C. L. Olson 

NRO APPROVED FOR 

RELEKSE 1 JULY 2015 rift FtelVtioi 

WIt 

.13.1F- 107- .5044 - (38 

Copy 2 of 3 

Page 1of 9 

Total Pages 9 

.7- 

24 October 1968 

To: L. A. Skantze 

Subject: PSPP update, Advance Plans, Section 17. 

Transmitted with this memo is a draft update of the Advance Plans 

section of MOL P. S. P. P. , as requested by Major H. Butler. 

The four original charts have been altered in accordance withcurrent guidance and cost estimates, and the text has been modified 

(as noted by margin marks) to reflect follow-on block designations. 

Attachments: 

PSPP. update, Advance plans, Section 17 

PIA-NOCE VIN BYEMAN 

tONTROL SYSTEM ONLY, 

OCT 28 19113 
NRO APPROVED FOR 

' RELEASE 1 JULY 2015 

v 

BIF-107-50225-68 

Page 2 

OR/ ►v 

17. 2.1 Short and Long Term Planning Considerations 

Since the advanced planning function is part of the MOL 

Program office, planning must concern itself with both 

short term and long term aspects. The fundamental 

objective is to evolve the MOL hardware in the most 

economic and effective manner. The short term factor 

is the consideration of how long one would continue to 

produce and fly the basic MOL system, with modest 

improvements, keeping in mind that the basic subsystems 

and hardware designs will be ten years old. The long 

term factor is the consideration of how the system can 

be evolved in a true growth step, providing substantial 

increases in mission duration and mission flexibility, yet 

at the same time evolving as economically as possible 

from the basic MOL system. A review of many options 

and trades between these two factors has led to the planning 

perspective and funding profile shown in Sections 17.3 and 

17. 4 which serve as the basic planning framework of the 

MOL follow- on systems. The remainder of the sections 

preceding these charts will discuss tasks and analyses 

related to these charts and the planning framework they 

reflect. The Advanced Planning Perspective Chart in 

section 17.3 reflects four vehicle b locks for purposes 

of identifying intermediate system evolution steps. 

a PiP 11/ 
BIF- 107- 50225- 68 

Page 3 a,,,,v NRO APPROVED FOR 

-RELEASE 1 JULY 2015 

17. 2. 1.1 Extension of the Baseline MOL System 

The anticipated procurement of a limited number of 

basic MOL follow- on vehicles, shown in Sections 17. 3 

and 17. 4 as Block II, will be considered in terms 

only modest improvements that can be reasonably 

incorporated into the system. The improvements fall 

into two categories: System modifications, and Mission 

Enhancements. 

17. 2. 1. 2. MOL Growth System 

A considerable number of studies, both in-house and by 

contractor, have examined how a true MOL growth 

system could be evolved. Consistent with the objective 

outlined in Section 17. 1. 4, a reference system referred 

to as the "Long Duration Operations" (LDO) system has 

been evolved. It consists of an initial MOL vehicle containing the payload and laboratory which is lifted into 

orbit and remains there continuously for one year, and a 

resupply vehicle which is launched every 60 days to change 

crews and provide the necessary expendables to sustain 

continuous mission operations. This reference system is 

reflected in the prespective and profile charts of Sections 

17. 3 and 17. 4 as Block III. . 
blicr 1UY-50ZZ5- 68 

Page 4 NRO APPROVED FOR 

.RELEASE 1 JULY 2015 

17. 2. 1, 2. 3 Advanced Optical Payload 

Preliminary feasibility studies of an advanced 

pptical payload have been initiated and are being 

conducted in support of the MOL program as well as 

the unmanned satellite programs. Requirements 

peculiar to a manned MOL of the LDO type have been 

incorporated into the_optical system studies. 

