(NASA-CR-178822) SPACE PLA1FOBK EXPENDABLES ~ 886-24735

BESOPPLY CONCEPT DEFINITION STUDY. VQLOHE 3:

IORK BfiEAKDOWK S1BOCTORE AND SOBK BREAKDOW N •

SIEUCTURE DICTIONiBY Technical Report, Har. Onclas

1984 - Dec. 1984 (Rockwell International G3/18 42940

SPACE PLATFORM EXPENDABLES

RESUPPLY CONCEPT DEFINITION STUDY

STS 85-0174

Volume III

Work Breakdown Structure

And

Work Breakdown Structure Dictionary

Contract NAS8-35618

For Period March 1984 - December 1984

2202e
SPACE PLATFORM EXPENDABLES

RESUPPLY CONCEPT DEFINITION STUDY

STS 85-0174

•

Volume III

Work Breakdown Structure

And

Work Breakdown Structure Dictionary

Contract NAS8-35618

For Period March 1984 - December 1984

2202e
CONTENTS

Page

INTRODUCTION 1

WBS DIAGRAMS 2

EXPENDABLES RESUPPLY MODULE SYSTEM WEIGHTS BY WBS 6

WBS DICTIONARY ' 8

WBS 1.1 Program Management & Systems Engineering 8

WBS 1.2 Design & Development . 8

WBS 1.3 Production & Manufacturing 9

WBS 1.4 Systems Verification & Test 10

WBS 1.5 Launch Operations 10

WBS 1.6 GSE & Payload Support 10

WBS 1.7 Mission Operations 10

WBS 1.8 Maintenance & Refurbishment 10

2202e -i-
INTRODUCTION

This document contains the work breakdown structure (VBS) for the space

Platform Expendables Resupply Concept Definition Study.

The ¥BS consists of a list of WBS elements, a dictionary of element

definitions, and an element logic diagram. The list and logic diagram

identify the interrelationships of the elements. The dictionary defines the

types of work that may be represented by or be classified under each specific

element.

The Space Platform Expendable Eesupply WBS, as defined herein, was

selected mainly to support the program planning, scheduling, and costing

performed in the programmatics Task (Task 3)«

The ¥BS is neither a statement-of-work nor a work authorization

document. Rather, it is a framework around which to define requirements, plan

effort, assign responsibilities, allocate and control resources, and report

progress, expenditures, technical performance, and schedule performance. The

WBS element definitions are independent of make-or-buy decisions,

organizatioinal structure, and activity locations unless exceptions are

specifically stated.

2202e - 1 -
WORK BREAKDOWN STRUCTURE FOR ERM PROGRAM

The selected work breakdown structure for the ERM program consists of the

following elements:

1.1 Program management and system engineering is the core of the

program and provides the overall program perspective necessary for

continuity and decision-making.

1.2 Engineering design

1.3 Manufacturing, procurement of purchased systems and assembly of

test articles and flight units.

1.4 Developmental, qualification, flight demonstration, and functional

testing.

1.3 Mission planning, flight support, and check-out necessary to

support the first launch and post-flight analysis.

•

1.6 Payload support for the resupply module in the orbiter payload bay

is GFE (this hardware is available from other programs).

1.7 & 1*3 Operational support beyond the baseline program has not been costed.

2202e - 2 -
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EEM SYSTEMS WORK BREAKDOWN STRUCTURE

The WBS numbers, used in the programmatics Task 3 Section are Orbiter/STS

designations.

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ERM SYSTEM WEIGHTS

The weights range for each ERM System reflects on 80 percent confidence that

the actual design weight will be between a low of 8260 and a high of 9170

pounds.

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2202 e - 7 -
DICTIONARY

1.0 SPACE PLATFORM EXPENDABLES RESUPPLY MODULE

This element encompasses tasks associated with development, production

and support of the Expendables Resupply Module. The tasks include system

design, fabrication, assembly, installation and checkout, and quality control;

engineering studies and testing; support equipment; tooling; procurement

activities; facility activation; system interface definition; control and

integration of government-furnished equipment (GFE) into the spares

provisioning; operations support; and requisite program management activities.

1.1 PROGRAM MANAGEMENT & SYSTEM ENGINERING

This element contains tasks associated with management and support

of the Expendables Resupply Module. The tasks include planning, organizaing,

and defining requirements; establishing schedules and allocating resources to

attain objectives; reporting progress and providing program status visibility;

and controlling the program activities.

