DEVELOPMENT OF HIGH WIND LAUNCHING SYSTEM

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78-03639A000500010004-5
• Release Decision: RIPPUB
• Original Classification: C
• Document Page Count: 26
• Document Creation Date: December 22, 2016
• Document Release Date: May 2, 2011
• Sequence Number: 4
• Publication Date: January 30, 1956
• Content Type: REPORT

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General Mills, Inc.
Mechanical Division
ENGINEERING RESEARCH & DEVELOPMENT
DEPARTMENT
2003 EAST HENNEPIN AVENUE
MINNEAPOLIS 13, MINN.
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N 'T IA.:
GENERAL MILLS, INC.
Mechanical,.Division
2003 East Hennepin Avenue
Minneapolis 13, Minnesota
Prepared for:
The Office of Naval Research
Department of the Navy
Washington 25, D. C.
Project 85028
Contract Now 875(00) Annex IV
* attach-
Submitted by:
H. E. FROEHLICH, Head
Balloon Systems Research Section
DEVELOPMENT OF HIGH WIND LAUNCHING SYSTEM
By,
P. E. YOST
:E.BARK
Engineering, Research & Development
Report No. 1502
Project: 85028
Date: 30 January 1956
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N T I A L
INTRODUCTION
The art of ballooning has progressed rapidly in the past few years. This
has been accomplished primarily by the use of newly developed construction
materials, modern manufacturing techniques, and new balloon designs.
Unfortunately, an inflated balloon is a very large vehicle and, con-
sequently, it is also a large obstruction for surface winds to strike.
The balloon industry has constantly been plagued by the problem of launch-
ing a unit under adverse weather conditions.
To meet the requirements of a scientific group who wished an all-weather
operation, it was decided to attempt to develop a high wind inflation and
launching system.
The balloon to be used in the final phase of this operation would have a
volume of 16,000 cubic feet and would be fully inflated (or nearly so) at the
time of launching.
This report will very briefly describe some of the problems which were en-
countered and the action taken to further improve the system.
Although much progress has been accomplished during these experiments, it
must be understood that a vast amount of knowledge remains to be obtained.
A feasible high wind launching technique for any type or size of balloon can
be developed by further investigation and experimentation.
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DEVEIAPMENT OF A HIGH WIND LAUNCHING SYSTEM
A preliminary study was conducted in order to ascertain the most feasible
method of conducting a satisfactory launching program with surface wind velo-
cities up to twenty miles per hour.
Two types of inflation methods seemed to be adaptable and it was decided
to conduct scale model inflations under actual high surface wind conditions.
The first type of inflation conducted was a method whereby the balloon
was encased in a shroud. This test was conducted on the afternoon of June 10,
1955, and the surface wind velocities were fifteen to twenty miles per hour.
In this experiment an old 25-foot diameter shelf balloon was used as the vehicle
and the encasing shroud was a standard flat 24-foot diameter parachute. Al-
though this operation was completely unsuccessful, it presented much informa-
tion which could be analysed for the development of a refined launching program
for future operations.
The second type of inflation used was a horizontal downwind method.
This test was conducted on the afternoon of June 11, 1955. Surface wind
velocities were again fifteen to twenty miles per hour and very suitable for
this type of experiment. The aft section of a helium trailer was used as a
platform to support the payload as far as possible from the ground. When in-
flation is begun, a tight bubble is maintained at all times; and, when inflation
is completed, the load would be released and would swing under the balloon.
This experiment, too, was unsuccessful; but enough information was gathered
to indicate that, with minor balloon structure changes, successful launchings
could probably be conducted from land or water in very high surface winds.
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On the afternoon of June 23, 1955, a surface wind of fifteen to twenty
miles per hour provided satisfactory conditions for the first simulated launch-
ing using a large balloon. A sixty-four foot diameter flat parachute was used
as a protective shroud over a 34-foot diameter natural shape, open appendix
balloon. The launching area was restricted to a rectangle having dimensions
of 22' x 25', thus simulating the actual size which would be used in the final
operation. A screw in type ground anchor was installed in each of the four
corners of the rectangular working area. These were used as attachment points
to connect and restrict the shroud during the inflation process.
