Science.gov

Sample records for air-to-air missile guidance

  1. Flight testing air-to-air missiles for flutter

    NASA Technical Reports Server (NTRS)

    Kutschinski, C. R.

    1975-01-01

    The philosophy of the design of air-to-air missiles and hence of flight testing them for flutter differs from that of manned aircraft. Primary emphasis is put on analytical and laboratory evaluation of missile susceptibility to aeroelastic and aero-servo-elastic instabilities and uses flight testing for confirmation of the absence of such instabilities. Flight testing for flutter is accomplished by using specially instrumented programmed missiles, air or ground launched with a booster to reach the extreme flight conditions of tactical use, or by using guided missiles with telemetered performance data. The instrumentation and testing techniques are discussed along with the success of recent flight tests.

  2. Laser-initiated ordnance for air-to-air missiles

    NASA Technical Reports Server (NTRS)

    Sumpter, David R.

    1993-01-01

    McDonnell Douglas Missile Systems Company (MDMSC) has developed a laser ignition subsystem (LIS) for air-to-air missile applications. The MDMSC subsystem is designed to activate batteries, unlock fins, and sequence propulsion system events. The subsystem includes Pyro Zirconium Pump (PZP) lasers, mechanical Safe & Arm, fiber-optic distribution system, and optically activated pyrotechnic devices (initiators, detonators, and thermal batteries). The LIS design has incorporated testability features for the laser modules, drive electronics, fiber-optics, and pyrotechnics. Several of the LIS have been fabricated and have supported thermal battery testing, integral rocket ramjet testing, and have been integrated into integral rocket ramjet flight test vehicles as part of the flight control subsystem.

  3. The analysis of a generic air-to-air missile simulation model

    NASA Technical Reports Server (NTRS)

    Kaplan, Joseph A.; Chappell, Alan R.; Mcmanus, John W.

    1994-01-01

    A generic missile model was developed to evaluate the benefits of using a dynamic missile fly-out simulation system versus a static missile launch envelope system for air-to-air combat simulation. This paper examines the performance of a launch envelope model and a missile fly-out model. The launch envelope model bases its probability of killing the target aircraft on the target aircraft's position at the launch time of the weapon. The benefits gained from a launch envelope model are the simplicity of implementation and the minimal computational overhead required. A missile fly-out model takes into account the physical characteristics of the missile as it simulates the guidance, propulsion, and movement of the missile. The missile's probability of kill is based on the missile miss distance (or the minimum distance between the missile and the target aircraft). The problems associated with this method of modeling are a larger computational overhead, the additional complexity required to determine the missile miss distance, and the additional complexity of determining the reason(s) the missile missed the target. This paper evaluates the two methods and compares the results of running each method on a comprehensive set of test conditions.

  4. Methodology for determination and use of the no-escape envelope of an air-to-air-missile

    NASA Technical Reports Server (NTRS)

    Neuman, Frank

    1988-01-01

    A large gap exists between optimal control and differential-game theory and their applications. The purpose of this paper is to show how this gap may be bridged. Missile-avoidance of realistically simulated infrared heat-seeking, fire-and-forget missile is studied. In detailed simulations, sweeping out the discretized initial condition space, avoidance methods based on pilot experience are combined with those based on simplified optimal control analysis to derive an approximation to the no-escape missile envelopes. The detailed missile equations and no-escape envelopes were then incorporated into an existing piloted simulation of air-to-air combat to generate missile firing decisions as well as missile avoidance commands. The use of these envelopes was found to be effective in both functions.

  5. Optical Kalman filtering for missile guidance

    NASA Technical Reports Server (NTRS)

    Casasent, D.; Neuman, C. P.; Lycas, J.

    1984-01-01

    Optical systolic array processors constitute a powerful and general-purpose set of optical architectures with high computational rates. In this paper, Kalman filtering, a novel application for these architectures, is investigated. All required operations are detailed; their realization by optical and special-purpose analog electronics are specified; and the processing time of the system is quantified. The specific Kalman filter application chosen is for an air-to-air missile guidance controller. The architecture realized in this paper meets the design goal of a fully adaptive Kalman filter which processes a measurement every 1 msec. The vital issue of flow and pipelining of data and operations in a systolic array processor is addressed. The approach is sufficiently general and can be realized on an optical or digital systolic array processor.

  6. Modern control theory for Army missile guidance

    NASA Astrophysics Data System (ADS)

    Travassos, R. H.; Levari, H.; Gupta, N. K.

    1982-11-01

    A Singular perturbation guidance law has been developed for medium-range surface-to-air missiles. This guidance law is a significant extension of a previously developed guidance law for short-range missiles; in medium-range intercepts, the problem of energy management should be addressed in addition to homing guidance. The mathematical formulation has been simplified by introducing separation of time scales. Target Trajectory Estimation: A recursive algorithm for estimation of autoregressive moving average (ARMA) model parameters from noisy samples has been developed. Application of this algorithm to parameter estimation problems has exhibited its fast convergence and unbiasedness in the presence of noise, even with short data records. The algorithm has two versions, a Recursive Maximum Likelihood (RML) form and a Recursive Prediction Error (RPE) form, both of which possess a parallel structure that makes them highly suitable for parallel-processing implementation. Adaptive autopilots: Lattice-form algorithms have been developed for fast, recursive identification and control of time-varying systems. These algorithms have excellent numerical properties and a modular structure that makes them suitable for on-board real-time implementation.

  7. Development of guidance laws for a variable-speed missile

    SciTech Connect

    Gazit, R.; Gutman, S. )

    1991-05-01

    The most used guidance law for short-range homing missiles is proportional navigation (PN). In PN, the acceleration command is proportional to the line-of-sight (LOS) angular velocity. Indeed, if a missile and a target move on a collision course with constant speeds, the LOS rate is zero. The speed of a highly maneuverable modern missile varies considerably during flight. The performance of PN is far from being satisfactory in that case. In this article the collision course for a variable-speed missile is analyzed and a guidance law that steers the heading of the missile to the collision course is defined. Guidance laws based on optimal control and differential game formulations are developed, and note that both optimal laws coincide with the Guidance to Collision law at impact. The performance improvement of the missile using the new guidance law as compared to PN is demonstrated. 19 refs.

  8. Laser beam riding artillery missiles guidance device is designed

    NASA Astrophysics Data System (ADS)

    Yan, Mingliang; Huo, Zhicheng; Chen, Wei

    2014-09-01

    Laser driving gun missile guidance type beam of laser information field formed by any link failure or reduced stability will directly lead to ballistic or miss out of control, and based on this, this paper designed the driving beam of laser guided missile guidance beam type forming device modulation and zoom mechanism, in order to make the missile can recognize its position in the laser beam, laser beam gun missile, by means of spatial encoding of the laser beam laser beam into information after forming device, a surface to achieve the purpose of precision guidance.

  9. Fast three-dimensional k-space trajectory design using missile guidance ideas.

    PubMed

    Mir, Roberto; Guesalaga, Andres; Spiniak, Juan; Guarini, Marcelo; Irarrazaval, Pablo

    2004-08-01

    Three-dimensional (3D) k-space trajectories are needed to acquire volumetric images in MRI. While scan time is determined by the trajectory efficiency, image quality and distortions depend on the shape of the trajectories. There are several 3D trajectory strategies for sampling the k-space using rectilinear or curve schemes. Since there is no evidence about their optimality in terms of image quality and acquisition time, a new design method based on missile guidance ideas is explored. Since air-to-air missile guidance shares similar goals and constraints with the problem of k-space trajectory design, a control approach for missiles is used to design a 3D trajectory. The k-space is divided into small cubes, and each one is treated as a target to be sampled. The main goal is to cover the entire space as quickly and efficiently as possible, with good performance under different conditions. This novel design method is compared to other trajectories using simulated and real data. As an example, a trajectory that requires 0.11 times the number of shots needed by the cylindrical 3DFT acquisition was designed. This trajectory requires more shots (1.66 times) than the stack of spirals, but behaves better under nonideal conditions, such as off-resonance and motion.

  10. A Simplified Guidance for Target Missiles Used in Ballistic Missile Defence Evaluation

    NASA Astrophysics Data System (ADS)

    Prabhakar, N.; Kumar, I. D.; Tata, S. K.; Vaithiyanathan, V.

    2013-01-01

    A simplified guidance scheme for the target missiles used in Ballistic Missile Defence is presented in this paper. The proposed method has two major components, a Ground Guidance Computation (GGC) and an In-Flight Guidance Computation. The GGC which runs on the ground uses a missile model to generate attitude history in pitch plane and computes launch azimuth of the missile to compensate for the effect of earth rotation. The vehicle follows the pre launch computed attitude (theta) history in pitch plane and also applies the course correction in azimuth plane based on its deviation from the pre launch computed azimuth plane. This scheme requires less computations and counters In-flight disturbances such as wind, gust etc. quite efficiently. The simulation results show that the proposed method provides the satisfactory performance and robustness.

  11. 44. Upper level, left to rightground missile guidance system liquid ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    44. Upper level, left to right--ground missile guidance system liquid cooling equipment, guidance and control coupler - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

  12. 43. Upper level, left to rightground missile guidance system liquid ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    43. Upper level, left to right--ground missile guidance system liquid cooling equipment, guidance and control coupler rack, programmer group - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

  13. A Self-Adaptive Missile Guidance System for Statistical Inputs

    NASA Technical Reports Server (NTRS)

    Peery, H. Rodney

    1960-01-01

    A method of designing a self-adaptive missile guidance system is presented. The system inputs are assumed to be known in a statistical sense only. Newton's modified Wiener theory is utilized in the design of the system and to establish the performance criterion. The missile is assumed to be a beam rider, to have a g limiter, and to operate over a flight envelope where the open-loop gain varies by a factor of 20. It is shown that the percent of time that missile acceleration limiting occurs can be used effectively to adjust the coefficients of the Wiener filter. The result is a guidance system which adapts itself to a changing environment and gives essentially optimum filtering and minimum miss distance.

  14. The optimization of an optical missile guidance tracker.

    PubMed

    Spiro, I J

    1969-07-01

    An antitank missile guidance system is described, which employs a tracker using two parallel optical paths and a pyrotechnic flare. Both optical channels are spectrally filtered; one rejects the target and views only the flare image; the other rejects the flare and views only the target. In performing the guidance tracking task, the operator superimposes the flare image on the target, thus providing steering signals to the missile. This paper describes an optimum flare as one with maximum luminous spectral emittance, minimum bandwidth, and minimum noise. Then with the selected flare as a basis, the optical components are matched individually and as an assembly to obtain maximum flare-filter system output. Calculated improvements of 100 to 250% were obtained in the performance of critical components which were reflected in the system operation and were subsequently verified by system field tests. The transmission ratios, visibility coefficients, improvement factors, and other bases for improvement are stated and discussed. Finally, the experiments performed and improvements achieved are described.

