NASA Technical Reports Server (NTRS) 20020022115: Rocket Design for the Future

14 Pages·0.43 MB·English

by  NASA Technical Reports Server (NTRS)

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William W. Follett
MDO Project Lead
Raj Rajagopal
RDCS Project Lead
::_. Rocketdyne Propulsion and Power
_i:i _ Boeing- Canoga Park
_i"i! : . Presented at:
mW_._?_"_-_ _ Air Force Research Lab (AFRL) Electronic Prototyping Review
_!{_,._ Boeing - SeattJe
_4i_:_! : July2s2oo_
AGENDA
• Vision
• Approach
ji.i!;_i • Optimization and Robust Design
',i • Knowledge Based Systems
_- • Collaborative Technologies
_) • Examples
__ :.,- S.gmmary
i ',_ _ ,_,._, . - -'J ,_C C
_: _I_!_ - _
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'Real time" analysis enable rap_ RPPengineers work fluently with
design, multidisciplinary anaiysis collaborators across the globe, providing
complete mission predictions & thebest so_Jtions bycombining
manufacturing worldwide resources
simulations
Automated Reasoning
Expert systems capture design
knowledge. Automated data analysis,
optimization, androbust design
: generate new knowledge.
t( SseMmDsOanCapurean
Expand Design Knowledge
Approach
_i!ntegrate design technologies into state of the art design systems
B_: -- Reduce time & cost required to create new products
_! Capture engineering expertise
,_2 Provide users with design environments customized to their problem
_l_p_._¢_n t__ hhology thrusts:
•-tii'fiization ar_l Robust Design
OllaDoratlve_ iecnnologles
__r,'__:_;/_'-._:_'_ ..., ': -;,..
Technology Thrust: Robust Design
Challenge: Reduce De_,elopment Coxt
Traditional Design Process Robust Design Process
Cost
Eliminate Failure Modes
Engineering Supporl
Design
Certification
Time
Time
Test-Fail-Fix Cycle
Representing 73% of Cost
REDUCE BY
FACTOR OF 4
RDCS Features
- ..... Robust Design Computation System
i:
<_': .... o,[kflow aids robust design F..ile.....S._.'.s.l_.fi.l....M...o.n.ilo.r............. Help
_ables fromdatabases I
lilJ_=_-__il_0delsincluda Vadablesl Math[
i_dai'dized andautomated ------ Model! Des-.
ii_.I_sls processes _-- Process
illgW_ " -_:-_'---_.... , Compute
im_m_'_ , ._;'_-,_,x., : Results t
_U)[OCesses _SVallaDle _
/.u_J_#meg__omputlng
RDCS Probabilistic Analysis - Results
Plot Tvr,e t_)p_m:,:ot
X_is kabe!
I1
Technology Thrust: Optimization
Implement Optimization Tools to Support Increased Design Complexit),
Technology Thrust: Optimization
hnplement Optimization Tools to Support Increased Design Complexi_
Technology Thrust: Knowledge Based Systems
• Future role of analysts/designers can become that of
i:i:i: owner/developer of expert shells or 'knowledge stations'
., • The expert shells interact with each other
'. semi-autonomously
IntHelylipgeernstonic DesiPgrnopulsAiodnvisor ExCpaerpttiuseres
:__ ",'__;iL-,T----,_"r.................
IDA System Architecture -- Engine Analysis Module
IDA System Architecture
/
' Inner Driver
Technology Thrust: C.llab.rative Technologies
Collaborative optimization algorithms
• Enable MDO among geographically dispersed teams
• Address MDO problems of unprecedented size and corpJexrty
_,_;_X,• Internet-Based Parallel Processing Tools
_. t ° Enable controlled access among design team members to
__;._ :. geograp.hically dispersed computational resources
___'},-"_ _:'_:_t,_.:J._•E_a',.-c,dit.a>tLe,,.';; effe.,ct .v.e use of ava lable computat ona resources for
ii_a_un_l_e.g., parallel process,ng)
l_V, irt0al collocation of personnel
.:[[;: '_r_:_:- _:_;_"! _-_ ,.>_: :
i:_;:_;'L5_/ ": : - " , BO'_/_O
_liul ..... =.lrl....... , .............
AGENDA
_<--. • Vision
: ° Approach
_:- ° Optimization and Robust Design
l_i{ ° Expert Systems
Collaborative
. Technologies
_.t._ ?d_ *" " "- ' ,B'OEI.,_
Potential to Reduce RLV Vehicle Weight Demonstrated through
Multidisciplinary Optimization" (MDO)
IBaseline-OptimizedSingleDisciplineWeight
0.00I
MDO
J
leductionachievedbyMDO ,.
°Ref AIAA 97-3374, NASA TM 110326
10 15
CASINO Reduces Cost and Complexity of
Aerospike Design by an Order of Magnitude
+ +
Captured Design & Parallel Computing
;I31[ & Automation
Analysis Knowledge & Optimization
• For 2000: _'_"
• $5M added engineeering value |
• 4000% return on investment in first _ear
• 61% improvement in predicted
payload-to-ISS
Multidisciplinary Optimization is Now a Design Tool
Triprope/lant Nozzle 3-O Supersonic Stator Vane
•Maximize thrust and minimize hotspots
load reduction, •Match target pressure profiles
•90% improvement achieved
Jetpump
Integrated Development
Multidisciplinary Linked Analysis & Design
Hydrodynamics analysis
blade and environment definition Mechanical design (Pro-E)
Pressure application Stress
results
Model
(ANSYS)
Impeller C_clc Time Reduced -6 Months to 1V<eek