WVU Rocketeers Critical Design Review WVU Justin Yorick

WVU Rocketeers Critical Design Review WVU Justin Yorick, Ben Province Advisors: Dr. Vassiliadis, Marc Gramlich Rock. Sat-C 2012 CDR 1

CDR Presentation Content • Section 1: Mission Overview – – – Mission Overview Organizational Chart Theory and Concepts Concept of Operations Expected Results • Section 2: Design Description – – – Requirement/Design Changes Since CDR De-Scopes/Off-Ramps Mechanical Design Elements Electrical Design Elements Software Design Elements Rock. Sat-C 2012 CDR 2

CDR Presentation Contents • Section 3: Prototyping/Analysis – Analysis Results • Interpretation to requirements – Prototyping Results • Interpretation to requirements – Detailed Mass Budget – Detailed Power Budget – Detailed Interfacing to Wallops jessicaswanson. com • Section 4: Manufacturing Plan – Mechanical Elements – Electrical Elements – Software Elements Rock. Sat-C 2012 CDR 3

CDR Presentation Contents • Section 5: Testing Plan – System Level Testing • Requirements to be verified – Mechanical Elements • Requirements to be verified – Electrical Elements • Requirements to be verified – Software Elements • Requirements to be verified • Section 6: Risks – Risks from PDR to CDR • Walk-down – Critical Risks Remaining Rock. Sat-C 2012 CDR 4

CDR Presentation Contents • Section 7: User Guide Compliance – Compliance Table – Sharing Logistics • Section 8: Project Management Plan – Schedule – Budget • Mass • Monetary – Work Breakdown Structure Rock. Sat-C 2012 CDR 5

Mission Overview Justin Yorick Rock. Sat-C 2012 CDR 6

Mission Overview • The goal of this mission is to measure and record information about the atmosphere. – These experiments will compare atmospheric readings to current models of atmospheric behavior. Rock. Sat-C 2012 CDR 7

Mission Overview • Experiment overviews – Flight Dynamics • This experiment will measure the kinematics of the rocket flight, and will be used as a reference for the other experiments. – Cosmic Ray Experiment • The atmosphere is constantly barraged by foreign charge particles and waves from a variety of sources. The atmosphere shields the surface of the earth from these particles. As one travels further from the surface of the earth, the shielding effect decreases. By using an array of Geiger tubes, the team hopes to measure the concentration of cosmic rays in the atmosphere. Rock. Sat-C 2012 CDR 8

Mission Overview • Radio Plasma Experiment – In the earth’s atmosphere, energetic sources cause the ionization of gas particles. This region is collectively known as the ionosphere. The particles are known to oscillate at a given frequency, as a function of charge density. By using a variable frequency radio sweep, one can in theory find the resonance frequency of the ambient plasma. With this information, one can find the plasma density as a function of altitude. Rock. Sat-C 2012 CDR 9

Mission Overview • Greenhouse Gas Experiment – Various gases are thought to play a major role in the warming trends of earth’s environment. Certain gases such as water vapor and carbon dioxide are thought to play the most major roles in this process. Most atmospheric data for gas concentration is measured from a fixed point on the ground. It is the goal of this experiment to measure the concentration of the gases as a function of altitude, and provide some insight into their concentration profiles. Rock. Sat-C 2012 CDR 10

Mission Overview • Dusty Plasma Experiment – Although a plasma is regularly composed of charged gas particles in a dynamic equilibrium. In a dusty plasma, neutral particles of much larger particle diameter are suspended in a lattice equilibrium position. In a normal dusty plasma suspension, gravity plays a key role in lattice formulation. It is the goal of this experiment to study these lattices in the microgravity portions of this flight. Rock. Sat-C 2012 CDR 11

Organizational Chart Project Manager Justin Yorick System Engineer Marc Gramlich Faculty Advisor Dimitris Vassiliadis Mark Koepke Yu Gu CFO Dimitris Vassiliadis Safety Engineer Phil Tucker Testing Partners ATK Aerospace WVU CEMR Sponsors WVSGC, Dept. of Physics, ATK Aerospace Structural Design Ben Province Legacy Components B. Province GHGE B. Province RPE Mike Spencer Rock. Sat-C 2012 CDR DPE J. Yorick Simulation and Testing J. Yorick 12

