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Write a program which simulates the launch of a rocket. Solve the differential equations for the velocity, acceleration and mass loss for the rocket using Euler's method, with a suitable time step. Assuming different amounts of fuel mass and thrust, investigate whether the rocket escapes into space, reaches orbit or falls back to Earth? The force (F) acting on a rocket of mass (m) are given by: F = -mg D+T for v > 0 F = - -mg+D-T for v<0 where mg is force of gravity, D is drag, T is thrust and v is velocity of the rocket. The air resistance force (drag force) on an object moving with speed v can be approximated by Fdrag = -0.5CpAv², where p is the air density and A is the cross section. The drag coefficient C depends on an object's shape and for a rocket we can assume C~0.1 The thrust of a rocket depends on the rate of propellant mass loss (fuel) and the exhaust velocity (Vexhaust), T = m fuel Vexhaust The density of the atmosphere can be approximated as p = poe-h/ho, where h is the current altitude, ho = 1.0 × 104 m, and po is air density at sea level (po = 1.25 kg m-³).

Write a program which simulates the launch of a rocket. Solve the differential equations for the velocity, acceleration and mass loss for the rocket using Euler's method, with a suitable time step. Assuming different amounts of fuel mass and thrust, investigate whether the rocket escapes into space, reaches orbit or falls back to Earth? The force (F) acting on a rocket of mass (m) are given by: F = -mg D+T for v > 0 F = - -mg+D-T for v<0 where mg is force of gravity, D is drag, T is thrust and v is velocity of the rocket. The air resistance force (drag force) on an object moving with speed v can be approximated by Fdrag = -0.5CpAv², where p is the air density and A is the cross section. The drag coefficient C depends on an object's shape and for a rocket we can assume C~0.1 The thrust of a rocket depends on the rate of propellant mass loss (fuel) and the exhaust velocity (Vexhaust), T = m fuel Vexhaust The density of the atmosphere can be approximated as p = poe-h/ho, where h is the current altitude, ho = 1.0 × 104 m, and po is air density at sea level (po = 1.25 kg m-³).

Database System Concepts
Database System Concepts
7th Edition
ISBN:9780078022159
Author:Abraham Silberschatz Professor, Henry F. Korth, S. Sudarshan
Publisher:Abraham Silberschatz Professor, Henry F. Korth, S. Sudarshan
Chapter1: Introduction
Section: Chapter Questions
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In python with Eulers method please:

Write a program which simulates the launch of a rocket. Solve the differential equations for the velocity, acceleration and mass loss for the rocket using Euler's method, with a suitable time step. Assuming different amounts of fuel mass and thrust, investigate whether the rocket escapes into space, reaches orbit or falls back to Earth? The force (F) acting on a rocket of mass (m) are given by: F = -mg D+T for v > 0 F = - -mg+D-T for v<0 where mg is force of gravity, D is drag, T is thrust and v is velocity of the rocket. The air resistance force (drag force) on an object moving with speed v can be approximated by Fdrag = -0.5CpAv², where p is the air density and A is the cross section. The drag coefficient C depends on an object's shape and for a rocket we can assume C~0.1 The thrust of a rocket depends on the rate of propellant mass loss (fuel) and the exhaust velocity (Vexhaust), T = m fuel Vexhaust The density of the atmosphere can be approximated as p = poe-h/ho, where h is the current altitude, ho = 1.0 × 104 m, and po is air density at sea level (po = 1.25 kg m-³).
Transcribed Image Text:Write a program which simulates the launch of a rocket. Solve the differential equations for the velocity, acceleration and mass loss for the rocket using Euler's method, with a suitable time step. Assuming different amounts of fuel mass and thrust, investigate whether the rocket escapes into space, reaches orbit or falls back to Earth? The force (F) acting on a rocket of mass (m) are given by: F = -mg D+T for v > 0 F = - -mg+D-T for v<0 where mg is force of gravity, D is drag, T is thrust and v is velocity of the rocket. The air resistance force (drag force) on an object moving with speed v can be approximated by Fdrag = -0.5CpAv², where p is the air density and A is the cross section. The drag coefficient C depends on an object's shape and for a rocket we can assume C~0.1 The thrust of a rocket depends on the rate of propellant mass loss (fuel) and the exhaust velocity (Vexhaust), T = m fuel Vexhaust The density of the atmosphere can be approximated as p = poe-h/ho, where h is the current altitude, ho = 1.0 × 104 m, and po is air density at sea level (po = 1.25 kg m-³).
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