TEST REPORT 592 SHOCK TESTS ON 1201117-0, 1201118-0 AND 1201119-0 PARACHUTE RELEASE

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP75B00285R000400070001-0
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 76
• Document Creation Date: December 15, 2016
• Document Release Date: October 8, 2002
• Sequence Number: 1
• Publication Date: September 27, 1962
• Content Type: REPORT

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REPORT NO. TR-592
DATE 27 September 1962
Page 1 of 6
Mt REPORT 592
Shock Tests on
1201117-0, 1201118-0 and 1201119-0
Parachute Release
FROM
?
PACIFIC SCIENTIFIC COMPANY
Manufacturing Facility
On file USAF release
instructions apply.
DATE PREPARED 27-6
PREPARED BY/e1119- eet
Test Engineer
CHECKED BY
, ANAHEIM, CALIFORNIA
APPROVED BY .?filikkg 0 /
Ingineering Manage
WITNESSED BY
REVISIONS
AFOCR
REV.
CATE
MADE EY
PAGES AFFECTED
REMARKS
"II
II
,
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000400070001-0
TR-592
TESTING
PACIFIC SCIENTIFIC COMPANY
Md !I., fa ! ? fc)I-Pla
TABLE OF CONTENTS
ENCLOSURES
Photograph 1 - Shock Test Set-Up
Photograph 2 - Oscillogram of Shock Waveform
REPORT NO
PAGE 2 OF 6
Elat
4 - 6
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PACIFIC SCIENTIFIC COMPANY
cdoto.ffo,,/
ADMINISTRATIVE DATA
PURPOSE OF TEST
To determine if 100 G's shock would cause parachute release to fire when
altitude was maintained at 19,500 feet, and to see if the shock would affect
the normal calibration setting.
MANUFACTURER
PACIFIC SCIENTIFIC COMPANY, 6280 Chalet Drive, Bell Gardens, California.
FACTORY: 1346 S. State College Boulevard, Anaheim, California.
MANUFACTURER'S TYPE OR MODEL NO.
1201117-0, 1201118-0 and 1201119-0
DRAWING, SPECIFICATION, OR EXHIBIT
Pacific Scientific Company drawings 1201117-0, 1201118-0 and 1201119-0.
QUANTITY OF ITEMS TESTED
Three.
SECURITY CLASSIFICATION OF ITEMS
None.
DATE TEST COMPLETED
25 September 1962.
TEST CONDUCTED BY
R. F. Whitney, Test Engineer.
DISPOSITION OF SPECIMENS
The three test units were returned to the customer.
APPF9Y14,,FPriRefleff2.0P1,0311P.,;.PIA7FtPli7f5IPPMRPfP?4PPP790,0:179fff
' 11111,1
IlfI III II III
'Nov
PACIFIC SCIENTIFIC COMPANY
Mantitacjurmp Far,blv, 4 1 h M Califonrra
TESTING
One parachute release at a time was placed in the altitude chamber and
mounted on the shock table, Photograph 1.
The shock machine was calibrated by using a Columbia Research Accelerometer
Model 304, a Tektronix Oscilloscope Type 531, and a Coleman-Beattie camera
attachment. A typical record at 100 G's is shown in Photograph 2.
Test No. 1
P/N 1201119-0, Main Deploy, S/N 109
Calibration before test 15,000.
Armed and dropped at 19,500.
30 G No fire No slippage of trigger
50 G = No fire No slippage of trigger
75 G = No fire No slippage of trigger
100 G = No fire Slight slippage of trigger
Under static condition chamber altitude was lowered and unit fired at 14,900.
Unit was reloaded and test repeated at:
100 G = No fire No slippage of trigger
100 G at 18,000 No fire Slight slippage of trigger
100 G at 16,000 = Fire (Could have been trigger displacement or
gear train/aneroid)
Unit was reloaded and test repeated at:
6, '5
100 G at 16,000 = Fire
(Could have been trigger displacement or
gear train/aneroid)
Unit was reloaded and test repeated at:
100 G at 16,000 = Fire Aneroid had released
Calibration check following tests:
15,100
15,000
*15,800
15,100
15,000
15,000
15,000
15,100
15,800
15,100
*15,800 firings possibly due to wear on 1 or 2 teeth. Will be checked during
overhaul.
Approved For Release
403/93t1oqA7RDP75B00205,00p4opo7oopi-o,
PACIFIC SCIENTIFIC COMPANY
Man,facfc,ng Facdtty, Ar?aheim. Cal/lc/ma
Test No. 2
P/N 1201118-0, Drogue Release, S/N 111
Calibration before test 15,900 to 16,100.
Armed and dropped
30 G = No fire
50 G . No fire
75 G = No fire
100 G = No fire
at 19,500.
Altitude lowered in
Armed and dropped
30 G No fire
50 G No fire
75 G = No fire
100 G = No fire
Altitude
at
No slippage of trigger
No slippage of trigger
No slippage of trigger
Slight slippage of trigger
chamber - fired at 16,000 (static).
19,500 with cover plate up.
No slippage
No slippage
No slippage
No slippage
of
of
of
of
trigger
trigger
trigger
trigger
lowered in chamber - fired at 16,000 (static).
Armed and dropped
30 G
50 G
75 G
100 G
Altitude
No fire
No fire
No fire
No fire
at
19,500 with cover plate down.
No slippage of trigger
Slight slippage of trigger
Slight increase of slippage
Slight increase of slippage almost to the firing point
lowered in chamber - fired at 15,800 (static).
Armed and dropped at 100 G with cover plate down at:
18,000 No fire
Slight slippage of trigger
Altitude lowered in chamber - fired at 15,900 (static).
Armed and dropped at 100 G with cover plate down at:
17,000 No fire
Slippage of trigger almost to firing point
Altitude lowered in chamber - fired at 16,000 (static).
r9YP
d'HW
Pil'119111
!IN! II ;11 !!,,!??
PACIFIC SCIENTIFIC COMPANY
Mdmilacturrng FacoNy. Anarie,in. Cdftforma
Test No. 3
P/N 1201117-0, S/N 114
Calibration before test NF 16,200, F 17,000.
Armed and dropped
at
15,200 cover plate up at:
30 G
No fire
No slippage
50 G
=
No
fire
Uo slippage
75 G
No
fire
Slipped half way
100 G
=
No
fire
Slight increase in slippage
Calibration check
(static):
16,200 NF
16,400 NF
16,500 NF
16,600 F
CONCLUSIONS
Test No. 1 - 1201119-0, Main Deploy, S/N 109
100 G's in plane of a straight drogue deployment at 18,000 feet did not cause
inadvertent firing or damage unit that would cause unit to fail to fire at a
lower than programed altitude.
Test No. 2 - 1201118-0, Drogue Release, S/N 111
a. Before subjecting units to high G shock tests all units calibrated with at
least a 400' interval between drogue release and main deploy.
After subjecting the main deploy unit to 100 G's - 2 firings out of 10 were
out of tolerance by 400' on the high side. This unit will be dismantled
and inspected in an effort to establish cause of firings to go out of
tolerance after 100 G's of shock.
Test No. 3 - 1201117-0t S/N 114
a. The unit in question fired within tolerances.
b. 100 G's in the 3 critical planes at 19,500' did not cause inadvertent
- firings or cause unit to go out of tolerance.
Approved For e1ea5e 2OO/O3(,1
II liii II
:?91,4;713, ID,P75590,285,R0,00400079001- ,
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TR-592
Photograph 1
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100?
ME
MUM IMIUMMIN
ROI MENNEN
NM ME=
Tjpip.... 10 ms/cm
SHOCK PULSE
TR-592
Photograph 2
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13 February 1963
SUBJECT: Transmittal of Technical Memorandum Report
ASNP-TM-63-1
STAT TO:
STAT
Enclosed is a cover letter and a copy of ASD Technical Memor-
andum Report ASNP-TM-63-1 concerning Lab tests of the paratimers.'
Please note the Lab has furnished, copies of the report to Firewel
and Pacific Scientifio. I am sending two copies to at
LAC to speed distribution as you were TDY.
Mr. Shepardson does not consider the defioiencies serious
enough for disqualification, but good Maintenance and Inspeotion
Manuals and procedures will be required.
:ttoh
I
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13 Fsbrusr 1963
rsntta1 of Technical Keeorandum Report
A3ITNIX-63 -1
is a cower letter and a copy of ASD Technical Hamar-
AS1.P.4%-63-1 concerning Lab testa of the peratiraere,
e the Lab has furnished copies of the report to
t1
o Scientific. I am sanding two 000-ww to
distribution as you were TDI.
Kr. Shepardson does not consider the d.efioienoiea serious
enough for disqualification, but good Saintonance and Inspsotion
MuMMals and prooedures eill be required.
2 Jitch
a
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HEADQUARTERS
SLdJttLL atis.t_uns
AIR FORCE SYSTEMS COMMAND
UNITED STATES AIR FORCE
WRIGHT-PATTERSON AIR FORCE BASE, OHIO
Ljhepariscn/:;
sumo' 1i A chnic...1 1.1emorandura Report
Reddin.7)
1. Inclosed herewith L.re four copies of subject report, :-epan,tc-
copies of .zich have been sent to both the 2irewell the
Pacific Scientific Comrany s inaicated in -ppendix iistribtuticn
List.
2. It is the opinion of the undersi:nel tnt the deficiencies ',acted
1. e., out-of-calibration operoti.:n after vibr:tion, cut-of-tolerance
ti me delay at temperature extrozor,.: and excesive runtines durirw tuid-
ity cycling are not consilered te he suficently serious to render the
devices unsuitable for use for the follow-in- reasons:
a. Out-of-calibration operation after vibraticn. ....his is the
most serious of the deficiencies found end efforts should be continued
to isolate the cause and correct this -deficiency if at oil nos:A.ble.
Potentially this could lead to a chance in the sequentil orertien of
the parachute. For example, the main ccnopy could deploy before release
of the first store parachute. It is believed with a prcper tech-
nicsl order type of document an procedures ?incerporatin,7 periodic chl-
ibration checks, such a ieficienc:, should be liscovered in releoseF
inst2.le1 In rachutes.
L. Out-of-tolerance ti..71e delay at temperature extremes. If it is
assu:a:i that the low tomporture 11 cause time delYe to increase,
there is no adverse effect except for the very low altitude escape oper-
ation. In this instance, the added delay of as much as .2 seconds could
be si?7-mificant.
d. Excessive rustini durn noidity cycling. It is believed that
this 'eficiency should result in no operatichl penalties. .ith a prop-
erly written technicd1 order an:] 1=pectioa procedures, releaser shoull
be removed from service lone before there ?cul )e L111; c..77riLlticn in
perfcrincc.., of the relea.se.
?
1. 3:2:2dT.03C.:
Taief, Crew Equipment Jivision
Directorte of Cperstional
Support Enineering
1 .tch
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cys)
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Aeronautical Systems Division
Air 'Force Systems Command
United States kir Force
Wright-Patterson Air Force Base, Ohio
Technical Memorandum Directorate of Operational
ASNP-TM-63-1 Support Engineering
24 January 1963 Account: 921i,.-97.42
TEstING OF THE
PACIFIC SCIENTIFIC COMPANY's ALTITUDE
SENSITIVE ACTUATORS, NOS. 207, 209, 211, 217,
222 and 228
I. PURPOSE
To evaluate three types of altitude sensitive actuators for possible
use in an Air Force multi-stage parachute system.
II. FACTUAL DATA
.??
1. Test Items:
a. Six altitude sensitive actuators, two each of Type 1201117-0
(main deploy), 1201118-0 (Drogue release), and 120119-0 (Drogue
deploy), (respective Serial Nos. 207 anu 217, 209 and 222, 211
and 228), manufactured by the Pacific Scientific Company and
submitted by the Firewell-Corporation, Buffalo, New York, were
subjected to qualification testing in accordance with the
appropriate requirements as outlined in Item 2, section II of
this report.
b. The actuators were designed to exert a force in excess of 100
pounds after a-time delay 'of from 0.08 to 0.11-j seconds after
a4uation.-.Actuators S/N 207, 209 and 211 were precalibrated
to fire at any altitude under 15,000 feet,, under 16,500 feet,
and over 19,4000 feet, ',respectively. Actuators s/N 217, 222,
? and 228 were precalibrated to fire at any altitude under 15,000
? feet, under 15,600 feet, and over 16,600 feet, respectively.
R. Test Requirements: The actuators were tested in accordance with
requirements outlined in ApPendix "B". These requiremsnts were
deri'(Ped frointhe following Pacific Scientific Company data reports:
fa. Wimbers G'5,.656, and 657 dated -4 October 1961.
be Number,642:(ss amendediby conference of 19 September 1961).
