university of wyoming dorin blodgett, kevin brown, heather choi, ben lampe
DESCRIPTION
University of Wyoming Dorin Blodgett, Kevin Brown, Heather Choi, Ben Lampe Eric Robinson, Michael Stephens, Patrick Weber October 7, 2010. Mission Overview. 3. 4. 5. 2. 1. 6. Scientific Objectives. Capture optical images of the earth. Collect space dust. - PowerPoint PPT PresentationTRANSCRIPT
1
University of Wyoming
Dorin Blodgett, Kevin Brown, Heather Choi, Ben LampeEric Robinson, Michael Stephens, Patrick Weber
October 7, 2010
2
Mission Overview
1
2
3
4
5
6
3
Scientific Objectives
oCapture optical images of the earth.
oCollect space dust.
o Provide perspective of what is in our atmosphere.
oMeasure thermal, seismic and pressure effects throughout duration of launch.
o Collect data for future projects
4
Engineering Objectives
o Engineer electronics systems for capturing and storing images from optical devices.
o Create extendable booms to mount imaging equipment and dust collector.
o Use AeroGel to collect space dust.
o Create protective water shield for housing data storage devices and encasing AeroGel collector during reentry and splashdown.
o Record thermal, seismic and pressure data in real time throughout launch using electronic sensors and transmit recorded data via provided Wallops telemetry.
5
Mission Requirements
The payload shall conform to the requirements set forth in the 2011 RockSat-X User Guide
6
TYPE QUANTITATIVE CONSTRAINT Physical Envelope
Cylindrical**: Diameter: ~12 inches Height: ~12 inches ** Deployables and booms are permitted once skin has been ejected
Weight Payload shall be: 30±1 lbf
Center of Gravity Lies within a 1 inch square in the plane of the RockSat-X plate.
Power and Telemetry
Telemetry Ten (10) 0 – 5V 16 bit A/D Lines One (1) parallel line One (1) asynchronous line Power One (1) redundant power line (28V) Three (3) non-redundant power lines (28V) 1 Ah capacity
High Voltage All payloads utilizing higher voltage (>28V) shall conformal coat all electronics.
Specifications: Physical Constraints
7
Specifications: Performance Parameters
KEY PERFORMANCE PARAMETER VALUE Altitude (km) ≈ 160 km
Spin Rate (Hz) at Burn-Out ≈ 1.3 Hz at Terrier burn out; ≈ 4.8 at Orion burn out
Maximum Ascent G-Load 25 G (Sustained) (50+ G Impulses Possible)
Rocket Sequence (Burn Timing) 5.2 s Terrier burn—9.8 s coast—25.4 s Orion burn
Chute Deploy (seconds) 489.2 s
Splash Down (seconds) 933 s
(Source: RockSat Payload Canister User’s Guide 2010)
8
Success Criteria
o At minimum, the payload shall gather data during launch, at apogee, and during reentry through the use of:
o Thermocoupleso 3-axis Accelerometerso Gyroscopes o Absolute Pressure Sensors
o Ideally, the payload should also extend telescopic booms outside of the payload and:
o Gather optical images of the Eartho Store photographs to on-board SD cardso Capture space dust using AeroGel
9
Expected Results
oSpace Dust Composition (10^-6)
oRocket FueloMeteor/ Metal FragmentsoGases
oEarth/Payload Images
oDetailed Data through Flight Duration
oThermal Data oSeismic DataoPressure Data
10
Concept of Operations
1
2
3
4
5
6
Circuits initialize and begin collecting and transmitting data.
Data continues to be transmitted.
Rocket skins are shed, pressure within canister drops, boom is extended and begins to collect samples/take photographs.
Power and telemetry is shut down and data collection and transmission ceases. Splashdown.
Payload hits atmosphere, pressure within canister rises, boom is retracted and AeroGel is sealed within shield. Data is still being collected and transmitted over telemetry.
Samples/photographs continue to be collected/taken during descent.
T = 0 min.
T = 1.3 min.
T = 2.8 min.
T = 4.5 min.
T = 5.5 min.
T = 15 min.
11
Design Overview
12
RockSat 2010 Payload Structure
Factor of Safety = 1.5
AerogelCamera
Electronics
13
Payload Functional Block Diagram
Power (NASA)
Microcontroller
X/Y Accelerometer
Z Accelerometer
Pressure Sensor
Thermocouple 1
Thermocouple 2
Thermocouple n
…
ADC
Microcontroller
Solid State Storage Device
Solid State Storage Device
Solid State Storage Device
Solid State Storage Device
G-Switch RBF (Wallops)
To Wallops Telemetry (10x 0-5V A/D 16-Bit, and Asynchronous)
Optical Camera 1 Optical Camera 2
Pressure Sensor
BoomActuator
Microcontroller
ADC
14
Design Specifications, Mechanical
oWater Shield
o Material (weight, thermal conductivity, impact and vibration resistance)o Sealing around data connectionso Dynamic sealing around AeroGel following successful data collection
oStructure
o Able to withstand 25G with 50G+ impulse loadso Harmonic Oscillations
oBoom
o Telescopic Mechanical Arm o Surviving launch and vibration loadso AeroGel retrieval
15
Design Specifications, Electrical
oAutomation
o Booms, Control Motorso Timed Exposures – Gyroscope and Light sensors
oData Acquisition
o Thermal (Thermocouples)o Seismic (Multi-Axis Accelerometers)o Pressure Measurements (Piezoelectric Strain Gage, Absolute)o Send Measurements through 10x 0-5V 16-bit A/D lines
oPhoto Capture
o Optical Camera (~390 – 750nm)
oImplementation
o Photos stored on redundant SD cards (Multi-GB)o Data sent through NASA telemetryo Payload powered by NASA
16
AstroX Team
17
Management
18
Management
o Schedule
o See Attachment
o Budget
o Mass (15-30lbs)o Boom (7 lbs)o Circuits (1 lb)o Water Shield (2 lbs)o Camera (4 lbs)o Other Sensors (1 lb)
o Monetary Budget
o $850
12%12%
18%12%12
%
35%
Monetary Budget
Optical EquipmentShieldExtendableMaterialsElectronicsAerogel
19
Conclusions
oMission RecapoCapture optical images of the earth.oCollect space dust via aerogel.oMeasure thermal, seismic and pressure effects
throughout duration of launch.
oIssueso Sufficient funds oEngineering successoWaterproofing payloadoExtreme vibrations
20
Questions?