world spacecraft digest by jos heyman 1996 version: 6 … · a satellite in the shuttle pointed...

WORLD SPACECRAFT DIGEST by Jos Heyman 1996 Version: 6 October 2015 © Copyright Jos Heyman

1996 001A (23762) Name: STS-72 Country: USA Launch date: 11 January 1996 Re-entry: 20 January 1996 Launch site: Cape Canaveral Launch vehicle: STS

Orbit: 185 x 470 km, inclination: 28.4°

Crewed spaceflight with astronauts B. Duffy (Cmdr.), B. Jett (Pilot), L. Chiao, W. Scott, D. Barry and K. Wakata (Japan), (all Mission Specialists) using the orbiter Endeavour as described for 1981 034A. The principal objective of the flight was to retrieve SFU (1995 011A) and deploy and retrieve Spartan-206 (1996 001B) as well as to conduct several EVAs, referred to as Extravehicular Development Flight Tests (EDFT)-3, to evaluate more than 20 tools and a variety of techniques (listed as DSOs and DTOs) that might be used in the assembly and maintenance of the International Space Station. The instruments involved in these EVAs were: 1. two Pre-Integration Truss Utility boxes, which were connected to simulate truss construction; 2. a Portable Rigid Umbilical Mount (PRUM), to move equipment around in the payload bay; 3. a Cable Caddy Assembly (CCA) a small carrier device planned to hold replacement electrical line for

the Space Station; 4. two Rigid Umbilicals (RU) which were installed diagonally across the payload bay; and 5. a Portable Work Platform (PWP), consisting of:

• the TERA (Temporary Equipment Restraining Aid), which attaches equipment to the robot arm using a Flight Releasable Grapple Fixture;

• the APFR (Articulating Portable Foot Restraint), which goes on the end of the robot arm and provides the astronaut with a place to stand; and

• the PFRWS (Portable Foot Restraint Workstation Stanchions) which attach to the APFR and provide handholds and tool holders for an astronaut working in the APFR.

Other experiments carried on board of the mission were: 1. the Shuttle Solar Backscatter Ultraviolet (SSBUV)-8 instrument as described for STS-34 (1989 084A); 2. the Shuttle Laser Altimeter (SLA), a laser remote sensing device to demonstrate surface lidar sensing

from Earth orbit; 3. the National Health Institutes Rodent (NIH R)-3 experiments as described for STS-66 (1994 073A)

which studied:

• the influence of gravity on spinal cord and muscle development of terrestrial mammals, including humans;

• the use of behavioral measures as a tool in examining the influence of the environment on the postnatal development of specific and critical brain/body systems;

4. the National Health Industries Collaborative (NIH C)-5 experiment as described for STS-59 (1994 020A) using the Space Tissue Loss (STL) facility as described for STS-45 (1992 015A);

5. the Protein Crystal Growth (PCG)-17 experiment as described for STS-51D (1985 028A); 6. the Thermal Energy Storage (TES)-2 experiment as described for STS-62 (1994 015A); 7. the Commercial Protein Crystal Growth (CPCG)-11 experiment as described for STS-49 (1988

109B); 8. three Getaway specials as described for STS-3 (1982 022A):

• G342: the S93-6 flexibeam experiment;

• G459: a protein crystal growth experiment;

• G740: the Pool Boiling Experiment as described for STS-57 (1993 037A); 9. Developmental Test Objective (DTO) experiments as described for STS-1 (1981 034A):

• DTO-301D: Ascent Structural Capability Evaluation;

• DTO-305D: Ascent Compartment Venting Evaluation;

• DTO-306D: Descent Compartment Venting Evaluation;

• DTO-307D: Entry Structural Capability Evaluation;

• DTO-312: External Tank Thermal Protection System Performance;

• DTO-414: Auxiliary Power Unit Shutdown Test;

• DTO-415: Water Spray Boiler Electrical Heater Capability;

• DTO-664: Cabin Temperature Survey;

• DTO-667: Portable In-Flight Landing Operations Trainer;

• DTO-668: Advanced Lower Body Restraint Test;

• DTO-671: EVA Hardware for Future Scheduled EVA Missions;

• DTO-672: EVA Maneuvering Unit Electronic Cuff Checklist;

• DTO-700-5: Trajectory Control Sensor;

• DTO-700-8: Global Positioning System Development Flight Test;

• DTO-805: Crosswind Landing Performance;

• DTO-833: EMU Thermal Comfort and EVA Worksite Thermal Evaluation;

• DTO-1210: EVA Operations Procedure/Trainer; 10. Detailed Supplementary Objective (DSO) experiments as described for STS-1 (1981 034A):

• DSO-330: In-Flight Evaluation of Urine Monitoring System;

• DSO-483: Back Pain Pattern in Microgravity;

• DSO-487: Immunological Assessment of Crewmembers;

• DSO-489: EVA Dosimetry Evaluation;

• DSO-491: Characterization of Microbial Transfer Among Crewmembers During Flight;

• DSO-492: In-Flight Evaluation of a Portable Clinical Blood Analyzer;

• DSO-493: Monitoring Latent Virus Reactivation and Shedding in Astronauts;

• DSO-494: Influence of Microgravity and EVA on Pulmonary Oxygen Exchange;

• DSO-603: Orthostatic Function During Entry, Landing and Egress;

• DSO-604: Visual-Vestibular Integration as a Function of Adaptation;

• DSO-626: Cardiovascular and Cerebrovascular Responses to Standing Before and After Space Flight;

• DSO-802: Educational Activities;

• DSO-901: Documentary Television;

• DSO-902: Documentary Motion Picture Photography; and

• DSO-903: Documentary Still Photography. On 13 January 1996 the orbiter retrieved SFU with the RMS and it was placed in the payload bay, following which, on 14 January 1996, Spartan-206 was deployed. On 14 January 1996 Chiao and Barry made an EVA of 6 hours, 9 minutes whilst Chiao and Scott made an EVA of 6 hours, 53 minutes on 17 January 1996. On 16 January 1996 Spartan-206 was retrieved. The orbiter landed at the Kennedy Space Centre after a flight of 8 days, 22 hours, 1 minute.

1996 001B (23763) Name: Spartan-206 Country: USA Launch date: 14 January 1996 Re-entry: 16 January 1996 Launch site: Cape Canaveral Launch vehicle: STS + RMS


A satellite in the Shuttle Pointed Autonomous Research Tool of Astronomy (Spartan) programme as described for 1985 048E. Spartan-206 was a 1198 kg experiment platform sponsored by the Office of Aeronautics and Space Technology and was also referred to as OAST. It was released from and retrieved by STS-72 (1996 001A). The experiments that were carried were: 1. the Return Flux Experiment (REFLEX); 2. the Global Positioning System Attitude Determination and Control (GADACS) experiment; 3. the Solar Exposure to Laser Ordinance Device Experiment (SELODE); and 4. the Spartan Packet Radio Experiment (SPRE), an amateur radio communications experiment

operating in the 14 MHz band to test satellite tracking using amateur radio and GPS. The spacecraft was deployed from the payload bay on 14 January 1996 and was retrieved on 16 January 1996.

1996 002A (23764) Name: Panamsat-3R Country: USA Launch date: 12 January 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L

Orbit: geostationary at 43°W Communications satellite owned by Pan American Satellite and based on the Hughes HS-601 platform. The satellite, which had a mass of 1291 kg, carried 12 transponders in the C band and 12 transponders in the Ku band. On 1 February 2007 the satellite was renamed as Intelsat-3R.

1996 002B (23765) Name: Measat-1 Country: Malaysia Launch date: 12 January 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L

Orbit: geostationary at 91°E

Communications satellite owned by Binariang Malaysia. The Malaysian/East Asian Satellite (Measat) used a Hughes HS-376 platform fitted with 4 transponders in the Ku band and 12 transponders in the C band. The satellite had a mass of 626 kg. In January 2008 the satellite was relocated to 46oE and was renamed as Africasat-1. This did not involve a change in ownership.

1996 003A (23768) Name: Mugunghwa-2 Country: South Korea Launch date: 14 January 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 7925

Orbit: geostationary at 116°E Communications satellite as described for 1995 041A. In 2009 the satellite was sold to Asia Broadcast Satellite as ABS-1A and was relocated to 75oE. In January 2015 it was relocated at 67oE.

1996 004A (23773) Name: Kosmos-2327 Country: Russia Launch date: 16 January 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 974 x 1034 km, inclination: 83.0° Parus military navigational satellite as described for 1974 105A.

1996 005A (23775) Name: Gorizont-31 Country: Russia Launch date: 25 January 1996 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton K/DM-2

Orbit: geostationary at 40°E Communications satellite as described for 1978 118A. The satellite was leased to Rimsat.

1996 006A (23779) Name: Palapa-8 Country: Indonesia Launch date: 1 February 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas IIAS


Third generation of communications satellite for Indonesia which was also referred to as Palapa C-1. The 2989 kg satellite was based on the Hughes HS-601 platform and carried 30 transponders in the C band and 4 transponders in the Ku band. A failure in the electrical system prevented the eclipse period power back-up from operating and the satellite was acquired by Hughes Global Services as HGS-3. A procedure was developed to maintain full operations except during eclipse itself and brief periods on either side of each eclipse event. This meant that for 88 days of the year the satellite had to be switched off for three hours per day on average, providing 96% service availability. The satellite was later sold as Anatolia-1. In December 2002 the satellite was sold to Pakistan and moved to 38oE, from where it began to operate as Paksat-1.

1996 007A (23781) Name: N Star-b Country: Japan Launch date: 5 February 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44P

Orbit: geostationary at 136°E Communications satellite as described for 1995 044A.

--- Name: Hyflex Country: Japan Launch date: 12 February 1996 Re-entry: n.a. Launch site: Tanegashima Launch vehicle: J-1 Orbit: sub-orbital to 110 km

The Hypersonic Flight Experiment (Hyflex) was a 1050 kg lifting body vehicle which was to test the re-entry technology for the proposed Hope spaceplane that was eventually cancelled. As was intended, it reached an altitude of 110 km from where it made a glide back into the atmosphere. The craft's parachutes deployed successfully but the craft broke away from its retaining harness and dropped into the sea app. 250 km north east of Ogosawana Island.

--- Name: Intelsat-708 Int. Agency: Intelsat Launch date: 14 February 1996 Re-entry: n.a. Launch site: Xichang Launch vehicle: CZ 3B Orbit: failed to orbit Communications satellite as described for 1993 066A. The satellite was to be placed at 50oW but failed to achieve orbit due to a failure of the launch vehicle.

