Attachment 3 - TPE TRD.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 NLT 3/31/22 (delivery of GFE payload + 4 months) 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 77 cm x 65 cm x 82 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 Gig-E & Space Wire Serial Telemetry & Command, Bi-Level discrete output PAY-11 Payload Analog Data Interface NLT 2 analog channels (0-5 V) available for P/L 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 THERM-1 Allowable Payload Heat Conduction Through Payload Interface

(Orbit-Avg) NLT 155 W with preference given to increased dissipation up to 300 W, or 0 W with bus providing face with unobstructed and persistent view of deep space

Software SW-1 Command Execution Accuracy +/- 1 sec SW-2 Software Uploads Yes SW-3 On-board Time Reference The space vehicles 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

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

HQ0850-20-R-0002 Attachment 3 - Bus Specification Table

Terminology:

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

Sheet1