3. Test Proced4re: A description of the testing appears in Appendix "C".
4.: 'test Results: The individual test results appear in Appendices
wD",threpugh:"10.,
A
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3 t ?
r
a
?
5. 'SUUMary of Test Results:. The test results are summarized in
Appendix ."K".
III. CONCLUSIONS
1. The original set of actuators did not meet all of the test require-.
ments (reference Appendix "Um).
2. The actuators, after modification by the manufacturer, Pacific
Scientific Company, passed the following tests:
a. HUMidi.ty
b. Sand and Dust
d. Acceleration
d. Shock
e. High Temperature
Aneroid Hysteresis
g?
Aneroid Accuracy
.h. Timei-A'ccuracy
3. The discrepancies listed in Appendix 8C8, which were not corrected
during subsequent testing, are not considered significant enough
to warrant a complete retest, unless full qualification is being
considered.
IV. RECOMPLNDATIONS
1. That the Drogue deploy actuator4 Type 1201119-0, be assigned a
service life of 100 escapement operations.
2. That the actuators not be considered a fully qualified item for
general personnel parachute usage.
Prepared by:
Publication Review
,IONalD C. LINLZACK
1LT, USAF
This report has been reviewed and is approved.
? ,Technical I?lemorandyan
;AENP-TM-63-1
WARREN . ski4.2-i.RDLON
Chi, Crew Equipment Division
Directorate of Operational Support
Engineering
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AIDPENDIX A
DILJTRIBUTION LIzT (=4)
Firewel Corporation (5)
3695 'Broadway Avenue
Buffalo, New York
Pacific Scientific Company (5)
10242 Placentia Avenue
Anaheim, California -
6511th Test Gp (FTLTGM) (2)
Naval Air Felty
El Centro Calif
ALI:QS (Re droducible)
A.t;NPLP-3 (12)
REPORT NOTICE
When Government drawines,,IspecifilatiOns, or other data are used for any purpose
other than in connection with a definitel-y related Government procurement operation,
the United .5tates Goternment hereincurs no,rusppnsibility nor any obligation
whatsoever; and the fact that the Government mayhave formulateU, furhisheU, or
411 any way supplied'the said drawinta, specifications, or other uutu, is not to
be regarded by implication or otherwise as in any manner licensinL. the holder or
any other persbil=-or corporation, or conveyiaL c,ny rights or permission to
manufacture, use, or sell any patented investionthat may in any way be related
thereto:
Technical Memorandum
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.#
,
APPMDIX B
TEST REqUIRDENTS
Note: The numbers in parenthesis refer to the pargraph numbers of Appendix NA"
? to -4ALC Exhibit WCLLX-1-23075, dated 26 November 1937, titled "Automatic
_garachute Ripcord Release".
1.0 (1.0) PURPOSE
To outline the test procedure.
2.0 (4.0) TEST PROCEDURE
The tests shall be conducted as follows:
3.0 (4.1) ELAMINATION OF PRODUCT
All actuators shall be inspected to etermine comeliance with the,
referenced specification and applicable drawing.
3.1 (4.'A ANEROID CYCI,INC
The actuator shall be subjected to an aneroid accuracy tet which
ahall be conducted prior to the start of the cycling test. With the arminL
pin inserted, the release shall be subjected to continuously varying altitude
cycles at room temperature, from sea level to 35,0,4 feet and return to sea
level. Upon completion of 1,000'cycle, and aneroid accuracy check shall
again be made. The accuracy shall be within plus or minus 500 ft. of the units
calibrated altitude.
3.2 (4.4) OVIRPEESURE
The actuator shall be subject et.ft to an absOlute pressure of 50
inches fig for a period of one hour. For a period of nOt les e than six hours
following this overpressure, the actuator shall not beubjected to any
operation other than atmoeeheric pressure. An accur4 test shall then be
made on the actuator and the accuracy shall be within i)lus or minus 500 ft.
of the units calibrated altitude..
3.3 (4.6) POWER ACTUATION AND EIFE TEST
The the actuators used in test 4.5 shall be loaded and operated
50 times with ft resisting fooce of 30 pun. The actuators shall then be
mounted on a.test fixture with the cable end down and a 100-pound weight
attached-to the terminal swain. The actuator shall lift the 100-pound
wieght two (2) inches each time. These tests will be conducted at room
temperature.
,
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15 hodi-161.' 1-While:at?this tempei-avture, the actuator shall be subjected to
,a timer accuracy, an aneroid accuracy, and, a pull test simultaneously. The
anerofd accuracy shall not exceed plus or minus 1000 feet.
5.3 (4.8.3) VITIATION
The actuator, cocked and with the arming pin inserted, shall
be subjected to linear vertical vibration for a period of 30 minutes in
each of three mutually perpendicular planes on a suitable vibration stand.
When mounted in the horizontal plane, the actuator shall be mounted upside
.down. In one of the positions, the actuator shall be so mounted that the
paw). forthe reel actuator shall have the additional force of gravity
tending to trip out this pawl. During. this period of vibration, the fre-
quency shall be varied continuously from 10 to 55 cps with a double ampli-
tude (total excursion) of 0.030 inch. The actuator shall not operate the
ripcord power cable during the period of vibration. The actuator shall
then be placed in an altitude chamber and subjected to a pressure corres-
ponding to plus or minus 1000 feet as applicable. The actuator- shall be
vibrated for at lease 30 minutes in each plane. Upon completion of the
vibration in each plane, the arming. pin shall be pulled and the altitude
brought up or down as applicable to ascertain the altitude at which the
actuator o-wrates; After the vibration teets, the actuator shall undergo
the tests-specified in paragraphs 4.2 and 4.3, notine particularly whether
the timer runs down without operating the -ripcord. No looseness in the
mechanism nor damage to any pat of theactuator shall result from this
test.
5.4 (4.8.0 at.Q0K
The actuator shall be mounted on sufficient M8.58 and dropped
from 'such a height that when decelbrated by resiliant impact a deceleration
of 3 g shall be obtained. The actuator cocked and with the arming pin
inse :tad Lhall be teste0 with the axis mounted in three different planes.
The actuator shall not pull the power cable during these tests. The
actuator shall be mounted in a horizontal plane with.a mountine side of the
timer down on a stock testing machine in an altitude chamber. .iet an altitude
of 1,000 feet above the elevation at which the actuetor should theoretically
' trip, the arming pin shall be removed. i.le still at this altitude, the
itctuator shall be subjected to a 30 g shock and shall not trip the power
cable. The test shall be repeated with the timer turned over 130.? for a ?
30.g shock under the same'conditions. The actuator shall then be subjected
A
to shock of 30 g in each of two additional planes at right angles to the
first,plane and at right angles-to each other. The device shall be
shocked -under the same con4tionsin two different positions reversed to
each other for each plane or a totalpf six different positions in,all.
A eecheniem eonforming.to Specification 3.N--4L4 may be used for conducting
these tests, except that the'calibrated-spring shall have a constant (X)
' Of 1,590 +lop pounds per inch in lieu of a sprieg rate of 5,000-51500
pou44s-per inch. After the shock test, the aetuator shall undergo the
rtee,fs specified in paragraphs 4.2 and 4.3. No looseness in the mechanism
nor damage?to any part of the actuator shall result from this teat.
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5.5 (4.8.14.1) SH0C4 LIFE, inTi
One type 1201117-0 actuator shall be mounted on sufficient
ss and dropped f,rom such a height that when decelerated by resilient
simpact a deceleration of 30 g's shall be obtained. The actuator uncocked
(but with the arming pin in.and.the selector arm in the "A' position)
shall be mounted in a ?'ne-rizontal plane with the cover up on a shock maehine
in an altitude chamber. The chamber shall be raised to an altitude of
20,000 feet and then lowered to 1000 feet below the actuators set firing
altitude and after removing the arming pin shall be subjected to a 30 g
shock and shall not trip the triggering mechanism. The actuator shall
then be mounted in a fixture capable of inserting and removing the arming
pin'by remote. control. The mounted actuator shall then be placee in an
altitude chamber, uncocked, with the selector arm in the "a" position and
'With the pin inserted. The chamber altitude shall then be raised to 20,000
feet at which time the arming pin shall be removes and the escapement .
mechanism alloWed to run. ,The chamber altitude shall then be lowered to
15,000 feet and the arming pin shall be inserted. The insertion and
subsequent removal of the ermine pin shall be considered one cycle. Twenty-
five cycles shall be made following each shock test until the actuator
prematurely actuates when subjected to the 30 g shock load. The actuator
shall successfully complete 200 cycles and accempanying shock tests before
failure occurs.'
5,6 (14.3.5) ACCaimliaTION
The actuator shall be mounted on the apparatus (centrifuee)
and the apparatus shall be operated at a speed that will produce 30 g.
The actuator 'shall be mounted first in a position parallel to the esdapoment
assembly (usually horizontal) on the center of the turntable which is
secured to the mounting platformeof the centrifuee. 'The applied acceleration
of 30 g shall be attained, stabilized,snd maintained for a period of not
less than one minute for each successive position. at the end of the one
minute period, .the arming pin shall be pulled. The actuator shall operete
under these 'conditions and the apparatus (centrifuge) slowed. The
actuator shall then be' checked and reset for the next test. The release
shall be subjected to tests where the release is mounted in positions that
will allow a 30 g force to be applied in the plus or minus direction along
the x, y and z axes and the actuator set in six different positions for
these axes. The actuator shall operate satisfactorily on all tests.
5.7 (4,8.6) SAND AND DUMT
The Actuator mounted in a parachute pack, or equivalent, shall
be subjected to the sand and dust tests in accordance with Procedure I of
Specification NIL-E-5272. The actuator shall then be subjected to the tests
specified in paragraphs 4.2 and 4.3. There shall be no evidence of sand or
dust within the actuator.
(
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5.8 (48.7) BUVUDITt
The actuator mounted in a parachute pack, or reasonable
engineeringyfacsimilie, shall be subjected to-humidity tests in accordanCe
.with Procedure I of apecification MaL-E-5272, for five cycles. At the
completion of the test, the releas4 shall be inspected for collection of
m'aiate-in.the in'Oertpr of the case, corrosion of metal parts, or other
damage. At the completjon of thelifth cycle, the actuator shall unde4Eo
the tests specified in paraEraphs 4. and 4.3.
8
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APPt;NDIX
PROCEDUaL
1. The testing was carried ,out' in six phases, as follows:
- _a.. Two actuators, one each of Type 1201117 (S/N 207) and 1201118
(si/N 209). wereatestedin accordance with paragraphs 5.3, 5.4 and 5.6
fT the requirements outlined in Appendix "Bm.
? b. Following the above testing, actuator S/N 207 was tested in
accordance with paraaraphs 5.7 and 5.8 of the requirements outlined in
Appendix "B".
c. Limultaneously withathe above testing, actuator a/N 211 (Type 1201119)
was tested in accordance with paragraph 4.3 of the requireeients outlined in
Appendix "B".
d. Actuator S/N 209 was concurrently tested with the above in accordance
with paragraphs 4.1, 4., 4.3, 3.1, 3.2 and 3.2 of the requirements outlined
in Appendix "B".
e. Actuator s/N 207aias resubmitted following investigation and
modification by the Pacific Scientific Company and was again tested in
accordance with paragraph 5.8 of the reauirements outlined in Appendix
liM
-fa' Three new actuators, one of each type (6/N 217, 422 and 228) were
submitted following the failure ot the original units to pass the vibration
requirement and were tested in ac6ordence with paraEraphs 5.3 and 3.5 of
the reqairements outlined in Appendix "B".
2. The followina discrepancies ware noted during the tests:
a. The test sample Serial No. 207 would not operate after being subjected
to the humidity test (reference Appendix "B", paragraph 3.8). Exteneive rust
was visible on several parts, ane this is believed to have been the cause of
failure. The actuator was returned to the Pacific Scientific Company for.
evaluation and modification. This was accomplished and the unit was returned
to the Aeronautical Systems Division for a rerun of the humidity test. The
device marginally passed the humidity test the second time as it as firing
from 300 to 500. feet above the allowable altitude limit. -
b. The Belleville washers and their guide shafts had to be replaced
prior to beginning the teetina as the guide tubes furnished were reporte ly
not hardened and caused loading difficulties.
C. Pacific Scientific Company Actuator serial No. 209 was adversely
affected by the vibraion test. The actuator would pot fire consistently
within the assaigned altitude limits of 16,500 feet 2500 feet. There were
. four firlmes recorded 'Outside of he assigned range. The actuator fired
twite following the vibration test at 17,400 feet. Testing was continued
? and eleven-firinas late r; during the overpressure test, the actuator fired
5
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
at 17,500 feet. The unit was retested five additional times for aneroid
accuracy with the following results: 16,500, 17,600, 16.400, 16,600, and .
