EDR.docx

REV:

ENGINEERING DATA REQUIREMENTS

(ATTACHMENT “A”)

NOTE: MILITARY SPECIFICATIONS STANDARDS WILL NOT BE FURNISHED IN THE BID SET.

1. THE FOLLOWING INSTRUCTIONS ARE FURNISHED FOR THE MANUFACTURE OF:

XXXXXXXXXXXXXXXX

2. PART NUMBER:

3. NATIONAL STOCK NUMBER:

1234-12-123-1234FG

4. THE FOLLOWING SPECIFICATIONS/STANDARDS, ETC, WILL BE USED IN LIEU OF THE DATA INDICATED. THE SUPERSEDED DATA WILL NOT BE FURNISHED UNLESS SO INDICATED.

(ATTACHMENT “A”)

NOTE: MILITARY SPECIFICATIONS / STANDARDS WILL NOT BE FURNISHED IN THE BID SET.

1. THE FOLLOWING INSTRUCTIONS ARE FURNISHED FOR THE MANUFACTURE OF A:

Clamp Kit, Separation – KMU364/E

2. PART NUMBER:

69A48340G4

3. NATIONAL STOCK NUMBER:

1440-00-148-7661

4. A supportability analysis was completed for this kit, which shows that all materials and components are available. See the embedded spreadsheet for details. This information is available to help with the purchasing process, but its use is not mandatory.

5. This EI adds documents S-133-1012-3-2-1, S-133-1012-3-2-2, and S-133-1012-35 since they are not available in JEDMICs and, as a result, are not in the bid package.

6. This EI also includes copies of two Request For Variances (RFVs) that add alternate adhesive Scotchcast 8N and Amorim Cork Composite Inc. as an alternate cork supplier. Engineering Orders (EOs) for both of these changes are in work but will not be ready in time to support this buy.

PREPARED BY:

RICHARD TILTON

OFFICE SYMBOL:

GBMAF

DATE:

20080411

PREPARED BY:

ALAN J LOVELESS

OFFICE SYMBOL:

414 SCMS/GUEA

DATE:

12/8/20

HILL AFB FORM 462 Page 1 of 1 S-133-1012-3-2-1.pdf

.% “’ “ .x

D

I 8245 -J5-1316

II

MARK 12 R/S

ELECTRO-EXPLOSIVE PRESSURE CARTRIDGE

DESIGN AND DEVELOPMENT REPORT o

CONTRACT NO. AF 04(694)731 4

JANUARY 26, 1967

t e

‘9

GE NE RAL@)EIECTRIC\

RE-ENTRV SVSTEMS DEPARTMENT

.9

W.-u.. a

Addendum to 3245-J5-1316 Febmarjy 23, 1967 l.. Pressure Refw:.lrenents a

8245 -J5-1316

MARK 12 R/S

ELECTRO-EXPLOSIVE PRESSURE CARTRIDGE

DESIGN AND DEVELOPMENT REPORT

CONTRACT NO. AF 04(694)731

Prepared by f.’ && 1/26/67

V. W. (hldie, Eng. REAEE

Reviewed by %% %., 1/26/67 M. M. West, ~upervising Eng.

Approved by 1/26/67 D. W. B~hr, Manager REAEE

GE NE RAL@~EIECTRIC

RE-ENTRV SVSTEMS DEPARTMENT

i/ii

ABSTRACT

Development tests performed on MK 12 pressure cartridges in-dicatethat the cartridge operates reliably after being exposedto pre-flight and flight environments. Functioning response andpres-sure output, for ambient condition from +20°F to +160°F, are suf-ficiently reliable for flight operation. All-fire and no-fire sensitivity tests show that the design requirements have been adequately met.

iii/iv

TABLE OF CONTENTS

PageSection

1.0 INTRODUCTION ● . ...****. . ****..*** ● ***

1.1 General ● **** 0a*9 ● *.**.*** ● ****.*.

DESIGN #m#***e*** ● ***9***** ● ********* ●

2.1 General ● *0*b**9e* ● *9******* ● *9*9*

2. 1.1 Cartridge Housing

2. 1.2 Header ● *****O*.* ● e***.*..*

2. 1.3 Connector .* ******* ● *9.****

2. 1.4 Bridge Circuit

2. 1.5 Ignition Charge

2. 1.6 Main Charge .* **....* .* ****

2. L 7 Housing Closure Disc

2. 1.8 Shielding Cap

DEVELOI?MENT TESTS

3.1 3.2 3.3

3.4

3.5

3.6

General ● **** m***9 . *******.* ● *O*** Test Plan ● e*e **e** ● ***.**** ● *.*** Pre-Flight and Flight Environmental

3. 3.1 Insulation Resistance

● O******** ● **.*,

● ***e **e** ● ***S*****

● **a ***e** ● aee4e9*9b

● *e ***e*** ● ***.*****

● ****S**.* 9 **...,...

● **9**.*** ● *****..**

.* ******* ● *.9***** ● *

● ****9*9** ● .*******.

● ***o ****a ● e*** e# ***

● O******** ● *..**..*.

Exposure ● ********* ●

3. 3.2 Application of No-Fire Current ● e******** ., ******

3. 3.3 Pressure-Time Measurements Sensitivity Tests . ***.***** ● ****O**** ● ****6***- ● *******

3.4.1 Bruceton Tests ● *b9e9 e*** ● ******O** ● *****.*** ● ** Tests using Bruceton Non-Fires

3. 5.1 Current Application - Non-Fire Condition

3. 5.2 Pressure-Time Measurements Dynamic Resistance and Related Time Measurements

3. 6.1 Bridge Wire Thermal Characteristics

SUMMARY AND CONCLUSIONS ● ****9**** ● *99 e***** ● eeee. e.e.

4.1 Pressure Characteristics ● *aame**ae ● ooee*o e** ● *********

4. 1.2 Variables Analysis ● *9*9***** ● 9...9**** ● o*******

4.2 Response Time

4.3 Sensitivity

4. 3.1 No-Fire Sensitivity .. *.***.* 9*******. ● *.. .. **e ● *

4. 3.1 All-Fire Sensitivity ● ***e **e** ● *me****** ● ***a **e*

TABLE OF CONTENTS (Continued)

PageSection

5.0 27

REIJABIIJTY AND SAFETY CONSIDERATIONS . . . . . . . . ● ● . . .

