| tangpt |
|
Table of contents
Procedure
TANGPT ( Ray-ellipsoid tangent point )
SUBROUTINE TANGPT ( METHOD, TARGET, ET, FIXREF, ABCORR,
. CORLOC, OBSRVR, DREF, DVEC, TANPT,
. ALT, RANGE, SRFPT, TRGEPC, SRFVEC )
Abstract
Compute, for a given observer, ray emanating from the observer,
and target, the "tangent point": the point on the ray nearest
to the target's surface. Also compute the point on the target's
surface nearest to the tangent point.
The locations of both points are optionally corrected for light
time and stellar aberration.
The surface shape is modeled as a triaxial ellipsoid.
Required_Reading
ABCORR
CK
FRAMES
NAIF_IDS
PCK
SCLK
SPK
TIME
Keywords
ELLIPSOID
GEOMETRY
RAY
Declarations
IMPLICIT NONE
INCLUDE 'frmtyp.inc'
INCLUDE 'zzabcorr.inc'
INCLUDE 'zzctr.inc'
CHARACTER*(*) METHOD
CHARACTER*(*) TARGET
DOUBLE PRECISION ET
CHARACTER*(*) FIXREF
CHARACTER*(*) ABCORR
CHARACTER*(*) CORLOC
CHARACTER*(*) OBSRVR
CHARACTER*(*) DREF
DOUBLE PRECISION DVEC ( 3 )
DOUBLE PRECISION TANPT ( 3 )
DOUBLE PRECISION ALT
DOUBLE PRECISION RANGE
DOUBLE PRECISION SRFPT ( 3 )
DOUBLE PRECISION TRGEPC
DOUBLE PRECISION SRFVEC ( 3 )
Brief_I/O
VARIABLE I/O DESCRIPTION
-------- --- --------------------------------------------------
METHOD I Computation method.
TARGET I Name of target body.
ET I Epoch in ephemeris seconds past J2000 TDB.
FIXREF I Body-fixed, body-centered target body frame.
ABCORR I Aberration correction.
CORLOC I Aberration correction locus: 'TANGENT POINT' or
'SURFACE POINT'.
OBSRVR I Name of observing body.
DREF I Reference frame of ray direction vector.
DVEC I Ray direction vector.
TANPT O "Tangent point": point on ray nearest to surface.
ALT O Altitude of tangent point above surface.
RANGE O Distance of tangent point from observer.
SRFPT O Point on surface nearest to tangent point.
TRGEPC O Epoch associated with correction locus.
SRFVEC O Vector from observer to surface point SRFPT.
Detailed_Input
METHOD is a short string providing parameters defining
the computation method to be used.
METHOD is currently restricted to the value
'ELLIPSOID'
This value indicates that the target shape is
modeled as a triaxial ellipsoid.
METHOD is case-insensitive, and leading and trailing
blanks in METHOD are not significant.
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.
If the target is identified by name rather than ID code,
the target name must be recognized by SPICE. Radii
defining a triaxial ellipsoid target shape model must be
available in the kernel pool. See the $Files section
below.
ET is the epoch associated with the observer, expressed as
ephemeris seconds past J2000 TDB. ET is the epoch at
which radiation is received by the observer, when an
observation is made, or in the case of transmission from
the observer, at which radiation is emitted.
ET is the epoch at which the state of the observer
relative to the solar system barycenter is computed.
When aberration corrections are not used, ET is also
the epoch at which the state and orientation of the
target body are computed.
When aberration corrections are used, the position
and orientation of the target body are computed at
ET-LT or ET+LT, where LT is the one-way light time
between the aberration correction locus and the
observer. The sign applied to LT depends on the
selected correction. See the descriptions of ABCORR
and CORLOC below for details.
FIXREF is the name of a body-fixed reference frame centered on
the target body. FIXREF may be any such frame supported
by the SPICE system, including built-in frames
(documented in frames.req) and frames defined by a
loaded frame kernel (FK). The string FIXREF is
case-insensitive, and leading and trailing blanks in
FIXREF are not significant.
The output points TANPT and SRFPT, and the
observer-to-surface point vector SRFVEC will be
expressed relative to this reference frame.
ABCORR indicates the aberration corrections to be applied
when computing the target's position and orientation.
See the description of the aberration correction
locus CORLOC for further details on how aberration
corrections are applied.
For remote sensing applications, where the apparent
tangent or surface point seen by the observer is
desired, normally one of the corrections
'CN+S' or 'NONE'
should be selected. For applications involving
transmission from the observer, normally 'XCN+S' or
'NONE' should be selected.
Light-time-only corrections can be useful for
testing but generally don't accurately model geometry
applicable to remote sensing observations or signal
transmission.
The supported options are described below.
ABCORR may be any of the following:
'NONE' Compute outputs without applying
aberration corrections.
'NONE' may be suitable when the
magnitudes of the aberration
corrections are negligible.
Let LT represent the one-way light time between the
observer and the aberration correction locus specified
by CORLOC. The following values of ABCORR apply to the
"reception" case in which radiation departs from the
aberration correction locus at the light-time corrected
epoch ET-LT and arrives at the observer's location at
ET:
'LT' Correct for one-way light time between
the aberration correction locus and
the observer, using a Newtonian
formulation. This correction yields the
position of the aberration correction
locus at the moment it emitted radiation
arriving at the observer at ET.
The light time correction uses an
iterative solution of the light time
equation. The solution invoked by the
'LT' option uses several iterations
but does not guarantee convergence.
Both the target position as seen by the
observer, and rotation of the target
body, are corrected for light time.
'LT+S' Correct for one-way light time and
stellar aberration using a Newtonian
formulation. This option modifies the
aberration correction locus solution
obtained with the 'LT' option to
account for the observer's velocity
relative to the solar system
barycenter. These corrections yield the
apparent aberration correction locus.
'CN' Converged Newtonian light time
correction. In solving the light time
equation, the 'CN' correction iterates
until either the solution converges or
a large iteration limit is reached.
Both the position and orientation of
the target body are corrected for light
time.
'CN+S' Converged Newtonian light time and stellar
aberration corrections. This option
produces a solution that is at least as
accurate at that obtainable with the
'LT+S' option. Whether the 'CN+S' solution
is substantially more accurate depends on
the geometry of the participating objects
and on the accuracy of the input data. In
some cases this routine will execute more
slowly when a converged solution is
computed.
For reception-case applications where
aberration corrections are applied, this
option should be used, unless the
magnitudes of the corrections are
negligible.
The following values of ABCORR apply to the
"transmission" case in which radiation *departs* from
the observer's location at ET and arrives at the
aberration correction locus at the light-time
corrected epoch ET+LT:
'XLT' "Transmission" case: correct for
one-way light time between the
aberration correction locus and the
observer, using a Newtonian
formulation. This correction yields the
position of the aberration correction
locus at the moment it receives radiation
emitted from the observer's location at
ET.
The light time correction uses an
iterative solution of the light time
equation. The solution invoked by the
'XLT' option uses several iterations
but does not guarantee convergence.
Both the target position as seen by the
observer, and rotation of the target
body, are corrected for light time.
'XLT+S' "Transmission" case: correct for
one-way light time and stellar
aberration using a Newtonian
formulation. This option modifies the
aberration correction locus solution
obtained with the 'XLT' option to
account for the observer's velocity
relative to the solar system
barycenter.
Stellar aberration is computed for
transmitted, rather than received,
radiation.
