REPORT
ON
Satellite Launch Vehicles and their Types
Shaikh Saahil Ahamed EJ/12
Kasim
EJ/13
Lecturer. Khan Aadil
(AIARKP) KALSEKAR POLYTECHNIC INSTITUTE .
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Breif Description on Satellite Launch Vehicles and their Types :
1.
A launch vehicle or carrier rocket is a rocket-propelled vehicle used to carry a payload from
Earth's surface to space, usually to Earth orbit or beyond. A launch system includes the
launch vehicle, launch pad, vehicle assembly and fuelling systems, range safety, and other
related infrastructure.
2.
Orbital launch vehicles can be grouped based on many different factors, most notably
payload mass, although price points are a major concern for some users. Most launch
vehicles have been developed by or for national space programs, with considerable national
prestige attached to spaceflight accomplishments. Payloads include crewed spacecraft,
satellites, robotic spacecraft, scientific probes, landers, rovers, and many more.
3.
Orbital spaceflight is difficult and expensive, with progress limited by the underlying
technology as much as human and societal factors.
4.
Satellite launch vehicles are used to place the satellites in their specific orbits. The function
of this vehicle is based on Newton’s third law of motion. ISRO has developed PSLV [ polar
satellite launch vehicle ].
5.
It consists of an engine which uses solid fuel that provides initial thrust which provides
certain velocity and takes it to certain height. There are four stages which uses solid and
liquid fuel alternatively.
6.
Once the first stage fuel is used up the engine and first stage gets detached from the main
body and falls into sea or unpopulated land. The weight got reduced and it moves with more
high speed. Once the fuel in first stage is exhausted the fuel in second stage is ignited and so
on.
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Types of Satellite Launch Vehicle :
1.
2.
3.
4.
5.
6.
7.
8.
Sounding Rockets
Satellite Launch Vehicle (SLV)
Augmented Satellite Launch Vehicle (ASLV)
Polar Satellite Launch Vehicle (PSLV)
Geosynchronous Satellite Launch Vehicle (GSLV)
Geosynchronous Satellite Launch Vehicle MK3 (GSLV Mk 3)
Reusable Launch Vehicle – Technology Demonstrator (RLV-TD)
Scramjet Engine
Sounding Rockets :
Sounding rockets are usually one or two-stage solid propellant rockets. They are primarily intended
for probing the upper atmospheric regions using rocket-borne instrumentation. They also serve as
platforms for testing prototypes of new components or subsystems intended for use in launch
vehicles and satellites.
The launch of the first sounding rocket US-made ‘Nike Apache’ from Thumba near
Thiruvananthapuram, Kerala on November 21, 1963, marked the beginning of the Indian Space
Programme.
In 1965, ISRO started launching a series of our own sounding rockets named Rohini from TERLS. RH75, with a diameter of 75mm was the first truly Indian sounding rocket, which was followed by RH100 and RH-125 rockets.
The sounding rocket program was indeed the bedrock on which the edifice of launch vehicle
technology was built. The experience gained was of immense value in the mastering of solid
propellant technology and allied systems of the launch vehicles. Several scientific missions with
national and international participation have been conducted using the Rohini sounding rockets.
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Satellite Launch Vehicles [SLV] :
The Satellite Launch Vehicle (SLV) project was born out of the need for achieving indigenous satellite
launch capability for communications, remote sensing and meteorology.
The Satellite Launch Vehicle-3 (SLV-3) was India’s first experimental satellite launch vehicle, which
was an all solid, four-stage vehicle weighing 17 tonnes. It had a height of 22m and it was capable of
placing 40 kg class payloads in Low Earth Orbit (LEO).
The first experimental flight of SLV3, in August 1979, was only partially successful. The next launch
on July 18, 1980, from Sriharikota Range (SHAR), successfully placed Rohini satellite, RS-1, into orbit,
thereby making India the sixth member of an exclusive club of space-faring. Apart from the July
1980 launch, there were two more launches held in May 1981 and April 1983, orbiting Rohini
satellites carrying remote sensing sensors.
The successful culmination of the SLV-3 project showed the way to advanced launch vehicle projects
such as the Augmented Satellite Launch Vehicle (ASLV), Polar Satellite Launch Vehicle (PSLV), and
the Geosynchronous Satellite Launch Vehicle (GSLV).
