ATTACHMENT C OCXGIRD Ins.pdf

NOT AN OFFICIAL Configuration Management Version Rev 1.2

418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRDl 1 1 Interface Requirements

GIRD2 1.1 1.1 Requirements Terminology

GIRD3 1.1.0-1 The term "shall" designates a requirement that must be achieved and is synonymous with the term

"threshold. 11

GIRD4 1.1.0-2 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."

GIRDS 1.1.0-3 All other terms, including "will", only designate statements of fact or intentions of the government and are not to be interpreted as contractor requirements.

GIRDS 1.1.0-4 An instrument may comprise more than one physical assembly, or unit. "Sensor unit" refers to the unit that contains the optics. "Instrument unit" means the sensor unit, electronics box (if applicable), or other units of the instrument.

GIRD7 2 2 Documents

GIRD8 2.1 2.1 Applicable Documents

GIRD9 2.1.0-1 MIL-STD-461C- Electromagnetic Emission and Susceptibility Requirements for the Control of

Electromagnetic Interference, 4 August 1986 {CCR-X000108)

GIRD143 2.1.0-2 MIL-STD-461G - Requirements for the Control of Electromagnetic Interference Characteristics of

Subsystems and Equipment, 11 December 2015 (CCR-X000108)

GIRDl0 2.1.0-3 ECSS-E-ST-50-12C Rev. 1- European Cooperation for Space Standardization (ECSS), SpaceWire - Links, nodes, routers and networks, 15 May 2019 {CCR-X000108)

GIRDll 2.1.0-4 ISO 14644-1:2015 Cleanrooms and associated controlled environments - Part 1: Classification of air cleanliness by particle concentration, December 15, 2015. {CCR-X000108)

GIRD12 2.1.0-5 CCSDS 133.0-8-2 Space Packet Protocol, Blue Book, Issue 2, June 2020 {CCR-X000108)

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD13 2.1.0-6 IEEE/ASTM Sl-10 - American National Standard for Metric Practice, 2016 {CCR-X000108)

GIRD14 2.1.0-7 417-R-RPT-0027 - The Radiation Environment for Electronic Devices on GOES-R Series Satellites, August

14,2006

GIRD16 2.1.0-8 CCSDS 301.0-8-4 - Time Code Formats. Blue Book. Issue 3-4, November 2010 {CCR-X000108)

GIRD17 2.1.0-9 NASA/TM-2001-211221 - Guideline for the Selection of Near-Earth Thermal Environment Parameters for

Spacecraft Design, October 2001

GIRD18 2.1.0-10 417-R-RPT-0050 - GOES-R Reliable Data Delivery Protocol Version 2.1 January 16, 2008

GIRD19 2.1.0-11 ISO/DIS 14644-3:2019 Cleanrooms and associated controlled environments - Part 3: Test methods, September 1, 2019 {CCR-X000108)

GIRD21 3 3 Requirements

GIRD22 3.1 3.1 General Requirements

GIRD23 3.1.1 3.1.1 On Orbit Concept

GIRD24 3.1.1.0-1 The satellite will operate in a geosynchronous orbit (Semi-major axis of approximately 42,164 Km) located at either 75° or 137° west longitude. Normal on-orbit operations entail periodic station keeping maneuvers that keep the satellite within a 0.2° inclination about the equator and within ±0.2° of the onstation longitude.

GIRD25 3.1.1.0-2

Instruments shall survive an anomaly resulting in a static instrument line-of-sight (LOS) such that the sun passes through the LOS at orbit rate.

GIRD26 3.1.1.0-3 Instruments, while operational, shall survive a spacecraft attitude anomaly resulting in the sun being at an arbitrary fixed location within the instrument field of regard (FOR) for an indefinite period of time.

GIRD27 3.1.1.0-4 The instrument will be in Survival Mode during launch.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD28 3.1.1.0-5 Instruments shall survive a spacecraft attitude anomaly resulting in the sun sweeping through the fieldof-view (FOV) of the instrument radiator from "horizon to horizon" at a rate of 6°/minute, passing through radiator normal.

GIRD29 3.1.2 3.1.2 Coordinates

GIRD30 3.1.2.0-1 The orbit reference frame (ORF) shall be defined as follows:

The ORF is orthogonal and right-handed.

The ORF origin is at the spacecraft center of mass.

The ORF +z axis points toward the center of the Earth.

The ORF +y axis points along the negative orbit normal.

The ORF +x axis completes the triad.

