Gemini 2 5 0 5

NSSDCA/COSPAR ID: 1965-100A

• Gemini 2 5 0 5 Scale
• Gemini 2 5 0 5 2

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Description

Gemini 7 was the fourth crewed Earth-orbiting spacecraft of the Gemini series, having been launched before Gemini 6A. It carried astronauts Frank Borman and Jim Lovell on the 14 day mission. Its mission priorities were (1) to demonstrate a 2-week flight, (2) to perform stationkeeping with the Gemini launch vehicle stage 2, (3) to evaluate the 'shirt sleeve' environment and the lightweight pressure suit, (4) to act as a rendezvous target for Gemini 6, and (5) to demonstrate controlled reentry close to the target landing point. The crew members had three scientific, four technological, four spacecraft, and eight medical experiments to perform.

Mission Profile

Gemini 7 was launched from Complex 19 at 2:30:03 p.m. (2:30:03.702 UT) on 4 December 1965 and inserted into a 161.6 x 328.2 km orbit at 2:36:11. Immediately after separation Gemini 7 began stationkeeping operations with the Titan II second stage at distances from 6 meters to 80 km over a period of 17 minutes. On the third revolution the perigee was raised to 230 km to ensure an orbital lifetime of 15 days. On 6 December, 45 hours into the mission, Lovell removed his spacesuit to evaluate the shirtsleeve environment. The first five days were spent conducting experiments and spacecraft tests. On 9 December the orbit was circularized to 299.7 x 303.7 to prepare for the rendezvous exercise with Gemini 6A. On 10 December 140 hours into the mission Lovell put his suit back on and Borman removed his. Some 20 hours later Lovell removed his suit as well and both astronauts operated without suits for the remainder of the mission except for the rendezvous with Gemini 6A and reentry.

Experiments were conducted over the next few days and on 15 December Gemini 6A was launched. Gemini 6A caught up to Gemini 7 and rendezvous was technically achieved and stationkeeping begun on 15 December at 2:33 p.m. EST with the two Gemini spacecraft in zero relative motion at a distance of 110 meters. Stationkeeping maneuvers involving the spacecraft circling each other and approaching and backing off continued for 5 hours 19 minutes over three and a half orbits. During the maneuvers, all four astronauts on both spacecraft took turns in the formation flying activities and photographs were taken from both spacecraft. This marked the first time two spacecraft were maneuvered with respect to each other by their crews. At the end of stationkeeping Gemini 6A fired thrusters to move to a position roughly 50 km away from Gemini 7 for drifting flight during the sleep period. Gemini 6A returned to Earth on December 16. Stat 8 0 3 – git integration with finder. Gemini 7 remained in Earth orbit and reentered two days later.

Retrorockets were fired at the end of revolution 206 on 18 December at 8:28:07 a.m. to begin the reentry sequence. Splashdown followed at 9:05:04 in the western Atlantic southwest of Bermuda at 25.42 N, 70.10 W, only 12.2 km from the target point. The astronauts were recovered by helicopter and brought aboard the aircraft carrier U.S.S. Wasp at 9:37. The spacecraft was recovered at 10:08. Total mission elapsed time was 330:35:01, making this the longest anyone had ever stayed in space. The astronauts were pronounced in 'better than expected' physical condition after their two week flight.

All primary mission objectives were successfully completed. The three scientific experiments: synoptic terrain photography, synoptic weather photography, and visual acuity in the space environment were all completed successfully. All other onboard experiments were performed except landmark contrast measurement and star occultation navigation, due to equipment failure. Only partially completed were in-flight sleep analysis, proton-electron spectrometer, and optical communication. Minor malfunctions related to fuel cells and attitude control thruster occurred but did not hamper the mission.

Spacecraft and Subsystems

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

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. 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 a fuel cell power system to a 22- to 30-volt DC two-wire system. https://siogradinli1984.mystrikingly.com/blog/macbook-png-to-jpg. During reentry and post-landing power was supplied by four 45 amp-hr silver-zinc batteries.

Communications

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. Terryburton barcode generator. 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 retrorocket module. The retrorockets consisted of four spherical-case polysulfide ammonium perchlorate solid-propellant motors mounted near the center of the reentry adaptor module, each with 11,070 N thrust. They would fire 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 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.

Gemini Program

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.

Alternate Names

• 01812
• Gemini7

Facts in Brief

Launch Date: 1965-12-04
Launch Vehicle: Titan II
Launch Site: Cape Canaveral, United States
Mass: 3663 kg

Funding Agency

Gemini 2 5 0 5 Scale

• NASA-Office of Manned Space Flight (United States)

Disciplines

• Space Physics
• Human Crew
• Earth Science

Additional Information

Questions and comments about this spacecraft can be directed to: Dr. David R. Williams

Gemini 2 5 0 5 2

Personnel

Selected References

• Gemini midprogram conference including experimental results, NASA, SP-121, 1966. (Papers Presented at the Manned Spaceflight Center, Houston, Feb. 23-25, 1966)
• Gemini summary conference, NASA, SP-138, Wash, DC, Feb. 1967.
• Grimwood, J. M., et al., Project Gemini technology and operations - A chronology, NASA, NASA SP-4002, Wash., DC, 1969.

Diagram of the Gemini capsule. Dragons lair 2: time warp 1 0 remastered download free. (Courtesy of NASA History Office.)

Gemini 6A

Gemini Books Online

Gemini Home Page
Chronology of U.S. Astronaut Missions - Mercury, Gemini, and Apollo

Gemini 7 Images - Catalog of Spaceborne Imaging
More Gemini 7 Images - Kennedy Space Center
More Gemini Diagrams - NASA History Office