor module, each with 11,070 N thrust. They would fire fired sequentially at 5.5 second intervals to initiate the spacecraft reentry into the atmosphere, with attitude being maintained by a reentry control system of 16 engines, each with 5.2 N thrust. The retrorockets could also be salvo fired in conjunction with a launch abort scenario above 15,000 feet to separate the spacecraft from the Titan II Launch vehicle. The retrorocket module would then be jettisonned, exposing the heat shield at the base of the reentry module. Along with the ablative heat shield, thermal protection during reentry was provided by thin Rene 41 radiative shingles at the base of the module and beryllium shingles at the top. Beneath the shingles was a layer of MIN-K insulation and thermoflex blankets. At an altitude of roughly 15,000 meters the astronauts would deploy a 2.4 meter drogue chute from the rendezvous and recovery section. At 3230 meters altitude the crew releases the drogue which extracts the 5.5 meter pilot parachute. The rendezvous and recovery section is released 2.5 seconds later, deploying the 25.6 meter main ring-sail parachute which is stored in the bottom of the section. The spacecraft is then rotated from a nose-up to a 35 degree angle for water landing. At this point a recovery beacon is activated, transmitting via an HF whip antenna mounted near the front of the reentry module.
Crews
→ List of all Gemini Crews
The atmospheric re-entry of Gemini 2 viewed through a pilot's window | |
Mission type | Test flight |
---|---|
Operator | NASA[1] |
Mission duration | 18 minutes, 16 seconds |
Range | 3,422.4 kilometers (1,847.9 nmi) |
Apogee | 171.1 kilometers (92.4 nmi) |
Spacecraft properties | |
Spacecraft | Gemini SC2 |
Manufacturer | McDonnell |
Start of mission | |
Launch date | January 19, 1965, 14:03:59.861 UTC |
Rocket | Titan II GLV,s/n 62-12557 |
Launch site | |
End of mission | |
Recovered by | USS Lake Champlain |
Landing date | January 19, 1965, 14:22:14 UTC |
Landing site | 16°36′N49°46′W / 16.600°N 49.767°W |
Gemini 3 → |
Gemini 2 (Gemini-Titan 2; GT-2)[2] was the second spaceflight of the American human spaceflight program Project Gemini, and was launched and recovered on January 19, 1965. Gemini 2, like Gemini 1, was an uncrewed mission intended as a test flight of the Gemini spacecraft. Unlike Gemini 1, which was placed into orbit, Gemini 2 made a suborbital flight, primarily intended to test the spacecraft's heat shield. Play street craps. It was launched on a Titan II GLV rocket. The spacecraft used for the Gemini 2 mission was later refurbished into the Gemini B configuration, and was subsequently launched on another suborbital flight, along with OPS 0855, as a test for the US Air Force Manned Orbital Laboratory. Gemini spacecraft no. 2 was the first craft to make more than one spaceflight since the X-15, and the only one until Space Shuttle Columbia flew its second mission in 1981.
Mission history[edit]
GLV[edit]
The Titan II/Gemini launch vehicle was dismantled to protect it from two hurricanes in August and September 1964. The second stage of the vehicle was taken down and stored in a hangar on August 26, 1964 in preparation for Hurricane Cleo, and the entire launch vehicle was subsequently dismantled and removed from Cape Kennedy Air Force Station's Launch Complex19 in early September before Hurricane Dora passed over Cape Kennedy on September 9. The Gemini launch vehicle was erected for the final time on 12 September 1964.
The prime and backup crews for Gemini 3, John Young (suited), Wally Schirra, Thomas P. Stafford (in shirtsleeves), and Gus Grissom (suited), practice egress from the Gemini 2 pad, in preparation for the upcoming Gemini 3 flight
Many ground tests were carried out on the Gemini 2 and Titan rocket in November 1964. On November 24, Gemini-Titan (GT) 2 successfully completed the Wet Mock Simulated Launch, a full-scale countdown exercise which included propellant loading. Procedures for flight crew suiting and spacecraft ingress and egress were practiced during simulated launch. The prime flight crew for Gemini 3 donned pressure suits and full biomedical instrumentation, assisted by their backup crew and the space suit bioinstrumentation and aeromedical personnel who would participate in the GT-3 launch operation. As a result of this practice operation, it was established that all physical examinations, bioinstrumentation sensor attachment, and suit donning would be done in the pilot ready room at Launch Complex 16.
