Reusable Launch Vehicle

A Technical Seminar report on,
“REUSABLE LAUNCH VEHICLE”
Submitted to,
VISVESVARAYA TECHNOLOGICAL UNIVERSITY
BELGAVI-590018
In Partial fulfillment of requirement for
Bachelor of Engineering
In
Aeronautical Engineering
Submitted by
N.UDAY BHASKAR REDDY
1AO15AE026
DEPARTMENT OF AERONAUTICAL ENGINEERING
ACHUTHA INSTITUTE OF TECHNOLOGY
GOPALPURA, BAGALUR (P), BANGALORE-562149
2018-19

DEPARTMENT OF AERONAUTICAL ENGINEERING
ACHUTHA INSTITUTE OF TECHNOLOGY
(Affiliated to Visvesvaraya Technological University)
GOPALPURA, BAGALUR (P), BANGALORE-562149
CERTIFICATE
This is to certify that the Technical Seminar entitled “REUSABLE LAUNCH VEHICLE”
carried by Mr. N.UDAY BHASKAR REDDY, bearing USN 1AO15AE026, a bonafide
student of Visvesvaraya Technological University, for the award of degree of Bachelor of
Engineering in Aeronautical Engineering of the Achutha institute of Technology,
Gopalpur, bagalur (P), Bangalore during the academic year 2018-2019. It is certified that
all corrections/suggestions indicated for internal assessment have been incorporated in the
report deposited in the department library. The seminar report has been approved as it
satisfies the academic requirements in respect of seminar work prescribed for corresponding
semester.
Seminar Co-ordinator Signature of HOD
(Mr. Aravind H) (Mr. Naresh D C)

ACKNOWLEDGEMENT
I am very much grateful to Mr. Naresh D C, HOD, Department of Aeronautical Engineering,
AIT for his constant guidance and suggestion during my seminar work.
I express my deep sense of gratitude to the Asst. Prof, Aravind H, Department of
Aeronautical Engineering, AIT who have always been there to clear my doubts and for his
valuable suggestions throughout the completion of my seminar.
I would like to express my sincere thanks to all the Vishwaretha, Ambaresh, members of
Department of Aeronautical Engineering, AIT for their valuable guidance and support.
I would specially like to thank my parents for supporting in completion of my degree.
N.UDAY BHASKAR REDDY
(1AO15AE026)

ABSTRACT
FALCON 9 believes a fully and rapidly reusable rocket is the pivotal breakthrough needed to
substantially reduce the cost of space access. The majority of the launch cost comes from
building the rocket, which flies only once. Compare that to a commercial airliner - each new
plane costs about the same as Falcon 9, but can fly multiple times per day, and conduct tens
of thousands of flights over its lifetime. Following the commercial model, a rapidly reusable
space launch vehicle could reduce the cost of traveling to space by a hundredfold. While most
rockets are designed to burn up on reentry, Falcon 9 rockets are designed not only to
withstand reentry, but also to return to the launch pad or ocean landing site for a vertical
landing.
The main idea was trying to understand why rockets were so expensive. Obviously the lowest
cost you can make anything for is the spot value of the material constituents. Musk formed
Space Exploration Technologies, or SpaceX, with two staggeringly ambitious goals: To make
spaceflight routine and affordable, and to make humans a multi-planet species.

TABLE OF CONTENTS
Certificate
Acknowledgement
Abstract
List of Figures
1. INTRODUCTION 1
1.1.Company Description 1
1.2. Space ﬂight 2
1.3.Launch vehicle 2
1.3.1. Types of Launch vehicle 2
1.4. Facts about Launch Vehicle 3
1.4.1 ISRO 3
2. FALCON FAMILY 4
2.1. Falcon Program Overview 4
2.2. Falcon 9 Family 5
3. FALCON 9 REUSABLE LAUNCH VEHICLE DESCRIPTION 6
3.1 Falcon 9R Vehicle Overview 6
3.2 Falcon 9 Reusable Launch vehicle Speciﬁcations 6
3.3 Falcon 9R first stage 7
3.3.1 First stage Re-Use 9
3.4 Falcon 9R Second stage. 11
3.5 Payload Fairing and Dragon V2 Spacecraft 12
4. FALCON 9 RE-USABLE LAUNCH VERTICAL LANDING IMAGES 14
5. FALCON 9 OVERVIER 15
5.1 Falcon launch vehicle safety 15
5.2 Retention, Release and Separation Systems 15
5.3 Programming in F9R 15
6. APPLICATIONS AND ADVANTAGES 17
6.1 Applications 17
6.2 Advantages 17
6.3 Disadvantages 17
7. CONCLUSIONS 18
REFERENCES 19

