Design Review. University of Kentucky Lexington, Kentucky 17 November 2006

Transcription

1 Design Review University of Kentucky Lexington, Kentucky 17 November 2006

2 Mission Partners

3 Schedule Welcome Basic Concept of Operations System Overview Tours Shake Testing Facilities Tour Vacuum Testing Facilities Tour Project Status Design Review Session I Bus Pinout Electrical Power System System Support Module VHF/UHF Radio S-Band Radio Camera Design Review Session II Antennas (RF) Antenna Deployment Solar Arrays Flight Software Ground Station Software Ground Station Hardware Electrical Engineering Facilities Tour Testing Review Session Shake Bake Communications Software Deployment Risks Schedule Solar Arrays Open Discussion Wrap Up 17 November /128

4 Concept of Operations 9:15 9:45am Mr. Daniel Erb

5 KySat Concept of Operations KySat will have two distinct modes of operation The first mode will be geared toward teachers, students and basic users The second mode will be geared toward advanced users and HAM radio enthusiasts 17 November /128

6 KySat Mode 1 Operation 17 November /128

7 KySat Mode 2 Operation 17 November /128

8 Hardware Systems Review 9:45 10:15am Mr. Daniel Erb

9 KySat System Priorities Critical Systems Required Systems Frame Solar Panels Passive Attitude Control Electrical Power System Support Systems Batteries Mass Storage VHF / UHF System Non-Critical Systems VHF / UHF Antenna S-Band Processor Board Camera 17 November /128

10 I2C Heat On System Block Diagram 5v VHF UHF 3.3v SD Card S-Band Radio S-Band X Matching Circuit 4 SPI 2 UART 5v 3.3v Vbatt VHF/UHF Radio Analog Audio SW UART I2C 2 2 Flight Computer I2C Heat On 2 Electrical Power System Vsc I2C 3.3v Solar Cells x6 5v UART 2 Function Off Vcc ADS Cam On I2C I2C Enable 2 3 GND 3.3v Vbatt I2C Antenna Deployment System Antenna Deployment Analog Audio System Support Module 5v 3.3v Battery Temp Sensor Heater Vbatt 3.3v UART 5v GND Camera Temp Sensor Heater 17 November /128

11 Timeline Status 11:30am 12:00pm Mr. Garrett Chandler

12 Overview Procurement VHF/UHF Radio Electronic Power System Solar Arrays Random Stuff from Pumpkin Random Stuff for Testing Solar Panel PCBs at 31mils Timeline Where We ve Been When We Plan on Arriving 17 November /128

13 Slides 13 through 17 intentionally left out of this distribution.

14 Where We ve Been February KySat ball rolls for the first time May 24 Consortium press conference June 12 Tech Team immersion experience Stanford interactions NASA Ames interactions High percentage of time-on-task August 9 KySat Briefing & Status Report August 19 Return to Kentucky Beginning of distributed work-effort November 1 - Kentucky University Presidents Meeting 17 November /128

15 When We Plan on Arriving December Engineering model complete December Base-level functional flight software complete January KySat 2 team comes onboard February Ground stations up and tracking March Flight software completed April Flight model complete May Thermal and Vac final tests June Operational testing July Shipment to launch-integrator August thru November Monitor CalPoly testing December 07 On Orbit 17 November /128

16 12:30 1:45pm Design Review Session I

17 Bus Pinout Mr. Daniel Erb

18 Bus Pinout A pinout is simply a standard to refer back to and keep everything organized It is a necessity especially when working with multiple teams at multiple locations The pinout began to be specified at the end of the summer and was completed during the fall term 17 November /128

19 Electrical Power System Mr. Daniel Erb

20 Electrical Power System Without the use of large batteries there must be a way of powering the satellite Different subsystems have different power requirements Communications systems have a very large power draw Must be extremely reliable 17 November /128

