Morehead State University

1.0 PROGRAM MANAGEMENT BUSEK, THE PROPULSION SYSTEM PROVIDER, SHALL MANAGE THE PROPULSION SYSTEM DEVELOPMENT. THE BUSEK PRINCIPAL INVESTIGATOR (PI) SHALL BE DR. MICHAEL TSAY. HIS EXPERIENCE AND QUALIFICATIONS CAN BE FOUND IN THE ATTACHED RESUME. THE PI SHALL MANAGE ALL ASPECTS OF THE TECHNICAL, BUSINESS, SUBCONTRACTS AND ADMINISTRATIVE REQUIREMENTS OF THE PROGRAM INCLUDING THE BUDGET AND SCHEDULE TO ENSURE A SATISFACTORY COMPLETION OF THE PROGRAM ON TIME AND WITHIN BUDGET. THE PI SHALL WORK CLOSELY WITH MSU AND THE ENTIRE LUNAR ICE CUBE TEAM AND PARTICIPATE IN ALL TECHNICAL INTERCHANGE MEETINGS, REVIEWS AND CORRESPONDENCE. 2.0 PROPULSION SYSTEM REQUIREMENTS AND SPECIFICATIONS BUSEK SHALL DEVELOP THE PROPULSION SYSTEM REQUIREMENTS AND SPECIFICATIONS. WORKING WITH THE TEAM, BUSEK WILL DEFINE THE PERFORMANCE REQUIREMENTS, FUNCTIONAL REQUIREMENTS, INTERFACE REQUIREMENTS (MECHANICAL, THERMAL, ELECTRICAL, HARNESSING, COMMAND AND DATA HANDLING, AND FAULT MANAGEMENT) AND QUALITY ASSURANCE REQUIREMENTS. 2.1 PERFORMANCE REQUIREMENTS BUSEK SHALL DEFINE THE PROPULSION SYSTEM PERFORMANCE REQUIREMENTS. THE REQUIREMENTS WILL BE DERIVED FROM A MISSION MANEUVERING PLAN THAT WILL INCLUDE A SPECIFIED 𝛥V BUDGET AND SPACECRAFT DRY MASS. PERFORMANCE SPECIFICATIONS SHALL BE DEFINED FOR EACH PROPULSION SUBSYSTEM COMPONENT INCLUDING THRUSTER/CATHODE, TANK, POWER PROCESSING UNIT, DIGITAL CONTROL UNIT, AND MANIFOLD/FEED SYSTEM. 2.2 FUNCTIONAL REQUIREMENT BUSEK SHALL DEFINE THE FUNCTIONAL REQUIREMENTS FOR THE PROPULSION SYSTEM INCLUDING BUT NOT LIMITED TO MECHANICAL, THERMAL, ELECTRICAL, HARNESSING, COMMAND AND DATA HANDLING, OPERATING MODES, SOFTWARE, FIRMWARE AND FAULT MANAGEMENT FUNCTIONAL REQUIREMENTS. 2.3 INTERFACE REQUIREMENTS BUSEK SHALL DEFINE THE PROPULSION SYSTEM INTERFACE REQUIREMENTS INCLUDING BUT NOT LIMITED TO MECHANICAL, THERMAL, POWER, GROUNDING, DATA BUS, AND COMMAND AND TELEMETRY DATA STRUCTURES. THE INTERFACE REQUIREMENTS SHALL BE DEFINED TO SUFFICIENT DETAIL TO ALLOW DETAILED DESIGN, MANUFACTURING AND TEST TO SUCCESSFULLY OCCUR. 3.0 PROPULSION UNIT DESIGN AND ANALYSIS BUSEK SHALL DEVELOP A PROPULSION SYSTEM CONCEPT DESIGN AND BEGIN PERFORMING RISK REDUCTION ACTIONS WHERE NEW TECHNOLOGIES OR DESIGNS INTRODUCE POTENTIAL RISK FOR MISSION SUCCESS. THE MAJOR PROPULSION SUBSYSTEM COMPONENTS INCLUDE THE POWER PROCESSING UNIT (PPU), TANK AND FEED SYSTEM, THRUSTER & CATHODE, STAGE GIMBAL, AND DIGITAL CONTROL INTERFACE UNIT WITH SOFTWARE. SHALL OPTIMIZE THE DESIGN OF THE PPU BASED ON CURRENT BREADBOARD HARDWARE AND DESIGNS. INCLUDED IN THIS DESIGN WILL BE THE RADIO FREQUENCY (RF) GENERATION CIRCUITS, GRID HIGH VOLTAGE CIRCUITS, CATHODE CIRCUIT AND FEED SYSTEM/TELEMETRY CIRCUITS. A PATH TOWARD A RADIATION TOLERANT PPU AND CRITICAL COMPONENTS SELECTION WILL BE IDENTIFIED. CRITICAL BREADBOARD ELECTRONICS WILL BE FABRICATED AND TESTED AS RISK REDUCTION STEPS. INITIAL THERMAL ANALYSIS WILL BE PERFORMED AS A BASELINE CASE. 3.2 STORAGE & FEED SYSTEM BUSEK SHALL OPTIMIZE THE DESIGN OF THE IODINE STORAGE AND FEED SYSTEM FOR THE BIT-3 RF ION THRUSTER AND CATHODE. THE MAJOR COMPONENTS OF THIS SYSTEM ARE THE STORAGE TANK, THE FEED LINES WITH INTEGRATED HEATERS, AND THE VALVE. THE UNIQUE CHARACTERISTICS OF THE BIT-3"™S HEATED, SOLID IODINE FEED SYSTEM NECESSITATES A RIGOROUS THERMAL ANALYSIS AND SIMULATION. BUSEK WILL FABRICATE CRITICAL BREADBOARD COMPONENTS OF THE IODINE STORAGE AND FEED SYSTEM AND TEST AS RISK REDUCTION TASKS.

