world spacecraft digest by jos heyman 2016 ... carried 12 c band transponders, 46 ku band...

WORLD SPACECRAFT DIGEST by Jos Heyman 2016 Version: 10 July 2016 © Copyright Jos Heyman

2016 001A (41238) Name: Belintersat-1 Country: Belarus Launch date: 15 January 2016 Re-entry: in orbit Launch site: Xichang Launch vehicle: CZ 3B/E

Orbit: geostationary at 51.5°E

Communications satellite owned by Belintersat of Belarus. The 5223 kg satellite, formerly referred to as Belarus Sat-1, was based on the DFH-4 platform and carried 20 C band transponders and 22 Ku band transponders provided by Thales Alenia. Some of the transponders were sold to China Satcom and were operated as ZX-15.

2016 002A (41240) Name: Jason-3 Country: France/USA Launch date: 17 January 2016 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Falcon 9 v1.1 Orbit: 1302 x 1323 km, inclination: 66.0o

The Jason-3 operational oceanographic satellite was built by Thales Alenia for the French Space Agency CNES, to undertake ocean altimetry to measure precisely sea surface height to monitor ocean circulation and sea level. Its orbit provided coverage of all ice-free ocean surfaces. The 553 kg satellite, based on the Proteus platform, carried a Poseidon-3B dual-frequency altimeter as its key instruments, as well as the DORIS precise orbit determination system, an Advanced Microwave Radiometer (AMR), a GPS payload (GPSP), and a Laser Retro-reflector Array (LRA). Jason-3 was a joint mission by NOAA, the European Organisation for the Exploitation of Meteorological Satellites (Eumetsat), NASA and the French space agency, Centre National d'Etudes Spatiales (CNES). The satellite used a platform owned by France but NOAA and Eumetsat had taken over the programme from CNES. Recovery of the first stage of the launch vehicle on a barge downrange in the Pacific Ocean, failed after one of the landing legs at the base of the booster did not lock in place during final descent, causing the vehicle to tip over.

2016 003A (41241) Name: IRNSS-1E Country: India Launch date: 20 January 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: geostationary at 111.7°E Navigational satellite as described for 2013 034A.

--- Name: New Shepard Test-3 Country: USA Launch date: 22 January 2016 Re-entry: 22 January 2016 Launch site: Van Horn Launch vehicle: New Shepard Orbit: sub-orbital to 101.7 km

Launch test of the New Shepard commercial crewed spacecraft as described as a cancelled project but in its role as a sub-orbital vehicle. The dummy Crew Capsule successfully separated from the Propulsion Module and descended back to Earth by parachute. This was the same Propulsion Module that was used for the flight of 23 November 2015. The Propulsion Module made a successful powered vertical landing after 11 minutes.

2016 004A (41308) Name: Intelsat-29e Int. Agency: Intelsat Launch date: 27 Januari 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 5ECA

Orbit: geostationary at 50.0°W

Communications satellite owned by Intelsat and built by Boeing using the BSS-702MP platform. The 6552 kg satellite carried 12 C band transponders, 46 Ku band transponders and 1 Ka band transponder. Intelsat-29e was the first satellite in the so called EpicNG series of satellites which provide four to five times more capacity per satellite.

2016 005A (41310) Name: Eutelsat 9-B Int. Agency: Eutelsat Launch date: 29 January 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton M/Briz M

Orbit: geostationary at 9°E

Communications satellite owned by Eutelsat and built by Airbus using the Eurostar E3000 platform. The 5162 kg satellite was fitted with 66 Ku band transponders. The satellite also carried the European Data Relay Satellite System (EDRS)-A data relay payload to enable very high data rate, bi-directional data relay communications by laser between Earth observation satellites in low-Earth orbits and a ground station. The satellite was originally referred to as Eurobird-9B.

2016 006A (41315) Name: Beidou 3M-3S Country: China Launch date: 1 February 2016 Re-entry: in orbit Launch site: Xichang Launch vehicle: CZ 3C

Orbit: 21513 x 21982 km, inclination: 55.0° Navigational satellite as described for 2015 019A.

2016 007A (41328) Name: Navstar 2F-12 Country: USA Launch date: 5 February 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas V 401

Orbit: 20442 x 20457 km, inclination: 55.1°

Navigational satellite as described for 2010 022A. It was also known as GPS 2F-12, USA-266, Betelgeuse, Navstar-70, Navstar-76 and SVN-70.

2016 008A (41330) Name: Komos-2514 Country: Russia Launch date: 7 February 2016 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Soyuz 2-1b/Fregat M

Orbit: 19119 x 19157 km, inclination: 64.8° Glonass M navigational satellite as described for 2001 053A.

2016 009A (41332) Name: Kwangmyongsong-4 Country: North Korea Launch date: 7 February 2016 Re-entry: in orbit Launch site: Sohae Launch vehicle: Unha 3


Earth observation satellite as described for 2012 072A, although, with its mass being estimated at 150 to 200 kg, it may be a different design. Observers have reported that the satellite is tumbling in orbit and that no signals have been received, indicating that it may be non-operational.

2016 010A (41334) Name: Topaz-4 Country: USA Launch date: 10 February 2016 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta 4 M+(5,2)

Orbit: 1078 x 1085 km, inclination: 123.0° Radar imaging satellite as described for 2010 046A. Also known as USA-267 and NROL-45. The orbital data is based on amateur observations..

2016 011A (41335) Name: Sentinel 3-A Int. Agency: ESA Launch date: 16 February 2016 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Rokot KM


Sentinel-3A was an Earth observation satellite within the GMES (Global Monitoring for Environment and Security) or Copernicus programme, a joint European Commission and ESA programme for global land observation and collection of data on vegetation, soil and water cover for land, inland waterways and coastal The 1250 kg Sentinel 3-A carried three instruments: 1. the Sea and Land Surface Temperature (SLST) radiometer to measure surface temperatures; 2. the Ocean and Land Color Instrument (OLCI) to measure ocean chlorophyll activity and land surface

vegetation; and 3. a Radar Altimeter (RA) to measure sea surface topography.

