assurance technology coporation : capabilities

Capabilities Overview

84 South Street • Carlisle, MA 01741

A S S U R A N C E T E C H N O L O G Y C O R P O R A T I O N

Evaluation And Test Services– Electrical, Structural And Thermal Modeling And Analysis

– Space, Avionics And Terrestrial Qualification And Special Test Programs

– Worldwide Deployment AndMaintenance Programs

– Parts Acquisition And Screening

– Failure Analysis

– Destructive Physical Analysis

– High Reliability Production Specializing In Surface Mount Technology

– EMC/EMI Design Evaluation AndTest Programs

– Reliability And Maintainability Demonstration Programs

Engineering And ManagementConsulting Services

– Systems Engineering

– Design Assurance

– Program Management

– Reliability And Maintainability

– Quality Assurance And Parts, Materials And Processes Engineering

– Integrated Logistics Support

– Technical Manuals And Training Programs

– Program Documentation

– SETA And Operational Support

Payload Controllers And Data Processors

Power Systems Ground Support AndTest Systems

SEPSDPU RPU

FMDS MBS

C4I Systems

USMC Unit OperationsCenter (UOC)

Army Airborne Command

And Control System

(A2C2S)

Light Armored Vehicle

C2 Variant (LAV-C2)

Army Embedded GPSReceiver (AEGR)

RF And OpticalPayload Systems

ROEM

DB-110

WindSat

AMANDAS

Systems, Hardware And Software Development For Space, Avionics And Tactical Applications

Major Areas Of Expertise

Assurance Technology Corporation - Capabilities 2011 2

Corporate Overview

Established In 1969, Providing Space Systems Research and Development, And Reliability And Quality Assurance Consulting, First Units In Space In 1973

Steady Growth And Achievement Over The Past Forty Years, Applying Reliability, Quality And Systems Development Heritage To Space, Avionics And Ground Applications.

Annual Sales In Excess Of $80 Million With Approximately 350 Employees; And Over 100,000 Square Feet Of Facilities At Four Major Locations.

Corporate History

Major Areas Of Expertise

Space RF Payloads And Scientific Instruments

Payload Controllers And Processors

Optical Payload Systems

Embedded Realtime Software

Power Systems

Reliability, FMECA And WCA

High Reliability Space Parts Processing

Failure Analysis/ Destructive Physical Analysis

Ground Support And Test Systems

Systems Effectiveness/ Quality Assurance/CM

C4ISR Systems

Software Definable Radios

Engineering And Management Consulting

Documentation

Corporate Locations

Corporate OfficesResearch AndDevelopment, ConsultingCarlisle, Massachusetts

Software DevelopmentCocoa, Florida

Research AndDevelopment, ConsultingAlexandria, Virginia

SETA And OperationsSupport FacilityChantilly, VA

Systems Engineering, ConsultingHuntsville, Alabama

ATC Power SystemsMerrimack, New Hampshire

Space Tactical Systems ProductionAnd Test Services FacilityChelmsford, Massachusetts


ATC Development Experience Overview


Areas Of Software Expertise

• Software Definable Radios

• Communications

• Tactical Internet Command And Control

• Real Time Applications

• Embedded Controllers

• Data Acquisition And Processing

• Image Processing

• COMSEC/TRANSEC

• Windows Development

• UML

ATC Facilities And Equipment Overview

» ATC Facilities And Equipment Have Evolved Over A 40 Year History In Space, Avionics And Ground Systems Development For Over 100 Government And Civilian Customers

» These ATC State-Of-The-Art Facilities And Equipment Have Supported Over $1 Billion Dollars In Space/Aerospace Electronics Systems Development And Production

» ATC Facilities And Equipment Have A Demonstrated Ability To Support The Design, Development, Test, And Documentation Of High Reliability Electronic Systems For Space, Avionics And Ground Systems

Automatic MicrocircuitTest SystemsHigh Reliability

Production Facility

SETA Facility

Chantilly, Virginia

High Reliability Surface Mount Technology (SMT)Production Facility

Tenney Engineering Model 4D3 Thermal Vacuum

Chamber

Scanning ElectronMicroscopes

Die Bond (500x)

Metalization Step (10,000)

Real TimeX-Ray System

EMI Test Facility

Dynavac Thermal Vacuum Chamber

FLX2011 LBV Automatic SMT Placement System

BTU Pyramax 98NConvection Oven


Major Consulting Services

Reliability,Maintainability,Logistics Support

» Program Planning & Implementation

» Design Review And Tradeoff Studies

» Failure Mode, Effect & Criticality Analysis

» RMA Modeling, Prediction And Assessment

» RMA Demonstration Test & Evaluation

» Life Cycle Cost Analysis

» Integrated Logistics Support (ILS)

» Operations And Maintenance Manuals

» Training Programs

» Provisioning

» Computer Based Training And Diagnostics

Quality Assurance, Parts Engineering

» Parts & Materials Selection/Approval

» Procurement & Process Specifications

» Parts Application Review

» Failure Reporting Systems

» Quality Assurance Planning

» Quality Control Systems

» Production Systems Planning

» Vendor Surveillance/Pre-Cap Visual

Systems Engineering, Design Assurance

» Systems Requirements Analyses/Design Concept Development

» Enabling Technologies And Architectures Development

» Design Review / Automated Design Analysis

» Human Factors / Systems Safety

» Equipment Qualification Test & Evaluation

» Parts Screening & Qualification

» Destructive Physical Analysis

» Failure Analysis

» Scanning Electron Microscope (SEM) Analysis

» Material / Process Evaluation & Control

» Technical Reference Modeling (TRM) And Architectures

Engineering Documentation

» Proposals, Plans And Procedures

» Engineering Drawing Packages

» Technical Specifications And Reports

» Fabrication/Test Inspection Procedures

» CDRL/DID Implementation

» On-Line Documentation

Management Systems

» Program Planning / Management

» Proposal Preparation & Evaluation

» Operating Policies And Procedures

» Management Visibility & Control Systems

» Configuration & Data Management

» Network Management Systems (CPM/PERT)

» Cost/Schedule Control Systems (CSCS)

» Systems Engineering Management Plans (SEMP)


Space Flight Applications


Areas Of Space Software Expertise

• Embedded Controllers

• On Orbit Reprogramming

• Real Time Applications

• Data AcquisitionAnd Processing

• Image Processing

• VHDL Based Firmware

Space Systems Development Experience


History In Space


NAVSTAR (2)

Gravity Gradient II

MSD (2)

• Upper Stage/ Dispenser

LIPS

• Comm. Experiment, Solar Array Experiment

LACE• Laser Experiment

TLD

• Upper Stage/ Dispenser

Clementine

• Lunar Mapping

WindSat

ICM

• GPS Navigation

CRRES

DMSP

Space Shuttle

DSCS III

AIRS

APEX

GOES (12 launches)