VERMONT TECHNICAL COLLEGE WILL DESIGN AND WRITE THE FLIGHT SOFTWARE FOR LUNAR ICECUBE. THEY WILL ALSO WRITE ANY NECESSARY GROUND SOFTWARE FOR COORDINATION WITH THE DEEP SPACE NETWORK. THE FLIGHT SOFTWARE WILL INTERFACE WITH THE BIRCHES INSTRUMENT, IRIS 2 RADIO, BUSEK ION ENGINE AND GIMBAL, PV PANEL CONTROLS, POWER SUPPLIES AND BLUE CANYON STAR TRACKER/ADACS SYSTEM. ANY OTHER COMPONENTS ON THE SPACECRAFT THAT NEED TO BE CONTROLLED OR HAVE DATA COLLECTED WILL HAVE A SOFTWARE INTERFACE. THE SOFTWARE WILL BE WRITTEN IN SPARK/ADA SO AS TO HAVE THE SMALLEST POSSIBLE CHANCE OF ERRORS POSSIBLE.

TASK ORDER DESCRIPTION CONTRACTOR, IN SUPPORT OF MOREHEAD UNIVERSITY, WILL PERFORM TASKS 1 DURING PHASE I AND TASK 2 DURING PHASE II (OPTIONAL) OF THE PROJECT: PHASE I. 1. TASK 1- DEVELOPMENT OF LUNAR ICECUBE THERMAL MODEL: 1.1. DEVELOPMENT OF THERMAL MODEL OF PAYLOAD AND BUS DETAILED ENOUGH TO DETERMINE HOT SPOTS 1.2. MODEL WILL INCLUDE OPTICAL AND THERMAL PROPERTIES OF MATERIALS AND SPACECRAFT ORBIT. 1.3. PROVIDE THE THERMAL MODEL TO MOREHEAD UNIVERSITY PHASE II (OPTIONAL). 2. TASK -2 DEVELOPMENT OF THERMAL MANAGEMENT SOLUTION FOR LUNAR ICECUBE 2.1. IDENTIFY & STUDY REGIONS OF EXCESSIVE HEAT WHICH ARE GENERATED BY PAYLOAD(S) AND BUS SUBSYSTEMS 2.2. DETERMINE BEST PATHS AND MEANS TO REJECT HEAT IN ORDER TO KEEP CRITICAL COMPONENT TEMPERATURES WITHIN OPERATIONAL LIMITS 2.3. FACILITATE TEMPERATURE DISTRIBUTION INSIDE OF THE S/C WHICH ALLOWS TEMPERATURE OF ALL COMPONENTS TO BE INSIDE OF PERFORMANCE ENVELOPE. 2.4. REDUCTION OF TEMPERATURE GRADIENTS ACROSS THE S/C 

