MONTHLY PROGRESS REPORT - ENGINEERING PROGRAM FOR THE DEVELOPMENT OF A LIGHTWEIGHT ANTI-TANK ROCKET

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78-03642A000800060019-7
• Release Decision: RIFPUB
• Original Classification: S
• Document Page Count: 33
• Document Creation Date: December 27, 2016
• Document Release Date: August 8, 2011
• Sequence Number: 19
• Publication Date: January 1, 1958
• Content Type: REPORT

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COPY No. I
HESSE-EASTERN
A DIVISION OF & 155 L 2 "
FLIGHTEX FABRICS INC.
CAMBRIDGE, MASS. 4rof/
REPORT NO. I -8-50G- I
MONTHLY PROGRESS REPORT
ENGINEERING PROGRAM FOR THE
DEVELOPMENT OF A LIGHTWEIGHT
ANTI-TANK ROCKET
CONTRACT NO. RD- 142
XI6VCRXXXRXII(X4MX1%XWIi J=
This document contains information affecting the
national defense of the United States within the
meaning of the Espionage Laws, Title 18, U. S. C.,
Sections 793 and 794. The transmission or the
revelation of its contents in any manner to an
unauthorized person is prohibited by law.
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nFi
Hesse-Eastern Progress Report #I-8-50G-I
H E S S E - EASTERN D I V I S 10 N
FLIGHTEX FABRICS, INC,
PROGRESS REPORT #5
ENGINEERING PROGRAM FOR THE DEVELOPMENT
OF A LIGHTWEIGHT ANTI-TANK ROCKET
CONTRACT NO. RD-142
~
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PREPARED BY
APPROVED 8
Paul V. C. Char Ies
Project Engineer General Manager
PREPARED BY
`"'~
Thomas P.
Project Engineer
SUBMITTED BY: HESSE-EASTERN DIVISION
FL I GHTEX FABRICS, INC.
CAMBRIDGE, MASSACHUSETTS
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WORK DONE DURING THE MONTH. OF JANUARY 1958
REPORTING PERIOD ii JANUARY TO 6 FEBRUARY 1958
SYSTEM EVA6UAT II O AM
A table showing all data obtained from tests of Evaluation Model
No. I was prepared and the project reviewed from the point of view of the
performance of Evaluation Model No. I. The last test with E. M. .Jo. I
components was conducted on 5 February; Nine rounds were dynamically
tested for penetration: Three fuze malfunctions occurred. Remedial action
was started to correct the malfunctioning condition. The dynamic penetra-
tion results are in line with the results obtained from the static penetra-
tion test. The improved version of the liner with a heavier wall was assem-
bled into 25 head bodies for static testing. Static tests were conducted
with the igniter assembly of the launcher. After overcoming some preliminary
difficulties, satisfactory initiation of the .22 cartridge was obtained.
Some redesign of the linkage from the trigger to the igniter assembly was
completed.
A meeting was held with representatives from your agency, and the
future course of action as regards the E. M. No. 2 was decided upon. The
problems encountered with the fuze assemblies were not included in this
discussion, since the malfunctions occurred the day after the conference.
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C FD-)
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MOTOR DEVELOPMENT PROGRAM
A table showing the data obtained from all flight tests to date
is enclosed. This shows that stability, velocity and accuracy of E. M.
No. I appear to be satisfactory. The test samples used were rather small.
However, the results are sufficiently consistent to warrant the above state-
ment. During January components for a 200 lot of E. M. No. 2 were being
manufactured. Some minor delays occurred in the delivery of components.
Two hundred igniter assemblies were also ordered. One half of this order
will have no provision to be used in conjunction with the launcher. The re-
mainder will be used for tests of the complete weapons system. Due to de-
lays in obtaining motor and other round components, testing of E. M. No. 2
will have to be postponed until the end of February or the beginning of
March. It, therefore, appears that March and April will be spent in inten-
sive flight testing of E. M. No. 2. It is expected that the manufacturing
delays encountered to date will be compensated by a speed-up of the test
program. The propellant was received from Radford Arsenal toward the end of
the reporting period. It was used for the first time on 31 January and
5 February. As far as can be determined from this test, the results compare
favorably with the machined propellant.
