The long range objective is to achieve technology readiness for one or more deployable platform systems by 1986. Engineering plans and approaches to meet this goal are presented in outline form

Jewell, R. E.

English

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DEPLOYABLE PLATFORM SYSTEMS DEVELOPMENT
R. E. Jewell
NASA
George C. Marshall Space Flight Center
Huntsville, Alabama
Large Space Systems Technology - 1981
Third Annual Technical Review
November 16-19, 1981
219
https://ntrs.nasa.gov/search.jsp?R=19820010417 2020-03-21T16:23:35+00:00Z
FUNCTIONAL PLAN
The flow chart shows the interaction between the different aspects
of platform systems technology. In order to perform technology in
the different discipline areas, shown below the dashed line, generic
platform systems must be established and used as reference in defining
and executing technology work in the discipline areas shown. Specific
outputs of the activity are indicated to the right of the chart.
VALIDATED
_ TECHNOLOGYBASE DATA
H PLATFORMSYS. ANALYSIS
FUNCTIONAL PLAN
PLATFORM
b- SYSTEMS I
TRADE
!
GENERIC SYSTEMS
TECHNOLOGY NEEDS
f SPECIFIC [PHASE A
• DEFINES CAPABILITY
AND LIMITATIONS
• DETERMINES VIABLE
NEAR TERM PROJECTS
• PROVIDES GUIDELINES
FOR TECHNOLOGY
GROWTH EMPHASIS
ENGLER
I
DEPLOYABLE
PLATFORM
STRUCTURAL
STUDIES
BUCHANAN
, ,hi
MILLERWAITERS
PLATFORM
CONTROL &
STABI LITY
STUDIES
TECHNOLOGY TRANSFER
PLATFORM
ASSEMBLY
TECHNOLOGY
PLATFORM
POWER
SUBSYSTEM
TECHNOLO(;Y
[
TECHNICAL GROWTH
EVALUATION PROCESS
INDUSTRY/UNIVERSITY
RELATED RESEARCH
WAGNON
PLATFORM
AUTOMATION
TECHNOLOGY
OTHER
RELATED
RTOP'S
]
• GENERATES
TECHNOLOGY
GROWTH
• DEFINES
TECHNOLOGY
"ROADBLOCKS"
• DEFINES VALIDATION
& REQUIREMENTS
• ASSESS VALUE
ADDED TECHNICAL
STUDIES
220
LONG RANGE OBJECTIVE
The long range objective is to achieve technology readiness for
one or more deployable platform systems by 1986. All technology areas
required for deployable platform structures will be identified and
worked.
APPROACH
A two-phase program is planned to insure attainment of the
development objective. In Phase I, engineering studies are performed
to identify various deployable platform structures concepts, and
based on established selection criteria, one or two viable concepts
are chosen for a follow-on concept design effort. Generic platform
design requirements are used in this effort. Phase II will expand
the technology work into hardware verification of the selected deploy-
able structure concept(s). In an incremental program, an orderly
progression from component to subsystem development and finally to an
overall system verification will take place. Flight experiments re--
quired to augment the ground test will be identified during this
program phase.
LONG RANGE OBJECTIVE
• DEVELOP TO TECHNOLOGY READINESS ONE OR MORE DEPLOYABLE
PLATFORM SYSTEM CONCEPTS BY 1086
APPROACH
• EXECUTE TWO PHASED PROGRAM TO INSURE ATTA INMENT OF DEVELOPMENT
OBJECTIVE
PHASE I ENGINEERING STUDY ACTIVITY
m CONCEPT DEVELOPMENT AND SELECTI ON
• CONCEPT DESIGN
PHASE IT HARDWARE DEVELOPMENT, TEST AND EVALUATI ON
• COMPONENTS AND SUBSYSTEMS
• SYSTEMS
• FLIGHT EXPERIMENT DEFINITION
221
OVERALL STUDY GUIDELINES
The goal of the Deployable Platform System Technology program is
to perform an integrated program with demonstrated technology readi-
ness in 1986 through test proven hardware on the system level. In
order to achieve versatility, point design of the system is avoided,
and a generic platform, incorporating features of presently conceived
platforms (LEO and GEO), is utilized. Other applied major guidelines
include the adaptation of a building block approach with self-contained
automatic deployed modules and minimum EVA for assembly and mainte-
nance. The basic launch vehicle is assumed to be the Space Shuttle
(STS).
