Attachment 3 Spacecraft and Ground Technical Specification Sheet (SGTSS).pdf

Attachment 3 Spacecraft and Ground Technical Specification Sheet (SGTSS) FA8809-24-R-B001

SPACE VEHICLE PERFORMANCE

1.1 LAUNCH VEHICLE COMPATIBILITY

1.1.1

Reference Launch Vehicle (LV) Configuration Space Vehicle (SV) used for mission (LV used for SV mission)

1.1.2 SV-LV Separation Mechanism

1.1.3 Fairing Diameter (last LV used)

1.1.4 Other Launch Vehicle Compatibility's

1.1.5 Prior Most Severe Vibration Environment and in what axis

1.1.x Other

1.2 REFERENCE ORBITS COMPATIBILITY

1.2.1 Apogee Altitude Range (km)

1.2.2 Perigee Altitude Range (km)

1.2.3 Inclination Range (deg)

1.2.4 Other Orbit Compatibility's

1.2.5 End-of-life (EOL) Capability

1.2.6 Prior Most Severe Magnetic Field Exposure

1.2.x Other

1.3 CLEANLINESS LEVELS ACHIEVED

1.3.1 Particulate

1.3.2 Molecular

1.3.3 Prohibited Materials / Processes

1.3.x Other

1.4 DESIGN LIFETIME

1.4.1 Probability of Success (Ps)

(0 <= Ps <= 1.0)

1.4.2 Operational Lifetime (for provided Ps) (years)

1.4.3 On Board Expendables Lifetime (years)

1.4.4 Areas of Redundancy

1.4.x Other

1.5 RADIATION TOLERANCE

1.5.1 Total Dose (kilorads)

1.5.2 Single Event Effects and System Sensitivity

1.5.x Other

1.6 PAYLOAD MODEL Configuration

COMPATIBILITY

ID UNITS

PERFORMANCE OR DESCRIPTION

(alphanumeric or numberic)

1.6.1 Payload (PL) Thermal Model (e.g., Format, Units, File type, etc.)

1.6.2 PL Computer Aided Design Model (e.g., Format, Units, File type, etc.)

1.6.3 PL Finite Element Model (e.g., Format, Units, File type, etc.)

1.6.x Other

SPACECRAFT PERFORMANCE

2.1

STRUCTURAL & MECHANICAL

CHARACTERISTICS

2.1.1 Form Factor (e.g., 6U, 12U, 1/2 ESPA Class, ESPA Class)

Xmin Xmax Ymin Ymax Zmin Zmax

2.1.3 Primary Structure Material(s)

2.1.4 System Mass, Launch Config. w/o PL, DRY (kg)

2.1.5 Maximum Fuel Mass if applicable (kg)

2.1.6 Maximum Payload Mass (kg)

2.1.7 Coordinate System Definition (Description or Graphic)

Xmin Xmax Ymin Ymax Zmin Zmax

Xmin Xmax Ymin Ymax Zmin Zmax

Ixx Iyy Izz Ixy Ixz Izy

Xmin Xmax Ymin Ymax Zmin Zmax

X Y Z -X -Y -Z

X Y Z

2.1.14 Deployables

No. and Types

2.1.10 Maximum Payload Moments of Inertia (MOI) (kg-m^2)

2.1.12 Maximum Payload Unobstructed Field-of-View (in SC coordiantes) (deg)

2.1.11

2.1.8 External Payload Envelope Dimenions (in Spacecraft (SC) coordinates) (mm)

2.1.9 Allowable Payload Center of Gravity (CG) Range (in SC coordinates) (mm)

2.1.13 Maximum Payload Alignment Accuracy (in SC coordinates) (deg)

2.1.2 Physical Dimensions (mm)

Internal Payload Envelope Availability

2.1.x Other

2.2 POWER AND ELECTRICAL SUBSYSTEM

2.2.1 Type/Architecture

2.2.2 Compatible Electrical Interfaces (RS-422, SpaceWire, etc.)

Digital Input Digital Output Analog Input Analog Output

Ability to Simultaneously Accommodate Multiple Electrical Interfaces on SC Which interfaces and how many on proven configuration?

