101 592 NASA Technical Memorandum 

STRUCTURAL MECHANICS DIVISION 

RESEARCH AND TECHNOLOGY PLANS FOR FY 1989 AND 

ACCOMPLISHMENTS FOR FY 1988 

Kay S. Bales 

July 1989 ? 

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RESEARCH AND TECHNOLOGY PLANS FOR FY 1989 AND 

ACCOMPLISHMENTS FOR FY 1988 

BY KAY S. BALES 

SUMMARY 

The purpose of this report is to present the Structural Mechanics Division’s research plans 

for FY 1989 and accomplishments for FY 1988. The work under each branch is shown by 

RTR Objectives, FY 1989 Plans, Approach, Milestones, and FY 1988 Accomplishments. 

Logic charts show elements of research and rough relationship to each other. This information is useful in program coordination with other government organizations in areas of 

mutual interest. 

ORGANlZATION 

The Langley Research Center is organized by directorates as shown on figure 1. The 

Structures Directorate includes Structural Mechanics Division, Materials Division, Structural Dynamics Division, and Acoustics Division. The Structural Mechanics Division consists of four branches and one program office as shown on figure 2. There have been 

significant changes in the organizational structure of the Division effective June 5, 1988. 

The Division was renamed Structural Mechanics (formerly Structures and Dynamics) and 

the dynamics work moved into the Structural Dynamics Division (formerly Loads and 

Aeroelasticity). Thermal Structures and Aerothermal Loads Branches were incorporated 

into the Division. The Structures Technology Program Office was created with Dr. John G. 

Davis, Jr., Head. Dr. Larry D. Pinson moved to the Structural Dynamics Division as Assistant Chief. Dr. Michael F. Card returned to Langley from his TDY assignment at Marshall. 

Dr. Clarence P. Young, Jr., returned to Systems Engineering Division effective February 1, 

1989, and Dr. James H. Starnes, Jr., was selected Assistant Chief, SMD, effective March 1, 

1989. Dr. Mark S. Shuart was selected Assistant Head, Structural Mechanics Branch, effective April 9, 1989, and Charles J. Camarda was selected Assistant Head, Thermal Structures 

Branch, effective May 7, 1989. 

FUNCTIONAL STATEMENT 

The Division conducts analytical and experimental research to provide structural concepts 

which meet functional requirements of advanced atmospheric and space flight vehicles. 

Develops and validates analytical methods of predicting stresses, deformation, structural 

strength, thermal loads and various thermoelastic phenomena. Develops and evaluates 

structural configurations embodying new material systems and/or advanced design concepts 

for general application and for specific classes of new aerospace vehicles. Develops and 

validates advanced structural analysis methods. Provides program support for structures 

technology programs in advanced composites research, hypersonic aircraft and advanced 

launch vehicles. Uses a broad spectrum of test facilities and develops new research techniques. Test facilities include the Structures and Materials Laboratory, the 8-foot High 

Temperature Tunnel, the Aerothermal Arc Tunnels, the 7-inch High Temperature Tunnel, 

and the Automated Assembly Facility. 

i 
TABLE OF CONTENTS 

I ORGANIZATION CHARTS 

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FACILITIES 

STRUCTURES TECHNOLOGY PROGRAM OFFICE (STPO) 

RTR 5 10-02-21-02 

RTR 763-01-41-12 4.8.2 Airframe Seals 

ALS (Advanced Launch Systems) 

NASP (National Aero-Space Plane) 

Advanced Composite Structures Technology Program 

STRUCTURAL MECHANICS BRANCH 

RTR 505-63-01-08 

RTR 505-63-01-09 

RTR 505-63-01-10 Computational Structural Mechanics 

RTR 510-02-21-01 

Mechanics of Composite Structures 

Advanced Composite Structural Technology/Concepts 

Advanced Composite Structures Technology Augmentation 

THERMAL STRUCTURES BRANCH 

RTR 505-63-31-03 Hypersonic Structures 

RTR 505-80-3 1-01 

RTR 506-43-31-04 

RTR 506-49-1 1-05 

RTR 506-80-31-01 

RTR 506-80-3 1-04 and 

RTR 763-01-41-13 4.5.1 Cryogenic Insulation 

RTR 763-01-41-21 

4.4.2 Engine Walls 

Thermal Structures for STS 

Thermostructural Concepts for 

Planetary Entry Vehicles 

4.6.1 Control Surfaces for Very High 

Temperatures 

4.7.6 Mechanics of Hot Structures 

RTR 763-01-41-18 

4.3.1 Airframe Leading Edges 

STRUCTURAL CONCEPTS BRANCH 

RTR 506-43-41-02 

RTR 585-02-31-01 Precision Reflector Structures 

RTR 591-22-11-01 Requirements for Pathfinder 

RTR 591-22-21-01 Construction Concepts 

Advanced Space Structural Concepts 

i i i PRECEDING PAGE BLANK NOT FILMED 

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RTR 591-22-31-01 Joining Methods 

RTR 591-22-41-01 Concepts/Technology Validation 

AEROTHERMAL LOADS BRANCH 

RTR SO6-40-2 1-0 1 Aero t 11 e r m a 1 Lo ads 

RTR 506-43-3 1-03 Integrated Fluid Thermal Structural 

Analysis Methods 

RTR 506-43-3 1-05 Aerothermal Test Facilities and Test 

Methods 

RTR 506-43-3 1-06 8-Ft. High Temperature Tunnel Controls 

RTR 506-80-3 1-05 4.7.4 Detailed Aerothermal Loads 

ACCOMPLISHMENT HIGHLIGHTS 

PUBLICATIONS AND PRESENTATIONS 

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I ORGANIZATION CHARTS 

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FACILI'I'I ES 

I The Structural Mechanics Division has two major facilities to support its research (shown in 

figure 3). 

The Structures and Materials Laboratory equipment includes a 1,200,000 Ib. capacity testing 

machine for tensile and compressive specimens up to 6-feet wide and 18-feet long; lower 

capacity testing machines of 300,000, 120,000, 100,000 and 10,000 Ib. capacity; torsion 

machine of approximately 60,000 in.-lb. capacity; hydraulic and pneumatic pressurization 

equipment; and vertical abutment-type backstop for supporting and/or anchoring large 

structural test specimens. 

The Aerothermal Loads Branch operates the 8-Foot High Temperature Tunnel (8'"TT) 

which is a unique hypersonic Mach 7 blowdown wind tunnel with an 8-ft. diameter test 

section (uniform temperature test core of 4 feet) that uses products of combustion (methane 

and air under pressure) as the test medium. The tunnel operates at dynamic pressures of 

250 to 1800 psf, temperatures of 2400 to 3600'R and Reynolds numbers of 0.3 to 2.2 x 106/ft. 

The tunnel is used to test 2-D and 3-D type models to determine aerothermal loads and to 

evaluate new high temperature structural concepts. A major CoF item is under way to 

provide Mach 4 and 5 capability and oxygen enrichment for the test medium. This is being 

done primarily to allow the tunnel to test models that have hypersonic air-breathing propulsion applications. 

Other facilities in the Aerothermal Loads Branch include the 7-Inch High Temperature 

Tunnel (7"HTT) and two Aerothermal Arc Tunnels. The 7"HlT is a nearly 1/12th scale of 

the 8'H'IT with basically the same capabilities as the larger tunnel. It is used primarily as an 

aid in the design of larger models for the 8'"IT and for aerothermal loads tests on subscale 

models. 

The two Aerothermal Arc Tunnels (20 MW and 5 MW) are used to test models in an 

environment that simulates the flight reentry envelope for high-speed vehicles such as the 

Space Shuttle. The amount of usable energy to the test medium in these facilities is 9 MW 

and 2 MW. The 5 MW is a three-phase AC arc heater while the 20 MW is a DC arc heater. 

Test conditions such as temperature, flow rate, and enthalpy vary greatly since a variety of 

nozzles and throats are available and model sizes are different (3-in. diameter to 1-ft. x 2-ft. 

panels). 

The Automated Assembly Facility (also shown in figure 3) is new. The facility is composed 

of a robot arm, a planar X-Y motion base platform, and a rotating motion base. The facility 

hardware was designed as a ground based system to permit initial evaluation of in-space 

assembly concepts. The facility also has an integrated video subsystem to permit the 

operator to view, at close range, the operations of the robot and end-effector. 

6 
7 ORIGINAL PAGE 

BLACK AND WHITE PHOTOGRAPH 
111 STRUCTURES TECHNOLOGY PROGRAM OFFICE 

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This Office was established to provide programmatic leadership and management support 

for focused structures technology development within the Structures Directorate for hypersonic cruise vehicles, advanced space transportation systems and advanced composite 

airframes for transport and military aircraft. 

The logic chart reflects broad elements that encompass multiple organizations. 

RTR 5 10-02-2 1 -02 Advanced Co nr posit e S t ruc t u res Tech no logy 

Program 

OBJECTIVE: 

To develop and verify innovative structural concepts and their associated materials science 

and structural mechanics technologies that exploit the benefits of advanced organic-matrix 

composites materials for cost-effective wing and fuselage primary structures for future civil 

and military aircraft. 

FY 1989 PLANS: 

Approval of program plan 

Award NRA contracts 

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Hold integration workshops/meetings (DOD, Industry, Universities) 

Update consensus of state-of-the-art for composite primary structures 

APPROACH: 

Innovative structural concepts that utilize advanced materials, advanced material forms and 

processing methods, and advancements in structural mechanics will be developed and 

evaluated. Design and fabrication methodologies will be integrated at the beginning of 

concept definition and development. Critical structural mechanics, materials and processing problems/issues will be defined on the basis of analytical evaluation of the concepts. 

Detailed structural mechanics analyses will be performed on areas where large stress 

gradients are predicted. Coupon, subelement and subcomponent articles will be designed, 

fabricated and tested to verify the material science and structural mechanics technologies 

and concept performance. 

Proposals from fifteen contractors have been selected for negotiation to develop new 

materials, new material forms, characterize new materials, develop and/or evaluate 

manufacturing methods, develop innovative concepts and to develop the associated structural mechanics foundation. 