2016 012A (41337) Name: Astro H Country: Japan Launch date: 17 February 2016 Re-entry: in orbit Launch site: Tanegashima Launch vehicle: H 2A-202


Previously known as New exploration X-Ray Telescope (NeXT) and also known as Hitomi, Astro-H was a space telescope to enable high sensitivity observations of celestial sources across a wide energy range, from X-rays to gamma-rays, bands presenting considerable technical challenges. In cooperation with institutions in the USA, Canada and Europe, the mission was to explore the structure and evolution of universe through imaging and spectroscopic observation. The 2400 kg spacecraft was fitted with: 1. the hard X-ray imaging system consisting of two identical mirror-detector instruments, the Hard X-ray

Telescope (HXT), which had conical-foil mirrors with graded multilayer reflecting surfaces, and the Hard X-ray Imager (HXI)), consisting of four-layers of 0.5 mm thick Double-sided Silicon Strip Detectors (DSSD) and one layer of 0.5—1 mm thick CdTe imaging detector to observe the behavior of soft and hard X-ray photons;

2. the Soft X-ray Spectrometer (SXS) consisting of the Soft X-ray Telescope (SXT-S), the X-ray Calorimeter Spectrometer (XCS) and the cooling system;

3. the Soft Gamma-ray Detector (SGD), a non-focusing soft gamma-ray detector with a 10—600 keV energy range and sensitivity at 300keV;

4. the soft X-ray imaging system consisting of the Soft X-ray Telescope (SXT-I), an imaging mirror and the Soft X-ray Imager (SXI), a CCD camera; and

5. the Canadian Astro-H Metrology System (CAMS). On 27 March 2016 contact was lost with the spacecraft and five objects (catalogued as 2016 012F, G, H, J and K) had been detected in the vicinity of the spacecraft which was observed to be tumbling in its orbit. Brief signals were received on three occasions until 28 March 2016 but after that the spacecraft was completely silent – likely due to the depletion of its onboard battery as no power is generated with the vehicle in a fast

spin. Optical and radar observations from the ground indicated that the roll rate on the spacecraft increased since the debris occurred A payload of 8 3U cubesats for commercial purposes, provided through Spaceflight Inc. and Japan Manned Space Systems Corporation (JAMSS), was deleted from the launch because they were not ready. They were to be deployed using the Sherpa space tug. Instead a mass simulator was carried.

2016 012B (41338) Name: ChubuSat-2 Country: Japan Launch date: 17 February 2016 Re-entry: in orbit Launch site: Tanegashima Launch vehicle: H 2A-202


ChubuSat-2, also known as Kinshachi-2, was a 50 kg satellite developed by the Nagoya and Daido Universities and several aerospace companies located in the Chubu region of Japan. The satellite was fitted with a radiation detector system to examine background radiation from the sun and Earth that could add noise to measurements by Astro-H (2016 012A).

2016 012B (41339) Name: ChubuSat-3 Country: Japan Launch date: 17 February 2016 Re-entry: in orbit Launch site: Tanegashima Launch vehicle: H 2A-202

Orbit: 559 x 578 km, inclination: 31.0° ChubuSat-3, also known as Kinshachi-3, was a 52 kg satellite developed by the Nagoya and Daido Universities and several aerospace companies located in the Chubu region of Japan. Using the same platform as used for ChubuSat-2 (2016 012B), this satellite carried a camera with a resolution of 10 m, to track the retreat of glaciers and shoreline changes to help study global warming as well as detecting space debris. In addition it carried a receiver for the Automatic Information System (AIS) to pick up positional and other information from ships at sea, and an instrument to relay messages between radio amateurs.

2016 012D (41340) Name: Horyu-4 Country: Japan Launch date: 17 February 2016 Re-entry: in orbit Launch site: Tanegashima Launch vehicle: H 2A-202


Horyu-4, also known as Arc Event Generator and Investigation Satellite (AEGIS), was a 10 kg technology demonstration satellite built by the Kyushu Institute of Technology. The primary objective was the demonstration of High-Voltage Solar Arrays and associated plasma mitigation techniques. Other instruments carried by the satellite were: 1. an onboard oscilloscope and an arc vision camera to acquire the current waveform and images of arcing

phenomena occurring on the solar arrays; 2. a power-system experiment to evaluate the degradation of filmed and coated triple-junction solar cells; 3. Double Langmuir probes to measure the density and temperature of the plasma the satellite flies through; 4. a Vacuum Arc Thruster interfacing with the 300-Volt solar array to complete a demonstration of a trigger-

less vacuum arc thruster; 5. an Electron-Emitting Film consisting of a 20-micrometer fluoro-polymer insulation film applied to the high-

voltage solar cells to avoid an excessive surface charging on the satellite; 6. the Secret Ink material science experiment to monitor several different polymer materials over an

extended period of time for an assessment of their degradation caused by atomic oxygen; 7. the Photoelectron Current Measurement for the generation of electrical spectra on a metal and isolator

when illuminated by the sun; 8. a CMOS camera to deliver color photos of Earth to be used in space awareness campaigns and

education; and 9. Digi-Singer, an amateur radio payload that can be used by radio operators to upload songs to the satellite

which can be sent back using the UHF frequency.

2016 013A (41380) Name: SES-9 Country: Luxembourg Launch date: 4 March 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Falcon 9 FT

Orbit: geostationary at 108.2°E

Communications satellite built by Boeing using the BSS-702HPplatfoorm. Owned by SES Satellite Leasing Ltd., a subsidiary of SES, the 5270 kg satellite carried 57 Ku band transponders. The spacecraft also had a xenon ion propulsion system (XIPS) for on-orbit maneuvering and a chemical bi-propellant system for initial orbit raising. Recovery of the first stage of the launch vehicle failed.

2016 014A (41382) Name: Eutelsat 65 West-A Int. Agency: Eutelsat Launch date: 9 March 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 5ECA

Orbit: geostationary at 65°W

Communications satellite owned by Eutelsat and built by Space Systems/Loral using the LS 1300 latform. The 6600 kg satellite was fitted with 10 C band, 24 Ku band transponders and a Ka band transponder. The launch was without the usual second satellite in the lower payload berth as Eutelsat wanted to get the satellite on location before the 2016 Olympic Games in Rio de Janeiro. No satellite for the lower payload berth could be found for a launch at the same time period.

2016 015A (41384) Name: IRNSS-1F Country: India Launch date: 10 March 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 016A (41386) Name: Resurs P-3 Country: Russia Launch date: 13 March 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Soyuz 2.1b

Orbit: 281 x 451 km, inclination: 97.3° Earth observation satellite as described for 2013 030A.

