preliminary design review - cosgc home 2013/te… · – system/project level requirement...

2013 PDR

WVU Rocketeers Preliminary Design Review

West Virginia University Alex Bouvy, Ben Kryger, Marc Gramlich

11-12-2012

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2013 PDR

PDR Presentation Content

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•  Section 1: Mission Overview –  Mission Overview –  Theory and Concepts –  Concept of Operations –  Expected Results

•  Section 2: System Overview –  Functional Block Diagram –  Drawings/Pictures of Design –  Critical Interfaces (ICDs?) –  System/Project Level Requirement Verification Plan –  User Guide Compliance –  Sharing Logistics

2013 PDR

PDR Presentation Contents

• Section 3: Subsystem Design – Organizational Chart – Structures – Power – Science – Command and Data Handling – Software – Other

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2013 PDR

PDR Presentation Contents

• Section 4: Initial Test/Prototyping Plan • Section 5: Project Management Plan

– Schedule – Budget – Availability Matrix – Team Contact info

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2013 PDR

Mission Overview Ben Kryger

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Mission Overview: Mission Statement

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•  Mission statement: Develop a payload which will measure the following properties of the space environment (up to 160 km) during the RockSat-X flight.

–  Plasma density/frequency –  Magnetic field –  Flight dynamics –  Magnetic effects on ferrofluids in microgravity –  Eject a standalone picosatellite. The satellite will house a basic payload

consisting of IMU and magnetometer, as well as a transceiver to transmit data back to earth.

•  Goal: To measure and analyze data from the flight, and compare the results

to known atmospheric models. Track the ejected picosatellite to obtain measurements as it descends to earth.

2013 PDR

Mission Overview: Theory and Concepts

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•  Plasma conditions continuously change in the ionosphere with altitude and time of day. At these given times, the plasma fields resonate at different frequencies. The experiment will compare the instantaneous plasma density and frequency distribution to current atmospheric models.

•  Earth’s magnetic field decreases as a function of distance from the center of the earth. The magnetic field reflects and traps many charged particles. Measuring field intensity can yield information required to accurately model this phenomena.

•  Comparison between these measurements and current models will show

if assumptions made in these models hold up to an extent that they can be accurately used in future atmospheric applications.

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Mission Overview: Theory and Concepts cont.

•  Ferrofluids are liquids that respond to magnetic fields. They are typically composed of iron particles suspended in a solvent (usually oil based). In near zero g conditions, it becomes difficult to control how a liquid is oriented in a container. Assuring the fluid remains in a certain location is useful in fuel tanks experiencing zero gravity. The goal is to use an electromagnet in order to sustain the location of the fluid within it’s container.

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2013 PDR

Mission Requirements: Mission Objectives

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•  A payload shall be constructed from which measurements can be made and viable science data obtained.

•  The power block designed shall distribute power to each and every subsystem, and each and every subsystem shall be powered on.

•  The science data obtained should improve upon current data from previous projects.

•  The full payload shall fit on a single RockSat-X deck.

•  The system shall survive the vibration characteristics prescribed by the RockSat-X program.

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Mission Requirements: System Level Objectives: Flight Dynamics (FD)

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•  A system shall be developed to measure the dynamics of the rocket flight, including acceleration, pitch, yaw, and roll.

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Mission Requirements: System Level Objectives: Ferrofluid Experiment (FFE)

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•  A system shall be developed such that a ferrofluid in a closed container can be monitored via external camera.

•  The containment vessel shall be designed/selected to prevent possible spills/leaks of the ferrofluid.

•  The camera system implemented shall properly record video/take pictures on command.

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Mission Requirements: System Level Objectives: Radio Plasma Experiment (RPE)

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•  A system shall be developed to measure the density of a low-energy plasma in the space environment.

•  Both a MHz and GHz antenna shall be designed and implemented to properly transmit corresponding MHz and GHz waves.

•  A functional Langmuir Probe shall be designed and implemented.

•  The antennas and probe should be interfaced to the RockSat-X deck in such a manner as to provide for optimal conditions for measurements to be made.

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Mission Requirements: System Level Objectives: Picosatellite Experiment (PSE)

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•  A picosatellite shall be developed to house a basic payload, as well as a transceiver to transmit telemetry.

•  A transmission protocol shall be implemented to dictate transmission format.

•  An ejection cylinder shall be designed to properly eject

the picosatellite upon command.

