Astronomy:Kosmos 144
| Mission type | Weather |
|---|---|
| COSPAR ID | 1967-018A |
| SATCAT no. | 02695 |
| Mission duration | 13 months |
| Spacecraft properties | |
| Spacecraft type | Meteor |
| Manufacturer | VNIIEM |
| Launch mass | 4730 kg [1] |
| Start of mission | |
| Launch date | 28 February 1967, 14:34:59 GMT |
| Rocket | Vostok-2M (8A92M) s/n N15000-55 |
| Launch site | Plesetsk, Site 41/1 |
| Contractor | OKB-1 |
| End of mission | |
| Last contact | 16 March 1968 |
| Decay date | 14 September 1982 |
| Orbital parameters | |
| Reference system | Geocentric[2] |
| Regime | Low Earth |
| Perigee altitude | 574 km |
| Apogee altitude | 644 km |
| Inclination | 81.25° |
| Period | 96.88 minutes |
| Epoch | 28 February 1967 |
Kosmos 144 (Russian: Космос 144 meaning Cosmos 144), was launched on 28 February 1967, Meteor No.6L, and was one of eleven weather satellites launched by the Soviet Union between 1964 and 1969.[3] Kosmos 144 was the second announced Russian meteorological satellite and the first interim operational weather satellite in the experimental Kosmos satellite 'Meteor' system. It was also the first launch of the semi-operational weather satellite from the Plesetsk site into a near-polar, near-circular orbit.[1] Unlike U.S. weather satellites, however, the orbit was prograde (not Sun-synchronous) because, as a result of geographic limitations, a retrograde orbit was not possible. Kosmos 144 was orbited to test, in a semi-operational mode, meteorological instruments designed for obtaining images of cloud cover, snow cover, and ice fields on the day and night sides of the Earth and for measuring fluxes of outgoing radiation reflected and radiated by the Earth-atmosphere system.
The launch of the Kosmos 144 satellite occurred after the success of the Kosmos 122 another meteorological satellite that was launched on 25 June 1966.[4] These satellites were used until 1969 when they were replaced with an upgraded model officially called Meteor 1.[4] The Kosmos 144 differed from the Kosmos 122 mission from Baikonur Cosmodrome to Plesetsk Cosmodrome that was used to get the satellite at the inclination that the satellite was left.[4] The Kosmos 144 was also soon joined by the Kosmos 156, on 27 April 1967, which due to the orbit at which the satellites were positioned made it to where one of the satellites would pass over every six hours.[4]
Spacecraft
The satellite was in the form of a large cylindrical capsule, 5 metres (16 ft) long and 1.5 metres (4 ft 11 in) in diameter. Kosmos 144 had a mass of 4,730 kilograms (10,430 lb).[1] Two large solar cell panels of four segments each were deployed from opposite sides of the cylinder after satellite separation from the launch vehicle. The solar panels were rotated to constantly face the Sun during satellite daytime by means of a Sun sensor-controlled drive mechanism fitted in the top end of the center body. The meteorological instruments, a magnetometer, 465-MHz radio antennas, and orbital control devices were housed in a complex, smaller, hermetically sealed cylinder located on the earthward-facing end of the cylindrical satellite body. The satellite was triaxially stabilized by a series of inertial flywheels, driven by electric motors, whose kinetic energy was dampened by torques produced by electromagnets interacting with the Earth's magnetic field. Kosmos 144 was oriented by Earth sensors with one of its axes directed earthward along the local vertical, a second oriented along the orbital velocity vector, and a third oriented perpendicular to the orbital plane. This orientation ensured that the optical axes of the instruments were constantly directed earthward.[1]
Instruments
This instrumentation consisted of two vidicon cameras for daytime cloud cover pictures, a high-resolution scanning infrared radiometer for nighttime and daytime imaging of the Earth and clouds, and an array of narrow-angle and wide-angle radiometers covering the 0.3 to 3-µm, 8 to 12-µm, and 3 to 3-µm channels for measuring the intensity of radiation reflected from the clouds and oceans, the surface temperatures of the Earth and cloud tops, and the total flux of thermal energy from the Earth-atmosphere system into space, respectively.[1]
Dual vidicon cameras