OFY 1986 TECHNOLOGY READINESS
• TEST PROVEN HARDWARE
• COMPLETE SYSTEM - NOT JUST A STRUCTURE
OGENERIC - NOT A BASEPOINT DESIGN
OVERSATILITY
oCAN BE USED TO BUILD PLATFORMS OF DIFFERENT CONFIGURATIONS
• "BUI LDING BLOCK" APPROACH - SELF-CONTA I NED MODULES
ODISTINCTION BETWEEN LEO AND GEO DESIGNS
OADAPTABLE FOR A WIDE RANGE OF PAYLOADS
OAUTOMAT IC DEPLOYMENT
oMINIMUM EVA
OBASED ON STS CAPABILITIES
222
MAJOR TECHNICAL CONCERNS
A listing of major technical concerns, which will be addressed
in the technology program, is shown. Special emphasis will be given
to the areas indicated.
_/ • DEPLOYMENT METHODS
• STRU CTURAL CONCEPTS
_/• UTILITIESINTEGRATION
• STRUCTURAL PERFORMANCE
_/ • COMPATIBILITY WITH ENVIRONMENTS
• DESIGN FLEXIBILITY
• CONTROL SYSTEM HARDWARE INTEGRATION
• CONTROL SYSTEM/STRUCTURAL SYSTEM INTERACTION
_/ • PACKAGING EFFICIENCY
• DEPLOYMENT A SSEMBLY
• POWER AND THERMAL SYSTEM INTEGRATION
• PROPULSION SYSTEM INTERACTION & INTEGRATION
_/ • SPACECRAFT OPERATIONS AND SERVICING
_/ • PAYLOAD INTEGRATION
• MATERIAL SELECTION
• COST TRADES
223
DEPLOYABLE PLATFORM SYSTEMS, PHASE I
This schematic depicts the study flow for the first phase of the
technology program. No hardware tests are planned during this seg-
ment of the effort which is performed Jn two parts.
DEPLOYABLE PLATFORM SYSTEMS
PHASE I
_ P_TFORi M F
REQUIiEMENTS J"
I GENE_IC1
I l-
I MATERIALL_
I SELECTION!
_ [ SUBSYSTEMREQUIREMENTS J
-- PART A
CONCEPT
EVALUATIONS
AND SELECTION
li UBSYSTEM [
VALUATION,
RISK ANALYSIS &
RADE STUDIES
GENERIC
PLATFORM
CONFIGURATION !
PART B
b"
_U OMPONENT &l
BSYSTEM
ESIGN J
PLATFORM 1 I PLATFORM
PR E LIMINARYI'_"_ DETAJL
DESIGN I I.. DESIGN
.t,
JSTRUCTURAL,_
:DYNAMIC | IiTHERMAL | SUBSYSTEM
iANALYSI $ ] INTEGRATION
PHASE
224
GENERIC DEPLOYABLE PLATFORM REQUIREMENTS
A matrix of requirements will be established to direct the design
of the generic spacecraft configuration and the development of concepts
for the platform design. Information will be extracted from the MSFC
summary document of the three focus missions. Other sources of require-
ments are JSC 0770, Vol. XIV, Space Shuttle System Payload Accommoda-
tions, and CR-160861, Shuttle Considerations for the Design of Large
Space Structures. The matrix will distinguish between LEO and GEO
requirements, where pertinent, and will include structural strength
and stiffness; payloads masses and sizes; materials environments and
temperatures; utilities quantity, sizes, and function; orbiter inte-
gration; space operations functions and mission equipment, such as
TT&C, solar arrays, batteries, and control system components.