16,600 feet.
d. The leak indicutors on two of the three units failed to indicate
a within huts. Actuator aerial No. 211, after the vibration test, would
remain at the sea level indication until the altitude chamber passed
through 15 M and would indicate 6 - 8 Mat 35 M. The leak indicator of
7 actuator 6erial.No. 209 was first observed to malfunction during the
overpressurcest. The leak indicator was not observed following vibratiofi
and prior to overpressure due to chamber mounting difficulties; however,
it is considered probable that the failure occurred as a result of the
vibration test.
e. 'Actuator Serial 14o. 209 failed to pass the timer accuracy test '
following the high altitude, low temperature test. The timer required
0.29 seconds to actuate (requirement 0.08 to 0.13 seconds).
f. Actuator Serial Nos. 222 and i28 failed to pass the vibration
requirement's; however, Serial No. 222 did fire within the allowable tolerance
i of +400 feet, but the initial calibration was ineorreci an, therefore,
.several firings were out of the assigned altitude range. aealal No. 228
would: not fire within +400 feet of the initial calibration firing altitude.
10
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'Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
'
Report No. -
?
/APPENDIX D
SAND AND DUST
Techn ,p.,a1 Memorandum
ANP-M-63-1
- .
Page
12-13
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Approved For Release 2003/03/10 : CIA-RDP751300285R000400070001-0
SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1)
2. AST NR.
p PART , A FINAL
3. DATE
21 FEB 1962
1. TEST TITLE
Seed and Dust Test
of an Automatic IDENT. NB.
ASTEVS-62
la-R
4. TASK. PROJECT. OR SYSTEM NR.
5778
Paraeb.ute tuator
Ac
S. PRIORITY .8 AF IMPORTANCE CATEG. MR.
1 13E
6. OBJECTIVE AND SUMMARY
a" 112218911911. i The objeetios of this
actuator to sand and dust teat conditions.
started and completed 6 February 1962.
?
b. ISST RESULTS AND DISOU3S1914
test was to determine the resistance of the
Efforts to achieve this objective were
by the Piscine Scientific Company
The actuator was identified as part
Deploy.
placed inside of a parachute peek and the peak
conforming to Procedure I of Specif-
the release was removed from the pack and
test facility, ;weber 45-11. The
feet altitude, actuated at 19,000 feet and was
(Continue on separate pogo)
(1) The parachute
et
the
actuator was manufactured
Firemel Corporation.
and was sibmitted.by
nr. 1201117-0, serial
(2) The actuator
was sabjested to sand
ication MIL-L..5272.
(3) At the end
subjected to functional
nr. 207, Drouge
was *cocked and
dust teat
and es:editions
the test period
tests in an altitude
at 19,000
actuator, which was preset
satisfactory.
7. TEST HOURS COMPLETED
12
TEST HOURS SUCCESSFULLY
COMP I-ETED 12
TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
100%
8. REQUESTING AGENCY
ASAPSp3
9. TEST STARTING DATE
6 February 1962_
?
?
INSTRUMENTATION
INSTALLATION
TEST PLANNING
11. TEST FACILITY
4156
21. DISTRIBUTION
ABTA - 1 Cy
ASNPSP3 - 1 ay
ASITE3 . Brig,
File (1)
10. TECHNICAL DOCUMENTARY REPORT
LF- YES ikii NO REP ORT NR.
(If Known)
TO BE ISSUED
12. TEST LOCATION(S)
Bldg. 45
13., FLIGHT TEST PILOT
N/A
ORGN SYMBOL
EXTENSION
14. DIRECTORATE TEST ENGINEER
iessiel P. Ormstela
ORGN SYMBOL
ASTI=
EXTENSION
25290
IS. INSTRUMENTATION ENGINEER
N/A
ORGN SYMBOL
EXTENSION
22. ATTACHMENTS
Ei APPENDICES
El TABLES
FIGURES
IS. PROGRAM MANAGER
R. O. iinebeek
ORGN SYMBOL
ASNP3p9
EXTENSION
22113
2/LA.
17. PREPARED BY
Nsmillill P. Orastela
TITLE
MIESallmrglat
ORGN SYMBOL
ASTIVri
EXTENSION
*290
18. DIRECTORATE CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
19 TECHNICAL DIRECTOR CONCURRENCE
earl X. Relehert
TITLE
Tesbnical Director
ORGN SYMBOL
AWE
EXTENSION
21177
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
AMNOV61
FORM 153
REPLACES ASO-0 FORM667 SECURITY CLASSIFICATION
WHICH IS OBSOLETE.
PAGE 1 OF pi?, PAGES
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
Test neport Nr.
ASTElki-62-1a-R
(4) The cover plate of the actuator was removed and the interior was visually
examined. No sand and dust had penetrated into the actuator.
c. GONCLUSIONs The actuator withstood the test conditions to which it was exposed.
d. NiCONMENDATIOISt It is recommended that the actuator be considered resistant to
sand and dust as represented by the above described test.
PREPARED BY: YaNDEL P. ORNSTEIN
Test Project Engineer
GONGLWRID IN: DWIGHT C. KENNARD. JR.
Chief, Environmental Division
Directorate of Engineering Test
Deputy Commander/Test and Support
APPROVED BYs
CARL E. REI HEAT
Technieal Direetor
Direetorate of Engineering Test
Deputy Oommandar/Test and Support
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
IPPENDIX E
HUMIDITY
Report No. Page
ASTEVL-62-1b-R 15-16
Technical. Memorandum
ASNP-TM-63-1
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1)
I. TEST TITLE
Automatic Parachute Actuator
.i,s7EVS-62
!DENT. FIR. lb-R
El PART rg FINAL
3 DATE S MAR 19-6
4. TASK, PSyNT. OR SYSTEM HR.
6. PRIORITY S AF IMPORTANCE CATEG. NR.
18E
6. OBJECTIVE AND SUMMARY
a. INTRoDuarlats The objective of this test was to determine the resistance of the
actuator to humidity test conditions conforming to Procedure I of Specification Nr.
MIL-E-3272. Efforts to achieve this objective were started 7 February 1962 and
completed 14 February 1962.
b. FAOTUAL DATA AND DISCUSSIONI
(1) The parachute actuator was manufactured by the Pacific Scientific Company
and submitted by the Firewel Corporation.
(2) The actuator was exposed to the prescribed test conditions for 120 hours in
accordance with Appendix K, Technioal Memorandum ASNMM-61-26.
(3) At the end of the test period the actuator was subjected to functional tests
in an altitude chamber, Facility Nr. 45-12, in the Space and Atmospheric Deterioration
Branch.
(4) The actuator, which was a drogue deploy type and preset to energize at
19,000 feet, failed to function while the altitude was raised from ground level to
20,000 feet. A second trial was conducted. The altitude was rained fraa ground
(Continuo on adopirrete pogo)
7. TEST HOURS COMPLETED
3.20
TEST HOURS SUCCESSFULLY
COMPLETED 120
TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
100%
EL REQUESTING AGENCY
ASAPSp3
9 TEST STARTING DATE
7 February 1962
NINSTRUMENTATION
INSTALLATION
TEST PLANNING
11. TEST FACILITY T 21. DISTRIBUTION
10. TECHNICAL DOCUMENTARY REPORT TO BE ISSUED
fl YES t] No REP ORT NR.
(If Known)
93. FLIGHT TEST PILOT
N/A
16-4
12. TEST LOCATIONIS)
Bldg. 145
ORGN SYMBOL
EXTENSION
14. DIRECTORATE TEST ENGINEER
Mendel P. Ornstein
ORGN SYMBOL
ASTEVS
EXTENSION
25290
IS. INSTRUMENTATION ENGINEER
N/A
ORGN SYMBOL
EXTENSION
16. PROGRAM MANAGER
2/Lt R. 0. Lineback
17. PREPARED BY
Mendel P. Ornstein
ORGN SYMBOL
ASNFSP3
EXTENSION
22113
ASNPSP3
ASTA
ASTMS
22. ATTACHMENTS
E APPENDICES
TABLES
ED FIGURES
TITLE
Metallurgist
ORGN SYMBOL
ASTEVS
EXTENSION
25290
16. DIRECTORATE CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
19. TECHNICAL DIRECTOR CONCURRENCE
Carl E. Reichert
TITLE
Technical Director
ORGN SYMBOL
ASTE
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
21177
EXTENSION
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FORM 153
SECURITY CLASSIFICATION
REPLACES ASD-0 F0RM667
WHICH IS OBSOLETE.
PAGE 1 OF 2 PAGES
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
Teat Report fir.
ASTEV3-62-1b.R
level to 35,000 feet. The actuator failed to energise.
(5) The cover of the actuator was removed and the interior was visually examined.
Rust was observed on the release pin* the latch* a gear* and a eliding oomponent. The
failure of the test item to function was attributed to the rust.
e. waLuanits The parachute actuator did not withstand the test conditions to whieh
it was exposed.
d. ffiE0OM4ENDATIONS1 It is recommended thats
(1) The actuator be considered nonresistant to humidity as represented by this
test.
(2) The components that rusted be fabricated of rust resistant materials.
P LizT
PREPARED an MINDIL P. ?Bonin
Test Project Engineer
Is IORT O. KENNARD, 2R.
n
1 ?
hist. Environmental Division
0Direetorate of Engineering Test
Deputy Oommander/Test and Support
APPROVED Ws
ae2.(,,g
001. X. BEIM=
Teehnisal Director
Directorate of Engineering Test
Deputy Commander/Test and Support
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Appromed For Release 2003/03/10 : CIA-RDP751300285R000400070001-0
APPENDIX F
TIMER.4KbANSROID ACCURACY, ANEROID CYIOLING, ANEROID HYSTE:-..a;:..,
HIGH ALTITUDEALOV TEMPER'ATUrZe, _HIGH `NMPLiiii.TUAE, AND OVERPRESURE
? ?
Re port No. ?age
LiTEVS -62-2 -B-7 - 18-21
f
a.
Technical Memorandum 17.
ASNP-TM-63-1
1.1
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See AS1)12 80-1)
2. ATHL
PART 41 FINAL
!.___1:1.Et 2 MAR
I. TEST TITLE
!DENT. NR.
Automatic Parachute Actuators
ASVMS.42..2..
R
_19_62_
4. TASK, PROJECT, OR SYSTEM NR.
5778
S. PRIORITY & AF IMPORTANCE CATEG. NR.
18E
6. OBJECTIVE AND SUMMARY
a. ismoDucnoph
when subjected to
b. FACTUAL DATA,
To obtain operational
various test conditions.
were manufactured
by the Firewel Corporation.
release, part
part nr. 1201119-0,
ripcord of a parachute
data on two automatic parachute actuators
by the Pacific Scientific Company and sub-
Two models were stibmitted, one
nr. 1201118.0, serial in'. 209, the other desig-
serial ar. 211. The actuators are
after a preset time delay provided they
Allowable operational tolerances for both
temperature and ?1000 feet at low or high
conducted in aceordance with a suborder sub-
the testing procedures in s000rdance with
Additional operational criteria
project engineer. Eaoh testing procedure
appropriate heading and respective paragraph
(Continue an &swats pogo)
(1) The actuators
mitted for testing
designated as a drogue
nated as a main deploy,
designed to pull the
are within a preset
releases are .1.500
ambient temperatures
(2) Testing of
mitted by ASINPSP9.
Appendix X of Technical
for these tests ware
covered by this report
nuMber referenced
passaurs altitude.
feet at normal ambient
(-450F and 1600F).
the actuators was
This suborder outlined
Memorandum ASUP-1M.61-28.
furnished by the
will eontain the
in Appendix K.
7. TEST HOURS COMPLETED
120
TEST HOURS SUCCESSFULLY
COMPLETED N/A
TEST HOURS REMAINING
0
DATA REDUCTION 'X COMPLETE
100%
8. REQUESTING AGENCY
ASNESP..3
9. TEST STARTING DATE
.5 February 1962
NI
a
?
INSTRUMENTATION
INSTALLATION
TEST PLANNING
11. TEST FACILITY
21. DISTRIBUTION
ASNP3P.3 . 1 ay
ASTA - 1 Cy
ASTMS - (Orig,
File)
10. TECHNICAL DOCUMENTARY REPORT
fl YES ZINC REPORT NR.
