The Mars Orbiter Mission (MOM), also known as Mangalyaan, is an Indian Space Research Organisation (ISRO) spacecraft orbiting Mars since September 2014. It was launched in November 2013 aboard the Polar Satellite Launch Vehicle (PSLV) due to issues with ISRO's Geosynchronous Satellite Launch Vehicle (GSLV). The probe weighed 1,350 kg at launch and 500 kg dry, carrying scientific instruments to study the Martian surface, atmosphere, morphology, and mineralogy. On September 24, 2014, the spacecraft successfully entered Mars orbit using its liquid engine to slow down for orbital insertion.

1. Active learningassignment
Sub : physics
“Topic: Mars orbiter mission”
GuidedBy:Prof. niravsir
Branch : Electrical Engineering Div: F-1

2. Vrajesh raval(140120109047)
Ashutosh patel(140120109029)
Amar patel(140120109027)

3. The Mars Orbiter Mission
(MOM), also called
“Mangalyaan” is a spacecraft
orbiting mars since 24
September 2014.
It was launched on 5th
november 2013 by the indian
space and reaserch organisation
(ISARO).

5.  As originally conceived, ISRO would have
launched MOM on its geosynchronous
satellite launch vehicle (GSLV).
 but as the GSLV failed twice in 2010 and ISRO
was continuing to sort out issues with
its cryogenic engine .
 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.
 ISRO opted to switch to the less-powerful
Poler satellite launch vehicle (PSLV). There is
no way to launch on a direct-to-Mars
trajectory with the PSLV . ISRO would first
launch it into Earth orbit .

7.  The orbiter's dry mass is 500 kgand it carries
852 kg of fueland oxidiser.
 Its main engine uses the combination
bipropellant monomethy-drazine and dinitrogen
tetroxideto achive 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.

8.  Mass: The lift-off mass was 1,350 kg .Dry
mass is 500 kg. Payload mass is 150kg.
 Bus: The spacecraft's bus is a modified I-
1K structure and propulsion hardware
configuration, similar to Chandrayan 1.
 The satellite structure is constructed of an
aluminium and composite fibre reinforced
plastic (CFRP) sandwich construction.

9. Power: Electric power is generated by three solar
panels of 1.8 m × 1.4 m (5 ft 11 in × 4 ft 7 in) , for a
maximum of 840 watts of power generation in Mars
orbit. Electricity is stored in a 36 Ah Li-ion battery.
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. Its propellant mass is
852 kg.

10.  The MOM mission concept began with a feasibility study
in 2010, after the launch of lunar satellite Chandrayaan-
1 in 2008.
 The Government of India approved the project on 3
August 2012, after the Indian space reaserch
Organisation completed 125 crore (US$20 million) of
required studies for the orbiter.
 The total project cost maybe up to 454 crore(us$74million)
. The satellite costs 153 crore (US$25 million) and the rest
of the budget has been attributed to ground stations
and relay upgrades that will be used for other ISRO
projects.

13.  Simulated view of Mars Orbiter Mission along
with Mars, Earth, Mercury and Sun on 3 October
2014 at 17ː00 UTC. The Mars Orbiter Mission
satellite is at an altitude of about 1300 miles
from Mars at the time
 On 30 November 2013 at 19:19 UTC, a 23-minute
engine firing initiated the transfer of MOM away
from Earth orbit .
 The probe travelled a distance of 780,000,000
kilometres (480,000,000 mi) to reach Mars.

14.  The plan for an insertion into MARS ORBITER was
on 24 September 2014, approximately 2 days
after the arrival of NASA's MAVEN orbiter.
 The 440N liquid apogee motor was successfully
test fired on 22 September for 3.968 seconds,
about 41 hours before actual orbit insertion.
 At IST 06:56:32 forward rotation started and
locked the position to fire,and with the help of
thrusters after eclipse started at IST 07:12:19
and LAM (Liquid Apogee Motor) started burning
at IST 07:17:32 and ended at IST 07:41:46.
 After that reverse manoeuvre took place, the
spacecraft successfully entered Martian orbit.

15. PSLV(polar satellite launch
vehicle)
GSLV(geosynchronous
satellite launch vehicle)

16.  Incorporate autonomous features to handle
contingency situations.
 Deep space communication, navigation,
mission planning and management.
 Exploration of Mars surface features,
morphology, mineralogy and Martian
atmosphere by indigenous scientific
instruments.

17.  Thank you.