> **LANDSAT DATA CONTINUITY MISSION**
>
> **OPERATIONAL LAND IMAGER**
>
> **SPECIAL CALIBRATION**
>
> **TEST REQUIREMENTS**
>
> **November 2, 2006**

![](media/image1.png)

**CM FOREWORD**

This document is a Landsat Data Continuity Mission (LDCM) Project
Configuration Management (CM)-controlled document. Changes to this
document require prior approval of the applicable Configuration Control
Board (CCB) Chairperson or designee. Proposed changes shall be submitted
to the LDCM CM Office (CMO), along with supportive material justifying
the proposed change. Changes to this document will be made by complete
revision.

Questions or comments concerning this document should be addressed to:

LDCM Configuration Management Office

Mail Stop 427

Goddard Space Flight Center

Greenbelt, Maryland 20771

# Signature Page {#signature-page .Style-Heading-1}

+--------------------------+-------+---------------------------+-------+
| Prepared by:             | Date  | Prepared by:              | Date  |
|                          |       |                           |       |
| Brian Markham            |       | Jim Storey                |       |
|                          |       |                           |       |
| LDCM Calibration         |       | LDCM Systems Engineer     |       |
| Validation Scientist     |       |                           |       |
|                          |       | SAIC, contractor to USGS  |       |
| NASA GSFC Code 614.4     |       | EROS                      |       |
+--------------------------+-------+---------------------------+-------+
| Reviewed by:             | Date  |                           |       |
|                          |       |                           |       |
| Jeanine Morris-Murphy    |       |                           |       |
|                          |       |                           |       |
| LDCM OLI Manager         |       |                           |       |
|                          |       |                           |       |
| NASA GSFC Code 427       |       |                           |       |
+--------------------------+-------+---------------------------+-------+
| Reviewed by:             | Date  |                           |       |
|                          |       |                           |       |
| LDCM Mission Systems     |       |                           |       |
| Manager                  |       |                           |       |
|                          |       |                           |       |
| Evan Webb                |       |                           |       |
|                          |       |                           |       |
| NASA GSFC Code 427       |       |                           |       |
+--------------------------+-------+---------------------------+-------+
| Approved by:             | Date  | Approved by:              | Date  |
|                          |       |                           |       |
| William Ochs             |       | USGS / EROS               |       |
|                          |       |                           |       |
| LDCM Project Manager     |       |                           |       |
|                          |       |                           |       |
| NASA GSFC Code 427       |       |                           |       |
+--------------------------+-------+---------------------------+-------+

#  Document Revision History {#document-revision-history .Style-Heading-1}

This document is controlled by the LDCM Project Management. Changes
require approval of the LDCM Project Manager, LDCM OLI Manager, and the
LDCM Mission Assurance Manager. Proposed changes shall be submitted to
LDCM Systems Engineering Manager.

  ------------- ---------- ---------- ----------------------------------------
  **RELEASE**   **DATE**   **BY**     **DESCRIPTION**

  −                                   Initial Version
  ------------- ---------- ---------- ----------------------------------------

# List of TBD's/TBC's/TBR's {#list-of-tbdstbcstbrs .Style-Heading-1}

This document contains information that is complete as possible. Items
that are not yet defined are annotated with TBD (To Be Determined).
Where final numerical values or data are not available, best estimates
are given and annotated TBC (To Be Confirmed). If there is an
inconsistency between two requirements then the best estimate is given
and annotated with a TBR (To Be Resolved). The following table
summarizes the TBD/TBC/TBR items in the document and supplements the
revision history.

  ---------- --------------- --------------------------------------------------
  **ITEM**   **REFERENCE**   **DESCRIPTION**

                             Data not supplied

                             

                             
  ---------- --------------- --------------------------------------------------

# Table of Contents {#table-of-contents .Style-Heading-1}

[Signature Page iii](#signature-page)

[Document Revision History iv](#document-revision-history)

[List of TBD's/TBC's/TBR's iv](#list-of-tbdstbcstbrs)

[Table of Contents 5](#table-of-contents)

[1 Introduction 6](#introduction)

[1.1 Purpose 6](#purpose)

[1.2 Definitions 6](#definitions)

[1.3 Scope 8](#scope)

[2 General Test Requirements 8](#general-test-requirements)

[3 Pre-flight Test Requirements 9](#pre-flight-test-requirements)

[3.1 Spectral Test Requirements 9](#spectral-test-requirements)

[3.2 Spatial test requirements 13](#spatial-test-requirements)

[3.3 Radiometric Test Requirements 14](#radiometric-test-requirements)

[3.4 Geometric Test Requirements 20](#geometric-test-requirements)

[4 On-Orbit Commissioning Phase Test Requirements
22](#on-orbit-commissioning-phase-test-requirements)

[4.1 Spatial Test Requirements 22](#spatial-test-requirements-1)

[4.2 Radiometric Test Requirements 22](#radiometric-test-requirements-1)

[4.3 Geometric Test Requirements 24](#geometric-test-requirements-1)

# Introduction 

##  Purpose

The LDCM program elements are dependent on the pre-flight and on-orbit
commissioning phase characterization and calibration of the imaging
sensor and related subsystems, and, in particular, on the data sets and
written reports from those tests. It is through the preflight test
reports that the required elements of the Image Assessment System will
be identified. In addition, the algorithms and input parameters to
process the image data will be developed using these preflight data
sets.

The purposes of the pre-flight and commissioning phase test requirements
are to:

-   verify that the instrument's operation conforms to specifications;

-   establish the instrument's as-built performance;

-   test for abnormalities in the sensor's response;

-   provide an at-launch estimate of the sensor\'s radiometric
    calibration;

-   provide characterization data sets that are otherwise unobtainable
    in flight or on the ground (such as spectral band characteristics,
    PSF parameters, and solar diffuser reflectance); and

-   determine the instrument's radiometric stability.

