PROGRESS REPORT SEPTEMBER 1960

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP75B00285R000400020040-2
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 30
• Document Creation Date: December 15, 2016
• Document Release Date: October 9, 2002
• Sequence Number: 40
• Publication Date: September 30, 1960
• Content Type: REPORT

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HEADQUARTERS
6511TII TEST GROUP (PARACHUTE)(ARDC)
AUXILIAIkY LANDING FIELD
El Centro, California
A. V. STAMM, Chief, Projects Branch
T. C. RAUDEBAUGH, Lt. Co one1, USAF, Commander
On file USAF release
instructions apply.
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T A B L E O F CONTENTS
TITLE
REPORTS RELEASED DURING THIS REPORT PERIOD
PROJECTS IN FINAL REPORT STATUS
80-4 DOCUMENTATION SUMMARY
PROGRAMS IN DEVELOPMENT AND TEST STATUS
Flight Test Projects
Support Projects
TECHNICAL FACILITIES BRANCH PROGRAMS
Space Track
Drop Aircraft Modification
Supersonic III Test Vehicle
Re-Entry Recovery System Testing
Instrumentation
Pararange
Whirl Tower
CROSS REFERENCE OF PROJECTS
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REPORT RELEASED DURING REPORT PERIOD
Program Structure 650A
FTL-165 RE-ENTRY RECOVERY SYSTEM TESTING
PROJECTS IN FINAL REPORT STATUS
Program Structure 580A
FTL-217 MINIATURE SURVIVAL KITS
Program Structure 720F
FTL-28 MISSILE AND TARGET RECOVERY PARACHUTE
Program Structure 720F
FTL-193 EXTENDED SKIRT PARACHUTE INVESTIGATION
Program Structure 720F
FTL-194 CLUSTER OF FOUR RECOVERY PARACHUTES
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80-4 DOCUMENTATION SUMMARY
Program Structure 520B
FTL-216 LOW LEVEL AERIAL DELIVERY
WADD has requested proposals for studies of a low level aerial delivery sys-
tem in accordance with Exhibit WCLEHA-62. Awaiting an approved test directive.
Program Structure 720F
FTL-219 PRESSURE PACKED PARACHUTE TEST
M. Steinthal & Co., Inc. has been authorized to conduct a study and ; drop
test program in accordance with Exhibit WCLEHR-130, dated 6 February 1959 under
Contractual Instrument No. AF 33(600)-39643. An approved test directive has been
received. A test program is being coordinated with WADD.
Program Structure 720F
FTL-228 100-FT. Do LECOVERY CHUTE
Clusters of 100-ft. Do recovery parachutes will be tested at 250 KEAS at
3,000- and 12,000-ft. pressure altitudes with weights ranging from 25,000 to
37,500 pounds. Awaiting an approved test directive.
Program Structure 720F
FTL-229 67-FT Do RECOVERY CHUTE
Clusters of 67-ft. Do recovery parachutes will be tested at 250 KEAS at
3,000- and 12,000-ft. pressure altitudes with a weight of 25,000 pounds. Await-
ing an approved test directive.
Lockheed Aircraft Company is developing a nose capsule parachute recovery
system which will be tested at this Group. An approved test directive has been
received. Awaiting contractor for test program coordination.
Program Structure 914A
FTL-213 MODIFIED C-11 CANOPY
Tests will be made to determine the effect of a secondary parachute placed
within the C-11 canopy. Awaiting an approved test directive.
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Program Structure 520B
WADD has requested that engineering testing be conducted to determine the
compatibility of the C-130 cargo aircraft using a modified 108-in. wide dual rail
system and two types of cargo re-supply platforms. The weight range of the loaded
platforms will be from 25,000 to 35,000 lb. Awaiting an approved test directive.
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PROGRAMS IN DEVELOPMENT AND TEST STATUS
FLIGHT TEST PROJECTS
Program Structure 040A
Twenty-three proficiency jumps were made. On each jump parachute deployment
and opening were satisfactory. Test information follows:
Aircraft
Jumps
Parachute
assembly
Launch
(IAS)
kt
Pressure Yree fall
altitude delay
f t _, see
C-130
2
A/P 285-2
110
2,000
C-130
1
A/P 28S-2
110
4,000
C-130
1
A/P 285-3
110
10, 000
C-130
2
A/P 28S-4
110
4,000
R-4D
4
50C7024-15
110
5,000
R-4D
4*
50C7024-15
110
6,000
R-4D
3
50C7024-15
110
8,000
R-4D
3
50C7024-15
110
8,000
C-130
3
5007024-15
110
10,000
* Water jumps
Teflon lined power cable housings and ripcord connector pulleys have been
installed on twelve (12) type 50C7024-15 parachute assemblies.
