Attachment F-6 418-XO-PPXUIID-0141_V_0_2_DRAFT.pdf

DRAFT

418-XO-PPXUIID-0141, GeoXO Partner Payload

(PPX) Unique Instrument Interface Document

(UIID)

DRAFT

Version: 0.2 Printed by: hlhedger Printed on: Monday, July 10, 2023

No filter applied.

No sort applied.

Generated from DOORS 9.7.2.4

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Contents

1 1Scope

1.1 1Document Overview

1.2 1Requirements Terminology

1.3 2Order of Precedence

2 3Documents

2.1 3Applicable Documents

2.2 3Reference Documents

3 4Allocations

3.1 4Command and Data Handling

3.1.1 4Instrument-to-Spacecraft Science Rate

3.1.2 4Telemetry Data Rate

3.1.3 4Application Process Identifiers

3.1.4 4GeoXO Reliable Data Delivery Protocol Packet Rate

3.2 4Power

3.2.1 4Average Operational Power

3.2.2 4Maximum Operational Power

3.2.3 4Average Survival Power

3.2.4 4Maximum Survival Power

3.3 5Mechanical

3.3.1 5Mass Properties

3.3.2 5Cabling Between Units

3.3.3 5Volume

3.3.4 5Optical Port Field-of-View (FOV)

3.3.5 6Radiator Field of View

3.3.6 6Mounting

3.4 6Mechanical Disturbances

3.4.1 6Integrated Angular Momentum

3.4.2 6Angular Momentum Limits

3.4.3 7Instrument Translation Acceleration Limits

3.4.4 8Predicted Interface Force and Torque (PIFT) Responses

3.4.5 9Spacecraft Mounting Stiffness

3.4.6 9External Sourced Translation Acceleration Limits

3.4.7 11Instrument Torque Limit

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

Contents ii

3.5 11Thermal

4 12Constraints

5 13GIRD Deviations

5.1 13On-Orbit Concept

6 14Acronyms

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

Contents iii

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

Page 1 of 14 Printed Monday, July 10, 2023

ID

PPXUIID1

PPXUIID2

PPXUIID3

PPXUIID4

PPXUIID5

PPXUIID6

PPXUIID7

PPXUIID8

PPXUIID9

PPXUIID10

PPXUIID11

PPXUIID12

PPXUIID13

PPXUIID14

PPXUIID15

PPXUIID16

Object Number

1.0-1

1.0-2

1.0-3

1.0-4

1.0-5

1.0-6

1.1

1.1.0-1

1.2

1.2.0-1

1.2.0-2

1.2.0-3

1.2.0-4

1.2.0-5

1.2.0-6

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

1 Scope

The purpose of this Unique Instrument Interface Document (UIID) is two-fold. The first is to allocate GeoXO series spacecraft resources to the Partner Payload Instrument (PPX). The second is to serve as a core building block on which the PPX-spacecraft interface can be designed. This document levies requirements on both the spacecraft and instrument.

This UIID will govern the development of an Interface Control Document (ICD), which will be a joint activity of the PPX and spacecraft contractors.

The PPX ICD establishes the details of the electrical, communications, mechanical, thermal, integration and test, and command and data handling (C&DH) interfaces between the PPX instrument and the GeoXO spacecraft.

The PPX is supplied by an external partner. This section of the UIID will describe the data collected by the instrument. The instrument collects data on a three-axis body-stabilized satellite in geostationary orbit.

The instrument requires primary power, and command input data from the spacecraft.

Instrument output data to the spacecraft contains instrument information, instrument telemetry and ancillary data.

The sensor unit contains the sensing subystems necessary for the PPX objectives.

Depending on the objectives these could include an optical subsystem, scanner, detectors and their cooling/heating systems and directly related electronics. The (optional) electronics unit contains the power supply module, command, control, and data processing circuitry.

