Sceptron vibration spectrum sensor, improved Sceptron/TM/ Final study report, 6 Jun. - 6 Oct. 1966
Fiber optic device for measuring missile vibration spectrum
VIBRATIONAL SPECTRUM↗
SEARCH · Search NASA
Results for “MISSILE VIBRATION”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
THE SUCESSFUL APPLICATION OF A REPEATED TEST-TO-FAILURE PROGRAM ON SERGEANT MISSILE ASSEMBLIES. PART I. THE DESIGN, APPLICATION, AND RESULTS OF THE COMBINED OPERATING TEMPERATURE VIBRATION TEST FOR MISSILE ASSEMBLIES RELIABILITY. PART II. STATISTICAL TECHNIQUES APPLIED TO THE SERGEANT REPEATED TEST-TO-FAILURE PROGRAM. PART III. CONCLUSIONS AND RECOMMENDATIONS
Reliability of sergeant missile assemblies - application of test-to-failure program
RELIABILITY↗
Digital random vibration analysis techniques.
Digital random vibration analysis of Saturn vehicle flight and booster static test data
RANDOM VIBRATION↗
Survey on vibration tests on missile-like structures and the effects of damping
Explore the source record for details and available documents.
Rodgers, E. J.↗
Three-dimensional test requirement for random vibration testing
An approach to defining and evaluating three-dimensional vibration test requirements is discussed. The approach is used to develop the three-dimensional space random-vibration test requirements for missile components subjected to truck transportation environments. One-dimensional testing parameters such as power spectral density and overall g rms values for three mutually perpendicular directions represent the test requirements. The coherence characteristics between each input axis were established and adjusted empirically in an attempt to simulate the cross-correlation in three-dimensional random vibration excitation.
Chang, Kurng↗
Summary of Flutter Experiences as a Guide to the Preliminary Design of Lifting Surfaces on Missiles
Presented is a limited review of some experiences in flight testing of missiles and of wing flutter investigations that may be of interest in missile design. Several types of flutter of concern in missile studies are briefly described. Crude criteria are presented for two of the most common types of flutter to permit a rapid estimate to be made of the probability of the occurrence of flutter. Many of the details of the flutter problem have been omitted, and only the broader elements have been retained so as to give the designer an overall view of the subject.
VIBRATION AND FLUTTER - BODIES↗
Performance of a Smart Vibration Isolator for Precision Spacecraft Instruments
Under the ARPA SMS Partnership Program for Synthesis and Processing of Smart Materials, Lockheed Missiles and Space company, Inc. has developed a demonstration prototype vibration cancelling mount using electrostrictive ceramic and shape-memory alloy actuators. Shape-memory actuators provide an adaptive-passive, self-damping support for isolation, while the electrostrictive actuators are employed to provide force and position control. The demonstration device was designed to address generic requirements for vibration stabilization of precision spacecraft instruments. It is reconfigurable to operate in any of four modes; passive isolation, active-passive isolation using force cancellation, active precision positioning, and active disturbance rejection. The presentation summarizes design of the device design and results of experimental evaluations of the device in isolation (active and passive) and positioning modes. Rejection of payload-borne disturbances is also discussed with reference to predictions from experimentally calibrated simulations. Finally, avenues for further development and refinement of the device are discussed.
