AS SMALL SATELLITES MANIFEST ON RIDESHARE LAUNCH OPPORTUNITIES AT AN ACCELERATED RATE THEIR VIABILITY AS A PLATFORM FOR EARTH REMOTE SENSING IMPROVES. HOWEVER THE CUBESATELLITE PLATFORM FACES SOME INHERENT SCALING LIMITATIONS IN TECHNOLOGIES ASSOCIATED WITH PRECISION ORBIT DETERMINATION (POD). HIGH-GAIN CHOKE RING GROUND PLANE GLOBAL NAVIGATION SATELLITE SYSTEM (GNSS) ANTENNAS ARE TYPICALLY TOO LARGE FOR THE CUBESATELLITE PLATFORM RESULTING IN THE NECESSARY USE OF GNSS ANTENNAS WITH REDUCED MULTIPATH PROTECTION. THIS REDUCES THE POD CAPABILITY OF CUBESATELLITES ON ORBIT. THE QUALITY OF MANY EARTH REMOTE SENSING OBSERVABLES SUFFERS IF THE POSITION OF THE OBSERVER IS UNCERTAIN. TO HELP CORRECT FOR THIS ONE COULD USE ADDITIONAL OBSERVABLES SUCH AS LOW-LOW INTERSATELLITE RANGE MEASUREMENTS BETWEEN CUBESATELLITE CONSTELLATION MEMBERS TO IMPROVE SATELLITE POSITIONING CAPABILITY. ENHANCEMENTS TO POD INHERENTLY IMPROVE ANY REMOTE SENSING MEASUREMENT OBTAINED BY THE SATELLITE. CURRENT POD CAPABILITIES FOR CUBESATELLITES ARE ON THE 10 METER LEVEL OF UNCERTAINTY WHICH IS FINE FOR MOST CURRENT APPLICATIONS OF THE CUBESATELLITE PLATFORM. HOWEVER BY REDUCING THIS POD ERROR WE EXPAND THE FEASIBLE REGION OF WHAT CAN BE ACCOMPLISHED WITH A CUBESATELLITE ARCHITECTURE. IMPROVED POD MAY ENABLE NEW CUBESATELLITE MISSION CONCEPTS IN AGGREGATE COORDINATED REMOTE SENSING GEODESY OR HIGH-BANDWIDTH DATA RELAY FOR REAL-TIME EARTH MONITORING (THROUGH LASER COMMUNICATION). THIS PROJECT WILL DEMONSTRATE WHAT LEVEL OF GAINS ARE AFFORDED TO THE POD OF ALL CONSTELLATION MEMBERS GIVEN THE ADDITION OF LOW-LOW INTERSATELLITE RANGE OBSERVABLES. THIS GOAL IS DIRECTLY ALIGNED WITH THE GOALS OF NASA S EARTH SCIENCE TECHNOLOGY PROGRAM (AS OUTLINED IN NASA S 2014 SCIENCE PLAN) TO ADVANCE EARTH OBSERVING INSTRUMENTATION MISSION COMPONENTS AND INFORMATION SYSTEMS TO MAKE FUTURE MISSIONS FEASIBLE AND AFFORDABLE. THE FIRST FOCUS WILL BE ON DEFINING THE REQUIREMENTS FOR THE INTERSATELLITE RANGE MEASUREMENTS AS WELL AS QUANTIFYING THE EXACT GAINS TO POD FOR ALL MEMBERS OF A SATELLITE CONSTELLATION BENEFITING FROM THESE ADDITIONAL INTERSATELLITE RANGE MEASUREMENTS. THIS WILL BE ACCOMPLISHED THROUGH SIMULATION AND ANALYSIS OF REAL DATA FROM A MISSION THE AUTHOR IS THE STUDENT LEAD ON. SECONDLY THIS PROJECT NATURALLY LENDS ITSELF TO THE TASK OF CONSTELLATION DESIGN FOR MAXIMIZING THE BENEFIT TO EARTH REMOTE SENSING THROUGH IMPROVED POD. CONSTELLATION DESIGN WILL BE CARRIED OUT USING OPTIMIZATION TECHNIQUES ALREADY DEVELOPED WITH A MODIFIED OBJECTIVE FUNCTION THAT MAXIMIZES POD CAPABILITY. OPTIMAL CONSTELLATION DESIGN THAT LEVERAGES INTERSATELLITE RANGING FOR POD WILL ENABLE NEW MISSION CONCEPTS EXPANDING THE SCIENCE CAPABILITIES OF THE CUBESATELLITE PLATFORM.