Fundamentals Of Rockets & Missiles Course Sampler

1. Professional Development Short Course On:
Fundamentals of Rockets & Missiles
Instructor:
Edward L. Keith
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2. Fundamentals of Rockets and Missiles
March 11-13, 2009 Course Outline
Laurel, Maryland 1. Introduction to Rockets and Missiles The Classifications
of guided, and unguided, missile systems is introduced. The
$1590 (8:30am - 4:00pm) practical uses of rocket systems as weapons of war, commerce
and the peaceful exploration of space are examined.
quot;Register 3 or More & Receive $10000 each 2. Rocket Propulsion made Simple. How rocket motors and
Off The Course Tuition.quot; engines operate to achieve thrust. Including Nozzle Theory, are
explained. The use of the rocket equation and related Mass
Properties metrics are introduced. The flight environments and
conditions of rocket vehicles are presented. Staging theory for
rockets and missiles are explained. Non-traditional propulsion is
addressed.
3. Introduction to Liquid Propellant Performance, Utility
and Applications. Propellant performance issues of specific
impulse, Bulk density and mixture ratio decisions are examined.
Summary Storable propellants for use in space are described. Other
propellant Properties, like cryogenic properties, stability, toxicity,
This course provides an overview of rockets and missiles
for government and industry officials with limited technical compatibility are explored. Mono-Propellants and single
propellant systems are introduced.
experience in rockets and missiles. The course provides a
practical foundation of knowledge in rocket and missile issues 4. Introducing Solid Rocket Motor Technology. The
and technologies. The seminar is designed for engineers, advantages and disadvantages of solid rocket motors are
examined. Solid rocket motor materials, propellant grains and
technical personnel, military specialist, decision makers and construction are described. Applications for solid rocket motors as
managers of current and future projects needing a more weapons and as cost-effective space transportation systems are
complete understanding of the complex issues of rocket and explored. Hybrid Rocket Systems are explored.
missile technology The seminar provides a solid foundation in
5. Liquid Rocket System Technology. Rocket Engines, from
the issues that must be decided in the use, operation and pressure fed to the three main pump-fed cycles, are examined.
development of rocket systems of the future. You will learn a Engine cooling methods are explored. Other rocket engine and
wide spectrum of problems, solutions and choices in the stage elements are described. Control of Liquid Rocket stage
technology of rockets and missile used for military and civil steering is presented. Propellant Tanks, Pressurization systems
purposes. and Cryogenic propellant Management are explained.
Attendees will receive a complete set of printed notes. 6. Foreign vs. American Rocket Technology and Design.
These notes will be an excellent future reference for current How the former Soviet aerospace system diverged from the
trends in the state-of-the-art in rocket and missile technology American systems, where the Russians came out ahead, and what
and decision making. we can learn from the differences. Contrasts between the Russian
and American Design philosophy are observed to provide lessons
for future design. Foreign competition from the end of the Cold War
to the foreseeable future is explored.
Instructor 7. Rockets in Spacecraft Propulsion. The difference
Edward L. Keith is a multi-discipline Launch Vehicle System between launch vehicle booster systems, and that found on
Engineer, specializing in integration of launch spacecraft, satellites and transfer stages, is examined The use of
vehicle technology, design, modeling and storable and hypergolic propellants in space vehicles is explained.
business strategies. He is currently an Operation of rocket systems in micro-gravity is studied.
independent consultant, writer and teacher of 8. Rockets Launch Sites and Operations. Launch Locations
rocket system technology. He is experienced in the USA and Russia are examined for the reason the locations
have been chosen. The considerations taken in the selection of
in launch vehicle operations, design, testing, launch sites are explored. The operations of launch sites in a more
business analysis, risk reduction, modeling, efficient manner, is examined for future systems.
safety and reliability. He also has 13-years of government 9. Rockets as Commercial Ventures. Launch Vehicles as
experience including five years working launch operations at American commercial ventures are examined, including the
Vandenberg AFB. Mr. Keith has written over 20 technical motivation for commercialization. The Commercial Launch Vehicle
papers on various aspects of low cost space transportation market is explored.
over the last two decades. 10. Useful Orbits and Trajectories Made Simple. The
student is introduced to simplified and abbreviated orbital
mechanics. Orbital changes using Delta-V to alter an orbit, and the
use of transfer orbits, are explored. Special orbits like
Who Should Attend geostationary, sun synchronous and Molnya are presented.
• Aerospace Industry Managers. Ballistic Missile trajectories and re-entry penetration is examined.
• Government Regulators, Administrators and 11. Reliability and Safety of Rocket Systems. Introduction to
sponsors of rocket or missile projects. the issues of safety and reliability of rocket and missile systems is
presented. The hazards of rocket operations, and mitigation of the
• Engineers of all disciplines supporting rocket and problems, are explored. The theories and realistic practices of
missile projects. understanding failures within rocket systems, and strategies to
• Contractors or investors involved in missile improve reliability, is discussed.
development. 12. Expendable Launch Vehicle Theory, Performance and
Uses. The theory of Expendable Launch Vehicle (ELV) dominance
• Military Professionals. over alternative Reusable Launch Vehicles (RLV) is explored. The
controversy over simplification of liquid systems as a cost effective
strategy is addressed.
What You Will Learn 13. Reusable Launch Vehicle Theory and Performance.
The student is provided with an appreciation and understanding of
• Fundamentals of rocket and missile systems. why Reusable Launch Vehicles have had difficulty replacing
• The spectrum of rocket uses and technologies. expendable launch vehicles. Classification of reusable launch
vehicle stages is introduced. The extra elements required to bring
• Differences in technology between foreign and stages safely back to the starting line is explored. Strategies to
domestic rocket systems. make better RLV systems are presented.
• Fundamentals and uses of solid and liquid rocket 14. The Direction of Technology. A final open discussion
systems. regarding the direction of rocket technology, science, usage and
• Differences between systems built as weapons and regulations of rockets and missiles is conducted to close out the
class study.
those built for commerce.
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4. Fundamentals of Rockets and Missiles
Class Sampler
This is an introductory class in rocket systems used
as launch vehicles and as weapons. Basic rocketry
principles are introduced to provide a foundation of
the principals of solid and liquid rockets. Existing
systems are discussed to understand why the
systems evolved to their present state.
© 2004, Edward L. Keith Fundamentals of Rockets and Missiles Sampler
ATI
Sample-1

