[Y.B.K] India's Mission To Mars Video By National Geography.mp4

India's Mission To Mars Video By National Geography

Mars Orbiter Mission
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This article is about the Indian Mars probe. For other Mars orbiters, see List of missions to Mars.
Mars Orbiter Mission
मंगलयान 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.gov.in/pslv-c25-mars-orbiter-mission
Mission duration Planned: 6 months[1]
Extension: 6 months[2]
Elapsed: 1 year, 9 months and 16 days
Spacecraft properties
Bus I-1K[3]
Manufacturer ISAC
Launch mass 1,337 kg (2,948 lb)[3]
BOL mass 550 kg (1,210 lb)[4]
Dry mass 500 kg (1,100 lb)
Payload mass 15 kg (33 lb)[5]
Dimensions 1.5 m (4.9 ft) cube
Power 840 watts[3]
Start of mission
Launch date 5 November 2013, 09:08 UTC[6]
Rocket PSLV-XL C25[7]
Launch site Satish Dhawan FLP
Contractor ISRO
Orbital parameters
Reference system Areocentric
Periareon 421.7 km (262.0 mi)[8]
Apoareon 76,993.6 km (47,841.6 mi)[8]
Inclination 150.0° [8]
Period 72 hours, 51 minutes, 51 seconds[8]
Epoch Planned
Mars orbiter
Orbital insertion 24 September 2014, 02:00 UTC
MSD 50027 06:27 AMT[9]

The Mars Orbiter Mission (MOM), also called Mangalyaan ("Mars-craft", from Sanskrit: मंगल mangala, "Mars" and यान yāna, "craft, vehicle"),[10][11] is a space probe orbiting Mars since 24 September 2014. It was launched on 5 November 2013 by the Indian Space Research Organisation (ISRO).[12][13][14][15] It is India's first interplanetary mission[16] and ISRO has become the fourth space agency to reach Mars, after the Soviet space program, NASA, and the European Space Agency.[17][18] It is the first Asian nation to reach Mars orbit, and the first nation in the world to do so in its first attempt.[19][20][21][22]

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.[23] The launch window was approximately 20 days long and started on 28 October 2013.[6] 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).[24] 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.[25] It carries five instruments that will help advance knowledge about Mars to achieve its secondary, scientific objective.[26] 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.[27]

Contents

1 History
1.1 Cost
2 Mission objectives
2.1 Primary objectives
2.2 Scientific objectives
3 Spacecraft specifications
4 Payload
5 Telemetry and command
5.1 Communications
6 Mission profile
6.1 Launch
6.2 Orbit raising manoeuvres
6.3 Trans-Mars injection
6.4 Trajectory correction manoeuvres
6.5 Mars orbit insertion
7 Status
8 Awards
9 Follow-up mission
10 See also
11 References
12 External links

History

On 23 November 2008, the first public acknowledgement of an unmanned mission to Mars was announced by then-ISRO chairman G. Madhavan Nair.[28] 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,[29] after the Indian Space Research Organisation completed ₹125 crore (US$19 million) of required studies for the orbiter.[30] The total project cost may be up to ₹454 crore (US$67 million).[12][31] 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.[32]

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.[6] Launch opportunities for a fuel-saving Hohmann transfer orbit occur every 26 months, in this case, 2016 and 2018.[33]

Assembly of the PSLV-XL launch vehicle, designated C25, started on 5 August 2013.[34] 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.[34] The satellite's development was fast-tracked and completed in a record 15 months.[35] Despite the US federal government shutdown, NASA reaffirmed on 5 October 2013 it would provide communications and navigation support to the mission.[36] 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.[37]
Cost

The total cost of the mission was approximately ₹450 Crore (US$73 million),[38][39] making it the least-expensive Mars mission to date.[40] 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.[41] BBC's Jonathan Amos mentioned lower worker costs, home-grown technologies, simpler design, and significantly less complicated payload than NASA's MAVEN.[26]
Mission objectives

The primary objective of the Mars Orbiter Mission is to showcase India's rocket launch systems, spacecraft building and operations capabilities.[42] Specifically, the primary objective is to develop the technologies required for designing, planning, management and operations of an interplanetary mission.[25] The secondary objective is to explore Mars' surface features, morphology, mineralogy and Martian atmosphere using indigenous scientific instruments.[42]
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:[43]: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:[43]: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.[43]:43
Spacecraft specifications

Mass: The lift-off mass was 1,350 kg (2,980 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.[42] 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.[3]
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.[44] Its propellant mass is 852 kg (1,878 lb).[3]

Payload
Scientific instruments
LAP Lyman-Alpha Photometer 1.97 kg (4.3 lb)
MSM Methane Sensor for Mars 2.94 kg (6.5 lb)
MENCA Mars Exospheric Neutral
Composition Analyser 3.56 kg (7.8 lb)
TIS Thermal Infrared Imaging Spectrometer 3.20 kg (7.1 lb)
MCC Mars Colour Camera 1.27 kg (2.8 lb)

The 15 kg (33 lb) scientific payload consists of five instruments:[5][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:[43]: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.[5] 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.[43]: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.[43]: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.[43]: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.[43]:58

Telemetry and command
Further information: Telemetry and Telecommand

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,[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.[3]
Mission profile
Timeline of Operations Phase Date Event Detail Result References
Geocentric phase 5 November 2013 09:08 UTC Launch Burn time: 15:35 min in 5 stages Apogee: 23,550 km (14,630 mi) [52]
6 November 2013 19:47 UTC Orbit raising manoeuvre Burn time: 416 sec Apogee: 28,825 km (17,911 mi) [53]
7 November 2013 20:48 UTC Orbit raising manoeuvre Burn time: 570.6 sec Apogee: 40,186 km (24,970 mi) [54][55]
8 November 2013 20:40 UTC Orbit raising manoeuvre Burn time: 707 sec Apogee: 71,636 km (44,513 mi) [54][56]
10 November 2013 20:36 UTC Orbit raising manoeuvre Incomplete burn Apogee: 78,276 km (48,638 mi) [57]
11 November 2013 23:33 UTC Orbit raising manoeuvre
(supplementary) Burn time: 303.8 sec Apogee: 118,642 km (73,721 mi) [54]
15 November 2013 19:57 UTC Orbit raising manoeuvre Burn time: 243.5 sec Apogee: 192,874 km (119,846 mi) [54][58]
30 November 2013, 19:19 UTC Trans-Mars injection Burn time: 1328.89 sec Successful heliocentric insertion [59]
Heliocentric phase December 2013 – September 2014 En route to Mars – The probe travelled a distance of 780,000,000 kilometres (480,000,000 mi) in a Hohmann transfer orbit[33] around the Sun to reach Mars.[49] This phase plan included up to four trajectory corrections if needed. [60][61][62][63][64]
11 December 2013 01:00 UTC 1st Trajectory correction Burn time: 40.5 sec Success [54][62][63][64]
9 April 2014 2nd Trajectory correction (planned) Not required Rescheduled for 11 June 2014 [61][64][65][66][67]
11 June 2014 11:00 UTC 2nd Trajectory correction Burn time: 16 sec Success [65][68]
August 2014 3rd Trajectory correction (planned) Not required[65][69] [61][64]
22 September 2014 3rd Trajectory correction Burn time: 4 sec Success [61][64][70]
Areocentric phase 24 September 2014 Mars orbit insertion Burn time: 1388.67 sec Success [8]
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