2016 017A (41388) Name: ExoMars/TGO Int. Agency: ESA Launch date: 14 March 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton M/Briz M Orbit: trans martian trajectory

Originally initiated in 2005 as a joint ESA/NASA programme and changed into a ESA/Roscosmos programme after NASA withdrew in 2012, the Exobiology on Mars (ExoMars) programme was a two spacecraft mission to search for biosignatures of Martian life, either in the past or in the present. In addition the mission was to investigate the water and geochemical distribution, to study the surface environment and identify hazards to future manned missions to Mars, to investigate the planet's subsurface and deep interior to better understand the evolution and habitability of Mars and achieve incremental steps ultimately culminating in a sample return flight. Developed by the European Space Agency in collaboration with Roscosmos, the mission consisted of:

• The Trace Gas Orbiter (TGO) and an EDM stationary lander called 'Schiaparelli'; and

• A Russian lander to deliver an ESA-built rover to the martian surface in 2018. The 4332 kg Trace Gas Orbiter (TGO), built in Europe, carried a 112 kg science payload: 1. Nadir and Occultation for MArs Discovery (NOMAD), two infrared and one ultraviolet spectrometers to

perform high-sensitivity orbital identification of atmospheric components, including methane and many other species, via both solar occultation and direct reflected-light nadir observations;

2. Atmospheric Chemistry Suite (ACS), a suite of three infrared instruments to investigate the chemistry and structure of the Martian atmosphere. ACS will complement NOMAD by extending the coverage at infrared wavelengths, and by taking images of the Sun to better analyse the solar occultation data;

3. Colour and Stereo Surface Imaging System (CaSSIS), a high resolution camera (5 m per pixel) capable of obtaining colour and stereo images over a wide swath. CaSSIS provided the geological and dynamical context for sources or sinks of trace gases detected by NOMAD and ACS; and

4. Fine Resolution Epithermal Neutron Detector (FREND), a neutron detector to map hydrogen on the surface down to a metre deep, revealing deposits of water-ice near the surface.

In addition the TGO carried the Entry, Descent and Landing Demonstrator Module (EDM), also named Schiaparelli, a 600 kg vehicle fitted with three clusters of 3 hydrazine pulse engines and two 12m diameter parachute. The lander was named after the 19th century astronomer Giovanni Schiaparelli. The Schiaparelli carried the Dust Characterisation, Risk Assessment, and Environment Analyser on the Martian Surface (DREAMS) package, consisting of a suite of sensors to measure the wind speed and direction (MetWind), humidity (DREAMS-H), pressure (DREAMS-P), atmospheric temperature close to the surface (MarsTem), the transparency of the atmosphere (Solar Irradiance Sensor, SIS), and atmospheric electrification (Atmospheric Radiation and Electricity Sensor; MicroARES). The Entry and Descent Module Descent Camera (DECA) on the EDM delivered additional scientific data and exact location data in the form of images during the descent.

After entering into an orbit around Mars in December 2016, the TGO will deploy the EDM Schiaparelli that will land at Meridiani Planum. TGO will then continue in a martian orbit to undertake its own observations as well as serving as a relay station for the EDM Schiaparelli and the 2018 lander. The second ExoMars mission, scheduled for launch in May 2018 will comprise a Russian lander fitted with a rover vehicle that will travel across the martian surface and drill two metres below the surface, and a stationary surface science platform. After landing on Mars in 2019, the rover will descend from the lander via a ramp. Then both, the lander and the rover, will begin their scientific operations.

2016 018A (41391) Name: Soyuz TMA-20M Country: Russia Launch date: 18 March 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Soyuz FG

Orbit: 206 x 422 km, inclination: 51.6° Crewed spaceflight with cosmonauts A. Ovchinin (Cmdr.), O. Skripochka (Fl.Eng) and J. Williams (USA)(Fl.Eng) using a modified Soyuz TMA spacecraft as described for 2010 052A. The mission was also known as ISS-46S and the call sign was Burlak. They were members of the forty seventh permanent crew (EX-47) and later the forty eigth permanent crew (EX-48) for ISS. The spacecraft docked at the Poisk nadir docking port of ISS (1998 067A) on 19 March 2016.

2016 019A (41393) Name: Cygnus Orb-6 Country: USA Launch date: 23 March 2016 Re-entry: 22 June 2016 Launch site: Cape Canaveral Launch vehicle: Atlas V-401


Cargo spacecraft as described for 2013 051A. Also referred to as OA-6, the spacecraft, also known as the SS Rick Husband, docked at the Earth facing port of the Unity module of ISS (1998 067A) on 26 March 2016. The spacecraft was fitted with an extended PCM. The launch vehicle for this flight had originally been intended for the GOES-R flight, which had been delayed. It carried 3513 kg of cargo comprising 1157 kg of crew provisions, 98 kg of computer resources, 1108 kg of vehicle hardware, 157 kg of EVA equipment and 777 kg of scientific and reseach equipment, including 20 Flock 2e’ Earth observation satellites, 5 Lemur 2 satellites as well as the Diwata-1 satellite. Diwata-1 (2998 067HT) was deployed on 27 April 2016. Flock 2e’1, Flock 2e’-3, Flock 2e’-2 and Flock 2e’-4 were deployed on 17 May 2016 as 1998 067HZ, 1998 067JA, 1998 067JB and 1998 067JC respectively. Lemur 2-5, 2-6, 2-7, and 2-8 were deployed on 18 May 2016 as 1998 067JF, 1998 067JJ, 1998 067JK and 1998 067JL respectively. Flock 2e’-5, Flock 2e’-6, Flock 2e-7 and Flock 2e’-8 were deployed on 31 May 2016 as 1998 067JR, 1998 067JS, 1998 067JT and 1998 067JU, whilst Flock 2e’-9 and Flock 2e’10 were deployed on 1 June 2016 as 1998 067JZ and 1998 067KA. On 2 June 2016 Flock 2e’-11 and Flock 2e’-12 were deployed as 1998 067KB and 1998 067KC. Once the Cygnus Orb-6 undocked on 14 June 2016, it was used in the Spacecraft Fire Experiment (SAFFIRE)-1 experiment to study how flames spread in weightlessness. The deliberate fire was be contained in an instrumented research box measuring 89 x 130 cm. NASA intends to run SAFFIRE experiments on three consecutive Cygnus spacecraft launching through the end of this year. The SAFFIRE-1 and -3 tests will use single combustion samples of 40 x 97 cm, whilst the SAFFIRE-2 test will use nine smaller combustion samples, each measuring 5 x 15 cm. The burns are expected to last 15 to 20 minutes and the development of the flames will be recorded by two cameras. In addition the spacecraft deployed four Lemur 2 satellites as 2016 019B, 2016 019C, 2016 019D and 2016 019E on 21 June 2016. A fifth Lemur 2 satellite failed to deploy and burned up in the atmosphere with Cygnus Orb-6.

