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Aerospace ' Systems Division

ALSEP FASTNER REDUCTION STUDY

FINAL REPORT

ALSEP FASTNER

REDUCTION STUDY

Submitted in Partial Fulfillment of Requirements

of CCP 90

Prepared by: J. H. Owens, Jr.

Approved by: ----~~~~~~~~------------------M. gineer

/Thermal Engineering

NO. REV. NO.

ATM-816

PAGE OF

DATE October 17, 1968

,

ALSEP Sunshield Pallet

Fastener Tie Down Investigation

1.0 SCOPE

This report covers a design and analysis investigation of the ALSEP compartment #1 sunshield pallet fastener tie down system, with the purpose of reducing the number of fasteners that the astronaut must release at time of deployment.

2.0 REFERENCES

(1) Drawing No. BSX 7517 ALSEP Revised Fastener and Pin Pattern - Sunshield Pallet

(2) Drawing No. BSX 7518 ALSEP Revised Fastener and Pin Pattern - Thermal Plate and Primary Structure

{3) Introduction to Matrix Methods of Structural Analysis -H. c. Martin, McGraw Hill Book company.

(4) Inderdepar~mental Memo 68-210-24M "ALSEP Compartment #1 Fasteners Reduction Study"

(5) Interdepartmental 68-210-37M "Summary Report of Changes to ALSEP Structure to make Smaller Number of Fasteners Possible.

(6) Internal Memorandum 1/17/68 toT. Fenske from J. Maszatics, D. Dewhirst, Subject: ALSEP Safety Factors and Limit Load Factors.

(7) "Dynamics of Structures" - Walter c. Hurty, Moshe F.

(8)

(9)

(10)

(11)

Rubinstein, Prentice-Hall, Inc. Englewood Cliffs, New Jersey.

Drawing No. 2330203 - Primary Structure Assembly

Drawing No. 2330301 - Basic Assembly Primary Structure

Drawing No. 2335161 - Sunshield Sub-Package No. 1

Tridair Industries Drawing CA 2773, Bolt Positive Locking Quick Rttlease ,

l

-2-

(12) Bulletin No. 118 and 119 , "Analysis of Flat Plates by the AlgE"braic Carry OVE"r Method" - Tuma and Havner, Oklahoma State University.

3.0 SUMMARY

It is concluded that the fasteners around the edge of the pallet can be reduced from sixteen to nine and one of the center fasteners can be removed with a weight increase of approximately 1.75#. Modifications as shown on references (l) and (2) would have to be made to the structure.

The following changes outlined in references (4) and (5) are repeated here for convenience: ,

sunshield Pallet Ref. (1)

1. 0.020 aluminum reinforcing doublers added to top and bottom of pallet around edge.

2. 'I'Welve taper pins added around edge of pallet.

3. Location of corner fasteners changed to attach to attach to inner flange rather than outer flange.

4. Front edge member or beam changed from 0.050 to 0.070.

5. Necessary changes made to pallet to relocate fasteners.

Thermal Plate and Primary Structure - Ref. (2)

1. Locally upper flange of primary structure has been increased to 0.25 11 t.:tt each fastener and to 0.125" at each pin.

2. Inner corner flanges are increased to 0.25".

3. Changes to edge of thermal plate to accommodate pin and fastener locations are necessary.

In general, materials, type of hardware, etc. have been kept the same as existing structure. No attempt has been made to refine or change existing design except.as necessary for the fastener change.

-3-

Preload on each fastener should be the max.imum within the limits of the astronaut to apply.

4.0 ANALYSIS

4.1 Discussion

Th~ analysis conducted in this study wa~ done to determine whether the changes and modifications as proposed would deleteriously effect the dynamic characteristics of the ALSEP stnacture and whether acceleration transmissibilities would be increased.

In general it can be shown that deflections of the sun- ~

shield pallet will not be more severe after removing the fasteners then they were with fastenEn:s and that no serious increases in transmissibilities are to be expected. Also based on Ref. (6) dynamic inputs to ALSEP are reduced from those originally used for design.

The following pages of calculations obtain deflections for an assumed unit load of.l# per Inch along each edge and comparing the existing pallet to the modified design:--- Deflections for the modified design compare favorably to the exi~ting design.

The following changes were made which affect the dynamic characteristics.

1. Local pads are placed at each fastener attaching point on primary structure. This markedly reduces flange qeflections particularly along the front (Beam 3) . .

2. Edge members of pallet have been reinforced by adding a 0.020 doubler around the edge top and bottom. This reduces deflections between fasteners and results in the pallet behaving more like a plate supported uniformly around the edge rather than as a plate supported at a ser ie~ of co.ncentrated points.

This was deemed advisable due to the reduction of the number of fasteners.

3. Fasteners in center were reduced from three to two. This has little effect on the pallet deflections or thermal plate. Thermal plate deflections are further alleviated by taper pins which prevent movement.

-4-

4.2 Analysis Procedure

4.2.1 Pallet Edge Members

Each pallet edge member was assumed to ~ continuous beam with a unit load of 1#/in acting up along the am. Each fastener was assumed to be a support point. These support points deflected under load due to bending,of the ange of the lower beam, deflection of the lower beam and elongat of the fastener. This investigation showed that deflection of the r structure flange was much the greatest cause of llet mov~1ent.

Given the EI's of the beams and AE's of fastener~ deflections of the upper beam were deter ned pallet, for the pallet without edge re for

s;,ting for beams 1 a11d

2 and with reinforcing for beams l, 2 and 3. (see s 6) •

Final de4flection curves are given on peJ.gil.'J's No deflection curves are shown for beams 4 5 s deflections are far less than other beams.

32-34 t

A study of deflection curves shows t t with the new

1.

fastener, pattern d4!flections -would be equal to or below ting deflections and no pronounced increase in transrniss to be expected.

The procedure for preforming th was or 1 ~et up using Castigliano 's Least Work equatione (pages 13-15 1.). However a computer program available at Bend Aerospace Sy·stems Division based on a matrix method given in References (3) and (7) was found applicable and saved considerable labor,

The basic matrix relationships are from ref. {7} and are as followss

< p ! i I i.. .J

.{6! fJ[

.J

[ K !

r ' l-1 {a} i D! K = ! l '

~ .,

) : fJ l \-1 J Q 1 = ki K· ! t I : i L ' I

= matrix for element deflection~ and rotations

= displacement compatibility matrix which insures the connectivity of the system

= stiffness coefficient matrix

a matrix of applied forces

= internal force matrix.

-5-

Detail procedures for determining these matrices are also discussed in Ref. (3). Pages 13-16m~give a sample procedure.

Primary deflections were dye to movements at attachment points. Deflections were also computed between points of support and are included in the deflection curves. These deflectiGns turn out to be relatively small .

. Pallet

The Pallet was investigated to determine the effect of removing one center fastener. Referring to pages 34-39 incl. fastener A was removed and the load carried by.thisfastener was distributed equally to fasteners B and c.

Using tables given in Ref. (12) it was shown on the curves pages 38, 39 that this had no appreciable effect on deflections.

4.2.3 Thermal Plate

The thermal plate, although one center fastener has been removed, should be more satisfactory then the previous design. The regularly spaced taper pins, at closer tolerances, should reduce plate deflection. Based on the results of this investi­gation the third fastener was contributing little to plate ' deflection.

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