5. Terminology and Conventions
Rocket
Vehicles Weapons
Propulsion
Rocket Missile
Surface to
Surface
Sounding Launch ICBM SAM
Rocket Vehicle IRBM ABM
SRBM Surface to Air
Reusable Expendable Air to Air
Launch Launch SLBM
Vehicle Vehicle CM * AAM
Cruise Missile
* Non Rocket
Upper Space- Transfer ASM
Air to Surface
Stage Craft Stage
© 2003, Edward L. Keith
Fundamentals of Rockets and Missiles Sampler
ATI
Sample-2

6. Rocket Engine and Nozzle
• A combustion chamber (or motor case) is the device to
burn a fuel and oxidizer [or decompose a mono-propellant]
to create hot, high-pressure gas with high thermal energy
• A throat and nozzle is a device to accelerate hot gas,
causing the thermal energy of that gas to be converted into
kinetic energy of high-velocity gas P3 Pressure at Exit Plane
• De Laval nozzle (Supersonic gas)
T1 (Chamber Temperature)
P1 (Chamber Pressure)
CHAMBER
P2 Pressure at Throat Plane
NOZZLE
(Sonic Velocity)
Fundamentals of Rockets and Missiles Sampler
© 2002, Edward L. Keith ATI
Sample-3

7. Why Exhaust Gasses are Fuel-Rich
• The performance (specific Impulse) of a rocket engine is
dependant on the temperature and molecular weight of the
combustion gasses
Isp = k T/
MW
• The highest performance through higher temperature has
limits in chemical energy, and engine cooling capacity
• There are, however, strategies that reduce gas molecular
weight with only small sacrifice in temperature
– Fuel rich gasses like H2 [MW=2] and CO [MW=28]) are
significantly lighter than H2O [MW=18] and CO2 [MW=44]
• The mixture ratio is selected to leave partially burned
fuel (H2, CO, etc.) in the exhaust for increased
performance
• The bright flame from rockets is afterburning
Fundamentals of Rockets and Missiles Sampler
© 2002, Edward L. Keith ATI
Sample-4

