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: http://www.stsci.edu/~sontag/spicedocs/cspice/subpt_c.html
Дата изменения: Sat Dec 17 06:09:56 2005 Дата индексирования: Sun Apr 10 23:27:50 2016 Кодировка: Поисковые слова: mars global surveyor |
Compute the rectangular coordinates of the sub-observer point on a target body at a particular epoch, optionally corrected for planetary (light time) and stellar aberration. Return these coordinates expressed in the body-fixed frame associated with the target body. Also, return the observer's altitude above the target body.
FRAME PCK SPK TIME
Variable I/O Description -------- --- -------------------------------------------------- method I Computation method. target I Name of target body. et I Epoch in ephemeris seconds past J2000 TDB. abcorr I Aberration correction. obsrvr I Name of observing body. spoint O Sub-observer point on the target body. alt O Altitude of the observer above the target body.
method is a short string specifying the computation method to be used. The choices are: "Near point" The sub-observer point is defined as the nearest point on the target relative to the observer. "Intercept" The sub-observer point is defined as the target surface intercept of the line containing the observer and the target's center. In both cases, the intercept computation treats the surface of the target body as a triaxial ellipsoid. The ellipsoid's radii must be available in the kernel pool. Neither case nor white space are significant in `method'. For example, the string " NEARPOINT" is valid. target is the name of the target body. `target' is case-insensitive, and leading and trailing blanks in `target' are not significant. Optionally, you may supply a string containing the integer ID code for the object. For example both "MOON" and "301" are legitimate strings that indicate the moon is the target body. This routine assumes that the target body is modeled by a tri-axial ellipsoid, and that a PCK file containing its radii has been loaded into the kernel pool via furnsh_c. et is the epoch in ephemeris seconds past J2000 at which the sub-observer point on the target body is to be computed. abcorr indicates the aberration corrections to be applied when computing the observer-target state. `abcorr' may be any of the following. "NONE" Apply no correction. Return the geometric sub-observer point on the target body. "LT" Correct for planetary (light time) aberration. Both the state and rotation of the target body are corrected for light time. "LT+S" Correct for planetary (light time) and stellar aberrations. Both the state and rotation of the target body are corrected for light time. "CN" Converged Newtonian light time corrections. This is the same as LT corrections but with further iterations to a converged Newtonian light time solution. Given that relativistic effects may be as large as the higher accuracy achieved by this computation, this is correction is seldom worth the additional computations required unless the user incorporates additional relativistic corrections. Both the state and rotation of the target body are corrected for light time. "CN+S" Converged Newtonian light time corrections and stellar aberration. Both the state and rotation of the target body are corrected for light time. obsrvr is the name of the observing body. This is typically a spacecraft, the earth, or a surface point on the earth. `obsrvr' is case-insensitive, and leading and trailing blanks in `obsrvr' are not significant. Optionally, you may supply a string containing the integer ID code for the object. For example both "EARTH" and "399" are legitimate strings that indicate the earth is the observer.
spoint is the sub-observer point on the target body at `et' expressed relative to the body-fixed frame of the target body. The sub-observer point is defined either as the point on the target body that is closest to the observer, or the target surface intercept of the line from the observer to the target's center; the input argument `method' selects the definition to be used. The body-fixed frame, which is time-dependent, is evaluated at `et' if `abcorr' is "NONE"; otherwise the frame is evaluated at et-lt, where `lt' is the one-way light time from target to observer. The state of the target body is corrected for aberration as specified by `abcorr'; the corrected state is used in the geometric computation. As indicated above, the rotation of the target is retarded by one-way light time if `abcorr' specifies that light time correction is to be done. alt is the "altitude" of the observer above the target body. When `method' specifies a "near point" computation, `alt' is truly altitude in the standard geometric sense: the length of a segment dropped from the observer to the target's surface, such that the segment is perpendicular to the surface at the contact point `spoint'. When `method' specifies an "intercept" computation, `alt' is still the length of the segment from the observer to the surface point `spoint', but this segment in general is not perpendicular to the surface.
None.
subpt_c computes the sub-observer point on a target body. (The sub-observer point is commonly called the sub-spacecraft point when the observer is a spacecraft.) subpt_c also determines the altitude of the observer above the target body. There are two different popular ways to define the sub-observer point: "nearest point on target to observer" or "target surface intercept of line containing observer and target." These coincide when the target is spherical and generally are distinct otherwise. When comparing sub-point computations with results from sources other than SPICE, it's essential to make sure the same geometric definitions are used.