Regelbrugge, Marc E.↗
2007 Research and Engineering Annual Report
Selected research and technology activities at NASA Dryden Flight Research Center are summarized. These following activities exemplify the Center's varied and productive research efforts: Developing a Requirements Development Guide for an Automatic Ground Collision Avoidance System; Digital Terrain Data Compression and Rendering for Automatic Ground Collision Avoidance Systems; Nonlinear Flutter/Limit Cycle Oscillations Prediction Tool; Nonlinear System Identification Using Orthonormal Bases: Application to Aeroelastic/Aeroservoelastic Systems; Critical Aerodynamic Flow Feature Indicators: Towards Application with the Aerostructures Test Wing; Multidisciplinary Design, Analysis, and Optimization Tool Development Using a Genetic Algorithm; Structural Model Tuning Capability in an Object-Oriented Multidisciplinary Design, Analysis, and Optimization Tool; Extension of Ko Straight-Beam Displacement Theory to the Deformed Shape Predictions of Curved Structures; F-15B with Phoenix Missile and Pylon Assembly--Drag Force Estimation; Mass Property Testing of Phoenix Missile Hypersonic Testbed Hardware; ARMD Hypersonics Project Materials and Structures: Testing of Scramjet Thermal Protection System Concepts; High-Temperature Modal Survey of the Ruddervator Subcomponent Test Article; ARMD Hypersonics Project Materials and Structures: C/SiC Ruddervator Subcomponent Test and Analysis Task; Ground Vibration Testing and Model Correlation of the Phoenix Missile Hypersonic Testbed; Phoenix Missile Hypersonic Testbed: Performance Design and Analysis; Crew Exploration Vehicle Launch Abort System-Pad Abort-1 (PA-1) Flight Test; Testing the Orion (Crew Exploration Vehicle) Launch Abort System-Ascent Abort-1 (AA-1) Flight Test; SOFIA Flight-Test Flutter Prediction Methodology; SOFIA Closed-Door Aerodynamic Analyses; SOFIA Handling Qualities Evaluation for Closed-Door Operations; C-17 Support of IRAC Engine Model Development; Current Capabilities and Future Upgrade Plans of the C-17 Data Rack; Intelligent Data Mining Capabilities as Applied to Integrated Vehicle Health Management; STARS Flight Demonstration No. 2 IP Data Formatter; Space-Based Telemetry and Range Safety (STARS) Flight Demonstration No. 2 Range User Flight Test Results; Aerodynamic Effects of the Quiet Spike(tm) on an F-15B Aircraft; F-15 Intelligent Flight Controls-Increased Destabilization Failure; F-15 Integrated Resilient Aircraft Control (IRAC) Improved Adaptive Controller; Aeroelastic Analysis of the Ikhana/Fire Pod System; Ikhana: Western States Fire Missions Utilizing the Ames Research Center Fire Sensor; Ikhana: Fiber-Optic Wing Shape Sensors; Ikhana: ARTS III; SOFIA Closed-Door Flutter Envelope Flight Testing; F-15B Quiet Spike(TM) Aeroservoelastic Flight Test Data Analysis; and UAVSAR Platform Precision Autopilot Flight Results.
Stoliker, Patrick↗
Protecting the Protectors
Program Manager Kurt Silvers helped protect the safety of U.S. troops who fought in Iraq and Afghanistan. PNNL researchers developed technology that monitored the battle-readiness of Hellfire II missiles onboard Army Apache helicopters. The technology continually monitors factors like vibration and temperature, providing key data when making decisions to deploy or retire weapons.
45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEF↗
An Investigation of the Natural Frequencies and Mode Shapes of Liquids in Oblate Spheroidal Tanks
An experimental investigation was conducted to gain some understanding of the character of the free vibration modes of liquids In oblate spheroidal tanks applicable in missile and space vehicle systems, Measured natural frequencies were obtained for the lowest three or four, antisymmetric modes of oscillation as a function of the liquid depth for three orientations of each of several such tanks of different size and oblateness. The orientations considered were such that: (a) the equator of the spheroid was horizontal and oscillations were along a diameter of the circular liquid surface; (b) the equator of the spheroid was vertical and the oscillations were along the minor axis of the elliptical liquid surface; and (c) the equator of the spheroid was vertical and the oscillations were along the major axis of the elliptical liquid surface; The frequency data are presented as dimensionless parameters developed for each orientation to permit the application of the experimental results to the prediction of the natural frequencies of tanks of different size and oblateness. Photographs we re made of representative surface wave or mode, shapes for each orientation.
Leonard, H. Wayne↗
New Los Alamos space instrument goes for a spin
Scientists and engineers at Los Alamos National Laboratory are using a unique centrifuge facility to evaluate a flight-ready telemetry system for evaluating a nuclear weapons test missile launch. "The telemetry unit was designed and manufactured by Los Alamos' Intelligence and Space Research Division," said Telemetry Program Manager Myles Fitzgerald. "Telemetry is a data stream of information on temperature, acceleration, vibration, strain, all the conditions a system encounters during a test flight." Because a test missile flight ultimately ends with the test system completely destroyed, telemetry data from the flight must be collected by receiving stations along the flight path. "The purpose of the centrifuge test is to subject the electronics to a high gravitational load (G-load) that's representative of what the system will experience when re-entering the Earth's atmosphere," said weapons test engineer Alex Cusick.
