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Mars Orbiter Mission From Wikipedia, the free encyclopedia This article is about the Indian Mars probe. For other Mars orbiters, see List of missions to Mars. Mars Orbiter Mission Mars Orbiter Mission - India - ArtistsConcept.jpg Artist's rendering of the MOM orbiting Mars Mission type	Mars orbiter Operator	ISRO COSPAR ID	2013-060A SATCAT №	39370 Website	www.isro.org/mars/home.aspx Mission duration	300 days Spacecraft properties Bus	I-1K[1] Manufacturer	ISAC Launch mass	1,337 kg (2,948 lb)[2] Dry mass	500 kg (1,100 lb)[3] Payload mass	15 kg (33 lb)[4] Dimensions	1.5 metres (4 ft 11 in) cube Power	840 watts[1] Start of mission Launch date	5 November 2013, 09:08 UTC[5] Rocket	PSLV-XL C25[6] Launch site	Satish Dhawan FLP Contractor	ISRO Orbital parameters Reference system	Areocentric Periareon	365.3 km (227.0 mi) Apoareon	80,000 km (50,000 mi) Inclination	150.0 [7] Period	76.72 hours Epoch	Planned Mars orbiter Orbital insertion	24 September 2014[8] (Planned) The Mars Orbiter Mission (MOM), informally called Mangalyaan (Sanskrit: मंगलयान, "Mars-Craft"), is a Mars orbiter that was successfully launched into Earth orbit on 5 November 2013 by the Indian Space Research Organisation (ISRO).[9][10][11] The mission is a "technology demonstrator" project aiming to develop the technologies required for design, planning, management and operations of an interplanetary mission.[12] The Mars Orbiter Mission probe lifted-off from the First Launch Pad at Sriharikota, Andhra Pradesh near Chennai, using a Polar Satellite Launch Vehicle (PSLV) rocket C25 at 09:08 UTC (2:38 PM IST) on 5 November 2013.[13] The launch window was approximately 20 days long and started on 28 October 2013.[5] It is India's first interplanetary mission and if successful, ISRO would become the fourth space agency to reach Mars, after the Soviet space program, NASA, and European Space Agency.[14] The MOM probe is currently in Earth orbit where it is in a month-long process of making six altitude-raising orbital manoeuvres before a planned insertion into a heliocentric Mars transfer orbit on 1 December 2013. Contents [hide] 1 History 2 Current status 2.1 Orbit raising manoeuvres 3 Objectives 4 Spacecraft 5 Payload 6 Launch, transfer and orbit 7 Tracking and command 8 See also 9 References 10 External links History[edit]

The MOM mission began with a feasibility study in 2010, after the successful launch of lunar satellite Chandrayaan-1 in 2008.[15] The government of India approved the project on 3 August 2012,[16] after the Indian Space Research Organisation completed INR125 crore (US$19 million) of required studies for the orbiter.[17] The total project cost may be up to INR454 crore (US$69 million).[9][18] The satellite costs INR153 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.[19] The space agency had initially planned the launch on 28 October 2013 but was postponed to 5 November 2013 following the inability of 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 about every 26 months, in this case, 2016 and 2018.[20] The Mars Orbiter's on-orbit mission life will be between six and ten months. Assembly of the PSLV-XL launch vehicle, designated C25, started on 5 August 2013.[21] The integration of the five scientific instruments was completed at ISRO Satellite Centre, Bangalore, and the finished spacecraft was shipped to Sriharikotta on 2 October 2013.[21] The satellite's development was fast-tracked and completed in a record 15 months.[22] Despite the U.S. federal government shutdown, NASA reaffirmed on 5 October 2013 it would provide communications and navigation support to the mission.[23] P. Kunhikrishnan was the PSLV-XL spacecraft launch Mission Director. Mylswamy Annadurai is the Program Director and Subbiah Arunan is the Project Director. S. K. Shivkumar of ISAC was responsible for the orbiting payload and also oversaw design and development of the orbiter.[24] Current status[edit]

