Attachment D UIID.pdf

Effective Date: April 20, 2021 418-XO-GXSUIID-0030 Expiration Date: Five years from date of last signature Baseline Version 1.0 Responsible Organization: GeoXO Flight Project/Code 418

Check the GeoXO portal at https://goesportal.ndc.nasa.gov to verify correct version prior to use.

Geostationary Extended Observations (GeoXO) Sounder (GXS)

Unique Instrument Interface Document (UIID) Signature page

Prepared by:

Electronically approved 04/23/2021

Nicolaas du Toit Date GeoXO Flight Project, Chief Staff Engineer NASA GSFC, Code 418

Reviewed by:

Electronically approved 04/12/2021

Alexander Krimchansky Date GeoXO Flight Project, Sys. Eng. Mgr.

NASA GSFC, Code 599

Approved by:

Electronically approved 04/20/2021

Jason H. Hair Date GeoXO Flight Project, Project Manager NASA GSFC, Code 418

/GeoXO Flight Project GXS Sounder

GXSUIID

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

Version: 1.0 Printed by: rkhoover Printed on: Thursday, April 22, 2021

No filter applied.

No sort applied.

Generated from DOORS 9.6.1.11

Contents

1 1Allocations

1.1 1Command and Data Handling

1.1.1 1Instrument-to-Spacecraft Science Rate

1.1.2 1Telemetry Data Rate

1.1.3 1Application Process Identifiers

1.1.4 1GEO-XO Reliable Data Delivery Protocol Packet Rate

1.2 1Power

1.2.1 1Average Operational Power

1.2.2 1Maximum Operational Power

1.2.3 1Average Survival Power

1.2.4 1Maximum Survival Power

1.3 2Mechanical

1.3.1 2Mass Properties

1.3.2 2Cabling Between Units

1.3.3 2Volume

1.3.4 2Optical Port Field-of-View

1.3.5 2Radiator Field-of-View

1.3.6 3Mounting

1.4 3Instrument-to-Spacecraft Disturbances

1.4.1 3Integrated Angular Momentum

1.4.2 3Angular Momentum Limits

1.4.3 4Instrument Translation Acceleration Limits

1.4.4 6Predicted Interface Force and Torque (PIFT) Responses

1.4.5 7Spacecraft Mounting Stiffness

1.4.6 7External Sourced Translation Acceleration Limits

1.5 9Thermal

1.6 9Instrument Purge Requirements

2 10Constraints

3 11GIRD Deviations

4 12Design Verification Requirements

4.1 12Radiated Emissions, Electric Field (RE 102)

4.2 12Radiated Emissions in DCS Receiver Bands

Project: GeoXO Flight Project GXS Sounder Module: GXSUIID Baseline Version: 1.0

Contents ii

5 14Acronyms

Contents iii

Page 1 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID26

GXSUIID27

GXSUIID28

GXSUIID29

GXSUIID30

GXSUIID31

GXSUIID32

GXSUIID33

GXSUIID34

GXSUIID35

GXSUIID36

GXSUIID37

GXSUIID38

GXSUIID39

GXSUIID40

GXSUIID41

GXSUIID42

GXSUIID43

GXSUIID44

Object Number

1.0-1

1.1

1.1.1

1.1.1.0-1

1.1.2

1.1.2.0-1

1.1.3

1.1.3.0-1

1.1.4

1.1.4.0-1

1.2

1.2.1

1.2.1.0-1

1.2.2

1.2.2.0-1

1.2.3

1.2.3.0-1

1.2.4

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

1 Allocations The GEO-XO provides communications, power and a platform for the Sounder instrument. The following paragraphs allocate these resources to Sounder.

1.1 Command and Data Handling

1.1.1 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 150 million (106) bits per second (TBR) when averaged over any 5 second period.

1.1.2 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.

1.1.3 Application Process Identifiers

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

1.1.4 GEO-XO Reliable Data Delivery Protocol Packet Rate

The Sounder shall transmit to the spacecraft no more than 300 GRDDP Packets per second.

1.2 Power

1.2.1 Average Operational Power

The Sounder shall draw operational average power, inclusive of heaters, of no more than 615 Watts from up to six (TBR) total feeds including primary and redundant feeds.

Operational average power is the total power into an instrument averaged over any 5 minute period.

1.2.2 Maximum Operational Power

The Sounder shall draw operational maximum power of no more than 845 Watts.