Program Structure 102A
Three functional tests were made on a 40.9-ft. Do ring-slot parachute with a
3
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Program Structure 102A (CONT'D)
FTL-211 (CONT'D) B-58 ESCAPE CAPSULE SYSTEM
560-lb. cylindrical test vehicle. Deployment of the parachute system was initi-
ated by the firing of an explosive charge two seconds after the cylindrical vehi-
cle dropped from the aircraft. The explosive charge blew off the vehicle door and
deployed a 40-in. Do vane-type pilot chry.t_, which deployed the main parachute. A
2000-lb. reefing.line 12.9 feet long was used with three Ordnance Associates OA2-C
2-sec. delay reefing-line cutters.
Test information follows:
Drop
Launch
EAS
kt
Pressure
altitude
ft
Open
time
(sec)
Down
time Oscillation
sec em__ W
Remarks
1641-F-60
351
1440
7.0
67.0
(1)
1587-F-60
430
1550
-
11.0
(2)
1867-F-60
351
1430
5.8
71.3
(3)
(1) The selvage edge was strained on 50% of the bottom three rings. One cut-
ter had a mechanical failure.
(2) All suspension lines were broken. The selvage edge was strained on 50%
of the bottom three rings. There were 31 blown sections throughout the canopy.
(3) The selvage edge was strained on 50% of the bottom three rings. Pilot
chute was blown and the bridle line broken. The apex lines had friction burns.
Two reefing line cutters had a mechanical failure.
.~.~.--,...,,?~,'-C~:s.v,.??~.~~~om~~aC9as~-ors.~s7siar3vr~~.:-.~~C~s~d.-~~.,--..?~~r~~.?:_ ...............,.~.~_~".....~.a.~.s.......-, -
FTL-221 SUPPORT SAMOS PARACHUTE RECOVERY
Six tests were made. One test each was made on a.6-ft. Do and a.6.8-ft. Do
OCtc'al=ribbon stabilization chute. A cylindrical vehicle weighted to 1700 lbs.
was used. Deployment was initiated one second after dropaway by ejection of the
parachute compartment door. Ten seconds after deployment the stabilization chute
was released and a 67.2-ft. Do extended skirt parachute deployed to recover the
load. One test was made with the 84-ft. Do ring-sail recovery chute with a reef-
ing line length 22ft. and 4-sec. delay reefing-line cutters; a 20-ft. Do ring-slot
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Program Structure 117L (COONT'D)
FTL-221 (CONT'D) SUPPORT SAMOS PARACHUTE RECOVERY
air pick-up chute was attached to the apex by a 165-ft. towline. One test was
made with a 20-ft. Do ring-slot air-pick-up chute attached to a 50-lb. load which
was contained in a 1646-lb. cylindrical test vehicle. One test was made with a
27-ft. Do conical-ribbon air-pick-up chu.e attached to a 90-lb. load which was
contained in a 1646-lb. cylindrical test vehicle. In each case the air-pick-up
chute deployed a 75-ft. Do ring-sail recovery parachute which was reefed with a
27-ft. 11-in. line and two 6-second cutters; the 75-ft. chute recovered r:.e 1646-
lb. test vehicle. One test was made with the 75-ft. Do ring-sail recove?:7 chute
with the 27-ft. Do conical ribbon air-pick-up chute attached to the apex by a
150-ft. towline. On all tests, deployment was initiated one second after dropaway
from the aircraft by ejection of the parachute compartment door. 'T'est information
follows:
Drop
Reefed
Launch Pressure Open Down open Opening
IAS altitude Load Parachute time* time* force force Remarks
(kt) (ft) lb sec sec lb lb) _ __
1640-F-60 254 6,000 1700 6-ft
FIST Ribbon
67.2-ft
E.S.
2,075
(1)
1841-F-60 200 6,000 1700 6.8-ft 1.8 126.2 - 3,025
FIST Ribbon
67.2-ft 20.4 126.2 4,.450. 4,.400 (1)
E.S.
1537.3 - 5,200 (2)
Ring slot (2)
1588-F-60 150 49,650 2185 20-ft Do
84-ft Do - 1537.3 10,500. 16,800 (3)
Ring sail
1839-F-60 141 49,550 50 20-ft Do 2.2 3,35Q (4)
Ring slot
1646 75-ft Do - 1675.1 11,250.. 7,950 (5)
Ring sail
* Stop watch
* Parachute deployment and opening were satisfactory and parachutes were un-
damaged unless otherwise indicated.
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Program Structure 117L (CONT'D)
FTL-221 (CONT'D) SUPPORT SAMOS PARACHUTE RECOVERY
Launch
IAS
Pressure
altitude Load Parachute
Reefed.
Open Down open
time* time* force
Opening
force
Remarks**
kt
tt b
sec (see) lb
lb
_
-._ ~...
1877-F-60
142
48,100
90
27-ft Do
Conical ribbon
2,600
1,475
1646
75-ft Do
Ring sail
3.6
1619.8
10,125
6,750
1876-F-60
144
49,100
1585
27-ft Do
Conical ribbon
--
1645.0
4,750
1,000
(6)
75-ft Do
Ring sail
7.9
1645.0
10,950
7,450
(1) Not a test item.
(2) Towline broke at snatch.
