world spacecraft digest by jos heyman 1968 version: 20 … · 2016. 8. 4. · kosmos-203 was the...

WORLD SPACECRAFT DIGEST by Jos Heyman 1968 Version: 20 August 2014 © Copyright Jos Heyman

1968 001A (03091) Name: Surveyor-7 Country: USA Launch date: 7 January 1968 Re-entry: 10 January 1968 Launch site: Cape Canaveral Launch vehicle: Atlas Centaur D Orbit: trans-lunar

Tycho Crater

Lunar landing craft as described for 1967 084A. Surveyor-7 carried the Survey Television Experiment Subsystem, the Alpha Scattering Experiment Subsystem and the Soil Mechanics Surface Sampler.

After a flight of 66 hours, 30 minutes, the spacecraft landed on the Moon at 40°52'S, 11°28'W (Tycho Crater). It dug seven trenches and performed chemical analysis of the soil. Until it ceased operations on 20 February 1968 it transmitted 21,274 pictures of the lunar surface. The overall result of the Surveyor programme confirmed that the lunar surface was capable to support an Apollo lunar module. It provided also data on the constituents of the lunar soil as well as many images of the surface.

1968 002A (03093) Name: Explorer-36 Country: USA Launch date: 11 January 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta DSV-3E1

Orbit: 1084 x 1577 km, inclination: 105.8° The objective of the Explorer-36 satellite, also known as the Geodetic Satellite (Geos)-2, was to provide information about the size and the shape of the Earth. It did so by determining the strength and variations of the Earth's gravitational field. The satellite was also used to establish the location of various tracking stations with an accuracy of 10 m. The payload of the 208 kg satellite consisted of: 1. an optical beacon system consisting of four xenon flash tubes which were photographed against a

background of stars; 2. a radio Doppler system of three transmitters and an ultra-stable oscillator to determine the line of sight

velocity of the satellite; 3. radio range and range rate transponders for simultaneous determination of satellite-to-groundstation

and line-of-sight velocity; 4. two C-band transponders and passive reflectors for range radar calibration; and 5. a laser detector. The satellite improved the techniques of accurately tracking satellites.

1968 003A (03099) Name: Kosmos-199 Country: USSR Launch date: 16 January 1968 Re-entry: 1 February 1968 Launch site: Plesetsk Launch vehicle: Voskhod

Orbit: 204 x 364 km, inclination: 65.6° Zenit 2 military reconnaissance satellite as described for 1962 ξ 1. On 24 January 1968 a capsule containing a transmitter was ejected. It was designated as 1968 003C (03115) and re-entered on 30 January 1968. Also on 24 January 1968 the main spacecraft was either fragmented or exploded.

1968 004A (03097) Name: Ferret-18 Country: USA Launch date: 17 January 1968 Re-entry: 7 July 1970 Launch site: Vandenberg Launch vehicle: TAT Agena D

Orbit: 450 x 546 km, inclination: 75.2° Military electronic intelligence gathering satellite as described for 1962 δ 1. Also known as Ops-1965 it was a Heavy Ferret-C.

1968 005A (03098) Name: KH 8-11 Country: USA Launch date: 18 January 1968 Re-entry: 4 February 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB

Orbit: 138 x 404 km, inclination: 111.5° Military reconnaissance satellite as described for 1966 069A. Also known as Ops-5028 and mission 4311.

1968 006A (03100) Name: Kosmos-200 Country: USSR Launch date: 19 January 1968 Re-entry: 24 February 1973 Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 523 x 537 km, inclination: 74.0° Tselina O military electronic intelligence gathering satellite as described for 1967 108A.

1968 007A (03106) Name: Apollo-5 Country: USA Launch date: 22 January 1968 Re-entry: 24 January 1968 Launch site: Cape Canaveral Launch vehicle: Saturn 1B

Orbit: 162 x 214 km, inclination: 31.6°

Apollo-5 was an automated test flight in the Apollo programme as described for 1966 059A, using Lunar Module (LM)-1 only. This was the first operational LM and the descent and ascent propulsion systems were tested. The ascent stage was designated as 1968 007A whilst the descent stage, designated as 1968 007B (03107), re-entered on 12 February 1968. They were not recovered. The mission was initially referred to as AS-204.

1968 008A (03113) Name: KH 4A-45 Country: USA Launch date: 24 January 1968 Re-entry: 27 February 1968 Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 176 x 430 km, inclination: 81.5° Military reconnaissance satellite as described for 1963 034A. Also known as Ops-2243 and mission 1045, the satellite ejected Hitchiker-17 (1968 008B) on 25 January 1968.

1968 008B (03114) Name: Hitchiker-17 Country: USA Launch date: 25 January 1968 Re-entry: 4 March 1970 Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 473 x 542 km, inclination: 81.7° Secondary payload as described for 1963 025B. The satellite was ejected from KH 4A-45 (1968 008A) and was also known as Ops-6236.

1968 009A (03118) Name: Kosmos-201 Country: USSR Launch date: 6 February 1968 Re-entry: 14 February 1968 Launch site: Baikonour Launch vehicle: Voskhod

Orbit: 204 x 337 km, inclination: 64.9° Zenit 4 military reconnaissance satellite as described for 1963 045A.

--- Name: --- Country: USSR Launch date: 7 February 1968 Re-entry: n.a. Launch site: Baikonour Launch vehicle: Molniya M Orbit: failed to orbit Type E-6LS lunar orbit spacecraft as described for 1968 027A, which failed to orbit.

1968 010A (03128) Name: Kosmos-202 Country: USSR Launch date: 20 February 1968 Re-entry: 24 March 1968 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I

Orbit: 213 x 482 km, inclination: 48.4° DS-U2-V minor military satellite as described for 1965 084A. Also referred to as DS-U2-V No.4.

1968 011A (03129) Name: Kosmos-203 Country: USSR Launch date: 20 February 1968 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 1178 x 1208 km, inclination: 74.1° Kosmos-203 was the first of the Sfera series of military geodetic satellites. The satellites had a mass of about 800 kg and were built by Reshetnev using the KAUR-1 platform and werfe also known as article 11F621.

1968 012A (03133) Name: NNSS-30180 Country: USA Launch date: 2 March 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Scout A

Orbit: 1035 x 1139 km, inclination: 90.0° Military navigational satellite as described for 1964 063B. Also known as Ops-7034.

1968 013A (03134) Name: Zond-4 Country: USSR Launch date: 2 March 1968 Re-entry: 9 March 1968 Launch site: Baikonour Launch vehicle: Proton K/D


The Zond-4 was a version of the cancelled Soyuz lunar spacecraft and was also known as Soyuz 7K-L1. The spacecraft consisted of: 1. the Soyuz service module as described for 1967 037A, but with a single KTDU-53 engine; 2. the re-entry module as for Soyuz; and 3. a docking collar. The spacecraft was also fitted with two solar panels. OKB-1 built 14 examples of the spacecraft. Three of these were intended for tests, seven were intended to be used for unmanned circumlunar flights and four were intended for manned circumlunar flights. Some of the subsequent Zond flights may have included the LK module.

After having been placed in a low-Earth parking orbit of 210 x 290 km with an inclination of 51.6°, Zond-4 was placed into a highly elliptical orbit opposite the Moon from which the spacecraft's abilities could be tested. It was to test navigation, communications as well as high speed re-entry. It also carried a proton sensor. The re-entry failed and the self destruction mechanism destroyed the spacecraft at an altitude of 10 km over the Atlatinc Ocean, 200 km off Africa. NASA still considers it as being in a solar orbit whilst other sources have suggested that it re-entered over China on 9 March 1968 and that the spacecraft is now on display in Beijing's Red Army military museum.