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Augmented Satellite Launch Vehicle (ASLV):
Augmented Satellite Launch Vehicle (ASLV) was developed to act as a low-cost intermediate vehicle
to demonstrate and validate critical technologies. With a lift-off weight of 40 tonnes, the 23.8 m tall
ASLV was configured as a five-stage, all-solid propellant vehicle, with a mission of orbiting 150 kg
class satellites into 400 km circular orbits. The strap-on stage consisted of two identical 1m
diameter solid propellant motors, Under the ASLV program, four developmental flights were
conducted.
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The first developmental flight took place on March 24, 1987,
and the second on July 13, 1988.
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ASLV-D3 was successfully launched on May 20, 1992, when SROSS-C (106 kg) was put into an orbit of
255 x 430 km.
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ASLV-D4 launched on May 4, 1994, orbited SROSS-C2 weighing 106 kg. It had two payloads, Gamma
Ray Burst (GRB) Experiment and Retarding Potential Analyser (RPA), and functioned for seven
years.
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ASLV provided valuable inputs for further development.
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Polar Satellite Launch Vehicle (PSLV) :
Polar Satellite Launch Vehicle (PSLV) is the third generation launch vehicle of India. It is the first
Indian launch vehicle to be equipped with liquid stages. PSLV has four stages using solid and liquid
propulsion systems alternately.
After its first successful launch in October 1994, PSLV emerged as the reliable and versatile
workhorse launch vehicle of India with 39 consecutively successful missions by June 2017.
During the 1994-2017 period, the vehicle has launched 48 Indian satellites and 209 satellites for
customers from abroad. Besides, the vehicle successfully launched two spacecraft – Chandrayaan-1
in 2008 and Mars Orbiter Spacecraft in 2013 – that later traveled to Moon and Mars respectively.
PSLV earned its title “the workhorse of ISRO” through consistently delivering various satellites to
Low Earth Orbits, particularly the IRS series of satellites.
It can take up to 1,750 kg of payload to sun-synchronous polar orbits of 600 km altitude. Due to its
unmatched reliability, PSLV has also been used to launch various satellites into Geosynchronous and
Geostationary orbits, like satellites from the IRNSS constellation. The PS4 is the uppermost stage of
PSLV, comprising of two Earth storable liquid engines.
Launched Missions → Chandrayaan-1, Mars Orbiter Mission, Space Capsule Recovery Experiment,
IRNSS, Astrosat.
Vehicle Variants and Launch Capability
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PSLV-Generic
PSLV-Core Alone
PSLV XL
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PSLV-Generic
No. of Solid Strap-ons : Six (9T)
Payload capability to SSPO (600 km) : 1550 kg
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PSLV – Core Alone
No. of Solid Strap-ons: NIL
Payload capability to SSPO (600 km) : 1100 Kg
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PSLV XL
No. of Solid Strap-ons: Six (12T)
Payload capability o SSPO (600 Km) : 1700 kg
Payload capability o sub GTO (284 x 20650 km) 1425 Kg
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Geosynchronous Satellite Launch Vehicle (GSLV) :
Geosynchronous Satellite Launch Vehicle (GSLV) is capable of placing 2 ton class of satellites like the
INSAT and GSAT series of communication satellites into Geosynchronous Transfer Orbit (GTO).
Geosynchronous Satellite Launch Vehicle Mark-II (GSLV Mk II) is the largest launch vehicle developed
by India, which is currently in operation. This fourth-generation launch vehicle GSLV Mk-II has the
capability to launch satellites of lift-off mass of up to 2,500 kg to the GTO and satellites of up to 5,000
kg lift-off mass to the LEO.
GSLV Mk-II is a 49 m tall, three stage vehicle with a lift-off mass of 416 ton.
The first stage comprises of a S139 solid booster with four liquid strap-on motors, each weighing 40
tons.
The second stage (GS2) is a liquid engine carrying 37.5 tons of liquid propellant.
The third stage is the indigenously built Cryogenic Upper Stage (CUS) which uses typically 15 tons of
cryogenic propellants (Liquid Hydrogen (LH2) as fuel and Liquid Oxygen (LOX) as Oxidiser).