  15. Optimal guidance law for cooperative attack of multiple missiles based on optimal control theory

    NASA Astrophysics Data System (ADS)

    Sun, Xiao; Xia, Yuanqing

    2012-08-01

    This article considers the problem of optimal guidance laws for cooperative attack of multiple missiles based on the optimal control theory. New guidance laws are presented such that multiple missiles attack a single target simultaneously. Simulation results show the effectiveness of the proposed algorithms.

  16. Missile guidance law design using adaptive cerebellar model articulation controller.

    PubMed

    Lin, Chih-Min; Peng, Ya-Fu

    2005-05-01

    An adaptive cerebellar model articulation controller (CMAC) is proposed for command to line-of-sight (CLOS) missile guidance law design. In this design, the three-dimensional (3-D) CLOS guidance problem is formulated as a tracking problem of a time-varying nonlinear system. The adaptive CMAC control system is comprised of a CMAC and a compensation controller. The CMAC control is used to imitate a feedback linearization control law and the compensation controller is utilized to compensate the difference between the feedback linearization control law and the CMAC control. The online adaptive law is derived based on the Lyapunov stability theorem to learn the weights of receptive-field basis functions in CMAC control. In addition, in order to relax the requirement of approximation error bound, an estimation law is derived to estimate the error bound. Then the adaptive CMAC control system is designed to achieve satisfactory tracking performance. Simulation results for different engagement scenarios illustrate the validity of the proposed adaptive CMAC-based guidance law.

  17. Recent Events in Guidance, Navigation and Control

    NASA Technical Reports Server (NTRS)

    Polites, Michael E.; Bullman, Jack (Technical Monitor)

    2001-01-01

    This article summarizes recent events in Guidance, Navigation, and Control (GN&C) in space, weapons and missiles, and aircraft. The section on space includes recent developments with the following NASA spacecraft and space vehicles: Near Earth Asteroid Rendezvous, Deep Space 1, Microwave Anisotropy Probe, Earth Observer-1, Compton Gamma Ray Observatory, the International Space Station, X-38, and X-40A. The section on weapons and missiles includes recent developments with the following missiles: Joint Air-to-Surface Standoff Missile, Storm Shadow/Scalp EG precision standoff missile, Hellfire missile, AIM-120C Advanced medium-range air-to-air missile, Derby missile, Arrow 2, and the Standard Missile SM-3. The section on aircraft includes recent developments with the following aircraft: Joint Strike Fighter, X-31, V-22, Couger/SUDer Puma Mk. 2, Predator B 001, and the Unmanned Combat Air Vehicle.

  18. Missile Guidance Law Based on Robust Model Predictive Control Using Neural-Network Optimization.

    PubMed

    Li, Zhijun; Xia, Yuanqing; Su, Chun-Yi; Deng, Jun; Fu, Jun; He, Wei

    2015-08-01

    In this brief, the utilization of robust model-based predictive control is investigated for the problem of missile interception. Treating the target acceleration as a bounded disturbance, novel guidance law using model predictive control is developed by incorporating missile inside constraints. The combined model predictive approach could be transformed as a constrained quadratic programming (QP) problem, which may be solved using a linear variational inequality-based primal-dual neural network over a finite receding horizon. Online solutions to multiple parametric QP problems are used so that constrained optimal control decisions can be made in real time. Simulation studies are conducted to illustrate the effectiveness and performance of the proposed guidance control law for missile interception.

  19. The Synthesis of Optimum Homing Missile Guidance Systems with Statistical Inputs

    NASA Technical Reports Server (NTRS)

    Stewart, Elwood C.; Smith, Gerald L.

    1959-01-01

    An analytical approach is presented which is applicable to the optimization of homing navigation guidance systems which are forced to operate in the presence of radar noise. The two primary objectives are to establish theoretical minimum miss distance performance and a method of synthesizing the optimum control system. The factors considered are: (1) target evasive maneuver, (2) radar glint noise, (3) missile maneuverability, and (4) the inherent time-varying character of the kinematics. Two aspects of the problem are considered. In the first, consideration is given only to minimization of the miss distance. The solution given cannot be achieved in practice because the required accelerations are too large. In the second, results are extended to the practical case where the limited acceleration capabilities of the missile are considered by placing a realistic restriction on the mean-square acceleration so that system operation is confined to the linear range. Although the exact analytical solution of the latter problem does not appear feasible, approximate solutions utilizing time-varying control systems can be found. One of these solutions - a range multiplication type control system - is studied in detail. It is shown that the minimum obtainable miss distance with a realistic restriction on acceleration is close to the absolute minimum for unlimited missile maneuverability. Furthermore, it is shown that there is an equivalence in performance between the homing and beam-rider type guidance systems. Consideration is given to the effect of changes in target acceleration, noise magnitude, and missile acceleration on the minimum miss distance.

  20. Benefits of HWIL simulation to develop guidance and control systems for missiles

    NASA Astrophysics Data System (ADS)

    Eguchi, Hirofumi; Yamashita, Tadashi

    2000-07-01

    The essential benefit of Hardware-in-the-loop (HWIL) simulation can be summarized as that the performance of missile guidance/control system is evaluated realistically without the modeling error by using actual hardware such as seeker systems, autopilot systems and servo equipments. HWIL simulation, however, requires very expensive facilities: in these facilities, target model generators are indispensable subsystems. In this paper, a target model generator for RF/IR seeker systems is introduced, and then, two technical problems with this facility are discussed: a method to overcome the line-of-sight (LSO) angle limitation and the RF/IR dual mode seeker simulation technique.

  1. Air-to-air radar flight testing

    NASA Astrophysics Data System (ADS)

    Scott, Randall E.

    1988-06-01

    This volume in the AGARD Flight Test Techniques Series describes flight test techniques, flight test instrumentation, ground simulation, data reduction and analysis methods used to determine the performance characteristics of a modern air-to-air (a/a) radar system. Following a general coverage of specification requirements, test plans, support requirements, development and operational testing, and management information systems, the report goes into more detailed flight test techniques covering a/a radar capabilities of: detection, manual acquisition, automatic acquisition, tracking a single target, and detection and tracking of multiple targets. There follows a section on additional flight test considerations such as electromagnetic compatibility, electronic countermeasures, displays and controls, degraded and backup modes, radome effects, environmental considerations, and use of testbeds. Other sections cover ground simulation, flight test instrumentation, and data reduction and analysis. The final sections deal with reporting and a discussion of considerations for the future and how they may affect radar flight testing.

  2. Precise terrestrial time: A means for improved ballistic missile guidance analysis

    NASA Technical Reports Server (NTRS)

    Ehrsam, E. E.; Cresswell, S. A.; Mckelvey, G. R.; Matthews, F. L.

    1978-01-01

    An approach developed to improve the ground instrumentation time tagging accuracy and adapted to support the Minuteman ICBM program is desired. The Timing Insertion Unit (TIU) technique produces a telemetry data time tagging resolution of one tenth of a microsecond, with a relative intersite accuracy after corrections and velocity data (range, azimuth, elevation and range rate) also used in missile guidance system analysis can be correlated to within ten microseconds of the telemetry guidance data. This requires precise timing synchronization between the metric and telemetry instrumentation sites. The timing synchronization can be achieved by using the radar automatic phasing system time correlation methods. Other time correlation techniques such as Television (TV) Line-10 and the Geostationary Operational Environmental Satellites (GEOS) terrestial timing receivers are also considered.

  3. Local oscillator arrangement for a monopulse receiver in a semiactive missile guidance system

    SciTech Connect

    Gregory, N.; Murphy, W.M.

    1993-08-03

    For use in a radar receiver for a guidance system on board a missile, such receiver is described including an intermediate frequency amplifier and a phase detector for demodulating signals out of such amplifier, an improved local oscillator arrangement comprising: (a) a voltage controlled crystal oscillator for producing an output signal; (b) frequency control means, responsive to the demodulated signals out of the phase detector, for changing the frequency of the output signal of the voltage controlled crystal oscillator; (c) frequency conversion means, responsive to the output signal of the voltage controlled crystal oscillator, for converting such signal into a comb of signals around a harmonic of the output signal of the voltage controlled crystal oscillator; (d) means for selecting one signal in the comb of signals; and (e) means, responsive to the selected signal, for generating the local oscillator signal for the intermediate frequency amplifier.

  4. Impact angle constrained three-dimensional integrated guidance and control for STT missile in the presence of input saturation.

    PubMed

    Wang, Sen; Wang, Weihong; Xiong, Shaofeng

    2016-09-01

    Considering a class of skid-to-turn (STT) missile with fixed target and constrained terminal impact angles, a novel three-dimensional (3D) integrated guidance and control (IGC) scheme is proposed in this paper. Based on coriolis theorem, the fully nonlinear IGC model without the assumption that the missile flies heading to the target at initial time is established in the three-dimensional space. For this strict-feedback form of multi-variable system, dynamic surface control algorithm is implemented combining with extended observer (ESO) to complete the preliminary design. Then, in order to deal with the problems of the input constraints, a hyperbolic tangent function is introduced to approximate the saturation function and auxiliary system including a Nussbaum function established to compensate for the approximation error. The stability of the closed-loop system is proven based on Lyapunov theory. Numerical simulations results show that the proposed integrated guidance and control algorithm can ensure the accuracy of target interception with initial alignment angle deviation and the input saturation is suppressed with smooth deflection curves.

  5. Impact angle constrained three-dimensional integrated guidance and control for STT missile in the presence of input saturation.

    PubMed

    Wang, Sen; Wang, Weihong; Xiong, Shaofeng

    2016-09-01

    Considering a class of skid-to-turn (STT) missile with fixed target and constrained terminal impact angles, a novel three-dimensional (3D) integrated guidance and control (IGC) scheme is proposed in this paper. Based on coriolis theorem, the fully nonlinear IGC model without the assumption that the missile flies heading to the target at initial time is established in the three-dimensional space. For this strict-feedback form of multi-variable system, dynamic surface control algorithm is implemented combining with extended observer (ESO) to complete the preliminary design. Then, in order to deal with the problems of the input constraints, a hyperbolic tangent function is introduced to approximate the saturation function and auxiliary system including a Nussbaum function established to compensate for the approximation error. The stability of the closed-loop system is proven based on Lyapunov theory. Numerical simulations results show that the proposed integrated guidance and control algorithm can ensure the accuracy of target interception with initial alignment angle deviation and the input saturation is suppressed with smooth deflection curves. PMID:27167987

  6. Digital fast pattern recognizer for autonomous target recognition and tracking for advanced missile guidance and UAV reconnaissance

    NASA Astrophysics Data System (ADS)

    Hastbacka, Albin A.

