WEIGHT REDUCTION OF THE U-2

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP33-02415A000400380195-0
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 6
• Document Creation Date: December 15, 2016
• Document Release Date: December 8, 2003
• Sequence Number: 195
• Publication Date: April 26, 1957
• Content Type: MF

Approved For Release 2003/12/23 : CIA-RDP33-02415A000400380195-0
SECRET
SAPC 15135
Copy/ of 7
26 April 1957
MEMORANDUM FOR: Project Director
SUBJECT: Weight Reduction of the U-2
1. Per your request as to suggestions on how we may reduce the
weight of the U-2 in order to increase its altitude capability, a
preliminary study has been made. This study is primarily confined
to weight reduction of installed equipment and accessories associated
with the various design functions of the U-2. Other factors affecting
ways and means of reducing weight have also been considered.
2. Going on the assumption that the U-2 will be employed primarily
for visual photography using the A-2, B or C configuration, all equip-
ment or accessories have been considered. There follows a list of the
equipment and accessories with the weight saving which would result
through elimination, weight reduction or substitution.
a. Landing lights--These could be eliminated with the
accompanying adverse effect on the operational safety factors. Saving
of an estimated 10`pounds.
b. AC generator--This accessory is necessary to supply power
to the C camera, systems III and IV end the APQ-56. This could be
eliminated except on those aircraft designated for use of the C camera.
Saving of 39.7 pounds.
c. AN/ARC-3L. (UHF transmitter receiver)--This could either
be removed or substituted by a smaller and less reliable VHF system,
but is not recommended. Saving 34.2 pounds if substituted and 73
pounds if removed.
d. Drag chute system including parachute--This could be
eliminated as it has been proved to be unreliable and is not opera-
tionally required. Saving 30.4 pounds.
e. Destructor--Elimination of this unit would save 10 pounds.
f. Drift site--Considered an absolute operational necessity
in order to ?.@).fficiently accomplish visual photography and navigation
with any degree of accuracy. If removed would save 40 pounds.
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g. Sextant--Considered operationally desirable and con-
tributes considerably to navigational accuracy. Elimination would
save 15 pounds.
h. Tracker camera--Considered valuable for ready confir-
mation of track flown for plotting of assumed coverage. Provides
a complete photographic record of the flight and has limited target
photographic value. If eliminated would save 55 pounds.
i. The primary cameras (A-2, B, C)--Weight reduction
(through design changes ) should be investigated.
J, System I--Provides electronic intelligence, but does
not contribute directly to visual photography. Could be eliminated
for a saving of 17 pounds.
k. System III--Provides more complete electronic intelli-
gence not contributing directly to visual photographic mission.
Could be eliminated for a saving of an estimated 35 pounds.
1. System IV--Replaces primary photographic capability.
Weight of permanently installed brackets, cable, etc., unknown.
in. I -All permanently installed brackets,
cabling, etc., could be removed. Weight saving unknown.
n. Auto pilot--This is considered to be an absolute opera-
tional necessity. Removal, however, would save 99.5 pounds.
o. II-Any brackets, wiring, etc., peculiar to this
installation could be eliminated. Weight saving unknown.
p. RADAN--Being an auxiliary to the APQ-56, the same comments
apply as to the
0
q. Clocks--The aircraft is equipped with two clocks--one
normal 8-day time clock and an elapsed time clock. One of these
could be eliminated, but this is not considered operationally desirable
since errors in time have a serious adverse effect on accurate navi-
gation. Elimination of one clock would save ':.$ pounds.
r. Remote pogo drop control:-Removal of all wiring and
cabling incident to the remote drop control of the pogo could be
eliminated. Current operations employs free fall of the pogos. If
it is desired to retain pogos for any reason, the ground inserted pins
can be left installed. Weight saving unknown.
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s. AN/ABN-6 radio compass--This is considered to be of
operational necessity and should not be removed. Removal, however,
would save 88.6 pounds.
t. Weather hatch--Any brackets, cabling, etc., could be
eliminated. Weight saving unknown.
u. Personal equipment--It is understood the original concept
was for personal equipment to be carried by the individual pilots and
was to consist of small articles carried in the clothing of the person.
However, individual selection of items to be included in survival kits
has risen weight-wise to as much as 40 pounds in some instances. If
possible, standardization with a view towards weight reduction and
elimination of some items could be carried out. Weight saving unknown.
v. Future pilot recruitment or retention should be directed
toward lighter weight men, all else being equal. Estimated average
saving 25 pounds.
w. Fuel--On less than maximum range missions reduction in
fuel load could be done in all cases with a saving of 6.5 pounds per
gallon.
x. Rainbow--This project will undoubtedly result in weight
addition as well as drag. The effects of these factors are unknown.
y. Removal of all extraneous brackets, cabling, etc.,
associated with other systems installations may save an estimated
maximum of 50 pounds.
z. Weight saving could be realized further by reducing the
film load. This is not recommended except under conditions where
excessive duplicate coverage would occur if a full film load were used.
