Rocket Propulsion - Self Assesment Training
Rocket Propulsion Knowledge Check
Test your understanding of rocket propulsion concepts with our comprehensive self-assessment quiz. This quiz covers various aspects of fluid mechanics, thermodynamics, and propulsion technologies, challenging your knowledge from basic principles to advanced applications.
- 24 questions to evaluate your expertise
- Multiple choice format for easy answering
- Ideal for students, enthusiasts, and professionals in the field
Why is particularily the Oxygen pump turbine prone to be low in efficiency ?
The turbine speed is limited by the pump
Oxygen is harder to pump
The flow rates are very high
The viscosity of oxygen is higher
Oxygen becomes more turbulent because of the higher density
What are the characteristics of turbines for stage combustion cycles ?
The pressure levels are above 150 bar
Extremely high power
The tip speed is low
The turbine pressure ratio is high
Low mass flows
What properties are important for the turbopump design ?
The nozzle exit pressure
The target combustion chamber pressure
The propellant densities
The shaft speed limitation
The atmospheric pressure during flight
Why is the turbine often of impulse type in liquid rocket propulsion?
In order to use a gear box
The flow velocities are very high compared to mechanical limits
The efficiency is always higher than for reaction designs
In order to reduce the stage count
The impulse of flow in the combustor must be high
Why are the turbines typically supersonic in open cycles?
The flow rates are large through the turbine
The temperature is higher than in closed cycles
The pump pressure is higher than in closed cycles
The turbine pressure ratio is higher
The turbine shaft speed is particularly high
What is the reason for multi-staging compared to single stage rockets?
Lower production costs
Storability of propellant
Lower structural coefficient
Higher attainable velocity for same payload ratio
Higher payload ratio for same velocity increment
Which forces need to be taken into account to calculate a launch vehicles trajectory at lift-off?
Atmospheric drag force
Coriolis force
Thrust force
Gravitational force
Buffeting forces
Why is the Hohmann transfer orbit considered most fuel efficient to go from Earth orbit to Mars orbit?
It utilizes the energy of Mars
It utilizes the gravity of the Sun
Velocity increments are collinear to object trajectory
It utilizes the kinetic energy of the Earth
It is the closest distance between Earth and Mars
What is a correct statement concerning dissociation?
Dissociation is associated with complete combustion, I.e. Either all the fuel or all the oxidant is consumed
Product dissociation shifts the maximum ISP to non-stoichiometric oxidizer-fuel mass ratio
Product dissociation increases ISP
Product dissociation usually occurs at high temperature levels
Dissociation is associated with a state of chemical equilibrium
Several propellants have theoretical exhaust velocities of over 3000 m/s. If the initial entalphy of the propellants is zero, what is the minimum amount of chemical energy that must be added to the propellant to attain this velocity?
30*10^5
15*10^5
45*10^5
6*10^5
9*10^5
The dimensioning factor for the combustion chamber length is related
The size of the injected droplets
The vaporization process of the liquid drops
The chemical reaction time
The wall heat transfer rate
The adiabatic flame temperature
Which of the following parameter changes will increases the wall heat flux per unit area?
Increased chamber pressure
Reduced molecular weigth of the exhaust gas
Increased nozzle length
Reduced throat diameter
Increased ambient pressure
Which of the following alternative will increase the vacuum specific impulse of a rocket nozzle?
Increased propellant mass flow
Increased area ratio
Increased molecular weigth of the exhaust gas
Increased chamber temperature
Increased chamber pressure
Which are the principle loss mechanisms that should be minimized when searching for an optimum nozzle configuration?
Expansion loss
Chemical kinetic loss
Divergency Loss
Viscous drag loss
Heat loss
What is required to achieve a constant thrust level for solid-propellant boosters?
The burning charge area has to remain constant
A tubular burning charge design has to be employed
A multi-fin burning charge design has to be employed
The burning rate needs to remain constant
The solid-propellant needs to be homogeneous
Metal powders are added to solid propellants to...
Increase the thrust
Enhance the heat capacity of the propellant
Increase the ISP
Enhance the mechanical properties of the propellant
Increase the specific weight of the propellant
A large pressure drop over the injector nozzle of a combustion chamber
Increases the propellant inlet velocities
Is desired
Increases the overall engine performance
Increases combustion instabilities
Enables good atomization of the fuel
Which of the following aspects are important for the dimensioning of rocket engine nozzles with respect to heat transfer?
The conductivity of the wall material
Film cooling effectiveness
The density variation of the atmosphere
Natural convection on the outer wall
Radiative heat transfer to the outside
Which of following statements is/are correct?
Propulsion energy is only limited by the size of the power plant I.e. Electrical rockets are power limited
In electrical rockets, a separate energy source is used only to start up the chemical reaction of the propelant I.e. Exhaust energy is not affected by external electrical energy source
Electrical propulsion is energy limited, I.e. Quantity of energy (per unit mass of propellant) that can be released during combustion is limited by the chemical behaviour of propellant materials (energy is contained in propellant).
In ion rockets, a separate electrical energy source is used to accelerate charged propellant particles in order to create thrust
Propulsion energy of an electrical propulsion system is only limited by the size of the propellant storage system .
In what specific-impulse range operate arcjet propulsion devices most efficiently?
Lower than 1000s
1000s to 2000s
Lower than 500s
Greater than 5000s
2000s to 5000s
What are the main concepts for electrical propulsion?
Electrodynamic
Nuclear
Electrostatic
Electromagnetic
E. Electrothermal
What are the main properties of electrical propulsion?
High specific impulse
Low propellant mass consumption
High thrust level
Low thrust level
Low exhaust velocity
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