LIST OF FIGURES
Figure 2.1: SpaceX vehicles are designed for high cross-platform commonality 4
Figure 2.2: Falcon Launch vehicle Family 5
Figure 3.1: Falcon 9R Technical Details 7
Figure 3.2: Falcon 9R Interior Design 8
Figure 3.3: Falcon 9 landing legs and grid ﬁns 10
Figure 3.4: Drone landing pad in Paciﬁc Ocean 11
Figure 3.5: Stage 2 separating from stage 1 12
Figure 3.6: Payload fairing and Dragon spacecraft 13
Figure 3.7: Launching and Vertical Landing of F9R 13
Figure 5.1:
Figure 5.2:
Vehicle safety
Stages parameters
16
16

REUSABLE LAUNCH VEHICLE 2018-19
Dept. of Aeronautical Engineering, AIT Page 1
CHAPTER 1
INTRODUCTION
1.1 Company Description
SpaceX offers a family of launch vehicles that improve launch reliability and increase access
to space. The company was founded on the philosophy that simplicity, reliability and cost
effectiveness are closely connected. We approach all elements of launch services with a focus
on simplicity to both increase reliability and lower cost. The SpaceX corporate structure is
flat and business processes are lean, resulting in fast decision-making and product delivery.
SpaceX products are designed to require low-infrastructure facilities with little overhead,
while vehicle design teams are co-located with production and quality assurance staff to
tighten the critical feedback loop. The result is highly reliable and producible launch vehicles
with quality embedded throughout the process.
Established in 2002 by ELON MUSK, the founder of Tesla Motors, PayPal and the Zip2
Corporation, SpaceX has developed and flown the Falcon 1 light-lift launch vehicle, the
Falcon 9 medium-lift launch vehicle, and Dragon, which is the first commercially, produced
spacecraft to visit the International Space Station. SpaceX is also developing the Falcon
Heavy, a heavy-lift vehicle capable of delivering over 53 metric tons to orbit. Falcon Heavy’s
first flight is planned for 2016; it will be the most powerful operational rocket in the world by
a factor of two, and dragon, which is the first commercially produced spacecraft to visit the
international space station.
SpaceX has built a launch manifest that includes a broad array of commercial, government
and international customers. In 2008, NASA selected the SpaceX Falcon 9 launch vehicle
and Dragon spacecraft for the International Space Station Cargo Resupply Services contract.
NASA has also awarded SpaceX multiple contracts to develop the capability to transport
astronauts to space.
SpaceX has state-of-the-art production, testing, launch and operations facilities. SpaceX
design and manufacturing facilities are conveniently located near the Los Angeles
International Airport. This location allows the company to leverage Southern California’s
rich aerospace talent pool. The company also operates cutting-edge propulsion and structural
test facilities in Central Texas, along with launch sites in Florida and California, and the
world’s first commercial orbital launch site in development in South Texas.[1]

