DINO PDR 23 October 2015 DINO Systems Team Jeff Parker Anthony Lowrey

DINO PDR April 21, 2023

DINO Systems Team

Jeff Parker

Anthony Lowrey

Colorado Space Grant Consortium


Big Picture

• Assure that DINO’s design meets all of DINO’s objectives

• DINO’s Mission Objectives:– DINO will demonstrate deployable structures for

nanosatellites– DINO will demonstrate onboard intelligent operations – DINO will measure cloud heights from space using a

stereoscopic imaging technique– DINO will provide educational support for K-12 and

college-level students



System Requirements

• The spacecraft system shall meet its Mission Objectives Requirements– Deployable objectives

– Intelligent operations objectives

– Science objectives

– Education objectives

• The spacecraft system shall meet its Operational Requirements– Survive launch

• Launched in a Space Shuttle

– Operate in space for 12 months

– Two-way communication between the spacecraft and ground for the full mission duration

– Full support from mission operation control center for mission duration



System-Level Tasks

• Keep the entire system on-track• Ensure that all deadlines are met• Ensure proper communication

– Between subsystems– With Industry/Academic supporters

• Ensure proper safety in each of DINO’s phases– Design, construction, integration, testing, transportation, and delivery

• Design, build, test all interfaces– Subsystem communication interfaces– Integration and test fixture– Ground support equipment

• Provide and manage all necessary documentation• Support all subsystems



System Tools

• Requirement Document– DINO’s Objective- and Operational-level requirements– System-level requirements– Subsystem-level requirements

• Design Documents– System Spreadsheet– TPS Reports– Electrical Interface Agreement Document (EIAD)