1.1 Document Overview

Together, the General Interface Requirements Document (GIRD) and the PPX UIID establish the PPX-spacecraft interface requirements. The GIRD applies to all GeoXO instruments while the PPX UIID is specific to the PPX. Section 1 explains the use of this document. Section 2 lists reference documents. Section 3 allocates spacecraft resources, such as mass, power, and data rate, to the PPX instrument. Section 4 contains government-accepted operation constraints. Section 5 contains government-accepted deviations from the GIRD. Section 6 contain a list of acronyms used within this document.

1.2 Requirements Terminology

The following requirements terminology is used throughout this document:

The use of “shall” designates a requirement that must be met.

The term “should” designates a desired level of performance the government would like the contractor to strive towards achieving and is synonymous with the term “goal.”

The use of “will” designates a statement of fact or intention of the government.

The use of “may” designates that permission has been granted by the government.

The term “(TBD)” means, “to be determined” and is used when no value is available with subsequent study needed to obtain it.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID17

PPXUIID18

PPXUIID19

PPXUIID20

PPXUIID21

PPXUIID22

PPXUIID23

PPXUIID24

PPXUIID25

Object Number

1.2.0-7

1.2.0-8

1.2.0-9

1.2.0-10

1.2.0-11

1.2.0-12

1.2.0-13

1.3

1.3.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

TBD requirement proposals are to be made in coordination with the government and may involve other contractors.

The contractor should request approval from the government before proceeding with its proposed TBD requirement or value.

The term “(TBR)” means “to be refined/reviewed” for a value that is subject to review for appropriateness and is subject to revision. The contractor is liable for compliance with the information marked “TBR” as if the “TBR” notation did not exist.

TBR requirement proposals will be made in coordination with the government and may involve other contractors.

The contractor should request approval from the government before proceeding with its proposed TBR requirement or value.

The term “TBS” means, “to be supplied.” The government will supply TBS requirements. The government will provide a date or milestone at which each TBS requirement will be supplied.

The orbit reference frame (ORF) is defined in the GIRD.

1.3 Order of Precedence

The order of precedence of interface requirements documents is the UIID at the highest level, followed in order by the GIRD, ICD, and Instrument Description Document (IDD).

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID26

PPXUIID27

PPXUIID28

PPXUIID29

PPXUIID30

Object Number

2.1

2.1.0-1

2.2

2.2.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

2 Documents

2.1 Applicable Documents

The following documents of the exact issue shown form a part of this UIID to the extent specified herein. In the event of conflict between the documents referenced and the contents of this UIID the latter shall be the superseding requirement.

1. 418-XO-GIRD-0041- General Interface Requirements Document (GIRD)

2.2 Reference Documents

The following documents provide reference material for part of this document.

1. CCSDS 133.0-B-2 - Space Packet Protocol, Blue Book, Issue 2, June 2020

2. CCSDS 301.0-B-4 - Time Code Formats. Blue Book. Issue 4, November 2010

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID31

PPXUIID32

PPXUIID33

PPXUIID34

PPXUIID35

PPXUIID36

PPXUIID37

PPXUIID38

PPXUIID39

PPXUIID40

PPXUIID41

PPXUIID42

PPXUIID43

PPXUIID44

PPXUIID45

PPXUIID46

PPXUIID47

PPXUIID48

PPXUIID49

PPXUIID50

Object Number

3.0-1

3.1

3.1.1

3.1.1.0-1

3.1.2

3.1.2.0-1

3.1.3

3.1.3.0-1

3.1.4

3.1.4.0-1

3.2

3.2.1

3.2.1.0-1

3.2.2

3.2.2.0-1

3.2.3

3.2.3.0-1

3.2.4

3.2.4.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

3 Allocations

The GeoXO spacecraft provides communications, power, and a platform for the PPX instrument. The following paragraphs allocate these resources to PPX.

3.1 Command and Data Handling

3.1.1 Instrument-to-Spacecraft Science Rate

The instrument science and engineering data rate, including all overhead associated with Consultative Committee for Space Data Systems (CCSDS) packetization by the instrument, at the spacecraft interface shall not exceed 75 million bits per second when averaged over any 5 second period.

3.1.2 Telemetry Data Rate

Housekeeping telemetry data rate, including all overhead associated with CCSDS packetization by the instrument, at the spacecraft interface shall not exceed 1024 bits per second when averaged over any 5 second period.

