WVU Rocketeers Preliminary Design Review West Virginia University

WVU Rocketeers Preliminary Design Review West Virginia University J. Yorick, B. Province, M. Gramlich Advisor: D. Vassiliadis October 26 2011 Rock. Sat-C 2012 PDR 1

PDR Presentation Content • Section 1: Mission Overview – – – Mission Overview Organizational Chart Theory and Concepts Concept of Operations Expected Results • Section 2: System Overview – – – Subsystem Definitions Critical Interfaces System Level Block Diagram System/Project Level Requirement Verification Plan User Guide Compliance Sharing Logistics Rock. Sat-C 2012 PDR 2

PDR Presentation Contents • Section 3: Subsystem Design – Power Supply Subsystem (PSS) • PSS Block Diagram • PSS Key Trade Studies • PSS Risk Matrix/Mitigation – Flight Dynamics Subsystem (FDS) • FDS Block Diagram • FDS Key Trade Studies • FDS Risk Matrix/Mitigation Rock. Sat-C 2012 PDR 3

PDR Presentation Contents • Section 3: Subsystem Design (cont. ) ―Cosmic Ray Experiment Subsystem(CRE) • CRE Block Diagram • CRE Key Trade Studies • CRE Risk Matrix Mitigation ―Radio Plasma Experiment Subsystem (RPE) • RPE Block Diagram • RPE Key Trade Studies • RPE Risk Matrix Mitigation Rock. Sat-C 2012 PDR 4

PDR Presentation Contents • Section 3: Subsystem Design (cont. ) ―Dusty Plasma Experiment Subsystem(DPE) • DPE Block Diagram • DPE Key Trade Studies • DPE Risk Matrix Mitigation – Greenhouse Gas Experiment Subsystem(GHGE) • GHGE Block Diagram • GHGE Key Trade Studies • GHGE Risk Matrix Mitigation Rock. Sat-C 2012 PDR 5

PDR Presentation Contents • Section 4: Prototyping Plan • Section 5: Project Management Plan – Schedule – Budget – Work Breakdown Structure Rock. Sat-C 2012 PDR 6

Mission Overview Ben Province Rock. Sat-C 2012 PDR 7

Mission Overview • Mission statement: develop a payload to measure properties of the space environment and conduct microgravity plasma experiments at approximately 110 km during Rock. Sat flight. – – – Measurement of high-energy particles (CRE) Radio-sounding of ionosphere plasma (RPE) Creation and control of dusty plasma in microgravity enviornment(DPE) Measurement of concentration of greenhouse gasses (GHGE) Comparison to flight dynamics • Goal: determine physical conditions during flight and compare to standard models • Data analysis will complete the cycle of experiment design and implementation. Rock. Sat-C 2012 PDR 8

Theory and Concepts • High-energy particles: cosmic rays arrive from solar, galactic, and other sources. Variations with altitude and energy provide information about their sources. • Plasma: the distribution of low-energy charged particles changes continuously in the ionospheric E region. The radio sounding experiment will measure the plasma density and magnetic field as a function of altitude. We will compare the measurements against standard models. • Dusty Plasma: When dust is introduced to a plasma environment, the dust particles become negatively charged due to the plasma sheath effect. These negatively charged dust particles repel the positive ions in the plasma and form a lattice. The properties of this lattice vary with temperature and pressure. Rock. Sat-C 2012 PDR 9

Theory and Concepts Continued • In meteorology, the rate at which the temperature of a volume of air would change with altitude is called a “lapse rate” • The environmental lapse rate is the actual rate of temperature change with altitude observed in the atmosphere. • An adiabatic lapse rate is the lapse rate calculated for an adiabatic differential volume of air. The adiabatic lapse rate varies with humidity and is a piecewise function for differential volumes that would include a H 2 O phase change within the interval over which the adiabatic lapse rate is being evaluated. (dry adiabatic lapse rate is a constant -9. 8 °C per km) • When the environmental lapse rate is less than the adiabatic lapse rate for the same location and conditions, the atmosphere is generally stable. When the environmental lapse rate is less than the adiabatic lapse rate for the same location and conditions, convection occurs. This often leads to a storm. Rock. Sat-C 2012 PDR 10