(71 Known)
TO BE ISSUED
12. TEST LOCATION(S)
13. FLIGHT TEST PILOT
N/A
ORGN SYMBOL
EXTENSION
14. DIRECTORATE TEST ENGINEER
Anthony Givetz
ORGN SYMBOL
ASTEVS
EXTENSION
25290
15. INSTRUMENTATION ENGINEER
s/A
ORGN SYMBOL
EXTENSION
22. ATTACHMENTS
IEI
TA
ri
APPENDICES
TABLES
FIGURES
EXTENSION
25290
16. PROGRAM MANAGER
Lt. R. G. Linsbaok
ORGN SYMBOL
A8UP3P.3
TITLE
Engr. Technician
EXTENSION
22119
ORGN SYMBOL
ASTEVS
17. PREPARED BY
Anthony Civetz
18. DIRECTORATE CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
19. TECHNICAL DIRECTOR CONCURRENCE
Carl E. Reichert
TITLE
Technical Director
ORGN SYMBOL
ASTE
EXTENSION
21177
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
ASD FORM 153
NOV 61
REPLACES ASD-0 FORM 667 SECURITY CLASSIFICATION
WHICH IS OBSOLETE.
PAGE I OF /1 PAGES
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1)
2. AST NR.
El PART rja FINAL I
3. DATE
I 2 MAR 1962
I. TEST TITLE
!DENT. NR.
Automatic Parachute Actuators
Aark,V3e4/2.2.?
R
4. TASK. PROJECT. OR SYSTEM NR.
5778
S. PRIORITY & AF IMPORTANCE CATEG. NR.
3.0E
6. OBJECTIVE AND SUMMARY
a. ksTRoDuarIppi
when subjected to
b. FACTUAL DATAI
To Obtain
various
by the
ripcord
pmmasere
feet
(-45,4
the
This
furnished
in Appendix
operational
test conditions.
were manufactured
Firewel Corporation.
data on two automatic parachute actuators
by the Pacific Scientific Company and sub-
Two models were submitted, one
1201110-0, serial nr. 209, the other desig-
serial or. 211. The actuators are
after a preset time delay provided they
Allowable operational tolerances for both
temperature and ?1000 feet at low or high
conducted in accordance with a suborder snb-
the testing procedures in accordance with
-Th-61-28. Additional operational criteria
project engineer. Each testing procedure
appropriate heading and respective paragraph
(Continuo on separate page)
(1) The actuators
mitted for testing
designated as a drogue
nated as a main deploy.
designed to pull the
are within a preset
releases are .4600
ambient temperatures
(2) Testing of
mitted by A5NPSp3.
Appendix X of Teohnical
for these tests were
covered by this report
nuiber referenced
release, part or.
part or. 1201119-0,
of a parachute
altitude.
at normal ambient
and 16007).
actuators was
suborder outlined
lokommundum AP
by the
will contain the
K.
7. TEST HOURS COMPLETED
120
TEST HOURS SUCCESSFULLY
COMPLETED N/A
TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
100%
8. REQUESTING AGENCY
ASNIRSP..3
9. TEST STARTING DATE
5 lrobrucary 1962
IIII
011
11.
INSTRUMENTATION
INSTALLATION
TEST PLANNING
11. TEST FACILITY
21. DISTRIBUTION
A5UPSP..3 .. 1 Cy
ASTA - 1 Cy
ASTEVS - (Orig.
File)
10. TECHNICAL DOCUMENTARY REPORT
fl YES Kii NO REP ORT NR.
(11 Known
TO BE ISSUED
12. TEST LOCATION(S)
13. FLIGHT TEST PILOT
N/A
ORGN SYMBOL
EXTENSION
14. DIRECTORATE TEST ENGINEER
Anthony Givetz
ORGN SYMBOL
AsTEVS
EXTENSION
45290
15. INSTRUMENTATION ENGINEER
N/A
ORGN SYMBOL
EXTENSION
22. ATTACHMENTS
fr_] APPENDICES
E TABLES
n FIGURES
16. PROGRAM MANAGER
Lt. R. C. Limbach
ORGN SYMBOL
ASAIP8P-3
EXTENSION
22113
17. PREPARED BY
Anthony Civetz
TITLE ORGN SYMBOL
agr. Technician J ASTRVS
EXTENSION
25290
18. DIRECTORATE CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
19. TECHNICAL DIRECTOR CONCURRENCE
Carl E. Reichert
TITLE
Technical Direetor
ORGN SYMBOL
ASTI
EXTENSION
21177
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMEith..
EXTENSION
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FORM 153
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PAGES
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Teat Fisport Ni.
ASTEVS-62-2-R
e. TNT gasuLTs AuD_Dxscussiovg
(1) Operetiomal testing of the actuators was started on 5 February 1962 and
was sompleted on 9 Adman 1962. As requested by the project engineer both
astuaters were subjeoted to the timer accuracy and emerald aceurasy test phases.
*Ouster ar. 211 was Shea subjested to the aneroid 'waling test phase while actuator
air. 209 was subjected to aneroid hysteresis high altitude - low temperature, high
temperature. sad overpressere. Operational diserepeaeles noted during these testa
were as follows. The aneroid leakage indicators on both actuators were defeetive
resultimg in inaocurate altitude indiestioas at simulated altitude coaditious. The
timer neehanisa on astuator nr. 209 operated shove the operational requirements As
the low emblem* temperature. Aneroid operation on actuator nr. 209 did not satisfy
the requirements at the overpressure test phase.
(2) Open eompletiou of testing the estuaters were returned to the project
eagimeer. A description of all tests is presested as Appendix A Or this report.
d. italaggais It is emeluded that.
(1) With the eteeptioa at the steroid leakage indicator failure, satuator ax.
211 operated as required duriag She thew assuraey aneroid aseurasy amd ameroid
eyelift test phases.
(2) Astuater Jar. 209 operated as regaired during the timer secarasy. amereld
assureeye amertdd hysterAsis and hi temperature test phases but did not meet the
eReeetleeel weielkelesete of the high altitude - is, temperature aid overpressure
test phases. Failure of the emerald leakage imdisater was also evident OR this
seluater.
19. 1111111111:301 It is reosemsaded that both antematie perectute actuators be
emeigered useatistastary tor service use umder the somditioms imputed by this test.
PI/SPAM Us
Test jest Sagiarer
6tcy2,7e-t-
COMONIRMID IN. Maga O. EUINAMD,IL
Mist. iherireassulcal Division
DirosSeralie
of Sagineerlog Teat
Dersliw Comaandarrnet alneert
AMMO Db
CARLA. MOM?
Teshaisel Direstor
Directorate at Dagimeering Test
Depot,' Oommenieritest and Serpent
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
APPINOIX ?A*
1. Timor Acouracy (Para. 4.7.2). Four timer operational cheeks were made as sash
actuator. The time delay, after pulling the arming pin, varied between .10 eat .12
&monde for *soh aotuator. These timer operations were within the operational
requirements of between .08 and .13 /monde.
2, Aneroid Aseureey (Para. 4.7.3). Roth actuator was subjected to a simulated altitude
of 20,000 foot and the arising pin was pulled. The test shah, altitude was levered at
a rate of 200 foot per seeond and sash aneroid release point was *elide Actuator ar.
211 operated at 15,000 feet which was within the operatioaal requirenent at 15.0002500
feet. Aetuator ar. 209 operated at 16,300 feet whish was within the operational require.
sent of 16,5001500 feet.
3. Aneroid Cycling (Para. 44). Actuator ar. 211 was sebjested to soatinueuely varying
altitude cycles at room temperature (475401) treat station pressure to 35,000 test sad
return to statics pressure. This sonstituted one samplete eyele and 1000 seek eyelike
were imposed on the *Ouster. Upon sompletioa of the 1000 eyeless an aneroid assume,
shook was made as the motivator. With ea altitude deems rate of 200 feet per mooed
She *fluster operated at 35,300 feet, whisk was within the operational requirement of
15,0001500 toot* The aneroid looked* indiester as the astuator was *hooked during the
first of the 1000 voles and periedisally during the 1000 solos and the same nalfuestiek
was noted seek tins. MO movement of the indicator was noted until the test 'harbor was
at 15,000 feet and only tad tested 5,000 foot with the teat sheiber a$ 35,000 feet.
4. Aneroid Hysteresis (Para. 4.7.4). Aotuator sr. 209 was subjeeted to a simulated
altitude of 30,000 feet and the armies Pin was Pw111(6 The twat whwabwr altitude was
lowered at a rate at 200 feet per soeamd and the aneroid release point was 'toted Sob*
at 16,000 fest. This 'piratic's was within the operational requirement of *jaws* feet.
5. 010 Altitugeol,es Temperature (Para. 4.0.1). Actuator ar. 209 was subjeoted to
ambient temperature of 45?12007 and a simulated altitude of 50,000 foot for a pedal of
tear hours. Urea *septettes of this exposure the astuater was subjested to an embiene
temperature or .44?1207 et station proems for an additioaal period of tar hewn.
Upon sompletion it this exposure, and while still at ..6541;21,7, an aneroid emirs', end
timer asouraey shook was made on the actuator. The aneroid operated at 35,700 foot
vilita was within the operational requirement et 16,500t1000 feet. The time delay an
five timer operation were 450, .32, t52. .25 and .25 ectonde. These timer operations
were in mess of the operational requirement at between Ali and ,13 seeseds.
411. High Temperature (Para. Actuate? ar. 209 was subjested seas eabieat tonbori
stare of 1600/2111 ter a period at 15 hears. Urea seepletioa of this exposure, and
while still at that temperature, an aneroid assurer, and timer aeoureer Cheek was muds
as the aetuator. The aneroid operated at 17,000 foot whisk was within the opteetisaal
requirweest of 166000.000 feet. The tine delay on five timer oPerlisiassimen AI, 41,
.12, .11 and .09 mummies Those timer operations were within the ?Devotional maim.
mint of between .00 and .13 seconds.
3
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
Test Report Nr.
AsTRVS-62-2-R
7. Overpressure (Para. 4.4). Astuator are 209 was subjeeted to an absolute pressure
of 50 bushes lig for a period or one hour. Upon completion at this one hour overpressure
the aetuator was returned to atmospheric' pressure and subjected to this condition for a
period of 20 hours. Six aneroid aeouracy cheeks were then mode with the actuator
operating at 17.500 feet, 16,500 feet, 17,600 feet, 16,400 feet. 16,600 feet and 16,600
feet. Two of the six cheeks made were not within the aerating requirements of 16,500 ?
500 feet. Prior to six operational cheeks the aneroid leakage ind tooter on the actuator
was shocked. No movement of the indicator was noted until the test ohexiller altitude was
at 12.000 feet and only indicated 6.000 fest with the test chamber at 20.000 feet.
Another leakage indieator check was made after the six aneroid cheeks. No movement of
the indicator was noted until the test slumber altitude was at 10,000 feet and only
indisated 5,000 feet with the test ohimaber at 25.000 feet.
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?
Report No.
AL;Ti.,Vi -6 2 -3c -R
?
Technical Memorandum
4NP-TM-03-1
G
si.CCELLEHA TI Gil
o
22
23-27
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SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(S O* ASDR 80-1)
.
Wk
PART EZ FINAL
?
1. DATE
f 8 MAR 1962
I. TEST TITLE
AUTOMATIC PARACHUTE62-30-R
ACTUATOR WENT.
NR
4. TASK, PROJECT, OR SYSTEM NR.
5778
S. PRIORITY & AF IMPORTANCE CATEG. NR.
18E
6. OBJECTIVE AND SUMMARY
a. Introduction:
The purpose of this test project is to evaluate the operational response and the
post test offsets of sustained Igo (acceleration) on two automatic parachute
actuators.
b. Test Result. and Discumeices
(1) Zhe two devices submitted for testing are used in a multistage parachute
operation. The design of both is nearly identical and differ substantially only
in the altitude at which each unit is set to trigger.
(2) The actuator identified as the drogue deploy (serial Nr. 207) is adjusted
to function at 19,000 ft MO ft, (room temp). It will not trip at sea level.
(3) Tao actuator identified as the drogue release (serial Kr. 209) is adjusted
to function at 17,000 ft 1500 ft, (roam temp). This unit will trip at sea level
it the locking pin is removed and the safety laver is on 'release'.
(Continue osi separate pitaa)
7. TEST HOURS COMPLETED
16
TEST HOURS SUCCESSFULLY
COMPLETED 16
TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
100%
S. REQUESTING AGENCY
ABITSP3
9. TEST STARTING DATE
a Feb 62
?
?
_
INSTRUMENTATION
INSTALLATION
TEST PLANNING
II. TEST FACILITY
Centrifuge Ni. 69
21. DISTRIBUTION
ASTEVD (Original)
A3NPSP3 (vellum)
ASTA (1 CT)
10. TECHNICAL DOCUMENTARY
REPORT
HR.