8. Introducing the Rocket Equation *
• Rocket Equation is essential for evaluation of any rocket
system
• Solves the Ideal Velocity Change (Delta-V or V) given the
rocket engine efficiency (specific impulse or Isp) and the
ratio of the mass at ignition to the mass at burnout
Ln (10) = 2.3
Ln (4) = 1.386 V = Isp * g * ln (M/m)
Ln (2) = 0.693
• Where:
– Delta-V is velocity (f/s [English]
– g is acceleration of gravity (32.2 f/sec2)
– “ln” is the natural logarithm function
– M is the initial Mass (Big M)
– m is the final mass (Little M)
* 1897 “The Tsiolkovsky Rocket Equation”
Fundamentals of Rockets and Missiles Sampler
© 2002, Edward L. Keith ATI
Sample-5

9. Staging Theory & the Rocket Equation
• The term “Rocket Trains’ describing staging theory was
described by Tsiolkovsky * (1857-1935)
– Higher velocity with more payload and less sensitivity
– Single Stage V = Isp * g * ln (M/m)
• For M/m = 2 and Isp = 300, V = 6,696 f/s
• For M/m = 4 and Isp = 300, V = 13,392 f/s
• For M/m = 6 and Isp = 300, V = 17,308 f/s
• For M/m = 8 and Isp = 300, V = 20,087 f/s
• For M/m = 10 and Isp = 300, V = 22,243 f/s
• For M/m = 22.33 and Isp = 300, V = 30,003 f/s
• Remember, it takes about 30,000 f/s to achieve LEO and m is both
dry rocket structure and usable payload
* 1929 “The Space Rocket Trains” by Tsiolkovsky
Fundamentals of Rockets and Missiles Sampler
© 2002, Edward L. Keith ATI
Sample-6

10. Extending the Rule to Engine T/W
• The two-thirds root rule can be extended to a key rocket
engine parameter – Thrust to weight ratio (T/W)
• Rule (conjecture) is based on adjusted volume flow rate
– Adjusted to the performance of that flow
T/W1 = T/W2 x (BD2/BD1) 0.6667 x (Isp2/Isp1)
• The correction seems to work, and again is explained by
the Volume to Surface area ratio
TW1 = TW2 * ( Isp2/Isp1 ) * (BD2/BD1) 0.667
The algorithm may be conjecture, but it seems
to fit reality better than any other rule. ATI
© 2002, Edward L. Keith Fundamentals of Rockets and Missiles Sampler
Sample-7

11. Hydrazine – Top Mono-Propellant
• Mono-propellant hydrazine decomposes to Ammonia,
Nitrogen and Hydrogen
– Catalyst “Shell 405” is generally accepted best material
• The temperature and species of the decomposed Hydrazine
is dependant on the catalyst and other factors
– 2N2H4  2NH3 + N2 + H2 @1,880 F
• Minimum Decomposition
– N2H4  N2 + 2H2 @1,100 F
– Maximum Decomposition
– Hydrazine achieves about 235 seconds specific impulse in
practical thrusters
– High Density (1.01 g/cc)
– Permanently storable
© 2002, Edward L. Keith
ATI
Fundamentals of Rockets and Missiles Sampler
Sample-8

12. Propellant Grains Can Be Tailored
• Progressive
Thrust
• Regressive
• Neutral
Time
Impulse
Thrust
Area under the
Curve (Pound-Seconds)
[Propellant Weight x Isp]
Time
Thrust
• Thrust profile determined by
Grain Geometry
ATI
© 2003, Edward L. Keith Fundamentals of Rockets and Missiles Sampler
Time Sample-9