1996 008A (23784) Name: NEAR Country: USA Launch date: 17 February 1996 Re-entry: 12 February 2001 Launch site: Cape Canaveral Launch vehicle: Delta 7925 Orbit: 1.0 x 2.5 AU

The Near Asteroid Rendez Vous (NEAR) mission was the first mission of the Discovery program that was begun by NASA in the early 1990s as the planetary counterpart to the Explorer missions. NEAR was placed in orbit around the asteroid Eros on 14 February 2000 for a one year observation programme of the asteroid. On its way to the asteroid it first encountered the asteroid Mathilde on 27 June 1997 and at a distance of 1200 km. NEAR then used a gravity assist from Earth on 23 January 1998 to fly towards Eros. A malfunctioning attitude control burn on 20 December 1998, prevented the spacecraft to be placed from being placed in orbit around the asteroid on 10 January 1999. Instead the spacecraft flew past the asteroid at a distance of 4100 km, returning some 1100 images of the asteroid. A corrective burn was made on 3 January 1999 following which the spacecraft was allowed to orbit the Sun until the 14 February 2000 encounter. Its intial orbit was 320 x 480 km. Early April 2000 the orbit was lowered to 100 km circular and in July 2000 to a 35 x 19 km orbit. The intended operational orbit around the 40 x 15 x 15 km asteroid was a mere 16 km altitude, depending on the shape and dynamics of the asteroid. The lowest altitude, of 5.3 km, was achieved on 26 October 2000. After a close approach of 2.74 km on 28 January 2001, the spacecraft was sent on a controlled descent onto the surface on 12 February 2001 and succesfully landed. The spacecraft continued to transmit data until 28 February 2001 when it was switched off as the asteroid went into a long period of darkness which the instruments were not expected to survive. The instruments on the 805 kg spacecraft included: 1. an X-ray and gamma ray spectrometer; 2. a magnetometer; 3. a multi-spectral imager to produce pictures of the asteroid; 4. a near-infrared spectrograph to map the surface of the asteroid; and 5. a laser altimeter with an accuracy of 5 m for topographical purposes. In 2000 the spacecraft was renamed Shoemaker.

1996 009A (23787) Name: Gonets D-1 Country: Russia Launch date: 19 February 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Tsyklon 3


The Gonets D message relay communications satellites used a store-and-forward mode and were based on the 'sextet' military communications satellite as described for 1985 003A. Their primary application was during natural and man-made disasters and emergencies. The operational Gonets system consisted of twelve satellites in four orbital planes each operating in the 200/400 MHz band. The satellites were built by Prikladnoi Mekhaniki. No announcement has been made as to the order of the satellites of this launch and the assignment is arbitrary.

1996 009B (23788) Name: Gonets D-2 Country: Russia Launch date: 19 February 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Tsyklon 3

Orbit: 1407 x 1414 km, inclination: 82.6° Message relay communications satellite as described for 1996 009A.

1996 009C (23789) Name: Gonets D-3 Country: Russia Launch date: 19 February 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Tsyklon 3

Orbit: 1410 x 1417 km, inclination: 82.6° Message relay communications satellite as described for 1996 009A.

1996 009D (23790) Name: Kosmos-2328 Country: Russia Launch date: 19 February 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Tsyklon 3

Orbit: 1411 x 1415 km, inclination: 82.6° Strela 3 military communications satellite as described for 1985 003A.

1996 009E (23791) Name: Kosmos-2329 Country: Russia Launch date: 19 February 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Tsyklon 3


1996 009F (23792) Name: Kosmos-2330 Country: Russia Launch date: 19 February 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Tsyklon 3


1996 010A (23794) Name: Raduga-33 Country: Russia Launch date: 19 February 1996 Re-entry: 6 May 2004 Launch site: Baikonour Launch vehicle: Proton K/DM-2

Orbit: 242 x 36502 km, inclination: 48.6° Communications satellite as described for 1975 123A. The fourth stage of the launch vehicle exploded just before the satellite separated.

1996 011A (23798) Name: Soyuz TM-23 Country: Russia Launch date: 21 February 1996 Re-entry: 2 September 1996 Launch site: Baikonour Launch vehicle: Soyuz U

Orbit: 202 x 240 km, inclination: 51.6° Crewed spaceflight with cosmonauts Y. Onufriyenko (Cmdr.) and Y. Usachov (Fl. Eng.) using a Soyuz TM spacecraft as described for 1986 035A. Their call sign was Skif and they were the twenty first permanent (EO-21) crew of the space station. On 23 March 1996 the third member of the crew, astronaut S. Lucid, arrived at the space station by STS-76 (1996 018A). On 23 February 1996 Soyuz TM-23 docked with the rear port of the Mir/Kvant-1 (1986 017A) space station. On 15 March 1996 Onufriyenko and Usachov conducted an EVA of 5 hours, 52 minutes to install a second Strela crane on the outside of the space station. On 20 May 1996 they made an EVA of 5 hours, 20 minutes to install a Lockheed Martin built solar panel as well as to inflate a large Pepsi Cola can which was filmed for a commercial. On 24 May 1996 they made a further EVA of 5 hours, 43 minutes to complete the solar panel installation. The solar panel was delivered to the space station on board of the STS-74 (1995 061A) and delivered 6 kW of power. It had a surface area of 42m2. On 30 May 1996 Onufriyenko and Usachov spent 4 hours, 20 minutes outside the spacecraft to place the Modular Optoelectrical Multi-spectral Scanner (MOM-2P) on the outside of the Priroda module (1996 023A). The EVA of 6 June 1996 was used to replace several experiments on the outside of the space station. It lasted 3 hours, 34 minutes. This was followed by an EVA on 13 June 1996 of 5 hours, 42 minutes during which the cosmonauts completed construction and repair works, including the erection of the Ferma-3 truss and the deployment of a large antenna for the Priroda's Travers imaging radar. On 2 September 1996 the spacecraft undocked and landed 100 km south-west of Akmola. Onufriyenko and Usachov had been in space for 193 days, 19 hours, 7 minutes. The flight also returned French Andre-Deshays who had arrived on the space station on Soyuz TM-24 (1996 047A). Lucid became a member of the EO-22 crew.

1996 012A (23801) Name: STS-75 Country: USA Launch date: 22 February 1996 Re-entry: 9 March 1996 Launch site: Cape Canaveral Launch vehicle: STS


USMP

Crewed spaceflight with astronauts A. Allen (Cmdr.), S. Horowitz (Pilot), F. Chang-Diaz (Payload Cmdr.), J. Hoffman, C. Nicollier (ESA), M. Cheli (ESA) (all Mission Specialists) and U. Guidoni (Italy) (Payload Specialist), using the orbiter Columbia as described for 1981 034A. The principal objective of the mission was to fly the third United States Microgravity Payload (USMP) as described for 1994 015A, which undertook four major experiments in the microgravity environment of the payload bay: 1. the Commercial Protein Crystal Growth (CPCG)-12 experiment as described for STS-49 (1988

109B); 2. the MEPHISTO experiment as described for STS-52 (1992 070A); 3. the Isothermal Dendritic Growth Experiment (IDGE) as described for STS-62 (1994 015A); and 4. the Advanced Automated Directional Solidification Furnace (AADSF) experiment as described for

STS-62 (1994 015A). Three combustion experiments were placed in the Middeck Glove Box Facility: 1. the Radioactive Ignition and Transition to Spread Investigation (RITSI), which studied radiative

ignition and the transition to flame spread in the presence of low-gravity and very low-speed air flows; 2. the Comparative Soot Diagnostics (CSD) experiment to study the changes in particle properties as

gravity effects decrease from microgravity to anogravity levels; 3. the Forced Flow Flame Spreading Test (FFFT), to study the influence of bulk fuel temperature and

low-speed flow velocity on the combustion characteristics of solid fuel in microgravity. Also in the cabin were: 1. the Orbiter Acceleration Research Experiment (OARE)-6 as described for STS-40 (1991 040A); 2. the Space Acceleration Measurement System (SAMS)-14 as described for STS-40 (1991 040A); 3. the Critical Fluid Light Scattering Experiment (CFLSE) or Zeno experiment as described for STS-62

(1994 015A); 4. Developmental Test Objective (DTO) experiments as described for STS-1 (1981 034A):






5. Detailed Supplementary Objective (DSO) experiments as described for STS-1 (1981 034A):

• DSO-331: Interaction of Shuttle Launch Entry Suits on Egress Locomotion;



• DSO-492: In-Flight Evaluation of a Portable Clinical Blood Analyzer;






• DSO-903: Documentary Still Photography. In addition the mission was to deploy the second Tethered Satellite System (TSS), an Italian built payload which was released from the payload bay on a 20 km tether. Deployment began on 25 February 1996 and after 4 hours, 45 minutes the tether broke and the payload was accidentally launched into orbit, becoming 1996 012B. The orbiter landed at the Kennedy Space Centre after a flight of 15 days, 17 hours, 40 minutes.

1996 012B (23805) Name: TSS-1R Country: Italy Launch date: 26 February 1996 Re-entry: 20 March 1996 Launch site: Cape Canaveral Launch vehicle: STS


TSS-1R was the same satellite which was partially released on STS-46 (1992 049A) and was not intended to be deployed as a free flying satellite. The 20.7 km tether line was to be deployed from STS-75 (1996 012A) in such a way that the satellite would fly above the orbiter for a period of 22 hours to study the electrodynamic effects of a tether moving through the upper atmosphere. The deployment commenced on 25 February 1996 but after 4 hours, 45 minutes, and after unreeling 19.7 km, during which 3500 volts were generated, the cable broke inside the boom and TSS-1R became an independent satellite on 26 February 1996 with a mass of 18 kg (the entire assembly, incl. the support structure in the payload bay was 5506 kg). The cause of the break was later traced to imperfect insulation which allowed an electrical arc to burn through the cable. Although the break occurred at an altitude of 295 km, the force of the break itself caused the satellite to be 'shot' into the cited elliptical orbit. The investigations to be conducted by TSS-1R were: 1. TSS Deployer Core Equipment and Satellite Core Equipment which measured and controlled the

electric current flowing through the cable; 2. Research on Orbital Plasma Electrodynamics, to understand the behaviour of charged particles in

the tether current production; 3. Research on Electrodynamic Tether Effects, to provide a profile of the electrical potential in the

plasma sheath and identify affected waves in the region around the satellite; 4. Magnetic Field Experiment, to map the magnetic fields around the satellite; 5. Shuttle Electrodynamic Tether System, to assess the ability of the tethered satellite to collect

electrons and to measure the resistance to current flow in the tether itself; 6. Shuttle Potential and Return Electron Experiment to measure the charged particle population around

the orbiter; 7. Tether Optical Phenomena Experiment, to collect visual data on the dynamics of the tether satellite

with a hand held camera; 8. Investigation of Electromagnetic Emissions For Electrodynamics Tether, to determine how

electromagnetic waves interact with trapped particles; 9. Observations of the Earth's Surface of Electromagnetic Transmissions, to investigate how well a

tether can be used to broadcast from space; 10. Investigation and Measurement of Dynamic Noise, to observe in real time the dynamics of the

tethered satellite;

11. Theoretical and Experimental Investigation of Dynamics, a further series of measurements to enhance the understanding of the dynamics of a tethered satellite; and

12. Theory and Modelling in Support of Tethered Satellite Application, to develop a range of models for future experimentation.