The LDCM contractor has the responsibility for providing an
instrument(s) capable of providing well calibrated, well characterized
and specification compliant data, to ensure Landsat data continuity. The
Government has the responsibility for independently assuring that the
delivered instrument will be specification compliant and sufficiently
well calibrated and characterized to fulfill the Mission objectives. The
following Special Calibration Test Requirements (SCTR's) are an
essential component of that independent assurance program

## Definitions

The observatory elements identified in Figure 1-1 and defined below are
provided for clarification of terms used in the SCTR and are not
intended to dictate a design implementation.

Refer to the LDCM Acronym List and Lexicon for more Definitions.

Figure 1‑1 Relationship of Elements in the SCTR

Operational Land Imager (OLI) -- The LDCM sensor payload designed to
collect data for the LDCM reflective bands 1 through 9 (433-2300 nm).

Sensor - The integrated instrument comprising optics, spectral bandpass
filters, sensing elements, electronics, calibration source(s), and
associated mechanisms and structural elements.

Focal Plane Array (FPA) -- The detectors and associated electronics
assembled with the spectral bandpass filters. A focal plane array
comprises one or more sensor chip assemblies illuminated by a common
optical path, and the associated electronics.

Calibration Source -- A component of the sensor that provides controlled
and/or measured reference radiance input to the RBS sensing elements for
purposes of calibration.

Simulated On-Orbit Operating Conditions -- Temperature and pressure
environmental conditions similar to those experienced on-orbit, i.e.,
thermal vacuum.

Vacuum -- Atmospheric pressure of 10-5 torr or less as defined in the
General Environmental Verification Standard (GEVS) For GSFC Flight
Programs and Projects.

Operational Temperature Range -- The range of temperatures over which an
LDCM subsystem or component is designed to operate while meeting all
specifications.

Determine -- Use one or more measurements and associated analyses to
estimate the value for a particular system parameter or performance
characteristic

## Scope

The following test requirements do not constitute a complete set of
tests. The Contractor is responsible for verification and validation of
[all]{.underline} LDCM requirements. The tests described herein shall be
included as part of the Contractor's overall validation program as
required in the Calibration/Validation Plan CDRL (CV-1). The contractor
shall report the results of these tests in accordance with the
Calibration/Validation Test Report CDRL (CV-3). For selected tests,
indicated by "(CV-9)" following the test description, the image data
collected during these tests shall be provided to the government in
accordance with CDRL CV-9.

# General Test Requirements

2.1 Sampling methods and their statistical validity shall be described
in the calibration/validation plan CDRL CV-1.

2.2 The sampling of the instrument and focal plane temperatures to be
used for the characterizations shall be described in the
calibration/validation plan (CV-1).

2.3 The Contractor shall calibrate radiance calibration sources to
National Institute of Standards and Technology (NIST) standards for
radiometric calibrations.

# Pre-flight Test Requirements 

## Spectral Test Requirements

3.1.1 The Contractor shall measure the spectral transmission of the
spectral bandpass filters per the parameters in table 3.1-1.

3.1.2 The Contractor shall measure the relative spectral radiance
response of a sample of detectors per the parameters in table 3.1-1.

3.1.3 The Contractor shall measure the spectral transmission or
reflectance of the optical elements of the instrument telescope per the
parameters in table 3.1-1.

3.1.4 The Contractor shall measure the in-band relative spectral
radiance response of the instrument per the parameters in Table 3.1-1
(note a. and b. sub-requirements).

3.1.5 The Contractor shall determine the out-of-band relative spectral
radiance response of the instrument for each band via measurements
conducted per the parameters in Table 3.1-1.

3.1.6 The Contractor shall characterize the stability of the spectral
transmission of the spectral band bandpass filters between ambient
pressure and vacuum conditions per the parameters in Table 3.1-1.

3.1.7 The Contractor shall measure the spectral transmission of the
thermal vacuum chamber optical window per the parameters in Table 3.1-1.

Rationale: These spectral calibration tests are used to determine
compliance with OLI spectral requirements (section 5.4 of OLI
Requirements Document \[OLIRD\]). Also, these measurements are required
in order to perform the radiometric calibration of the instrument and
provide the user community the fundamental spectral characteristics of
the data. The component level measurements (3.1.1 -- 3.1.3) will be used
to predict the system level response and assure the final system will
likely meet relative spectral response requirements; however, measuring
the response on the assembled instrument in as close to operational
conditions as possible is required for an adequate characterization
(3.1.4). The spectral uniformity requirement, in particular, requires
characterization of the variation in the system level responses (section
5.6.2.3 of OLIRD). It is difficult to obtain sufficient energy to
measure the out-of-band response at the integrated instrument level, so
measurements at the detector mated to filter assembly level are allowed
for this characterization (3.1.5). Spectral bandpass filters have
historically shown stability problems in the transition from ambient to
vacuum conditions, apparently due to the outgassing of absorbed water.
Current filter fabrication techniques have reduced this problem
significantly; test 3.1.6 is intended to verify that the OLI filters do
not have this problem and will likely meet the spectral stability
requirement for OLI (section 5.4.5 of OLIRD). The spectral and
radiometric characterizations of the integrated instrument will occur
with the instrument in the Thermal Vacuum chamber and the calibration
sources outside; a characterization of the spectral transmission of the
optical window is thus required.