1.2 Space flight
There are two types of spaceflights or space travel that is
1. Commercial travel
2. Spaceflights
Spaceflight (also written space flight) is ballistic flight into or through outer space.
Spaceflight can occur with spacecraft with or without humans on board. Examples of human
spaceflight include the U.S. Apollo Moon landing and Space Shuttle programs and the
Russian Soyuz program, as well as the ongoing International Space Station. Examples of
unmanned spaceflight include space probes that leave Earth orbit, as well as satellites in orbit
around Earth, such as communications satellites. These operate either bytelerobotic control or
are fully autonomous. A spaceflight typically begins with a rocket launch, which provides the
initial thrust to overcome the force of gravity and propels the spacecraft from the surface of
the Earth. Once in space, the motion of a spacecraft-both when unpropelled and when under
propulsion-is covered by the area of study called astrodynamics. Some spacecraft remain in
space indefinitely, some disintegrate during atmospheric reentry, and others reach a planetary
or lunar surface for landing or impact.
1.3 Launch vehicle
In spaceflight, a launch vehicle or carrier rocket is a rocket used to carry a payload from
Earth’s surface into outer space. A launch system includes the launch vehicle, the launch pad,
and other infrastructure. Although a carrier rocket’s payload is often an artificial satellite
placed into orbit, some spaceflights, such as sounding rockets, are sub-orbital, while others
enable spacecraft to escape Earth orbit entirely. Earth launch vehicles typically have at least
two stages, and sometimes as many as four or more.
1.3.1 Types of Launch vehicle
Expendable are designed for one-time use. They usually separate from their payload and
disintegrate during atmospheric reentry. In contrast, reusable launch vehicles are designed to
be recovered intact and launched again. The Space Shuttle was the only launch vehicle with
components used for multiple orbital spaceflights. But nowadays SpaceX is developing a
reusable rocket launching system for their Falcon 9 and Falcon Heavy launch vehicles.

1.4 Facts about Launch Vehicle
About 1,100 active satellites, both government and private. Plus there are about 2,600 ones
that no longer work. Launched the ﬁrst satellite, Sputnik 1, in 1957. The oldest one still in
orbit, which is no longer functioning, was launched in 1958.
1.4.1 ISRO
ISRO is the Indian Space Agency run by the Indian government. Launch vehicles of India are
SLV, PSLV, and GSLV. Total of 81 satellites launched till date form ISRO made , were 46
satellite are launched form the ISRO made Launch Vehicle as above mentioned. After the
launch of Falcon 9R a special team is being made to built our own reusable launch vehicle by
2020.

CHAPTER 2
FALCON FAMILY
2.1 Falcon Program Overview
Drawing on a history of prior launch vehicle and engine programs, SpaceX privately
developed the Falcon family of launch vehicles. Component developments include first- and
second-stage engines, cryogenic tank structures, avionics, guidance and control software, and
ground support equipment. With the Falcon 9 and Falcon Heavy launch vehicles, SpaceX is
able to offer a full spectrum of medium- and heavy-lift launch capabilities to its customers
(Figure 2.1). SpaceX operates Falcon launch facilities at Cape Canaveral Air Force Station,
Kennedy Space Center, and Vandenberg Air Force Base and can deliver payloads to a wide
range of inclinations and altitudes, from low Earth orbit to geosynchronous transfer orbit to
escape trajectories for interplanetary missions. Future missions will also be flown from the
commercial orbital launch site under development in South Texas. Falcon 9 has conducted
successful flights to the International Space Station (ISS), low Earth orbit (LEO),
geosynchronous transfer orbit (GTO), and Earth-escape trajectories.
Figure 2.1: SpaceX vehicles are designed for high cross-platform commonality (source:
SpaceX)

Figure 2.2: Falcon Launch vehicle Family (source: SpaceX)
2.2 Falcon 9 Family
Falcon 9 is a family of two-stage-to-orbit launch vehicles[2]
, named for its use of nine
engines, designed and manufactured by SpaceX. The Falcon 9 versions are the Falcon 9 v1.0
(retired), Falcon 9 v1.1 (retired), and the current Falcon 9 full thrust, a reusable launch
system. Both stages are powered by rocket engines that burn liquid oxygen (LOX) and
rocket-grade kerosene (RP-1) propellants. The first stage is designed to be reusable, while the
second stage is not. The three Falcon 9 versions are in the medium-lift range of launch
systems. The current Falcon 9 (”full thrust upgrade”) can lift payloads of at least 13,150
kilograms to low Earth orbit, and at least 5,300 kilograms to geostationary transfer orbit. Full
payload capacity is kept private, and may vary depending on whether the first stage follows a
reusable or expendable flight profile.