45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEF↗
New Los Alamos space instrument goes for a spin
Scientists and engineers at Los Alamos National Laboratory are using a unique centrifuge facility to evaluate a flight-ready telemetry system for evaluating a nuclear weapons test missile launch. "The telemetry unit was designed and manufactured by Los Alamos' Intelligence and Space Research Division," said Telemetry Program Manager Myles Fitzgerald. "Telemetry is a data stream of information on temperature, acceleration, vibration, strain, all the conditions a system encounters during a test flight." Because a test missile flight ultimately ends with the test system completely destroyed, telemetry data from the flight must be collected by receiving stations along the flight path. "The purpose of the centrifuge test is to subject the electronics to a high gravitational load (G-load) that's representative of what the system will experience when re-entering the Earth's atmosphere," said weapons test engineer Alex Cusick.
45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEF↗
Research on Liquid Dynamics in Missile Fuel Tanks
This report presents the results of work completed during the period of 1 July 1961 through 30 September 1961 on the studies of vibrations of flexible tanks containing a liquid with a free surface. The coupling between free surface motion and tank bending is dis- cussed in some detail and preliminary experimental results are given which tend to collaborate the theoretical analysis. Experimental results for the effect of an internal fluid on the breathing frequencies of a circular cylindrical shell are also given. apparently new type of free surface sloshing motion induced by high frequency breathing vibrations is reported.
MISSILE↗
Vibration studies
Computer program calculations of upper and lower bounds to nonzero bending frequencies of missiles
GUIDED MISSILE↗
(abstract) JPL Cryocooler Development and Test Program Overview
Many near-term and future space-instrument programs within NASA and the Ballistic Missile Defense Organization (BMDO) depend on the successful development of long-life, low-vibration space cryocoolers. The most demanding near-term programs include a number of science instruments selected for NASA's Earth Observing System (Eos) program, and a number of space reconnaissance instruments associated with the BMDO's Brilliant Eyes program; both of these programs require delivery of similar types of flight coolers in the next few years. To help ensure the success of these cooler commitments, JPL has implemented an extensive cryocooler program in support of the NASA/JPL AIRS project, the Air Force Phillips Laboratory (AFPL), and the Air Force Space and Missiles Systems Division (SMC). This program is directed at assisting industry in developing advanced cryocoolers that successfully address the broad array of complex performance requirements needed for NASA and BMDO long-life space instruments. The JPL cryocooler program includes extensive characterization and life testing of industry-developed cryocoolers, development and flight testing of advanced sorption cooler systems for detector cooling to 10 K , development of mechanical cryocooler enhancement technologies, and flight tests of advanced low-vibration Stirling-cooler systems.
development design testing↗
Transonic-flutter Investigation of Wings Attached to Two Low-acceleration Rocket-propelled Vehicles
Two low-acceleration transonic-flutter vehicles were launched and flown. The first carried two test wings, one of which fluttered at M = 0.92 at a frequency of 61.4 cycles per second. The reference flutter speed determined from two-dimensional theory for an unswept wing in incompressible flow is conservative when compared to the experimental flutter speed. The second vehicle carried two test wings, one of which failed at M = 0.71 because of low-frequency divergent oscillation. Since this failure was not caused by conventional flexure-torsion flutter, no comparison with a reference flutter speed can be made.
MISSILES, SPECIFIC TYPES↗
JPL Cryocooler Development and Test Program: A 10 year Overview
In the 1998 timeframe increasing numbers of proposed space-instrument programs within NASA and the Balistic Missile Defense Organization (BMDO) were in need of high-reliablility, long-life, low-vibration space cryocoolers.
cryocooler↗
Summary of
A 325-page Guidelines document [1], whose objectives are to increase the accuracy and reduce the errors and variability commonly found in the measurement of structural shock and vibration and of acoustic and aerodynamic noise, wea recently submitted to the Air Force Space and Missile Systems Center.
scope↗