RockSat-C 2012 CDR WVU Rocketeers Critical Design Review WVU Justin Yorick, Ben Province Advisors:...

RockSat-C 2012

CDR

WVU RocketeersCritical Design Review

WVUJustin Yorick, Ben Province

Advisors: Dr. Vassiliadis, Marc Gramlich

1

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

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

RockSat-C 2012

CDR


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

RockSat-C 2012

CDR


5

• Section 7: User Guide Compliance– Compliance Table– Sharing Logistics

• Section 8: Project Management Plan– Schedule– Budget

• Mass• Monetary

– Work Breakdown Structure

RockSat-C 2012

CDR

Mission OverviewJustin Yorick

6

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

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

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

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

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

RockSat-C 2012

CDR

Organizational Chart

12

Project ManagerJustin Yorick

System EngineerMarc Gramlich

Faculty AdvisorDimitris Vassiliadis

Mark KoepkeYu Gu

SponsorsWVSGC,

Dept. of Physics,ATK Aerospace

Testing PartnersATK Aerospace

WVU CEMR

Safety EngineerPhil Tucker

Legacy ComponentsB. Province

GHGEB. Province

RPEMike Spencer

DPEJ. Yorick

Structural DesignBen Province

CFODimitris Vassiliadis

Simulation and TestingJ. Yorick

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 OFFDPE OFF

h=117 km (T=02:53)Apogee

h=0 km (T=13:00)Splashdown

h=10.5 km (T=05:30)Chute deploysRedundant atmo. valve closed

h=52 km (T=00:36)End of Orion burn

DPE begins

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=TBDCV decompresses to T= -5C

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.

RockSat-C 2012

CDR

Expected Results: CRE

16

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

RockSat-C 2012

CDR

RockSat 2012 GHGE Temperature RangesT

empe

ratu

re (

C)

Time (s)

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)1 5 1748 40 126.69 513.80 115.502 35 27060 40 13.34 98.46 22.133 322 17294 -5 27.30 177.46 39.894 352 10065 -5 58.55 190.47 42.825 382 6591 -5 63.07 114.63 25.776 412 5497 -5 64.98 83.87 18.857 442 5119 -5 65.70 72.25 16.248 472 4739 -5 66.45 60.01 13.499 502 4406 -5 67.13 48.79 10.97

10 532 4061 -5 67.86 36.66 8.2411 562 3728 -5 68.59 24.44 5.4912 592 3392 -5 69.35 11.57 2.6013 622 3090 -5 70.06 142.07 31.9414 652 2784 -5 70.79 147.34 33.1215 682 2420 -5 71.70 153.87 34.5916 712 2132 -5 72.43 159.23 35.8017 742 1838 -5 73.21 164.90 37.07

Pre

ssur

e (P

a)

Time (s)

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

RockSat-C 2012

CDR

Design DescriptionBen Province

21

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.

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

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

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

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

RockSat-C 2012

CDR

Payload Mechanical Overview (1)

RockSat-C 2012

CDR

Payload Mechanical Overview (2)

RockSat-C 2012

CDR

Payload Mechanical Profile

RockSat-C 2012

CDR

GHGE Mechanical Overview (1)

Color Code:Plates Which Must Be MachinedThreaded RodUnthreaded Rod

17-Tooth Cog

ANSI #35 Roller-Chain

17-Tooth Cog

ANSI #35 Roller-Chain

9-Tooth CogANSI #35

Roller-Chain

9-Tooth CogANSI #35

Roller-Chain

26-LinkANSI #35

Roller-Chain(not shown)

26-LinkANSI #35

Roller-Chain(not shown)

3/8” Ball Shaft3/8” Ball Shaft

3/8” Ball Nut3/8” Ball Nut

Thrust BearingsThrust Bearings

2” Bore X 1.5” Stroke Pneumatic

Cylinder

2” Bore X 1.5” Stroke Pneumatic

Cylinder

Control Volum

e

Control Volum

e

Solenoids

Solenoids

1/8” NPT Piping(not finalized)

1/8” NPT Piping(not finalized)

RockSat-C 2012

CDR



RockSat-C 2012

CDR



Adapter Platemates to canister floor

Adapter Platemates to canister floor

Optical Encoder Wheel(not finalized)

Optical Encoder Wheel(not finalized)

10-Tooth PulleyMXL Timing

Chain


Chain

75-Tooth LoopMXL Timing

Chain

75-Tooth LoopMXL Timing

Chain


Chain


Chain

12VDCElectric Motor

12VDCElectric Motor

¼” to 3/8”

Coupler

¼” to 3/8”

Coupler

¼” Threaded Rodsupports plates

¼” Threaded Rodsupports plates

RockSat-C 2012

CDR



RockSat-C 2012

CDR



GHGE Control Board

GHGE Control Board

RPE Rx

Board

RPE Rx

Board

Makrolon Plate(not finalized)

Makrolon Plate(not finalized)