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Mission Requirements: Minimum Success Criteria

1.  The payload shall conform to the requirements set forth in the RockSat-X User Guide

2.  The system shall measure the density of a low-energy plasma throughout the flight at no less than 50Hz.

3.  The system shall measure data from each and every inertial sensor throughout the flight at no less than 50Hz.

4.  The system shall observe the effects of ferrofluids in the presence of an electromagnet intermittently throughout flight, accumulating no less than 2 total minutes of video footage.

5.  The payload shall eject a picosatellite to produce a rapidly decaying orbit. Telemetry data shall be received from the picosatellite.

6.  The system shall save high resolution data on a hard disk. 7.  The system shall transmit acquired data through WFF-provided

telemetry for data assurance. 14

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Mission Overview: Expected Results: Plasma

•  Expect at least one or two peaks: –  Plasma frequency –  Gyrofrequency –  Other frequencies possible (upper-hybrid frequency)

•  Gyrofrequency varies little with altitude, plasma frequency significantly:

0.00E+00

5.00E+05

1.00E+06

1.50E+06

2.00E+06

2.50E+06

3.00E+06

3.50E+06

4.00E+06

4.50E+06

0 20 40 60 80 100 120 140 160

Freq

uenc

y (H

z)

Altitude (km)

Frequency Variability

f_ce (Hz)

f_pe (Hz)

f_uh (Hz)

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•  The observed magnetic field is expected to decay following an inverse cube law as a function of distance from the Earth.

•  Note: Earth’s magnetosphere is dynamic and should not be overgeneralized by

an inverse cube law. However, considering an expected altitude maximum of 160 km, standard dipole magnetism models are expected.

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Mission Overview: Expected Results: Magnetic Field

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Mission Overview: Expected Results: Ferrofluid

•  Under the influence of a strong magnetic field, it is expected that the magnetic fluid remain oriented towards the electromagnet throughout the duration of the flight.

•  Fluid sloshing should be reduced in comparison to the non-magnetic control fluid.

•  The control fluid is expected to move freely in it’s container.

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h=0 km (T=0) Launch

h=160 km (T=2.8 min) Apogee Nose Cone Separation Picosatellite Ejected

h=10.5 km (T=5.5 min) Chute deploys

h=0 km (T=15 min) Splashdown

RockSat-X 2013: Concept of Operations

h=10.5 km (T=5.78 min) Experiments Power Off

h=52 km (T=.5 min) End of Malamute Burn

h=0 km (T=-2 min) All systems on, begin data

acquisition

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System Overview Alex Bouvy

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Design Overview

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•  For most experiments (Flight Dynamics, Radio Plasma) heritage elements from previous WVU RockSat-C flights will be integrated into this year’s design.

•  These experiments will go largely unchanged.

•  The remaining Ferrofluid and Picosatellite Experiments will be implemented from scratch.

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Functional Block Diagram Picosatellite Ejection

uController System

Langmuir Experiment

Flight Dynamics

Radio Plasma Experiment

Wallops Power & Telemetry lines

GSE-‐1

GSE-‐2

TE-‐R

TE-‐NR1

TE-‐NR2

TE-‐NR3

Parallel Bits 1-‐8

Power Block

Langmuir Board

IMU

Z-‐Accelerometer

Magnetometer

uController

Ejection Cylinder

Langmuir Probe

SD Card Power

Distribution

LEGEND Power: Red

Digital Signal: Gold

Analog Signal: Olive

Parallel Bits: Lavendar

RPE Board

Antenna

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FBD – Mechanical Diagram (rough)

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Power

LP

RPE

FD

FFE

RPE LPE

Makrolon Layer 1 (PCBs)

Makrolon Layer 2 (Exp. Apparatus)

PSE

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Design Overview: SolidWorks Rendering v1

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PSE

FFE RPE

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Design Overview: Multi View Drawings

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Critical Interfaces: PCBs/RockSat Deck

•  Brief Description –  All of the PCBs for each subsystem must be attached to the RockSat

deck. The PCBs must withstand at least 25 Gs of quasi-static loading in all three axes with possible impulses of approximately 50 Gs in the Z (longitudinal) axis.

•  Possible Solution

–  In the past, the PCBs have been loosely mounted to makrolon plates using aluminum machine screws. Additionally, plastic risers were implemented to mitigate stress.

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Critical Interfaces: uC/PSE

•  Brief Description –  The microcontroller must be connected to the ejection cylinder

of The PSE in such a manner to allow autonomous ejection.

•  Possible Solution –  One potential fix is to make use of an SSR (as used in some

legacy subsystems) to allow triggering of the event.

