1. DINO Peer Review 20 September 2015 Tip Mass Presentation Anders Fornberg – Team Lead/Imaging Kate Worster– Power Siddharth Shetty – Comm Jen Getz & Terry Song – Structures Joshua Stamps – Thermal

2. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium2 Overall Mission of the tip-mass Main Mission –Provide gravity-gradient stabilization for DINO Functions –Capture and send pictures Deployment of FITS Deployment of Aero-fins DINO main module Tip-Mass

3. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium3 Top-Level Requirements 5kg mass Tip-Mass shall not connect to DINO other than via the boom Separate power system Wireless communications from DINO to Tip- Mass module Tip-Mass shall meet all NASA safety requirements

4. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium4 General Layout of Tip Mass 5 V COMM Serial Camera Power Imaging-FPGA RS-232802.11b Trigger 5 V On RS-232 5 V Counter

5. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium5 Overall Tip Mass Subsystem Test Plan Proper operations of the tip mass when given specific commands –Triggering of camera –Resetting of camera’s memory –Receiving image for camera’s memory –Initialization of power save mode –Return to non-power save mode –Accomplished with software that simulates commands that the flight computer would send to the tip mass “Initial on” counter can initially activate the tip mass subsystem –Accomplished by connecting counter to power subsystem and running multiple test to ensure reliability

6. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium6 COMM Tip-Mass Subsystem Siddharth Shetty

7. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium7 COMM System Requirements Fast and reliable wireless link Transmit over 6 meter distance (tested over >33m distance successfully without packet loss) Utilizes 5 V DC power line RS-232 Compatible

8. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium8 TPS Options Infrared –Very low range –Line of sight required Bluetooth –Recommended Receiver sensitivity: -70dBm –Standard not as open as compared the IEEE 802.11 –Operates in license-free band IEEE 802.11b –Open and widely used standard –Recommended Receiver sensitivity: -90dBm (higher range) –Operates in license-free band

9. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium9 Processor with a serial RS-232 port FPGA Chip Serial port of processor 802.11 air interface Wiser 2400 unit (OTC wireless) RS-232 serial interface port of WISER 2400 Serial RS232 port terminating on the FPGA chip Main sat module Tip Mass Communication system Wiser 2400 is the interface between the wireless 802.11 link and the RS232 serial port on the FPGA Chip

10. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium10 Features - WISER 2400 Operates In the ISM band (2.4GHz – 2.495GHz), no FCC license required No driver on the host device is required for radio operation Independent of the operating system on the host equipment or device as long as a RS232 port is properly supported Industry standard IEEE 802.11b-compliant wireless interface; Interoperable Client radios from other vendors

11. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium11 Specifications-WISER 2400 Frequency: ISM band (2.4GHz – 2.495GHz) Link Distance: ~6 meters in open space Voltage, current: 5v, max 480mA (in transmit mode) Data rate: Capable of supporting up to 115K baud (possible limitation on the digital camera side to transmit data) Weight : 3.7ounces:the radio with case,1.7 ounces is the weight of the case Antenna type: Integrated dipole antenna (omni- directional) with ~2dBi gain

12. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium12 Implementation details One Wiser unit will act as the Access Point and the other will play the role of a station ‘Beacon’ packets show supported data rates of 1,2,5.5,11 Mbps Cap on the serial interface; a 9600 baud rate is currently set (default value), which can be increased up to 115K

13. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium13 Agilent Tool

14. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium14 Radio test results Distance (m) wiser1-V, wiser2-V wiser1-H, wiser2-H wiser1-V, wiser2-H wiser1-H, wiser2-V signal level (dbm) 12-71-67-76-62 20-71 -72 33-78 -75 Preliminary radio tests conducted over distances up to 30m with error-free communication

15. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium15 Link Budget Free space loss in space Lp(dB)= 92,45 + 20log10 F+20 log10d For 10m L~ 60dB at 2.45GHz and ~70dB for 30m Power at Rx (20m)= 14dBm + 2dBm – 70dB + 2dB = -52dBm ( > Receiver sensitivity of -80dBm)

16. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium16 Power Drain Beacons transmitted at 100msec intervals by Access Point (Infrastructure mode) Effective time of transmission of beacon frames ~ 3.8sec per hour Power drain in Receive mode higher ~250mA Support for power-save mode available Circuitry to cut off power at times of ‘No use’

17. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium17 Future tests Exhaustive radio test to be carried out by attaching the wiser units behind isogrids to simulate actual working conditions and also takes into account the orientation of units Throughput calculations to be performed using programs to transfer bulk data over these units and observing the transmit success rate

18. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium18 Power Tip-Mass Subsystem Kate Worster

19. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium19 Requirements on other TM systems Equipment 4 A-hr NiCad Cells @ 1.2V ea. –Charge time 14-16hrs or 1hr MAX1672 DC/DC Power Converter Structure to contain and support battery Fuse, derated; appropriate-sized wires, also derated FET’s or relays for inhibit switching Requirements imposed by TM-EPS Battery must be maintained between 0 and 45º Celsius Battery cannot be drawn below 0.9V Cell dimensions (DxH) 33mmx60mm Structure must not damage TM-EPS during thermal cycling Mating battery to structure will need attention Any commands to TM-EPS must come from C&DH on main S/C Leads for monitoring cell voltage and temperature, as well as inhibit status from the GSE must be provided

20. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium20 Power Safety and Operations Safety Two-fault tolerant battery inhibit system No shunt diodes Battery case must contain any leaks and prevent shorts in the battery Fuse must be provided on ground leg of battery System will be un-powered until TM separation from DINO Launch with fully charged battery Need shunt diodes on ea. cell All cell vents must be oriented upward during launch Operations System will switch on and off via a photo-sensor C&DH will turn the system back off if no images are to be taken on a given orbit Inhibit switches open until the boom is deployed Separation switches detect boom deployment 2 MOPS scenarios

21. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium21 Power System Requirements Tip Mass Electrical Power System (TM-EPS) must provide 5V regulated line to TM subsystems 802.11b wireless transceiver Digital Camera TM-EPS must provide power for at least 180 minutes Will need to image on at least 3 different orbits Boom deployment FITS deployment Aero-fin deployment TM-EPS will meet all NASA safety requirements TM-EPS will share as many components as possible with DINO main S/C Inhibits and monitors must be able to be verified from Ground Support Equipment (GSE)

22. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium22 TM-EPS Block Diagram 1.2V, 4A-hr NiCad Cell 5V DC/DC Converter Inhib 2 Inhib 3? Inhib 1 Sub- Systems Sep Sw. #1 Sep Sw. #2 System lines Inhibit lines Ground (Version 1)

23. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium23 Power System Overview clock FPGA counter EPS SCI COMM (Version 2)

24. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium24 Power System Action Items Accomplished Action Items Performed battery profile Trade study for charging scenarios Determined battery choice – NiCad First version of power budget Preliminary EPS system schematic Upcoming Action Items Trade study for inhibits Finish power distribution design Final version of power budget Prototype EPS

25. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium25 Power Tip Mass Test Plan Proper power levels to each subsystem –Communication’s wiser 2400 unit is given a controlled 5 Volt line –Imaging’s Jam-Cam is given a controlled 5 Volt line –Accomplished using a multi-meter and slightly varying the input voltage to simulate noise Inhibits are operating properly Receives and can initialize power save mode –Software that simulates a “power save” command given to power by the FPGA Receives and can initialize non-power save mode –Software that simulates a “non-power save” command given to power by the FPGA

26. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium26 Imaging Tip-Mass Subsystem Anders Fornberg

27. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium27 Science TP Sub-System Requirements Take clear pictures of FITS and Aero-Fins Deployment and main DINO module Serial connection to FPGA Chip Powered by 5 Volt line Pass all NASA specification on materials –No ABS material

28. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium28 Trade Study (Jam-Cams in Tip-Mass) Pros –Already know software –Lens is Non-ABS –Cheap –Readily Available Cons –Not good pictures –Long storage time –Not very good at manual controls –Low camera memory –Low Resolution

29. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium29 Canon Powershot S-10 for Tip-Mass Pros –Can use both serial and USB connection –High resolution (2.1 MP) –Better lens and parts –Short storage and loading times –Linux Compatible Cons –More expensive (≈$120) –Don’t know software/commands –Don’t know if lens mounting is ABS plastic

30. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium30 Trade Study Review Due to the boom redesign the tip-mass structure will be positioned closer to the main module. This will require a less resolution camera. Also, because of the faster deployment of such a design, storage time is not such an issue. The ability of the S-10 to use serial and USB could allow for use in main satellite as well as tip mass module. S-10 is a better camera all around except that there are a lot of unknowns

31. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium31 Tip-Mass Camera Decision Jam-Cams will be the primary camera at this point Will do a dual development with the jam-cams and the Canon S-10 In the process of purchasing one S-10 to do ABS plastic detection

32. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium32 Preliminary Command list for Science All of Jam-Cams operations can be controlled through the serial Port Camera Power (on/off) Camera Trigger (take picture) Receive images Clear Memory Ping Camera

33. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium33 FPGA Board Studying 3CS Science Jam-Cam FPGA Board Will have to modify for DINO Uses only on camera Has to be connect to power

34. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium34 Test Plan and future studies Reliable serial connection to FPGA board Program to test commands given to Jam-Cam Test image quality at 6 meters with bright background ABS plastic testing on S-10 with help from main science team

35. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium35 Structure Tip-Mass Subsystem Terry Song and Jen Getz

36. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium36 Structures Design Requirements Total Mass: 5 kg Components Mass (estimates): Batteries (including structure): 500-600g Camera (w/o case): 68 g Comm (w/o case): TBD Top Half of the Lightband Deployment System: 2.1 kg Internal Deployment System: Mechanism to deploy: 1.0 kg Attachment Tether: ~1.0 mg Internal/External Support Boxes: Constructed of 6061 Aluminum Density: 2698.79064 kg/m3 Ballast will be used as necessary to meet mass requirements.

37. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium37 Structures Design Requirements Total Volume: 420.5 in 3 –Bottom Plate will have a half inch lip to decrease tension and increase stability. Interior Dimensions (estimates): –Battery Box: TBD –Camera Box: TBD –Comm Box: TBD –Boom Deployment System Box: 3.5” x 4.0” x 4.0” Center of Mass must be along the z-axis –The boom is parallel to the z-axis –The length of the boom is 6 meters long

38. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium38 Structures Design Detail The main design driver is the mass requirement –The 5kg mass limit is critical in designing every component Maximizing interior space without failing to meet the design requirements –Hexagon shape has been selected due to its large volume capacity

39. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium39 Structures Design Detail

40. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium40 Subsystem Test Plan for Tip-Mass COMM –Transmit and receive from both FPGA and flight computer Structures –Keep on improving the design to optimize structural performance meanwhile meeting mass requirement –Testing will be done in coordination with the main satellite Science –Image quality for objects at 6 meters (~60 feet) –Proper communications with FPGA Power –All system power test to ensure 2 hour operation

41. DINO Peer Review 20 September 2015 Colorado Space Grant Consortium41 Issues and Concerns STR –Protection for internal components, necessary? –Exceeding the mass requirement is still possibly an issue COMM –Power drain due to continuous “beacon” transmission PWR –Effects on power from tether to boom (if any) –MOPS counter vs. switch for initial power on SCI –Non-ABS material with Canon S-10 –Complications of redesigning camera selection