2016 019B (41595) Name: Lemur-2 Bridgeman Country: USA Launch date: 21 June 2016 Re-entry: in orbit Launch site: Cygnus Orb-6 Launch vehicle: ---

Orbit: 389 x 393 km, inclination 51.6° Meteorological and navigational satellite as described for 2015 052D. The satellite was deployed from Cygnus Orb-6 (2016 019A).

2016 019C (41596) Name: Lemur-2 Dr Muzz Country: USA Launch date: 21 June 2016 Re-entry: in orbit Launch site: Cygnus Orb-6 Launch vehicle: ---


2016 019D (41597) Name: Lemur-2 Nate Country: USA Launch date: 21 June 2016 Re-entry: in orbit Launch site: Cygnus Orb-6 Launch vehicle: ---


2016 019E (41598) Name: Lemur-2 Cubecheese Country: USA Launch date: 21 June 2016 Re-entry: in orbit Launch site: Cygnus Orb-6 Launch vehicle: ---


2016 020A (41394) Name: Kosmos-2515 Country: Russia Launch date: 24 March 2016 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Soyuz 2.1a

Orbit: 328 x 541 km, inclination: 97.6° Bars M topographical satellite as described for 2015 009A.

2016 021A (41434) Name: Beidou 2-IGSO6 Country: China Launch date: 30 March 2016 Re-entry: in orbit Launch site: Xichang Launch vehicle: CZ 3A

Orbit: 35676 x 35890 km, inclination: 55.3° Navigational satellite in the Compass system as described for 2007 011A.

2016 022A (41436) Name: Progress MS-02 Country: Russia Launch date: 31 March 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Soyuz 2-1a

Orbit: 403 x 406 km, inclination: 51.6° Cargo transfer spacecraft as described for 2015 080A. Progress MS-02 docked at the Zvezda port of ISS (1998 067A) on 2 April 2016. The flight was also known as ISS-63P. The spacecraft was scheduled to undock in July 2016. Progress MS-02 also carried the Tomsk-TPU 120 cubesat which was to be released at a later date.

--- Name: New Shepard Test-4 Country: USA Launch date: 2 April 2016 Re-entry: 2 April 2016 Launch site: Van Horn Launch vehicle: New Shepard Orbit: sub-orbital to 103.4 km Launch test of the New Shepard commercial crewed spacecraft as described as a cancelled project but in its role as a sub-orbital vehicle. The dummy Crew Capsule successfully separated from the Propulsion Module and descended back to Earth by parachute. The Propulsion Module made a successful powered vertical landing after 11 minutes. This was the same Propulsion Module that was used for the flights of 23 November 2015 and 22 January 2016. The flight also carried two experiments into a sub-orbital trajectory without deploying them: 1. Collisions Into Dust Experiment (COLLIDE), an experiment developed at the University of Central Florida

consisting of a marble being launched into a bed of dust in microgravity conditions. The impact of the marble on the dust was filmed to possibly reveal mechanisms of dust collisions in the early solar system and interactions of particles within planetary rings, also looking at dust on bodies with insignificant gravitational fields; and

2. Box of Rocks Experiment (BORE), a pair of boxes filled with small rocks prepared by the Southwest Research Institute Experiment to better understand the behavior of loose rocky soil on asteroids and other bodies.

2016 023A (41448) Name: SJ-10 Country: China Launch date: 5 April 2016 Re-entry: 18 April 2016 Launch site: Jiuquan Launch vehicle: CZ 2D


Shi Jian (SJ)-10 was a 3600 kg recoverable satellite carrying twenty different scientific experiments: 1. Space Experiment of Evaporation and Fluid Interfacial Effects (EFILE) to study the thermocapillary effects

at the liquid-gas phase change interface in an evaporation process; 2. Phase Separation and dynamic clustering in granular ga, an experiment to study the physics behind

granular transportation in microgravity; 3. SOBER-SJ10 (Single bubble pool boiling experiment aboard SJ-10), to study local convection and heat

transfer on an isolated local vapor bubble during nucleate boiling on a simple flat plate heater outfitted with a number of sensors to measure the temperatures underneath the bubble;

4. Space experiment on surface wave of thermocapillary convection using thermal sensors, infrared imagers and a displacement sensor to gain knowledge on flow patterns, oscillations, and transition issues of thermocapillary convection;

5. Study on the colloidal assembling (SJY305-10), an experiment to look at self-assembly processes in colloidal media to uncover mechanisms behind the creation of colloidal crystals;

6. Study on ignition, soot emission and smoke distribution of wire insulations by overload, to investigate the pre-ignition characteristics of wire insulation in microgravity;

7. Investigation of the coal combustion and pollutant formation characteristics under microgravity, comprising two investigations to uncover fundamental processes and mechanisms in combustion of solid materials as single particles or pulverized clouds of typical coals found in China;

8. Ignition and burning of solid materials in microgravity to study flame propagation using eight fuel samples, in order to develop fire safety systems for future spaceflights;

9. Solidification and crystal growth in space, to synthesize large semiconductor crystals with uniform composition and virtually no defects, and high quality metal alloys that can not be obtained in gravity;

10. Synthesis and characterization of high-performance thermoelectric semiconductors with favorable thermal/electrical properties to permit a study of their microstructure;

11. Soret coefficients of crude oil (SCCO), a joint Chinese/ESA experiment to study the Soret Coefficient of crude oil which has implications for the understanding of Earth’s oil reservoirs;

12. Molecular biology mechanism of space radiation mutagenesis, using plant samples located in three different radiation environments inside the satellite to extract information on biological changes undergone by the organisms as a function of radiation dose;

13. Roles of space radiation on genomic DNA and is genetic effects, using radiation-sensitive mutant mammalian cells and fruit flies that are exposed to the space radiation environment to examine the quantitative effects of radiation on the stability of the species’ genomes;

14. Effects of space environment on silkworm embryo development and mechanism of mutation; 15. Biological Effects and the signal transduction of microgravity simulation in plants in order to understand

how plants sense microgravity; 16. Biomechanics of mass transport of cell interactions under microgravity in order to understand how

mammal cells can sense microgravity; 17. Photoperiod-controlling flowering of arabidopsis and rice in microgravity, to study the mechanisms behind

the light-induced flowering signal traveling from the leaf to the shoot apex; 18. an experiment to study the three-dimensional cell culture of neural and hematopoietic stem cells in space; 19. Development of mouse early embryos in space, to study the effects of the space environment on

mammalian reproductive systems using mouse embryos; and 20. an experiment to study potential and molecular mechanism of osteogenic differentiation from human bone

mesenchymal stem cells. The spacecraft was successfully recovered. SJ-10 was originally to be launched a few years after SJ-8 (2006 035A) but was delayed until a restructure the Chinese space research program in 2011 following which the China Academy of Sciences was handed authority over scientific missions.