These corrections yield the analog for
the transmission case of the apparent
aberration correction locus.
'XCN' "Transmission" case: converged Newtonian
light time correction. In solving the
light time equation, the 'XCN' correction
iterates until either the solution
converges or a large iteration limit is
reached. Both the position and rotation of
the target body are corrected for light
time.
'XCN+S' "Transmission" case: converged Newtonian
light time and stellar aberration
corrections. This option produces a
solution that is at least as accurate at
that obtainable with the 'XLT+S' option.
Whether the 'XCN+S' solution is
substantially more accurate depends on the
geometry of the participating objects and
on the accuracy of the input data. In some
cases this routine will execute more
slowly when a converged solution is
computed.
For transmission-case applications where
aberration corrections are applied, this
option should be used, unless the
magnitudes of the corrections are
negligible.
Case and embedded blanks are not significant in
ABCORR. For example, the string
'Cn + s'
is valid.
CORLOC specifies the aberration correction "locus," which is
the fixed point in the frame designated by FIXREF for
which light time and stellar aberration corrections are
computed.
Differential aberration effects across the surface of
the target body are not considered by this routine. When
aberration corrections are used, the effective positions
of the observer and target, and the orientation of the
target, are computed according to the corrections
determined for the aberration correction locus.
The light time used to determine the position and
orientation of the target body is that between the
aberration correction locus and the observer.
The stellar aberration correction applied to the
position of the target is that computed for the
aberration correction locus.
The descriptions below apply only when aberration
corrections are used.
The values and meanings of CORLOC are:
'TANGENT POINT' Compute corrections at the
"tangent point," which is the
point on the ray, defined by DREF
and DVEC, nearest to the target's
surface.
'SURFACE POINT' Compute corrections at the
point on the target's surface
nearest to the tangent point.
Case and leading and trailing blanks are not significant
in CORLOC.
OBSRVR is the name of the observing body. This is typically
a spacecraft or a surface point on an extended
ephemeris object. 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 'MOON' and '301' are legitimate strings
that indicate the Moon is the observer.
If the observer is identified by name rather than ID
code, the observer name must be recognized by SPICE. See
the $Files section below.
DREF is the name of the reference frame relative to which
the ray direction vector is expressed. This may be
any frame supported by the SPICE system, including
built-in frames (documented in the Frames Required
Reading) and frames defined by a loaded frame kernel
(FK). The string DREF is case-insensitive, and
leading and trailing blanks in DREF are not
significant.
When DREF designates a non-inertial frame, the
orientation of the frame is evaluated at an epoch
dependent on the frame's center and, if the center is
not the observer, on the selected aberration
correction. See the description of the direction
vector DVEC for details.
DVEC is a ray direction vector emanating from the observer.
The tangent point on the ray and the point on the target
body's surface nearest to the tangent point are sought.
DVEC is specified relative to the reference frame
designated by DREF.
Non-inertial reference frames are treated as follows:
if the center of the frame is at the observer's
location, the frame's orientation is evaluated at ET.
If the frame's center is located elsewhere, then
letting LTCENT be the one-way light time between the
observer and the central body associated with the
frame, the orientation of the frame is evaluated at
ET-LTCENT, ET+LTCENT, or ET depending on whether the
requested aberration correction is, respectively, for
received radiation, transmitted radiation, or is
omitted. LTCENT is computed using the method
indicated by ABCORR.
Detailed_Output
TANPT is the "tangent point": the point on the ray defined by
DREF and DVEC nearest to the target body's surface.
TANPT is a vector originating at the target body's
center, expressed in the reference frame designated
by FIXREF, the orientation of which is evaluated at
TRGEPC (see description below). Units are km.
If the ray intersects the surface, TANPT is the
nearest point of intersection to the observer.
If the ray points away from the surface---that is, if
the angle between the ray and the outward normal at the
target surface point nearest to the observer, computed
using the specified aberration corrections, is less than
or equal to 90 degrees---then TANPT is set to the
position of the observer relative to the target center.
TANPT is computed using the aberration corrections
specified by ABCORR and CORLOC.
When the aberration correction locus is set to
'TANGENT POINT', and the position of TANPT is
corrected for aberration as specified by ABCORR, the
resulting point will lie on the input ray.
ALT is the altitude of the tangent point above the
target body's surface. This is the distance between
TANPT and SRFPT. Units are km.
If the ray intersects the surface, ALT is set to the
exact double precision value 0.D0. ALT may be used as
an indicator of whether a ray-surface intersection
exists.
RANGE is the distance between the observer and the tangent
point. Units are km.
If the ray points away from the surface (see the
description of TANPT above), RANGE is set to the
exact double precision value 0.D0. RANGE may be used
as an indicator of whether this geometric condition
exists.
SRFPT is the point on the target body's surface nearest to the
tangent point.
SRFPT is a vector originating at the target body's
center, expressed in the reference frame designated
by FIXREF, the orientation of which is evaluated at
TRGEPC (see description below). Units are km.
SRFPT is computed using the aberration corrections
specified by ABCORR and CORLOC.
When the aberration correction locus is set to
'SURFACE POINT', and the position of SRFPT is
corrected for aberration as specified by ABCORR, the
resulting point will lie on the ray emanating from
the observer and pointing in the direction of SRFVEC.
If the ray intersects the surface, SRFPT is the point of
intersection nearest to the observer.
If the ray points away from the surface (see the
description of TANPT above), SRFPT is set to the target
surface point nearest to the observer.
TRGEPC is the epoch associated with the aberration correction
locus. TRGEPC is defined as follows: letting LT be the
one-way light time between the observer and the
aberration correction locus, TRGEPC is the epoch ET-LT,
ET+LT, or ET depending on whether the requested
aberration correction is, respectively, for received
radiation, transmitted radiation, or omitted. LT is
computed using the method indicated by ABCORR.
TRGEPC is expressed as seconds past J2000 TDB.
The name TRGEPC, which stands for "target epoch,"
is used for compatibility with other SPICE high-level
geometry routines. Note that the epoch it designates
is not associated with the target body's center.
SRFVEC is the vector from the observer's position at ET to
the surface point SRFPT, where the position of SRFPT
is corrected for aberrations as specified by ABCORR
and CORLOC. SRFVEC is expressed in the target
body-fixed reference frame designated by FIXREF,
evaluated at TRGEPC. Units are km.
One can use the SPICELIB function VNORM to obtain the
distance between the observer and SRFPT:
DIST = VNORM ( SRFVEC )
The observer's position OBSPOS, relative to the
target body's center, where the center's position is
corrected for aberration effects as indicated by
ABCORR and CORLOC, can be computed via the call:
CALL VSUB ( SRFPT, SRFVEC, OBSPOS )
To transform the vector SRFVEC from the reference frame
FIXREF at time TRGEPC to a time-dependent reference
frame REF at time ET, the routine PXFRM2 should be
called. Let XFORM be the 3x3 matrix representing the
rotation from the reference frame FIXREF at time
TRGEPC to the reference frame REF at time ET. Then
SRFVEC can be transformed to the result REFVEC as
follows:
CALL PXFRM2 ( FIXREF, REF, TRGEPC, ET, XFORM )
CALL MXV ( XFORM, SRFVEC, REFVEC )
Parameters
None.
Exceptions
1) If the specified aberration correction is unrecognized, an
error is signaled by a routine in the call tree of this
routine.