21 Electrical Power System Requirements 5W Regulated 3.3v Converter 5W Regulated 5v Converter Unregulated Battery Voltage on Bus Over/Under Voltage Protection for Battery Charging Regulator for 2 Lithium Ion Cells Battery Fuel Gauge Overcurrent Protection on each rail Current Monitoring on each rail Current Monitoring on each Solar Panel I2C interface to processor for data acquisition Capability for 6 solar panels (one on each face) Autonomous Battery Heater Control Components Shall be Rated for -40C to 85C 17 November /128

22 Electrical Power System DIY vs COTS DIY Exactly fit requirements Total control over design, manufacturing, and testing Little to no external support May not have enough expertise COTS Saves time Support from manufacturer Support from other consumers May not fit requirements Have to live with what manufacturer has chosen 17 November /128

23 Electrical Power System Clyde Space Satellite power system manufacturer Commissioned by Pumpkin Inc. for a CubeSat Power system KySat team met with a representative at the Small Sat conference Will be receiving prototype for testing/integration 17 November /128

24 Electrical Power System Clyde Space Datasheet Meets all requirements Has some additional functionality Multiple voltages from the solar cells Full autonomous control Power Point Tracking Includes battery 17 November /128

25 System Support Module Mr. Daniel Erb

26 System Support Module Need System will at some point become out of spec System will need to be reset There must be a reliable way to remotely reset the processor if all internal mechanisms fail Additional Functionality There will also be some additional functions implemented on the System Support Module board These functions are also mission critical which adds to the importance of the System Support Module 17 November /128

27 System Support Module Functionality Reset the processor both onboard and remotely Control the satellite without a computer Highly accurate mission time clock Robust and dependable antenna deployment mechanism Camera interface 17 November /128

28 SSM Block Diagram UART Cam_On 2 I2C Switch I2C Enable Antenna Deployment Signal 5v 3.3v Camera Interface I2C Antenna Deployment 3.3v Real Time Clock & Watchdog Timer Backup Battery TCXO Vbatt WDT Expiration 5v Analog X Audio Conditioning Network DTMF Decoder Data 5 RC Timing Supervisor Processor to Off_Vcc to Flight Computer 3 3.3v 17 November / v

29 System Support Module DTMF Decoder Used to command the satellite while bypassing the flight computer Used to issue a hard reset to the flight computer if it becomes out of spec Highest power consumption on the System Support Module Zarlink MT88L70 17 November /128

30 System Support Module Real Time Clock Running Mission Time Survives resets/power outages with backup power Uses highly accurate temperature compensated crystal oscillator Needed to schedule commands and to timestamp events and files 17 November /128

31 System Support Module Watch Dog Timer Used to reset the flight computer if it becomes out of spec Can take care of most resets autonomously Has a user selectable time up to 99 seconds Integrated into the real time clock DS November /128

32 System Support Module Temperature Compensated Crystal Oscillator Controls the timing of the real time clock Will give accurate readings in any temperature Accuracy of 10 parts per million compared to 180 DS32kHz 17 November /128

33 System Support Module Backup Power A power source is needed to backup the real time clock in case of power resets/outages Two primary batteries will be used In parallel the pair will give a minimum life of 5 years Hermetically sealed lithium ion 17 November /128

34 System Support Module Backend Logic Microcontroller based Low power Customizable Highly functional 17 November /128

35 Antenna Deployment Highly Mission Critical Robust Dependable System Dual Redundant Deployment Scheme Protected from both Open Circuit and Closed Circuit failures 17 November /128

36 System Support Module Current State Design finalized at the end of summer Bill of materials finalized and ordered Final Schematic Done PCB Layout needs to be completed 17 November /128

37 System Support Module Additional Work Need to finish layout Manufacture and assemble boards Test functionality Program Microcontroller 17 November /128

38 VHF/UHF Radio Mr. Dale McClure

39 VHF/UHF Requirements Primary Communications Power output Limited input power Transmit Receive Doppler shift compensation 17 November /128

40 VHF/UHF Radio Solution.25W or 1W Stensat Efficient Receiver and transmitter can be turned on separately Doppler shift Standard Ham frequency 17 November /128