GIRD31 3.1.2.0-2 The body reference frame (BRF) shall be defined as follows:

The BRF is orthogonal and right-handed.

The BRF is fixed to the body of the spacecraft.

The location of the BRF origin will be specified by the spacecraft contractor.

The BRF axes are nominally parallel to the ORF axes when spacecraft attitude is in its nominal

Earth-pointing, upright yaw attitude with zero attitude error.

The roll, pitch, and yaw axes are defined to be parallel to the BRF x, y, and z axes, respectively.

GIRD32 3.1.2.0-3 If there is a yaw-flip, the spacecraft will be flown upright (+Y BRF pointed in the +Y ORF direction) during northern hemisphere winter and inverted (+Y BRF pointed in the -Y ORF direction) during northern hemisphere summer. i.e., the +Y BRF axis is generally in the same hemisphere as the Sun.

GIRD33 3.1.2.0-4 If there is no yaw-flip, the spacecraft will be flown upright all year.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD34 3.1.2.0-5 The reference coordinate system of each instrument unit shall be nominally parallel to the spacecraft

BRF coordinate system, with the exception of solar-pointing instruments.

GIRD35 3.1.3 3.1.3 Yaw Flip

GIRD37 3.1.3.0-1 Instruments shall meet all performance requirements whether or not the spacecraft performs a yaw flip.

{CCR-XOOOlOB)

GIRD38 3.2 3.2 Interface Requirements

GIRD39 3.2.0-1 All instrument-to-spacecraft interfaces shall be single fault tolerant.

GIRD40 3.2.1 3.2.1 Mechanical

GIRD41 3.2.1.0-1 The instrument contractor will provide all kinematic mounts, plus vibration isolation and thermal isolation mounting hardware.

GIRD42 3.2.1.1 3.2.1.1 Nadir Pointed Instrument Alignment

GIRD43 3.2.1.1.1 3.2.1.1.1 Placement

GIRD44 3.2.1.1.1.0-1 The placement of the instrument alignment reference frame with respect to the spacecraft IRU reference frame shall be to within 0.25 degrees per axis, including variation over all launch and on-orbit environments .

GIRD45 3.2.1.1.2 3.2.1.1.2 Initial Alignment Knowledge

GIRD46 3.2.1.1.2.0-1 The prelaunch alignment knowledge of the instrument alignment reference frame with respect to the spacecraft IRU input axes shall be 300 microradians or better per axis.

GIRD47 3.2.1.1.3 3.2.1.1.3 Alignment Rate of Change

GIRD48 3.2.1.1.3.0-1 The rate of change of the alignment of the instrument mounting frame with respect to the spacecraft IRU input axes shall not exceed 100 microradians per hour per axis. This requirement includes on-orbit environments and spacecraft structural and thermal stability.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD49 3.2.1.2 3.2.1.2 Attitude and Disturbances for Nadir Pointed Instruments

GIRD50 3.2.1.2.1 3.2.1.2.1 Attitude Error

GIRD51 3.2.1.2.1.0-1 The attitude error of the instrument mounting frame relative to the desired ORF-referenced attitude shall not exceed 360 microradians, 3-sigma, per axis. Attitude error is defined as the difference between the desired attitude and the actual, or true, attitude of the instrument mounting frame.

GIRD52 3.2.1.2.1.0-2 The instrument mounting frame attitude shall be stable to within 500 microradians, peak-to-peak, per axis, over any 60 sec window.

GIRD53 3.2.1.2.2 3.2.1.2.2 Attitude Rate Error "'- "'

GIRD54 3.2.1.2.2.0-1 For a given total spacecraft gyro signal phase delay, the instrument mounting frame attitude rate error relative to the desired ORF-referenced attitude shall not exceed ± the corresponding limit from the Total

Spacecraft Gyro Signal Phase Delay and Rate Error Trade Space Figure provided below, per axis, when the rate is filtered by a fourth order Butterworth low pass filter with a -3dB frequency of 15 Hz.