GOES-R

POES

METOP

NPOESS

ST-7

Product Assurance

• Reliability Engineering

• Worst Case Analysis

• Quality Assurance

• Parts Materials and Processes

• Failure Analysis

• Radiation Hardness Assurance

• Thermal/Structural Analysis

ProgramDocumentation

• Specifications

• Technical Documentation Packages

• Plans and Schedules

• Technical Briefings

• Test Reports

• Configuration and Data Management

Parts Procurement And Processing

• Parts Selection and Control

• Parts Procurement

• Parts Screening

• Destructive Physical Analysis

• Parts Qualification Programs

Systems Engineering

Spacecraft Development

TLD Development

Secondary Mission Development

• Payload Data Management System (PDMS)

• Radio Frequency Systems

• Payload Technology

• On Board Processor (OBP)

• Power Converters

• Microcats Command and Telemetry System

• Advanced System Controller (ASC)

• Microcats Command and Telemetry

• Accelerometer Sensor Assembly

• SLDCOM IV Integrated Communications Systems

Satellite Systems Development And Support


Range, Ephemeris And GMT (REG) Unit

Developed Under Contract To The U.S. Naval Research Laboratory

ATC Accomplished The REG Design, Qualification, And Flight Units

The REG Contains 14 Plug-In PC Boards, Backplane, Bus Interface Unit And Redundant Power Converter

Fully Redundant, Radiation Hard SBP 9989 Microprocessor Based Spaceborne Computer

Refines Satellite Range Measurements, Computes Present Position (Ephemeris) And Covariances, Maintains Greenwich Mean Time (GMT), And Generates Commlink Tracking Reference Data

Range And Synchronizer Subsystem (RSS)

ATC Developed And Produced The RSS Power Converters

ATC Later Took Design Responsibility For The Entire RSS, Enhanced And Qualified The Design And Produced 7 Flight RSS Units And 4 Flight TDS Units

Major Design Enhancements Performed On EMI/EMC And Receiver Areas

The RSS Functions In A Multiple Satellite System, Providing:

– Intersatellite Range Measurement

– System Timing And Synchronization

– Intersatellite Data Transfer


Payload Data Management System (PDMS) – Subsystems

MSD

AT&CS Systems On Continuous Evolution Path

Continuous Architecture Improvement Based Upon Lessons Learned

Latest Enabling Technology, Always A Generation Ahead

Highly Reliable, Fully Redundant, Fail Safe, Critical Command Paths

Clementine

ICATS1973 • Pulsed Coupled Collector Logic (PCCL)

• Separate CMD/ZTLM Controller

• 5 Different Command Distribution, Telemetry Collection Boxes

MSD

Advanced ICATS1976

• Core Memories (4k x 16)

• On-Board Stored Command

• On-Board Telemetry Archive/Dump

• Re-programmable Commutator Local Commands

MICROCATS1984

TLD

LACE

• Extended Memory Processor Support For Centralized Command And Control GMT Service

AdvancedMICROCATS

1993

• 64k x 16 Core Memory

• High Speed Data Bus

• Memory/Control Box

• Reduced Box Count

AT&CS2000

TLD

• Advanced System Controller (ASC)

• Remote Interface Unit (RIU)

• Redundant 1750 Multi-Processor Architecture

• MIL-STD-1553 Data Bus

• Spacecraft Command Language (SCL)

ICM

WindSat

NTS 2

Advanced Telemetry & Command System (AT&CS) Evolution


Space Systems Development

High Technology Satellite Controller

MIL-STD-1750A CPU With 3.2 MIPS Throughput

1MEGA Word Global Memory

Spacecraft Command Language (SCL) Expert System Software Architecture

On-Orbit Reprogrammable

Intelligent 80C86 Controllers For MIL-STD-1553 Bus And Link Interfaces

Redundant, Radiation Hard Implementation Using SEM-E/ SMT-ASIC Technology

First Software Based Radio Developed and Fabricated by ATC

Function:

– Tunable UHF Satellite Transponder Provides Analog/Digital Repeater With Mailboxes for Store/Forward, Broadcast Capability, On Board Email

Development Languages: C and Assembly

Development Environment:

– Dual DSPs and One 8086 Processor

– Three Emulators Attached to Target

Software Challenges:

– All Software Modem

– Interprocessor Signaling

– High Reliability On-Orbit Loading

SLDCOM IVIntegrated Communications System (ICS)

Advanced System Controller (ASC)


Space Systems Development (Continued)

Modular Architecture - 500 To 3,600 Watt Average Output

Microprocessor Based; Readily Accepts Battery And Solar Array Technology Advances

On-Orbit Programmable

Direct Energy Transfer Architecture, Efficiency Maximized

Minimum NRE For New Applications

Reduced Power Block Being Considered For Smaller Satellite Applications

ATC Designed , Developed, Fabricated and Tested the Electronics System

VHF Experiment (VHFE) Electronics Power Block Controller (PBC)

Shunt #4

Shunt #3

Shunt #2

Shunt #1

Controller

VHFE RF Electronics

VHFE



ATC Developed The MAHRSI Electronic Assembly (MCEA) And MAHRSI Drive Electronics Assembly (MDEA) For The NRL Space Science Division (SSD)

The MAHRSI Experiment Is A Tethered Shuttle Experiment That Measures The Ultra Violet Characteristics Of The Earth’s Middle Atmosphere

MECA Employs Radiation Hard 80C86 Microprocessor Based Technology

Prototype And Flight Systems Were Produced And Qualified

Developed For USAF Phillips Laboratory

The Primary Radiation Effects Package On CRRES

Measured Total Dose (TD) And Single Event Upset (SEU) Characteristics Of Advanced Microelectronics Devices

Measured Radiation Environment

Highly Elliptical Orbit

14 Month Highly Successful Mission

CRRES Microelectronics RadiationEffects Package (MEP)

Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI)



Experiment Controller And Power Source Developed By ATC For Phillips Laboratory

System Senses Static Charge Build-Up On Spacecraft Exterior And Generates A Zenon Gas Plasma To Safely Neutralize Charge

Flown On A Defense Satellite Communications System (DSCS III) Satellite

Demonstrate Potential Of High Temperature Superconductor (HTS) Electronic Components And Subsystems In Satellite Applications

Quick Reaction Development (14 Months)

High Temperature Superconductivity Space Experiment (HTSSE)

Flight Model Discharge System (FMDS)

FMDS Controller Electronics

FMDS Plasma Source Electronics


Clementine

Nine Module SEM-E Packaged Spacecraft Controller

RH1750 With 512K Memory Module Provides Primary Processing

R3081 RISC Processor Used As Image Processor

Includes Integral Command, Telemetry, And Control Functions

Interfaces With Uplink/Downlink Transponder, Solid State Data Recorder, Reaction Wheels (4), Inertial Measurement Units (2), Power Subsystem, Valves, And Thrusters

Data Acquisition System (DAS)Deep Space Program Science Experiment (DSPSE)

Quick Reaction Program (10 Months) Including Proposal, System Design And NRL Integration

Four (4) Month Development Of Data Acquisition System (DAS) Including:

– 2,193 Lines Of C Code And 1,504 Lines Of Assembly Code For Experiment Control, Data Collection And Command & Telemetry

