TRANSMITTAL OF BALLOON INFORMATION

• Document Type: FOIA
• Collection: FOIA Collection
• Document Number (FOIA) /ESDN (CREST): 05415894
• Release Decision: RIPPUB
• Original Classification: U
• Document Page Count: 55
• Document Creation Date: December 28, 2022
• Document Release Date: February 15, 2017
• Case Number: F-2008-00941
• Publication Date: October 23, 1956

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263P TECHNICAL REPORT
Contract No. Nonr 875(00)
Annex IV
PREPARED FOR
THE OFFICE OF NAVAL RESEARCH
WASHINGTON,, D. C.
Prepared by: 3. C. Warren
Date: 30 September 1954
Report No. 1332
GENERAL MILLS,, INC.
Mechanical Division
ENGINEERING RESEARCH AND DEVELOPMENT
2003 E. Hennepin Ave.
Minneapolin 13, Minn.
of rages and is /amber
, and the following attach:
attrid.)
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Table of Contents
Page
SUMMARY 0000000 004000000000000 1
THE FEW DESIGN 00000000000000 1
_ .
A. Theory of the Natural Shape .-. 000000000 1
B. Selection of Proper Shape 000000000 2
III.TIHA1GABTESTooaaoasaoeoaaaaaaaa 3
le Objectives a 00000000000000060
2. Details of Testing a 00000000000000 3
3. Conclusions OOO 00.0000006000 14.
IV. TlfllGllTTESTaaaaeaaaaaaoaaaaoaa 11
le Objectives aaaaaeaaaaaaaaaaa4
2, Details of Testing 00000000000000 4
3. Conclusions a a 00000660000000000
APPENDIX
Time/Altitude Flight 1140
Trajectory Flight 1140
Gross Load vs. Altitude 263P
263P Drawings
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A personnel-carrying balloon with a volume of 80o0 cubic feet was
designed acoording to "Natural Shape" specifications. The design was
subjected to it hangar test on 17 February 1954 and was flown successfully
on 6 May 1954. This report will cover both experimente.
INTRODUCTION
A study of the sphere cone envelopes previously used resulted in the
finding of both horizontal and vertical stress concentrations in the
envelopes. In the "Natural Shape" balloon, circumferential-stresses are
eliminated. This concept motivated the redesign of personnel-carrying
balloons.
II. TEE NEW DESIGN
A. Theory of the Natural Shape
Since ballbons can be manufactured in any desired shape of closed
surface, it is clear that there is a most desired shape.
The principal consideration was stresses, the consequent strain and
the relationship between surface area and volnma contained. Stresses on
the surface area arise from (1) supporting the payload. and (2) gas pressure.
Those stresses Which hive a direction which is tangent to the surface and
which lie in a vertical plane are called meridional etresses. Tests have
shown that the meridional stresses are transferred from the tepee onto the
surface area uniformly.
Curvature in a stresses surface produces an inward force per unit
area. In a balloon, this force ia opposed by the difference in pressure
of gas inside and outside. If the inward force created by the meridional
stress is nullified everywhere by the gas pressure, the balloon is said to
have a "Natural Shape" and has zero circumferential tension.
These ideas Were conceived and reduced to practice by General
Mills, Inc. under Air Force sponsorship in 1951. Since then, much of the
work done on balloon design has been implemented by the University of
Minnesota Balloon Physics Group development of design nomographs from
use of the analog computer.
Each shape is characterized by a value of the "balloon fabric
parameter ZE ", esherea. is a dimensionless parameter that enters the
differential equations when the effect of finite fabric weight is taken
into account. The method of obtaining the shapes from the differential
equations is as follows:
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Nine different values ofZ were chaaen, and for each value the
differential eqUations were solved using the analog computer. These nine
shapes were then nermalized to give the shape coordinates T, Z, S for
balloons of unit gore length, where r and Z. give the profile of the
balloon and S is.the-distance of a point on the profile from the bottom
apex (measured up along the gore).
Since the .5. value is a ratio of the gross load to balloon weight,
the design becomes unique for each case. The following design is based
on a maximum load-and provides ample material for the envelope to assume
its natural shape.
B. Selection of Proper Shape
1. Each shape is characterized by a value of 2E , where 4E = 0
corresponds to the so-called "weightless natural shape", and larger
corresponding to the more 'oblate shape with heavier fabric weight. The
proper value of lE is uniquely determined by the following quantities.
V = Volume
L = Payload suspended from bottom apex.
W = Weight of fabric material per unit area.
/2,
= .028
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Using the University of Minnesota nomograph, curve #2 was selected
where = .05. This ajf value produces an envelope profile as shown in
Figure
Note: The nine different values of2 chosen were from zero to .40 in .05
increMenti; Since the opt/Mum value (.028) lie between curve for
0 and .05, .05 was selected. This means there is slightly more material
than needed for the envelope to assume its natural ahape with existing
loads.