41 S Band Radio Mr. Dale McClure

42 S-Band Radio Requirements Experimental High-Bandwidth Adjustable data rate Adjustable power output Doppler shift compensation 17 November /128

43 S-Band Radio Solution Microhard MHX-2400 Up to 115,200bps Can go as low as 2,400bps 1mW 1W adjustable output Can compensate for 20khz Doppler shift 17 November /128

44 Onboard Digital Camera Mr. Gregory Strickler

45 Onboard Digital Camera Payload As a group we decided that an onboard camera was essential for KySat1. Gives the schools / students the recognition / pride of taking an actual picture of the earth from space. 17 November /128

46 Camera Specs CO Media s C Operates at 3.3volts with a current of 60mA Operating temperature range 0 25C Weighs approximately 5 grams. Fairly inexpensive. ~$50.00 Multiple resolution JPEGs Serial interface 17 November /128

47 Operation TakePic() command sent to KySat1 Camera turns on Picture sequence Multiple resolutions (max: 640x480) Stores pictures on the file system Camera turns off 17 November /128

48 2:15 3:30pm Design Review Session II

49 Antennas Mr. Dale McClure

50 Antenna Solution Gold plated tape measure Gold gives good conductivity Spring steel allows for collapsibility Monopole, only one null 17 November /128

51 Antenna Deployment Mr. William Hutchison III

52 Requirements Longest antenna deploys two shorter ones Reliable actuation Stowed profile within P-POD limits Eliminate cold welding possibility Restraint of stowed antennas in all dimensions Cannot scratch solar cells stowed No detachable parts/debris Steel antenna spring force must overpower passive stab magnet attraction 17 November /128

53 EoS Decisions Monofilament nylon vs. cotton Heated nichrome wire line cutter Use side-force to encourage contact w/cutter Degradable nylon link for eventual fail-safe Straight pull deployment line, no pulleys Possible auxiliary coil spring to tension line Use of cover glass to protect cells Use of kapton tape to prevent cold welding Exact placement of line cutter left for later 17 November /128

54 Progress since EoS Thinner solar array boards allows design iteration of mounts, radius blocks, locators to simpler, hand-fitted versions. EoS side-force cutter too complicated, too small Instead, use stretched nichrome wire coil Re-design of solar arrays allows surface placement of cutter terminals = straight pull, lowest height, no loose wires, no pulleys Locate cutter on abbreviated A face (where no solar cells) P-POD height/rail gauge 17 November /128

55 EoS Deployment Design Cotton Line Nichrome wire Debris containment Cute-1 Cotton line cutter EoS side-force cotton-line cutter (Tokyo Institute of Technology) 17 November /128

56 New Deployment Design Nichrome coil Cotton line U of Hawaii at Manoa describes extreme difficulty in winding nichrome wire coil to diameters smaller than ~1mm. Therefore, coil is not in intimate contact with line and coil may short turn-to-turn. Stretched out nichrome coil increases minimum coil diameter, forces intimate contact with line, prevents turn-to-turn shorts and allows redundant cuts of line. A Teflon-coated glass capillary tube with fabric filters at ends traps debris. 17 November /128

57 Schedule S-band antenna mount Dec 06 Produce antenna-adapted solar board art EoY 06 Mock deploy mechanism (for thermal test) EoY 06 Solar boards available for testing Jan 07 Machine flight model frame for UHF/VHF mounts & fitting of antennas Mar 07? Flight Model Mar 07? 17 November /128

58 Problems Cover glass on cells beneath stowed antennas? ME has no experience w/ PCB design software Hand-fitting entails likely mistakes/delays 17 November /128

59 Example of Level of Detail 17 November /128

60 Solar Arrays Mr. William Hutchison III

61 Requirements Design around Spectrolab TASC cells Groups of at least two cells in series Expose as many as possible Use Pumpkin mounting clips 4 different face designs Endure launch stresses Protect cells in space environment Produce useful power for life of mission 17 November /128

