SECOR (Sequential Collation of Ranges) was a series of small United States Armed Forces satellites launched in the 1960s for geodesy measurements that precisely determined the locations of points on the Earth's surface, particularly of isolated islands in the Pacific. This data allowed for improved global mapping and precise positioning of ground stations for other satellites.
Any SECOR satellite could be linked to four mobile ground stations: three were placed in accurately determined known locations, and a fourth one was placed in an unknown location. By measuring a satellite's distance from the three known stations, its position in space was determined. Then, the distance between the unknown ground station and the previously determined satellite's position was used to compute the unknown ground station's coordinates. This process was repeated many times, to enhance the accuracy of the measurement. Once the unknown station's position was accurately determined, it became a known station. Then one of the four stations was moved to a new unknown point, and the process began again.
Fifteen dedicated SECOR satellites were made, and eight SECOR transponders flew as a subsystem of other satellites.
Two versions of SECOR satellites were built, Type I and Type II. They had several differences, but they also shared many features. Therefore, a detailed description is provided for Type I, and a differences-only summary for Type II.
The Type 1 SECOR satellites were spherical, 50.8 cm (20 in) in diameter, in construction similar to Vanguard III and the early SOLRAD/GRAB spacecraft. The satellites massed 16.8 kg (37 lb) in average, with most of it being batteries and voltage regulators. Their surface was made of polished aluminium covered with a thin layer of silicon monoxide to help with thermal regulation. There were nine collapsible antennas, eight around the equator for distance measurement and one atop the sphere for telemetry and command. A hollow cone connected the upper stage of the launch vehicle to the base of the satellite. Expected lifespan was one year.
Six sets of 160 solar cells were mounted on aluminium plates around the surface, providing 17 volts. Within the sphere, a vertically aligned cylinder housed the batteries and voltage regulators. A stable voltage was essential for accurate transponder operation, and, in addition to the voltage regulators, each battery cell in the battery was matched to within 0.03 volts in their discharge curves.
The transponder was placed on a framework within the remaining space.
Each satellite was equipped to transmit data such as battery charge, voltages, temperature of equipment inside the satellite, etc. Later satellites had more telemetry channels.
On the inner side of the skin, a magnetic rod was placed. It aligned itself with Earth's magnetic field, thus keeping the satellite in a constant orientation. Also inside the skin, many despin coils were placed. These devices were used to stop undesired rotation induced by launch vehicle separation, and by passing near the magnetic poles of earth. The despin coils were simply large wire coils that were electrically shorted. Rotational movement within Earth's magnetic field induced current on the coils. The current in the coils generated a magnetic field of its own that opposed Earth's, thus slowing the satellite's rotation. As the coils were shorted, the electric current was converted to heat and dissipated to space. The initial braking took several days because of the weak magnetic field at the typical SECOR orbital altitudes.
These later satellites were made in the shape of a rectangular prism, measuring 25.3 x 29.8 x 34.9 cm (9.95 x 11.75 x 13.75 in). They were almost fully covered in solar cells, and the antennas were made of flexible steel tape. They were much more compact, and thus worked better as secondary payloads. They were designed to avoid removing covers and panels during satellite pre-launch checks. Their antennas were perforated, to diminish antenna shadow over the solar panels.
SECOR transponders were also attached to a number of satellites. While the specific implementation was done on a case-by-case basis, the general idea was to place a transponder either outside/inside of a host satellite, sharing power, antennas, and telemetry with other experiments.
The ground stations were transportable. They consisted of three shelters, one for radio equipment, one for data handling, and one for storage. Generators and air conditioning for the electronic equipment were included.
Lighter weight, solid-state equipment was eventually developed to replace the initial units.
The equipment was designed for all-weather operation.
The data was recorded on magnetic tape, and processed by a computer.
First, the distances between each station and a satellite were obtained and recorded. The distances between the known positions and this satellite were used to determine the satellite's location in space, and then, the previously measured distance from the fourth station and the calculated satellite position were used to calculate the coordinates of the fourth station with respect to the three known stations.
