LSG BOYD BOLT RELEASE TEST REPORT 1 .... 1 ~ •• _ 8 ~

OAT~ 20 Septa 1971 .

This ATM documents the System Safety Analysis performed on the LSG Boyd Bolt Interface.

Prepared by: W. Lav1n, Syst m Safety Engineer

Approved by: ~-..,.,1"-~--r--f-A-'-"-_;;:_--"'----­s, Supervisor

A pport Engineering

LSG Experiment

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IATM 1057

LSG Boyd Bolt Release Test Report 2 8

~ 1 DATI! 20 Sept. 1971

1. 0 INTRODUCTION AND SUMMARY

I. 1 Purpose

The purpose of this ATM is to perform a "worst case" analysis of LSG/Boyd Bolt interface using the data recorded at the tests performed at Arthur D. Little Incorporated on 15 July through 21 July 1971 to determine the inherent safety of the design.

1. 2 Background and Summary

In ATM 1017, Gross Hazard Analysis- LSG, published 11 June 1971 9

the LSG Subpack No. 1 interface was identified as having a potentially cata­strophic safety hazard. It was theorized that release of boyd bolts or boyd bolt failure on the LSG Experiment could cause possible damage to equipment or personnel since release of the bolts also releases the energy stored in the sun­shield. The sunshield on the LSG has a tensile preload of 1200 to 2000 lbs. divided equally among the four bolts. See Figure 1.

This analysis was performed in accordance with A TM-9 35, "System Safety Program Plan for ALSEP Flight Array E 11

• The results of this analysis and the test show that the normal release of the boyd bolt does not present a safety hazard.

However, under a highly unlikely situation of a boyd bolt failure and using 11worst case'' assumptions, it can be assumed that a failed bolt can strike an astronaut EMU. The effect of a failed bolt upon the integrity of an EMU cannot be determined sufficiently at this time to classify the hazard as Safety Negligible.

2. 0 GENERAL DESCRIPTION OF TESTS

Two sets of tests were performed at A. D. Little, Incorporated. Both sets of tests were made using the LSG structural model.

The first tests were performed to determine the deflections within the LSG Experiment under various preloads, to ascertain whether permanent dis­tortion occurs within the instrument and to determine the axial loads on the bolts after release of each bolt for the three possible release sequences. A vernier height gauge was used to determine deflections and load cells were

.ATM 1057

LSG Boyd Bolt Release Test Report 3 8

DATi: 20Sept. 1971

used in measuring the tension in the bolts. The preloading was accomplished using 1/4 - 20 stainless steel bolts.

The second set of tests were performed to determine the axial load imp.arted to the Universal Handling Tool (UHT) and the torque required on the UHT to release the bolt. Serialized boyd bolts were used for the release. Data obtained from the first set of tests was utilized in setting the preload on the LSG Experi~ent for the second series of tests. After the preload was set, releases we:re'performed using a UHT simulator. In the final test at 2000 lbs. the bolts were removed using a crew training model UHT.

Releases were recorded with two cameras. Camera No. l used a normal lens and recorded pictures at 64 fps. The viewing angle permitted recording a view of the total experiment during releases. Camera No. 2 used a telephoto lens and focused on the vibration fixture, boss, boyd bolt guide cup, and UHT simulator head. Film speed was 45 to 50 fps.

A third camera was used during significant releases when the LSG was preloaded to the 2044 lb. and 2000 lb. level. This camera recorded the same view as camera one. The f-rame rate was approximately 500 frames per second. The camera recorded timing marks every. 01 second for exact timing calculations. This camera was used to record the total time it took for the sunshade to rise.

In addition to the film the comments of the crew engineering representa­tive who performedthe releases was also recorded.

Releases were performed at· the following LSG pre1oads:

1) 1101bs. 2) 286lbs. 3) 385 lbs. 4) 638 lbs. 5) 946 lbs. 6) 1364lbs. 7) 1600 lbs. 8) 2044 lbs. 9) 2000 lbs.

A more detailed description of the tests and the recorded data is given in Appendix A, "Boyd Bolt Tests", Arthur D. Little, Incorporated.

