Mars Orbiter Mission

The Mars Orbiter Mission (MOM), also called Mangalyaan ("Mars-craft", from Sanskrit: मंगल mangala, "Mars" and यान yāna, "craft, vehicle"),^[9][10] is a space probe orbiting Mars since 24 September 2014. It was launched on 5 November 2013 by the Indian Space Research Organisation (ISRO).^{[11][12][13][14]} It is India's first interplanetary mission^[15] and ISRO has become the fourth space agency to reach Mars, after the Soviet space program, NASA, and the European Space Agency.^[16][17] It is the first Asian nation to reach Mars orbit, and the first nation in the world to do so in its first attempt.^{[18][19][20][21]}

The Mars Orbiter Mission probe lifted-off from the First Launch Pad at Satish Dhawan Space Centre (Sriharikota Range SHAR), Andhra Pradesh, using a Polar Satellite Launch Vehicle (PSLV) rocket C25 at 09:08 UTC on 5 November 2013.^[22] The launch window was approximately 20 days long and started on 28 October 2013.^[5] The MOM probe spent about a month in Earth orbit, where it made a series of seven apogee-raising orbital manoeuvres before trans-Mars injection on 30 November 2013 (UTC).^[23] After a 298-day transit to Mars, it was successfully inserted into Mars orbit on 24 September 2014.

The mission is a "technology demonstrator" project to develop the technologies for designing, planning, management, and operations of an interplanetary mission.^[24] It carries five instruments that will help advance knowledge about Mars to achieve its secondary, scientific objective.^[25] The spacecraft is currently being monitored from the Spacecraft Control Centre at ISRO Telemetry, Tracking and Command Network (ISTRAC) in Bangalore with support from Indian Deep Space Network (IDSN) antennae at Byalalu.^[26]

History

On 23 November 2008, the first public acknowledgement of an unmanned mission to Mars was announced by then-ISRO chairman G. Madhavan Nair.^[27] The MOM mission concept began with a feasibility study in 2010 by the Indian Institute of Space Science and Technology after the launch of lunar satellite Chandrayaan-1 in 2008. The government of India approved the project on 3 August 2012,^[28] after the Indian Space Research Organisation completed ₹125 crore (US$19 million) of required studies for the orbiter.^[29] The total project cost may be up to ₹454 crore (US$67 million).^[11][30] The satellite costs ₹153 crore (US$23 million) and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects.^[31]

The space agency had planned the launch on 28 October 2013 but was postponed to 5 November 2013 following the delay in ISRO's spacecraft tracking ships to take up pre-determined positions due to poor weather in the Pacific Ocean.^[5] Launch opportunities for a fuel-saving Hohmann transfer orbit occur every 26 months, in this case, 2016 and 2018.^[32]

Assembly of the PSLV-XL launch vehicle, designated C25, started on 5 August 2013.^[33] The mounting of the five scientific instruments was completed at Indian Space Research Organisation Satellite Centre, Bangalore, and the finished spacecraft was shipped to Sriharikota on 2 October 2013 for integration to the PSLV-XL launch vehicle.^[33] The satellite's development was fast-tracked and completed in a record 15 months.^[34] Despite the US federal government shutdown, NASA reaffirmed on 5 October 2013 it would provide communications and navigation support to the mission.^[35] During a meeting on 30 September 2014, NASA and ISRO officials signed an agreement to establish a pathway for future joint missions to explore Mars. One of the working group's objectives will be to explore potential coordinated observations and science analysis between the MAVEN orbiter and MOM, as well as other current and future Mars missions.^[36]

Cost

The total cost of the mission was approximately ₹450 Crore (US$73 million),^[37][38] making it the least-expensive Mars mission to date.^[39] The low cost of the mission was ascribed by K. Radhakrishnan, the chairman of ISRO, to various factors, including a "modular approach", few ground tests and long (18–20 hour) working days for scientists.^[40] BBC's Jonathan Amos mentioned lower worker costs, home-grown technologies, simpler design, and significantly less complicated payload than NASA's MAVEN.^[25]