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 Islands. The launch was rescheduled for 5 November 2013.[25] The PSLV rocket successfully lifted off at 09:08 UTC (2:38 p.m. IST), and placed the satellite into Earth orbit at 09:50 UTC,[26] with a perigee of 264.1 km, an apogee of 23,903.6 km, and inclination of 19.20 degrees,[27] with both the antenna and all three sections of the solar panel arrays being deployed.[28] During the first three orbit raising operations, ISRO has progressively tested the autonomy functions of the spacecraft that are essential for trans-Mars injection and Mars orbit insertion.[29] The systems tested satisfactorily are: The prime and redundant chains of gyros and accelerometers. Liquid motor attitude control thrusters. Attitude, orbit control electronics and associated logics for their fault detection isolation, and reconfiguration. Functioning of the prime and redundant star sensors. Orbit raising manoeuvres[edit] Orbit-raising burns Date	Burn time Resulting apogee (Km) 5 November (Launch)	15:35 min in 5 stages[30]	23,903 6 November	416 s	28,825 7 November	570.6 s	40,186 8 November	707 s	71,636 10 November	Incomplete	78,276 12 November (Supplementary)	303.8 s	118,642 [31] 16 November	243.5 s	192,874 Several orbit raising operations were conducted from the Spacecraft Control Centre (SCC) at ISRO Telemetry, Tracking and Command Network (ISTRAC) at Peenya, Bangalore on 6, 7, 8, 10, 11, 12 and 16 November by using the spacecraft's on-board propulsion system and Earth flybys for gravity assist. The aim is to gradually build up the necessary escape velocity (11.2 km/s) to break free from Earth's gravitational pull while using minimal fuel. The first three orbit raising manoeuvres were successfully completed, while the fourth was only partially successful. However, the subsequent supplementary manoeuvre raised the orbit to the intended altitude aimed for in the original fourth manoeuvre. First orbit raising The first orbit-raising manoeuvre was performed in 6 November 2013 at 19:47 UTC when the 440 Newton liquid engine of the spacecraft was fired for 416 seconds. With this engine firing, the spacecraft's apogee was raised to 28,825 km, while its perigee is at 252 km.[32] Second orbit raising The second orbit raising manoeuvre, starting at 20:48:51 UTC on 7 November 2013, with a burn time of 570.6 seconds has been successfully completed. The resulting apogee was 40,186 km.[31][33] Third orbit raising The third orbit raising manoeuvre, starting at 20:40:43 UTC on 8 November 2013, with a burn time of 707 seconds was successfully completed. The apogee was increased to 71,636 km.[31][34] Fourth orbit raising The fourth orbit raising manoeuvre, starting at 20:36 UTC on 10 November 2013, only imparted an incremental velocity of 35 m/s to the spacecraft instead of the planned 135 m/s as a result of underburn by the liquid apogee motor.[35][36] Because of this, the apogee was boosted to 78,276 km instead of the planned 100,000 km.[35] 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.[29] Supplemental burn An unscheduled supplemental burn was performed on 12 November 2013 that successfully increased the apogee to 118,642 km,[29][31] the apogee originally intended to be obtained in the fourth manoeuvre. Fifth orbit raising The apogee was raised in 16 November to 192,874 km in this final orbit raising manoeuvre.[37][31] Objectives[edit]

The primary objective of the Mars Orbiter Mission is to showcase India's rocket launch systems, spacecraft-building and operations capabilities.[38] Specifically, the primary objective is to develop the technologies required for design, planning, management and operations of an interplanetary mission, comprising the following major tasks:[12] Design and realisation of a Mars orbiter with a capability to perform Earth-bound manoeuvres, cruise phase of 300 days, Mars orbit insertion / capture, and on-orbit phase around Mars. Deep-space communication, navigation, mission planning and management. Incorporate autonomous features to handle contingency situations. The secondary objective is to explore Mars' surface features, morphology, mineralogy and Martian atmosphere using indigenous scientific instruments.[38] Spacecraft[edit]