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~TM 1057 I LSG Boyd Bolt Release Test Report 4 8

DATil! 20 Sept. 1971

3. 0 ANALYSIS

The energy which is capable of propelling boyd bolts is stored in the LSG by means of deflection of the LSG Experiment. The deflection is divided among the following assemblies.

a. Axial deflection within the instrument {insulating cones and bending of the instrument housing cover)

b. Bending of top shade beam c. Bending of shade hinges d. Elongation of upper shade e. Bending of "T-beam" at lower end of upper shade

After release of the four bolts holding down the instrument, all com­ponents of the preloading system return to their normal unloaded position. No permanent deformation of parts occurs. This is shown by the no load boss to fixture clearance with the boyd bolts finger tight. The clearance varied from .093 inch to .096 inch and averaged .095 inch over the period of the testing. This variation is insignificant with regard to the total deflections of the LSG. Since deformation did not occur the LSG deflection can be regarded as pure spring deflection, that is, the energy stored is identical to that stored in a spring.

There are three methods that can be postulated in which the energy stored in the LSG Experiment may be hazardous to personnel or equipment. They are as follows:

1. During release of the boyd bolt on the LSG enough energy is imparted to the astronaut to throw him off balance.

2. Since the UHT does not have the capability of removing boyd bolts and the sunshade is a relatively stiff mechanism, after the first bolt is released, release of the second bolt on the same side of the sunshade may allow the sunshade to rise further and propel the bolt that is not being restrained by the UHT and astro­naut force. See figure 2.

3. Failure of the bolt while the LSG is preloaded may cause the LSG to propel the bolt with sufficient energy to damage equip­ment or injure personnel.

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" TM 1057 r- .... .,. r- ~

LSG Boyd Bolt Release Test Report 5 8

DATI! 20Sept. 1971

3. 1 Analysis of Problem No. 1 - Normal Boyd Bolt Release

The LSG Experiment can be regarded as a spring restrained by four bolts. The total energy stored in the spring is defined by the following equation.

E = 1/2 KX 2 p

where K is the force constant of the spring and X is the distance that the spring is displaced.

K can be calculated using the following relationship:

F = KX

F is the spring force and X is the distance the spring is displaced.

At 2000 lbs., as shown in the last release test, the total displacement averaged • 081 inch.

F = KX 2000 lbs. = (K)(. 081 in)

24, 700 lbs /in= K

The total energy stored in the LSG deflection under a 2000 lb. preload is:

E = 1/2 KX 2

E = 1/2 (24, 700 lbs /in) (. 081 in)2

E=8l.Oin.lbs. E = 6. 75 ft-lbs.

This is a worst-case calculation since the preload is at the maximum specification limit.

The energy is not released with the release of a single bolt 9 and depending on the sequence the amount of energy released varies. There are basically three possible release sequences in which the amount of energy varies.

¥\ TM 1057

LSG Boyd Bolt Release Test Report 6 8

DATi: 20 Sept. 1971

The release sequences are:

1. Bolt 1, 3, 2 and 4 2. Bolt 1, 2, 3 and 4 3. Bolt 1, 4, 2 and 3

See Figure 3.

Using the data from the load versus shade deflection tests performed on 15 July and 16 July, the total energy released can be calculated by deter­mining the total energy remaining in the sunshield. The energy released with the release of each bolt is given below as a percentage of the total energy stored in the LSG.

Release Seg,. No. 1 Release Seg,. No. 2 Release Seg,. No. 3

Bolt No. 1 - 45% Bolt No. 1 - 45% Bolt No. 1 - 45% Bolt No. 3 -- 36% Bolt No. 2 - 53% Bolt No. 4 - 41% Bolt No. 2 - 17% Bolt No. 3 - 2% Bolt No. 2 - 14% Bolt No. 4 2% Bolt No. 4 - O% Bolt No. 3 - O%

From this it can be seen that the maximum stored energy that can be released from the release of a boyd bolt is 53% of 6. 75 ft-lbs. or 3. 58 ft-lbs.

3. 2 Analysis of Problem No. 2 - Throwing of a Previously Released Boyd Bolt

In the release tests performed at Arthur D. Little Corporation, the released boyd bolts were not removed from the sunshade in order that this possibility could be investigated. The cameras were arranged so that the rear bolt could be viewed if it were thrown into the air. In the last release test, using release Seq. No. 2 at a 2000 lb initial preload, upon release of bolt No. 2, Bolt No. 1 was thrown approximately 1/2 inch into the air. In lunar gravity this would be approximately 3 inches and using a 1 OOo/o safety margin about 6 inches.