Rock. Sat 2011: Concept of Operations h=117 km (T=02: 53) Apogee h=75 km (T=01: 18) RPE Tx ON h=75 km (T=04: 27) RPE Tx 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 PDR 11

Expected Results: CRE • CRE The number of particle collisions is expected to increase as the rocket moves higher into the atmosphere. This is expected due to the relatively closer proximity of the detector to the particle sources. Rock. Sat-C 2012 PDR 12

Expected Results: RPE Expect at least one of several peaks: – This experiment expects to see a variation in plasma frequency. The plasma frequency (green) is a function of plasma charge density. The group expects this frequency to increase with altitude, indicating an increase in charge density. The gyrofrequency(red) isn’t expected to vary much with altitude. This is because the gyrofrequency is a function of the earth’s magnetic field. This field varies relatively little with respect to the range of travel of the payload, thus, the frequency varies relatively little compared to the primary frequency. E Region Plasma Frequency Variability 4. 50 E+06 4. 00 E+06 3. 50 E+06 Frequency (Hz) • 3. 00 E+06 f_ce (Hz) 2. 50 E+06 f_pe (Hz) 2. 00 E+06 f_uh (Hz) 1. 50 E+06 1. 00 E+06 5. 00 E+05 0. 00 E+00 0 20 40 60 80 100 120 140 160 Altitude (km) Rock. Sat-C 2012 PDR 13

Expected Results: DPE • A dusty plasma is a plasma which has much larger neutral particles suspended within the plasma. Under normal conditions, the electric forces are balanced by the weight of the dust particles, to form a well defined equilibrium lattice. This study seeks to see what variations in equilibrium and dynamic behaviors occur under microgravity conditions. It is suspected that these properties will be noticeably different under these varied conditions. • We would like to attain as many of the following milestones during the experiment as possible: – Ionization of gas to create a plasma – Suspension of dust within plasma environment – Optical confirmation of lattice structure – Manipulation of lattice structure – Observations at various pressures – Demonstrate deformation of lattice structure under shear Rock. Sat-C 2012 PDR 14

Expected Results: GHGE • Assuming that the atmosphere is well-mixed, carbon dioxide and water-vapor should both be evenly distributed throughout the atmosphere. This (incorrect) assumption is used as a simplification in most basic greenhouse effect models. • Creating a local altitude profile of the CO 2 concentration will provide insight into the reliability of models that assume CO 2 is evenly distributed throughout the atmosphere. • Water-Vapor is clearly not evenly distributed within the atmosphere as indicated by moisture-dependent weather systems and the water cycle. From this experiment, atmospheric lapse rates can be extrapolated and compared to calculated adiabatic lapse rates for the given conditions. The lapse rate profiles as well as their deviation from the dry adiabatic lapse rate should correspond to the weather systems and conditions observed near WFF on the day of launch. Rock. Sat-C 2012 PDR 15

System Overview Justin Yorick Rock. Sat-C 2012 PDR 16

System Overview FD PSS CRE RPE DPE GHGE microprocessor Rock. Sat-C 2012 PDR Flash Memory 17

Probe Design – Physical Model Patch Antenna Langmuir Probe Rock. Sat-C 2012 PDR 18

Design in Canister Location of future planned levels FD subsystem PSS Radio Tx(GHz) Radio Tx (MHz) Rock. Sat-C 2012 PDR 19

Critical Interfaces Interface Name Brief Description Potential Solution The PSS is a universal power supply to the payload. The experiments as well as the CPU are dependent on this structure. This structure’s survival and properation is paramount for mission success. The PSS will be a custom PCB to minimize stray wires and mass. The batteries will be placed below the board to maximize space usage efficiency. The FD board contains multiple dynamic sensors that will be used to compare the flight’s dynamics to WFF telemetry. It is key that this board is attached to the payload in such a way to avoid stray vibration or resonance phenomena. Secure connections are the primary tool to combat unwanted vibration. Prototyping and subsystem testing will reveal if further measures are needed. The RPE must have a secure and reliable connection to the special port Further research and design will allow the team to chose the most reliable connection methods to secure mission success DPE/Structure The DPE experiment will require use of a sealed, low pressure vessel to test the dusty plasma. The experiment will be imaged by a laser and imaging device. Stray vibrations from improper mounting could destroy image quality, and thus this experiment. Properly designed connections and components should minimize the risk of destructive vibrations. Further research will provide insight into additional potential solutions. GHGE/Atmospheric port . The GHGE requires a reliable connection to the atmospheric port. Design should ensure that a sufficient atmospheric sample can be given to the GHG sensors. It is also critical that the safety valves will operate correctly during the splashdown event. Proper calculation of major and minor losses in the tubing should ensure that the sensors will see their proper sample quantities. Simple test will ensure the safety valves will not allow water into the system. PSS/all FD/Structure RPE/Special port Rock. Sat-C 2012 PDR 20