    2003-08-01

    A digital Fast Pattern Processor (DFPP) system under development for the Naval Air Warfare Center, is funded under a SBIR, Phase III contract. It is an automatic target recognizer and tracker candidate for supersonic missile guidance and unmanned air vehicle (UAV) reconnaissance to meet the U.S. navy's time-critical strike objectives. The former application requires rapid processing of moderate size, real time image arrays, versus large real time image arrays for the latter case. The DFPP correlates operator selected target filters against observed imagery at 1500 correlations per second as currently implemented with programmable logic devices (PLD's) - equivalent to thirty Pentium III (1 GHz) PC's. High performance and low weight, power, size, cost of the current version make it ideal for on-board image data processing in UAV's and cruise missiles or for ground station processing. Conversion to application specific integrated circuit (ASIC) technology provides scalable performance to meet future ATR/ATT needs. The Sanders proprietary DFPP technology embodies a Power-FFT, which is the fastest digital fast Fourier transform (DFTT) in the world with performance exceeding supercomputers, at a small fraction of the cost, size, weight, and power. The DFPP operates under control of Sanders Correlation Image Processor (SCIP) program and enables correlation against a plethora of stored target filters (templates).

  7. Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.

    PubMed

    Xingling, Shao; Honglun, Wang

    2015-07-01

    This paper proposes a novel composite integrated guidance and control (IGC) law for missile intercepting against unknown maneuvering target with multiple uncertainties and control constraint. First, by using back-stepping technique, the proposed IGC law design is separated into guidance loop and control loop. The unknown target maneuvers and variations of aerodynamics parameters in guidance and control loop are viewed as uncertainties, which are estimated and compensated by designed model-assisted reduced-order extended state observer (ESO). Second, based on the principle of active disturbance rejection control (ADRC), enhanced feedback linearization (FL) based control law is implemented for the IGC model using the estimates generated by reduced-order ESO. In addition, performance analysis and comparisons between ESO and reduced-order ESO are examined. Nonlinear tracking differentiator is employed to construct the derivative of virtual control command in the control loop. Third, the closed-loop stability for the considered system is established. Finally, the effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations.

  8. Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.

    PubMed

    Xingling, Shao; Honglun, Wang

    2015-07-01

    This paper proposes a novel composite integrated guidance and control (IGC) law for missile intercepting against unknown maneuvering target with multiple uncertainties and control constraint. First, by using back-stepping technique, the proposed IGC law design is separated into guidance loop and control loop. The unknown target maneuvers and variations of aerodynamics parameters in guidance and control loop are viewed as uncertainties, which are estimated and compensated by designed model-assisted reduced-order extended state observer (ESO). Second, based on the principle of active disturbance rejection control (ADRC), enhanced feedback linearization (FL) based control law is implemented for the IGC model using the estimates generated by reduced-order ESO. In addition, performance analysis and comparisons between ESO and reduced-order ESO are examined. Nonlinear tracking differentiator is employed to construct the derivative of virtual control command in the control loop. Third, the closed-loop stability for the considered system is established. Finally, the effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations. PMID:25776190

  9. Application of boost guidance to NASA sounding rocket launch operations at the White Sands Missile Range

    NASA Technical Reports Server (NTRS)

    Montag, W. H.; Detwiler, D. F., Jr.; Hall, L.

    1986-01-01

    This paper addresses the unique problems associated with launching the Black Brant V, VIII, and IX sounding rocket vehicles at White Sands Missile Range (WSMR) and the significance of the introduction of the S19 to the NASA Goddard Space Flight Center Wallops Flight Facility sounding rocket program in terms of launch flexibility, improved impact dispersion, higher flight reliability, and reduced program costs. This paper also discusses salient flight results from NASA 36.011UL (the first S19 guided Black Brant launched at WSMR) and the NASA Comet Halley missions (36.010DL and 36.017DL).

  10. Design considerations for air-to-air laser communications

    NASA Astrophysics Data System (ADS)

    Casey, William L.; Doughty, Glenn R.; Marston, Robert K.; Muhonen, John

    1991-06-01

    The US Air Force has identified laser communications (lasercom) as a viable technology for several air-to-air communications applications, namely Strategic Data Exchange (SDE) between airborne command post (ABCP) aircraft and intraformation data links among fighter aircraft or low-flying, close-formation aircraft. Lasercom offers low probability of intercept (LPI), jam resistance, and high bandwidth capabilities due to its very short wavelength compared to radio frequency (RF) systems. This paper examines the requirements of lasercom systems to support these missions and presents the systems link analysis necessary to select preferred approaches. The state of key technologies such as lasers, detectors, filters, coding, acquisition, etc., form a basis to structure conceptual systems that meet mission requirements. There have been recent advances in these key technologies, which will significantly improve air-to-air lasercom system performance. The resultant systems are low risk and could be developed in minimum time. Adverse weather is a factor in lasercom capability, so several weather conditions are included in the analysis. The preferred systems are described and, finally, conclusions and recommendations are given that could lead to development of a prototype terminal for one of the above missions.

  11. A two-dimensional air-to-air combat game - Toward an air-combat advisory system

    NASA Technical Reports Server (NTRS)

    Neuman, Frank

    1987-01-01

    Air-to-air combat is modeled as a discrete differential game, and by constraining the game to searching for the best guidance laws from the sets of those considered for each opponent, feedback and outcome charts are obtained which can be used to turn one of the automatic opponents into an intelligent opponent against a human pilot. A one-on-one two-dimensional fully automatic, or manned versus automatic, air-to-air combat game has been designed which includes both attack and evasion alternatives for both aircraft. Guidance law selection occurs by flooding the initial-condition space with four simulated fights for each initial condition, depicting the various attack/evasion strategies for the two opponents, and recording the outcomes. For each initial condition, the minimax method from differential games is employed to determine the best choice from the available strategies.

  12. Simulation model air-to-air plate heat exchanger

    SciTech Connect

    Wetter, Michael

    1999-01-01

    A simple simulation model of an air-to-air plate heat exchanger is presented. The model belongs to a collection of simulation models that allows the eflcient computer simulation of heating, ventilation, and air-conditioning (HVAC) systems. The main emphasis of the models is to shorten computation time and to use only input data that are known in the design process of an HVAC system. The target of the models is to describe the behavior of HVAC components in the part-load operation mode, which is becoming increasingly important in energy eficient HVAC systems. The models are intended to be used for yearly energy calculations or load calculations with time steps of about 10 minutes or larger. Short- time dynamic effects, which are of interest for different aspects of control theory, are neglected. The part-load behavior is expressed in terms of the nominal condition and the dimensionless variation of the heat transfer with change of mass flow and temperature. The effectiveness- NTU relations are used to parametrize the convective heat transfer at nominal conditions and to compute the part-load condition. If the heat transfer coefficients on the two exchanger sides are not equal (i. e. due to partial bypassing of air), their ratio can be easily calculated and set as a parameter. The model is static and uses explicit equations only. The explicit model formulation ensures short computation time and numerical stability, which allows using the model with sophisticated engineering methods like automatic system optimization. This paper fully outlines the algorithm description and its simplifications. It is not tailored for any particular simulation program to ensure easy implementation in any simulation program.

  13. Heat Recovery Ventilation for Housing: Air-to-Air Heat Exchangers.

    ERIC Educational Resources Information Center

    Corbett, Robert J.; Miller, Barbara

    The air-to-air heat exchanger (a fan powered ventilation device that recovers heat from stale outgoing air) is explained in this six-part publication. Topic areas addressed are: (1) the nature of air-to-air heat exchangers and how they work; (2) choosing and sizing the system; (3) installation, control, and maintenance of the system; (4) heat…

  14. Weapon system interoperability testing between target acquisition systems and missile guidance sections utilizing adjacent hardware-in-the loop sensor test facilities

    NASA Astrophysics Data System (ADS)

    LeSueur, Kenneth G.; Burroughs, Eddie, Jr.; Robinson, Richard M.

    1997-07-01

    Laboratory Test and Evaluation of imaging infrared (I2R) systems is being greatly enhanced through the use of the Electro-Optics Sensor Flight Evaluation Laboratory (EOSFEL) and the Electro-Optics Target Acquisition Sensor Evaluation Laboratory (EOTASEL) at the US Army Redstone Technical Test Center. In addition to other standard and future test support, these laboratories will be utilized to support tactical I2R missile system interoperability testing. The EOSFEL is a state-of-the-art, performance grade, Hardware-In-the-Loop test capability for in-band, closed- loop test and evaluation of optically guided missile seekers, guidance sections, and control sections. The EOTASEL is a class 100,000 clean room laboratory, with state-of-the-art test capability for evaluating the performance of electro-optical target acquisition and fire control subsystems in a hardware/human-in-the-loop environment. With I2R missile systems being developed to work with electro-optical target acquisition subsystems, such as the second generation Forward Looking Infrared sights, the need arises for testing the interoperability of these sensor subsystems within the cost effective confines of the laboratory. Interoperability testing today is currently performed at the system level in real-world field environments, which is very expensive and costly to identify problems at this level. This paper describes a realistic technique for performing high fidelity laboratory interoperability testing which utilizes the EOSFEL and EOTASEL including two Dynamic Infrared Scene Projector systems, a five-axis flight motion simulator, a two-axis platform motion simulator, climatic chambers, supporting instrumentation, and computer control.

  15. Cold Climate and Retrofit Applications for Air-to-Air Heat Pumps

    SciTech Connect

    Baxter, Van D

    2015-01-01

    Air source heat pumps (ASHP) including air-to-air ASHPs are easily applied to buildings almost anywhere for new construction as well as retrofits or renovations. They are widespread in milder climate regions but their use in cold regions is hampered due to low heating efficiency and capacity at cold outdoor temperatures. Retrofitting air-to-air ASHPs to existing buildings is relatively easy if the building already has an air distribution system. For buildings without such systems alternative approaches are necessary. Examples are ductless, minisplit heat pumps or central heat pumps coupled to small diameter, high velocity (SDHV) air distribution systems. This article presents two subjects: 1) a summary of R&D investigations aimed at improving the cold weather performance of ASHPs, and 2) a brief discussion of building retrofit options using air-to-air ASHP systems.

  16. Dynamic Performance of a Residential Air-to-Air Heat Pump.

    ERIC Educational Resources Information Center

    Kelly, George E.; Bean, John

    This publication is a study of the dynamic performance of a 5-ton air-to-air heat pump in a residence in Washington, D.C. The effect of part-load operation on the heat pump's cooling and heating coefficients of performance was determined. Discrepancies between measured performance and manufacturer-supplied performance data were found when the unit…

  17. Supersonic aerodynamic trade data for a low-profile monoplanar missile concept. [air launched maneuvering missile design

    NASA Technical Reports Server (NTRS)

    Graves, E. B.; Robins, A. W.

    1979-01-01

    A monoplanar missile concept has been studied which shows promise of improving the aerodynamic performance of air-launched missiles. This missile concept has a constant eccentricity elliptical cross-section body. Since current guidance and propulsion technologies influence missile nose and base shapes, an experimental investigation has been conducted at Mach number 2.50 to determine the effects of variations in these shapes on the missile aerodynamics. Results of these tests are presented.