– Inclusion Of An Additional NASA Experiment Within 2 Months Of Delivery

– Fabrication Of A Test Unit With 2,500 Lines Of C Code To Emulate Ground Control

The Clementine Satellite Was Launched January 1994 On A Titan IIG

The Trajectory Was As Follows: 1.) 1.5 To 7 Days In LEO (Dependent On Launch Date) 2.) 27 Days In Transfer Trajectory To Enter Lunar Orbit and 3.) 2 Months In Lunar Mapping The Moon

The Primary Mission Was To Demonstrate BMDO Lightweight Technologies


Sensor ElectronicsPower Supply

(SEPS)

Atmospheric Infrared Sounder (AIRS)

AquaSpacecraft


Supports NASA’s Earth Observing System (EOS) Satellite

Provides Power For Loral’s Atmospheric Infrared Sounder (AIRS) Instrument

High Reliability, Dual Redundant Power Supply; Consists Of Two Identical Power Modules; Each Has A Complete And Identical Set Of Input And Output Interfaces

Power Converter Provides Simultaneous Outputs Of ±5V, ±12.5V, ±15.5V, +28V, And ±32V, With Overvoltage Protection And Current Limiting

Sensor Electronics Power Supply (SEPS) International Space Station (ISS)Interim Control Module (ICM)

Mission Overview

– Launch On Space Shuttle (Long Tunnel ODS Baselined) And Mate With ISS At Russian FGB

– Provide Re-Boost And Attitude Control Of ISS During Phase 2A - 7A (8A)

– One Year Operation (Propellant Is Life Limiting Factor), 3 Year Design Life

– De-Orbit At End-Of-Life (Permanent Control Module Operational Prior To De-Orbit)

– Maximum Use Of Existing Hardware

– Primary Control Using NASA Ground Assets

– NRL Engineering Node (NEN) Provides Mission Monitoring Through NASCOM

– EVA For 120V Converter Connection (Additional Power If Required After 4A)

– Single Fault Tolerant To Mission Success



Adaptive Multi-Mission Analog And DigitalAdvanced SBIFE-SBT (AMANDAS)

WindSat Mission Overview

Space Qualified S-Band Radio Receiver

Both Coarse And Fine Tuning Over 2-4 GHz Range

Both Wide Field Of View (WFOV) And Narrow Field Of View (NFOV) Capability

Both Continuous Wave (CW) And Pulse Code Modulation (PCM) Capacity

High Sensitivity With Low Phase Noise

4 Channel Sub-Band Tuner With On-Orbit Programmable Band Widths

Snapshot Mode For High Data Rates

Special Features:

– Demonstrate Polarimetric Radiometry

– Risk Reduction For National Polar-OrbitingOperational Environmental Satellite System(NPOESS)

– Space Test Program Satellite Bus

– Sensor To Shooter Direct Data Read-Out

Capability/Improvements:

– Measure Ocean Surface Wind Direction (Non-Precipitating Conditions)

– 3 X Improvement In Horizontal Resolution (Viz. SSMI)

– Secondary Measurements: Sea Surface Temperature, Soil Moisture, Rain Rate, Ice, And Snow Characteristics, Water Vapor

ATC Designed And Developed The RF Receiver And RF Digital Data Processing

Characteristics/Description:

– Measures Ocean Surface Wind Speed, Wind Direction, Using Polarimetric Radiometer On A Modified Satellite Bus, Launched Into A 830 km 98.7°Orbit By The Titan II Launch Vehicle


OscillatorSlice

BatterySlice

PilotfishSlice

Ch. A/Ch. BSlice

Ch. C/CommSlice

SolarArray

Power Control Board

Pilotfish Board Ch. A Board Ch. C Board

OverchargeProtection Circuit

Ch. B Board Common Board

Batteries

GroundStation

Remora

A Standalone, Synergistic, Non-Invasive, Self Supporting, Bolt On Satellite Experiment

ATC Designed, Developed The Receivers And C2 Subsystems And Also Integrated The Remora Payload


Power Processing Units (PPU) - Four PPU, Each Dedicated to a Separate Thruster, Provide The Required Voltages Necessary To Operate The Thruster

Micro Newton Thrusters Of The Disturbance Reduction System (DRS) For The NASA ST-7 Satellite Support Spacecraft Isolation From Disturbances Allowing Orbits To Be Maintained To A Precision 100 Times Greater Than Ever Before

The ST-7 Is A Pathfinder For The Joint ESA / NASA Laser Interferometer Space Antenna (LISA)

Digital Control Interface Unit (DCIU) - A Microprocessor Based Control System That Provides The Digital Command And Telemetry Interface With The Satellite Avionics And Controls The Thrusters By Adjusting Electrode Voltages, Colloid Flow Rates And Thruster Temperatures

The Power Processing Units (PPU) And The Digital Control Interface Unit (DCIU) Were Jointly Developed And Produced by Busek Corporation And ATC. The Electronics Were Packaged, Fabricated, Assembled, Integrated And Tested By ATC

Micro Newton Thruster


MPS-LO

SGPS-1 and 2

EHIS

30ev – 30 keVElectrons & Protons

Electrons: 50 keV – 4 MeVProtons: 80 keV – 12 MeV

Protons: 1 MeV – 500 MeVAlphas: 4 MeV – 500 MeVIntegral Protons >500 MeV

10 MeV – 200 MeV H+HeHeavy Ions To Iron

GOES-R Space Weather Sensor Suite

DPU

MPS-HI


GOES NO/PQ

Measures the Following:

– 0.5 to >4 MeV Electrons in 3 Integral Energy Bands

– 0.8 to 500 MeV Protons in 7 Differential Energy Bands

– 3.2 to 400 MeV Alpha Particles in 6 Differential Energy Bands


– 350 to >700 MeV Protons in 4 Differential Energy Bands

– 640 to 850 MeV/Nucleon Alpha Particles in 2 Differential Energy Bands

Field-Of-View:

– 34 Degrees Half Angle

XRS Telescope Measures X-Ray Flux in Two Wavelength Bands:

– 0.05 - 0.3 and 0.1 - 0.8 nm

3 EUV Telescopes Measure EUV Flux in Five Wavelength Bands:

– 5-15, 25-34, 52-65, 73-90 and 119-127 nm

Measures Low Energy Protons in 5 Energy Bands:

– 80-100, 110-170, 170-250, 250-350 and 350-800 KeV

Simultaneous Measurements in 9 Directions

Measures Low Energy Electrons in 5 Energy Bands:

– 30-50, 50-100, 100-200, 200-350 and 350-600 KeV

Simultaneous Measurements in 9 Directions

X-Ray And

Extreme UV

Sensor

(XRS/EUV)

MAGnetospheric

Proton Detector

(MAGPD)

MAGnetospheric

Electron Detector

(MAGED)

High Energy Proton

Alpha Detector

(HEPAD)

Energetic

Proton Alpha

Detector

(EPEAD)

ATC Designed, Fabricated, Calibrated and Tested the X-Ray and Extreme Ultraviolet Sensor (XRS/EUV), Magnetospheric Electron Detector (MAGED), Magnetospheric Proton Detector (MAGPD), Energetic Proton Alpha Detector (EPEAD) and High Energy Proton Alpha Detector (HEPAD)