Requirement Verification Method Description The PSS fully activates and stays on during launch. Demonstration Triggering the g-switches will allow the group to test the power out put to various system components using a DMM The RPE activates at the appropriate prescribed time, and deactivates at its assigned time Demonstration During the PSS testing, the team will inspect the RPE and test to see if it activates at the proper times. The DPE is able to survive the vibrations during the rocket flight. Testing The entire system meets the mass, CG, and electrical requirements as prescribed by Rock. Sat-C guidelines Inspection Rock. Sat-C 2012 PDR Vibration testing with partner ATK Physical test will ensure Rock. Sat-C compliance 21

Rock. Sat-C 2012 User’s Guide Compliance • Current team calculations place the mass of the payload at around 14 lbs • At the current time, the CG is expected to lie within its required space. • High voltage components are used in the CRE experiment, although this is a low power application. – Development of safety schematics are pending the finalization of the experiments. – Both the Special port, as well as the Atmospheric port will be used on this mission. Rock. Sat-C 2012 PDR 22

Subsystem Design Power Supply Subsystem(PSS) Ben Province Rock. Sat-C 2012 PDR 23

PSS: Functional Block Diagram Remainder of Payload Alkaline Batteries G-switch (1) G-switch (2) Thyristor Circuit G-switch (3) Legend Remove Before Flight Voltage Regulators Data/ Control Power PSS Rock. Sat-C 2012 PDR 24

PSS: Risk Matrix PSS. RSK. 3 PSS. RSK. 2 Consequence • Risks for this subsystem are unlikely, but fundamental to the success of the mission. PSS. RSK. . 1 Possibility PSS. RSK. 1: Single G switch fails/is connected incorrectly PSS. RSK. 2: Some wire connections don’t survive launch PSS. RSK. 3: RBF not removed correctly Rock. Sat-C 2012 PDR 25

Subsystem Design Flight Dynamics (FD) Ben Province Rock. Sat-C 2012 PDR 26

FD: Functional Block Diagram Legend Data/ Control Power Rock. Sat-C 2012 PDR 27

FD: Risk Matrix • FD. RSK. 3 Consequence FD. RSK. 1 FD. RSK. 4 • This subsystem is still the “main” board since it contains the microprocessor and flash storage for all experiments. Its functionality will ensure the success of many mission objectives. FD. RSK. 6 FD. RSK. 5 FD. RSK. 2 Possibility FD. RSK. 1: IMU damaged Low-rate flight-dynamics measurements not collected FD. RSK. 2: Poor soldering of surface-mount devices (SMDs) soldering damaged during travel/prior to launch FD. RSK. 3: Microcontroller fails in flight FD. RSK. 4: Analog magnetometer damaged FD. RSK. 5: High voltage disturbs calibration of analog magnetometer FD. RSK. 6: If launch is delayed into midday, magnetometer calibration may be incorrect depending on temperature Rock. Sat-C 2012 PDR 28

Subsystem Design Cosmic Ray Experiment (CRE) Ben Province Rock. Sat-C 2012 PDR 29

CRE: Functional Block Diagram Geiger Tube (1) Geiger Tube (2) Geiger Tube (3) Geiger Tube (4) Geiger Counter Flash Memory Legend Power Board Data/ Control Micro Controller Power CRE Rock. Sat-C 2012 PDR 30

CRE: Risk Matrix • CRE. RSK. 2 Consequence CRE. RSK. 1 This subsystem will be largely unchanged from previous years and should be fairly reliable. Possibility CRE. RSK. 1: Connectivity issues CRE. RSK. 2: Geiger tubes damaged/not properly secured Rock. Sat-C 2012 PDR 31

Subsystem Design Radio Plasma Experiment (RPE) Ben Province Rock. Sat-C 2012 PDR 32