GENERIC DEPLOYABLE PLATFORM REQUIREMENTS
STRUCTURAL
• SUITABLE FOR EITHER AREA OR LINEAR PLATFORM
• STRUCTURAL ELEMENT SIZE:
• STRUCTURAL FREQUENCY
• STRENGTH OF BEAM
• STIFFNESS OF BEAM
• MATERIAL
DEPLOYMENT/STOWAGE/RETRACTION
• MUST DEPLOY AUTOMATICALLY
• SHOULD BE ABLE TO RETRACT
• PACKAGING RATIO 10 TO 30:1 (DEPLOYED/STOWED)
• MUST OBSERVE SHUTTLE ORBITER PAYLOAD BAY CONSTRAINTS
UTILITY INTEGRATION AND INTERFACES
• POWER RANGE
• DATA RATE
• THERMAL CONTROL
• UTILITIES CABLES, AND LINES, MUST BE FULLY INTEGRATED INTO THE
DEPLOYED TRUSS WORK
• UNIVERSAL INTERFACE HARDWARE ADAPTER CAPABILITY AS A GOAL
225
GENERIC PLATFORM REQUIREMENTS
(CONT'D)
SUBSYSTEM INTEGRATION
• POWER SYSTEM SOLAR ARRAYS : AUTOMATICALLY DEPLOYED
• PROPULSION SYSTEM : ALTITUDE/ATTITUDE CONTROL/REBOOST
• THERMALCONTROL
PAYLOAD INTEGRATION
• PAYLOAD MASS AND
POSITION SENSITIVITY
: AUTOMATICALLY DEPLOYED OR MOUNTED ON
DEPLOYED STRUCTURE
• ACCESSABI LITY/SERVICEABI LITY REQ'TS
OPERATIONS AND SERVICING
• PLATFORM MUST BE COMPATIBLE WITH ORBITER DOCKING AND BERTHING
METHODS AND HARDWARE
MISSION
• PRIMARY ORBIT
• ORBITAL MANEUVERS
• 30 YEAR LIFE
: LOW EARTH ORBIT (400 TO 600 km) WITH
GEOSYNCHRONOUS ACCESS.
: ALTITUDE CHANGES
ORBIT R EBOOST
: LONG TERM ENV. EFFECTS, MATERIALS & SUBSYSTEMS
226
MATURED STRUCTURAL CONCEPTS
Applicable structural concepts will be compiled for structures
system selection. Both new and mature concepts, as shown, will be
investigated.
O
ECONTINUOUS i
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227
ADDITIONAL DEPLOYABLE STRUCTURES CONCEPTS
Applicable structural concepts will be compiled for structures
system selection. Both new and mature concepts, as shown, will be
investigated.
Type
Warren
Truss -
Transverse
Fold
Cable
Cross-Braced-
Transverse
Fold
Q Cable
Crou-Brared -
Transverse
and Longitudinal
Fold
K Brace -
Longitudinal
Fold
® K Brace -
Longitudinal
Fold
Deployed
Partially
Deployed Packaged
228
UTILITIES INTEGRATED WITH STRUCTURE
The overall spacecraft design will be broken down into separate
design areas, and several concepts will be developed for each area.
The areas which will be developed are"
o
O
o
O
o
o
Folding/deployable structural trusses--including the existing
diamond truss and double-cei!, double-fold.
Deployable methods and mechanisms.
Installation, attachment, and deployment of utilities.
Expansion/contraction in fluid lines.
Interfaces between structure and modules (payloads, control
module, RCS, etc.).
Interfaces between utilities and modules.
A typical design problem, integrated utilities, is depicted in this
picture.
Power
__1/ End View, Collapsed
\ / "Oa,a
End View, _ Fluid _- /
Deployed
• Truss With Utilities Double Looped __y_jE-_ Loop
229
ELEMENTS OF DEPLOYABLE PLATFORM SYSTEM
A generic linear and area shaped deployable spacecraft configu-
ration will be developed from the requirement established. The
purpose of the spacecraft configurations is not to freeze the design,
but to help understand and solve the localized problems which will be
encountered, i.e., to see the forest in addition to seeing the trees.