1996 013A (23802) Name: Polar Country: USA Launch date: 24 February 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta 7925


The Polar satellite, built by Astro Space and having a mass of 730 kg, studied plasma field physics. It carried eleven instruments to provide global multi-spectral images of the footprint of the magnetospheric energy deposition into the ionosphere and the upper atmosphere. These experiments were: 1. the Polar Plasma Wave Investigation (PWI), using the 130 m and 2100 m antennas of the spacecraft

to study electric and magnetic fields; 2. the Electric Field Instrument (EFI), using the same 130 m and 2100 m antennas for further studies of

electric and magnetic fields; 3. the Magnetic Field Experiment (MFI), using shorter antennas to investigate the magnetic fields; 4. the Toroidal Imaging Mass-Angle Spectrograph (TIMAS), to study ion fluxes; 5. the Thermal Ion Dynamics Experiment (TIDE), to investigate the connections between the polar

ionosphere and the magnetosphere; 6. the Plasma Source Instrument (PSI), to complement the TIDE investigations; 7. the Visible Imaging System (VIS), to image auroral emissions in visible light; 8. the Ultraviolet Imager (UVI), to image auroral emissions in ultraviolet; 9. the Polar Ionospheric X-Ray Imaging Equipment (PIXIE), to study X-rays produced by energetic

electrons in the upper atmosphere; 10. the Charge and Mass Magnetospheric Ion Composition Experiment (CAMMICE) to study the isotopic

composition of energetic ions; and 11. the Comprehensive Energetic Particle Pitch Angle Distribution (CEPPAD) instrument to study

high-energy electrons and protons.

1996 014A (23814) Name: REX-2 Country: USA Launch date: 9 March 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Pegasus XL

Orbit: 801 x 832 km, inclination: 89.9° The Radiation Experiment (REX)-2 satellite, which had a mass of 113 kg, carried experiments to study ionospheric density irregularities that affect radio communications. Also known as P94-2, the satellite carried the Rome Laboratory Communications Experiment and the GPS attitude determination and control experiment. The launch vehicle was released from the L-1011 carrier aircraft off the Californian coast.

1996 015A (23816) Name: Intelsat-707 Int. Agency: Intelsat Launch date: 14 March 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44LP

Orbit: geostationary at 1°W Communications satellite as described for 1993 066A.

1996 016A (23818) Name: Kosmos-2331 Country: Russia Launch date: 14 March 1996 Re-entry: 11 June 1996 Launch site: Plesetsk Launch vehicle: Soyuz U

Orbit: 184 x 350 km, inclination: 67.1° Yantar 4K2 military reconnaissance satellite as described for 1981 080A. The satellite also carried a US built BINRAD (S93-1) payload to detect the presence of beryllium at the orbital altitudes.

1996 017A (23827) Name: IRS P-3 Country: India Launch date: 21 March 1996 Re-entry: in orbit Launch site: Sriharikota Launch vehicle: PSLV


Earth observation satellite as described for 1988 021A. In addition it carried a Modular Opto-electronic Scanner operating in the visible near-infrared region for oceanographic applications, and a Wide Field Sensor (WiFS) as described for 1995 072A. Finally three Pointed Proportional Counters (PPC) and an X-ray Sky Monitor (XSM) were provided for astronomical observations.

1996 018A (23831) Name: STS-76 Country: USA Launch date: 22 March 1996 Re-entry: 31 March 1996 Launch site: Cape Canaveral Launch vehicle: STS


Crewed spaceflight with astronauts K. Chilton (Cmdr.), R. Searfoss (Pilot), R. Sega, M. Clifford, L. Godwin and S. Lucid (all Mission Specialists), using the orbiter Atlantis as described for 1981 034A. The primary objective of the mission was to dock with the Mir (1986 017A) space station to deliver 2330 kg of scientific equipment and supplies as well as astronaut Lucid. The Space Shuttle docked with the Shuttle Docking port of Mir on 23 March 1996. During their stay, the crew participated in various space medicine experiments such as those described for STS-71 (1995 030A). The orbiter carried a single Spacehab module (FU2) as described for 1993 037A, which contained: 1. Biorack as described for STS-61A (1985 104A) used to investigate the effect of cosmic radiation,

high-energy particles and microgravity on plant tissue, bacteria and insects through conducting eleven experiments;

2. the Life Sciences Laboratory Equipment Refrigerator/Freezer (LSLE) to store sample materials; 3. KidSat-1, the first in a series of student experiments consisting of a digital video system commanded

from classrooms and used to obtain real time images of Earth; 4. the Space Vision System (SVS) as described for STS-41G (1984 108A); 5. the Shuttle Amateur Radio Experiment (SAREX)-22 as described for STS-51F (1985 063A); 6. the Trapped Ions in Space (TRIS) experiment as described for STS-41G (1984 108A), which was

flown as the G312 Getaway Special and was probably also known as S85-2; 7. the Liquid Phase Sintering (LPS)-1 experiment which studied the formation of defects and voids in

sintering metal samples; 8. Developmental Test Objectives (DTO) experiments as described for STS-1 (1981 034A):




• DTO-648: Electronic Still Photography Test;



• DTO-700-10: Orbiter Space Vision System Flight Video Taping;

• DTO-700-13: Signal Attenuation Effects of ET During Ascent;


• DTO-1118: Photographic and Video Survey of Mir Space Station;

• DTO-1210: EVA Operations Procedure/Trainer; 9. Detailed Supplementary Objective (DSO) experiments as described for STS-1 (1981 034A):


• DSO-483: Back Pain Pattern in Microgravity;


• DSO-489: EVA Dosimetry Evaluation;



• DSO-902: Documentary Motion Picture Photography;

• DSO-903: Documentary Still Photography; 10. a number of Risk Mitigation Experiments (RME) as described for STS-74 (1995 061A):

• RME-1301: Mated Shuttle and Mir Structural Dynamics Test;

• RME-1302: Mir Electric Field Characterization (MEFC) Test 1 and 2 to collect data on the internal and external radio interference in the 400 MHz and 18 GHz bands

• RME-1304: Mir/Environmental Effects Payload (MEEP) to gather data on space debris;

• RME-1306: Mir Wireless Network Experiment;

• RME-1310: Shuttle/Mir Alignment Stability Experiment; and

• RME-1315: Trapped Ions in Space Experiment. During an EVA by Godwin and Clifford which took place on 27 March 1996 and lasted 6 hours, 3 minutes, the four MEEP panels were attached to the outside of the Mir space station. The panels, identified as Polished Plate Micrometeoroid Debris (PPMD), Orbital Debris Collector (ODC) and Passive Optical Sampler (POSA)-1 and -2, were recovered on STS-86 (1997 055A). During the EVA the astronauts also tested hardware for the International Space Station, such as tether hooks and foot restraints. When Atlantis undocked on 29 March 1996 and it left Lucid on the space station whilst it took also 560 kg of goods from Mir. Lucid returned on STS-79 (1996 057A). The planned landing at the Kennedy Space Centre was first delayed due to bad weather and eventually the orbiter was diverted to Edwards AFB for its landing, where it landed on 31 March 1996. The flight had lasted 9 days, 5 hours, 16 minutes.

1996 019A (23833) Name: Navstar 2A-16 Country: USA Launch date: 28 March 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 7925

Orbit: 20078 x 20282 km, inclination: 54.7° Navigational satellite as described for 1989 013A. Also known as USA-117, Navstar-33, Navstar-37 and SVN-33.

1996 020A (23839) Name: Inmarsat 3-1 Int. Agency: Inmarsat Launch date: 3 April 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas IIA.


Maritime communications satellite owned by Inmarsat and built by Astro Space using the AS4000 platform. The 2064 kg satellite was fitted with two transponders operating in the C and the L bands as well as a GPS navigational instrument. The latter instruments was also used in the ERGNOS system as described for 2001 029A.

1996 021A (23842) Name: Astra-1F Country: Luxembourg Launch date: 8 April 1996 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton K/DM-3


1996 022A (23846) Name: MSat-1 Country: Canada Launch date: 20 April 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 42P

Orbit: geostationary at 106°W

Mobile communications satellite owned by TMI Communications and built by Hughes and Star Aerospace using the HS-601 platform. The 2855 kg satellite was fitted with 2 transponders operating in the Ku band and 16 transponders in the L band. The satellite has also been referred to as AMSC-2.

1996 023A (23848) Name: Priroda Country: Russia Launch date: 23 April 1996 Re-entry: 23 March 2001 Launch site: Baikonour Launch vehicle: Proton K


Earth observation module for the Mir space station (1986 017A) which was based on the TKS module as described for 1977 066A. It was also known as article 11F77I. The payload included: 1. the Mos-Obsor multi-spectral scanner of modular configuration designed to analyse selected visible

and near-infrared portions of reflected radiation; 2. a series of microwave radiometers for the analysis of meteorological parameters, vegetation, snow

and ice. These were designated R40, RP600, Ikar-N, RP225, R30, R80 and R135; 3. the Istok-1 infrared spectrometer to measure spectral characteristics of atmospheric radiation in mid

and thermal infrared regions as well as temperature, trace gas and moisture analysis; 4. the Travers synthetic aperture radar for surface mapping; 5. the Greben altimeters for ocean swell and current determination; 6. Alisa laser infrared radar altimeter, a French experiment; 7. the Ozone M ozone probe; 8. the MOM-02P Earth imaging instrument; 9. a Marina-2 radiometer; 10. the DK-35 photometer; 11. the Canopus experiment; 12. the MSU-5K multi-spectral scanner; 13. the Delta-2P multi-channel scanning radiometer; and 14. KAP-100/-350 television cameras. In addition Priroda carried, as cargo, a range of experiments which were used on the Mir space station, including: 1. the Microgravity Isolation Mount (MIM), a Canadian facility; 2. the Queen's University Experiment in Liquid Diffusion (QUELD), a Canadian experiment; 3. the Space Acceleration Measurement System (SAMS) as described for STS-40 (1991 040A); 4. the Binary Colloiday Allay Test (BCAT) experiment to study the behaviour of crystal alloys made from

two separate materials which normally do not mix; and

5. the Bio-Technology System (BTS) which supported cell structure experiments. Priroda docked with the front port of Mir on 25 April 1996 and was moved to the left port on 27 April 1996. It had a length of 11.90 m, a diameter of 4.35 m and a mass of 19,700 kg. At re-entry the spacecraft was still attached to the Mir space station.