NOT AN OFFICIAL Configuration Management Version

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD59 3.2.1.2.3.0-2 Tl'anslational Acceleration Limits fol' Spacecraft to Instl'ument Table Peak Peak Peak fl f2 Limit fl fl Limit fl f2 Limit (Hz) (Hz) (mg) (Hz) (Hz) (mg) (Hz) (Hz) (mg)

0.0 512.0 18.44 26.9 30.2 0.40 114.0 128.0 2.40

0.9 10.1 1.50 28.5 32.0 0.40 120.8 135.6 2.40

6.3 32.0 1.00 30.2 33.9 1.40 128.0 143.7 2.40

20.2 101.6 4.29 32.0 35.9 1.40 135.6 152.2 1.40

64.0 322.5 10.55 33.9 38.1 1.40 143.7 161.3 1.40

203.2 512.0 15.16 35.9 40.3 1.40 152.2 170.9 1.40

9.0 10.1 0.40 38.1 42.7 1.40 161.3 181.0 3.02

9.5 10.7 0.40 40.3 45.3 1.40 170.9 191.8 3.02

10.1 11.3 0.40 42.7 47.9 1.40 181.0 203.2 3.02

10.7 12.0 0.40 45.3 50.8 1.40 191.8 215.3 3.02

11.3 12.7 0.40 47.9 53.8 1.40 203.2 228.1 2.56

12.0 13.5 0.40 50.8 57.0 3.18 215.3 241.6 2.56

12.7 14.3 0.40 53.8 60.4 3.18 228.1 256.0 2.56

13.5 15.1 0.40 57.0 64.0 3.18 241.6 271.2 2.56

14.3 16.0 0.40 60.4 67.8 3.18 256.0 287.4 2.56

15.1 17.0 0.40 64.0 71.8 3.18 271.2 304.4 2.56

16.0 18.0 0.40 67.8 76.1 3.18 287.4 322.5 2.56

17.0 19.0 0.40 71.8 80.6 1.40 304.4 341.7 2.56

18.0 20.2 0.40 76.1 85.4 1.40 322.5 362.0 2.56

19.0 21.4 0.40 80.6 90.5 1.40 341.7 383.6 2.56

20.2 22.6 0.40 85.4 95.9 1.40 362.0 406.4 2.56

21.4 24.0 0.40 90.5 101.6 1.40 383.6 430.5 2.56

22.6 25.4 0.40 95.9 107.6 1.40 406.4 456.l 2.56

24.0 26.9 0.40 101.6 114.0 1.40 430.5 483.3 2.56

25.4 28.5 0.40 107.6 120.8 2.40 456.l 512.0 2.56

Rev 1.2

GIRD60 3.2.1.2.3.0-3 The translational accelerations at the spacecraft side of each instrument sensor unit mount shall produce an absolute peak acceleration Shock Response Spectra (SRS) less than the limits set in the On Orbit

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

Operational SRS Acceleration Limits Table below. The limits apply to each orthogonal axis for SRS natural frequencies when using a quality factor, Q, of 50. The SRS is computed after the acceleration is high pass filtered with a fourth order Butterworth filter with a -3d8 cut off at 1.0 Hz. Use a logarithmic interpolation for both frequency and acceleration terms in the On Orbit Operational SRS Acceleration

Limits Table.

GIRD61 3.2.1.2.3.0-4 Ou Orbit Openitioaal SRS A«deration Limih Tabk

SRS

SRS

SRS

SRS

r Limit

Limit/ limit

Limit/

{Uz) {mg) Q r

(mg)

(mg) (lb) (mg)

10 10.0 020 138 45.0 0.90

30 10.0 0.20 165 45.0 0.90

30 30.0 t.60 177 140.7 2_81

52 30.0 0.60 198 140.7 2.81

59 135.2 2.70 210 45.0 0.90

66 1352 2.70 225 45.0 0.90

73 30.0 0.60 236 103.9 2.08

90 30.0 0.60 264 103.9 2.08

90 45.0 0.90 275 45.0 0.90

112 45.0 0.90 285 45.0 0.90 ll8 102.3 2.05 295 82.2 L64

132 102.3 2.05 300 82.2 1.64

GIRD62 3.2.2 3.2.2 Thermal "

GIRD63 3.2.2.1 3.2.2.1 Thermal Control Concept

GIRD64 3.2.2.1.0-1 The instrument units installed on the spacecraft bus fall under one of the following categories:

a. Thermally-independent units are conductively and radiatively decoupled from the spacecraft and reject their heat directly to space.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

b. Thermally-coupled units dissipate their heat to the spacecraft.

GIRD65 3.2.2.1.0-2 In general:

• Instrument electronic units are thermally-coupled .

• Instrument sensor units are thermally-independent .

GIRD68 3.2.2.1.1 3.2.2.1.1 Coupled Unit Heat Transfer Flux Density

GIRD69 3.2.2.1.1.0-1 For conductively-coupled units, peak local heat transfer fluxes conducted to the spacecraft shall be less than 0.25 watts per square centimeter.