+----+------+----+-------+-------+--------+--------------+------+---+
| Te | Asse | Un | M     | Sa    | Wave   | Wavelength   | P    | O |
| st | mbly | it | easur | mples | length | Sampling and | reci | t |
|    | L    |    | ement |       | Range  |              | sion | h |
|    | evel |    | Condi |       |        | Wavelength   |      | e |
|    |      |    | tions |       |        | Resolution   |      | r |
|    |      |    |       |       |        |              |      |   |
|    |      |    |       |       |        | (FWHM)       |      |   |
+----+------+----+-------+-------+--------+--------------+------+---+
| 3  | C    | Fi | O     | 5 per | Across | In-band: 1   | 0    |   |
| .1 | ompo | lt | perat | f     | range  | nm below 1   | .001 |   |
| .1 | nent | er | ional | light | of     | μm; 2 nm     | (1   |   |
|    |      |    | an    | f     | sensi  | above 1 μm   | σ)   |   |
|    |      |    | gular | ilter | tivity |              | in   |   |
|    |      |    | and   | wafer | (to    | Out-of-band: | b    |   |
|    |      |    | t     |       | 0.0001 | 5 nm below 1 | and; |   |
|    |      |    | emper |       | of     | μm; 10 nm    | SNR  |   |
|    |      |    | ature |       | peak   | above 1 μm   | \>10 |   |
|    |      |    | condi |       | res    |              | down |   |
|    |      |    | tions |       | ponse) |              | to   |   |
|    |      |    |       |       | of     |              | 0.   |   |
|    |      |    |       |       | det    |              | 0005 |   |
|    |      |    |       |       | ectors |              | of   |   |
|    |      |    |       |       |        |              | peak |   |
|    |      |    |       |       |        |              | tr   |   |
|    |      |    |       |       |        |              | ans. |   |
+----+------+----+-------+-------+--------+--------------+------+---+
| 3  | C    | De | O     | 1% of | Across | In-band: 1   | 0    |   |
| .1 | ompo | te | perat | dete  | range  | nm below 1   | .001 |   |
| .2 | nent | ct | ional | ctors | of     | μm; 2 nm     | (1   |   |
|    |      | or | an    | unif  | sensi  | above 1 μm   | σ)   |   |
|    |      |    | gular | ormly | tivity |              | in   |   |
|    |      |    | and   | d     | (to    | Out-of-band: | b    |   |
|    |      |    | t     | istri | 0.0001 | 10 nm below  | and; |   |
|    |      |    | emper | buted | of     | 1 μm; 20 nm  | SNR  |   |
|    |      |    | ature | a     | peak   | above 1 μm   | \>10 |   |
|    |      |    | condi | cross | res    |              | down |   |
|    |      |    | tions | each  | ponse) |              | to   |   |
|    |      |    |       | f     | of     |              | 0.   |   |
|    |      |    |       | light | det    |              | 0005 |   |
|    |      |    |       | SCA   | ectors |              | of   |   |
|    |      |    |       | per   |        |              | peak |   |
|    |      |    |       | band  |        |              |      |   |
+----+------+----+-------+-------+--------+--------------+------+---+
| 3  | C    | O  | O     | 3     | Across | In-band: 1   | 0    |   |
| .1 | ompo | pt | perat | sa    | range  | nm below 1   | .001 |   |
| .3 | nent | ic | ional | mples | of     | μm; 2 nm     | (1   |   |
|    |      | al | an    | of    | sensi  | above 1 μm   | σ)   |   |
|    |      | S  | gular | each  | tivity |              | in   |   |
|    |      | ur | and   | op    | (to    | Out-of-band: | b    |   |
|    |      | fa | t     | tical | 0.0001 | 10 nm below  | and; |   |
|    |      | ce | emper | su    | of     | 1 μm; 20 nm  | SNR  |   |
|    |      | s/ | ature | rface | peak   | above 1 μm   | \>10 |   |
|    |      | w  | condi |       | res    |              | down |   |
|    |      | it | tions |       | ponse) |              | to   |   |
|    |      | ne |       |       | of     |              | 0.   |   |
|    |      | ss |       |       | det    |              | 0005 |   |
|    |      | s  |       |       | ectors |              | of   |   |
|    |      | am |       |       |        |              | peak |   |
|    |      | pl |       |       |        |              |      |   |
|    |      | es |       |       |        |              |      |   |
+----+------+----+-------+-------+--------+--------------+------+---+
| 3  | In   |    | Va    | Same  | B      | 1 nm below 1 | 0.01 |   |
| .1 | tegr |    | cuum; | dete  | etween | μm;          | (1   |   |
| .4 | ated |    | o     | ctors | 0.005  |              | σ)   |   |
| .a | In   |    | perat | as in | re     | 2 nm above 1 | a    |   |
|    | stru |    | ional | 3.1.2 | sponse | μm           | bove |   |
|    | ment |    | focal |       | points |              | 0.1  |   |
|    |      |    | plane |       |        |              | RSR; |   |
|    |      |    | t     |       |        |              | SNR  |   |
|    |      |    | emper |       |        |              | \>10 |   |
|    |      |    | ature |       |        |              | b    |   |
|    |      |    |       |       |        |              | elow |   |
|    |      |    |       |       |        |              | 0.1  |   |
|    |      |    |       |       |        |              | RSR  |   |
+----+------+----+-------+-------+--------+--------------+------+---+

