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

2. RockSat-C 2012 CDR CDR Presentation Content 2 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

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

4. RockSat-C 2012 CDR CDR Presentation Contents 4 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

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

6. RockSat-C 2012 CDR Mission Overview Justin Yorick 6

7. RockSat-C 2012 CDR 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. 7

8. RockSat-C 2012 CDR 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. 8

9. RockSat-C 2012 CDR 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. 9

10. RockSat-C 2012 CDR 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. 10

11. RockSat-C 2012 CDR 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. 11

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

13. RockSat-C 2012 CDR 13 RockSat 2011: Concept of Operations h=0 km (T=00:00) Launch; G-switch activation All systems power up except RPE Tx and DPE h=75 km (T=01:18) RPE Tx ON DPE ON h=75 km (T=04:27) RPE Tx OFF DPE OFF h=117 km (T=02:53) Apogee h=0 km (T=13:00) Splashdown h=10.5 km (T=05:30) Chute deploys Redundant atmo. valve closed h=52 km (T=00:36) End of Orion burn DPE begins

14. RockSat-C 2012 CDR 14 RockSat 2012 GHGE: Detailed Con-Ops #1 H=1.7 km t=005s (T=40C) #2 H=27.1 km t=035s (T=40C) #3 H=17.2 km t=322s (T=-5C) #4 H=10.0 km t=352s (T=-5C) … #17 H=1.8 km t=742s (T=-5C) H=1.52 km t=004.x s Wallops Valves Open H=1.52 km t=771 s Wallops Valves Close H=TBD km t=TBD CV decompresses to T= -5C

15. RockSat-C 2012 CDR Expected Results 15 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.

16. RockSat-C 2012 CDR Expected Results: CRE 16

17. RockSat-C 2012 CDR 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. 17

18. RockSat-C 2012 CDR RockSat 2012 GHGE Temperature Ranges Temperature (C) Time (s)

19. RockSat-C 2012 CDR RockSat 2012 GHGE Detailed Con-Ops Sample#Time (s)Altitude(km)T_target (C )P_target (kPa)F_max (N)F_max (lbf) 15174840126.69513.80115.50 235270604013.3498.4622.13 332217294-527.30177.4639.89 435210065-558.55190.4742.82 53826591-563.07114.6325.77 64125497-564.9883.8718.85 74425119-565.7072.2516.24 84724739-566.4560.0113.49 95024406-567.1348.7910.97 105324061-567.8636.668.24 115623728-568.5924.445.49 125923392-569.3511.572.60 136223090-570.06142.0731.94 146522784-570.79147.3433.12 156822420-571.70153.8734.59 167122132-572.43159.2335.80 177421838-573.21164.9037.07 Pressure (Pa) Time (s)

20. RockSat-C 2012 CDR 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. 20

21. RockSat-C 2012 CDR Design Description Ben Province 21

22. RockSat-C 2012 CDR De-Scopes 22 –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.

23. RockSat-C 2012 CDR 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. 23

24. RockSat-C 2012 CDR 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. 24

25. RockSat-C 2012 CDR 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. 25

26. RockSat-C 2012 CDR 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. 26

27. RockSat-C 2012 CDR Payload Mechanical Overview (1)

28. RockSat-C 2012 CDR Payload Mechanical Overview (2)

29. RockSat-C 2012 CDR Payload Mechanical Profile

30. RockSat-C 2012 CDR GHGE Mechanical Overview (1) Color Code: Plates Which Must Be Machined Threaded Rod Unthreaded Rod 17-Tooth Cog ANSI #35 Roller-Chain 17-Tooth Cog ANSI #35 Roller-Chain 9-Tooth Cog ANSI #35 Roller-Chain 9-Tooth Cog ANSI #35 Roller-Chain 26-Link ANSI #35 Roller-Chain (not shown) 26-Link ANSI #35 Roller-Chain (not shown) 3/8” Ball Shaft 3/8” Ball Nut Thrust Bearings 2” Bore X 1.5” Stroke Pneumatic Cylinder Control Volum e Solenoid s 1/8” NPT Piping (not finalized) 1/8” NPT Piping (not finalized)

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

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

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

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

35. RockSat-C 2012 CDR Optical Plate Mechanical Overview Optical Camera Geiger Tubes Power Board FD Board

36. RockSat-C 2012 CDR Optical Plate Mechanical Top View

37. RockSat-C 2012 CDR Optical Plate Mechanical Bottom View CRE Geiger Board

38. RockSat-C 2012 CDR DPE Mechanical Overview Plasma Control Volume Laser Optical Camera DPE Control Board

39. RockSat-C 2012 CDR DPE Mechanical Top View

40. RockSat-C 2012 CDR Electrical Design Elements PSS pcb : 40

41. RockSat-C 2012 CDR Electrical Design Elements FD pcb 41

42. RockSat-C 2012 CDR Electrical Design Elements CRE pcb 42

43. RockSat-C 2012 CDR Electrical Design Elements: FD Board 43 Power flow Comm/Con Data flow Legend Power/Reg Comp/Store Sensors Thermistor uMag X/Y/Z uController Flight Dynamics Flash Memory Z Accel Gyro X/Y ADCADC Inertial Sensor DIGITALDIGITAL Geiger Counters Mag X/Y/Z P/Q/R Ax/Ay/Az Temperature Battery Camera Optical Port Camera μg PSS