  18. The Effects of Target and Missile Characteristics on Theoretical Minimum Miss Distance for a Beam-Rider Guidance System in the Presence of Noise

    NASA Technical Reports Server (NTRS)

    Stewart, Elwood C.; Druding, Frank; Nishiura, Togo

    1959-01-01

    A study has been made to determine the relative importance of those factors which place an inherent limitation on the minimum obtainable miss distance for a beam-rider navigation system operating in the presence of glint noise and target evasive maneuver. Target and missile motions are assumed to be coplanar. The factors considered are the missile natural frequencies and damping ratios, missile steady-state acceleration capabilities, target evasive maneuver characteristics, and angular scintillation noise characteristics.

  19. Hardware-in-the-loop tow missile system simulator

    SciTech Connect

    Waldman, G.S.; Wootton, J.R.; Hobson, G.L.; Holder, D.L.

    1993-07-06

    A missile system simulator is described for use in training people for target acquisition, missile launch, and missile guidance under simulated battlefield conditions comprising: simulating means for producing a digital signal representing a simulated battlefield environment including at least one target movable therewithin, the simulating means generating an infrared map representing the field-of-view and the target; interface means for converting said digital signals to an infrared image; missile system hardware including the missile acquisition, tracking, and guidance portions thereof, said hardware sensing the infrared image to determine the location of the target in a field-of-view; and, image means for generating an infrared image of a missile launched at the target and guided thereto, the image means imposing the missile image onto the field-of-view for the missile hardware to acquire the image of the missile in addition to that of the target, and to generate guidance signals to guide the missile image to the target image, wherein the interfacing means is responsive to a guidance signal from the hardware to simulate, in real-time, the response of the missile to the guidance signal, the image means including a blackbody, laser means for irradiating the blackbody to heat it to a temperature at which it emits infrared radiation, and optic means for integrating the radiant image produced by heating the blackbody into the infrared map.

  20. Nonlinear estimation for vision-based air-to-air tracking

    NASA Astrophysics Data System (ADS)

    Oh, Seung-Min

    framework for fusing the many sources of information in the design of integrated navigation systems. In this framework, several aiding sensor measurements with different size and update rates are easily fused with basic high-rate IMU processing. In order to provide a new mechanism that estimates ownship states, a new non-linear filtering framework, called the unscented Kalman filter (UKF) with sequential measurement updates, is developed and applied to the design of a new integrated navigation system. The UKF is known to be more accurate and convenient to use with a slightly higher computational cost. This filter provides at least second-order accuracy by approximating Gaussian distributions rather than arbitrary nonlinear functions. This is compared to the first-order accuracy of the well-known EKF based on linearization. In addition, the step of computing the often troublesome Jacobian matrices, always required in the design of an integrated navigation system using the EKF, is eliminated. Furthermore, by employing the concept of sequential measurement updates in the UKF, we can add the advantages of sequential measurement update strategy such as easy compensation of sensor latency, easy fusion of multi-sensors, and easy addition and subtraction of new sensors while maintaining those of the standard UKF such as accurate estimation and removal of Jacobian matrices. Simulation results show better performance of the UKF-based navigation system than the EKF-based system since the UKF-based system is more robust to initial accelerometer and rate gyro biases and more accurate in terms of reducing transient peaks and steady-state errors in ownship state estimation. In order to estimate target tracking states or target kinematics, a new vision-based tracking system is designed by using a UKF in the scenario of three-dimensional air-to-air tracking. The tracking system can estimate not only the target tracking states but also several target characteristics including target size and

  1. Air to air view of Endeavour, OV-105, atop SCA approaches Ellington runway

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Air to air view of Endeavour, Orbiter Vehicle (OV) 105, atop a Shuttle Carrier Aircraft (SCA) NASA 911, a modified Boeing 747, approaches touchdown for a brief stopover at Ellington Field, near JSC. Visible below the spacecraft/aircraft combination are the NASA T-38 flight line, NASA aircraft hangars and facilities, and a runway. OV-105 rolled out at Rockwell's Palmdale facility on 04-25-91 to once more bring to four the total of NASA Shuttles available for flight assignment. The spacecraft and aircraft-tandem left Houston later on this day headed for another stop in Mississippi before landing in Florida on 05-07-91. This photograph was taken from a T-38 aircraft by Sheri J. Dunnette of JSC's Image Science Division (ISD).

  2. Air to air view of Endeavour, OV-105, atop SCA flies over JSC enroute to KSC

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Air to air view shows Endeavour, Orbiter Vehicle (OV) 105, atop a Shuttle Carrier Aircraft (SCA) NASA 911, a modified Boeing 747, flying over the Clear Lake / NASA JSC area prior to a brief stopover at Ellington Field, near JSC. JSC site appears behind and below the orbiter/aircraft combination with Clear Creek and Egret Bay Blvd in the foreground and Clear Lake and Galveston Bay in the background. OV-105 rolled out at Rockwell's Palmdale facility on 04-25-91 to once more bring to four the total of NASA Shuttles available for flight assignment. It left Houston later on this day headed for another stop in Mississippi before landing in Florida on 05-07-91. This photograph was taken from a T-38 aircraft by Sheri J. Dunnette of JSC's Image Sciences Division (ISD).

  3. Two-axis gimbal for air-to-air and air-to-ground laser communications

    NASA Astrophysics Data System (ADS)

    Talmor, Amnon G.; Harding, Harvard; Chen, Chien-Chung

    2016-03-01

    For bi-directional links between high-altitude-platforms (HAPs) and ground, and air-to-air communication between such platforms, a hemispherical +30°C field-of-regard and low-drag low-mass two-axis gimbal was designed and prototyped. The gimbal comprises two servo controlled non-orthogonal elevation over azimuth axis, and inner fast steering mirrors for fine field-of-regard adjustment. The design encompasses a 7.5cm diameter aperture refractive telescope in its elevation stage, folded between two flat mirrors with an exit lens leading to a two mirrors miniature Coude-path fixed to the azimuth stage. Multiple gimbal configurations were traded prior to finalizing a selection that met the requirements. The selected design was manifested onboard a carbon fiber and magnesium composite structure, motorized by custom-built servo motors, and commutated by optical encoders. The azimuth stage is electrically connected to the stationary base via slip ring while the elevation stage made of passive optics. Both axes are aligned by custom-built ceramic-on-steel angular contact duplex bearings, and controlled by embedded electronics featuring a rigid-flex PCB architecture. FEA analysis showed that the design is mechanically robust over a temperature range of +60°C to -80°C, and with first mode of natural frequencies above 400Hz. The total mass of the prototyped gimbal is 3.5kg, including the inner optical bench, which contains fast steering mirrors (FSMs) and tracking sensors. Future version of this gimbal, in prototyping stage, shall weigh less than 3.0kg.

  4. Influence of HX size and augmentation on performance potential of mixtures in air-to-air heat pumps

    SciTech Connect

    Rice, C.K.

    1993-05-01

    A modified Carnot analysis with finite heat exchanger (HX) sizes, counterflow HX configurations, and ideal glide matching was conducted for an air-to-air heat pump application. The purpose of the analysis was to determine the envelope of potential HX size and refrigerant-side augmentation benefits for ideal mixtures relative to pure refrigerant alternatives. The mixture COP benefits examined are those due to exact external fluid glide-matching of idealized mixtures in more effective heat exchangers. Maximum possible mixture COP gains are evaluated for four steady-state air-to-air heat pump conditions. Performance improvement opportunities are found to be primarily in the cooling mode. The effects of deviation from counterflow by use of crossflow and countercrossflow HX configurations are addressed. Refrigerant-side augmentation with pure and mixed refrigerants is examined for air-side dominant and air-to-refrigerant balanced HXs.

  5. Technology Candidates for Air-to-Air and Air-to-Ground Data Exchange

    NASA Technical Reports Server (NTRS)

    Haynes, Brian D.

    2015-01-01

    Technology Candidates for Air-to-Air and Air-to-Ground Data Exchange is a two-year research effort to visualize the U. S. aviation industry at a point 50 years in the future, and to define potential communication solutions to meet those future data exchange needs. The research team, led by XCELAR, was tasked with identifying future National Airspace System (NAS) scenarios, determining requirements and functions (including gaps), investigating technical and business issues for air, ground, & air-to-ground interactions, and reporting on the results. The project was conducted under technical direction from NASA and in collaboration with XCELAR's partner, National Institute of Aerospace, and NASA technical representatives. Parallel efforts were initiated to define the information exchange functional needs of the future NAS, and specific communication link technologies to potentially serve those needs. Those efforts converged with the mapping of each identified future NAS function to potential enabling communication solutions; those solutions were then compared with, and ranked relative to, each other on a technical basis in a structured analysis process. The technical solutions emerging from that process were then assessed from a business case perspective to determine their viability from a real-world adoption and deployment standpoint. The results of that analysis produced a proposed set of future solutions and most promising candidate technologies. Gap analyses were conducted at two points in the process, the first examining technical factors, and the second as part of the business case analysis. In each case, no gaps or unmet needs were identified in applying the solutions evaluated to the requirements identified. The future communication solutions identified in the research comprise both specific link technologies and two enabling technologies that apply to most or all specific links. As a result, the research resulted in a new analysis approach, viewing the

  6. 33 CFR 334.1280 - Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 33 Navigation and Navigable Waters 3 2014-07-01 2014-07-01 false Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force. 334.1280 Section 334.1280 Navigation and Navigable... REGULATIONS § 334.1280 Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force....

  7. 33 CFR 334.1280 - Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force. 334.1280 Section 334.1280 Navigation and Navigable... REGULATIONS § 334.1280 Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force....

  8. 33 CFR 334.1280 - Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 33 Navigation and Navigable Waters 3 2013-07-01 2013-07-01 false Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force. 334.1280 Section 334.1280 Navigation and Navigable... REGULATIONS § 334.1280 Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force....

  9. 33 CFR 334.1280 - Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force. 334.1280 Section 334.1280 Navigation and Navigable... REGULATIONS § 334.1280 Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force....

  10. 33 CFR 334.1280 - Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force. 334.1280 Section 334.1280 Navigation and Navigable... REGULATIONS § 334.1280 Bristol Bay, Alaska; air-to-air weapon range, Alaskan Air Command, U.S. Air Force....

  11. Missile aerodynamics; Proceedings of the Conference, Monterey, CA, Oct. 31-Nov. 2, 1988

    SciTech Connect

    Mendenhall, M.R.; Nixon, D.; Dillenius, M.F.E.

    1989-01-01

    The present conference discusses the development status of predictive capabilities for missile aerodynamic characteristics, the application of experimental techniques to missile-release problems, prospective high-performance missile designs, the use of lateral jet controls for missile guidance, and the integration of stores on modern tactical aircraft. Also discussed are semiempirical aerodynamic methods for preliminary design, high angle-of-attack behavior for an advanced missile, and the dynamic derivatives of missiles and fighter-type configurations at high angles-of-attack.