(3) Peak force only, tensiometer time base failed after reefed open.
(4) One section blown.
(5) Two sections blown
(6) For this test the air-pick-up chute was reefed with a 6-ft. 8-in. reefing
line and 6-sec. delay reefing line cutters.
* Stop watch
Parachute deployment and opening were satisfactory and parachutes were un-
damaged unless otherwise indicated.
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Program Structure 201B
FTL- 204 LIVE JUMPS OF MODEL "B" SEAT
Twenty-eight tests were made to determine the reliability of the "B" seat pari-
chute system. Twenty-four of the drops were conducted with articulated dummies
dressed with the contractor modified personnel parachutes, demonstrating an overside
bailout performance. Two of the seat d.-c.)ps were made with articulated dummies from
a C-130 aircraft to similate the actual live jump configuration of the latest produc-
tion F-106 B seat. Two:gravity.seat drops were made from a C-130 aircraft withpara-
chute test jumpers using the same production F-106 B ejection seat. All `.':ie person-
nel parachutes used were modified by the contractor. These modification, were: (1)
larger grommets on seven-of the pack flaps and (2) a shorter pack closing loop for
the top flaps of the pack. These changes were incorporated for better deployment of
the pilot chute. Test information follows:
a.
Modified Parachute Tests with Dummy
Drop
Launch
IAS
Pressure
altitude
Open
time*
Down
time*
Deployment
Remarks-**
kt
ft
(sec)
sec
1594-F-60
120
2000
6.5
83.9
poor
1644-F-60
10.0
1500
5.1
60.5
poor
1645-F-60
100
1500
6.1
63.2
poor
1646-F-60
100
1500
6.4
63.4
good
-
1647-'F-60
100
1500
6.5
62..1
good
1648-F-60
100
1500
5.0
62.6
good
-
1649-F-60
100
2000
5.6
73.4
good
1650-F-60
100
2000
7.7
67.8
poor
.-
1651-F-60
100
2000
6.4
75.4
poor
..
1652-F-60
100
2000
7.5
78.5
poor
1653-F-60
100
2000
8.0
76.1
poor
-
1654-F-60
100
2000
5.7
90.9
good
1655-F-60
100
2000
5.2
76.0
poor
-
Stop watch
* Dummy was recovered satisfactorily by the main parachute in each test unless
otherwise indicated.
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Program Structure 201B (CONT'D)
FTL-204 (CONT'D) LIVE JUMPS OF MODEL "B" SEAT
Drop
Launch
IAS
Pressure
altitude
Open
time*
Down
time*
Deployment
Remarks**
kt
ft
sec
sec
1656-F-60
100
2000
5.3
82.4
poor
1657-F-60
100
2000
6.0
81.4
poor
1659-F-60
100
2000
7.1
74.7
poor
1.660-F-60
100
2000
8.3
70.6
good
1.661-F-60
100
2000
8.7
80.3
poor
1662-F-60
100
2000
-
31.3
(1)
1663-F-60
100
2000
-
21.2
(2)
1664-F-60
100
2000
7.0
77.2
poor
1.665-F-60
100
2000
6.4
66.7
poor
1666-F-60
100
2000
7.1
72.4
poor
1667-F-60
100
2000
-
35.8
(3)
(1) Pilot chute did not deploy. Recovered by reserve.
(2) Recovered by reserve. F-1B arming ball not pulled to open pack.
(3) 28-ft. canopy tangled with dummy. _ .Recovered .by_r'eserve.
* Stop watch
** Dummy was recovered satisfactorily by the main parachute in each test unless
otherwise indicated.
b. Dummy Gravity Drop Tests with Complete Seat
Drop
Dummy-seat 28-ft chute
Launch Pressure separation open
IAS altitude time* time* Remarks
kt ft (sec) (sec)
1712-F-60 110 15,000
2.3 6.5 (1)
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Program Structure 201B (CONT'D)
FTL-204 (CONT'D) LIVE JUMPS OF MODEL "B" SEAT
Drop
Dummy-seat 28-ft chute
Launch Pressure separation open
IAS altitude time* time* Remarks
(kt) ft -- (see)__ (sec)_
1713-:F-60 110 30,000 51.5 54.8 (2)
(1) Dummy was recovered. Survival kits backlashed. Seat was not recovered
because seat recovery static line tangled with pilot chute used to deploy neat
recovery parachute.
(2) Dummy.and seat were recovered. Static line to actuate seat recovery
parachute was tied permanently to dummy and broke free from canopy. No kit back-
lash resulted. Used 100-lb. break cord on survival kit anti-backlash line; it
functioned satisfactorily. Seat was rotating prior to dummy-seat separation.
* Separation and opening times evaluated from motion picture.
c. Live Gravity Drop Tests with Complete Seat
1842-F-60
110
15,000
2.4
6.3
(1)
1843-F-60
130
15,000
2.5
6.4
(2)
(1) Jumper and seat were recovered. Static line was used to deploy seat
recovery parachute. Static line entangled with jumper during seat separation and
parachute descent. Kits increased parachute oscillation during descent. Kit was
jettisoned prior to ground impact. Landing was uneventful.