GIRD66 3.2.2.1.2 3.2.2.1.2 Independent Unit Net Heat Transfer

GIRD67 3.2.2.1.2.0-1 For Independent Units, the net heat transfer averaged over the instrument independent unit interface plane area shall be less than 15.5 watts/m2

GIRD70 3.2.2.2 3.2.2.2 Interface Temperatures

GIRD71 3.2.2.2.0-1 For planning and preliminary design purposes, the interface temperature (spacecraft side) for

Earthviewing instruments shall be:

- a. 0°c to 40°C during operation

b. -30°C to 50°C during non-operation

GIRD144 3.2.2.2.0-2 The instrument shall perform during Spacecraft level Thermal Vacuum in at least the following two orientations:

a. a) Spacecraft +Y BRF axis aligned with gravity and pointed down.

b. b) Spacecraft -z BRF axis aligned with gravity and pointed down

(CCR-X000108)

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD72 3.2.3 3.2.3 Instrument Electrical Power

GIRD73 3.2.3.1 3.2.3.1 Electrical Power Interfaces

GIRD74 3.2.3.1.0-1 The spacecraft shall supply functionally independent, redundant operational power buses to each instrument for normal instrument operation.

GIRD75 3.2.3.1.1 3.2.3.1.1 Power Definitions "'

GIRD76 3.2.3.1.1.0-1 The following definitions shall be used when calculating average power, maximum power, and peak current values.

GIRD77 3.2.3.1.1.0-2 Average Power (Operational) - The total power into an instrument averaged over any 5 minute period.

GIRD78 3.2.3.1.1.0-3 Average Power (Survival) - The total power into an instrument averaged over any 72 minute period.

GIRD79 3.2.3.1.1.0-4 Maximum Power {Operational or Survival) - The total power into an instrument averaged over any 20ms period.

GIRD81 3.2.3.1.1.0-5 The instrument shall operate in accordance with the instrument performance specification with a steady-state DC voltage of 28 +/- 2.0 volts at the instrument operational power input connector. {CCR-X000108}

GIRD147 3.2.3.1.1.0-6 The instrument shall operate the instrument survival heaters and associated passive control circuitry to maintain minimum turn-on temperatures with a steady-state DC voltage of TBD +/- 2.0 (TBR) volts applied at the instrument survival heater power input connector. {CCR-X000108}

GIRD82 3.2.3.2 3.2.3.2 Instrument Operational Power Grounding

GIRD83 3.2.3.2.0-1 The instrument electrical power grounding shall be in accordance with the Electrical Grounding Figure.

ID Object Number

GIRD84 3.2.3.2.0-2

GIRD86 3.2.3.3

GIRD87 3.2.3.3.0-1

GIRD88 3.2.3.4

GIRD89 3.2.3.4.0-1

GIRD90 3.2.3.5

418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

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Electrical Grounding Figure

3.2.3.3 Data Transfer Between the Instrument and Spacecraft

All data transferred between the instrument and the spacecraft shall use the European Cooperation for

Space Standardization (ECSS) ECSS-E-ST-50-12( Rev. 1 (Space Wire) standard through the packet layer as a minimum. (CCR-XOOOlOB)

3.2.3.4 Guaranteed Delivery

All data transferred between the instrument and the spacecraft shall provide guaranteed data delivery as defined in GOES R Reliable Data Delive(Y Protocol document.

3.2.3.5 Source Packet Format

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD91 3.2.3.5.0-1 All data transferred over the Space Wire shall use the CCSDS 133.0-8-1 Section 4.1 Protocol Data Unit definition shown in the Source Packet Definition Figure.

Source Packet Definition Figure

PR MARY HEADER

SECONDARY HEADER

PACKET IDENTIFICATION

PACKET SEQUENCE

PACKET

CONTROL

PACKET DATA VARIABLE

VERSION

SEC. PACKET

DATA

TME COOE ANO

NUMBER PACKET

HOR

APPLICATION SEQUENCE

SEQUENCE

LENGTH

ANCILLARY

TYPE

FLAG

PROCESS D FLAGS

COUNT DATA

3 bits 1 bit 1 bit 11 bits 2bits 14 bits 16bits 104 bits

2 octets 2 octets 13- 8192 octets

{CCR-X000108)

GIRD145 3.2.3.5.0-2 Data transferred over the SpaceWire data bus shall be clocked at 300 Mhz (TBR). (CCR-X000108)

GIRD146 3.2.3.5.0-2.0-1 Note: This clock rate allows for a 240 Mbps (TBR) data rate accounting for Space Wire overhead. {CCR-

X000108)

GIRD92 3.2.3.6 3.2.3.6 Pulse Per Second {PPS) \

GIRD93 3.2.3.6.0-1 The spacecraft shall provide the instrument a 1 PPS time code sequence accurate to ±10 microseconds relative to UTC.

