Swaged tube and duct connector feasibility
Design of fluid line connectors depending solely upon cold forming of metal to carry structural loads and to make helium leak-tight seal
SEALING↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Air shock parameters and design criteria for rocket explosions
Rocket explosion air blast parameters and design in relation to structural load calculations
ROCKET FIRING↗
Gemini Program Mission Report for Gemini-Titan 1 (GT-1)
The Gemini-Titan 1 (GT-1) space vehicle was comprised of the Gemini spacecraft and the Gemini launch vehicle. The Gemini launch vehicle is a two-stage modified Titan II ICBM. The major modifications are the addition of a malfunction detection system and a secondary flight controls system. The Gemini spacecraft, designed to carry a crew of two men on earth orbital and rendezvous missions, was unmanned for the flight reported herein (GT-1). There were no complete Gemini flight systems on board; however, the C-band transponder and telemetry transmitters were Gemini flight subsystems. Dummy equipment, having a mass and moment of inertia equal to flight system equipment, was installed in the spacecraft. The Spacecraft was instrumented to obtain data on spacecraft heating, structural loading, vibration, sound pressure levels, and temperature and pressure during the launch phase.
Source record↗
Dynamic stability of space vehicles. Volume 14 - Testing for booster propellant sloshing parameters
Recommended procedures for stability, control, and structural loading analysis of large liquid fueled rocket booster sloshing parameters
Eggleston, D. M.↗
Rocket exhaust-plume problems and some recent related research.
Rocket exhaust plume problems including heating, structural loads, line of sight interference and radio signals attenuation
Andrews, E. H., Jr.↗
Helicopter rotor periodic differential pressures and structural response measured in transient and steady-state maneuvers
Helicopter rotor blade differential pressure and structural load characteristics in transient and steady state maneuvers
Ward, J. F.↗
Flight tests of cross, modified ringsail, and disk-gap-band parachutes from a deployment altitude of 3.05 km /10,000 ft/
Flight tests of cross, modified ringsail, and disk-gap-band parachute deployment performance from low altitudes with structural load data
Eckstrom, C. V.↗
Some Aspects of NASTRAN Solution Accuracy
Accuracy, adequacy, and limitations of NASTRAN computer program static load structural analysis solutions
Haggenmacher, G. W.↗
A launch vehicle stability analysis using the parameter plane method
Launch vehicle attitude control system for lateral drift minimization and prevention of structural load limit exceeding maneuvers, presenting stability analysis
Seltzer, S. M.↗
The application of optimal control technqiues to advanced manned missions, volume 1
Two problems are presented in the area of optimal control and its application to the design of attitude control systems for advanced complex aerospace vehicles. The problems discussed are specification of performance criteria in terms of structural load minimization and/or maximum orbital payload injection requirements of the controlled vehicle; and formulation and solution of the optimization problem such that practical control systems are obtained.
Connor, C. L.↗
An analytical study of airplane-autopilot response to atmospheric turbulence
An analytical study has shown that, with proper selection of feedback gains, an automatic control system can reduce excursions in altitude of a jet transport flying in turbulence without increasing structural loads. The control system uses feedback of attitude-angle and pitch-rate signals to the elevator and uses feedback of altitude and altitude-rate signals to the throttle.
Oehman, W. I.↗
Structural design aspects of reusable surface insulation thermal protection systems.
Low density fiber ceramic materials coated with refractory ceramics meet the requirements of reusable low weight thermal protection systems. The structural characteristics of this class of material impose unique design and analysis requirements on the application to spacecraft structural elements. Finite element type stress analysis techniques are required to adequately predict the structural response of the system. Parametric analyses have been performed to determine the response of the system to variations in geometry, and to thermal and structural load conditions. Sensitivity of coating, insulation and attachment stresses are presented and critical failure modes are identified.