Preliminary configurations of an optical payload of 

this size have been developed and the critical technology identified. A preliminary LDO configuration, 

incorporating the_optical payload has been 

developed and further studies of the LDO concept will 

be coordinated and updated in parallel with the 

optical systems studies. Based upon work to 

date, the bench mark for possible introduction of 

such a system is shown in Section 17. 3 as Block IV. 

Do 

O P( f~A✓ 
• NRO APPROVED FOR 

RELEASE 1 JULY 2015 IHRETI) 6 Fi iv 

BIF- 107-50225-68 

Page 5 

17. 2. 1. 1. 1 Subsystem Modification 

Earth atmosphere dynamics for the 1973-1977 time 

period will permit reduction in orbit keeping propella 

This will allow addition of expendables for mission 

duration up to 45 days. Additional expendables and 

equipment can be adapted from the MOL development 

program. The extended duration capability can be 

attained with minor modifications to the basic MOL 

system design. Timely utilization of MOL Development Program experience can minimize development 

cost. 

17. 2. 1. 1. 1. 1 Program Benefits 

Extension of MOL orbital duration capability 

permits an equivalent increase in product quantity 

per mission, with attendant improvements in 

mission economics. Alternatively, the added 

propellant required for extended duration could be 

used to improve mission product quality through 

intermittent low altitude flight, or expendables 

weight could be traded for mission payload 

improvements. 
tr. --to5 

:Ala 

c 0 N 

,te a 

0 

U 

0 

N 

BASELINE 

i L- 0 

o 

00 

► 

0 0 N 

0 

0 

NO 

0 

0 

tt 

(.3 N 

0 N 

0 c) r,

a z • 

o 

U Z 

F.1 u) fr4 

9 a2.ed 

-G770c -1 AT -.rig 

90' 

0 0 

0 

•44 M (NI 

0 0 • 

0 

1-1 
'fiatt 4) 

2 

a 

w

. 

O 

0 

1-1 

O 

<17 

• 0 

'31 

• 0 0• 

cn 

C; 

N 

z E-1 

0 

E-1 or4 4 

N z H 

E-44 

Z a Z 

0 

0 0 

g41- 

,-1 

ORBITING V

EHICLE I

MPROVEMENTS 

0 ADDITIONAL SYSTEM APPLI

CATIONS 

ADDITIONALDODPAYL

OADS/MISSIONS 

• 

L 3S-ed 

89 -SZZOS -LOT -AM 
C' 

-4 

CO N 

N. 

N 

Cfs 

Cvl 

N 

Cfs 

O N 

.64 

8 02"ed 

897-SZZOS-L01-314I 

••+-41WTf 

4 

.20 

z 

2 

4 

0 

A 

0 

<4 

41 P-I H ›-f 

<4 cn a 

a, In ›-t Z Z 41 H cn o 

W 0 z pa H rx1 P. A 

Z U iP l u) 121 ELI >1 

a 41 

41 ;:ff z 41 r.,1 p-, 

41 al E' 

f:14 0 IT.1 0 

O A A U Ft g4 

> c;) 

o

a

a 4 rzi <4 A 

41 4 <4 

g 

Ef 4 

• W < 0 z (.) 

as 

 

41 4 0 41 Z 

A E-1 

A X X Z >4 r-1 

o

U Z < w Z Z 

a R 0 1 

., ri, g4 

t-I

• 

, 

0 

.cri 0 • 

a 

DC 

• 0 • 

y 
0 

a 

a, 

0 

• • 0 _ • 

ADDITIONAL SYSTEM APPLICATIONS 

• 

ON- ORBITOPTICALTES 

P 0 

u) 4 

as a 

Pl >4 

cf) 

z 

• Q 

w • E., 

<4 

(.) W P4 0 A ,tf r

Z 4 0 0 4-1 

W.) Z 

• Z 41 

• 

U) 

0 

a, 

W 

4 H 

0 

a 

u-, 

0 2 LL 

6 02eci 

89 -MOS -LOT -dig 

t(' 0 431M