Ariane Rocket Engines Quiz
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Questions and Answers

Which engine was used for Ariane 4?

  • Vulcain
  • Viking (correct)
  • Vinci
  • HM7

    • Which engine was used for Ariane 5 in 2002?

  • Vulcain 2
  • Vulcain (correct)
  • Vinci
  • HM7

    • Which engine is associated with the Aestus?

  • Viking
  • Vulcain
  • Vulcain 2
  • HM7 (correct)

    • What is the name of the company that owns the rights to the information in the documents?

    <p>Snecma (A)</p> Signup and view all the answers

    What is the main focus of the information provided in the document?

    <p>The development of the different engines used in the Ariane rocket program (B)</p> Signup and view all the answers

    What is the significance of the text "CONFIDENTIEL" on the documents?

    <p>It indicates that the documents are confidential and should not be shared without permission (B)</p> Signup and view all the answers

    What does the abbreviation FLTOM likely stand for in the document?

    <p>Flight Test and Operational Management (C)</p> Signup and view all the answers

    What is the primary focus of the content provided?

    <p>Modeling of solid propellant combustion (D)</p> Signup and view all the answers

    Which specific type of instability is mentioned in the content?

    <p>Acoustic instabilities (B)</p> Signup and view all the answers

    What does the acronym 'MPS 230' likely refer to in this context?

    <p>A specific type of rocket engine (A)</p> Signup and view all the answers

    What is the function of the 'Wall Vortex Shedding' simulation?

    <p>To analyze the flow of propellant inside the combustion chamber (C)</p> Signup and view all the answers

    What specific factor is mentioned as influencing the two-phase flow in the content?

    <p>The presence of aluminum particles in the solid propellant (B)</p> Signup and view all the answers

    What is the most likely reason for the repeated mention of 'CONFIDENTIEL' in the document?

    <p>To emphasize the proprietary nature of the information (C)</p> Signup and view all the answers

    What is the likely implication of the phrase 'LIQUID PROPULSION, SOMEWHAT COMPLEX'?

    <p>Liquid propulsion requires more sophisticated modeling techniques than solid propulsion (D)</p> Signup and view all the answers

    Which of the following is NOT explicitly mentioned as a topic of research in the content?

    <p>The design of innovative rocket engine chambers (B)</p> Signup and view all the answers

    What is the thrust at lift-off for the Ariane IV launcher?

    <p>5400 kN (D)</p> Signup and view all the answers

    How long is the flight duration of the Ariane IV?

    <p>20 min (B)</p> Signup and view all the answers

    What is the price of the Ariane IV launcher in millions of euros?

    <p>570 M€ (C)</p> Signup and view all the answers

    How much propellant is used in the Ariane IV launcher?

    <p>435 tonnes (B)</p> Signup and view all the answers

    What is the payload capacity of the Ariane IV?

    <p>4.5 tonnes (A)</p> Signup and view all the answers

    How does the lifetime of the Ariane IV compare to that of the Boeing 747-300?

    <p>Boeing 747-300 has a longer lifetime (C)</p> Signup and view all the answers

    What is the cost of propellant per kilogram for the Ariane IV?

    <p>60 F / Kg (B)</p> Signup and view all the answers

    How does the mass at lift-off of the Ariane IV compare to that of the Boeing 747-300?

    <p>Boeing 747-300 is heavier than Ariane IV (A)</p> Signup and view all the answers

    What is the maximum thrust of the Vinci engine?

    <p>180 kN (D)</p> Signup and view all the answers

    How many times can the Vinci engine be reignited?

    <p>5 times (C)</p> Signup and view all the answers

    What type of propellant is used in the Vinci engine?

    <p>LOX - LH2 (C)</p> Signup and view all the answers

    What is the combustion pressure of the Vinci engine?

    <p>60 bar (B)</p> Signup and view all the answers

    Which nozzle type is mentioned for the Vinci engine?

    <p>Deployable nozzle (A)</p> Signup and view all the answers

    What cycle does the Vinci engine operate on?

    <p>Expander cycle (C)</p> Signup and view all the answers

    What is the thrust of the Aestus engine used in the Ariane 5 Upper Stage?