2016 024A (41452) Name: Dragon CRS-8 Country: USA Launch date: 8 April 2016 Re-entry: 11 May 2016 Launch site: Cape Canaveral Launch vehicle: Falcon 9 v 1.2

Orbit: 402 x 406 km, inclination: 51.6° Resupply mission for the International Space Station using the Dragon C spacecraft as described for 2010 066A. The mission carried 3,136 Kilograms of cargo, including 640 kg of science investigations, 547 kg of crew supplies, 306 kg of systems hardware including maintenance equipment and replaceable parts, 12 kg of spacewalk equipment, 108 kg of computer resources and cameras, 33 kg of Russian Hardware, whilst 1413 kg accounted for the Bigelow Expandable Activity Module (BEAM) was carried as external cargo. The spacecraft was docked with the nadir port of the Harmony module of ISS (1998 067A) on 10 April 2016.

BEAM

The Bigelow Expandable Activity Module (BEAM) was an expandable module that remained attached to the ISS for a period of two years as part of a test of an expandable space habitat in the actual mission environment over a longer time scale On 16 April 2016. the Canadarm2 robotic arm took the pallet that carried BEAM and attached it to the aft Common Berthing Mechanism on the Tranquility module (Node-3). Dragon CRS-8 undocked on 11 May 2016 and re-entered the same day. It carried 1570 kg of cargo on this return flight. This cargo included a faulty space suit as well as the Flock 2b-11 and -12 satellites that failed deployment on 7 October 2015. The spacecraft was successfully recovered in the Pacific Ocean. The first stage of the launch vehicle was successfully recovered.

2016 025A (41456) Name: Sentinel -1B Int. Agency: ESA Launch date: 25 April 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT Orbit: 695 x 700 km, inclination: 98.2o Earth observation satellite as described for 2014 016A.

2016 025B (41457) Name: MicroSCOPE Country: France Launch date: 25 April 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT Orbit: 712 x 724 km, inclination: 98.2o

The Micro-Satellite à traînée Compensée pour l'Observation du Principe d'Equivalence (MicroSCOPE) was a gravity-research satellite to conduct a fundamental physics experiment relating to the general theory of relativity and in particular the Weak Equivalence Principle (WEP). The .. kg satellite was fitted with: 1. the Twin-Space Accelerometer for Gravity Experiment (T-SAGE), a differential accelerometer consisting

of a set of two cylindrical concentric electrostatic differential accelerometers; 2. the Drag-Free Attitude Control System (DFACS), the attitude actuator and measurement system to

provide accurate measurements of the spacecraft accelerations in 6-DoF (Six Degrees of Freedom).; and 3. the Cold Gas Propulsion System (CGPS), two identical and independent subsystems of

microthrusters.Microscope - Small CNES science satellite to prove Einstein's equivalence principle to a greater degree of precision than other measurements to date.

2016 025C (41458) Name: OUFTI-1 Country: Belgium Launch date: 25 April 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT Orbit: 442 x 687 km, inclination: 98.2o

The Orbital Utility For Telecommunications/Technology Innovations (OUFTI)-1 was a 1U cubesat developed by students at the Université de Liège in Belgium. The 1 kg satellite tested the use of the D-STAR communication protocol in space. It also carried an innovative electrical power system provided by Thales Alenia. The satellite was originally to be flown on the Vega launch of 13 February 2012 but was not completed in time.

2016 025D (41459) Name: e-St@r-2 Country: Italy Launch date: 25 April 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT Orbit: 442 x 687 km, inclination: 98.2o The Educational SaTellite @ politecnico di toRino (e-st@r)-2, developed at the Universitu di Torino, Italy, was a re-flight of e-st@ar-1 (2012 006C) to demonstrate an attitude control system using measurements of Earth’s magnetic field.

2016 025E (41460) Name: AAUSat-4 Country: Denmark Launch date: 25 April 20126 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT Orbit: 442 x 687 km, inclination: 98.2o

AAUSat-4 tested a student built AIS (Automated Identification System) receiver. It was developed at the University of Aalborg, Denmark.

2016 026A (41464) Name: MVL-300 Country: Russia Launch date: 28 April 2016 Re-entry: in orbit Launch site: Vostochny Launch vehicle: Soyuz 2.1a/Volga Orbit: 472 x 487 km, inclination 97.3o

The Mikhail Vasilyevich Lomonosov (MVL)-300 satellite has been developed by the M. V. Lomonosov Moscow State University and was named to honour the 300th birthday of the Russian scientist with the same name. The satellite used a surplus platform of the Kanopus V programme and was equipped for the observation of ultra-high energy cosmic rays and studies of transient phenomena in the Earth's upper atmosphere. The instruments were:

1. The Tracking Ultraviolet Set Up (TUS) orbital telescope to observe UV radiation bursts in the night atmosphere of the Earth;

2. BDRG, an instrument for monitoring and locating of gamma-sources at the celestial vault within the gamma-range;

3. UFFO, an instrument for the study of gamma-bursts with a 20-cm UV-optic telescope and X-ray camera;

4. Dosimeter of Electrons, PROtons and Neutrons (DEPRON) for the measurements of the absorbed doses and linear energy transfer spectra from high-energy electrons, protons and nuclei of space radiation, and for detecting of thermal and slow neutrons flux;

5. ShOK an instrument consisting of two stationary fast wide-angle cameras; 6. The Electron Loss and Fields Investigator for Lomonosov (ELFIN-L) consisting of a Flux Gate

Magnetometer (FGM), an Energetic Particle Detector for Electrons (EPDE), and an Energetic Proton Detector for Ions (EPDI); and

7. IMISS-1, an instrument to test the performance quality of microelectromechanical inertial measuring modules in space.

A launch by a Dnepr launch vehicle, was originally planned for November 2011 to mark the 300th birthday anniversary of the Russian scientist.