A Major Source of “Space Weather Data” for Over 20 Years

GOES D-M

ATC Designed, Fabricated, Calibrated and Tested the Energetic Particle Sensor (EPS)

Sensor Configuration:

– 1 Telescope Containing 2 SSD‟s

– 3 Domes Each Containing 1 SSD Behind an Aluminum or Copper Moderator

– 1 Telescope Containing 2 SSD‟s and a Cerenkov Radiator Coupled to a PMT


– 0.5 to >4 MeV Electrons in 3 Integral Energy Bands

– 0.8 to >700 MeV Protons in 11 Differential Energy Bands

– 3.2 to 850 MeV Alpha Particles in 8 Differential Energy Bands

Energetic Particle Sensor (EPS) X-Ray Sensor (XRS)

ATC Designed, Fabricated, Calibrated and Tested the X-Ray Sensor (XRS)

Detectors:

– Dual Ion Chamber

– Minimum X-Ray Flux Generates Approximately 100 X 10-15 Amps

– A Strong Magnetic Field Sweeps Out Electrons Below ~4 MeV Which Would Otherwise Provide a “Large” Background Current

– Measures X-Ray Flux in 2 Wavelength Bands:

– 0.05 to 0.3 nm

– 0.1 to 0.8 nm

– Field-of-View:

– +/- 2 Degrees


TIROS/METOP Space Environment Monitor (SEM)

ATC Designed, Fabricated, Calibrated and Tested the Total Energy Detector (TED) and Medium Energy Proton Electron Detector (MEPED)

Detectors:

– Eight Curved Plate Electrostatic Analyzers Coupled to Continuous Dynode Electron Multipliers (CDEMs)

– Two Electron Telescopes Each Containing a Single SSD

– Two Proton Telescopes Each Containing Two SSDs

– Four Omni-Directional Domes Each Containing a Single SSD Behind an Aluminum Moderator


– 50 eV to >300 KeV Electrons in 11 Energy Bands

– 50 eV to > 140 MeV Protons in 18 Energy Bands


Rum Runner Spacecraft Mission Payload

RF Power Unit(RPU)

DigitalHardware Unit

(DHU)

RF Hardware Unit(RHU)

The Rum Runner Program Is a Follow on of the Perseus Spaceflight Payload Whereby the System Has Been Updated to Incorporate Newly Available Technology Enhancements. Additionally, the System Was Modified for Deployment in a Strenuous Avionic Environment. Modifications Included Ruggedized Packaging and Conversion to Forced Air Cooling

ATC Partnered With Titan Aerospace Electronics Division, Now a Division of L3 Communications, As a Subcontractor on Both the Perseus and Rum Runner Programs. The TAED Designed Electronics Were Packaged, Fabricated, Integrated and Environmentally Tested by ATC. The System Completed Production and Test in Late 2005 and Test Flights Were Initiated in 2006

RHU Contains 15 Separate Sandwich-Slice Modules Of 5 Functional Types:

– Up-Converter

– Local Oscillator, Low

– Dual Down Converter

– Compensation/Local Oscillator, High

– Built-In-Test-Equipment

DHU Contains 8 SEM-E Modules Of 3 Functional Types

– Digital Filter

– Digital Detector

– Control Processor Unit

RPU Contains Four Power Amplifier Channels Each Consisting Of Pairs Of:

– A Custom Hybrid Power Amplifier

– Hybrid Switches, Couplers, Attenuators And Loads

– An EMI Filter Assembly

Rum Runner Program


Input Characteristics

– DC Input Voltage: 22V to 36V

– Reverse Polarity Protection, Under-voltage Lockout, and Active Inrush Current Limiting

Output Characteristics

– Isolated DC/DC Converter with 7 Regulated Outputs:

– Overload and Short Circuit Protection And Common Mode Post Filtering on All Outputs

HD-1003 Star Tracker (DC/DC Converter)

Assurance Technology Corporation (ATC) Under Contract with BF Goodrich Company Designed, Developed, Fabricated and Tested the DC/DC Power Converter (PC) For the HD-1003 Miniature Star Tracker (MST)

– Meets High Reliability Space Standards (Operational System)

– 10 Year Mission Lifetime Reliability

– Class S or S Equivalent Parts

– 100 kRads Total Dose

– Latchup Immune – SEU Tolerant

– Less Than 1 Pound - Approx. 4.6” x 4.2” x 1.4” Volume

– 2 Boards, One Input - One Output

– Withstands 43 G‟s RMS Vibration

– Greater Than 65% Efficiency

– Fourth Generation Power ConverterOf Series

– First Generation Developed In 1987

– 87 Flight Power Converters Delivered


Lakewood Short Wave IR SensorFor NRL Upper Atmospheric Phenomenology Survey

ATC is the Lakewood Payload Prime Contractor: Payload System Engineering and Power Converter Design and Manufacture

Millennium Space Systems Spacecraft

Polar Orbit @ 1200 km, 2 Year Mission


Lakewood Sensor PayloadDelivered to Millennium Space Systems – March 15, 2010

Array Format: 640 x 512 pixels, 25 mm Pitch

Integrated Thermo-electric Cooler

Rad Hard Power Converter and Camera Electronics

Aperture 23.8 cm, F/10

DC/DC Power Converter

Star Tracker

IMU

SiC Telescope InGaAs SWIR Array and Electronics

Radiator

Optical Bench Assembly


CMOS Imager Experiment (CIE)

Developed by ATC in 20 months andDelivered to NRL in January 2009 forthe MISSE7 Experiment on theInternational Space Station.

Launched on the Space Shuttle STS-129,MISSE7 was Installed on ISS, andBecame Operational on 23 November2009. A 19 Month Experiment is Planned.

CIE is Characterizing the Performance ofIts Advanced CMOS Image Sensor in theSpace Environment.

CIE, a Self Contained Instrument, Includes a 1.2 Megapixel Imaging Array, Redundant Light Source and Light Source Monitor, Dosimeter to Monitor the Ambient Radiation Environment, an Image Controller, a Solid State Data Recorder and Embedded Processor for On-board Analysis of the Array Output, a Communication Interface for Command Upload and Data Download During on Orbit Operations, a DC/DC Power Converter, and a Radiator for Thermal Control. CIE Weighs Less Than 7 Pounds and Operates on Less Than 15 Watts of Power.