CHAPTER 3
FALCON 9 REUSABLE LAUNCH VEHICLE DESCRIPTION
3.1 Falcon 9R Vehicle Overview
Falcon 9 full thrust-also known as Falcon 9 v1.1 Full Thrust[3],
and earlier as Falcon 9 v1.2,
Enhanced Falcon 9, Full-Performance Falcon 9, Upgraded Falcon 9, and Falcon 9 Upgrade is
the third major version of the SpaceX Falcon 9 orbital launch. Designed in 2014-2015, it
began launch operations in December 2015, and has a large manifest of over 40 launches
contracted over the next five years. In 21 December 2015, the full thrust version of the Falcon
9 was the first launch vehicle on an orbital trajectory to successfully vertically a first stage
and recover the rocket, following an extensive technology development program in 2011-
2015 that had developed some of the technology on Falcon 9 v1.0 and Falcon 9 v1.1 launch
vehicle first stages. Falcon 9 full thrust is a substantial upgrade over the older Falcon 9 v1.1
rocket, which flew its last mission in January 2016. With updated first- and second-stage
engines, larger second-stage propellant tankage, and propellant densification, the vehicle can
carry substantial payload to geostationary orbit and perform a propulsive landing for
recovery.
3.2 Falcon 9 Reusable Launch vehicle Specifications
Falcon 9 (Figure 3.1) is a two-stage launch vehicle powered by liquid oxygen (LOX) and
rocket-grade kerosene (RP-1). The vehicle is designed, built and operated by SpaceX. Falcon
9 can be flown with a fairing or with a SpaceX Dragon spacecraft. All first-stage and second-
stage vehicle systems are the same in the two configurations; only the payload interface to the
second stage changes between the fairing and Dragon configurations. Falcon 9 v1.1 is a two-
stage launch vehicle that stands 68.4 meters tall, is 3.66 meters in diameter with a liftoff mass
of 505,846 Kilograms when flying in its F9R version with re-usable first stage. The launcher
can deliver payloads of up to 13,150 Kilograms to Low Earth Orbit and 4,850kg to
Geostationary Transfer Orbit. Aiming to become a re-usable launcher, Falcon 9’s first stage is
modified with a reaction control system, four grid fins for steering and four deployable
landing legs.

Figure 3.1: Falcon 9R Technical Details (source: SpaceX)
Dropping the second stage off on its way to orbit, the first stage goes through a series of
complex propulsive maneuvers before guiding itself through the atmosphere towards a target
landing site for a soft touchdown under the power of one of its Merlin engines to be reused
on a future flight.
3.3 Falcon 9R First stage
The first stage of the Falcon 9 v1.1 is largely based on the first stage used on the v1.0 version
featuring stretched propellant tanks and a modified engine compartment. The v1.1 first stage
stands about 41.2 meters tall and is 3.66 meters in diameter featuring the standard design with
the oxidizer tank located above the fuel tank. Monocoque structure is utilized on the oxidizer
tank while the fuel tank features a stringer and ring-frame design that adds strength to the
vehicle. The first stage tank walls and domes are made from aluminum lithium alloy and
utilize reliable welding techniques to provide maximum strength. The first stage uses Liquid
Oxygen oxidizer and Rocket Propellant-1 as fuel which is highly refined Kerosene. The LOX
feedline is routed through the center of the fuel tank to supply oxidizer to the engines.
According to official FAA documentation, the first stage of Falcon 9 v1.1 is capable of
holding 119,100 Kilograms of Rocket Propellant 1 and 276,600kg of Liquid Oxygen. The
empty mass of the first stage is not known, but can be estimated at around 23 to 26 metric
tons, depending on the version used (earlier estimates ranged from 18 to 25 metric tons). Like
the v1.0, the v1.1 version of Falcon 9 features nine Merlin engines on its first stage, but v1.1

no longer uses the Merlin 1C used on the v1.0. Falcon 9 v1.1 sports nine Merlin 1D engines
which are more powerful than the 1C version. Merlin 1D uses improved manufacturing and
quality control techniques to enable SpaceX to produce a greater number of engines per year
while reducing overall risk. The M1D design is simplified over the M1C by removing no-
longer-needed subassemblies. Electro- plating of a nickel-cobalt alloy on the chamber to
create the jacket that endures the primary stress of the pressure vessel was replaced by using
an explosively formed metal jacket.
Figure 3.2: Falcon 9R Interior Design (source: SpaceX)
These changes provide the Merlin 1D with an increased fatigue life and greater thermal
margins for the chamber and nozzle. The first stage tank walls and domes are made from
aluminum lithium alloy and utilize reliable welding techniques to provide maximum strength.
The first stage uses Liquid Oxygen oxidizer and Rocket Propellant-1 as fuel which is highly