ATM 1057

LSG Boyd Bolt Release Test Report 7- .@f 8

DATI 20 Sept. 1971

3. 3 Analysis of Problem No. 3 - Boyd Bolt Failure

From the analysis performed for boyd bolt release it can be seen that failure of a bolt will release forty-five percent of the energy stored in deflec­tion of the LSG. The total energy stored can be as much as 6. 75 ft. lbs. This means that 3. 04 ft-lbs. of energy are released upon failure of a bolt. The weight of a 2363296-214 boyd bolt with nut, spring, and guide cup attached is less than • 01 lb. on the Lunar Surface. If all the stored energy is released into the boyd bolt, it can be thrown several hundred feet.

4. 0 CONCLUSIONS

4. 1 Normal Boyd Bolt Release

During normal boyd bolt release, no more than 3.' ft.-lbs. of potential energy are released from the LSG Experiment. It is within the capability of an astronaut to absorb this much energy while deploying the LSG Experiment. The Interface Control Specification for Astronaut/ ALSEP E, IC 314134, states that the astronaut can provide steady state forces as high as 20 lbs. and dynamic forces as high as 60 lbs. A 20 lb. fon:.e would permit the boyd bolt to rise • 18 ft. This is not sufficient to constitute an astronaut hazard.

4. 2 Throwing of a Previously Released Boyd Bolt

From the high speed film taken of LSG boyd bolt releases it has been determined using a 1 000/o safety margin that a previously released boyd bolt cannot be thrown more than 6 inches on the lunar surface. This does not present a safety hazard.

4. 3 Boyd Bolt Failure

Theoretically, on the lunar surface, if all the potential energy released upon failure of a bolt is transferred into the bolt, then it can be thrown several hundred feet. This distance may be calc-ulated using the following equation.

E = Wd

E = energy in ft-lbs W = weight in lbs d = distance in feet

3. 04 = (. Ol)(d) 304ft = d

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~TM 1057 H

LSG Boyd Bolt Release Test Report 8 8 · PAGfl- CF-

DATil! 20 Sept. 1971

However, all the potential energy stored in the LSG cannot be released into the bolt upon failure. A fast release does not translate all potential energy into kinetic energy and much of the energy would be consumed in twisting of the sunshade and shearing of the bolt, but these ;values cannot readily be determined analytically. It can, though, be reasonably assumed that the bolt can fly at least several feet upward upon failure.

The failed bolt may strike an astronaut EMU. It is by this means that it may create a potential hazard. Although the impact would be at a low energy level, it is not known whether the EMU has the capability of withstanding the impact that would result from failure of a bolt.

It may be noted that failure of boyd bolts used in the LSG installation is a highly improbable situation. Nominal preload is 400 lbs. per bolt. Maximum preload is 500 lbs. per bolt. Tests con~ecl in 1968 and documented in ATM 807 indicate that normal installation (torquiag the ESNA nut to 44 in-lbs) produces axial loads of 500 lbs. Destructive testing of bolts, also documented in the san1e ATM shows that boyd bolts fail with axial loads of greater than 1000 lbs. This presents a 2. 0 safety factor at maximum preload. It should also be noted that boyd bolts have never failed in this manner when properly installed and it must be remembered that in order for the boyd bolt to possibly present an astronaut hazard, it must fail in the specific interval of time that the astronaut would be in the proximity of Subpackage No. I.

In summary the effect of a failed bolt upon the integrity of an EMU can.•·wt be determined sufficiently to permit classifying the hazard as safety negligible. Based on the fact tha.t boyd bolts will withstand twice the axial loads required in LSG installation and the failed boyd bolt would be a low energy projectile with no sharp edges, it appears that the potential hazard is an acceptable risk for an astronaut to take.

It is recommended that the potential hazard be reported to the MSC System Safety Office as a residual hazard with a recommendation that the capability of the EMU to sustain the impact of a low energy projectile be determined.

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LUNAR SURFACE GRAVIMETER I

.. Bendix Subcontract SC-850 C-73007 AUGUST 10, 1971

BOYD.BOLT.TESTS

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MEMORANDUM

To: G. Parish. Case: , 7300i-l5 Date: 6 August 1971 Page: 1 of 5 t.

Subject: Boyd Bolt Tests

I. INTRODUCTION

Under Change Order No. 10 (Bendix TWX No. S-1370) dated 8 July 1971, Arth~r

D. Little, Inc. was directed to perform the tasks described in the test outline

of BXA TWX S-1354 dated 6 July 1971. The purposes of the tasks were to obtain

defl~ctions of the gravimeter shades uttder various c~nditions of bolt loads and,

under the direction of Bendix, the human factorc; assessmer..t of the effects of

Boyd Bolt relea$e. These tasks were completed in the month of July 1971.