The Kosmos 144 dual vidicon camera experiment was designed to test the capability of Russian weather satellites to provide daytime pictures of the Earth's cloud cover distribution, local storms, and global weather systems for use by the Soviet Hydrometeorological Service. The instrumentation consisted of two identical vidicon cameras that were mounted in the satellite base and were directed toward the Earth. Each camera viewed a 500 kilometres (310 mi) by 500 kilometres (310 mi) area – one to the left and the other to the right of nadir – with a resolution of 1.25 kilometres (0.78 mi) at nadir from a satellite altitude of 600 kilometres (370 mi) to 700 kilometres (430 mi). The cameras took a one-frame image of the Earth's cloud cover with slight overlapping of successive frames to provide continuous coverage. The cameras switched on automatically any time the Sun was more than 5° above the horizon. Because the Earth illumination varied so much, automatic sensors adjusted the camera apertures to produce high-quality pictures under a variety of illumination conditions.[5]
The image formed by each vidicon tube either was transmitted directly to the ground if the satellite was in radio contact with either of the two ground stations in Moscow or Novosibirsk or was recorded on magnetic tape for later transmission if the satellite was beyond the zone of radio communication. The TV images received by these ground stations were processed and transmitted to the Hydrometeorological Center in Moscow, where they were analyzed and used in various forecast and analysis products. The pictures were archived at the Hydrometeorological Center. The Kosmos 144 cameras, although having 2.5 times the resolution of those carried on the ESSA satellites, could not provide continuous overlapping global coverage as do the ESSA cameras owing to the lower orbit of the Kosmos 144 satellite (609 kilometres (378 mi) compared to 1,400 kilometres (870 mi)). Thus, to close the gaps in coverage, at least two satellites were required in the weather satellite system. In addition, cloud cover mosaics were produced from 10 or more individual cloud cover pictures at the Hydrometeorological Center to provide a more comprehensive view of global weather systems.[5]
Some of the individual pictures and the cloud mosaics were transmitted to various foreign meteorological centers as part of an international meteorological data exchange program. The United States received some of these pictures at the National Environmental Satellite Service (NESS) in Suitland, Maryland, via the "cold line" facsimile link with Moscow. Pictures from Kosmos 144 were transmitted to NESS from 2 March 1967, through 25 October 1967, interspersed with some from Kosmos 156. The transmission was renewed on 23 December 1967 and continued until 16 March 1968, when it is believed that experiment operations were terminated. These pictures were archived at NESS for 1 year and then, unless of unusual interest, were discarded.[5]
Scanning high-resolution infrared radiometer
The high-resolution scanning infrared (IR) radiometer was designed to make measurements of cloud distribution and snow and ice cover on the dayside and nightside of the Earth. The radiometer measured the outgoing radiation from the Earth-atmosphere system in the 8 to 12 µm atmospheric window. Measurements made in this spectral region permitted the construction of brightness patterns of the thermal relief and determination of equivalent radiation temperatures of the Earth's surface and cloud tops. The instrument was a narrow-angle scanning radiometer with an instantaneous viewing angle of 1.5 x 1.5°. It was mounted in the base of the satellite in a sealed instrument compartment with its optical axis directed along the local vertical and toward nadir. The radiometer measured the intensity of the outgoing radiation by comparing the Earth's radiation flux with the radiation flux from space. Each type of radiation entered the radiometer through separate windows, which were oriented in mutually perpendicular directions. The radiation from the Earth-atmosphere system fell on a plane scanning mirror that was mounted at an angle of 45° to the satellite velocity vector and scanned through an angle of ± 50° from nadir.[6]