MILESTONES: 

o Program plan approved, February 1989 

Complete award of NRA-87-LaRC-2 contracts, March 1989 

Conduct contractor/Government workshop, April 1989 
FY 1988 ACCOMPLISHMENTS: 

Selected fifteen NRA-87-LaRC-2 proposals for negotiation 

Established STPO to manage/coordinate multiple contract efforts 

RTR 763-01-41-12 4.8.2 Airframe Seals 

OBJECTIVE: 

To develop viable seals for control surfaces and doors, develop analytical methods for 

design, develop manufacturing processes, and verify concepts by analysis and test. 

FY 1989 PLANS: 

Complete tests and analysis of in-house and contractor seals specimens at medium 

temperature Mach 6 

Complete design, thermal analysis, and fabrication of in-house and contractor 

seals specimens at high temperature 

APPROACH: 

Coordinate with priced option contractors (4.8.3 and 4.8.4) to provide and utilize analysis 

methods, identify and resolve design and manufacturing problems, and provide adequate 

test facilities and techniques. 

MILESTONES: 

Complete medium temperature Mach 6 tests, February 1989 

Complete medium temperature Mach 6 test analysis, June 1989 

Complete high temperature test article design, June 1989 

Complete high temperature test article thermal analysis, June 1989 

Complete high temperature test article fabrication, September 1989 

Completed medium temperature test model design 

FY 1988 ACCOMPLISHMENTS: 

Completed medium temperature test model blockage tests 

Completed medium temperature test model thermal analysis 

Completed medium temperature test model flow analysis 

ALS MATERIALS AND STRUCTURES 

FY 1989 PLANS: 

ANALYSIS: 

e Extend LARCNESS to 3-D 

e Prepare structural and dynamic math models of fly-back booster 

12 
AI-Li AND ADVANCED PROCESSING: 

Complete design trade-offs to select candidate SPF skin-stiffener concepts 

Select Al alloy compositions for skin and SPF stiffeners 

Property and process characterization of weldalite and XD weldalite material 

Verify performance of internal foam system 

Fabricate and test evacuated H/C insulation 

Program plan approved and resources released 

Adaptive, unstructured mesh generator (LAXNESS) operational for 2-D fluid 

analysis problems 

INSULATION SYSTEMS: 

Cyclic performance of high-temperature (400'F) external foam verified with LHe 

temperatures 

Completed extensive property and process characterization Al-Fe-V-Si Alloy 

Superplastic forming of isogrid demonstrated 

HIGH-TEMPERATURE ALUMINUM: 

INSULATION SYSTEMS: 

FY 1988 ACCOMPLISHMENTS: 

ANALYSIS: 

HIGH-TEMPERATURE ALUMINUM: 

AL-LI AND ADVANCED PROCESSING: 

NASP STRUCTURES TECHNOLOGY MATURATION 

FY 1989 PLANS: 

PLAN AND COORDINATE TMP: 

0 

0 

Leverage TMP with consortium tasks results 

Keep TMP Director and JPO informed on state-of-the-art 

Push for OGL requests and beyond FY 1990 program 

Highlight NASA laboratory results used by contractors 

FY 1988 ACCOMPLISHMENTS: 

PLANNED AND COORDINATED TMP: 

Established FY 1989 budget 

e Developed team consensus 

0 

e 

Reported progress to JPO 

Provided technical direction to priced option contracts 

Highlighted technology deficiencies to TMP Director 

Organized and conducted sessions at 4th and 5th symposia 

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Defined test capability needs 

Supported search for facilities and associated issues 

Defined areas requiring research and development 

DIRECTED STRUCTURAL CERTIFICATION REQUIREMENTS STUDY: 

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IV STRUCTURAL MECHANICS BRANCH 

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This Branch conducts analytical and experimental research on the response of complex 

structures subject to static and dynamic loads. Explores basic behavior, develops advanced 

methods of analysis and design, and confirms validity of analysis by conducting tests of 

elements and large-scale structural models. Develops efficient structural concepts that exploit the benefits of composite materials for advanced aircraft structural components. Typical investigations concern stability, strength, damage tolerance, and tailoring of structures 

made of composite materials. Special emphasis is focused on identification of structural 

deformations and failure modes, development of verified failure analysis, development of 

structurally-efficient composite structural concepts, and prediction of nonlinear structural 

response phenomena. Develops advanced computational structural mechanics analysis 

methods to exploit predicted future computer hardware architecture. Conceives new static 

and dynamic test techniques and uses the Structures and Materials Research Laboratory. 

RTR 505-63-01-08 

OBJECTIVE: 

Mechanics of Composite Structures 

To develop structural mechanics technology required for verified design of structurally-efficient, damage-tolerant advanced-composite airframe structural components and to formulate advanced analysis methods to predict static and dynamic nonlinear response and ultimate strength of composite structures. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 emphasis is on anisotropic plate and shell analyses and modal interaction for 

nonlinear structural analysis. Structural mechanics issues of advanced concepts for composite structural components will be studied analytically and experimentally. Mechanical 

and pressure loads representative of wing and fuselage components will be considered. 

Methods will be developed for predicting strength, stiffness, buckling and postbuckling 

behavior of composite components including those with local gradients, discontinuities, 

eccentricities and damage. Procedures will be developed that predict large deformations 

and 3-D stresses in flat and curved composite panels. Failure mechanisms will be identified 

and analytical models for predicting failure will be developed and compared with failure 

criteria. 

MILESTONES: 

Develop modal interaction capability for nonlinear structural analysis 

Initiate development of equivalence transformation for nonlinear shell problems 

with multiple modes and ex and modal interaction capability for nonlinear strucInitiate study of nonlinear materials and viscoelastic effects on compressionloaded composites with discontinuities, January 1989 

Complete development of VICON analysis for curved composite panels with 

transverse stiffeners, April 1989 

turd analysis problems in S f AGS, October 1988 

17 
Conduct study of bending boundary layer attenuation lengths for anisotropic 

structures, June 1989 

Complete study of skin-stiffener interface stress analysis for problems with 

transverse bending, September 1989 

Com lete study of cross-sectional warping of nonlinear stiffened composite 

pane P s, September 1989 

FY 1988 ACCOMPLISHMENTS: 

0 Initial study of cross-sectional warping on nonlinear behavior of stiffened composite compression panels indicates that stiffener flange anisotropy causes larger 

deflections and higher stresses than orthotropic flanges 

Completed SRB ET attachment ring analysis. Identified effect of joint tailoring 

on bolt failure sequence 

Geometric imperfections included in recontinuization method for error analysis 

for nonlinear plate problems. Method provides accurate prediction for transverse 

shear forces as well as error estimates for shear and moments. 

Completed and implemented into STAGS development of equivalence transformation for multiple modes 

Initiated VICON analysis for curved composite panels with transverse stiffeners 

and studies of anisotropic plates and shells 

Completed preliminary structural efficiency study of composite rib concepts subjected to shear and compression 

RTR 505-63-0 1-09 Advanced Composite St ruct u ra I 

Tech no I ogy/Co n ce p t s 

OBJECTIVE: 

To develop verified composite structural mechanics and design technologies and structural 

concepts needed to realize the improved performance, structural efficiency, and cost-effective advantages offered by new material systems and fabrication procedures for advancedcomposite airframe primary structural components. 

FY 1989 PLANS: 

Evaluate stiffened thermoplastic compression panel concepts 

Study eccentricity effects caused by stiffener run out in composite compression 

panels I 

APPROACH: 

In FY 1989 emphasis is on evaluating structurally-tailored wing-box subcomponent design 

concepts and thermoplastic panel concepts. Advanced structural mechanics, design technology, and concepts for primary structures applications will be developed and evaluated for 

structural efficiency, damage tolerance and improved performance. The effects of design 

constraints, such as those imposed by aeroelastic tailoring and laminar flow requirements, 

will be included in the design of new structural concepts for aircraft components. Mechani18 
cal and pressure loads representative of wing and fuselage structural components will be 

considered. Structural mechanics issues peculiar to these new design concepts will be 

studied and selected concepts will be evaluated experimentally. 

MILESTONES: 

e Evaluate effectiveness of selective adhesive interleaving concept for increasing 

residual compression strength of minimum-weight graphite-epoxy laminates with 

impact damage, November 1988 

Complete evaluation of Protection and Detection System (PADS) for low-speed 

impact-damage threat to heavily-loaded graphite-epoxy compression panels, 

December 1988 

Complete design studies of high-aspect-ratio aeroelastically-tailored transport 

wings and define critical subcomponent test specimens for subsequent fabrication 

and testing, January 1989 

Evaluate the performance of hat-, blade- and T-stiffened raphite-thermoplastic 

compression panel specimens. The T-stiffened panels will % e made of LaRC-TPI 

at Langley Research Center, March 1989 

Initiate study of molded graphite-thermoplastic structural details for advanced 

subcomponent concepts, April 1989 

Develop structurally-efficient stiffener run-out concepts for gra hite-epoxy com1989 

pression panels and fabricate and test specimens to evaluate t R e concepts, May 

Complete preliminary structural-efficiency study of composite transport-wing ribs 

subjected to combined com ression, shear and fuel pressure loadings. Initiate 

detailed study of effects of Me-len th effects on rib structural efficiency, ribJune 1989 

cover joint-stiffness requirements, !% an nonlinear effects due to pressure loading, 

Complete development of POSTOP I1 postbuckled panel design optimization 

code that accounts for nonlinear torsional flexural stiffener behavior, July 1989 

Initiate study of structurally-tailored graphite-epoxy cylindrical shells, August 

1989 

Complete assembly and test of graphite-epoxy C- 130 center-wing-box technologyintegration box beam, September 1989 

Successfully fabricated and tested filament-wound, graphite-epoxy geodesicallystiffened spar based on C-130 center-wing-box design. Response predicted 

analytically 

0 Fabricated and tested graphite-epoxy three-J-stiffener ultruded wing plank 

based on C-130 center-wing-box design to evaluate per P ormance and damage 

tolerance 

FY 1988 ACCOMPLISHMENTS: 

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Com leted design of eraphite-epoxy C- 130 center-wing-box technology-integration E ox beam and Critical Design Review held July 13, 1988. Selected design 

concepts for covers and spars 

Completed SRB ET attachment ring joint analysis and drafted documentation, 

Initiated analysis of STA-3 test to identify SRB buckling characteristics in bending 

Com leted designs of 5 hat-stiffened and 1 blade-stiffened graphite-thermoplastic 

pane P s. Fabrication of specimens under way for subsequent testing 

Identified analytically effects of axial compression and external pressure on buckling of thick-walled graphite-epoxy cylindrical shells 

Completed and verified by experiment development of compression failure 

analysis for multi-directional laminates 

Identified adhesive interleaving as an effective concept for raising the compression strength of graphite-epoxy structures with dropped-ply thickness discontinuities 

Identified stiffener crippling failure mechanisms for graphite-epoxy stiffeners 

Formulated structural tailoring procedure for stiffened composite panels with 

cutouts 

RTR 50563-0 I - IO Computational Striictural Mechanics 

OBJECTIVE: 

To develop advanced structural analysis and computational methods that exploit advanced 

computer hardware, and develop research testbed software system for structural analysis. 