2. Tailoring of the shape selection consisted Of the following.
� a. The gore layout was modified at stations #19 and. #29 so that
the profile would be symmetrical.
b. To provide for a, two point suspension at the bottom apex of
the balloon, tiro gores were tailored in the following manner, A line was
drawn from a point; corresponding to the desired width at the base of the
balloon, tangent to the gore. The resulting pattern provided the necessary
width at the balloon base and precluded the inclusion of separate wedge
gores. This device in no way affected the balloon diameter; and the minimum
addition had only a negligible effect on the volume of the balloon.
III. THE HANGAR TEST
1, Objectives
A balloon was fabricated on the basis of the foregoing specifications
and hangar-tested on 17 February 1954. Objectives of the test were as
follows:
a. Test the new design.
b. Determine effects of tailored gores to provide a two point
suspension.
c. Measure M1 plastic value capacity in a stable atmosphere.
d. Confirm the design volume.
2. Details of Testing
The following pictures show the balloon at 200 pounds of lift,
400 pounds of lift and when full at 517 pounds of lift.
At full inflation the syetem was lifted off the ground and thrown
down again several tithes sending shock waves up and down the fabric and
creating a whipping action.
Two tests of the value, one for one minute and the other for five
minutes, were made.
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3m Conclusions and Recanaendations
a. Generally, the new design proved very efficient, remaining un-
damaged under conditions more severe than those expected in flight.
b. It was decided to apply tapes to the wedge gore. This will
provide symmetry to load-bearing members on the balloon.
c. The M1 plastic value loss of lift in pounds per mlnu
consistent in both testing periods at 1k lbs./min,
d. The groes lead of 517 pounds, using helium as the lifting gas,
confirmed the design volume at 7900 cubic feet.
IV, THE MOT TEST
le Objectives
A manned balloon flight, GMI #lil-0,was made on 6 May 1954.
Objectives of the flight were as follows:
a. To flight-test the new 263P balloon.
b, To determine the flight capabilities of the 263P balloon.
c. To approve the 263? balloon for production.
d. To test the hydroneal generator.
2. Details of Testing
The inflation and launching was accomplished without any real
difficulty except that it was not possible to meet the time schedule
because of difficulties with the hydroneal generator. Surface winds
remained less than 5 MPH during most of the period, which simplified
handling the balloon over the three and one-half hour inflation period.
Take-off-was made at 0750 with the balloon rising at Wo F.P.M. to
its ceiling of 5000 feet. The flight was characterized by the instability
that was evidenced shortly after the balloon had reached its ceiling. The
pilot was kept buny riding .out the series of up and down drafts. A
total ballast of 29 poUnde was required to keep the system in a safe
altitude range. Total valving time for the four hour duration was only
1 1/4 minutes with the major portion of this being required for landing.
Indicative of the instability was the pilot's notation at 1130. "Small
brown leaf observed in air near balloon - altitude 3200 feet". The
first attempt at a landing resulted in the balloon being caught in a
downdraft over a wooded area. The balloon descended into tree tops
approximately 10 feet above the base of the balloon. Numerous tears in
the balloon were observed� The balloon then rose above the tree and
was valved to landing a few Minutes later.
A
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3 Conclusions and ReCoMmendations
a. The 263P balloon withstood a severe test flight and performed
excellently under existing conditions.
b. The 263P, as designed, is an acceptable item and ready for
production.
c. The hydroneal generator did not produce the 4000 CFH as indicated
but gave 3000 CFH, prolonging inflation over 1 1/2 hours.
d. That the hydroneal gas has a distinct ammonia odor was evidenced
by the pilot in flight and the crew members during inflation,
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APPENDIX
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263? DRAWINGS
A-15352 Inflation Tube and Duct
A-15351-B Duct Installation
A-15394-B Reefing Sleeve
A-15350-B DUct Attachment
A-16596-B Gore Pattern
A-16749-B Loaation of Wedge Gore Tapes
A-16621-0 Valve and Rip Panel Instaflation
A-17232-C 263P Assembly
A-30004-A RiP Panel Bolt
A-30005-A Rip Panel Nut
A-30006-A Rip Panel Gasket
A-11877-A Suepension Harness
A-30704-B Fibre Bushing installation
A-11876-B Attachment Pad
A-30708-B Balloon Base
A-120724i Seal thru Balloon Baas
A-16883-A One Way ClJp
A-16619-B Device for Securing Duct
A-16618-C Rip Device for Balloon Base
Valve Drawings
A-16525-A Valve Spring
A-16524-A Stud
A-16523-B V Seat Mtg. Disk
A-16553-B Valve Seat
A-16521-C Valve Plate
A-16554-C ValVe 8-Crean
A-16552-C Valve Gasket
A-16551-C Valve Ring
A-16555-C Valve Assembly
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