1996 024A (23851) Name: MSX Country: USA Launch date: 24 April 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Delta 7920


The prime objective of the Midcourse Space Experiment (MSX) satellite was to test methods to detect, track and discriminate missiles during mid-course stages of their flight against terrestrial Earth limb and celestial backgrounds, as well as undertake upper atmospheric research. The satellite had a mass of 2680 kg and the instruments were: 1. the Space Infrared Imaging Telescope (SPIRIT)-III, a cryogenic cooled infrared sensor which

discriminated between thermal objects, detected cold targets, measured Earth limb clutter and determined the composition of the Earth's atmosphere;

2. the Ultraviolet Visible Imagers and Spectrographic Imagers (UVISI), a group of nine imagers operating in the ultraviolet and visible bands to collect data on missiles in all phases of their flight and collect auroral and polar magnetospheric data;

3. the Space Based Visible (SBV) instrument, a telescope which was coupled to a CCD camera for deep space surveillance and asteroid tracking;

4. the On-board Signal and Data Processor, an experiment to test the radiation hardening of such an instrument; and

5. the Contamination Instrumentation Complement (CIC) experiment, to determine contamination of the telescope mirrors by water vapor and materials outgassed by the spacecraft.

As part of the scientific programme the satellite tracked missiles fired from the Kauai Test Facility and Vandenberg. It was intended that this was to involve two Stars missiles carrying payloads as part of Operational and Deployment Experiment Simulator (ODES) programme. Eventually only one flight, identified as MSX Dedicated Target (MDT)-II, took place on 31 August 1996 and was launched from the Kauai Test Facility. It deployed a total of 26 projectiles. MSX also tracked Kosmos-1278 (1981 058A), Kosmos-2227 (1992 093A) and a Titan transtage. It has been reported that on 24 August 1996 and 12 September 1996 two emissive reference spheres were released, however, it does not appear these have been catalogued. The satellite carried five of such spheres with a diameter of 2 cm which were a source of infrared thermal emission used in the calibration of SPIRIT III and UVISI.

During the early phases of its operational life the satellite, and in particular the SPIRIT-III experiment, was used to observe small solar system bodies. The spacecraft also successfully observed two Super Chief missiles launched from Wallops Island on 12 February 1997 and 23 February 1997 as part of the Combined Experiments Program (CEP) programme. These flights were indicated as MSX CEP-1 and -2 as well as MDT-IV and III, respectively. The MSX programme also involved various Space Shuttle flights, commencing with STS-63 (1995 004A). After that the programme was completed, in 1998, the satellite was used to locate ‘missing’ satellites for NORAD. The satellite was shut down on 10 July 2008.

1996 025A (23853) Name: Kosmos-2332 Country: Russia Launch date: 24 April 1996 Re-entry: 28 January 2005 Launch site: Plesetsk Launch vehicle: Kosmos 3M

Orbit: 294 x 1564 km, inclination: 82.9° Yug minor military satellite as described for 1979 100A.

1996 026A (23855) Name: Vortex 2-2 Country: USA Launch date: 24 April 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan 401A

Orbit: geostationary at 11°E Military electronic intelligence gathering satellite as described for 1994 054A. Also known as USA-118.

1996 027A (23857) Name: SAX Country: Italy Launch date: 30 April 1996 Re-entry: 30 April 2003 Launch site: Cape Canaveral Launch vehicle: Atlas I


The Satellite per Astronomia in raggi X (SAX) satellite studied X-ray sources within and outside the galaxy with a particular emphasis on black holes and neutron stars. The instrumentation consisted of two wide field cameras, three medium-energy concentrators, a low-energy concentrator, a phoswich detector system and a high-pressure gas scintillation detector system. The satellite had a mass of 900 kg and was later renamed as Beppo SAX, after the astronomer Beppo. The observation programme lasted up to four years.

1996 028A (23860) Name: Progress M-31 Country: Russia Launch date: 5 May 1996 Re-entry: 1 August 1996 Launch site: Baikonour Launch vehicle: Soyuz U

Orbit: 163 x 190 km, inclination: 51.6° Cargo transfer spacecraft as described for 1989 066A. Progress M-31 docked with the front port of the Mir space station (1986 017A) on 7 May 1996. It undocked on 1 August 1996. The payload included a Pepsi Cola balloon which was inflated from the space station on 21 May 1996. After filming, it was deflated and stowed.

1996 029A (23893) Name: USA-119 Country: USA Launch date: 12 May 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 403A

Orbit: 1051 x 1165 km, inclination: 63.4° Surveillance satellite as described for 1976 038C.

1996 029B (23907) Name: USA-120 Country: USA Launch date: 12 May 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 403A


1996 029C (23908) Name: USA-121 Country: USA Launch date: 12 May 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 403A


1996 029D (23862) Name: NOSS 2-4 Country: USA Launch date: 12 May 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 403A

Orbit: 1186 x 1194 km, inclination: 63.4° Second generation military ocean surveillance satellite as described for 1976 038A. Also known as USA-122. On 20 June 1996 the TiPS pair of tethered satellites were released as 1996 029E and 1996 029F.

1996 029E (23936) Name: TiPS-1 Country: USA Launch date: 20 June 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 403A


On 20 June 1996 a pair of tethered satellites were released from NOSS-11 (1996 029D). They were identified as Tethered Physics and Survivability (TiPS). The two bodies, which had a mass of 10.4 kg and 37.7 kg, were connected by a 4 km tether line and the purpose was to study the behaviour of the tether line. The spacecraft, which carried only a data transmitter and laser reflectors, will remain in orbit for 27 years. Twenty weeks after release, the tetherline remained intact and the spacecraft had assumed a gravity gradient attitude. Visual observation have indicated that the tether may eventually have broken by September 2006. TiPS-1 was also known as USA-123.

1996 029F (23937) Name: TiPS-2 Country: USA Launch date: 20 June 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 403A

Orbit: 1021 x 1021 km, inclination: 63.4° Tethered satellite as described for 1996 029E and also known as USA-124.

--- Name: --- Country: Russia Launch date: 14 May 1996 Re-entry: n.a. Launch site: Baikonour Launch vehicle: Soyuz U Orbit: failed to orbit Kometa mapping satellite as described for 1981 015A. The satellite carried the United States’ Space Information 2 m (Spin-2) experiment which involved photography with a resolution of 2 m. The launch vehicle failed 49 seconds after launch and was destroyed.

1996 030A (23864) Name: Palapa-9 Country: Indonesia Launch date: 16 May 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L

Orbit: geostationary at 108°E Communications satellite as described for 1996 006A. In November 2014 it was re-located at 146oE.

1996 030B (23899) Name: Amos-1 Country: Israel Launch date: 16 May 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L


Communications satellite owned and built by Israel Aircraft Industry. The 996 kg African Mediterrenean Orbital System (Amos) satellite had 9 transponders in Ku band. In 2009 the satellite was sold to Intelsat as Intelsat-24 and relocated at 31oE. The satellite was retired in July 2012.

1996 031A (23868) Name: MSTI-3 Country: USA Launch date: 17 May 1996 Re-entry: 11 December 1997 Launch site: Vandenberg Launch vehicle: Pegasus


The Miniature Sensor Technology Integration (MSTI)-3 satellite carried out tests of new sensor technology for ballistic missile detection with a particular emphasis on infrared emissions. In 1997 the satellite was used the Army Mid Infrared Advanced Chemical experiment, an anti-satellite system which illuminated the satellite by a laser beam. The 200 kg satellite was released from the L-1011 carrier aircraft off the Californian coast.

1996 032A (23870) Name: STS-77 Country: USA Launch date: 19 May 1996 Re-entry: 29 May 1996 Launch site: Cape Canaveral Launch vehicle: STS


TEAMS payload

Crewed spaceflight with astronauts J. Casper (Cmdr.), C. Brown (Pilot), D. Bursch, M. Runco, A. Thomas and M. Garneau (Canada) (all Mission Specialists) using the orbiter Endeavour as described for 1981 034A on the Technology Experiments Advancing Mission in Space (TEAMS) mission which made use of the Spacehab facility (FU1) as described for 1993 037A. The mission also launched Spartan-207/IAE and PAMS/STU and recovered Spartan-207. The instruments include: 1. the Technology Experiments Advancing Mission in Space (TEAMS) experiments consisting of:

• the GPS Attitude and Navigation Experiment (GANE), to determine the accuracy with which GPS can provide attitude data to the orbiter. This experiment was also known as Risk Mitigation Experiment (RME)-1316 in the RME series of experiments as described for STS-74 (1995 061A);

• the Vented Tank Resupply Experiment (VTRE), to test methods for in-space refuelling;

• the Liquid Metal Thermal Experiment (LMTE) also known as S93-5 and PL-206, which tested heat pipes;

2. the Commercial Float Zone Furnace (CFZF) as described for STS-63 (1995 004A); 3. the Space Experiment Facility (SEF) as described for STS-60 (1994 006A) with 12 separate crystal

growth experiments; 4. the Advanced Separation Process for Organic Materials (ADSEP)-1 facility to improve separation and

purification capabilities in the production of pharmaceuticals; 5. the Commercial Generic Bioprocessing Apparatus (CGBA)-9 as described for STS-50 (1992 034A)

which supported 272 separate experiments; 6. the Plant Generic Bioprocessing Apparatus (PGBA)-1 to study changes in the production of

secondary metabolites in microgravity; 7. the Fluid Generic Bioprocessing Apparatus (FGBA)-2 as described for STS-63 (1995 004A); 8. the Hand Held Diffusion Test Cell (HHDTC) as described for STS-63 (1995 004A); 9. the IMMUNE experiment as described for STS-60 (1994 006A), to test the ability of an insulin growth

factor in microgravity;

10. the Commercial Protein Crystal Growth (CPCG)-13 experiment as described for STS-49 (1988 109B);

11. the Gas Permeable Polymeric Membrane (GPPM)-3 experiment as described for STS-57 (1993 037A);

12. the National Health Industries Collaborative (NIH C)-7 experiment as described for STS-59 (1994 020A) incorporating the Space Tissue Loss (STL) instrument as described for STS-45 (1992 015A);

13. the Tank Pressure Control Experiment (TPCE) as described for STS-43 (1991 054A); 14. the Brilliant Eyes Ten Kelvin Sorption Cryocooler Experiment (BETSCE) to study the rapid cooling of

infrared and other instruments in zero-gravity; 15. the Aquatic Research Facility (ARF) to study the effect of microgravity on small aquatic creatures; 16. the Biological Research In Canisters (BRIC)-7 as described for STS-64 (1994 059A) which helped

investigators to discover the mechanisms behind one endocrine system in insects; 17. a number of Getaway specials as described for STS-3 (1982 022A):

• G056: the Gamma-ray Astrophysics Mission (GAMCIT) to study gamma ray bursts;

• G063: various experiments by Penn State University;

• G142 and G144: two German experiments designated MAUS to undertake material science experiments;

• G163: The Diffusion Coefficient Measurement Facility (DCMF), to measure the speed at which Mercuric Iodide (solid) is evaporated and then transported as a vapor under microgravity conditions;

• G200: three experiments including popcorn kernels in zip lock bags as an experiment by an elementary school;

• G490: a British experiment to verify that a low-level gravitational field can be measured by observing their effect on the convection currents present in a heated liquid and an experiment with samples of seeds, oats, wheat, barley and nape-oil to quantify the effects of space flight on growth patterns.

