Earth-to-Mars End-to-End Mission Design – SNOPT

版本 1.0.0 (16.4 MB) 作者: David Eagle
Design and optimize a trajectory from Earth park orbit to encounter at Mars using the SNOPT nonlinear programming algorithm.
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更新时间 2024/11/17

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This submission is a MATLAB script named e2m_matlab_snopt that can be used to design and optimize ballistic interplanetary missions from a Earth park orbit to encounter at Mars. The software assumes that interplanetary injection occurs impulsively from a circular park orbit. The type of final Mars-centered (areocentric) mission “targeting” and the target values are defined by the user.
The first part of this MATLAB script solves for the minimum delta-v using a zero-sphere-of-influence (ZSOI), two-body Lambert solution for the heliocentric transfer trajectory from Earth to Mars. Using this solution as an initial guess, the second part implements a simple shooting method that attempts to optimize the characteristics of the geocentric injection hyperbola while numerically integrating the spacecraft’s geocentric and heliocentric equations of motion and targeting to user-defined mission constraints at Mars.
The spacecraft motion within the Earth’s sphere-of-influence (SOI) includes the Earth’s J2 oblate gravity effect and the point-mass perturbations of the sun and moon. The heliocentric equations of motion include the point-mass gravity of the sun and the first seven planets of the solar system.
The user can select one of the following delta-v optimization options for the two-body solution of the interplanetary transfer trajectory;
  1. minimize departure delta-v
  2. minimize arrival delta-v
  3. minimize total delta-v
The user also selects the type of final mission constraints from the following script options;
  1. B-plane (B dot T and B dot R)
  2. orbital elements (radius and inclination)
  3. EI conditions (altitude and flight path angle)
  4. grazing flyby
  5. node/apse alignment
The characteristics of the final user-defined areoocentric (Mars-centered) mission constraints can be calculated in one of the following coordinate systems;
  1. Earth mean equator and equinox of J2000
  2. Mars mean equator and IAU node of epoch
This MATLAB script reads JPL DE421 lunar and solar ephemerides in a machine-independent binary format (kernels) which are available from the SPICE web site and by anonymous ftp from ftp://ssd.jpl.nasa.gov/pub/eph/planets/bsp. These *.bsp ephemeris files are IEEE-Little Endian style of binary kernel. This is the binary form native to PC/Linux, PC/Windows and MAC/Intel machines. Additional information about JPL ephemerides can be found at http://naif.jpl.nasa.gov/naif/.
The e2m_matlab_snoptscript uses routines from the MICE software suite to read and evaluate the JPL ephemeris file. Platform-specific MICE mex files, support functions and the binary ephemeris file (de421.bsp) are available at naif.jpl.nasa.gov/naif/toolkit_MATLAB.html. MICE is a MATLAB implementation of the SPICE library created by JPL.
MATLAB versions of SNOPT for several computer platforms can be purchase/requested at Professor Philip Gill’s web site which is located at http://scicomp.ucsd.edu/~peg/. Professor Gill’s web site also includes a PDF version of the SNOPT software user’s guide.

引用格式

David Eagle (2025). Earth-to-Mars End-to-End Mission Design – SNOPT (https://ww2.mathworks.cn/matlabcentral/fileexchange/175903-earth-to-mars-end-to-end-mission-design-snopt), MATLAB Central File Exchange. 检索时间: .

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1.0.0