Operational maximum power is the total power into an instrument averaged over any 20ms period.

1.2.3 Average Survival Power

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

1.2.4 Maximum Survival Power

Page 3 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID114

GXSUIID59

GXSUIID60

GXSUIID61

GXSUIID62

GXSUIID63

GXSUIID64

GXSUIID65

GXSUIID66

GXSUIID67

GXSUIID68

GXSUIID69

Object Number

1.3.5.0-2

1.3.6

1.3.6.0-1

1.3.6.0-2

1.3.6.0-3

1.4

1.4.0-1

1.4.1

1.4.1.0-1

1.4.2

1.4.2.0-1

1.4.2.0-2

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

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 General Interface Requirements Document (GIRD, 418-XO-GXIGIRD-0025).

1.3.6 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.

1.4 Instrument-to-Spacecraft Disturbances

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

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

Filtered Integrated Angular Momentum Limits

Axis

Limit (N-m-s2)

Roll 0.462 Pitch 0.325 Yaw 0.484

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

Angular Momentum Limits

Axis

Limit (N-m-s)

Roll 0.09 Pitch 0.06 Yaw 0.10

The absolute value of the band pass filtered instrument angular momentum shall not exceed the values listed in the One-Sixth Octave Band Filtered Angular Momentum Limits table. The table limits apply for each orthogonal axis. The band pass filters for

Page 4 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID69

GXSUIID70

GXSUIID71

Object Number

1.4.2.0-2

1.4.3

1.4.3.0-1

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID) the angular momentum are defined as a series of Butterworth band pass filters with -3 dB cutoff frequencies separated by one sixth of an octave, with a fourth order roll off and with a center frequency one-twelfth octave between the cutoff frequencies. The Filtered Angular Momentum Limits apply when the center frequency for the filter is greater than f1 and less than or equal to f2. The series of filters starts with a center frequency at 0.015625 Hz, and the center frequency is stepped by one-twelfth octave increments.

One-Sixth Octave Band Filtered Instrument Angular Momentum Limits f1 (Hz) f2 (Hz)

Limit (N-m-s)

0.01 0.25 0.050

0.25 1.0 0.020

1.0 10.0 0.015

1.4.3 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 at least a fourth-order band pass Butterworth filter with -3dB frequencies at f1 and f2 and with a fourth order roll off. Note that the filter has a fourth-order roll-off on both sides of the response.

Page 7 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID78

GXSUIID79

GXSUIID80

GXSUIID81

GXSUIID82

GXSUIID83

GXSUIID84

GXSUIID85

GXSUIID86

GXSUIID87

GXSUIID88

Object Number

1.4.4.0-5

1.4.4.0-6

1.4.4.0-7

1.4.4.0-8

1.4.4.0-9

1.4.4.0-10

1.4.4.0-11

1.4.5

1.4.5.0-1

1.4.6

1.4.6.0-1

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

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

The Sounder shall send to the spacecraft predicted forces and torques at least 250 ms prior to the predicted time.

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

The Sounder shall send to the spacecraft predicted force data with a minimum resolution of 0.001 N.

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

The Sounder shall send to the spacecraft predicted force data with an accuracy of +/-

0.03 N.

The Sounder shall send to the spacecraft predicted torque data with an accuracy of +/- 0.03 N-m.

1.4.5 Spacecraft Mounting Stiffness

Reserve

1.4.6 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 External Source Translational Acceleration Limits for Spacecraft to Instrument Table below. The limits apply to each orthogonal axis after the acceleration is filtered using at least a fourth-order band pass Butterworth filter with -3dB frequencies at f1 and f2 and with a fourth order roll off. Note that the filter has a fourth-order roll-off on both sides of the response.

Page 10 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID95

GXSUIID96

GXSUIID97

Object Number

2.0-1

2.0-2

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

2 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.

Page 11 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID98

GXSUIID99

Object Number

3.0-1

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

3 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.

