The team presented a design for a 3U CubeSat called ROCKY to measure lift, drag, magnetic fields, radiation, and GPS performance in low Earth orbit (LEO). Key features of the design include actively controlling descent into the atmosphere to maximize time in LEO using a Vacco Palomar micropropulsion system. Subsystems presented included a Bartington Spacemag magnetometer, Teledyne UDOS007 radiation dosimeter, Radius 3U structure, MAI 400 attitude determination and control system, and components from partners including a propulsion system from Tuskegee University. The team used agile processes and decision analysis to select components to meet requirements within a $1.52 million budget and launch
Space Radiation Superconductive Shield (SR2S) is an EU funded FP7 project which is researching new technology to protect astronauts in space from radiation. On 9th April 2014 in Torino, Italy, SR2S held their first conference to give an update on the project so far.
For more information visit:
www.sr2s.eu
Twitter - @SR2SMars
Space Radiation Superconductive Shield (SR2S) is an EU funded FP7 project which is researching new technology to protect astronauts in space from radiation. On 9th April 2014 in Torino, Italy, SR2S held their first conference to give an update on the project so far.
For more information visit:
www.sr2s.eu
Twitter - @SR2SMars
Space Radiation Superconductive Shield (SR2S) is an EU funded FP7 project which is researching new technology to protect astronauts in space from radiation. On 9th April 2014 in Torino, Italy, SR2S held their first conference to give an update on the project so far.
For more information visit:
www.sr2s.eu
Twitter - @SR2SMars
Importance of SSPS in SDG and ESG, and importance of antennas in SSPSAdvanced-Concepts-Team
A space solar power satellite system or SSPS can generates electricity without CO2 gas nor harmful debris with competitive cost. So, it should be attached importance in SDG and ESG programs. The SSPS is a huge system working in space so that several key technologies have to be innovated or verified in space before the final manufacture. I will introduce those key technologies in terms of difficulty in applying to SSPS. In a research and development plan, key technologies with more difficulty should be ranked higher. Antennas are typically difficult ones. It is explained how the antenna is challenging compared with the existing antennas on the ground and in space. Finally, I will show you a R&D plan to put SSPS into practical use in about 30 years.
Multi-channel Detector Readout Integrated Circuits with ADCs for X-ray and Ga...Gunnar Maehlum
We are developing detector readout integrated circuits (ROICs) for X-ray and Gamma-ray spectroscopy. The ROICs are applications specific (ASICs) for satellite instrumentation in space. The ICs described in this article belong to the VATA family with integrated analog-to-digital converters (ADCs) for fully digital readout of x-ray and gamma-ray detectors. The VATAs are ideal for the readout of cadmium zinc telluride (CZT), cadmium telluride (CdTe), silicon pads and strips, and large area avalanche photodiodes (APDs) with scintillators.
The SpaceDrive Project - First Results on EMDrive and Mach-Effect ThrustersSérgio Sacani
Propellantless propulsion is believed to be the best option for interstellar travel. However, photon rockets or solar sails have thrusts so low that maybe only nano-scaled spacecraft may reach the next star within our lifetime using very high-power laser beams. Following into the footsteps of earlier breakthrough propulsion programs, we are investigating different concepts based on non-classical/revolutionary propulsion ideas that claim to be at least an order of magnitude more efficient in producing thrust compared to photon rockets. Our intention is to develop an excellent research infrastructure to test new ideas and measure thrusts and/or artefacts with high confidence to determine if a concept works and if it does how to scale it up. At present, we are focusing on two possible revolutionary concepts: The EMDrive and the Mach-Effect Thruster. The first concept uses microwaves in a truncated cone-shaped cavity that is claimed to produce thrust. Although it is not clear on which theoretical basis this can work, several experimental tests have been reported in the literature, which warrants a closer examination. The second concept is believed to generate mass fluctuations in a piezo-crystal stack that creates non-zero time-averaged thrusts. Here we are reporting first results of our improved thrust balance as well as EMDrive and Mach-Effect thruster models. Special attention is given to the investigation and identification of error sources that cause false thrust signals. Our results show that the magnetic interaction from not sufficiently shielded cables or thrusters are a major factor that needs to be taken into account for proper μN thrust measurements for these type of devices.