3.1.3 Application Process Identifiers

The PPX shall use no more than 255 consecutive Application Process Identifiers (APIDs) for science, telemetry, and command packets.

3.1.4 GeoXO Reliable Data Delivery Protocol Packet Rate

The PPX shall transmit to the spacecraft no more than 400 GOES Reliable Data Delivery Protocol (GRDDP) Packets per second.

3.2 Power

3.2.1 Average Operational Power

The PPX shall draw operational average power, inclusive of heaters, of no more than 170 Watts from up to four total feeds including primary and redundant. Operational average power is the total power into an instrument averaged over any 5 minute period.

3.2.2 Maximum Operational Power

The PPX shall draw operational maximum power of no more than 275 Watts from up to four total feeds. Operational maximum power is the total power into an instrument averaged over any 20ms period.

3.2.3 Average Survival Power

The PPX shall draw average survival power of no more than 110 Watts. Average survival power is the total power into an instrument averaged over any 72 minute period.

3.2.4 Maximum Survival Power

The PPX shall draw maximum survival power of no more than 165 Watts. Survival maximum power is the total power into an instrument averaged over any 20ms period.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID51

PPXUIID52

PPXUIID53

PPXUIID54

PPXUIID55

PPXUIID56

PPXUIID57

PPXUIID58

PPXUIID59

PPXUIID60

PPXUIID61

PPXUIID62

Object Number

3.3

3.3.0-1

3.3.1

3.3.1.0-1

3.3.2

3.3.2.0-1

3.3.2.0-2

3.3.3

3.3.3.0-1

3.3.3.0-2

3.3.4

3.3.4.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

3.3 Mechanical

The requirements in this section apply to the structural and mechanical components of the instrument flight units (sensor unit, electronics unit and, if applicable, auxiliary electronics unit).

3.3.1 Mass Properties

The PPX, including all units and cabling between units, shall have mass less than 150 kilograms.

3.3.2 Cabling Between Units

If there are external units mounted directly to the spacecraft, the PPX shall accommodate any cable length between the units up to but not exceeding the lengths of 4 meters.

Cables between PPX units shall be the responsibility of the PPX provider.

3.3.3 Volume

The PPX sensor shall be mounted on the Earth Pointing Platform (EPP) or Nadir Deck of the spacecraft.

The PPX Sensor Unit stowed and operational (deployed) configurations, including mounts, thermal blankets and connectors, shall have dimensions that do not exceed the limits provided below.

Depth (Z direction, Nadir or interface plane): 1500 millimeters Width (X direction, parallel to orbit): 1290 millimeters Height (Y direction, normal to orbit): 1230 millimeters

Rationale: The narrow dimension allows for other instruments to share the EPP with the

PPX

3.3.4 Optical Port Field-of-View (FOV)

The spacecraft shall provide the sensor unit’s optical port a clear field-of-view within 65 degrees of nadir as shown in the following figure. A clear FOV is an instrument FOV free of any obstructions.

Optical Port Field-of-View

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID63

PPXUIID64

PPXUIID65

PPXUIID66

PPXUIID67

PPXUIID68

PPXUIID69

PPXUIID70

PPXUIID71

PPXUIID72

PPXUIID73

PPXUIID74

PPXUIID75

PPXUIID76

PPXUIID77

Object Number

3.3.5

3.3.5.0-1

3.3.5.0-2

3.3.5.0-3

3.3.6

3.3.6.0-1

3.3.6.0-2

3.3.6.0-3

3.4

3.4.0-1

3.4.1

3.4.1.0-1

3.4.1.0-2

3.4.2

3.4.2.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

3.3.5 Radiator Field of View

The instrument shall dedicate the +Y face of the instrument for a radiator surface with the axis in the Body Reference Frame (BRF) as defined in the GIRD.

The spacecraft shall provide the sensor unit’s radiator face a 2π steradian field-of view to space excepting a field-of-view blockage with less than 40 W/m^2 infrared back loading.