The balloon vehicle and attached gondola were completely enclosed in a
box which could be opened and disassembled after inflating and prior to launch-
ing. Refer to attached photographs for method of diffuser attachment and
accordion type of balloon folding used to enable a box-type of inflation.
The inflation procedure progressed very satisfactorily, although it was
noted that some changes would be necessary to improve the system for future
use. After the balloon was completely inflated, it was decided to attempt a
launching in order to gain as much information as possible from the experiment.
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Two nylon safety lines, each 150 feet long, were attached to the balloon and
extended dowr.wind, where they were attached to ground anchors. These were
to allow the balloon to be launched from the shroud but to maintain it in a
captive form, so that it could then be destroyed. The dow,4-wind restraining
lines of the shroud were released, thus allowing the balloon to make an "Under
the Side" launch. The balloon became ailtorne in a satisfactory manner, but
the nylon safety lines yielded, thus allowing the balloon to make an unplanned
flight carrying 750 pounds of sand.
Enough information was gathered to establish a definite launching procedure
and to design a restraining shroud for the purpose of launching this type of
balloon. The new type of shroud would:
1. Be manufactured from Orlon material to minimize the generation of
a static electrical charge. (New York University Technical Report
No. 208.04 prepared for Signal Corps Engineering Laboratories.)
2. Be circular in shape.
3. Be manufactured in two sections, which could be released rapidly
by a chain-type of lacing for rapid launching.
A demonstration launching was planned and conducted on June 28, 1955-
Flight No. 1434. This day provided the most severe surface winds which we
bad encountered throughout this series of tests. The new type of Orlon shroud
was not yet completed, so it became necessary to resort to the 64-foot diameter
parachute as a launching shroud. The inflation process and launching were con-
ducted without mishap, and a routine manned balloon flight ensued.
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The next demonstration flight was conducted on June 30, 1955 - Flight
No. 1435 - and was accomplished with the aid of the manufactured launching
shroud. Although this experiment was very successful in all phases, it was
noted that many modifications in the system would be required in order to
simplify the inflation and launching process. A study of the experiment
and photographs acquired during the test suggested the following changes:
1. The accordion-type of balloon folding and box-type of inflation
would not be necessary.
2. A system employing four block and tackle assemblies at the anchor
points would ease the inflation process. The four controlling lines
to the blocks could be extended above the ground to a central loca-
tion, thus allowing one man to raise the shroud as inflation pro-
gressed.
3. One line attachment point on the upwind side of the shroud would
be beneficial for the purpose of forming a sail during the inflation.
This line would be attached to a ground anchor upwind of the shroud
and maintained taut until the balloon began to fill the shroud com-
pletely. The effect of this practice would be to maintain the
bubble in a vertical position during early stages of inflation and
to minimize the whipping of the shroud material by the wind.
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The system was prepared and used in the launching of balloon Flight
No. 1445 on the morning of July 21, 1955.
This is the only balloon which received any damage throughout the tests
by the shroud type of launching.
The balloon used was a 343P, which was equipped with an external duct
appendix.
The duct was situated at A 900 angle to the shroud opening during in-
flation; and, upon shroud release at launch time, the entire shroud section
passed over the duct and duct attachment, which caused a small fracture in the
balloon envelope. Future production balloons should use the new type of
integral duct, which would eliminate this possibility of balloon damage.
On the standard present type of balloon, the duct will not be damaged if it
is guided into a position directly under the lacing during inflation. Thus,
during the launching process, a minimum amount of shroud material will pass
over the duct.
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Other changes suggested by a study of the preceding experiment are:
1. To simplify the unlacing system, whereby the present chain stitch
type of lacing would be replaced by a system of interlocking attached
loops.
