 Space technology : The study of space called astronomy.

 Nehru was the first PM to promote space research in India

 Indian Na onal Commi ee for Space Research (INCOSPAR), set up by the Government of
India in 1962
 INCOSPAR name changed to ISRO in 1969
 ISRO Estb. In 1969
 DOS(Department of space) was set up and ISRO was brought under DOS in 1972

IMORTANT POINTS:
1962 INCOSPAR
1965 SSTC (space science technology centre)
1969 ISRO
1971 SDSC (Sa sh Dhawan space centre)
1975 Aryaba a
1979 Baskara
1980 Rohini 1st ar ficial satellite
1981 INSAT
1984 Rakesh Sharma
(1st person go into the space from India) On this journey to the space
sta on Salyut 7, two Soviet
h ps://artsandculture.google.com/story/rakesh-
sharma/qgVRNmrdDkh0FQ?hl=en cosmonauts, commander Yury
Malyshev and flight engineer
Gennady Strekalov accompanied
him
1993 PSLV

2001 GSLV

2008 Chandrayan 1 Madavan 6th

2013 MOM 9th
2019 Chandrayan 2 Sivam 10th
2023 Chandrayan 3 , Adiya L1, Somanath 11th
2024 XPoSat Somanath 11th

1 Dr. Vikram Ambalal Sarabhai GJ

2 M G K Menon KA
3 Sa sh Dhawan J&K  100th birth anniversary in 2023
 Longest service as a chairman 12yr
4 Udupi Ramachandra Rao KA
5 Dr K Kasturirangan KL
6 G Madhavan Nai KL
7 K. Radhakrishnan KL
8 Sailesh Nayar GJ Short me served 12 days
9 A S Kiran Kumar KA
10 K Sivan TN Chandrayan 2
 11 S. Somanath KL Chandrayan 3 , Aditya L1 , Xposat
12 V. Narayan TN

 Management of ISRO--- DOS(Department of space)

 Supervisor of Indian space – PM
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VSSC , Thiruvananthapuram Launch Vehicles are built Old name: SSTC(Space science
(Vikram Sarabhai Space Centre) technology centre)
 URSC, Bengaluru Satellites are designed and
(U R Rao Satellite Centre) developed
SDSC , Sriharikota Integra on and launching of Since 2012 onwards its called
(Sa sh Dhawan Space Centre) satellites and launch vehicles SDSC
LPSC , Valimala Bengaluru Development of liquid stages
(Liquid Propulsion Systems including cryogenic stage
Centre)
SAC , Ahmadabad Sensors for Communica on
(Space Applica ons Centre) and Remote Sensing satellites
and applica on aspects of the
space technology
NRSC , HYD Remote Sensing satellite data
(Na onal Remote Sensing recep on processing
Centre)
LPSC , Thiruvanthapuram design, development and
(Liquid Propulsion Systems realisation of liquid
Centre) propulsion
IPRC , Mahendragiri TN assembly, integration and
ISRO Propulsion Complex testing of earth storable
propellant engines,
cryogenic engines and
stages for launch vehicles
NARL , Tirupa atmospheric research for Metrological day march 31th
( National Atmospheric metrological 2024 theme: the front line of
Research Laboratory) climate ac on

NESAC , Umiam Meghalaya

(North Eastern-Space
Applications Centre)
IIST , KL
(Indian Institute of Space
Science and Technology)
NSIL , Bengaluru
(New Space India Limited)

Lunch vehicles:
SLV 1980 Weight=17 ton
Height=22m
1ST India’s Payload capacity=40kg
experimental Orbit = LEO
satellite Propulsion =4 stages solid
ASLV 1987 W=39 ton
Auraminted sat H=23.5m
lunching vehicle Payload= 150kg
Orbit= LEO
4 Stages solid
PSLV 1993 W=294 ton Variants: 2023-2024:
H=44m PSLVG -general standard
Mass= 320 ton version - 4 stage 6 startup
*1st India’s liquid Payload = 1000kg min and boosters. *PSLV-C60/SpaDeX
propulsion launch 1800kg max PSLV CA core alone - sun Mission
vehicle. 4 stages with alterna ve of solid synchronous orbit -no
*Workhorse of ISRO and liquid startup boosters. *PSLV-C59/Proba-3
stages in PSLV-- PSLV XL -extra-large - Mission
stage1 solid: motor= s-139 present used mostly
Stage 3 solid motor= s7 PSLV HP - hyper *PSLV-C58 / XPoSat
Fuel = HTPB performance - LEO - Mission
(hydroxyl terminated 6 startup boosters
polybutadiene) PSLV 3S - three stages- 6 *PSLV-C57/Aditya-L1
oxidiser ammonium perchloride startup boosters Mission
stage2 liquid: Vikas engine PSLV DS defence sector -
Stage 4 liquid used for defence purpose *PSLV-C56/DS-SAR
Storable engine Mission
Fuel =USDH (unsymmetrical
dimethylhydrazine) *PSLV-C55/TeLEOS-2
oxidizer—DNTO dinitrozen Mission
tectodiser