The instrument should consider meeting its performance requirements with an incident 40 W/m^2 infrared back loading on the radiator surface.

3.3.6 Mounting

The spacecraft shall provide the instrument sensor unit a nadir-facing mounting surface.

The sensor unit mechanical interface shall lie within the anti-nadir plane of the sensor unit envelope.

The instrument sensor unit shall use kinematic mounts for its mechanical interface to the spacecraft.

3.4 Mechanical Disturbances

These requirements apply while the instrument is in orbit and operating.

3.4.1 Integrated Angular Momentum

The absolute value of the high pass filtered angular momentum integrated with respect to time shall not exceed the values listed in Filtered Integrated Angular Momentum Limits table. The filter is a second order Butterworth filter with a -3 dB cutoff frequency at 0.01 Hz.

ACX Integrated Angular Momentum Limits

Axis Limit

(N-m-s2) roll 0.5 pitch 0.3 yaw 0.5

The satellite center of mass will be within 2 meters of the centroid of the sensor unit mounts.

3.4.2 Angular Momentum Limits

The absolute value of the high pass filtered angular momentum produced by the sensor unit referenced at the satellite center of mass shall not exceed the values listed in the Angular Momentum Limits table. The high pass filter is a second order Butterworth filter with a -3 dB cutoff frequency at 0.01 Hz.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID77

PPXUIID78

PPXUIID79

PPXUIID80

Object Number

3.4.2.0-1

3.4.2.0-2

3.4.3

3.4.3.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

ACX Angular Momentum Limits

Axis Limit

(N-m-s) roll 0.1 pitch 0.05 yaw 0.1

The absolute value of the band pass filtered instrument angular momentum in each orthogonal axis shall not exceed the values listed in the One-Sixth Octave Band Filtered Angular Momentum Limits table. The bandpass filters for this requirement are defined as a series of eighth-order Butterworth bandpass filters with -3 dB bandwidth of one sixth of an octave. The first filter in the series has its center frequency at 0.015625 Hz, and the center frequencies for the series are spaced at one-twelfth octave up to 10 Hz.

The Bandpass‐Filtered Angular Momentum Limits apply to filters with center frequency greater than f1 and less than or equal to f2.

3.4.3 Instrument Translation Acceleration Limits

The translational accelerations induced by the instrument sensor at each mount shall not exceed the limits specified in the Instrument-to-Spacecraft Linear Acceleration Limits table below. The accelerations are those induced by operation of the sensor unit while mounted to a flexible interface. The limits apply to each orthogonal axis after the acceleration is filtered using an eighth-order band pass Butterworth filter with -3dB frequencies at f1 and f2. Note that the filter has a fourth-order roll-off on both sides of the response.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID80

PPXUIID81

PPXUIID82

PPXUIID83

PPXUIID84

PPXUIID85

PPXUIID86

Object Number

3.4.3.0-1

3.4.3.0-2

3.4.4

3.4.4.0-1

3.4.4.0-2

3.4.4.0-3

3.4.4.0-4

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

The translational accelerations induced by the instrument sensor unit at each mount shall produce an absolute peak acceleration Shock Response Spectra (SRS) less than the limits set in the Instrument to Spacecraft Linear Acceleration SRS/Q Limits Table.

The limits apply to each orthogonal axis when using a quality factor, Q, of 50, and normalizing the SRS dividing by Q. The SRS is computed after the translational accelerations are filtered with a fourth-order high pass Butterworth filter with a -3dB cut off at 1.0Hz. For SRS resonant frequencies from 10.0Hz to 512.0 Hz, the limits are calculated using logarithmic interpolation for both frequency and acceleration terms in the Instrument to Spacecraft Acceleration SRS/Q Limits Table.

3.4.4 Predicted Interface Force and Torque (PIFT) Responses

The PPX shall send predicted forces, torques and future times to the spacecraft in a CCSDS source packet per the Command and Data Handling section of the GIRD.

The PPX shall send to the spacecraft predicted forces and torques resulting from normal instrument operations including any calibration operations.

The PPX shall send to the spacecraft predicted forces and torques computed in the instrument coordinate system.