TO BE ISSUED
12. TEST LOCATION(S)
Bldg 93
1.1 YES 0 NO IMPORT
Known
IS. FLIGHT TEST PILOT
ORGN SYMBOL
EXTENSION
IA, DIRECTORATE TEST ENGINEER
niehard C. Mciendry
ORGN SYMBOL
ASTEVD
EXTENSION
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IS. INSTRUMENTATION ENGINEER
ORGN SYMBOL
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22. ATTACHMENTS
1 E APPENDICES
n TABLES
1 Eli FIGURES
IS. PROGRAM MANAGER
2/Lb. N.C. Linabeek ABNPSP3
ORGN SYMBOL
22113
EXTENSION
17. PREPARED BY
Riehard C. Maiendry Test
TITLE
Project Eng!
TITLE
ORGN SYMBOL
TEVD
ORGN SYMBOL
EXTENSION
34245
EXTENSION
IS. DIRECTORATE CONCURRENCE 1
IS. TECHNICAL DIRECTOR CONCURRENCE
CAM A. IIIIICIMIT
TITLE
Technical Director
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211-71
EXTENSION
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TITLE
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NOV 61 "
SECURITY CLASSIFICATION
REPLACES ASD-0 FOR146417
WHICN 15 OBSOLETE.
AF-WP-B-DEC 62 30
4
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Test Report ASTEVD Nr. 62-3o-R
(4) For the acceleration tests, the specimens were mounted on a suitable
fixture and secured to the test platform of the instrument centrifuge. Some devia-
tions from the requirements stated in Paragraph 4.8.5 of the specification
(Technical Memorandum ASNP.44-61-28) were requested by the project engineer. The
operation of tripping under altitude conditions during acceleration wee waived for
both specimens.
(5) The test procedure pUretted in the case of the drogue deploy, consisted of
loading and leaking the specimen, then subjecting the unit to an acceleration of
30 g for one minute' followed by a test run in an altitude ohamber to determine the
firing altitude. This reutine was repeated for each of six mounting positions along
X, /0 and Z axes. Figure I, Appendix A indicates the tripping altitudes.
(6) In accordance with the changes required by the project engineer, the drogue
release was initially loaded, looked and maintained in this manner while being
subjected to the specified acceleration in both directions, along the X, Y, Z axes.
At the completion of all the aceeleration tests, the specimen was installed in an
altitude chamber and tested to determine the tripping altitude. This occurred at
16,000 feet. Figure 1, previously referenced, includes this figure.
(7) It should be noted that the principle purpose of applying sustained le to
an assembled mechanism is to seek out the unbalance at every fulcrum. Produoing
this unbalance in an automatic parachute actuating device may represent the differ-
ence between inadvertent firing or a critical mechanicel suspense", which in turn
may cause a malfunction under service conditions. The factor of safety indicated
in the proper application of sustained Igi was entirely voided in the test procedure
requested by the project engineer.
0. Conclusionst
As far as can be determined from the results of an extremely modified test
procedure, the specimens submitted for test were not appreciably affected by the
applied
d. Recommendp,ion,
It is recommended that any test program concerned with the operation of automatic
parachute actuating devices include, functional operation at the specified altitude
and sustained Ile applied, in the 4. and - direction of the X, Tend Z ales.
2
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Report ASTSID Ir. 62-30.11
/84:6"Act?
POPO= SYs RICKARD C.
catmint= nil
APPROIED
3
Test Project Inginarr
Offf C. XENSAND, Jr.
Chief, luviremmoutal Division
Directorate of Engineering INA
Deputy OommanderAlost and Support
CAXI, Z. MGM
Toohnioal Director
Direotorate of b?1D1 Tut
Deputy Commander Teat and Support
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Test Roper% anvil) Ir. 62-3o41
APPIIMIZ *10
non
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Yi
:VROCtEpRoGa
LifcrsPidy ! AXIS
Z.
A I MO Al -
X a. ittm" 10. ?
/ I MI00 yi ?
Y a. fad Y1-
?
z I /9,16-0 z. / ?
?
/6,20
Rd)
nificffaealii
NOTE ACTUATrofts
ITIMATIc A
-
inAVIOnalli
I MOM. ?
5-7 g
IP YAW
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4
APPI-21DIX H
LA-JOCK AND VII3PATION
Report No,
AS'rEVD-62-3a-R
Teeh.nical kemorandum 28
ANP-63-].
29-40
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?
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SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1)
-U-3a-
. NTrRir.
0 PART
3. DATE 2()
MAR ig-EZ
X-1 FINAL
I. TEST TITLE
WENT. HR.
AUTOMATIC PARACHUTE ACTUATORS
4. TASK, PROJECT, OR SYSTEM NR.
5778
IL PRIORITY & ,11,F IMPORTANCE CATEG. NR.
6.
Precedence 18R
C OBJECTIVE AND SUMMARY
a. Introductions
report is to evaluate
and altitude simultaneously
are contained
on 31 Jan 62.
Discussions
automatic parachute actuators under
and vibration and altitude simulta-
in ASNP-14-61 -28. TastPbegan on the
within a parachute system which releases the
feet or above. Primary deoign of this
of high altitude aircraft or apace
actuntor are contained in Table Nr. I,
62-651, Appendix B of this report shows
within this system which releases the main
has reached 16,500 feet. 3ignificant
in Table Wr. II, Apoendix A of this
B of this report shows this physical
procedure was
(Continuo on noporate page)
The purpose of this
conditions of shodk
neously. Specific requirements
15 Jan 62 and were completed
b. Test Results and
(1) Actuator S/N 207 is the device
deploy parachute automatically at 19,000
actuator is for use with man-carrying capsules
craft. Significant chatacteristics of this
Appendix A of this report. Photograph Nr.
this physical actuator.
(2) Actuator 0 209 is the device
parachute automatically when the altitude
characterietics of this actuator are contained
report. enotograph De. 02-554A, Appendix
actuator. The vibration-altitude evaluation
7. TEST-HOURS COMPLETED
160
TEST HOURS SUCCESSFULLY
COMPLETED
160
TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
1CCIA
3. REQUESTING AGENCY
ASNPSP-3
9. TEST STARTING DATE
15 January 1962
?
?
INSTRUMENTATION
INSTALLATION
TEST PLANNING Chamber
It. TEST FACILITYid...
and Ja :g-
21. DISTRIBUTION
ASTNVA (Original)
ASIIP3P3 (Venue)
ASTA (Copy)
10. TECHNICAL DOCUMENTARY REPORT
EA YES A NO REPORT NR.
(If Known)
TO BE ISSUED
12, TEST LOCATION(S)
IS. FLIGHT TEST PILOT
ORGN SYMBOL
EXTENSION
14. DIRECTORATE TEST ENGINEER
Howard R. Rime
ORGN SYMBOL
ASTRVD
EXTENSION
34245
15. INSTRUMENTATION ENGINEER
ORGN SYMBOL
EXTENSION
22. ATTACHMENTS
2-i APPENDICES
4] TABLES
rj FIGURES
IC PROGRAM MANAGER
Lt. R.C. Limbos&
ORGN SYMBOL
ASNPSP-3
EXTENSION
2-2113
17. PREPARED BY
HOWARD R. KlifUll
TITLE
Test Project Engr.
ORGN SYMBOL
ASTEVD
EXTENSION
34245
IS. DIRECTORATE CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
19. TECHNICAL DIRECTOR CONCURRENCE
CARL N. RUCKERT
TITLE
Technical Director
ORGN SYMBOL
ASTEVD
EXTENSION
21177
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
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NOV 61
REPLACES ASO-0 F0RM667 SECURITY CLASSIFICATION
WHICH IS OBSOLETE.
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Report Nr. ASTEVD 62-3.-R 62 and
62-3b-11
accomplished first. Bach actuator was mounted on the Calidyne Nbdel 44 shaker within
the Nold-Sold altitude chamber as shown in Photograph Nr. 62-554, Appendix *Bly of
this report. An MB Model 124 velocity type pickup and an MB /Modal Maa vibration meter
were used to measure the double amplitude of vibration. An electric motor was used
to change the control lever from the reset position to the armed position remotely
while the actuator was at a simulated altitude.
(3) qta 207 actuator was vibrated for a total of 3 hours as follows: (a)
longitudinally for 1/2 hour at room ambient pressure, cocked with the arming pin in
and the control lever in the reset position; (b) longitudinally for 1/2 hour at
a simulated 17,500 feet altitude with arming pin removed and the control lever set
in the armed position, (a) Vibration was stopped and the altitude brought up until
the actuator operated, (d) the altitude of operation was recorded, (e) the altitude
was returned to roam ambient.
(4) The actuator was reset and vibrated similerly along the lateral and vertical
axe*, in sequence, for one hour along each axis, and the altitude of operation was
also recorded in each case. The frequency of vibration use oontimouslyveried between
10 and 55 'voles per second with a double amplitude of 0.030 inch applied es required
by Technical Memorandum Nr. A31IP-T4,61.,28, Paragraph 4.8.3. 8/1 209 was vibrated for
a total of 3 1/2 hours with the following conditions differing from those applied to
8/N 207 (all room ambient altitude conditions being the sems)1 (a) the control
lever was set in the armed position remotely at 18,000+ Net simulated altitude
after the room altitude vibration, (b) the simulated altitude vibration was conducted
at 18,000+ teat (instead of 17,500 feet), (0) after vibration altitude was redwood
until the &Aunt*? operated, (1) an additional 1/2 hour of lateral vibration at 18,000
feet was applied to Ws 209 because this speetmen had operated at the end of the first
1/2 hour of lateral vibration at 18,000 feet, (e) there was no visable damage
inflicted on either specimen resulting from vibration. Neither spamilmatmalfunationed
during vibration except for the possibility of 4/11 209 operating out of tolerance
during lateral vibration during the first half hour at altitude. S/N 207 operated
at 19,100 feet after longitudinal vibration; at 19,500 feet after lateral vibratiomo
at 20,200 feet after vertical vibration. Mhen a recheck without additional vibration
wan made on SiN 207 fallowing its operation at 20,200 feet, it operated at 19,300
feet. The tolerance is 1500 feet from the set value of 19,000 feet. S/N 209 operated
at 16,400 feet after longitudinal vibration; at 16,400 feet after lateral vibration;
and at 17,400 feet after* vertical vibration. When a recheck without additional vibra-
tion was made an Of 209 following it. operation at 17,400 feet, it operated at
17,350 feet and wee witnessed by the project engineer. The tolerance is j500 feet free
the eet value of 16,500 feet, (4 the project 'veneer asserted that there has been
excessive variation in the altitude of operation of the actuators previously. It is
very possible that the very mild vibration requirements had no effect upon the achseteme.
Transportation vibration requirement's outlined in Specification M110-16.4970, Paragraph
4.6.3 are lunch nere severe and apply to such equipment being shipped far installatien.
(5) 'Or the shook-altitude evaluation, actuator S/N 207 was mounted on a shook
nachine (JAN-&44) within an altitude chamber as shown in Photograph Nr. 62.610.
Calculations for the shock value (30 g) are found in Table L. Ile Appendix "AP.
2
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Deport Nr. ASTEVD 62.3a-R and
62-3b-R
Remote control was used to raise and release the carriage of the shock machine.
The teat procedure was as follows
Actuator was reset
Arming pin was removed
Control lever it in the armed position
Member brought to 17,000 ft altitude
Shock applied to actuator
Increased altitude in chamber until actuator operated, record altitude
Repent entire procedure for each direction of the mutually perpendicular
axme.
Data end results are oontained in Table III, Appendix A. The actuator operated satis-
falkcily within the required altitude limits. There was no visible deluge.
0. Gonclusionss
Even though the actuator failed to operate consistently eithim tolerance after
vibration, the cause is not necessarily vibration since pre-Jvibration trials had not
been consistent according to the project engineer. The actuator operated satisfac-
torily within the requirements of AUP-71461-21 in relation to the required shock
inputs.
d. atecontendationia
It in suggested that the shot* and vibration requirements or specificetion
NIL-14970, 'Environmental Testing, Ground 3upport Equipment, General Specificetiona,
paragraph 4.6.3 and 4.12.3 be considered as an additional requirement for all
actuators. This is based upon the possibility of greater dynamic inputs (luring
transportation and handling phases.
1_?#,111'Sv
PREPARED En 44trtifilLINUOI
Test Project Engineer
CONGURRED /Ns DWIGHT C. KENNARD, Jr.
Chief, Environmental Division
Directorate of Engineering Test
Deputy Cemsnanclortfest and Support
3
gao2
APPROVED BY: CARL E. REICHER?
