Encyclopedia Astronautica
Resurs F1-14F40



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Resurs F-1
Credit: © Oliver Haa
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Resurs F1
Resurs F1 cutaway drawing
Russian earth land resources satellite. 7 launches, 1986.07.16 (Cosmos 1762) to 1988.02.18 (Cosmos 1920). The Resurs-F earth resource satellite was based on the recoverable Zenit-4 spy satellite.

Film resolution was 10-11 m black and white, 31-33 m multispectral. Swath width 147 to 225 km; total area covered per mission 27 to 76 million square km. A restartable engine allowed adjustment of orbit during mission.

A decree of 5 May 1977 authorized development of three earth resource satellites. The Ministry of Defense was tasked with developing these systems, even though they did not contribute directly to any military mission. Despite this political decision, the orders were followed. One of these was Resurs-F, which became Fram, based on the recoverable Zenit-4 spy satellite. The spacecraft's mission was investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. Typical orbital profile: inclination 81.3 to 82.6 degrees with altitude of 180-235 km or 185-280 km; maneuvering to an altitude of 260-275 km or 180-280 km; maneuvering to an altitude of 325-340 km. First flight: Cosmos 1762. Last flight: Cosmos 1920. Transmission frequencies observed in West: 231.5 PCM-FM.

With two missions in 1993, the Resurs-F1 program achieved 50 orbital flights (and two launch failures) during its 14-year operation with missions lasting up to 23 days. Based on the Vostok spacecraft developed in the late 1950's, Resurs-F1 spacecraft were designed and manufactured at the Samara (formerly Kuibyshev) Foton Design Bureau and the Progress Plant both of the Central Specialized Design Bureau.

The Resurs-F1 vehicle, launched by the Soyuz-U booster from Plesetsk, was 7 m long with a maximum diameter of 2.4 m and a mass of 6,300 kg and was comprised of three major modules. The central portion of the spacecraft was a sphere of 2.3 m diameter and a mass of about 2.4 metric tons containing the photographic apparatus, electronic control equipment, and the recovery system. This section was secured to a 3 m long, 2.4 m wide service and re-entry propulsion module with four straps which were released after retrofire. On the opposite end of the recoverable capsule was a 1.9 m by 1 m propulsion unit used for minor orbital adjustments. The propulsion unit was also jettisoned prior to re-entry and could carry additional, releasable payloads (up to 75 cm by 90 cm) for secondary missions. Secondary payloads up to 30 kg or more could also be carried inside or outside the recoverable capsule for return to Earth.

Two photographic systems were normally available on Resurs-F1 missions: the SA-20M with a KFA-1000 camera and the SA-34 with its KATE-200 camera. The former operated in two spectral bands (0.57-0.68 micrometer and 0.68-0.81 micrometer) with a ground swath of 80 km and a resolution of 5-8 m. Up to 1,800 frames measuring 300 mm by 300 mm could be taken on each mission. The SA-34 operated in three spectral bands (0.51-0.60 micrometer, 0.60-0.70 micrometer, and 0.70- 0.85 micrometer) with a ground swath of 225 km and a resolution of 15-30 m. The SA-34 had a capacity of 1,200 frames, each 180 mm by 180 mm. All film frames of both systems were etched with codes to identify vital camera parameters, including camera and frame number, film number, focal length, and timing codes.

Each Resurs-F1 spacecraft carried multiple camera systems. The Priroda 4 payload configuration included two SA-20M and three SA-34 devices. One of the SA-34's was linked to a SA-33 stellar camera to provide simultaneous star backgrounds for precise geographical location determination. The SA-34 survey regions were aligned with common axes, but the SA-20M cameras were each oriented 8 degrees off nadir for a total separation of 16 degrees between the camera axes, permitting a 5% image overlap when both systems were operated simultaneously. Six modes of operation were possible with 2-5 camera systems operating at one time. Although the maximum spacecraft lifetime was 25 days, the electrical system fed only by storage batteries limited active operations to no more than 14 days. The last two Resurs-F1 missions were flown in 1993 as Resurs-F 18 (June-July) and Resurs-F 19 (August-September, both on 17 day missions.

Characteristics

Spacecraft delta v: 114 m/s (374 ft/sec).

AKA: 14F40.
Gross mass: 6,300 kg (13,800 lb).
First Launch: 1986.07.10.
Last Launch: 1988.02.18.
Number: 7 .

More... - Chronology...


Associated Countries
See also
  • Soyuz The Russian Soyuz spacecraft has been the longest-lived, most adaptable, and most successful manned spacecraft design. In production for fifty years, more than 240 have been built and flown on a wide range of missions. The design will remain in use with the international space station well into the 21st century, providing the only manned access to the station after the retirement of the shuttle in 2011. More...

Associated Launch Vehicles
  • Soyuz Russian orbital launch vehicle. The world's first ICBM became the most often used and most reliable launch vehicle in history. The original core+four strap-on booster missile had a small third stage added to produce the Vostok launch vehicle, with a payload of 5 metric tons. Addition of a larger third stage produced the Voskhod/Soyuz vehicle, with a payload over 6 metric tons. Using this with a fourth stage, the resulting Molniya booster placed communications satellites and early lunar and planetary probes in higher energy trajectories. By the year 2000 over 1,628 had been launched with an unmatched success rate of 97.5% for production models. Improved models providing commercial launch services for international customers entered service in the new millenium, and a new launch pad at Kourou was to be inaugurated in 2009. It appeared that the R-7 could easily still be in service 70 years after its first launch. More...
  • Soyuz 11A511U Russian standardised man-rated orbital launch vehicle derived from the original R-7 ICBM of 1957. It has been launched in greater numbers than any orbital launch vehicle in history. Not coincidentally, it has been the most reliable as well. After over 40 years service in Russia, ESA built a new launch pad at Kourou which will keep it in service from three launch sites in three countries well into the mid-21st Century. More...