1968 014A (03138) Name: OGO-5 Country: USA Launch date: 4 March 1968 Re-entry: 2 July 2011 Launch site: Cape Canaveral Launch vehicle: Atlas Agena D


The Orbiting Geophysical Observatory (OGO)-5 conducted measurements of the Earth's trapped radiation belts, the magnetosphere and interplanetary space. The instruments included: 1. spherical retarding potential analysers; 2. spherical retarding potential plasma analysers; 3. a planar retarding potential analyser; 4. a scintillation and proportional counter telescope; 5. a scintillator telescope; 6. an electron/proton magnetic spectrometer; 7. a cylindrical electrostatic analyser; 8. a cosmic ray spark chamber; 9. a Cerenkov scintillator telescope; 10. scintillator solid-state telescopes; 11. a tri-axial electron electrostatic analyser; 12. a cosmic X-ray telescope; 13. a tri-axial fluxgate magnetometer and six solid-state detectors; 14. tri-axial fluxgate and rubidium vapor magnetometers; 15. tri-axial search coil magnetometers; 16. curved surface electrostatic analysers plus a Faraday cup analyser; 17. a magnetic ion mass spectrometer; 18. micrometeorite detectors; 19. a cosmic noise receiver; 20. an airglow ultraviolet photometer; 21. a geocoronal detector cell; 22. a solar X-ray proportional counter spectrometer; and

23. antennas to study plasma oscillations. Some of the experiments on the 611 kg satellite, failed after a short time. Findings by OGO-5 provided evidence of electric fields in the bow shock of the magnetosphere. The orbit was changed several times.

1968 015A (03139) Name: Kosmos-204 Country: USSR Launch date: 5 March 1968 Re-entry: 2 March 1969 Launch site: Plesetsk Launch vehicle: Kosmos 2I

Orbit: 275 x 844 km, inclination: 71.0° DS-P1-I radar calibration satellite as described for 1962 αδ 1. Also referred to as DS-P1-I No.3.

1968 016A (03140) Name: Kosmos-205 Country: USSR Launch date: 5 March 1968 Re-entry: 13 March 1968 Launch site: Plesetsk Launch vehicle: Voskhod

Orbit: 199 x 292 km, inclination: 65.7° Zenit 2 military reconnaissance satellite as described for 1962 ξ 1.

1968 017A (03141) Name: Explorer-37 Country: USA Launch date: 5 March 1968 Re-entry: 16 November 1990 Launch site: Wallops Island Launch vehicle: Scout B


The 90 kg Explorer-37, also known as the Solar Explorer-B or Solrad-9, measured and monitored selected solar X-ray and ultraviolet emissions. The payload consisted of: 1. a scintillation counter; 2. two Geiger-Mueller counters; 3. five X-ray photometers; and 4. two ultraviolet photometers. Due to a malfunction of the second stage the intended 1000 km circular orbit was not attained although the objectives of the mission were still achieved.

--- Name: --- Country: USSR Launch date: 6 March 1968 Re-entry: n.a. Launch site: Kapustin Yar Launch vehicle: Kosmos 2I Orbit: failed to orbit

DS-U1-Ya (U: Unifitsirovannye = unifunctional; 1: unoriented with chemical power source; Ya: Yadernoye = nuclear) scientific satellite as described for 1962 θ 1 which failed to orbit as the second stage failed 216 seconds after launch. The satellite had a mass of 367 kg. Also referred to as DS-U1-Ya No.1.

1968 018A (03148) Name: KH 8-12 Country: USA Launch date: 13 March 1968 Re-entry: 24 March 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 019A (03150) Name: Kosmos-206 Country: USSR Launch date: 14 March 1968 Re-entry: 22 April 1989 Launch site: Plesetsk Launch vehicle: Vostok

Orbit: 598 x 640 km, inclination: 81.2° Experimental meteorological satellite which returned weather and infrared images as well as thermal data.

1968 020A (03152) Name: KH 4A-46 Country: USA Launch date: 14 March 1968 Re-entry: 10 April 1968 Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 178 x 391 km, inclination: 83.0° Military reconnaissance satellite as described for 1963 034A. Also known as Ops-4849 and mission 1046, the satellite ejected Hitchiker-18 (1968 020B) on 14 March 1968.

1968 020B (03153) Name: Hitchiker-18 Country: USA Launch date: 14 March 1968 Re-entry: 3 January 1970 Launch site: Vandenberg Launch vehicle: Thorad Agena D


1968 021A (03154) Name: Kosmos-207 Country: USSR Launch date: 16 March 1968 Re-entry: 24 March 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 022A (03156) Name: Kosmos-208 Country: USSR Launch date: 21 March 1968 Re-entry: 2 April 1968 Launch site: Baikonour Launch vehicle: Voskhod

Orbit: 208 x 274 km, inclination: 65.0° Kosmos-208 was the first Zenit 2M military reconnaissance satellites which was based on the Zenit 2 military reconnaissance satellite as described for 1962 ξ 1. They were built by TsKB as article 11F690 and were fitted with a Ftor-2R3 camera system. The mass was approximately 6300 kg and the typical mission duration was 12 days. The spacecraft, which were also known as Gerakl, were modified by the addition of a capsule for an ancillary payload. Identified as Nauka (science), this capsule had a diameter of 1.9 m and a mass of 200 kg and was mounted on the forward end of the spherical re-entry module. It gave the spacecraft a basic mass of 5900 kg and a length of 5.9 m.

Nauka capsule

Details of several Nauka capsules are known but many more had undisclosed payloads. The capsule of Kosmos-208 carried a gamma ray flux package and was ejected on 29 March 1968 as 1968 022C (03167). It re-entered on 6 April 1968.

1968 023A (03158) Name: Kosmos-209 Country: USSR Launch date: 22 March 1968 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Tsyklon 2A

Orbit: 183 x 343 km, inclination: 65.0° US-A military ocean surveillance satellite fitted with radar equipment as described for 1967 127A. The satellite

was placed in an orbit of 871 x 944 km with an inclination of 65.3° on 28 March 1968.

1968 024A (03168) Name: Kosmos-210 Country: USSR Launch date: 3 April 1968 Re-entry: 11 April 1968 Launch site: Plesetsk Launch vehicle: Voskhod

Orbit: 200 x 373 km, inclination: 81.4° Zenit 2 military reconnaissance satellite as described for 1962 ξ 1. The satellite carried also an ancillary Earth resources payload.

1968 025A (03170) Name: Apollo-6 Country: USA Launch date: 4 April 1968 Re-entry: 4 April 1968 Launch site: Cape Canaveral Launch vehicle: Saturn 5


Apollo-6 was an automated test flight in the Apollo programme as described for 1966 059A using CSM-020 and LTA-2 to further test the CM heatshield performance at simulated lunar return re-entry speed. Although the second stage malfunctioned and the third stage failed to restart, the spacecraft was successfully

placed in orbit. The spacecraft was recovered on the same day near Hawaii at 27°38'N, 157°0'W. The mission was initially referred to as AS-502.

1968 026A (03173) Name: OV1-13 Country: USA Launch date: 6 April 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Atlas F


Scientific satellite as described for 1965 078A. The 107 kg Orbiting Vehicle (OV)1-13 was to measure radiation at altitudes below 8000 km, evaluate the space environment's effects on bearings and on friction between various material combinations as well as evaluate flexible cadmium sulphide solar cells. The payload consisted of: 1. a Geiger-Mueller counter; 2. four spectrometers; 3. a magnetic analyser; 4. an electrostatic analyser; 5. various material combinations for the friction and wear experiment; and 6. experimental cadmium sulphide solar cells.

1968 026B (03174) Name: OV1-14 Country: USA Launch date: 6 April 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Atlas F

Orbit: 571 x 9913 km, inclination: 100.0° Scientific satellite as described for 1965 078A. The 100 kg Orbiting Vehicle (OV)1-14 was to measure solar Lyman-alpha radiation and VLF and LF radiation in the Van Allen belts. The payload consisted of: 1. particle detectors to measure proton fluxes, proton spectra, electron spectra and the time dependence

of particles; 2. dE/dX telescopes; and 3. a Lyman-alpha experiment. Due to a power failure the satellite ceased transmitting data after one week.

1968 027A (03178) Name: Luna-14 Country: USSR Launch date: 7 April 1968 Re-entry: ? Launch site: Baikonour Launch vehicle: Molniya M Orbit: trans-lunar Luna-14 was a type E-6LS lunar orbiter which was developed from Luna-10 as described for 1966 027A. On

10 April 1968 it was placed in a lunar orbit of 160 x 870 km with an inclination of 42° and conducted experiments on the Moon's gravitational field, cosmic rays and charged particles as well as the lunar mass. It is also understood that electric motors for the Lunokhod vehicle were carried for testing purposes. The spacecraft ceased transmitting early in 1969 and it will have impacted on the Moon since then.

1968 028A (03181) Name: Kosmos-211 Country: USSR Launch date: 9 April 1968 Re-entry: 10 November 1968 Launch site: Plesetsk Launch vehicle: Kosmos 2I

Orbit: 199 x 1532 km, inclination: 81.9° DS-P1-Yu radar calibration satellite as described for 1964 042A. Also referred to as DS-P1-Yu No.13.