refined Kerosene. The LOX feedline is routed through the center of the fuel tank to supply
oxidizer to the engines. According to official FAA documentation, the first stage of Falcon 9
v1.1 is capable of holding 119,100 Kilograms of Rocket Propellant 1 and 276,600kg of
Liquid Oxygen. The empty mass of the first stage is not known, but can be estimated at
around 23 to 26 metric tons, depending on the version used (earlier estimates ranged from 18
to 25 metric tons). Like the v1.0, the v1.1 version of Falcon 9 features nine Merlin engines on
its first stage, but v1.1 no longer uses the Merlin 1C used on the v1.0. Falcon 9 v1.1 sports
nine Merlin 1D engines which are more powerful than the 1C version. Merlin 1D uses
improved manufacturing and quality control techniques to enable SpaceX to produce a
greater number of engines per year while reducing overall risk. The M1D design is simplified
over the M1C by removing no-longer-needed subassemblies. Electro-plating of a nickel-
cobalt alloy on the chamber to create the jacket that endures the primary stress of the pressure
vessel was replaced by using an explosively formed metal jacket. These changes provide the
Merlin 1D with an increased fatigue life and greater thermal margins for the chamber and
nozzle.
3.3.1 First stage Re-Use
The overall goal of SpaceX is to make the first stage of Falcon 9 (and the three cores of
Falcon Heavy) fully re-usable by returning them to a landing site through a series of complex
maneuvers performed after separation from the launcher using a small portion of leftover
propellant. To rapidly re-use the first stage of the vehicle, Falcon 9 is ultimately planned to
fly the stage back to the launch site after separation and land it vertically on deployable
landing legs. Initial attempts of demonstrating the return flight were made by soft-landing
stages in the ocean before upgrading to landing the first stage boosters on a floating platform.
The re-usable version of Falcon 9 is known as F9R which itself does not represent a fully
different launcher and is more of an add-on to the v1.1 version in the form of the Nitrogen
Cold Gas Attitude Control System, the four deployable landing legs and four grid fins used
for three-axis control during atmospheric flight, especially during non-propulsive flight
phases. The overall design driver for the landing legs was mass since adding significant
weight to the first stage would have resulted in a significant payload penalty. Safety was also
a major concern - the leg design had to be such that no premature deployment during
powered ascent was possible which would result in a certain loss of the entire vehicle and
payload.

Figure 3.3: Falcon 9 landing legs and grid fins (source: SpaceX)
Made of aluminum honeycomb and carbon- composite materials, the four legs have a total
mass of around 2,100 Kilograms consisting of a single-load bearing strut and aerodynamic
fairing assembly. The central struts of the legs interface with the load-carrying structure of
the first stage while the fairings have two structural interfaces at the base of the engine
compartment heat shield and one interface on the lower portion of the leg. During flight, the
legs are stowed against the rocket body, covered by the fairings that ensure no additional
aerodynamic disturbance is introduced by the legs. Deployment is accomplished by a
pneumatic system using high-pressure helium. When deployed, the legs have a span of about
18 meters, capable of supporting the forces of landing and the mass of the nearly empty first
stage. Grid-fins perform well in all velocity ranges including supersonic and subsonic speeds
with the exception of the trans-sonic regime due to the shock wave enveloping the grid.
These properties make them ideally suitable for the Falcon 9 first stage that starts out at
supersonic speeds and returns to subsonic velocity as it travels through the atmosphere, en-
route to the landing site. Before attempting to land first stages on land, SpaceX commissioned
a floating platform that can be deployed in the ocean, downrange from the launch site to
provide a landing pad for the first stage boosters. Known as the Autonomous Spaceport
Drone Ship, the floating landing platform was built at a Louisiana shipyard and measures 91
meters by 52 meters with a prominent SpaceX marks the Spot” logo in the center The return
flight of the first stage booster starts at the moment of separation from the Falcon 9 second
stage that is delivered to a trajectory from where it can boost the payload into its desired
orbit. First stage burn duration in missions that include a propulsive return is on the order of