2) If METHOD is not equivalent to 'ELLIPSOID', when case and
blanks are ignored in the comparison, the error
SPICE(NOTSUPPORTED) is signaled.
3) If CORLOC is not equivalent to either 'TANGENT POINT' or
'SURFACE POINT', when case and blanks are ignored, the
error SPICE(NOTSUPPORTED) is signaled.
4) If the direction vector DVEC is the zero vector, the error
SPICE(ZEROVECTOR) is signaled.
5) If either the target or observer input strings cannot be
converted to an integer ID code, the error
SPICE(IDCODENOTFOUND) is signaled.
6) If OBSRVR and TARGET map to the same NAIF integer ID code,
the error SPICE(BODIESNOTDISTINCT) is signaled.
7) If triaxial radii of the target body have not been loaded
into the kernel pool prior to a call to this routine, an
error is signaled by a routine in the call tree of this
routine.
8) If the number of radii associated with the target body is not
three, the error SPICE(INVALIDCOUNT) is signaled.
9) If the input target body-fixed frame FIXREF is not
recognized, the error SPICE(NOFRAME) is signaled. A frame
name may fail to be recognized because a required frame
specification kernel has not been loaded; another cause is a
misspelling of the frame name.
10) If the input frame FIXREF is not centered at the target body,
the error SPICE(INVALIDFRAME) is signaled.
11) If the reference frame designated by DREF is not recognized
by the SPICE frame subsystem, the error SPICE(NOFRAME) is
signaled.
12) If insufficient ephemeris data have been loaded prior to
calling TANGPT, an error is signaled by a routine in the call
tree of this routine. Note that when light time correction is
used, sufficient ephemeris data must be available to
propagate the states of both observer and target to the solar
system barycenter. If light time correction is used and
the ray's frame DREF is non-inertial, sufficient ephemeris
data must be available to compute the state of that frame's
center relative to the solar system barycenter.
13) If the target and observer have distinct identities but are
at the same location (for example, the target is Mars and the
observer is the Mars barycenter), the error
SPICE(NOSEPARATION) is signaled.
14) The target must be an extended body: if any of the radii of
the target body are non-positive, an error is signaled by a
routine in the call tree of this routine.
15) If the observer does not coincide with the target, but the
observer is located inside the ellipsoid modeling the
target body's shape, the error SPICE(INVALIDGEOMETRY) is
signaled.
16) If the transformation between the ray frame DREF and the
J2000 frame cannot be computed, an error is signaled by a
routine in the call tree of this routine.
17) If the transformation between the J2000 frame and the
target body-fixed, body-centered frame FIXREF cannot be
computed, an error is signaled by a routine in the call tree
of this routine.
18) If the nearest point to the target on the line containing
the input ray cannot be computed, an error is signaled by a
routine in the call tree of this routine. This type of error
may result from degenerate geometry; for example, if after
scaling the reference ellipsoid axes to make the longest
semi-axis a unit vector, another scaled axis is so short that
its squared length underflows to zero, no result can be
computed.
19) It is not an error for the ray to intersect the target body
or to point away from it so that the nearest point
to the ellipsoid on the line containing the ray lies behind
the ray's vertex.
Files
Appropriate kernels must be loaded by the calling program before
this routine is called.
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.
- 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.
- Target orientation data: rotation data for the target body
must be loaded. These may be provided in a text or binary PCK
file, or by a CK file.
The following data may be required:
- SPK data: if aberration corrections are used, and if the ray
frame DREF is non-inertial, ephemeris data for that frame's
center must be loaded. The state of that object relative to
the solar system barycenter must be calculable from the
available ephemeris data.
- Frame specifications: 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. Similarly, the frame definition required to map between
the frame designated by DREF and the target body-fixed frame
must be available. Typically the definitions of frames not
already built-in to SPICE are supplied by loading a frame
kernel.
- Ray frame orientation data: if the frame to which DREF refers
is non-inertial, PCK or CK data for the frame's orientation
are required. If the frame is fixed to a spacecraft instrument
or structure, at least one CK file will be needed to permit
transformation of vectors between that frame and both the
J2000 and the target body-fixed frames.
- Ray direction data: if the ray direction is defined by a
vector expressed in a spacecraft reference frame, an IK may be
required to provide the coordinates of the ray's direction in
that frame.
- SCLK data: if a CK file is needed, an associated SCLK kernel
is required to enable conversion between encoded SCLK (used to
time-tag CK data) and barycentric dynamical time (TDB).
- Leapseconds data: if SCLK data are needed, a leapseconds
kernel usually is needed as well.
- Body name-ID mappings: if the target or observer name is
not built into the SPICE software, the mapping between the
name and the corresponding ID code must be present in the
kernel pool. Such mappings are usually introduced by loading
a frame kernel or other text kernel containing them.
In all cases, kernel data are normally loaded once per program
run, NOT every time this routine is called.
Particulars
Given an observer, the direction vector of a ray emanating from
the observer, and an extended target body represented by a
triaxial ellipsoid, TANGPT computes the "tangent point": a point
nearest to the target body's surface nearest to the ray. The
corresponding surface point nearest to the tangent point is
computed as well.
For remote sensing observations, for maximum accuracy, reception
light time and stellar aberration corrections should be used.
These corrections model observer-target-ray geometry as it is
observed.
For signal transmission applications, for maximum accuracy,
transmission light time and stellar aberration corrections should
be used. These corrections model the observer-target-ray geometry
that applies to the transmitted signal. For example, these
corrections are needed to calculate the minimum altitude of the
signal's path over the target body.
In some cases, the magnitudes of light time and stellar
aberration corrections are negligible. When these corrections
can be ignored, significantly faster execution can be achieved
by setting the input ABCORR to 'NONE'.
This routine ignores differential aberration effects over the
target body's surface: it computes corrections only at a
user-specified point, which is called the "aberration correction
locus." The user may select either the tangent point or
corresponding surface point as the locus. In many cases, the
differences between corrections for these points are very small.
The $Examples header section below presents geometric cases for
which aberration correction magnitudes are significant, and cases
for which they are not.
Examples
The numerical results shown for these examples 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.
1) The following program computes tangent and surface points for
the MAVEN IUVS instrument. The observer is the MAVEN
spacecraft; the target body is Mars. The ray direction is
that of the boresight of the MAVEN IUVS instrument.
The aberration corrections used in this example are often
suitable for remote sensing observations: converged Newtonian
light time and stellar aberration "reception" corrections. In
some cases it is reasonable to omit aberration corrections;
see the second and third example programs below for
demonstrations of the effects of different aberration
correction choices.
In this example, the aberration correction locus is the
tangent point, meaning that converged light time and stellar
aberration corrections are computed for that point. The epoch
TRGEPC is used to compute the light time-corrected target
position and orientation, and the stellar aberration
correction applicable to the tangent point is applied to the
observer-target position vector, in order to model apparent
observation geometry.
Three geometric cases are covered by this example:
- The "normal" case, in which the ray defined by the
MAVEN IUVS boresight passes over Mars at low altitude.
In the example code, there are two computations that fall
into this category.
- The "intercept" case, in which the ray intersects Mars.
- The "look away" case, in which the elevation of the ray's
direction vector, measured from the local level plane at
the sub-spacecraft point, is greater than or equal to 0.
The aberration corrections used to compute the
sub-observer point for this case are those applicable to
the aberration correction locus.