Rock. Sat 2011: Concept of Operations h=117 km (T=02: 53) Apogee h=75 km (T=01: 18) RPE Tx ON DPE ON h=75 km (T=04: 27) RPE Tx OFF DPE OFF h=52 km (T=00: 36) End of Orion burn DPE begins h=10. 5 km (T=05: 30) Chute deploys Redundant atmo. valve closed h=0 km (T=13: 00) Splashdown h=0 km (T=00: 00) Launch; G-switch activation All systems power up except RPE Tx and DPE Rock. Sat-C 2012 CDR 13

Rock. Sat 2012 GHGE: Detailed Con-Ops H=TBD km t=TBD CV decompresses to T= -5 C #2 H=27. 1 km t=035 s (T=40 C) #3 H=17. 2 km t=322 s (T=-5 C) #4 H=10. 0 km t=352 s (T=-5 C) … #17 H=1. 8 km t=742 s (T=-5 C) #1 H=1. 7 km t=005 s (T=40 C) H=1. 52 km t=771 s Wallops Valves Close H=1. 52 km t=004. x s Wallops Valves Open Rock. Sat-C 2012 CDR 14

Expected Results • FD – The expected results of the FD are the same as previous years, as the flight conditions are expected to vary little. • CRE – The CRE is expected to vary little from the 2010 rocksat flight. In general, the counts are expected to increase as the vehicle gains altitude. Rock. Sat-C 2012 CDR 15

Expected Results: CRE Rock. Sat-C 2012 CDR 16

Expected Results • GHGE – Current models predict that Carbon Dioxide is uniformly distributed in the lower atmospheric regions. The team assumes that this hypothesis is true due to the relatively homogenous nature of the lower atmosphere. Rock. Sat-C 2012 CDR 17

Temperature (C) Rock. Sat 2012 GHGE Temperature Ranges Rock. Sat-C 2012 Time (s) CDR

Rock. Sat 2012 GHGE Detailed Con-Ops Pressure (Pa) Sample# Time (s) Altitude(km) T_target (C ) P_target (k. Pa) F_max (N) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 5 35 322 352 382 412 442 472 502 532 562 592 622 652 682 712 742 1748 27060 17294 10065 6591 5497 5119 4739 4406 4061 3728 3392 3090 2784 2420 2132 1838 40 40 -5 -5 -5 -5 126. 69 13. 34 27. 30 58. 55 63. 07 64. 98 65. 70 66. 45 67. 13 67. 86 68. 59 69. 35 70. 06 70. 79 71. 70 72. 43 73. 21 513. 80 98. 46 177. 46 190. 47 114. 63 83. 87 72. 25 60. 01 48. 79 36. 66 24. 44 11. 57 142. 07 147. 34 153. 87 159. 23 164. 90 Rock. Sat-C 2012 Time (s) CDR F_max (lbf) 115. 50 22. 13 39. 89 42. 82 25. 77 18. 85 16. 24 13. 49 10. 97 8. 24 5. 49 2. 60 31. 94 33. 12 34. 59 35. 80 37. 07

Expected Results • DPE – In a regular dusty plasma, gravitational forces play a key role in the equilibrium position of the plasma lattice. The team expects to see an equilibrium lattice that is different in size and shape from standard models. Rock. Sat-C 2012 CDR 20

Design Description Ben Province Rock. Sat-C 2012 CDR 21

De-Scopes – GHGE – Originally, the team had hoped to measure the concentration of more GHG’s in real time. This setup could not be realized under the current power, size and weight restrictions on the payload. Instead, the team has settled on measuring water vapor and Carbon Dioxide concentration, as a series of discrete steps throughout the payload’s flight. Rock. Sat-C 2012 CDR 22

Descopes • RPE – Originally, the team hoped to use a relatively large Langmuir probe to verify the data found by the swept antennae. The size of the Langmuir probe has been reduced in size to be in compliance with WFF regulations. Rock. Sat-C 2012 CDR 23

Descopes • DPE – The original goal for the DPE was to control and stimulate a dusty plasma under microgravity conditions. At this point, the team is focusing on solely creating a dusty plasma in a microgravity setting. Rock. Sat-C 2012 CDR 24

Off-Ramps • GHGE – The team is currently finalizing a temperature control system for the GHG control volume. As it stands, current calculations show the air temperatures to be below chosen sensor ranges for portions of the flight. To control this problem, the team is attempting to use a master piston and cylinder to compress the air until it reaches the desired temperature. If this control scheme cannot be fully realized, the team will not take samples during portions of the flight with unacceptable temperatures. Rock. Sat-C 2012 CDR 25