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2013 PDR

Critical Interfaces: FFE/RockSat Deck

•  Brief Description –  The ferrofluid experiment, consisting of a camera and a

sealed vessel containing a ferrofluid, must be mounted to the RockSat-X Deck. The container must be mounted in such a manner as to avoid leaks.

•  Possible Solution

–  In previous years, containers filled with liquid have been successfully mounted through a portion of a makrolon plate with no incident. This approach may again be utilized.

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Critical Interfaces: PSE/RockSat Deck

•  Brief Description –  The ejection cylinder must have a clear path to space free of

obstructions in order to launch the satellite. –  The cylinder must be securely mounted in order to properly

eject the picosatellite.

•  Possible Solution –  In order to securely fasten the ejection cylinder, metal set

screws can be utilized to lock the cylinder into place.

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2013 PDR

Requirements Verification (1 of 2)

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Requirement Verification Method Description

The full system shall fit on a single RockSat-X deck Inspection Visual inspection will verify this

requirement

The sytem shall survive the vibration characteristics prescribed by the RockSat-X program.

TestThe system will be subjected to these vibration loads in June during testing week.

FFE: The containment vessel shall be designed/selected to prevent possible spills/leaks of the ferrofluid.

Test

The system will be subjected to these vibration loads in June during testing week. Additionally, thorough in-house testing will occur prior to this.

FFE: The camera system implemented shall properly record video/take pictures on command.

Demonstration The camera system will be demonstrated to verify proper operation.

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Requirements Verification (2 of 2)

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Requirement Verification Method Description

RPE: Both a MHz and GHz antenna shall be designed and implemented to properly transmit corresponding MHz and GHz waves.

Demonstration

System will be demonstrated to verify proper transmission and propagation of waves using such devices as an oscilloscope and a spectrum analyzer.

RPE: A functional Langmuir Probe shall be designed and implemented.

Demonstration Proper operation of the Langmuir Probe will be demonstrated in a lab setting.

RPE: The antennas and probe should be interfaced to the RockSat-X deck in such a manner as to provide for optimal conditions for measurements to be made.

Analysis

The probe and antennas should be placed in the most functional position allowed by the envelope of other subsystems. CAD modeling will be used as a planning aid to most efficiently place subsystems.

PSE: The ejection cylinder shall properly eject the picosatellite upon command.

Demonstration System will demonstrate that the picosatellite is ejected on command.

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RockSat-X 2013 User’s Guide Compliance

Preliminary Mass Budget

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Subsystem/ Component Mass (lb)

RPE 2 Total Mass Alotted (lb)FFE 1 15±0.5FD 0.5PSE 3 Total Mass (lb)uC 0.25 10

Power Block 0.25Makrolon/Deck 2

Other 1

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RockSat-X 2013 User’s Guide Compliance

Timed Event Lines: –  One timed event line will be used to time the ejection of our picosatellite.

ADC Lines:

–  The 5 allotted ADC lines for our team will be used for the RPE subsystem.

Parallel bits: –  The 8 parallel bits allotted will monitor the status of each of our

individual subsystems. Asynchronous line:

–  Our asynchronous line will be used for RS-232 communications to transmit data from our other subsystems (Flight Dynamics, etc.). Bit rate will be shared evenly with canister partner.

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2013 PDR

Shared Can Logistics

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Johns Hopkins University: •  Measure electron density using a dual frequency

GPS as well as observe effects on an aerogel container.

•  Communication will consist of team e-mails, phone calls, and occasional in-person meetings.

•  Payloads will be interfaced at WFF. Interfacing standards TBD.

2013 PDR

Subsystem Design Ben Kryger

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2013 PDR

Organizational Chart

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Project Manager Alex Bouvy

Systems Engineer Ben Kryger

Faculty Advisors Dimitris Vassiliadis

Marcus Fisher Sponsors WVSGC,

Dept. of Physics, Testing Partners ATK Aerospace

WVU CEMR

Safety Engineer Phil Tucker

RPE A. Bouvy (lead)

M. Gramlich

FFE B. Kryger (lead)

A. Bouvy

FD B. Kryger (lead)

A. Bouvy

Power Mgmt. M. Gramlich (lead)

A. Bouvy

Test Lead M. Gramlich

PSE A. Bouvy (lead)

B. Kryger

2013 PDR

Subsystem Design: Flight Dynamics (FD)

•  Critical components: –  Inertial Measurement Unit (IMU) –  Magnetometer –  Hi-Res Accelerometer –  Hi-Res Gyroscope

•  Approximate mass: .5 lb.