Table 3.1-1: Spectral Test Minimum Acceptable Requirements

+----+------+-----+-------+------+--------+------------+------+------+
| 3  | In   |     | Va    | 10%  | B      | 2 nm below | 0.01 |      |
| .1 | tegr |     | cuum; | of   | etween | 1 μm;      | (1   |      |
| .4 | ated |     | o     | d    | 0.005  |            | σ)   |      |
| .b | In   |     | perat | etec | re     | 4 nm above | a    |      |
|    | stru |     | ional | tors | sponse | 1 μm       | bove |      |
|    | ment |     | focal | u    | points |            | 0.1  |      |
|    |      |     | plane | nifo |        |            | RSR; |      |
|    |      |     | t     | rmly |        |            | SNR  |      |
|    |      |     | emper | dis  |        |            | \>10 |      |
|    |      |     | ature | trib |        |            | b    |      |
|    |      |     |       | uted |        |            | elow |      |
|    |      |     |       | ac   |        |            | 0.1  |      |
|    |      |     |       | ross |        |            | RSR  |      |
|    |      |     |       | f    |        |            |      |      |
|    |      |     |       | ocal |        |            |      |      |
|    |      |     |       | p    |        |            |      |      |
|    |      |     |       | lane |        |            |      |      |
+----+------+-----+-------+------+--------+------------+------+------+
| 3  | Asse | Ma  | O     | Same | Across | 10 nm      | SNR  | Use  |
| .1 | mbly | ted | perat | d    | range  | below 1    | \>10 | 3    |
| .5 | or   | F   | ional | etec | of     | μm;        | down | .1.3 |
|    | a    | ilt | an    | tors | sensi  |            | to   | res  |
|    | bove | er/ | gular | as   | tivity | 20 nm      | 0.   | ults |
|    |      |     | and   | in   | (to    | above 1 μm | 0005 | to   |
|    |      | De  | t     | 3    | 0.0001 |            | of   | r    |
|    |      | tec | emper | .1.2 | of     |            | peak | epre |
|    |      | tor | ature |      | peak   |            | resp | sent |
|    |      |     | condi |      | res    |            | onse | op   |
|    |      | As  | tions |      | ponse) |            |      | tics |
|    |      | sem | with  |      | of     |            |      | if   |
|    |      | bly | adj   |      | det    |            |      | no   |
|    |      | Le  | acent |      | ectors |            |      | in   |
|    |      | vel | bands |      |        |            |      | stru |
|    |      | or  | i     |      |        |            |      | ment |
|    |      | ab  | llumi |      |        |            |      | l    |
|    |      | ove | nated |      |        |            |      | evel |
|    |      |     |       |      |        |            |      | test |
+----+------+-----+-------+------+--------+------------+------+------+
| 3  | C    | Fil | Am    | 1    | Across | In-band: 1 | 0    | Re   |
| .1 | ompo | ter | bient | fi   | range  | nm below 1 | .001 | peat |
| .6 | nent | w   | condi | lter | of     | μm; 2 nm   | (1   | amb  |
|    |      | itn | tions | per  | sensi  | above 1    | σ)   | ient |
|    |      | ess | then  | b    | tivity | μm;        | in   | meas |
|    |      | s   | in    | and; | (to    |            | b    | ure- |
|    |      | amp | v     | 3    | 0.0001 | Out-of     | and; |      |
|    |      | les | acuum | s    | of     | band: 5 nm | SNR  | m    |
|    |      |     | after | pots | peak   | below 1    | of   | ents |
|    |      |     | 1, 3, | per  | res    | μm, 10 nm  | \>10 | e    |
|    |      |     | 5 and | fi   | ponse) | above 1 μm | down | very |
|    |      |     | 7     | lter | of     |            | to   | 6    |
|    |      |     | days  |      | det    |            | 0.   | mo   |
|    |      |     | of    |      | ectors |            | 0005 | nths |
|    |      |     | v     |      |        |            | of   | u    |
|    |      |     | acuum |      |        |            | peak | ntil |
|    |      |     | exp   |      |        |            | tr   | lau  |
|    |      |     | osure |      |        |            | ans. | nch. |
+----+------+-----+-------+------+--------+------------+------+------+
| 3  | Test | T/V | Am    | 5    | Across | Within any | 0    |      |
| .1 | E    | C   | bient | s    | range  | band's     | .001 |      |
| .7 | quip | ham | Condi | pots | of     | in-band    | (1   |      |
|    | ment | ber | tions |      | sensi  | response:  | σ)   |      |
|    |      | O   |       |      | tivity | 1 nm below | in   |      |
|    |      | pti |       |      | (to    | 1 μm; 2 nm | b    |      |
|    |      | cal |       |      | 0.0001 | above 1    | and; |      |
|    |      | Win |       |      | of     | μm;        | SNR  |      |
|    |      | dow |       |      | peak   | Ou         | of   |      |
|    |      |     |       |      | res    | t-of-band: | \>10 |      |
|    |      |     |       |      | ponse) | 5 nm below | down |      |
|    |      |     |       |      | of any | 1 μm, 10   | to   |      |
|    |      |     |       |      | band's | nm above 1 | 0.   |      |
|    |      |     |       |      | det    | μm         | 0005 |      |
|    |      |     |       |      | ectors |            | of   |      |
|    |      |     |       |      |        |            | peak |      |
+----+------+-----+-------+------+--------+------------+------+------+

## Spatial test requirements

3.2.1 The Contractor shall characterize the spatial edge response based
on measurements at the integrated instrument level, pre- and
post-vibration testing, under simulated on-orbit operating conditions
across the entire FOV in all bands. (CV-9).

Measurement conditions:

> 11 field angles (scale factors of field-of-view (FOV): -1, -.89, -.77,
> -.63, -.44, 0, .44, .63, .77, .89, 1.0)
>
> 0.05 IFOV increments from ± 3 IFOV from center of detector in both
> along-track and across-track directions
>
> 0.5 IFOV increments from 3 to 10 IFOV from center of detector in both
> along track and across-track directions
>
> At the nominal and the high and low acceptance temperatures

Rationale: These measurements will be used to verify the OLI Edge
Response requirements (Section 5.5.2 of the OLIRD). Edge response may be
a function of location with the focal plane, hence the requirement to
characterize across the entire FOV. The angular sampling provides equal
enclosed area increments.

3.2.2 The Contractor shall demonstrate the edge slope response of the
instrument VNIR bands remains within specification following
observatory-level vibration testing at one previously measured
(non-zero) field angle for each band.

3.2.2.a. The contractor may select the off-axis angle to be verified to
provide the simplest test setup but the selected angle shall be
documented in the calibration/validation plan (CV-1).

3.2.3. The Contractor shall characterize the stray light rejection and
internal light scattering of the instrument based on measurements at the
component level or above and analysis.

3.2.3.a The stray light model shall be developed using a
Government-approved non-sequential ray trace method, e.g. ASAP, APART,
GUERAP, or Trace Pro.

3.2.3.b The stray light model shall encompass the entire optical system,
including baffles and the focal plane, detectors and mounting devices
and all portions of the satellite bus and other payloads that may
reflect light into the sensor.

Rationale: These measurements and analysis will be used to verify
section 5.5.4 of the OLIRD and section \_\_ of the IRD.