Near Real-Time

Imagery To Users

Sub-Aperture

Telescope

Combiner

Telescope

Geosynchronous Altitude

Free-Flying Constellation

Sparse Aperture

Configuration

Full Earth Coverage

On-Site 24-7

Multispectral

Low Rate Video

Revolutionary Imaging Technology (RIT)

The RIT Program Explores Concepts for Achieving Extremely Large, Effective Optical Aperture Diameters in Space

The Intelligence Payoff of Such a Capability Is the Ability to Capture High Resolution Imaging From Orbits That May Be As High As Geosynchronous

Program Elements Supported By ATC Include:

– Space System Concept Development

– Metrology Subsystem Laboratory Development

– High Altitude Sensor Testing

– Large Area Visible Focal Plane (LAVA) Development


Sub-Aperture

Telescope

Beam Combiner

Telescope


ATC Provided Electro-Optical System Engineering Support for the Concept Development Phase to Include:

– Developing the Optical Error Budget for a Sparse Aperture Telescope System

– Designing an Integrated Sensor Test Bed

– Developing Concepts for a Thermal Infrared Version of the Sensor

System Studies Conclude That Telescope Apertures From 40 Meters to Over 200 Meters Flown at Geosynchronous Altitude Would Provide Significant Intelligence Benefits

The Problem Is That Current Optical and Mechanical Technologies Are Heavy and Take up So Much Volume As to Precluded Launch Using Any Available or Foreseen Launch System

RIT Developed the Technology of “Sparse Aperture Telescopes” Which Included:

– A 40 Meter Diameter Sparse Aperture Telescope With Connected Sub-Apertures With Each the Size of the Hubble Space Telescope

ATC Provided Lead Engineer, Optical System Engineering, Optical Test Engineering, Mechanical Design, and Technician Support for This Phase of the Program

The Metrology and Control Test Bed Uses a Laser Metrology Technique to Measure and Control the Very Tight Positional Tolerances Acquired By the Sparse Imaging Optics

RIT 2-Aperture Test Bed Provides Experimental Verification of the Sub-Aperture Phasing Concept


Space System Concept Development

Metrology Subsystem Laboratory Development

Metrology And Control Test Bed

High Altitude Sensor Testing

In the Spatial Regime, Sparse Apertures Behave Much Like Electrical or RF Notch Filters Behave in the Temporal Regime. Certain Frequency Bands, Either Spatial or Temporal, Are Not Transmitted by the System. In the Case of a Sparse Aperture Telescope the Filtering Causes Artifacts in the Resulting Image. The Artifacts Are Scene Dependent. Because the Scene Is, in Some Sense, Random and Non-stationary, the Artifacts Are Random and Non-Stationary

The RIT Team Developed Image Processing Algorithms to Mitigate the Artifacts

A High Altitude Image Collection Campaign Was Undertaken to Provide Realistic Imagery for Algorithm Verification, Evaluation, and Tuning

ATC Provided:

– System Engineering Support for Platform Selection and Sensor Concept Development

– System Performance Characterization

Large Area Visible Focal Plane (LAVA)

Early On, the RIT Program Realized That Large Area Focal Planes Suitable for Use With Sparse Aperture Optical Systems Were Not Available

RIT Developed a Visible Light Sensitive Array Having 4000 x 4000 Pixels on a 5 Micron Pitch. Each Pixel Was 12 Bits Deep, and the Array Could Run at a Frame Rate of up To 17 Frames Per Second. A to D Converters Were Built Into the Array Along Two Edges So That the CMOS Exposure Masks Could Rotated and Stepped to Build up a Seamlessly Stitched 8000 x 8000 Pixel Array. The Sensor Design and Fabrication Work Was Contracted to Rockwell Scientific

ATC Participation Included:

– Development of the Technical Specification for the LAVA Sensor Chip

– Design, Procurement, Integration, Testing and Delivery of a Digital Camera System Incorporating the Focal Plane Interface Board



Gondola Equipped With 2-Axis Gimbal, Communications And

Battery Systems

Focal Plane Interface Board

LAVA Sensor Chip

Five Band Multi-Spectral Camera System

Camera Control And Image Capture System

Sample Image2,000 Feet Altitude

Sensor System Experiment

Overview

– Determine If the Color Bands of a Multi-Spectral Image Are Taken Sequentially, How Much Time Can Elapse Between the Frames Before the Information Content Begins to Degrade

– Develop a Flight Test With a Camera Head Incorporating 5 Individual Cameras, Four With Nearly Identical Optical Properties and One Wide-Angle Camera to Provide Image Context

ATC Provided:

– Technical Expertise in the Platform Selection Process (Antonov AN-2 Biplane)

– Vibration Environment Characterization

– System Design Capable of Capturing and Storing Imagery From 5 Time-Synchronized CMOS Cameras With a Format of 1280 x 1024 Pixels at 10 Bits Per Pixel at a Rate of 20 Frames Per Second. In Addition the System Was Sized to Capture 2nd Generation LAVA at 4000 x 4000 Pixels, 12 Bits Per Pixel at a Rate of 17.5 Frames Per Second for 90 Minutes of Continuous Operation

Discriminating Interceptor Test Program (DITP)

Overview

– Develop And Demonstrate a Combined Laser Radar, Passive Infrared Interceptor Head That Could Be Launched on a Black Brandt Sounding Rocket (Integrated Optical Subsystem (IOS))

– The Interceptor Would Demonstrate Its Ability To Acquire Long Range Targets That Deployed Multiple Decoys and Discriminate Those Decoys Within a Timeframe That Permits Interception of the “Real Warhead”

ATC Participation:

– Develop the IOS Specification and Work With Optical Systems Vendors Throughout the Design Process

– Generate the Specification for the Beam Steering Mirror

– Specify Mirror Coatings and Conduct Laser Damage Testing


RIT Transitional Programs

Integrated Optical System (IOS)

Orbital Express Program

Overview

– Study Concepts for Large, Robotically Deployed, Space Optics, for Passive and Active Target Acquisition for Use in Space, and for Flash 3D Proximity Imaging

ATC Contribution:

– Bring Forth the Concept of Segmented Aperture Optics Using Wavefront Sensing and Active Mirror Surface Figure Control to Maintain Full Optical Imaging Performance in the Presence of Static, Dynamic, and Thermal Disturbances

– Perform Trade Studies Between Visible and IR Sensors, Between Passive Sensors and Laser Radar, and Between Scanning Laser Radar and Imaging Laser Radar

Star Tracker (Foreign Comparative Testing Program)

Overview

– Test a Star Tracker Designed and Built by the Danish Aerospace Company TERMA for Possible Use on US Government Satellites

– Develop a Comprehensive Performance Test Laboratory Capable of Ascertaining That the TERMA Star Tracker Can Meet All of the Requirements of the US Government Programs

ATC Participation

– Developed the Concept of the Star Simulator Then Specified the Unit for Procurement

– Provided Technical Contract Monitoring, Procurement of a NIST Traceable Photon Counter, and Calibration of the Simulator

– Specified and Selected Optical Alignment Equipment

– Assisted in the Performance Testing and Data Reduction Phases


RIT Transitional Programs

30m On-Orbit Optical Assembly Concept

TERMA Star Tracker

(Without Optical Baffle)

Camera Head Electronics

Date Handling Unit

Active Mirror Telescope Actuator Control Electronics Module (CEM)

ATC Designed, Fabricated And Qualified The Actuator Control Electronics Module (CEM) To Provide Multiplexing Functionality For The Addressing, Operation And Control Of 414 Actuators Used To Correct Mirror Self-Deformation And System-Level Wavefront Error

Flight Unit CEM, Flight Spare And Spare Circuit Card Assemblies Delivered In 1st Quarter Of CY 2006