Use the meta-kernel shown below to load the required SPICE
kernels.
KPL/MK
File name: tangpt_ex1.tm
This meta-kernel is intended to support operation of SPICE
example programs. The kernels shown here should not be
assumed to contain adequate or correct versions of data
required by SPICE-based user applications.
In order for an application to use this meta-kernel, the
kernels referenced here must be present in the user's
current working directory.
All kernels referenced by this meta-kernel are available
from the MAVEN SPICE PDS archive.
The names and contents of the kernels referenced
by this meta-kernel are as follows:
File name Contents
--------- --------
mar097s.bsp Mars satellite ephemeris
maven_iuvs_v11.ti MAVEN IUVS instrument
information
maven_orb_rec_201001_210101_v1.bsp MAVEN s/c ephemeris
mvn_v09.tf MAVEN frame
specifications
mvn_app_rel_201005_201011_v01.bc MAVEN Articulated
Payload Platform
attitude
mvn_iuvs_rem_201001_201231_v01.bc MAVEN IUVS instrument
internal mirror
attitude
mvn_sc_rel_201005_201011_v01.bc MAVEN s/c attitude
mvn_sclkscet_00086.tsc MAVEN SCLK coefficients
naif0012.tls Leapseconds
pck00010.tpc Planet and satellite
orientation and radii
\begindata
KERNELS_TO_LOAD = (
'mar097s.bsp',
'maven_iuvs_v11.ti',
'maven_orb_rec_201001_210101_v1.bsp',
'maven_v09.tf',
'mvn_app_rel_201005_201011_v01.bc',
'mvn_iuvs_rem_201001_201231_v01.bc',
'mvn_sc_rel_201005_201011_v01.bc',
'mvn_sclkscet_00086.tsc',
'naif0012.tls',
'pck00010.tpc' )
\begintext
End of meta-kernel
Example code begins here.
PROGRAM TANGPT_EX1
IMPLICIT NONE
C
C Parameters
C
CHARACTER*(*) FMT1F7
PARAMETER ( FMT1F7 = '(1X,A,F15.7)' )
CHARACTER*(*) FMT3F7
PARAMETER ( FMT3F7 = '(1X,A,3F15.7)' )
CHARACTER*(*) META
PARAMETER ( META = 'tangpt_ex1.tm' )
CHARACTER*(*) TIMFMT
PARAMETER ( TIMFMT =
. 'YYYY-MM-DD HR:MN:SC.###### UTC ::RND' )
INTEGER BDNMLN
PARAMETER ( BDNMLN = 36 )
INTEGER CORLEN
PARAMETER ( CORLEN = 10 )
INTEGER FRNMLN
PARAMETER ( FRNMLN = 32 )
INTEGER LNSIZE
PARAMETER ( LNSIZE = 72 )
INTEGER LOCLEN
PARAMETER ( LOCLEN = 25 )
INTEGER NCASE
PARAMETER ( NCASE = 3 )
INTEGER NTIMES
PARAMETER ( NTIMES = 4 )
INTEGER ROOM
PARAMETER ( ROOM = 12 )
INTEGER SHPLEN
PARAMETER ( SHPLEN = 25 )
INTEGER TIMLEN
PARAMETER ( TIMLEN = 35 )
C
C Local variables
C
CHARACTER*(CORLEN) ABCORR
CHARACTER*(LNSIZE) CASENM
CHARACTER*(LNSIZE) CASES ( NCASE )
CHARACTER*(FRNMLN) FIXREF
CHARACTER*(BDNMLN) INSNAM
CHARACTER*(LOCLEN) LOCUS
CHARACTER*(BDNMLN) OBSRVR
CHARACTER*(FRNMLN) RAYFRM
CHARACTER*(SHPLEN) SHAPE
CHARACTER*(BDNMLN) TARGET
CHARACTER*(TIMLEN) TIMSTR
CHARACTER*(TIMLEN) UTCTIM ( NTIMES )
DOUBLE PRECISION ALT
DOUBLE PRECISION BOUNDS ( 3, ROOM )
DOUBLE PRECISION ET
DOUBLE PRECISION RANGE
DOUBLE PRECISION RAYDIR ( 3 )
DOUBLE PRECISION SRFPT ( 3 )
DOUBLE PRECISION SRFVEC ( 3 )
DOUBLE PRECISION TANPT ( 3 )
DOUBLE PRECISION TRGEPC
INTEGER I
INTEGER NVEC
C
C Initial values
C
DATA CASES /
. 'Ray slightly above limb',
. 'Intercept',
. 'Look-away' /
DATA INSNAM / 'MAVEN_IUVS' /
DATA UTCTIM /
. '2020-10-11 16:01:43.000000 UTC',
. '2020-10-11 16:17:43.000000 UTC',
. '2020-10-11 16:49:07.000000 UTC',
. '2020-10-11 17:12:08.000000 UTC' /
C
C Load kernels.
C
CALL FURNSH ( META )
WRITE(*,*) ' '
WRITE(*, '(A)') 'Instrument: ' // INSNAM
WRITE(*,*) ' '
C
C Get the instrument reference frame name and
C the instrument boresight direction in the
C instrument frame.
C
CALL GETFVN ( INSNAM, ROOM, SHAPE,
. RAYFRM, RAYDIR, NVEC, BOUNDS )
C
C Initialize inputs to TANGPT, except for time.
C
TARGET = 'MARS'
OBSRVR = 'MAVEN'
FIXREF = 'IAU_MARS'
ABCORR = 'CN+S'
LOCUS = 'TANGENT POINT'
C
C Compute the apparent tangent point for each time.
C
WRITE(*,'(A)') 'Aberration correction: ' // ABCORR
WRITE(*,'(A)') 'Aberration correction locus: ' // LOCUS
DO I = 1, NTIMES
CALL STR2ET ( UTCTIM(I), ET )
CALL TANGPT ( 'ELLIPSOID',
. TARGET, ET, FIXREF, ABCORR,
. LOCUS, OBSRVR, RAYFRM, RAYDIR,
. TANPT, ALT, RANGE, SRFPT,
. TRGEPC, SRFVEC )
C
C Set the label for the geometric case.
C
IF ( ALT .EQ. 0 ) THEN
CASENM = CASES(2)
ELSE IF ( RANGE .EQ. 0.D0 ) THEN
CASENM = CASES(3)
ELSE
CASENM = CASES(1)
END IF
C
C Convert the target epoch to a string for output.