3.2.4 The Contractor shall include a stray light analysis of the solar
diffuser panel(s) in the deployed position.

3.2.4.a This analysis shall include glints and shadowing on the diffuser
by other observatory structures as well as the instrument itself.

3.2.4.b As part of this analysis, the Contractor shall demonstrate that
diffuser measurements on orbit are not contaminated by reflected light
from the Earth and the atmosphere.

3.2.4.c The contractor shall validate, by measurements at the integrated
instrument level in two separate bands, the diffuser stray light model's
(excluding observatory effects) prediction of the reflectance
enhancement due to the diffuser instrument proximity.

Rationale: This characterization will allow the solar diffuser to be
used as an absolute calibration source: the observatory, the sensor
itself and the Earth may all contribute stray light to the solar
diffuser.

3.2.5 The Contractor shall verify the ghosting requirements (sec 5.5.5
of the OLIRD) are met by using the stray light model in 3.2.3.

3.2.6 The Contractor shall verify the ghosting requirements (sec 5.5.5
of the OLIRD) are met by test at the integrated instrument level using a
broad-band far-field illuminated object.

3.2.6.a The test object shall be scanned across the full FOV of the
telescope.

3.2.6.b. The test object shall be at least 0.1 of the FPA across-Track
FOV.

3.2.7 The Contractor shall measure the optical power and distortion of
the thermal vacuum chamber optical window under expected thermal vacuum
operating conditions.

Rationale: Spatial measurements performed through the chamber window
will be affected by the window's optical properties.

## Radiometric Test Requirements

3.3.1 The Contractor shall radiometrically calibrate all detectors at
the integrated instrument level per the parameters in Table 3.3-1.
(CV-9).

3.3.2 The Contractor shall characterize the radiometric response of all
detectors across the expected instrument operating temperature range per
the parameters in Table 3.3-1 (CV-9).

3.3.3 The Contractor shall collect calibration data sets and
characterization data to demonstrate that the calibrated data will meet
the absolute radiometric accuracy, pixel-to-pixel uniformity and
radiometric stability requirements on orbit per the parameters in Table
3.3-1 (CV-9).

3.3.4 The Contractor shall determine the mathematical equation(s) to
convert the instrument output in DN to input radiance per the parameters
in Table 3.3-1.

Rationale: These tests (3.3.1-3.3.4) provide the basic radiance
calibration of the instrument. The characterization of the mathematical
form of the radiance calibration (e.g., linear) may be more accurately
performed before integration of the focal plane into the instrument,
whereas the final pre-launch calibration (3.3.1) is performed on the
integrated instrument. Characterization of the temperature sensitivity
of this calibration (3.3.2) is performed on a subset of the radiance
levels used for the primary calibration. Verification that the
instrument, the radiance calibration and the radiance calibration
algorithm perform to requirements for accuracy, stability and
pixel-to-pixel uniformity (in part) (sections 5.6.1, 5.6.2.3, 5.6.5)
occur in 3.3.3.

3.3.5 The Contractor shall characterize the spectral bidirectional
reflectance of the solar diffuser panel across the range of solar
incidence angles and focal plane view angles to be used on orbit.

Measurement Details:

10 nm increment from 0.4 to 0.9 μm;

25 nm increment from 1.5 to 2.4 μm;

5 degree increment of solar zenith angle;

5 degree increment of view zenith angle;

5 degree increment of relative azimuth angle;

Measurements performed to 5 degrees beyond expected angles of usage.

3.3.5.a The Contractor shall characterize the reproducibility of the
diffuser deployment angle at the integrated instrument level.

Rationale: The solar diffuser provides the reflectance-based calibration
of the instrument (section 5.6.1 of OLIRD); the characterization of the
reflectance and deployment angles of the diffuser are required to use
the solar diffuser as a reflectance calibration source, as well as a
radiance calibration source assuming a knowledge of the solar spectral
irradiance.

3.3.6 The Contractor shall characterize the stability of the internal
calibration lamp system including the warm-up behavior until
stabilization to within 0.1% of final output per the parameters in Table
3.3-1 (CV-9).

Rationale: The internal light sources provide the only technique for
monitoring the short-term stability of the radiometric calibration,
i.e., minutes to days.

3.3.7 The Contractor shall provide an integrated instrument-level
observation of at least one on-board calibration device that is expected
to be radiometrically stable through launch (CV-9).

3.3.7.a This observation shall be repeatable on orbit to assess the
transfer of the pre-launch radiometric calibration to on-orbit
calibration (i.e., Transfer to Orbit Measurement).

Rationale: A recurring problem with satellite sensors is a loss of
certainty in the absolute calibration of the instrument during the
launch process. Changes in conditions between ground and on-orbit, e.g.
gravity, make certain devices perform differently. The contractor is
required to provide a transfer to orbit calibration source (5.9.2.f of
the OLIRD) that is free of known differences in performance between
these environments. This device needs to be exercised during pre-launch
testing and once on-orbit to assess the instruments stability through
this period.

3.3.8 The Contractor shall characterize the Signal to Noise Ratio
(section 5.6.2.1 of OLIRD) of all detectors per the parameters in Table
3.3-1. (CV-9).

3.3.9 The Contractor shall characterize the predictability of all
imaging detector biases from the dark reference detectors for each SCA
per the parameters in Table 3.3-1 (CV-9).

3.3.10 The Contractor shall characterize the bias stability and noise
levels of all imaging and dark reference detectors per the parameters in
Table 3.3-1 (CV-9).

Rationale: The bias stability of the imaging detectors and the
correlation of the imaging detectors variation with the dark reference
detectors are fundamental to the performance of the bias determination
algorithm and thus ability to determine the bias values applicable to an
individual acquisition. The longest continuous WRS-2 path over land
masses is about 30 minutes in length.

3.3.11 The Contractor shall characterize the detector bias and gain
stability across expected on-orbit on-off cycling of the instrument per
the parameters in Table 3.3-1 (CV-9).

Rationale: Instruments when power cycled may restart in different bias
and/or gain states.