Technical Director
Directorate ofTait
Deputy CommendeM:rstrSupport
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Report NO. ASTRO 62.3a-aavd
62.5h.R
APPENDIX PA"
Table Nr. I
General Ghareeteristies of Speeimen
Manufacturers Paola* Scientific Caspian Los Amgeles,
Nomenclatures Drogue Deploy
Part Nrs 1201117.0
Serial Nrs 207
Weight' 1.65 lb
Operaticsts Set to operate at or above 19,000 feet altitude
Tolerance . 400 fee,
Gable Pulled . 2 inches
Dimensions'
Length . 9 5/6 inches
%am. 3 lushes
Height . 1 1/2 inches
Gable (extended) . 12 3/4 inches
2 Haunting Roles for 1/8 inch bolts, 5 inches on minters
4
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Report Nr. ASTEVD 62.3a-R and
6241s-R
APPENDIX NAN
Table Nr. /I
General Characteristics of Specimen
Manufacturers Pacific Scientific' Company, Los Angeles, Calif.
Nomenclatures Drops Release
Part Mrs 1201118.0
Serial Net .209
Weights 1.65 lb
Operations Set to operate at er below 16,500 feet altitude
Teleran** . 2500 feet
Gable pulled - 2 inches
Dimensions
5
Length - 9 5/0 indbes
Width - 3 inches
Haight - 1 ;A bushes
Cable extension (extended) . 12 3Y4 inches
2 Mounting Holes for 1/S inch belts, 5 inches en canters
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Rei,nrt Nr. 3TWD 62-3a-R and
62-3b-R
APPENDIX "A"
Table Nr. III
Results of shock and Altitude Test
Automatic Parachute Actuator, Serial Nr. 207
Shock 30 g
Direction of Shoat
Longitudinal, cable up
Longitudinalscable down
Lateral-cable below arming-pin socket
Lateral-Cable above arming pin socket
Vertical upright
? Vertical inverted
6
.5hook Altitude
17,200 feet
17,400
17,400
17,400
17,400
17,400
Actuating Altitude
19,300 feet
19,000
19,100
18,750
19,100
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Report Ni. A3TEVD 62-3a-a and
62-3b-11
APPENDI1 "A"
Table Nr. IV
Semple Calculations
JAN-S-44 Shock Machine
Spring Constant - 1990 Pounds per inch = K
Total Carriage weight including specimen - 15 pounda = W
Mock Requirei - 30gg
Drop Height H al(g)2 x 11/21
= 30 x 30 x 15/2 x 1990
H 43,500/3180=4 V4 indubs
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41 :,ort Nr. ;71:10 6..3a-.h and
623b-.R
APP3NDIX ?rp
Photographs Nra . 132-650 651
62.554 and 554A
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7tt4..Kqr
PAC LFIC SC IENTI FIC .A.T.rromk T1
flThOT L'Ai-tACHUTE
AS TKVIL-62.- `3E.
ASD
ASTDP
, JAN 62.
42-65o
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VAC I FIC SC IINTI FIG AUTOMATIC
ki..t-;TUAIOR
kihT01-re AS Tat) -62-18-R
ASD
ASTDP
31 JAN 62
NEG . NH. 62-651
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PACIFIC SC Tv4TIFIC AUTOMATIC
&LAW-JUTE
.4.1111.-; HT Ali TE1/11.-
ASD
ASTDP
JAN bb2-554
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ASD
ASTDP
JAN 62
2-554A
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Report No.
- 62-35-R
-
-
APPENDIX I
? ?
f
HUMIDITY .
Te qhnical Memorandum 41
AZ,Np -TM-63-1
2_411a,,
42-44
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SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1)
---177W1M7-
PART
4 FINAL
1962
ig
S. DATE
1 0 MAY
I. TEST TITLE
D
Au IENT. NR.
tomatic Parachute Actuators
ASTEVS-62-
3.5?N
4. TASK. PROJECT. OR SYSTEM HR.
5778
5. PRIORITY 6 AF IMPORTANCE CATEG. NR.
18N
6. OBJECTIVE AND SUMMARY
a. IOTRODUQTION, The purpose of this tent was to determine the resistance of two
automatic parachute actuators to humidity test conditions.
b. FACTOAL DATA)
(1) The actuators were manufactured by the Pacific Scientific) Company and sub-
mitted for testing by the Firewel Corporation. Two models were submitted, one desig-
nated as a drogue release, part az. 1201118-0, eerie' nr. 209, the other designated
as a drogue deploy, part az. 1201117-0, serial az. 207. The actuators are designed
to pull the ripcord of a parachute after a preset time delay provided they are within
the preset pressure altitude. Allowable operational tolerances for both releases are
1500 feet at normal cab tent temperature.
(2) Testing of the actuators was condueted in acocrdance with a suborder sub-
mitted by ASNPS15 dated 2 March 1962. This suborder outlined the humidity test con-
ditions to conform to Procedure I of Specification Nr. NIL -E-5272 for five (wales
followed by a visual inspection and an aneroid accuracy test.
c. TOT RESULTS OD D1.90118410N3e
(1) With both actuators peeked within
a parachute peek ne eltmallrA ixere
7. TEST HOURS COMPLETED
TEST HOURS SUCCESSFULLY
TEST HOURS REMAINING
DATA REDUCTION % COMPLETE
COMPI-ETED
122
100%
5. REQUESTING AGENCY
ASNEep,
9. TEST STARTING DATE
16 April 1962
on
p I
NI
INSTRUMENTATION
INSTALLATION
TEST PLANNING
11. TEST FACILITY
#4
21. DISTRIBUTION
AsiesP3
10. TECHNICAL DOCUMENTARY REPORT TO BE ISSUED
12. TEST LOCATION(S)
ASIA
fl YES PINOaldg.
Of Knovm)
45
ASTETS
IS. FLIGHT TEST PILOT
ORGN SYMBOL
EXTENSION
N/A
14. DIRECTORATE TEST ENGINEER
ORGN SYMBOL
EXTENSION
Anthony Civets
ASTEVS
25290
IS. INSTRUMENTATION ENGINEER
ORGN SYMBOL
EXTENSION
22. ATTACHMENTS
N/A
GE APPENDICES
16. PROGRAM MANAGER
ORGN SYMBOL
EXTENSION
Ej TABLES
Lt. R. C. Lineback
AMOS?)
22119
el
FIGURES
19. PREPARED BY
TITLE
ORGN SYMBOL
EXTENSION
Anthony Civets
Saar. Technician
ABUTS
25290
18. DIRECTORATE CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
19. TECHNICAL DIRECTOR CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
Carl E. Reichert
Technical Director
ASTE ,
21177
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
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NOV 61
REPLACES ASD-0 FORM667 SECURITY CLASSIFICATION
WHICH IS OBSOLETE.
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Test
142ert
A
2.35.R
enbjeeted to the hmaidity test oonditions preessibed iR Freeman's 2 of Spesitisatioa
NIL.N.5272 for the required ties wales (120 hours). The test conditions were
started on 16 April 1962 and were completed on 20 April 1962. On 21 April 1962, 56
hours after the completion of the last humidity vele, a visual imarcetioa and an
operational test were made on sash actuator after removal from the parishute peek.
The cover on cash actuator was removed and the interior of sash actuator was visually
inspected. No visible adverse *auditions were noted on the drogue release actuator
but rust formation was noted on the arming latch of the drogue deploy aetuater. This
rust formation is shown in a photograph. nr. 62.1359, attaehed to this report.
(2) An android aseuracy test INIS then conducted on *ash actuators The drogue
release actuator was subjeote4 to a simulated altitude of 20,000 feet ead the Grates
lever was moved to the armed position. The altitude was then levered at a rate of
200 fest per second and the aneroid release point was noted te be at 160300 feet.
This was within the operational requirement of 16,500t500 test, The drogue deploy
actuator, containing a reveres esti.' aneroid, was subjested to a siemlated altitude
of 230000 feet. The altitude was then lowered to 15,000 feet end the "maim lever
wee moved to the armed position. The altitude was raised and the aneroid release
pOint was noted to be 20,600 feet, latish was mot within the operational requirement
of 1900001500 fest. No further testing was 'emanated an4 the actuators were yawned
to the project engineer.
d. sisoksuggi 11 is eoneluded that.
(1) The drogue release actuator, serial are 209, satistastorily net the test son-
ditto**.
(2) The dreams doyley actuators serial lir. 207, did net meet the test conditions
due to the rust fermatioa and uneatistaetery aneroid ?mattes,
? Aammagaggs It is resonesded thats
(1) The drogue release *Ouster, serial ay. 209, be considered satisfactory for
servies use under the ecegitiene inpeoed by this but.
(2) The drogue dopier actuator, aerial ax'. 207, be elluddered beheeibibraebeelf for
service use under the oinditiees lapasel by this test.
(3) Beth &Ousters be empleiely disassembled and inspected ter iateraal rust
formation. All parts found to be rested Should be fabricated it rust resistant
material.
2
PIVINARED DT: AMMO 'UTZ
Test 1sJ.t lamer
MOM= frbwxur a. Krasuaa,
'k Okla, Invirenneatel Division
Directorate of Sagiagering Test
Deputy Omenandererent amd Sanest
AMOY= Ste GAIL I. WORM
Thehnieal Direetor
Directorate it lag issuing Tent
Deputy Oommenderiftet sad Support
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?
1.0
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liVii 3fIaLlactc1V
?
Report No.
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APPENDIX J
VIBRATION
Page
A3TEVB-62-105-R 46-49
???
4
Technical Memorandum-
'4%,NB-T1,4-163-1
)45
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
SECURITY CLASSIFICATION
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1)
2. AST NR.
p PART
0.1_1b FINAL
L TEST TITLE
AUTOKATIC PARACHUTE ACTIJAVEL
!DENT. HR.
62-105?R
S. DATE 12 OCTiqc
4. T ASK5P711fett7r)SYSTEM 9111.
5. PRIORITY .5 AF IMPORTANCE CATEG. NR.
PreCedenCe 18E
6. OBJECTIVE AND SUMMARY
a. introductions
The purpose of this report is to evaluate an antonatic parachute actuator under
? conditions of vibration and altitude simultaneously. Specific requirements are mow
- tabled in ASRP411-61-28. Test began 25 Jay 1962 and use completed 27 July 1962.
The project emeneer asked the monufacturer to furnish another test specimen Chid'
was to be evaluated also. On 1 October, it was decided to close out this test
because the manufacturer did not respond in a reasonable time.
b. Teat Results and Discussions
10.
a parachute amenably
is at or below 16,500
of high altitude aircraft
are contained in Table
at room altitude
and vibrated longitudinally
hour at 17500 to 18.000 feet
(Continue
which
or
before
for
on
(1) The actuator is
releases the main pared-hate
and is used with nen carrying
Sigeificant Characteristics
A ef this report.
(2) The actuator les
josted to vibration. It
at room Altitude and for
the device within
Chen the altitude
automatically
feet (1500 feet)
apace craft.
Ir. 1, Appendix
being stb-
a half hour
eimilated
separate tango)
cepseles
of this actuator
cocked and operated
lee recodked
another half
7. TEST HOURS COMPLETED
ha
TEST HOURS SUCCESSFULLY
COMP I.ETED h0
" TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
100%
IL REQUESTING AGENCY
Aill118P-3
9. TEST/STARTING DATE
25 July 1962
INSTRUMENTATION
INSTALLATION
TEST PLANNING
11. TEST FACILITY Iola Rold
Alt Chamber & Cagdinowliedel
12. TEST LOCATION(S)
Bldg 93, ROOK 1
21. DISTRIBUTION
ASTRO (original)
LIIIPSP-3 (copy)
ABTA (cow)
TECHNICAL DOCUMENTARY REPORT TO BE ISSUED
YES ogj NO REPORT NR.
(11 Known
13. FLIGHT TEST PILOT
ORGN SYMBOL
EXTENSION
14. DIRECTORATE TEST ENGINEER
lismard R. 1inim
ORGN SYMBOL
A8TILTD
EXTENSION
34245
15. INSTRUMENTATION ENGINEER
Lt. R.C. Linebook
ORGN SYMBOL
ASNPS10-3
EXTENSION
2,2113
22. ATTACHMENTS
Al
APPENDICES
TABLES
FIGURES
16. PROGRAM MANAGER
Lt. R.C. Linebeck
ORGN SYMBOL
AIDDISP-3
EXTENSION
2-2113
ri
17. PREPARED BY
Namard a. Ileum
TITLE
Toot Project Emir.
ORGN SYMBOL
&STUD
EXTENSION
34216
16. DIRECTORATE CONCURRENCE
Carla. Beiciaert
TITLE
Technical Director
ORGN SYMBOL
ABU
EXTENSION
21177
IS. TECHNICAL DIRECTOR CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
20. AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
SECURITY CLASSIFICATION
Aso FORM in REPLACES ASD-0 FORM 667
NOV 61 WHICH IS OBSOLETE.