2.2.5 Power Capacity Full Sun Watts (W)

2.2.6 Peak Payload Power at End-of-Life (EOL) (W)

2.2.7 Orbit Average Payload Power at EOL (W)

2.2.8 Allowable Payload Standy Power (W)

2.2.9 Bus Voltage, Nominal Range (list regulated and unregulated) (V)

2.2.10 Bus Voltage, Minimum (V)

2.2.11 Bus Voltage, Maximum (V)

2.2.12 Solar Array-Total Array Area (m^2)

2.2.13 Solar Array-EOL Power (total) (W)

2.2.14 Solar Array-Beginning of Live (BOL) Power (total) (W)

2.2.15 Solar Array-Cell Type, efficiency and No.

2.2.16 Solar Array Mounting

2.2.17 Solar Array-Articulation

(axies=0,1,2 ,3)

2.2.18 Battery-Capacity (AHr)

2.2.19 Battery-Depth of Discharge (%)

2.2.20 Battery-Cell Type

2.2.21 Number of Batteries

2.2.22 Number of Cells per Battery

2.2.23 Battery Charging Type

2.2.24 Battery-Fault Protection

2.2.25 Typical Mission Power Profile

2.2.x Other

2.3 PROPULSION SUBSYSTEM

2.3.1 Type/Architecture

2.2.3 Number of Inputs and Outputs for Each Type

2.2.4

(Yes or No, and specific details)

2.3.2 Propellant Type

2.3.3 Pressurant Type (if applicable)

2.3.4 Maximum Propellant Load (kg)

2.3.5 Attitude Control Capability (Yes or No)

2.3.6 Total Impulse Capability (m/sec)

2.3.x Other

2.4 ATTITUDE CONTROL SUBSYSTEM

2.4.1 Type/Architecture (e.g., 3 axis stabalized, spin stabilized, etc.)

2.4.2 Spin Axis, if applicable (X, Y or Z)

In Track Cross Track Altitude

Roll Pitch Yaw

2.4.5 Pointing Stability/Jitter (arcsec/sec)

Roll Pitch Yaw

2.4.7 Maximum Maneuver Rates (deg/sec)

2.4.8 Pointing Stabilization Time Period (Following LV Separation and/or After a Maneuver) (sec)

2.4.9 Pointing Constraints due to Solar Array Configuration

2.4.10 Pointing Constraints for Thermal, Sun, Earth, and/or Moon

2.4.11 Star Trackers

No. and Types

2.4.12 Reaction Wheels

No. and Types

2.4.13 Torque Rods

No. and Types

2.4.14 GPS

2.4.15 Sensors-Coarse, Fine Sun Sensors

No. and Types

2.4.x Other

2.5

COMMAND AND DATA HANDLING

SUBSYSTEM

2.4.3 Orbit Knowledge (km)

2.4.4 Pointing Accuracy (arcsec)

2.4.6 Pointing Knowledge (arcsec)

2.5.1 Type/Architecture (e.g., Consultative Committee for Space Data Systems (CCSDS) formatting)

2.5.2 Data Handling Capacity (kb/sec)

2.5.3 Data Storage Capacity (Mb)

2.5.4 Error Detection And Correction (EDAC)

2.5.5 Selectable Data Rates

(Yes or No, and specify)

2.5.6 Processor Architecture/Type

Processing Speed (MHz) RAM (KB) ROM (KB)

EEPROM

(KB)

2.5.9 Command Type (mnemonic, bit file, other)

2.5.x Other

2.6 COMMUNICATION SUBSYSTEM

2.6.1 Receive Frequency Band (L, S, C, X, UHF, VHF Ka, Ku, etc.)

2.6.2 Receiver Bandwidth

2.6.3 Transmit Frequency Band (L, S, C, X, UHF, VHF Ka, Ku, etc.)

2.6.4 Transmit Bandwidth

2.6.5 Effective Isotropic Radiated Power (EIRP) (W)

2.6.6 Gain-to-Noise (G/T) (dB/K)

2.6.7 Type of Modulation

2.6.8 Range of Modulation Index

2.6.9 Coding Schemes

2.6.10 Ranging (tones) (Yes or No)

2.6.11 2-way Doppler (Yes or No)

2.6.12

Network Compatibility (Spacecraft Tracking and Data Acquisition Network (STDN), Deep Space Network (DSN), Tracking and Data Relay Satellite System (TDRSS), Space Ground Link Subsystem (SGLS), other)

2.5.7 On-Board Computer Capacity

2.5.8 Stored Commanding Capability (Yes or No)

Number of Command Queues Limitations

TYPE GAIN PATTERNS

RANGE OF

TRAVEL

(alphanumeric) (numeric) (alphanumeric) (degrees)

2.6.14 Total Telemetry Transmit Rate (kbps)

2.6.15 Available PL Telemetry Transmit Rate (kbps)

2.6.16 Command Receive Rate (kbps)

2.6.17 Survival/Backup Mode Link and Data Rate

(Frequency & kbps)

2.6.18 Number of Transmit Channels

2.6.19 Subcarrier Capability on Transmitter (Yes or No)

2.6.20 Transmitter Power

2.6.21 Amplifier Gain

2.6.22 % of Time Transmitter can be on (%)

(Yes or No) (Specify)