GSLV 2001 3 stages GSLV Variants:

Solid GSLV Mark 1 *GSLV-F14/INSAT-
Liquid 2 3DS Mission
Cryogenic 3/LVM3:
Payload weight – 3000kg * GSLV-F12/NVS-01
Like GSLV other Height--- 49m Weight : 4000kg Mission
countries lunch Weight—414 tonnes *Three stage vehicles with
vehicles: Orbit --- GSO two solid strap-on motors LVM3 Previous
Deltra 2 ---USA (S200) – 204 tonnes. missions:
Long march ---china one liquid core stage (L110)
Arian 4 --- EU ---115 tonnes * LVM3 M4 /
epsilon ---- Japan cryogenic upper stage Chandrayaan-3
Soyaz ---Russia (C25) --- 28 tonnes. Moon Mission
The overall length of the
vehicle is 43.5 m with a LVM3 M3 / OneWeb
gross li -off weight of 640 India-2 Mission
tonnes and a 5m-diameter
payload fairing. LVM3 M2 / OneWeb
India-1 Mission

LVM3 - M1 /
Chandrayaan-2
Mission
SSLV *3 stage Launch Vehicle configured
with three Solid Propulsion Stages *SSLV-D3/EOS-08
and liquid propulsion-based Mission
Velocity Trimming Module (VTM)
as a terminal stage.
*SSLV is 2m in diameter * SSLV-D2/EOS-07
*Length---34m MISSION
*Weight of ~120 tonnes.
*SSLV is capable of launching
~500kg satellite in 500km planar
orbit from SDSC/SHAR
RLV-DT

PSLV-C60/SpaDeX *PSLV-C60 is the first Vehicle integrated upto PS4

Mission stage at PIF and moved to MST/FLP for Satellites
assembly and Launch.
18th core alone

PSLV-C59/Proba-3 *PSLV-C59 vehicle will carry Proba-3 spacecra

Mission into a highly ellip cal orbit as a Dedicated
commercial mission of New Space India Limited
*Date: dec 2 (NSIL).
*Proba-3 is an In-Orbit Demonstra on (IOD)
*First lunch pad at mission of the European Space Agency.
SDSC-SHAR *The mission goal is to demonstrate precise
forma on flying.
*PSLV XL 26TH *It consists of 2 spacecra s viz.
PSLV 61ST the Coronagraph Spacecra (CSC) and the
Occulter Spacecra (OSC) and it will be launched
together in a stacked configura on
PSLV-C58 / XPoSat * XPoSat (X-ray Polarimeter Satellite) is the first
Mission dedicated scien fic satellite from ISRO to carry
out research in space-based polarisa on
Date: Jan 1 2024
Rocket : PLSV DL (4th) measurements of X-ray emission from celes al
and 60th PSLV sources.
Payload: XPoSat payloads :
Vehicle Height= 44.4 m POLIX (Polarimeter Instrument in X-rays)
Li -off Mass =260 t *POLIX is realized by Raman Research Ins tute
Propulsion Stages= XSPECT (X-ray Spectroscopy and Timing).
First Stage 2PSOM-XL+ * XSPECT is by Space Astronomy Group of URSC.
S139
Second Stage PL40(HP)
Third Stage HPS3
Fourth Stage L1.6(Ti)
PSLV-C57/Aditya-L1 Payloads = 7 ASPEX (Aditya Solar wind
Mission VELC : (Visible Emission Line Coronagraph) Par cle Experiment)
* Study solar corona and dynamics of coronal *ASPEX is developed at
*Mission type =solar mass ejec ons. Physical Research
observa on *Developed by Indian Ins tute of Astrophysics, Laboratory, Ahmedabad.
*operator =ISRO Bengaluru. PAPA(Plasma Analyser
*dura on =5.2 yr SUIT : (Solar Ultra-violet Imaging Telescope) Package for Aditya)
*manif=ISRO , IUCAA * To image the Solar Photosphere and *To study the solar wind
Pune ,IIA Bengaluru Chromosphere in near Ultra-violet (UV) and, to and energe c ions, as well
*lunch date sep 2023 measure the solar irradiance varia ons in near as their energy
*reached L1 point jun UV. distribu on.
6 2024 *Developed by Inter University Centre for *PAPA is developed at
*mass=1475kg Astronomy and Astrophysics, Pune. Space Physics Laboratory,
*sensors W – 24.4kg SoLEXS : (Solar Low Energy X-ray Spectrometer) VSSC,Thiruvananthapuram.
*rocket – PSLV XL HEL1OS :(High Energy L1 Orbi ng X-ray MAG (Magnetometer)
*Project director – Spectrometer) *measuring interplanetary
Nigar Shaji are designed to study the X-ray flares from the magne c fields at the L1
Sun over a wide X-ray energy range. Both these point.
payloads are developed at U R Rao Satellite *Developed at Laboratory
Centre, Bengaluru. for Electro Op cs Systems,
Bengaluru.

