cadre_overview
TRANSCRIPT
CubeSat Investigating AtmosphericDensityResponse to Extreme Driving
115 May 2015
Overview
• Goals & Objectives
• Payload (WINCS)
• Structure
• Electrical Power System
• Attitude Determination and Control
• Command & Data Handling
• Communications
• Concept of Operations
• Michigan eXploration Lab
• Project Organization
• Concept of Operations2
Project Organization
3
ADCDae "Young" Lee (L)Luke DeGalanPrince Kuevor
C&DHSo-Hee Kang (L)Bobby Huddleston
COMSrinagesh Sharma (L)Anton Frolenkov
EPSCharles Lacy (L)Lucas Mason
STRAri Porter (L)Josh WeissKaitlyn BurkeJosh LipshawGarrett Cullem
NRL Payload PIDr. Andy Nicolas
SPRL LiaisonDamen Provost
ADC – Attitude Determination and Control EPS – Electrical Power SystemC&DH – Command and Data Handling COM – CommunicationNRL – Naval Research Laboratory PI – Principle InvestigatorSPRL – Space Physics Research Laboratory STR – Structures
Black - StudentBlue - Faculty / Staff / Gov
Science PIDr. Aaron Ridley
Engineering PIDr. Jamie Cutler
Project ManagersCasey SteuerDan Abramov
Systems EngineerTyler Rose
Goals & Objectives
Mission Objective
CADRE will measure the magnitude and direction of ion and neutral winds, as well as temperature and composition of the thermosphere in the auroral zone.
Technology Demonstration
• On orbit WINCS demonstration
• 1.0°/0.1° CubeSat attitude control / knowledge accuracy
• High data rate S-band radio
4
Goals & Objectives
Science Objectives
1. What are the scale sizes of thermospheric gradients in auroralzone?
2. How does thermospheric response to energy input spread away from location of input?
3. What are the interhemispheric asymmetries in the response of the thermospheric energy input?
5
WINCS
• NRL has developed a made-for-CubeSats in situ sensor:• Volume: 7.62 x 7.62 x 7.11 cm• Mass: 635 g• Power: 1.3 W
• 4 Electrostatic Analyzers (2 WTS, 2 IDS)• Wind and Drift• Horizontal and Vertical Direction
• 2 Mass Spectrometers (NMS/ IMS)• Coupled together they are called GEMS
• Gated Electrostatic Mass Spectrometer• Ion and Neutral Composition• Crossed Paths of flight
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Winds Ions Neutrals Composition Suite
WINCSIDTS/WTS
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• At the heart of the WTS/IDS instruments is the small-deflection energy analyzer (SDEA)
• The upper and exit plates are biased at voltage VSDEA (typically less than 10 volts in flight) while the entrance and lower plates are at ground potential.
• The top of the left chamber in the illustration below can be used to deflect the ambient ions and to ionize neutrals. One half of the SDEA can be utilized for ions (e.g., bottom half) while the other half (e.g., top) can be utilized for neutrals.
WINCSIDTS/WTS
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• Two separate analyzers measure the angular-energy distributions in two planes• This is why WTS1/IDS1 and WTS2/IDS2 have slits perpendicular to each other
• The position of the maximum flux in each analyzer specifies the horizontal and vertical angles in whichthe particles enter the detector. By sweeping in energy, the magnitude of the velocity can be determined.
• WINCS contains two GEMS as time-of-flightmass spectrometers.
• Shortly after the potential is turned on, lowmass particles will be deflected enough thatthey start to come through the exit slit.Some time later, heavier particles will startto come through.