Vehicle Versions
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GSLV Mk-I : (Russian Cryogenic)
GSLV Mk-II : (Indigenous Cryogenic)
GSLV Mk-III : (Indigenous Cryogenic)
Cryogenic rocket engine – Fuel or oxidizer (or both) is gases liquefied and stored at very low
temperatures.
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Geosynchronous Satellite Launch Vehicle MK3 (GSLV Mk 3) :
The Geosynchronous Satellite Launch Vehicle Mark III (GSLV MkIII) also known as LVM3, is the next
generation launcher being developed by ISRO for achieving self-reliance in the launch of 4 ton class
of communication satellites to Geosynchronous Transfer Orbits (GTO).
GSLV Mk-III is a 43.43 m tall three stage vehicle with a lift-off mass of 640 tones.
The launcher is designed to be a versatile launcher to launch payloads to other orbits as well and
will have a payload capability in excess of 10 tons to Low Earth Orbits (LEO). Once GSLV-MkIII
becomes operational, India would be able to dispense the procured launches for 4-ton class
communication satellites.
The powerful cryogenic stage of GSLV Mk III enables it to place heavy payloads into Low Earth Orbits
of 600 km altitude. The Cryogenic Upper Stage (C25) is powered by CE-20, India’s largest cryogenic
engine, designed and developed by the Liquid Propulsion Systems Centre. GSLV Mk III uses two S200
solid rocket boosters to provide the huge amount of thrust required for lift off. The S200 was
developed at Vikram Sarabhai Space Centre.
It will allow India to achieve complete self-reliance in launching satellites as –
It will be capable of placing 4-tonne class Geosynchronous satellites into GTO
It will be capable of placing 8-tonne class satellites into LEO
Significance of GSLV MK3
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GSLV will cost just one-third of the money spent on foreign agencies, which will reduce satellite
launch cost as well as will save Forex
It will enhance India’s capability to be a competitive player in the multimillion-dollar commercial
launch market. It will help in earning foreign exchange.
The GSLV will help ISRO put heavier communication satellites of GSAT class into orbit.
Reduction of dependence on foreign agencies gives a strategic boost in this high tech sector
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Reusable Launch Vehicle – Technology Demonstrator (RLV-TD) :
Reusable Launch Vehicle – Technology Demonstrator (RLV-TD) is one of the most technologically
challenging endeavours of ISRO towards developing essential technologies for a fully reusable
launch vehicle to enable low-cost access to space.
The configuration of RLV-TD is similar to that of an aircraft and combines the complexity of both
launch vehicles and aircraft.
The winged RLV-TD has been configured to act as a flying testbed to evaluate various technologies,
namely, hypersonic flight, autonomous landing, and powered cruise flight. In the future, this vehicle
will be scaled up to become the first stage of India’s reusable two-stage orbital launch vehicle.
RLV-TD consists of a fuselage (body), a nose cap, double delta wings, and twin vertical tails. It also
features symmetrically placed active control surfaces called Elevons and Rudder. This technology
demonstrator was boosted to Mach no: 5 by a conventional solid booster (HS9) designed for low burn
rate.
The selection of materials like special alloys, composites, and insulation materials for developing
an RLV-TD and the crafting of its parts is very complex and demands highly skilled manpower. Much
high technology machinery and test equipment were utilized for building this vehicle.
Objectives of RLV-TD:
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Hypersonic aero thermodynamic characterisation of wing body;
Evaluation of autonomous Navigation, Guidance and Control (NGC) schemes;
Integrated flight management;
Thermal Protection System Evaluation;
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Scramjet Engine :
The satellites are launched into orbit by multi-staged satellite launch vehicles that can be used only
once i.e. they are expendable. These launch vehicles carry oxidiser along with the fuel for combustion
to produce thrust.
Launch vehicles designed for one time use are expensive and their efficiency is low because they can
carry only 2-4% of their lift-off mass to orbit. Thus, there is a worldwide effort to reduce the launch
cost.
Nearly 70% of the propellant (fuel-oxidiser combination) carried by today’s launch vehicles consists
of oxidiser. Therefore, the next generation launch vehicles must use a propulsion system which can
utilise the atmospheric oxygen during their flight through the atmosphere which will considerably
reduce the total propellant required to place a satellite in orbit.