3.3.12 The Contractor shall characterize the baseline 1/f noise
parameters for all imaging and dark reference detectors per the
parameters in Table 3.3-1 (CV-9).

3.3.13 The Contractor shall characterize the coherent noise of the
instrument (section 5.6.2.4 of OLIRD) per the parameters in Table 3.3-1
(CV-9).

3.3.14 The Contractor shall characterize the dark level coherent noise
of the instrument (section 5.6.2.4 of OLIRD) per the parameters in Table
3.3-1 (CV-9).

3.3.15 The Contractor shall characterize the linear polarization
sensitivity of the instrument (section 5.6.4 of OLIRD) by component
level measurements and analysis.

3.3.15.a The Contractor shall measure the linear polarization
sensitivity of a sampling of detectors from each band (center and edges
of field of view) per the parameters in Table 3.3-1.

3.3.16 The Contractor shall verify the bright target recovery and
pixel-to-pixel electrical crosstalk requirements of the instrument
(section 5.6.6 of OLIRD) per the parameters in Table 3.3-1.

3.3.17 The Contractor shall provide and maintain a detector operability
status list which include dead, inoperable, and out-of-spec detectors
for each band.

Table 3.3-1 Radiometric Test Minimum Acceptable Requirements

+----+-------+-------+-------+---------------------+------+----------+
| Te | Ass   | M     | M     | Radiance Levels     | Cal  | Comments |
| st | embly | easur | easur |                     | ibra |          |
|    | Level | ement | ement |                     | tion |          |
|    |       |       | T     |                     | So   |          |
|    |       | Am    | emper |                     | urce |          |
|    |       | bient | ature |                     | Loca |          |
|    |       | A     | Condi |                     | tion |          |
|    |       | tmosp | tions |                     |      |          |
|    |       | heric |       |                     |      |          |
|    |       |       |       |                     |      |          |
|    |       | Condi |       |                     |      |          |
|    |       | tions |       |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | Th    | No    | Dark and 10 levels  | Amb  | Internal |
| 3. | rated | ermal | minal | between 0.3         | ient | Lamps to |
| 1, | Instr | V     | o     | Ltypical and LMAX   | vi   | be       |
| 3. | ument | acuum | perat |                     | ewed | operated |
| 3. |       |       | ional | (dark and only 5    | thr  | and      |
| 6, |       | (no   | focal | levels required for | ough | warm-up  |
|    |       | minal | plane | 3.3.13)             | cha  | behavior |
| 3. |       | te    | t     |                     | mber | chara    |
| 3. |       | mpera | emper |                     | wi   | cterized |
| 8, |       | ture) | ature |                     | ndow | during   |
| 3. |       |       |       |                     |      | these    |
| 3. |       |       |       |                     |      | tests    |
| 13 |       |       |       |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | Th    | Alte  | Dark and 5 levels   | Amb  | Internal |
| 3. | rated | ermal | rnate | between 0.3         | ient | Lamps to |
| 2, | Instr | V     | focal | Ltypical and LMAX   | vi   | be       |
| 3. | ument | acuum | plane |                     | ewed | operated |
| 3. |       |       | t     |                     | thr  | and      |
| 6, |       |       | emper |                     | ough | warm-up  |
|    |       |       | ature |                     | cha  | behavior |
| 3. |       |       | set   |                     | mber | chara    |
| 3. |       |       | p     |                     | wi   | cterized |
| 8, |       |       | oints |                     | ndow | during   |
| 3. |       |       |       |                     |      | these    |
| 3. |       |       |       |                     |      | tests    |
| 13 |       |       |       |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | Th    | No    | Dark and 5 levels   | Amb  | Internal |
| 3. | rated | ermal | minal | between 0.3         | ient | Lamps to |
| 2, | Instr | V     | o     | Ltypical and LMAX   | vi   | be       |
| 3. | ument | acuum | perat |                     | ewed | operated |
| 3. |       | (high | ional |                     | thr  | and      |
| 6, |       | and   | focal |                     | ough | warm-up  |
| 3. |       | low   | plane |                     | cha  | behavior |
| 3. |       | t     | t     |                     | mber | chara    |
| 8, |       | emper | emper |                     | wi   | cterized |
| 3. |       | ature | ature |                     | ndow | during   |
| 3. |       | plat  |       |                     |      | these    |
| 13 |       | eaus) |       |                     |      | tests    |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | Th    | No    | Simulated orbits    | Amb  | Internal |
| 3. | rated | ermal | minal | with external       | ient | Lamps to |
| 3, | Instr | V     | o     | calibration source, | vi   | be       |
| 3. | ument | acuum | perat | repeated to         | ewed | operated |
| 3. |       |       | ional | captured 16 day     | thr  | and      |
| 6, |       |       | focal | requirements        | ough | warm-up  |
| 3. |       |       | plane |                     | cha  | behavior |
| 3. |       |       | t     |                     | mber | chara    |
| 8, |       |       | emper |                     | wi   | cterized |
| 3. |       |       | ature |                     | ndow | during   |
| 3. |       |       |       |                     |      | these    |
| 11 |       |       |       |                     |      | tests;   |
|    |       |       |       |                     |      | FPA      |
|    |       |       |       |                     |      | reset as |
|    |       |       |       |                     |      | per      |
|    |       |       |       |                     |      | on-orbit |
|    |       |       |       |                     |      | ops      |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Focal | No    | No    | 20 levels between   |      |          |
| 3. | plane | r     | minal | dark and LMAX for   |      |          |
| 4, | level | equir | o     | 3.3.4               |      |          |
| 3. | or    | ement | perat |                     |      |          |
| 3. | above |       | ional |                     |      |          |
| 16 |       |       | focal |                     |      |          |
|    |       |       | plane |                     |      |          |
|    |       |       | t     |                     |      |          |
|    |       |       | emper |                     |      |          |
|    |       |       | ature |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | Th    | At    | Dark Level,         | N/A  |          |
| 3. | rated | ermal | each  | measurements over   |      |          |
| 9, | Instr | V     | o     | 40 minutes (may be  |      |          |
|    | ument | acuum | perat | sampled) in         |      |          |
| 3. |       |       | ional | simulated orbits,   |      |          |
| 3. |       |       | focal | three repeats at    |      |          |
| 10 |       |       | plane | nominal temperature |      |          |
|    |       |       | t     | set point           |      |          |
|    |       |       | emper |                     |      |          |
|    |       |       | ature |                     |      |          |
|    |       |       | set   |                     |      |          |
|    |       |       | point |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | Th    | At    | Dark Level,         | N/A  | No FPA   |
| 3. | rated | ermal | each  | continuous          |      | on-off   |
| 12 | Instr | V     | o     | measurements over   |      | cycling  |
|    | ument | acuum | perat | 40 minutes          |      | or       |
|    |       |       | ional |                     |      | resets   |
|    |       |       | focal |                     |      | during   |
|    |       |       | plane |                     |      | the      |
|    |       |       | t     |                     |      | meas     |
|    |       |       | emper |                     |      | urements |
|    |       |       | ature |                     |      |          |
|    |       |       | set   |                     |      |          |
|    |       |       | point |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | O     | Th    | At    | Dark Level          | N/A  |          |
| 3. | bserv | ermal | each  |                     |      |          |
| 14 | atory | V     | o     |                     |      |          |
|    |       | acuum | perat |                     |      |          |
|    |       |       | ional |                     |      |          |
|    |       | (high | focal |                     |      |          |
|    |       | and   | plane |                     |      |          |
|    |       | low   | t     |                     |      |          |
|    |       | t     | emper |                     |      |          |
|    |       | emper | ature |                     |      |          |
|    |       | ature | set   |                     |      |          |
|    |       | plat  | point |                     |      |          |
|    |       | eaus) |       |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+
| 3. | Integ | No    | At    | No requirement      | N/A  |          |
| 3. | rated | r     | o     |                     |      |          |
| 15 | Instr | equir | perat |                     |      |          |
| .a | ument | ement | ional |                     |      |          |
|    |       |       | focal |                     |      |          |
|    |       |       | plane |                     |      |          |
|    |       |       | t     |                     |      |          |
|    |       |       | emper |                     |      |          |
|    |       |       | ature |                     |      |          |
|    |       |       | set   |                     |      |          |
|    |       |       | point |                     |      |          |
+----+-------+-------+-------+---------------------+------+----------+