The numerical results shown for this example may differ across platforms. The results depend on the SPICE kernels used as input, the compiler and supporting libraries, and the machine specific arithmetic implementation. In the following example program, the file spk_m_031103-040201_030502.bsp is a binary SPK file containing data for Mars Global Surveyor, Mars, and the Sun for a time interval bracketing the date 2004 JAN 1 12:00:00 UTC. pck00007.tpc is a planetary constants kernel file containing radii and rotation model constants. naif0007.tls is a leapseconds kernel. Find the sub-observer point of the Mars Global Surveyor (MGS) spacecraft on Mars for a specified time. Perform the computation twice, using both the "intercept" and "near point" options. #include <stdio.h> #include "SpiceUsr.h" int main () { #define METHODLEN 25 SpiceChar method [2][METHODLEN] = { "Intercept", "Near point" }; SpiceDouble alt; SpiceDouble et; SpiceDouble lat; SpiceDouble lon; SpiceDouble radius; SpiceDouble spoint [3]; SpiceInt i; /. Load kernel files. ./ furnsh_c ( "naif0007.tls" ); furnsh_c ( "pck00007.tpc" ); furnsh_c ( "spk_m_031103-040201_030502.bsp" ); /. Convert the UTC request time to ET (seconds past J2000 TDB). ./ str2et_c ( "2004 JAN 1 12:00:00", &et ); /. Compute sub-spacecraft point using light time and stellar aberration corrections. Use the "target surface intercept" definition of sub-spacecraft point on the first loop iteration, and use the "near point" definition on the second. ./ for ( i = 0; i < 2; i++ ) { subpt_c ( method[i], "MARS", et, "LT+S", "MGS", spoint, &alt ); /. Convert rectangular coordinates to planetocentric latitude and longitude. Convert radians to degrees. ./ reclat_c ( spoint, &radius, &lon, &lat ); lon *= dpr_c (); lat *= dpr_c (); /. Write the results. ./ printf ( "\n" "Computation method: %s\n" "\n" " Radius (km) = %25.15e\n" " Planetocentric Latitude (deg) = %25.15e\n" " Planetocentric Longitude (deg) = %25.15e\n" " Altitude (km) = %25.15e\n" "\n", method[i], radius, lat, lon, alt ); } return ( 0 ); } When this program is executed, the output will be: Computation method: Intercept Radius (km) = 3.387970765126046e+03 Planetocentric Latitude (deg) = -3.970227239033073e+01 Planetocentric Longitude (deg) = -1.592266633611679e+02 Altitude (km) = 3.731735060549094e+02 Computation method: Near point Radius (km) = 3.387984503271711e+03 Planetocentric Latitude (deg) = -3.966593293571449e+01 Planetocentric Longitude (deg) = -1.592266633611679e+02 Altitude (km) = 3.731666361282019e+02
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If any of the listed errors occur, the output arguments are left unchanged. 1) If the input argument `method' is not recognized, the error SPICE(DUBIOUSMETHOD) is signaled. 2) If either of the input body names `target' or `obsrvr' cannot be mapped to NAIF integer codes, the error SPICE(IDCODENOTFOUND) is signaled. 3) If `obsrvr' and `target' map to the same NAIF integer ID codes, the error SPICE(BODIESNOTDISTINCT) is signaled. 4) If frame definition data enabling the evaluation of the state of the target relative to the observer in target body-fixed coordinates have not been loaded prior to calling subpt_c, the error will be diagnosed and signaled by a routine in the call tree of this routine. 5) If the specified aberration correction is not recognized, the error will be diagnosed and signaled by a routine in the call tree of this routine. 6) If insufficient ephemeris data have been loaded prior to calling subpt_c, the error will be diagnosed and signaled by a routine in the call tree of this routine. 7) If the triaxial radii of the target body have not been loaded into the kernel pool prior to calling subpt_c, the error will be diagnosed and signaled by a routine in the call tree of this routine. 8) The target must be an extended body: if any of the radii of the target body are non-positive, the error will be diagnosed and signaled by routines in the call tree of this routine. 9) If PCK data supplying a rotation model for the target body have not been loaded prior to calling subpt_c, the error will be diagnosed and signaled by a routine in the call tree of this routine.
Appropriate SPK, PCK, and frame data must be available to the calling program before this routine is called. Typically the data are made available by loading kernels; however the data may be supplied via subroutine interfaces if applicable. The following data are required: - SPK data: ephemeris data for target and observer must be loaded. If aberration corrections are used, the states of target and observer relative to the solar system barycenter must be calculable from the available ephemeris data. Typically ephemeris data are made available by loading one or more SPK files via furnsh_c. - PCK data: triaxial radii for the target body must be loaded into the kernel pool. Typically this is done by loading a text PCK file via furnsh_c. - Further PCK data: rotation data for the target body must be loaded. These may be provided in a text or binary PCK file. Either type of file may be loaded via furnsh_c - Frame data: if a frame definition is required to convert the observer and target states to the body-fixed frame of the target, that definition must be available in the kernel pool. Typically the definition is supplied by loading a frame kernel via furnsh_c. In all cases, kernel data are normally loaded once per program run, NOT every time this routine is called.
C.H. Acton (JPL) N.J. Bachman (JPL) J.E. McLean (JPL)
None.
-CSPICE Version 1.0.2, 22-JUL-2004 (NJB) Updated header to indicate that the `target' and `observer' input arguments can now contain string representations of integers. -CSPICE Version 1.0.1, 27-JUL-2003 (NJB) (CHA) Various header corrections were made. The example program was upgraded to use real kernels, and the program's output is shown. -CSPICE Version 1.0.0, 31-MAY-1999 (NJB) (JEM)
sub-observer point