62 EoS Decisions Design art for only one face available Art is adaptable to other faces May modify to suit antenna design/placement KySAT team will adapt Pumpkin Art 17 November /128

63 Progress Since EoS Thinner PCB s proposed and ordered (one face only) Central mechanical attachment needed to hold arrays planar Cover glass is optional for LEO Affordable encapsulant found & ordered Toaster oven successful as reflow chamber Removal of flux solved Have three working 62 mil arrays available for shake/bake Power loss estimate due to encapsulant &/or glass Broken cells still produce power Nov 9 th : ME now tasked with producing adapted art 17 November /128

64 Schedule Receive encapsulant Nov 06 Unmodified boards ordered Nov 06 Above available for shake/bake tests Dec 06 Produce antenna-adapted art by EoY 06 Available for shake/bake tests Jan 07 Opt l test w/ cover glass &/or thick PCB s Feb 07 Flight models available within 2 weeks or less of successful shake/bake tests Mar November /128

65 Problems Available art incompatible with current s/w ME unfamiliar with PCB design software Thinner PCB s = weaker, likely less vibe resistant Thinner PCB s = need shim for clips - solved/untried Thinner PCB s = smaller antenna radii Thinner PCB s = less material to work with. Requires hand fitting and shaping of antenna mounts, radius blocks and deployment mechanism (takes more time due to likely mistakes) 17 November /128

66 Flight Software Mr. Samuel Hishmeh

67 Presentation Scope Implementation Current software status Design decisions Future goals 17 November /128

68 Challenges Student designed Time frame Complexity Missing pieces File system Audio Camera System Support Module Power System 17 November /128

69 Software Flow Diagram 17 November /128

70 Packet Format TNC2 Header 20 bytes Esc : APRS 2 bytes Raw Packet KCOM Data 2 to 62 bytes Esc \r Source 6 bytes TNC2 Header Dest 6 bytes Esc > Esc, Path 6 bytes Frame ID 1 byte KCOM Data Payload (0 to 15) * 4 bytes Frame Length 1 byte File Access File ID 4 bytes Dir ID 1 byte Packet ID 2 bytes Payload Data 0 to 38 bytes Encoding MIME Blue KS64 Red Timestamp Year Month Day Hour Minute Second 6 bits 4 bits 5 bits 5 bits 6 bits 6 bits 17 November /128 Time - Green

71 Incoming Packets VHF radio receives data Sends to MSP430 Timer A enabled GPIO Pin Timer A receives and adds to queue GPIO Interrupt start flag data Timer A Packet Rx 17 November /128

72 Packet Received Packet Rx receives bytes Waits for packet delimiter Checks packet Decodes packet Adds command 17 November /128

73 Command Received Appropriate function executed Acknowledgement sent, if any 17 November /128

74 Implemented Commands Beacon Change beacon period Telemetry Send telemetry packet Acknowledgement Enable/disable acknowledgement Audio Play audio Real Time Clock Set time 17 November /128

75 Full Command List 17 November /128

76 Telemetry vs. Beacon Beacon Sends information at timed interval Sends information in APRS format Telemetry Sends information only on request Sends information as KCOM data 17 November /128

77 Telemetry Format (1/2) Hard State Data Soft State Data 32 bytes 10 bytes No. of Received VHF Packets No. of Sent UHF Packets No. of DTMF Cmds Received No. of Received S-band Packets No. of Sent S-band Packets 2 bytes 2 bytes 2 bytes 2 bytes 2 bytes Solar Cell Voltage 1 (mv) 2 bytes Solar Cell Voltage 2 (mv) 2 bytes Solar Cell Voltage 3 (mv) 2 bytes Solar Cell Voltage 4 (mv) 2 bytes Solar Cell Voltage 5 (mv) 2 bytes Solar Cell Voltage 6 (mv) 2 bytes Solar Cell Current 1 (ma) 2 bytes Solar Cell Current 2 (ma) 2 bytes Solar Cell Current 3 (ma) 2 bytes Solar Cell Current 4 (ma) 2 bytes Solar Cell Current 5 (ma) 2 bytes Solar Cell Current 6 (ma) 2 bytes Bus Voltage 1 (mv) 2 bytes Bus Voltage 2 (mv) 2 bytes Bus Current 1 (ma) 2 bytes Bus Current 2 (ma) 2 bytes 17 November /128