  12. A qualitative analysis of future air combat with 'fire and forget' missiles

    NASA Technical Reports Server (NTRS)

    Shinar, J.; Davidovitz, A.

    1987-01-01

    A set of previous examples have demonstrated that the two-target game formulation is adequate for modeling air-to-air combat between two aggressively motivated fighter aircraft. The present paper describes such an engagement between two aircraft of different speed but equipped with the same 'fire and forget' type guided missiles. The results of the analysis suggest a new concept of air combat tactics for future scenarios.

  13. Analysis and compilation of missile aerodynamic data. Volume 2: Performance analysis

    NASA Technical Reports Server (NTRS)

    Burkhalter, J. E.

    1977-01-01

    A general analysis is given of the flight dynamics of several surface-to-air and two air-to-air missile configurations. The analysis involves three phases: vertical climb, straight and level flight, and constant altitude turn. Wind tunnel aerodynamic data and full scale missile characteristics are used where available; unknown data are estimated. For the constant altitude turn phase, a three degree of freedom flight simulation is used. Important parameters considered in this analysis are the vehicle weight, Mach number, heading angle, thrust level, sideslip angle, g loading, and time to make the turn. The actual flight path during the turn is also determined. Results are presented in graphical form.

  14. Thermal Gradient Behavior of TBCs Subjected to a Laser Gradient Test Rig: Simulating an Air-to-Air Combat Flight

    NASA Astrophysics Data System (ADS)

    Lima, Rogerio S.; Marple, Basil R.; Marcoux, P.

    2016-01-01

    A computer-controlled laser test rig (using a CO2 laser) offers an interesting alternative to traditional flame-based thermal gradient rigs in evaluating thermal barrier coatings (TBCs). The temperature gradient between the top and back surfaces of a TBC system can be controlled based on the laser power and a forced air back-face cooling system, enabling the temperature history of complete aircraft missions to be simulated. An air plasma spray-deposited TBC was tested and, based on experimental data available in the literature, the temperature gradients across the TBC system (ZrO2-Y2O3 YSZ top coat/CoNiCrAlY bond coat/Inconel 625 substrate) and their respective frequencies during air-to-air combat missions of fighter jets were replicated. The missions included (i) idle/taxi on the runway, (ii) take-off and climbing, (iii) cruise trajectory to rendezvous zone, (iv) air-to-air combat maneuvering, (v) cruise trajectory back to runway, and (vi) idle/taxi after landing. The results show that the TBC thermal gradient experimental data in turbine engines can be replicated in the laser gradient rig, leading to an important tool to better engineer TBCs.

  15. Preliminary performance estimates of an oblique, all-wing, remotely piloted vehicle for air-to-air combat

    NASA Technical Reports Server (NTRS)

    Nelms, W. P., Jr.; Bailey, R. O.

    1974-01-01

    A computerized aircraft synthesis program has been used to assess the effects of various vehicle and mission parameters on the performance of an oblique, all-wing, remotely piloted vehicle (RPV) for the highly maneuverable, air-to-air combat role. The study mission consists of an outbound cruise, an acceleration phase, a series of subsonic and supersonic turns, and a return cruise. The results are presented in terms of both the required vehicle weight to accomplish this mission and the combat effectiveness as measured by turning and acceleration capability. This report describes the synthesis program, the mission, the vehicle, and results from sensitivity studies. An optimization process has been used to establish the nominal RPV configuration of the oblique, all-wing concept for the specified mission. In comparison to a previously studied conventional wing-body canard design for the same mission, this oblique, all-wing nominal vehicle is lighter in weight and has higher performance.

  16. Performance evaluation of a selected three-ton air-to-air heat pump in the heating mode

    SciTech Connect

    Domingorena, A.A.; Ball, S.J.

    1980-01-01

    An air-to-air split system residential heat pump of nominal three-ton capacity was instrumented and tested in the heating mode under laboratory conditions. This was the second of a planned series of experiments to obtain a data base of system and component performance for heat pumps. The system was evaluated under both steady-state and frosting-defrosting conditions; sensitivity of the system performance to variations in the refrigerant charge was measured. From the steady-state tests, the heating capacity and coefficient of performance were computed, and evaluations were made of the performance parameters of the fan and fan motor units, the heat exchangers and refrigerant metering device, and the compressor. System heat losses were analyzed. The frosting-defrosting tests allowed the observation of system and component performance under dynamic conditions, and measurement of performance degradation under frosting conditions.

  17. Design verification programme for an air-to-air type rocket motor with CFRP composite case and reduced smoke propellant

    NASA Astrophysics Data System (ADS)

    Fossumstuen, Kai; Raudsandmoen, Geir; Heie, Ingar H.; Wurtinger, Horst

    1993-06-01

    A design verification program was performed for an air-to-air type rocket motor, having a carbon fiber reinforced epoxy motor case and reduced smoke, nitramine containing, composite propellant. Structural design of the motor case is presented, including choice of material and method of attaching metal parts. Structural tests, including environmental and handling damage tests, of the motor case were performed. On the complete motor, design verification work was performed for insulation, bonding, propellant properties, grain design and motor case behavior. Six flight-weight motors were tested, including firing at extreme temperatures, environmental loads, firing with launch bending moment, ageing and pressure pulsing. Two motors were also used for insensitive munition tests, fast cook-off and bullet impact. Some performance data that are classified, have been omitted.

  18. Phoenix Missile Hypersonic Testbed (PMHT): System Concept Overview

    NASA Technical Reports Server (NTRS)

    Jones, Thomas P.

    2007-01-01

    A viewgraph presentation of the Phoenix Missile Hypersonic Testbed (PMHT) is shown. The contents include: 1) Need and Goals; 2) Phoenix Missile Hypersonic Testbed; 3) PMHT Concept; 4) Development Objectives; 5) Possible Research Payloads; 6) Possible Research Program Participants; 7) PMHT Configuration; 8) AIM-54 Internal Hardware Schematic; 9) PMHT Configuration; 10) New Guidance and Armament Section Profiles; 11) Nomenclature; 12) PMHT Stack; 13) Systems Concept; 14) PMHT Preflight Activities; 15) Notional Ground Path; and 16) Sample Theoretical Trajectories.

  19. VIEW OF SECOND LEVEL OF MISSILE LAB WITH MISSILE TUBE ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    VIEW OF SECOND LEVEL OF MISSILE LAB WITH MISSILE TUBE WITH HATCH ON LEFT AND CONTROL PANEL ON RIGHT. VIEW FACING SOUTHEAST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  20. Game theoretic target assignment approach in ballistic missile defense

    NASA Astrophysics Data System (ADS)

    Wei, Mo; Chen, Genshe; Pham, Khanh; Blasch, Erik; Wu, Yingli

    2008-04-01

    In this paper, both Pareto game theory and learning theory algorithms are utilized in a resource management module for a practical missile interception system. The resource management module will determine how many and which antimissiles will be launched for interception. Such interception decisions are based on the number of invading missiles, availability of antimissiles, special capability of antimissiles, and realistic constraints on the movements of both invading missiles and antimissiles such as minimum turning radius, maximum velocity, fuel range, etc. Simulations demonstrate performance improvements when compared to existing strategies (i.e. random assignment), independent of guidance laws (i.e. Proportional Navigation (PN) or the Differential-Game-based Guidance Law (DGL) guidance laws) under end-game interception cases or midcourse interception situations.

  1. Modular missile borne computers

    NASA Technical Reports Server (NTRS)

    Ramseyer, R.; Arnold, R.; Applewhite, H.; Berg, R.

    1980-01-01

    The modular missile borne computer's architecture with emphasis on how that architecture evolved is discussed. A careful analysis is given of both the physical constraints and the processing requirements.

  2. 33 CFR 334.670 - Gulf of Mexico south and west of Apalachicola, San Blas, and St. Joseph bays; air-to-air firing...

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Gulf of Mexico south and west of Apalachicola, San Blas, and St. Joseph bays; air-to-air firing practice range, Tyndall Air Force Base, Fla. 334..., DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.670 Gulf of Mexico south and west...

  3. 33 CFR 334.490 - Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for...

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 33 Navigation and Navigable Waters 3 2014-07-01 2014-07-01 false Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for fighter and bombardment aircraft, U.S. Air... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.490 Atlantic Ocean...

  4. 33 CFR 334.490 - Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for...

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for fighter and bombardment aircraft, U.S. Air... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.490 Atlantic Ocean...

  5. 33 CFR 334.490 - Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for fighter and bombardment aircraft, U.S. Air... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.490 Atlantic Ocean...

  6. 33 CFR 334.490 - Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for...

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Atlantic Ocean off Georgia Coast; air-to-air and air-to-water gunnery and bombing ranges for fighter and bombardment aircraft, U.S. Air... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.490 Atlantic Ocean...

  7. 33 CFR 334.670 - Gulf of Mexico south and west of Apalachicola, San Blas, and St. Joseph bays; air-to-air firing...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Gulf of Mexico south and west of Apalachicola, San Blas, and St. Joseph bays; air-to-air firing practice range, Tyndall Air Force Base, Fla. 334..., DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.670 Gulf of Mexico south and west...

  8. 33 CFR 334.1300 - Blying Sound area, Gulf of Alaska, Alaska; air-to-air gunnery practice area, Alaskan Air Command...

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Blying Sound area, Gulf of Alaska, Alaska; air-to-air gunnery practice area, Alaskan Air Command, U.S. Air Force. 334.1300 Section 334.1300... AND RESTRICTED AREA REGULATIONS § 334.1300 Blying Sound area, Gulf of Alaska, Alaska;...

  9. 33 CFR 334.1300 - Blying Sound area, Gulf of Alaska, Alaska; air-to-air gunnery practice area, Alaskan Air Command...

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 33 Navigation and Navigable Waters 3 2013-07-01 2013-07-01 false Blying Sound area, Gulf of Alaska, Alaska; air-to-air gunnery practice area, Alaskan Air Command, U.S. Air Force. 334.1300 Section 334.1300... AND RESTRICTED AREA REGULATIONS § 334.1300 Blying Sound area, Gulf of Alaska, Alaska;...

  10. Nanotechnology for missiles

    NASA Astrophysics Data System (ADS)

    Ruffin, Paul B.