India's PSLV launch vehicle The spacecraft structure and propulsion hardware configurations are similar to Chandrayaan 1, India's first successful robotic lunar orbiter that operated from 2008 to 2009, with specific improvements and upgrades needed for a Mars specific mission.[38] Mass The lift-off mass was 1,350 kg (2,980 lb), including 852 kg (1,878 lb) of propellant mass. Dimensions Cuboid in shape of approximately 1.5 m (4 ft 11 in) Bus The spacecraft's bus is a modified I-1 K structure and propulsion hardware configurations similar to Chandrayaan 1, India's successful lunar orbiter that operated from 2008 to 2009, with specific improvements and upgrades needed for a Mars mission.[38] The satellite structure is of aluminum and composite fiber reinforced plastic (CFRP) sandwich construction. Power Electric power is generated by three solar array panels of 1.8 × 1.4 m (5 ft 10 in × 4 ft 7 in) each (7.56 m2 (81.4 sq ft) total), for a maximum of 840 W generation in Martian orbit. Electricity is stored in a 36 Ah Li-ion battery.[1] Propulsion Liquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit. Communications Two 230 W 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 meter 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.[1] Payload[edit]

The 15 kg (33 lb) scientific payload consists of five instruments:[4][39][40] 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 the amount of water loss to outer space to be estimated. Methane Sensor For Mars (MSM) — will measure methane in the atmosphere of Mars, if any, and map its sources.[4] Particle environment studies Mars Exospheric Neutral Composition Analyzer (MENCA) — is a quadrupole mass analyzer capable of analyzing the neutral composition of particles in the exosphere. Surface imaging studies Thermal Infrared Imaging Spectrometer (TIS) — will measure the temperature and emissivity of the Martian surface, allowing for the mapping of surface composition and mineralogy of Mars. Mars Color Camera (MCC) — will provide images in the visual spectrum, providing context for the other instruments. Launch, transfer and orbit[edit]

The ISRO used its PSLV-XL (Polar Satellite Launch Vehicle) rocket to launch the Mars Orbiter Mission.[17] The launch, on 5 November 2013, placed the Mars Orbiter Mission into Earth orbit. Six orbit raising operations were conducted on 6, 7, 8, 10, 11 and 16 November by using the craft's on-board propulsion system, which is a derivative of the system used on India's communications satellites.[41][42] These manoeuvres raised the orbit to one with an apogee of 192,000 km (119,000 mi) and perigee of 252 km (157 mi),[43][44] where it will remain for about 15 days.[8][45] A firing on 1 December 2013 will send MOM onto an interplanetary trajectory.[8][46][47] Mars orbit insertion is planned for 24 September 2014,[8] and would allow the spacecraft to enter a highly elliptical orbit with a period of 76.72 hours and a periapsis of 365.3 km (227.0 mi) and apoapsis of 80,000 km (50,000 mi) around Mars.[44] The Mars Orbiter will have to travel a distance of 780 million kilometers (484 million miles) to reach Mars.[48] The spacecraft's dry mass is 500 kg (1,100 lb), and it carries 852 kg (1,878 lb) of fuel and oxidiser. The main engine uses the bipropellant combination monomethylhydrazine and dinitrogen tetroxide to achieve the thrust necessary for escape velocity from Earth, and later, to slow the probe for Mars orbit insertion and subsequently for orbit corrections.[3] The probe is expected to arrive in Mars orbit in September 2014 approximately at the same time as NASA's MAVEN orbiter.[49] Tracking and command[edit]

The Indian Space Research Organisation 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,[50] and after the spacecraft's apogee becomes more than 100,000 km, two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised.[51] NASA's Deep Space Network will provide position data through its three stations located in Canberra, Madrid and Goldstone on the U.S. West Coast during the non-visible period of ISRO's network.[52] Additional monitoring is provided by technicians on board two leased ships from Shipping Corporation of India, SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific near Fiji