The radiation was reflected from the scanning mirror through a stationary modulating disk and filter window onto a parabolic mirror that focused the parallel beam through a movable modulating disk onto a thermistor bolometer. The stationary and movable modulating disks provided the channel switching, sending first the Earth-atmosphere radiation and then the space radiation to the parabolic mirror and finally to the bolometer. The bolometer converted the radiant flux into variable electric voltages (0 to 6 V) whose frequency was equal to the modulator frequency and whose magnitudes were proportional to the differences in the radiant flux intensities between Earth and space developed at the bolometer output. During the movement of the scanning mirror through a ± 40° sector, line scanning (40 lines/min) of the target area was accomplished in a plane normal to the orbital plane using a forward and back path, while scanning along the flight path was provided by the relative motion of the satellite with respect to the Earth. In each scan, with the indicated viewing and scanning angles from the satellite's orbital altitude, the radiometer recorded the mean radiation intensities from a band about 1,100 kilometres (680 mi) wide with a resolution of about 15 kilometres (9.3 mi) at nadir to about 24 kilometres (15 mi) to 27 kilometres (17 mi) at the edges. The radiometer was capable of measuring radiation temperatures within 2 or 3° for temperatures above 273 K and within 7 to 8° for temperatures below 273 K.[6]
The video signals were amplified and sent either to the satellite memory unit for later transmission or to the radio-telemetry unit for direct transmission to Earth, depending on whether the satellite was beyond or within the zone of radio communications with a ground receiving station, respectively. The ground receivers recorded the transmitted data in digital form on magnetic tape and simultaneously on 80-mm photographic film in the form of a brightness image of the thermal relief of the Earth-atmosphere system. The data on magnetic tape was processed by computer at the Soviet Hydrometeorological Center and was used to produce a digital map of the equivalent radiation temperature field with a superposed geographic grid. The photographic film was developed and processed into an infrared picture also with a superposed grid. The pictures were archived at the Hydrometeorological Center. Some of these pictures were transmitted to the various foreign meteorological centers as part of an international meteorological data exchange program. The United States received these pictures at the National Environmental Satellite Service (NESS), Suitland, Maryland, via the "cold line" facsimile link with Moscow. Pictures were transmitted to NESS from early March 1967 until mid-March 1968, when it is believed that experiment operations ended. These infrared pictures were kept at NESS for 1 year and then, unless of unusual interest, were discarded.[6]
Actinometric instrument
The actinometric experiment was designed to measure the outgoing longwave radiation (3 to 30 µm) from the Earth-atmosphere system; the outgoing near ultraviolet (UV), visible, and near infrared (IR) solar radiation (0.3 to 3 µm) reflected and backscattered by the Earth-atmosphere system; and the effective radiation temperature of the Earth's surface and cloud tops (8 to 12 µm).[7]
The instrumentation consisted of four radiometers: a pair of scanning, narrow-angle, two-channel radiometers and a pair of nonscanning, wide-angle, two-channel radiometers. The narrow-angle (4 by 5° field of view (FOV)) radiometers measured radiation in all three spectral bands, while the wide-angle (136 to 140° FOV) radiometers operated only in the 0.3 to 3 and 3 to 30 µm bands. In the narrow-angle radiometer, the 0.3 to 3 µm band was measured in one channel and the 8 to 12 and 3 to 30 µm bands were combined in the second channel. In the second channel, the two bands were separated by the exchange of corresponding filters as the radiometer scanned in alternate directions.[7]
The Earth radiation entered the narrow-angle radiometer through a cylindrical fairing (KRS-5 crystal) and fell onto a conical scanning mirror. The radiation was reflected from the mirror through a three-lobed rotating mirror chopper that modulated the radiation flux at a frequency of 80 Hz. The chopper alternately reflected Earth radiation and space radiation, which entered through a separate KRS-5 crystal window, onto one of three openings in a color filter wheel – one filter for each spectral band. The particular spectral band that was passed through then fell on an off-axis parabolic mirror that focused the radiation flux onto a bolometric receiver. Periodic calibration was made when the scanning mirror moved to a 90° angle from nadir with simultaneous turning on and viewing of a silicon standard lamp.[7]