2. To add a swivel eyelet at the top of the balloon, which would be
held in place by the shroud release pin. This would keep the bal-
loon centered in the shroud during inflation.
3. To tailor the shroud into the shape required to fit a fully inflated,,
shroud-restrained balloon. The shape was derived by a method of
photographic abstraction using former flight shroud photographs as
models.
4. To attach a bungee cord between the four anchor points of the shroud
and a ground anchor at the base of each corner. These units would
provide an additional force which would accelerate the removal of the
shroud from the balloon at release time.
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Upon completion of the aforementioned modifications, a field trip to
Huron, South Dakota, was made to test the shroud's operating characteristics.
The first flight was conducted on October 18, 1955 (Flight 1527), which
was a 180 system experiment, using a partially inflated 33.8 balloons. Sur-
face winds were light, and no difficulties were encountered throughout the
inflation and launching processes. A great improvement was noted in the
operation of the interlocking loop type of shroud release, the balloon cap
centering attachment to the shroud, and in the tailored shape of the shroud
which was both adequate in size and shape.
The second flight was launched on October 19, 1955 (Flight 11+80), which
utilized a type 302P personnel-carrying balloon. The surface winds were very
light before and during the inflation process; but, due to the urgency of the
development program, it was decided to proceed, rather than to wait for high
wind velocities. Upon launching, it was noted that the balloon had slight
difficulty in freeing itself from the shroud. A post-launch discussion re-
vealed that a surface wind is beneficial for a shroud-type of balloon
launching, due to the added forces provided, which aid in the release action.
It was decided to modify the shroud in order to obtain a four-way releasing
action, which would separate the shroud into four separate fictions before
conducting the next flight.
This modification was incorporated and preparations were made to launch
Flight No. 1528 (a 180 system experiment) on October 25, 1955. When the
shroud release pin was tripped, the unlacing action began to function in all
four quadrants; but, due to the unequal forces prevailing at each release
seam, the unlacing action began to malfunction.
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The shroud again was constructed so as to release into two sections,
and very successful operations were conducted on October 26, 1955 (Flight
No. 1529) and October 27, 1955 (Flight No. 1530), both of which were 302P
personnel carrying balloons.
After reviewing all of the information gathered in the preceding ex-
periments, it was now possible to design and construct a shroud of refined
and finished proportions.
This was accomplished using a lightweight Orlon material, which was
cut into tailored gores and sewn together to form the two halves of the
completed shroud. Many other structural design improvements of lesser im-
portance were incorporated in the manufacture of the refined launching shroud.
In order to verify a satisfactory operation of the new shroud, two
flights (No. 1613 - 12/20/55 and No. 161+ - 12/21/55) were flown with ease
and the shroud development program was considered completed for this type
of operation.
An invitation to witness a series of demonstration launchings was ex-
tended to our sponsors of the program, and a series of four flights ensued.
Each of the four flights was launched by a three main crew. The
balloons were rendered airborne under adverse weather conditions without
difficulty, whereas an operation of this sort would have been impossible
prior to this development program
I wish to thank all of the people who participated so energetically
with great cooperation throughout this series of experiments. Although many
hazards existed and many unknown factors prevailed, no person objected at
any time.
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Our 3roup can be very proud to have developed a launching system so
satisfactorily in such a short period of time. This system will egable the
balloon industry as a whole to progress more rapidly and perhaps more suc-
cessfully.
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Experiment #1. Shroud type i aflation using 2-5-foot diameter ? balloon
and. a a'-foot diameter restraining shroud . June 10 e:, 19 _
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iflattd2 ko wit 'di iser Ott ;
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said a t ~h ent 1i be forced horizontal dt7e3 to e tc? r~e~,a r d.
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,prion s rOUd showing att:
Trail ung6e 'cord T
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#2 `Orio t shroM, t~ cent showi g;
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