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2013 PDR

Subsystem Design: Flight Dynamics (FD) Schematics

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2013 PDR

Subsystem Design: Flight Dynamics (FD) Schematics

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Subsystem Design: Flight Dynamics (FD) Model

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Flight Dynamics

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Subsystem Design: Radio Plasma Experiment (RPE)

•  Critical components: –  Langmuir Probe –  GHz Antenna –  MHz Antenna

•  Approximate Mass: 2 lb.

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2013 PDR

Subsystem Design: Radio Plasma Experiment (RPE) Schematics

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2013 PDR

Subsystem Design: Radio Plasma Experiment (RPE) Schematics

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2013 PDR

Subsystem Design: Radio Plasma Experiment (RPE) Model

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2013 PDR

Subsystem Design: Ferrofluid Experiment (FFE)

•  Critical components: –  HD Camera

•  Prospective camera: GoPro HD Hero –  Ferrofluid vessel –  Potential full experiment enclosure depending on tested

durability. •  Prevent leaks •  Protect camera and vessels

•  Approximate Mass: 1 lb. •  Electrical configuration

–  GoPro (included in FD PCB) –  Backlit grid powered from Power PCB

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FFE

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2013 PDR

Subsystem Design: Picosatellite Ejection (PSE)

•  Critical components: –  Ejection cylinder –  Payload (IMU/Magnetometer) –  Transceiver

•  Approximate Mass: 3 lb.

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2013 PDR

Test/Prototyping Plan Alex Bouvy

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2013 PDR

Test/Prototyping Plan: FFE

•  Experiment will be constructed and tested qualitatively. Vessel containing ferrofluid will be thoroughly tested to ensure no leaks will occur.

•  Experiment will also be tested to determine the magnetic field produced by the electromagnet with respect to distance from the magnet. –  Magnetometers can be calibrated using know magnetic

values. Earth’s magnetic field in Morgantown, WV= 0.5256 gauss. (source: www.ngdc.noaa.gov)

•  Additionally, the GoPro camera will be thoroughly experimented

with to demonstrate proper operation through autonomous use.

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2013 PDR

Test/Prototyping Plan: FD

•  Board will be constructed and individual sensors tested as follows:

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Sensor Testing Plan

MagnetometerMagnetic field by latitude and longitude of the earth is known. Magnetic field magnitude for Morgantown is known. In the presence of no magnet,

the magnetometer reading should produce this.

AccelerometerBy moving the board around, increases/decreases in respective directions

for the accelerometer should be observed. Additionally, at rest the accelerometer should read 9.81 m/s^2

Hi-‐Res Accelerometer

Same as Accelerometer

Temperature Temperature taken with respect to a reference temperature.

GyroscopeSimilar to the approach with the accelerometer, changes in corresponding

xyz-‐directions should be observed when moving the sensor.

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Test/Prototyping Plan: RPE

•  RPE will be tested to verify MHz and GHz transmissions are being made. This will include oscilloscope testing as well as spectrum analysis.

•  By placing conductive materials opposite the antennas, a varying received signal response can be observed.

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2013 PDR

Test/Prototyping Plan: PSE

•  Upon completion, ejection cylinder will be tested to verify proper operation.

•  Picosatellite payload will be tested in the same fashion as FD sensors.

•  Picosatellite transmission will be tested on the ground to verify transmissions are made and received.

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2013 PDR

Test/Prototyping Plan: Power System

•  Upon completion, the output voltages and amperages of the power system simply should be measured in order to verify proper operation. By measuring these values, it can be ensured that our power system will provide the calculated values to other subsystems.

•  Our power system can then be integrated to remaining subsystems to verify proper operation of subsystems from supplied power.

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2013 PDR

Risk Analysis Alex Bouvy

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2013 PDR

Risk Analysis

•  Mission Requirements: –  RSK.1: The system does not survive the vibration

characteristics prescribed by the RockSat-X program. –  RSK.2: During flight, the power block does not properly

operate and fails to provide power to the subsystems.

•  System Requirements: FFE: –  RSK.3: During flight, the containing vessel fails and

ferrofluid is leaked into the surrounding environment. –  RSK.4: Upon testing the electromagnet to be implemented, it

is determined that too strong a magnetic field will be produced and will interfere with others’ payloads.

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2013 PDR

Risk Analysis

•  System Requirements: RPE: –  RSK.5: The antennas/probe are interfaced in such a manner

that meaningful data is not received.