5.1 Safety ● **O****** ● *e*e ***o* ● 0*0* eO*90 ● *em*e* e*. ● *****

5. 1.1 Electrostatic Hazards

5. 1.2 Electromagnetic Radiation Susceptibility

5.2 Reliability ● *9*9*99*** ● 909000900 ● eOe*e***** 9*** *O***S

Appendices Page

A-1Work Statement No. 8245-J5-056 ● *9*0 ****8 ● *******O* ● ******

Electron Deposition Experiments-RF Analysis of Shielding Cap . *9******.* 9**ee ****s ● ****D.**** 99*.*9***** ● *******

A

B B-1 c-1

D-1 c

D

Cartridge Specifications ● **9 **0*** ● **** e***e ● O******** ● ****

13ruceton Data Sheets ● ****e**** ● **9****** ● m*******e ● ***O**

LIST OF ILLUSTRATIONS “

Figure Title Page

Electroexplosive Pressure Cartridge ● ***9 **9** ● *e* b**e** ● ** 42-1

Expenditure of Hardware ● *#0* 9*e** ● **ee 0*9** ● ********* ● *** Instrumentation Block Diagram ● *0*9 e*o*e ● ********9 ● ******* Typical Pressure-Time Trace Spent Cartridges and Abnormal Residue Dynamic Resistance and Functioning Time

3-1 3-2

3-3

3-4

3-5

23Frequency Distribution of Pressure . . . . . . . . . . . . . . . . . . . . . . ● .4-1

13ST OF TABLES

PageTable Title

Pressure-Time Measurements .

(Environmentally Exposed Hardware) Pressure-Time Measurements (Bruceton Tests) ● ********* ● **9****** ● e**e***** ● ********** 9 Pressure-Time Measurements (Non-Fires from Bruceton Tests) ● ********* ● ****-***** ● **** Dynamic Resistance Measurements. . . . . . . . . . . . . . . . .0.....-.

1.0 INTRODUCTION

1.1 General

This report provides a detailed description of the design, development and testing performed for an Electro-Explosive Pressure Cartridge hereintiter called the cartridge. The cartridge is intended for use in MK12 R/S Program as a high pressure gas generating source forthe following components:

(a) R/V Release Bolt

(b) Thruster Assembly

The common cartridge concept utilizes a standard configuration whose pressure output is varied by changing the quantity of the main explosive charge to reliably actuate the above components. All parts of the cartridge are ident ic al, except for the larger quantity of output charge required for the Thruster Assembly.

The cartridge is identified by G. E. drawing No. 66 C49103 and G. E. Specifications S-133 -1012-3-2-1 and S-1375-03-0003.

1/2

2.0 DESIGN

2.1 General

The cartridge design utilizes a five pin connector configuration conforming to the Bendix JT (Junior Tri-Lock) series type. Five connector pins are required for the bridgewire circuit continuity circuit and ground circuit. The cartridge design is the same for the R/V release bolt and thruster assembly except for the difference re-quired to meet the quantity of main charge for specific pressure output requirements.

The cartridge (See figure 2-1) consists essentially of the following parts:

a.

b.

c.

d.

e.

f.

g* h.

Cartridge Housing

Header

Connector Pins

Bridge Circuit

Ignition Charge

Main Charge

Housing Closure Disc

Shielding Cap

Detailed evaluation of all component materials and dimensions were made, and a final detailed drawing was completed by the vendor into rporating the results of this study.

A work statement (8245 -J5-056 Appendix A), was submitted to initiate this assignment and reliable pyrotechnic vendors were called to perform the design and development program. The work statement defined the performance, environmental, safety, and test requirements in accordance with internal environmental specifications.

Request for quotes were submitted to three different vendors, their proposals were evaluated, and Hi-Shear Corporation was selected to perform the work because of their overall superior competence and experience in the pyrotechnic industry. In addition to this departments evaluation, their effort also received the support of a GERSD engineer-ing quality control and a manufacturing team.

2. 1.1 Cartridge Housing

The cartridge housing is fabricated in one piece from 17-4PH stainless steel heat treated to the requirements of MIL-H-6875. The threaded end has a .562-18 UNF-2A thread for mating to the release devices. This high strength corrosion resistant material is used because it withstands high operating temperatures and pressures and requires no protective finish except passivation. The output end of the housing shall be hermetically sealed, after loading, by welding with a stainless steel closure disc. The closure disc shall be coined so that it orange peels without fragmenting the

I-P

1.110 .——..-—----a-

I // // 2 w’ f

SECTION-A-A

CIRCUIT DUUWMM

Figure 2-1. Electroexplosive Pressure Cartridge cartridge as it is fired. A self-locking insert is provided to prevent loosening of the cartridge and to prevent gas leakage when assembled to either the Release Bolt or Thruster Assembly.

2. 1.2 Header

The header assembly consists of a 94-96% alumina wafer metallized for brazing the connector pins and for soldering of the header to the cartridge housing. The header is designed to withstand the extremeIy high internaI pressures in addition to temper-a tures generated by the explosive without damage. Alumina is used as the header material because of its high thermal and low electrical conductivity, this results in high electrical insulation values in reproducible, stable dimensional properties.

2. 1.3 Connector Pins

The connector pins are made from .040 diameter Kovar material. The pins are hard gold pIatedin accordance with MIL-G-45204 thereby providinga corrosion-resistant surface with superior electrical characteristics. Kovar, which isanickel-iron alloy was selected for the contact pins because of its low thermal expansion which makes it compatible with the header material.

2. 1.4 Bridge Circuit

The bridge circuit is a high resistance material capable of being projection welded re-liably to the connector pins. The bridgewire circuit is capable of meeting a .20-.40 ohm resistance requirement after welding to flush connector pins mounted in the header.

The bridge circuit is the only circuit allowed internal to the explosive cavity.

2. 1.5 Ignition Charge

The ignition charge consists of 25 mg of normal lead potassium perchIorate consolidated to 10,000 psig in

2. 1.6 Main Charge styphnate and 70 mg of zirconium the header cavity.

The main charge has the following quantities of zirconium potassium perchlorate com-pacted and sized to meet the designated pressure output requirements as measured in a 10 cc closed bomb. These output requirements are as stated below:

Item Qty (charge) Pressure

R/V Release Bolt 70 +5 Mg 940 *1OO psig

Thruster Assembly 1050 +5 Mg 6250 +1250 psig

The explosive material consists of readily available materials, andneither the mate-rials or manufacturing process is” proprietary. The explosive materials ofall the cartridges used for this program shall be of this same basic formulation.

2.1.7 Housing Closure Disc

The housing closure disc is made of stainless steel, and is that it can peel open. This disc is also readily weldable to

2.1.8 Shielding Cap

capable of being coined so the housing.

A metal protective cap capable of protecting the connector pins against environmental exposure and provide RF shielding is assembled to the cartridge thereby providing adequate protection for transportation, handling, and storage. The cap was analyzed to ensure that RF penetration will notoccur thru openings or directly thru the metal itself. This analysis is shown in Appendix B.