• Communication– Subsystem to subsystem– Industry/Academic supporters

• Budgeting– Mass– Power

• Control of DINO’s design iterations



System Functional Diagram

Imaging

Cam A Cam B

Legend

USB

ADCSTR1

TR2

TR3

MAG

Sun Sensors

x6

Rate Gyro x3

Data Bus

Power Lines

Thermal

+5V Line

+/-12V Line

MLI Blkts

Therm x30

Data Line

Comm

TxAnt / Radio / TNC

Ext TNC

Serial / I2C

C&DH

Flight Computer

Interface Board

Wireless

Power

Li-Poly Battery

+15V Unreg. Line

+28V Line

Prim SA

Body SA PCB

Mechanisms

EMC Hinges x4

HOP

Tip-Mass Upper LB

Tip-Mass

TM Cam

TMComm

Battery

Tether Release

Mech

TM Lower

LB

PCB

MicroProc

IB

RxAnt / Radio / TNC

Tip-MassAnt / Modem



Daytime Operations Diagram

Imaging

Cam A Cam B

Legend

USB

ADCSTR1

TR2

TR3

MAG

Sun Sensors

x6

Rate Gyro x3

Data Bus

Power Lines

Thermal

+5V Line

+/-12V Line

MLI Blkts

Therm x30

Data Line

Comm

TxAnt / Radio / TNC

Ext TNC

Serial / I2C

C&DH

Flight Computer

Interface Board

Wireless

Power

Li-Poly Battery

+15V Unreg. Line

+28V Line

Prim SA

Body SA PCB

Mechanisms

EMC Hinges x4

HOP

Tip-Mass Upper LB

Tip-Mass

TM Cam

TMComm

Battery

Tether Release

Mech

TM Lower

LB

PCB

MicroProc

IB

RxAnt / Radio / TNC

Tip-MassAnt / Modem



Nighttime Operations Diagram

Imaging

Cam A Cam B

Legend

USB

ADCSTR1

TR2

TR3

MAG

Sun Sensors

x6

Rate Gyro x3

Data Bus

Power Lines

Thermal

+5V Line

+/-12V Line

MLI Blkts

Therm x30

Data Line

Comm

TxAnt / Radio / TNC

Ext TNC

Serial / I2C

C&DH

Flight Computer

Interface Board

Wireless

Power

Li-Poly Battery

+15V Unreg. Line

+28V Line

Prim SA

Body SA PCB

Mechanisms

EMC Hinges x4

HOP

Tip-Mass Upper LB

Tip-Mass

TM Cam

TMComm

Battery

Tether Release

Mech

TM Lower

LB

PCB

MicroProc

IB

RxAnt / Radio / TNC

Tip-MassAnt / Modem



Safe Mode Diagram

Imaging

Cam A Cam B

Legend

USB

ADCSTR1

TR2

TR3

MAG

Sun Sensors

x6

Rate Gyro x3

Data Bus

Power Lines

Thermal

+5V Line

+/-12V Line

MLI Blkts

Therm x30

Data Line

Comm

TxAnt / Radio / TNC

Ext TNC

Serial / I2C

C&DH

Flight Computer

Interface Board

Wireless

Power

Li-Poly Battery

+15V Unreg. Line

+28V Line

Prim SA

Body SA PCB

Mechanisms

EMC Hinges x4

HOP

Tip-Mass Upper LB

Tip-Mass

TM Cam

TMComm

Battery

Tether Release

Mech

TM Lower

LB

PCB

MicroProc

IB

RxAnt / Radio / TNC

Tip-MassAnt / Modem



Mass BudgetMain Satellite Mass Budget

ADCS9%

Solar Panels

8%

Power8%

Comm5%Margin

25%

Str/Mech36%

Thermal2%

C&DH2%

Systems3%

Science2%

• Total Allocated Mass: 18.75 kg• Margin: 6.25 kg• Total Mass: 25 kg

Tip-Mass Mass Budget

Comm8%

Science9%

Systems2%

Thermal2%

Power15%Str/Mech

39%

Margin25%

• Total Allocated Mass: 3.75 kg• Margin: 1.25 kg• Total Mass: 5 kg



Power Budget

Normal Operating Daytime

Science5%

Comm Tx6%

Comm Rx4%

Thermal3%

ADCS13%

C&DH13%

Power31%

Margin25%

• Total Allocated Power: 22.0 W-hr• Margin: 5.5 W-hr• Total Power: 27.5 W-hr

Normal Nighttime

Comm Tx

10%

ADCS11%

Comm Rx6%

Thermal1%

Power22%

C&DH25%

Margin25%




Power BudgetSafe Mode

C&DH31%

Power34%

Comm Rx9%

Thermal1%

Margin25%


Tip-Mass

Power17%

Comm45%

Imaging11%

C&DH2%

Margin25%




Integration and Test PlanPower

IntegrationComm.