C
CALL TIMOUT ( TRGEPC, TIMFMT, TIMSTR )
WRITE(*,*) ' '
WRITE( *, '(A)') ' Observation Time = ' // UTCTIM(I)
WRITE( *, '(A)') ' Target Time = ' // TIMSTR
WRITE(*, FMT1F7) ' ALT (km) = ', ALT
WRITE(*, FMT1F7) ' RANGE (km) = ', RANGE
WRITE(*, FMT3F7) ' TANPT (km) = ', TANPT
WRITE(*, FMT3F7) ' SRFPT (km) = ', SRFPT
WRITE(*, FMT3F7) ' SRFVEC (km) = ', SRFVEC
WRITE( *, '(A)') ' Geometric case = ' // CASENM
END DO
WRITE(*,*) ' '
END
When this program was executed on a PC/Linux/gfortran/64-bit
platform, the output was:
Instrument: MAVEN_IUVS
Aberration correction: CN+S
Aberration correction locus: TANGENT POINT
Observation Time = 2020-10-11 16:01:43.000000 UTC
Target Time = 2020-10-11 16:01:42.983021 UTC
ALT (km) = 99.4262977
RANGE (km) = 5090.1928435
TANPT (km) = -2273.0408575 1072.4423944 -2415.6104827
SRFPT (km) = -2208.5678350 1042.0234063 -2346.3031728
SRFVEC (km) = -2138.0677257 3050.4078643 3470.3929222
Geometric case = Ray slightly above limb
Observation Time = 2020-10-11 16:17:43.000000 UTC
Target Time = 2020-10-11 16:17:42.993820 UTC
ALT (km) = 0.0000000
RANGE (km) = 1852.8381880
TANPT (km) = 752.0909507 -1781.3912506 -2775.5390159
SRFPT (km) = 752.0909507 -1781.3912506 -2775.5390159
SRFVEC (km) = -700.9743439 1162.4766255 1261.0679662
Geometric case = Intercept
Observation Time = 2020-10-11 16:49:07.000000 UTC
Target Time = 2020-10-11 16:49:06.998907 UTC
ALT (km) = 218.2661426
RANGE (km) = 327.7912133
TANPT (km) = 2479.8672359 -1772.2350525 1931.8678816
SRFPT (km) = 2330.3561559 -1665.3870838 1814.0966731
SRFVEC (km) = 77.3692694 325.9571470 -207.0099587
Geometric case = Ray slightly above limb
Observation Time = 2020-10-11 17:12:08.000000 UTC
Target Time = 2020-10-11 17:12:08.000000 UTC
ALT (km) = 969.2772042
RANGE (km) = 0.0000000
TANPT (km) = -58.1087763 2034.6474343 3844.2010767
SRFPT (km) = -45.2530638 1584.5115999 2985.8825113
SRFVEC (km) = 12.8557125 -450.1358344 -858.3185654
Geometric case = Look-away
2) The following program computes tangent and surface points for
the MRO MCS A1 instrument, for a single epoch. The observer is
the MRO spacecraft; the target body is Mars. The ray direction
is that of the boresight of the MRO MCS A1 instrument.
The aberration corrections used in this example are converged
Newtonian light time and stellar aberration corrections,
converged Newtonian light time alone, and "none."
For remote sensing observations made by a spacecraft in low
orbit about Mars, both the combination of light time and
stellar aberration corrections and omission of aberration
corrections may be valid. See the output of this program and
of the third example program below for examples of how results
differ due to the choice of aberration corrections.
Use of light time corrections alone is presented to
illustrate, by way of contrast, the effect of this choice.
This choice can be useful for testing but is unlikely to be
correct for modeling actual observation geometry.
Separate computations are performed using both the tangent
point and the corresponding surface point---the nearest point
on the target surface to the tangent point---as the aberration
correction locus.
Three geometric cases are covered by this example:
- The "normal" case, in which the ray defined by the
MRO MCS A1 boresight passes over Mars at low altitude.
In the example code, there are two computations that fall
into this category.
- The "intercept" case, in which the ray intersects Mars.
- The "look away" case, in which the elevation of the ray's
direction vector, measured from the local level plane at
the sub-spacecraft point, is greater than or equal to 0.
The target position and orientation used for this
computation are the same as those used to compute the
aberration correction locus.
Use the meta-kernel shown below to load the required SPICE
kernels.
KPL/MK
File: tangpt_ex2.tm
This meta-kernel is intended to support operation of SPICE
example programs. The kernels shown here should not be
assumed to contain adequate or correct versions of data
required by SPICE-based user applications.
In order for an application to use this meta-kernel, the
kernels referenced here must be present in the user's
current working directory.
All kernels referenced by this meta-kernel are available
from the MRO SPICE PDS archive.
The names and contents of the kernels referenced
by this meta-kernel are as follows:
File name Contents
--------- --------
mar097.bsp Mars satellite ephemeris
mro_mcs_psp_201001_201031.bc MRO MCS attitude
mro_mcs_v10.ti MRO MCS instrument
information
mro_psp57_ssd_mro95a.bsp MRO s/c ephemeris
mro_sc_psp_201027_201102.bc MRO s/c bus attitude
mro_sclkscet_00095_65536.tsc MRO SCLK coefficients
mro_v16.tf MRO frame specifications
naif0012.tls Leapseconds
pck00008.tpc Planet and satellite
orientation and radii
\begindata
KERNELS_TO_LOAD = (
'mar097.bsp',
'mro_mcs_psp_201001_201031.bc',
'mro_mcs_v10.ti',
'mro_psp57_ssd_mro95a.bsp',
'mro_sc_psp_201027_201102.bc',
'mro_sclkscet_00095_65536.tsc',
'mro_v16.tf',
'naif0012.tls',
'pck00008.tpc' )
\begintext
End of meta-kernel
Example code begins here.
PROGRAM TANGPT_EX2
IMPLICIT NONE
C
C Parameters
C
CHARACTER*(*) FMT1F7
PARAMETER ( FMT1F7 = '(1X,A,F15.7)' )
CHARACTER*(*) FMT3F7
PARAMETER ( FMT3F7 = '(1X,A,3F15.7)' )
CHARACTER*(*) FMT1F4
PARAMETER ( FMT1F4 = '(1X,A,F10.4)' )
CHARACTER*(*) FMT3F4
PARAMETER ( FMT3F4 = '(1X,A,3F10.4)' )
CHARACTER*(*) META
PARAMETER ( META = 'tangpt_ex2.tm' )
CHARACTER*(*) TIMFMT
PARAMETER ( TIMFMT =
. 'YYYY-MM-DD HR:MN:SC.###### UTC ::RND' )
INTEGER BDNMLN
PARAMETER ( BDNMLN = 36 )
INTEGER CORLEN
PARAMETER ( CORLEN = 10 )
INTEGER FRNMLN
PARAMETER ( FRNMLN = 32 )
INTEGER LOCLEN
PARAMETER ( LOCLEN = 25 )
INTEGER NCASE
PARAMETER ( NCASE = 5 )
INTEGER ROOM
PARAMETER ( ROOM = 4 )
INTEGER SHPLEN
PARAMETER ( SHPLEN = 25 )
INTEGER TIMLEN
PARAMETER ( TIMLEN = 35 )
C
C Local variables
C
CHARACTER*(CORLEN) ABCORR
CHARACTER*(CORLEN) CORRS ( NCASE )
CHARACTER*(FRNMLN) FIXREF
CHARACTER*(BDNMLN) INSNAM
CHARACTER*(LOCLEN) LOCI ( NCASE )
CHARACTER*(LOCLEN) LOCUS
CHARACTER*(BDNMLN) OBSRVR
CHARACTER*(FRNMLN) RAYFRM
CHARACTER*(SHPLEN) SHAPE
CHARACTER*(BDNMLN) TARGET
CHARACTER*(TIMLEN) TIMSTR
CHARACTER*(TIMLEN) UTCTIM
DOUBLE PRECISION ALT
DOUBLE PRECISION BOUNDS ( 3, ROOM )
DOUBLE PRECISION DIFF ( 3 )
DOUBLE PRECISION ET
DOUBLE PRECISION RANGE
DOUBLE PRECISION RAYDIR ( 3 )
DOUBLE PRECISION SRFPT ( 3 )
DOUBLE PRECISION SRFVEC ( 3 )
DOUBLE PRECISION SVALT
DOUBLE PRECISION SVEPOC
DOUBLE PRECISION SVRANG
DOUBLE PRECISION SVSRFP ( 3 )
DOUBLE PRECISION SVSRFV ( 3 )
DOUBLE PRECISION SVTANP ( 3 )
DOUBLE PRECISION TANPT ( 3 )
DOUBLE PRECISION TRGEPC
INTEGER I
INTEGER NVEC
C
C Initial values
C
DATA CORRS / 'CN+S', 'CN+S',
. 'CN', 'CN',
. 'NONE' /
DATA INSNAM / 'MRO_MCS_A1' /
DATA LOCI / 'TANGENT POINT',
. 'SURFACE POINT',
. 'TANGENT POINT',
. 'SURFACE POINT',
. 'TANGENT POINT' /
DATA UTCTIM /
. '2020-10-31 00:01:23.111492 UTC' /
C
C Load kernels.