    2004-07-01

    Nanotechnology development is progressing very rapidly. Several billions of dollars have been invested in nanoscience research since 2000. Pioneering nanotechnology research efforts have been primarily conducted at research institutions and centers. This paper identifies developments in nanoscience and technology that could provide significant advances in missile systems applications. Nanotechnology offers opportunities in the areas of advanced materials for coatings, including thin-film optical coatings, light-weight, strong armor and missile structural components, embedded computing, and "smart" structures; nano-particles for explosives, warheads, turbine engine systems, and propellants to enhance missile propulsion; nano-sensors for autonomous chemical detection; and nano-tube arrays for fuel storage and power generation. The Aviation and Missile Research, Development, and Engineering Center (AMRDEC) is actively collaborating with academia, industry, and other Government agencies to accelerate the development and transition of nanotechnology to favorably impact Army Transformation. Currently, we are identifying near-term applications and quantifying requirements for nanotechnology use in Army missile systems, as well as monitoring and screening research and developmental efforts in the industrial community for military applications. Combining MicroElectroMechanical Systems (MEMS) and nanotechnology is the next step toward providing technical solutions for the Army"s transformation. Several research and development projects that are currently underway at AMRDEC in this technology area are discussed. A top-level roadmap of MEMS/nanotechnology development projects for aviation and missile applications is presented at the end.

  11. New Air-Launched Small Missile (ALSM) Flight Testbed for Hypersonic Systems

    NASA Technical Reports Server (NTRS)

    Bui, Trong T.; Lux, David P.; Stenger, Mike; Munson, Mike; Teate, George

    2006-01-01

    A new testbed for hypersonic flight research is proposed. Known as the Phoenix air-launched small missile (ALSM) flight testbed, it was conceived to help address the lack of quick-turnaround and cost-effective hypersonic flight research capabilities. The Phoenix ALSM testbed results from utilization of two unique and very capable flight assets: the United States Navy Phoenix AIM-54 long-range, guided air-to-air missile and the NASA Dryden F-15B testbed airplane. The U.S. Navy retirement of the Phoenix AIM-54 missiles from fleet operation has presented an excellent opportunity for converting this valuable flight asset into a new flight testbed. This cost-effective new platform will fill an existing gap in the test and evaluation of current and future hypersonic systems for flight Mach numbers ranging from 3 to 5. Preliminary studies indicate that the Phoenix missile is a highly capable platform. When launched from a high-performance airplane, the guided Phoenix missile can boost research payloads to low hypersonic Mach numbers, enabling flight research in the supersonic-to-hypersonic transitional flight envelope. Experience gained from developing and operating the Phoenix ALSM testbed will be valuable for the development and operation of future higher-performance ALSM flight testbeds as well as responsive microsatellite small-payload air-launched space boosters.

  12. New Air-Launched Small Missile (ALSM) Flight Testbed for Hypersonic Systems

    NASA Technical Reports Server (NTRS)

    Bui, Trong T.; Lux, David P.; Stenger, Michael T.; Munson, Michael J.; Teate, George F.

    2007-01-01

    The Phoenix Air-Launched Small Missile (ALSM) flight testbed was conceived and is proposed to help address the lack of quick-turnaround and cost-effective hypersonic flight research capabilities. The Phoenix ALSM testbed results from utilization of the United States Navy Phoenix AIM-54 (Hughes Aircraft Company, now Raytheon Company, Waltham, Massachusetts) long-range, guided air-to-air missile and the National Aeronautics and Space Administration (NASA) Dryden Flight Research Center (Edwards, California) F-15B (McDonnell Douglas, now the Boeing Company, Chicago, Illinois) testbed airplane. The retirement of the Phoenix AIM-54 missiles from fleet operation has presented an opportunity for converting this flight asset into a new flight testbed. This cost-effective new platform will fill the gap in the test and evaluation of hypersonic systems for flight Mach numbers ranging from 3 to 5. Preliminary studies indicate that the Phoenix missile is a highly capable platform; when launched from a high-performance airplane, the guided Phoenix missile can boost research payloads to low hypersonic Mach numbers, enabling flight research in the supersonic-to-hypersonic transitional flight envelope. Experience gained from developing and operating the Phoenix ALSM testbed will assist the development and operation of future higher-performance ALSM flight testbeds as well as responsive microsatellite-small-payload air-launched space boosters.

  13. Hypersonic missile propulsion system

    SciTech Connect

    Kazmar, R.R.

    1998-11-01

    Pratt and Whitney is developing the technology for hypersonic components and engines. A supersonic combustion ramjet (scramjet) database was developed using hydrogen fueled propulsion systems for space access vehicles and serves as a point of departure for the current development of hydrocarbon scramjets. The Air Force Hypersonic Technology (HyTech) Program has put programs in place to develop the technologies necessary to demonstrate the operability, performance and structural durability of an expendable, liquid hydrocarbon fueled scramjet system that operates from Mach 4 to 8. This program will culminate in a flight type engine test at representative flight conditions. The hypersonic technology base that will be developed and demonstrated under HyTech will establish the foundation to enable hypersonic propulsion systems for a broad range of air vehicle applications from missiles to space access vehicles. A hypersonic missile flight demonstration is planned in the DARPA Affordable Rapid Response Missile Demonstrator (ARRMD) program in 2001.

  14. Two-target game model of an air combat with fire-and-forget all-aspect missiles

    NASA Technical Reports Server (NTRS)

    Davidovitz, A.; Shinar, J.

    1989-01-01

    An air combat duel between similar aggressive fighter aircraft, both equipped with the same type of guided missiles, is formulated as a two-target differential game using the dynamic model of the game of two identical cars. Each of the identical target sets represents the effective firing envelope of an all-aspect fire-and-forget air-to-air missile. The firing range limits depend on the target aspect angle and are approximated by analytical functions. The maximum range, computed by taking into account the optimal missile avoidance maneuver of the target, determines the no-escape firing envelope. The solution consists of the decomposition of the game space into four regions: the respective winning zones of the two opponents, the draw zone, and the region where the game terminates by a mutual kill. The solution provides a new insight for future air combat analysis.

  15. Advanced missile technology. A review of technology improvement areas for cruise missiles. [including missile design, missile configurations, and aerodynamic characteristics

    NASA Technical Reports Server (NTRS)

    Cronvich, L. L.; Liepman, H. P.

    1979-01-01

    Technology assessments in the areas of aerodynamics, propulsion, and structures and materials for cruise missile systems are discussed. The cruise missiles considered cover the full speed, altitude, and target range. The penetrativity, range, and maneuverability of the cruise missiles are examined and evaluated for performance improvements.

  16. Non-destructive missile seeker flight testing: HWIL in the sky

    NASA Astrophysics Data System (ADS)

    Clements, Jim; Robinson, Joe; Robinson, Richard M.

    2010-04-01

    Surface to air missile development programs typically utilize hardware-in-the-loop (HWIL) simulations when available to provide a non-destructive high volume test environment for what are typically very expensive guidance sections. The HWIL, while invaluable, hasn't been able to obviate the need for missile flight tests. Because of the great expense of these missiles the designers are only allowed to perform a fraction of the desired tests. Missile Airframe Simulation Testbed (MAST) is a program conceived by US Army Aviation and Missile Research Development and Engineering Center (AMRDEC) that blends the non-destructive nature of HWIL with the confidence gained from flight tests to expand the knowledge gained while reducing the development schedule of new missile programs.

  17. A piloted simulation investigation of the normal load factor and longitudinal thrust required for air-to-air acquisition and tracking

    NASA Technical Reports Server (NTRS)

    Whalley, Matthew S.

    1993-01-01

    A piloted simulation study was performed by the U.S. Army Aeroflighydynamics Directorate to develop insight into the maneuverability requirements for aggressive helicopter maneuvering tasks such as air-to-air combat. Both a conventional helicopter and a helicopter with auxiliary thrust were examined. The aircraft parameters of interest were the normal and longitudinal load factor envelopes. Of particular interest were the mission performance and handling qualities tradeoffs with the parameters of interest. Two air-to-air acquisition and tracking tasks and a return-to-cover task were performed to assess mission performance. Results indicate that without auxiliary thrust, the ownship normal load factor capability needs to match that of the adversary in order to provide satisfactory handling qualities. Auxiliary thrust provides significant handling qualities advantages and can be substituted to some extent for normal load factor capability. Auxiliary thrust levels as low as 0.2 thrust/weight can provide significant handling qualities advantages.

  18. 37. Upper level, chromate tanks (formerly provided coolant to missile ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    37. Upper level, chromate tanks (formerly provided coolant to missile guidance section, retractor cables for lock pin in front of ladder at left - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

  19. The Talos guidance system

    NASA Astrophysics Data System (ADS)

    Gulick, J.; Hyatt, W. C.; Martin, O. M., Jr.

    1982-06-01

    A description is given of the design principles and performance capabilities of the Talos surface-to-air missile's homing system, which over the course of its development came to be virtually unjammable, as well as the associated antiradiation seeker, which enables the Talos to operate against radar signal-emitting targets. The interferometric homing system chosen employs widely spaced, airframe-fixed antennas compatible with ramjet inlet geometry and simpler than the alternative gimballed dish antenna. Early Talos missile guidance systems used scanning interferometry, but for subsequent models a continuous wave interferometer was developed, followed by a monopulse seeker. Attention is given to the use of the Talos system as a long range antiradiation missile for radar suppression in the Vietnam conflict.

  20. Phoenix Missile Hypersonic Testbed (PMHT): Project Concept Overview

    NASA Technical Reports Server (NTRS)

    Jones, Thomas P.

    2007-01-01

    An over view of research into a low cost hypersonic research flight test capability to increase the amount of hypersonic flight data to help bridge the large developmental gap between ground testing/analysis and major flight demonstrator Xplanes is provided. The major objectives included: develop an air launched missile booster research testbed; accurately deliver research payloads through programmable guidance to hypersonic test conditions; low cost; a high flight rate minimum of two flights per year and utilize surplus air launched missiles and NASA aircraft.

  1. 77 FR 64564 - Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-22

    ... COMMISSION Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles AGENCY....221 on Design-Basis Hurricane and Hurricane Missiles.'' The purpose of this ISG is to supplement the guidance regarding the application of Regulatory Guide 1.221, ``Design-Basis Hurricane and...

  2. An adaptive maneuvering logic computer program for the simulation of one-on-one air-to-air combat. Volume 1: General description

    NASA Technical Reports Server (NTRS)

    Burgin, G. H.; Fogel, L. J.; Phelps, J. P.

    1975-01-01

    A technique for computer simulation of air combat is described. Volume 1 decribes the computer program and its development in general terms. Two versions of the program exist. Both incorporate a logic for selecting and executing air combat maneuvers with performance models of specific fighter aircraft. In the batch processing version the flight paths of two aircraft engaged in interactive aerial combat and controlled by the same logic are computed. The realtime version permits human pilots to fly air-to-air combat against the adaptive maneuvering logic (AML) in Langley Differential Maneuvering Simulator (DMS). Volume 2 consists of a detailed description of the computer programs.

  3. Tactical missile turbulence problems

    NASA Technical Reports Server (NTRS)

    Dickson, Richard E.

