Range, Ephemeris and GMT (REG) Unit

• 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
• 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

CRRES Microelectronics Radiation Effects Package (MEP) Program Participation

• Developed By ATC For NRL And Phillips Laboratory
• The Primary Radiation Effects Package On CRRES
• Measured Total Dose (TD) And Single Event Upset (SEU) Characteristics Of Microelectronics Devices For The 1990's
• Measured Radiation Environment
• Highly Elliptical Orbit
• 14 Month Highly Successful Mission 7/90 - 10/91

Range and Synchronizer Subsystem (RSS)

• The RSS Functions In A Multiple Satellite System, Providing:
• Intersatellite Range Measurement
• System Timing And Synchronization
• Intersatellite Data Transfer
• 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 Were Accomplished In The Packaging Design, EMI/EMC And Receiver Areas

Power Block Controller

• 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

Advanced System Controller (ASC)

• 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

Deep Space Program Science Experiment (DSPSE)

• 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

Clementine Radiation Experiment

• Quick Reaction Program (10 Months) Including Proposal, System Design And NRL Integration
• Four (4) Month Development Of Data Acquisition System (DAS) Including:
• 2193 Lines Of C Code And 1504 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 2500 Lines Of C Code To Emulate Ground Control

SLDCOM IV Integrated Communications System (ICS)

• Tuneable UHF Receive/Transmit System (225-400 MHz)
• Provides Analog And Digital Repeater, Digital Store And Forward, And Uplink/Downlink Format, Modulation And Rate Conversion
• Supports Scheduled Broadcasting, And Provides E-Mail System
• Modular Capabilities Enable Integration On Host Platform; Or Use On Free Flyer With Comms, TT&C, ACS And EPS Management In One Box
• Quick Reaction Development (11 Months)

Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI) Program

• The MAHRSI Experiment Is A Tethered Shuttle Experiment That Measures The Ultra Violet Characteristics Of The Earth's Middle Atmosphere
• ATC Developed The MAHRSI Electronic Assembly (MCEA) And MAHRSI Drive Electronics Assembly (MDEA) For The NRL Space Science Division (SSD)
• MECA Employs Radiation Hard 80C86 Microprocessor Based Technology
• Prototype And Flight Systems Were Produced And Qualified

High Temperature Superconductivity Space Experiment (HTSSE)

• Demonstrate Potential Of High Temperature Superconductor (HTS) Electronic Components & Subsystems In Satellite Applications
• Quick Reaction Development (14 Months)

Flight Model Discharge System (FMDS)

• Experiment Controller And Power Source Developed By ATC For Phillips Laboratory
• System Autonomusly Senses Static Charge Build-Up On Spacecraft Exterior And Generates A Zenon Gas Plasma To Safely Neutralize Charge
• Launched On A Defense Satellite Communications System DSCS II Satellite In 1995 And Has Performed Flawlessly To Date

Sensor Electronics Power Supply (SEPS)

• Supports NASA's Earth Observing System (EOS) Satellite; Space Borne, Global Observation System Designed To Obtain Comprehensive Long Term Measurements Of Earth Processes Affecting Global Change
• Provides Power For Loral's Atmospheric Infrared Sounder (AIRS) Instrument; Uses Measurement Technique Based On Passive IR Remote Sensing Using A Single, High Spectral Resolution Nadir Viewing Grating Spectrometer Operating In The 3.7 - 15.4 mm Region
• High Reliability, Dual Redundant Power Supply; Consists Of Two Identical Power Modules; Each Of The Modules 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

Perseus Spaceflight Payload

• Complete Spacecraft Mission Payload Consisting Of Four Functional Subsystems:
• RF Hardware Unit (RHU)
• Digital Hardware Unit (DHU)
• RF Power Unit (RPU)
• Digital Power Unit(DPU)
• RHU Contains 11 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
• DPU Provides Compatible Interfaces With 4 Spacecraft Primary Power Buses And Provides Regulated DC Power To The Perseus Subsystems In Redundant Configuration Response To Power Bus Activation Commands

Magnetics Bearing Subsystem (MBS) Electronics

• Microprocessor Based (TMS 320C40) Controller For Precision Magnetic Bearing Subsystem; Advanced Technology Avionics Application To Be Demonstrated In Late 1994 Flight Tests
• Light Weight (13.3 Lbs.) Modular Design Features Dip Brazed Housing; Liquid Coolant Accommodates Operation Over A Wide Temperature Range
• Digital Interface Module Provides Data Acquisition, Housekeeping And Watch Dog Timer; System Interface Provided By Fiber Optic Module
• Caging Module Controls Caging Mechanism; Resolver Module Provides Interface To Absolute Position Resolver
• Torque Motor Drive Module Controls 3 Phase Brushless Motor; Three Actuator Modules Control 6 Axes Of Motion
• Switching Power Converter Synchronized By The Microprocessor Provides Multiple Outputs Of +5V, ±15V And ±80V, Undervoltage Protection And Current Limiting

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