Space Radiation Superconductive Shield (SR2S) is an EU funded FP7 project which is researching new technology to protect astronauts in space from radiation. On 9th April 2014 in Torino, Italy, SR2S held their first conference to give an update on the project so far.
For more information visit:
www.sr2s.eu
Twitter - @SR2SMars
Importance of SSPS in SDG and ESG, and importance of antennas in SSPSAdvanced-Concepts-Team
A space solar power satellite system or SSPS can generates electricity without CO2 gas nor harmful debris with competitive cost. So, it should be attached importance in SDG and ESG programs. The SSPS is a huge system working in space so that several key technologies have to be innovated or verified in space before the final manufacture. I will introduce those key technologies in terms of difficulty in applying to SSPS. In a research and development plan, key technologies with more difficulty should be ranked higher. Antennas are typically difficult ones. It is explained how the antenna is challenging compared with the existing antennas on the ground and in space. Finally, I will show you a R&D plan to put SSPS into practical use in about 30 years.
Multi-channel Detector Readout Integrated Circuits with ADCs for X-ray and Ga...Gunnar Maehlum
We are developing detector readout integrated circuits (ROICs) for X-ray and Gamma-ray spectroscopy. The ROICs are applications specific (ASICs) for satellite instrumentation in space. The ICs described in this article belong to the VATA family with integrated analog-to-digital converters (ADCs) for fully digital readout of x-ray and gamma-ray detectors. The VATAs are ideal for the readout of cadmium zinc telluride (CZT), cadmium telluride (CdTe), silicon pads and strips, and large area avalanche photodiodes (APDs) with scintillators.
The SpaceDrive Project - First Results on EMDrive and Mach-Effect ThrustersSérgio Sacani
Propellantless propulsion is believed to be the best option for interstellar travel. However, photon rockets or solar sails have thrusts so low that maybe only nano-scaled spacecraft may reach the next star within our lifetime using very high-power laser beams. Following into the footsteps of earlier breakthrough propulsion programs, we are investigating different concepts based on non-classical/revolutionary propulsion ideas that claim to be at least an order of magnitude more efficient in producing thrust compared to photon rockets. Our intention is to develop an excellent research infrastructure to test new ideas and measure thrusts and/or artefacts with high confidence to determine if a concept works and if it does how to scale it up. At present, we are focusing on two possible revolutionary concepts: The EMDrive and the Mach-Effect Thruster. The first concept uses microwaves in a truncated cone-shaped cavity that is claimed to produce thrust. Although it is not clear on which theoretical basis this can work, several experimental tests have been reported in the literature, which warrants a closer examination. The second concept is believed to generate mass fluctuations in a piezo-crystal stack that creates non-zero time-averaged thrusts. Here we are reporting first results of our improved thrust balance as well as EMDrive and Mach-Effect thruster models. Special attention is given to the investigation and identification of error sources that cause false thrust signals. Our results show that the magnetic interaction from not sufficiently shielded cables or thrusters are a major factor that needs to be taken into account for proper μN thrust measurements for these type of devices.
Multiphase Flow Modeling and Simulation: HPC-Enabled Capabilities Today and T...inside-BigData.com
In this video from the 2014 HPC User Forum in Seattle, Igor Bolotnov from North Carolina State University presents: Multiphase Flow Modeling and Simulation: HPC-Enabled Capabilities Today and Tomorrow.
Learn more: http://insidehpc.com/video-gallery-hpc-user-forum-2014-seattle/
University of Victoria Talk - Metocean analysis and Machine Learning for Impr...Aaron Barker
A presentation given on Metocean analysis and Machine Learning for improved estimates of energy production in WECs by Aaron Barker at the University of Victoria on the 7th of December 2017
Principles and Practices of Traceability and CalibrationJasmin NUHIC
To learn and understand different types of measurements units, measurement constants, calibration and measurement standards as well as principles and practices of treaceability.
