reveal passive illumination by radar (pair). overview payload / mission communication launch orbit...
TRANSCRIPT
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reVeal
Passive Illumination by Radar (PAIR)
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Overview
• Payload / Mission• Communication• Launch• Orbit• Power• Thermal• Attitude• Propulsion• Finance
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Radar Illumination
Primary Mission:
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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
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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)
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Communications
•PRIMARY DUTY–Transmit Radar Energy
•SECONDARY DUTY–Link Data and Communications–Instant access to any user–Fast and reliable services
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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
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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 %
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Launch Vehicles
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Launch Vehicles
• Task: – Deliver 18 satellites successfully
to orbit
• Shared Launch– Efficiencies
• Cost• Time• Resources
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Launch Vehicles
• Titan IV– Reliable
• 92% Success Rate
– American made• Creator: Lockheed Martin
– Our Purpose• Cape Canaveral Launch• High payload capacity
– Cost Effective• Recoverability
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Launch Vehicles
• Ariane 4– Reliable
• 93% Success Rate
– European origin• Creator: European Space Agency
– Our Purpose• Kourou, Brazil Launch
– Cost Effective• Recoverability
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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
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Orbit Responsibilities
Equatorial
Polar 1
Polar 2
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Orbital
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Power Subsystem
•Power Source–Solar Photovoltaic
•Cell Type–Silicon
•Required Area–80 m^2
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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
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Thermal Subsystem
• Passive Control– Radiators, Insulation,
and surface finishes• Control the amount of
solar energy absorbed
• Active Control– Heaters and Louvers
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Attitude Control
• Control Techniques– Passive– Three Axis Control
• Disturbance Torques– Gravity– Solar Radiation– Magnetic– Aerodynamic
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Attitude Control
• Actuators– Types for control
• Sensors– Required sensors
• Stabilization– How will this be achieved?
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Propulsion
• Orbital Insertion– Propulsion type
• Attitude Control– Propulsion type
• Shared System or Separate System
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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
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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
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Summary
• Payload / Mission• Communication• Launch• Orbit• Power• Thermal• Attitude• Propulsion• Finance