This element also defines requirements for the design, development,

production, and test of the Expendables Resupply Module, including analyses

that support the development of designs and verify compatibility of designs

with requirements and tasks required to control and direct engineering

activities related to the design of the system.

1.2 PLIGHT HARDWARE DESIGN, DEVELOPMENT, AND QUALIFICATION

This element includes detailed design of structures, system

components, interface hardware, testing, evaluation, and utilization of test

results to finalize ERM production designs. Work effort includes inspection,

procurement, and support to safety and reliability.

This element is subdivided into the following Level 7 elements:

Structural Systems

Mechanical Systems

Fluid Systems

Electrical Power Systems

Electrical Control Systems

Avionics

Environmental Control Systems

2202e/4-ll-85 - 8 -
1..3 PRODUCTION/MANUFACTURING

This element includes all design, manufacture, inspection, and acceptance

test activities that are unique to the production of specific flight units of

the Expendables Resupply Module. Included are the manufacturing and assembly

of the developmental test article, the qualification test article, the first

flight units, and the refurbishment systems salvaged from the developmental

and qualification test articles, and assembly into a second flight unit.

1.3.1.1.2 STRUCTURES

This element includes design, development, and qualification of

structural components for the expendable fluid resupply, including

primary and secondary structures and thermal protection items for

structures.

1.3.1.1 ADAPTOR FOR ERM/OMV

This element includes the design, development, and qualification of

truss structure between the ERM and OMV for attachment of robotics for

spacecraft servicing, separation bolts, and helium tanks.

1.3.2.3 FLUID SYSTEM

This-element includes design, development, and qualification of

propellant storage and transfer components, including fluid lines,

umbilical interfaces, helium tanks, propellant pumps, compressors,

disconnects, valves, tanks, and component thermal protection items.

Also included are assembly and testing of the complete fluid system.

1.3.3 ELECTRICAL POWER SYSTEM

This element includes the design, development, and qualification of

44K¥/Hr. rated batteries.

1.3.4 AVIONICS SYSTEM

This element includes design, development, and qualification of

instrumentation, displays, controls, data processing, and

electrical distribution and control components of the system. Also

included are assembly and testing of the complete avionics system.

1.3.4.6 ELECTRICAL CONTROL SYSTEM

This element includes the design, development, and qualification of

electrical regulation and distribution subsystems and actuation

sequence controllers.

22C2e/4-ll-85 - 9 -
1.3-5 ENVIRONMENTAL CONTROL SYSTEMS

This element includes the design, development, and qualification of

cold plates and heaters, thermal protection systems, and blankets and

covers.

1.3.7.8 MECHANICAL SYSTEM

This element includes design, development, and qualification of RMS

end effectors, docking umbilical actuators, and pyros.

1.4 SYSTEM VERIFICATION AND TEST

This element contains the task of verifying the expendable resupply

module concept with two test articles: developmental and qualification. The

developmental test article will be tested first at the White Sands Test Range

to verify fluid transfer, docking and release, pressurant transfer, and

tankage monitoring capability. In addition, the ERM will be fit tested to the

orbiter and the OMV to verify their compatability.

The qualification test article will be tested first at Johnson Space

Center for acoustic vibrations, thermal vacuum and random vibrations. Then,

the qualification test article will be shipped to White Sands Test Facility

for fluid transfer tests beyond the ERM's design limits.

1.5 LAUNCH OPERATIONS

This element includes the test and checkout of the first flight unit

prior to launch, mission planning, operations support, and post-flight

analysis of the first operational flight.

1.6 GSE & PAYLOAD SUPPORT

This element includes government supplied equipment such as the IUS

forward cradle, STS fitting, and latches. The cost of these elements are not

included in the baseline program cost estimate.

1.7 MISSION OPERATIONS

This element includes the mission support for managing the day-by-day

operations of the expendable resupply module. This cost is not included in

the baseline program cost estimate.

1.8 MAINTENANCE AND REFURBISHMENT

This element includes the logistic support for repairing and refurbishing

the expendable resupply modules as required. This cost is not included in the

baseline 'program cost estimate.

2202e/4-ll-85 - 10 -