78 Telemetry Format (2/2) Hard State Data Soft State Data 26 bytes 14 bytes No. of Audio Files Played 2 bytes Solar Cell Solar Cell Solar Cell Solar Cell Solar Cell Solar Cell Temperature 1 Temperature 2 Temperature 3 Temperature 4 Temperature 5 Temperature 6 ( Cx10-3) ( Cx10-3) ( Cx10-3) ( Cx10-3) ( Cx10-3) ( Cx10-3) 2 bytes 2 bytes 17 November bytes 2 bytes 2 bytes 2 bytes No. of No. of No. of No. of No. of No. of CW Battery Autonomously DigiBeacons Seconds Pictures Beacons Heater Duty Executed Sent Passed Taken Sent Cycle Cmds 2 bytes 2 bytes 2 bytes 2 bytes 2 bytes 2 bytes Secondary Secondary Charger Camera VHF UHF Processor Battery Battery Current Temperature Current Current Temperature Voltage Temperature (ma) ( Cx10-3) (ma) (ma) ( Cx10-3) (mv) ( Cx10-3) 2 bytes 2 bytes 2 bytes 2 bytes 2 bytes 2 bytes 2 bytes 82/128

79 Beacon Format 17 November /128

80 Audio Command executor calls audio playback function Audio playback specifies file and enables Timer B to play audio every 8 khz Play byte function converts to analog Analog data sent to radio Command Executor Audio Playback Timer B Play Byte UHF Radio 17 November /128

81 Audio Playback Command to Play Audio File Call the Play Audio Function Already Playing? yes Ignore no Enable 8kHz interrupt 17 November /128

82 Send Packet Packet Tx polls queues Forwards beacon Encodes raw 17 November /128

83 Hardware Allocation Timer A UHF send digital 1,200 baud VHF receive digital Timer B 4,800 baud Operating system ticks 100 Hz UHF send audio 8,000 Hz USART0 UART I2C SPI USART1 UART SPI Camera Radio Control Power System SSM (System Support Module) Watch dog timer Real time clock Camera temperature sensor SD Flash S-Band Radio Not used 17 November /128

84 Future Goals Command Scheduler Camera Control Take Pictures Check temperature Power System Telemetry Windows File System Send file Receive file UHF/VHF radio control S-Band Radio control 17 November /128

85 Questions? 17 November /128

86 Ground Station Software Mr. Gregory Strickler

87 Ground Station Software The Ground Station software will be written in Python. Python is a scripting language that has many advantageous properties that our ground station will harness. GUI Serial Interface Libraries TelNet Libraries Portability End users usage 17 November /128

88 Purpose Run the satellite Execution of commands Monitoring key telemetry points Reassembly of packets Disassembly of packets Download packets from APRS network 17 November /128

89 Command Categories Beacons Digital Uplink Control Acknowledge Control Acknowledge Telemetry Windows Real Time System Reset Photograph Power Mode Auto Power Down Play Audio S-Band Control Beacon Request Stop Action Command Scheduler Request File Send File 17 November /128

90 Structures Used Frame: border Fields: to enter arguments Buttons: to execute commands Textbox: to show telemetry data and assemble and disassemble files. 17 November /128

91 Ground Station Hardware Ms. Jennifer Carter

92 Presentation Overview Systems Overview Hardware Evolution Stanford/CalPloy Ground Operations UHF/VHF System Design Layout S-Band System Design Layout Implementation Plan 17 November /128

93 System Overview KySat Primary Ground Station Command and Control User Students, Teachers, Ham Operators 17 November /128

94 Ground Operations Track KySat Use SatPC32 & NORAD Keps Command KySat Transmit Data files Voice and Image House Keeping Telemetry Upload Data files Transmit Data files Voice 17 November /128

