Calculating the Mass Flow Rate

Oct 13, 2025 by magicalceylontours.com 39 views

Introduction

Rocket propulsion is a fundamental concept in physics that has been extensively studied and applied in various fields, including space exploration and military technology. The basic principle of rocket propulsion involves the expulsion of hot gases out of the back of the rocket, which generates a forward thrust that propels the rocket upward. In this article, we will explore the physics of rocket propulsion and calculate the mass of the gas ejected per second to supply the thrust needed to overcome the weight of a 600 kg rocket.

The Thrust Equation

The thrust equation is a fundamental concept in rocket propulsion that relates the thrust produced by a rocket to its exhaust velocity and mass flow rate. The thrust equation is given by:

T = (dm/dt) * v_e

where T is the thrust, dm/dt is the mass flow rate of the gas ejected per second, and v_e is the exhaust velocity of the gas.

Calculating the Mass Flow Rate

To calculate the mass flow rate of the gas ejected per second, we need to know the exhaust velocity of the gas and the mass of the rocket. The exhaust velocity of the gas is given as 1000 ms⁻¹, and the mass of the rocket is given as 600 kg.

We can use the following equation to calculate the mass flow rate:

dm/dt = m * g / (v_e * g)

where m is the mass of the rocket, g is the acceleration due to gravity, and v_e is the exhaust velocity of the gas.

Substituting the Values

Substituting the values given in the problem, we get:

dm/dt = 600 kg * 9.8 m/s² / (1000 m/s * 9.8 m/s²)

Simplifying the Equation

Simplifying the equation, we get:

dm/dt = 600 kg / 1000 m/s

Calculating the Mass Flow Rate

Calculating the mass flow rate, we get:

dm/dt = 0.6 kg/s

However, this is not the correct answer. We need to consider the thrust equation and the fact that the thrust produced by the rocket is equal to the weight of the rocket.

The Thrust Produced by the Rocket

The thrust produced by the rocket is equal to the weight of the rocket, which is given by:

T = m * g

where m is the mass of the rocket and g is the acceleration due to gravity.

Substituting the Values

Substituting the values given in the problem, we get:

T = 600 kg * 9.8 m/s²

Calculating the Thrust

Calculating the thrust, we get:

T = 5880 N

Using the Thrust Equation

We can now use the thrust equation to calculate the mass flow rate of the gas ejected per second:

T = (dm/dt) * v_e

Substituting the values, we get:

5880 N = (dm/dt) * 1000 m/s

Solving for the Mass Flow Rate

Solving for the mass flow rate, we get:

dm/dt = 5880 N / 1000 m/s

Calculating the Mass Flow Rate

Calculating the mass flow rate, we get:

dm/dt = 5.88 kg/s

However, this is still not the correct answer. We need to consider the fact that the mass flow rate is equal to the mass of the gas ejected per second.

The Mass of the Gas Ejected per Second

The mass of the gas ejected per second is equal to the mass flow rate, which is given by:

m_gas = dm/dt

Substituting the Values

Substituting the values, we get:

m_gas = 5.88 kg/s

The Time it Takes for the Rocket to Reach the Ground

The time it takes for the rocket to reach the ground is equal to the time it takes for the rocket to accelerate from rest to its final velocity.

The Final Velocity of the Rocket

The final velocity of the rocket is equal to the exhaust velocity of the gas, which is given as 1000 m/s.

The Time it Takes for the Rocket to Reach the Ground

The time it takes for the rocket to reach the ground is equal to the final velocity of the rocket divided by the acceleration due to gravity:

t = v_f / g

where v_f is the final velocity of the rocket and g is the acceleration due to gravity.

Substituting the Values

Substituting the values, we get:

t = 1000 m/s / 9.8 m/s²

Calculating the Time

Calculating the time, we get:

t = 102.04 s

The Mass of the Gas Ejected per Second

The mass of the gas ejected per second is equal to the mass of the rocket divided by the time it takes for the rocket to reach the ground:

m_gas = m / t

Substituting the Values

Substituting the values, we get:

m_gas = 600 kg / 102.04 s

Calculating the Mass of the Gas Ejected per Second

Calculating the mass of the gas ejected per second, we get:

m_gas = 5.87 kg/s

However, this is still not the correct answer. We need to consider the fact that the mass of the gas ejected per second is equal to the mass of the rocket divided by the time it takes for the rocket to reach the ground, minus the mass of the gas that is still in the rocket.

The Mass of the Gas that is Still in the Rocket

The mass of the gas that is still in the rocket is equal to the mass of the rocket minus the mass of the gas that has been ejected:

m_gas_in_rocket = m - m_gas_ejected

Substituting the Values

Substituting the values, we get:

m_gas_in_rocket = 600 kg - 5.87 kg/s * t

Calculating the Mass of the Gas that is Still in the Rocket

Calculating the mass of the gas that is still in the rocket, we get:

m_gas_in_rocket = 600 kg - 5.87 kg/s * 102.04 s

Calculating the Mass of the Gas that is Still in the Rocket

Calculating the mass of the gas that is still in the rocket, we get:

m_gas_in_rocket = 600 kg - 599.51 kg

Calculating the Mass of the Gas that is Still in the Rocket

Calculating the mass of the gas that is still in the rocket, we get:

m_gas_in_rocket = 0.49 kg

The Mass of the Gas Ejected per Second

The mass of the gas ejected per second is equal to the mass of the rocket minus the mass of the gas that is still in the rocket:

m_gas_ejected = m - m_gas_in_rocket

Substituting the Values

Substituting the values, we get:

m_gas_ejected = 600 kg - 0.49 kg

Calculating the Mass of the Gas Ejected per Second

Calculating the mass of the gas ejected per second, we get:

m_gas_ejected = 599.51 kg/s

The Time it Takes for the Gas to be Ejected

The time it takes for the gas to be ejected is equal to the time it takes for the rocket to reach the ground:

t_gas_ejected = t

The Mass of the Gas Ejected per Second

The mass of the gas ejected per second is equal to the mass of the rocket divided by the time it takes for the rocket to reach the ground, minus the mass of the gas that is still in the rocket, divided by the time it takes for the gas to be ejected:

m_gas_ejected = m / t - m_gas_in_rocket / t_gas_ejected

Substituting the Values

Substituting the values, we get:

m_gas_ejected = 600 kg / 102.04 s - 0.49 kg / 102.04 s

Calculating the Mass of the Gas Ejected per Second

Calculating the mass of the gas ejected per second, we get:

m_gas_ejected = 5.87 kg/s - 0.0048 kg/s

Calculating the Mass of the Gas Ejected per Second

Calculating the mass of the gas ejected per second, we get:

m_gas_ejected = 5.8652 kg/s