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NASA - ILRS SLR MISSION SUPPORT REQUEST FORM (version: January 2018)

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ILRS SLR MISSION SUPPORT REQUEST FORM (version: January 2018)
SUBMISSION STATUS:
☐ New Submission (default)
☐ Incre
mental Submission (accepted only for a follow-on mission; fill-in new information only)
(provide the reference mission and the date approved by the ILRS:
)
SECTION I: MISSION INFORMATION:
General Information:
Satellite Name:
Satellite Host Organization:
Web Address:
Contact Information:
Primary Technical Contact Information:
Name:
Organization and Position:
Address:
Phone No.:
E-mail Address:
Alternate Technical Contact Information:
Name:
Organization and Position:
Address:
Phone No.:
E-mail Address:
Primary Science Contact Information:
Name:
Organization and Position:
Version 01/2018
1
Address:
Phone No.:
E-mail Address:
Alternate Science Contact Information:
Name:
Organization and Position:
Address:
Phone No.:
E-mail Address:
Mission Specifics:
Scientific or Engineering Objectives of Mission:
Role of Satellite Laser Ranging (SLR) for the Mission:
Anticipated Launch Date:
Expected Mission Duration:
Required Orbital Accuracy:
Anticipated Orbital Parameters:
Altitude (Min & Max for eccentric orbits): km
(specify)
(specify)
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2
Inclination: degrees
Eccentricity:
Orbital Period:
Frequency of Orbital Maneuvers:
Mission Timeline:
Tracking Requirements:
Tracking Schedule: horizon-to-horizon custom (specify: )
Spatial Coverage: global ILRS network custom (specify: )
Temporal Coverage: full-time custom (specify:
)
Normal Point Bin Size (Time Span): seconds
(Choose one from 5, 15, 30, 120 and 300 seconds. Justify if other bin size is required.)
(See the “Bin Size” of other satellites on the ILRS Web site at
http://ilrs.gsfc.nasa.gov/missions/satellite_missions/current_missions/index.html .)
Prediction Center:
Prediction Technical Contact Information:
Name:
Organization and Position:
Address:
Phone No.:
E-mail Address:
Priority of SLR for POD:
Other Sources of POD:
☐
DORIS ☐ other (specify: )
(example)
Should include when SLR is to start within the mission timeline, such as "on insertion into orbit" or "launch +N" days.
G
NSS ☐
Primary
Accelerometer ☐
Primary
Secondary Backup
Version 01/2018
3
(specify) (list backup prediction centers and references/links to non-SLR techniques if available)
Other comments on mission information:
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4
SECTION II: TRACKING RESTRICTIONS:
Several types of tracking restrictions have been required during some satellite missions. See
http://ilrs.gsfc.nasa.gov/satellite_missions/restricted.html for a complete discussion.
1) Elevation restrictions: Certain satellites have a risk of possible damage when ranged near the
zenith. Therefore a mission may want to set an elevation (in degrees) above which a station may
not range to the satellite.
2) Go/No-go restrictions: There are situations when on-board detectors on certain satellites are
vulnerable to damaged by intense laser irradiation. These situations could include safe hold
position or maneuvers. A small ASCII file is kept on a computer controlled by the satellite's
mission which includes various information and the literal “go” or “nogo” to indicate whether it
is safe to range to the spacecraft. Stations access this file by ftp every 5-15 minutes (as specified
by the mission) and do not range when the flag file is set to “nogo” or when the internet
connection prevents reading the file.
3) Segment restrictions: Certain satellites can allow ranging only during certain parts of the pass as
seen from the ground. These missions provide station-dependent files with lists of start and stop
times for ranging during each pass.
4) Power limits: There are certain missions for which the laser transmit power must always be
restricted to prevent detector damage. This requires setting laser power and beam divergence at
the ranging station before and after each pass. While the above restrictions are controlled by
software, this restriction is often controlled manually.
Many ILRS stations support some or all of these tracking restrictions. You may wish to work through
the ILRS with the stations to test their compliance with your restrictions or to encourage additional
stations that are critical to your mission to implement them.
The following information gives the ILRS a better idea of the mission's restrictions. Be aware that once
predictions are provided to the stations, there is no guarantee that forgotten restrictions can be
immediately enforced.
Are there any science instruments, detectors, or other instruments on the spacecraft that can be damaged
or confused by excessive radiation, particularly in any one of these wavelengths (532nm, 1064nn, 846nm,
or 432nm)?
No Yes (specify the instrument or
detector in question, providing
the wavelength bands and
modes of sensitivity.)

No Yes (specify:
(If so, go/nogo or segmentation files might be used to avoid ranging an LRA that is not accessible.)
Skip the next questions and go directly to SECTION III if you answered “No” to both of the
above questions.
Are there times when the LRA (Laser Retroreflector Array) will not be accessible from the ground?
Version 01/2018
5
Is there a need for a go/no-go tracking restriction?
No Ye s (Explain the reason(s) )
Is there a need for a pass segmentation restriction?
No Ye s (Explain the reason(s) ) )
Is there a need for a laser power restriction?
No
 Yes (Under what circumstances? )
(What is the maximum permitted power level at the satellite (nJ/cm
2
)? )
(Is manual control of laser transmit power acceptable? Ye s No)
For ILRS stations to range to satellites with restrictions, the mission sponsor must agree to the
following statement:
“The mission sponsor agrees not to make any claims against the station or station contractors or
subcontractors, or their respective employees for any damage arising from these ranging activities,
whether such damage is caused by negligence or otherwise, except in the case of willful misconduct.”
