Mission Goals Brandi Casey (Project Manager) 1
What is it? TREADS NanoSat (TREADS-N) Testbed for Responsive Experiments And Demonstrations in Space (TREADS) TREADS is a 'full-service' technology demonstration and science gathering platform TREADS-N is a member of the TREADS family of testbeds that provides: Pointing capabilities Increased power generation over TREADS-H Greater downlink capacity than TREADS-H 2
Mission Goals The TREADS-N will compliment the TREADS family by providing a free-flyer platform for instrument testing that will provide extra utilities for customers requiring extra functionality such as more precise pointing, improved data rates, or extra power. Risk-reduction for large projects First to market for commercial products Essential science for principal investigators 3
Our Focus Your technology is the primary payload In-situ demonstrations and risk-reduction Increase TRL Baseline science/tactical capabilities 'Technology slots' available for 1 to 6 instruments Several 'customers' per flight (up to 80kg total) Don't have to be chosen (i.e. prime/sub) Don't need a dedicated s/c 'per-slot' basis You decide when you fly! Self-Manifest SM SBIR Phase III Demonstration Platform 4
Configurations 3 configurations to keep costs low and perform to customer specifications Hosted Platform Low Cost Board-Level Electronics CubeSat Platform Nanosat Platform Large Payload Size Pointing Ability 5
Today's Focus Nanosat Platform (riding within RideShare Adapter (RSA) or ESPA) A testing structure for board-level electronics and stand-alone components Specific components chosen for possible future flight 6
Description of TREADS-N Description Free-flying satellite Released from the RSA or the Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) 15 lightband adapter Designed for specific payloads Mission/Orbit Envelope Falcon 1 launch vehicle Test orbits from equatorial to polar Test altitudes from 300 km to 700 km 1 year mission 7
Milestones TREADS-H CDR Dec. 2008 TREADS-N CoDR Feb. 2009 Worked towards PDR design from Feb April 2009 TREADS-N PDR Space Grant Symposium TREADS-N First week of May a PDR Design Delivery of TREADS-N Personalized Projects from Redfine Technologies 8
Schedule Overview Spring work 2009: TREADS Nanosat (TREADS-N). TREADS Hosted seeking phase III approval for SBIR. Redefine seeking launch opportunity in 2010. Redefine seeking more customers to further progress TREADS-C, TREADS-H and TREADS-N. 9
Redefine Technologies Steve Wichman CEO, Redefine Technologies Software Design Space Grant Brandi Casey (Project Manager) Brian Sanders Research Coordinator Andrew Bath (Systems Lead) Jay Trojan (ADCS Lead) Nate Bailey (Structures Lead) Sreyasi Vinjamuri (Comm Lead) Jay Trojan (Power Lead) Curtis Miller (Thermal Lead) Malcolm Young (Systems) Brian Macumber (Structures) Robin Blenden (Comm.) 10
DUT and Payload Overview Brandi Casey (Project Manager) 11
Supporting a DUT Device-Under-Test (DUT) Various DUT interfaces 6U, 3U, PC104, Space104 cpci, 1553, SpaceWire, RS422, etc Exterior connection for components Radiation resistant test controller & flight computer exercise DUT and record data Communication link Downlink results, uplink new configurations Lifetime Nominal: 12 months Extended: 3 years 12
Systems Presented by: Andrew Bath Malcolm Young 13
System Objectives Ref 0.OBJ.01 Description The TREADS-N platform will provide payloads a LEO space environment in which to test and verify their hardware for space applications. 0.OBJ.02 0.OBJ.03 0.OBJ.04 0.OBJ.05 0.OBJ.06 0.OBJ.07 0.OBJ.08 0.OBJ.09 0.OBJ.10 The TREADS-N will downlink data to a control center via a ground station. The TREADS-N will accommodate various numbers and types of customer's payloads. This TREADS-N will be designed to reduce recurring engineering costs. The TREADS-N will be designed to integrate to the RSA and ESPA payload adapter as outlined in their respective user's documents. The TREADS-N will be designed to keep its utilities operable for greater than 1 year. The TREADS-N will provide 3-axis pointing. The TREADS-N will provide more power, more mass, and more data throughput than the TREADS hosted solution to payloads. The TREADS-N will use parts of the TREADS-H to reduce design complexity and allow interchangeability of parts. The control center will work with the customer to make configuration changes to DUT software and DUT manager software during the mission. 14
