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The Design – Analysis of a Rocket Transient State Supersonic Flow Simulation | ANSYS Fluent

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A rocket is a missile, spacecraft, aircraft, or another vehicle that obtains thrust from a rocket engine. Rocket engine exhaust is formed entirely from the propellant carried within the rocket. Rocket engines work by action and reaction and push rockets forward simply by expelling their exhaust in the opposite direction at high speed and can, therefore work in the vacuum of space.

In fact, rockets work more efficiently in space than in an atmosphere. Multistage rockets are capable of attaining escape velocity from Earth and therefore can achieve unlimited maximum altitude. Compared with airbreathing engines, rockets are lightweight and powerful and capable of generating large accelerations. To control their flight, rockets rely on momentum, airfoils, auxiliary reaction engines, gimballed thrust, momentum wheels, deflection of the exhaust stream, propellant flow, spin, or gravity.

Rocket propellant is mass that is stored, usually in some form of propellant tank or casing, before being used as the propulsive mass that is ejected from a rocket engine in the form of a fluid jet to produce thrust. For chemical rockets often the propellants are a fuel such as liquid hydrogen or kerosene burned with an oxidizer such as liquid oxygen or nitric acid to produce large volumes of very hot gas. The oxidizer is either kept separate and mixed in the combustion chamber or comes premixed, as with solid rockets.

Sometimes the propellant is not burned but still undergoes a chemical reaction, and can be a ‘monopropellant’ such as hydrazine, nitrous oxide, or hydrogen peroxide that can be catalytically decomposed to hot gas.

Alternatively, an inert propellant can be used that can be externally heated, such as in steam rocket, solar thermal rocket, or nuclear thermal rockets.

For smaller, low-performance rockets such as attitude control thrusters where high performance is less necessary, a pressurized fluid is used as a propellant that simply escapes the spacecraft through a propelling nozzle.

Alternatively, an inert propellant can be used that can be externally heated, such as in steam rocket, solar thermal rocket, or nuclear thermal rockets.

For smaller, low-performance rockets such as attitude control thrusters where high performance is less necessary, a pressurized fluid is used as a propellant that simply escapes the spacecraft through a propelling nozzle.

In this analysis, we tried to Analysis of a Rocket Transient State Supersonic Flow Simulation by ANSYS Fluent software.

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The Design – Analysis of a Rocket Steady State Supersonic Flow Simulation | ANSYS Fluent

A rocket is a missile, spacecraft, aircraft, or another vehicle that obtains thrust from a rocket engine. Rocket engine exhaust is formed entirely from the propellant carried within the rocket. Rocket engines work by action and reaction and push rockets forward simply by expelling their exhaust in the opposite direction at high speed and can, therefore work in the vacuum of space.

In fact, rockets work more efficiently in space than in an atmosphere. Multistage rockets are capable of attaining escape velocity from Earth and therefore can achieve unlimited maximum altitude. Compared with airbreathing engines, rockets are lightweight and powerful and capable of generating large accelerations. To control their flight, rockets rely on momentum, airfoils, auxiliary reaction engines, gimballed thrust, momentum wheels, deflection of the exhaust stream, propellant flow, spin, or gravity.

Rocket propellant is mass that is stored, usually in some form of propellant tank or casing, prior to being used as the propulsive mass that is ejected from a rocket engine in the form of a fluid jet to produce thrust. For chemical rockets often the propellants are a fuel such as liquid hydrogen or kerosene burned with an oxidizer such as liquid oxygen or nitric acid to produce large volumes of very hot gas. The oxidizer is either kept separate and mixed in the combustion chamber or comes premixed, as with solid rockets.

Sometimes the propellant is not burned but still undergoes a chemical reaction, and can be a ‘monopropellant’ such as hydrazine, nitrous oxide, or hydrogen peroxide that can be catalytically decomposed to hot gas.

Alternatively, an inert propellant can be used that can be externally heated, such as in steam rocket, solar thermal rocket, or nuclear thermal rockets.

For smaller, low-performance rockets such as attitude control thrusters where high performance is less necessary, a pressurized fluid is used as a propellant that simply escapes the spacecraft through a propelling nozzle.

Alternatively, an inert propellant can be used that can be externally heated, such as in steam rocket, solar thermal rocket, or nuclear thermal rockets.

For smaller, low-performance rockets such as attitude control thrusters where high performance is less necessary, a pressurized fluid is used as a propellant that simply escapes the spacecraft through a propelling nozzle.

In this analysis, we tried to Analysis of a Rocket Transient State Supersonic Flow Simulation by ANSYS Fluent software.

Geometry & Grid

Geometry and mesh have been generated in Design Modeler and Ansys meshing software respectively. Cell types are unstructured. ANSYS Meshing software has been used for meshing including 383239 elements, and 104677 nodes.

Model

In this analysis, k-epsilon Realizable model has been used to simulate the flow turbulency flow. In this analysis, a pressure-based & transient solver is used.

Boundary Condition

The inlet has been defined as Velocity Inlet. The outlet is considered a pressure-outlet condition.

Discretization of Equations

To solve the equations, the COUPLED algorithm is used in the second-order model. Finally, results are represented as Mach Number and Pressure contours.

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