5
PAGE 1 OF PAGES
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
--...-..... --....._ .___
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-1) --I
2. AST HR.
PARTFINAL
ei
S. DATE 1 2 OCT ig
I. TEST TITLE
AUTOMATIC PARACHUTE ACTUATOR IDENT. HR.
,
62.4.0541
4. TASIC5/1843.66)5Y5TEM NR.
5. PRIORITY 6 AF IMPORTANCE CATEG. NR.
Precedence 18E
6. OBJECTIVE AND SUMMARY
a. Introductions
this report is to evaluate
and altitude simataneously.
Test began 25
asked the manufacturer
else. On 1 Octobers
did not respond
Discession:
.................
an automatic
July 1962 and
to furnish
it was decided
in a reasonable
a parachute
is at
of high altitude
are contained
at room
and vibrated 1angitudina113r
hour at 17500
parachute
Specific
completed
requirements
test
out
Whist
or
before
for
on
actuator under
are con,
27 July 1962.
specimen which
this test
The purpose of
conditions of vibration
tamed in ASMP-21141-28.
' The project engineer
was to be evaluated
because the 1111MUrattlirOr
b. Test Results and
was
another
to close
time.
assembly
or below 16,500
aircraft
in Table
altitude
to 28,000 feet
(Continue
(1) The actuator
the main
parachute
is the device within
when the altitude
carrying ampoules
of this actuator
was cocked and operated
It nes rececked
for another half
ontonatically
feet (2500 feet)
space craft.
Hr. 1, Appendix
being sub-
a half hour
sivolatod
impatats page)
releases
and is used with man
Significant diaractoristics
A of this report.
(2) The actuator
jected to vibration.
at room Altitude and
7. TEST HOURS COMPLETED
h0
TEST HOURS SUCCESSFULLY
COMPLETED 14
TEST HOURS REMAINING
0
DATA REDUCTION % COMPLETE
100%
9. REQUESTING AGENCY
ASNPSP-3
9. TEST/STARTING DATE
25 july 1962TEST
?
?
_
INSTRUMENTATION
INSTALLATION
PLANNING
II. TEST FACILITY bold Hold
Alt Cheiber & Caildggdel
21. DISTRIBUTION
AMEND (original)
ASNPSP-3 (copy)
ABTA (copy)
22. ATTACHMENTS
10. TECHNICAL DOCUMENTARY REPORT
YES K1 NO REPORT NR.
(II Known)
TO BE ISSUED
12. TEST LOCATIONIS)
Dldg 93, E. 1
IS. FLIGHT TEST PILOT
ORGN SYMBOL
EXTENSION
EXTENSION
34245
inN
14. DIRECTORATE TEST ENGINEER
thovord R. Elmo
ORGN SYMBOL
MUD
IS.
INSTRUMENTATION ENGINEER
Lt. R.C. Lineheck
UMUM0Ymoy,
ASNPSP-3
2,2113
[:11
jJ
APPENDICES
TABLES
FIGURES
16.
PROGRAM MANAGER
Lt. R.C. Linebeck
ORGN SYMBOL
ADMPSP-3
EXTENSION
2-2113
17.
PREPARED BY
Sward R. Limn
TITLE
Tort Project Env.
ORGN SYMBOL
ASTI=
EXTENSION
34245
16.
DIRECTORATE CONCURRENCE
Carl E. Reichert
TITLE
Technical Director
OPIGN SYMBOL
ASTE
EXTENSION
21177
19.
TECHNICAL DIRECTOR CONCURRENCE
TITLE
ORGN SYMBOL
EXTENSION
20.
AST DEPUTY APPROVAL
TITLE
ORGN SYMBOL
EXTENSION
ASD FONOV61 RM 153
SECURITY CLASSIFICATION
REPLACES ASD-0 FORM667
WHICH IS OBSOLETE.
PAGE 1 OF
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5
PAGES
? Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
ASTEVD Test Report 62-105R
altitude as required. After this vibration, the arming pin was pulled remotely
at 18,000 feet simulated altitude.
(3) The actuator operated 1000 feet above tolerance. At the project engineer's
request the actuator was recocked and subjected to a simulated altitude of 22,500
feet. It operated immediately when the arming pin was pulled at that altitude.
It was recocked and subjected to a simulated altitude of 33,000 feet. When the
arming pin was pulled, it did not operate until the simulated altitude was
reduced to 22,800 feet.
(4) At the project engineer's request, the actuator was considered to have
failed and the test on it was terminated. The specimen was returned to the pro-
ject engineer.
c. Conclusion:
The actuator is unsatisfactory regarding vibration.
d. Recommendations:
None. Data are submitted for information.
2
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
MOM *A*
Table Ir. 1
lisaaraaterwrs Padfts Salantifie Osapiaw, Ia. Moles, CaWorst*
Illomaelatavet Drops beleaas
Vast irs 3201113-0
&alai firs 209
Vagilits 1.45 lb
Oporatiast 1st te swift at sr balm 16,500 feat *Mtn&
Talame* sas toot
Canal Palled - 2 Saabs'
inamodanse
Lang* - 5/8 imam
adlib - 31i
NNW - 1 3492 Amebas
0ablo ittseded - 12 3A, laabra
2 Iiimating Ns.lea for 1/11 lash baits* 5 tubas ea aestars.
3
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, Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
00110111210 111.
AMID Tent "sport 62-3161
gragS111_,? ??A4AIA4nW
Togt Wt
JL DLkw
B. WARM
CkLer, larrinarrstal illvieles
Direakeente et Ingiageriag Teat
Delft te. Tart aid leggperk
,7.
t1. ti" 11. MOM
lesigniagi Bireeter
Direeteredie et 'Wagering Teat
lierstr Ouggendarillget and lifeprpert
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Approved?Fbr Release 2003/03/10 : CIA-RDP75B00285R000400070001-0
Fie-port . No,
AsT4VD-62-175-R
.11
TO;chni9a1 Plemoranctal#
4P -6.1.
APPENDIX K
VII5RATION .A:trD-6110C,K LIFE TE8T
? ?
, 50
Page
51-61
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[T.
Approved For Release IAfl_flI
r. AST MR.
FLIGHT AND ENGINEERING TEST REPORT
DEPUTY FOR TEST AND SUPPORT
(See ASDR 80-11
TEST TITLE
AUTWATIC PARAMUS ACTUATORS
6. -OBJECTIVE -AND SUMMARY
ASTEVD.
?fl.
L._
DATE
PART
FINAL
, 4. TASK, rROJECT, OR SYSTEM NR.
IDENT. MR. 62.4.75-it ' 1.7457.4.1
FS. PRIORITY AF IMPORTANCE CATEG. NR.
a. littablAtft
The purpose of this report ie to evaluate automatic) parachute actuators under
conditions of vibration and altitude simultaneoun1y and shock and altitude simUlta,
neoualy. Specific vibration requirements are contained in ASIP416-61.20. Shook
requirements are special ea outlined by the project engineer. Teets began 2 Nov 62
and were oompleted 15 Nov 62.
b. Test BeaU1tk,a4?4scuseioncj
(1) Actuator 8/0 222 is a device within a parachute asagebly which releases a
drogn Chute for stabilisation. The color code is white. The actuator operates at
or below 13,800 ft. Table No. 1, Appendix B contains its Significant charecterieti
It was submitted for vibration with altitude test only.
(2) Actuator S/N 22d is a device within the asaemb1y which releases the main
chute,. The color code is yellow and the actuator operates at or below 15,000 ft.
Significant Characteristic's are contained in Table Nr. 2, Appendix B. It wee NUS-
pitted for vibration with altitude test only.
7. TEST HOURS COMPLETED FTEST HOURS SUCCESSFULLY 1 TEST HOURS REMAINING
120
120
E. 9E00F STING AGENCY
COMPLETED
AliNpS11.3 (Lt. !Ameba&
TEST ST.ARTING DATE
INST3UMENTATION
P4 ST AL LA TION
2 Nov 62
!TEST PLANNING
10. TECHNICAL DOCUMENTARY REPORT TO RE ISSUED
YES No
13. FLIGH1 TEST PILOT
14. DIRECTORATE TEST ENGINEER
ward__&__Ktungt___
Is. INSTRUMENTATION ENGINEER
PROGRAM MANAGER
Lt. R.C. Linebalk
17. PREPARED BY
Howard R. Kin=
0
'Continue on separate page)
DATA REDUCTION % COMPLETE
11. TEST FACILITY
12. T ST
LOCATION IS)
Killtr?12
Na. 1, Bldg 093, Area B
ORGN SYMBOL TEXTENSION
Molt
T 21 DISTRIBUTIOhl
ORGN SYMBOL EXTENSION
ASTBVD (orig.) ,
AWSP.3 (val lorm
ASTA (00
i AWN (qr)
A4TIA/D L 34245
1 ORGN SYMBOL EXTENSION 22. ATTACHMENT",
311 -1 A-PENDIcES 7.1IRGN SYMBOL F z-ENSION TA-E F
-
TITLE
CRGN SYMPDL ErIXTUERNESSI:'N
AMPSP6.3 22113
t TVA rc&iect&gr. .14311:1111t 34244
16. DIRECTORATECONCURRENCF iTITLE: IORGNSYMBOL !EXTENSION
1
TECHMCALDIRECTORCONCURRENCE ITITLE TORGN oL_ IEXTENSION
?
20. AST DEPUTY APPROVAL I 1 I
TITLE ORGN srme,DL EXTENSION
Carl B. NeiOhert i_Technical Director 21177
ASD 153
1.10?.' El
REPLACES SD-G FORM 667
WHICH IS OBSOLETE. AF-WF-8 DEC 61 2 400
SECURITY CLASSIFICATION
r AGE PA rE
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2
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(3) Aertuator 4/1 217 ie a devise within the assembly whish deploys this bilk
altitude drogue chute if the altitude is at leeet 16,600 feet. The solar *ode is
blue. Significant oberacteristies ere emtained in Table Nr. 3, APPeedix 1. It
was submitted feta speeiaI shodk-altitude-esospenent-operatim test.
(4) Aatuatore 44 222 and Of 220 were calibrated for altitude at operation
prior to vihnotion by pulling the pin resetelY (the lever beimg in the armed
position when the actuators were In the ahallur at a simmlated altitude of. 20,000
ft) and by slowly reducing the simulated altitude until the, operated, Atter
?animation, each actuator (while 'oohed with the arming pia inserted) was vibrated
for three hours as fallowes
(a) Longitudinally for one half hour at room pressure with the oomtrel
lever in the reset position.
(h) Longitudinal/y for one belt hour at 1000 feet above the calibrated
tiring altitude -with the control lever in the armed position.
(10 Vibration was stepped and the simulated altitude was reduced umtil
the actuator operated. This altitude was recorded.
(4) The actuator was reeocked and the procedure was repeated for vibra-
tion along the axis perpendicular to its mounting base and again for lateral vibra-
tion.
(o) The vihratory frequency was eontinumely varied between 10 ani 55 oPo
and the total excursion was 0.030 inch.
(f) Logs of the vibration tests are contained in Tables Nrp. 4 end 5,
Appendix 24
(5) Beth actuators were near the altitude tolerant* Unite before vibratiou.
Neither actuator remained within the tolerant...* of 1400 ft. SiN 222 was 4400 tt
and S/N 220 was 1100 ft.
(4) Actuators such at Spelt 217 are Janie( in service. It is believed that a
embisetion of oho* and operation Is produeing these failures. /he project
engineer outlined a special test to 'amulet* ?mations believed musing them
failures. The preeedhni* that was followed is outlined in Appendix A of tbie report.
A of this test is contained in ?able Br. 4 ippon:11x 3. otograOhs Mrs.
31 aa4 62402 er 4pendix 0 of this report show the remote operation device
be eseapaseat mocha
(7) A tots/ of seveateen vertical shocks in the direction tending to expand
the bellows and eleven eerie* of 25 movement operations (275 operations) were
applied bear* the calibration indicated that the egeipment had failed to neat the
specified tolerance. Sven, then, failure was in the marginal region.
(0) There was mo visible damage to amy actuators.
(9) Mr. Nike Dougherty of MEW.) assisted throughout the tort on Or 217
and recorded all pertinent data.
o. Gonclugionst
(1) Nor* damage appears to have been done to SiN 222 and wi 228 during
shipment than during the vibration tort.
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
,
(2) The oho* t.tint requirement misers to be too mild,.
d. At23621diatTIELL
It is suggested that the shook and Vibration requirement* of P1b-8TD-E10,
*Environmental Test Rothoda for Acroapoce end around Ihrolpnantil, method 514,
equipment Class 6 and method 516, Proeedure III, bereonsidered as an additional
requirensnt for all actuators. This is based epos tho possibility of greater
dynamic Inputs during transportation and handlimg phases.