1968 029A (03183) Name: Kosmos-212 Country: USSR Launch date: 14 April 1968 Re-entry: 19 April 1968 Launch site: Baikonour Launch vehicle: Soyuz

Orbit: 186 x 225 km, inclination: 51.8° Kosmos-212 was a docking target for Kosmos-213 (1968 029A). It was based on the Soyuz spacecraft as described for 1967 037A and docked with Kosmos-213 on 15 April 1968 and remained so for 3 hours, 50 minutes. The spacecraft was fitted with external cameras and was also used in maneuvering tests, changing its orbit several times.

1968 030A (03193) Name: Kosmos-213 Country: USSR Launch date: 15 April 1968 Re-entry: 20 April 1968 Launch site: Baikonour Launch vehicle: Soyuz

Orbit: 188 x 254 km, inclination: 51.7° Kosmos-213, which was based on the Soyuz spacecraft as described for 1967 037A, conducted docking tests using Kosmos-212 (1968 029A) as a target. The two spacecraft docked on 15 April 1968 and remained attached for 3 hours, 50 minutes. External cameras mounted on Kosmos-212 provided a detailed view of the progress of the docking. In addition Kosmos-213 carried an extensive payload including a new type of luminescent micrometeorite detector, an ultraviolet photometer, a radiation sensing package incorporating Cerenkov detectors, as well as a cryogenic superconducting magnet and scintillation gas discharge detector.

1968 031A (03199) Name: KH 8-13 Country: USA Launch date: 17 April 1968 Re-entry: 29 April 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 032A (03203) Name: Kosmos-214 Country: USSR Launch date: 18 April 1968 Re-entry: 26 April 1968 Launch site: Plesetsk Launch vehicle: Voskhod

Orbit: 200 x 373 km, inclination: 81.4° Zenit 4 military reconnaissance satellite as described for 1963 045A. The satellite carried also an ancillary Earth resources payload.

1968 033A (03205) Name: Kosmos-215 Country: USSR Launch date: 19 April 1968 Re-entry: 30 June 1968 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I


DS-U1-A (U: Unifitsirovannye = unifunctional; 1: unoriented with chemical power source; A: Atmosfery = atmosphere) scientific satellite as described for 1962 θ 1. The 339 kg satellite carried eight telescopes for astronomical observations of the Sun. Also referred to as DS-U1-A No.1.

1968 034A (03207) Name: Kosmos-216 Country: USSR Launch date: 20 April 1968 Re-entry: 28 April 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 035A (03209) Name: Molniya 1-8 Country: USSR Launch date: 21 April 1968 Re-entry: 29 January 1974 Launch site: Baikonour Launch vehicle: Molniya M

Orbit: 391 x 39738 km, inclination: 64.9° Communications satellite as described for 1965 030A.

--- Name: --- Country: USSR Launch date: 22 April 1968 Re-entry: n.a. Launch site: Baikonour Launch vehicle: Proton K/D Orbit: failed to orbit A Soyuz spacecraft (1967 037A) similar to Zond-4 (1968 013A), which failed to orbit due to the second stage failure of the launch vehicle after 260 seconds. The escape system was activated and the spacecraft landed 520 km from the launch site and was recovered. It has been suggested the spacecraft was re-used on 20 January 1969.

1968 036A (03216) Name: Kosmos-217 Country: USSR Launch date: 24 April 1968 Re-entry: 26 April 1968 Launch site: Baikonour Launch vehicle: Tsyklon 2A

Orbit: 144 x 262 km, inclination: 62.2° I2M target satellite for anti-satellite technology tests as described for 1967 104A. Injection into a final orbit failed. Also known as article 5V91T.

1968 037A (03217) Name: Kosmos-218 Country: USSR Launch date: 25 April 1968 Re-entry: 25 April 1968 Launch site: Baikonour Launch vehicle: Tsyklon

Orbit: 123 x 162 km, inclination: 49.6° OGCh fractional orbit bombardment system (FOBS) test flight as described for 1966 088A.

1968 038A (03220) Name: Kosmos-219 Country: USSR Launch date: 26 April 1968 Re-entry: 2 March 1969 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I

Orbit: 215 x 1745 km, inclination: 48.4° DS-U2-D scientific satellite as described for 1962 θ 1 and 1966 117A. The 300 kg satellite studied the electron density. Also referred to as DS-U2-D No.2.

1968 039A (03228) Name: KH 4B-3 Country: USA Launch date: 1 May 1968 Re-entry: 15 May 1968 Launch site: Vandenberg Launch vehicle: Thorad Agena D


1968 040A (03229) Name: Kosmos-220 Country: USSR Launch date: 7 May 1968 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 675 x 760 km, inclination: 74.1° Tsiklon military navigational satellite as described for 1967 045A.

1968 041A (03233) Name: ESRO-2B Int. Agency: ESRO Launch date: 17 May 1968 Re-entry: 8 May 1971 Launch site: Vandenberg Launch vehicle: Scout B


The seven experiments carried on board of European Space Research Organisation (ESRO)-2B or the Infrared Interferometer Spectrometer or International Radiation Investigation Satellite (IRIS) satellite, were for the study of solar X-rays and cosmic and galactic particles. The instruments were to: 1. measure the changes over time in the Van Allen belt particle population; 2. measure protons and solar alpha particles and protons in the Van Allen belt following solar events; 3. determine the ratio of high-energy solar alpha particles to solar protons; 4. measure the flux and energy spectrum of high-energy primary cosmic ray electrons; 5. study solar X-rays in two different wavelengths; and 6. measure solar and galactic protons as well as alpha particles. The satellite, which had a mass of 75 kg, was a replacement for ESRO-2A which failed to orbit on 29 May 1967.

--- Name: Nimbus-B Country: USA Launch date: 18 May 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Thorad Agena D Orbit: failed to orbit

Nimbus-B spacecraft sensory ring located in 100 m of water off the coast of Southern California.

The Nimbus-B experimental meteorological satellite carried the following instruments: 1. an infrared interferometry spectrometer to provide global measurements of the atmosphere's vertical

temperature, water vapor and ozone distribution; 2. a satellite infrared spectrometer; 3. an interrogation, recording and location system; 4. an instrument to monitor ultraviolet solar energy; 5. an image dissector camera; 6. a high resolution infrared radiometer; 7. a medium resolution infrared radiometer; 8. a rate measuring package; and 9. a SNAP 19 power unit. A guidance malfunction of the launch vehicle caused the 572 kg payload to be destroyed after 2 minutes. The SNAP 19 unit was subsequently recovered.

--- Name: Secor-10 Country: USA Launch date: 18 May 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Thorad Agena D Orbit: failed to orbit Geodetic satellite as described for 1964 001C. The satellite was also known as OCE-704 and S68-2. A guidance malfunction of the launch vehicle caused the 20 kg payload to be destroyed after 2 minutes.

1968 042A (03266) Name: P35-20 Country: USA Launch date: 23 May 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Thor Burner II

Orbit: 817 x 904 km, inclination: 98.9° Improved version of the RCA Block 4A series of military meteorological satellites as described for 1966 082A. The satellites, identified as RCA Block 4B, had a mass of 195 kg. P35-20 was also known as Ops-7869.

1968 043A (03269) Name: Kosmos-221 Country: USSR Launch date: 24 May 1968 Re-entry: 31 August 1969 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I


1968 044A (03272) Name: Kosmos-222 Country: USSR Launch date: 30 May 1968 Re-entry: 11 October 1968 Launch site: Plesetsk Launch vehicle: Kosmos 2I


1968 045A (03274) Name: Kosmos-223 Country: USSR Launch date: 1 June 1968 Re-entry: 9 June 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 046A (03276) Name: Kosmos-224 Country: USSR Launch date: 4 June 1968 Re-entry: 12 June 1968 Launch site: Baikonour Launch vehicle: Voskhod

Orbit: 203 x 256 km, inclination: 51.8° Zenit 4 military reconnaissance satellite as described for 1963 045A. The satellite carried also an ancillary payload for the study of atmospheric composition and luminescence.

--- Name: --- Country: USSR Launch date: 4 June 1968 Re-entry: n.a. Launch site: Plesetsk Launch vehicle: Kosmos 3M Orbit: failed to orbit Sfera geodetic satellite as described for 1968 011A and which failed to orbit.

