CubeSat Proximity Operations Demonstration (CPOD) Mission Update Cal Poly CubeSat Workshop San Luis Obispo, CA

Transcription

1 CubeSat Proximity Operations Demonstration (CPOD) Mission Update Cal Poly CubeSat Workshop San Luis Obispo, CA Austin Williams VP, Space Vehicles

2 ConOps Overview - Designed to Maximize Mission Success Probability Separate and Continue Checkout Orbit Maneuvering to Initial Proximity Distance (Walking Safety Ellipse) 4b-c 5 CubeSat A performs RPO relative to CubeSat B 6 A Decreased Range RPO & Docking Scenarios 7 Initial SOH Checkout 4a B Release together from 6U dispenser 3 Residual Ops 8 Disposal 9 2 Launch Ground Network Main RPO Experiment Phases Mission-Planning / Pre-Launch 1 Mission Operations Center 2

3 Deployment Configurations and Vehicle Checkout 3 Connected 6U Configuration 4a First Panel Deploy Deploy UHF Antenna Initial SOH Checkout 4b-c Vehicle Separation Second Panel Deploy Complete Checkout 3

4 Space Vehicle Architecture EPS Health & State Sensors Heater Power Sequencing SYSTEM PROCESSOR ADCS State Estimation & Control Processor 3-axis IMU Star Trackers w/ dedicated processing COMM S-BAND (downlink) UHF 3-axis Reaction Wheel Set 3-axis Sun Sensor Set GPS 3-axis Magnetometer Set Inter-Satellite link (Comm / Ranging) 3-axis Mag. Torquer Set RPO Wide Field Visible Imager Infrared Imager Infrared Imager Docking Sensor Relative Position Estimation Processor (Imaging Processor) Maneuver Planning Processor (GN&C) Docking Mechanism Optical Target Aid 8-thruster Cold Gas CONTRIBUTIONS Tyvak Nano-Satellite Systems Applied Defense Solutions Tyvak (Prev. 406 Aerospace) VACCO 4

5 Vehicle Configuration -External Isometric Views Thermal Radiators Solar Panel Arrays with MPPTs GPS Patch Docking Mechanism S-Band Patch Separation Devices Thermal Radiator Star Trackers UHF Antennas 5

6 Vehicle Configuration -Internal Arrangement and Packaging GPS Receiver Battery Module Cold Gas Thrusters (8) S-Band Transmitter UHF Radio Inertial Reference Module (IRM) Battery Module Endeavour Bus Propulsion Module RPOD Module 6

7 Payload Tyvak s RPO Module 7

8 EDU Build-Up - System 8

9 Component and Subsystem Environmental Testing Early component and subsystem environmental testing used to reduce risk of issues at system level Risk reduction environmental testing completed on low TRL components (RWA, battery module, star camera, and IMU show on right) Modules used to enable testing complex subsystems before full vehicle integration (IRM, RPOD, etc.) Lessons Learned Thermal test before thermal vacuum testing Design for repeated assembly and disassembly of complex modules Feature rich test interfaces are invaluable when attempting to understand issues without deintegration Component Vibration Testing Subsystem Vibration Testing 9

10 Hardware in the Loop (HITL) Testing Complex distributed ADCS/GNC system necessitated real time hardware in the loop testing Sensors and actuators simulated in real time with flight like dynamics Autocoded truth and flight code enable rapid iteration and commonality be software only simulation and HITL testing HITL platform operational and system is currently under test Lessons Learned HITL testing is possible for CubeSat class missions HITL interfaces should be included in system and EGSE design from initial conception 10

11 Range and Pose Determination Simulation 11

12 Air Table Testing (Video) Docking Mechanism Alignment 12

13 Air Table Testing Vehicle Separation 13

14 EDU Deployable Test 14

15 Development Status EDU vehicle assembled and undergoing final system functional tests System level functional EMI self compatibility Vibration Thermal vacuum Flight vehicles in assembly Schedule margin to be used for additional mission assurance Considering multiple launch options Q Pursuing follow on missions to transition from technology demonstration to operational missions 15

16 CPOD Performance Summary Capability Specification Comments Average Power Generated ~17W to 30W OAP Polar Sun-Sync Average Load ~15W Fully Active Pointing Accuracy degrees (1σ) Summation of Real World Error Sources Mission Data Downlink ~60MB / day UHF and S-Band Delta-V ~30 m/s Cold Gas Total Mass 5.990kg Wet Mass (13% Margin) 16

17 Questions?