Mission objectives

The primary objective of the mission is to develop the technologies required for designing, planning, management and operations of an interplanetary mission.^[24] The secondary objective is to explore Mars' surface features, morphology, mineralogy and Martian atmosphere using indigenous scientific instruments.^[41]

Primary objectives

The main objectives are to develop the technologies required for designing, planning, management and operations of an interplanetary mission comprising the following major tasks:^[42]:42

• Orbit manoeuvres to transfer the spacecraft from Earth-centred orbit to heliocentric trajectory and finally, capture into Martian orbit
• Development of force models and algorithms for orbit and attitude computations and analysis
• Navigation in all phases
• Maintain the spacecraft in all phases of the mission
• Meeting power, communications, thermal and payload operation requirements
• Incorporate autonomous features to handle contingency situations

Scientific objectives

The scientific objectives deal with the following major aspects:^[42]:43

• Exploration of Mars surface features by studying the morphology, topography and mineralogy
• Study the constituents of Martian atmosphere including methane and CO₂ using remote sensing techniques
• Study the dynamics of the upper atmosphere of Mars, effects of solar wind and radiation and the escape of volatiles to outer space

The mission would also provide multiple opportunities to observe the Martian moon Phobos and also offer an opportunity to identify and re-estimate the orbits of asteroids seen during the Martian Transfer Trajectory.^[42]:43

Spacecraft design

• Mass: The lift-off mass was 1,337.2 kg (2,948 lb), including 852 kg (1,878 lb) of propellant.^[3]
• Bus: The spacecraft's bus is a modified I-1 K structure and propulsion hardware configuration, similar to Chandrayaan-1, India's lunar orbiter that operated from 2008 to 2009, with specific improvements and upgrades needed for a Mars mission.^[41] The satellite structure is constructed of an aluminium and composite fibre reinforced plastic (CFRP) sandwich construction.
• Power: Electric power is generated by three solar array panels of 1.8 m × 1.4 m (5 ft 11 in × 4 ft 7 in) each (7.56 m² (81.4 sq ft) total), for a maximum of 840 watts of power generation in Mars orbit. Electricity is stored in a 36 Ah Lithium-ion battery.^[2]
• Propulsion: A liquid fuel engine with a thrust of 440 newtons is used for orbit raising and insertion into Mars orbit. The orbiter also has eight 22-newton thrusters for attitude control.^[43] Its propellant mass at launch is 852 kg (1,878 lb).^[2]

Payload

The 15 kg (33 lb) scientific payload consists of five instruments:^[44][45][46]