RockSat-C 2012

CDR

Optical Plate Mechanical Overview

Optical CameraOptical Camera

Geiger TubesGeiger Tubes

Power BoardPower Board

FD Board

FD Board

RockSat-C 2012

CDR

Optical Plate Mechanical Top View

RockSat-C 2012

CDR

Optical Plate Mechanical Bottom View

CREGeigerBoard

CREGeigerBoard

RockSat-C 2012

CDR

DPE Mechanical Overview

PlasmaControlVolume

PlasmaControlVolume

LaserLaser

OpticalCameraOpticalCamera

DPEControlBoard

DPEControlBoard

RockSat-C 2012

CDR

DPE Mechanical Top View

RockSat-C 2012

CDR

Electrical Design Elements

• PSS pcb:

40

RockSat-C 2012

CDR


• FD pcb

41

RockSat-C 2012

CDR


• CRE pcb

42

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

uControllerFlight Dynamics

FlashMemory

Z Accel

Gyro X/Y

ADCInertial

Sensor

DIGITAL

GeigerCounters

Mag X/Y/Z

P/Q/R

Ax/Ay/Az

Temperature

Battery

CameraOptical Port

Cameraμg

PSS

RockSat-C 2012

CDR

Electrical Design Elements: PSS board

44

Power flow

Comm/Con

Data flow

Legend

Power/Reg

Comp/Store

Sensors

Power Supply G RBF +3.3V

+5V

-5V

+9V

555Timer

GND

Batt V

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

uControllerFlight Dynamics

FlashMemory

Z Accel

Gyro X/Y

ADCInertial

Sensor

DIGITAL

GeigerCounters

Mag X/Y/Z

P/Q/R

Ax/Ay/Az

Temperature

Battery

CameraOptical Port

Cameraμg

PSS

RockSat-C 2012

CDR

Software Design Elements

46

RockSat-C 2012

CDR

Prototyping/AnalysisJustin Yorick

47

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.

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

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

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

RockSat-C 2012

CDR

Detailed Mass Budget

52

Part Mass+ (g) Mass- (g) Quantity Cumulative Mass (g) Target Mass (g) +2% kgPrevious Payload 2346 1 2346 5942 6060.84 6.06084- Batteries 45.6 10 1890-antennas and CLE* 100 1 1790

1790 lbfGHGE Solenoids 50 5 2040 13.333848GHGE Cylinder 540 1 2580GHGE Motor* 750 1 3330GHGE brackets 190 1 3520GHGE Rods 283 1 3803GHGE Bearings, couplers, etc.* 300 1 4103GHGE Plumbing* 300 1 4403DPE* 900 1 5303

5303Batteries 45.6 15 5987

* indicates an estimate

GHGE rods assumed to be steelGHGE brackets assumed 1/4" aluminum

RockSat-C 2012

CDR

Detailed Power Budget

53

Power BudgetSubsystem Component Voltage (V) Current (A) Time On (min) Amp-Hours

Netburner +3.3 .120 20 .04 Netburner +3.3 .120 20 .04 uMag XYZ +5 .020 20 .0066 IMU +5 .070 20 .0233 GYRO XZ +3.3 .0065 20 .00216 Z Accelerometer +5 .001 20 .00033 Thermistor +3.3 .00033 20 .00011Flash +3.3 .006 20 .002Flash +3.3 .006 20 .002Op Amp -5 .068 20 .02266Op Amp +5 .068 20 .02266DPE +3.7 .438 10 .073GHGE +12 1 2 .4CRE +3.3 .120 20 .04

Total (A*hr): .67482Over/Under .32518

RockSat-C 2012

CDR

Manufacturing PlanBen Province

54

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

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

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

RockSat-C 2012

CDR

Mechanical Elements

• RPE– The antennae must be procured, and

properly attached to the payload.

58

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

RockSat-C 2012

CDR

Mechanical Elements

60

Mechanical element construction Gant ChartDecember January February

Construction and Mounting of Geiger array

Purchase of piston cylinderPurchase of tubing and solenoid valvesPurchase of minor mechanical system componentsFabrication of piston assemblyPurchase of GHGE sensors

Construction of patch antenna

Construction of CV for DPE

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

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

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

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

RockSat-C 2012

CDR

Electrical Elements

65

Electrical Element construction ChartDecember January February

Revision of FD PCB

Construction of CRE

Design of GHGE PCBConstruction of GHGE PCB

RPE PCB revisions

DPE PCB designDPE PCB Construction

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

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

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

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

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

RockSat-C 2012

CDR

Testing PlanJustin Yorick

71

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

RockSat-C 2012

CDR


• 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

RockSat-C 2012

CDR


• 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

RockSat-C 2012

CDR


• Schedule

75

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

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

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

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

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

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

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

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

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

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

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

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

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

RockSat-C 2012

CDR

RisksBen Province

89

RockSat-C 2012

CDR

Risk Walk-Down

90

• 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.

RockSat-C 2012

CDR

Risk Walk-Down

91

• 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.

RockSat-C 2012

CDR

User Guide ComplianceBen Province

92

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

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.

RockSat-C 2012

CDR

Project Management PlanJustin Yorick

95

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.

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.

RockSat-C 2012 CDR WVU Rocketeers Critical Design Review WVU Justin Yorick, Ben Province Advisors:...

Documents

Transcript of RockSat-C 2012 CDR WVU Rocketeers Critical Design Review WVU Justin Yorick, Ben Province Advisors:...