For example: reducing the film load in the B camera by one half would
save 70 pounds.
aa. The increase in altitude which will be realized as a
result of increasing the allowable EGT to 6300 is not known.
3. A resume of the maximum weight reduction possible is listed
below. It is pointed out that this would leave only the basic capa-
bility of taking visual photography with either the A-2 or B cameras.
The accuracy of photography and navigation as well as safety would
be greatly impaired (in my opinion) to an unacceptable degree.
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a.
Landing lights (removal)
10.0 (estimated)
b.
AC generator--needed for C camera
(removal)
39.7
AN/ARC-31 UHF radio (elimination)
73.0
c.
d
Drag chute (removal)
30.4
.
e
Destructor (removal)
10.0 (estimated)
.
f
Drift site (removal)
40.0
.
Sextant (removal)
15.0
g.
h
Tracker camera (removal)
55.0
.
i
System I (removal)
17.0
.
J
System III (removal)
35.0 (estimated)
.
k.
Auto pilot (removal)
99.5
1
Clock (removal)
.
m
AN/ARN-6 radio compass (removal)
88.6
.
n
Miscellaneous brackets, cablin,
etc.
50.0 (estimated)
o
Maximum reduction possible
3M. 6
4. It is considered to be an absolute necessity that functions of
the following equipment be retained if an acceptable degree of accuracy,
safety and efficiency of operation is to be retained. Weight reduction
of these functions without reduction of the scope of capability or
reliability would, of course, be acceptable.
a. Landing lights
b. AC generator (when C camera is used)
c. AN/ARC-34 UFH radio
d. Drift site
e. Sextant
f. Auto pilot
g. Both clocks
h. AN/ARN-6 radio compass
5. There, therefore, remains the following equipment which can be
removed without affecting the operational capability or reliability.
a
AC generator (when not using C camera)
39.7
.
b
Drag chute
30.4
.
c
Destructor
10.0 (estimated)
.
d
System I
17.0
.
e
System III
35.0
.
f
Tracker camera
55.0
.
Miscellaneous brackets and cabling
50.0 (estimated)
g.
'Weight which can be feasibly removed
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6. Weight-wise, at altitude, one pound affects the cruise-climb
profile one foot. Removal of the items listed in paragraph 5 above
would, therefore, increase the operational altitude by 236 feet. It
can, therefore, be seen that removal of equipment will have an almost
negligable affect on the operational altitude.
7. Reduction of the fuel load is considered to be the only area
in which a substantial weight reduction is possible. The fuel used
in the U-2 weighs 6. ounds per gallon. It can, therefore, be seen
that reducing the fuel load by 300 gallons would increase the cruise-
climb profile 1950 feet. At the same time it must be remembered, the
operating time would be reduced from 10 hours to 8 hours and total
mission length from les. By close fuel computation on
less than maximum range miss ons an increase in the cruise profile can
be realized directly proportional to the amount of the fuel load
reduction.
a. The following represents a comparative range and altitude
profile which would result under the listed conditions:
Alt start Alt at
cruise zero fuel
Full fuel, equip
para 5 installed, 65000
A-2 oonf
Full fuel, equip
para removed 65,236
(236) A-2 conf
36 gal fuel re-
moved (236) equip 65,236
para 5 installed,
A-2 conf
Time flown Range
9:)40
8. It has been noted that throughout the profiles of actual missions,
occasional losses of altitude are experienced. This is caused primarily
by the loss of lift while making turns. It may be possible to reduce the
number and extent of turns through more careful and considerate initial
as well as detailed flight planning. These losses may also be reduced
by more careful attention to altitude by the pilots while making turns.
It may also be possible to reduce these altitude losses by decreasing
the airspeed schedule slightly while in a turn. This possibility is
being investigated.
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9. In summary, it is concluded that:
a. A maximum of 236.3 pounds of equipment can be removed
without affecting t1e accuracy or safety of operations.
b. Reduction of fuel load is the area wherein the greatest
weight reduction is possible.
c. Excessive personal survival equipment is being carried
in some instances.
d. Altitude loses occur as a result of turning.
10. It is recommended that:
a. The items listed in paragraph 5 above be removed when
not required for a particular mission.
b. On all missions of less than maximum range, the fuel load
in excess of that required be left off,
c. A survey of survival gear be undertaken with a view
towards elimination of unnecessary items.
d. More attention be given to initial and detailed flight
planning with a view towards reducing the number of turns required.
11. All weight figures quoted herein are drawn from Lockheed
publications except for those which are qualified as an estimate.
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CFQ:bm
1 - Addressee
2 - Dep Proj Dir
3 - Cont
4-LO
5-Ops subj
6 - Ops chron
7 - Admin chron
`SET, .
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