44. RockSat-C 2012 CDR Electrical Design Elements: PSS board 44 Power flow Comm/Con Data flow Legend Power/Reg Comp/Store Sensors Power Supply GRBF +3.3V +5V -5V +9V 555 Timer GND Batt V

45. RockSat-C 2012 CDR Electrical Design Elements: FD Board 45 Power flow Comm/Con Data flow Legend Power/Reg Comp/Store Sensors Thermistor uMag X/Y/Z uController Flight Dynamics Flash Memory Z Accel Gyro X/Y ADCADC Inertial Sensor DIGITALDIGITAL Geiger Counters Mag X/Y/Z P/Q/R Ax/Ay/Az Temperature Battery Camera Optical Port Camera μg PSS

46. RockSat-C 2012 CDR Software Design Elements 46

47. RockSat-C 2012 CDR Prototyping/Analysis Justin Yorick 47

48. RockSat-C 2012 CDR Analysis Results 48 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.

49. RockSat-C 2012 CDR 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. 49

50. RockSat-C 2012 CDR 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. 50

51. RockSat-C 2012 CDR 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..) 51

52. RockSat-C 2012 CDR Detailed Mass Budget 52

53. RockSat-C 2012 CDR Detailed Power Budget 53 Power Budget Subsystem ComponentVoltage (V)Current (A)Time On (min)Amp-Hours Netburner+3.3.12020.04 Netburner+3.3.12020.04 uMag XYZ+5.02020.0066 IMU+5.07020.0233 GYRO XZ+3.3.006520.00216 Z Accelerometer+5.00120.00033 Thermistor+3.3.0003320.00011 Flash+3.3.00620.002 Flash+3.3.00620.002 Op Amp-5.06820.02266 Op Amp+5.06820.02266 DPE+3.7.43810.073 GHGE +1212.4 CRE+3.3.120 20.04 Total (A*hr):.67482 Over/Under.32518

54. RockSat-C 2012 CDR Manufacturing Plan Ben Province 54

55. RockSat-C 2012 CDR 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. 55

56. RockSat-C 2012 CDR 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. 56

57. RockSat-C 2012 CDR 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. 57

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

59. RockSat-C 2012 CDR 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. 59

60. RockSat-C 2012 CDR Mechanical Elements 60

61. RockSat-C 2012 CDR 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. 61

62. RockSat-C 2012 CDR 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. 62

63. RockSat-C 2012 CDR 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. 63

64. RockSat-C 2012 CDR 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. 64

65. RockSat-C 2012 CDR Electrical Elements 65

66. RockSat-C 2012 CDR 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. 66

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

68. RockSat-C 2012 CDR 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. 68

69. RockSat-C 2012 CDR 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. 69

70. RockSat-C 2012 CDR 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. 70

71. RockSat-C 2012 CDR Testing Plan Justin Yorick 71

72. RockSat-C 2012 CDR 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. 72

73. RockSat-C 2012 CDR 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. 73

74. RockSat-C 2012 CDR 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 ConOps section. 74

75. RockSat-C 2012 CDR System Level Testing Schedule 75

76. RockSat-C 2012 CDR 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. 76

77. RockSat-C 2012 CDR 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. 77

78. RockSat-C 2012 CDR 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. 78

79. RockSat-C 2012 CDR 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. 79

80. RockSat-C 2012 CDR 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 5v. 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. 80

81. RockSat-C 2012 CDR 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. 81

82. RockSat-C 2012 CDR 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. 82

83. RockSat-C 2012 CDR 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. 83

84. RockSat-C 2012 CDR 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. 84

85. RockSat-C 2012 CDR 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. 85

86. RockSat-C 2012 CDR 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. 86

87. RockSat-C 2012 CDR 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. 87

88. RockSat-C 2012 CDR 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. 88

89. RockSat-C 2012 CDR Risks Ben Province 89

90. RockSat-C 2012 CDR Risk Walk-Down 90 Consequence Netburner fails in flight RPE sweep timing Failure DPE CV pressure loss GHGE thermal controller fails Geiger tube array breaks on launch Possibility 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.

91. RockSat-C 2012 CDR Risk Walk-Down 91 Consequence Patch antenna Not properly calibrated GHGE piston controller fails GHGE temp sensors fail Possibility 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.

92. RockSat-C 2012 CDR User Guide Compliance Ben Province 92

93. RockSat-C 2012 CDR User Guide Compliance Mass : current predictions have payload at 13.33lbf 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 9volt alkaline batteries. 93

94. RockSat-C 2012 CDR Sharing Logistics 94 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.

95. RockSat-C 2012 CDR Project Management Plan Justin Yorick 95

96. RockSat-C 2012 CDR Budget 96 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.

97. RockSat-C 2012 CDR Conclusion 97 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.