WARHEAD DEVELOPMENT PROGRAM
Twenty-five head bodies were matched with 25 liners at the Eastern
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Tool Company and soldered together. Note was taken of the run-out-between
the inside wall of the head bodies and the center line of the liner. As
mentioned in last month's report, the head bodies had been already manufac-
tured before it was possible to change the tolerances. The heads were re-
ceived toward the end of the reporting period. It is planned to measure the
volume of Comp B very carefully and by running a comparison with the weight
to find the density of the load. It is also planned to take Xrays of the
charges before conducting the static penetration test. Upon completion of
this preparatory work, the static test will be conducted as soon as possible.
Ogives and head bodies for E. M. No. 2 were being manufactured
during the month. Some sample ogives were received at the end of the report-
ing period.
DYNAMIC PENETRATION TEST.- 5.FEBRUARY-1958
Nine rounds were fired for dynamic penetration. One was tested
on 31 January and the remainder on 5 February. Due to the fact that three
fuze failures occurred, penetration results are available only on six rounds.
The test was conducted by firing the rocket against a steel target
at a zero angle of obliquity. The target consisted of two pieces of armor
plate having a thickness of 3" each with an air space of 1/4" in between.
Only one of the six rounds penetrated both pieces of armor plate.
The remaining rounds appear all to have penetrated the first plate. The na-
ture and bulk of the target did riot permit a measurement of the exact extent
of the penetration of each round.
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The results of this test confirm the test results obtained from
the static penetration test. The liners used were the first design having
a thinner wall than the new lot of liners which is presently being readied
for a test.
It is expected that better penetration results will be obtained
when the heavier wall liners and the improved methods of assembly (See
December Report) will be used. Since this was an "either-or"' test, no
Xrays of the charges were taken.
F DEVELOP ENT PROGRAM
INTROOUCT!QN
Parts for the new fuze model (shroud design) were detailed and
manufactured. No malfunctions showed up in the static tests with this de-
sign. Nine fuzes were used in conjunction with the dynamic penetration test
on 5 February. Three failed to function. The design used was C-8162 (double
ball design). An investigation into the cause for the malfunctions is In
progress. it was possible to recover one of the three fuzes in question.
A program to speed up the fuze development was formulated. initial steps
were taken to obscure the design. A photographic record of the fuze assembly
procedure was prepared.
STATIC TEST OF THE SNODES ION
Design No. 0-8242 (See photograph enclosed in appendix) was statically
fir' --J~
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tested by dropping the fuze on its tare from a height sufficient to set back
the triggering components (approximately 36"). This test was performed on
15 fuzes and repeated 50 times. No malfunctions occurred. Twenty sets of
components were ordered to conduct dynamic tests at the earliest possible
opportunity.
DYNAMIC TEST WITH THE DOUBLE BALL DESIGN
Nine fuzes were flight tested with HEAT heads on 31 January and
5 February. Three rounds failed to function. Due to the fact that HEAT
heads were used, the disassembly of these rounds presented a prc'tlem. it
was felt that, since the test on 5 February (when all the malfunctions oc-
curred) was a penetration test and the number of rounds insufficient for a
fuze functioning test, another functioning test would be run as soon as parts
for E. M. No. 2 become available. Only one of the rounds could be disassem-
bled without endangering personnel. The examination of this fuze showed that:
1. The rotor was in the unarmed position.
2. The triggering components had set back.
3. The firing pin had been released and had struck the rotor ap-
proximately 0.20-0.30" from the retaining hole.
EVALUATION OF RESULTS QF DYNAMIC TEST
In evaluating the problem encountered inasfar as this can be done
to date, we refer to the Progress Report of September, 1957, page 34,
Section B.