II. TASK DESCRIPTION

There were two series of tests and/or measurements performed. Th,ese were

defined in Bendix TWX S-1354 and this telegr8Jll is repeated here.

SERIES I TESTS

This serie& of tests is to be conducted using the structural model and con­

ventional high strength bolts. Instrumentation to determine load in each bolt

and deflection of the sun shade at various locations is required.

A. Determine deflections vs gim~al preload at the following

locations for a gimbal pr.eload range of 1200 to 2000 pounds:

1. Across top shade

2. Across top shade hinges

3. Across lower T-beam of the upper shade~

4. Elongation of upper shade

5. Total gap between upper shade and bolt receptacle.

B. Determine repeatability of item A-5 above

C. Determine method of preloading sun shade to obtain gap compatible

with :Scyd Bolt length before Bolt installation if such preloading

is required.

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At;;l · 115-869 Arthur D Little. Inc

•

,

MEMORANDUM - ....... ___...

To: G. Parish. Case: 73007-15 Date: 6 August 1971 Page: 2

Subject: Boyd Bolt Tests

(Upon completion of Items A and B, Bendix will advise ADL whether or not

Boyd Bolt installation is feasible without a preload on the sun shade.)

D. Determine load in each bolt after installation per determined pro­

cedure and after release of each bolt for the following sequences of

release:

1. Diagonal 1-3, diagdnal 2-4

2. Short side 1-2, short side 3-4

3. Long side 1-4, long side 2-3

E. Determine changes in deflections listed in Item A at release of each

bolt per sequences listed in Item D.

SERIES II TESTS

These test are to be conducted using the structural model, Boyd Bolts, and

UHT to determine astronaut interface loads. The following measurements are to

be made when releasing the bolts in the sequences listed in Items D-1,, D-2, and

D-3 above.

A. Axial load imparted to Universal Handling Tool (UHT)

B. Torque required on UHT to release bolt

ADL was not required to reduce the test data. It is to be noted that in

Series I, A, 4, elongation is a derived quantity and not a direct measurement.

III. INSTRUMENTATION AND ACCURACY

SERIES I

The attached ADL photographs 11379-1,2,3 and 4 show the instrumentation used

for the Series I tests. Photograph 1 shows how one strain indicator was used with

a bridge switching and balancing network to ~ead the strain (load) in the four bolt

load cells. Photograph 2 is a view of the +Y side of the gravimeter with the load

cells installed and photograph 3 includes the vernier height gage in combination

with a dial indicator for the deflection measurements. A close-up view of the in­stalled load cell is shown in photograph 4.

Frmn........................................................................................ Bldg./Room ............................ Ext ........................... .

ADL-1 15-669 Arthur D Little, Inc.

•

,_.

~EMORANDUM

To; G. Parish· f •

Case: 73007-15 Date: 6 August 1971 Page: 3

Subject: Boyd Bolt Tests

The structural model was used for all Series I and II tests. The model con­

sisted of all shades without cable restraints and with the detent mechanism made

inoperable. The gimbal housing, instrument housing and cover were assembled

according to the latest drawings. However, the instrument housing was empty of

parts and open to the atmosphere. Also included were the inner and outer container

completely assembled. The insulating cones were installed according to the latest . configuration including the dusting of the cone surfaces. There was no other in­

sulation. In summary, all of those elements that are in the load path were included

in the assembly. The gravimeter was mounted to the vibration fixture (Drawing

4009-009, Rev. A) which was three-point supported on an inspection surface plate.

The vernier height gage was also on this surface plate so all dimensional data was

referenced to the same flat surface. Gross fixture distortion was calculated at

a conservative 0.002 inches (at 2000 pounds) from the center to edge of the fixture

and the 3-point support was located to minimize this effect.

The vernier height gage was checked (re-zeroed) before and after any one set

of readings (one load condition) by re-measuring the height of an arbitrary ref­

erence block which also r~sted on the surface plate. The vernier height measure­

ments were read and recorded to the nearest 0.001 inch and the accuracy of the

system was +0.0005. All readings were made by two individuals.