N 1989 PLANS: 

Study error analysis and correction techniques for detailed stress analysis 

Study hierarchical and substructuring structural analysis techniques for aircraft 

structures 

Develop large-scale modeling plans; e.g., V-22 or composite transport 

APPROACH: 

In FY 1989 emphasis will be on developing error analysis techniques that can be used to 

detect and control analysis errors during detailed stress analysis of composite structures. 

Methods research will emphasize procedures that exploit multiple vector processor computers. To aid in the methods development research, a testbed system will be created. It 

will consist initially of software for Langley’s VAX and FLEX computers and NASA’s NAS 

computers and will then be installed on other powerful multiple vector processor computers 

for evaluating methods on large, complex problems. This software system will be aimed at 

the computers and aerospace structural analysis problems of the 1990’s and beyond. 

MILESTONES: 

Publish program developer’s document describing procedure for installing new 

modules in testbed, January 1989 

20 
Develop and demonstrate a problem decomposition technique suitable for parallel computation of stress distributions in composite structures, May 1989 

Demonstrate prototype of parallel data manager for testbed on new CSM MIMD 

computer, May 1989 

Demonstrate an error detection and control technique for stress calculations in 

composite structures, September 1989 

Initiate research program on two new composites focus problems, September 

1989 

FY 1988 ACCOMPLISHMENTS: 

Documented analysis of SRB aft skirt, SRB/ETA ring, and SRB shell with 

memorandums, publications, and presentations 

Demonstrated capability to use PATRAN as testbed post processor. Color used 

to indicate stress intensity 

Developed capability for solving global/local stress analysis problems when deformations are inplane. 

Developed new vector e uation solvers for NAS Cray 2 that reduced solution 

Used FORCE (rather than PISCES) to aid transfer of parallel equation solvers 

from Flex computer to NAS Cray 2. These solvers were then used to carry out 

performance studies on NAS 

time by up to a factor of 2 9 compared with existing scaler solver 

RI’R 510-02-21-01 Advanced Cotnposite Structures Technology 

Augmentation 

OBJECTIVE: 

To exploit the benefits of advanced composites for transcentury aircraft primary structural 

applications by providing the enabling structures technology and the necessary scientific 

basis for verified innovative structurally-efficient, cost-effective structural concepts. 

FY 1989 PLANS: 

Award contracts and grants for structural concepts and structural mechanics innovative primary composite structures 

APPROACH: 

In FY 1989 emphasis is on development of innovative wing and fuselage subcomponent 

concepts and related structural mechanics technology. Innovative structural concepts that 

exploit the benefits of advanced composites and lend themselves to cost-effective fabrication procedures will be developed for future primary structures application and verified 

experimentally. Structural mechanics technologies will be developed including analysis, 

design and test methodologies for structurally-tailored and structurally-efficient wing and 

fuselage components and subcomponents with local gradients, discontinuities and complex 

mechanical and aerodynamic loadings. Subcomponent interaction, failure mechanisms and 

analyses, damage tolerance and containment, buckling, postbuckling, and other nonlinear 

effects for these new structural concepts will be studied analytically and experimentally. 

21 
Scaling laws for composites will be developed to enable research subscale laboratory models 

of wing boxes and fuselage shells to be extrapolated to full-scale designs. 

MILESTONES: I 

Award structural concepts and structural mechanics contracts and grants for innovative primary composite structures, June 1089 

Initiate design of advanced rib, spar and cover panel concepts, July 1985) 

Initiate design of structurally-tailored advanced concept wing-box models, August 

1989 

Initiate design of advanced fuselage frame and shell-wall concepts, September 

1989 

FY 1988 ACCOMPLISHMENTS: 

Selected fifteen NRA-87-LaRC-2 proposals for negotiation 

22 
V THERMAL STRUCTURES BRANCH 

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V THERMAL STRUCTURES BRANCH 

This Branch conceives structural concepts for future high-speed aircraft and space transportation systems including primary airframe structures, reusable cryogenic tanks, thermal 

protection systems, for both acreage and stagnation heating areas and structures for 

airbreathing hypersonic propulsion systems. Verifies promising concepts via analyses and 

tests in various high temperature and cryogenic facilities. Develops new analysis and test 

techniques as required to verify advanced concepts. 

RTR 505-63-3 1-03 Hypersonic Structures 

OBJECTIVE: 

To develop and evaluate actively cooled structural concepts for hydrogen-fueled scramjet 

engines which operate at speeds in excess of Mach 5, and to develop high-temperature test 

capability. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 emphasis is on performance of actively cooled structures. Fabricate under 

contract a full-size, flightweight fuel-injection strut for a scramjet engine concept. Windtunnel test the strut in-house under actual combustion conditions. Fabricate and test inhouse a similar copper strut for measuring the thermal and pressure load environment in 

the tunnel. Reactivate actively cooled test stand (ACTS) apparatus for glycol-cooled structural testing. Develop LH2 capability for active cooling. 

MILESTONES: 

Complete fabrication of flight-weight strut 

Reactivated ACTS apparatus 

Complete fabrication of flightweight strut, June 1989 

Complete testing of stainless steel strut, September 1989 

FY 1988 ACCOMPLISHMENTS: 

Completed Rockwell International Corp. cooled panels tests 

Designed heat exchanger specimen for National Bureau of Standards (NBS) tests 

Completed fabrication of copper calibration strut 

RTR 505-80-3 1-0 I 4.2.4.2 Engine Walls 

OB JEC'I'IVE: 

To conduct structural and thermal analysis on candidate engine wall concepts using material 

properties for advanced material systems and conduct tests on selected engine wall and 

surface heat exchanger concepts. 

25 
FY 1989 PLANS: 

Develop actively cooled apparatus at NIST (National Institute of Standards and Technofoyg) (formerly National Bureau of Standards) and complete initial tests 

APPROACH: 

In FY 1989 emphasis will be on developing the capability to test engine heat exchanger 

specimens at NIST. After completion of detailed analysis of candidate concepts, an engine 

wall concept will be selected for testing. Surface heat exchanger specimens will be tested at, 

NIST to determine heat transfer and pressure drop characteristics, and an engine wall 

configuration will be tested in a hot gas rocket test stand at NASA LeRC. Fabricate and test 

flightweight engine strut which includes actively cooled walls. 

MILESTONES: 

Complete initial pin-fin heat exchanger testing, March 1989 

Initiate channel heat exchanger tests, June 1989 

Complete initial flow tests on strut, September 1989 

Delivered engine heat exchanger thermal/structural optimizer code to engine companies 

Developed heat exchanger test apparatus at NBS 

Designed nozzles for film cooling experiments to maximize engine cooling effectiveness 

FY 1988 ACCOMPLISHMENTS: 

Theriiial Structures for STS 

OBJECTIVE: 

To develop and validate, through analysis and test, efficient structural concepts and thermal 

management techniques critical to the design of future space transportation systems (STS). 

FY 1989 PLANS: 

APPROACH: 

For FY 1989 the primary emphasis will be on the performance of passively cooled thermal 

structures. Perform studies of attractive structural concepts and validate via tests. Support 

in-houqe studies to identify critical structural material research requirements. Effort will be 

focused on improved thermal analysis methods and test techniques with combined thermalmechanical loads. 

MILESTONES: 

Complete thermoelastic tests on curved TPS panels 

Complete thermoelastic tests of curved metallic (thermal protection system) TPS 

concepts, June 1989 

l e Demonstrate improved transfinite element-tliermostructural analysis, June 1989 

i Develop radiation element for hierarchical conduction elements, June 1989 

26 
FY 1988 ACCOMPLISHMENTS: 

Delivered improved view factor analysis code 

Refurbished and upgraded ACTS; completed Rockwell International Corp. water 

cooled panel tests 

Completed design and fabrication of test fixture for thermal stress tests of curved 

TPS panel at Dryden Flight Research Facility 

Completed finite element model (FEM) for curved TPS 

RTR 506-49-1 1-05 Thermostructural Concepts for Planetary Entry 

Vehicles 

OBJECTIVE: 

To develop and validate, through analysis and test, efficient structural concepts and thermal 

management techniques critical to the design of future planetary entry vehicles. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 emphasis will be on development of equivalent shell analysis. Support in-house 

studies to identify critical structures and materials technologies. Perform studies of attractive thermostructural concepts. 

MILESTONES: 

Complete equivalent shell analysis development 

Complete development of conceptual weight analysis code, June 1989 

Initiate vehicle conceptual studies, June 1989 

Complete first version of “SMARTt vehicle systems analysis, September 1989 

Completed design study of heat-pipe-cooled leading edges for hypersonic vehicles 

Designed and initiated fabrication of a Shuttle I1 leading edge heat pipe 

FY 1988 ACCOMPLISHMENTS: 

IWK 506-80-3 1-0 I 4.6.1 Control Surfaces for Very High ‘I’einperatrrres 

OBJECTIVE: 

To develop and demonstrate materials, fabrication, joint designs and fastening techniques, 

design and analysis, testing and nondestructive inspection methods required to construct the 

least weight movable control surface. 

FY 1989 PLANS: 

Fabricate and test carbodcarbon control surface subcomponents 

27 
APPROACH: 

In FY 1989 the primary emphasis is on design and fabrication of a carhonlcarbon control 

surface test article. A control surface for NASP vehicle configuration will be selected for 

the focal point of this effort. Performance requirements will be defined. Preliminary 

designs will be developed for several candidate concepts and the belst concept will be 

selected. A development and evaluation program will be defined and initiated to develop 

the required design and fabrication technology. A full-scale segment of the control surface 

design will be fabricated and tested to verify the adequacy of the concept. 