Off-Ramps • DPE – As it currently stands, the team hopes to create, stabilize, and study a dusty plasma in microgravity conditions. If it becomes impossible to achieve all of these goals for one reason or another, the team may simply focus on creating the dusty plasma, and forgo the controlled stimulations of the sample. Rock. Sat-C 2012 CDR 26

Payload Mechanical Overview (1) Rock. Sat-C 2012 CDR

Payload Mechanical Overview (2) Rock. Sat-C 2012 CDR

Payload Mechanical Profile Rock. Sat-C 2012 CDR

GHGE Mechanical Overview (1) 17 -Tooth Cog ANSI #35 Roller-Chain 3/8” Ball Shaft 3/8” Ball Nut 26 -Link ANSI #35 Roller-Chain (not shown) Thrust Bearings 9 -Tooth Cog ANSI #35 Roller-Chain 2” Bore X 1. 5” Stroke Pneumatic Cylinder Control Volum e Solenoids 1/8” NPT Piping (not finalized) Rock. Sat-C 2012 CDR Color Code: Plates Which Must Be Machined Threaded Rod Unthreaded Rod

GHGE Mechanical Overview (2) Color Code: Plates Which Must Be Machined Threaded Rod Unthreaded Rock. Sat-C 2012 CDR

GHGE Mechanical Overview (3) 12 VDC Electric Motor 10 -Tooth Pulley MXL Timing Chain ¼” to 3/8” Coupler 75 -Tooth Loop MXL Timing Chain Optical Encoder Wheel (not finalized) 60 -Tooth Pulley MXL Timing Chain Color Code: Plates Which Must Be Machined Threaded Rod Unthreaded Rod ¼” Threaded Rod supports plates Adapter Plate mates to canister floor Rock. Sat-C 2012 CDR

GHGE Mechanical Overview (4) Color Code: Plates Which Must Be Machined Threaded Rod Unthreaded Rock. Sat-C 2012 CDR

GHGE Mechanical Overview (5) Color Code: Plates Which Must Be Machined Threaded Rod Unthreaded Rod GHGE Control Board Makrolon Plate (not finalized) RPE Rx Board Rock. Sat-C 2012 CDR

Optical Plate Mechanical Overview Power Board FD Board Optical Camera Geiger Tubes Rock. Sat-C 2012 CDR

Optical Plate Mechanical Top View Rock. Sat-C 2012 CDR

Optical Plate Mechanical Bottom View CRE Geiger Board Rock. Sat-C 2012 CDR

DPE Mechanical Overview Plasma Control Volume Laser DPE Control Board Optical Camera Rock. Sat-C 2012 CDR

DPE Mechanical Top View Rock. Sat-C 2012 CDR

Electrical Design Elements • PSS pcb: Rock. Sat-C 2012 CDR 40

Electrical Design Elements • FD pcb Rock. Sat-C 2012 CDR 41

Electrical Design Elements • CRE pcb Rock. Sat-C 2012 CDR 42

Electrical Design Elements: FD Board Flash Memory PSS Camera μg Geiger Counters Temperature Ax/Ay/Az Inertial Sensor P/Q/R Camera Optical Port Mag X/Y/Z D I G I T A L u. Mag X/Y/Z u. Controller Flight Dynamics A D C Thermistor Z Accel Gyro X/Y Legend Power/Reg Power flow Comp/Store Comm/Con Sensors Data flow Rock. Sat-C 2012 CDR Battery 43

Electrical Design Elements: PSS board Batt V +9 V Power Supply RBF G +3. 3 V +5 V 555 Timer -5 V GND Legend Power/Reg Power flow Comp/Store Comm/Con Sensors Data flow Rock. Sat-C 2012 CDR 44

Electrical Design Elements: FD Board Flash Memory PSS Camera μg Geiger Counters Temperature Ax/Ay/Az Inertial Sensor P/Q/R Camera Optical Port Mag X/Y/Z D I G I T A L u. Mag X/Y/Z u. Controller Flight Dynamics A D C Thermistor Z Accel Gyro X/Y Legend Power/Reg Power flow Comp/Store Comm/Con Sensors Data flow Rock. Sat-C 2012 CDR Battery 45