• Atmospheric studies:
  • Lyman-Alpha Photometer (LAP) – a photometer that measures the relative abundance of deuterium and hydrogen from Lyman-alpha emissions in the upper atmosphere. Measuring the deuterium/hydrogen ratio will allow an estimation of the amount of water loss to outer space. The nominal plan to operate LAP is between the ranges of approximately 3,000 km (1,900 mi) before and after Mars periapsis. Minimum observation duration for achieving LAP's science goals is 60 minutes per orbit during normal range of operation. The objectives of this instrument are as follows:^[42]:56,57
    • Estimation of D/H ratio
    • Estimation of escape flux of H2 corona
    • Generation of hydrogen and deuterium coronal profiles.
  • Methane Sensor for Mars (MSM) – will measure methane in the atmosphere of Mars, if any, and map its sources.^[44] MSM is designed to measure methane (CH₄) in the Martian atmosphere with parts-per-billion (ppb) accuracy and map its sources. Data is acquired only over illuminated areas as the sensor measures reflected solar radiation. Methane concentration in the Martian atmosphere undergoes spatial and temporal variations. Hence, global data are collected during every orbit. Since the field of view of MSM is limited, scanning is essential. Seven Apoareion Imaging scans of the entire disc, and Periareion Imaging are planned as it scans over the periareion in every orbit.^[42]:57
• Particle environment studies:
  • Mars Exospheric Neutral Composition Analyser (MENCA) – is a quadrupole mass analyser capable of analysing the neutral composition of particles in the range of 1–300 amu (atomic mass unit) with unit mass resolution. The heritage of this payload is from Chandra's Altitudinal Composition Explorer (CHANCE) payload aboard the Moon Impact Probe (MIP) in Chandrayaan-1 mission. MENCA is planned to perform five observations per orbit with one hour per observation.^[42]:58
• Surface imaging studies:
  • Thermal Infrared Imaging Spectrometer (TIS) – TIS measures the thermal emission and can be operated during both day and night. It would map surface composition and mineralogy of Mars and also monitor atmospheric CO₂ and turbidity (required for the correction of MSM data). Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement. Many minerals and soil types have characteristic spectra in TIR region. TIS can map surface composition and mineralogy of Mars.^[42]:59
  • Mars Colour Camera (MCC) – This tricolour camera gives images and information about the surface features and composition of Martian surface. It is useful to monitor the dynamic events and weather of Mars like dust storms/atmospheric turbidity. MCC will also be used for probing the two satellites of Mars, Phobos and Deimos. MCC would provide context information for other science payloads. MCC images are to be acquired whenever MSM and TIS data is acquired. Seven Apoareion Imaging of the entire disc and multiple Periareion images of 540 km × 540 km (340 mi × 340 mi) are planned in every orbit.^[42]:58

Telemetry and command

The ISRO Telemetry, Tracking and Command Network performed navigation and tracking operations for the launch with ground stations at Sriharikota, Port Blair, Brunei and Biak in Indonesia,^[47] and after the spacecraft's apogee became more than 100,000 km, an 18 m (59 ft) and a 32 m (105 ft) diameter antenna of the Indian Deep Space Network were utilised.^[48] The 18 m (59 ft) dish antenna was used for communication with the craft until April 2014, after which the larger 32 m (105 ft) antenna was used.^[49] NASA's Deep Space Network is providing position data through its three stations located in Canberra, Madrid and Goldstone on the US West Coast during the non-visible period of ISRO's network.^[50] The South African National Space Agency's (SANSA) Hartebeesthoek (HBK) ground station is also providing satellite tracking, telemetry and command services.^[51]

Communications

Communications are handled by two 230-watt TWTAs and two coherent transponders. The antenna array consists of a low-gain antenna, a medium-gain antenna and a high-gain antenna. The high-gain antenna system is based on a single 2.2-metre (7 ft 3 in) reflector illuminated by a feed at S-band. It is used to transmit and receive the telemetry, tracking, commanding and data to and from the Indian Deep Space Network.^[2]

Mission profile

Launch

As originally conceived, ISRO was to launch MOM on its Geosynchronous Satellite Launch Vehicle (GSLV),^[71] but as the GSLV failed twice in 2010 and ISRO was continuing to sort out issues with its cryogenic engine,^[72] it was not advisable to wait for the new batch of rockets as that would have delayed the MOM project for at least three years.^[73] ISRO opted to switch to the less-powerful Polar Satellite Launch Vehicle (PSLV). Since the PSLV was not powerful enough to place MOM on a direct-to-Mars trajectory, the spacecraft was launched into a highly elliptical Earth orbit and used its own thrusters over multiple perigee burns (to take advantage of the Oberth effect) to place itself on a trans-Mars trajectory.^[71]

On 19 October 2013, ISRO chairman K. Radhakrishnan announced that the launch had to be postponed by a week as a result of a delay of a crucial telemetry ship reaching Fiji. The launch was rescheduled for 5 November 2013.^[5] ISRO's PSLV-XL placed the satellite into Earth orbit at 09:50 UTC on 5 November 2013,^[29] with a perigee of 264.1 km (164.1 mi), an apogee of 23,903.6 km (14,853.0 mi), and inclination of 19.20 degrees,^[52] with both the antenna and all three sections of the solar panel arrays deployed.^[74] During the first three orbit raising operations, ISRO progressively tested the spacecraft systems.^[58]