PSLV-C56/DS-SAR * PSLV-C56 carrying DS-SAR satellite, along with 6 5.Galassia-2, a 3U

Mission co-passengers from the first launch-pad of SDSC- nanosatellite that will be
SHAR, Sriharikota. orbi ng at low earth orbit.
* The DS-SAR satellite is developed under a 6.ORB-12 STRIDER ,
Date: July 30th 2023 partnership between DSTA (represen ng the satellite is developed
Payload: DS-SAR Government of Singapore) and ST Engineering. under an interna onal
Site: Sriharikota * DS-SAR carries a Synthe c Aperture Radar (SAR) collabora on
payload developed by Israel Aerospace Industries
(IAI)
The co-passengers are:
1.VELOX-AM,
2.ARCADE Atmospheric Coupling and Dynamics
Explorer
3.SCOOB-II , a 3U nanosatellite flying a technology
demonstrator payload
4.NuLIoN by NuSpace, an advanced 3U
nanosatellite enabling seamless IoT connec vity
in both urban & remote loca ons
PSLV-C55/TeLEOS-2 *PSLV-C55 is a Dedicated Commercial PSLV *Vehicle Height= 44.4 m
Mission mission of New Space India Limited (NSIL), for the *Li off Mass =228.355 t
interna onal satellite customer from Singapore. *Propulsion Stages
Date: April 22 2023 First Stage S139
*In this mission, TeLEOS-2 a Synthe c Aperture
Second Stage PL40
Payload :TeLEOS-2 Radar satellite will be the primary satellite and Third Stage HPS3(7.6 t)
Lumelite-4 a Technology Demonstra on nano- Fourth Stage L1.6(0.8 t)
satellite will be co-passenger satellite. (Ti)
* The TeLEOS-2 satellite is developed under a
partnership between DSTA (represen ng the
Government of Singapore) and ST Engineering.
* TeLEOS-2 will be able to provide all-weather day
and night coverage, and capable of imaging at 1m
full-polarimetric resolu on.
*This is the 57th flight of PSLV and 16th mission
using the PSLV Core Alone configura on (PSLV-
CA). *PSLV-C55 adopted “Integrate, Transfer and
Launch (ITL)” concept using PSLV Integra on
Facility (PIF).
GSLV-F14/INSAT-3DS * Aims at deploying the INSAT-3DS *Vehicle Height 51.7 m
Mission meteorological satellite into the Geosynchronous *Li off mass 420 t Stages
Transfer Orbit (GTO). 3
Date: February 17,
*The first stage (GS1) comprises a solid propellant *First Stage (GS1)
2024
(S139) motor having 139-ton propellant and four S139+4L40H
Payload : INSAT-3DS earth-storable propellant stages (L40) strapons *Second Stage (GS2)
which carry 40 tons of liquid propellant in each. GL40HT
16th mission of GSLV *The second stage (GS2) is also an earth-storable *Third Stage (GS3) CUS 15
and 10th flight with propellant stage loaded with 40-ton propellant. (Indigenous)
Indigenous Cryogenic *The third stage (GS3) is a cryogenic stage with a *Three-stage 51.7 m long
stage.
15-ton propellant loading of liquid oxygen (LOX) launch vehicle having a
7th opera onal flight of and liquid hydrogen (LH2). li off mass of 420 tonnes.
GSLV with indigenous *During the atmospheric regime, the Satellite is
Cryogenic stage. protected by Ogive payload fairing.