Software Design Elements Rock. Sat-C 2012 CDR 46

Prototyping/Analysis Justin Yorick Rock. Sat-C 2012 CDR 47

Analysis Results • CRE • The CRE has been prototyped thus far by building a Geiger circuit and developing code to interface this circuit with the Netburner microprocessor. • Initial prototyping results suggest that the circuit will interface without major problems or failures. • FD • To ensure the FD subsystem functions as required a drop tower is being developed to test the accelerometers in axial directions, while spin testing with WVU CEMR will provide a suitable testing platform to monitor spin. Rock. Sat-C 2012 CDR 48

Analysis Results • GHGE – The designs for the GHGE are reaching a finalized state. With final dimensions, ANSYS finite element modeling will be utilized to calculate system stresses as well as heat transfer information in the piston, testing volume, and piping. – Temperatures in the system are derived from an isentropic expansion of air. As the rocket is traveling above Mach 1, these assumptions yield the team with guideline values only. – If needed, simple CFD may be performed using ANSYS or a suitable program. Rock. Sat-C 2012 CDR 49

Analysis Results • RPE – The RPE requires the successful timing of two swept frequency radio transmitters and receivers. The circuits are to be built, and tested using proper computational programs(name? ) and oscilloscopes. Rock. Sat-C 2012 CDR 50

Analysis Results • DPE – The dusty plasma requires a RF transmitter with sufficient power to excite and ionize gas particles in a control volume. Once the circuit is finalized, the emitter must be tested both with an oscilloscope to ensure proper circuit output. – The system must be used to actually excite a gas as well to ensure proper emitter design. (not sure how we test this. . ) Rock. Sat-C 2012 CDR 51

Detailed Mass Budget Rock. Sat-C 2012 CDR 52

Detailed Power Budget Subsystem Component Netburner u. Mag XYZ IMU GYRO XZ Z Accelerometer Thermistor Flash Op Amp DPE GHGE CRE Voltage (V) +3. 3 +5 +5 +3. 3 -5 +5 +3. 7 +12 +3. 3 Current (A). 120. 020. 070. 0065. 001. 00033. 006. 068. 438 1. 120 Time On (min) 20 20 20 10 2 20 Total (A*hr): Over/Under Rock. Sat-C 2012 CDR Amp-Hours. 04. 0066. 0233. 00216. 00033. 00011. 002. 02266. 073. 4. 04. 67482. 32518 53

Manufacturing Plan Ben Province Rock. Sat-C 2012 CDR 54

Mechanical Elements • FD – The FD subsystem needs little modification or manufacturing. The only foreseeable modifications could come in ballast placement to ensure proper GC and mass alignment of the canister. Rock. Sat-C 2012 CDR 55

Mechanical Elements • CRE – The CRE pcb must be finalized and readied for flight. The board will be ordered from PCBexpress. – The Geiger array with varying shielding must be either rebuilt or reused from a previous flight. This is not anticipated to be an area of concern for the team. Rock. Sat-C 2012 CDR 56

Mechanical Elements • GHGE – The control volume must be assembled, most likely a custom glass vessel built by the chemistry department or the team. – The appropriate tubing must be bought for the inputs, as well as control solenoids for the valve operations. – A piston is to be ordered, and must be soundly interfaced to the system such that it forms an air tight seal with the CV, even at relatively high pressures. – These components must all be assembled so that the experiment can control input temperatures during the flight. Rock. Sat-C 2012 CDR 57

Mechanical Elements • RPE – The antennae must be procured, and properly attached to the payload. Rock. Sat-C 2012 CDR 58

Mechanical Elements • DPE – The DPE will most likely required the use of a custom made, low pressure sealed experimental control volume. The team must also build a mechanism to disperse the dust within the vessel during flight. The team must also properly design, build, and attach the RF generator to the control volume. Rock. Sat-C 2012 CDR 59

Mechanical Elements Rock. Sat-C 2012 CDR 60

Electrical Elements • FD – The FD board requires little if any revision. • CRE – The team will utilize a custom built pcb for the Geiger array. This board must have the various components soldered to their correct locations. Rock. Sat-C 2012 CDR 61

Electrical Elements • GHCE – A pcb must be designed to enable to the sensors to interface with the Netburner, and also allow the Netburner to control the piston and valve system. – Although this circuit should be relatively simple, some revisions may be needed because this will be the first round of the design process for the system component. Rock. Sat-C 2012 CDR 62

Electrical Elements • RPE – Multiple heritage elements will be used in this pcb. Slight revisions may be needed due to a change in antenna type from previous flights. – The patch antenna itself must still be finalized and built. Although less likely, it is possible the antenna itself may need to be revised if not satisfactory. Rock. Sat-C 2012 CDR 63