2016 026B (41465) Name: Aist-2D Country: Russia Launch date: 28 April 2016 Re-entry: in orbit Launch site: Vostochny Launch vehicle: Soyuz 2.1a/Volga Orbit: 471 x 486 km, inclination: 97.3o

Aist-2D was a 531 kg technology satellite developed by TsSKB Progress in partnership with Samara State Aerospace University, to demonstrate a new small spacecraft design. It was fitted with a high-resolution hyperspectral imaging camera and an innovative radar operating in P-band. In addition there were instruments that monitor the performance of the satellite itself.

2016 026C (41466) Name: SamSat 218 Country: Russia Launch date: 28 April 2016 Re-entry: in orbit Launch site: Vostochny Launch vehicle: Soyuz 2.1a/Volga Orbit: 471 x 486 km, inclination: 97.3o

SamSat 218 was a 3U cubesat designed and built by students at Samara State Aerospace as an educational and technology demonstration. One of the cubes was added for aerodynamic stability and was empty.

2016 027A (41469) Name: IRNSS-1G Country: India Launch date: 28 April 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 028A (41471) Name: JC Sat-14 Country: Japan Launch date: 6 May 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Falcon 9 v.1.2


Communications satellite owned by SKY Perfect JSAT and built by Space Systems/Loral (SSL) using the LS-1300 platform. The 4700 kg satellite was fitted with 26 C band transponders and 18 Ku band transponders. The first stage of the launch vehicle was recovered. Operationally it was known as JC Sat-2B.

2016 029A (41473) Name: YW-30 Country: China Launch date: 15 May 2016 Re-entry: in orbit Launch site: Jiuquan Launch vehicle: CZ 2D

Orbit: 628 x 656 km, inclination: 97.9° Earth observation satellite as described for 2006 015A. The satellite was fitted with electro-optical equipment and was also known as Jian Bing 6-6.

--- Name: RLV-TD-1 Country: India Launch date: 23 May 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: Rohini Orbit: sub-orbital 65 km

The RLV-TD-1, was a scaled-down prototype of a future uncrewed single-stage reusable spaceplane, known as Avatar, and on this flight evaluated various technologies needed in the development of Avatar. In particular the test concentrated on powered cruise flight, autonomous landing and hypersonic flight using an air-breathing propulsion system and was also been identified as the Hypersonic flight Experiment (HEX). The 6.5 m long RLV-TD had a mass of around 1750 kg and was a delta-wing design with a pair of angled tail fins. Around 600 thermal protection tiles were fixed to the underside of the vehicle and its nose featured a carbon-carbon cap to withstand temperatures of 1,200°C occurring at re-entry. At an altitude of 56 km the vehicle separated from the launch vehicle and coasted to an altitude of 65 km before descending in a glide path towards a spot in the Bay of Bengal, 450 km east of the launch site. The flight lasted 12 minutes, 50 seconds.

2016 030A (41549) Name: Galileo FOC-7 Int. Agency: ESA Launch date: 24 May 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT

Orbit: 23563 x 23609 km, inclination: 57.4° Navigational satellites as described for 2014 050A. Galileo FOC-7 was also named Antonianna and has also been referred to as Galileo FM-10 and GSat-0207.

2016 030B (41550) Name: Galileo FOC-10 Int. Agency: ESA Launch date: 24 May 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Soyuz 2-1b/Fregat MT

Orbit: 23569 x 23698 km, inclination: 57.4° Navigational satellites as described for 2014 050A. Galileo FOC-10 was also named Daniele and has also been referred to as Galileo FM-11 and GSat-0210.

2016 031A (41552) Name: Thaicom-8 Country: Thailand Launch date: 27 May 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Falcon 9 v.1.2 Orbit: geostationary at 78oE

Communications satellite built by Orbital ATK using the GeoStar-2 platform. The 3100 kg satellite was be fitted with 24 Ku band transponders. The first sage of the kaunch vehicle was recovered.

2016 032A (41554) Name: Komos-2516 Country: Russia Launch date: 29 May 2016 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Soyuz 2-1b/Fregat M

Orbit: 19127 x 19152 km, inclination: 64.8° Glonass M navigational satellite as described for 2001 053A.

2016 033A (41556) Name: Zi Yuan 3-2 Country: China Launch date: 30 May 2016 Re-entry: in orbit Launch site: Taiyuan Launch vehicle: CZ 4B

Orbit: 484 x 500 km, inclination: 97.5° Earth resources satellite as described for 2012 001A.

2016 033B (41557) Name: NuSat-1 Country: Argentina Launch date: 30 May 2016 Re-entry: in orbit Launch site: Taiyuan Launch vehicle: CZ 4B


Earth observation satellite which was part of Satellogic S.A.’s Aleph-1 Earth Observation Constellation consisting of 25 Aleph-1 satellites. The satellites had a mass of 37 kg and carried an imaging system operating in the visible and near infrared spectrum, generating still imagery and video of Earth at a ground resolution of up to one meter. In addition NuSat-1 carried the Lusex radio amateur payload. NuSat-1 was also known as Fresco.

2016 033C (41558) Name: NuSat-2 Country: Argentina Launch date: 30 May 2016 Re-entry: in orbit Launch site: Taiyuan Launch vehicle: CZ 4B

Orbit: 482 x 499 km, inclination: 97.5° Earth observation satellite as described for 2016 033B. NuSat-2 was also known as Batata.

2016 034A (41579) Name: GEO IK 2-1 Country: Russia Launch date: 4 June 2016 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Rokot Briz KM

Orbit: 936 x 962 km, inclination: 99.3° Geodesy satellite as described for 2011 005A. It was also known as Kosmos-2517.

2016 035A (41581) Name: Intelsat-31 Int. Agency: Intelsat Launch date: 9 June 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton M/Briz M


Communications satellite owned by Intelsat and built by Space Systems/Loral using the LS 1300 latform. The 6450 kg satellite was fitted with 4 C band and 72 Ku band transponders and was also known as DLA-2.

2016 036A (41584) Name: Orion-7 Country: USA Launch date: 11 June 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 4 Heavy Orbit: geostationary at 102.6oE Military electronic intelligence gathering satellite as described for 1995 022A. Also known as NROL-37 and USA-268. It was observed in a geostationary rbit by amateurs.

