I need actual data for the international space station (ISS) position vector so I can create the orbit. I tried to copy the SGP4 propagator in the Space Track website in MATLAB, but I could not manage to run it. Can you give me the data or the code to run the propagator?
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I need actual data for the international space station (ISS) position

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- I created an orbit of the ISS in MATLAB. I want to validate my data. How and where can I get actual data of the ISS orbit? I would need the time history of the position vectors?Can you help me with a matlab code? I am trying to plot the keplerian orbital elements over time. I would usually find the orbit using cartesian system and then transform into keplerian orbital elements. Is there a way to directly integrate keplerian orbital elements?Please assist with this question. I reviewed the lecture notes that was given and do not understand. Please answer with a detailed explanation. Thank you. I believe there is an easier way to solve this using matlab apparently but I dont know. I will have an image of the reference slide.
- I created a MATLAB code to plot the orbit of a satellite at an altitude of 300 km (LEO). I wanted to propagate my code for 2 revolutions but instead I used (180*60) because it takes 90 minutes to make a full rotation around the earth in LEO. Is that correct? Also, if I wanted to use revolutions how would I propagate it for 2 revs? Would my t = [0 4*pi].Please examine how you got answer step by step pleaseI am trying to code in MATLAB the equations of motion for malankovich orbitlal elements. But, I am having a problem with the B matrix. Since f matrix is 7x1 and a_d matrix has to be 3x1, the B matrix has to be 7x3. I don't know how that is possible. Can you break down the B matrix for me and let me know what size it is?
- I want to run the SGP4 propagator for the ISS (ID = 25544) I got from spacetrack.org in MATLAB. I don't know where to get the inputs of the function. Where do I get the inFile and outFile that is mentioned in the following function. % Purpose: % This program shows how a Matlab program can call the Astrodynamic Standard libraries to propagate % satellites to the requested time using SGP4 method. % % The program reads in user's input and output files. The program generates an % ephemeris of position and velocity for each satellite read in. In addition, the program % also generates other sets of orbital elements such as osculating Keplerian elements, % mean Keplerian elements, latitude/longitude/height/pos, and nodal period/apogee/perigee/pos. % Totally, the program prints results to five different output files. % % % Usage: Sgp4Prop(inFile, outFile) % inFile : File contains TLEs and 6P-Card (which controls start, stop times and step size) % outFile : Base name for five output files %…hi ive have nearly completed this model but i am stuck on a couple last parts. Firstly, the holes on the top need to be placed 30 degrees from the y axis as shown in the handout but also the middle part is meant to have triangular "supports" rather than rectangular and im not sure how to cut them down. This is in autodesk inventor but any help here would be appreciated Once again just the top holes being moved 30 degrees and the support being cut down to the triangular shape shown in the handoutYou walk along the beach towards a dock while your friend rows a boat towards the same dock on a flat lake. Your friend's boat approaches the dock on a straight course, but also rotates about its center-of-mass since your friend is not pulling evenly on the oars. If you knew your own velocity (vwalker), the magnitude of boat's angular velocity (thetaboat), and radius vector from yourself to your friend in the boat (rfriend) at any given time, you could use the following equation to calculate the your friend's velocity: vfriend = vwalker + (thetaboat)k x rfriend where k is a unit vector in the vertical direction. True False