The orbiter's dry mass is 500 kg (1,100 lb), and it carried 852 kg (1,878 lb) of fuel and oxidiser at launch. Its main engine, which is a derivative of the system used on India's communications satellites, uses the bipropellant combination monomethylhydrazine and dinitrogen tetroxide to achieve the thrust necessary for escape velocity from Earth. It was also used to slow down the probe for Mars orbit insertion and, subsequently, for orbit corrections.

Orbit raising manoeuvres

Orbit trajectory diagram (not to scale).

Several orbit raising operations were conducted from the Spacecraft Control Centre (SCC) at the ISRO Telemetry, Tracking and Command Network (ISTRAC) at Peenya, Bangalore on 6, 7, 8, 10, 12 and 16 November by using the spacecraft's on-board propulsion system and a series of perigee burns. The first three of the five planned orbit raising manoeuvres were completed with nominal results, while the fourth was only partially successful. However, a subsequent supplementary manoeuvre raised the orbit to the intended altitude aimed for in the original fourth manoeuvre. A total of six burns were completed while the spacecraft remained in Earth orbit, with a seventh burn conducted on 30 November to insert MOM into a heliocentric orbit for its transit to Mars.

The first orbit-raising manoeuvre was performed on 6 November 2013 at 19:47 UTC when the spacecraft's 440-newton (99 lb_f) liquid engine was fired for 416 seconds. With this engine firing, the spacecraft's apogee was raised to 28,825 km (17,911 mi), with a perigee of 252 km (157 mi).^[53]

The second orbit raising manoeuvre was performed on 7 November 2013 at 20:48 UTC, with a burn time of 570.6 seconds resulting in an apogee of 40,186 km (24,970 mi).^[54][55]

The third orbit raising manoeuvre was performed on 8 November 2013 at 20:40 UTC, with a burn time of 707 seconds resulting in an apogee of 71,636 km (44,513 mi).^[54][56]

The fourth orbit raising manoeuvre, starting at 20:36 UTC on 10 November 2013, imparted an incremental velocity of 35 m/s (110 ft/s) to the spacecraft instead of the planned 135 m/s (440 ft/s) as a result of underburn by the motor.^[57][75] Because of this, the apogee was boosted to 78,276 km (48,638 mi) instead of the planned 100,000 km (62,000 mi).^[57] When testing the redundancies built-in for the propulsion system, the flow to the liquid engine stopped, with consequent reduction in incremental velocity. During the fourth orbit burn, the primary and redundant coils of the solenoid flow control valve of 440 newton liquid engine and logic for thrust augmentation by the attitude control thrusters were being tested. When both primary and redundant coils were energised together during the planned modes, the flow to the liquid engine stopped. Operating both the coils simultaneously is not possible for future operations, however they could be operated independently of each other, in sequence.^[58]

As a result of the fourth planned burn coming up short, an additional unscheduled burn was performed on 12 November 2013 that increased the apogee to 118,642 km (73,721 mi),^[54][58] a slightly higher altitude than originally intended in the fourth manoeuvre.^[54][76] The apogee was raised to 192,874 km (119,846 mi) on 15 November 2013, 19:57 UTC in the final orbit raising manoeuvre.^[54][76]

Trans-Mars injection

On 30 November 2013 at 19:19 UTC, a 23-minute engine firing initiated the transfer of MOM away from Earth orbit and on heliocentric trajectory toward Mars.^[23] The probe travelled a distance of 780,000,000 kilometres (480,000,000 mi) to reach Mars.^[77]