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The examination of the parts of the recovered fuze reveals a con-
dition similar to the one discussed in this paragraph, i.e., the triggering
components have gone.back and latched. However, the firing pin was released
to immediately (or in an extremely short increment of time) be driven into
the rotor by the firing spring. This condition could be caused by exces-
sive overtravel. The likelihood of this is, however, not very great, since
the effect of overtravel would be the same whether the set-back forces are
great or small. It must be remembered that this condition was not encountered
in static testing nor was it encountered in all the fuzes fired dynamically.
All the fuzes fired on 5 February were statically tested at least 3 times
before final assembly.
the possiL;Iity that some other condition than excessive over-
travel caused the malfunctions must then be faced. In trying to arrive at a
solution, the following has to be taken into consideration:
When the inertia element hits the base plate of the fuze upon set
back, its backward motion is arrested. The greater the set-back force the
greater will be the velocity and energy of the inertia element at this point
in time. if we assume that no deformation of any parts occurs, we find that
the reaction to the energy developed by the inertia element, and the trigger-
ing components contained therein will equal the energy with which it hits the
base plate. The triggering components will then be moved forward again but
not merely by the action of the firing spring but by this additional energy.
The inertia element can only go forward as far as the latching spring will
permit. However, the triggering sleeve is held on by the frictional
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force of the balls only. if the triggering components then have enough en-
ergy from the reaction here discussed, the possibility exists that the trig-
gering sleeve will be thrown off and the firing pin fired prematurely.
Another way in which premature release of the firing pin could be
brought about is through overtravel. However, If overtravel would cause
the malfunctions, it would have shown up during the static tests. The cause
for prematurely throwing off the triggering sleeve under conditions of ex-
cessive overtravel is the action of the firing spring which would be the same
during static and dynamic operation as long as the triggering components are
set back.
Immediately after the dynamic test more static testing was conduc-
ted. This time the fuzes were dropped from a greater height to come closer
to the acceleration encountered when the rocket is fired. Some malfunctions
occurred. preparations have been completed to take high speed camera pic-
tures of a transparent fuze setting back. A Lucite fuze body is being ma-
chined at the present time. The result of these tests will show the way to
overcome the present difficulties. It is very probable that the answer will
consist in putting a buffer behind either the inertia element or the whole
fuze. This will have the effect of absorbing the excess energy of the trig-
gering components and thus avoid the condition described above.
SAFETY PIN
Some components have been completed, and others are still in pro-
cess. As soon as a full set of components - consisting of housings with the
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appropriate groove, safety sleeves and safety pins - have been received,
static and dynamic testing of the safety concept will commence. Since the
round has to travel a distance of approximately 2" before the safety pin is
ejected, there exists a possibility that reliable fuze functioning will oc-
cur as soon as the safety pin is used in dynamic tests. The reason for this
is the fact that the steepest part of the acceleration curve is likely to be
encountered during the first I" or.2" of motion.
FUTURE PROGRAM
intensive static testing will be conducted to try to correlate
the failures encountered during the last period to the static testing pro-
gram, i.e., to obtan the same type of malfunction statically. Different
approaches to the problem will be tried out, and dynamic testing will com-
mence as soon as the static program has shown results.
The dynamic testing program will consist of tests of approximately
50 rounds. These will be used to eliminate the malfunctioning conditions
and to establish operation of the safety device. The next lot of test rounds
will be used to establish arming distance. If possible, heavy walled motor
bodies will be used in order to be able to use motors repeatedly. It is not
anticipated that the problems encountered so far will result in a dealy of
the fuze program.
ASSET 8L..Y M=DURE
A step-by-step photographic record of the fuze assembly procedure
is enclosed in the appendix.
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LAUNCHER DEVELOPMENT PROGRAM
Extensive laboratory tests were conducted during January to deter-
mine the over-all workability of the design and to bring the igniter and
trigger assembly to the point where a reliable design has been established.
One hundred tests were conducted to establish initiation of the
.22 blank cartridge. Some trouble was experienced at first in consistently
setting off the cartridge. it was found that the strength of the firing
spring had to be increased and the distance between the point of the firing
pin and the cartridge lengthened. The shape of the firing pin also had to
be modified.