    <p>29 kN (A)</p> Signup and view all the answers

    What is one example of a staged combustion engine?

    <p>SSME (C)</p> Signup and view all the answers

    What is indicated about the deployable nozzle for the A6 upper stage?

    <p>It is not deployable (D)</p> Signup and view all the answers

    Which propellant is used in the Aestus engine?

    <p>MMH – N2O4 (A)</p> Signup and view all the answers

    What is the specific impulse (Isp) of the Aestus engine?

    <p>324 s (C)</p> Signup and view all the answers

    What is the mass of the Aestus engine?

    <p>125 kg (C)</p> Signup and view all the answers

    What is the diameter of the Aestus engine?

    <p>1.3 m (A)</p> Signup and view all the answers

    At what combustion pressure does the Aestus engine operate?

    <p>10.5 bar (D)</p> Signup and view all the answers

    What is the tank pressure condition for the Aestus engine?

    <p>18.5 bar (A)</p> Signup and view all the answers

    Which engine is associated with the expand cycle method for Ariane 5?

    <p>Vinci (A)</p> Signup and view all the answers

    What does the acronym LH2 stand for in the context of the diagram?

    <p>Liquid Hydrogen (B)</p> Signup and view all the answers

    Which component represents coolant in the provided schematic?

    <p>GAM Oil (D)</p> Signup and view all the answers

    What is the primary role of LOX in the diagram?

    <p>Oxidizer (B)</p> Signup and view all the answers

    Which gas is indicated as being heated before its use in the system?

    <p>GCh + GHe (D)</p> Signup and view all the answers

    What purpose does the component marked as 'CP' serve in the schematic?

    <p>Control Panel (D)</p> Signup and view all the answers

    Which of the following gases is used as a propellant in the system?

    <p>GH2 (D)</p> Signup and view all the answers

    In the context of this schematic, what does 'VGC' represent?

    <p>Vent Gas Collector (B)</p> Signup and view all the answers

    What is the significance of 'TP LH2' in the fluid schematic?

    <p>Transfer Pipe liquid hydrogen (D)</p> Signup and view all the answers

    Which component serves as the main fuel in the system?

    <p>LH2 (D)</p> Signup and view all the answers

    Which of these components is responsible for the combustion process in the engine?

    <p>CBJTH (B)</p> Signup and view all the answers

    What is the function of the 'VCO' in the schematic?

    <p>Ventilation Control Output (B)</p> Signup and view all the answers

    What type of liquid is represented as 'GOX + GHe' in the diagram?

    <p>Gaseous Oxygen with Gaseous Helium (A)</p> Signup and view all the answers

    Which component is usually positioned to manage pressurizing gases?

    <p>VCH (D)</p> Signup and view all the answers

    Study Notes

    Ariane 5

    • The Ariane 5 is a reference launch vehicle
    • It has had 76 successful launches
    • 90 launches since June 4, 1996

    Newton's Third Law

    • When one body applies a force on another, the second body simultaneously applies an equal and opposite force on the first body.
    • This principle is fundamental to rocket propulsion.

    Newton's Third Law: Rocket Engines

    • The force generated by the gas pressure within a rocket engine's combustion chamber is not balanced by an outside force.
    • The difference in pressure between inside and outside the chamber propels the rocket upward, opposing the direction of the escaping gas.

    Tsiolkovsky Equation

    • The equation describes the change in velocity of a rocket as fuel is expelled.
    • It considers the initial mass of the rocket, alongside the expelled fuel at a constant speed relative to the rocket.
    • The speed of the expelled fuel stays constant during the time interval, known as v.

    Rocket Thrust

    • The thrust of a propelled system is calculated according to the Euler equation.
    • Thrust is calculated by the product of the mass flow rate of expelled gas (m), the exhaust velocity (v), plus the pressure difference (P - P) multiplied by the exit plane area (A).

    Exhaust Velocity

    • Exhaust velocity is derived from the gas's kinetic energy change in enthalpy as it cools and expands within the nozzle.
    • This process exemplifies the conservation of total enthalpy between the combustion chamber and nozzle exit, assuming no entropy change.
    • Exhaust velocity is significantly higher (ve) than the rocket's velocity (V), within a combustion chamber with a relatively low Mach number.
    • For isentropic expansion with perfect gases, an equation allows for exhaust velocity calculation.