    1987-01-01

    Of particular interest is atmospheric turbulence in the atmospheric boundary layer, since this affects both the launch and terminal phase of flight, and the total flight for direct fire systems. Brief discussions are presented on rocket artillery boost wind problems, mean wind correction, turbulent boost wind correction, the Dynamically Aimed Free Flight Rocket (DAFFR) wind filter, the DAFFR test, and rocket wake turbulence problems. It is concluded that many of the turbulence problems of rockets and missiles are common to those of aircraft, such as structural loading and control system design. However, these problems have not been solved at this time.

  4. On the design of fuzzified trajectory shaping guidance law.

    PubMed

    Lin, Chun-Liang; Lin, Yu-Ping; Chen, Kai-Ming

    2009-04-01

    Midcourse guidance is commonly designed to save as much energy as possible so that the missile's final speed can be maximized while entering the homing stage. For this purpose, a competitive guidance design should be able to generate an admissible flight trajectory as to bring the interceptor to a superior altitude for a favorable target engagement. In this paper, a new adaptive trajectory shaping guidance scheme based on the adaptive fuzzy inference system, which is capable of generating a variety of trajectories for efficient target interception, is presented. The guidance law is developed with the aim of saving the interceptor's energy conservation while improving performance robustness. Applications of the presented approach have included a variety of mission oriented guidance, such as cruise missile guidance, anti-ballistic missile guidance, etc.

  5. Opportunities and challenges for MEMS technology in Army missile systems applications

    NASA Astrophysics Data System (ADS)

    Ruffin, Paul B.

    1999-07-01

    The military market drives the thrust for the development of robust, high performance MicroElectroMechanical Systems (MEMS) devices with applications such as: competent and smart munitions, aircraft and missile autopilots, tactical missile guidance, fire control systems, platform stabilization, smart structures with embedded inertial sensors, missile system health monitoring, aerodynamic flow control, and multiple intelligent small projectiles. Army missile applications will be a fertile market for MEMS products, such as MEMS-based inertial sensors. MEMS technology should significantly enhance performance and provide more robust mission capability in applications where arrays of MEMS devices are required. The Army Aviation and Missile Command Missile Research, Development, and Engineering Center is working diligently with other government agencies, academia, and industry to develop high performing MEMS devices to withstand shock, vibration, temperature, humidity, and long-term storage conditions often encountered by Army missile systems. The goals of the ongoing DARPA MEMS technology programs will meet a significant portion of the Army missile systems requirements. In lieu of presenting an all-inclusive review of Army MEMS applications, this paper addresses a number of opportunities and associated challenges for MEMS systems operating in military environments. Near term applications and the less mature, high-risk applications of MEMS devices are addressed.

  6. 15 CFR 742.5 - Missile technology.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 15 Commerce and Foreign Trade 2 2012-01-01 2012-01-01 false Missile technology. 742.5 Section 742... BASED CONTROLS § 742.5 Missile technology. (a) License requirements. (1) In support of U.S. foreign... establish the existence of a contract. (d) Missile Technology Control Regime. Missile Technology...

  7. 15 CFR 742.5 - Missile technology.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 15 Commerce and Foreign Trade 2 2013-01-01 2013-01-01 false Missile technology. 742.5 Section 742... BASED CONTROLS § 742.5 Missile technology. (a) License requirements. (1) In support of U.S. foreign... establish the existence of a contract. (d) Missile Technology Control Regime. Missile Technology...

  8. 15 CFR 742.5 - Missile technology.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 15 Commerce and Foreign Trade 2 2011-01-01 2011-01-01 false Missile technology. 742.5 Section 742... BASED CONTROLS § 742.5 Missile technology. (a) License requirements. (1) In support of U.S. foreign... establish the existence of a contract. (d) Missile Technology Control Regime. Missile Technology...

  9. Preliminary Low-Speed Wind-Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions Near Airplane Wings

    NASA Technical Reports Server (NTRS)

    Alford, William J., Jr.; Silvers, H. Norman; King, Thomas J., Jr.

    1954-01-01

    A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.

  10. Problems of National Missile Defense

    NASA Astrophysics Data System (ADS)

    Cornwall, John

    2000-04-01

    The currently-proposed national missile defense (NMD) is supposed to counter accidental Russian or Chinese launches of intercontinental nuclear-armed missiles, or rogue nation launches of similar nuclear missiles or of missiles armed with biological weapons, by using mid-course hit-to-kill vehicles guided by IR and radar. But it seems very likely that any nation capable of building (or buying) such a missile offense can build (or buy) effective countermeasures to NMD. These include anti-simulation decoys made of multi-layer insulation (MLI), with warheads covered in MLI sheaths so their signatures resemble those of the decoys. MLI can be effective against both passive IR and radar detection/discrimination. Biological warheads can counter any mid-course defense by releasing a great number of submunitions early in flight. Both nuclear and biological weapons can be deployed by other means, including covert ships in port; trucks; and cruise missiles. The best defense against Russian/Chinese accidental launches is assistance to these countries in improving their launch control systems.

  11. Missile airframe simulation testbed: MANPADS (MAST-M) for test and evaluation of aircraft survivability equipment

    NASA Astrophysics Data System (ADS)

    Clements, Jim; Robinson, Richard; Bunt, Leslie; Robinson, Joe

    2011-06-01

    A number of techniques have been utilized to evaluate the performance of Aircraft Survivability Equipment (ASE) against threat Man-Portable Air Defense Systems (MANPADS). These techniques include flying actual threat MANPADS against stationary ASE with simulated aircraft signatures, testing installed ASE systems against simulated threat signatures, and laboratory hardware-in-the-loop (HWIL) testing with simulated aircraft and simulated missile signatures. All of these tests lack the realism of evaluating installed ASE against in-flight MANPADS on a terminal homing intercept path toward the actual ASE equipped aircraft. This limitation is due primarily to the current inability to perform non-destructive MANPADS/Aircraft flight testing. The U.S. Army Aviation and Missile Research and Development and Engineering Center (AMRDEC) is working to overcome this limitation with the development of a recoverable surrogate MANPADS missile system capable of engaging aircraft equipped with ASE while guaranteeing collision avoidance with the test aircraft. Under its Missile Airframe Simulation Testbed - MANPADS (MAST-M) program, the AMRDEC is developing a surrogate missile system which will utilize actual threat MANPADS seeker/guidance sections to control the flight of a surrogate missile which will perform a collision avoidance and recovery maneuver prior to intercept to insure non-destructive test and evaluation of the ASE and reuse of the MANPADS seeker/guidance section. The remainder of this paper provides an overview of this development program and intended use.

  12. Conceptual design of an ascent-phase interceptor missile

    SciTech Connect

    Salguero, D.E.

    1994-11-01

    A conceptual design for an air-launched interceptor missile to defend against theater ballistic missiles is presented. The missile is designed to intercept the target while ascending, during Or just after the boost phase, before it reaches exo-atmospheric flight. The interceptor consists of a two-stage booster and a shrouded kinetic-kill vehicle. This report concentrates on the booster design required to achieve reasonable standoff ranges. The kinetic-kill vehicle and shroud (the payload) is assumed to weigh 80 lb{sub m} (36 kg) and assumed to contain guidance computers for both the kill vehicle and the booster. The interceptor missile is about 6 m long, .48 m in diameter and weighs about 900 kg. Allowing 25 sec for target detection, trajectory estimation, and interceptor launch, it can intercept 90 sec after target launch from a 220 km stand-off range at an altitude of 60 km. Trade-off studies show that the interceptor performance is most sensitive to the stage mass fractions (with the first-stage mass fraction the most important), the first-stage burn time and the payload weight.

  13. Partial stabilization-based guidance.

    PubMed

    Shafiei, M H; Binazadeh, T

    2012-01-01

    A novel nonlinear missile guidance law against maneuvering targets is designed based on the principles of partial stability. It is demonstrated that in a real approach which is adopted with actual situations, each state of the guidance system must have a special behavior and asymptotic stability or exponential stability of all states is not realistic. Thus, a new guidance law is developed based on the partial stability theorem in such a way that the behaviors of states in the closed-loop system are in conformity with a real guidance scenario that leads to collision. The performance of the proposed guidance law in terms of interception time and control effort is compared with the sliding mode guidance law by means of numerical simulations.

  14. The Oak Ridge Heat Pump Models: I. A Steady-State Computer Design Model of Air-to-Air Heat Pumps

    SciTech Connect

    Fischer, S.K. Rice, C.K.

    1999-12-10

    The ORNL Heat Pump Design Model is a FORTRAN-IV computer program to predict the steady-state performance of conventional, vapor compression, electrically-driven, air-to-air heat pumps in both heating and cooling modes. This model is intended to serve as an analytical design tool for use by heat pump manufacturers, consulting engineers, research institutions, and universities in studies directed toward the improvement of heat pump performance. The Heat Pump Design Model allows the user to specify: system operating conditions, compressor characteristics, refrigerant flow control devices, fin-and-tube heat exchanger parameters, fan and indoor duct characteristics, and any of ten refrigerants. The model will compute: system capacity and COP (or EER), compressor and fan motor power consumptions, coil outlet air dry- and wet-bulb temperatures, air- and refrigerant-side pressure drops, a summary of the refrigerant-side states throughout the cycle, and overall compressor efficiencies and heat exchanger effectiveness. This report provides thorough documentation of how to use and/or modify the model. This is a revision of an earlier report containing miscellaneous corrections and information on availability and distribution of the model--including an interactive version.

  15. 15 CFR 742.5 - Missile technology.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... systems (including ballistic missile systems, space launch vehicles, and sounding rockets) and unmanned air vehicle systems (including cruise missile systems, target drones, and reconnaissance drones... determined to be destined to a manned aircraft, satellite, land vehicle, or marine vessel, in...

  16. Hardware-in-the-loop simulation (HWIL) facility for development, test, and evaluation of multispectral missile systems: update

    NASA Astrophysics Data System (ADS)

    Mobley, Scott B.; Gareri, Jeff P.

    2000-07-01

    The U.S. Army Aviation and Missile Command (AMCOM) Advanced Simulation Center (ASC) provides hardware-in-the-loop (HWIL) simulation support to Program Executive Officers (PEO) and Project Managers (PM) who are responsible for developing and fielding precision guided missiles and sub-munitions for the U.S. Army. The ASC is also engaged in cooperative HWIL simulation tasks supporting other Armed Service Agencies, NATO and other U.S. allies. HWIL simulation provides a means of exercising missile guidance and control hardware in simulated flight, wherein the missile sensors are stimulated with input signals which make the system behave as though it were in actual operation. Real-time computers are used to control the target and countermeasure signatures and battlefield scenarios. Missile flight dynamics, responding to the commands issued by the guidance and control system hardware/software, are simulated in real-time to determine the missile trajectory and to calculate target intercept conditions. The ASC consists of 10 HWIL simulation facilities developed over a period of 20 years. These facilities contain special purpose infrared and RF signal generation equipment, flight motion simulators, radiation chambers, optics, and computers. They provide in- band target signatures, countermeasures, and background scenarios in the microwave, millimeter wave, infrared and visible regions of the electromagnetic spectrum. The ASC HWIL simulation facilities are an important source of test and evaluation data and have a critical role in all phases of a missile system life cycle. The development of a new generation of missile systems that use multi-spectral seekers has imposed unique and difficult requirements on ASC HWIL simulation facilities. For the past three years, the U.S. Army Aviation and Missile Command (AMCOM) has been developing a HWIL simulation facility to test common aperture multi-spectral missile seekers. This paper discusses the problems encountered during the

  17. An Optimal t-{Delta}v Guidance Law for Intercepting a Boosting Target

    SciTech Connect

    Ng, L.C.; Breitfeller, E.; Ledebuhr, A.G.