(2) Jumper and seat were recovered. Seat recovery static line entangled
with jumper during seat separation and descent. Jumper disconnected static line.
Kits increased parachute oscillation during descent. Kits released to 30-ft.
below jumper prior to ground impact. Landing was uneventful.
Separation and opening times evaluated from motion picture.
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Program Structure 201B
F'TL-207 F-106 (ICES) SURVIVAL KITS
Program Structure 426L
FTL-191 XQ-4B DRONE RECOVERY, STAGE II
All tests at El Centro have been completed. Testing will continue at Holloman
FTL-198 TEST OF LOW COST PARACHUTES
Program Structure 530A
One test was conducted on a G-11A parachute. A 12-ft. Do ring-Blot pilot
chute was permanently attached to the apex of the G-11A parachute with a 25-ft.
bridle. The G-11A parachute was reefed with a 44-ft. reefing line.. Four
Ordnance Associates OA-A9 reefing-line cutters with 1-sec. time delay were used.
The 6900-lb. test vehicle was launched at 200 KIAS and at 2,500-ft. pressure al-
titude. The vent area of the G-11A was reduced from 11.5 f t.2 to 3.1 ft.2 by a
12-in. wide strip of 4.75-oz. nylon cloth sewn to vent band. This was the final
test on the program. A technical report is being written. Test information
follows. 10
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Program Structure 530A (CONT'D)
FTL?140 (CONT'D)
Reefed Full
Snatch open open Parachute full
Drop force force force open time*
1b (lb) _(lb)_ sec) W
1436F-60 13,000 27,000 16,500
(1) Parachute damage consisted of one section blown, five 2-in. to )-in.
tears and 15 broken vent line casings.
? Tirde was checked, by movie with.:timing.light and by Force-versus Time
telemetric record.
No tests. Testing of riser cutter installation will be accomplished in
conjunction with Project 6015, Test Parachute Components, FTL?201. Testing
has been suspended on FTL-201 pending delivery of contractor furnished test
items which are scheduled for delivery in October 1960.
Program Structure 609A
No tests. The three tests scheduled for the Salton Sea Range were
cancelled. Three tests are planned for the latter part of October 1960.
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Program Structure 720F
Three tests were conducted with a cluster of three 28-ft. Do flat circular
parachutes (C-9 canopy). All parachutes were reefed with 750-lb. braided nylon
cord 10-ft. long. On each parachute, three 2-sec. time-delay cutters were used.
A 66-in. flat circular pilot chute was permanently attached to the apex of each
of the three 28-ft. parachutes with a 9-ft. bridle. The load weight was an 860-
lb. cylindrical vehicle. The vehicle was launched at 1500-ft. pressure altitude.
Two seconds after release of the vehicle from the aircraft, deployment - the
parachute cluster was initiated by ejection of the test vehicle door. ye door
extracted a 48-in. R.G.S. extraction parachute which was attached with a 12-ft.
bridle to each of the three 28-ft. parachute bags. Test information follows:
Drop
Snatch
force
lb
Reefed
open
force
lb
Full
open
force
lb
Parachute full
open time
(sec_ _
Launch
IAS
kt
Remarks
1.582-F-60 C*
8500
14,500
4200
1st
2200
5,800
2100
4.0
325
(1)
2nd
1500
3,400
700
4.2
-
(2)
3rd
2300
4,900
600
5.9
-
(3)
1741-F-60 C*
5800
11,600
4300
-
250
1st
1900
4,000
3500
3.6
250
(4)
2nd
1050
3,030
500
5.1
250
(4)
3rd
2100
3,900
500
5.9
250
(4)
1750-F-60 C*
6300
11,500
3800
-
250
1st
1700
5,100
2750
3.8
250
(5)
2nd
1650
3,400
500
4.0
250
(5)
3rd
1600
3,500
600
4.1
250
(5)
* Cluster :riser.. forces. ,. .
(1) One section. blown; two 6-in tears in apex.
12
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Program Structure 720F (CONT'D)
FTL-143 (CONT'D) CLUSTER OF THREE RECOVERY PARACHUTES
(2) No damage.
(3) Three sections blown and several 1-in. holes in apex.
(4) Parachutes were damaged after contact with the ground. No photo cover-
age or Askania data was obtained due to adverse weather conditions at the time of
the test.
(5) No damage to parachutes.
Program Structure 720F
Two tests were conducted with the 24-ft. flat circular canopies using B-4
packs and A-3 pilot chutes with 32-in. bridle lines of 4500-lb. breaking strength.
One test was made from the Whirl Tower and one test was made from the C-130 air-
craft at 500 feet above the test area. The canopies tested were both in Porosity
Group 5. Air permeability readings at 1/2-in. water pressure differential were
taken after the drop tests. Test information follows:
Drop
Canopy
Launch
IAS
kt
Open
time
(sec)
Down
time
(sec)
Average air permeabilit
of.cloth area.-in cfm/.ftZ
- - -
Remark.
