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Text File  |  1991-02-27  |  4KB  |  64 lines
  1. ORBIT PROPAGATION
  2.  
  3. This disk contains several orbital mechanics utilities, plus an
  4. orbit propagator.  They are all provided for educational purposes.
  5. Please note that I have not made attempt to code the most numerically
  6. safe or efficient algorithms, but have for the most part coded
  7. straightforward textbook techniques which should be fairly easy to
  8. follow with a reference on orbital mechanics (e.g. the Bate, Mueller,
  9. White book) at hand.
  10.  
  11. Executable and source code is provided, as well as a set of input test
  12. data and the resulting output data.
  13.  
  14. All code was compiled under PC-DOS 3.3, using Microsoft C 5.1.
  15. All code was compiled using the simple
  16.    CL /AL xxxx.c
  17. command, except for twobdy.c, which required a /STACK:4096 parameter
  18. in the link step.
  19.  
  20. THE USUAL NOTE:  THIS CODE IS PROVIDED AS IS, WITH NO WARRANTY WHATSOEVER
  21. AS TO ITS FITNESS OR MERCHANTABILITY FOR ANY PARTICULAR PURPOSE. 
  22.  
  23. FILES ON THIS DISK:
  24.  
  25. Source     Executable     Test Data     Descriptionsc
  26. orbcons.h  ---            ---           Include file of constants
  27. k2ce.c     k2ce.exe       ---           Keplerian to Cartesian conversion
  28.                           k2cexxxx.in   Input test data:
  29.                                         xxxx = orb1 is the orbit used
  30.                                                in the C User's Journal art.
  31.                                              = circ is a circular, equatorial
  32.                                                orbit
  33.                                              = polr is a polar orbit
  34.                                              = retr is a retrograde orbit
  35.                                              = orb2 is a more general
  36.                                                retrograde orbit
  37.                           k2cexxxx.out  Outputs from the above tests
  38. c2ke.c     c2ke.exe       ---
  39.                           c2kexxxx.in   Input test data, as above.
  40.                           c2kexxxx.out  Outputs, as above.
  41. sk.c       sk.exe         ---           Solves Kepler's equation
  42.                           sk.out        Outputs from the sk tests.
  43. enu.c      enu.exe        ---           Converts between true and
  44.                                         eccentric anomaly
  45.                           enu.out       Outputs from the enu tests.
  46. twobdy.c   twobdy.exe     ---           Two-body orbit propagator
  47.                           twobdy.in       Input test data.  Look at the
  48.                                         main routine in the twobdy source
  49.                                         code.  You'll see that the tau
  50.                                         value in this input file is
  51.                                         overwritten for the tests.  The
  52.                                         input pos/vel here is from
  53.                                         k2ceorb1.out. 
  54.                           twobdy.out    Outputs.  The input vector is
  55.                                         propagated to each quarter period
  56.                                         until it completes one revolution.
  57.               c2ke1q.in     The first output point from the
  58.                                         twobdy tests:  the input vector
  59.                                         propagated to the first quarter
  60.                                         period.
  61.                           c2ke1q.out    The first output point from the
  62.                                         twobdy tests, converted to
  63.                                         Keplerian elements. 
  64.