The Shape of Power in SpaceUltra• Lightweight: 1/3 total mass* (150 W/kg BOL)• High strength: Designs with strength >5 g's, flight

proven*• High Deployed Stiffness: 3-8x higher 1st mode*,

designs with 3-5 Hz available• Compact: 1/4 stowage volume and footprint*

(40 kW/m3)• Reliable: flight proven; deployment powered by a

single (electrically redundant) motor

Flexible • Interchangeable with rigid array technology• Scalable: ~Ø1.7 m (0.5 kW) to Ø10 m (20 kW) and

beyond• Customizable: may be optimized for $/W, W/kg,

deployed frequency, etc.• Maneuverable: option to withstand >5 g’s deployed

(e.g. for landing, docking, or transfer orbit power)• All photovoltaic technologies accommodated

including with concentrators

Motor Driven Deployment / Staging Options:• “Standard” wing staging (e.g. Phoenix, CRS, InSight)• Options with hinged standoff boom (e.g. Orion CEV)

UltraFlex™ Solar Array Systems

Breakthrough Performance, Competitive Cost, Space Flight Proven

* compared with rigid panel solar array of same power

northropgrumman.com ©2018 Northrop Grumman Corporation. All Rights Reserved. FS007_15_1

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600

700

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2000

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5000

6000

10 15 20 25 30 35 40

Array  Pow

er,  B

OL  (kW,  2  wings)

Array  M

ass  (kg,  2  wings)

Wing  Dia  (m)

2 decades of development and Flight Heritage

www.atk.com

Non-export controlled – Marketing Level 12/4/13

UltraFlex Solar Array Systems MegaFlex Array-level (2 wings) performance

vs. Diameter (30% TJ cells)

Program

Dat

e Hardware Built

Wing Dia. (m)

Cell Technology (efficiency)

Maturity Achieved Comments

Qualification UltraFlex

solar array wing 19

94 -

1995 Qual Wing

(1 active gore)

3.1 BSFR Silicon (13.7%)

Successfully completed full

wing level qualification

tests

Qual-wing system (with one active gore) successfully qualified - survived all thermal, vibration, and vacuum environments. Successful coupon testing: 1650 cycles -150C to 100C.

Mars 01-Lander 19

98 2 Flight Wings

2.1

High Efficiency

Silicon(17%)

Flight hardware built, qualified, and delivered.

Robust design deploys without offloading in 1g. Program cancelled due to NASA budget constraints. Successful coupon testing 200 cycles -140C to 80C.

Mars Phoenix Lander

2004

- 20

07

2 Flight Wings

2.1 TJ(24%)

100% Flight success

Robust design deploys without offloading in 1g environment and provides >103 watts/kg specific power

NASA-New Millenium ST8

2004

-200

9

Full-scale EDU

5.5Mass

Simulators

Completed CDR; TRL 6

achieved. Mission

Cancelled

Scale-up hardware and modeling capability validated by extensive hardware build & test program

NASA CEV - Orion

(now MPCV) 2008

-201

1

Many validation coupons

6 TJ(28%)

PDR 8/2009 (on hiatus)

UF Technology selected for flagship manned NASA mission 2.7g’s on-orbit strength. Coupon qualifications.

Orbital CRS Cygnus

2011

-201

4

10 Flight wings

3.7 ZTJ Luna (29%)

Delivered, flight pending

UF selected for ISS "COTS" resupply cargo mission. ~5 g's deployed strength to withstand Station plume loads.

MegaFlex: Advanced Solar Array

for SEP 2012

-201

4

Full-scale Flight-like

Wing9.6

Large-area TJ & IMM coupons

TRL 5 demonstration

program

Technology Development to enable near-term Solar Electric Propulsion missions of 30-50kW with scalability to 250kW.

Mars Insight

2013

-201

5

2 Flight Wings

2.15

High Aspect ratio ZTJ 29.5+%

Red / BOL optimized

CDR 3/2014(in production)

Scaled-up of Mars Phoenix arrays; 75 m/s Martian wind load capability.

Two Decades of Development and Flight Heritage

MegaFlex350kW Spacecraft in EELVMegaFlex incorporates a folding panel for twice the power on a given launch vehicle.

10 15 20 25 30 35 400100

Arr

ay P

ower

, BO

L (k

W, 2

win

gs)

Arr

ay M

ass

(kg,

2 w

ings

)

MegaFlex Array-level (2 wings) Performancevs. Diameter (30% TJ cells)

Wing Diameter (m)

200300400500600700

01000

200030004000500060007000

LEO

GEO

Planetary Lander

Deep Space (Solar Electric Propulsion)

Successfully completed full wing level qualification tests

Flight hardware built, qualified, and delivered.

100% Flight success

Completed CDR; TRL 6 achieved. Mission Cancelled

PDR 8/2009 (on hiatus)

Flown 3 Missions

TRL 5 demonstration program

Delivered2018 Flight

BSFR Silicon (13.7%)

High E�ciency Silicon (17%)

TJ (24%)

Mass Simulators

TJ (28%)

ZTJ Luna (29%)

Large-area TJ & IMM coupons

HIgh Aspect ratio ZTJ 29.5+%Red / BOL optimized

Qual Wing (1 active gore)

2 Flight Wings

2 Flight Wings

Full-scale EDU

Many validation coupons

10 Flight wings

Full-scale Flight-like Wing

2 Flight Wings

3.1

2.1

2.1

5.5

6

3.7

9.6

2.15

‘94-’95

‘98

04’-07’

04’-09’

08’-11’

11’-14’

12’-14’

13’-15’

Qual-wing system (with one active gore) successfully qualified - survived all thermal, vibration, and vacuum environments.Successful coupon testing: 1650 cycles - 150C to 100C.

Robust design deploys without o¥oading in 1g. Program cancelled due to NASA budget constraints. Successful coupon testing 200 cycles -140C to 80C.

Robust design deploys without o¥oading in 1g environment and provides >103 watts/kg specific power

Scale-up hardware and modeling capability validated by extensive hardware build & test program

UF Technology selected for flagship manned NASA mission 2.7g’s on-orbit strength. Coupon qualifications.

UF selected for ISS "COTS" resupply cargo mission. ~5 g's deployed strength to withstand Station plume loads.

Technology Development to enable near- term Solar Electric Propulsion missions of 30-50kW with scalability to 250kW.

Scale-up of Mars Phoenix arrays; 75 m/s Martian wind load capability.

Program Started

ZTJ Luna (29%)

2 Flight Wings

6.118’-21’ Scale-up of CRS/Cygnus design, engineered for 5.1AU deep space environment.

MarsInsight

LUCY

MegaFlex:AdvancedSolar Arrayfor SEP

Orbital ATKCRSCygnus

NASA CEV -Orion(now MPCV)

NASA - NewMilleniumST8

MarsPhoenixLander

QualificationUltraFlexSolar ArrayWing

Mars 01 -Lander

CommentsMaturityAchieved

CellTechnology(e�ciency)

WingDiameter

(m)

HardwareBuilt

DateYear(s)Program

Qualified for all Space Environments:

More InformationNorthrop Grumman Space ComponentsDeployables600 Pine AvenueGoleta, California 93117(805) 685-2262Info-SpaceComponents@ngc.com