95 Hardware Evolution Stanford Ground Station CalPoly Antennas on top of building Control room the size of a broom closet Ground Station Antenna s on top of building Small control area big capabilities Standard UHF/VHF Ground Station Taken from Amateur Low Cost Ham Designs MSU approach 17 November /128

96 UHF/VHF Block Diagram Lightening Arrestors RS-232 RS-232 RS November /128

97 UHF/VHF Antenna System Used to track, command, receive & upload data files to KySat Transmit frequency: ~144 MHz Receive frequency: ~433 MHz Low risk component of KySat Standard system RF engineer on-site (Jeff Kruth) Easy and Quick to assemble About a weekend after site preparation 17 November /128

98 UHF/VHF Components Computer Any running MS Windows Tracking (SatPC32) Command, control & downlink (KySat team) Telemetry & Data files Webcam On-orbit operations can be viewed on KySat website via webcam 17 November /128

99 UHF/VHF Components Terminal Node Controller (TNC) PacComm Packet Controller Interface between transceiver and computer Converts audio to digital & digital to audio AX.25 Protocol 17 November /128

100 UHF/VHF Components Transceiver ICOM Transmit Power: 100 W Completely Computer Controllable Doppler Tuning via SatPC32 Power Supply Astron 50 Amp 13.8 Volt Power Amplifier (optional) Would provide ~ 3dB extra Power PC Software: SatPC32 -Track KySat Command Data Aquisition 17 November /128 RS-232 ICOM Transceiver Power Amplifier (Optional)

101 UHF/VHF Components Rotator Controller Zl2AMD Auto-tracking LNA Circular Polarized Combiner Az/El Rotator Lightening Arrestors PolyPhaser Protect from power surge Rotator Cable Antenna Cables Lightening Arrestor LMR400 Flex Coax 17 November /128

102 UHF/VHF Components Cables FMR 600 Run together from LER to antenna tower Low loss UHF/VHF Convert to FMR 400 Flex Coax Cross Polarization Combiner Low Noise Amplifier (LNA) Gain 15 db Noise Figure ~ < 1dB Az/El Rotator- Yaesu UHF VHF (70 cm circular polarized) (2 meter circular polarized) LNA Circular Polarized Combiner 600 Low Loss Coax Az/El Rotator 400 Flex Coax 17 November /128

103 UHF/VHF Components Antennas M2 Antenna Systems Tx: 2 Meter (VHF) Gain dbdc UHF (70 cm circular polarized) VHF (2 meter circular polarized) Rx: 70 Cm (UHF) Gain 16.8 dbdc Cross Dipole Yagi Circular polarization KySat rotation LNA Circular Polarized Combiner Az/El Rotator 400 Flex Coax 17 November /128

104 S-Band Antenna System Microhard: Validate Transceiver GHz Output Power = 1 W Frequency hopping Desirable because: Commercial Off-the-Shelf Component Low cost ($600 compared to $6000) High Bandwidth (115,200 baud) Moderate Risk Payload (Experimental) Frequency hopping: Causes a delay issue that may lead to loss of data poor synchronization Relatively low EIRP Doppler Shift ~ 20x worse than VHF 17 November /128

105 S-Band Feed Currently do not have an S-Band Feed horn Design by Jeff Kruth Standard Conical Feed Horn Two Probes Physical and Phase Orthogonal S-band Microhard Radio In Out Coaxial Transfer Relay LHCP RHCP Coaxial 90 Quadrature Hybrid Coupler Vertical Probe Horizontal Probe 17 November /128

106 21 M Tracking Antenna Final Commissioning Fall 2006 Verified for LEO tracking Drive Speeds Azimuth: 3 /s Elevation: 2 / s Drive Acceleration Az/El: 1.5 /s 2 Can track LEO s as low as 350 miles up to 77 without keyhole effect S-Band Gain Analysis Assume Uniform Illumination Gain = ηa4π / λ 2 With η = 60% and λ = 12.5 cm Diameter = 21 m Area = π D 2 /4 = 346 m 2 Gain = 52.2 db 17 November /128