Performed Electrical / Mechanical Design; Mechanical CAD; Thermal / Structural And Worst Case Design Margin Analyses; Parts Procurement And Screening; Fabrication, Assembly And Test


Software Defined Radio Overview

ATC Has Developed SoftwareDefined Radios For SpaceApplications Since 1989

The Most Recent, SoftwareReconfigurable Payload (SRP),Is Currently Being DevelopedBy ATC And The NavalResearch Laboratory

RF/Digital Payload (RDP)Was Developed in 2007/2008 for The Operationally Responsive Space (ORS) Program Under A BAA Award

The RDP Is A Prototype Flight Unit With Three Processors, One Transmitter and Receiver, Power Converter andDigital Transceiver

Both SRP And RDP Software Use A Modified JTRS Operating Environment. RDP was Demonstrated with Two Test Waveforms. A SGLS Waveform Was Prototyped in MATLAB

The Unit Is Sized to Add An INFOSEC Module and Two More Transmitter/Receiver Modules

The RDP System And Its Predecessors Provide Unique, Proven Advanced Technologies For SASSA 1.0 And 1.5


Includes:

– Compact Tunable RF Transceiver

– Wideband Digital Transceiver

– Reconfigurable Low Power Computing Resources (3)

– RDP Infrastructure Software

– Web Based Ground Station Control Software

– RDP Assembly with Power Converter

ORSTECH Advanced On-Orbit Software Reprogrammable RF/Digital Payload (RDP)

Background

– High Priority Responsive Space Missions Enabled Through the Development of Space Based Software Defined Radio and Low Power Processing Technologies

– On-Demand Tactical Mission Capability using In Theater and On-Orbit Reprogrammability

– Flexible and Agile in Bandwidth and Frequency

– Directly Applicable to 48% of the Missions Identified by the COCOMs for TacSat 3 and 4

– Use of Open Standard Spacecraft Interfaces


SASSA Demonstration System

SASSA Demonstration System Is Hosted on Two Spacecraft:

– Host 1 Includes Radar Warning Receiver (RWR) and Dedicated SASSA Communication (DSC) Sensors. Four Additional Sensor Locations Are Unused

– Host 2 Includes RWR and Optical (SSU) Sensors

SASSA Space Segment Is Centered Around a Common Interface Unit (CIU) That Provides a Single, Simple Spacecraft Interface That Encrypts Downlink Data and Decrypts Uplinked SASSA Commands. CIU Configured For Six SA Instruments.

SASSA Ground Station Provides Mission Planning, AFSCN Interface, Host Interface, Commanding/Telemetry/Mission Data Processing With Embedded Cryptography


Avionics And Tactical Military Systems


Avionics And Tactical Systems Development Evolution

LIPSSatellite

Uplink

Command

Encoder

Receiver

(ULCER)

TRE

Concept Exploration

And VerificationTechnology Transfer To Industry

• MATT

• IDM

• BMATT • Radiant Hail

4 GenerationsOf Equipment

MSDSatellite

• Success Radio (Army)

• Constant Source (AF)

• TRE/TRAP (Navy)

JSTARS

AH-64UH-60OH-58D

F-16

Abrams

A/OA-10

CH-47

E2-C

MLRS

• Raider

• A2C2S• EUT

• AEGR

Advanced

Technology

LAV AAV UOC

UH-1N

• GBS

• JTRS

HLS WHCA

1982 1984 1986 1988 1990 1992 1994 1996 1998 2000 2002 2004

GBSReceiver

C-SAW

BMATTRadiant

Hail Raider

End UserTerminal

(EUT)

AEGR

JCIT

AAV / LAV

WHCA

HLS

UCIM

A2C2S

MATT IDM

HAIPIS

HSV

JTRSSINCGARS

INC

Platforms Supported:

Shadow

SRP

2008

• SRP


Communications Systems Product Evolution

JTRS Waveforms

• SINCGARS/ESIP

• (INC) 188-220

SLDCOM IV Integrated

CommunicationsSystems (ICS)

Multi-Mission Advanced Tactical Terminal (MATT)

Joint CombatInformation

Terminal(JCIT)

Tactical ReceiveEquipment

(TRE)

Enhanced Briefcase

MATT

Single Channel Radio

Early Software BasedCommunications

Technology

Software Definable Radio (SDR) Technology Evolution

Improved Data Modem

(IDM)

HeritageWaveforms

• SINCGARS/SIP

• HAVEQUICK II (VOICE)

• HF SSB

• VHF ATC

• VHF AM

• VHF FM Public Radio

• ATC HF Data Link

• UHF AM/FM PSK LOS

• TRAP

• TADIX-B

• TIBS

• UHF DAMA SATCOM (Partial)

• HF/VHF/UHF Scanning JTRS Test Suite

ATC Waveform Development System (V2)

Waveform Development System (V1)


Technical Approachl Leverage OSD and ONR Funded Concept Studies and

Technology Demonstrations (STAFE)l Evaluate Mission Needs, System Requirements,

Enabling Technologies and Candidate Architecturesl Develop Representative Application Software For

Evaluation:l Communications Relay (VHF/UHF) – IP Routingl Anti-Jam Filter – AIS Receive

l Develop Functional Prototype To Prove The Concepts and Technologies

l Develop Integrated Prototype To Further Advance Technologies

Military Relevance/Operational Impact

l Flexible: On-The Fly Reconfigurable, Multiple, Simultaneous Missions And Applications in A Single Payload.

l Extensible: Rapid Payload Upgrades In Response To Changes In Threats, Missions

l Modular: Additional Capabilities Can Be Added

l Joint/Interoperable: Joint Standards – Formats/Protocols

Mission Areas Addressed

l Baseline: Communications –Voice, Data, IP Routing, Signals Intelligence (VHF/UHF), ECCM

l Near Term: Reconnaissance, Target Identification/Designation, Battle Management, Sensor Support – CBRNE, other.

Shadow UAS Pod

Software Reprogrammable Payload (SRP)


Printer

(1)

Maneuver Commanders Environment (MCE)

Communications Segment

Links

HAVEQUICK II

SINCGARS/SIP

TADIXS-B/TRAP

TIBS

SATCOM/DAMA

GPS

HF (ARC-220) *

EPLRS *

NTDR *

SCDL Echo

Civilian LawEnforcement

Aviation

Maritime

* Discrete Implementation

JCIT #1

ARC-220

VHF RFM

JCIT #2UHF RFM (1)

AIM

EPLRS

NTDR

LAN

• • •

Workstations (1-5)

CPU

1a/1b

Power

External Power

A2C2SLoads

CPU

2a/2b

Matrix Switch

(1)

EMI Filter

Assembly (1)

Circuit Breaker

Assembly

Power Conversion Unit A (1)

Power Conversion Unit B (1)

Battery

Aircraft Power

NetworkInterface Unit

(NIU)

Central Display

Smart

Media

(1)KY-100

Army Airborne Command And Control System (A2C2S)

A2C2 S is a UH60 Command and Control System With Computer Controlled Power, Comm, and Maneuver Elements

Development Languages:

