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Rocket Calculator: Input the properties of a rocket and its orbit to determine possible orbital maneuvers

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AERSP 424 Final Project

Initial Setup:

  1. Download all files

  2. Using CMake, build the solution

  3. Run the program

This program has 2 distinct interactive menus:

  1. Rocket Builder

  2. TLE Loader

ROCKET BUILDER

In the Rocket Builder menu, choose to either Select from one of the Pre-Made Rockets or Build your Own

  1. Premade Rockets: Pick the file that corresponds to the rocket you wish to use.

    Tip: You can make your own premade rocket by creating a .txt file and following the format given in .../ReferenceMaterial/Rocket_Data_Info.txt

  2. Build your Own:

    a. Name the rocket

    b. Choose the number of stages you want your rocket to have (A tab will open up for every stage)

    c. Enter the values for the structural mass, fuel mass, and the engine's specific impulse for each stage

    Tip: You can simulate the final payload by including a fuel weight of 0 in the final stage

    d. Click done

    e. Next, choose how much fuel you want to expend and some optional additional parameters such as the orbit altitude or the launch site location.

    f. Click calculate. The computer will output the delta-V obtained from burning the specified amount of fuel as well as possible orbit manuever options.

TLE Loader

In TLE loader, choose either from Load TLE from File or Select from available TLE data

  1. Loading TLE from file

    a. In the dialogue box, enter the full filepath and name of the TLE file to import into the program

  2. Select from available TLE data

    a. Choose from one of the example data files to see the data associated with that satellite

Notes

All of the custom-built functions that this program needs is in a static library whose source code is inaccessible. The original source code for these functions can be found in the file names beginning with "Archived" located in the src folder.

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Rocket Calculator: Input the properties of a rocket and its orbit to determine possible orbital maneuvers

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