ReVeal Passive Illumination by Radar (PAIR). Overview Payload / Mission Communication Launch Orbit...

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