2016 037A (41586) Name: Beidou 2-G7 Country: China Launch date: 12 June 2016 Re-entry: in orbit Launch site: Xichang Launch vehicle: CZ 3C

Orbit: geostationary at 144°E Navigational satellite in the Compass system as described for 2007 011A.

2016 038A (41588) Name: Eutelsat 117 West-B Int. Agency: Eutelsat Launch date: 15 June 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Falcon 9 v.1.2


Originally ordered as Satmex-9, Eutelsat 117 West-B was built by Boeing using a BSS-702SP platform. The 1963 kg satellite was fitted with 48 transponders in the Ku band. It also carried a hosted payload enabling the U.S. Federal Aviation Administration (FAA) to enhance aviation safety. The FAA payload was the first in a series of Wide-Area Augmentation System (WAAS) commercial space missions.

2016 038B (41589) Name: ABS-2A Country: Hong Kong Launch date: 15 June 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Falcon 9 v.1.2


Commuunications satellite owned by Asia Broadcast Satellite (ABS) and builot by Boeing using the BSS-702SP platform. The 2000 kg satellite was fitted with 48 Ku band transponders.

2016 039A (41591) Name: BRISat Country: Indonesia Launch date: 18 June 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 5ECA Orbit: geostationary at 150.5oE

BRISat was a communications satellite owned by Bank Rakyat Indonesia (BRI) to link thousands of bank branches scattered over Indonesia’s islands. The 3540 kg satellite was built by Space Systems/Loral using the LS-1300 platform and was fitted with 36 C and 9 Ku-band transponders.

2016 039B (41592) Name: Echostar-18 Country: USA Launch date: 18 June 2016 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 5ECA Orbit: geostationary at 110oW

Communications satellite owned DISH Network. He 6300 kg Echostar-18 satellite was based on the Space Systems/Loral LS-1300 satellite platform and was fitted with 78 Ku band transponders.

--- Name: New Shepard Test-5 Country: USA Launch date: 19 June 2016 Re-entry: 19 June 2016 Launch site: Van Horn Launch vehicle: New Shepard Orbit: sub-orbital to 101 km Launch test of the New Shepard commercial crewed spacecraft as described as a cancelled project but in its role as a sub-orbital vehicle. The dummy Crew Capsule successfully separated from the Propulsion Module and descended back to Earth by parachute after a flight of 8 minutes.

2016 040A (41599) Name: Cartosat-2C Country: India Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 501 x 509 km, inclination: 97.5° Cartographic satellite as described for 2007 001B.

2016 040B (41600) Name: SathyabamaSat Country: India Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


SathyabamaSat (SB Sat) was a 1.5 kg 2U cubesat built at the Sathyabama Universit in India. The satellite measured the densities of the greenhouse gases over the region over which it moved, using an ARGUS 1000 IR Spectrometer.

2016 040C (41601) Name: SkySat-3 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 500 x 515 km, inclination: 97.5° SkySat-3 was the first operational satellite in Terra Bella’s (formerly Skybox Imaging) constellation of 21 Earth observation satellites, and followed two prototype satellites launched as SkySat-1 (2013 066C) and SkySat-2 (2014 037D). The 120 kg satellite was fitted with a Ritchey-Chretien Cassegrain telescope with a focal length of 3.6 m, and a focal plane consisting of three 5.5 Mpixel CMOS imaging detectors. The satellite was built by SS/Loral using a Skybox-licensed design that incorporates a modular propulsion system.

2016 040D (41602) Name: GHGSat-D Country: Canada Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


The Greenhouse Gas Satellite – Demonstrator (GHGSat-D) satellite, nicknamed Claire, was a 15 kg satellite to demonstrate an advanced miniature hyperspectral SWIR imaging spectrometer for monitoring targeted greenhouse gas emitters. It also carried an instrument to measure clouds and aerosols. The satellite was built by UTIAS Space Flight Laboratory (SFL).

2016 040E (41603) Name: LAPAN A-3 Country: Indonesia Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


The Lembaga Penerbangan dan Antariksa Nasional (LAPAN) A-3 was a 115 kg Earth observation satellite developed in Indonesia. The payload consisted of a Video camera (PAL RGB) for 80 km width coverage and a 3 band multi-spectral imaging camera with a ground resolution of 24 m and 154 km swath width. It also carried the Attitute Determination Instrument (AID) star tracker, an Automatic Identification System (AIS) payload to monitor maritime shipping and a radio amateur transponder.

2016 040F (41604) Name: BIROS Country: Germany Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


The Berlin InfraRed Optical System (BIROS) was a German fire detection satellite based on the TET-X platform. It operated alongside TET-1 (2012 039D) The 130 kg satellite was fitted with: 1. the Firebird payload, an imaging instrument consisting of three pushbroom cameras, one in the VNIR

(Visible Near Infrared) range and two imagers in the infrared region. The objective of this payload was to detect and analyse high temperature events like wildfires and volcanoes;

2. the Optical Space Infrared Downlink System (OSIRIS) to demonstrate three different laser systems for downlink communications and a four quadrant laser detector onboard for improved pointing accuracy and a beacon laser in uplink to support attitude control;

3. the Autonomous Vision Approach Navigation and Target Identification (AVANTI), an optical navigation experiment to demonstrate autonomous rendez-vous operation with a target, in this case BeeSat-4 that was to be deployed from BIROS using a spring mechanism. Deployment was to take place after the successful check-out and commissioning of all relevant BIROS subsystems;

4. the Verification of Autonomous Mission Planning On-board a Spacecraft (VAMOS) software experiment with the objective to schedule and re-command tasks.

BeeSat-4 was a cubesat developed at the TU Berlin. The 1 kg satellite was to be deployed from BIROS (2016 040F) after about six weeks using a spring mechanism and was used in the Autonomous Vision Approach Navigation and Target Identification (AVANTI) optical navigation experiment to demonstrate autonomous rendez-vous operation, with BeeSat-4 serbing as the target.