1968 047A (03278) Name: KH 8-14 Country: USA Launch date: 5 June 1968 Re-entry: 17 June 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 048A (03279) Name: Kosmos-225 Country: USSR Launch date: 11 June 1968 Re-entry: 2 November 1968 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I


DS-U1-Ya (U: Unifitsirovannye = unifunctional; Ya: Yadernoye = nuclear) scientific satellite as described for 1962 θ 1. The 255 kg satellite carried instruments to investigate electron flux and cosmic rays. Also referred to as DS-U1-Ya No.2

1968 049A (03282) Name: Kosmos-226 Country: USSR Launch date: 12 June 1968 Re-entry: 18 October 1983 Launch site: Plesetsk Launch vehicle: Vostok

Orbit: 579 x 639 km, inclination: 81.2° Experimental meteorological satellite which returned many cloud cover photos. It is generally held that this was the last precursor to the Meteor series as described for 1969 029A.

1968 050A (03284) Name: IDSCS-19 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC

Orbit: 33758 x 33841 km, inclination: 0.2° Military communications satellite as described for 1966 053B. Also known as Ops-9341.

1968 050B (03285) Name: IDSCS-20 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


1968 050C (03286) Name: IDSCS-21 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


1968 050D (03287) Name: IDSCS-22 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


1968 050E (03288) Name: IDSCS-23 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


1968 050F (03289) Name: IDSCS-24 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


1968 050G (03290) Name: IDSCS-25 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


1968 050H (03291) Name: IDSCS-26 Country: USA Launch date: 13 June 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


--- Name: --- Country: USSR Launch date: 15 June 1968 Re-entry: n.a. Launch site: Baikonour Launch vehicle: Kosmos 3 Orbit: failed to orbit Strela 2 military communications satellite as described for 1965 112A which failed to orbit.

1968 051A (03294) Name: Kosmos-227 Country: USSR Launch date: 18 June 1968 Re-entry: 26 June 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 052A (03296) Name: KH 4A-47 Country: USA Launch date: 20 June 1968 Re-entry: 16 July 1968 Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 193 x 326 km, inclination: 85.0° Military reconnaissance satellite as described for 1963 034A. Also known as Ops-5343 and mission 1047, the satellite ejected Hitchiker-19 (1968 052B) on 20 June 1968.

1968 052B (03297) Name: Hitchiker-19 Country: USA Launch date: 20 June 1968 Re-entry: 11 January 1970 Launch site: Vandenberg Launch vehicle: Thorad Agena D


1968 053A (03298) Name: Kosmos-228 Country: USSR Launch date: 21 June 1968 Re-entry: 3 July 1968 Launch site: Baikonour Launch vehicle: Voskhod

Orbit: 199 x 252 km, inclination: 51.6° Zenit 2M military reconnaissance satellite as described for 1968 022A. The satellite carried an ancillary payload to study ionising radiation. A Nauka capsule as described for 1968 022A, which was designated 1968 053G (03306), was ejected on 1 July 1968 and carried a cosmic ray payload. It re-entered on 7 July 1968.

1968 054A (03304) Name: Kosmos-229 Country: USSR Launch date: 26 June 1968 Re-entry: 4 July 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 055A (03307) Name: Explorer-38 Country: USA Launch date: 4 July 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta DSV-3J


Explorer-38, also called Radio Astronomy Explorer (RAE)-1, studied radio emissions from cosmic, solar and Earth sources. It carried four antennas arranged in a cross shape and with a span of 457 m. Two of the antennas pointed towards the Earth and two away from the Earth. During the satellite's operational life the instruments were saturated with Earth radio noise for up to 40% of the time and scientific observations were consequently limited. The mass of the satellite was 189 kg.

1968 056A (03308) Name: Kosmos-230 Country: USSR Launch date: 5 July 1968 Re-entry: 2 November 1968 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I

Orbit: 285 x 543 km, inclination: 48.4° DS-U3-S scientific satellite as described for 1962 θ 1 and 1967 061A. The satellite was a solar observatory and had a mass of 367 kg. Also referred to as DS-U3-S No.2.

1968 057A (03310) Name: Molniya 1-9 Country: USSR Launch date: 5 July 1968 Re-entry: 15 May 1971 Launch site: Baikonour Launch vehicle: Molniya M


1968 058A (03316) Name: Kosmos-231 Country: USSR Launch date: 10 July 1968 Re-entry: 18 July 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 059A (03318) Name: OV1-15 Country: USA Launch date: 11 July 1968 Re-entry: 6 November 1968 Launch site: Vandenberg Launch vehicle: Atlas F


OV1-15 and OV1-16

Scientific satellite as described for 1965 078A. The Orbiting Vehicle (OV)1-15 studied air density and solar radiation to identify the cause of large and sudden fluctuations in a satellite orbit with the ultimate goal of being able to predict such occurrences. The instruments consisted of: 1. a microphone density gauge; 2. several ion gauges; 3. various mass spectrometers; 4. several energetic particle detectors; 5. a solar X-ray monitor; 6. an ultraviolet monitor; 7. an ionosphere monitor; and 8. a tri-axial accelerometer. The 213 kg satellite has also been referred to as Solar Perturbation of Atmospheric Density Experiments Satellite (Spades).

1968 059B (03319) Name: OV1-16 Country: USA Launch date: 11 July 1968 Re-entry: 19 August 1968 Launch site: Vandenberg Launch vehicle: Atlas F

Orbit: 163 x 554 km, inclination: 90.0° Scientific satellite as described for 1965 078A. The Orbiting Vehicle (OV)1-16 measured the time and space variations of atmospheric density at altitudes as low as 120 km. Also referred to as Cannonball-1 or Low Altitude Density Satellite (Loads)-1, the satellite was a brass sphere with a diameter of 58 cm and a mass of 272 kg giving it a density equal to 690.5 kg/cubic meter, required to ensure that the satellite would not have decayed immediately. It carried a tri-axial accelerometer.

1968 060A (03322) Name: Kosmos-232 Country: USSR Launch date: 16 July 1968 Re-entry: 24 July 1968 Launch site: Plesetsk Launch vehicle: Voskhod

Orbit: 189 x 348 km, inclination: 65.3° Zenit 4 military reconnaissance satellite as described for 1963 045A. The satellite carried also an ancillary payload consisting of a passive microwave telescope.

1968 061A (03326) Name: Kosmos-233 Country: USSR Launch date: 18 July 1968 Re-entry: 7 February 1969 Launch site: Plesetsk Launch vehicle: Kosmos 2I


1968 062A (03332) Name: Kosmos-234 Country: USSR Launch date: 30 July 1968 Re-entry: 5 August 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 063A (03334) Name: Canyon-1 Country: USA Launch date: 6 August 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas Agena D

Orbit: 31680 x 39860 km, inclination: 9.9° The Canyon series of satellites were signals intelligence gathering satellites which were placed in so-called quasistationary orbits. These differ from a geostationary orbit in that they have an inclination of 3o to 10o with altitudes between 30,000 km and 42,000 km. With these parameters the satellite does not remain stationary relative to the Earth, but moves in a complex elliptical trajectory, thereby providing a broad view in the course of a day. This orbit also allows the direction to radio emitters to be measured from various points of the orbit which allows the determination of the location of the emitters through triangulation. The satellites were part of the National Reconnaissance Office’s Program A. The highly classified satellites were developed by the US Air Force and were also known as Program 827 or AFP-827. It is believed the satellites were 1.5 m in diameter and were fitted with one or more 3 m diameter antennas or a single 10 m antenna. Successor programmes to Canyon were known as Chalet and Vortex although these might be merely new cover names for upgrades to the same system. Canyon-1 was located over the Indian Ocean and was also known as Ops-3334 and Ops-2222 as well as the USSR designation RER-1E-1, with RER meaning Radio Elektronnaya Razvedka. For many years the satellite was thought to be the first Ballistic Missile Early Warning System (BMEWS) satellite, described as a cancelled project, to replace the earlier Midas system of military early warning satellites as described for 1960 ζ 1.

1968 064A (03335) Name: KH 8-15 Country: USA Launch date: 6 August 1968 Re-entry: 16 August 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 065A (03336) Name: KH 4B-4 Country: USA Launch date: 7 August 1968 Re-entry: 27 August 1968 Launch site: Vandenberg Launch vehicle: Thorad Agena D


1968 066A (03337) Name: Explorer-39 Country: USA Launch date: 8 August 1968 Re-entry: 22 June 1981 Launch site: Vandenberg Launch vehicle: Scout B

Orbit: 670 x 2538 km, inclination: 80.7° Explorer-39 or the Air Density Explorer (AD-E) investigated the density and temperature of the atmosphere at intermediate latitudes. It also measured the particle flux and energy and conducted observations in conjunction with Explorer-40 (1968 066B). The satellite was a 3.60 m mylar balloon inflated with nitrogen gas and painted with a polka dot pattern. The balloon was tracked optically and was also fitted with a radio beacon. It had a mass of 9.5 kg.