Upon completion of the above modifications, the assembly worked
reliably. The restraining plunger stop was also redesigned. The tube sur-
rounding the triggering link has been extended rearward in order to protect
the parts from damage if the weapon should be dropped on its and. Modifica-
tions were also made to the trigger assembly in order to obtain more finger
room.
The discussion of the launcher during the conference on 4 February
produced the following decisions:
1. The trigger components will be redesigned still further to in-
crease room available for the trigger finger.
2. The trigger and safety handle will be designed with a plastic
covering over the trigger. This will result in a better feel of the weapon.
3. A three-round package will be considered for shipping purposes.
The handle assembly will be designed in such a way as to permit folding it
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sideways if necessary to reduce bulk.
4. We will assume that a light (perhaps wooden) plug will be used
as the forward stop when the weapon is packed.
5. Two safety pins will be incorporated. One will be located in
the safety handle, the other in the igniter assembly. Both pins will have
to be manually withdrawn before the weapon can be made operative.
FUTURE CROGRAM
1. Static Testing
Fuze tests to investigate and eliminate malfunctions if this
can be done statically.
Static. launcher tests to obtain proper sights, weight distri-
bution and ease of handling.
2. Design Tasks
Petform necessary changes as indicated by static and dynamic
testing.
Modify launcher details to make it possible to adopt inexpen-
sive methods of production (slide machines, moldings, punchings, etc.).
3. Dynamic Testing
Formulate program of intensive dynamic tests with 200 rounds to
check out E. M. No. 2. Basically, these tests will consist of the following:
(a) Stability and accuracy of E. M. No. 2 at both extremes
of temperature.
(b) Establishing reliable fuze operation.
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(c) Operation of safety pin.
(d) Arming distance.
(e) Graze functioning.
(f) Dynamic penetration.
4. Static Penetration Test with the New Liners
This will be conducted as soon as possible to check out head
design.
Evaluated vs. costs expended for the month Project Engineer
A+- 6(3 W
(14ftral Manager
Q`S
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APPEND!
Pictorial Record of fuze Lssembl~
Firing
Triggering Sleeve
Firing Pin Inertia Element
Photograph No. 42
Shcuing fuze housing and rotor assembly and
triggering components ready for assembly.
Note split sleeve and solid sleeve used for
assembling lock spring. Double ball design
Illustrated.
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Step I
Photograph No. 43
Inserting firing pin into inertia elenent
SC R
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`J',tfN;,01N'Is a.
Step 2
Photograph No. 44
Placing first of three retaining balls in position
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Step 3
Photograph No. 45
Holding bail already in position by means of
triggering sleeve and dropping next ball into
its hole. (Special slots are provided in the
shroud type design to facilitate assembly.)
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`J a `X ILA A .
Step 4
Photograph No. 46
Cropping triggering sleeve in place. Firing
pin is now held and a check should be made
that it has the proper amount of radial and
axial play.
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Step 5
Photograph No. 47
Using split sleeve to hold locking spring in place
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Step 6
Photograph No. 48
Second half of split sleeve is in position
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Step 7
Photograph No. 49
Inertia element is pushed into solid
sleeve. (This makes assembly into
the fuze housing easier. However,
this step may be omitted.)
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Stop 8
Photograph No. 50
Testing tiring pin
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Step 9
Photograph No. 51
inserting locking balls
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Step 10
Photograph No. 52
Inertia element firing pin and balls
being assembled into fuze housing.
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40 %a
Step II
Photograph No. 53
Pushing components into position. Note rotor
held in unarmed position against torque spring.
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Stop 12
Photograph No. 54
Assembling firing spring
('49 R 10- T
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,11( 1111
Step 13
Photograph No. 55
Base assembted. (Scotch tape is used for test
fuzes in order to be able to re-use parts. This-
will rater be substituted by crimp. Total assem-
bly time approximately 1 1/2 minutes per fuze.
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Phatogwaph No 6i 96
Fuze, Shroud Design
Drawing No. 0-4262-
-3)
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