��· MIS/MCS COST.ESTIMATE �ov.t.... o A

ASSUMPTIONS: (1) LAUNCH VEHICLE AND OPS PROVIDED GFE BY NASA (2) ATP PROVIDED NOW(I), RESOURCES AVAILABLE NOW (3) MISSION OPS -10 MONTH MTO, 14 MONTH DATA COLLECION

(4) INSTRUMENTS + GSE PROVIDED GSE

SPACECRAFT MIS BUS $20M IN-PLACE CONTRACT MCS BUS $12 M IN-PLACE CONTRACT SOLAR ARRAY(MCS) $2M MOD EXISTING CONTRACT PROPULSION SYS $4M IN-PLACE CONTRACT HIGH GAIN COMM $2.5M NEW

· BREAKING STAGE $1M NEW SOFTWARE $4M IN-PLACE CONTRACT

INTEGRATION & TEST $10M IN-PLACE CAPABILITIES

GSE $1M IN-PLACE CONTRACT RANGE COSTS $3M REIMBURSABLE MISSION OPS . . PLANNING $1 M IN-PLACE CONTRACT EXECUTION $5M IN-PLACE CONTRACT

TOTAL $65.5 MILLION I •

PROGRAMMATIC APPROACH

USE MSTI-3 HARDWARE ALREADY ON ORDER FOR MARS IMAGING S/C

USE MSTI-4 HARDWARE ON ORDER FOR MARS COMM S/C SUPPLEMENT MSTI-4 ORDER WITH ADDITIONAL COMPONENTS

PURCHASE STAR 30BP BRAKING MOTOR

DELTA II LV GFE FROM NASA OR PROCURED FROM AF

SCIENCIE INSTRUMENTS GFE FROM JPL · · MOCA SPARE MOLA SPARE RECONFIGURE GRS FROM EXISTING SPARES .·

NEAR TERM PROGRAMMATIC ISSUES

·,·. ·-� ··

MUST REDUCE DELTA II INTEGRATION TIME

LONG LEAD PROCURMENTS BRAKING MOTOR COMMUNICATION GEAR PROPULSION COMPONENTS SOLAR ARRAY FOR MSC

$$$ REQUIRED NOW FOR LONG LEAD COMPONENTS

MSTI-3 TMD MISSION SLIP 7 MOS MSTI-4 TMD MISSION ·SLIP 4 MOS '"·· ...

BENEFITS -OPTION

SATISFIES M.O. PRIMARY SCIENCE OBJECTIVES:

HI-RES VISIBLE OBSERVATIONS · MOCA 1.4 M RESOLUTION MSTI MARS IMAGING SPACECRAFT LASER ALTIMETER MOLA

· 2.1 M RESOLUTION

GAMMA RAY SPECTROMETER GRS MSTI MARS COMMUNICATION .. MARS BALLOON RELAY RADIO MBR SPACECRAFT

USES S/C HARDWARE ALREADY IN PIPELINE

TOTAL S/C COST< $65M

MARS COMMUNICATION SPACECRAFT WILL'SUPPORT·RELAY FOR RUSSIAN OR '·AMERICAN ROVERS/PROBES

• • ... ' � ·�·:� ::: : ••�·; 1·•• ·: ' •• : • .· . . ·, �- .�::"._>��·_ .. �:./:: ::::'< . ; " ' .. " '• r I (���

CRITICAL ORBITAL PARAMETERS/ISSUES

• Injection Mass Capabilities at C3 = 10 (km/s)A2 :

- 2200 lbs by Delta II, 3-Stage 7925

- 1100 lbs by Titan II G/STAR48

• To Circularize at Orbit Altitude= 378 km, need AV = 2.06km/ s

m, = 1.96 km/ s • Injection Mass Ratio, • , • m

'·

..

• Baseline Departure from ETR

. ' . - . "r '��·"· • li .,

' \

MARS AT ARRIVAL

··. ' ECLIPTIC PRO,JECT I ON

Inner Planets

Year: 1995 I Mon t11: Aug I Dau: 27 Jlour: 0 Min: 0

-.Tulian Date: 2-1'19956.5

Position of Mars

Ueliocentt>ic

Ec 1 i pt i c Ft>a11e: '· ·

D ::: 1.54-12 au I.a t:::-9. e-2 c:tllll8 r.on::::232. "1

Geocentric Equator Fr>a11e:

D ::: 1..9906 au RA :::2BB.9 DEC :::--B. B6�f dt::u ;'� / \ ' \

EARTH A• DEPARTURE

ECLIPTIC PllOJECTJON

Inner Planets

Year: 1'994 Month: Oct

Da�J: 2<4 tlour: 0 Min: 0

Julian Date: 2-14�6-19.5

Position of Earth

Ueliocentric Ecliptic Frane:

D ::: 0.��47 au I.at:::a. a I.un:::3B. 3-17 deg

Geocentric Equator FriUle:

n ::: B.t:t Hi\ ::: B.B DEC ::: B.B