Earth Viewing Systems Satellite Sensor Project, for Professor DiNardo's Course.
The presentation was given on 14th May, 2009.
______________________________________
I realize that some of the graphics do not have their sources cited, but I did not make those slides, and the group members who made them did not remember their sources. So, please forgive this oversight, since I consider it important enough to students of the earth surveillance class at The City College of New York (and elsewhere) that old presentations be available to them.
If, however, you can give me the sources of the graphics that you see, then I will be grateful, and I will be happy to cite them.
2. ROCKY
Goal: Design and Develop a 3U CubeSat
Measures lift, drag, magnetic fields, radiation, and GPS
Performance in LEO
Actively controls descent into the atmosphere to maximize
duration in LEO
Customer: U.S. Army Space and Missile Defense Command
Process: Agile SE processes
1
3. Team CD
PCE
Nathan
Sandlin
College of
Charleston
Team Lead
Wendell
Paul
AE
Ricardo
AE
Qioa
Environment
Austin
Sci Ops
Jeremiah
SCE
Justin
Sandlin
Thermal
Andrew
Tuskegee
Kiante’
Structure
Hagen
UTEP
Daniel
LSE
Janelle
Williams
ESTACA
Team Lead
Calin
Emeric
Antoine
Emilie
Yohann
PM
Eric
Powell
Luis
Aaron
Hugo
Team Lead
Christian
Kenneth
= UAH Engineering
= CofC Science
= Tuskegee Engineering
= UTEP Engineering
= ESTACA Engineering
2
5. Requirements
Project:
Specifications
3U Cubesat < 10kg
Volume no larger than 3U CubeSat
form factor
Increase orbital lifetime by no less
than 10%
Adhere to CubeSat Design
Specification Rev. 13
Cannot violate any Space
Policy/Treaties
DRM:
350 km circular orbit @ 28.5°
Additionally:
Actively Controls Descent into
Atmosphere in LEO
Science:
Measures:
Lift & Drag,
Magnetic Fields,
Radiation
Location in orbit
Science Enhancement
Measure radiation effects
through elliptical LEO
Test possible methods of
shielding against radiation
4
6. Requirements
Functionality:
Communicate with ground
station
Send and receive data
Can generate & distribute
self sustaining power
Tumble
reduction/Stabilization of 3U
CubeSat
Environmental:
Survivable in LEO
radiation
magnetic fields
temperature fluctuations
No space debris after 25 years
5
7. Developed for Evaluation
Alternative Concepts
GPS
Picosat NAV
piNAV-L1
piNAV-NG
Magnometer
MAG3110
Spacemag
Spacemag Lite
Radiometer UDOS0007
Propulsion
VACCO
Palomar
MEMS
Radio
SWIFT KTX
SWIFT XTS
LI-1
Heater
HK6915
HAP6948
HM6962
Structure
Clyde
Radius
ISIS
ADACS
BCT XACT
MAI 400
Cube ADCS
6
8. Weights of F.O.M
Best
OptionRaw score
Multi-Criteria Decision Analysis Method
Step 1: Identify and define a criteria for
selection
Step 2: Establish Weight Factors for each
criteria(1,3,9)
Step 3: Brainstorm different components
Step 4: Analyze different components
Step 5: Fill matrix for each component
Step 6: Calculate score for each component
Decision Analysis
7
9. Final Decision Concept
Our final of the available options resulted in the selection
of the following components:
1. Radius 3U Cubesat structure
since each offered similar specs, we opted for the low
cost solution
2. MAI 400 ADCS
A compromise of size and cost, with a high
survivability rating
3. piNAV-NG GPS module
low mass with high accuracy
4. Vacco Palomar micro propulsion system
8 independent thrusters with 6 DOF capability
5. Teledyne UDOS007 micro dosimeter
ultra compact and space flight heritage
6. LI-1 Radio Transceiver
low mass with low cost
7. HM6962 Heaters
most power efficient
