Transcript WVU Sounding Rocket Student Payload Development Conceptual

WVU Rocketeers 2012
Conceptual Design Review
John Hailer, Ben Province, Justin Yorick
Advisors: Dimitris Vassiliadis, Marc Gramlich
West Virginia University
October 4rd, 2012
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CoDR Presentation Contents
• Section 1: Mission Overview
– Mission Overview
– Theory and Concepts
– Mission Requirements
– Concept of Operations
– Expected Results
• Section 2: Design Overview
– Design Overview
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CoDR Presentation Contents
• Section 3: Management
– Team Organization
– Schedule
– Budget
– Mentors (Faculty, industry)
• Section 4: Conclusions
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Mission Overview
• Mission statement: Develop a payload which will measure the
following properties of the space environment (up to110 km)
during the RockSat C flight.
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High-energy particles
Low-energy (plasma) density
Magnetic field
Gravitational field
Flight Dynamics
GHG experiment
Dusty Plasma Experiment
• Goal: To measure and analyze data from the flight, and
compare the results to known atmospheric models.
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Mission Overview: Theory
• High energy particles constantly barrage our atmosphere. Measuring
the intensity of various species of these particles can reveal much about
the source of these emissions, as well as the atmosphere’s composition.
• 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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Payload Experiments
-Brief overview of science goals:
1. Flight Dynamics: identify the dynamics of
rocket flight with on-board instrumentation
- Acceleration
- Rotation
- Compare with WFF telemetry
2. Greenhouse Gases: measure concentrations of
climate-forcing gasses
- Measurement of water vapor, carbon dioxide,
and other greenhouse gas concentrations
- These measurements necessitate access to an
atmospheric port
Payload Experiments (cont.)
3. Cosmic-ray particles:
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Identify intensity of cosmic rays during rocket
flight
Use an array of Geiger counters
4. Plasma frequencies in radio spectrum:
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Rocket apogee of 115-120 km: access to ionospheric
E region peak (during daytime)
Experiment measures plasma frequency (~1.3
MHz, simple function of density) and harmonics
Atmosphere becomes ionized above 85 km
Rocket Apogee of 115-120 km: ionosphere E region
Also considering adding an experiment to
measure the effects of microgravity on a dusty
plasma.
Mission Overview: Mission Requirements
General:
• Apogee: an altitude of ~120 km will allow cosmic-ray and
plasma sensors to sample sufficient count levels.
• Time: dawn-dusk launch preferable, due to daytime decrease
of E-region peak; decrease is greatest in June due to seasonal
variation.
• Data Acquisition: data intake rates should provide a
resolution greater than 80m.
• Electronics: payload voltages and currents must meet WFF
safety guidelines.
• Weight/Mass Distribution: The payload must weigh less than
88N (20lbs), while the COG must lie within 1cm of the central
rotation axis.
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Mission Overview: Mission Requirements (cont.)
Sensor and Payload Specifications:
• Flight Dynamics: flight camera requires access to optical port
• Radio Plasma Experiment: probe requires access to special
port. Scanning range should have a bandwidth of at least
1MHz (1.2-2.2MHz). Swept frequency of 1-6MHz preferred
with a resolution of greater than 10kHz
• Green House Gases: experiment will require access to
dynamic atmospheric port. Sensors for this experiment must
be able to detect key GHG’s even in relatively low
concentrations (ppm).
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Mission Overview: Mission Requirements (cont.)
Minimum Success Criteria:
• All sensors must activate and provide information at their
assigned times.
• 45 seconds of low noise acquired data provides atmospheric
information over a useable range of altitudes.
• Data must be consistent enough to provide insight into
accuracy of atmospheric models. Such information will be
useful in future applications of aerospace engineering and
radio communications by allowing designers to have detailed
information about particle conditions in the lower
atmosphere.
• Successful experiments with GHG detection entail accurate
species concentration profiles, which could provide useful
information for climate scientist interested in changes in
lower atmospheric composition.
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RockSat 2011: Concept of Operations
h=117 km (T=02:53)
Apogee
h=75 km (T=01:18)
RPE ON
Dusty Plasma ON
h=75 km (T=04:27)
RPE OFF
Dusty Plasma OFF
h=10.5 km (T=05:30)
Chute deploys
H=.6 km (T=00:3)
Entire payload fully activated
except for RPE, Dusty Plasma
h=0 km (T=00:00)
Launch; G-switch activation
h=0 km (T=13:00)
Splashdown
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Payload Design Examples
• Sample hardware for various experiments:
Measured
Variable
Instrument
Brand
Model
Trajectory
Inertia Measurement
Unit (IMU)
Analog Devices
ADIS16405
Z accelerometer
Analog Devices
ADIS16227
Magnetic Flux Density
Micromagnetometer
Honeywell
HMC2003
Visual Observations
Camera
GoPro
Hero
Radiation
Geiger Tubes
Images Company
Note: models cited are representative only. Actual models may comprise several functions on a single component,
similar to an inertial sensor.
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Mission Overview: Expected Results: Cosmic
Rays
• Geiger count rates (2010 flight):
173 s: Apogee
124 s: Payload separation
369 s: Chutes deploy
910 s: Splashdown
39 s: Orion burnout
• In 2012 payload, such profiles will depend on detector
resolution and sensitivity.
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Mission Overview: Plasma: Expected Results
• 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+06
4.00E+06
Frequency (Hz)
3.50E+06
3.00E+06
f_ce (Hz)
2.50E+06
f_pe (Hz)
2.00E+06
f_uh (Hz)
1.50E+06
1.00E+06
5.00E+05
0.00E+00
0
50
100
150
200
Altitude (km)
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Design Overview
• For most experiments (flight, Cosmic-ray
experiment, Geiger counters, etc) heritage
elements from previous WVU Rocksat flights
will be integrated into this year’s design.
– Structure: Makrolons, brackets, and mounting
hardware.
– PCBs: main and breakout boards will be revised
to accommodate differences in sensor specs.
– Circuits and sensors: revised to accommodate
updated experiments.
• Radio/plasma experiment: significant changes
in design planned
• Flight Dynamics and camera will likely remain
largely unchanged with new redundant fail
safe systems built in
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FD/RPE Functional Block
Power Supply
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Design Overview: Payload Layout
Flight Dynamics
Board
RPE Radio
Board
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Design Overview: RockSat-C 2012 User’s Guide Compliance
Mass Budget
Mass of 2011 Payload
+2.5 kg
Minus CLE Experiment
-0.2 kg
Plus two Makrolon plates
+0.5kg
Mass available for additional experiments
+3.0 kg
Total allowable payload mass (excluding canister)
+5.8 kg (12.7 lbs)
• Predicted volume: payload expected to fit in requested volume
(full canister)
• Activation: standard, based on G-switches, and compliant
with WFF no-volt regulation. No early activation needed
• RBF straps for power system
• Shorting wires: patterned after RockSat 2009-2010
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Management/ Facilities
• Student Design Team: J. Hailer, B. Province, J. Yorick
• Advisors: D. Vassiliadis, M.Gramlich
• Construction and testing performed at WVU Engineering and
Physics departments.
• Collaboration with ATK for external payload testing.
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Conclusion
• The mission of the WVU payload for RockSat C 2012 is to
measure several properties of the space environment above 100
km. To facilitate mission development, previous structures and
electronics will be modified or redesigned from prior WVU
RockSat missions.
• At this time, the team is considering adding more experiments to
the payload.
• At this time, the team resources are being focused on the detailed
development of the experiments outlined in this presentation.
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Questions?
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