•  System Requirements: PSE: –  RSK.6: During flight, the picosatellite fails to eject. –  RSK.7: It is deemed that ejection of the picosatellite will be

unsafe. –  RSK.8: It is determined that picosatellite radio transmissions

will interfere with WFF telemetry.

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2013 PDR

Risk Analysis

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Con

sequ

ence

RSK.2

RSK.3 RSK.5 RSK.6 RSK.7

RSK.1 RSK.4

RSK.8

Possibility

2013 PDR

Risk Analysis: Risk 1

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Risk Title RSK.1: Critical Failure on Vibration Testing

Risk Statement The system does not survive the vibration characteristics prescribed by the RockSat-X program.

Context Statement The system will be submitted to vibration testing at WFF in June. It is possible that this vibration testing will cause critical failure in one or more of the components/subsystems.

Closure Criteria If the system experiences a critical failure, the team must re-evaluate designs and rebuild before launch.

Consequence Rationale Likelihood Rationale

2 Upon failure, the team will be forced to re-evaluate designs and rebuild failed systems. The team will have approximately 2 months to do this.

2 Because the system will be submitted to vibration testing (through ATK) before vibration testing at WFF, the team should be fully prepared for vibration testing.

Con

sequ

ence

RSK.1

Possibility

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Risk Title RSK.2: Power Block Failure

Risk Statement During flight, the power block does not properly operate and fails to provide power to the subsystems.

Context Statement If the power block fails, no subsystems will receive power and will therefore not be active during flight.

Closure Criteria This is a realized risk. Thorough testing will be done prior to flight to ensure this mission critical element is in place.


4 If no systems power on, this means that no data will be obtained and minimum success criteria will not be met.

1 This is unlikely to happen. The power block will be thoroughly tested prior to integration.

Con

sequ

ence

RSK.2

Possibility

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Risk Title RSK.3: Ferrofluid Containment Failure

Risk Statement During flight, the containing vessel fails and ferrofluid is leaked into the surrounding environment.

Context Statement The ferrofluid must be contained in a sealed vessel. It is possible that vessel will break, and the ferrofluid will leak out.

Closure Criteria The vessel must be thoroughly tested before flight to mitigate risk of leaks.


3 If the ferrofluid spills and contacts other system components, it could cause a critical failure to the subsystem.

1

As in the case of the power block , this is another component that will be thoroughly tested before flight. It will be submitted to both vibrations and thermal testing at ATK, and then vibrations testing again at WFF.

Con

sequ

ence

RSK.3

Possibility

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Risk Title RSK.4: Electromagnet Too Strong

Risk Statement Upon testing the electromagnet to be implemented, it is determined that too strong a magnetic field will be produced and will interfere with others’ payloads.

Context Statement It is possible that, upon measuring the magnitude of the magnetic field output from the electromagnet, the field will be deemed too strong to use as it may cause interference with ours and other payloads.

Closure Criteria If the magnetic field is deemed too strong, the experiment may be removed.


2 The discovery of unmitigable interference may result in the removal of the subsystem. 3

It is known that the electromagnet will produce a considerably strong field. It is very possible that it will be discovered that this field interferes with other payload subsystems.

Con

sequ

ence

RSK.4

Possibility

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Risk Title RSK.5: Antenna/Probe Misplacement

Risk Statement The antennas/probe are interfaced in such a manner that meaningful data is not received.

Context Statement

If the Langmuir probe is placed too close to the center of the payload, it may not interact with the space environment in an ideal manner. Additionally, if the GHz antenna is placed in such a manner that interference will be produced, its results may also be clouded.

Closure Criteria The payload subsystems should be laid out such a manner that the probes are placed in ideal positions.


3 If the probes are not placed correctly, valid science data may not be received from the subsystem.

2 It most likely that placing the probe/antenna near the edge will result in acceptable readings, providing valid science data/

Con

sequ

ence

RSK.5

Possibility

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Risk Title RSK.6: PSE Ejection Failure

Risk Statement During flight, the picosatellite fails to eject.

Context Statement It is possible that upon command, the picosatellite will not eject, and remain in the payload.

Closure Criteria The ejection cylinder will be thoroughly tested prior to launch. Additionally, if the picosatellite does not launch, it is possible that telemetry data from the satellite will still be received.


3 If the payload is not ejected, minimum success criteria will not be met. 2 This subsystem component will be tested

thoroughly prior to launch to help avoid this issue.

Con

sequ

ence

RSK.6

Possibility

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Risk Title RSK.7: PSE Ejection Deemed Unsafe

Risk Statement It is deemed that ejection of the picosatellite will be unsafe.

