Attachment 3 - TRD (Rev 1).pdf

Mission Requirements Value MISS-1 Nominal Orbit Altitude 1000 +/- 50 km (circular) MISS-2 Acceptable Orbit Inclinations 60 - 90 degrees MISS-3 SV Operational Lifetime (After Checkout) 1 year MISS-5 Mission Class D (per NASA NPR 8705.4 as tailored per government approval) MISS-6 Disposal Must comply with "U.S. Government Orbital Debris Mitigation Standard Practices, November 2019 Update" and AFI 91-202 (12 Mar 2020), where ODMSP takes precedence

MISS-7 Initial Launch Capability No later than 31 March 2022 Payload Accomodations PAY-1 Payload Mass Space vehicle shall accommodate a GFE payload with mass less than 60 kg PAY-2 Payload Moments of Inertia Ixx, Iyy: NLT 3.4 kg*m2; Izz: NLT 2.6 kg*m2 PAY-3 Payload Orbit Average Power Threshold: NLT 150 W; preference given to increased power up to 300 W PAY-4 Payload Peak Power NLT 500 W PAY-5 Payload Eclipse Operation Yes PAY-6 Payload Volume NLT 52 cm x 70 cm x 52 cm (X, Y, Z axes) PAY-7 Payload Unobstructed Field of View During imaging operations, no space vehicle component shall vignette the FOV, or reflect light into the FOV, of the top/front surface of the highest optic of the GFE OPIR payload

PAY-8 Payload Data Handling NLT 250 Mbps capacity PAY-9 Payload Data and Telemetry Storage Threshold: NLT 300 GB capacity; Objective: 600 GB capacity PAY-10 Payload Digital Command/Data Interface 1000Base-T Gigabit Ethernet link (1 Gbit per sec) or SpaceWire required; bi-level discrete output available PAY-11 Payload Analog Data Interface NLT 2 analog channels (0-5 V) available for payload health and status PAY-12 Material Selection Low outgassing materials (< 1% TML, < 0.1% CVCM) when tested in compliance with

ASTM-E595-84

PAY-13 Facility Cleanliness Class 100,000 for SV integration/test activities (bag & purge with dry N2 when not being handled); Class 1,000A for payload testing if optics are exposed (bag & purge with filtered, clean, dry N2 or air otherwise).

PAY-14 Payload Center of Gravity Location NTE 21 cm above payload mounting surface, in nadir/+Z direction PAY-15 Payload First Fundamental Frequency NLT 85 Hz Attitude and Orbit Control AOC-1 Stabilization Method 3-axis AOC-2 Pointing Modes Nadir, Off-Nadir Inertial Point/Track (including star calibration), Sun Pointing, Safe

AOC-3 Attitude Knowledge NTE 0.05 deg (worst axis, 3 sigma, Threshold), NTE 0.01 deg (worst axis, 3 sigma, Objective)

AOC-4 Attitude Control NTE 0.24 deg (worst axis, 3 sigma) AOC-5 Jitter High-Frequency Jitter shall not exceed 0.0025 deg (worst axis, 1 sigma) for frequencies above 13.4 Hz.

Low-Frequency Jitter shall not exceed 0.005 deg (worst axis, 1 sigma, over a 1 sec duration) for frequencies below 13.4 Hz.

AOC-6 Orbit Position Knowledge NTE 10 m (3 sigma) at a rate of ≥ 50 Hz AOC-7 Orbit Velocity Knowledge NTE .02 m/s (3 sigma) at a rate of ≥ 50 Hz Telemetry and Commanding TTC-1 Telemetry and Command Message Format Contractor Provided TTC-2 Communication Frequency Band Contractor Provided TTC-3 Command Rate Contractor Provided TTC-4 Telemetry Rate Contractor Provided TTC-5 Encryption All links shall be encrypted using an NSA-approved encryption solution Structure and Mechanisms MECH-1 Payload Random Vibration NTE 14.1 g RMS in plane, NTE 18.3 g RMS out of plane MECH-2 Payload Mechanical Interface Pinned interface to nadir-facing panel with alignment knowledge to attitude control system Electrical Power EPS-1 Bus Voltage to Payload 28 V +/- 4 V DC EPS-2 Minimum Number of Power Feeds 3 Thermal Control

X-axis = Velocity Y-axis = Pitch Z-axis = Nadir

Attachment 3 - Bus Specification Table (Rev 1)

Terminology:

NTE = Not To Exceed NLT = No Less Than Capacity = Maximum capability of hardware or software

THERM-1 Allowable Payload Heat Conduction Through Payload Interface (Orbit-Avg)

0 W (adiabatic) with bus providing face with unobstructed and persistent view of deep space for payload radiator

THERM-2 Survival Heater Power Space Vehicle shall provide NLT 70W OAP Survival Heater Power during unpowered payload operations. If Survival Heater Power is not available during launch, it is required no later than 70 min after launch.

Software SW-1 Command Execution Accuracy +/- 1 sec SW-2 Software Uploads Yes SW-3 On-board Time Reference The space vehicle shall provide an on-board time reference 1 PPS (pulse per second) with an accuracy of less than 100 ns with respect to UTC.

SW-4 Stored Command Execution Yes Data Download DATA-1 Minimum Data Download Threshold: 250 GB/day (average); preference given to higher data rates

20200625