1968 066B (03338) Name: Explorer-40 Country: USA Launch date: 8 August 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Scout B


Also known as Injun-5 and Ionospheric Explorer (IE)-C, Explorer-40 was a 71 kg satellite to conduct magnetospheric studies to measure the particle flux and energy, VLF transmissions and atmospheric density in conjunction with Explorer-39 (1968 066A). The instruments consisted of: 1. the Low-Energy Proton Electron Differential Energy Analyser, consisting of three detectors and three

Geiger-Mueller tubes, which measured low-energy particles; 2. the Solid State Detector, including a proton/electron telescope and an alpha particle detector; 3. a VLF experiment comprising a magnetic receiver, with a loop antenna carried on a 3 m folding boom,

and two spherical antennas mounted on two shorter booms, measuring radio emissions at frequencies between 30 KHz and 10 KHz; and

4. the Spherical Retarding Potential Analyser, which consisted of two spherical analysers mounted on folding booms, one recording electrons, the other protons.

1968 067A (03339) Name: Kosmos-235 Country: USSR Launch date: 9 August 1968 Re-entry: 17 August 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 068A (03344) Name: ATS-4 Country: USA Launch date: 10 August 1968 Re-entry: 17 October 1968 Launch site: Cape Canaveral Launch vehicle: Atlas Centaur D


The Applications Technology Satellite (ATS)-4 was to test communications systems, evaluate gravity stabilisation, test an imaging orthicon camera and evaluate the station keeping abilities of an ion engine. The satellite was built by Hughes as a type HS-306. It had a mass of 391 kg, carried: 1. two gravity gradient booms; 2. two microwave repeaters; 3. an image orthicon camera with a resolution of 3 km; and 4. ion engines with two micro-thrusters. The second stage of the launch vehicle failed to restart and the desired geostationary orbit west of South America, was not achieved. Nevertheless, the ion engines were operated in five separate tests for a total of 23 hours.

1968 069A (03345) Name: ESSA-7 Country: USA Launch date: 16 August 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta DSV-3N


Meteorological satellite as described for 1966 008A. In addition the Environmental Sciences Services Administration (ESSA)-7 satellite carried a second Advanced Vidicon Camera System, radiometer sensors to measure the global distribution of solar radiation reflected by the Earth and the atmosphere, whilst the Automatic Picture Transmission system was deleted.

--- Name: OV 5-8 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Scientific satellite as described for 1967 040D. The 9 kg Orbiting Vehicle (OV)5-8 satellite, also known as ERS-19, was to conduct a materials friction experiment. The protective shroud surrounding the second stage of the launch vehicle failed to separate and the thirteen satellites, collectively referred to as SESP P68-1, were not deployed.

--- Name: Radcat-1 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit The 180 kg Radcat-1 satellite was to provide a radar calibration target. It was also known as RTD-802. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: LCS-3 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit The Licoln Calibration Sphere (LCS)-3, with a mass of 34 kg, was to be used for radar calibration. It was also known as RTD-701. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Grid Sphere Drag-A Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit One of four spheres of 10 kg to be used in an atmospheric drag experiment. The four spheres were collectively also known as AVL-802. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Grid Sphere Drag-B Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Atmospheric drag experiment as described for Grid Sphere Drag-A. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Grid Sphere Drag-C Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Atmospheric drag experiment as described for Grid Sphere Drag-A. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Grid Sphere Drag-D Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Atmospheric drag experiment as described for Grid Sphere Drag-A. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Orbis Cal-1 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Orbis Cal-1 was a 37 kg satellite to measure the effect of the ionosphere on communications. It was also known as NAS-801. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Secor-11 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Geodetic satellite as described for 1964 001C. It was also known as OCE-801. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Secor-12 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit Geodetic satellite as described for 1964 001C. It was also known as OCE-802. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: Lidos Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit The 53 kg Large Inclination Doppler Only Satellite (Lidos) was a US Navy experiment to investigate the Earth's sphericity and gravitational fields. It was also known as NAS-804. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: RM-18 Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit The objective of the 51 kg RM-18 satellite was to measure the Earth's infrared background radiation. It was also known as SSD-827. The protective shroud of the second stage of the launch vehicle failed to separate.

--- Name: UV Radiometer Country: USA Launch date: 16 August 1968 Re-entry: n.a. Launch site: Vandenberg Launch vehicle: Atlas Burner II Orbit: failed to orbit The UV Radiometer was an ultraviolet radiation experiment. Also known as SSD-801 and Earth Limb Measurement. The protective shroud of the second stage of the launch vehicle failed to separate.

1968 070A (03347) Name: Kosmos-236 Country: USSR Launch date: 27 August 1968 Re-entry: 4 March 1990 Launch site: Baikonour Launch vehicle: Kosmos 3

Orbit: 588 x 630 km, inclination: 56.1° Strela 2 military communications satellite as described for 1965 112A.

1968 071A (03348) Name: Kosmos-237 Country: USSR Launch date: 27 August 1968 Re-entry: 4 September 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 072A (03351) Name: Kosmos-238 Country: USSR Launch date: 28 August 1968 Re-entry: 1 September 1968 Launch site: Baikonour Launch vehicle: Soyuz

Orbit: 188 x 214 km, inclination: 51.7° Kosmos-238 tested Soyuz parachute recovery systems prior to the resumption of the Soyuz programme. The Soyuz spacecraft has been described for 1967 037A.

1968 073A (03353) Name: Kosmos-239 Country: USSR Launch date: 5 September 1968 Re-entry: 13 September 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 074A (03375) Name: KH 8-16 Country: USA Launch date: 10 September 1968 Re-entry: 25 September 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 075A (03388) Name: Kosmos-240 Country: USSR Launch date: 14 September 1968 Re-entry: 21 September 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 076A (03394) Name: Zond-5 Country: USSR Launch date: 15 September 1968 Re-entry: 21 September 1968 Launch site: Baikonour Launch vehicle: Proton K/D Orbit: circumlunar

Zond-5 was a test of a Soyuz lunar spacecraft as also described for 1968 013A, and carried a re-entry module which incorporated a biological sciences package including an instrumented dummy cosmonaut, two turtles, fruit flies, 237 drosophila melanogaster fly eggs, meal worms, spiderwort plants and various seeds, as well as an Earth photography system, instruments to study the solar wind and cosmic rays, instruments for the photometric measurement of various stars as and a communication system. The primary objective was, however, to test the re-entry heat shield. After an initial low-Earth orbit of 193 x 219 km, the spacecraft was placed in a circumlunar orbit in which it flew around the Moon achieving a minimum distance from the Moon of 1950 km, on 18 September 1968. During the flight around the Moon it also returned images from the far side of the Moon. Eventually the spacecraft

re-entered over the Indian Ocean where it was recovered at 32°38'S, 65°33'E. During the flight several mid-course corrections were made whilst communications were also tested. It has been suggested that due to a control failure the re-entry trajectory was too steep and a cosmonaut would have been killed. On 14 July 1968 a similar spacecraft, destined for launch on 19 July 1968, blew up on the launch pad due to a ruptured fuel tank. Although the spacecraft was not damages, it was crapped.

1968 077A (03398) Name: Kosmos-241 Country: USSR Launch date: 16 September 1968 Re-entry: 24 September 1968 Launch site: Plesetsk Launch vehicle: Voskhod


--- Name: Intelsat 3-F1 Int. Agency: Intelsat Launch date: 18 September 1968 Re-entry: n.a. Launch site: Cape Canaveral Launch vehicle: Delta DSV-3M Orbit: failed to orbit Communications satellite as described for 1968 116A. Due to a fault in the pitch rate system the first stage of the launch vehicle fell apart after 107 seconds in flight. It intended geostationary orbit was 31oW.

1968 078A (03408) Name: KH 4A-48 Country: USA Launch date: 18 September 1968 Re-entry: 8 October 1968 Launch site: Vandenberg Launch vehicle: TAT Agena D

Orbit: 167 x 393 km, inclination: 83.0° Military reconnaissance satellite as described for 1963 034A. Also known as Ops-0165 and mission 1048, the satellite ejected Hitchiker-20 (1968 078B) on 18 September 1968.