13. All Solid Rocket Motor Launch Vehicle
• The Taurus (Right) is one of three all-solid
rocket motor American launch vehicles
• Stages two, three and four (left) are the
same as are used for stages one, two and
three on the Air-Launched Pegasus
http://www.atk.com/homepage/products/
© 2003, Edward L. Keith Fundamentals of Rockets and Missiles Sampler
ATI
Sample-10

14. Relative Production Cost
Relative Production Cost
According to TRANSCOST 7.0 Model
200
Man-Years of Effort
150 Liquid Rocket Stage *
100
Solid Rocket Stage
50
0
0 500 1000 1500 2000 2500 3000 3500
Stage Mass (kg)
* 20% Engine, 80% Stage
© 2003, Edward L. Keith
Fundamentals of Rockets and Missiles Sampler
ATI
Sample-11

15. Liquid Rockets are New Technology
• Robert Goddard (below) was an early pioneer of liquid
rocket propulsion
– Gasoline and liquid oxygen
– Pressure-fed
– Unguided
GN2
CV CV
Reg.
Gasoline LOX
© 2003, Edward L. Keith
Fundamentals of Rockets and Missiles Sampler
ATI
Sample-12

16. N-1 Soviet Moon Rocket Strategy
• The Soviet N-1 Moon Rocket also shows
typical Russian features
– Stage 1 used 30 NK-33 engines
– Stage 2 used 8 NK-43 engines
– Similar to NK33 but higher expansion
– Stage 3 used 4 NK-39 engines
– Stage 4 used 1 1 NK-31 engines
– Similar to NK-39
• Note that most Russian rockets (Soyuz,
Proton, N-1) tend to be tapered, with a fatter
base than the middle and upper sections
– Aerodynamic stability increase for better
control during passage through high winds
aloft near max-q
– Four failed flights (1969-1972) ATI
© 2003, Edward L. Keith http://www.aerospaceguide.net/n-1.html
Fundamentals of Rockets and Missiles Sampler
Sample-13

17. Current Space Shuttle RCS
Fundamentals of Rockets and Missiles Sampler
ATI
Sample-14

18. Surface to Surface Missile Proliferation
• 19 Countries with Scud Missiles
– Belarus, Bulgaria, Czech
Republic, Hungary, Poland,
Romania, Russia, Slovakia,
Ukraine, Egypt, Iran, Iraq, Libya,
Syria, Yemen, Afghanistan,
Kazkhastan, Tajikistan and
North Korea
• North Korean Taepo Dong is a
Third World ICBM
– Technology exported to Iran?
• Which has an aggressive
Nuclear Program
Fundamentals of Rockets and Missiles Sampler
Sample-15

19. Microcosm – Hardware Demonstration
Scorpius® is a new
generation of expendable
launch vehicles intended to
reduce the cost of launch to
orbit by a factor of 5 to 10.
The Scorpius® program is a
total quot;clean-sheetquot;
development using new
technologies for pressure-
fed, LOX/Jet-A propellants,
all new low cost ablative
engines, and GPS/INS
guidance/control. Funding
for the ongoing Scorpius
program has been provided
primarily by the Air Force,
Ballistic Missile Defense
Organization (BMDO), http://www.smad.com/ns/nsframessr3.html
NASA, and Microcosm Scorpius –According to Microcosm
internal R&D.
Fundamentals of Rockets and Missiles Sampler
ATI
Sample-16

20. Soyuz Launch Vehicle
• No space launch vehicle
has flow to more than the
Russian “Soyuz” family
– Sputnik 1 (1957)
– All Russian Manned
Missions
– A flight per week on
average for 22 years
http://www.spaceandtech.com/spacedata/elvs/soyuz_sum.shtml
Fundamentals of Rockets and Missiles Sampler
Sample-17

21. Relationships Between Safety and Reliability
• Safety and Reliability are closely related
– If a system failure causes loss of property, injury or loss
of life, it is a Safety Problem
– If a system failure causes premature loss of the rocket,
or causes the mission to fail, it is a Reliability Problem
• Common denominator can be unexpected failures
Safety Safety and Reliability
Reliability
Fundamentals of Rockets and Missiles Sampler
ATI
© 2002, Edward L. Keith Sample-18

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