Michalak, R. J.↗
Development of lightweight graphite/polyimide sandwich panels, phases 3, 4 and 5
Work performed in the last three phases of the program included: (1) face sheet processing; (2) honeycomb core manufacture; (3) face sheet-to-core bonding development; and (4) sandwich panel fabrication and testing. Resin cure studies were a major portion of this effort since processing problems traced to the polyimide matrix resin had to be resolved before quality core and face sheets could be fabricated. Honeycomb core fabrication and testing were conducted by Hexcel Corporation. A total of four graphite/polyimide resin composite cores were fabricated, tested, and reported. Two sandwich panels weighing .48 and .58 lb/sq ft, respectively were designed and fabricated which meet the support structure loads for the shuttle orbiter thermal protection system.
Merlette, J. B.↗
Rocket ascent G-limited moment-balanced optimization program (RAGMOP)
This document describes the RAGMOP (Rocket Ascent G-limited Momentbalanced Optimization Program) computer program for parametric ascent trajectory optimization. RAGMOP computes optimum polynomial-form attitude control histories, launch azimuth, engine burn-time, and gross liftoff weight for space shuttle type vehicles using a search-accelerated, gradient projection parameter optimization technique. The trajectory model available in RAGMOP includes a rotating oblate earth model, the option of input wind tables, discrete and/or continuous throttling for the purposes of limiting the thrust acceleration and/or the maximum dynamic pressure, limitation of the structural load indicators (the product of dynamic pressure with angle-of-attack and sideslip angle), and a wide selection of intermediate and terminal equality constraints.
Lyons, J. T.↗
Environmental testing of REI-Mullite thermal protection system for the space shuttle orbiter
Tests conducted to evaluate performances in the natural environments of salt spray, humidity, rain, vacuum, and cryogenic temperatures have shown the ceramic mullite fiber is completely compatible and that these environments have no adverse effects on subsequent mission performance. Rain erosion testing has indicated a damage threshold that must be accounted for in the final design. Tests conducted to evaluate the performance of ceramic mullite fiber to induced acoustic, re-entry, and structural load environments again have shown complete capability to fulfill mission environments. Although minor cracking of the sidewall coating was seen to occur throughout the induced environment test program, sidewall designs configured to provide increased flexibility have been successfully tested.
Gluck, R.↗
Development of lightweight graphite/polyimide sandwich panels.
Lightweight graphite/polyimide composite honeycomb core and sandwich panels were fabricated and tested. Honeycomb cores of 1/4-in. and 3/8-in. cell sizes of hexagonal configuration were produced from thin plus or minus 45 deg cross plied sheets of prepreg producing core weights between 1.8 and 3.6 lb/cu ft. Thin gauge prepreg using Hercules graphite tow and Monsanto Skybond 710 polyimide resin were manufactured to produce cured ply thicknesses of 0.001 to 0.002 in. Graphite core properties measured at temperatures from -150 to 600 F are reported. Core properties which are superior to available materials were obtained. Sandwich panels weighing less than 0.5 lb/sq ft were designed and fabricated which meet the support structure loads for the shuttle orbiter thermal protection system.
Poesch, J. G.↗
Space Shuttle booster recovery planning.
At the initiation of the Space Shuttle Program, recoverable solid rocket boosters were base-lined, with an estimated savings of 30 per cent over expendable solid rockets. Present studies indicate that the solid rocket boosters in the 142-inch diameter range can be recovered using state-of-the-art recovery systems. Marshall Space Flight Center is conducting extensive studies to establish the most cost effective recovery system for the present Shuttle boosters. Model drop testing, in various facilities, and structural load testing are being conducted with model sizes ranging from 6 inches to 120 inches in diameter.
Godfrey, R. E.↗
Large amplitude flutter of a low aspect ratio panel at low supersonic speeds comparison of theory and experiment
Flutter boundaries, as well as flutter limit cycle amplitudes, frequencies and stresses were computed for a panel of length-width ratio 4.48 exposed to applied in-plane and transverse loads. The Mach number range was 1.1 to 1.4. The method used involved direct numerical integration of modal equations of motion derived from the nonlinear plate equations of von Karman, coupled with linearized potential flow aerodynamic theory. The flutter boundaries agreed reasonably well with experiment, except when the in-plane loading approached the buckling load. Structural damping had to be introduced, to produce frequencies comparable to the experimental values. Attempts to compute panel deflections or stress at a given point met with limited success. There is some evidence, however, that deflection and stress maxima can be estimated with somewhat greater accuracy.
Ventres, C. S.↗