Trajectory correction manoeuvres

Four trajectory corrections were originally planned, but only three were carried out.^[61] The first trajectory correction manoeuvre (TCM) was carried out on 11 December 2013 at 01:00 UTC by firing the 22-newton (4.9 lb_f) thrusters for a duration of 40.5 seconds.^[54] After this event, MOM was following the designed trajectory so closely that the trajectory correction manoeuvre planned in April 2014 was not required. The second trajectory correction manoeuvre was performed on 11 June 2014 at 11:00 UTC by firing the spacecraft's 22 newton thrusters for a duration of 16 seconds.^[78] The third planned trajectory correction manoeuvre was postponed, due to the orbiter's trajectory closely matching the planned trajectory.^[79] The third trajectory correction was also a deceleration test 3.9 seconds long on 22 September 2014.^[70]

Mars orbit insertion

The plan was for an insertion into Mars orbit on 24 September 2014,^[7][80] approximately 2 days after the arrival of NASA's MAVEN orbiter.^[81] The 440-newton liquid apogee motor was successfully test fired on 22 September at 09:00 UTC for 3.968 seconds, about 41 hours before actual orbit insertion.^[80][82][83]

After these events, the spacecraft performed a reverse manoeuvre to reorient from its deceleration burn and successfully entered Martian orbit.^[8][84][4]

Status

The orbit insertion put MOM in a highly elliptical orbit around Mars, with a period of 72 hours 51 minutes 51 seconds, a periapsis of 421.7 km (262.0 mi) and apoapsis of 76,993.6 km (47,841.6 mi).^[8] At the end of the orbit insertion, MOM was left with 40 kg (88 lb) of fuel on board, more than the 20 kg (44 lb) necessary for a six-month mission.^[85]

On 28 September 2014, MOM controllers published the spacecraft's first global view of Mars. The image was captured by the Mars Colour Camera (MCC).^[86]

On 7 October 2014, the ISRO altered MOM's orbit so as to move it behind Mars for Comet Siding Spring's flyby of the planet on 19 October 2014. The spacecraft consumed 1.9 kg (4 lb) of fuel for the manoeuvre. As a result, MOM's apoapsis was reduced to 72,000 km (45,000 mi).^[87] After the comet passed by Mars, ISRO reported that MOM remained healthy.^[88]

On 4 March 2015, the ISRO reported that MOM's methane sensors were functioning normally and are studying Mars' albedo, the reflectivity of the planet's surface. The Mars Colour Camera was also returning new images of the Martian surface.^[89][90]

On 24 March 2015, MOM completed its initial six-month mission in orbit around Mars. ISRO extended the mission by an additional six months; the spacecraft has 37 kg (82 lb) of propellant remaining and all five of its scientific instruments are working properly.^[91] The orbiter can reportedly continue orbiting Mars for several years with its remaining propellant.^[92]

A 17-day communications blackout occurred from 6 to 22 June 2015 while Mars' orbit took it behind the Sun from Earth's view.^[42]:52

On 24 September 2015, ISRO released its "Mars Atlas", a 120-page scientific atlas containing images and data from the Mars Orbiter Mission's first year in orbit.^[93]

In March 2016, the first science results of the mission were published in Geophysical Research Letters, presenting measurements obtained by the spacecraft's MENCA instrument of the Martian exosphere.^[94][95]

Recognition

The Mars Orbiter Mission team won US-based National Space Society's 2015 Space Pioneer Award in the science and engineering category. NSS said the award was given as the Indian agency successfully executed a Mars mission in its first attempt; and the spacecraft is in an elliptical orbit with a high apoapsis where, with its high resolution camera, it is taking full-disk colour imagery of Mars. Very few full disk images have ever been taken in the past, mostly on approach to the planet, as most imaging is done looking straight down in mapping mode. These images will aid planetary scientists.^[96][97][98]

An illustration of the Mars Orbiter Mission spacecraft is featured on the reverse of the ₹2,000 currency note of India.^[99]

Follow-up mission

ISRO plans to develop and launch a follow-up mission called Mangalyaan 2 with a greater scientific payload to Mars by 2020.^[100] The mission will consist of an orbiter, and will not include a lander or rover as suggested earlier.^[101] Mangalyaan 2 will be launched after the Chandrayaan 2 Moon mission scheduled for December 2018.

