A brief summary of the Gemini flight results reveals how successful the Gemini program was. All of the major objectives were met as well as many other objectives assigned to each mission. There were two uncrewed test flights and 10 crewed flights - all launched on a Titan II missile.
Image Galleries History Videos. Four of these thrusters, located 90 degrees apart from one and other and firing perpendicular to the spacecrafts long axis, provided translation control in two axis.
Two additional thrusters, firing forward, provided braking thrust. Eight reaction control thrusters, located near the base of the equipment section, provided roll, yaw, and pitch control. Two thrusters, firing aft and perpendicular to the main spacecraft axis, provided forward thrust. Environmental control system components, oxygen tanks, fuel cells, battery containers, fuel tanks for the orbital maneuvering system, and other electrical equipment, were housed in this section.
Equipment varied according to each missions objectives. For instance, the longer duration missions carried fuel cells, while the shorter missions relied on batteries for electrical power. Photos of a Gemini fuel cell on display at the U.
Space and Rocket Center. Developing techniques for orbital rendezvous and docking were among the goals for project Gemini. Two spacecraft were developed to provide docking targets for Gemini missions. Additions to the standard Agena included extra communications equipment, a radar transponder, acquisition lights, and a docking cone.
The docking cone was designed to receive the nose of a Gemini capsule. An indexing bar, protruding from the side of the Gemini spacecrafts nose, slid into a matching v-notch on the docking cone, assuring proper radial alignment between the docked spacecraft. Equipment within the docking cone allowed the spacecraft to be securely attached. While docked, equipment in the Gemini capsule allowed astronauts to control the Agena spacecraft.
The Gemini-Agena combination could use the Agena engine to make significant orbital maneuvers. Gemini 8, launched shortly after, was able to rendezvous with and perform the first ever docking between two orbiting spacecraft. GATV-8 was later used as a passive rendezvous target for Gemini Gemini 10, launched shortly after, was able to rendezvous with and dock with the Agena. While docked, the Gemini 10 crew were able to command firings of the Agena main engine, raising the spacecrafts orbit from km to km.
Gemini 11, launched shortly after, was able to rendezvous with and dock with the Agena. While docked, the Agena engine was used to raise the spacecrafts orbit to a record apogee of km.
Gemini 12, launched shortly after, was able to rendezvous with and dock with the Agena. A problem with the Agena engine prevented planned orbit changes. Stabilization and attitude control were accomplished with a series of 16 thrusters. A number of running lights, along with white and black stripes painted on the hull, aided visual acquisition of the docking target. Only one ATDA was flown. Unfortunately, the payload shroud failed to separate completely. Cookie Settings Accept.
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The cookie is used to store the user consent for the cookies in the category "Analytics". The cookies is used to store the user consent for the cookies in the category "Necessary". The adaptor module made up the base of the spacecraft. It was a truncated cone The re-entry module consisted of a truncated cone which decreased in diameter from The reentry module was 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.
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