-
1601-F-60
322523
150
5.1
20.0
176
(1)(4)(3)
7447-F-60
322520
150
1.5
-
144
(2)(5)
(1)
Test from C-130 aircraft.
(2)
Test from Whirl Tower.
(3)
Pilot chute hesitated
(4)
risers.
Three twists were packed into the suspension lines directly above the
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Program Structure 720F (CONT'D)
FTL-147 (CONT'D) TESTS OF PARACHUTES IN VARIOUS PERMEABILITY GROUPS
(5) Canopy packed without twists in the suspension lines.
Program Structure 720F
FTL-199 CLUSTER PARACHUTES (PIONEER)
Four tests were made on a cluster of three 28-ft. Do heavy duty flat cir-
cular parachutes with an 850-lb. cylindrical test vehicle. Deployment of the
parachute system was initiated by the firing of an explosive charge two seconds
after the cylindrical vehicle dropped from the aircraft. The explosive charge
blew off the vehicle door and deployed a 32-in. ribless-guide-surface extraction
chute which deployed the three parachutes. Test information follows:
Launch
EAS
(kt)
Pressure
altitude
ft
Parachute.
Open
time
(sec)
Reefed
open
lb
Full
open
lb
Remarks
1639-F-60
300
14,700
5.2
5900
3500
(1)
(2)
3rd
6.0
6800
400
(3)
1731-F-60
325
14,770
1st
5.5
7000
3950
(4)
2nd
5.55
5350
2100
(5)
3rd
5.9
6100
500
(6)
1853-F-60
400
1500
1st
5.7
(7)
2nd
6.5
(8)
3rd
8.6
(9)
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Program Structure 720F (CONT'D)
FTL-199 (CONT'D) CLUSTER PARACHUTES (PIONEER)
Launch Pressure Open Reefed Full
Drop EAS altitude Parachute time open open Remarks
kt ft _ _._ ...,.., sec 1b lb
1751-F-60 350 15,000 -
(1) Four 1-in. cutter burns.
(2) Gore 14 Section 2, five 2-in. tears.
(3) Three cutter 1-in. burns.
(4) Gore 7 section 3, three 3-in. tears.
(5) No damage
(6) Gore 2 section 3, blown.
Gore 11 section 1, blown.
Gore 14 section 3, seven 2-in. tears.
Gore 15 section 3, four 2-in. tears.
Gore 15 section 1, five 1-in. cutter burns.
(7:) Gore 22 section 4, three 2-in. holes.
Gore 24 section 4, one 2-in. hole.
(8) Strained seams throughout.
Gore 23 section 3, one 1-in. hole.
Four 2-in. holes near the skirt.
(9) Strained seams throughout the canopy.
Gore 25, 26, 27 section 3 blown.
All gores , section 3, 52 small holes; section 4, 9 small holes.
Telemetry failed during this test.
(10) Data not presently available. To be included in next report.
(10)
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 Approved ForRe1'ease 2002/11/08 : CIA-RDP75B00285i1!000400020040-2
Program Structure 720F
Seven twisted line tests were conducted on the 50 C 7024-15 assembly, six-
teen on the T-10 reserve assembly, and fifteen.tests on the NT-1 assembly.
On the eleventh test of the MT-1 kssembly, the twists failed to move down
the lines following line stretch and a streamer occurred. This nullified these
eleven drops in accordance with AF Specification Bulletin No. 505.
Program Structure 720F
No tests. Testing of the experimental pack opening cutter has been sus-
pended pending delivery of contractor furnished test items. All testing to
date has been accomplished on prototypes constructed within the engineering
shops at WADD. Contractor delivery of test items is scheduled for October 1960.
Program Structure 720H
FTL-144 TESTS OF ANTI-FRICTION TREATED SUSPENSION LINES ON C-9 CANOPIES
Program Structure 750A
No tests. Aircraft and equipment have not been received for testing.
16
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 Approved For ease 2002/11/08 : CIA-RDP75B002800400020040-2
Program Structure 912A
FTL-172 B-5 PACK WITH MODIFIED SIDE FLAPS
Programs Structure 912A
FTL-177 MODIFIED HARNESS FOR LIVE JUMPS
Two tests were made from the Whirl Tower at 200 knots with
B-Harnesses modified with chest D-rings for riser attachment and with
modift saddles. A bent form dummy was used as the test load. The
weight of the total load was 313 pounds. A strain gage was us,-d in each
shoulder riser. No forces were recorded due to telemetric equipment
failure. On the first test the friction bar on the left side adapter
broke. Also, the stitdhing connecting the chest strap to the main
webbings broke on the left side. No damage occurred to the second
harness tested.
Program Structure 912A
One drop was made from the Whirl Tower at 100 knots with a 250-1b
torso dummy (weight of telemetry package included). This test was made
to determine the pilot chute forces and main canopy forces during the
canopy opening. The pilot chute bridle had a fixed length of 34 inches.