Electrical Elements • DPE – The DPE makes use of an RF generator, a laser , as well as a camera. The complexity of this task will result in an equally complex circuit. – Due to the relatively complexity of this circuit, it seems probable that multiple revisions may be needed to have an acceptable and usable experiment. Rock. Sat-C 2012 CDR 64

Electrical Elements Rock. Sat-C 2012 CDR 65

Software Elements • FD – Some code modification will be needed to successfully activate and record data from new experiments. – This code block affects all others because it controls the activation of further subsystems. Rock. Sat-C 2012 CDR 66

Software Elements • CRE – The CRE code will remain largely unchanged from previous years, and has little affect on other code blocks. Rock. Sat-C 2012 CDR 67

Software Elements • RPE – The general layout for this experiment’s coding will remain largely unchanged from previous flights. Changes will be focused on improving system performance and adapting the system to a new antenna. Rock. Sat-C 2012 CDR 68

Software Elements • GHGE – The code blocks for this must execute two primary functions. The first must record data from the gas sensors. – The second major block must control valve settings and piston position, based on temperature predictions in addendum to current temperature readings. – The team is considering the addition of a second Netburner to aid in control and data processing for this experiment. Rock. Sat-C 2012 CDR 69

Software Elements • DPE – The DPE code is yet to be fully developed, but is expected to accomplish the following: • The code must be able to activate and deactivate the experiment at the desired points in flight. • The code must be able control the stimulation of the dusty plasma upon release of the dust into the CV. Rock. Sat-C 2012 CDR 70

Testing Plan Justin Yorick Rock. Sat-C 2012 CDR 71

System Level Testing • FD – As a whole, the FD must activate with g-switch triggering, as well as provide accurate recording of flight kinematics. • CRE – The CRE must activate and deactivate at its assigned times in flight (see Con-Ops). – The CRE must also be able to detect high energy particles. To test this, the CRE will be placed next to known radioactive samples. Rock. Sat-C 2012 CDR 72

System Level Testing • RPE – The RPE must activate and deactivate at its assigned times. – The transmitter and receiver will be tested on ground. The results aren’t expected to match ionosphere conditions, but this test will provide insight into the proper timing of the system. Rock. Sat-C 2012 CDR 73

System Level Testing • DPE – The DPE must activate and deactivate at proper times. The system must also be able to produce a plasma in the CV, and insert the dust particles at the proper time, as determined in the Con. Ops section. Rock. Sat-C 2012 CDR 74

System Level Testing • Schedule Rock. Sat-C 2012 CDR 75

Mechanical Testing • FD – The FD subsystem will be assessed by placing it on a drop tower and then a spin platform. These test will not only verify the mechanical soundness of the system, but will aid in instrument calibration for the kinematic sensors. – Test will also be used to find system mass and CG location. Rock. Sat-C 2012 CDR 76

Mechanical Testing • CRE – The CRE will be subjected to vibration and spin testing in addition to test that will measure the subsystem mass and CG. • RPE – The RPE will be vibration and spin tested. The subsystem will also be tested to find its mass and CG. Rock. Sat-C 2012 CDR 77

Mechanical Testing • GHGE – The redundant valves must be tested such that they are able to properly seal the canister in a water landing. This can tested by placing the valves in water. – The solenoid control valves must be tested with pressurized air to ensure they are able to reach the required compression values. – The piston should be strain tested to ensure failure is improbable. – Spin and vibration testing will be used as well to ensure the system will survive. – The mass and CG of this experiment are also very important due to the relative size of the piston. Rock. Sat-C 2012 CDR 78

Mechanical Testing • DPE – The DPE testing must verify that the low pressure CV will not break during the harsh conditions of the rocket launch. The subsystem will be spin and vibration tested to ensure its stability. – The mass and CG of the system will also be found. Rock. Sat-C 2012 CDR 79

Electrical Testing • FD – The FD circuits remain largely unchanged. Testing with a DMM will ensure proper power distribution to other subsystems and the microprocessor. • CRE – The CRE must provide a digital out signal at less than 5 v. The team must ensure this is met to avoid destroying the Netburner. The circuit must also provide the high potential voltage to the Geiger tubes. Both of these parameters can be verified with a DMM. Rock. Sat-C 2012 CDR 80