Electron Deposition experiments were performed on the cartridge. The test plan and results are included in Appendix B.

3.0

3.1

This

DEVELOPMENT TESTS

General development program is intended to characterize parametric criteria pertaining to the operational reliability of the component and to provide confirmation that thede-sign goals meet the requirements as definedby specifications. To attain the desired design goals this cartridge must meet the following requirements:

(1)

(2)

(3)

(4)

Minimum All Fire - requires 3.5 amperes of pulse application (no greater than 20 milliseconds)

Maximum No Fire - the cartridge shall not function when 1.0 ampere is applied for 5 minutes

Time to Peak Pressure - this period is no greater than 10 milliseconds when fired with 4.5 amperes

Peak Pressure - the peak pressure is 940 +100 PSI

3.2 Test Plan

A total of 68 pressure cartridges were tested, as shown below, during this program.

Sensitivity tests (Brucetons) utilize 40 units, half of which fired during test. The 20 non-fire were retested for supplemental information. All tests were conducted in a closed bomb of 10 CC internal volume. Pressure-time traces were recorded for all fired cartridges. Dual pressure transducers were used throughout to insure against loss of information and to check the accuracy and stability of our measuring equipment.

Figure 3-2 depicts a block diagram of our instrumentation. Figure 3-3 shows a typical pressure-time trace and voltage trace measured acress the bridgewire of the cartridge.

3.3 Pre-flight and Flight Environmental Exposure

3.3.1 Insulation Resistance

Insulation resistance values of Temperature Humidity cycling after exposure.

3.3.2 Application of No-Fire

the eight cartridges, which were subjected to 14 day with shielding caps in place, was measured prior to and

Current

Cartridges 47736, 47748, 47721, and 47740, were subjected to a bridge current of 1.0 amperes for a minimum duration of 5 minutes. None of these cartridges were initiated during the test, but were subsequently fired with no noticeable degradation in output characteristics.

co

68 UNITS

10 SECOND

BRUCETON TEST

IUON$IRES—=——+ !0

10 MILLISECOND

BRUCETON TEST

v ! ? v

● f v T * * v 9 !

4 /

12 4 0 2 1? 2 4 8 II

FIRES 3.5 AMPS 4.5 AMPS 3.5 AMPS 4.5 AMPS 13 AMPS 13 AMPS 4.5 AMPS FIRES

& 4 4 *

, v v

F’igure 3-l. Expenditure of Hardware n----a- om n---mu ----D

1 I

RI = 13JL CURRENT

LIMITING RESISTOR

R2= (J Iofi cuRRENT

MEASURING RESISTOR

TRANSDUCER NO. I = KISTLER

TRANSDUCER N02 =KISTLER

TRIGGER

DUAL BEAMO

SCOPE

INPUT I

o

INPUT 2

CALIBRATOR

AMPLIFIER

4b

RI ~TRANsDucER NO. I

VARIABLE

POWER

R2

10 CC BOMB VI SIC ORDER

SOURCE —

U TRANSDUCER N02

PRESSURE

CARTRIDGE d CALIBRATOR

S/N

607L OR 605B

607L OR 605B,0R DYNISCO

47736

47748

47714

47728

47721

47704

47740

47738

J?igwe 3-2. Instrumentation Block Diagr~

Insulation Resistance before after

>1. KM.~ 10M~

>1, KM~ 60 Mf_&

>1. KM~J 30M(?

>1. KM~’ 9 Ma

>1. KM~ 60 Mfi

>10 KM~~ 45 Ma

>10 KM~L 100 Mfil

>1. KMf~ 120 MO

Upper trace - voltage across bridge wire

0.5 volts/div.

1.0 msidiv.

Lower trace - pressure response 500 psi/div.

.1.0 ms/div.

Figure 3-3. Typical Pressure-Time Trace

3.3.3 Pressure-Time Measurements

Groups of pressure cartridges were exposed to specific pre-flight and/or flight envi-ronments and test fired with various currents at temperatures of from +ZO”F to +160”F.

Pressure-time characteristics were recorded. The results of the pressure-time mea-surements are listed in Table 1. Thepre-conditioning environments are shown coded from A to D, and correspond to the following conditions as described in GE specification S-133-1012-3-2-1. (Appendix C) .

(A)

(B)

(c)

(D)

Ground Vibration and Random Vibration (during random vibration the cartridge was exposed to “g” loads twice that specified).

Machine shock

Acceleration

14 day Temperature Humidity cycling.

47743

47711

47715

47707

47751

47686

47690

47744

47736

47748

47714

47728

47717

47721

47704

47740

47738

47732

47735

47719

47693

47733

47737

47722

47723

TABLE 1. PRESSURE-TIME MEASUREMENTS

Pre-conditioning

A,B, &C

A,B, &C

A,B, D

NONE

A,B, C

A,B, C

*Peak

Pressures

(psi)

‘1

P2

Time (millisec)

To Start of Pressure

2.4

2.5

1.3

2,6

3.5 ‘-

0.3

0.3

4.5

0.15

0.20

4.9

4.9

5.1

TO Peak

Pressure

2.7

1.4

2.8

2.6

2.8

3.7

0.31

0.32

4.6

4.6

0.2

0.4

5.0

5.2

5.3

Temp.

(“F)

+ 70

+ 70

+160

+160

+ 20

+ 20

Firing

Current

(amps)

13.0

*p

- From transducer 1 (Kistler607L) – PO - from transducer2 (Kistler607L)

Considerable variation in peak pressure (800 to 1650 psi) was observed during these tests. In most of the cases the output of the two transducers failed to agree. Investi-gation indicated that the transducer calibrations were varying in a random manner up to a maximum of 10%, and that transducer No. 2 was damaged. The remainder of our test program was performed using either Kistler 605B or dynisco PT 135 transducers.

Time to peak pressure for current inputs as low as 3.5 amperes and at a temperature of +20“F was well within the 10 millisecond requirement. At the recommended firing level of 4.5 amperes, the time-to peak pressure was no greater than 3.7 milliseconds, with most of the observation being about 2.7 milliseconds.

3.4 Sensitivity Tests

Sensitivityy tests were performed according to the method outlined in the “Bruceton Report”. *

The Bruceton method of statistical analysis is an experimental procedure which may be used to define the sensitivity of EEDs. With this method the pulse width of the stimulus is fixed and is either raised or lowered by a fixed logarithmic increment (d), depending upon whether the preceding observation was a no-fire or a fire, respectively.