From SDSC-SHAR, * Various departments of the Ministry of Earth

Sriharikota. Sciences (MoES) such as
India Meteorology Department (IMD),
Na onal Centre for Medium-Range Weather
Forecas ng (NCMRWF),
Indian Ins tute of Tropical Meteorology (IITM),
Na onal Ins tute of Ocean Technology (NIOT),
Indian Na onal Centre for Ocean Informa on
Services (INCOIS)
will be using the INSAT-3DS Satellite data to
provide improved weather forecasts and
meteorological services
GSLV-F12/NVS-01 * The configura on of GSLV-F12 Payload Fairing is Vehicle Height 51.7 m Li
Mission 4 m dia Ogive version. off Mass 420 t Stages 3
*Weight : 2232kg First Stage (GS1)
Date: May 29, 2023 *Payloads opera ng in L1, L5 and S bands S139+4L40H Second Stage
(GS2) GL40HT Third Stage
15th flight of India’s *Orbit: Geosynchronous Transfer Orbit. (GS3) CUS 15 (Indigenous)
GSLV and the 9th flight *Launch : Second Launch Pad (SLP) at SDSC-SHAR
with Indigenous
Cryogenic stage. *6th opera onal flight of GSLV with indigenous
Cryogenic stage.

SSLV-D3/EOS-08 *SSLV-D3 is the third developmental flight of SSLV. *Satellites = Agency

MISSION *Mission objec ves: EOS-08 = URSC, ISRO,
1. Demonstra on of repeatable flight SR-0 DEMOSAT =Space
*Date: Aug 16 ,2024
performance of SSLV Vehicle Systems. Kidz India
*Orbit: Circular LEO 2. Injec on of EOS-08 satellite and SR-0
DEMOSAT passenger satellite into 475 km circular
*Mission life :1 year orbit.
*EOS-08 carries three payloads: Electro Op cal
Infrared Payload (EOIR), Global Naviga on
Satellite System-Reflectometry payload (GNSS-R),
and SiC UV Dosimete
* The EOIR payload is designed to capture images
in the Mid-Wave IR (MIR) and Long-Wave IR
(LWIR) bands, both during the day and night, for
applica ons such as satellite-based surveillance,
disaster monitoring, environmental monitoring,
fire detec on, volcanic ac vity observa on, and
industrial and power plant disaster monitoring
*GNSS-R-based remote sensing for applica ons
such as ocean surface wind analysis, soil moisture
assessment, cryosphere studies over the
Himalayan region, flood detec on, and inland
waterbody detec on.
*The SiC UV Dosimeter monitors UV irradiance at
the viewport of the Crew Module in the
Gaganyaan Mission and serves as a high-dose
alarm sensor for gamma radia on
SSLV-D2/EOS-07 *Demonstra on of designed
MISSION
* Payload capability of SSLV in LEO
Date :Feb 10 2023

Orbit : LEO
 *Injec on of EOS-07 satellite and two passenger
satellites Janus-1 & AzaadiSAT-2 into 450 km
circular orbit.

* EOS-07 ---ISRO
Janus-1 --- ANTARIS ,USA
AzaadiSAT-2 ---space kidz India (combined effort
of about 750 girl students across India guided by
Space Kidz India, Chennai)

Gaganyaan Payloads : Ins tu ons :

1. HRL(Human Rated LVM3) 1.HAL,Bengaluru ---
Other names: Gi 2. OM(Orbital Module) CM,CES
mission/sky OM is equipped with state-of-the-art 2.DRDO ---Human centric
cra /Human space avionics systems with adequate system
flight
redundancy considering human safety. 3.HAL+DRDO+ISRO –
Announced ;2018  Crew Module (CM) Structure of the mission
Date : 2024/25 Earth like environment in space 4. Yuri Gagarin Cosmonaut
for the crew. Training Centre, Russia
Project cost : 10,000cr.  Service Module (SM) 5. Astronaut Training
providing necessary support to Facility, USA ---physical
Rocket : LVM3 M4/ fitness, yoga, micro
CM while in orbit and containing
GSLV MARK 3/HSLV gravity(Charles brown
thermal system, propulsion
effect)
system, power systems, avionics
6. Defence food research
systems and deployment
laboratory, Mysore
mechanisms.
3. CES(Crew Escape System)
*The four astronaut- 4. LSS(life suppor ng system)
designates are
Prasanth Balakrishnan
Nair, Different Phases:
Ajit Krishnan, Tes ng phase:
Angad Pratap, and
Wing Commander o Integrated Air Drop Test (IADT)
Shubhanshu Shukla o Pad Abort Test (PAT)
o Test Vehicle (TV) flights: The Test Vehicle is
a single-stage liquid rocket developed for
this abort mission.