160 seconds. Initially, the first stage uses its cold gas thrusters for attitude control - starting
with a maneuver to depart the engine plume of the second stage before re-orienting to an
engines-first position that is maintained past the point of apogee.
Figure 3.4: Drone landing pad in Pacific Ocean (source: SpaceX)
Around T+4.5 minutes into the mission, the first stage re-lights a subset of its engines for a
boost-back maneuver that slows the vehicle down and controls the downrange travel distance
of the stage, beginning to target the planned landing site - either on land or in the ocean. The
duration of the boost-back burn depends on the target landing site and is also driven by
propellant availability for the return which varies depending on payload mass and insertion
orbit. Heading back into the dense layers of the atmosphere, the first stage completes its
supersonic retro propulsion burn using three engines that are red for about 20 seconds starting
at an altitude of 70 Kilometers.
3.4 Falcon 9R Second stage
The second stage of the Falcon 9R is based on the design of the v1.0 second stage which is
essentially a smaller version of the first stage. SpaceX has always followed a policy of
choosing simple solutions to reduce cost and risk in order to manufacture a robust launch
system. Using the same materials, tools and manufacturing techniques for the two stages is a
perfect example of that policy. As with the first stage, the exact dimensions of the second
stage have not yet been disclosed by SpaceX. The second stage matches the first stage’s

diameter of 3.66 meters. Documentation shows the stage to be 13.8 meters in length without
payload adapter and 1st Stage Interstage with an intert mass just under four metric tons. The
second stage can hold 64,820kg of LOX and 27,850kg of RP-1 giving it a launch mass of
96,600kg. The second stage also uses Rocket Propellant 1 as fuel and Liquid Oxygen as
oxidizer. One Merlin 1D engine is powering the second stage. This engine differs from the
first stage engines as it is optimized for operation in vacuum featuring an extended nozzle
with a high expansion ratio.
Figure 3.5: Stage 2 separating from stage 1 (source: SpaceX)
M1D is also a turbo pump-fed gas generator engine; it also operates at a chamber pressure of
97 bars. The system is fully redundant, constantly checking itself to verify that all GNC
components are functioning properly. SpaceX uses commercial off-the-shelf parts that are
radiation tolerant instead of radiation hardened (cost reduction). The flight computers run on
Linux with software written in C++.
3.5 Payload Fairing and Dragon V2 Spacecraft
The Payload Fairing is positioned on top of the stacked vehicle and its integrated spacecraft.
It protects the vehicle against aerodynamic, thermal and acoustic environments that the
launcher experiences during atmospheric flight. When the launcher has left the atmosphere,
the fairing is jettisoned. Separating the fairing as early as possible increases ascent
performance. Falcon 9’s standard Fairing is 13.1 meters in length and 5.2 meters in diameter.
The fairing consists of an aluminum honeycomb core with carbon-fiber face sheets fabricated
in two half-shells.

Figure 3.6: Payload fairing and Dragon spacecraft(source: SpaceX)
Figure 3.7: Launching and Vertical Landing of F9R(source: SpaceX)

CHAPTER 4
FALCON 9 RE-USABLE LAUNCH VERTICAL LANDING
IMAGES
(source: SpaceX)