1968 078B (03409) Name: Hitchiker-20 Country: USA Launch date: 18 September 1968 Re-entry: 28 September 1969 Launch site: Vandenberg Launch vehicle: TAT Agena D


1968 079A (03414) Name: Kosmos-242 Country: USSR Launch date: 20 September 1968 Re-entry: 13 November 1968 Launch site: Plesetsk Launch vehicle: Kosmos 2I

Orbit: 272 x 406 km, inclination: 71.0° DS-P1-I radar calibration satellite as described for 1962 αδ 1. Also referred to as DS-P1-I No.4.

1968 080A (03418) Name: Kosmos-243 Country: USSR Launch date: 23 September 1968 Re-entry: 4 October 1968 Launch site: Baikonour Launch vehicle: Voskhod

Orbit: 213 x 293 km, inclination: 71.3° Zenit 2M military reconnaissance satellite as described for 1968 022A. On 2 October 1968 a Nauka capsule as described for 1968 022A, designated as 1968 080C (03452) was ejected to explore the shortcomings of conventional weather satellites by testing an instrument to study the thermal radiation of the Earth with a microwave receiver. This instrument was similar to a radioastronomy instrument except that it was aimed at the Earth. The capsule re-entered on 12 October 1968.

1968 081A (03428) Name: OV2-5 Country: USA Launch date: 26 September 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


Scientific satellite as described for 1965 082A. The Orbiting Vehicle (OV)2-5 satellite collected data on the space environment at a synchronous orbit altitude, including cosmic rays, trapped particle fluxes and changes in fluxes arising from solar and geomagnetic disturbances. The payload consisted of: 1. proton and electron spectrometers; 2. a dE/dX range telescope; 3. a low-energy Faraday cup; 4. an electron detector fan; 5. a VLF signal antenna; 6. a Lyman-alpha scanning photometer; 7. a magnetometer; 8. positive and negative plasma sensors; and 9. an Orbis High beacon antenna. Although only seven of the twelve appendages of the satellite deployed successfully, most of the instruments provided data. OV2-5 had a mass of 204 kg. The combined payloads on this flight have also been referred to as P67-2.

1968 081B (03429) Name: ERS-21 Country: USA Launch date: 26 September 1968 Re-entry: 15 February 1971 Launch site: Cape Canaveral Launch vehicle: Titan IIIC

Orbit: 184 x 35787 km, inclination: 26.4° Scientific satellite as described for 1967 040D. The 10 kg Environmental Research Satellite (ERS)-21 was also known as Orbiting Vehicle (OV)5-2 and was ejected from the launch vehicle during the early stages of the flight. The satellite conducted radiation studies by monitoring the electron and proton environments in the Van Allen belts. The instruments consisted of three sets of omni-directional spectrometers, several Geiger-Mueller tubes and directional detectors to measure electrons and protons.

1968 081C (03430) Name: ERS-28 Country: USA Launch date: 26 September 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


Scientific satellite as described for 1967 040D. The Environmental Research Satellite (ERS)-28 was also known as Orbiting Vehicle (OV)5-4 and P67-2. The 12 kg satellite obtained experimental data on the heat transfer in liquid under zero-gravity conditions in support of the SNAP design of propellant systems. The test tank contained heating elements immersed in fluid freon and an expandable bellows externally pressurised with a fluid mixture to permit constant vapor pressure measurements. The fluid pressures and temperatures were measured at various points in the tank. The experiment failed prematurely.

1968 081D (03431) Name: LES-6 Country: USA Launch date: 26 September 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan IIIC


The Lincoln Experimental Satellite (LES)-6 conducted communications tests to aid the development of a tactical communications system. It was also known as RTD-704. The payload consisted of: 1. an electronically despun antenna system; 2. a high-efficiency electrical power system; 3. an automatic self contained station keeping system; 4. instruments for radiation measurements; 5. a radio frequency interference experiment; and 6. a solar cell dosimeter. The satellite had a mass of 163 kg.

1968 082A (03449) Name: Kosmos-244 Country: USSR Launch date: 2 October 1968 Re-entry: 2 October 1968 Launch site: Baikonour Launch vehicle: Tsyklon

Orbit: 134 x 158 km, inclination: 49.6° OGCh fractional orbit bombardment system (FOBS) test flight as described for 1966 088A.

1968 083A (03457) Name: Kosmos-245 Country: USSR Launch date: 3 October 1968 Re-entry: 15 January 1969 Launch site: Plesetsk Launch vehicle: Kosmos 2I


1968 084A (03459) Name: ESRO-1A Int. Agency: ESRO Launch date: 3 October 1968 Re-entry: 26 June 1970 Launch site: Vandenberg Launch vehicle: Scout B


The 86 kg European Space Research Organisation (ESRO)-1A satellite, which was also known as Aurorae, studied the ionosphere and auroral phenomena. The instruments that were carried consisted of: 1. two photometers with interference filters for the measurement of auroral luminosity; 2. two boom mounted planar Langmuir probes for the measurement of electron density and

temperature; 3. a boom mounted spherical Langmuir probe for the measurement of the ion composition and

temperature; 4. a scintillator for the measurement of trapped and precipitated electron flux and energy spectra; 5. electrostatic analysers followed by channeltrons for the measurement of trapped and precipitated

electrons and protons with high time resolution; 6. three solid-state detectors to measure trapped and precipitated electrons; 7. four Geiger-Mueller counters to measure the pitch angle and distribution of electrons and protons with

high time resolution;

8. a ratemeter with an analogue output from a 90° Geiger-Mueller counter to measure trapped electrons and protons; and

9. a solid state detector and scintillator telescope with a half angle of 30° to measure flux and energy spectra of solar protons.

1968 085A (03469) Name: Molniya 1-10 Country: USSR Launch date: 5 October 1968 Re-entry: 16 July 1976 Launch site: Baikonour Launch vehicle: Molniya M


1968 086A (03472) Name: Ferret-19 Country: USA Launch date: 5 October 1968 Re-entry: 26 March 1971 Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 483 x 511 km, inclination: 75.0° Military electronic intelligence gathering satellite as described for 1962 δ 1. Also known as Ops-0964 it was a Heavy Ferret-D.

1968 087A (03473) Name: Kosmos-246 Country: USSR Launch date: 7 October 1968 Re-entry: 12 October 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 088A (03484) Name: Kosmos-247 Country: USSR Launch date: 11 October 1968 Re-entry: 19 October 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 089A (03486) Name: Apollo-7 Country: USA Launch date: 11 October 1968 Re-entry: 22 October 1968 Launch site: Cape Canaveral Launch vehicle: Saturn 1B


Rendez-vous with S-IVB stage

Crewed spaceflight with astronauts W. Schirra (Commander), D. Eisele (CM Pilot) and W. Cunningham (LM Pilot) using Apollo spacecraft CSM-101 as described for 1966 059A. The back-up crew consisted of T. Stafford, J. Young and E. Cernan. Mission objectives included the examination of combined operations of Saturn 1B, CSM and the Manned Space Flight Network, the manual control of the S-IVB stage prior to separation, the separation and simulated docking using SLA environmental guidance and navigation systems, SPS engine checkouts and subsequent rendez-vous with the S-IVB stage. In addition two photographic and three medical experiments were carried out. All mission objectives were met. The flight duration was 10 days, 20 hours, 9 minutes and the spacecraft was recovered by the USS Essex

app. 600 km south of Bermuda at 27°32'N, 64°4'W. The mission was initially referred to as AS-205.

1968 090A (03503) Name: Kosmos-248 Country: USSR Launch date: 19 October 1968 Re-entry: 26 February 1980 Launch site: Baikonour Launch vehicle: Tsyklon 2A

Orbit: 475 x 543 km, inclination: 62.3° I2M target satellite for anti-satellite technology tests as described for 1967 104A. Kosmos-248 was a target vehicle for Kosmos-249 (1968 091A) and Kosmos-252 (1968 097A).

1968 091A (03504) Name: Kosmos-249 Country: USSR Launch date: 20 October 1968 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Tsyklon 2A

Orbit: 493 x 2157 km, inclination: 62.4° I2P interceptor satellite for anti-satellite technology tests as described for 1967 104A. It was also known as article 4Ya11. Kosmos-249 intercepted Kosmos-248 (1968 090A) and self-destructed after the closest approach.