MILESTONES: 

Complete detail analysis and design, December 1988 

Initiate complete fabrication of full-scale segment, March 1989 

Define test and evaluation plan, September 1989 

Fabricate and test subelement components, September 1989 

Completed concept design study of control surfaces 

Initiated high-temperature carbodcarbon fastener program 

FY 1988 ACCOMPLISHMENTS: 

0 

RTR 506-80-31-04 and RTR 763-01-41-18 

Structures 

Initiated detailed design and analysis of control surface concept 

Completed tests and analysis of carbon/carbon stiffened compression panels and 

shear panels 

4.7.6 Mechanics of Hot 

OBJECTIVE: 

To develop improved analytical capability to predict local and global. temperature distribution in vehicle structure and to predict structural response to combined thermal and 

mechanical loads. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 emphasis is on the development of approximate analysis codes for conceptual 

vehicle studies. Systematically refine analytical model to hypersonic aircraft structures and 

determine the level of detail necessary to get usable results. Develop improved thermal/structural analysis capability, including the effects of joints. Veri@ improved methods 

hy comparing results with available test results. 

MILESTONES: 

0 Complete thermal discretization study 

Complete initial development of structural finite elements for LIFTS, September 

I989 

28 
Complete global thermal stress analyses mods for "SMART' 

Complete thermal stress discretization study 

Developed Sizing and Optimization Language (SOL) to improve implementation 

of formal thermostructural optimization 

Demonstrated feasibility of equivalent plate theory application to fuselage structure 

FY 1988 ACCOMPLISHMENTS: 

Version 1.0 of METCAN released by NASA LeRC for metallic matrix composite 

analysis 

Developed 3-D hierarchical conduction element in SPAR 

RTR 763-01-41-13 4.5.1 Cryogenic Insulation 

OBJECTIVE: 

To define the cryogenic insulation design requirements and criteria necessary to meet the 

NASP mission and develop an insulation system to meet the requirements. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 emphasis is on development of a high delta temperature calorimeter. Determine insulation requirements for each wall configuration under consideration. Candidate 

insulations include existing cryogenic foams, evacuated superinsulations, and evaluated multiwall and new ideas such as fibrous insulations with reflectively coated fibers. Insulations 

will be studied in detail to select the most promising. Manufacturing developments effort 

will include small test items to address key issues. If evacuation is necessary, considerable 

effort may be required to develop techniques to fabricate foil encapsulated insulations 

which maintain an acceptable thermal conductivity over the life of the vehicle. Panel sized 

specimens will be fabricated and subjected to cyclic thermal and structural tests. 

Complete developmentof high delta T thermal conductivity apparatus 

MILESTONES: 

Complete initial liquid hydrogen conductivity tests of evacuated honeycomb, 

March 1989 

Complete manufacturing development of cry0 insulation system, September 1989 

N 1988 ACCOMPLISHMENTS: 

Develo ed thermal conductivity apparatus for cryogenic (LHe) insulation systems 

tests ( rs BS) 

Established feasibility of evacuated, foil gage honeycomb cryogenic insulation 

29 
RTR 763-01-41-21 4.3.1 Airframe Leading Edges 

OBJECTIVE: 

To develop innovative wing heat-pipe-cooled leading edge concepts for NASP type vehicles 

which offer substantial benefits such as reduced mass or increased reliability over other 

actively cooled design concepts. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 emphasis is on the design of a carbodcarbon heat pipe. Design, fabricate and 

test a carbodcarbon refractory metal heat pipe leading edge. Verify analytical methods by 

testing a 6-ft. liquid metal heat pipe designed for Shuttle I1 by McDonald Douglas Corp. 

MILESTONES: 

Complete design of carbodcarbon refractory metal heat pipe 

(MW 

o 

Complete design, September 1989 

Begin fabrication, September 1989 

FY 1988 ACCOMPLISHMENTS: 

FY 1989 new start 

Initiate testing of MDC heat pipe, March 1989 

30 
VI STRUCTURAL CONCEPTS BRANCH 

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32 
VI STRUCTURAL CONCEPTS BRANCH 

This Branch develops structures technology required to design future space systems including platforms, antennas, and space station. Research encompasses structural concepts, 

packaging, deployment, erection, and in-space construction. Theoretical work is supported 

by hardware development and experimental research. 

RTR 506-43-4 1 -02 Advanced Space Structural Concepts 

OBJECTIVE: 

To develop deployable and erectable structural concepts and associated design technology 

for antenna and reflector structures and for space station. 

FY 1989 PLANS: 

Support NASA JSC WETF (Weightless Environmental Training Facility) Mobile 

Transporter simulator tests 

Conduct truss accuracy analysis and design studies 

Conduct automated assembly tests of precision reflector truss 

APPROACH: 

In FY 1989 the main focus will be static and dynamic testing of a two-ring truss robotically 

constructed of 2-meter struts. Individual joints will also be tested and all results will be 

correlated with analysis. Continued emphasis will be placed on computer-aided design aids 

for structures. 

MILESTONES: 

0 

Static and dynamic tests of robotically assembled truss, February 1989 

Correlation of above test results with analysis, April 1989 

Fabricate and test all-composite erectable joint, June 1989 

Develop concept for a monorail astronaut mover, September 1989 

Completed, installed, and tested a Mobile Transporter simulator for JSC WETF 

Completed ground test of Mobile Transporter 

FY 1988 ACCOMPLISHMENTS: 

Completed 1-g tests of Mobile Transporter 

o Installed Mobile Transporter in NASA MSFC Neutral Buoyancy Simulator (NBS) 

e 

Conducted simulated 0-g test in MSFC NBS 

Developed 1-inch robotic compatible joint for automated assembly of high accuracy truss support structures 

33 
RTR 585-01 -31 -01 Precision Reflector Structures 

OBJECTIVE: 

To develop deployable and erectable structural concepts for precision reflectors. 

FY 1989 PLANS: 

Fabricate 2-ring PACTRUSS 

Fabricate 2-rin erectable truss with dynamic and accuracy tests and provide to 

Jet Propulsion k ab (JPL) 

APPROACH: 

In FY 1989 the main focus will be fabrication and testing of segments of an erectable and 

deployable PACTRUSS support structure. Also, a 2-ring erectable truss will be supplied to 

JPL as a testbed experimental article. NASTRAN analyses will be made of both test articles 

and results compared with test results. 

MILESTONES: 

Complete 2-ring erectable truss, March 1989 

Complete PACTRUSS deployable segment, March 1989 

Complete erectable LaRC tests, May 1989 

Complete PACTRUSS LaRC test, July 1989 

Complete correlation with NASTRAN, September 1989 

Held first technical interface meeting at JPL 

Initiated ASTRO PACTRUSS design task 

Developed new stepped PACTRUSS concept for eliminating deployment hard 

points 

Designed and fabricated two "zero-free play" deployable joints for PACTRUSS; 

testing initiated 

FY 1988 ACCOMPLISHMENTS: 

Developed erectable truss design 

Developed 1-inch erectable joint design 

RTR 591-22-11-01 Requirements for Pathfinder 

OBJECTIVE: 

To define structural and operational requirements for generic, heavily loaded mechanical 

joints. The joints will be used to assemble large spacecraft components on-orbit. 

I FY 1989 PLANS: 

I Complete definition of Pathfinder focus problem 

34 
APPROACH: 

A study will be conducted to (1) collect vehicle and mission descriptions from various 

NASA sources; (2) define structural and operational requirements for mechanical joints, 

such as loads, stiffness, component alignment, separation tolerances, and assembly time; and 

(3) identify existing and emerging mechanical joint technologies which enable on-orbit 

construction and identify the vehicle locations where mechanical joints may be applied. 

MILESTONES: 

Develop first draft of Pathfinder requirements document, June 1989 

FY 1988 ACCOMPLISHMENTS: 

Conducted first Pathfinder on-orbit construction inter-Center advisory group 

meeting in Washington, D. C. 

L 

Made Code Z mission study data dump to on-orbit construction advisory group at 

LaRC 

Conducted on-orbit construction advisory group FY 1989 planning meeting in 

Washington, D. C. 

RTR 59 1-22-2 1-01 Construction Concepts 

OBJECTIVE: 

The primary focus problem of the Pathfinder In-Space Assembly and Construction Program 

will be a large reentry spacecraft. In this task, construction concepts for the aerobrake 

support truss, which is part of the focus problem, will be developed and validated. 

FY 1989 PLANS: 

APPROACH: 

A study will be performed to size the aerobrake support truss. Concepts for constructing 

the support truss will be developed and evaluated based on design-for-construction criteria, 

Space cranes will be required to assemble the support truss. A 2-D space crane mockup will 

be designed and fabricated to serve as a testbed for evaluating crane actuator and articulating joint concepts. Concepts for telerobotic assembly sequence planning, which can be 

applied to an aerobrake support truss, will be developed. 

MILESTONES: 

FY 1988 ACCOMPLISHMENTS: 

0 FY 1989new start 

Develop space crane design and fabricate articulated joint 

Complete definition of 100-meter space crane, June 1989 

RTR 59 1 -22-3 1 -0 1 Joining Methods 

OBJECTIVE: 

To design heavily-loaded mechanical joint concepts for the aerobrake support truss. 

FY 1989 PLANS: 

35 
FY 1989 PLANS: 

APPROACH: 

Identify design concepts which meet the aerobrake support truss structural and construction 

requirements. The joint concepts will be assessed for ease of assembly, structural efficiency, 

tion. 

MILESTONES: 

FY 1988 ACCOMPLISHMENTS: 

FY 1989 new start 

Develop joint design for 200,000-pound aerobrake strut 

I 

I reliability, and ease of automated assembly. Candidate joints will be selected for fabricaFabricate a first generation heavily-loaded mechanical joint concept, April 1989 

I KTR 591 -22-4 1-01 Concept s/Tec h no logy Va I id at ion 

OBJECTIVE: 

To develop a testbed for evaluating heavily-loaded mechanical joints. 

FY 1989 PLANS: 

Develop testbed for evaluating heavily-loaded mechanical joints 

APPROACH: 

Test methodology will be developed for testing heavily-loaded mechanical joints. The 

methodology will assure that all joint concepts are compared and assessed on an equal basis, 

A testbed will be developed for testing joint strength, stiffness, and ease of assembly. 