See also

• Department of Space
• ExoMars Trace Gas Orbiter
• List of ISRO missions
• List of Mars orbiters
• List of missions to Mars
• Mars Express

References

External links

Wikimedia Commons has media related to Mars Orbiter Mission.

• Mars Orbiter Mission website
• Mars Orbiter Mission brochure

Spacecraft missions to Mars
Current	Orbiters ExoMars Trace Gas Orbiter Mars Express Mars Orbiter Mission Mars Reconnaissance Orbiter MAVEN 2001 Mars Odyssey Rovers Curiosity Timeline Opportunity Observations
Past	Flybys Dawn Mariner 4 Mariner 6 Mariner 7 Mars 1† Mars 6 Mars 7 Nozomi† Rosetta Zond 2† Orbiters Mariner 9 Mars 2 Mars 3 Mars 4† Mars 5† Mars Climate Orbiter† Mars Global Surveyor Mars Observer† Phobos program Phobos 1† Phobos 2† Viking program Viking 1 Viking 2 Landers Beagle 2† ExoMars Schiaparelli† Mars 2† Mars 3† Mars 6† Mars 7† Mars Pathfinder Mars Polar Lander† / Deep Space 2† Phoenix Viking 1 Viking 2 Rovers Prop-M† Sojourner Spirit Observations Special Zond 3 (crossed Mars orbit)
Failed at launch	Fobos-Grunt / Yinghuo-1 Kosmos 419 1M No.1 1M No.2 2MV-4 No.1 2MV-3 No.1 Mariner 3 2M No.521 2M No.522 Mariner 8 Mars 96
Planned	InSight / Mars Cube One (2018) Red Dragon (2018) ExoMars (rover) / ExoMars 2020 surface platform (2020) Mangalyaan 2 (2020) Mars Hope (2020) Mars 2020 (2020) 2020 Chinese Mars Mission (2020)
Proposed	BOLD Icebreaker Life Inspiration Mars Mars 2022 Mars Geyser Hopper Mars-Grunt Mars One Mars sample return mission MELOS rover MetNet Northern Light PADME Phootprint SCIM Sky-Sailor
Cancelled / concepts	ARES Astrobiology Field Laboratory Beagle 3 Mars 4NM & 5NM Mars 5M (Mars-79) Mars-Aster Mars Astrobiology Explorer-Cacher Mars Surveyor Lander Mars Telecommunications Orbiter NetLander Vesta Voyager
Related	Features and artificial objects on Mars Features and memorials on Mars
† indicates failure en route or before intended mission data returned.

2013 in space
Launches	Space probes LADEE Mars Orbiter Mission MAVEN Chang'e 3 Yutu Space observatories IRIS Hisaki Gaia
Impact events	Chelyabinsk meteor Chelyabinsk meteorite
Novae	Nova Centauri 2013 V339 Delphini
Comets	C/2011 L4 (PANSTARRS) C/2012 F6 (Lemmon) C/2012 K1 (PANSTARRS) C/2012 S1 (ISON) C/2013 A1 (Siding Spring) P/2013 P5 (PANSTARRS) C/2013 R1 (Lovejoy)
NEOs	(7888) 1993 UC (52760) 1998 ML14 (285263) 1998 QE2 (163364) 2002 OD20 (277475) 2005 WK4 2006 BL8 2011 BT15 2012 YQ1 2013 EC 2013 ET 2013 MZ5 2013 PJ10 2013 TV135 2013 XY8 2013 YP139 367943 Duende 3361 Orpheus
Exoplanets	DENIS-P J082303.1-491201 b Gliese 504 b Gliese 667 Cd Gliese 667 Ce Gliese 667 Cf Gliese 667 Cg Gliese 667 Ch HD 106906 b HD 95086 b Kepler-37b Kepler-37c Kepler-37d Kepler-61b Kepler-62b Kepler-62c Kepler-62d Kepler-62e Kepler-62f Kepler-65 Kepler-66 Kepler-67 Kepler-68b Kepler-68c Kepler-68d Kepler-69b Kepler-69c Kepler-76b Kepler-78b Kepler-87c PSO J318.5-22 ROXs 42Bb
Others	Asteroid close approaches GRB 130427A Hercules–Corona Borealis Great Wall Herschel Space Observatory retiring The Day the Earth Smiled
Category:2012 in space — Category:2013 in space — Category:2014 in space