Integration

Installationin Boxes

Verify

Verify

FunctionalTesting

SubsystemTesting

Mountingon Isogrid

Installation ofMechanisms

on Isogrid

RouteWiring

Harness

CloseStructure

FunctionalTesting

MechanismsTesting

Mount SolarPanels

Verify SolarPanels

FunctionalTesting

ElectricalIntegration

MechanicalIntegration



Mission Mode Timeline

LaunchICU, DINODeployment

MissionActivation

TetherDeployment

FITSDeployment

AerofinDeployment

SafeMode

SafeMode

Normal DaytimeOperations

Normal NighttimeOperations

SafeMode

AttitudeStabilization



Overall Mission Timeline

Laun

ch

ICU

Dep

loym

ent

DIN

O D

eplo

ymen

t

Mis

sion

Act

ivat

ion

Tet

her

Dep

loym

ent

FIT

S D

eplo

ymen

t

Aer

ofin

Dep

loym

ent

Nor

mal

Sci

ence

Ope

ratio

ns



Launch Phase

Sys

tem

Che

ck

Laun

ch

ICU

Dep

loym

ent

from

Orb

iter

DIN

O

Dep

loym

ent

Mis

sion

A

ctiv

atio

n

ICU

Sep

arat

ion



Mission Activation Phase

Mis

sio

n A

ctiv

atio

n

Po

wer

Up

Orbit

SunlitEclipse

Flig

ht S

yste

m P

owe

r up

Flig

ht C

ompu

ter

Pow

er U

p

Po

we

r S

yste

m A

ctiv

ate

d

Com

m,

Th

erm

al,

AD

CS

Po

we

r U

p

Sys

tem

Hea

lth C

heck

AD

CS

Act

ivat

ion

Co

mm

un

icat

ion C

omm

In

itia

lizat

ion

Bea

con

Tra

nsm

issi

on

Gro

und

Com

mun

icat

ion

Dep

loym

ent

Ph

ase



Deployment Phase

Tet

her

Dep

loym

ent

Orbit

SunlitEclipse

Tet

her

Sys

tem

Hea

lth C

heck

Att

itude

Sta

biliz

atio

n C

hec

k

Tet

her

Dep

loym

ent

Gro

und

Com

mun

icat

ion

Tip

-Mas

s P

ower

Up

Tip

-Mas

s H

ealth

Che

ck

Tet

her

Sys

tem

Hea

lth C

heck

Tet

her

Im

age

Acq

uisi

tion

and

D

own

link

Gro

und

Com

mun

icat

ion

Tip

-Mas

s P

ower

Do

wn

AD

CS

Sta

bili

zati

on



Deployment Phase

FIT

S D

eplo

ymen

t

Orbit

SunlitEclipse

Att

itude

Sta

biliz

atio

n C

hec

k

So

lar

Arr

ay A

ctiv

atio

n

FIT

S D

epl

oym

ent

Gro

und

Com

mun

icat

ion

Tip

-Mas

s P

ower

Up

Tip

-Mas

s H

ealth

Che

ck

Flig

ht S

yste

m H

ealth

Che

ck

Tip

-Mas

s Im

age

Dow

nlin

k

Gro

und

Com

mun

icat

ion

Tip

-Mas

s P

ower

Do

wn

Tip

-Mas

s Im

age

Acq

uisi

tion



Deployment Phase

Aer

ofi

n D

eplo

ymen

t

Orbit

SunlitEclipse

Att

itude

Sta

biliz

atio

n C

hec

k

EM

C H

inge

Dep

loym

ent

Gro

und

Com

mun

icat

ion

Tip

-Mas

s P

ower

Up

Tip

-Mas

s H

ealth

Che

ck

Flig

ht S

yste

m H

ealth

Che

ck

Tip

-Mas

s Im

age

Dow

nlin

k

Gro

und

Com

mun

icat

ion

Tip

-Mas

s P

ower

Do

wn

Tip

-Mas

s Im

age

Acq

uisi

tion



Science Operations Phase

No

rmal

Op

erat

ion

s

Orbit

SunlitEclipse

Att

itude

Sta

biliz

atio

n

Sci

ence

Im

age

Acq

uisi

tion

Gro

und

Com

mun

icat

ion

Flig

ht S

yste

m H

ealth

Che

ck

Bat

tery

Cha

rgin

g



Safety

• Current Progress– Safety designs incorporated into PDR design– Good knowledge for what safety aspects must be included

• Next Step– Safety courses in September

• Safe parts-manufacturing

• Safe handling of electrical components

• Buddy System!

– Prototyping

• Future Plans– Follow DINO’s safety regulations



Subsystem Risk Assessment

AD

CS

C&

DH

Com

m

Imaging

Mechanism

s

Pow

er

Softw

are

Structures

Therm

al

Tip-M

ass

Overall P

rogram

Assessm

ent

Performance

Schedule

Cost

Safety

Testing

Manpower

Facilities

Overall Subsystem Assessment

= low risk

= medium risk

= high risk

= N/A



Contingency PlansRisk Level Responsible Party Contingency Plan

FITS delivery failure High Systems Team Increase efficiency of body-mounted cells; double-deployment of aerofins

EMC hinge / aero-fin delivery Med Systems Team Eliminate aerofins

Body-mounted solar panel delivery

Med Power Purchase through / provided by other vendor

Power system delivery Med Power Implement in-house design of power system

Tether deployment failure Med Str/Mech Use magnetic torque rods as primary ADCS control

FITS deployment failure Med Str/Mech Go into low-power mission mode

Tether stability, orientation failure

High ADCS Go into failed-stability mission mode; cut tether



Issues and Concerns

• Mass– Structures / Solar Panels do not have enough mass allocated to

them– Others are swiftly approaching mass limits

• Power– Loss of structural size – less room for body-fixed solar panels– Increased mission activation / deployable timeline– Close to budget

• Complete all trade studies– Comm antenna– Science imaging design– Spacecraft configuration (FITS arrays locations)



Appendix



Mass Budget



Power Budget



Power Budget Cont.



Power Budget Cont.



Tip-Mass Power Budget



Design Deadlines

Trade Study 75% Confidence Date

Deadline

Comm Antenna Design Sept 1st Sept 8th

Imaging Camera Design Aug 18th Sept 1st

Flight Configuration