Test information follows:
Drop Pilot dhute Opening Pilot chute Hain canopy
diameter time max. :force max. force
(in.) (sec.) (lb.) (lb.)
7449 36' 2.0 255 2250
emarks:
Partial Inversion. Cores 11, 12, and 13 were burned during
deployment by pilot chute telemetry lead which was tacked to line
channel 13. Section 4 of gore 28 blown. Dummy was recovered.
.,.:sssasbs~staaesas~ssasest~:e~r~~~=:: ~~W- s_--, ~.a~6?-.~o~a?a~..s,?^m~.t=e..a,-3,-~~asscessssaaasassnsaesaseae
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 Approved For i ease 2002/11/08 : CIA-RDP75B00285f3(iU0400020040-2
Program Structure 921A,
FTL-225B AP-22S FULL PRESSURE SUIT TESTS
Two dummy drops and six live,jumps were conducted to evaluate the AP-22S full
pressure suit, back type oxygen organ and 1500-cubic inch seat kit. Two modified
parachutes, P/N 50C7024-15, and two experimental multi-stage parachutes were pro-
vided by tk}e ARDC coordinator to support the pressure suit tests.
The initial test program required the use of parachute assembly 3OC7024-15, as
modified for oxygen organ:, seat kit and reserve parachute retention. The ARDC coor-
dinator who was also the test subject was :completely equipped with the modified para-
chute, oxygen organ, seat kit, reserve ...rachute and AP-22S uil pres8ure,s it. A
6511th Test Group test jumper precede,:'.he ARDC test subject on each jump caring the
same equipment as the test subject minus the seat hit and the AP-22S full pressure
suit. The ARDC test subject encountered a severe flat spin during the first exten-
ded free-fall delay (51 seconds) from 15,000 feet pressure altitude with the full
pressure suit and the seat hit. The high rate of spin. (approx. 130 :pm), attributes`,
to the wei;ht and configuration of seat kit and other test items attached to the ;umpe:_
necessitated manual opening of the parachute by the test subject. Testing with this
cunfiguration was discontinued flue to a requirement that the test subject must be
stable.
Two experimental multi-stage parachutes and a rigger qualified to pa:. -hem were
provided by the ARDC coordinator. A revised test program as prepared. All tests,
matte at 110 knots from the C-130 aircraft, had an initial free-fail time delay of 12
seconds before actuation of the first stage parachute. TO automatic release used to
initiate deployment of the main parachute was set for 5000-ft, pressure altitude,
followed by a 2-second time delay.' Information concerning tests using the multi-stage
parachute follows: I
Drop
Type load
Pressure
altitude
Results
0
1796-F-60
Articulated Dummy*
10,000
Satisfactory
1797-F-60
Articulated Dummy*
15,000
Satisfactory
1817-F-60
Test Jumper*
15,000
Satisfactory
1818-F-60
Test Subject**
15,000
(1)
1859-F-60
Test Jumper*.
31,900
(2)
1860-_F-60
Test Subject**
31,900
(.3)
** Full test equipment.
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 Approved For (ease 2002/11/08 : CIA-RDP75B002800400020040-2
Program Structure 921A (CONT'D)
FTL-225B (CONT'D) AP-22S FULL PRESSURE SUIT TESTS
(1) Kit caused severe oscillation. There was minor pack and canopy
damage. Main parachute automatic release and mou*ting plate was torn
out.
(2) Main parachute deployment bag extracted when first stage
deployed. Main. canopy was destroyed. Landing was made with emergency
parachute.
(3) Main parachute was partially deployed with first stage parachute.
There were twists in the main canopy suspension lines from risers
nearly to canopy skirt. Two lines were over the main canopy. Gore
No. 8 was destroyed. Test subject landed with the emergency parachute.
FTL-225B has been terminated. A report will be prepared by the
ARDC coordinator,
Program Structure 921A
FTL-167 REEFING LINE CUTTER ENVIRONMENTAL TESTS
No change in status. The Hoover Oscillators used to record
reefing. line cutter acceleration were being used on a higher priority
test program, designated as FTL-212, titled "MC-1 Cutter Environmental
Tests." Testing will be resumed after completion of test_program
PTL-212 or upon r.eceipt.of additional.Hoover oscillators.
-----------------------------------
Program Structure 921A
FTL-203 C-130 HEAVY DROP CAPABILITY
One 41,740-lb. single load was extracted from a C-130 aircraft
which had been modified in the area of the ramp support rod floor
attachments for a maximum loading of 50,000 pounds.