– ADA, C and Assembly


– PPC, PIC, 68356, Pentium, Sun, 320C54 DSP

– VxWorks, Assembly, Solaris, NT


– Software Radio With Multiple Processors Executing Waveforms

– Inter-processor Signaling

– High Reliability Power Waveforms


Multipurpose SoftwareDefinable Radio (SDR)

Provides Multi-Channel RF,INFOSEC, Key ManagementAnd Application Processing

Multiple User Interfaces

Programmable Waveforms

Development Languages: C, C++


– 68 Processors Including PPCs, 68356, 320C54 DSPs

– VxWorks, DSP JTAG Emulator


– Software Radio With Multiple Processors Executing Waveforms

– Multi Radio-I/O Resource Allocation

– Security Subsystem Design With Bypass

Joint Combat Information Terminal (JCIT)

RedModules Red/Black

Modules BlackModules


GPS VME Card

GPS Engine

Army Embedded GPS Receiver (AEGR)

Embedded GPS Receiver for ABRAMS M1A2 SEP Tank

VME Single Slot Module Plugs In Host and Provides Time and Location

Precise Time and Position Service

Development Languages: C


– 68356

– VxWorks


– Critical External Timing Events

– Interface to SINCGARS Radio, PLGR GPS, HQII Radio

– Tank Failsafe Interface


4-Way Switch

The Four-Way Switch Allows An Operator With A Single Headset Or Handset To Hear The Receiver Outputs From Any One, Two, Three, Or Four Military Radios Simultaneously, And Quickly To Select Any One Of The Radios For Transmission

The Switch Is Compatible With The Standard Military Radio Handset, Or With The Racal Headset That Is Used With The Thales PRC-148 M-BITR Radio, Or With Some Other Headsets

Supports SINCGARS, PRC-117, PRC-150, And Similar Radios

The Switch Can Be LocatedUp To Fifteen Feet From TheFour Radios, And TheOperator Can Be LocatedUp To Fifteen Feet FromThe Switch


C4I Systems


Integrated C4I Achievements To Date


Antennas

• SATCOM (Aircraft)

• GPS

• LOS (3)(Mission Kit)

C4I Systems Development


JCIT• Four Programmable Radios

a) FH And CT SINCGARS Voice/Data

b) VHF to UHF Scan Function

c) SINCGARS Standard Data Mode

d) UHF Voice

e) Intel Broadcasts (TRAP And TIBS)

f) Civil (Maritime, Air Traffic, Police, Fire)

g) HF Voice (Future Use)

• Fifth Radio Is A Dedicated 802.11 Link (Wireless LAN)

• Dedicated GPS Receiver

ICS

PSC-5

Laptop

• Common Application Software

– C2PC

– FalconView

• 10/100 Base-T Ethernet

UH-1N C2 Demonstration Package Unit Operations Center (UOC)

High Mobility Multipurpose Wheeled Vehicle (HMMWV) With SICPS V4 RWS S-832

5-Ton ConfigurationWith Large SICPS (LSS) 3-1 Expandable Shelter

Interim Fast Attack Vehicle (IFAV)

C4I Systems Development (Continued)

LAV C2 On The Move

Interior View

Light Armored Vehicle (LAV)C2 Variant Program

JCIT (2)RFM

AAV-C7 ATD

Interior View

Assault Amphibious Vehicle (AAV)C2 Variant Program


Universal Communication Interface Module (UCIM)

UCIM Capabilities

UCIM Turns A Stovepipe C2 Platform Into A Flexible, Robust, Quickly Reconfigurable, Network Converged C2 System

Scalable, Network Converged UCIM System Provides Integrated Access To Voice, Data And Video C4ISR Information.Features Include:

– Access To Platform Assets Via Voice Over IP Net

– Enclave To Enclave Net Extension

– Radio Cross Banding

– Conferencing

– Remote Radio Control

– On The Move Functional Reconfiguration

– Inter And Intra Platform Cosite Mitigation

Provides Scaleable, Modular Hardware/Software That Supports Platforms Ranging From 2 Operator Systems, To Large Distributed Systems With Multiple Platforms And Hundreds Of Operators

Enables Common Tactical Operational Understanding Of The Battlespace And Accelerates Battle Planning, Command And Decision Making

Common UCIM Solution Readily Tailored To A Wide Range Of USMC And Navy C4ISR Platforms

Platform PMs Can Integrate Radio, Antennas, Cosite, Network, C2 Applications And Power Using UCIM

Decreases C4ISR Platform Costs, Improves C4ISR Platform Capabilities And Provides A Transition Path From Legacy Radios To JTRS Radios

UCIM Accomplishments

Capabilities Set Demonstrated During Limited User Evaluation (LUE) Of LAV-C2, HMMWV And UH1 In October 2004

Delivered Built To Print “Technical Data Package”

Software Uses Open Standards-Based Design Thereby Enabling Future Upgrades

Platform Integration Packaging

Enclave RackRadio Rack Radio/Computer Rack

Basic Remote Controller (BRC)

Intercom Radio Interface (IRI)

Module

Matrix Switch Assembly - (MSA)

Receive Tunable Filter - (RTF)

Keyboard Video Switch Matrix -

(KVSM)

KVSM Control Head

Fast Ethernet Switch - (FES)

Firewall Router Module - (FRM)

Symmetrical Digital Subscriber

Line - (SDSL)

Plain Old Telephone

System - (POTS)

Power System

Memory Stick Interface Module


Reconnaissance Surveillance And Targeting Vehicle (RST-V)

ATC’s Participation With The RST-V Program Was A Quick Reaction Tasking With The Marines To Build A Shock Isolated / Ruggedized Rack Of Communications Gear That Fit In The Rear Of The RST-V Crew Compartment Behind The Driver

The Communications Gear Included:

– EPLGR With PRC-117

– PRC-150 Radio

– EPLRS Legacy Radios

– Basic Remote Controller (BRC) Unit

– Fast Ethernet Switch (FES) Module

– Intercom Radio interface (IRI) Module

– Firewall Router Module (FRM)


Homeland Security

In the Late 1990’s ATC Was Instrumental in Development and Operation of an NRL Satellite Insertion Vehicle

This Led to the InfraLynx Concept of Combining Wideband Satellite Connectivity With Local Communications Requirements

InfraLynx Integrates the Ability to Provide Mobile Remote Access to Satellite Wideband With Local Communication Infrastructures to Achieve Phone, Cell System, Fax, and STU, Internet Service (Commercial Internet, NIPRNET and SIPRNET), Voice Over IP and Military and Civilian Communications Crossovers Services

In 2002, the HLS ACTD Was Implemented to Define, Refine, and Transition Technologies and Concepts of Operation That Significantly Increase the DoD Homeland Security Responsiveness in Consequence Management, Crisis Response, Deterrence, Prevention, and Intelligence Coordination

These Systems Provided an Immediate Response Capability, Rapid Reconstruction of Communication Infrastructure, Land Mobile Radio Interoperability, Streaming Video, and a Full Command Post (Incident Command Center)

A Number of Vehicles and Different Communications Packages That Have Been Developed and Fielded Based Upon These Concepts