The PPX shall send to the spacecraft forces and torques predicted for a uniformly spaced series of future times.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID87

PPXUIID88

PPXUIID89

PPXUIID90

PPXUIID91

PPXUIID92

PPXUIID93

PPXUIID94

PPXUIID95

PPXUIID96

PPXUIID97

PPXUIID98

Object Number

3.4.4.0-5

3.4.4.0-6

3.4.4.0-7

3.4.4.0-8

3.4.4.0-9

3.4.4.0-10

3.4.4.0-11

3.4.5

3.4.5.0-1

3.4.5.0-2

3.4.6

3.4.6.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

The PPX shall increment the future time values for predicted forces and torques sent to the spacecraft by 50 ms.

The PPX shall send to the spacecraft predicted forces and torques 250 ms prior to the predicted time.

The PPX shall send to the spacecraft predicted forces and torques with the future time data using the P-field format in the GIRD.

The PPX shall send to the spacecraft predicted force data with a minimum resolution of

0.001 N.

The PPX shall send to the spacecraft predicted torque data with a minimum resolution of 0.001 N-m.

The PPX shall send to the spacecraft predicted force data with an accuracy of +/- 0.03 N.

The PPX shall send to the spacecraft predicted torque data with an accuracy of +/-

0.03 N-m.

3.4.5 Spacecraft Mounting Stiffness

The instrument should consider meeting its performance requirements while the sensor unit is mounted to a rigid plate supported at three flexible points with a first mode of 20 +/- 5 Hz and with the 6th mode less than 50 Hz.

The instrument should consider meeting its performance requirements when the diagonal modal viscous damping factors associated with the three flexible points are 0.1%.

3.4.6 External Sourced Translation Acceleration Limits

The translational accelerations responses from sources external to the instrument sensor unit at the spacecraft side of each instrument sensor unit mount shall not exceed the limits specified in the Externally-Sourced Translational Acceleration Bandpass Limits Table. The limits apply to each orthogonal axis after the acceleration is filtered using an eighth-order band pass Butterworth filter with -3dB frequencies at f1 and f2.

Note that the filter has a fourth-order roll-off on both sides of the response.

Externally-Sourced Translational Acceleration Bandpass Limits Table

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID104

PPXUIID105

Object Number

4.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

4 Constraints

In order to ensure proper instrument performance or to prevent possible instrument damage, the following Government-approved constraints are imposed by the instrument developer on spacecraft integration and test activities, including launch, activation and operations.

No constraints have been identified at this time.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID106

PPXUIID107

PPXUIID108

PPXUIID109

Object Number

5.0-1

5.1

5.1.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

5 GIRD Deviations

This section identifies GIRD requirements that the Government has deviated from for this instrument. Where appropriate, corresponding GIRD paragraph titles and numbers are identified in parentheses.

5.1 On-Orbit Concept

GIRD67 shall not be applicable to PPX. GIRD67 serves to notify the PPX that spacecraft yaw flips are a possibility and that performance objectives remain with the authority of the PPX supplier.

Project: Howard Hedger Module: PPXUIID Baseline Version: 0.2

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ID

PPXUIID110

PPXUIID111

Object Number

6.0-1

418-XO-PPXUIID-0141, RM Version, GeoXO Partner Payload (PPX) Unique Instrument Interface Document (UIID)

6 Acronyms

APID Application Process Identifier BRF Body Reference Frame C&DH Command and Data Handling CCSDS Consultative Committee for Space Data Systems EPP Earth Pointing Platform FOV Field of View GeoXO Geostationary Extended Observations GIRD General Interface Requirements Document GOES Geostationary Operational Environmental Satellite GRDDP GOES Reliable Data Delivery Protocol Hz Hertz ICD Interface Control Document IDD Instrument Description Document NASA National Aeronautics and Space Administration ORF Orbit Reference Frame PIFT Predicted Interface Force and Torque PPX Partner Payload Instrument for GeoXO SRS Shock Response Spectra TBD to be determined TBR to be resolved TBS to be specified UIID Unique Instrument Interface Document