The load cells were 1.5 inch long, 6061-T6 aluminum tubes, 3/8 OD with a

wall thickness of 0.049 inches. Each tube was instrumented with a 4 arm Wheatstone

bridge using foil strain gages to achieve independence of torsion, bending and

temperature effects. The cells were cycled in compression and calibrated (trace­

able to NBS) to 1000 pounds each or a material stress of 20,000 psi. The individual

load cell sensitivity was 5.18 micro-inches per pound and readings w~re made and

recorded to the nearest micro-inch or 0.2 pounds. From the beginning to end of

the Series I test (two days) there was a net drift (or zero shift) of the load

cells. of an aver€lge + 10 micro-inches or + 2 pounds. The recorded total load in

the data sheets was accurate to ± 1/2 percent and at the same time individual bolt

loads were within the desired load by ! 2 pounds at a total load of 1200 pounds

and + 5 pounds at the maximum total load of 2,000 pounds.

Fro1n ....................................................................................... . Bldg./Room ............................ Ext ........................... .

ADL-115-869 Arthur D Little, Inc

MEMORANDUM

, To: G. P~rish. Case: 73007-15 Date: 6 August 1971 Page: 4

Subject: Boyd Bolt Tests

Bolt threads, nuts and washers were coated with Mos2 to reduce friction for

smooth load changes. The bolts were 1/4-20, 303 stainless steel mated with con­

,ventional steel nuts.

It is of interest to note that the load indicator beam in the top shade was

accurately indicating the total load. This feature was used in 'the Series II

tests to verify total load (in addition to measured deflections).

SERIES II

The basic instrumentation for the Series II test were 16mm motion picture

cameras with color film. The background contained a 2 inch square grid and at

the bolt location was included a inch scale and a 1/2 second division stopwatch.

One battery operated camera, with a telep~oto lens operated at 45 to 50 frames a I

second and recorded a close-up of the bolt location including reference marks on

the UHT. A second spring would camera with a no~l lens recorded the entire

assembly, but riot including the operator's hand, at 64 frames per second. Part

way through the tests, a Fastax camera was employed. This camera, also with a

telephoto lens, operated at about 500 frames per second and timing marks at 1

millisecond intervals were included along the edge of this film. The purpose of

this camera was to define the deflection vs time data of the UHT in order to

deduce the force pulse to the operators hand. A direct measurement of this force

was considered ambiguous. Viewing all of the film will make the above description

obv~ous. All cameras were maintained in a fixed position and the gravimeter was

turned to position the bolt of interest in the field of view. The telephoto lens

and normal lens cameras were mounted on their tripods in an inverted position to

maintain a horizontal field of view. The Fastax camera was in a normal upright

position.

One torque measurement of Boyd Bolt release ~as made using a Bendix torque

wrench and is so reported in the data.

The basic approach to installing the Boyd Bolts with known axial loads (any

reasonable instrumented load cell would be impossible to use with these bolts)

was as follows:

Fron1 ....................................................................................... . Bldg./Room ............................ Ext. .......................... .

AOL-115-8i>9 Arthur D Little. Inc

MEMORANDUM

To: G. Parish.

-·~· ... --Case: 73007-15 Date: 6 August 1971

Subject: Boyd Bolt Tests

Page: 5

The assembly was bolted down with four conventional bolts to a predetermined

shade~to-fixture clearance. From the Series I tests and other tests these clear­

ances were directly related to known bolt loads. Then, one at a time, the conven­

tional bolts and nuts were replaced with Boyd Bolt assemblies to achieve the sarue

clearances. In effect, the gravimeter was preloaded (or predeflected) by this

method. In other instances, the Boyd Bolts themselves were used to produce the

desired deflections. In no case were the load cells used with conventional bolts

in this process because there was no assurance that a load was maintained after

Boyd Bolt substitution. Deflection (or clearance) measurements were just as

accurate and considerably more convenient. The examination of the Series I tests

and experience showed that although individual bolt loads could be made to be

different by a considerable amount, the total desired load could be achieved quite

,accurately. Furthermore, as individual bolt loads were controlled as desired,

defl~ctions and clearances were fairly reproducible.

As the tests progressed to higher total loads, the shade-to-fixture clearance

method of determining individual bolt load was augmented by the total load indica­

tor pin measurement which had been shown to be accurate and very reproducible.

IV. TEST RESULTS

The test results of both series of tests are included with this report in

raw form as the data was recorded. Series I test results are presented in the

first 19 sheets. Series II test results are presented in the last 6 sheets and

describes the development of the loads, the photographic notation on the 16mm film,

and the operators Boyd Bolt release comments.

Also included as data with this report is one copy each of the 8 reels of

unedited 16mm film obtained during the Series II tests.

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