1968 092A (03510) Name: P35-21 Country: USA Launch date: 23 October 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Thor Burner II

Orbit: 797 x 855 km, inclination: 99.0° Military meteorological satellite as described for 1968 042A. Also known as Ops-4078.

1968 093A (03511) Name: Soyuz-2 Country: USSR Launch date: 25 October 1968 Re-entry: 28 October 1968 Launch site: Baikonour Launch vehicle: Soyuz

Orbit: 170 x 210 km, inclination: 51.7° Automatic flight of a Soyuz spacecraft as described for 1967 037A. Soyuz-2 provided a passive target for Soyuz-3 (1968 094A) which was to dock with Soyuz-2. Unlike the earlier docking tests with Kosmos-186 (1967 105A) and Kosmos-188 (1967 107A) as well as Kosmos-212 (1968 029A) and Kosmos-213 (1968 029A), in which the passive target was launched after the active spacecraft, the Soyuz-2/3 tests saw the passive spacecraft launched first. Originally the Soyuz-2 flight was intended to be a flight of three cosmonauts with V. Bykovsky, A. Yeliseyev and Y. Khrunov with the objective to rendez-vous with Soyuz-1 (1967 037A) and perform a formation flight and crew transfer, as would later be conducted by Soyuz-4 (1969 004A) and Soyuz-5 (1969 005A). The back-up crew would have consisted of P. Belyayev or A. Nikolayev, V. Kubasov and V. Gorbatko.

1968 094A (03516) Name: Soyuz-3 Country: USSR Launch date: 26 October 1968 Re-entry: 30 October 1968 Launch site: Baikonour Launch vehicle: Soyuz

Orbit: 177 x 203 km, inclination: 51.7° Crewed spaceflight with cosmonaut G. Beregovoi using a Soyuz spacecraft as described for 1967 037A. His call sign was Argon. During the 3 days, 22 hours, 51 minutes flight, Beregovoi succeeded in getting within a few meters of the Soyuz-2 (1968 093A) by using automatic and manual controls and made two unsuccessful docking attempts on 26 October 1968 and a further attempt on 27 October 1968. The cause of the failure was an incorrect alignment of the two spacecraft. During the remainder of the flight the cosmonaut, whose back-up was V. Shatalov, gathered geophysical data and photographed the Earth surface for resource studies.

1968 095A (03526) Name: Kosmos-250 Country: USSR Launch date: 30 October 1968 Re-entry: 15 February 1978 Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 522 x 542 km, inclination: 74.0° Tselina O military electronic intelligence gathering satellite as described for 1967 108A.

1968 096A (03528) Name: Kosmos-251 Country: USSR Launch date: 31 October 1968 Re-entry: 12 November 1968 Launch site: Baikonour Launch vehicle: Voskhod

Orbit: 201 x 255 km, inclination: 64.9° Kosmos-251 was the first of the Zenit 4M series of military reconnaissance satellites also known as Fram and was developed from the Zenit 4 military reconnaissance satellite as described for 1963 045A. With a mass of 6300 kg, they were built by TsKB as article 11F691 and were equipped with the Ftor-6 high resolution camera system. The design incorporated a maneuvering engine which allowed the orbit to be changed. Other modules of the spacecraft were the instrument module, a re-entry module and a camera equipment module. The engine module was usually separated towards the end of the mission. The typical mission duration was 14 days and it is understood some satellites were equipped with film return capsules as well as ancillary payloads. Kosmos-251 carried an ancillary payload for gamma flux radio astronomy.

1968 097A (03530) Name: Kosmos-252 Country: USSR Launch date: 1 November 1968 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Tsyklon 2A

Orbit: 531 x 2149 km, inclination: 62.3° I2P interceptor satellite for anti-satellite technology tests as described for 1967 104A. Kosmos-252 intercepted Kosmos-248 (1968 090A) and then fragmented near the target.

1968 098A (03531) Name: KH 4B-5 Country: USA Launch date: 3 November 1968 Re-entry: 23 November 1968 Launch site: Vandenberg Launch vehicle: TAT Agena D


1968 099A (03532) Name: KH 8-17 Country: USA Launch date: 6 November 1968 Re-entry: 20 November 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 100A (03533) Name: Pioneer-9 Country: USA Launch date: 8 November 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta DSV-3E1

Orbit: 0.756 x 0.99 AU, inclination: 0.09°

Interplanetary spacecraft as described for 1965 105A except that it carried three, instead of one, single-axis magnetometers as well as a celestial mechanics experiment to refine the measurements of the Earth-Moon mass ratio, the Sun-Earth distance, planetary orbits and to check the theory of relativity. The 67 kg spacecraft was placed in a 297 day solar orbit inside that of the Earth.

1968 100B (03534) Name: TTS-2 Country: USA Launch date: 8 November 1968 Re-entry: 19 September 1979 Launch site: Cape Canaveral Launch vehicle: Delta DSV-3E1

Orbit: 378 x 940 km, inclination: 32.9° Test target for NASA's Manned Space Flight Network as described for 1967 123B. Ut was also known as ERS-31.

1968 101A (03535) Name: Zond-6 Country: USSR Launch date: 10 November 1968 Re-entry: 17 November 1968 Launch site: Baikonour Launch vehicle: Proton K/D Orbit: circumlunar Test flight in the Soyuz lunar space programme as described for 1968 013A. The objective of the Zond-6 flight was more or less similar to that of Zond-5 (1968 076A). The flight tested, however, a new re-entry technique which made it land in the USSR rather than in the Indian Ocean. This technique employed a skip-return trajectory in which the upper atmosphere was used to aerodynamically reduce the speed of the spacecraft from 11 km/sec to 7.6 km/sec. The spacecraft passed behind the Moon at a distance of 2420 km on 14 November 1968. A biological payload consisting of animals and seeds was carried as well as micrometeorite detection equipment, a cosmic ray instrument and a standard aerial camera with a focal length of 400 mm which was used to take stereographic photos of the Moon. During re-entry the parachute released too early at an altitude of 5300 m as the seal of the re-entry capsule had developed a leak and the altimeter malfunctioned. The spacecraft crashed 16 km from the launch site and the photo were successfully recovered. After the flight, it was formally announced that Zond-4 (1968 013A), Zond-5 and Zond-6 had been precursors to crewed circumlunar flights.

1968 102A (03542) Name: Kosmos-253 Country: USSR Launch date: 13 November 1968 Re-entry: 18 November 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 103A (03544) Name: Proton-4 Country: USSR Launch date: 16 November 1968 Re-entry: 24 July 1969 Launch site: Baikonour Launch vehicle: Proton K


The Proton-4 satellite, which had a mass of 17,010 kg, studied high-energy cosmic rays and the energy spectrum of high-energy electrons. It carried an ionisation chamber. It has been suggested the satellite also tested the Salyut space station structure and that the scientific payload was merely a payload of opportunity.

1968 104A (03562) Name: Kosmos-254 Country: USSR Launch date: 21 November 1968 Re-entry: 29 November 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 105A (03574) Name: Kosmos-255 Country: USSR Launch date: 29 November 1968 Re-entry: 7 December 1968 Launch site: Plesetsk Launch vehicle: Voskhod


1968 106A (03576) Name: Kosmos-256 Country: USSR Launch date: 30 November 1968 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 1175 x 1227 km, inclination: 74.1° Sfera geodetic satellite as described for 1968 011A.

--- Name: STV-1 Int. Agency: ELDO Launch date: 30 November 1968 Re-entry: n.a. Launch site: Woomera Launch vehicle: Europa 1 Orbit: failed to orbit

The Satellite Test Vehicle (STV)-1 was a 250 kg technology satellite for the European Launcher Development Organisation (ELDO)'s Europa 1 launch vehicle. The flight was designated F-7. The satellite was a symmetrical polyhedron built in Italy and contained instruments for tracking and telemetry purposes. The third stage of the launch vehicle separated but fired for only 7 seconds and the desired orbit of 350 x 1000 km was not achieved. The satellite did transmit telemetry data for 15 minutes.