MILESTONES: 

FY 1988 ACCOMPLISHMENTS: 

FY 1989newstart 

0 

Define testbed requirements and complete testbed design, May 1989 

J 

36 
VI1 AEROTHERMAL LOADS BRANCH 

37 
VI I AEROTHERMAL LOADS BRANCH 

This Branch conducts analytical and experimental research to identify and understand flow 

phenomena and flow/surface intereaction parameters required to define detailed aerothermal loads for thermal protection system and structural designs for high-speed flight vehicles. 

Devises and evaluates techniques for testing in high-energy true-temperature wind tunnels. 

Develops fluid-thermal-structural analysis methods and applies them to support experimental aerothermal loads investigations and to evaluate new structural concepts. Operates the 

%Foot High Temperature Tunnel, the Aerothermal Arc Tunnels (20 and 5 MW), and the 

7-Inch High Temperature Tunnel. 

The Experimental Facilities and Techniques Section of this Branch directs the operation 

and maintenance and effects improvements of equipment and operational techniques of the 

above-named facilities. Improves wind-tunnel technology, test techniques, and instrumentation for experimental determination of aerospace vehicle aerothermal loads, structural 

performance characteristics, and airbreathing engine performance. The prime purpose of 

this Section is the continued safe and efficient operation of these highly complex, high 

energy facilities. 

RTR 506-40-2 1-0 1 Aerothermal Loads 

OBJECTIVE: 

To define aerothermal loads for important viscous dominated flows including mass addition 

cooling, with emphasis on effects of surface roughness and 3-D structural interactions. 

Develop database and methodology for accurate prediction of aerothermostructural loads 

required to reduce design margins. 

IT 1989 PLANS: 

Document experimental results of Chine gap heating, and turbulent boundary 

layer characterization 

Validate analysis tools with experimental data for swept cylindrical leading edge, 

swept shock-on-lip, axial compression corner, and hypersonic vehicle (Mach 20) 

and fighter 

Develop implicit time marching scheme 

Improve triangle adaptive unstructured remeshing scheme for 3-D 

Evaluate higher order elements for CFD (Computational Fluid Dynamics) 

APPROACH: 

In FY 1989 a major milestone is the development of aposteriori error estimates for adaptive 

h and p finite element methods. Detailed flow field and surface distributions of pressures, 

temperatures, skin friction, and heat flux in laminar and turbulent flow will be obtained 

experimentally and analytically for viscous interacting flows attendant to generic configurations such as leading edges, gaps, corners, protuberances, wavy surfaces, and engine inlets. 

38 
Design, fabricate, and/or test simulated leading edge models, simulated compression surfaces, corners, slot film cooling and transpiration cooled, and other viscous interacting 

models. 

MILESTONES: 

Initiate development of combined h and p adaptive methods for finite element 

analysis of aerothermal loads in high-speed flows, December 1988 

Develop Taylor-Galerkin implicit finite element algorithm for unstructured grids, 

March 1989 

Develo aposteriori error indicators for adaptive meshing and hierarchical 

metho cf s for finite element fluid mechanics, June 1989 

Calibrate entropy variable based finite element algorithm on experimental and 

analytical shock-shock interaction results, September 1989 

FY 1988 ACCOMPLISHMENTS: 

Im lemented new finite element adaptive unstructured meshin procedures in 

L$SC pa e code, "Adaptive Com utational Methods for Aerot a ermal Heating Analysis," H, MSC-HEC PR F22577 f December 1987 

Documented experimental aerothermal results for split elevon as NASA TP 

Acquired VAX host computer to support experimental and analytical programs 

Developed implicit algorithm and ada tive grid techni ue for accurate prediction 

structured Grid Solver for the Euler and Navier Stokes Equations," AIM Paper 

No. 88-0036, January 1988 

Completed tests of turbulent boundary layer characterization in 8'HTT 

Calibrated adaptive Runge-Kutta finite element scheme for the Euler and Navier 

Stokes equation for shock-on-lip phenomena through comparison with experiment. "Application of Finite Element and Remeshing Techni ue to Shock Interference on a Cylindrical Leading Edge," AIAA Paper No. 88-0 8 68, January 1988 

Implemented real gas chemical equilibrium model in Runge-Kutta Euler code, 

AIAA Paper No. 88-0036 

of heat transfer rates. Incorporated E ARCNESS co 3 e. "A Point Implicit UnRTR 506-43-3 1-03 Integrated Fluid Thermal Structural Analysis 

Met hods 

OBJECTIVE: 

To develop advanced fluid-thermal-structural analysis methods for predicting the coupled 

nonlinear behavior of aerospace structures under combined fluid, thermal, and mechanical 

loads. 

FY 1989 PLANS: 

Extend adaptive unstructured grid enhancement to thermal and structural analysis 

Evaluate constitutive relationships/algorithms for nonlinear structural behavior 

39 
APPROACH: 

In FY 1989 a major milestone is the extension of LIFTS to three-dimensional thermal and 

structural analysis and the inclusion of the LARCNESS CFD algorithm. Analytical 

developments are focused on improved integrated fluid-thermal-structural analysis 

capability. Continue development of 2-D and 3-D integrated finite elements and apply to 

practical space transportation vehicles (Shuttle 11, NASP). Initiate/develop, in-house and 

under grant, finite element analysis capability focused on compressible viscous interactions 

and unified viscoplastic theory. Principal application focus will be to develop the capability 

to include surface interaction effects on steady and unsteady viscous flows about complex 

vehicle components including wing and fin leading edges and body junctions, protuberances, 

mass addition cooling, and control surfaces. 

MILESTONES: 

Incorporate LARNCESS fluid algorithm into LIFTS, December 1988 

Extend LInS thermal and structural capability to three dimensions, March 1989 

Evaluate implementation of viscoplasticity in LIFTS, September 1989 

Develop and validate model to account for the effects of temporal and s atial free 

tember 1989 

N 1988 ACCOMPLISHMENTS: 

Coupled flow-thermal-structural analysis of aerodynamically-heated, hydrogen 

cooled leadin edges with shock-on-lip with LIFTS code. "Flow-Thermal-Structural Study o f Aerodynamically Heated Leading Edges," AIM Paper No. 88- 

224S-CP, April 1988 

Prototype three-dimensional ada tive unstructured remeshin technique 

stream nonuniformities on stagnation point heating in incompressible K ow, Sepdemonstrated. "Finite Element E! uler Computations in Three B imensions," 

and dis ersion properties identi f ied. "An Ada tive Quadrilateral and Triangular 

AIAA Paper No. 88-0032, January 1988 

Two-dimensional unstructured rid enhancement technique developed; stability 

Finite k lement Scheme for Compressible F ows," AIAA Paper No. 88-0033, 

January 1988 

P 

RTR 506-43-3 1-05 Aerothermal Test Facilities and Test Methods 

OBJECTIVE: 

Provide test facilities required to support development of aerothermal loads database, advanced thermostructural concepts, and randscramjet engines. 

FY 1989 PLANS: 

APPROACH: 

In FY 1989 a major milestone is the shakedown of the 8'HTT. Test generic configurations 

to provide database for thermal structural design and validation of prediction techniques. 

Test advanced TPS under radiant heating, and under aerothermal conditions in Aerother0 Complete shakedown of transpiration cooled nozzle and oxygen 

40 
mal Loads Branch complex to verify thermal structural performance. Maintain high enthalpy facilities in ALB complex required for the determination of critical aerothermal loads for 

structural design and verification and certification of advanced thermostructural and airbreathing engine concepts. 

MILESTONES: 

Complete verification of DAS software for Modcomp, March 1989 

Complete development of VAX software for data reduction and verify, March 

1989 

Overhaul elevator cylinder and complete change to new hydraulic oil, March 1989 

Complete shakedown of transpiration cooled nozzle and oxygen, June 1989 

Initiate shakedown of Mach 4 and 5 nozzles and mixer, September 1989 

Completed aerothermal tests of Government NASP baseline vehicle, turbulent 

boundary layer study, and DoD shroud removal studies 

Completed checkout of Modcomp DAS 

Completed development and initiated verification of DAS software for Modcomp 

Verified, through use, the structural integrity of the 8’HTT water cooled approach 

section 

FY 1988 ACCOMPLISHMENTS: 

RTR 506-43-3 1 -06 8-Ft. High Temperature Tunnel Controls 

OBJECTIVE: 

To provide test facilities required to support development of aerothermal loads database, 

advanced thermostructural concepts, and radscramjet engines. 

FY 1989 PLANS: 

Integrate existing controls with new controls 

Build spare platelets for transpiration cooled nozzle 

APPROACH: 

A major milestone for FY 1989 is fabrication of a partial set of spare platelets for the 

transpiration cooled nozzle. Test generic configurations to provide database for thermal 

structural design and validation of prediction techniques. Test advanced TPS under radiant 

heating, and under aerothermal conditions in Aerothermal Loads Branch complex to verify 

for the determination of critical aerothermal loads for structural design and verification and 

certification of advanced thermostructural and air-breathing engine concepts. 

MILESTONES: 

t thermal structural performance. Maintain high enthalpy facilities in ALB complex required 

Fabricate spare platelet stacks for backup air transpiration cooled nozzle, March 

1989 

41 
FY 1988 ACCOMPLISHMENTS: 

Awarded contract for upgrade to 8'HT control system 

RTR 506-80-3 1-05 4.7.4 Detailed Aerotheriiial Loads 

OBJECTIVE: 

To define detailed aerothermal loads for important viscous dominated flows including heat 

transfer, skin friction and pressure with emphasis on effects of surface roughness, 3-D 

structural interactions, mass addition, and real gas effects. Develop a data base for accurate 

prediction of aerothermostructural loads required to reduce design margins. 

FY 1989 PLANS: 

Complete tests in Calspan and Langley tunnels for Mach Nos. 11-19 swept leading 

edge shock-on-li , transpiration cooled leadinl; edge with shock-on-lip, slot 

shock wave 

cooled model wit R shock wave interaction, and axial corner model with impinging 

Complete up rade Reynolds and Mach No. capability of Calspan 48"HST (HyperDocument results of NASP baseline vehicle aerodynamics - NASP/Boeing, and 

Mach 8 swept leading edge 

Fabricate and instrument perpendicular fuel injector model, and axial corner flow 

model 

Fonic Shock + unnel) 

APPROACH: 

In FY 1989 major thrusts will be the extension of the 2-D adaptive unstructured remeshing 

technique to three dimensions, and the completion of the slot film cooling and the transpiration cooled leading edge tests in the Calspan shock tunnels. Detailed flow field and surface 

distributions of pressure, temperatures, heating rates, and skin friction in laminar and turbulent flow will be obtained experimentally for leading edges, corners, protuberances, mass 

additional cooling concepts, and engine inlets. 