2016 040G (41605) Name: M3M Country: Canada Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


The Maritime Monitoring and Messaging Micro-satellite (M3M) was a technology satellite built by the Canadian Com Dev company for the Canadian government. The 85 kg satellite the Advanced Integrated Microsatellite (AMS) platform and the payload consisted of: 1. Automatic Identification System - Payload Electronics Module (AIS-PEM), to receive the AIS signals

transmitted by ships; 2. Low Data Rate System - Payload Electronics Module (LDRS-PEM), a transponder to demonstrate two-

way communications at a low data rate system to support a range of services; and 3. Dielectric Deep Charge Monitor (DDCM), a technology demonstration to monitor the electrical potential

of a dielectric sample due to charging by the space environment. It was originally to be placed in orbit by the Russian Soyuz-2-1b/Fregat-M that was launched on 8 July 2014 but deployment was cancelled due to the crisis in the Ukraine. After that it was rescheduled for the PSLV XL launch of 28 September 2015 but that was delayed.

2016 040H (41606) Name: Flock 2p-6 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 500 x 515 km, inclination: 97.5° Earth observation satellite as described for 1998 067DG and also known as Dove 0E19. The satellite was released from a CubeSat Deployer System.

2016 040J (41607) Name: Swayam Country: India Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


Swayam was an 1U cubesat developed at the College of Engineering, Pune (COEP), India. Essentially an educational project for students, it was fitted with a pair of hysteresis rods and a magnet to stabilize the satellite. It also carried a communications payload operating in the radio amateur frequencies.

2016 040K (41608) Name: Flock 2p-11 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 040L (41609) Name: Flock 2p-2 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 500 x 515 km, inclination: 97.5° Earth observation satellite as described for 1998 067DG and also known as Dove 0E0E. The satellite was released from a CubeSat Deployer System.

2016 040M (41610) Name: Flock 2p-9 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 040N (41611) Name: Flock 2p-4 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 040P (41612) Name: Flock 2p-10 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 500 x 514 km, inclination: 97.5° Earth observation satellite as described for 1998 067DG and also known as Dove 0E2F. The satellite was released from a CubeSat Deployer System.

2016 040Q (41613) Name: Flock 2p-8 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 040R (41614) Name: Flock 2p-12 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 500 x 514 km, inclination: 97.5° Earth observation satellite as described for 1998 067DG and also known as Dove 0E3A. The satellite was released from a CubeSat Deployer System.

2016 040S (41615) Name: Flock 2p-7 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 040T (41616) Name: Flock 2p-5 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 040U (41617) Name: Flock 2p-1 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL

Orbit: 500 x 514 km, inclination: 97.5° Earth observation satellite as described for 1998 067DG and also known as Dove 0E0D. The satellite was released from a CubeSat Deployer System.

2016 040V (41618) Name: Flock 2p-3 Country: USA Launch date: 22 June 2016 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV XL


2016 041A (41622) Name: MUOS-5 Country: USA Launch date: 24 June 2016 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas V-511

Orbit: geostationary at ?° Military communications satellite as described for 2012 009A.

2016 042A (41624) Name: ZGZ Shiyan Zhuangzhi Country: China Launch date: 25 June 2016 Re-entry: in orbit Launch site: Wenchang Launch vehicle: CZ 7


The Zai Guijia Zhu (ZGZ) Shiyan Zhuangzhi was an in-orbit fluid-transfer experiment. It was mounted on the upper stage of the launch vehicle and remained attached.

2016 042C (41626) Name: Aoxiang Zhixing Country: China Launch date: 25 June 2016 Re-entry: in orbit Launch site: Wenchang Launch vehicle: CZ 7


Aoxiang Zhixing was a 12U scientific demonstration cubesat developed by the Shaanxi Engineering Laboratory for Microsatellites (SELM) of NPU. The mission of the 18 kg satellite was to detect polarized skylight and to measure gravity.

2016 042D (41627) Name: DFFC Country: China Launch date: 25 June 2016 Re-entry: in orbit Launch site: Wenchang Launch vehicle: CZ 7


First launch of the CZ 7 launch vehicle. The Duoyongtu Feichuan Fanhui Cang (DFFC) was a scaled-down version of a re-entry capsule to be used by China’s future crewed space vehicle identified as the Next Generation Crew Vehicle. The re-entry module was of a blunt cone shape with a docking port on its forward end and an ablator heat shield in the aft. On re-entry the spacecraft opened a Supersonic Stabilization Chute before deploying a Drogue Chute that slowed the craft down for the deployment of the lone Main Parachute to slow the capsule for touchdown in the Badain Jaran Desert on 26 June 2016, after a flight of 19 hours and 41 minutes.

2016 042F (41629) Name: Aolong-1 Country: China Launch date: 25 June 2016 Re-entry: in orbit Launch site: Wenchang Launch vehicle: CZ 7

Orbit: 200 x 378 km, inclination 40.8° Aolong-1 was an active space debris removal experiment.

2016 042L (41636) Name: Tiange Feixingqi -1 Country: China Launch date: 25 June 2016 Re-entry: in orbit Launch site: Wenchang Launch vehicle: CZ 7

Orbit: 277 x 287 km, inclination: 40.8° Tiange Feixingqi-1 was a small satellite to demonstrate intersatellite communication links with Tiange Feixingqi-2.

2016 042M (41637) Name: Tiange Feixingqi -2 Country: China Launch date: 25 June 2016 Re-entry: in orbit Launch site: Wenchang Launch vehicle: CZ 7

Orbit: 277 x 289 km, inclination: 40.8° Small satellite as described for Tiange Feixingqi-1 (2016 042L).

2016 043A (41634) Name: SJ-16-2 Country: China Launch date: 29 June 2016 Re-entry: in orbit Launch site: Jiuquan Launch vehicle: CZ 4B

Orbit: 596 x 619 km, inclination: 75.0° Shijian technology satellite as described for 2013 057A to test advanced technologies.

2016 044A (41639) Name: Soyuz MS-01 Country: Russia Launch date: 7 July 2016 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Soyuz FG


Crewed spaceflight with cosmonauts A. Ivanishin (Cmdr.), T. Onishi (Japan)(Fl.Eng.) and K. Rubins (USA)(Fl.Eng) using a spacecraft based on the Soyuz TMA as decribed for 2010 052A but wiith a TsVM-101 computer as well as the MBITS digital telemetry system, more power efficient solar panels, improved communications systems and modified docking and altitude control engines for increased fault tolerance during docking and deorbit burns. The mission was also known as ISS-47S and the call sign was Irkut. They were members of the forty eigth permanent crew (EX-49) and later the forty ninth permanent crew (EX-49) for ISS. The spacecraft docked at the Rassvet docking port of ISS (1998 067A) on 9 July 2016. It will remain attached until October 2016.

world spacecraft digest by jos heyman 2016 ... carried 12 c band transponders, 46 ku band...

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