HLS ACTD

InfraLynx

InfraLynx

Immediate Response Capability

– Turn Key System – Self Contained

– On Station and Operational in Conuswithin 24hrs

– Airlift May be RequiredTo Meet Deployment Times

Infrastructure Reconstruction:

– Wideband Satellite Connectivity

– Full Suite of Military and Civilian

– Communications Equipment

– Phone Lines (POTS), Fax, STU (Commercial and DSN)

– Internet Service (Commercial Internet, NIPRNET & SIPRNET)

– Net Centric Voice Over IP (VOIP) Connectivity

– Allows Central HQ to Communicate to Field Agents Seamlessly With Existing Conventional Communications (HF/VHF/UHF/800MHz)

Full Command Post (Incident Command Center)

– Will Support up to 30 Personnel in Tent or Rigid Shelter


Unmanned Aerial Vehicle (UAV)

Interior Views

Dragon Warrior Ground Station (DWGS)

ATC, In Conjunction With the Naval Research Laboratory (NRL), Produced a Mobile Ground Station for Control of the Dragon Warrior Unmanned Aerial Vehicle (UAV)

The Ground Station Is Integrated Into a Suburban. The Custom Center Console Houses Radios, a Scanner and the Emergency Lighting and Siren Control

In Addition, the Rear of the Vehicle Contains Two Custom Racks That House the Computer Equipment That Controls the UAV Flight and Receives the Video and Data From the UAV


Chemical Biological Incident Response Force (CBIRF)

The Chemical Biological Incident Response Force (CBIRF) Was Formed by the Marine Corps System Command (MARCORSYSCOM) Several Years Ago to Help Respond to Disasters That Include a Building Collapse, or a Chemical or Germalogical Attack

ATC Participated in the Development of a Solution That Gave This New Team a Interoperable Communication Platform That Included Both Military and Civilian Communications

In Addition to Voice Communications, the System Takes the CBIRF Sensor Data and Retransmits It Over the Satellite Back to Their Main Command Post


Federal Emergency Management Agency (FEMA)

The Federal Emergency Management Agency (FEMA) division of the Urban Search and Rescue Team (USRT) has twenty eight task forces across the country

These task forces respond to any technical rescues such as confined space, collapse, high angle and trench rescue

ATC worked with NRL to develop a mobile communication suite that provided the USRT with on-the-move Internet, television, and telephony reach back

The Suburban contains a custom center console that houses seven different radios, a scanner and the emergency lighting and siren control

The rear of the vehicle has two custom racks that house the computer equipment, multiple satellite phones, VOIP phones, vehicle tracking hardware and power system

Interior Views

Rear View


Optical Systems


Read-Out Electronics Module (ROEM)

Provides Unprecedented Night Reconnaissance Capability And Sensitivity

Low Noise Electronics Read Out A High performance Four Color 2880x12 Detector Focal Plane Array

Digitizes 48 Channels Of Multiplexed Video Data At 260 Detectors Per Second

Provides On-Board Programmable Time Delay Integration, Gain, Offset, And Scene Based Offset Correction To Each Pixel

Digitally Multiplexed Fiber Optic Output Uses 1.06 GBPS Fiber Channel Standard

Cryocooler

Image ProcessingElectronics


Advanced Digital Imagery Camera System (ADICS)

High Performance, Multi-Platform Daylight Mapping System

Provides Resolution And Area Coverage Rates 6 – To 10 Times Competing Systems

– Coverage Of Up To 600 Sqmi/hr

– Nominal Ground Resolution Of 6 in. From 10,000 Ft.

All Digital Processing Chain From Focal Plane To Fibre Channel Digital Mass Storage

8196 Pixels With 96 Stages Of TDI, 10 Bit Pixel Data, Up To 32,768 Lines Per Frame

Programmable Operation For Wide Range Of Platforms

Full Kinematic Subsystem For Geolocation To The Pixel Level

Operator Station (PC)

Data Handling Unit (DHU)

EO Camera


Ground Support Segment

Reconnaissance Management System

Global MotorPower Amplifier

E/O OpticsGimbal

Internet Link

EO/IR Dual Band Reconnaissance System (DB-110)

Low Cost Dual High Resolution Camera System Designed For Tactical And High Altitude Standoff Applications

Digitally Controlled Gimbal System Designed For Severe Vibration Environments

Integral Reconnaissance Management System Compatible With Solid State Recording, Digital Tape Recorders, And Digital Data Links

Ground Test Set Provides Real Time Image Processing And Display Of Images And Auxiliary Data Via Internet Compatible Protocol


Airborne Multi-Camera Synchronized Real-Time Imaging System (AMSRIS)

Camera Array:

– 5 Silicon Imaging 1300 visible CMOS cameras; 1280 x 1024 x 12 bit pixels

– User selectable „C-mount‟ optics (Schneider Optics)

– Camera Link electronic interface

Frame Grabbers:

– 5 IO Industries, DVR Express CL160 video recorder boards

– Synchronized to within + 1.0 msec.

– Direct write to disk storage array, bypassing control PC

Computer:

– Purpose is low rate camera control and data post-processing

– Rack-mounted single board PC with passive PCI backplane

– Windows XP

Data Rates, Data Storage:

– 42 image frames per sec per camera in free run mode

– 21 image frames per sec per camera in sync mode

– Each frame of each camera has time tag embeddedin the frame

– Correlated GPS stream stored along with the frames

– 10 SCSI disk RAID 0 for real time storage,1.6 terabyte capacity

Ground Station:

– Similar PC with RAID controller

– Used for archiving and image processing

Roll Axis Stabilization Gimbal

AMSRIS Installed On Antonov AN-2 Airplane


Medical Technology Equipment


Viscosity Measurement Instrument (VMI)

Viscosity Measurement Instrument (VMI)

Provides Measurements Of Viscosity Of Body Fluids To Benefit Fertilization Of Humans, and For Use In Animal Husbandry

Empirical Data Demonstrates Accuracy To Greater Than 95% Of True Viscosity

Digital Readout Displays Viscosity Of Measured Sample

Ruggedized For Use In Farm (Barn) Environment As Well As Doctor’s Office / Hospital

Supports Data Profiling Of Individual For Projected Peak Periods Of Fertility

Testing at The University Of Vermont School Of Animal Husbandry Showed Use Of Instrument Increases Bovine Fertilization By Twice That Of Current Procedures

Viscosity Measurement Instrument (VMI) (Cystic Fibrosis)

Research Has Indicated A Correlation Between The Viscosity Of Meconium And The Probability Of Contracting Cystic Fibrosis (CF)

The VMI Has Been Calibrated For Sensitivity To This Sensor Material And Is Accurate To 1% Up To 60,000 cSt

An Infant Is Unlikely To Have CF If Viscosity Is Less Than 50,000 cSt. Likelihood Increases With Measurements Greater Than 65,000 cSt

VMI Can Be Used As Diagnostic Tool To Preclude Expensive Blood Work In Healthy Infants While Indicating Those Infants That Should Undergo Further Testing

100,000

75,000

50,000

25,000

cSt


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