2.6.x Other

2.7 THERMAL CONTROL

2.7.1 Type/Architecture

2.7.2 PL Interface Temperature Range (Survival and Operational) (C)

2.7.3 Available PL Thermal Capacity from Core SC (Orbit Averaged) W

2.7.x Other

2.8 SOFTWARE SUBSYSTEM

2.8.1 Flight Development Environment

2.8.2 Flight Verification Environment

2.8.3 Flight Resuse/Rework (%)

2.8.4 Ground Support Equipment (GSE) Development Environment

2.8.5 GSE Verification Environment

2.8.6 GSE Reuse/Rework (%)

2.8.x Other

GROUND SOLUTION PERFORMANCE

3.1 DATA DISTRIBUTION

3.1.1 Data Transport Network

3.1.2 Support for Streaming Data

3.1.3 Support for File Data

3.1.4 Data Transport Protocols

2.6.23 Ability to Accommodate Type 1 Encryption and description of ability to do so

2.6.13 Spacecraft Antenna

3.1.5 Naming Conventions

3.1.x Other

3.2 GROUND SYSTEM

3.2.1 Real-time

3.2.1.1 What real-time engine is used for C2 (e.g. Neptune, RAPTOR, etc.)

3.2.1.2 Virtualized? (Yes or No)

3.2.1.3 Containerized? (Yes or No)

3.2.1.4 Automated? (Yes or No)

3.2.1.5 Initializes Hardware (e.g., Front-End-Processors (FEPs) and cryptographic unit (crypto)) (Yes or No)

(Yes or No) (Specify)

3.2.1.7 Estimated Coding Effort to Create New Autonomous Procedures (Yes or No)

3.2.1.8 Continued Technical Support Available? (Yes or No)

3.2.1.x Other

3.2.2 Mission Planning

32.2.1 Contact Planning (Yes or No)

(Yes or No) (Specify)

3.2.2.3 Station Keeping Planning

(Yes No, N/A) (Yes or No) (Specify)

3.2.2.5 SC/PL Memory Management (Yes or No)

3.2.2.6 Continued Technical Support Available? (Yes or No)

3.2.2.x Other

3.2.3 Flight Dynamics

(Yes or No) (Specify)

3.2.3.2 Propulsive Maneuver (for station-keeping, momentum dumping, rendevous, etc.)

(Yes No, N/A)

3.2.3.3 Orbit Determination (Yes or No)

3.2.3.4 Sun Angle Estimation (Yes or No)

3.2.3.5 Visibility (on ground and in space) (Yes or No)

3.2.3.6 Command Scripting (Yes or No)

PL Operations Planning

Attitude Maneuver (for target pointing, etc.)3.2.3.1

3.2.2.2

3.2.2.4

3.2.1.6 Autonomously Respond to Spacecraft Telemetry

Spacecraft Bus Maintenance Planning & Tasking

3.2.3.x Other

3.2.4 Post-Pass Processing

3.2.4.1 Report Generation (Yes or No)

3.2.4.2 Out-of-Limits Telemetry Analysis (Yes or No)

3.2.4.3 Trending? (Yes or No)

3.2.4.4 PL Data Distribution Method and Lantency

3.2.4.x Other

3.2.5 Spectrum

3.2.5.1 Ground Federal Communications Commission (FCC) License/ National Telecommunication Information Administration (NTIA) Certification

3.2.5.2 Ground FCC License/NTIA Certification Expiration

Date

3.2.5.3 Ground FCC License/NTIA Radio Frequency

Assignment

3.2.5.4 Ground FCC License/NTIA Certification of

Spectrum Supportability Control Number

3.2.5.5 Space Vehicle FCC License/NTIA Certification

3.2.5.6 Space Vehicle FCC License/NTIA Certification

Expiration Date

3.2.5.7 Space Vehicle FCC License/NTIA Radio Frequency

Assignment

3.2.5.8 Space Vehicle FCC License/NTIA Certification of

Spectrum Supportability Control Number

3.2.5.x Other

PROGRAMMATIC & OTHER

4.1 Heritage Missions

4.1.1 Mission Names and Dates (contract duration, launch date, mission duration)

4.1.2 Mission CAD Model Images

4.1.3 Number of PL in Each Mission

4.1.4 Mission Unclass, CUI or Classified

(Yes No, N/A)

(Specify)

4.2 Nominal Schedules

4.2.1 Nominal Schedule to PL Integration (Months)

4.2.2 Nominal Schedule to ILC (Months)

4.3 Disposal Requirements

4.1.5 Prime for Ground Solution, Mission Operations & Location

4.3.1 Maximum Orbit Altitude to Meet Disposal Lifetime Requirements (km)

4.3.2 Disposal Concerns

4.x Other

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