8. Bartington Spacemag magnetometer
highest accuracy with low mass
8
10. Key Features
Magnetometer (SpaceMag)
Function:
Altitude sensing as well
as measurement of
magnetic signature and
geomagnetic field mapping
Key Features:
3-axis field of view
Shock and vibration tested to
NASA-STD-7001
Measurement Range: (+/-)100𝞵T
Temperature Range: -55 to +125 (°C)
Mass: 175g
Power: 0.57W
Volume: 40 x 40 x 31mm
Dosimeter (UDOS007)
Function:
Measure total ionizing dose (TID) of
radiation to estimate exposure rates of
other components
Key Features:
Small volume and mass to provide
mounting for multiple locations
Class K equivalent screening
Measurement Range:
100 keV to 15 MeV (Ionizing)
Temperature Range: -30 to 45 (°C)
Mass: 20 grams
Power:
13 to 40 (VDC)
Volume:
922.3248 (𝑚𝑚3)
9
12. Component Interfacing
Most sensors compatible with UART & 𝐼2 𝐶
Physical Connections to be made with bolts
Connections such as wires and heaters to be secured using adhesive and ties
11
13. Function:
Automate Spacecraft by sending
Commands, Formatting and Saving Data
Key Features:
MSP430 Microcontroller
Temperature Range: -40(°C) to 85(°C)
Mass: ~2 g
Power: 0.001 W
Volume: 0.173 𝑐𝑚3
Partners: UTEP
Command and Data Handling
12
14. Command and Data Handling
Function:
Automate Spacecraft by sending
Commands, Formatting and
Saving Data,
Key Features:
Kingston 16 GB SD card
Temperature Range: -25(°C) to 85(°C)
Mass: ~2 g
Power: ~ 0.3 W (during writes)
Volume: 0.614 𝑐𝑚3
13
16. Propulsion (Palomar)
Function:
Provide propulsion to prolong mission
Key Features:
Provides six degrees of freedom
Eight independent thrusters
Over 200,000 thruster firings in a
simulated space environment
Operating Parameters:
Max Operating Pressure....150 psia
Proof Pressure......................225 psia
Burst Pressure.......................375 psia
Thrust.....................................35 mN
Internal Leakage ................3.0 scc/hr
External Leakage................1.0 x 10 -6 scch
Operating Temperature.... 0°C to +50°C
Non-Operating Temperature
-10°C to +60°C
Vibration..............................23 Grms
Cycle Life ..........................120,000 firings
Total Impulse..................... 85 N/sec
Minimum Impulse Bit……. 0.75 mN/sec
Operating Voltage ……...4.75 to 5.25 vdc
Peak Power......................<5 watts (2 thrusters)
Dry Mass............................ 890 grams
Propellant Mass ……....... 173 grams
Total Mass ..................... 1,063 grams
15
17. Power
Function:
Collect and distribute power
across spacecraft
Key Features (components):
NanoPower P110 Solar panels
Temperature Range: -40(°C) to 85(°C)
Mass: 26 g
Power: 2.3 W/package
Volume: 8.9 𝑐𝑚3
Partners: UTEP
16
18. Power
Function:
Collect and distribute power
across spacecraft
Key Features (components):
CubeSat Kit Battery Module 1
Temperature Range: -40(°C) to
85(°C)
Mass: 310 g
Power(Capacity): 40 W hr
Volume: 225 𝑐𝑚3
Partner: UTEP
17
19. Structure
Function:
Housing and
protection from any debris,
radiation, and temperatures while
in LEO
Temperature Range: -170°C to 123°C
Mass: 255 grams
Volume: 340.5mm X 100mm X 100mm
Key Features:
Frame: Aluminum 7075
anodized, hardcoat, and
Alodine 1200.
18
20. Communications
Function :
Transmit data and receive
commands to and from ground
station.
Key components: LI-1Radio
Estimated Mass: 52 grams
Volume: 21.45 𝑐𝑚3
Operating Temp: -30(°C) to + 70(°C)
Frequency: 130-450 MHz
Partners: UTEP
19
21. Communications
Function:
Transmit data and receive
commands to and from
ground station.