GIRD94 3.2.3.7 3.2.3. 7 Control and Monitoring

GIRD95 3.2.3.7.0-1 The spacecraft shall provide remote access to all critical telemetry and control.

GIRD96 3.2.3.7.0-2 Critical telemetry is defined as telemetry points that are required to monitor the instrument in powered off state.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD97 3.2.3.7.0-3 Non-critical telemetry is defined as telemetry points that are required to monitor the instrument in powered on state.

GIRD98 3.2.3.7.0-4 Engineering telemetry are data required to process instrument sensor data to higher level products.

GIRD99 3.2.3.7.0-5 Housekeeping telemetry are data required to monitor instrument operation, health, and safety.

GIRDl00 3.2.4 3.2.4 Environmental Conditions

GIRD101 3.2.4.1 3.2.4.1 On Orbit Radiation Environment "'-'

GIRD102 3.2.4.1.0-1 The instruments and spacecraft shall comply with the on-orbit radiation requirements that are described in the GSFC document 417-R-RPT-0027 titled "The Radiation Environment for Electronic Devices on the

GOES-R Series Satellites."

GIRD103 3.2.4.2 3.2.4.2 Launch Environment

GIRD104 3.2.4.2.0-1 The instruments and spacecraft shall survive and operate after exposure to an envelope of environments for the following launch vehicles: SpaceX Falcon 9 Heavy, Vulcan Centaur with 6 solids, and New Glenn.

{CCR-X000108)

GIRD105 3.2.4.3 3.2.4.3 Eclipse

GIRD106 3.2.4.3.0-1 Solar Eclipse shall be considered as part of the environmental variation. The Solar Eclipse season occurs twice yearly, with each eclipse season lasting approximately 45 days. The maximum eclipse duration is

72 minutes.

GIRD107 3.3 3.3 Attitude and Orbit Data

GIRD108 3.3.0-1 All attitude, rate and orbit data shall be included in the spacecraft ancillary data packet.

GIRD109 3.3.1 3.3.1 Attitude Knowledge

GIRD110 3.3.1.0-1 The spacecraft shall provide a periodic attitude estimate to the instrument.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD111 3.3.1.1 3.3.1.1 Accuracy

GIRD112 3.3.1.1.0-1 The attitude knowledge static error shall not exceed 1200 microradians, 3-sigma, per axis, precalibration.

GIRD113 3.3.1.1.0-2 This requirement together with the next two define separate static, diurnal and dynamic attitude knowledge components. These requirements bound the knowledge error, which is the difference between the estimated attitude and the true attitude.

GIRD114 3.3.1.1.0-3 The attitude knowledge diurnal error shall not exceed 45 microradians, 3-sigma, per axis. Diurnal error refers to that portion of the error that repeats from day-to-day.

GIRD115 3.3.1.1.0-4 The attitude knowledge dynamic error shall not exceed 30 microradians, 3-sigma, per axis. Dynamic error includes all non-static and non-diurnal errors.

GIRD116 3.3.1.2 3.3.1.2 Update Rate

GIRD117 3.3.1.2.0-1 The spacecraft shall update the attitude estimate at a rate no less than 1 Hz.

GIRD118 3.3.1.3 3.3.1.3 Latency

GIRD119 3.3.1.3.0-1 The attitude estimate latency shall not exceed 100 milliseconds.

GIRD120 3.3.2 3.3.2 Spacecraft Angular Rate

GIRD121 3.3.2.0-1 The spacecraft shall provide a periodic angular rate estimate to the instrument.

GIRD122 3.3.2.1 3.3.2.1 Accuracy

GIRD123 3.3.2.1.0-1 The integrated rate error of the spacecraft angular rate estimate shall not exceed 1 microradian, 3sigma, in the x and y axes, and 1.5 microradians, 3-sigma, in the z-axis over any 1 second window.

GIRD124 3.3.2.1.0-2 The integrated rate error of the spacecraft angular rate estimate shall not exceed 2 microradians, 3sigma, in the x and y axes, and 2.5 microradians, 3 sigma in the z-axis, over any 30 second window.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

GIRD125 3.3.2.1.0-3 The integrated rate error of the spacecraft angular rate estimate shall not exceed 7 microradians, 3sigma, per axis, over any 300 second window.