CHAPTER 5
FALCON 9 OVERVIER
5.1 Falcon launch vehicle safety
We continue to push the limits of rocket technology as we design the safest crew
transportation system ever flown while simultaneously advancing toward fully reusable
launch vehicles. Our emphasis on safety has led to advancements such as increased structural
factors of safety[4]
, greater redundancy and rigorous fault mitigation
5.2 Retention, Release and Separation Systems
The first and second stages are mated by mechanical latches at three points between the top
of the interstage and the base of the second-stage fuel tank. After the first-stage engine shut
down, a high- pressure helium circuit is used to release the latches via redundant actuators.
For added reliability, a redundant center pusher attached to the first stage is designed to
dramatically decrease the probability of re-contact between the stages following separation.
5.3 Programming in F9R
The Flight Software team is about 35 people. We write all the code for Falcon 9,
Grasshopper, and Dragon applications; and do the core platform work, also on those vehicles;
we also write simulation software; test the flight code; write the communications and analysis
software, deployed in our ground stations. We also work in Mission Control to support active
missions. The Ground Software team is about 9 people. We primarily code in Lab VIEW. We
develop the GUIs used in Mission and Launch control, for engineers and operators to monitor
vehicle telemetry and command the rocket, spacecraft, and pad support equipment. We are
pushing high bandwidth data around a highly distributed system and implementing complex
user interfaces with strict requirements to ensure operators can control and evaluate
spacecraft in a timely manner. SpaceX uses an Actor-Judge system to provide triple
redundancy to its rockets and spacecraft. The Falcon 9 has 3 dual core x86 processors
running an instance of Linux on each core. The flight software is written in C/C++ and runs
in the x86 environment. For each calculation/decision, the”flight string” compares the results
from both cores. If there is a inconsistency, the string is bad and doesn’t send any commands.
If both cores return the same response, the string sends the command to the various
microcontrollers on the rocket that control things like the engines and grid fins. The
microcontrollers, running on PowerPC processors, received three commands from the three
flight strings. They act as a judge to choose the correct course of actions. If all three strings

are in agreement the microcontroller executes the command, but if 1 of the 3 is bad, it will go
with the strings that have previously been correct.
Figure 5.1: Vehicle safety
Figure 5.2: Stages parameters(source: SpaceX)

CHAPTER 6
APPLICATIONS AND ADVANTAGES
6.1 Applications
1. It’s a type of launch vehicle which can lift up satellite to the orbits can take payload to the
International Space Station and can also take humans using dragon vehicle.
2. As this is the 1st reusable launch vehicle ever used is the pivotal breakthrough needed to
substantially reduce the cost of space access.
3. The reusable launch vehicle can reused within 24 hours after the Stage-1 F9R lands
vertically.
4. Falcon 9R is being said to be used in human MARS mission in 2020.
5. In a single launch F9R can put 15 satellite of orbit of each of 200kg.
6. As being said the in future when a colony will be formed in MARS the transportation for
human beings are being carried out of next versions of FALCON launch vehicle was said by
the SPACEX CEO.
7. Can be used in Military applications.
6.2 Advantages
1. Compared to other launch vehicles the F9R is a reusable launch vehicle.
2. By using F9R the cost is being reduced by 40 percent.
3. Total liftoff mass1400 metric tons (14 Lakh Kilo) by using in a single launch have been
planned this year.
4. The stage-1 can be landed any were means in a ship or sea drone which is very efficient.
5. Falcon 9R is a highly reliable launch vehicle.
6.3 Disadvantages
1. The Falcon 9 experiences major temperature changes during its ﬂights, as well as intense
pressures and vibrations from the winds in the atmosphere.
2. Refurbishing a rocket engine is often expensive. And if those repairs take too long,
company can’t launch its vehicles as frequently. Refurbishment costs are too expensive.
3. To launch F9R the climate condition should be absolute normal, if anything goes wrong
the return stage-1 of falcon 9 will get damaged.
4. The vertical landing of F9R is very complicated.

CHAPTER 7
CONCLUSION
If one can figure out how to effectively reuse rockets just like airplanes, the cost of access to
space will be reduced by as much as a factor of a hundred. A fully reusable vehicle has never
been done before. That really is the fundamental breakthrough needed to revolutionize access
to space. FALCON 9 believes a fully and rapidly reusable rocket is the pivotal breakthrough
needed to substantially reduce the cost of space access. The majority of the launch cost
comes from building the rocket, which flies only once. Compare that to a commercial airliner
- each new plane costs about the same as Falcon 9, but can fly multiple times per day, and
conduct tens of thousands of flights over its lifetime. The main idea was trying to understand
why rockets were so expensive. Obviously the lowest cost you can make anything for is the
spot value of the material constituents. To make spaceflight routine and affordable, and to
make humans a multi-planet species.

REFERENCE
1. www.spacex.com
2. www.spacex.com/falcon9
3. www.en.wikipedia.org/wiki/Falcon9fullthrust
4. www.spacex.com/sites/spacex/ﬁles/falcon9/usersguiderev2.0

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