The test can also be made by holding the magnitude of the stimulus constant and using the pulse width as the independent variable. The testing procedure consists of the following steps:

(1) Choose a stimulus (h) at which the first specimen will be tested, and an inter-val (d) which will be the difference between stimuli. On the basis of past ex-perience with EEDs it is usually possible to make good estimates of the mean firing stimulus and the standard deviation of a sample of EEDs. If (a) and (b) are the estimated mean and standard deviation respectively, then good choices for h and d are simply h = a and d = b. These may not be the best choices for all circumstances, but they will serve very well for most purposes.

(2) If the first, or any other, specimen initiates when tested at level h, the suc-ceeding specimen will be tested at level h -d. If initiation does not occur, however, the succeeding specimen will be tested at level h+ d.

* statistical Analysis pared by Statistical for a New Procedure in Sensitivity Experiments, July 1944. Pre- Research Group, Princeton University (SRG Report No. 40) for the Applied Mathematics Panel, NDRC, and redesignated AMP Report 101. R. Avail-able from DDC, No. ATI-34 558.

(3) The test is continued for the desired number of specimens, (without retesting any which were not initiated). In this manner one will obtain a sequence of initiations (marked x on the test record) and non-initiations (marked ~ from— which can be derived a mean firing stimulus and standard deviation. Desired firing probabilities with appropriate confidence are derived from the test re-sults as follows:

Firing probability, with confidence = antilog (X * Kp u + C. 1. )

C.I. = confidence interval = 0 ~K Pn c where the mean X and standard deviation 0 (from Bruceton test) are in log units.

K = constant for desired probability P

Kc = constant for desired confidence

CT = standard deviation of sensitivity test

G2+K2E12

CT =0

P n n = 1/2 total sample tested

G and H from graphs III and IV from ‘Bruceton Report

WF = weighing Factor

3.4.1 Bruceton Tests

The firing sensitivity of the pressure cartridge was determined for current application times of 10 milliseconds and 10 seconds at room temperature. Data sheets and c ilcu- Iations are in Appendix D. The results are summarized below. Table 2 lists pressure-time measurements recorded for the devices that fired during the tests.

Currents for Expected Firing Probabilities Pulse Application

Time (seconds) 0.05%* 5 o~, 99. 95%*

10.0 1.76 amps. 1.98 amps. 2.22 amps.

0.010 2.10 amps. 2.63 amps. 3.30 amps.

* with 95~0 confidence

TABLE 2. PRESSURE-TIME MEASUREMENTS

Peak

Pressure

(psi) Time (milliseconds) Firing , To Start To Peak Current

‘1 ‘2 of Pressure Pressure

Pre-Test 48577 1000 1000 Varied from 40. ms Ranged from 1.8

48598 1040 1040 to9. seconds to2.1 amperes

48572 930 930 10. See

48592 950 980 Test

48516 950 970

48618 1100 880

48595 930 850

48613 930 930

48587 1000 900

48644 960 1000

48680 980 1000

48793 1000 950

Pre-Test 48634 955 930 9.6 ms 10.Oms Ranged from2. 5

48642 950 960 10.0 10.4 to 2.8 amperes

48702 1050 1050 10.0 10,2

48646 910 960 10.0 10 ms 10”2

48693 1000 1020 9.2 Test

9,5

48696 1000 1020 9.4 9.7

48628 1070 1070 8.1 8.3

48679 950 880 8.8 9.1

48687 1250 1200 8.9 992

48684 1040 1040 8.4 8.6

48626 1100 1200 10.0 10*3k T Transducers calibrated periodically throughout tests PI and I?z rec@rded wfth Kistler transducers Mode1605B

3.5 Tests Using Bruceton Non-Fires

3.5.1 Current Application (Non-Fire Condition)

The recommended current that may be applied to the bridgewire without causing ignition is specified as 1.0 ampere, applied for 5 minutes. By plotting the no fire points from the 10 ms and 10 second sensitivity tests on a log-log scale and extrapolating to 5 min-utes we can estimate a no fire current of 1.3 amperes, or greater. To increase our confidence in the 1.0 ampere no fire requirement, 5 cartridges were subjected (S/N 48638, 48687, 48651, 48624, and 48655) to 1.25 amperes for 5 minutes, and none of the cartridges in this group fired.

3.5.2 Pressure-Time Measurements

The 20 non-fires, including the 5 subjected to 1.25 amperes for five minutes, from the sensitivity tests, were tested at various currents and temperatures. Pressure-time was recorded; and is summarized in Table 3.

The Pressure-Time response of these cartridges was seen to be fairly reproducible.

In general, pressure peak measured with the strain gage transducer (dynisco) was lower than that seen for the Kistler piezeo electric transducer. This is to be expected since the strain gage does not have the high response characteristics of the crystal transducer.

In general, the residue left in the bomb after ignition varied from shot to shot from a grayish to blackish material of approximately the same volume except for one shot where an exceedingly large quantity of carboneous like residue was produced.

This change in behavior was accompanied by a pressure-time trace that differed from all the other observations. Pressure peaked to about 970 psi and rose slowly (4 ms) to a 1000 psi and maintained the pressure for a relatively long time. This response is indicative of a “long burn” and is currently being investigated. It is possible that a potting compound, used internally in the cartridge, was applied in excess and could be the culprit. Figure 3-4 shows a typical fired cartridge, residue, and pressure trace compared to the “maverick.”

3.6 D~amic Resistance and Related Time Measurements

The dynamic resistance characteristics and functioning delay various bridgewire currents.

time were determined for

Upon application of an input stimulus to the bridgewire system of an EED the wire ele-ment undergoes resistance changes, which are related to the thermal properties not only of the wire but of its environment. The dynamic resistance characteristics and related responses of the EED often reflect functioning abnormalities that might other-wise go undetected, such as a discontinuity in the functioning time response, or

TABLE 3. PRESSURE-TIME MEASUREMENTS

Peak

Time (milliseconds) Temp.

Pressure (psi) Firing

To Start To Peak ‘F Current

PI

‘2 of Pressure Pressure

48705 980 980 2.1 2.5 160° 4.5

48585 1140 1080 2.2 2.6 amps.

48638 970 970 2.0 2.4

48650 1100 1090 2*2 2.4

48666 1090 1010 z!. 2 2.4

48658 1070 1000 2.0 2.2

48660 1100 1050 2.0 2.3

48624 1100 1100 2.1 2.4 160°

48589 1090 920 2.4 -2.6 20°

48622 1000 850 2.5

48647 1090 920 2.4

48588 980 800 2.4

48630 1040 900 2.4 I.:

48662 1070 930 2.3

48631 1000 910 2.4

48579 1050 950 2.4 =2.6 200

48651 1100 1080 2.3 2.4 70°

48652 1000 970 2.3 2.4

48599 990 970 2*4 2.5

48610 1000 990 2.4 2.6 70° amps.

