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  • Rocket Thrust Equations - NASA
    On this slide, we have collected all of the equations necessary to calculate the thrust of a rocket engine In a rocket engine, stored fuel and stored oxidizer are ignited in a combustion chamber The combustion produces great amounts of exhaust gas at high temperature and pressure
  • Ion Thruster Performance Analysis: Thrust Calculation
    This calculator provides the calculation of thrust produced by an ion thruster Calculation Example: Ion thrusters are a type of electric propulsion that uses the principle of ion acceleration to produce thrust They are characterized by their high specific impulse, which makes them suitable for long-duration missions
  • rockets - Ion Thruster Thrust Calculation Problem - Space Exploration . . .
    The thrust is equal to the mass and velocity of one nitrogen ion times the number of ions per second, for which you are using the maximum current of the transformer: $$F = \frac{dp}{dt} = m_{N_2} \ v \ \frac{dn}{dt} = m_{N_2} \ v \ I \ \times \ 6 2 \times 10^{18},$$
  • Lecture 2 Thrust Equation, Nozzles and Definitions - Stanford University
    Advanced Rocket Propulsion Stanford University • Combined to obtain the thrust force • Introduce the mass flow rate: • Two terms can be combined by introducing the effective exhaust velocity, V e • Maximum thrust for unit mass flow rate requires – High exit velocity – High exit pressure • This cannot be realized
  • Rocket Thrust Calculator - CalcTool
    You will meet the equation, learn how to calculate the thrust of a rocket and its element, the importance of pressure, mass, and velocity on the performance of a rocket, and an example of the application of the rocket thrust equation
  • Electrostatic Propulsion Ion Engines (Ion Thrusters)
    AE6450 Rocket Propulsion Electrostatic Thruster Power - Losses • Ionization losses –energy used to create ions (e g , Xe Xe+) –minimum loss given by ionization potential ( I) for atom (typically 4-20 eV, electron volts) times current • Thrust correction –beam divergence, multiple ionization, sputtering (ion impacts on grid)
  • Lecture 2: Rocket Nozzles and Thrust Rocket Thrust (Thermal rockets)
    So, momentum balance gives the Thrust Equation What does an Energy Balance give? Start with a near-stagnant flow in the upstream plenum (“combustion chamber”, or “nuclear heater” or “arc heated plenum”) The total specific enthalpy 1 2 2 hh tc =+ c υ c ≅h c may be different for different streamlines, due to combustion
  • Thrust Equations Summary | Glenn Research Center | NASA
    On this slide, we have collected all of the equations necessary to calculate the thrust of a rocket engine In a rocket engine, stored fuel and stored oxidizer are ignited in a combustion chamber The combustion produces great amounts of exhaust gas at high temperature and pressure
  • Worked Example #5 Calculate the ideal Thrust and Thrust Coefficient
    Calculate the ideal Thrust and Thrust Coefficient for a rocket motor operating at 68 atmospheres chamber pressure and exhausts to ambient The nozzle has a throat diameter of 10mm and has an exit diameter of 20mm The nozzle exit pressure is 4 atmospheres The propellant is KNSB Po = Stagnation pressure (chamber pressure), 68 atmospheres
  • ION THRUSTER THRUST VECTORING BY GRID TRANSLATION - Electric Rocket
    Three-dimensional and two-dimensional Particle-in-Cell simulation codes were developed to calculate the ion beam deflection phenomena by grid translation in ion thrusters Beamlet behavior in ion optics with ordinal circular apertures and slit apertures was simulated using these codes





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