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

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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?

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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

15

Structure

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Structure

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Deployable panels being tied down

80 pound fishing wire

wrapped around

burn resistor

Electrical Power System

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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

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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

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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

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Mezzanine board forextra SD cards

C&DH board with integrated astrodev UHF radio (right side).

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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

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Astrodev Li RadioUHF

(included with FCPU slide)

Indigo S-BandRadio

Power Amplifier for Indigo

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CommunicationsGround Station

• 2 Ground Stations at University of Michigan

• Long tradition of working with helpful HAMS

• Possible use of NASA Ames 8m Dish