1 INTRODUCTION THE MOREHEAD STATE UNIVERSITY SPACE SCIENCE CENTER IS SUBMITTING AN UPDATED ROM SCHEDULE AND BUDGET PURSUANT TO A COLLABORATION FOR THE LUNAR ENVIRONMENTAL MONITORING SYSTEM (LEMS) TELECOMMUNICATION SYSTEM. THE EFFORT INVOLVED WOULD ENCOMPASS END-TO-END TELECOMMUNICATION SYSTEM DEVELOPMENT. 2 WORK BREAKDOWN STRUCTURE (WBS) AND SCHEDULE THE BUDGETED WBS INCLUDES THE FOLLOWING TELECOMMUNICATION MACRO WORKFLOW: -OVERALL SYSTEM DESIGN -ADMINISTRATIVE REPORTS (MILESTONE, MONTHLY, WEEKLY REPORTS) -WEEKLY MEETINGS -DESIGN REVIEW SUPPORT -TELECOMMUNICATION-RELATED DOCUMENTATION DEVELOPMENT (REQUIREMENT DEFINITION, INTERFACE CONTROL DOCUMENTS, TEST AND PERFORMANCE REPORTS, RESOURCE BUDGETS, DSN/LTN/OTHER INTERFACE INFORMATION/DATA) -FLIGHT HARDWARE TRANSCEIVER, SSPA, LNA (FLIGHT TRANSCEIVER SUITABILITY TRADE STUDY, PROCUREMENT OF FLIGHT TRANSCEIVER, SOLID STATE POWER AMPLIFIER (SSPA), LOW-NOISE AMPLIFIER (LNA), AND ASSOCIATED SUB-COMPONENTS, FLIGHT SYSTEM CHARACTERIZATION - RF CHARACTERIZATION AND POWER CHARACTERIZATION - ENVIRONMENTAL TESTING TAILORED TO RISK POSTURE, LEMS-TO-GROUND DATA RELAY COMPATIBILITY TESTING) -FLIGHT ANTENNAS (RESEARCH AND DEVELOPMENT (R&D) AND ASSEMBLY, INTEGRATION, AND TEST (AI&T) FOR UPLINK AND DOWNLINK LOW GAIN ANTENNAS (LGA) SUITABLE FOR COMMAND AND CONTROL AND R&D AND AI&T OF MEDIUM GAIN ANTENNA (MGA) SUITABLE FOR DOWNLINK OF SCIENCE DATA PRODUCTS) -UPLINK/DOWNLINK FREQUENCY LICENSING (NTIA STAGE 1 THROUGH LICENSE ACQUISITION) -WEEK IN THE LIFE TESTING -AS NEEDED, NON-DSN, GROUND OPERATIONS UTILIZING DSS-17 -POST LAUNCH SUPPORT, AS NEEDED THIS WBS IS BASED UPON AN ATP+10MONTH DELIVERY OF TELECOMMUNICATIONS FLIGHT HARDWARE AND DOCUMENTATION. DELIVERABLES: MSU ON CONTRACT: T0 = 0 DELIVERY RF COMM SYSTEM TO GSFC T = T0+9.5 MONTHS

VECTOR INTERFEROMETRY SPACE TECHNOLOGY USING AERO (VISTA)