‘1

- Kistler 605B transducer

‘2

- 605B at +160°F, Dynisco PT135 used at +70°, and -20°

4!

Figure 3-4. Spent Cartridges md Abnormal Residue bridgewire rupture (for high to the surrounding explosive currents), before adequate energy has been transferred to cause initiation

Dynamic resistance, or time rate of change of bridgewire resistance of EEDs, is de-termined by passing a known constant current through the bridgewire and recording the voltage across the bridge as a function of time. During these tests, functioning (delay) time is also recorded as a functioning of input current.

Table 4 lists the measurements of dynamic resistance and functioning time (time from initial application of current pulse until first pressure rise is noted) that are shown plotted in Figure 5.

3.6.1 Bridgewire Thermal Characteristics

Observations of the dynamic voltage across the bridgewire for constant current con-ditions, may be used to estimate and verify the temperature profile of the bridgewire environment. Any deviation from the expected response may indicate that marginal conditions exist between the bridgewire and ignition charge interface. If conditions exist that cause the bridgewire to heat to its melting point before ample heat is transferred to the ignition material than it is feasible that bridge burn-out could occur without initiating the pyrotechnic composition.

The current through the bridge may be considered a constant with time. The inclusion of a 13 ohm series current limiting resistor offsets dynamic changes in the bridge wire system. Voltage changes, then, represent resistance variation which are directly related to the temperature of the bridge wire environment, as expressed the equation

T=

AR=

R. =

0!=

AR

T=—

R. a , where

“c

Change in ohms

Initial resistance ohms

Temp coefficient of resistivi~

For this cartridge configuration the following information applies:

Q!of bridge wire = 0.00067

Melting point of wire =955°C

R. = O.22 ohms

Ignition charge is Lead S@-phinate with an ignition

Temperature of approximately 250”C or O.1 sec application time.

by

The example used in the following calculations is representative of all of the tested devices. The data was derived from the voltage trail of cartridge 47717 shown in Fig-ure 3 and illustrated below.

It may be concluded that the first abrupt increase in voltage is caused by the ignition of the charge surrounding the wire. The calculated value of 300”C compares favorably with the theoretical ignition temperature of 250 “C. We would expect the ignition tem-perature to be higher since the heat is applied for a relatively short time. The second change in voltage characteristic occurs at approximately 1130 “C, which is within 10% of the estimated melting point, 955 “C, of the wire. We may conclude from this study that ignition is taking place well within tolerable limits of the bridge wire system.

AR,

7“ w

~ 3.5MS

AR1 = & = 0.0445 ohms

AR2 = ~ = 0.167

T1 = .0445

0. 22(. 00067)

ARIAT

(OHMSI=C)

ohms

= 300°C , T = 0.167 2 = 1130°cO.22(. 00067) —

R2

FUNCTIONING TIME

BRIDG: CURREN? (AM:ERES

10.0 , 2.0

,0 FUNCTIONING TIME

(MILLlsEcONDs)

0.5

X2 ml

Figure 3-5. Dynamic Resistance and Functioning Time

TABLE 4. DYNAMIC RESISTANCE AND FUNCTIONING

TIME MEASUREMENTS

Current AR A T and Functioning Time

A R/AT

(Amperes) (Ohms) (Milliseconds) (Ohms/See)

47733 3.5 0.0545 4.9 Avg. 11.1 Avg.

47737 0.0545 4.9 11.1

47722 0.0545 5.1 4.9 10.7 11.1

47723 0.0545 5.1 10.7

47738 0.0545 4.5 12.1

47743 4.5 0.0555 2.4 23.1

47711 0.049 2.5 19.6 47715 0.049 2.5 19.6 47707 0.0555 2.5 22.2

47751 0.0466 1.3 2.5 25.9 20.4 47686 0.0535 2.6 20.6

47690 0.049 2.5 19.6 47744 0.049 2.5 19.6

47717 0.0445 3.5 1207

47732 13 0.0108 0.15 72.0 47735 0.0154 0.20

.19 77.0

47719 0.0154 0.20 77.0 76.

47693 0.0154 0.20 77.0

21/22

4.0 SUMMARY AND CONCLUSIONS

4.1 Pressure Characteristics

Several of the initial pressure peaks that were observed were erratic and widely dispersed. (Table 1) This was found to be due to a faulty transducer anti calibration drift in our equipment. FolIowing tests were performed using new transducers and the equipment was calibrated at frequent intervals. Some variation (out side of design goals of 940 + 100 psi) was still found to exist; but in general the pressure peaks, as recorded by the two transducer systems, were found to agree.

Figure 4-1 depicts a histogram of the average (both transducers) peak pressures re-corded during the sensitivity tests and the retests of the Bruceton non fires. The distribution of pressures, seen here, for all practical purposes may be considered normal. These readings reflect not only inherent variations from cartridge to cartridge but variation in the measuring instruments.

Based on this data, calculations were performed to define pressure reliability. Again it must be emphasised that the data reflects both cartridge and instrument at ion varia-tion; the true pressures lie somewhere between the extreme values recorded.

IL

IL

n

800 850 900 950 1000 1050 1100 I 150 1200

TO TO TO TO TO

::9 ;:9 ::9 999 1049 1099 I ::9 1199 1249

PEAK PRESSURE (P S I )

Figure 4-1. Frequency Distribution of Average Peak Pressures

It was noted that the residue remaining in the bomb after ingition varied froma grey I to a black material in a random fashion. No noticeable affect on the Pressure time response was evident due to the variation except in one case. The residue from one cartridge (out of 68 tests) was excessive (See Figure 3-4). The pressure trace deviated I from the normal expected response. Instead of rising to a peak and decaying gradu-aHy, this unit rose to about 970 psi initially and continued to rise to about 1000 psi in 4 milliseconds. This pressure was maintained for a considerable time. This I response is usually indicative of a slow burn and is possibly due to the combustion of potting compound used in excess internally in the cartridge. This problem is currently under investigation by both G. E. and the cartridge vendor. II

4.1.2 Variables Analysis

The following steps, for defining the reliability of a variable parameter, in this case pressure peak, are taken:

1.

2.

3.

4.

5.

Determine homogenei~ and normalacy of the parameter data for ‘each specific operating conditions. Tests for homogeneity of variation include Bartlettts Test, range or variance control charts. If heterogeneity exists, several alternatives are available;

may be applied.

