Exhibit 5 - L10 Spacecraft Specifications Fill-in.pdf

Spacecraft Technical Specification Fill-In

Name of Bus Product Line for Proposed Solution:

Subsystem Proposed Spec/Capability Product Line Spec/Capability Units Notes SC Bus Top Level Information

Bus Design Life yr Launch Vehicle Compatibility (list) N/A

Mass SC Bus Dry Mass kg Proprellant Tank Capacity kg SC Wet Mass (excluding Instrument) kg

Power Power System Design Mission Life yr Power System Generation per Orbit W Power System Storage Capability per Orbit Ah Bus Voltage VDC Bus Regulation (Reg or Unreg.)

Bus type - Direct Energy Transfer (DET), Peak Power Tracker (PPT) Total Solar Array Area Solar Array EOL Power W Solar Array BOL Power W Number Solar Array Wings Number Solar Array Panels/Wing Solar Array articulation - Fixed, Single Axis, Two Axis Number of batteries Battery Capacity, Nameplate Ah Battery Capacity, EOL Ah Battery Capacity, BOL Battery Cell Management Required? Y/N Battery Qualified No. of Charge/Discharge Cycles Battery Cell Type Battery Chemistry

Electrical Instrument Power Capability, Orbital Avg W Instrument Power Capability, Max. Peak W SC Power Consumption, Orbital Avg. W SC Power Consumption, Max. Peak W Total unswitched services Total switched services

Propulsion Total delta-V Capability m/s System Type (Chemical or Electrical) System Regulation (Regulated or Blowdown) Propellant Type (Monopropellant or Bipropellant) Number of Thrusters Thruster Nominal Thrust N Thruster EOL Thrust N De-orbit Reliability, Components % Surge suppression device(s) used? Y/N Pressure Transducer EOL Full Scale Accuracy %

Thermal Heater Circuit Control (Software, Hardware or Both?)

Number of Heater Circuits Heater control bands (+/-) C Heat Pipes, Qty Loop Heat Pipes, Qty Heater, Wattage Range W Power Consumption, Orbital Avg W Power Consumption, Maximum W

Mechanical, Structure & Mechanisms Quantity of release actuators for launch locks Quantity of motors incorporated into mechanisms Minimum modal frequency, lateral and axial Hz Diameter of mechanical mating/separation interface to LV mm

Attitude Control Number of/List of ACS Control Modes E.g., earth observing, safe, Delta-V Controller bandwidth (ideally mode-by-mode) Hz Controller gain stability (ideally mode-by-mode) dB Controller rigid body phase stability (ideally mode-by-mode) deg Controller flex gain stability (ideally mode-by-mode) dB Momentum Bias Configurable? Y/N Power Consumption, Orbital Avg W Power Consumption, Maximum W

GNSS

Receiver Redundancy? Y/N Frequency Bands MHz Antenna Type Antenna Redundancy? Y/N Antenna, Qty Antenna, Coverage Sr

Actuators ACS Control Actuators, Qty (by mode) ACS Control Actuator Type, by mode ACS Steered Actuators, Qty (by mode) ACS Steered Actuator Type, by mode

Reaction Wheels, Qty Reaction Wheel/Bearing Rated Life Yr Reaction Wheel Momentum Capacity Nms Reaction Wheel Torque Ability Nm Torque Bar/rods, no. of axes controlled Torque Bar/rods, redundancy Torque Bar rating Am^2

Sensors Number of Sensors in Each Control Loop Star Trackers, Qty Gyro Sensor and Type CSS Coverage Sr Magnetometers, no. of axes sensed Magnetometers, redundancy Magnetometer, sensitivity nT

Attitude Flight Software Processing Rate Hz Ground-based calibration of ACS sensors needed Y/N Number of ground-uploadable parameters FSW provision to correct actuator and sensor polarity errors Y/N FSW updates patchable from the ground Y/N FSW reboot preserves previous parameter configuration Y/N Number of fault flags monitored

Communications Command Link Security

Encryption Type (GCM or CCM) Transmitted MAC Length bits Number of flight keys Compatible Ground Equip

Cmd & Telemetry General Parameters Transceiver Model Transceiver TRL Antenna Model Antenna TRL Estimated EIRP (boresite) dBW Estimated G/T (boresite) dB/K

Service Coding 28 kbps DTE Telemetry Service Coding 3 Mbps DTE Telemetry Service Coding 1 ksps DTE Command Service Coding 32 ksps DTE Command Service Coding 128 ksps DTE Command Service Coding

Science Link Transmitter Model Transmitter TRL High Speed Data Interface Model HPA Model

HPA TRL

HPA OBO dB HPA Power (@NOP) dBm Antenna Model Antenna TRL Antenna Diameter m Estimated Antenna Gain (boresite) dBi Gimbal Model (if applic) Gimbal TRL Estimated EIRP (boresite) dBW Total Information Rate (LHCP + RHCP) Gbps Modulation Coding (If SCCC, specify ACM mode) Baseband Filtering

Command & Data Handling Power Consumption, Orbital Avg W Power Consumption, Maximum W Instrument Interface, Bus #1

Data standard Nominal Transfer rate Gbps

Instrument Interface, Bus #2 Data standard Nominal Transfer rate Gbps

Instrument Interface, Bus #3 Data standard Nominal Transfer rate Gbps

Processor Type Clock Speed MHz Volatile Memory Capacity GB No. of FSW copies in Non-volatile memory

Mass Storage Device Memory Technology SEFI modes (list) EOL Capacity TB TID Rating Gy EDAC scheme Scrubbing rate MB/s

Flight Software

Dedicated SW Development Environment Y/N Primary Implementation Language(s) (list) Real-Time Operating System (name) Software Re-Use, Approximate Amount % Relative to standard FSW load & per Landsat 10 requirements

Name of Bus Product Line for Proposed Solution: NCC-1701 Constitution Class

Subsystem Proposed Spec/Capability Product Line Spec/Capability Units Notes SC Bus Top Level Information

Bus Design Life 10 15 yr Mass

SC Bus Dry Mass 1200 1500 kg Proprellant Tank Capacity 200 350 kg

Power Power System Design Mission Life 10 15 yr Power System Generation per Orbit 1000 1000 W Bus Voltage 28 Requires Customization VDC Product line std is 70VDC bus Bus Regulation (Reg or Unreg.) Reg Reg Solar Array EOL Power 800 900 W Battery Chemistry LiPo Requires Customization Product line std is NiCAD

Thermal Heat Pipes, Qty 5 5 Loop Heat Pipes, Qty N/A N/A LHPs are not utilized

EXAMPLE Spacecraft Technical Specification Fill-In EXAMPLE