1968 107A (03578) Name: Kosmos-257 Country: USSR Launch date: 3 December 1968 Re-entry: 5 March 1969 Launch site: Plesetsk Launch vehicle: Kosmos 2I


1968 108A (03594) Name: KH 8-18 Country: USA Launch date: 4 December 1968 Re-entry: 12 December 1968 Launch site: Vandenberg Launch vehicle: Titan IIIB


1968 109A (03595) Name: HEOS-1 Int. Agency: ESRO Launch date: 5 December 1968 Re-entry: 28 October 1975 Launch site: Cape Canaveral Launch vehicle: Delta DSV-3E1


The Highly Eccentric Orbit Satellite (HEOS)-1 studied interplanetary space and solar particles. The 108 kg satellite carried: 1. a tri-axial fluxgate magnetometer to measure interplanetary magnetic fields and investigate the fine

structure at the shock front and the magnetosphere boundary; 2. two Cerenkov scintillator telescopes to investigate the directional anisotropy of relativistic protons in

relation to interplanetary magnetic fields; 3. two four-element surface barrier solid state detector telescopes covering the proton range from 1 to

20 MeV, to measure the energy spectrum and arrival direction of solar protons as well as to correlate these with the magnetic field configuration;

4. a Faraday cup collector to measure the energy spectrum and angular distribution of positive components;

5. a four-element solid state detector telescope to measure the flux and spectra of electrons, protons and alpha particles of solar and galactic origin; and

6. a four-element telescope with a gas Cerenkov counter and lead glass Cerenkov absorber to measure the flux and energy spectrum of the primary electron component of cosmic radiation.

In addition the satellite released a cloud of barium on 17 March 1969 at an altitude of 75,000 km. The expansion and motion of this cloud was observed by ground stations to discover how the expansion and motion are controlled by the physical environment at the release point.

The satellite's perigee was later raised whilst the inclination was changed to 60.1°.

1968 110A (03597) Name: OAO-2 Country: USA Launch date: 7 December 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas Centaur D


The Orbiting Astronomical Observatory (OAO)-2 carried: 1. four telescopes for the observation of hot main sequence stars in the ultraviolet; 2. a small detector for the study of nebulae; 3. four telescopes for stellar photometry; and 4. two ultraviolet stellar spectrometers. The satellite conducted the first ever sky survey in the ultraviolet and transmitted data for four years. It observed the first supernova from a satellite and made the first ultraviolet observations of Uranus. The satellite, which had a mass of 2016 kg, also measured the brightness of the other planets in the solar system.

1968 111A (03602) Name: Kosmos-258 Country: USSR Launch date: 10 December 1968 Re-entry: 18 December 1968 Launch site: Baikonour Launch vehicle: Voskhod


1968 112A (03604) Name: KH 4A-49 Country: USA Launch date: 12 December 1968 Re-entry: 28 December 1968 Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 169 x 248 km, inclination: 81.0° Military reconnaissance satellite as described for 1963 034A. Also known as Ops-4740 and mission 1049, the satellite ejected Hitchiker-21 (1968 112B) on 14 December 1968.

1968 112B (03605) Name: Hitchiker-21 Country: USA Launch date: 14 December 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Thorad Agena D

Orbit: 1391 x 1468 km, inclination: 80.3° Secondary payload as described for 1963 025B. The satellite was ejected from KH 4A-49 (1968 112A) and was also known as Ops-7684. It was a satellite in the Program 989 sub-series.

1968 113A (03612) Name: Kosmos-259 Country: USSR Launch date: 14 December 1968 Re-entry: 5 May 1969 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I

Orbit: 215 x 1331 km, inclination: 48.4° DS-U2-I scientific satellite as described for 1962 θ 1 and 1966 043A. The payload conducted ionospheric studies. It had a mass of 325 kg. Also referred to as DS-U2-I No.3.

1968 114A (03615) Name: ESSA-8 Country: USA Launch date: 15 December 1968 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta DSV-3N

Orbit: 1410 x 1473 km, inclination: 101.9° Meteorological satellite as described for 1966 008A.

1968 115A (03619) Name: Kosmos-260 Country: USSR Launch date: 16 December 1968 Re-entry: 9 July 1973 Launch site: Baikonour Launch vehicle: Molniya M

Orbit: 518 x 39570 km, inclination: 64.9° Molniya 1 communications satellite as described for 1965 030A which probably failed to become operational.

1968 116A (03623) Name: Intelsat 3-F2 Int. Agency: Intelsat Launch date: 19 December 1968 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta DSV-3M

Orbit: geostationary at 31°W Third generation communications satellite for the Intelsat organisation. The Intelsat 3 series satellites, which were built by TRW, were equipped with four transponders operating in the C band. The satellites had an in-orbit mass of 150 kg. Originally only six satellites were ordered and the final two satellites in the series, Intelsat 3-F7 (1970 032A) and Intelsat 3-F8 (1970 055A), were built from spares and a prototype and served as replacements for the failed satellites Intelsat 3-F1 and Intelsat 3-F5 (1969 064A).

1968 117A (03624) Name: Kosmos-261 Country: USSR Launch date: 20 December 1968 Re-entry: 12 February 1969 Launch site: Plesetsk Launch vehicle: Kosmos 2I


DS-U2-GK (U: Unifitsirovannye = unifunctional; 2: unoriented with solar power; GK: Geofizicheskiye Kompleksnye = geophysical complex) scientific satellite as described for 1962 θ 1. The objective of Kosmos-261 was to study the electrons and protons in the upper atmosphere of the Earth and investigate the nature of aurorae, including the atmospheric density during auroral activity. The instruments were provided by research institutes in Bulgaria, Czechoslovakia, the German Democratic Republic, Romania, Poland and the USSR and the satellite is often regarded as the first of the Interkosmos series, without being designated as such. The satellite had a mass of 440 kg. Also referred to as DS-U2-GK No.1.

1968 118A (03626) Name: Apollo-8 Country: USA Launch date: 21 December 1968 Re-entry: 27 December 1968 Launch site: Cape Canaveral Launch vehicle: Saturn 5 Orbit: circumlunar

Crewed spaceflight with astronauts F. Borman (Commander), J. Lovell (CM Pilot) and W. Anders (LM Pilot) using Apollo spacecraft CSM-103 and LTA-B as described for 1966 059A. The back-up crew consisted of N. Armstrong, E. Aldrin and F. Haise. Apollo-8 was originally scheduled to be a 'D' mission to be flown by J. McDivitt, D. Scott and R. Schweickart with C. Conrad, R. Gordon and A. Bean as their back-ups. By mid 1968 it was, however, obvious that the Lunar Module (LM) development was seriously behind schedule and NASA had to chose between a six months delay in Apollo-8 or selecting an alternative mission profile that did not require a LM. The scheduled Apollo-8 commander, McDivitt, had the first refusal on such a revised mission and opted to wait for the LM on which he had trained extensively. Consequently the Apollo-8 and Apollo-9 (1969 018A) crews, and their back-ups, exchanged places. As there was little point in simply repeating the Apollo-7 (1968 089A) mission, NASA opted for a circumlunar mission. Specific objectives included the demonstration of co-ordinated performance of the crew, CSM and support facilities during a crewed Saturn 5 mission, trans-lunar injection, CSM navigation and communications over lunar distances, mid-course corrections, consumables assessment and passive thermal control.

After an initial 182 x 189 km low-Earth parking orbit with an inclination of 32.6°, trans-lunar injection was initiated in the second orbit at 2 hours, 56 minutes after launch. Two mid-course corrections were made at 10 hours, 55 minutes and 60 hours, 58 minutes after launch and the spacecraft achieved an initial lunar orbit

of 112 x 313 km with an inclination of 168° at 69 hours, 12 minutes after launch. The orbit was later circularised at 112 km. Ten lunar orbits totalling 20 hours were made before the return journey was commenced 89 hours, 19 minutes hours after launch. Only one mid-course correction was required on the return journey and the SM was successfully separated

at 146 hours, 31 minutes after launch. The crew was recovered at 8°8'N, 165°1'W app. 1700 km north of Hawaii near the USS Yorktown. The total flight time had been 6 days, 3 hours, 1 minute. The mission was initially referred to as AS-503.

1968 119A (03629) Name: Kosmos-262 Country: USSR Launch date: 26 December 1968 Re-entry: 18 July 1969 Launch site: Kapustin Yar Launch vehicle: Kosmos 2I


DS-U2-GF (U: Unifitsirovannye = unifunctional; 2: unoriented with solar power; GF: Geofizicheskiye = geophysical) scientific satellite as described for 1962 θ 1. The mission undertook radiation studies and carried an X-ray monitor. It had a mass of 352 kg.

world spacecraft digest by jos heyman 1968 version: 20 … · 2016. 8. 4. · kosmos-203 was the...

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