Define specification limits

Calculate the mean ~) and either transformation, or variance weighted data

(SL) that must be met.

t the sigma (s) for each parameter.

i z=+x L,(J= -L ● n-1 n

Calculate values of K for the pc

K =SL - X

pc s parameters

Kpc is the constant reflecting reliability at a

Calculate, for a given confidence (O.95), the measured parameter.

The expression; K

2=KP+KC ~ (l-KC ) n(2f)

In) given confidence.

operational reliability of the

K 2 1/2+

( )1P z

()1 - KC2

2f

24 “ is the exact soIution for defining the factor Kpc (probability with confidence).

In our case we have defined Kpc and Kc and it is necessary to solve for Kp.

The foIlowing approximate equation is used r-

Kp=~ K

~ + (Kpc)-Kc n

2f

6. Define reliability (with O. 95% confidence) by consulting cumulative normal distribution tables for individual values of K .

Solution:

1. Based on the frequency distribution of the pressure readings we will assume a linear normal distribution (See Figure 4-l).

2. Limits (SL) = 840 to 1040 psi

3. ~, (pressure peak) = 1000 psi o, standard deviation of pressure = 67 psi

4. K ~ 1040 - 1000 pc = 0.6 (Upper Limit)

K 840 - 1000 = 0.9 (Lower Limit) pc =

5. Kp = .33 (Upper Limit)

Kp = .70 (Lower Limit)

6. Firing reliability (Upper Limit) = 63% with 95% conf.

(Lower Limit) = 76X with 95% COnf.

The analysis indicates that if future cartridges are tested under existing conditions (same instrumentation) then statistically it is feasible that peak pressures outside of the design goals will occur. These statistical variations, from a practical point of view should not affect the reliability or operation of the mated hardware (ball lock release assembly and thruster assembly). Approximately thkrty tests of the cartridge mated to the ball lock assembly performed satisfactorily.

If we take cartridge and instrumentation variations into account we can specify practical operational limits of the observed peak pressures, that will reflect desired reliability from a quality control point of view.

Pressure Specifications Predicted Reliability with 95% Conf.

1000 + 275 psi

1000 + 255 psi

1000 + 141 psi

99. 95%

99. 9%

95%

4.2 Response Time

The response time of all the cartridge was well within the specified 10 minis econds alloted. This was true from temperature environments from 20° F to 160° F. Except for two ignition times of 1.3 and 3.5 milliseconds the times ranged between 2.1 and

2.8 milliseconds.

4.3 Sensitivity

4.3.1 No Fire Sensitivity

The requirement that the cartridge shall not function when 1.0 ampere is applied for 5 minutes has been met. A sensitivity test using 10 second pulse durations defines a current of 1.76 amperes that may be applied for 10 seconds with a reliability of 99. 95% with 95% confidence that none of the items will fire. For 5 minute pulse application times, of 5 each, subjected to 1.0 ampere and 1.25 amperes, none fired.

4.3.2 All Fire Sensitivity

A firing current of 3.3 amperes applied for 10 milliseconds corresponds to a firing probability of 99. 95% with 95% co~idence. The recommended all fire current is specified as 4.5 amperes, which is more than adequate to cause ignition reliably.

Cartridges tested with 13 amperes exhibit reproducible firing characteristics, and do not indicate that any ignition problems exist due to “over-powering” the bridge circuit.

26’

5.0 RE LIABILITY AND SAFETY C ONSH)ERATIONS

5.1 Safety

5. 1.1 Electro-Static Hazards

During handling, inspection, or installation it is possible that electro-static charges stored on human operators or associated fixtures could be inadvertently delivered to the pyrotechnic device. If the static pulse discharges through the explosive material, it is quite possible, under the right conditions, that ignition may occur, resulting in damage and/or injury to equipment and personnel. It is of utmost importance that adequate safety procedures be strictly adhered to. The pyrotechnic system shall be fabricated in such a manner that electro-static discharge applied either directly to the bridgewire or from bridgewire to case shall not cause initiation or degradation of the device upon application of 200,” ()()() ergs from a 500 micro-micro farad capaciter.

5. 1.2 Electromagnetic Radiation Susceptibility

Manufacturers and users of ordnance devices are cognizant of the hazards associated with electromagnetic radiation. During its operating and non-operating life, EED?s may be subjected to RF fields of varying magnitude and frequency.

The program requirements call for a demonstrate ion of the EE D!s ability to survive an RF field with an intensity of 2 watts per square meter for the frequency range from 150 mc to 50 mc and 100 watts per square meter from 30 mc to 10,000 mc.

The requirement is not limited to the EED itself but is primarily concerned with the sensitivity of the firing circuit. The EED’s require shielding practices that will attenuate this field sufficiently so as not to cou@e harmful energy into the pyrotechnic bridgewire.

In general, the prediction of the RF hazard to an EED requires analysis of all electrical configurations associated with the device. These are:

a. E ED not connected to any other circuit.

b. Installed in electro-mecha,nical device.

co Installed and connected to firing circuit.

C ondit ions A and B are usually referred to as ~~handheld’! configurations. C ondit ion C is the “installed” configuration. Laboratory tests have been formulated to define the devices RF susceptibility by applying RF power directly to the bridgewire and from bridgewire to case.

5.2 Reliability

The pressure cartridge, based on redundant application, maybe considered alow risk component in terms of failure. The pressure cartridge design is considered sufficiently simiIar to other pressure cartridge designs which in past performance were shown to be highly reIiable. A reliability value of 0.995 has been assigned to the cartridge as a realistic value on the basis of history and past performance of the generic family of pressure cartridges.

1.:

APPENDIXES

WORK STATEMENT NO: 8245 -J5-056

AMENDMENT 4 December 1, 1966

APPENDIX A

DESIGN AND DEVELOPMENT OF

THE THRUSTER ASSEMBLY FOR THE

MK 12 RE -ENTRY SYSTEM PROGRAM

A-1

WORK STATEMENT NO: 8245-J5-056

Amendment 4, December 1, 1966

100 Scope $

1.1

THIS

General - The work shall consist of the design, development and manufacture of a Thruster Assembly. The assembly is intended for use in a re-entry vehicle for the retention and release of a shroud ‘V” band. The thruster with the ex-plosive squib assembled shall be referred to herein as the Thruster Assembly.

AMENDMENT TO THE BASIC WORK STATEMENT MODIFIES THE ORIGINAL

WORK STATEMENT AND IN ANY INSTANCE OF CONFLICT THIS AMENDMENT

GOVERNS.

1.2 Specific - The subcontractor shall provide the necessary personnel and equip-ment to accomplish the following:

1.2.1 Phase I

Provide a thruster assembly capable of meeting the requirements specified in Paragraphs 3. 12.1 and 3.12.2. The responsible GE-RSD Engineer shall review the design before the subcontractor finalizes the design details.