The load was extracted at 150 KIAS from an altitude of 5000 feet
above the test area. Six G-11A 100-ft. D? cargo parachutes were used
to recover the 37,740-lb. suspended test weight. The, Et-rdraft was in-
strumented with (1) strain gauges located on the floor ramp support
rods, (2) an extraction velocity recorder, and (3) a gyro compass
mounted in the pilot compartment to record the angle and rate of air-
craft pitch-up during extraction. A pilot-signal system was installed
to indicate when the platform was clear of the aircraft. Full power
was applied by the pilot immediately following release of the cluster
of one. each 28-ft. ring-slot parachute and 22-ft. ring-slot extraction
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 Approved For)Wease 2002/11/08 : CIA-RDP75B002800400020040-2
Program Structure 921A (CONT?D)
:DTI'.,-203 (CONT?D) C-130 HEAVY DROP CAPABILITY
parachutes after which a nose down correction was when the, si ;na k.
indicated the platform system was clear of the
The aircraft "pitch-zip" foil ~w:Lng extracc.tion iwa than on
previous drops and the recovery to level. flight i=_npo e(1 G forces which
were more noticeable to the crew than on previous drops. The sequence
recovy
of events following extraction up to partial d,.,..t~1G:, < the
parachute canopies appeared satisfactory. Four of the ?'(_c.o7,7 'ry para,-
chutes reefed with 60-ft. lines with 6-sec. cutter, >c-:p;Ar?ated from
the load immediately following line stretch and prior to the cutter time
elapse. Two of the parachutes incurred friction breaks o the 6-l'-)_y
cluster risers and two were stress breaks. 'Tae weight platform made
ground impact suspended from two C-11A recovery ?para.chut:?s in a squid
configuration with a total down time of 22.3 oe.ccnds. No determination
of the exact cause of the recovery parachute failure has been made.
However, photo evaluation does not disclose any relation of the mal-
function to the non-standard system.FFurther study will he made of this
malfunction.
------------------------ -------------- ------
Program Structure 921A
Two tests were made on a 28-ft. Do Fist ribbon parachute with a
2000-lb. cylindrical, test vehicle as the suspended load. The parachute
was reefed with a 2 ply 6000-lb. nylon reefing line 22?--ft. long. Two
MC-1 reefing line cutters with 6-second time delays were attached to
the skirt of the 28-ft. parachute 180? apart. Two 10013-C accoleronmyeters,
weighted to simulate the MC-J. cutter ware installed on the pa?ac Mute
skirt 1.80? apart and 90? from the cutters. Two secbndds after release
of the cylindrical test vehicle from the aircraft, doplo;ncent of the
parachute was initiated by ejection of the parachute ccxspart ae:nt door.
The door extracted a 72-in. heavy-duty ribJ..eac ~~A uide iaarlace; pilot.
chute which was attached with a 2-ply IO,OC0-119. 12-'ft. +h.;.id1e:
(Mil-W-4088B, Type XIX) to the bag of the 428-ft. parachute . A 1,13-ply
10,000-lb. cgncentric nylon 6-ft. riser (M1.i-TtT-408889 Type XIX) c.oa-
ne.cte.d the 21$-ft. pargehute to the test vehicle. Test Lnforaaa, ticaa
follows.
Drop
Launch
JAS
Pressure
altitude
Full Open
tiic1a
Down
t: me
1.tex.
ifor?ca
Max.
acce?.,
1732
F
400
3000
10.7
42.4
37,500
520
(1)
60
1.584
F
497
3000
J.4.4
40.7
(2)
60
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 Approved Forlease 2002/11/08: CIA-RDP75130028100400020040-2
Program Structure 921A (CONT'D)
FTL-212 (CONT'D) MC-1 CUTTER ENVIRONMENTAL TESTS
(1) The pilot chute and main chute bag broke away before complete
deployment of the main canopy.
(2) The telemetering malfunctioned and the force and "C" load data
were not obtained.
:~a~asara~emacsa~m~,vpa~-.m~aas~~~ssoems~sa?ecea~aastwmaaezaasa:~~racawmnm~wmm~ee~en?aa~mee~msarnade~a~~rs ~~s~~~r~~~e,~xez.,=~r
FTL-196
Terminated,
MERCURY CAPSULE RECOVERY
Program Structure 921C
Two functional tests and one strength test were made on the
13.4-ft. Do FIST ribbon deceleration chute. The two functional tests
were made using a 500-1b. cylindrical vehicle. The strength test was
made using a 7200-lb. two-stage cylindrical vehicle. This vehicle
was programmed to free-fall for 10 seconds to accelerate to 310 BIAS
'before the 13.4-ft. A;q FIST ribbon chute deployed. Fifteen seconds
after deployment, the 13.4-ft. Do VIST ribbon chute was pr.ogra Tied
to separate from the vehicle and deploy two 75-ft. Do extended skirt
recovery parachutes.
Test information follows:
l
ad
L Drop
Launch
IAS
Presofure
altitude
Reefing
line
length
Reefing
time
delay
Reefed
open
Lime
Full.
opez)l
ii::im.e
Down.
tine
R_.-
(
b
kt
ft
ft
see.
ec.l
ec
2
se
1&42F-60 : 500
400
10,060
11
6
1.8
-
8.5
120.6
(1)
1&(-F-60 ..'500
490
10,070
12
6
1.8
8.5
124,8
(2)
1.838?F-6G Y200
250
10,500
12
6
(3)
*Stopwatch time from initiation of deployment..ins?tead of from launch.