## Geometric Test Requirements

3.4.1 The Contractor shall measure each detector's LOS relative to the
instrument coordinate system, to an accuracy ≤ 6 μrad (3-sigma), at the
integrated instrument level.

Rationale: Band-to-band and image-to-image registration error budgets
are driven by platform stability and line-of-sight knowledge and
stability. The current error budgets assume 6 μrad (3-sigma) LOS
knowledge and stability. On-orbit results from ALI showed focal plane
calibration consistency of 3.9 μrad (3-sigma) for SCA-level offset,
rotation and scale parameters.

3.4.2 The Contractor shall demonstrate the relative thermal stability of
the detector lines of sight by measuring the relative locations of a
selected set of detectors at the nominal, maximum and minimum expected
operating temperatures, to an accuracy ≤ 3 μrad (3-sigma), at integrated
instrument or observatory level, post-vibration.

3.4.2.a The selected set of detectors shall include, at a minimum, the
first, middle, and last detector in each row, if multiple rows of
detectors are provided, e.g., due to even/odd detector stagger or the
inclusion of redundant detectors, from each band on each SCA.

Rationale: Line-of-sight stability (over the range of expected operating
temperatures) of 6 μrad (3-sigma) or better is required by the current
band registration and image registration error budgets. The measurements
intended to demonstrate stability to this level must be more accurate by
a factor of 2 or better.

3.4.3 The Contractor shall characterize the detector-sampling timing
pattern, to an accuracy of 150 microseconds (3-sigma) or better, via
measurement of any detector-specific electronic delays, sample phasing
(e.g., even/odd detector timing offsets), and frame rate (i.e., time
between samples) for each detector.

Rationale: Detector to detector timing/latency variations must not
significantly degrade the line-of-sight knowledge of 6 μrad (3-sigma).
Timing knowledge to 50 microseconds corresponds to an additional LOS
uncertainty of approximately 1.5 μrad. This is slightly less that the
overall absolute timing knowledge accuracy requirement of 200
microseconds (3-sigma) cited in SSRD sections 11.1 and 12.1.

3.4.4 The Contractor shall measure the alignment of the instrument
optical axes relative to the OLI alignment reference/ alignment cube.

Rationale: The prelaunch alignment of the instrument to the ACS
reference frame is an initial measurement used to get the on-orbit
calibration procedure started. The actual instrument alignment is
expected to shift due to launch and zero-G release. This measurement is
the instrument portion of the overall OLI to observatory ACS alignment
measurement. The geodetic accuracy error budgets are based on on-orbit
alignment calibration accuracy so the accuracy of the prelaunch
measurements is not critical.

3.4.5 The Contractor shall demonstrate the ability to reconstruct and
register images in all spectral bands from data collected under
conditions that simulate the on-orbit target motion (CV-9).

Note: This demonstration may be performed in segments over the full FOV
of the instrument.

Rationale: This test is intended to verify the integrity of the
instrument to recorder data path.

3.4.6 Following observatory-level vibration testing, the Contractor
shall demonstrate that the data from the VNIR detectors are mapped to
the correct locations in the observatory downlink data stream.

Note: This test may be performed using an internal source.

Rationale: This observatory level test is intended to demonstrate that
the instrument and spacecraft data handling systems were successfully
integrated and that no data connections were damaged during vibration
testing. An internal source that provides input that varies across the
focal plane should be sufficient for verifying the integrity of the data
path.

# On-Orbit Commissioning Phase Test Requirements 

## Spatial Test Requirements

4.1.1 The Contractor shall examine the stray light and ghosting of the
instrument using the moon at least twice, using data acquired at least
16 days apart.

