Rocket Propulsion Exam 1 NEWEST EXAM COMPLETE
QUESTIONS AND CORRECT DETAILED ANSWERS (VERIFIED
ANSWERS) |ALREADY GRADED A+||BRAND NEW!!2025-
2026
In a __ rocket, energy from a nuclear thermal, hydrogen
nuclear
process is used to heat a
working fluid (usually
_______ ) to high
temperatures and
the hot gases are expanded
through a typical de Laval
nozzle
Given the following for an 1,653.5
Ideal Rocket: mass flow = 9
lbm/s
exit velocity =
6000 ft/s exit
pressure = 10
lbf/in^2
ambient pressure = 14.7
lbf/in^2 nozzle exit area
= 5 in^2
Find the thrust of the rocket
PBV is an acronym for post boost velocity
KKV - a name for an
match the following interceptor LEO - a
name for an orbit
SRM - a class of propulsion system
the derivative of acceleration false
is velocity
, escape from earth - 42,500 ft/s
Match the following missions satellite to orbit about the earth -
with their 30,000-41,000 ft/s earth to the
corresponding Actual Delta V
moon and back - 105,000 ft/s
requirement estimates
space-based interceptor -
10,000 ft/s launch to LEO -
29,000 - 30,000 ft/s
typical final burnout altitudes false
for ballistic missiles are
250,000 to 500,000 ft
The R-4D liquid apogee true
engine uses storable bi-
propellants for orbit
circularization and in-flight
maneuvers
the Centaur upper stage false
uses the R-4D storable bi-
propellants engine for
propulsion
In Dr. Frederick's lecture, he system, lower
mentioned that "Poorly
drafted requirements at the
system level will drive the
____ design to ____
performance, will increase
cost and
decrease production
a good estimate of the false
delta velocty
requirement for an
easterly from cape
kennedy to a
geosynchronous orbit is
29,000-29,500 ft/s
the gravitational force of the false
earth is
proportional to the radius of
the satellite orbit divided by
the radius of the earth
, propellant - the fuel and oxidizer expended to fulfill the
primary acceleration of the vehicle
match the following
inert components - non-propellants components within
the propulsion system payload components - the
object or system we are trying to accelerate
the specific impulse can be true
defined as the
impulse (total impulse)
provided per pound of
propellant
QUESTIONS AND CORRECT DETAILED ANSWERS (VERIFIED
ANSWERS) |ALREADY GRADED A+||BRAND NEW!!2025-
2026
In a __ rocket, energy from a nuclear thermal, hydrogen
nuclear
process is used to heat a
working fluid (usually
_______ ) to high
temperatures and
the hot gases are expanded
through a typical de Laval
nozzle
Given the following for an 1,653.5
Ideal Rocket: mass flow = 9
lbm/s
exit velocity =
6000 ft/s exit
pressure = 10
lbf/in^2
ambient pressure = 14.7
lbf/in^2 nozzle exit area
= 5 in^2
Find the thrust of the rocket
PBV is an acronym for post boost velocity
KKV - a name for an
match the following interceptor LEO - a
name for an orbit
SRM - a class of propulsion system
the derivative of acceleration false
is velocity
, escape from earth - 42,500 ft/s
Match the following missions satellite to orbit about the earth -
with their 30,000-41,000 ft/s earth to the
corresponding Actual Delta V
moon and back - 105,000 ft/s
requirement estimates
space-based interceptor -
10,000 ft/s launch to LEO -
29,000 - 30,000 ft/s
typical final burnout altitudes false
for ballistic missiles are
250,000 to 500,000 ft
The R-4D liquid apogee true
engine uses storable bi-
propellants for orbit
circularization and in-flight
maneuvers
the Centaur upper stage false
uses the R-4D storable bi-
propellants engine for
propulsion
In Dr. Frederick's lecture, he system, lower
mentioned that "Poorly
drafted requirements at the
system level will drive the
____ design to ____
performance, will increase
cost and
decrease production
a good estimate of the false
delta velocty
requirement for an
easterly from cape
kennedy to a
geosynchronous orbit is
29,000-29,500 ft/s
the gravitational force of the false
earth is
proportional to the radius of
the satellite orbit divided by
the radius of the earth
, propellant - the fuel and oxidizer expended to fulfill the
primary acceleration of the vehicle
match the following
inert components - non-propellants components within
the propulsion system payload components - the
object or system we are trying to accelerate
the specific impulse can be true
defined as the
impulse (total impulse)
provided per pound of
propellant