C
CALL FURNSH ( META )
WRITE( *, * ) ' '
WRITE( *, '(A)') 'Instrument: ' // INSNAM
C
C Get the instrument reference frame name and
C the instrument boresight direction in the
C instrument frame.
C
CALL GETFVN ( INSNAM, ROOM, SHAPE,
. RAYFRM, RAYDIR, NVEC, BOUNDS )
C
C Initialize inputs to TANGPT that are common to all
C cases.
C
TARGET = 'MARS'
OBSRVR = 'MRO'
FIXREF = 'IAU_MARS'
C
C Compute the apparent tangent point for each case.
C
DO I = 1, NCASE
WRITE(*,*) ' '
ABCORR = CORRS(I)
LOCUS = LOCI(I)
WRITE(*, '(A)') 'Aberration correction: '
. // ABCORR
WRITE(*, '(A)') 'Aberration correction locus: '
. // LOCUS
WRITE(*,*) ' '
CALL STR2ET ( UTCTIM, ET )
CALL TANGPT ( 'ELLIPSOID',
. TARGET, ET, FIXREF, ABCORR,
. LOCUS, OBSRVR, RAYFRM, RAYDIR,
. TANPT, ALT, RANGE, SRFPT,
. TRGEPC, SRFVEC )
C
C Convert the target epoch to a string for output.
C
CALL TIMOUT ( TRGEPC, TIMFMT, TIMSTR )
WRITE(*, '(A)') ' Observation Time = '
. // UTCTIM
WRITE(*, '(A)') ' Target Time = '
. // TIMSTR
WRITE(*, FMT1F7) ' ALT (km) = ', ALT
WRITE(*, FMT1F7) ' RANGE (km) = ', RANGE
WRITE(*, FMT3F7) ' TANPT (km) = ', TANPT
WRITE(*, FMT3F7) ' SRFPT (km) = ', SRFPT
WRITE(*, FMT3F7) ' SRFVEC (km) = ', SRFVEC
IF ( I .EQ. 1 ) THEN
C
C Save results for comparison.
C
SVALT = ALT
SVEPOC = TRGEPC
SVRANG = RANGE
CALL VEQU( TANPT, SVTANP )
CALL VEQU( SRFPT, SVSRFP )
CALL VEQU( SRFVEC, SVSRFV )
ELSE
C
C Compare results to CN+S, tangent point
C locus case.
C
WRITE(*,*) ' '
WRITE(*, '(A)')
. ' Differences from case 1 outputs:'
WRITE(*, FMT1F4)
. ' Target time delta (ms) = ',
. 1.D3 * ( TRGEPC - SVEPOC )
WRITE(*, FMT1F4)
. ' ALT delta (m) = ',
. 1.D3 * ( ALT - SVALT )
WRITE(*, FMT1F4)
. ' RANGE delta (m) = ',
. 1.D3 * ( RANGE - SVRANG )
CALL VSUB ( TANPT, SVTANP, DIFF )
CALL VSCLIP ( 1.D3, DIFF )
WRITE(*, FMT3F4)
. ' TANPT delta (m) = ', DIFF
CALL VSUB ( SRFPT, SVSRFP, DIFF )
CALL VSCLIP ( 1.D3, DIFF )
WRITE(*, FMT3F4)
. ' SRFPT delta (m) = ', DIFF
CALL VSUB ( SRFVEC, SVSRFV, DIFF )
CALL VSCLIP ( 1.D3, DIFF )
WRITE(*, FMT3F4)
. ' SRFVEC delta (m) = ', DIFF
END IF
WRITE(*,*) ' '
END DO
END
When this program was executed on a PC/Linux/gfortran/64-bit
platform, the output was:
Instrument: MRO_MCS_A1
Aberration correction: CN+S
Aberration correction locus: TANGENT POINT
Observation Time = 2020-10-31 00:01:23.111492 UTC
Target Time = 2020-10-31 00:01:23.106946 UTC
ALT (km) = 39.1034486
RANGE (km) = 1362.8659249
TANPT (km) = -2530.9040220 -1630.9806346 1644.3612074
SRFPT (km) = -2502.1342299 -1612.4406294 1625.4496512
SRFVEC (km) = -589.3842679 -234.0892764 -1206.9635473
Aberration correction: CN+S
Aberration correction locus: SURFACE POINT
Observation Time = 2020-10-31 00:01:23.111492 UTC
Target Time = 2020-10-31 00:01:23.106944 UTC
ALT (km) = 39.1014434
RANGE (km) = 1362.8679108
TANPT (km) = -2530.9025464 -1630.9796845 1644.3602376
SRFPT (km) = -2502.1342295 -1612.4406300 1625.4496511
SRFVEC (km) = -589.3866439 -234.0905954 -1206.9643086
Differences from case 1 outputs:
Target time delta (ms) = -0.0019
ALT delta (m) = -2.0052
RANGE delta (m) = 1.9859
TANPT delta (m) = 1.4757 0.9501 -0.9698
SRFPT delta (m) = 0.0004 -0.0006 -0.0000
SRFVEC delta (m) = -2.3760 -1.3189 -0.7614
Aberration correction: CN
Aberration correction locus: TANGENT POINT
Observation Time = 2020-10-31 00:01:23.111492 UTC
Target Time = 2020-10-31 00:01:23.106946 UTC
ALT (km) = 39.1714711
RANGE (km) = 1362.8658567
TANPT (km) = -2530.9135880 -1631.0820975 1644.3878335
SRFPT (km) = -2502.0942100 -1612.5090527 1625.4434517
SRFVEC (km) = -589.3346511 -234.0562242 -1206.9963133
Differences from case 1 outputs:
Target time delta (ms) = 0.0000
ALT delta (m) = 68.0225
RANGE delta (m) = -0.0683
TANPT delta (m) = -9.5660 -101.4629 26.6261
SRFPT delta (m) = 40.0199 -68.4233 -6.1994
SRFVEC delta (m) = 49.6168 33.0522 -32.7661
Aberration correction: CN
Aberration correction locus: SURFACE POINT
Observation Time = 2020-10-31 00:01:23.111492 UTC
Target Time = 2020-10-31 00:01:23.106944 UTC
ALT (km) = 39.1714973
RANGE (km) = 1362.8658326
TANPT (km) = -2530.9135902 -1631.0821391 1644.3878436
SRFPT (km) = -2502.0941931 -1612.5090815 1625.4434492
SRFVEC (km) = -589.3346210 -234.0562071 -1206.9963050
Differences from case 1 outputs:
Target time delta (ms) = -0.0019
ALT delta (m) = 68.0487
RANGE delta (m) = -0.0924
TANPT delta (m) = -9.5682 -101.5045 26.6362
SRFPT delta (m) = 40.0368 -68.4521 -6.2020
SRFVEC delta (m) = 49.6469 33.0694 -32.7577
Aberration correction: NONE
Aberration correction locus: TANGENT POINT
Observation Time = 2020-10-31 00:01:23.111492 UTC
Target Time = 2020-10-31 00:01:23.111492 UTC
ALT (km) = 39.1090103
RANGE (km) = 1362.9233525
TANPT (km) = -2530.9082604 -1630.9831041 1644.3638384
SRFPT (km) = -2502.1343747 -1612.4404639 1625.4495931
SRFVEC (km) = -589.4063032 -234.0970874 -1207.0162978
Differences from case 1 outputs:
Target time delta (ms) = 4.5460
ALT delta (m) = 5.5616
RANGE delta (m) = 57.4276
TANPT delta (m) = -4.2384 -2.4695 2.6310
SRFPT delta (m) = -0.1448 0.1655 -0.0581
SRFVEC delta (m) = -22.0352 -7.8109 -52.7505
3) The following program computes tangent and surface points for
a ray pointing from the Goldstone DSN station DSS-14 to the
location of the MRO spacecraft, for a single epoch. The target
body is Mars.