• G564 and G565: the Nanocrystal Get Away Special (NANO-GAS) and Atlantic Canada Thin Organic Semiconductors (ACTORS) to investigate new materials with applications in high performance lasers and in electronic equipment and components;

• G703: the Microgravity Smoldering Combustion (MSC) experiment as described for STS-69 (1995 048A);

• G741: an experiment to study the fundamentals of nucleate pool boiling heat transfer under the microgravity conditions of space;

18. Developmental Test Objective (DTO) experiments as described for STS-1 (1981 034A):


• DTO-305D: Ascent Compartment Venting Evaluation;

• DTO-306D: Descent Compartment Venting Evaluation;



• DTO-415: Water Spray Boiler Electrical Heater Capability;

• DTO-700-8: Global Positioning System Development Flight Test;

• DTO-805: Crosswind Landing Performance; 19. Detailed Supplementary Objective (DSO) experiments as described for STS-1 (1981 034A):









• DSO-903: Documentary Still Photography.

Spartan-207 (1996 032B) was deployed on 20 May 1996 and was retrieved again on 21 May 1996. PAMS/STU (1996 032D) was deployed on 22 May 1996 following which the crew made four rendez-vous tests with that satellite. The orbiter landed at the Kennedy Space Centre after a flight of 10 days, 0 hours, 39 minutes.

1996 032B (23871) Name: Spartan-207 Country: USA Launch date: 20 May 1996 Re-entry: 21 May 1996 Launch site: Cape Canaveral Launch vehicle: STS + RMS


A satellite in the Shuttle Pointed Autonomous Research Tool of Astronomy (Spartan) programme as described for 1985 048E. Using the same spacecraft that had been used for Spartan-204 (1995 004B), the 1296 kg satellite carried the Inflatable Antenna Experiment (IAE). Spartan-207 was deployed from STS-77 (1996 032A) by means of RMS on 20 May 1996. IAE was deployed 2 hours, 9 minutes later whilst IAE was separated and became 1996 032C, on 20 May 1996, 3 hours, 38 minutes after the Spartan-207 deployment. Spartan-207 was retrieved on 21 May 1996.

1996 032C (23872) Name: IAE Country: USA Launch date: 20 May 1996 Re-entry: 22 May 1996 Launch site: Cape Canaveral Launch vehicle: STS + RMS


The Inflatable Antenna Experiment (IAE) consisted of a large inflatable structure which was inflated whilst still attached to Spartan-207 (1996 032B) and was then released. The experimental antenna, which had a diameter of 14 m, was made of mylar with an aluminium coating and was mounted on an inflatable tripod. The structure, which had a mass of 60 kg, was inflated by nitrogen. After release from Spartan-207, IAE eventually burned up over the Atlantic Ocean.

1996 032D (23876) Name: PAMS/STU Country: USA Launch date: 22 May 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: STS + RMS


The 52 kg Passive Aerodynamically Stabilised Magnetically Dampened Satellite/Satellite Test Unit (PAMS/STU) was used to conduct rendez-vous operations as well as to demonstrate the use of metal bars in the stabilisation of spacecraft using the Earth magnetic field. It was released from STS-77 (1996 032A).

1996 033A (23877) Name: Galaxy-9 Country: USA Launch date: 24 May 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 7925


1996 034A (23880) Name: Gorizont-32 Country: Russia Launch date: 25 May 1996 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton K/DM-2

Orbit: geostationary at 52°E Communications satellite as described for 1978 118A. The satellite was leased to Rimsat and was also referred to as Presidentsky.

--- Name: Cluster Int. Agency: ESA Launch date: 4 June 1996 Re-entry: n.a. Launch site: Kourou Launch vehicle: Ariane 5G Orbit: failed to orbit

Remnants of one of the satellites in the swamps of Kourou

Cluster was a set of four satellites to study small scale structures in the Earth's plasma environment and the associated turbulence in the magnetosphere and the geomagnetic tail from adjustable non-coplanar orbits. The payloads included two tri-axis fluxgate sensors, a tri-axis search coil sensor; probes to measure certain electric fields, an instrument to measure the total electron density and the natural plasma, an experiment to study the transmission of certain waveforms, a digital wave processor to study electron density, an electron drift instrument, an ion spectrometer, a plasma electron and current analyser and several solid state detectors. Ultimately the satellites, with a mass of 550 kg each, would have been placed in orbit of 25500 x 140300 km with an inclination of 90o . The Ariane 5G launch vehicle was destroyed 37 seconds after the launch.

1996 035A (23915) Name: Intelsat-709 Int. Agency: Intelsat Launch date: 15 June 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44P


Communications satellite as described for 1993 066A. The satellite was later moved to 50°W and to 47.5oE in September 2012.

1996 036A (23931) Name: STS-78 Country: USA Launch date: 20 June 1996 Re-entry: 7 July 1996 Launch site: Cape Canaveral Launch vehicle: STS


Crew with Olympic flame

Crewed spaceflight with astronauts T. Henricks (Cmdr.), K. Kregel (Pilot), S. Helms (Payload Cmdr.), R. Linnehan, C. Brady (both Mission Specialists), J. Favier (France) and R. Thirsk (Canada) (both Payload Specialists) using the orbiter Columbia as described for 1981 034A. The objective of the mission was to fly the Life and Microgravity Spacelab (LMS) mission and conduct 17 life sciences and 24 microgravity experiments. Using a Spacelab module (LM2) as described for 1983 116A, the experiments consisted of: 1. a series of metabolic experiments including:

• the direct measurement of the initial bone response to spaceflight;

• the measurement of energy expenditure during spaceflight with the Doubly labelled water method; 2. the study of pulmonary functions in weightlessness; 3. the study of human behaviour and performance in space, including:

• human sleep, circadian rythms and performance in space;

• the effects of microgravity on standardised cognitive performance measurements using the Performance Assessment Work Station (PAWS) as described for STS-65 (1994 039A);

4. the Torque Velocity Dynamometer (TVD) which measured human muscle strength with a particular emphasis on the elbow and the ankle to investigate in conjunction with pre- and post flight investigations by Magnetic Resonance Imaging (MRI):

• the effects of weighlessness on human single muscle fiber function;

• the relationship of long-term electromyographic activity and hormonal function to muscle atrophy and performance;

• the effects of microgravity on skeletal muscle contractile properties;

• the effects of microgravity on the biomedical and bioenergetic characteristics of human skeletal muscle;

5. a series of neuroscience investigations, comprising:

• the torso rotation experiment;

• canal and otolith interaction studies; 6. three space biology experiments:

• the Lignin formation and the effects of microgravity;

• the development of fish (Medaka) in microgravity;

• the role of corticosteroids in bone loss during spaceflight; 7. the Advanced Protein Crystallisation Facility (APCF)-4 as described for STS-57 (1993 037A) used

for a range of separate experiments:

• the crystallization of EGFR-EGF;

• the crystallization of crustacyanin subunits;

• the crystallization of engineered 5S rRNA molecules;

• the crystallization of thermus thermophilus AspRS;

• the monitoring of lyszozyme protein crystal growth in microgravity via a Mach-Zehnder interferometer;

• the crystallization of the nucleosome core particle in space;

• the ehanced resolution through improved crystal quality in the crystal structure analysis of photosystem I;

• the mechanisms of membrame protein crystal growth;

• the crystallization in a microgravity environment on CcdB;

• the crystallization of sulfolobus solfataricus alcohol;

• the growth of lysozyme crystals at low nucleation density; 8. the Advanced Gradient Heating Facility (AGHF)-1 to investigate advanced semi-conductor materials

and alloys, supporting a range of experiments which orignially were to have flown on STS-65 (1994 039A) as part of the IML-2 mission:

• the comparative study of cells and dendrites during directional solidification of a binary aluminum alloy at 1G and microgravity;

• the coupled growth of hypermonotectics;

• the effects of convection on interface curvature during the growth of concentrated ternary compounds;

• the equiaxed solidification of aluminum alloy;

• the interactive response of advancing phase boundaries to particles;

• the particle engulfment and pushing by solidifying interfaces; 9. the Bubble Drop and Particle Unit (BDPU) as described for STS-65 (1994 039A), to undertake a

number of fluid dynamics experiments:

• the bubbles and drops interaction with solidification fronts;

• the evaporation and condensation kinetics in a liquid vapor interface;

• the efficient cooling of high powered small electronic devices by boiling under microgravity;

• the electrohydrodynamics of liquid bridges;

• the non-linear surface tension driven bubble migration;

• the oscillatory Marangoni instability;

• the thermocapillary migration and interaction of bubbles and drops; 10. the Microgravity Measurement Assembly (MMA)-2 as described for STS-55 (1993 027A); 11. the Orbital Acceleration Research Experiment (OARE)-7 as described for STS-40 (1991 040A); 12. the Space Acceleration Measurement System (SAMS)-15 as described for STS-40 (1991 040A); 13. the Biological Research in Canisters (BRIC)-8 payload as described for STS-64 (1994 059A) which

investigated the somatic embryogenesis of day lily plant cells; 14. the Shuttle Amateur Radio Experiment (SAREX)-23 as described for STS-51F (1985 063A); 15. the Midcourse Space Experiment (MSX) as described for STS-63 (1995 004A); 16. the Space Tissue Loss (STL) instrument as described for STS-45 (1992 015A); 17. Developmental Test Objective (DTO) experiments as described for STS-1 (1981 034A):




• DTO-319D: Orbiter/Payload Acceleration and Acoustics Environment Data;

• DTO-623: Cabin Air Monitoring;


• DTO-675: Voice Control of Closed Circuit Television System;

• DTO-1126: KCA Video Teleconferencing Demonstration;

18. Detailed Supplementary Objective (DSO) experiments as described for STS-1 (1981 034A):








• DSO-903: Documentary Still Photography. The flight also tested the Water Spray Boiler Quick Restart methodology, which will allow larger payloads to be carried, and the Vernier Rebound Capability to demonstrate the use of the vernier thrusters to increase altitude. The mission also carried the Olympic flame into space. The orbiter landed at the Kennedy Space Centre after a flight of 16 days, 21 hours, 47 minutes.

--- Name: --- Country: Russia Launch date: 20 June 1996 Re-entry: n.a. Launch site: Plesetsk Launch vehicle: Soyuz U Orbit: failed to orbit Yantar 4K2 military reconnaissance satellite as described for 1981 080A. The launch vehicle failed after 50 seconds.

1996 037A (23950) Name: TOMS-EP Country: USA Launch date: 2 July 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Pegasus XL


The Total Ozone Mapping Spectrometer - Earth Probe (TOMS-EP) was a 295 kg payload to monitor the sulfur dioxide emitted into the atmosphere by volcanic eruptions. The launch vehicle was released from the L-1011 carrier aircraft off the Californian coast.

