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High power rocket simulation
High power rocket simulation












high power rocket simulation

This is a relatively high drag coefficient airfoils, for comparison, have values of C D well below 0.05.Īir density is more complicated to calculate, because it will decrease exponentially as the rocket ascends through the atmosphere. The drag coefficient is difficult to determine without making physical tests on the rocket, but we will assume a value of C D = 0.75, which represents a flying shape somewhere between a cylinder and a cone. The diameter of each rocket is given, so A will be known. Where ρ is the air density (kg/m 3), v is the velocity of the rocket, C D is the drag coefficient, a A is the cross-sectional area of the rocket.

#High power rocket simulation skin#

The equation for drag force due to atmospheric skin friction is: Atmospheric drag, a form of parasitic drag, is a damping force opposite to the rocket’s motion due to skin friction between the surrounding air molecules and the surface of the rocket.

high power rocket simulation

The drag acting on the rocket can be separated into two components: atmospheric drag and wave drag. However, we can also assume that a rocket flying at any non-zero angle would generate a small amount of aerodynamic lift that would counteract this reduction in vertical thrust. Therefore the actual vertical component of the thrust would be slightly lower than it is here. In a realistic rocket flight, the rocket would launch perpendicular to the surface, and then rotate by a small degree in flight to begin forming a parabolic trajectory. It is important to note that this model is purely one-dimensional.

high power rocket simulation

Therefore: t he thrust force is dependent on time only. The constant value of the thrust will be known for each rocket model used in the simulation. In other words, the thrust force is a constant up until the time at which the rocket runs out of fuel, after which it is zero. A mathematical representation of the thrust force could be: For the sake of the project, we are assuming that the thrust of the model rocket is constant for the duration of the ascent.

high power rocket simulation

For a liquid-fuel rocket, thrust would be controlled during the ascent by a throttle, responding to rocket performance and adjusting thrust over time to control the trajectory. The majority of all rockets which have entered into orbit have been liquid-fuel rockets, as opposed to solid-fuel rockets (the notable exception being the Space Shuttle, which uses both). Finally, we will see the results of this simulation for different rocket models. In this article I will explore each term of the equation of motion, covering the various dependencies that must be accounted for in the code, as well as any assumptions or simplifications made. The equation of motion for a rocket is therefore: The biggest difference between the two problems is that because a rocket’s thrust force is much larger than any damping forces, it will not exhibit chaotic motion like the pendulum. In the case of rocket motion, these forces are represented by the rocket’s weight, atmospheric and wave drags, and its thrust force. At the most basic level, the equation of motion for a rocket can be treated in the same way as the damped driven pendulum - both are affected by three forces: gravitational force, a damping drag force, and a driving force. One example involved the Euler-Cromer method for solving the equation of motion for a pendulum both damped by atmospheric elements and driven by an outside force. In PHYS 375 we have studied several applications for numerical methods in solving otherwise impossible, or at least prohibitively difficult, differential equations.














High power rocket simulation