107 Implementation Plan UHF/VHF Antenna System Assemble and test all components Pour foundation Rotator Test with other cubesats (February 2007) S-band Antenna System Design/construct S-band feed horn (Spring 2007) Test (Fall 2007) 17 November /128

108 4:00 4:30pm Testing Plans Review Session

109 Shake & Bake Mr. Dale McClure

110 Vibration Testing Test if all components will survive launch Comply with CalPoly and DNEPR specifications Currently testing new solar panel PCB s 17 November /128

111 Thermal/Vacuum Testing Place all components under vacuum Thermal cycle Test electronic component integrity Test for outgassing Outgassing will cause: Solar cells inefficiencies Poor picture quality 17 November /128

112 Communications Mr. Dale McClure

113 Communications Testing Test S-Band Doppler shift compensation Test input power of all radios Test output power of all radios Test SWR at each antenna Check antenna patterns for nulls 17 November /128

114 Software Mr. Samuel Hishmeh

115 Software Testing Past Compiler debugger Present Hyper Terminal (radio simulation) Near Future VHF/UHF radios Future Integration with ground station software Exhaustive test bench 17 November /128

116 Deployment Mr. William Hutchison III

117 Deployment Sequence P-POD door opens Exit from P-POD ( 44.5N spring force, 1.5g)) Spring separators operate ( 13N, 0.7g) Deployment switch operation & initial power up Time delay to line-cutter actuation Antenna deployment Line-cutter shutdown Full electrical operation: radio transmit, EPS schedule, heater Eclipse Sunlight ( 2.2g max) Passive stabilization & antenna orientation Receive commands, transmit telemetry, charge/discharge cycles, heater cycles Respond to commands, store data, transmit data from commands 17 November /128

118 Deployment Testing Stresses Acceleration Spin (angular velocity) Thermal Sunlight/State of Charge Vacuum Combinations of the Above Divorce shake/bake/out-gassing tests from operational deployment testing Test Pod may substitute for a P-POD Resign to testing individual components separately in a smaller vacuum chamber in order that we may achieve a higher vacuum level Thermal stresses are likely not extreme during deployment since the hardware has not cooled yet 17 November /128

119 Testing Considerations Acceleration (low level & probably not necessary to test -- if survive vibe tests) Spin (low level & difficult to test under operation) -- do without Thermal Difficult to access thermal/vac chamber to confirm operation Substitute conventional oven/dry ice ( -78C) Vacuum Satellite w/ antennas too big to test in thermal/vacuum chamber Could build a chamber out of 6 PVC pipe with a pass-through for wiring. Do not know what vacuum level we could achieve Or, assume out-gassing vacuum levels are sufficient stress & proof of operation if survive before and after Smaller items (i.e. separation switch and electronic boards) could be tested in a smaller vacuum chamber Sunlight/State of Charge (optional since it extends into Operational Testing) Substitute halogen lights to excite solar cells Manually change or discharge batteries 17 November /128

120 Possible Deployment Tests Stress Dimensional fit/slide test T Spring separator function (optional, probably not necessary) T Deployment switch operation & actuation of electronics T,V Time delay to line cutter actuation T,V Antenna deployment T,V Line cutter shutdown T,V Full electrical operation: radio transmit, EPS schedule, heater T,V Receive commands, transmit telemetry, charge/discharge cycles, heater cycles T,V Respond to commands, store data, transmit data from commands T,V T = Thermal, V = Vacuum An additional battery of tests may incorporate Eclipse/Sunlight (or State of Charge) to extend further into Operational Testing Operational Testing? 17 November /128

121 Project Risks Discussion 4:30 5:00pm Mr. Garrett Chandler

122 5:00 5:30pm Open Discussion

123 5:30 5:45pm Wrap Up

124 First, the vision for space exploration is a multi-generational program. It will require decades. The people who will be taking us to Mars and beyond are in elementary and middle school. - NASA Administrator Mike Griffin 6/10/2005