System Requirements TREADS-N shall be sized such that two will fit into the ESPA envelope with a 15" lightband between them Avionics shall fit into the standardized boxes designed for TREADS-H Shall have as large of an optical hole as possible in one of the sides Shall have >75W available for payloads 100% of the time Shall have >40kg mass available for payloads Shall have >180 MB/72 hrs download capability Shall have >3 MB/72 hrs upload capability Shall have three ground stations will be baselined (PR, HI and CO) Shall have pointing accuracy to +/- 1 arcsec, attitude knowledge to within +/- 0.1 arcsec note: may require RTOS and floating point capability on flight computer Shall use SIL batteries Shall use ClydeSpace solar panels 15
Baseline Payloads Space Micro Inc Transponders The Space Micro Transponders are microwave communication transponders built to withstand the rigors of the space environment. These transponders may be modified to increase the radiation mitigation abilities, including Total Dose, SEU, and SEL prevention. Optical Tube The Optical tube specs are being used as the Orion 150mm Mak-Cass Telescope Tube. This is just a baseline design to further understand the requirements of a similar telescope tube. In addition to the Orion telescope tube, there will be a camera box on the top of the tube, something like a 3U size CCD with a second board to support it. Pyxis GPS Reciever The Pyxis receiver is available as a stand-alone receiver or 3U cpci board LEO Precision Orbit Determination receiver (Pyxis-POD), as a Radio Occultation and POD GNSS Receiver (Pyxis-RO), and as a GEO Precision Orbit Determination receiver (Pyxis-GEO). 16
Baseline Payloads Space Micro MicroRad 100 Dosimeter "The MicroRAD 100 is a low power, high performance space dosimeter solution that meets the challenges of space and satellite harsh environment platforms Redefine CMDRS Technology Demonstration Kit 1x3U card consuming approximately 10W. SIRF Flight Experiment 6U Card consuming approximately 10W 17
System Layout Physical System Layout: Light band adaptor (stacked configuration) Skinned isogrid design Directional antenna Deployed solar arrays Holes for telescope and star trackers 18
Physical Layout Attitude Sensors Activation Signal GSE Space Micro MicroRad 100 Pyxis GPS Solar Panel Array Avionics Box Sil Intellipack 33.6V Torque Rods/ Reaction Wheels Antenna DUT Test Box Space Micro Transponder Imaging Payload 19
Electrical Layout Two Main Boxes Torque Rods Avionics To Attitude Sensors RS-485 to Magnetometer Torque Rod Driver 5V CPCI RS-485 RS-422 5V 12V 5V 3.3V DUT Test Box DUTs Coaxial Antenna RS-232 to GSE 33.6V Battery RS-422 Battery Solar Panel Radio (MHX 2420) Flight Computer (RPB MRA) PCU 5V RS-232 5V GPIO I2C RS-422 cpci RS-422 28V 12V 5V 3.3V Backplane I^2 (sensors) RS-422 5V 12V 5V 3.3V 28V Backplane 28V 3.3V RS-485 RS-422 (x8) CPCI (x2) CPCI RS-485 RS-422 5V 12V 5V 3.3V 28V DUT Manager (PROTON 200K) DUTs Activation Signal External DUTS 20
Orbital Environment 1 Year+ Mission Mission Duration Dependant on Risks of Hardware Failure 21
Subsystem Overview - CDH Design Backplane for data and power transmission inside boxes Proton 200k for DUT manager RPB MRA for flight computer cpci, RS-485, RS-422, and GPIO support for DUTS, both internal and external Current Progress CDH system is being ported over from TREADS-H design. Currently no personnel allocated to improve the current design 22
Design Subsystem Overview - COM S-Band Antenna/Radio Extremely high data rate requirements Supporting optical payload which takes 6Mb pictures Current Progress Data transmission rates being investigated Link Budgets being created to ensure links Boulder Hawaii Puerto Rico 23
Subsystem Overview - THM Design Getting a preliminary idea thermal environment Analyzing un-mitigated temperatures in several target orbits in two different software packages Thermal desktop MATLAB Current Progress Several orbits analyzed and characterized Alodine coating required White paint on payloads Non thermally-conductive connections between solar arrays and structure Current models indicate no need for more thermal mitigation 24
Subsystem Overview - ADC Design Ensure pointing accuracy to +/- 1 arcsec, and attitude knowledge to within +/- 0.1 arcsec for supporting optical payload Torque rods Reaction wheels Sun sensor Magnetometer IMU Star tracker Provide solar panel power estimates based on pointing Current Progress Antenna/ Optical Vector Simulations showing jitter, reaction wheel storage/sizing y Body axes x z Sun Vector 25
Subsystem Overview - EPS Design 90 watt continuous draw allocated for system completion 75W allocated for PDR level 200W solar array to support this Rigid 90 degree deployment - Low complexity - Simple deployment mechanism - Low cost Sil Intellipack 33.6V battery pack Provide +/-28V, 12V, 5V, and 3.3V to satellite Current progress Significant work done on power modes Solar Array Petal Design Battery and solar arrays sized based on pointing requirements 26
