The trajectory I'm attaching is a repeating free-return trajectory that encounters the moon once every 5 spacecraft orbits around the Earth. I'll attach some plots to show the kinds of cool trajectories you can get when you include the Earth and Moon's gravity fields. For example, the way I simulate this is by numerically integrating this 1st order state space differential equations: You can use ode45 to call a function that including the equations of motion describing the acceleration felt by the spacecraft due to the influence of the Earth and the Moon. You may want to consider numerically integrating the relative equations of motion that describe the acceleration of two point sources moving in circular motion around one another. Have you considered simulating the Circular Restricted Three-Body Problem (CR3BP)? Your simulations look great! It might be time for you to graduate to a higher fidelity model. Quote from: C5C6 on 06:37 pm Hi!! I'm trying to make an orbit simulation with Matlab, and I'm having some trouble making it simulate real scenarios such as the ISS, the Moon or a sattelite in Geosynchronous orbit. Hope you enjoy it, greetings from Argentina!!! I tried to calculate this geosynchronous orbit with the regular orbital speed of 3 km/s but it just 'fell to earth'. Here you got a trajectory calculated with a mass of 14000 kg, an initial orbital speed of 300000 m/s (yes, 300 km/s!! ), and a starting distance of 35786 km. I'll obviously never be able to simulate it perfectly, but there's something I'm missing and I'm apologizing for any lack of respect to y'all by trying to simplify something so complex in some few potentially wrongly-designed equations. (escala_tiempo is a variable used to make the simulation faster) Gravedad = -((G*(masa_tierra*masa_satelite))/(distancia^2)) Īcc_tierra_y = gravedad*abs(sin(angulo)) Īcc_tierra_x = gravedad*abs(cos(angulo)) Vel_sat_y = vel_sat_y + acc_tierra_y*escala_tiempo ĭistancia = sqrt(pos_sat_y^2+pos_sat_x^2) Vel_sat_x = vel_sat_x + acc_tierra_x*escala_tiempo Pos_sat_y = pos_sat_y + vel_sat_y*escala_tiempo Pos_sat_x = pos_sat_x + vel_sat_x*escala_tiempo The sattelite is given an initial distance from the center of the earth, an initial orbital speed and a mass. The key is the orbital speed, I believe my mistake is here. The Earth does not move, it's not affected by the satellite's gravitational pull. My model is extremely simple, I avoided so many facts I'm kind of embarassed presenting this here, but perhaps you could help me with some advices.īasically what I did was just consider the gravitational attraction between two spots in a cartesian coordinate system. Hi!! I'm trying to make an orbit simulation with Matlab, and I'm having some trouble making it simulate real scenarios such as the ISS, the Moon or a sattelite in Geosynchronous orbit.
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