1996 038A (23945) Name: SDS 2-1 Country: USA Launch date: 3 July 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Titan 405A


Also known as USA-125, it is believed the satellite was the first of a second generation of Satellite Data Systems (SDS) satellites as described for 1976 050A. It was built by Hughes using the HS-389 platform. It has been suggested that earlier SDS 2 satellites were launched as 1989 061B, 1990 097B,and 1992 086B. The operational SDS system, which has also been referred to as AFB-658, is believed to consist of six satellites of which three are in high elliptical orbits and three in a geostationary orbit, believed to be 10oW, 140oW and 75oE.

1996 039A (23943) Name: Apstar-3 Country: Hong Kong Launch date: 3 July 1996 Re-entry: in orbit Launch site: Xichang Launch vehicle: CZ 3


Communications satellite as described for 1994 043A. The satellite was a replacement for the one lost on 25 January 1995. It was also known as Apstar-1A. In September 2010 the satellite was moved to 51.5oE and was renamed Zhongxing-5D.

1996 040A (23948) Name: Arabsat-2A Int. Agency: Arabsat Launch date: 8 July 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L.


Communications satellite owned by Arabsat and based on the Aerospatiale Spacebus 3000 platform. The 2617 kg satellite carried 22 transponders in the C band and 12 transponders in the Ku band.

1996 040B (23949) Name: Turksat-1C Country: Turkey Launch date: 8 July 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L.

Orbit: geostationary at 42°E Communications satellite as described for 1994 049B. The satellite was a replacement for Turksat-1A which had been lost on 24 January 1994.

1996 041A (23953) Name: Navstar 2A-17 Country: USA Launch date: 16 July 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 7925

Orbit: 20272 x 20365 km, inclination: 55.0° Navigational satellite as described for 1989 013A. Also known as USA-126, Navstar-38, Navstar-40 and SVN-40.

1996 042A (23967) Name: UHF-7 Country: USA Launch date: 25 July 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas II

Orbit: geostationary at 23°W Military communications satellite as described for 1993 015A. Also known as USA-127, the satellite carried two additional EHF transponders operating at 44/20 GHz offering a further 20 communications channels.

1996 043A (24071) Name: Progress M-32 Country: Russia Launch date: 31 July 1996 Re-entry: 21 November 1996 Launch site: Baikonour Launch vehicle: Soyuz U

Orbit: 193 x 248 km, inclination: 51.6° Cargo transfer spacecraft as described for 1989 066A. Progress M-32 docked with the front port of the Mir space station (1986 017A) on 1 August 1996. It undocked on 18 August 1996 and was redocked at the rear port of Mir/Kvant-1 on 3 September 1996. It finally undocked on 21 November 1996.

1996 044A (24208) Name: Italsat-2 Country: Italy Launch date: 8 August 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L

Orbit: geostationary at 10°E Communications satellite as described for 1991 003A. The satellite carried 36 transponders in the 30/20 GHz band as well as three transponders operating in the L band for the European Land Mobile Service (EMS), an experimental mobile communications facility marketed by Nuova Telespazia.

1996 044B (24209) Name: Telecom 2-D Country: France Launch date: 8 August 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L


1996 045A (24273) Name: Molniya 1-89 Country: Russia Launch date: 14 August 1996 Re-entry: 7 April 2012 Launch site: Plesetsk Launch vehicle: Molniya M

Orbit: 498 x 40828 km, inclination: 63.0° Communications satellite as described for 1965 030A.

1996 046A (24277) Name: Midori-1 Country: Japan Launch date: 17 August 1996 Re-entry: in orbit Launch site: Tanegashima Launch vehicle: H 2


Also known as Advanced Earth Orbiting System (ADEOS)-1, the 3560 kg Earth observation satellite carried: 1. the Ocean Color and Temperature Scanner (OCTS), an optical radiometer to study ocean conditions

with a resolution of 120 m; 2. the Advanced Visible and Near Infrared Radiometer (AVNIR), to monitor deforestation and pollution; 3. the Improved Limb Atmospheric Spectrometer (ILAS), an instrument to observe the ozone depletion

in the upper atmosphere; 4. the Reflector In Space (RIS), to measure minor atmospheric constituents; 5. the Interferometric Monitor for Greenhouse Gases (IMC) to study the gasses causing the greenhouse

effect; 6. the Polarization and Directionality of Earth Reflectances (POLDER) instrument to map the ozone

distribution; 7. the NASA Scatterometer (NSCAT) to gather data on ocean winds; and 8. the Total Ozone Mapping Spectrometer (TOMS), an optical sensor to measure the albedo of the

Earth's atmosphere.

1996 046B (23278) Name: Oscar-29 Country: Japan Launch date: 17 August 1996 Re-entry: in orbit Launch site: Tanegashima Launch vehicle: H 2

Orbit: 797 x 1317 km, inclination: 98.6° Also known as Japanese Amateur Radio satellite (JAS-3), Fuji-3 and FO-29, this radio amateur satellite had transponders operating in the 145/435 MHz band. The satellite had a mass of 49 kg.

1996 047A (24280) Name: Soyuz TM-24 Country: Russia Launch date: 17 August 1996 Re-entry: 2 March 1997 Launch site: Baikonour Launch vehicle: Soyuz U

Orbit: 235 x 287 km, inclination: 51.6° Crewed spaceflight with cosmonauts V. Korzun (Cmdr.), A. Kaleri (Fl. Eng.) and C. Andre-Deshays (France) (Cosm. Res.) using a Soyuz TM spacecraft as described for 1986 035A. Their call sign was Fregat and Korzun and Kaleri were the twenty second permanent (EO-22) crew of the space station. S. Lucid, who had arrived on STS-76 (1996 018A) was the third member of the EO-22 crew and was on 19 September 1996 replaced by J. Blaha, who arrived on the space station on STS-79 (1996 052A). On 15 January 1997 Blaha was replaced by J. Linenger, who arrived on STS-81 (1997 001A). On 19 August 1996 the spacecraft docked with the front port of the Mir/Kvant (1986 017A) space station. About a week before the launch the original crew of G. Manakov and P. Vinogradov was replaced when Manakov was diagnosed with heart problems. This replacement did not affect the crew assignment of France's Andre-Deshays, whose back-up was L. Eyharts. The French involvement in the mission was designated as Cassiopee and involved experiments in human physiology with the Physiolab and Cognilab, biological studies with the Fertile instrument, the measurements of micro-vibrations with the Dynalab instrument and the use of Trellis, a mechanical truss structure with several active and passive damping systems. Korzun and Kaleri performed two spacewalks in December. The first one of 5 hours, 57 minutes took place on 2 December 1996 when they worked on the connections of the Cooperative Solar Array and relocated the Ferma-2 boom. They undertook a further EVA on 9 December 1996 when, over a period of 6 hours, 38 minutes, they completed the solar array connection and also fixed an antenna to the Kurs docking system. As a member of the EO-22 crew, Blaha was involved in a range of US sponsored experiments, including the Passive Accelerometer System (PAS), the Space Acceleration Measurement System (SAMS), the Metabolic Gas Analyser System (MGAS) and the Belt Pack Amplifier System (BPAS). He also grew two crops of wheat as part of a Utah State University experiment but on return to Earth, the wheat was found to be seedless. Andre-Deshays returned to Earth on 2 September 1996 on Soyuz TM-23 (1996 011A) and had spent 15 days, 18 hours, 23 minutes in space. Korzun, Kaleri and the US astronaut Linenger, who had arrived on the space station on STS-81 (1997 001A), moved Soyuz TM-24 to the space station’s rear port on 7 February 1997. On 2 March 1997 Korzun and Kaleri, along with Ewald, who had arrived on Soyuz TM-25 (1997 003A), undocked the spacecraft and landed the same day 131 km east of Dzhezkazgan. Korzun and Kaleri had been in space for 197 days, 17 hours, 26 minutes.

1996 048A (24282) Name: Zhongxing-7 Country: China Launch date: 18 August 1996 Re-entry: in orbit Launch site: Xi Chang Launch vehicle: CZ 3


Communications satellite owned by Chinastar and built by Hughes, using a HS376 platform with 16 transponders operating in the C band. Failure of the third stage of the launch vehicle prevented the 1384 kg satellite from achieving its desired geostationary orbit. Based on operational requirements, the geostationary location was probably 125oE. The satellite was returned to Hughes and was operated for some time as HGS-2.

1996 049A (24285) Name: FAST Country: USA Launch date: 21 August 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Pegasus XL


The Fast Auroral Snapshot Explorer (FAST) was a 180 kg satellite launched to investigate the magnetic and electric fields and charged particles above the auroras. Experiments included: 1. the Electrostatic Analyser to measure energetic electrons and ions with a high resolution; 2. the Electric Field Experiment; 3. the Time-of-Flight Energy Angle Mass Spectrograph; and 4. the Instrument Data Processor Unit. The launch vehicle was released from the L-1011 carrier aircraft off the Californian coast. The satellite was also known as SMEX-2 in the Small Explorer programme as well as Explorer-70.

1996 050A (24291) Name: Musat Country: Argentina Launch date: 29 August 1996 Re-entry: 12 November 1999 Launch site: Plesetsk Launch vehicle: Molniya M


Musat was a 30 kg technology satellite built by the Institute Universitario Aeronatica in Cordoba. It carried two CCD cameras with 70 m and 2 km resolutions.

1996 050B (24292) Name: Magion-5 Country: Czech Rep. Launch date: 29 August 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Molniya M


Scientific satellite as described for 1995 039F.

1996 050C (24293) Name: Interball-2 Country: Russia Launch date: 29 August 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Molniya M


Scientific satellite as described for 1995 039A. Unlike Interball-1, this satellite was in an orbit that crossed the auroral oval.

1996 051A (24297) Name: Kosmos-2333 Country: Russia Launch date: 4 September 1996 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Zenit 2

Orbit: 842 x 852 km, inclination: 71.0° Tselina 2 military electronic intelligence gathering satellite as described for 1984 106A.

1996 052A (24304) Name: Kosmos-2334 Country: Russia Launch date: 5 September 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M


1996 052B (24305) Name: Oscar-30 Country: Mexico Launch date: 5 September 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M


The satellite was a replacement for the one lost on 28 March 1995. The 17 kg radio amateur satellite, also known as Unamsat-2 and MO-30, was to operate in the 437/145 MHz and 40 MHz band but transmission failed due to damage of the instruments resulting from cold weather at the launch site.

1996 053A (24307) Name: Inmarsat 3-2 Int. Agency: Inmarsat Launch date: 6 September 1996 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton K/DM-2

Orbit: geostationary at 15°W Maritime communications satellite as described for 1996 020A. The GPS instrument was also used in the ERGNOS system as described for 2001 029A.

1996 054A (24315) Name: GE-1 Country: USA Launch date: 8 September 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas IIA.


Communications satellite owned by GE Americom and based on the Lockheed Martin A2100 platform. The 2784 kg satellite carried 24 transponders in the C band and 24 transponders in the Ku band. As part of a merger with SES as SES Americom, the satellite was renamed AMC-1 in November 2001. It was moved to 129.2oW in August 2015.