MILESTONES: 

Im lement and calibrate Baldwin-Lomax algebraic turbulence model in LARCN 8 SS code, December 1988 

Im lement and calibrate real gas chemical equilibrium model in LARCNESS 

I co B e, December 1988 

Com lete tests in Cals an 48"HST and data reduction for slot film cooling includComplete data reduction and documentation of transpiration cooled leading edge 

shock-on-lip study, March 1989 

Complete u grade to Calspan 48"HST for increased Mach and Reynolds number 

ing s K ock interaction e F fects, December 1988 

range, Marc Yl 1989 

I 

I 

42 
Complete axial compression corner with shock interaction tests with ceramic 

modevphase change paint at LaRC, reduce data, and document, March 1989 

Document 8'I-€TT aerothermal loads test results for baseline NASP vehicle, 

March 1989 

Demonstrate three-dimensional ada tive unstructured grids with inviscid analysis 

of NASP vehicle and viscous swept s K ock-shock interaction model, March 1989 

Document results from slot film cooling study, June 1989 

Initiate design, fabrication, and instrumentation of metallic axial compression 

corner model for shock tunnel tests in FY 1990, June 1989 

Design, fabricate, and instrument axial compression model for corner shock interaction aerothermal loads tests in the Calspan 48HST in FY 1990, September 

1989 

Complete following tests in Calspan shock tunnels: (a) 3-D laminar separation 

from interacting flows in an axial compression corner, and (b) flat plate/swept 

compression wedge, September 1989 

Fabricate wall fuel injection model for tests in FY 1990, September 1989 

FY 1988 ACCOMPLISHMENTS: 

Documented experimental results of shock-on-lip tests at Mach Nos. 11-19 including effects of multiple shock interaction. Studies of Aerothermal Loads 

Generated in Re ions of ShocMShock Interaction in Hypersonic Flow," AIAA 

Designed and fabricated ceramic axial compression corner model which simulates 

engine compression ramps and control surfaces 

Com leted aerothermal loads tests of NASP baseline vehicle in NASA LaRC 

Paper No. 88-047 .$ , January 1988 

8" 7Er 

Designed, fabricated, instrumented, and initiated tests of film cooled model with 

shock interaction in the Calspan 48"HST 

Contract awarded to Calspan for transpiration cooled leading edge shock-on- lip 

study and upgrade to Calspan 48"HST for increased Mach and Reynolds number 

range 

\ 

43 
VI11 

f 

ACCOMPLISHMENT HIGHLIGHTS 

PRECEDING PAGE BUNK NOT FlLMED 

45 
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85 
IX PUBLICATIONS AND PRESENTATIONS 
I IX PUBLICATIONS AND PRESENTATIONS 

The FY 1988 accomplishments resulted in a number of publications and presentations. 

They are listed below as Formal Reports, High-Nmbered Technical Memorandums, Contractor Reports, Journal Articles and Other Publications, Meeting Presentations, Technical 

Talks, Computer Programs, Tech Briefs, and Patents. 

Formal Reports 

Camarda, C. J.; and Riley, M. F.: Application of Formal Optimization Techniques in ThermaVStructura1 Design of a Heat-Pipe-Cooled Panel for a Hypersonic Vehicle. NASA TM89131, October 1987 

Glass, C. E.; and Hunt, L. R.: Aerothermal Tests of Quilted Dome Models on a Flat Plate 

at a Mach Number of 6.5. NASA TP-2804, May 1988 

Lake, M. S.; and Wu, K. C.: Preliminary Investigation of Stability of a Fin-Stiffened Slender 

Strut. NASA TM-4034, April 1988 

Noor, A. K.; and Mikulas, M. M., Jr.: Continuum Modeling of Large Lattice Structures - 

Status and Projections. NASA TP-2767, February 1988 

Nowak, R. J.: Gas-Jet and Tangent-Slot Film Cooling Tests of a 12.5 Degree Cone at Mach 

Number of 6.7. NASATP-2786, May 1988 

High-Numbered Technical Menioranduins 

Bales, K. S.: Structures and Dynamics Division Research and Technology Plans for FY 1988 

and Accomplishments for FY 1987. NASA TM-100585, May 1988 

Blosser, M. L.: Thermal Stress in High Temperature Cylindrical Fasteners. NASA TM100611, May 1988 

Dechaumphai, P.; Thornton, E. A.; and Wieting, A. R.: Fluid-Thermal-Structural Study of 

Aerodynamically Heated Leading Edges. NASA I’M- 100579, April 1988 

Dorsey, J. T.: Structural Analysis of the Space Shuttle Solid Rocket Booster/External Tank 

Attach Ring. NASA TM-100510, January 1988 I 

Gillian, R. E.; and Lotts, C. G.: The CSM Testbed Software System: A Development 

Environment for Structural Analysis Methods on the NAS CRAY-2. NASA TM-100642, 

September 1988 

I 

I Greene, W. H.; and Haftka, R. T.: Computational Aspects of Sensitivity Calculations in 

Transient Structural Analysis. NASA TM-100589, April 1988 

88 
Jegley, D. C.: An Analytical Study of the Effects of Transverse Shear Deformation and 

Anisotropy on Natural Vibration Frequencies of Laminated Cylinders. NASA TM- 100554, 

January 1988 

Jegley, D. C.: An Analytical Study of the Effects of Transverse Shear Deformation and 

Anisotropy on Buckling Loads of Laminated Cylinders. NASA TM-100508, October 1987 

Knight, N. F., Jr.; Gillian, R. E.; and Nemeth, M. P.: Preliminary 2-D Shell Analysis of the 

Space Shuttle Solid Rocket Boosters. NASA TM-1005 15, March 1988 

Lucas, S. H.; and Scotti, S. J.: The Sizing and Optimization Language (SOL) - A Computer 

Language for Design Problems. NASA TM-100565, April 1988 

McComb, H. G., Jr. (Compiler): Redesign of Solid Rocket Booster/External Tank Attachment Ring for the Space Transportation System. NASA TM-100476, October 1987 

Raju, I. S.; and Fichter, W. B.: A Finite-Element Alternating Method for Two-Dimensional 

Mode-I Crack Configurations. NASA TM-100616, May 1988 (SES 88-89) 

Sawyer, J. W.: Investigation of Test Techniques for Measuring Interlaminar Shear Strength 

of Two-Dimensional Carbon-Carbon Composites. NASA TM- 100647, September 1988 

Sawyer, J. W.: Effects of Impact Damage and Holes on Compression Strength of Two-Dimensional Carbon-Carbon Composites. NASA TM-89150, October 1987 

Scotti, S. J.; Martin, C. J., Jr.; and Lucas, S. H.: Active Cooling Design for Scramjet Engines 

Using Optimization Methods. NASA TM-100581, March 1988 

Watson, J. J.; and Heard, W. L., Jr.: A 60-Meter Erectable Assembly Concept for a Control 

of Flexible Structures Flight Experiment. NASA TM-100497, February 1988 

Wieting, A. R.; Dechaumphai, P.; Bey, K. S.; Thornton, E. A.; and Morgan, K.: Application 

of Integrated Fluid-Thermal-Structural Analysis Methods. NASA TM- 100625, May 1988 

Contractor Reports 

Barkey, D. A.; and Madan, R. C.: Manual for Program PSTRESS: Peel Stress Computation. NASA CR-178408, December 1987 (McDonnell Douglas Corporation, NAS 1-17970) 

Madan, R. C.: Composite Transport Wing Technology Development. NASA CR-178409, 

February 1988 (NAS1- 17970, McDonnell Douglas Corporation) 

Rankin, C. C.: Consistent Linearization of the Ekrnent-Independent Corotational Formulation for the Structural Analysis of General Shells. NASA CR-178418, January 1988 

(NAS1-18101, Lockheed Missiles and Space Company, Inc.) 
Sensmeier, M. D.; Griffin, 0. H., Jr.; and Johnson, E. R.: Static and Dynamic Large Deflection Flexural Response of Graphite- Epoxy Beams. NASA CR-4203, March 1988 (NAGI343, Virginia Polytechnic Institute and State University) 

I Journal Articles and Other Publications 

Camarda, C. J.; and McGowan, D. M.: (Subject sensitive, title omitted). NASP TM-1022, 

June 1988 (Special Document) c 

Card, M. F.; and Starnes, J. H., Jr.: Current Research in Composite Structures at NASA's 

Langley Research Center. Sadhana, Volume 11, Parts 3 & 4, December 1987, p. 277-298 

I Davis, J. G., Jr.: (Subject sensitive, title omitted). NASP TM-1017, May 1988 

Davis, J. G., Jr.; and Dixon, S. C.: Beyond Simulation. Aerospace America, July 1988, 

Volume 26, No. 7, p. 38-42 

Greene, W. H.; Knight, N. F., Jr.; and Stockwell, A. E.: Structural Behavior of the Space 

Shuttle SRM Tang-Clevis Joint. Journal of Propulsion and Power, Volume 4, No. 4, July - 

August 1988, p. 317-327 ' Haftka, R. T.; and Starnes, J. H., Jr.: Stiffness Tailoring for Improved Compressive Strength 

of Composite Plates with Holes. AIAA Journal, Vol. 26, No. 1, January 1988, p. 72-77 

I 

I 

~ 

Holden, M. S.; Wieting, A. R.; and Glass, C. E.: (Subject sensitive, title omitted). NASP I CR-1014, May 1988 (Special Document) 

Knight, N. F., Jr.; and Starnes, J. H., Jr.: Postbuckling Behavior of Selected Curved Stiffened Graphite-Epoxy Panels Loaded in Axial Compression. AIM Journal, Vol. 26, No. 3, 

March 1988, p. 344-352 

Nemeth, M. P.: Buckling Behavior of Compression-Loaded Symmetrically Laminated 

Angle-Ply Plates with Holes. AIM Journal, Vol. 26, No. 3, March 1988, p. 330-336 

Noor, A. K.; and Mikulas, M. M., Jr.: Continuum Modeling of Large Lattice Structures: 

A. K. Amos, eds., Springer-Verlag, 1988, p. 1-34 

I 

I 

Status and Projections. In Large Space Structures: Dynamics and Control, S. N. Atluri and 

Thurston, G. A.; and Stein, P. A,: An Experiment for Determining the Euler Load by 

Direct Computation. Experimental Mechanics, Volume 28, No. 1, March 1988, p. 70-76 ~ 

Thurston, G. A.; Reissner, J. E.; Stein, P. A.; and Knight, N. F., Jr.: Error Analysis and 

Correction of Discrete Solutions From Finite-Element Codes. AIAA Journal, Volume 26, 

No. 4, April 1988, p. 446-453 
Meeting Presentations 

Blosser, M. L.: Thermal Stress in High 'Temperature Cylindrical Fasteners. Presented at 

the AIAA, ASME, et al., 29th Structures, Structural Dynamics and Materials Conference, 

April 18-20, 1988, Williamsburg, Virginia. AIM Paper No. 88-2246-CP 

Bonnani, D. L.; Johnson, E. R.; and Starnes, J. H., Jr.: Local Crippling of Thin-Wailed 

Graphite-Epoxy Stiffeners. Presented at the AIM, ASME, et al., 29th Structures, Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, Virginia. 