Associated Manufacturers and Agencies
  • MOM Russian agency overseeing development of spacecraft. Ministry of General Machine Building (Moskva, Russia), Moscow, Russia. More...
  • Kozlov Russian manufacturer of rockets and spacecraft. Kozlov Central Specialized Design Bureau, Samara, Russia. More...

Associated Programs
  • Resurs Zenit-derived satellites used for earth resources studies as part of the 'Resurs' and 'Gektor-Priroda' project. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: here.
  • Voevodin, Sergey A, "Sergey A. Voevodin's Reports", VSA072 - Space Apparatus, Web Address when accessed: here.
  • McDowell, Jonathan, Launch Log, October 1998. Web Address when accessed: here.
  • Kozlov, D I, Konstruirovanie avtomaticheskikh kosmicheskikh apparatov, Mashnostroenie, Moscow, 1996.

Associated Launch Sites
  • Plesetsk Plesetsk was the Soviet Union's northern cosmodrome, used for polar orbit launches of mainly military satellites, and was at one time the busiest launch centre in the world. The collapse of the Soviet Union put the main launch site of Baikonur in Kazakh territory. It now seems that once the Proton rocket is retired, Baikonur will be abandoned and Plesetsk will be Russia's primary launch centre. Upgrades to existing launch facilities will allow advanced versions of the Soyuz rocket and the new Angara launch vehicle to be launched from Plesetsk. Plesetsk's major drawback was the lower net payload in geosynchronous orbit from a northern latitude launch site. However Russia is planning to remove the disadvantage by looping geosynchronous satellites around the moon, using lunar gravity to make the necessary orbital plane change. More...
  • Plesetsk LC16/2 R-7 launch complex. Complex 16 was the second R-7A ICBM launch complex to become operationall at Plesetsk, in 1960. In 1969, Pad 2 was cannibalized to upgrade the Area 1 facility in Baikonur. Pad 2 was not again brought into operation until 1979. It was then completely renovated as a space launch pad for Molniya 8K78M/Soyuz 11A511U class vehicles. The first launch was on 19 February 1981, and it continued in use in this role into the 21st Century. More...

Resurs F1-14F40 Chronology


1986 July 10 - . 08:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1762 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-14F40. Duration: 8.00 days. Decay Date: 1986-07-24 . USAF Sat Cat: 16855 . COSPAR: 1986-051A. Apogee: 263 km (163 mi). Perigee: 177 km (109 mi). Inclination: 82.5000 deg. Period: 88.90 min. Summary: Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. .

1986 August 2 - . 09:20 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1768 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-14F40. Duration: 14.00 days. Decay Date: 1986-08-16 . USAF Sat Cat: 16890 . COSPAR: 1986-058A. Apogee: 273 km (169 mi). Perigee: 180 km (110 mi). Inclination: 82.6000 deg. Period: 89.00 min. Summary: Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. .

1986 October 31 - . 08:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1789 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-14F40. Duration: 14.00 days. Decay Date: 1986-11-14 . USAF Sat Cat: 17054 . COSPAR: 1986-084A. Apogee: 272 km (169 mi). Perigee: 178 km (110 mi). Inclination: 82.6000 deg. Period: 89.00 min. Summary: Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. .

1987 May 21 - . 07:44 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/4. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1846 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-14F40. Duration: 14.00 days. Decay Date: 1987-06-04 . USAF Sat Cat: 18004 . COSPAR: 1987-045A. Apogee: 283 km (175 mi). Perigee: 178 km (110 mi). Inclination: 82.3000 deg. Period: 89.10 min. Summary: Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. .

1987 June 18 - . 07:24 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/3. LV Family: R-7. Launch Vehicle: Soyuz 11A511U. LV Configuration: Soyuz 11A511U 77015-105. FAILURE: Booster exploded on pad.. Failed Stage: 0.
  • Resurs-F1 14F40 - . Payload: Resurs-F1 14F40 No. 105. Nation: USSR. Agency: UNKS. Program: Resurs. Spacecraft: Resurs F1-14F40. COSPAR: F870618A. Summary: Pad was badly damaged and not put back into service until December 1988..

1987 September 15 - . 10:30 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/4. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1882 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-14F40. Duration: 21.00 days. Decay Date: 1987-10-06 . USAF Sat Cat: 18348 . COSPAR: 1987-077A. Apogee: 269 km (167 mi). Perigee: 253 km (157 mi). Inclination: 82.3000 deg. Period: 89.70 min. Summary: Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. .

1988 February 18 - . 09:50 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1920 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-14F40. Duration: 20.00 days. Decay Date: 1988-03-09 . USAF Sat Cat: 18860 . COSPAR: 1988-010A. Apogee: 232 km (144 mi). Perigee: 185 km (114 mi). Inclination: 82.6000 deg. Period: 88.70 min. Summary: Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. .

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