Key components: ISIS UHF Antenna
Estimated Mass: < 100 grams
Volume: 6.7 𝑐𝑚3
Operating Temp: -30 (°C) to + 70 (°C)
Frequency: 130-500 MHz
Partners: UTEP
20
22. Thermal
Function:
Maintain operating temperature ranges
on board the CubeSat
Key Features (components):
Polymide Thermofoil heater
Temperature Range:-150(°C) to 600 (°C)
Mass: 141 g
Power: ~7.5 W (maximum)
Volume: 29 𝑐𝑚2
21
23. ADACS
Function: Stabilize & aim the CubeSat
Key components: MAI 400
Estimated Mass: 694 grams
Estimated Power :
Steady State/ Typical W: 3.17
(0.63amps @ 5V)
Peak Wattage: 7.23 (145 amps @ 5V)
Volume: 10x 10 x 5.9cm
Partners: Tuskegee University
22
25. University of Texas, El Paso (UTEP)
Communication:
• 2 Video Conferences & email
• Responsible for Power and C&DH
subsystem
• Expertise: Team of senior electrical
engineering majors
Tasks:
• Create Data budget based on
sensors, processor, and memory sizing
• Provide flow diagram showing data
interfacing and power connections
• Calculate data transmission limits
between CubeSat and ground
station
24
26. College of Charleston (CofC)
Budget
Assigned a minimal
budget including:
Mass for science
enhancement to be
kept below 0.5 kg
Power will be less
than 1 Watt, not
including required
orientation
maneuvers.
Allowable data
usage will be
determined by UTEP
Interfaces must
communicate
directly with C&DH.
Tasks
Responsible for the
science
enhancement
objective
Will attempt to
determine the
effectiveness of
different methods of
radiation shielding
Requesting the use
of elliptical orbit
Requires pointing
ability of the
cubesat to provide
best radiation test
data
Communication
Area was
recovering from
tropical storm
during semester
Email
communication has
been unreliable at
best
Held a video
conference with the
entire team
25
27. ESTACA
Current collaboration done by email, video networking in future
ESTACA future deliverables
Orbital analysis
Model varying velocity and acceleration based on CubeSat dimensions
Determine an average rate of decay depending of change in mass and
velocity
Time ratio of sun contact and change in internal energy for solar power
26
28. Programmatics
Total Estimated Cost: $1.52 Mil
System US$
Structure 5,330.00$
Propulsion 138,260.00$
ADACS 118,000.00$
Thermal 977.30$
Communication 11,570.00$
Payload Sensors 99,130.00$
Pow er 2,000.00$
Command and Data 27.00$
Man Hours 1,139,200.00$
Total Estimated Cost 1,514,494.30$
3U CubeSat Cost: $ 375,295
No current compliance issues. 27
30. RDR Sprint
Defined program
requirements for the
cubesat and the
subsystems
Defined driving
requirements
Defined Perturbations in
requirements
Gained knowledge of
state of the art cubesat
technology
ADAR Sprint
Developed Figures of
Merit for the cubesat
and subsystems
Used decision analysis
technique to determine
solutions
Developed alternatives
for subsystems
Defined key
performance
parameters for partners
Determined key risks
SDR Sprint
Determined concept that
satisfied requirements
Partner requirements
Developed Component
breakdown
Provided preliminary cost
for the program
Provided preliminary
schedule for the program
Identified key risks
Semester Summary: Agile
29
31. 1. Finalize Detailed Design using
CATIA or other software
2. Complete Bill of Materials for
ordering components
3. Order Components
4. Apply for Ham License
5. Apply for flight approval
6. Complete Risk-Mitigation
Analysis
7. Build prototype for testing
8. Finalize ROCKY and prepare
for flight
9. Upon successful deployment,
collect and analyze data for
life span of ROCKY
Next Steps
30
32. “
”
Design is not just what it looks like
and feels like.
Design is how it works.
STEVE JOBS