1.2.2 Phase II

Fabricate and development test pro&ype models. The models tested by the subcontractor shall be witnessed by the GE-RSD Engineer to assure com-pliance to the requirements given in Paragraphs 3.12.1 and 3.12.2.

1.2.3 Phase III

Deliver to GE-RSD complete thruster assemblies as scheduled in Para-graph 4.0. The subcontractor shall provide and maintain a Quality Control Pro-gram to insure all details and assembly of the thruster are inspected, and that in-process records show compliance with specifications and drawings. This program shall be subject to review by GE-RSD Quality Control representatives.

This work statement requires source inspection and preliminary acceptance at the subcontractor?s plant. The inspection shall include verified acceptance on the subcontractor?s shipping documents and shall be conducted by either or both Air Force and GE-RSD inspectors.

2.0 Applicable Specification

2.1 General - This work statement shall take precedence over any specification where a conflict in specification arises.

A-2

2.2 t.

2.3

WORK STATEMENT: 8245 -J5-056

Government Documents - The following government documents of the issue listed, form a part of this work statement and the thruster assembly must satisfy these requirements.

MIL-S-’7742A Screw Threads, Standard, Optimum 21 June 1963 Selected Series, General Specification

MIL-I-8500B Interchangeability and Replaceability 10 October 1960 of Components, Parts for

MIL-STD-130B

24 April 1962

MIL-STD-463

29 October 1962

MIL-STD-810

14 June 1962

64A51300

MIL-STD-202

Non-Government Documents

Identification, Marking of U. S. Military Property

Inspection, Radiographic

Environmental Test Methods for Aerospace and Ground Equipment

Finishes and Coatings

Test Methods for Electronic and Electrical Component Parts

- The following non- ~overnment documents formu w a part of this work statement.

S0070-02-0016 Supplier Reliability Program and Configuration Control Requirements for Cartridge Pressure

SO070-03-OO04 Supplier Failure Reporting and Analysis Requirements

SO070-03-0005 Test Procedures and Reports

389L491 Selected Parts List

SO020-02-0001 Internal Environmental Requirements (Qualification) for Mark 12 R/S

3.0 Desi gn Requirements

3.1 Materials - Materials used shall be of a type, grade and quality which is suffi-cient to ensure the proper operation of the thruster assembly in conformance with specified design requirements.

A-3

3.3

3.4

3.6

3.7

3.8

3.9

3.10

3.11

3.12

A-4

WORK STATEMENT: 8245-J5-056

Dissimilar Metals - Dissimilar metals, as defined in MS 33586, shall not be used in intimate contact unless suitably protected against electrolytic corrosion.

Corrosion Resistance - Materials selected shall be corrosion resistant or shall be suitably protected by plating, painting or other surface treatment selected from Drawing 6~51300.

E!!2?w - Materials which provide nutrients for fungus shall not be used in this design.

Assembly - The thruster assembly shall be capable of being assembled into the next higher assembly with standard tools and shop practices.

Screw Threads - Unified screw threads conforming to the requirements of specification MIL-S-7742 shall be used throughout the component.

Dimensions - The configuration and overall dimensions of the thruster assembly shall not exceed the envelope of GE Dwg. ER 66C49114.

Wei@t - The thruster assembly weight shall be held to O.3 pounds (max) con-sistent with good design practice. Prior to final development and/or manufacture of the assembly, an estimated weight shall be determined.

Storage - Thruster assembly shall be capabie of being stored for a period of five (5) years without affecting its operating characteristics.

Identification - The thruster assembly shall be marked for identification as de-fined in MIL-STD-130.

lhterchangeability - All components having the same manufacturer’s part num-ber shall be directly and completely interchangeable with each other. The thruster assembly shall be interchangeable or replaceable to the extent required by MIL- I- 8500.

Performance - The assembly shall be capable of the following performance before and after exposure to the conditions specified in paragraphs 3.13 and 3.14.

3.12.1 Squib Performance

3.12. 1.1 All Fire Current - The “all fire” current shall not ex-ceed 4.5 amperes applied for 10 milliseconds at ambient temperatures.

Reliability shall be O.9995 at 95% confidence.

3.12. 1.2 No-Fire Current - The ?tno- fireft current shall exceed

1.0 ampere and the squib shall not fire when one ampere is applied for 5 minutes at ambient temperature.

confidence.

3.12. 1.3 Auto-ignition - The be greater than 250”F.

Reliability shall be 0.9995 at 95% auto-ignition temperature shall

3.12. 1.4 BridgeWire resistance - The bridgewire resistance shall be O. 25 tn O. 30 ohms.

3. 12.1.5 Insulation Resistance - The insulation resistance of the squib shall be 100 megohms minimum. The measurement shall be made between shorted circuits and between each shorted circuit and the case the current shall be limited to O. 050 amperes. AU units shall be tested in accordance with Method 302, Test Condition B of MIL-STD- 202.

3.12. 1.6 Static Discharge -electrostatic discharge of 200,000

3.12. 1.7 Pressure Output -

The squib shall be subjected to an ergs from a 500 ~ pfd capacitor.

The squib shall be capable of devel-oping 4000 psi * 800 psi in a L(). O cu. cm. closed bomb in 5 milliseconds when fired with a minimum of 4.5 amperes of current at ambient tem-peratures.

3.12. 1.8 RF Sensitivity Requirement - No squib shall exposed to the following RF environment:

fire when

Frequency Range Field Intensity

150 kc to 50 mc 2 watts/square meter 50 mc to 10,000 mc 100 watts/ square meter

3.12. 1.9 Circuits - The squib shall have a single bridge circuit, a continuity monitor circuit removed from the explosive cavity and a ground circuit consisting of one connector pin connected to the body.

3.12.1.10 Explosives - All explosive materials shall consist of readily available material and neither the materials nor manufacturing processes will be proprietary in nature.

A-5

3.12.2

WOItK STATEMENT NO: 8245-J5-056

3.12.1.11 Seals - All explosive containing areas shall be sealed to the extent that they will not leak helium at a rate greater than 1 x 10-6 cc per second when exposed to a pressure differential of a standard atmosphere.

3.12.1.12 Shielding Cap - Each squib shall be fitted with a shield-ing cape

3.12.1.13 Continuity monitor circuit resistance - The resistance of the continuity loop shall not exceed O.1 ohm.

Thruster Assembly Performance

3.12. 2.1 Thruster assemblv action. - Upon application of the firing current to the squib the thruster action shall take place in less than 10 milliseconds.

3.12. 2.2 Separation Time - The thruster assembly separation time shall be reproducible within 1.5 milliseconds, but the vendor shall have a design goal of O.5 milliseconds & O.25 milliseconds.