AIM Paper No. 88-225 1-CP 

Bostic, S. W.; and Fulton, R. E.: Vibration Analysis Using a Parallel Lanczos Method, 

Presented at the ASCE National Convention on Parallel and Distributed Processing in 

Structural Engineering, May 9- 13, 1988, Nashville, Tennessee. In Proceedings, Parallel and 

Distributive Processing in Structural Engineering Session 

Camarda, C. J.: (Subject sensitive, title omitted). Presented at the Fourth National AeroSpace Plane Technology Symposium, February 17- 19, 1988, Monterey, California. In NASP 

CP-4027, Volume VI, p. 157-188 

Camarda, C. J.: Thermostructural Applications of Heat Pipes for High-speed Aerospace 

Vehicles. Presented at the Third International Heat Pipe Symposium, September 12- 14, 

1988, Tsukuba City, Japan. In Proceedings, p. 348-357 

Card, M. F.; and Starnes, J. H., Jr.: Current Research in Composite Structures at NASA's 

Langley Research Center. Presented at the Indian Institute of Technology, Aeronautical 

Society of India, et al., International Conference on Composite Materials and Structures, 

January 6-9, 1988, Madras, India. In Composite Materials and Structures, K. A. V. Pandalai, 

ed., Academy of Sciences, Bangalore, India, 1988, p. 5-26 

Davis, J. G., Jr.: (Subject sensitive, title omitted). Presented at the Fourth National AeroSpace Plane Technology Symposium, February 17- 19, 1988, Monterey, California. In NASP 

CP-4027, Volume VI, p. 1-70 

Davis, R. C.: Direct Solution for Thermal Stresses in a Nose Cap Under an Arbitrary 

Axisymmetric Temperature Distribution. Presented at the AIAA, ASME, et al., 29th Structures, Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, 

Virginia. AIAA Paper No. 88-2247-CP 

Dechaumphai, P.; Thornton, E. A.; and Wieting, A. R.: Flow-Thermal-Structural Study of 

Aerodynamically Heated Leading Edges. Presented at the AIAA, ASME, et al., 29th Structures, Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, 

Virginia. AIAA Paper No. 88-2245-CP 

91 
Dechaumphai, P.; Wieting, A. R.; and Pandey, A. K.: Finite Element Flow-Thermal-Structural Analysis of Aerodynamically Heated Leading Edges. Presented at the Second 

NASA/Air Force Symposium on Recent Experiences in Multidisciplinary Analysis and Optimization, September 28-30, 1988, Hampton, Virginia. NASA CP pending 

I Dechaumphai, P.; Wieting, A. R.; and Thornton, E. A.: (Subject sensitive, title omitted). 

19, 1988, Monterey, California. In NASP CP-4027, Volume VI, p. 71-90 I 

Presented at the Fourth National Aero-Space Plane Technology Symposium, February 17- 

I 

I 

Dorsey, J. T.; Stein, P. A,; and Bush, H. G.: Lightweight Structural Design of a Bolted Case 

Joint for the Space Shuttle Solid Rocket Motor. Presented at the AIAA/ASME/SAE/ASEE 

24th Joint Propulsion Conference and Exhibit - "Thrust for the 21st Century," July 11-13, 

1988, Boston, Massachusetts. AIAA Paper No. 88-3321 

Gillian, R. E.: CSM Research: Testbed Development. Presented at the NASA Workshop 

on Computational Structural Mechanics, November 18-20, 1987, Hampton, Virginia. 

NASA CP-10012, Part 2, February 1989, p. 387-417 

I Heard, W. L., Jr.; Bush, H. G.; and Watson, J. J.: Space Truss Construction Studies. Presented at the ASCE, U.S. Army Corps of Engineers, et al., SPACE 88 - Engineering, 

Construction, and Operations in Space Conference, August 29-3 1, 1988, Albuquerque, New 

Mexico. In Proceedings, p. 722-733 , 

Heard, W. L., Jr.; Bush, H. G.; Watson, J. J.; Spring, S. C.; and Ross, J. L.: Astronaut/EVA 

Construction of Space Station. Presented at the AIMNASA Space Station Symposium, 

April 21-22, 1988, Williamsburg, Virginia. AIAA Paper No. 88-2454-CP 

Heard, W. L., Jr.; Watson, J. J.; Ross, J. L.; Spring, S. C.; and Havens, K. A.: EVA Space 

Construction: Experience and Fundamental Issues. Presented at the 34th Annual Meeting 

of the American Astronautical Society on Space - A New Community of Opportunity, 

November 2-5, 1987, Houston, Texas. Proceedings pending 

Jegley, D. C.: An Analytical Study of the Effects of Transverse Shear Deformation and 

Anisotropy on Natural Vibration Frequencies of Laminated Cylinders. Presented at the 4th 

Japan-United States Conference on Composite Materials, June 27-29, 1988, Washington, 

D.C.(SES 88-89). Proceedings pending 

Knight, N. F., Jr.: CSM Research: Methods and Application Studies. Presented at the 

NASA Workshop on Computational Structural Mechanics, November 18-20, 1987, Hampton, Virginia. NASA CP-10012, Part 2, February 1989, p. 521-570 

I 

I Knight, N. F., Jr.; Gillian, R. E.; and Nemeth, M. P.: Nonlinear Analysis of Large Shell 

Structures, Presented at the 1988 International Conference on Computational Engineering 

Science (ICES '88), April 10-14, 1988, Atlanta, Georgia, In Proceedings, Volume 1, Section 

26.4 

, 

92 
Librescu, L.; and Stein, M.: The Use of Higher-Order Theory in the Postbuckling Analysis 

of Shear-Deformable Symmetrically-Laminated Composite Flat Panels. Presented at the 

16th Congress of the International Council of the Aeronautical Sciences (ICAS), August 

28-September 2, 1988, Jerusalem, Israel 

Lopez, 0. F.; Jegley, D. C.; and Shuart, M. J.: Advanced Concepts for Composite Structures. Presented at the AFWAL Materials Laboratory Twelfth Annual Mechanics of Composites Review, October 16-17, 1987, Bal Harbour, Florida. Abstract published in proceedings, p. 58-67 

Lucas, S. H.; and Scotti, S. J.: The Sizing and Optimization Language (SOL)-A Computer 

Language to Improve the User/Optimizer Interface. Presented at the Second NASA/Air 

Force Symposium on Recent Experiences in Multidisciplinary Analysis and Optimization, 

September 28-30, 1988, Hampton, Virginia 

Madan, R. C.; and Shuart, M. J.: Impact Damage and Residual Strength Analysis of Composite Panels with Bonded Stiffeners. Presented at the ASTM Symposium on Composite 

Materials: Testing and Design, April 27-29, 1988, Sparks, Nevada 

McGowan, P. E.; Edighoffer, H. H.; and Ting, J. M.: Structural Dynamics Research on 

Scale Model Spacecraft Trusses. Presented at the Second NASADOD CSI Technology 

Conference, November 17- 19, 1987, Colorado Springs, Colorado. Proceedings pending 

Ramakrishnan, R.; Bey, K. S.; and Thornton, E. A.: An Adaptive Quadrilateral and Triangular Finite Element Scheme for Compressible Flows. Presented at the AIAA 26th Aerospace Sciences Meeting, January 11-14,1988, Reno, Nevada. AIM Paper No. 88-0033 

Ramakrishnan, R.; Thornton, E. A.; and Wieting, A. R.: An Adaptive Finite Element 

Procedure for Compressible Flows With Strong Viscous-Inviscid Interactions. Presented at 

the AIAA Thermophysics, Plasmadynamics, and Lasers Conference, June 27-29, 1988, San 

Antonio, Texas. AIAA Paper No. 88-2694 

Sawyer, J. W.: Investigation of Test Techniques for Measuring Interlaminar Shear Strength 

of Two-Dimensional Carbon-Carbon Composites. Presented at the United States Advanced Ceramics Association 12th Conference on Composites Materials and Structures, 

January 10-22, 1988, Cocoa Beach, Florida. In NASA CP-3018 

Scotti, S. J.; and Martin, C. J., Jr.: (Subject sensitive, title omitted) Presented at the Fourth 

National Aero-Space Plane Technology Symposium, February 17- 19, 1988, Monterey, California. In NASP CP-4027, Volume VI, p. 117-140 

Scotti, S. J.; Martin, C. J., Jr.; and Lucas, S. H.: Active Cooling Design for Scramjet Engines 

Using Optimization Methods. Presented at the AIM, ASME, et al., 29th Structures, Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, Virginia. 

