reVeal Passive Illumination by Radar (PAIR)

Overview Payload / Mission Communication Launch Orbit Power Thermal Attitude Propulsion Finance

Radar Illumination Primary Mission:

L Band Antenna L-Band –1-2 GHz –15-30 cm –“Long” range Phased Array –Allows for flat antenna profile –Easily compacted and deployed –Lightweight

LEO/MEO SAT STEALTH TARGET TARGET SHADOW EARTH RECEIVER ARRAY RADAR ILLUMINATION SCATTERED RADAR CENTRALIZED COMPUTER ANALYSIS AND SIGNAL PROCESSING NETWORK BACKBONE AWAC / JSTAR AIR ASSETS GROUND ASSETS PERSONAL USER INTERFACE GENERAL SURVEILLANCE RADAR NAVAL ASSETS reVeal Passive Area Illumination by Radar (PAIR)

Communications PRIMARY DUTY –Transmit Radar Energy SECONDARY DUTY –Link Data and Communications –Instant access to any user –Fast and reliable services

Communications PAYLOAD PARAMETERS PARAMETER UP AND DOWN LINK Frequency (GHz)42/45 Transmitter Output Power (W)20 Number Beams and Transmitters1 Antenna Beamwidth (deg)0.4 Antenna Diameter (m)1.25 Antenna Mass (kg)5 Transmitter Mass (kg)3.5 Transmitter Input Power (W)80

Communications LINK BUDGET Transmit Antenna Gain (net)49.2dB Equiv. Isotropic Radiated Power61.22dB Receive Antenna Diameter6m Receive Antenna Gain (net)62.84dB Data Rate2.5Gbps Signal-Noise Ratio24.36dB Bit Error Rate<10E-7 Margin17.36dB Rain Attenuation14dB Availability98%

Launch Vehicles

Task: –Deliver 18 satellites successfully to orbit Shared Launch –Efficiencies Cost Time Resources

Launch Vehicles Titan IV –Reliable 92% Success Rate –American made Creator: Lockheed Martin –Our Purpose Cape Canaveral Launch High payload capacity –Cost Effective Recoverability

Launch Vehicles Ariane 4 –Reliable 93% Success Rate –European origin Creator: European Space Agency –Our Purpose Kourou, Brazil Launch –Cost Effective Recoverability

Orbital Less is more –Minimization Maximize your potential –Don’t be antisocial Our task –Primary Concern: Radar Illumination –Secondary: Global Communication How we did it –Optimal orbits 1 Equatorial 2 Polar

Orbit Responsibilities Equatorial Polar 1 Polar 2

Orbital

Power Subsystem Power Source –Solar Photovoltaic Cell Type –Silicon Required Area –80 m^2

Power Subsystem Continued Power Storage –Primary Battery Not Necessary for long term missions –Secondary Battery Provides power during eclipse periods Chose NiH2 –Provides a high depth of discharge

Thermal Subsystem Passive Control –Radiators, Insulation, and surface finishes Control the amount of solar energy absorbed Active Control –Heaters and Louvers

Attitude Control Control Techniques –Passive –Three Axis Control Disturbance Torques –Gravity –Solar Radiation –Magnetic –Aerodynamic

Attitude Control Actuators –Types for control Sensors –Required sensors Stabilization –How will this be achieved?

Propulsion Orbital Insertion –Propulsion type Attitude Control –Propulsion type Shared System or Separate System

Finance Itemization Patch Heater$100 Louver$1,500 L-Band Antenna$4,200 Momentum Wheel$282 Cold Gas Thruster$26,215 Solar Panel for 80 m 2 $249, kg for Structure$ in materials

Finance Satellite ≈ $306,445 x 18 = $5,516,010 Titan IV (one launch) Centaur ≈ $350- $450 million Ariana 42P, H-10, (two Launches) ≈ $85- $170 million Total: $525,516,010 ~ $625,516,010

Summary Payload / Mission Communication Launch Orbit Power Thermal Attitude Propulsion Finance