RPE: Functional Block Diagram RPE Amplifier Patch Antenna (Special Port) Receiver Micro Controller Swept f Pulse Tx Transmitter Legend Flash Memory Data/ Control Power PSS Rock. Sat-C 2012 PDR 33

RPE: Risk Matrix Consequence RPE. RSK. 4 RPE. RSK. 6 RPE. RSK. 1 RPE. RSK. 3 RPE. RSK. 2 • • This board has several points of failure with consequences for the experiment. Results were inconclusive last year with internal antenna RPE. RSK. 5 Possibility RPE. RSK. 1: Wiring failure RPE. RSK. 2: Plasma reflection not strong enough RPE. RSK. 3: Tx and/or Rx sweep fails RPE. RSK. 4: Tx-Rx sweep not synchronized RPE. RSK. 5: Uncertainty in ionospheric conditions (ionospheric storm) RPE. RSK. 6: Patch antenna not properly secured Rock. Sat-C 2012 PDR 34

Subsystem Design Dusty Plasma Experiment (DPE) Ben Province Rock. Sat-C 2012 PDR 35

DPE: Block Diagram Dust Injector RF Signal Generator/ Amplifier Micro Controller Plasma Containment Volume Antenna Pressure and Temperature Sensors Optical Detection Laser Legend Flash Memory Data/ Control Camera Power Optical DPE PSS Rock. Sat-C 2012 PDR 36

DPE: Trade Studies Camera DVR 523 V HERO M 3185 A Cost 6 4 8 Size and Mass 7 6 10 Resolution (video) 2 8 2 Convenience of Interface 10 9 1 Power Requirements 6 5 10 Average: 6. 2 6. 4 6. 2 Rock. Sat-C 2012 PDR 37

DPE: Risk Matrix DPE. RSK. 1 DPE. RSK. 4 DPE. RSK. 2 DPE. RSK. 3 • • Consequence • This experiment is new to our payload. Due to the nature of the experiment, partial success is unlikely. All risks are of high consequence Possibility DPE. RSK. 1: Dust Injector fails DPE. RSK. 2: Dust contacts container walls before forming lattice DPE. RSK. 3: Leak causes pressure anomaly DPE. RSK. 4: RF equipment damaged on launch Rock. Sat-C 2012 PDR 38

Subsystem Design Greenhouse Gas Experiment (GHGE) Ben Province Rock. Sat-C 2012 PDR 39

GHGE: Functional Block Diagram Inlet Solenoids Solenoid Controller Pyroelectric CO 2 Sensor Experimental Volume H 2 O Vapor (Humidity) Sensor Outlet Solenoids Pressure and Temperature Sensors Static Atmospheric Outlet Solenoid Controller Legend Micro Controller TEC/Driver (for maintaining CO 2 sensor temp) Thermistor Data/ Control Flash Memory Power Airflow PSS Rock. Sat-C 2012 PDR 40

GHGE: Trade Studies: CO 2 Sensor • • • Note: The SOHA Tech SH-300 -DTH is a dual sensor that measures both CO 2 and relative humidity. No suitable domestic suppliers of IR CO 2 sensors could be found. Requests for quotes have been sent to suppliers of each of the sensors below. * indicates supplier has not delivered a price quote to date CO 2 Sensor Apollo IRC-A 1 Dynament TDS 0057 SOHA Tech SH-300 -DTH Cost * * * Accuracy 1 6 9 Warm Up Time 1 6 4 Signal Conditioning 3 10 10 Power Requirements 2 6 6 Repeatability 2 8 8 Average: 1. 8 7. 2 7. 4 Rock. Sat-C 2012 PDR 41

GHGE: Trade Studies: Humidity Sensor Honeywell HCH-1000 -002 MEAS HM 1500 LF SOHA Tech SH-300 -DTH Cost 9 1 10 (free if used for CO 2) Accuracy 9 6 3 Response Time 4 6 1 Signal Conditioning 3 8 10 Power Requirements 9 9 9 Operating Temp 10 6 N/A Average: 7. 3 6 6. 6 H 20 Sensor • The Honeywell HCH-1000 -002 is clearly a good addition to the payload even if the SH-300 -DTH dual sensor is also used. The low price of this sensor ($5. 39) makes this decision easy to justify. Rock. Sat-C 2012 PDR 42