Rationale: Although a true characterization of the stray light response
and ghosting is not possible using the moon, the data can be examined
for effects that are not predicted by the stray light model. In other
instruments, e.g. ALI and ASTER lunar views have revealed stray light
and ghosting issues.

## Radiometric Test Requirements

4.2.1 The Contractor shall characterize on-board lamp based calibrator
on-orbit performance and stability including warm-up behavior and within
and between orbit stability relative to the instrument.

4.2.2 The Contractor shall characterize the variation in the BRF of the
solar diffuser across the range of azimuth and zenith angles to be used
for on-orbit calibration.

4.2.3 The contractor shall characterize the reproducibility of the solar
calibration technique with a minimum of 5 measurements, with each
measurement acquired a minimum of 1 day apart.

4.2.4 The contractor shall complete the on-orbit portion of the Transfer
to Orbit Measurement (See SCTR 3.3.7).

4.2.5 The Contractor shall characterize the stability of the instrument
by reference to the internal lamps by a minimum of daily measurements.

4.2.6 The Contractor shall update the absolute calibration coefficients
and uncertainties as required to meet performance specifications.

4.2.7 The Contractor shall characterize any variations in detector
responsivity over a minimum of 2 instrument outgassing cycles, if
outgassing is required.

4.2.8 The Contractor shall characterize the relative detector response
for detectors within a band and update the calibration parameters to
correct pixel-to-pixel non-uniformity as necessary.

4.2.9 The Contractor shall characterize both the coherent and total
noise of the instrument at dark and at multiple (at least 2) illuminated
levels between dark and Lhigh at least twice with data acquired at least
16 days apart.

4.2.10 The Contractor shall characterize the bias stability for all
imaging and dark reference detectors over a 40-minute period at least
twice, with data acquired a minimum of 16 days apart.

4.2.11 The Contractor shall characterize the 1/f noise parameters for
all imaging and dark reference detectors over a 40-minute period at
least twice, with data acquired a minimum of 16 days apart.

4.2.12 The Contractor shall characterize the predictability of the
imaging detectors biases from the dark reference detectors over a
40-minute period at least twice, with data acquired a minimum of 16 days
apart.

4.2.13 The Contractor shall characterize the performance of the bias
determination algorithm using on-orbit data for acquisition intervals of
up to 40 minutes.

4.2.14 The Contractor shall support imaging the full lunar disk at a
phase angle of 5° to 9° or -9° to -5°.

4.2.14.a At least 2 SCA\'s shall image the moon at least twice during
commissioning at the same phase angle, one lunar cycle apart.

4.2.14.b All SCA\'s shall image the moon at least once within this same
4° increment of phase angles.

4.2.15 If Landsat-7 is still operational, the Contractor shall support
collection of data of common ground targets within 20 minutes of the
Landsat-7 ETM+ acquisitions.

4.2.16 The Contractor shall update the detector operability status list
with newly identified dead, inoperable, and out-of-spec detectors for
each band.

Rationale: To the extent possible, the pre-launch radiometric tests need
to be repeated on orbit to assess whether anything has changed since
pre-launch testing and to characterize the system under its actual
operating conditions. Noise levels, particularly coherent noise, may
change with the change in grounding of the spacecraft. The radiometric
response, both absolute and relative, may change during launch.
Calibration techniques not readily available prior to launch, e.g.,
solar and lunar calibration, need to be conducted and their
repeatability assessed.

## Geometric Test Requirements

4.3.1 The Contractor shall characterize the instrument to Attitude
Determination System Reference alignment.

Rationale: The instrument alignment is expected to change due to launch
shift and zero-G release, so an on-orbit update is required to achieve
the required on-orbit geodetic accuracy performance. The accuracy is
here left as a component of the overall geodetic error budget to be
determined by the contractor. Internal error budgets call for an
alignment calibration accuracy of 45 microradians (3-sigma).

4.3.2 The Contractor shall characterize the detector arrays lines of
sight for bands 1-8 relative to the panchromatic band using ground
targets at least twice, using data acquired at least 16 days apart.

Rationale: The prelaunch line-of-sight calibration could change on-orbit
due to the reaction of the optical system to launch and/or zero-G
release. Any such changes would be expected to be slowly varying (not
detector-by-detector) and subject to calibration using SCA-level
on-orbit adjustments (as was done for the ALI). Once on-orbit, these LOS
measurements are necessarily relative, so the calibration operation
measures the offsets of bands 1-8 relative to the panchromatic band. The
accuracy is here left as a component of the overall band registration
error budget to be determined by the contractor. Internal error budgets
call for a band alignment calibration accuracy of 6 microradians
(3-sigma).

4.3.3 The Contractor shall characterize the alignment of band 9 (cirrus)
relative to the other reflective bands using the lunar scan data
described in 4.2.

Rationale: The band alignment procedure used for bands 1-8 (see previous
requirement) are unlikely to be effective for the cirrus band which will
not provide clear images of ground targets. Instead, this procedure must
be carried out using the lunar scan data. The accuracy is here left as a
component of the overall band registration error budget to be determined
by the contractor. Internal error budgets call for a band alignment
calibration accuracy of 6 microradians (3-sigma).

4.3.4 The Contractor shall characterize the relative locations of the
individual SCA\'s on the focal plane at least twice, using data acquired
at least 16 days apart.

Rationale: The prelaunch line-of-sight calibration could change on-orbit
due to the reaction of the optical system to launch and/or zero-G
release. Any such changes would be expected to be slowly varying (not
detector-by-detector) and subject to calibration using SCA-level
on-orbit adjustments (as was done for the ALI). Once on-orbit, these LOS
measurements are necessarily relative, so the calibration operation
measures the offsets of each SCA relative to the mean of the SCA\'s. The
accuracy is here left as a component of the overall image-to-image
registration error budget to be determined by the contractor. Internal
error budgets call for an SCA alignment calibration accuracy of 6
microradians (3-sigma).