AIAA Paper No. 88-2265-CP 

93 
Shuart, M. J.: Failure of Compression-Loaded Multi-Directional Composite Laminates. 

Presented at the AIMASME, et al., 29th Structures, Structural Dynamics and Materials 

Conference, April 18-20, 1988, Williamsburg, Virginia. AIM Paper No. 88-2293-CP 

Shuart, M. J.; Haftka, R. T.; and Campbell, R. L.: Optimum Design of Swept-Forward 

High-Aspect Ratio Graphite-Epoxy Wings. Presented at the Second NASA/Air Force Symposium on Recent Experiences in Multidisciplinary Analysis and Optimization, September 

28-30, 1988, Hampton, Virginia. NASA CP pending 

Sistla, R.; and Thurston, G. A.: Error Analysis of Finite Element Solutions for Postbuckled 

Plates. Presented at the AIMASME, et al., 29th Structures, Structural Dynamics and 

Materials Conference, April 18-20, 1988, Williamsburg, Virginia. AIAA Paper No. 88- 

22 16-CP 

Starnes, J. H., Jr.; and Johnston, N. J.: Advanced Composites Technology Program at 

NASA Langley. Presented at the Fifth AFWAL Industry/Government Review of Thermoplastic Matrix Composites, February 8-11, 1988, San Diego, CA 

Stein, M.: Postbuckling of Eccentric Open-Section Stiffened Composite Panels. Presented 

at the AIMASME, et al., 29th Structures, Structural Dynamics, and Materials Conference, 

April 18-20, 1988, Williamsburg, Virginia. AIAA Paper No. 88-22 15-CP 

I Stein, M.: Postbuckling Analysis of Composite Plates. Presented at the AFWAL Materials 

Laboratory Twelfth Annual Mechanics of Composites Review, October 16-17, 1987, Bal 

Harbour, Florida. Abstract published in proceedings, p. 99- 108 

Stein, M.: Postbuckling of Eccentric Open-Section Stiffened Composite Panels. Presented 

by Dr. G. Thurston at the 16th Congress of the International Council of the Aeronautical 

Sciences (ICAS), August 28-September 2, 1988, Jerusalem, Israel. ICAS Paper No. 88-5.6.2 

Stewart, J. R.; Thareja, R. R.; Wieting, A. R.; and Morgan, K.: Application of Finite 

Element and Remeshing Technique to Shock Interference on a Cylindrical Leading Edge. 

Presented at the AIAA 26th Aerospace Sciences Meeting, January 11-14, 1988, Reno, 

Nevada. AIAA Paper No. 88-0368 

Storaasli, 0. 0.: CSM Parallel Structural Methods Research. Presented at the NASA 

Workshop on Computational Structural Mechanics, November 18-20, 1987, Hampton, Vir- 

~ ginia. NASA CP pending 

Storaasli, 0. 0.; Bostic, S. W.; Patrick, M.; Mahajan, U.; and Ma, S.: Parallel Methods for 

Structural Vibration Analysis. Presented at the AIMASME, et al., 29th Structures, Structural Dynamics and Materials Conference, Apil 18-20, 1988, Williamsburg, Virginia. 

AIAA Paper No. 88-2391-CP 

94 
. 

Storaasli, 0. 0.; Poole, E. L.; Ortega, J. M.; and Cleary, A. J.: Solution of Structural 

Analysis Problems on a Parallel Computer. Presented at the AIMASME, et al., 29th 

Structures, Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, 

Virginia. AIAA Paper No. 88-2287-CP 

Swanson, G. D.; Gurdal, 2.; and Starnes, J. H., Jr.: Structural Efficiency Study of GraphiteEpoxy Aircraft Rib Structures. Presented at the AIAA, ASME, et al., 29th Structures, 

Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, Virginia. 

AIAA Paper No. 88-2218-CP 

Taylor, A. H.: Advanced Carbon-Carbon for Piston Structures. Presented at the United 

States Advanced Ceramics Association 12th Conference on Composites Materials and 

Structures, January 20-22, 1988, Cocoa Beach, Florida. In NASA CP-3018 

Taylor, A. H.: Design Considerations for Advanced Cryogenic Tank Structural Concepts. 

Presented at the ASM/WESTEC Aluminum Lithium Symposium, March 22-24, 1988, Los 

Angeles, California. Proceedings pending 

Wieting, A. R.; Dechaumphai, P.; Bey, K. S.; Thornton, E. A.; and Morgan, K.: Application 

of Integrated Fluid-Thermal- Structural Analysis Methods. Presented by P. Dechaumphai 

at the 16th Congress of the International Council of the Aeronautical Sciences (ICAS), 

August 28-September 2, 1988, Jerusalem, Israel. ICAS Paper No. 88-2.3.3 

Wieting, A. R.; Thareja, R. R.; Stewart, J. R.; and Morgan, K.: (Subject sensitive, title 

omitted). Presented at the Fourth National Aero-Space Plane Technical Symposium, February 17-19, 1988, Monterey, California. In NASP CP-4027, Volume VI, p. 225-246 

Technical Talks 

Camarda, C. J.: Aerothermal and Radiant Heating Tests of a Heat-Pipe-Cooled Leading 

Edge. Presented at the National Space Development Agency of Japan (NASDA) Workshop on Prospects of Future Thermal Technology in Space, September 16, 1988, Tokyo, 

Japan 

Camarda, C. J.: Use of Formal Optimization Methods for Designing Hybrid Heat-Pipe 

Actively Cooled Panels for Hypersonic Transport Vehicles. Presented at the National 

Space Development Agency of Japan (NASDA) M’orkshop on Prospects of Future Thermal 

Technology in Space, September 16,1988, Tokyo, japan 

Holden, M.; Wieting, A. R.; Mosselle, J.; and Glass, C.: Studies of Aerothermal Loads 

Generated in Regions of Shock-Shock Interaction in Hypersonic Flow. Presented at the 

AIAA 26th Aerospace Sciences Meeting, January 11-14, 1988, Reno, Nevada. AIAA Paper 

NO. 88-0477 

95 
Jegley, D. C.: Advanced Concepts for Composite Structures. Presented at the Annual 

Committee Meeting of the American Helicopter Society at Langley, November 5,1987 

Lucas, S. H.; and Scotti, S. J.: The Sizing and Optimization Language - A Computer Language for Design Problems. Presented at the AIAA, ASME, et al., 29th Structures, Structural Dynamics and Materials Conference, April 18-20, 1988, Williamsburg, Virginia 

Mikulas, M. M., Jr.: On-Orbit Construction of Large Space Structures, Presented at the 

International Space University Project, July 14, 1988, Boston, Massachusetts 

Peraire, J.; Peiro, J.; Farmaggia, L.; Morgan, K.; and Zienkiewiez, 0.: Finite Element Euler 

Computations in Three Dimensions. Presented at the AIAA 26th Aerospace Sciences Meeting, January 11-14,1988, Reno, Nevada. AIAA Paper No. 88-0032 

Puster, R. L.; and Reubush, D. E.: Development and Modification of the Langley 8-Foot 

High Temperature Tunnel for Propulsion Testing and Improved Test Capability. Presented 

at the 68th Semiannual Meeting of the Supersonic Tunnel Association, October 22-23, 1987, 

Columbus, Ohio 

Thareja, R.; Stewart, J.; Hasson, 0.; Morgan, K.; and Peraire, J.: A Point Implicit Unstructured Grid Solver for the Euler and Navier Stokes Equations. Presented at the AIAA 

26th Aerospace Sciences Meeting, January 11-14, 1988, Reno, Nevada, AIAA Paper No. 

88-0036 

Computer Programs 

Sistla, R. (Analytical Services and Materials, Inc.); Thurston, G. A.; and Bains, N. J. C. 

(Langley Research Center): EAC: A Program for the Error Analysis of STAGS Results for 

Plates (DEC, VAX Version). NASA Tech Brief LAR-14063 

Sistla, R. (Analytical Services and Materials, Inc.); Thurston, G. A.; and Bains, N. J. C. 

(Langley Research Center): EAC: A Program for the Error Analysis of STAGS Results for 

Plates (CDC, CYBER Version). NASA Tech Brief LAR-14064 

Tech Briefs 

Camarda, C. J.; and Ransone, P. 0.: Heat-Pipe-Cooled Carbon-Carbon Panels. NASA 

Tech Brief LAR-13761 

Pate n t s 

Davis, R. C.; and Jackson, L. R.: Truss-Core Corrugation for Compressive Loads. U.S. 

Patent 4,769,968, issued September 13, 1988 

Davis, R. C.; Taylor, A. H.; Jackson, L. R.; and McAulifee, P. S.: Cryogenic Insulation 

System. U.S. Patent 4,774,118, issued September 27,1988 

96 
Singh, J. J.; Sprinkle, D. R.; and Puster, R. L.: Method and Device for Determining Heats 

of Combustion of Gaseous Hydrocarbons. U.S. Patent 4,761,744, issued August 2, 1988 

Taylor, A. H.: Composite Piston. U.S. Patent 4,736,676, issued April 12, 1988 

v 

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I 

97 
Report Documentation Page 

1. Report No. 

NASA TM-101592 

2. Government Accession No. 

4. Title and Subtitle 

Structural Mechanics Division 

Research and Technology Plans for FY 1989 and 

Accomplishments for FY 1988 

Kxey Words (Suggested by Authorlsjl 

Objective, Plans, Approach, Milestones, 

Accomplishments 

7. Authork) 

___-__ 18. Clistribution Statement 

Urclassified - Unlimited 

Subject Category 39 

- ___ 

Kay S. Bales 

19. Security Classif. (of this report) 20. Security Classif. lof this pes e) 

Uncl ass i f i ed Unclassifjed 

9. Performing Organization Name and Address 

21. No. of pages 22. Price 

102 A06 

NASA Langley Research Center 

Hampton, VA 23665-5225 

12. Sponsoring Agency Name and Address 

National Aeronautics and Space Admini strati on 

Washington, DC 20546-0001 

15. Supplementary Notes 

3. Recipient's Catalog No. 

5. Report Date 

July 1989 -____ 

6. Performing Organization Code 

8. Performing Organization Report No. 

10. Work Unit No. 

506-40-21-01 

11. Contract or Grant No. 

13. Type of Report and Period Covered 

Technical Memorandum 

14. Sponsoring Agency Code 

16. Abstract 

This paper presents the Objectives, FY 1989 Plans, Approach, and FY 1989 

Milestones for the Structural Mechanics Division's research programs. 

FY 1988 Accomplishments are presented where applicable. 

is useful in program coordination with other governmental organizations 

in areas of mutual interest. 

This information 

Y