    Thrust Ratio Coefficient

    • The Thrust Ratio Coefficient (CF) illustrates the nozzle efficiency in extracting energy from hot gas within the combustion chamber.
    • Formula for the perfect gas assumption is available.

    Characteristic Velocity

    • The characteristic velocity (c*) represents the efficiency measurement of a rocket's combustion process.
    • Perfect gas assumption yields a specific equation.
    • An example is provided for H2/O2.

    Specific Impulse

    • Specific impulse measures a rocket's efficiency, relating force to the propellant used per unit time.
    • A higher specific impulse implies less propellant is needed for a given thrust or delta V.
    • Specific impulse (Isp) and the vacuum specific impulse (Isp vacuum) are linked by a set formula.

    Essential Relations

    • Variations in chamber pressure minimally impact a rocket's performance.
    • Conversely, only a slight increase in combustion efficiency noticeably improves performance.

    Propulsion Parameters

    • The delta-V is an extremely important parameter for propulsion calculations.
    • The delta-V is connected to the specific impulse (Isp), initial and final mass.

    Choice of Propellants

    • The fuel and oxidizer combination, the ratio thereof, the temperature at combustion and the exhaust velocity are significant parts of choosing a propellant.
    • Tables of various fuels, oxidizers, and their ratios, combustion temperatures and exhaust velocity values, and propellant mean density are offered for comparison.

    RM & Optimization

    • Mixture Ratio (RM) in propulsion science, signifying the ratio of oxidizer to fuel mass, is a critical parameter, particularly for combinations such as H2/O2.

    European Launchers

    • The evolution of Ariane launchers, from Ariane I to Ariane 5, along with associated details of price, flight duration, lifetime, mass at launch, thrust, cost, and propellant quantities and payload capacities, is described.

    Russian Launchers

    • Various Russian launchers, their characteristics, including the Energia and Soyuz rocket, and their different attributes are detailed, including height, mass at launch, propellant quantities and lifetime, as well as thrust data.

    Chemical Propulsion Systems

    • Various propulsion types (liquid/gas, solid, hybrid) and their attributes are presented
    • Details of design, ignition, operational conditions, and use are given for each type.

    Solid Propulsion

    • Solid propellants are used in various grain shapes and forms.
    • Solid propellant burn time and thrust characteristics depend on the grain shape and size.
    • Solid propellant manufacturing and composition information are noted.

    Solid Propellant Combustion Modeling

    • The burning rate (Vc), also an essential factor, depends on chamber pressure, initial propellant temperature, propellant composition, and granulometry (grain size).
    • Numerical simulations account for propellant geometry to accurately model solid propellant burning.

    Solid Propellant Combustion Instabilities

    • Combustion instabilities are a significant challenge in solid rocket propulsion models due to challenging measurements.
    • Numerical solutions are used to study complex multi-dimensional and multi-physics conditions.

    Ariane 5 EAP

    • Provides a summary of the Ariane 5 EAP stage performance in terms of burn time, thrust, pressure, mass quantities, dimensions and other performance metrics.

    Ariane Engines

    • Various Ariane engines (HM7, Vulcain, Vulcain 2, Vinci, etc.) are presented along with the respective years of introduction, along with other data.

    Gas Generator Cycle

    • Detailed descriptions and schematics of how gas generator cycles function in various engines (Vulcain, Vulcain 2, HM7B).

    Pressure-Fed Cycle

    • Overview of the pressure-fed cycle engine design, including propellant types and associated masses.

    Expander Cycle

    • Engine operation in an expander cycle, with propellant types, thrust, and cycle duration highlighted.

    Staged Combustion Engines

    • Introduction to staged combustion engines (SSME, RD0120) and their design features.

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    Related Documents

    Ariane 5 Propulsion Fundamentals - PDF

    Description

    Test your knowledge about the engines used in the Ariane series of rockets. This quiz covers engines associated with Ariane 4, Ariane 5, and Aestus, along with related information about the documentation's significance and ownership. See how much you know about these key elements in aerospace engineering!

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