Unmanned missions: It will be for technology

Other countries like demonstra on, safety and reliability verifica on
Gaganayan missions: and will be heavily instrumented to study the
USA—NASA performance of systems before crewed flight.
ASC(Aerial space Some advanced tests are:
cra )/Aeteris-1
Robots—HELga, Johar o Airdrop test
o Water Survival Test Facility (WSTF): ISRO,
along with the Indian Navy carried out
WSTF to ini al recovery trials of Crew
Module in Feb 2023. The trials were part of
the prepara on for crew module recovery
opera ons.
o Vyom Mitra: The ‘female’ robot astronaut
the humanoid designed and developed ISRO
to fly aboard unmanned test missions
before the Gaganyaan human space-flight
mission.

Manned mission: Human spaceflight module of

Gaganyaan will be followed by the two unmanned
missions.

OSIRIS-REX Mission *OSIRIS-REx is the first U.S. mission to collect a *Mission Design and
sample from an asteroid. Management--
(Origins Spectral *It returned to Earth on Sept. 24, 2023, to drop NASA's Goddard Space
Interpreta on
off a capsule with material from asteroid Bennu. Flight Centre / University
Resource Iden fica on
Security Regolith *A er dropping off the sample through Earth's of Arizona
Explorer) atmosphere, the spacecra was renamed OSIRIS- *Launch Vehicle---
APEX and sent on a new mission to explore Atlas V 411 (no. AV-067)
Life me : 7 years asteroid Apophis in 2029 *Launch Date and Time--
* 60 grams sample from 101955 bunny aseriod Sept. 8, 2016 / 23:05 UT
*Launch Site---
Cape Canaveral, Fla. / SLC-
41
NISAR Mission * NASA-ISRO SAR (NISAR) is a Low Earth Orbit
(LEO) observatory being jointly developed by
Mission type: Radar NASA and ISRO.
imaginary system

Dura on: 3 years * It carries L and S dual band Synthe c Aperture

Radar (SAR).
Lunch date: sep 24 ,
2023 *G S L V Mark III lunch vehicle
*Understand climate change , natural disaster,
Site: SDSC measure the earth ocean ground levels, volcanics,
tsunami
Payloads: L- band
(produced by NASA),
S- band (by ISRO)
Project cost: 12,150cr.

NAVIC *IRNSS
Naviga on with Indian *India 6th country a er usa eu china Russia Japan
consulta on *total 7 sat to send
SDSC
*last rocket : PSLV C 33
MCF(Muster control of
facili es , hassan , * LAST DATE: June 28 2016
bengulore) *
Rocket:PSLV C22
July 1 2013
Sat name:IRNSS 1A

MOM Distance : 78cr km

Weight : 1339kg
Date: NOV 5 2013 Payloads
*Lyman Alpha Photometer (LAP)
Rocket : PSLV C25
*Methane Sensor for Mars (MSM)
Site : SDSC *Mar an Exospheric Neutral Composi on
first lunch pad Explorer (MENCA)
*Mars Colour Camera (MCC)
COST : 450cr *TIR Imaging Spectrometer (TIS).

Chandrayan 3 Chandrayan 2 Chandrayan 1

Lunch date: 14 JULY 2023 22 JULY 2019 22 OCT 2008
23 AUG 2023 08 NOV 2008
NATIONAL SPACE DAY
Weight: 3900kg 3850kg 1380kg

Height 43.5m 44.5m

Density 4m
Li of mass 640 ton 320 ton
Orbit Lunar orbit
Stages 3 stages S200 solid rocket First stage:
Two straps on rocket boosters PS1 (S139+PSOM-XL)
boosters HTPB Solid
Two Vikas engines L110 liquid stage Propellant
Cryogenic engine
C25 upper stage Second stage
PS2 (PL40),
UH25+N,O,, Liquid
3 Space Probes: Propellant
Orbitor(1444kg)
lifespan = 7.5yr Third stage
(working me 2yr 8 HPS3 HTPB Solid
months 22 days) Propellant

Fourth stage
 Lander and rover = PS4 (L2.5),
14 days MMH+MoN3 Liquid
Propellant
Power genera on *Propulsion Module: 758 W*Manjinus
Symphiloous
*Lander Module: 738W, WS between these
with Bias mountains the
chandrayan 2 rover
*Rover: 50W land