PREPARED ET I
CONCURRED IN:
311/-14,1-
EDWARD R. RIM
Test Project thiginera?
c- 40---`- -
JOON S. MAMMA
Chief, Environmental Divimilms
1' Dirsotorate of Engineering Teat
Deputy for Toot and Support
,
CARL E. REM
Technics' Director
Diroctorato of Engineering Test
Dwpaby for Teat and Suppmrt
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
APPENDIX *A"
Yellowed for Special Shook Test for Drogue Release
Before applyiqg shock or operating the trigger mechanism, the actuator
was calibrated by costing it and placing it in the altitude chamber with the
lever in the armed position and with" the pin in pigmy while the altitude
was brought up to 20,000 feet and then reduced to 16,400 feet. The 'lotus..
tor operated when the pin was pulled. This procedure was repeated except
that the altitude was brought down to 16,200 feet before the pin was pulled.
The actuator did not operate at the simulated altitude or 16,200 feet; hence,
the calibration indicated operation between 16,200 and 16,400 root.
After calibration the actuator (still cocked) was mounted in the
.TAX-8.44 shock machine with the lever set and taped in the armed position
and the pin pulled. It was mounted to receive a 30 914* shock in the direction
tending to extend the aneroid bellows. The altitude was raised to 15,400
feet where the actuator was given a 30 ""g" *bock. The shock did not cause
the actuator to operate. After the shock the altitude was raised to 16,800
feet where the actuator operated.
After Choc* the actuator was mounted on the special fixture designed
and fabricated by Mr. Steve Alex of ASTRO. This fixture was used to push
the arming pin in and out with remote control while the actuator is being
subjected to simulated altitude conditions. The actuator and fixture
were placed in the altitude chamber with the lever taped in the armed posi-
tion and the pin in place.
The altitude was raised to 20,000 feet then lowered to 17,500. The
pin was pulled, allowing the trigger mechanism to operate. The altitude
was lowered to 15,000 feet and the pin was pushed in. The latitude was
raised to 20,000 feet again and this procedure repeated 24 time. more.
After this the actuator was recalibrated as before and the entire
procedure was repeated, as before, for 10 complete series of Chock fol..
lowed by 25 pin pullings. After the eleventh calibration the program :manager
decided to increase the severity of the test' therefore, the ;hook was applied
at 15,950 feet instead of 15,400 feet. The actuator operated am a result
of Chock applied near to the normal operating altitude. The actuator was
recorded and Chocked at 15,800 feet. It operated as a result at shock.
It was recorded and Chocked at 15,400 feet. It remained cocked. It was
shocked again at 15,600 feet. It operated atter *bout a stmt. delay.
Another series of 25 *movement operations were applied as before. Another
calibration was made as before. Three more Shocks were applied' one at
15,100 feet, one at 15,300 feet, and one at 15,500 feet. The actuator
remained cocked after the first two but operated as a result at shook
at 15,500 feet. The actuator was out of tolerance at this time. Alti-
tudes of operation are recorded in Table Mr. 6, Appendix !B.*
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
APPENDIX 1.8"
Table Nr. 1
Significant Characteristics of Specimen
Nomenclature: Drogue Release
Manufacturer: Pacific Scientific Company
Part Nr: 1201118-0
Serial Nr: 222
Weight: 1.65 lb.
Code Color: White
Operation: Set to operate at or below 15,800 feet
Tolerance -14olo feet
Cable Pulled - 2 inches
Dimensions:
Length - 9 5/8 inches
Width - 3 inches
Height - 1 1/2 inches
2 mounting holes for 1/8 inch bolts, 5 inches on centers
Cable Extension (Extended) - 6 5/3 inches
2
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APPEBDU *S*
Table 16.. 2
SUPitioant Charetterietics of Specimen
Ne3attei Min Deploy
Manufacturers Pacific Scientific Company
Part En 1201119-0
220
WeiOht: 1.65 lb.
Code Color: Yellow
Operation: Ost to operate at or below 15,000 feet
Tolerance 1400 test
Cable Pulled - 2 inehes
Dimensionos
Length - 9 $/8 inches
Width 3 inches
MeIght - 1/2 :inches
Cable rxtonaion (Extended) - 7 I/2 inches
2 mounting holes for 1/8 inch bolts, 5 inches on ?enters
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
ARM= or
foible lr. 3
Significant Chereeteriaties c ectriten
leameeelatures Progooio
IbmnfOoturer: Swine Selentifie Company
Pert Sri 1201117
Serial lirs 217
Weights 1.61 lb.
Code CeIors Blue
CtoolvticoU 8ot to Operate et or above 16,600 feet
Tolerance 430 feet
Coble Pulled - 2 Indbee
itinensione:
Length 9 /8 inches
Width - 3 babes
Reigbt - 1 I/2 tonnes
Cable Wesel= (Rstesslad) - 5 7/8 inches
2nount1ng bole* for 1/8 Inch bolts, 5 inches on center
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
Yak=
rredritalli
Leagituitinal-
Loagttudina
AIM= 1V"
WA, Ile.
Legof Myatt= Toot for Drove Selene
(211. $22)
16/1111108 OP
UMNI.
Roca
17,030 to 17,
Pervandloular to Rom
Kotattas Vase
Pargeolleulnr to 17,000 to 17400 tt. 1/2 hour
ilineiting Sass
1111L.
0
1/2 hour
I/2 how
1/2 how
Lateral
Lateral
Soot 1/2 hour
17,0tX) to 17,500 ft. 1/2 hour
Alin= CV MMUS litta
BEEDV.L.,*.
16.110 rt. +90o rt.
16tuto rt. 432D rt.
14360 rt.
3.6,04co rt. 4600 rt.
.560
* The drogue relaaoe was eat at the factory to operate at 15,800 ft. the tolerance
ie 000 ft.
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Approved For Release 2003/03/10 : CIA-RDP75600285R000400070001-0
A= CV
iraPliA4
Prewelbration
Longitudinal
Longitudinal
Perpendicular to
Mounting gee.
Perpendicular to
Mounting Base
Lateral
loitere1
main dap
La ft.
6
Amen
Table Mr. 5
Log of Vitwation Toot for Mein Deploy
(8/1 288)
Az at
Neara...
Roan
46,200 to 16,700 ft.
ROCS
16,200 to 16,700 rt.
BOOM
16,200 to 16/700 ft. 1/2 hour 15,900 ft.
vae set at factory to operate at 35,000 tt. altitude.
WPM
0
1/2 lour
3111 hoar
1412 bow
1/2 boar
1/2 bow
ALTTIVICU CV
SIESSIAL-
15,imx
35,40 rt.
15,4C0
=wen
*
*boo rt.
Tte tolerance
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oils= "r
vable *ye 6
Los cir lawational Altitudes for Drogue Release
VegeniUMBS
First Oration
Fire% Calibration
First 30 ?fr swat
Altitude Weed
Second Calibration
Swoon& Caliberation
Second Caliterati=
*mend 30 ne Shook
Altitude Raised
Third Calibration
Ibird Calibration
Odra 30 ye Shock
Altitude Weed
Fourth Calibration
Fourth Calibration
Fourth 30 we Shook
Altitude Paiseed
Fifth Calibration
Fifth Oalibratice
Fittk 30 eShook
Altitude Raised
Sixth Calibration
Sixth Calibration
Sixth Shook
Altitude Reload
Seventh Oalthration
Seesnth Oilibration
Seventh 30 ils" Sten*
Altitvele Raised
tghtbCalibratice
RUM Calibration
itighth 30 Ne Meek
AUtitade liaised
7
WEN
16,1600 rt. Operated
16,200 ft. MA not operate
13,400 ft. WA not operate
160800 rt. Qpereted
16,600 ft. Operated
16,400 ft. Operated
16,200 rt. DUI not operate
131400 ft. Did not operate
17,200 ft. Operated
16,600 ft. Operated
16,400 ft. KA not operate
13,400 ft. Did not operate
160800 rt. Operated
16,1.00 ft. Operated
16,200 ft. Did not operate
13,1100 ft. Did not operate
16,700 rt. coorated
3.6,1400 rt. Operated
16,200 rt. Did net operate
13,400 ft. Did not operate
16,700 ft. Operated
16,230 ft. Operated
16,000 rt. Did not operate
13,403 ft. Did not operate
16,100 ft. OP?rated
16,230 ft. Operated
16,150 ft. Did not operate
15,400 ft. Did not wont.
16,900 ft. Operated '
4160 ti ft. erated
16, i ft. MA not operate
15,400 ft. Did not operate
16,900 rt. operstea
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Tabte ? 6 Continued
MEM
ath Calibration
Ninth Oallbration
Math 30 age Shook
Altitude Based
Tenth Calibration -
Tenth Oallieratioste
Tenth 30 Nei /took
Altitude Raised
aleventh Calibration
lleventh Calibration
Blerwenth 30 Ile Shock
Twelfth 30 Ise Shock
Thirteenth 3,1) ?Pte &Oak
Yourteenth 30 *if Shook
Twelfth Calibration
Twelfth Calibration
Fifteenth 30 *gm Shook
Sixteenth 30 *g" Shook
Seventeenth 30 n's* Moak
FOREMSO *Mt*
1.606aort.
16,10w rt.
15,403:0 rt.
17,250 rt.
16, KO ft.
16,100 it.
15,400 rt.
16,5o3 rt.
1.6,2oo ft.
16,3.00 ft.
15,00 ft.
IMOD tte
15,400 rt.
1%6w it.
16,000 ft.
13,900 ft.
13400 ft.
15,300 ft.
13,300 ft.
Operated
Did not operate
Did not operate
Operated
Operated
Did not eperrate
Did not operate
Operated
Operated
Dia not operate
Ceperated
Operated
Did not operate
Operated after 1 iinute
Way
Operated
Did not operate
Did not operate
Did not operate
Operated
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NUmber-
3.0 (4.1)'
3.1 (4.3)'
3.2 (4.4)
3,3 (4.6)i
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1% APPENDIX
,..1.511AMARY OF TLT R.66ULTS
berta
Test Title
207
409
211
,E,2,ramination of ,Product
Aneroid Cycling
F-2
Overpressure
F-4
Power, Actuation Life Test
f_5
4.1 (4.7.2) Timer Accuracy
2 (4.7.3) Aneroid Accuracy
4.3 (4,7.4) Aneroid Hysteresis
? 4.4 (4,7.5) Arming Pin Pull
.54 (4.8.1) High Altitude-Low Temperature
5.2 (44,8.4 High Temperature
, 5.3 (4.8.3) Vibrtion F-4 F-4
5.4 (4.8.4) shock
5.5 (4.6.4.1) A.ock Life' Test
5.6 (4.8.5) Acceieration
5.7: (4.8.6) and and. Lust
5.8 (4.8.7) Humidity F-1 2
Humidity (Retest) F-4
Notes:
AO,
AO
Numbers.-
217 222 228
tab
at
011 MO
Of*
- Indicatsb re/ease not subjected. to-this test
P ?assed specified test procedure. 1
F 4'ai1ed to Pass specified test procedure in the following area only.
F-1 Would not actuate due to excessive interior rust; however, a rerun of this
tes produed reasonably taccessfhl results;
F-2 ' 10,e4age indicator malfuctioning.
F-3 Timing mechaniaL'failed to fire lthin limits.
Actuatorfiring not within applicable altitude limits.
F-5 Actuator coy.144. 4ot be cocked. It was modified by the Pacific;)-cientific Co.
F-Ab' ' .Adtuater firing within tolerance; however, initial calibration was incorrect.
,
62
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?1.
PACIFIC SCIENTIFIC COMPANY
CREATIVE MANUFACTURING AND DEVELOPMENT
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Approved For Release 2003/03/10 : CIA:RDP75B0 28517000400070 0 -0
LOS ANGELES OFFICE
PACIFIC SCIENTIFIC AEROPRODUCTS
ANAHEIM, CALIFORNIA
LOS,A'NGELES FURNACE DIVISION
SAN FRANCISCO OFFICE
SEATTLE OFFICE
PORTLAND OFFICE
ARLINGTON, TEXAS OFFICE
PACIFIC SCIENTIFIC COMPANY
LOS ANGELES
Office and Factory:
6280 Chalet Drive, Bell Gardens, California
PACIFIC SCIENTIFIC AEROPRODUCT6.
10242 Placentia Avenue, Anaheim, California
*
SAN FRANCISCO
760 Harrison Street
SEATTLE
421 Michigan Street
PORTLAND
1218 S. E. 7th Avenue
ARLINGTON, TEXAS
702A Abram Street
SAN DIEGO
339 W. Broadway (Suite 440)
Representatives:
Eastern U.S.
AERO ENGINEERING CO.
Canada
GARRETT MFG. CORP.
5M? 558 ? 6198 PRINTED IN U. S. A.
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