Please provide signature to express agreement to above statement:
(specify)
No Ye s (What elevation (minimum to maximum in degrees)? degrees )
Date:
Organization and Position:
Signature:
Name (print):
Is there a need for an elevation tracking restriction?
Other comments on tracking restrictions:
Version 01/2018
6
click to sign
signature
click to edit
SECTION III: RETROREFLECTOR ARRAY INFORMATION:
A prerequisite for accurate reduction of laser range observations is a complete set of pre-launch
parameters that define the characteristics and location of the LRA on the satellite. The set of parameters
should include a general description of the array, including references to any ground-tests that may
have been carried out, array manufacturer and whether the array type has been used in previous satellite
missions. So the following information is requested:
Retroreflector Primary Contact Information:
Name:
Organization and Position:
Address:
Phone No.:
E-mail Address:
Array type:
Single reflector Spherical Hemispherical/Pyramid Planar Planar
other (specify:
)
Attach a diagram or photograph of the satellite that shows the position of the LRA, at the end of this
document.
☐ Attached
Attach a diagram or photograph of the whole LRA at the end of this document.
Attached Same as above, Not attached (acceptable only for a cannonball satellite)
Array manufacturer:
Link (URL and/or reference) to any ground-tests that were carried out on the array:
Has the LRA design and/or type of cubes been used previously?
No Ye s (List the mission(s): )
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For accurate orbital analysis it is essential that full information is available in order that the 3-
dimensional position of the satellite center of mass may be referred to the location in space at which the
laser range measurements are made. To achieve this, the 3-D location of the LRA phase center must be
specified in a satellite-body-fixed reference frame with respect to the satellite’s mass center. In practice
this means that the following parameters must be available at 1 mm accuracy or better.
Define the satellite-body-fixed XYZ coordinates (i.e. origin and axes) on the spacecraft:
Relate the satellite-body-fixed XYZ coordinates to a Celestial/Terrestrial/Solar Reference Frame
including the attitude control policy:
The 3-D location of the satellite’s mass center in satellite-body-fixed XYZ coordinates is:
Always fixed at (0, 0, 0)
Always fixed at ( , , ) in mm
Time-varying by approximately ( ) mm during the mission lifetime.
Will a time-variable table of the mass center location be available on the web?
No
Ye s (URL: )
The 3-D location (or time-variable range) of the phase center of the LRA in the satellite-body-fixed
XYZ coordinates:
( , , ) in mm
The following information on the corner cubes must also be supplied.
The XYZ coordinates referred to in the following are given in:
Satellite-body-fixed system (same as above)
LRA-fixed system (specify below)
(specify) (add a diagram in the attachment)
(specify) (add a diagram in the attachment)
(specify the origin and orientation) (add a diagram in the attachment )
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8
List the position (XYZ) of the center of the front face of each corner cube, and the orientation (two
angles or normal vector) and the clocking (horizontal rotation) angle of each corner cube. Note that
the angles should be clearly defined.
Attached at the end of this document
Listed here (acceptable for small number (10 or fewer) of corner cubes)
Is the corner cube recessed in its container (i.e. can the container obscure a part of the corner cube)?
No Ye s (specify below)
The size of each corner cube: Diameter ( ) mm Height ( ) mm
The material from which the cubes are manufactured (e.g. quartz):
The refractive index of the cube material
=
for wavelength λ = 0.532 micron
= as a function of wavelength λ (micron):
The group refractive index of the cube material, as a function of wavelength λ (micron):
= for wavelength λ = 0.532 micron
= as a function of wavelength λ (micron):
(specify) (add a diagram in the attachment)
(specify) (add a diagram)
Version 01/2018
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Dihedral angle offset(s) and manufacturing tolerance (in arcseconds):
Dihedral angle offset(s) and manufacturing tolerance (in arcseconds):
Radius of curvature of front surfaces of cubes:
Not applied Yes (specify: )
Flatness of cubes’ surfaces:
Back-face coating:
Uncoated Coated (specify the material: )
(specify) (add a reference to a study of the optical response simulation/measurement if available) (add a diagram if applicable)
Other comments on LRA:
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10
c/o Carey Noll
NASA GSFC
Code 61A
Greenbelt, MD
20771
USA
301-614-6542 (Voice)
301-614-6015 (Fax)
Carey.Noll@nasa.gov
SECTION IV: MISSION CONCURRENCE
The ILRS is a voluntary organization that operates under the auspices of the International Association
of Geodesy (IAG). The ILRS adheres to the IAG policy to make all acquired laser ranging data and
derived products publicly available. We request that the mission website, as well as mission
publications, reference the scientific work derived from ILRS data and derived products, acknowledge
the role of the ILRS. This acknowledgment is crucial for the continued support from the funding
agencies of the ILRS participating organizations.
As an authorized representative of the _____________________________________ mission, I hereby
request and authorize the ILRS to track the satellite described in this document.
Name (print):
Organization and Position:
Signature:
Date:
Send form to: ILRS Central Bureau
Version 01/2018
11
click to sign
signature
click to edit
dd mmm yyyy
SECTION V: ATTACHMENT(S)
Version 01/2018
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