The spacecraft configuration will be configured to support the
reference payload group (selected from the three focus missions) for
LEO or GEO applications. The drawing of the generic deployable space-
craft configuration shows the following typical elements:
o Structure
o Control module
o Propulsion system
o RCS--distributed thrusters
o Solar array
o Electric power distribu-
tion
o Docking/berthing provisions
o Payloads--the reference
payload group
o Radiators
o Interfaces between structure
and modules/payload/RCS
o Module-to-module interface
o Fluid line routing
ROTATING
JOINT
DEPLOYABLE/RETRACTABLE
STRUCTURE
INTERFACES
WITH SUBSYSTEMS
UTILITIES
INTEGRATION
INTERFACES WITH PAYLOADS
SUBSYSTEMS & REBOOST
INTERFACES
DOCKING/
ASSEMBLY/
EVA INTERFACES
230
SYSTEM LEVEL CONCEPT DEVELOPMENT TRADES
The concepts for separate components or subsystems will be
screened and then matched to each other to form integrated platform
systems. For example, each foldable truss will be matched with the
type deployment mechanism to which it is best suited. Similarly, the
various concepts of utilities installation will be matched with
structures and deployment methods. The objective is to produce inte-
grated systems, each capable of deploying a structural truss complete
with (as far as possible) all of the utilities, plus interfaces and
interconnects for payloads and modules. The emphasis is placed on
the system, not individual pieces or subsystems. A subsystem, however
ingenious it may be, will be discarded if it cannot perform its role
as part of the integrated system. An integrated system forms the
basis of a series of building blocks which can be assembled to con-
struct deployable platforms of various configurations. The integrated
process will be supported by analyses in all of the pertinent areas:
o Deployment methods/mechanisms--external mechanisms, strain
energy.
o Structures--strength, stiffness, member shape and size,
attachments.
o Utilities installation--cable bend radii, flexing, fatigue.
o Materials--aluminum, composites, structures, utilities.
ELEMENT DEPLOYABLE STR. CONCEPT /
CONCEPTS SYSTEM SYS. TRADES AND DEVEL.
CONCEPTS
I
f I IAAIHIIILITVt |
I oec_rlon$, /
\',..,_ svsT_
COd4C._PT
D(F|m[D
231
SYSTEM LEVEL CONCEPT DEVELOPMENT TRADES (Cont'd)
The criteria for selection of a deployable platform system will
encompass basic structure performance, subsystem accommodation, space
assembly operations, orbiter integration implications, and development
cost. With these categories, the specific criteria will be developed;
for example, such structures performance criteria as thermal stability,
weight, packaging efficiency, etc. For each set of criteria, the
methodology to be used in the screening process involving a combination
of numerical data (where feasible) and engineering judgments to apply
a point rating scheme and summary comparisons will be developed. For
each type of criteria, a written definition of what constitutes accept-
able numerical or qualitative limits will be prepared. Detailed
engineering data from the concept characteristics matrix will be com-
bined to form a set of overall ratings, based on the selection
criteria. The sum of possible points and total costs for each concept
will then be compared on summary screening charts, and one or two
structural concepts selected for design and analysis to complete
Phase I of the Technology program.
232
DEPLOYABLE PLATFORM SYSTEM TECHNOLOGY SCHEDULE
The schedule shows the overall program consisting of two phases.
Phase I was discussed in detail. Phase II effort will deal in
component, subsystem, and system development. Extensive hardware
design, fabrication, and validation effort is planned to achieve the
demonstrated technology readiness by 1986.
ACTIVITI ES
PHASE I
CONCEPT DEVELOPMENT
CONCEPT SELECTION
DESIGN & ANAL OF SEL. CONC,
REPORT
l_r
m
FY 82 FY 83 FY 84 FY 85 FY 86 FY 87
2NO 3RD 4TH IST 2ND 3RC 4TH 151" 2ND _IRD 4TH 1ST 2ND 3RD 4TH 1$T 2ND ]RD 4TH 1ST 2NC 3RD
m
El
EE
4TH
PHASE II (DEVELOPMENT)
DES. COMPONENT & SUBSYST.
HDW,
FAB. COMPONENT & SUBSYST.
HDW.
TEST COMPONENT & SUBSYST.
HDW,
EVALUATION & RISK
ASSESSMENT
_sHASE I I
YSTEM DEVELOPMENT)
DES. SYSTEM TEST HDW.
FAB. SYSTEM TEST HOW.
TEST SYSTEM
EVALUATION & RISK
ASSESSMENT
FLIGHT EXPERIMENT DEF.
BaNal
== m
BBBB mBB
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233



Deployable platform systems development

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