(1) The lower lightweight ribbons showed strains.
(2) The tensiometer indicated a force in excess of 19,000-lbs.
No parachute damage.
(3) Normal deployment and opening of the 13.4-ft. Do FIST ribbon decelera-
tion chute. There were five broken ribbons and strains in the lower
ribbons. The two 75-ft. Do recovery parachutes had not fully opened at
time of impact.
--~? Y--es-?evo exa~o_~~m- ----------
ora~~mA~ eKS~~ ~ ~~ ~ W V eas _?
Approved For Release 2002/11/08: g1A-RDP75B00285R000400020040-2
Approved
Program Structure 921B
 Approved For`` lease 2002/11/08 : CIA-RDP75B00285a@00400020040-2
Program Structure 650A
The development contract with Radioplane Company has been terminated.
Further modification and tests of the Transonic III vehicle will be accom-
plished by this Group.
Program Structure 650A
FTL-158 SUPERSONIC II TEST VEHICLE
No change in status. The ground acceptance test of the vehicle is
scheduled to start 17 October 1960.
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 Approved For11ease 2002/11/08 : CIA-RDP75B002800400020040-2
TECHNICAL FACILITIES BRANCH PROCIEW}S
TEST FACILITIES
Program. Structure 496L
Program Structure 650A
FTL-160 DROP AIRCRAFT MODIFICATION
No change in status.
FTL-162 SUPERSONIC III TEST VEHICLE
Test directive was forwarded to ARDC through AFFTC and to request
performance of wind tunnel tests.
Final report was received from Chance-Vought Aircraft under study contract.
Report completes contract.
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 Approved For''Rdiease 2002/11/08 : CIA-RDP75B0028-8000400020040-2
No change in status.
No change in status.
No change in status.
IN3TR NTATI0N
WHIRL, TOWER
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 Approt;F1rase 2002/11/08 : CIA-HDP75B002850404020040-2
W -4 C O 4-3 U 4.) U C' CU f?i, (U 44 ?ri U- 4
CO r^4 "I Cut co N (d C), () C) I 4) CC 'iy Cd t]O
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f < CJ C} 1-4 E-4 E 4 C) r.1 (a) rti'i C4 , U) .'x',
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(U 14 C) U rC) U ? 4 U ?14 W . i
td iH C) 44 td -rC U li 0 ' rU 1-I .11
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,
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14 ('.) t)) rri CO [-I [-I l 4) : r~-, CO t3q
(,7 ?f1 14 e a) U C) U
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i1) ^r4 "r', y Cd 6U' r1 ,-4 0 C) 1?4 .4 (U Q)
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tt +) ,r ;S O O O 0 Ci
f*4 r-4 P-? CU C) 0 r Co C43 r"' N 0 Pq
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\0 '.-)' \O \0 tD cu I'D Cd \0 \0 \0 \0
CTt C: ON 01 O1 Ca 4J 0 C C'. 0 LT (T
r-I ? 4 r-I r4 r-4 ?r4 14 r-I ?~ r-1 .4 r-4 ,.4
4-1
O
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r~4 0 z rr4 C/) E 4 P4 A E4 P rr4 u) N
U
Cd
co Cr)
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C.", rY N 4-i N U P-i
.r-I Cd P4 P4
'C) 4) O P-4 4J
I-I l) 4I
0 0
'H 00
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`-1 Cl) 0
r-4 C?)
U
4J P CY, C4 0 :3 0 0 44 r
r A to d r*i O
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:y 44 0' M -4 U (1) ,a > 4)
) IN C') C14 (.I C-I N N N
L., C
(o r. m
C\I N N
N N C")
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0 C i r' r-A C) C) r 4 r~-1 O
 Approved For Mefease 2002/11/08 : CIA-RDP75B0028SQ,p00400020040-2
SUMMARY
GENERAL
Programs carried forward from last report
39
New programs initiated (FTL-225B, 'FTL-228, F'cL 23 and FTL-229
4
Programs completed (FTL?165, 191, 196, 22515)
4
Total programs at end of September 1960
39
STATISTICAL DATA
Durrriy, bomb and cargo tests
102,
Live jumps of test items
10
Total tests from aircraft
i12
Training and proficiency jumps
13
Whirl Tower drops of test items
14
Drop Tower drops (Instrument Lab.)
`i
Total weight dropped from aircraft (1b)
107,915
Total weight dropped fro Whirl Tower (lb)
2,53
Total weight Drop Tower dropped (lb)
Grand total weight dropped (lb)
111, 94t3
Air Force missions flown
1-3-;
Air Force missions flown by Navy
27
Range No. of radar controlled drops
e;9
No. of drops requiring Askania
51
No . ' of drops, requiring Contrives
Instrumentation No. of telemetry channels recorded
Data reduction No. of frames read
9-1,39-2
No. of drops reduced, computed and plotted
477
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