2014 in space
Space probes	Chang'e 5-T1 (Moon mission launched) Hayabusa 2 PROCYON (asteroid mission launched) Venus Express (Venus mission ends) Dawn (approaches 1 Ceres) Rosetta/Philae (orbits/landing 67P/Churyumov–Gerasimenko)
Impact events	2014 AA impact 2014 Ontario fireball
Supernovae	SN 2014J
Notable comets	C/2012 K1 (PANSTARRS) C/2013 A1 (Siding Spring) (Mars close approach) C/2013 R1 (Lovejoy) C/2013 V5 (Oukaimeden) C/2014 E2 (Jacques) C/2014 Q2 (Lovejoy)
NEOs	Asteroid close approaches 2000 EM26 (163132) 2002 CU11 (388188) 2006 DP14 2007 VK184 (410777) 2009 FD 2009 RR 2009 WM1 2014 AF5 2014 DX110 2014 EC 2014 HQ124 2014 LY21 2014 OO6 2014 RC 2014 SC324 2014 XL7
Exoplanets	51 Eridani b Gliese 15 Ab Gliese 180 c Gliese 682 c Gliese 832 c HIP 116454 b Kapteyn b Kepler-186f Kepler-296e Kepler-296f Kepler-298d Kepler-419b Kepler-419c Kepler-421b GU Piscium b
Discoveries	Rings of Chariklo 2012 VP113 2013 FY27 C/2014 E2 (Jacques) 2014 OL339 (quasi-satellite of Earth)
Deep space rendezvous	MAVEN (Mars orbit injection) Mars Orbiter Mission (Mars orbit injection)
Category:2013 in space — Category:2014 in space — Category:2015 in space

Indian space programme
Indian Space Research Organisation (ISRO)
Organisations	Department of Space (DoS) Antrix Corporation Indian Institute of Space Science and Technology (IIST) Indian Institute of Remote Sensing (IIRS) Laboratory for Electro-Optics Systems (LEOS) National Atmospheric Research Laboratory (NARL) Physical Research Laboratory (PRL) Physical Research Laboratory (DECU)
Programmes	Bhaskara GAGAN GSAT INSAT IRNSS IRS Cartosat RISAT Rohini SROSS Chandrayaan Human spaceflight programme Orbital Vehicle
Spacecraft	One-off missions APPLE Aditya Aryabhata Astrosat HAMSAT IMS-1 Megha-Tropiques NISAR SARAL SAARC Satellite SRE SRE II Kalpana-1 CARE Planetary missions Chandrayaan-1 Chandrayaan-2 Mars Orbiter Mission Mangalyaan 2 Venus orbiter mission
Rockets	Orbital SLV ASLV PSLV GSLV GSLV Mk.III Suborbital Rohini ATV Concepts ULV Under development RLV-TD
Facilities	Indian Deep Space Network (IDSN) ISRO Satellite Centre (ISAC) ISRO Telemetry, Tracking and Command Network (ISTRAC) Master Control Facility (MCF) Satish Dhawan Space Centre (SDSC) Thumba Equatorial Rocket Launching Station (TERLS) ISRO Satellite Integration and Testing Establishment (ISITE)
See also	SAGA-220
List of Indian satellites List of Satish Dhawan Space Centre launches List of ISRO missions