Page 12 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID100

GXSUIID101

GXSUIID102

GXSUIID103

GXSUIID104

GXSUIID105

GXSUIID106

GXSUIID107

GXSUIID108

GXSUIID109

GXSUIID110

GXSUIID111

Object Number

4.0-1

4.1

4.1.0-1

4.1.0-2

4.2

4.2.0-1

4.2.0-2

4.2.0-3

4.2.0-4

4.2.0-5

4.2.0-6

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

4 Design Verification Requirements The following requirements represents only a portion of the overall system verification ( i.e., contractor derived requirements are not described) that must be integrated into the total system program which verifies that the system will meet the mission requirements. A system performance verification program documenting the overall verification plan, implementation, and results is required which will provide traceability from mission specification requirements to launch and initial on-orbit capability. This will also provide the baseline for tracking on-orbit performance versus pre-launch capability.

4.1 Radiated Emissions, Electric Field (RE 102)

Radiated narrow band electric field levels generated by the instrument shall not exceed the levels specified in the Sensor Unit and Electronics Unit Notches Table below except for the DCS Receiver bands specified in GXSUIID99.

Radiated Emissions Notch Table:

Frequency Range (MHz) Limits (dBuV/meter)

1560‐1595 (TBR) 10 (TBR)

1660‐1670 (TBR) 45 (TBR)

2022‐2038 (TBR) 11 (TBR)

7210‐7223 (TBR) 39 (TBR)

The test procedure used for this test shall be in accordance with MIL-STD-461, RE102.

4.2 Radiated Emissions in DCS Receiver Bands

Radiated emission measurements in the DCS receiver bands shall be made in accordance with MIL-STD-461, RE102 with the EMI meter replaced by a spectrum analyzer preceded by a low noise pre-amplifier such that the test system noise figure is equal to or less than 3 dB, e.g., an HP-8566 spectrum analyzer preceded by a MITEQ AU-2A-0550 pre-amplifier or equivalent.

The spectrum analyzer levels and the difference in the levels shall be recorded for both white noise and spurious signals before and after power is applied to the instrument clock and control signals.

The test antenna shall be tuned to the center of the frequency band specified in DCS EMC Test Parameters Table (GXSUIID99).

Prior to making the actual measurements, the test antenna shall be de-mated and the cable terminated with 50 ohms for self calibration.

The noise floor of the measuring equipment shall be verified to be lower than the specified maximum signal level in a 100 Hz resolution bandwidth.

Radiated emission levels generated by the instrument shall not exceed the maximum signal levels specified in the DCS EMC Test Parameters Table below.

Page 13 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID111

Object Number

4.2.0-6

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

DCS EMC Test Parameters Table

Unit Name DCS Band (MHz)

Measurement Bandwidth

(Hz)

Dwell Time

(Seconds)

Minimum Measurement Time Analog Measurement

Receiver (sec/kHz)

Max.

Filed

Intensity (dBuV/m)

Instrument Electronics

Box

401.700

402.400

100 .015 0.15 10 (each box)

Page 14 of 14 Printed Thursday, April 22, 2021

ID

GXSUIID112

GXSUIID113

Object Number

5.0-1

418-XO-GXSUIID-0030, RM Version, GeoXO hyperspectral radiometric Sounder (GXS) Unique Instrument Interface Document (UIID)

5 Acronyms APID Application Process Identifier C&DH Command and Data Handling CCSDS Consultative Committee for Space Data Systems GIRD General Interface Requirements Document GOES Geostationary Operational Environmental Satellite GSFC Goddard Space Flight Center GXS GEO-XO Sounder Hz Hertz ICD Interface Control Document IDD Instrument Description Document kg kilogram m meter Mbps million bits per second mg milli-g’s (where g is gravitational acceleration at Earth surface) NASA National Aeronautics and Space Administration PORD Performance and Operational Requirements Document SRS Shock Response Spectra TBD to be determined TBR to be resolved TBS to be specified UIID Unique Instrument Interface Document

Effective Date: April 20, 2021 418-XO-GXSUIID-0030 Expiration Date: Five years from date of last signature Baseline Version 1.0 Responsible Organization: GeoXO Flight Project/Code 418

Check the GeoXO portal at https://goesportal.ndc.nasa.gov to verify correct version prior to use.

Document Change Record (DCR)

CCR GeoXO#:X00012 Rev: Title: 418-XO-GXSUIID-0030: GeoXO Sounder UIID baseline Contract # N/A GOES S/C: GeoXO Effectivity: Instruments CCB Status: Approved Doc #: 418-XO-GXSUIID-0030 CCB Date: 04/20/2021 Doc Version: 1.0 Contract Mod#: N/A DOORs Version: 1.0 Doc Change Date: April 20, 2021 DOORs ID #: 1.0