1996 055A (24313) Name: Echostar-2 Country: USA Launch date: 11 September 1996 Re-entry: in orbit aunch site: Kourou Launch vehicle: Ariane 42P


1996 056A (24320) Name: Navstar 2A-18 Country: USA Launch date: 12 September 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 7925

Orbit: 17055 x 33649 km, inclination: 61.5° Navigational satellite as described for 1989 013A. Also known as USA-128, Navstar-30, Navstar-39 and SVN-30. There is no record of Navstar-42.

1996 057A (24324) Name: STS-79 Country: USA Launch date: 16 September 1996 Re-entry: 26 September 1996 Launch site: Cape Canaveral Launch vehicle: STS


Space suit storage bag

Crewed spaceflight with astronauts W. Readdy (Cmdr.), T. Wilcutt (Pilot), J. Apt, T. Akers, C. Walz and J. Blaha (all Mission Specialists), using the orbiter Atlantis as described for 1981 034A. The primary objective of the mission was to dock with the Mir (1986 017A) space station to deliver 924 kg of scientific equipment and supplies and 636 kg of water. Blaha remained on the space station as a member of the EO-22 crew. He relieved S. Lucid, who had arrived on the station on STS-76 (1996 018A). Blaha returned to Earth on STS-81 (1997 001A). The Space Shuttle docked with the Shuttle Docking port of Mir on 19 September 1996. During their stay, the crew participated in various space medicine experiments such as those described for STS-71 (1995 030A). The orbiter carried two Spacehab modules (FU2 and FU3) as described for 1993 037A. Both were used to carry the Mir supplies. In addition one of the modules carried: 1. the Commercial Protein Crystal Growth (CPCG)-14 experiment as described for STS-49 (1988

109B); 2. the Materials in Devices As Superconductors (MIDAS) experiment to measure the electrical

properties of high temperature superconducting materials; 3. the Commercial Generic Bioprocessing Apparatus (CGBA)-10 as described for STS-50 (1992 034A); 4. the Commercial Vapor Diffusion Apparatus (CVDA) for the processing of several of the materials

used by CPCG; 5. the Mechanics of Granular Materials (MGM)-1 experiment to understand the behavior of cohesionless

granular materials; 6. the Gaseous Nitrogen Dewar (GND)-3 protein crystal growth experiment as described for STS-71

(1995 030A) which was left on Mir and retrieved by STS-81 (1997 001A); 7. the Diffusion Controlled Crystallization Apparatus for Microgravity (DCAM)-2 as described for STS-

73 (1995 056A); and 8. the Extreme Temperature Translation Furnace (ETTF) for investigations into zero-gravity processing

of materials. Other experiments included: 1. the Real Time Radiation Monitoring Device (RRMD) to measure cosmic radiation;

2. the Shuttle Amateur Radio Experiment (SAREX)-24 as described for STS-51F (1985 063A); 3. the Midcourse Space Experiment (MSX) as described for STS-63 (1995 004A); 4. Developmental Test Objective (DTO) experiments as described for STS-1 (1981 034A):

• DTO-255: Wraparound DAP Flight Test Verification;






• DTO-700-14: Single String Global Positioning System Test;


• DTO-837: Vernier RCS Reboost Demonstration;

• DTO-840: Hand-Held Lidar Procedures;

• DTO-1118: Photographic and Video Survey of Mir space station; 5. Detailed Supplementary Objectives (DSO) experiments as described for STS-1 (1981 034A):



• DSO-902: Documentary Motion Picture Photography;

• DSO-903: Documentary Still Photography; 6. a number of Risk Mitigation Experiments (RME) as described for STS-74 (1995 061A):

• RME-1301: Mated Shuttle and Mir Structural Dynamics Test;

• RME-1302: Mir Electric Field Characterization Test 1 and 2;

• RME-1303: Shuttle/Mir Experiment Kit Transportation;

• RME-1310: Shuttle/Mir Alignment Stability Experiment;

• RME-1312: Intra-Vehicular Radiation Environment Measurement Experiment;

• RME-1313: Active Rack Isolation System (ARIS); and

• RME-1319: Inventory Management System Test for the SPACEHAB. Atlantis undocked on 24 September 1996 and the orbiter landed at the Kennedy Space Centre after a flight of 10 days, 3 hours, 18 minutes. Lucid had been in space for 188 days, 4 hours, 0 minutes.

1996 058A (24435) Name: Ekspress-2 Country: Russia Launch date: 26 September 1996 Re-entry: in orbit Launch site: Baikonour Launch vehicle: Proton K/DM-2M

Orbit: geostationary at 80°E Communications satellite as described for 1994 067A. The satellite also carried the Geostationary Orbit Impact detector (GORID), a joint ESA/Russian instrument to measure the level of meteorite flux and man made space debris in the geostationary orbit.

1996 059A (24634) Name: FSW 2-3 Country: China Launch date: 20 October 1996 Re-entry: 3 December 1996 Launch site: Jiuquan Launch vehicle: CZ 2D

Orbit: 168 x 332 km, inclination: 63.0° Recoverable spacecraft as described for 1992 051A. The satellite was also known as Jian Bing 1A-3. The re-entry capsule was recovered on 4 November 1996.

1996 060A (24640) Name: Molniya 3-48 Country: Russia Launch date: 24 October 1996 Re-entry: 18 October 2007 Launch site: Plesetsk Launch vehicle: Molniya M

Orbit: 608 x 40649 km, inclination: 62.8° Communications satellite as described for 1974 092A.

1996 061A (24645) Name: SAC-B/HETE-1 Country: Argentina/USA Launch date: 4 November 1996 Re-entry: 7 April 2002 Launch site: Wallops Island Launch vehicle: Pegasus XL


The Satellite de Aplicaciones Cientificas (SAC)-B was a 183 kg scientific satellite which carried X-ray CCD sensors for the investigation of solar physics with an emphasis on solar flares, gamma ray bursts and cosmic X-ray background. The 118 kg High Energy Transient Experiment (HETE)-1 was to study gamma ray bursts. It carried an Omni-directional Gamma Ray Spectrometer, a Wide Field X-ray Monitor and an Ultraviolet Transient Camera Array. The launch vehicle was released from the L-1011 carrier aircraft off Wallops Island but the payloads failed to separate from the third stage which entered orbit along with the satellites. The total mass was 480 kg.

1996 062A (24648) Name: Mars Global Surveyor Country: USA Launch date: 7 November 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Delta 7925 Orbit: trans-martian

The Mars Global Surveyor, with a mass of 1060 kg, reached Mars on 11 September 1997 and it was intended that by January 1998 it would have been in a martian polar orbit of 350 x 410 km, with an inclination of 93o. However, during the aerobraking phase of the spacecraft’s flight around Mars, one of the large solar panels experienced too much stress. This solar panel had been damaged shortly after the launch. The aerobraking phase was amended and the desired orbit of 384 x 406 km with an inclination of 93o, was achieved in February 1999. The instruments carried on board of the spacecraft were: 1. the Magnetometer and Electron Reflectometer (MAG/ER) which studied the magnetic field and solar

wind interaction with Mars; 2. the Mars Orbiter Camera (MOC), which was used for surface and atmospheric imaging; 3. the Mars Orbiter Laser Altimeter (MOLA), which undertook gravity field studies and surface

topography observations; 4. the Mars Relay (MR) radio package; 5. the Thermal Emission Spectrometer (TES) to make mineralogical, condensates, dust, thermal and

atmospheric measurements; and 6. an ultrastable oscillator to conduct radio science for gravity field and atmospheric studies. Through the delay in the areobraking phase the scientific programme was delayed by a year. In July 1998 the alignment of the Sun was incorrect for mapping and it was necessary to wait until 9 March 1999, before mapping could begin. Budget restrictions, at that point in time, prevented the extension of the observation programme beyond the one year time period, but following excellent results the mission was extended to February 2001. The programme was subsequently extended to April 2002. After the observation programme the satellite continued to be used as a data relay station for subsequent lander craft until, on 5 November 2006 contact with the spacecraft was lost.

1996 063A (24652) Name: Arabsat-2B Int. Agency: Arabsat. Launch date: 13 November 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L

Orbit: geostationary at 32°E Communications satellite as described for 1996 040A. In January 2012 it was relocated to 34.5oE.

1996 063B (24653) Name: Measat-2 Country: Malaysia Launch date: 13 November 1996 Re-entry: in orbit Launch site: Kourou Launch vehicle: Ariane 44L

Orbit: geostationary at 148°E Communications satellite as described for 1996 002B. In 2010 the satellite was relocated to 5.7oE and was renamed as Africasat-2. This did not involve a change in ownership. The satellite was retires in April 2013.

1996 064A (---) Name: Mars-8 Country: Russia Launch date: 16 November 1996 Re-entry: 17 November 1996 Launch site: Baikonour Launch vehicle: Proton K/D-2


Referred to as Mars96 during development, Mars-8 was a 6640 kg spacecraft built by Lavochkin with a three fold purpose to place an orbiter around Mars, place two landers on the surface of Mars and to shoot two penetrators into the surface of Mars. In addition, the spacecraft was to perform scientific investigations during its flight to Mars. The instruments on board of the orbiter were: 1. the HRSC high-resolution TV camera; 2. the WAOSS wide angle TV camera; 3. the Planetary Fourier Spectrometer (PFS) for observations in the infrared; 4. OMEGA, a visible and infrared mapping spectrometer; 5. Thermoscan, a mapping radiometer; 6. the SVET high-resolution mapping spectrophotometer; 7. the UVS-M spectrophotomoter operating in ultraviolet; 8. the Long Wave Radar (LWR); 9. PHOTON, a gamma ray spectrometer; 10. the Neutron S spectrometer; 11. the MAK quadropole mass spectrometer; 12. ASPERA-S, an energy mass ion spectrograph and neutral particle imager; 13. FONEMA, the fast omni-directional non-scanning energy-mass ion analyser; 14. DIMIO, an omni-directional ionospheric energy-mass spectrometer; 15. MARIPROB, several ionospheric plasma spectrometers; 16. MAREMF, an electron analyser and magnetometer; 17. the ELISMA plasma wave detectors; 18. SLED-2, a low-energy charged particle spectrometer; 19. the Precision Gamma Spectrometer (PGS); 20. the LILAS-2 cosmic and solar gamma-burst spectrometer; 21. SPICAM-S, a solar spectrometer; 22. SPICAM-E, a stellar spectrometer; 23. the EVRIS stellar oscillation photometer; and

24. RADIUS-M, a system for radiation and dosimetry control. The two landers were designated as MAS and had a mass of 40 kg. They were fitted with: 1. the Meteorology Instrument System (MIS) which incorporated sensors to measure the temperature,

pressure and relative humidity at the landing sites, as well as optical depth sensors and an ion anemometer;

2. the Descent Phase Instrument (DPI) systems consisting of accelerometers, pressure and temperature sensors;

