WVU Rocketeers 2013 Conceptual Design Review

Transcription

1 WVU Rocketeers Conceptual Design Review West Virginia University Alex Bouvy, Ben Kryger, Marc Gramlich Advisors: Dimitris Vassiliadis, Marcus Fisher

2 Presentation Content Section 1: Mission Overview Mission Statement Theory and Concepts Mission Requirements Concept of Operations Expected Results Section 2: Design Overview Design Overview Functional Block Diagrams Payload Layout RockSat-X User s Guide Compliance Shared Deck Space (if applicable) 2

3 Presentation Contents Section 3: Management Team Organization Schedule Budget Mentors (Faculty, industry) Section 4: Conclusions 3

4 Mission Overview: Mission Statement 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 very 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. 4

5 Mission Overview: Theory and Concepts 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. 5

6 Mission Overview: Payload Experiments 1. Flight Dynamics (FD): identify the dynamics of rocket flight with on-board instrumentation - Acceleration - Rotation 2. Radio Plasma Experiment (RPE): - Consists of 3 subsystems: - Langmuir Probe: Measures the density of the plasma. Continuously sweeps voltage to generate I-V curves at different altitudes, from which plasma density can be derived. - GHz/MHz Antennas: Measures plasma frequency (~1.6 MHz, simple function of density) and harmonics. - Magnetometer: Measures the magnitude of the magnetic field of the earth. 6

7 Mission Overview: Payload Experiments 3. Picosatellite Ejection (PSE): eject a picosatellite to produce a decaying low-earth orbit from which the following measurements can be made and transmitted to earth: - Health status of solar panels/battery - XYZ-Rotation - Low resolution magnetometer reading - High resolution magnetometer reading 4. Ferrofluid Stabilization (FFE): Reduce liquid sloshing and movement unpredictability by applying an electromagnetic field. Conform ferrofluid to a certain area within a sealed container. Reduce movement and sloshing within the container. Minimize vibration, orientation, and centrifugal effects on the liquid imposed by rocket flight 7

8 Mission Requirements: 1. The payload shall conform to the requirements set forth in the RockSat-X User Guide 2. The system shall measure the density of the electric field of a lowenergy plasma throughout the flight at a specified rate. 3. The system shall measure data from each and every inertial sensor throughout the flight at a specified rate. 4. The system shall observe the effects of ferrofluids in the presence of an electromagnet intermittently throughout flight. 5. The system shall transmit acquired data through WFF-provided telemetry. 6. The payload shall effectively eject a picosatellite to produce a decaying low-earth orbit, from which telemetry data is received. 7. The system should save high resolution data on a hard disk for data assurance and system redundancy. crestock.com 8

9 RockSat-X : Concept of Operations h=160 km (T=2.8 min) Apogee Nose Cone Separation Picosatellite Ejected h=52 km (T=.6 min) End of Orion Burn h=10.5 km (T=5.5 min) Chute deploys h=10.5 km (T=5.78 min) Experiments Power Off h=0 km (T=15 min) Splashdown h=0 km (T=0) Launch; G-switch activation. All systems on, begin data acquisition 9

10 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: Frequency Variability 4.50E E E+06 Frequency (Hz) 3.00E E E E E E+05 f_ce (Hz) f_pe (Hz) f_uh (Hz) 0.00E Altitude (km) 10

11 Mission Overview: Expected Results: Magnetic Field 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. 11

12 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. Under parachute, the control fluid should respond solely to gravity s pull, whereas the ferrofluid is expected to remain mostly oriented toward the magnet. 12

13 Design Overview For most experiments (Flight Dynamics, Radio Plasma, Langmuir Probe) 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 experiment will be implemented from scratch. 13

14 LEGEND Power: Red Picosatellite Ejection Functional Digital Signal: Gold Block Diagram Analog Signal: Olive Ejection Cylinder Langmuir Board Langmuir Experiment Radio Plasma Experiment RPE Board Parallel Bits: Lavendar Langmuir Probe Antenna Wallops Power & Telemetry lines GSE- 1 GSE- 2 TE- R Power Block TE- NR1 TE- NR2 TE- NR3 Parallel Bits 1-8 Magnetometer Flight Dynamics SD Card ucontroller Z- Accelerometer Power Distribution ucontroller System IMU

15 FBD Mechanical Diagram (rough) Makrolon Layer 1 (PCBs) Power FD LPE Makrolon Layer 2 (Exp. Apparatus) FFE RPE LP uc RPE PSE 15

16 Design Overview: Shared Can Logistics Tentative plans have recently been made to share deckspace with Johns Hopkins University. Hopkins plans to discover electron density using a duel frequency GPS and observe effects on an aerogel container. Communication will consist of team s, phone calls, and occasional in-person meetings. 16

17 Management Team Organization Chart Name Alex Bouvy Role PM/ Payload design/development Ben Kryger Social outreach/ Payload design/development Marc Gramlich Payload design/development 17

18 Management Team Mentors Dr. Dimitris Vassiliadis Physics Department Faculty Plasma Physics Research Team Advisor/Lecturer Dr. Marcus Fisher Engineering Department Faculty Picosatellite Logistics Team Advisor 18

19 Conclusion Mission statement: Develop a payload which will measure the following properties of the space environment (up to 160 km) during the RockSat X flight. Low-energy (plasma) density Magnetic field Flight dynamics Magnetic effects on ferrofluids in microgravity and flight 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. 19

20 Concerns: Nose ejection/picosatellite ejection timing Telemetry interference on 435 MHz band Magnetic interference from FFE From here: Begin to model subsystems. 20

21 Questions? 21