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WINCSGEMS
WINCS
Flight Heritage
• ISS
• STP-Sat3
• SENSE
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WIB and PIM
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Payload Interface Module (PIM)
WINCS Interface Board (WIB)
Concept of Operations
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Time in Mission (min) Event
Deployment: T+0 Spacecraft power on
T+60 Antenna and panels deploy
T+65 Begin RF beaconing
After Ground Contact Subsystem checkouts / commanding tests
After Ground Contact Determination of successful panel deployment
(automatic)* ADCS sensor calibration and detumble
T+20 Days Payload commissioning
*Next slide has conops diagram
Concept of Operations
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Electrical Inhibits
Approved Inhibit Design
Structure
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Structure
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Structure
17
Deployable panels being tied down
80 pound fishing wire
wrapped around
burn resistor
Electrical Power System
18
C&DH
FCPU
PIM
Batteries
AMBER
Body Panels
Depl. Panels
-Z
COMM
Indigo
Power Amplifier
S-BA
ND
MOBO
ADCS
Photodiodes
Star Tracker
IMU
Magnetometer
SENSO
RS
WINCS
WINCS interface Board
Payload
Antenna
UHF
Antenna Reaction Wheels
AC
TUA
TOR
S
TCB
Magnetorquers
EPS
NOTE• UHF Radio is on
C&DH Board
• Flight Heritage
• Li Ion Batteries
• 8 Solar Panels• 4 Deployable
• 4 Body-mounted
• 64 Solar Cells
Key EPS Components
19EPS Board Battery Pack Solar Panels
Attitude Determination & Control
20
BUS LINE
5 V
3.3 V
VBat
EPS
C&DH
Payload
COMM
Sensors Actuators
Torquercontrol board
(I2C)
RX
N W
hee
ls(U
AR
T)
Star Tracker
Switch
EpsonIMU(SPI)
Switch
Photodiodes(I2C)
Magnetometers(I2C)
Motherboard
Switch
ADIS 16405 IMU
Boeing Star Tracker
Honeywell HMC5883L (8)
- ZInterface
Board
On Deployables
(I2C)
Switch
Switch
Switch
SFH
24
30
(12
)
(SPI)
(UART/GPIO)
ADIS 16405 IMU
(not in use)
Processor BoardMSP430
Air CoreMagnetorquer
Metal CoreMagnetorquer
Metal CoreMagnetorquer
Torquer Control Board (TCB)
21Prototype TCB
Sinclair Reaction Wheel (x3)
22
Fit checking the reaction wheel
with our structure
Mass models are used for initial vibration testing
Boeing Star Tracker
• Quaternion returnedfrom photos of starfield.
• Contains 2 IMUsfrom Analog Devices
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Command & Data Handling
24
EPS
ADCS
Payload
COMM
FCPUBUS LINE
5 V
3.3 V
VBat
Stamp Debug(UART)
Power Amplifier
Taskit Stamp 9G20
MSP430
AT91SAM9G20
Processor
WDT(UART)
AstrodevLi Radio(UART)
UHF
RTC(SPI Backup)
RTC(I2C Primary)
SD Card 1
SD Card 2
SD Card 3
SD Card 4Regulator Regulator
Multiplexer
Low Power
Data Line
RTC
512 MB Flash Memory
Muti-MediaCard
Payload InterfaceModule
Antenna
Face
Power Switch Isolator
Power Switch Isolator
Power Switch Isolator
Power Switch Isolator
Command & Data Handling
25
Mezzanine board forextra SD cards
C&DH board with integrated astrodev UHF radio (right side).
26
CommunicationsS-Band
BUS LINE
5 V
3.3 V
VBat
EPS
C&DH
Payload
ADCS
Indigo
Igor
FPG
ASPI
Memory
LDOLDO
1.5 V
DC-DCBuck95%
Low Power Amplifier
RFMDSZM-3166Z
Body of CADRE
Patch Antenna
Digital/Analog
Converter
Low Freq./High Freq. Mixer
LDO Low Dropout Regulator Low Frequency
High Frequency
Radios
27
Astrodev Li RadioUHF
(included with FCPU slide)
Indigo S-BandRadio
Power Amplifier for Indigo
28
CommunicationsGround Station
• 2 Ground Stations at University of Michigan
• Long tradition of working with helpful HAMS
• Possible use of NASA Ames 8m Dish