The 0.3 to 3 µm channel did not use the two-beam system or filter switching. The output from the modulated flow of radiation on the bolometer was amplified, rectified, filtered, and fed into the radio-telemetry system over eight channels. The wide-angle radiometers had identical optical systems for both channels. The Earth radiation entered the radiometer through a hemispherical shell composed of quartz or KRS-5 crystal with a coating that determined the passband. The radiation was then modulated with a frequency of 64 Hz and fell on a bolometric receiver. As in the narrow-angle radiometers, the bolometer output was processed and fed into the radio-telemetry system. The wide-angle radiometer was standardised simultaneously with the narrow-angle radiometer by the input of a standard 64 Hz calibrating frequency into the amplification circuit.[7]
The relative RMS measuring error for both types of radiometers was about 0.5%. To provide a backup capability, one wide-angle and one narrow-angle radiometer were held in reserve and could have been activated on command from the ground. The orientation of the Kosmos 144 satellite insured that the primary optical axes of the radiometers were oriented vertically downward toward the survey of the Earth's surface by both radiometers was carried out by the motion of the satellite relative to the Earth. In addition, the narrow-angle radiometer scanned 66° to either side of nadir in a plane normal to the orbital plane by rocking the scanning mirror about the optical axis. The radiometers covered a strip about 2,500 kilometres (1,600 mi) wide on the Earth's surface and had a ground resolution of 50 kilometres (31 mi) at nadir.[7]
The data were reduced at the ground stations and were transmitted in binary form to the Hydrometeorological Center in Moscow, where they were recorded in digital form on magnetic tape and were used to produce various analysis products such an Earth-atmosphere albedo charts and radiation temperature maps. The data were archived at the Hydrometeorological Center. Some of these charts were transmitted in graphical form to various foreign meteorological centers, including the National Environmental Satellite Service (NESS), Suitland, Maryland. These actinometric charts were received at NESS via the "cold line" facsimile link with Moscow from early March 1967 to late October 1967 and late February 1968 to mid-March 1968, when, it is believed that experiment operations terminated. The charts were microfilmed and archived at the National Climatic Center (NCC), Asheville, North Carolina.[7]
Mission
Kosmos 144 was launched using a Vostok-2M (8A92M) s/n N15000-55 carrier rocket, which flew from Site 41/1 at Plesetsk. The launch occurred at 14:34:59 GMT on 28 February 1967 and was successful. Kosmos 144 was operated in a low Earth orbit, at an epoch of 28 February 1967, it had a perigee of 574 kilometres (357 mi), an apogee of 644 kilometres (400 mi), an inclination of 81.25° and an orbital period of 96.88 minutes.[2] Kosmos 144 ceased its operations in March 1968.
When two of the Kosmos "Meteor" system satellites were in operation at the same time in near-polar orbits and with suitable differences in the longitudes of the ascending nodes, data could be received from one-half the Earth's surface in a 24-hr period.[1]
References
- ↑ 1.0 1.1 1.2 1.3 1.4 1.5 "Cosmos 144: Display 1967-018A". NASA. 27 February 2020. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1967-018A. Retrieved 3 April 2020.
This article incorporates text from this source, which is in the public domain.
- ↑ 2.0 2.1 "Cosmos 144: Trajectory 1967-018A". NASA. 27 February 2020. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/displayTrajectory.action?id=1967-018A. Retrieved 3 April 2020. This article incorporates text from this source, which is in the public domain.
- ↑ Meteorological Satellite Systems, 1. S.l.: Springer, New York, 2014, Print.
- ↑ 4.0 4.1 4.2 4.3 Hendrickx, Bart. "A History of Soviet/Russian Meteorological Satellites". Space Chronicle: JBIS 57 (2004): pp. 56-102. Web. 17 April 2016.
- ↑ 5.0 5.1 5.2 "Cosmos 144: Experiment 1967-018A-01". NASA. 27 February 2020. https://nssdc.gsfc.nasa.gov/nmc/experiment/display.action?id=1967-018A-01. Retrieved 3 April 2020. This article incorporates text from this source, which is in the public domain.
- ↑ 6.0 6.1 6.2 "Cosmos 144: Experiment 1967-018A-02". NASA. 27 February 2020. https://nssdc.gsfc.nasa.gov/nmc/experiment/display.action?id=1967-018A-02. Retrieved 10 April 2020. This article incorporates text from this source, which is in the public domain.
- ↑ 7.0 7.1 7.2 7.3 7.4 7.5 "Cosmos 144: Experiment 1967-018A-03". NASA. 27 February 2020. https://nssdc.gsfc.nasa.gov/nmc/experiment/display.action?id=1967-018A-03. Retrieved 10 April 2020. This article incorporates text from this source, which is in the public domain.
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