Also, if those vehicles are made re-usable, the cost of launching satellites will further come down
significantly. Thus, the future re-usable launch vehicle concept along with air-breathing propulsion
is an exciting candidate offering routine access to space at far lower cost.
Considering the strategic nature of air-breathing technology which has the potential to bring a
significant shift in the launch vehicle design, worldwide efforts are on to develop the technology for
air breathing engines.
Ramjet, Scramjet and Dual Mode Ramjet (DMRJ) are the three concepts of air-breathing engines
which are being developed by various space agencies.
A ramjet is a form of air-breathing jet engine that uses the vehicle’s forward motion to compress
incoming air for combustion without a rotating compressor. Fuel is injected in the combustion
chamber where it mixes with the hot compressed air and ignites. A ramjet-powered vehicle requires
an assisted take-off like a rocket assist to accelerate it to a speed where it begins to produce thrust.
Ramjets work most efficiently at supersonic speeds around Mach 3 (three times the speed of sound)
and can operate up to speeds of Mach 6. However, the ramjet efficiency starts to drop when the
vehicle reaches hypersonic speeds.
A scramjet engine is an improvement over the ramjet engine as it efficiently operates at hypersonic
speeds and allows supersonic combustion. Thus it is known as Supersonic Combustion Ramjet or
Scramjet.
A dual-mode ramjet (DMRJ) is a type of jet engine where a ramjet transforms into a scramjet over
Mach 4-8 range, which means it can efficiently operate both in subsonic and supersonic combustor
modes. An important development in ISRO’s Air Breathing Propulsion Project (ABPP) occurred on
August 28, 2016, which was the successful flight testing of its Scramjet.
The first experimental mission of ISRO’s Scramjet Engine towards the realisation of an Air Breathing
Propulsion System was successfully conducted from Satish Dhawan Space Centre SHAR, Sriharikota
on August 28, 2016. With this flight, critical technologies such as ignition of air breathing engines at
supersonic speed, holding the flame at supersonic speed, air intake mechanism and fuel injection
systems have been successfully demonstrated.
The Scramjet engine designed by ISRO uses Hydrogen as fuel and the Oxygen from the atmospheric
air as the oxidiser. The August 28 test was the maiden short duration experimental test of ISRO’s
Scramjet engine with a hypersonic flight at Mach 6.
ISRO’s Advanced Technology Vehicle (ATV), which is an advanced sounding rocket, was the solid
rocket booster used for this test of Scramjet engines at supersonic conditions.
Some of the technological challenges handled by ISRO during the development of Scramjet engine
include the design and development of Hypersonic engine air intake, the supersonic combustor,
development of materials withstanding very high temperatures, computational tools to simulate
hypersonic flow, ensuring performance and operability of the engine across a wide range of flight
speeds, proper thermal management and ground testing of the engines. India is the fourth country
to demonstrate the flight
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Actual Procedure Followed :
Step 1. Litrerature survey on internet
Step 2. Finding Best Quality of Content and Collecting Them
Step 3. Cheking Report for Any Mistake
Step 4. Combining All the Contents and Writing Them in a Report
Responsible Student : Shaikh Saahil Ahamed
Kassim
•
Actual Resource Used :
SR.NO
1.
Resource/Material Specifications QTY
Laptop
Processor
1
Intel(R)
Core(TM) i510300H CPU
@ 2.50GHz
2.50 GHz
Installed RAM
8.00 GB
System type
64-bit
operating
system, x64based
processor
Pen and touch
No pen
or touch input
is available for
this display
Remarks
ok
2.
Internet
OK
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Action Plan :
JIO FIBER
150 [MBPS]
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Sr.No
Details of
Activity
Planned Start
Date/Planned
finish Date
20-04-2022
Name of
Responsible
Team Members
Shaikh Saahil
Ahamed
kassim
Shaikh Saahil
Ahamed
Kassim
1.
Internet Search
2.
Litrerature
survey
20-04-2022
3.
Format idea
20-04-2022
Shaikh Saahil
Ahamed
Kassim
4.
Report Writing
20-04-2022
Shaikh Saahil
Ahamed
Kassim
Group Information :
Name of Student
Shaikh Saahil Ahamed
Kassim
Roll No.
12
13
Class / Sem
EJ/6I
EJ/6I