The aberration corrections used in this example are
CN+S
XCN+S
CN
NONE
Results using CN+S corrections are computed for both locus
choices: TANGENT POINT and SURFACE POINT.
For each case other than the one using CN+S corrections for
the TANGENT POINT locus, differences between results for the
former and latter case are shown.
Use the meta-kernel shown below to load the required SPICE
kernels.
KPL/MK
File: tangpt_ex3.tm
This meta-kernel is intended to support operation of SPICE
example programs. The kernels shown here should not be
assumed to contain adequate or correct versions of data
required by SPICE-based user applications.
In order for an application to use this meta-kernel, the
kernels referenced here must be present in the user's
current working directory.
All kernels referenced by this meta-kernel are available
from the NAIF SPICE server in the generic kernels area
or from the MRO SPICE PDS archive.
The names and contents of the kernels referenced
by this meta-kernel are as follows:
File name Contents
--------- --------
mar097.bsp Mars satellite ephemeris
mro_psp57_ssd_mro95a.bsp MRO s/c ephemeris
earthstns_itrf93_201023.bsp DSN station locations
naif0012.tls Leapseconds
pck00010.tpc Planet and satellite
orientation and radii
earth_latest_high_prec.bpc High accuracy Earth
attitude
\begindata
KERNELS_TO_LOAD = (
'mar097.bsp'
'mro_psp57_ssd_mro95a.bsp'
'earthstns_itrf93_201023.bsp'
'naif0012.tls'
'pck00010.tpc'
'earth_latest_high_prec.bpc' )
\begintext
End of meta-kernel
Example code begins here.
PROGRAM TANGPT_EX3
IMPLICIT NONE
C
C Parameters
C
CHARACTER*(*) FMT1F3
PARAMETER ( FMT1F3 = '(1X,A,F14.3)' )
CHARACTER*(*) FMT3F3
PARAMETER ( FMT3F3 = '(1X,A,3F14.3)' )
CHARACTER*(*) FMT1F6
PARAMETER ( FMT1F6 = '(1X,A,F14.6)' )
CHARACTER*(*) FMTMF3
PARAMETER ( FMTMF3 = '(1X,A,2F13.3,F10.3)' )
CHARACTER*(*) META
PARAMETER ( META = 'tangpt_ex3.tm' )
CHARACTER*(*) TIMFMT
PARAMETER ( TIMFMT =
. 'YYYY-MM-DD HR:MN:SC.###### UTC ::RND' )
INTEGER BDNMLN
PARAMETER ( BDNMLN = 36 )
INTEGER CORLEN
PARAMETER ( CORLEN = 10 )
INTEGER FRNMLN
PARAMETER ( FRNMLN = 32 )
INTEGER LOCLEN
PARAMETER ( LOCLEN = 25 )
INTEGER NCASE
PARAMETER ( NCASE = 5 )
INTEGER TIMLEN
PARAMETER ( TIMLEN = 35 )
C
C Local variables
C
CHARACTER*(CORLEN) ABCORR
CHARACTER*(CORLEN) CORRS ( NCASE )
CHARACTER*(FRNMLN) FIXREF
CHARACTER*(LOCLEN) LOCI ( NCASE )
CHARACTER*(LOCLEN) LOCUS
CHARACTER*(BDNMLN) OBSRVR
CHARACTER*(FRNMLN) RAYFRM
CHARACTER*(BDNMLN) SC
CHARACTER*(BDNMLN) TARGET
CHARACTER*(TIMLEN) TIMSTR
CHARACTER*(TIMLEN) UTCTIM
DOUBLE PRECISION ALT
DOUBLE PRECISION DIFF ( 3 )
DOUBLE PRECISION ET
DOUBLE PRECISION RANGE
DOUBLE PRECISION RAYDIR ( 3 )
DOUBLE PRECISION RAYLT
DOUBLE PRECISION SRFPT ( 3 )
DOUBLE PRECISION SRFVEC ( 3 )
DOUBLE PRECISION SVALT
DOUBLE PRECISION SVEPOC
DOUBLE PRECISION SVRANG
DOUBLE PRECISION SVSRFP ( 3 )
DOUBLE PRECISION SVSRFV ( 3 )
DOUBLE PRECISION SVTANP ( 3 )
DOUBLE PRECISION TANPT ( 3 )
DOUBLE PRECISION TRGEPC
INTEGER I
C
C Initial values
C
DATA CORRS / 'CN+S', 'XCN+S',
. 'CN', 'NONE',
. 'CN+S' /
DATA LOCI / 'TANGENT POINT',
. 'TANGENT POINT',
. 'TANGENT POINT',
. 'TANGENT POINT',
. 'SURFACE POINT' /
DATA UTCTIM /
. '2020-12-30 00:00:00 UTC' /
C
C Load kernels.
C
CALL FURNSH ( META )
C
C Set name of spacecraft used to define ray direction.
C
SC = 'MRO'
C
C Initialize inputs to TANGPT that are common to all
C cases.
C
TARGET = 'MARS'
OBSRVR = 'DSS-14'
FIXREF = 'IAU_MARS'
RAYFRM = 'J2000'
C
C Convert observation time to TDB seconds past J2000.
C
CALL STR2ET ( UTCTIM, ET )
C
C Generate ray direction vector. Use apparent position
C of the MRO spacecraft.
C
CALL SPKPOS ( SC, ET, RAYFRM,
. 'CN+S', OBSRVR, RAYDIR, RAYLT )
WRITE(*,*) ' '
WRITE( *, '(A)') 'Observer: ' // OBSRVR
WRITE( *, '(A)') 'Target: ' // TARGET
WRITE( *, '(A)') 'Spacecraft: ' // SC
C
C Compute the apparent tangent point for each case.
C
DO I = 1, NCASE
WRITE(*,*) ' '
ABCORR = CORRS(I)
LOCUS = LOCI(I)
WRITE(*, '(A)') 'Aberration correction: '
. // ABCORR
WRITE(*, '(A)') 'Aberration correction locus: '
. // LOCUS
WRITE(*,*) ' '
C
C Compute tangent point.