Payloads: Propulsion module Orbiter payloads -- 8 11

(2148kg) =1 ISRO 5
1.Terrain Mapping 1.Terrain Mapping
SHAPE(Spectro-polarimetry Camera 2 (TMC 2) Camera (TMC)
of HAbitable Planet Earth) 2.Chandrayaan-2 2.Hyper Spectral
*Payload to study the Large Area So X-ray Imager (HySI)
Spectro-polarimetric Spectrometer 3.Lunar Laser
signatures of the habitable (CLASS) Ranging Instrument
planet Earth in the near- 3.Solar X-ray Monitor (LLRI)
infrared (NIR) wavelength (XSM) 4.High Energy X - ray
range (1-1.7 μm). 4.Orbiter High Spectrometer (HEX)
Resolu on Camera 5.Moon Impact
Lander (Vikram) (1752kg)=4 (OHRC) Probe(MIP)
RAMBHA(Radio Anatomy of 5.Imaging IR
Moon Bound Spectrometer (IIRS) NASA 2
Hypersensi ve ionosphere 6.Dual Frequency 1. Moon Mineralogy
and Atmosphere) Synthe c Aperture Mapper (M3)
*To measure the near Radar (DFSAR) 2. Miniature
surface plasma (ions and 7.Chandrayaan 2 Synthe c Aperture
electrons) density and its Atmospheric Radar (Mini SAR)
changes with me. Composi onal EUA 3
CHaSTE(Chandra’s Surface Explorer 2 (CHACE 2) 1.Chandrayaan-I X-
Thermo physical 8.Dual Frequency ray Spectrometer
Experiment) Radio Science (DFRS) (CIXS)
*Carry out the experiment 2.Near Infrared
measurements of thermal Spectrometer (SIR -
proper es of lunar surface 2)
near polar region. 3.Sub keV Atom
ILSA(Instrument for Lunar Reflec ng Analyzer
Seismic Ac vity) (SARA)
*To measure seismicity
around the landing site and BULGERIA 1
delinea ng the structure of 1.Radia on Dose
the lunar crust and mantle. Monitor (RADOM)
LRA(Laser Retroreflector
Array)
* It is a passive experiment
to understand the dynamics
of Moon system
 Rover (Pragyan)=2
LIBS(Laser Induced
Breakdown Spectroscope)
*To determine the
elemental composi on
(Mg, Al, Si, K, Ca,Ti, Fe) of
lunar soil and rocks around
the lunar landing site.
APXS(Alpha Par cle X-Ray
Spectrometer)
*To derive the chemical
composi on and infer
mineralogical composi on
to further enhance our
understanding of lunar
surface.
Site: SDSC SDSC SDSC
Second lunch pad
Rocket : LVM3 M4 LVM3 M4 PSLV C11
Landing point Shivashak point Teranga point
name:
*World 1st mission in South
pole and 4th in so -landing
on moon
(US,Russia,China,IND,Japan)
*14 days = 1 lunar day = 14
earth days
* Propulsion Module:
Communicates with IDSN
*Lander Module:
Communicates with IDSN
and Rover. Chandrayaan-2
Orbiter is also planned for
con ngency link.
*Rover: Communicates only
with Lander

Project cost: 613cr 978cr 386cr

Project director Mission director : Mohan Mu ayavanitha
Kumar
Project director : Mission director:
Veeramuthuvel Ritulearidhal
Deputy PD ; chain Da a
tejpur
Associa on PD : Kalapana
(Chi oor district)
VSSC Director: S
Unnikrishnan Nair
URSC Director : M Sankaran
Phases: The various mission phases
are classified as follows:
 1. Earth Centric Phase
(Phase-1)
Pre-launch Phase
Launch and Ascent Phase
Earth-bound Manoeuvre
Phase
2. Lunar Transfer Phase
(Phase-2)
Transfer Trajectory Phase
3. Moon Centric Phase
Lunar Orbit Inser on Phase
(LOI)-(Phase-3)
Moon-bound Manoeuvre
Phase (Phase-4)
PM and Lunar Module
Separa on (Phase-5)
De-boost Phase (Phase-6)
Pre-landing Phase (Phase-7)
Landing Phase (Phase-8)
Normal Phase for Lander
and Rover (Phase-9)
Moon Centric Normal Orbit
Phase
(100 km circular orbit) - For
Propulsion Module (Phase-
10)