3. the Alpha-particle, Proton and X-ray (APX) spectrometer; 4. the Optimism set of instruments consisting of a seismometer, magnetometer and inclinometer; 5. the PanCam panoramic camera system; 6. the DesCam descent phase camera system; and 7. the Mars Oxidant (MOx) experiment. The two penetrators had a mass of 65 kg and were fitted with solid fuelled boosters. The instruments consisted of: 1. PTV-1 television camera; 2. the MEKOM meteorological package including temperature, pressure, wind speed and direction and

humidity sensors; 3. the PEGAS gamma ray spectrometer; 4. ANGSTROM, an X-ray spectrometer; 5. the ALPHA spectrometer to measure alpha and proton particles; 6. NEUTRON-P, a neutron spectrometer; 7. the GRUNT set of accelerometers; 8. the THERMOZOND temperature sensors; 9. KAMERTIN, a seismometer; and 10. the IMAP-7 magnetometer. Following its launch the Mars-8 spacecraft was placed in a low-Earth orbit from where it was intended to boost it into a trans-martian trajectory which would have seen it arrive at Mars on 12 September 1997. It would then have been placed in a martian orbit of 300 x 22000 km with an inclination of 101.1o, following which the landers and the penetrators would have been released. The landers would have operated for 700 days, whilst the penetrators would have operated for 350 days. However, the final stage of the launch vehicle did not fire long enough to place the spacecraft into the desired trajectory. The spacecraft is believed to have re-entered on the third orbit. An upper stage continued to orbit and was initially thought to be the spacecraft when it was given designation 1996 064A (24656). It re-entered off the South American coast near Easter Island on 18 November 1996 although it has been suggested debris also came down in Chile. The spacecraft itself never received an international designation.

1996 065A (24660) Name: STS-80 Country: USA Launch date: 19 November 1996 Re-entry: 7 December 1996 Launch site: Cape Canaveral Launch vehicle: STS


Crewed spaceflight with astronauts K. Cockrell (Cmdr.), K. Rominger (Pilot), T. Jernigan, T. Jones and S. Musgrave (all Mission Specialists), using the orbiter Columbia as described for 1981 034A. The primary objective of the mission was to deploy and retrieve Orfeus/SPAS-2 (1996 065B) and WSF-3 (1996 065C). The former was deployed on 20 November 1996 and retrieved on 4 December 1996. The WSF-3 was deployed on 22 November 1996 and was retrieved on 26 November 1996. Other experiments that were carried on the orbiter were: 1. the Commercial Materials Dispersion Apparatus ITA Experiments (CMIX)-5 as described for STS-52

(1992 070A); 2. the Visualisation in an Experimental Water Capillary Pumped Loop (VIEW-CPL) experiment to

investigate a method of spacecraft thermal regulation; 3. the Cell Culture Module A (CCM A)-1 experiment, also known as ASPWS-701, to grow cell cultures

in microgravity. This experiment was previously known as the National Health Industries Collaborative (NIH C)-6 experiment as described for STS-59 (1994 020A);

4. the Biological Research In Canisters (BRIC)-9 experiment as described for STS-64 (1994 059A) which studied the influence of microgravity on genetically altered tomato and tobacco seedlings that had been modified to contain elements of soybean genes;

5. the National Health Institutes Rodent (NIH R)-4 experiments as described for STS-66 (1994 073A) which studied the blood pressure regulation and function in rats;

6. the Space Experiment Module (SEM)-1, an educational facility utilising a Getaway canister as described for STS-3 (1982 022A), to allow student experiments to be carried which on this flight included a range of experiments prepared by a number of educational institutions;

7. the Midcourse Space Experiment (MSX) as described for STS-63 (1995 004A); 8. the Shuttle Amateur Radio Experiment (SAREX)-25 as described for STS-51F (1985 063A); 9. Risk Mitigation Experiment (RME) as described for STS-74 (1995 061A):

• RME-1311: Relative Global Positioning System (GPSCON); 10. Developmental Test Objective (DTO) experiments as described for STS-1 (1981 034A):

• DTO-255: Wraparound DAP Flight Test Verification;





• DTO-700-11: Orbiter Space Vision System Flight Unit Testing;

• DTO-833: EMU Thermal Comfort and EVA Worksite Thermal Evaluation;

• DTO-840: Hand-Held Lidar Procedures; 11. Detailed Supplementary Objective (DSO) experiments as described for STS-1 (1981 034A):

• DSO-485: Inter-Mars Tissue Equivalent Proportional Counter;





• DSO-903: Documentary Still Photography. In addition Jernigan and Jones were to perform two EVAs of 6.5 hours each, during which they were to undertake space station assembly experiments, in particular a large manually operated crane to move equipment, new tether lines for astronauts and an improved portable work platform. A stuck air lock door prevented these EVAs, which were designated as Extravehicular Development Flight Test (EDFT)-5, from taking place. The landing was postponed twice, first due to dense fog over the Kennedy Space Centre, then due to high winds over Edwards. Eventually it landed at the Kennedy Space Centre after a flight of 17 days, 15 hours, 53 minutes.

1996 065B (24661) Name: Orfeus/SPAS-2 Country: USA Launch date: 20 November 1996 Re-entry: 4 December 1996 Launch site: Cape Canaveral Launch vehicle: STS + RMS


Retrievable scientific spacecraft as described for 1993 058C except that the remote sensing and IMAX cameras had been replaced by the ATV Rendezvous Pre-Development Project (ARP) and the Student Experiment on Astro SPAS (SEAS). It was deployed from STS-80 (1996 065A) on 20 November 1996 and retrieved on 4 December 1996.

1996 065C (24662) Name: WSF-3 Country: USA Launch date: 22 November 1996 Re-entry: 26 November 1996 Launch site: Cape Canaveral Launch vehicle: STS + RMS


Materials sciences spacecraft as described for 1995 048C. It was deployed from STS-80 (1996 065A) on 22 November 1996 and was 80 km ahead of Orfeus/SPAS-2 (1996 065B) with the Orbiter 30 km ahead of WSF-3. During the flight Orfeus/SPAS came closer to WSF-3 than was expected and whilst a collision was out of the question, it threatened the space the orbiter needed for recovery maneuvers. It was retrieved on 26 November 1996.

1996 066A (24663) Name: Progress M-33 Country: Russia Launch date: 19 November 1996 Re-entry: 12 March 1997 Launch site: Baikonour Launch vehicle: Soyuz U

Orbit: 255 x 308 km, inclination: 51.6° Cargo transfer spacecraft as described for 1989 066A. Progress M-33 docked with the rear port of the Mir/Kvant-1 space station (1986 017A) on 22 November 1996. Leading up to the docking of Soyuz TM-25 (1997 003A), the spacecraft was undocked from the rear port on 6 February 1997. It was intended to fly the spacecraft separately behind the space station until the Soyuz TM-24 (1996 047A) spacecraft had left the space station, early March. Progress M-33 was then to redock at the rear port using the TORU remotely operated rendez-vous system. Several attempts failed and the spacecraft was eventually allow to re-enter.

1996 067A (24665) Name: Hot Bird-2 Int. Agency: Eutelsat Launch date: 21 November 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas IIA


Communications satellite as described for 1995 016B but built by Matra Marconi using the Eurostar 2000 platform and fitted with 20 transponders operating in the Ku band. Also known as Eutelsat 2-7 and later became Eurobird-9 and Eutelsat W-48, when located at 48oE.In March 2012 it was renamed as Eutelsat 48-A.

1996 068A (24667) Name: Mars Pathfinder Country: USA Launch date: 4 December 1996 Re-entry: 4 July 1997 Launch site: Cape Canaveral Launch vehicle: Delta 7925 Orbit: trans-martian

The Mars Pathfinder was a 890 kg Mars exploration spacecraft consisting of a cruise vehicle, an entry vehicle and a lander. It was the second mission in NASA’s Discovery programme. The lander included the Mars Parthfinder Microrover, named Sojourner, a 11.5 kg vehicle which was 63 cm long, 48 cm wide and 31 cm high. The lander also carried: 1. Imager for Mars Pathfinder, a stereoscopic system to view the landing area; 2. the Alpha Proton X-ray Spectrometer (APXS), which determined elemental chemistry of the surface

materials 3. the Atmospheric Structure Instrument/Meteorological (ASI/MET) package which undertook

measurements during the entry descent and landing, incl. temperatures, pressure and wind sensors. It was also used after the landing as a meteorological station.

The spacecraft made a successful landing on Mars on 4 July 1997. The landing site was at Ares Valles, at app. 19o20’N, 33o55’W, an area which was initially targeted for the landing of Viking-1 (1975 075A), which was scheduled 21 years ago for 4 July 1976.

Sojourner

After the landing the Mars Pathfinder was renamed the Carl Sagan Memorial Station. The next day the Sojourner was released. Although intended to operate only for one week, Sojourner continued to operate until 27 September 1997, when contact was lost. The mission was formally terminated on 4 November 1997.

1996 069A (24670) Name: Kosmos-2335 Country: Russia Launch date: 11 December 1996 Re-entry: 1 January 1999 Launch site: Baikonour Launch vehicle: Tsyklon 2

Orbit: 403 x 417 km, inclination: 65.4° US-PU military ocean surveillance satellite fitted with electronic equipment as described for 1974 103A and 1993 029A.

1996 070A (24674) Name: Inmarsat 3-3 Int. Agency: Inmarsat Launch date: 18 December 1996 Re-entry: in orbit Launch site: Cape Canaveral Launch vehicle: Atlas IIA

Orbit: geostationary at 22°W Maritime communications satellite as described for 1996 020A.

1996 071A (24677) Name: Kosmos-2336 Country: Russia Launch date: 20 December 1996 Re-entry: in orbit Launch site: Plesetsk Launch vehicle: Kosmos 3M


1996 072A (24680) Name: Advanced KH 11-3 Country: USA Launch date: 20 December 1996 Re-entry: in orbit Launch site: Vandenberg Launch vehicle: Titan 404A

Orbit: 152 x 949 km, inclination: 97.9° Military reconnaissance satellite as described for 1992 083A. Also known as USA-129 and NROL-02. The orbit may have been modified at a later date. This was the first satellite launched for the National Reconnaissance Office (NRO) that was given a designation in the NROL series. The series was not in a strict sequential order of the launch and instead it is suspected that the designations were related to the order in which the spacecraft were procured.

1996 073A (24701) Name: Bion-11 Country: Russia Launch date: 24 December 1996 Re--entry: 7 January 1997 Launch site: Plesetsk Launch vehicle: Soyuz U

Orbit: 255 x 401 km, inclination: 62.8° Biological satellite as described for 1973 083A with a mass of 6000 kg. The satellite carried two rhesus monkeys, named Multik and Lapik, as well as a collection of bugs, newts, flies and snails, to test the effects of weightlessness. The satellite was successfully recovered but Multik died during post-flight experiments.

world spacecraft digest by jos heyman 1996 version: 6 … · a satellite in the shuttle pointed...

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