C
CALL TANGPT ( 'ELLIPSOID',
. TARGET, ET, FIXREF, ABCORR,
. LOCUS, OBSRVR, RAYFRM, RAYDIR,
. TANPT, ALT, RANGE, SRFPT,
. TRGEPC, SRFVEC )
C
C Convert the target epoch to a string for output.
C
CALL TIMOUT ( TRGEPC, TIMFMT, TIMSTR )
WRITE(*, '(A)') ' Observation Time = '
. // UTCTIM
WRITE(*, '(A)') ' Target Time = '
. // TIMSTR
WRITE(*, FMT1F3) ' ALT (km) = ', ALT
WRITE(*, FMT1F3) ' RANGE (km) = ', RANGE
WRITE(*, FMT3F3) ' TANPT (km) = ', TANPT
WRITE(*, FMT3F3) ' SRFPT (km) = ', SRFPT
WRITE(*, FMT3F3) ' SRFVEC (km) = ', SRFVEC
IF ( I .EQ. 1 ) THEN
C
C Save results for comparison.
C
SVALT = ALT
SVEPOC = TRGEPC
SVRANG = RANGE
CALL VEQU( TANPT, SVTANP )
CALL VEQU( SRFPT, SVSRFP )
CALL VEQU( SRFVEC, SVSRFV )
ELSE
C
C Compare results to CN+S, tangent point
C locus case.
C
WRITE(*,*) ' '
WRITE(*, '(A)')
. ' Differences from case 1 outputs:'
WRITE(*, FMT1F6)
. ' Target time delta (s) = ',
. TRGEPC - SVEPOC
WRITE(*, FMTMF3)
. ' ALT delta (km) = ', ALT - SVALT
WRITE(*, FMTMF3)
. ' RANGE delta (km) = ', RANGE - SVRANG
CALL VSUB ( TANPT, SVTANP, DIFF )
WRITE(*, FMTMF3)
. ' TANPT delta (km) = ', DIFF
CALL VSUB ( SRFPT, SVSRFP, DIFF )
WRITE(*, FMTMF3)
. ' SRFPT delta (km) = ', DIFF
CALL VSUB ( SRFVEC, SVSRFV, DIFF )
WRITE(*, FMTMF3)
. ' SRFVEC delta (km) = ', DIFF
END IF
WRITE(*,*) ' '
END DO
END
When this program was executed on a PC/Linux/gfortran/64-bit
platform, the output was:
Observer: DSS-14
Target: MARS
Spacecraft: MRO
Aberration correction: CN+S
Aberration correction locus: TANGENT POINT
Observation Time = 2020-12-30 00:00:00 UTC
Target Time = 2020-12-29 23:52:40.613204 UTC
ALT (km) = 140.295
RANGE (km) = 131724847.608
TANPT (km) = 1351.574 1182.155 -3029.495
SRFPT (km) = 1298.181 1135.455 -2908.454
SRFVEC (km) = 121233989.354 -5994858.328 51164606.676
Aberration correction: XCN+S
Aberration correction locus: TANGENT POINT
Observation Time = 2020-12-30 00:00:00 UTC
Target Time = 2020-12-30 00:07:19.347692 UTC
ALT (km) = 4921.539
RANGE (km) = 131713124.520
TANPT (km) = -413.404 -8220.856 -1193.471
SRFPT (km) = -168.808 -3356.879 -483.938
SRFVEC (km) = 120615301.766 -13523495.083 51160641.665
Differences from case 1 outputs:
Target time delta (s) = 878.734488
ALT delta (km) = 4781.244
RANGE delta (km) = -11723.089
TANPT delta (km) = -1764.978 -9403.011 1836.024
SRFPT delta (km) = -1466.989 -4492.334 2424.517
SRFVEC delta (km) = -618687.588 -7528636.755 -3965.012
Aberration correction: CN
Aberration correction locus: TANGENT POINT
Observation Time = 2020-12-30 00:00:00 UTC
Target Time = 2020-12-29 23:52:40.613219 UTC
ALT (km) = 3409.162
RANGE (km) = 131724843.177
TANPT (km) = 1933.641 5183.696 -3951.091
SRFPT (km) = 965.945 2589.501 -1962.095
SRFVEC (km) = 121233070.966 -5997405.747 51166472.910
Differences from case 1 outputs:
Target time delta (s) = 0.000015
ALT delta (km) = 3268.868
RANGE delta (km) = -4.431
TANPT delta (km) = 582.067 4001.541 -921.596
SRFPT delta (km) = -332.236 1454.046 946.360
SRFVEC delta (km) = -918.388 -2547.420 1866.234
Aberration correction: NONE
Aberration correction locus: TANGENT POINT
Observation Time = 2020-12-30 00:00:00 UTC
Target Time = 2020-12-30 00:00:00.000000 UTC
ALT (km) = 781.382
RANGE (km) = 131718986.013
TANPT (km) = 615.190 -3545.867 -2111.285
SRFPT (km) = 500.266 -2883.463 -1713.075
SRFVEC (km) = 120983074.323 -9765994.151 51162607.074
Differences from case 1 outputs:
Target time delta (s) = 439.386796
ALT delta (km) = 641.087
RANGE delta (km) = -5861.595
TANPT delta (km) = -736.384 -4728.022 918.210
SRFPT delta (km) = -797.915 -4018.919 1195.379
SRFVEC delta (km) = -250915.031 -3771135.823 -1999.603
Aberration correction: CN+S
Aberration correction locus: SURFACE POINT
Observation Time = 2020-12-30 00:00:00 UTC
Target Time = 2020-12-29 23:52:40.613204 UTC
ALT (km) = 140.308
RANGE (km) = 131724847.611
TANPT (km) = 1351.579 1182.159 -3029.507
SRFPT (km) = 1298.181 1135.455 -2908.454
SRFVEC (km) = 121233989.351 -5994858.332 51164606.689
Differences from case 1 outputs:
Target time delta (s) = 0.000000
ALT delta (km) = 0.013
RANGE delta (km) = 0.003
TANPT delta (km) = 0.005 0.004 -0.012
SRFPT delta (km) = -0.000 0.000 0.000
SRFVEC delta (km) = -0.003 -0.005 0.013
Restrictions
1) This routine is applicable only to computations for which
radiation paths can be modeled as straight lines.
2) This routine does not account for differential aberration
corrections across the target body surface: when aberration
corrections are used, the entire target ellipsoid's position
and orientation are modified by the corrections that apply at
the aberration correction locus.
3) A cautionary note: if aberration corrections are used, and if
DREF is the target body-fixed frame, the epoch at which that
frame is evaluated is offset from ET by the light time
between the observer and the *center* of the target body.
This light time normally will differ from the light time
between the observer and the tangent or surface point.
Consequently the orientation of the target body-fixed frame
at TRGEPC will not match that of the target body-fixed frame
at the epoch associated with DREF. As a result, various
derived quantities may not be as expected: for example,
SRFVEC would not be parallel to DVEC.
In many applications the errors arising from this frame
discrepancy may be insignificant; however a safe approach is
to always use as DREF a frame other than the target
body-fixed frame.
Literature_References
None.
Author_and_Institution
N.J. Bachman (JPL)
M. Costa Sitja (JPL)
Version
SPICELIB Version 1.0.0, 20-OCT-2021 (NJB) (MCS)
|
Fri Dec 31 18:37:01 2021