The accuracy of the position calculations was enhanced by the great amount of data obtained in each satellite pass. At about 70 measurements per second, and considering the time the satellite was visible from the ground station, a typical satellite pass yielded approximately 48,000 measurements. Because depending on the exact angle between the satellite and a ground station, the precision could have variation, data was collected during several passes. This allowed data from the best passes to be selected, while still conserving a great amount of redundancy.
Once enough measurements had been made to ensure the unknown position was precisely established, one of the stations was moved to a different place and became the new unknown position. In this way, former measurements helped establish new positions.
Sources differ in details such as names and launch dates. When there are inconsistencies, sources are provided for both.
|Name||Launch date||International Designator||Launch vehicle||Launched from||Satellite type||Notes|
|Transit 3B||February 21 or 22, 1961||1961-007A||Thor DM-21 Ablestar||Cape Canaveral Air Force Station||Shared||Launch failure, satellites failed to separate and were placed in a low orbit. Decayed 37 days after launch.|
|DISCOVERER||October 20, 1961||1961-F10? 23 oct 1961||Shared||Partial success|
|DISCOVERER||November 6, 1961||1961-029A?||Shared||Partial success|
|DISCOVERER||December 12, 1961||1961-034A?||Shared||Partial success|
|COMPOSITE I||January 24, 1962||Thor DM-21 Ablestar||Type I||Launch failure. The second stage failed to add enough velocity.|
|ANNA I A||May 11, 1962||Shared||Launch failure.|
|ANNA I B||October 31, 1962||Shared||Partial success|
|SECOR1, SECOR 1B, EGRS 1||January 11, 1964||1964-001C||Thor Augmented Delta-Agena D||Vandenberg AFB||Type II||Success.|
|SECOR 3, EGRS 3||March 9, 1965||1965-016E||Thor Augmented Delta-Agena D||Vandenberg AFB||Type II||Success.|
|SECOR2, EGRS 2||March 10 or 11, 1965||1965-017B||Thor Augmented Delta-Agena D||Vandenberg AFB||Type II||Success.
Decayed 25 February 1968
|SECOR 4, EGRS 4||April 3, 1965||1965-027B||Atlas-Agena D||Vandenberg AFB||Type II||Transponder failure.
|EGRS V||August 10, 1965||Type I||Partial success|
|GEOS A||November 6, 1965||Shared||Success.|
|SECOR 6, EGRS 6||June 9, 1966||1966-051B||Atlas-Agena D||Vandenberg AFB||Type II||Success.
|SECOR 7, EGRS 7||August 19, 1966||1966-077B||Atlas-Agena D||Vandenberg AFB||Type II||Partial success|
|SECOR 8, EGRS 8||October 5, 1966||1966-089B||Atlas-Agena D||Vandenberg AFB||Type II||Transponder failure.
|SECOR 9, EGRS 9||June 29, 1967||1967-065A||Thor/Burner||Vandenberg AFB||Type II||Success.
|GEOS B||January 11, 1968||Shared||Success. |
|SECOR 10, EGRS 10||May 18, 1968||1968-F04||Thorad-SLV2G Agena-D||Vandenberg AFB||Type II||Launch failure.|
|SECOR 11, EGRS 11||August 16, 1968||1968-F07||Atlas-SLV3 Burner-2||Vandenberg AFB||Type II||Launch failure.|
|SECOR 12, EGRS 12||August 16, 1968||1968-F07||Atlas-SLV3 Burner-2||Vandenberg AFB||Type II||Launch failure.|
|SECOR 13, EGRS 13||April 14, 1969||1969-037B||Thor/Agena||Vandenberg AFB||Type II||Success.
|TOPO I||April 8, 1970||Type II||Success.|
EGRS (Engineer Geodetic Research Satellite) was the U.S. Army Corps of Engineers acronym for the SECOR satellites.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.