Gemini 2 had been scheduled for launch on December 9, 1964. On that date, the countdown reached zero and the first stage engines were ignited. The launch vehicle's Malfunction Detection System detected technical problems due to a loss of hydraulic pressure and shut down the engines about one second after ignition.
On the second launch attempt on January 19, 1965, Gemini 2 lifted off from Launch Complex 19 at Cape Kennedy at 9:03:59 a.m. EST (14:03:59.861 UTC).
Shortly after launch the Mission Control Center suffered a power outage. Control of the mission was transferred to a tracking ship. Iexplorer 4 1 17. The outage was later traced to an overload of the electrical system from the network television equipment used to cover the launch.[3]
Gemini 2 flew a ballistic suborbital arc over the Atlantic Ocean reaching a maximum altitude of 92.4 nautical miles (171.1 km). The spacecraft was run by an onboard automatic sequencer. At 6 minutes 54 seconds after launch, retrorockets were fired. The spacecraft landed 1,847.9 nautical miles (3,422 km) downrange from the launch pad. The flight lasted 18 minutes 16 seconds. The landing was 14 nautical miles (26 km) short of the planned impact point, and 45 nautical miles (83 km) from the recovery aircraft carrier, USS Lake Champlain. The spacecraft was brought aboard the carrier at 15:52 UT (10:52 a.m. EST). Most goals were achieved, except the fuel cells had failed before liftoff and were turned off. The spacecraft cooling system temperature also was found to be too high. The Gemini 2 spacecraft was in excellent condition. Its heat shield and retrorockets functioned as expected. The Gemini 2 mission was supported by 6,562 United States Department of Defense personnel, 67 aircraft, and 16 ships.
Gemini 2 had flight instrumentation pallets installed in the crew cabin, similar to those in Gemini 1. Gsn casino free download.
MOL[edit]
The Gemini 2 reentry module was refurbished and flown again on November 3, 1966 in a test flight for the United States Air ForceManned Orbiting Laboratory program. It was launched on a Titan IIIC rocket on a 33-minute suborbital flight from LC-40 at Cape Kennedy. It is the only Gemini spacecraft to have flown with U.S. Air Force insignia, but there is an unflown Gemini B spacecraft in USAF markings on display at the National Museum of the United States Air Force at Wright-Patterson Air Force Base in Dayton, Ohio.
Gallery[edit]
- SC2 is launched for a second time aboard a Titan 3C in November 1966, on a suborbital test flight for the USAF MOL project.
- Gemini 2 instrument pallets (NASA) Rapidweaver 8 1 – create template based websites rapidly using.
- Gemini 2 spacecraft on display at the Air Force Space and Missile Museum, Cape Canaveral Air Force Station, Florida.
- Gemini 2 spacecraft on display at the Air Force Space and Missile Museum, Cape Canaveral.
See also[edit]
References[edit]
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
- ^Hacker, Barton C.; Grimwood, James M. (February 2003) [First published 1977]. 'Table of Contents'. On the Shoulders of Titans: A History of Project Gemini. NASA History Division, Office of Policy and Plans. NASA History Series. Washington, D.C.: NASA. NASA SP-4203. Retrieved September 12, 2013.
- ^'Gemini 2'. NASA Space Science Data Coordinated Archive (NSSDCA). NASA. 2017. GEMINI2.
- ^Chris Kraft, Flight, p. 206.
External links[edit]
Wikimedia Commons has media related to Gemini 2. |
- The Gemini II Reentry Mission - 1965 - NASA on YouTube
- Gemini II reentry at real speed - HD source on YouTube
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