Power Budget Top-down PHASED AVERAGE POWER ALLOCATION Phase AO SCR PDR CDR PQR Flight Margin 50% 35% 25% 15% 5% 0% Design Power 50.00 W 65.00 W 75.00 W 85.00 W 95.00 W 100.00 W SUBSYSTEM ALLOCATION STR THM ADC EPS COM CDH Science TOTAL Allocation 0% 4% 17% 15% 7% 25% 32% 100% Allocated Power 0.00 W 3.00 W 12.75 W 11.25 W 5.25 W 18.75 W 24.00 W 75.00 W COMPARISON BETWEEN ESTIMATION AND ALLOCATION STR THM ADC EPS COM CDH Science TOTAL Under Allocation 0.00 W 0.18 W 0.10 W 0.25 W 0.54 W 1.50 W 0.54 W 3.12 W by 0% 6% 1% 2% 10% 8% 2% 4.16% Bottom-up CURRENT SUBSYSTEM ESTIMATE STR THM ADC EPS COM CDH Science TOTAL Contingency Power 0.00 W 2.82 W 12.65 W 11.00 W 4.71 W 17.25 W 23.46 W 71.88 W Contingency 0% 15% 10% 10% 10% 15% 10% 11% Average Power 0.00 W 2.45 W 11.50 W 10.00 W 4.28 W 15.00 W 21.33 W 64.55 W Peak Power 0.00 W 7.35 W 23.50 W 10.00 W 25.66 W 15.00 W 66.05 W 147.56 W 27
Mass Budget PHASED MASS ALLOCATION Phase AO SCR PDR CDR PQR Flight Margin 50% 35% 25% 15% 5% 0% Design Mass 45.00 kg 58.50 kg 67.50 kg 76.50 kg 85.50 kg 90.00 kg SUBSYSTEM ALLOCATION Top-down STR THM ADC EPS COM CDH Science TOTAL Allocation 31.8% 3.3% 14.3% 20.4% 2.00% 8.2% 20.0% 100.0% Allocated Mass 21.47 kg 2.23 kg 9.65 kg 13.77 kg 1.35 kg 5.54 kg 13.50 kg 67.50 kg COMPARISON BETWEEN ESTIMATE AND ALLOCATION STR THM ADC EPS COM CDH Science TOTAL Under Allocation 1.28 kg 0.13 kg 0.53 kg 0.57 kg 0.10 kg 0.31 kg 1.07 kg 4.00 kg by 6% 6% 6% 4% 8% 6% 8% 5.92% Bottom-up CURRENT SUBSYSTEM ESTIMATE STR THM ADC EPS COM CDH Science TOTAL Contingency Mass 20.18 kg 2.10 kg 9.12 kg 13.20 kg 1.25 kg 5.23 kg 12.43 kg 63.50 kg Contingency 5% 5% 10% 10% 10% 10% 10% 8% Estimation 19.22 kg 2.00 kg 8.29 kg 12.00 kg 1.14 kg 4.75 kg 11.30 kg 58.70 kg 28
Power Budget Conclusions Peak power (All payloads operating simultaneously) is very high Duty cycles will insure that this situation will not happen Duty cycles on components reduce average orbital power draw This will be enforced by DUT manager and flight computer Mass Currently under mass Payloads require far less mass than initially expected Structure will need further reinforcement This will be covered more in depth by our structures team 29
Concept of Operations Presented by: Malcolm Young 30
Concept of Operations Falcon 1 User s Guide, SpaceX Launch TREADS-N Operations (1 Year) 31
LV Activities Nominal Timeline Mission Start FC Boot Up Attitude Determined and Adjusted First Ground Contact System Checkout Nominal Operations 12 months Schedule Uplink Customer Feedback Exec. Schedule Exec. DUT Test(s) Data Downlink TREADS-N Power On Charge Batteries Ground Ops S/C Ops 32 Secondary Payload Release Primary Payload Release Launch
Activities Overview Legend -Sun point -Slews -Take images -Back orbit activities -Not optical pointing activities -Pass activities -Orbit durations 33
Normal Orbit Activities Imaging orbit Pass orbit Pointing activities grouped to increase sun point time Receiver always on DUT s turned off prior to pass to lessen power load 34
Risks and Mitigations Reference 1 2 3 Risk Description Likely Severity Insufficient volume for manifested payloads Design Risks Solar Arrays changing thermal environment affects efficiency Insufficient materials for TREADS capabilities for TREADS customers 2 3 3 4 Mitigation 1) adjust placement of TREADS-N system components 2) Design new mounting scheme Investigate solar array thermal coatings 3 3 Manifest Forms 4 3 3 <> 35
Risks and Mitigations (cont) Reference A B C Mission Risks Risk Description Likely Severity Primary structure failure 5 5 Data from the payloads exceeds allocated capacity 2 3 Lack of suitable ground station for different orbital inclinations 2 4 Mitigation 1) Increase panel thickness or Isogrid skin 2) Decrease Isogrid triangular pattern 3) Consider other materials 1)Data should be dowlinked before it reaches the storage margin 2)Acquisition of data should be minimized in the next pass. Investigating multiple ground stations 36
Risk Chart System A C 2 B 1 3 37
Conclusion and Future Work Conclusions Design progress is at PDR level Requires further investigation: Verify components meets thermal environment Advance design to meet most extreme stress loads Each subsystem design has to progress to CDR level Attitude control system is within pointing requirements Under mass budget Under power budget To Do (this semester) Make all quick improvements from PDR Submit design documents Updated PowerPoints To Do (after this semester) Progress to CDR 38