GHGE: Risk Matrix • GHGE. RSK. 3 • GHGE. RSK. 2 GHGE. RSK. 1 Consequence • This experiment is ambitious given the available technology and volume and mass restrictions Partial success is feasible if the microcontroller is programmed to continue parts of the experiment when failure criteria is met for others. IE: Thermal equilibrium cannot be reached, so solenoids are opened so that pressure, temperature, and humidity readings are continued. GHGE. RSK. 4 Possibility GHGE. RSK. 1: A suitable pyroelectric CO 2 sensor cannot be obtained GHGE. RSK. 2: The pyroelectric sensor cannot be maintained at a stable temperature GHGE. RSK. 3: Solenoids fail GHGE. RSK. 4: Thermal equilibrium time severely limits data acquisition rate Rock. Sat-C 2012 PDR 43

Prototyping Plan Justin Yorick Rock. Sat-C 2012 PDR 44

Prototyping Plan Risk/Concern Action Improper mounting or soldering could cause total system failure Prototype PSS and ensure connections are mechanically and electrically sound FD Vibrations Vibration testing with industrial partner ATK to ensure proper design CRE Damage to Geiger tube array could compromise experiment Use previously successful heritage design for container RPE Timing or signal between Tx and receiver not calibrated. Ground testing can verify timing calibration of subsystem PSS Rock. Sat-C 2012 PDR 45

Prototyping Plan DPE GHGE RF generators must be properly designed to overcome vibrations and spin of rocket, to ensure dynamic stability of lattice Explore options with Physics Dept. to develop a suitable control process Use of static ports do not provide sufficient samples for GHG sensors Build prototype and test readings on ground. Consider addition of small impellor if needed. Rock. Sat-C 2012 PDR 46

Project Management Plan Ben Province Rock. Sat-C 2012 PDR 47

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 PDR DPE J. Yorick Simulation and Testing J. Yorick 48

Schedule • • • 11/7 Component selection should be complete, all electronic components ordered 11/25 Circuit schematics complete, PCBs ordered 11/30 CDR due (mass and power budgets virtually complete, placement of all components demonstrated in CAD) 2/13 ISTR due (subsystem prototypes should be fully functional, microprocessor programming drafted) 2/22 Detailed comparison between CAD and payload; testing 3/21 All subsystems fully assembled (most should be mounted on plates) 4/2 PSITR due (payload should be virtually complete, microprocessor programming well drafted) 4/23 FFMSTR due 5/28 LRR due (payload fully complete, microprocessor programming finalized) 6/15 Integration at WFF 6/21 Launch Rock. Sat-C 2012 PDR 49

Budget • • Approximate budget: • PSS: $100 • FD incl. magnetometers: $1100 • RPE: $600 • CLE: $500 • GHGE: $600 • DPE: $800 • Other: $500 • Total: $4200 If budget exceeds means, legacy components can be salvaged from previous payloads. • Lead times: of the order of <1 week to 4 weeks. • Funding sources: West Virginia Space Grant Consortium, department of physics. Rock. Sat-C 2012 PDR 50

Work Breakdown Schedule • The subsystems are prioritized from left to right. The level of priority drops from left to right. The priority of events for each subsystem drops from top to bottom of each block. GHGE DPE • Finalize sensor selection • Design Plasma Container and order sensors • CAD design mechanical systems to interface with atmospheric port and optical detection system • Design RF signal generator • Work towards previously listed dusty plasma milestones • Finalize physical location and shielding to prevent interference with RPE • Finalize sweep frequencies • Complete patch antenna and Langmuir Probe design Rock. Sat-C 2012 PDR PSS • Review/update voltage regulator circuits to ensure that this year’s power requirements are met • Determine alkaline cell quantity configuration FD • Reprogram Netburner in order to integrate new systems 51

Conclusion • Action Items – Finalize selection of all electronic components – Design DPE and GHGE circuitry – Build, simulate, or analyze all electronic subsystems to determine precise power requirements (dependant on item above) – Complete detailed mass budget including batteries (dependant on item above) – Use computer modeling to design patch antenna and Langmuir probe to withstand dynamic pressure and thermal requirements – Complete mechanical design of new subsystems and integrate them into a full-canister structural CAD drawing Rock. Sat-C 2012 PDR 52