reveal passive illumination by radar (pair). overview payload / mission communication launch orbit...
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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 ANALYSISAND SIGNAL PROCESSING
NETWORK BACKBONE
AWAC / JSTAR
AIR ASSETSGROUND ASSETS
PERSONAL USER INTERFACE
GENERAL SURVEILLANCE RADAR
NAVAL ASSETS
reVealPassive 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
CommunicationsPAYLOAD PARAMETERS
PARAMETERUP AND
DOWN LINK
Frequency (GHz) 42/45
Transmitter Output Power (W) 20
Number Beams and Transmitters 1
Antenna Beamwidth (deg) 0.4
Antenna Diameter (m) 1.25
Antenna Mass (kg) 5
Transmitter Mass (kg) 3.5
Transmitter Input Power (W) 80
CommunicationsLINK BUDGET
Transmit Antenna Gain (net) 49.2 dB
Equiv. Isotropic Radiated Power 61.22 dB
Receive Antenna Diameter 6 m
Receive Antenna Gain (net) 62.84 dB
Data Rate 2.5 Gbps
Signal-Noise Ratio 24.36 dB
Bit Error Rate <10E-7
Margin 17.36 dB
Rain Attenuation 14 dB
Availability 98 %
Launch Vehicles
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 m2 $249,000
55 kg for Structure $148.34 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