3.12. 2.3 Impulse - The thruster assembly shall be capable of providing a minimum of three (3) pound-seconds impulse to the separable elements when preloaded from O to 7500 pounds.

1..,

3.13 Service Conditions - operating - The thruster assembly shall be capable of operating while exposed h the following powered flight conditions:

(a) Shock Powered Flight - 3og - one half sine pulse for 0.5 ms in each direction along each of three mutualIy perpendicular axes.

(b) Acceleration - 21 g all axis

(c) Temperature - + 50° to+ 160”F

(d) Power Flight - Acoustic Noise 2

- 150 db overall (ref. O.0002 dynes/tin )

(e) Vibration - Random - see figure 2

(f) Atmospheric Pressure - 0 psia

A-6

3.14

3.15

--.———--— .—— - -—--— ---- ---- - A--

WORK STATEMENT NO: 8245-J 5-U56

Service Conditions - Non-Operating - The thruster assembly shall be capable of operating after being exposed to the following transportation, storage, handling and pre- flight conditions:

(a) Shock - handling shocks up b 100 g~s

(b) Temperature - -35°F to + 160”F

(c) Vibration - Transportation (unpackaged)

Frequency Acceleration

5 to 50 Cps 3.5 grins

50 to 300 Cps 1.5 grins

(d) Humidity - 100% RH at temperatures up to 135°F

(e) Sand and Dust - MIL-STD-81O, Method 510

(f) Fungus - MIL-STD-81O, Method 508, Procedure I

(4 Salt Spray - MIL-STD-81O, Method 509

(h) Pressure - 19.5 to O psia

Environmental Conditions - The thruster assembly shall be capable of satisfactory operation after being subjected to the following environmental test requirements:

3.15.1

3.15.2

3.15.3

Vibration - Transportation (unpackaged) - The thruster assembly shall be exposed to the sine tests delineated in Figure 1, along each of three mutually perpendicular axes.

Vibration - Powered Flight - The thruster assembly shall be exposed to a random vibration test as depicted in Figure 2. The vibration shall be applied along each of three mutually perpendicular axes.

Acceleration - The thruster assembly shall be subjected along the longitudinal axis and one lateral axis to an acceleration of 21 g + 0.5 g-O. O g for two minutes, per axis.

A-7

SINUSOIDAL

FREQUENCY RANGE 5 - 50 Cps 50 - 300 Cps

TEST AMPLITUDE 3.5 g rms 1.5 g rms 4 1 *

NOTES:

1. The sinusoidal vibration shall be swept from 5 to 300 cps at a constant (one-half) octave/minute sweep rate for two complete up and down sweep cycles.

2. Limit vibration to 0.4 inch double amplitude.

Figure 1. Vibration Tests

3.15.4

3.15.5

3.15.6

3.15.7

3.15.8

3.15.9

A-8

Temperate - Humidity - The thruster assembly shall be subjected to MIL-STD-304, 14 day cycle, with the exception that the low tempera-ture shall be -35°F.

J:

Machine Shock - While non-operating and unpackaged, the thruster assembly shall be subjected to one (1) terminal peak sawtooth shock pulses, as defined by Figure 3, in both directions through the equip-ment mounting points along each of three (3) mutually perpendicuhx axes (6 shocks).

Shock Powered Flight - The thruster assembly shall be subjected to a 300 g, O.5 ms half sine shock pulse. One pulse shall be imparted to the component successively in each direction of three (3) mutually per-pendicular axes (6 shocks).

El!%!!E - The thruster assembly shall be exposed to MIL-STD-81O, Method 508, Procedure 1.

Sand and Dust - The thruster assemblv shall be exoosed to MIL-STD- U

810, Method

Salt Spray - Method 509, 510.

The thruster assembly shall be except that the high temperature exposed to MIL-STD-81O, shall be limited to 135°F.

3.15.10 Temperature/Altitude, Unpackaged - The thruster assembly, unpack-aged, shall be subjected to the tbllowing temperature, time histnry at the pressures indicated for three cycles.

Duration (hours) Temperature (degrees F) Pressure

1/2 amb. to 1600F 14.7 psia 8 at +160° F 14.7 psia 1 +160° F to -35° F 14.7 psia 8 -35°F 1.7 psia 1/2 -35° F to amb. 14.7 psia 1 at amb. 14.7 psia

3.15.11 High Temperature/Altitude - The thruster assembly shall be placed non-operating in the chamber and the chamber cooled to a temperature of 50°F. After temperature stabilization, the cartridge shall be condi-tioned at 50”F for a period of 8 hours. Air velocity through the chamber shall not exceed 10 mph. At the conclusion of the 8 hour period, the chamber temperature shall be increased to 160° F at a maximum rate of of change of 1.8 degrees F per second. After test item temperature stabilization and while maintaining the 160° F chamber temperature, the chamber pressure shall be reduced to a pressure of 10-1 torr over a period of from 7 to 10 minutes. Upon completion of this test return the conditions to ambient.

3.15.12 Time Pressure Test - The squib shall be fired at the following tem-peratures using 4.5 amperes into an enclosure having a total volume equivalent to the device or system which it is to operate. From the application of current to ignition shall not exceed 10 milliseconds. The firing temperatures shall be:

a. ambient

b. 160°

c. 50°

NOTE A: The squib shall meet the test requirements of S0020-02-0001-6 paragraph

4.7. The vendor shall submit a cost and schedule for manufacturing sufficient squibs to meet the qualification test requirements of S00 20-02- 0001-6, para 4. 7.3 and special test requirements of S0020-02-0001-6, para 4.7.5. Authorization to proceed with manufacturing these squibs will be negotiated by a future amendment to this work statement.

A-9

WORK STATEMENT NO: 8245-J5-O 56

NOTE B: A qualification test program to demonstrate the ability to meet these environmental requirements and qualify the design shall not be a part of the work specified in this work statement. Qualification tests shall be conducted by the General Electric Company at their facility. GE?s conducting of the test does not remove the vendor’s responsibility to produce acceptable parts. The vendor may witness the subject tests if he desires. Failure of any thruster assembly or squib during qualifi-cation testing shall reject the lot.

4.0 Drawings, Reports and Schedules

4.1 One reproducible and two copies of assembly and detail production type drawings, test fixtures and electrical schematics shall be delivered as indicated in para-graph 4.4.

4.2 Progress reports shall be submitted weekly in letter form with 3 copies to

General Electri~ Company, RSD 3198 Chestnut Street Philadelphia, Pa. 19101

Attn: J. G. Smith Room 6509

4.3 A complete detailed engineering report shall--be in one reproducible and four…