GIRD126 3.3.2.1.0-4 The integrated rate error of the spacecraft angular rate estimate shall not exceed 20 microradians, 3sigma, per axis, over any 900 second window.

GIRD127 3.3.2.2 3.3.2.2 Bandwidth "'

GIRD128 3.3.2.2.0-1 The spacecraft angular rate estimate shall have a minus 3dB bandwidth of greater than 25 Hz.

GIRD129 3.3.2.3 3.3.2.3 Update Rate

GIRD130 3.3.2.3.0-1 The spacecraft shall update the angular rate estimate at a rate no less than 100 Hz.

GIRD131 3.3.3 3.3.3 Spacecraft Orbit

GIRD132 3.3.3.0-1 The spacecraft shall provide a periodic spacecraft orbit estimate to the instrument via the ancillary data packet.

GIRD133 3.3.3.1 3.3.3.1 Accuracy \

GIRD134 3.3.3.1.0-1 The spacecraft position estimate shall be accurate to 100 meters 3-sigma, in-track (ORF x-axis), crosstrack

(ORF y-axis) and radial (ORF z-axis) directions.

GIRD135 3.3.3.1.0-2 The spacecraft velocity estimate shall be accurate to within 6 cm/sec, 3-sigma, per axis.

GIRD136 3.3.3.2 3.3.3.2 Update Rate

GIRD137 3.3.3.2.0-1 The spacecraft shall update the orbit estimate at a rate no less than 1 Hz.

GIRD138 3.4 3.4 Instrument-to-Spacecraft Disturbances

GIRD139 3.4.0-1 At any time during the operational mode of the spacecraft, the sum of the magnitude of the instrument sensor unit's uncompensated torques and the magnitude of its uncompensated linear forces multiplied by a lever arm of 2 meters shall not exceed 1.0 N-m.

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

Rev 1.2

GIRD140 3.4.0-2 The magnitude of the instrument unit's uncompensated angular momentum shall not exceed 1.0 N-msec.

GIRD141 4 4 Acronyms , GIRD142 4.0-1 %AC percent area coverage

A Ampere(s)

ASD Acceleration Spectral Density

SOL beginning of life

BRF body reference frame bps bits per seconds

C Celsius (Degrees) cm centimeter db decibel de Direct Current

ECSS European Cooperation for Space Standardization

EEO Electro-Explosive Device

EEE Electrical, Electronic and Electromechanical

ESD electro static discharge

FOR field of regard

FOV field-of-view

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD) g Earth's gravitational acceleration

GIRD General Interface Requirements Document

GOES Geosynchronous Operational Environmental Satellite

GSE Ground Support Equipment

GSFC Goddard Space Flight Center

Hz hertz

ICD Interface Control Document

IDD Instrument Description Document

IRU inertial reference unit

ISO International Office for Standardization

K kelvin kg kilogram

Km kilometer kPa Kilo Pascals

LOS line-of-sight

LSB Least Significant Bit m meter ma milli-ampere(s)

Mbps Mega bits per seconds

Rev 1.2

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

MHz Mega hertz mm millimeter

MAT Mission Allowable Temperatures

MEFL Maximum Expected Flight Level m-g milli-g (Earth's gravitational acceleration)

MU Multi-layer insulation

Ms milli-seconds

NASA National Aeronautics and Space Administration

N-m Newton-meter

N-m-sec Newton-meter-second nPa Nano Pascals

NVR Non-Volatile Residue

- ORF Orbit reference frame

OSR Optical solar reflectors

PPB Parts Per Billion

PPM Parts Per Million

PPS Pulse Per Second

PSD power spectral density

QCM Quartz Crystal Microbalance

ID Object Number 418-XO-GXIGIRD-0025, RM Version, GeoXO General Interface Requirements Document (GIRD)

RIU Remote Interface Unit

SCF SPP Coordinate Frame

SI International System of Units

SINDA System Integrated Numerical Differential Analyzer

SIS Solar Imaging Suite

SPP Sun-Pointing Platform

SRS Shock Response Spectra

TSO to be determined

TBR to be refined/reviewed

THC Total Hydrocarbons

UIID Unique Instrument Interface Document

UTC Universal Time Code µsec mico-seconds

V Volts

Vdc Volts-Direct Current w Watts