Electrical Testing • RPE – The RPE board must produce a relatively high frequency signal output with swept pulses. Upon completion, this circuit will be attached to an oscilloscope for output signal verification. – The receiver can be attached to a similar scope to verify the receiver picks up the output pulses from the transmitter. – This data must also be output in a form that can be recorded by the Netburner. Rock. Sat-C 2012 CDR 81

Electrical Testing • DPE – The DPE electrical components must produce an RF signal capable of producing a plasma in the low pressure CV environment. An oscilloscope would be a good tool to measure the outputs of this emitter. – A DMM can be used to measure the signal outputs to the scanning laser. – A more in depth software based approach may be needed to verify that the camera works to its specifications. Rock. Sat-C 2012 CDR 82

Electrical Testing • GHGE – The GHGE electronics must be able to provide sufficient power to the piston actuator, while also being able to power the solenoid valves. This can be tested by doing a test run in static air, as well as with a DMM. – The signals from the GHGE sensors must also be within an acceptable voltage range to be successfully recorded by the Netburner. Rock. Sat-C 2012 CDR 83

Software Testing • FD – By triggering the g-switch, the team will be able to see if the current code will activate the payload as well record flight dynamics information. – Although this code is paramount for other codes to activate, it is a successful heritage element from previous flights and major modifications are not expected. Rock. Sat-C 2012 CDR 84

Software Testing • CRE – The CRE code must be able to decipher digital pulses into a numerical count. This code sequence is also a heritage element, and little modification work is expected. Rock. Sat-C 2012 CDR 85

Software Testing • RPE – The RPE is expected to be able to send variable frequency wave pulses into a plasma environment. The coding must accurately control the RF circuit such that the pulse out and received are properly compared to one another. – This task will require the completion of the previously mentioned electrical testing of this subsystem. Rock. Sat-C 2012 CDR 86

Software Testing • DPE – This code must be able to control the RF generation circuit and record the sensor data from the refracted laser. – This software testing will rely heavily on the successful mechanical and electrical completion of the system. Rock. Sat-C 2012 CDR 87

Software Testing • GHGE – The GHGE code must be able to maintain the CV temperature in the prescribed range. – To do this the team will simulate flow temperatures with compressed air. The algorithm must be able to position the piston such that the CV temperature lies within the acceptable range. Rock. Sat-C 2012 CDR 88

Risks Ben Province Rock. Sat-C 2012 CDR 89

Risk Walk-Down Netburner fails in flight RPE sweep timing Failure DPE CV pressure loss • GHGE thermal controller fails Consequence • Further research and Design have mitigated multiple risk in this mission. Further time must still be spent to lower the risk in the DPE apparatus. Geiger tube array breaks on launch Possibility Rock. Sat-C 2012 CDR 90

Risk Walk-Down • Patch antenna Not properly calibrated GHGE temp sensors fail • Consequence GHGE piston controller fails • One risk of particular interest is the failure of the temperature controller mechanism in the GHGE Design refinement and thorough testing will result in a much lesser risk of this component failing. The risk of antenna failure will be lessened through the previously mentioned prototyping procedures. Possibility Rock. Sat-C 2012 CDR 91

User Guide Compliance Ben Province Rock. Sat-C 2012 CDR 92

User Guide Compliance • Mass : current predictions have payload at 13. 33 lbf • CG: Although the CG is yet to be found through testing, it is believed to lie in the proper space, due in part to properly distributed battery cells and the relative magnitude of mass in the GHGE. It can be noted from the solid models that this experiment lies in the central axis of the payload. • Batteries: current power predictions have the total battery count as 15 9 volt alkaline batteries. Rock. Sat-C 2012 CDR 93

Sharing Logistics • The optical port from the Puerto Rico team canister will be used as the Special Port for the WVU payload. • This is the only sort of sharing for this flight, because the WVU team purchased the entire canister space. Rock. Sat-C 2012 CDR 94

Project Management Plan Justin Yorick Rock. Sat-C 2012 CDR 95

Budget • Approximate budgets: • PSS: $200 • FD incl. magnetometers: $1100 • RPE: $600 • CRE: $200 • GHGE: $375 • Lead times: of the order of <1 week to 10 days. • Funding sources: West Virginia Space Grant Consortium, department of physics. Rock. Sat-C 2012 CDR 96

Conclusion • At this point, the GHGE and DPE need to be finalized in design. • Once all component designs are finalized, the prototyping plan outlined in this presentation will be enacted. Rock. Sat-C 2012 CDR 97