Context Statement It is possible that it will be determined by WFF that the ejection of the picosatellite is not safe.

Closure Criteria In this case, the satellite cannot be ejected and will become a fixed component in the payload. Satellite telemetry will still be implemented and measurements obtained.


3 If the picosatellite cannot be ejected, the subsystem must be redesigned and implemented as a fixed component.

3 It is very possible that the deployable will be deemed unsafe, as this is at the discretion of WFF.

Con

sequ

ence

RSK.7

Possibility

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Risk Title RSK.8: PSE Telemetry Interference

Risk Statement It is determined that picosatellite radio transmissions will interfere with WFF telemetry.

Context Statement It is possible that WFF will determine that transmissions on the 435MHz band will interfere will WFF telemetry and will not be permitted.

Closure Criteria In this case, satellite telemetry will likely be removed from the subsystem, and the measurements stored on a hard disk.


2 Again, in the case of this, the subsystem must be redesigned. 3

It is considerably possible that the transmissions will interfere, as this is a common RF band used for telemetry.

Con

sequ

ence

RSK.8

Possibility

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Project Management Plan Ben Kryger

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Schedule

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Task Start DateDuration (days)

End Date

Critical Design Review12-‐Nov 28 10-‐Dec

Wallops Deliverable:

FD Development12-‐Nov 21 3-‐Dec

Internal Deadline:

FFE Development 12-‐Nov 28 10-‐DecRPE Development 26-‐Nov 28 24-‐Dec

Power Block Development 17-‐Dec 35 21-‐Jan

PSE Development 14-‐Jan 28 11-‐FebIndividual Subsystem

Testing Report 21-‐Jan 28 18-‐FebSubsystem Integration 18-‐Feb 28 18-‐MarPayload Subsystem and

Integration Report 18-‐Feb 28 18-‐MarDITL Test Report 1 18-‐Mar 28 15-‐AprDITL Test Report 2 15-‐Apr 28 13-‐May

Integration Readiness Review 13-‐May 21 3-‐Jun

Launch Readiness Review 3-‐Jun 49 22-‐Jul

Legend:

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12-Nov 1-Jan 20-Feb 11-Apr 31-May 20-Jul

Critical Design Review

FD Development

FFE Development

RPE Development

Power Block Development

PSE Development

Individual Subsystem Testing Report

Subsystem Integration

Payload Subsystem and Integration Report

DITL Test Report 1

DITL Test Report 2

Integration Readiness Review

Launch Readiness Review

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Budget

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Subsystem Cost ($)FD 1000 Total Budget ($)FFE 200RPE 300PSE 500 Total Spending ($)

Power Block 200 2200

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Team Availability Matrix

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Monday Tuesday Wednesday Thursday Friday

7:00 AM no no no no no

8:00 AM no no no no no All times Eastern Time Zone

9:00 AM no no no

10:00 AM no no no

11:00 AM no no yes yes no

12:00 PM yes no yes yes no

1:00 PM no no no yes no

2:00 PM no no yes no no

3:00 PM yes no yes no no

4:00 PM yes no yes yes no

11/13-‐11/16 RS-‐X Team Availability Matrix

WVU Rocketeers

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Contact Matrix

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Role Name Phone Email Citizenship OK to Add to Mailing List?PM Alex Bouvy (304) 376-‐0770 [email protected] U.S. YesFaculty advisorDimitris Vassiliadis (304) 293-‐4920 [email protected]. Yes" " (202) 315-‐6976 [email protected] -‐ -‐Media/Web William Kryger (444) 878-‐5166 [email protected] U.S. YesTeam Member Marc Gramlich (304) 550-‐3462 [email protected] U.S. Yes

WVU RocketeersFall 2012 RS-‐X Contact Matrix

2013 PDR

• D-sub connector

• Thermal protection container: model suggestions

Conclusion

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2013 PDR

•  Mission statement: Develop a payload which will measure the following properties of the space environment (up to 160 km) during the RockSat-X flight.

–  Plasma density/frequency –  Magnetic field –  Flight dynamics –  Magnetic effects on ferrofluids in microgravity –  Eject a standalone picosatellite. The satellite will house a basic payload

consisting of IMU and magnetometer, as well as a transceiver to transmit data back to earth.

Action Items: –  Begin FD construction/ testing / software development –  Begin FFE construction/ testing/ software development

Conclusion

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preliminary design review - cosgc home 2013/te… · – system/project level requirement...

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