    2002-06-30

    Lawrence Livermore National Laboratory (LLNL) have developed a new missile guidance law for intercepting a missile during boost phase. Unlike other known missile guidance laws being used today, the new t-{Delta}v guidance law optimally trades an interceptor's onboard fuel capacity against time-to-go before impact. In particular, this guidance law allows a missile designer to program the interceptor to maximally impact a boosting missile before burnout or burn termination and thus negating its ability to achieve the maximum kinetic velocity. For an intercontinental range ballistic missile (ICBM), it can be shown that for every second of earlier intercept prior to burnout, the ICBM ground range is reduced by 350 km. Therefore, intercepting a mere 15 seconds earlier would result in amiss of 5,250 km from the intended target or approximately a distance across the continental US. This paper also shows how the t-{Delta}v guidance law can incorporate uncertainties in target burnout time, predicted intercept point (PIP) error, time-to-go error, and other track estimation errors. The authors believe that the t-{Delta}v guidance law is a step toward the development of a new and smart missile guidance law that would enhance the probability of achieving a boost phase intercept.

  18. Novel applications of femtosecond laser in missile countermeasures

    NASA Astrophysics Data System (ADS)

    Marquis, E.; Pocholle, J. P.

    2005-11-01

    Femtosecond lasers have been widely used in laboratories for years and are now suitable for industrial applications and new military ones. Due to their very short pulse duration, they have the capability to generate intense electric fields and plasmas in targeted materials. We present here a novel scheme of missile counter-measure that is using such an intense laser source to disrupt the operation of IR guidance systems. Classical lasers for missile defense are based on thermal effects on the target whereas photons are used as the kill vehicle [1,2]. In femtosecond countermeasure, the average power is quite low, but the very intense field creates ionization effects than can damage sensitive optics and also plasma that can be used as active decoys against IR homing electronics. As the recent systems are compact and portable, an airport protection scheme is proposed to eliminate manpads threats in the vicinity of a civilian airport.

  19. Comprehensive missile aerodynamics programs for preliminary design

    NASA Technical Reports Server (NTRS)

    Dillenius, M. F. E.; Hemsch, M. J.; Sawyer, W. C.; Allen, J. M.; Blair, A. B., Jr.

    1982-01-01

    Two different classes of missile aeroprediction programs have been recently developed. The first class of programs provides rapid engineering predictions and includes MISSILE1 and MISSILE2 applicable to missile configurations with axisymmetric bodies. The second class of programs consists of the DEMON series, including a simplified version NSWCDM, designed to calculate detailed loadings acting on supersonic missiles which may have non-circular body cross sections. Both classes account for high angles of attack and track vortices from canard or wing section to the tail section. Extensive comparisons with experimental data are presented including nonlinear effects of canard control.

  20. Historical development of world wide guided missiles

    NASA Technical Reports Server (NTRS)

    Spearman, M. L.

    1978-01-01

    This paper attempts to put in perspective the development of missiles from early history to present time. The influence of World War II in accelerating the development of guided missiles, particularly through German scientists, is discussed. The dispersion of German scientists to other countries and the coupling of their work with native talent to develop guided missiles is traced. Particular emphasis is placed on the evolution of the missile in the U.S. and the U.S.S.R. Since the Soviets possess what is probably the world's most complete array of dedicated missile system types, their known inventory is reviewed in some detail.

  1. Global positioning system missile test range applications

    SciTech Connect

    Partridge, M.E.

    1986-06-01

    Using the Global Positioning System (GPS), a missile under test could transmit its own position, reducing radar tracking requirements while still providing three-dimensional position and velocity data with the required accuracy. This study investigated minimum package size requirements for GPS implementation on the SRAM II missile as part of the joint test assembly telemetry system. Reported GPS missile test range applications are reviewed. The two missile tracking system implementations considered are a complete GPS package onboard the missile and onboard frequency translator that retransmits the GPS satellite signals. Accuracy and operation of the two methods are compared. A functional description of the GPS is provided.

  2. The problem of missile defence

    NASA Astrophysics Data System (ADS)

    Webber, Philip

    2014-05-01

    The idea of building a missile system to defend a nation from the horrors of nuclear attack first entered the public consciousness in the 1980s, when US president Ronald Reagan - backed by prominent (and controversial) scientific advisers such as the physicist Edward Teller - promoted the Strategic Defense Initiative as a supposedly impenetrable shield against the Soviet Union's nuclear arsenal.

  3. Growing Pumpkins Where Missiles Grew

    ERIC Educational Resources Information Center

    Loret, John

    1976-01-01

    Purposes of transforming the former Nike-Ajax missile base into a living historical homestead environmental center, resembling an 1800 Long Island village, were to build a homestead environmental center and develop materials, using homestead and pioneer skills, that could be used for education and recreation programs for the schools and community.…

  4. Historical development of worldwide guided missiles

    NASA Technical Reports Server (NTRS)

    Spearman, M. L.

    1983-01-01

    The development of missiles from early history to present time is put in perspective. The influence of World War II in accelerating the development of guided missiles, particularly through German scientists, is discussed. The dispersion of German scientists to other countries and the coupling of their work with native talent to develop guide missiles is traced. Particular emphasis is placed on the evolution of the missile in the U.S. and the U.S.S.R. Since the Soviets possess what is probably the world's most complete array of dedicated missile system types, their known inventory is reviewed. Some philosophical observations of missile design trends and missile purposes are made as related to the interests of various countries.

  5. Historical review of missile aerodynamic developments

    NASA Technical Reports Server (NTRS)

    Spearman, M. Leroy

    1989-01-01

    The development of missiles from early history up to about 1970 is discussed. Early unpowered missiles beyond the rock include the spear, the bow and arrow, the gun and bullet, and the cannon and projectile. Combining gunpowder with projectiles resulted in the first powered missiles. In the early 1900's, the development of guided missiles was begun. Significant advances in missile technology were made by German scientists during World War II. The dispersion of these advances to other countries following the war resulted in accelerating the development of guided missiles. In the late 1940's and early 1950's there was a proliferation in the development of missile systems in many countries. These developments were based primarily on experimental work and on relatively crude analytical techniques. Discussed here are some of the missile systems that were developed up to about 1970; some of the problems encountered; the development of an experimental data base for use with missiles; and early efforts to develop analytical methods applicable to missiles.

  6. Issues in national missile defense

    SciTech Connect

    Canavan, G.H.

    1998-12-01

    Strategic missiles and weapons are proliferating rapidly; thus, the US and its Allies are likely to face both capable bilateral threats and multilateral configurations with complex coalitions for which defenses could be essential for stability. Current hit-to-kill interceptor and radar and infrared detection, track, and discrimination technology should suffice for limited threats, but it is necessary to meet those threats in time while maintaining growth potential for the more sophisticated threats likely to follow. National Missile Defense faces a confusing array of threats, programs, and alternatives, but the technologies in development are clearly an appropriate first step towards any of them. They are likely to succeed in the near term; the challenge is to retain flexibility to provide needed options in the mid and long terms.

  7. Ballistic missile proliferation: An emerging threat 1992

    SciTech Connect

    Nagler, R.G.

    1992-10-01

    This report, based solely on information available from unclassified sources, provides a coherent picture of the scope and trends of ballistic missile proliferation. The focus is on countries developing, producing, or owning ballistic missiles capable of threatening the military forces, assets, or populations of neighboring or geographically remote countries. The report also identifies other countries expected to obtain operational ballistic missile capabilities, discusses expected growth in performance, and examines the projected availability of warheads of mass destruction. The emphasis is on ballistic missiles of ranges greater than approximately 300 km, though shorter range battlefield weapons are discussed as forerunners. The assessment excludes principal U.S. allies and countries formerly in the Warsaw Pact, except where these countries have sold missiles, technology; or personnel services to developing nations in support of their missile programs.

  8. An overview of some monoplanar missile programs

    NASA Technical Reports Server (NTRS)

    Spearman, M. L.

    1984-01-01

    A historical review is presented of some monoplanar missile systems in which the vehicle flight control was similar to that for a conventional aircraft. The review is essentially chronological, beginning prior to World War I, and includes worldwise programs. Illustrative examples of aerodynamic research with monoplanar missiles are presented including some comparisons with cruciform missiles. Some examples of current programs are presented and some particular mission applications for monoplanar systems are discussed.

  9. Technical issues in theater missile defense

    SciTech Connect

    Canavan, G.H.

    1992-05-01

    This note discusses technical issues in theater missile defenses in the terminal, midcourse, and boost phases. The first two are familiar and developed, but face fundamental countermeasures. Boost phase intercepts engage missiles when they are most vulnerable, but have been studied less for theater defense because the engagement times are short. Overall, theater missile defenses resemble strategic defenses, complicated by the tenfold shorter boost phase. 12 refs.

  10. 5. MISSILE TEST AND ASSEMBLY BUILDING, FRONT AND RIGHT SIDES, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    5. MISSILE TEST AND ASSEMBLY BUILDING, FRONT AND RIGHT SIDES, LOOKING SOUTHEAST. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  11. 3. MISSILE TEST AND ASSEMBLY BUILDING, REAR SIDE, LOOKING NORTH. ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    3. MISSILE TEST AND ASSEMBLY BUILDING, REAR SIDE, LOOKING NORTH. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  12. 1. MISSILE TEST AND ASSEMBLY BUILDING, FRONT, LOOKING SOUTH. ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    1. MISSILE TEST AND ASSEMBLY BUILDING, FRONT, LOOKING SOUTH. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  13. 6. MISSILE TEST AND ASSEMBLY BUILDING, REAR AND LEFT SIDES, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    6. MISSILE TEST AND ASSEMBLY BUILDING, REAR AND LEFT SIDES, LOOKING NORTHWEST. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  14. 7. PHOTOCOPY, PLANS, ELEVATIONS, AND SECTION DRAWING FOR MISSILE TEST ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    7. PHOTOCOPY, PLANS, ELEVATIONS, AND SECTION DRAWING FOR MISSILE TEST AND ASSEMBLY BUILDING. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  15. 2. MISSILE ASSEMBLY BUILDING, RIGHT SIDE, LOOKING NORTH. NIKE ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    2. MISSILE ASSEMBLY BUILDING, RIGHT SIDE, LOOKING NORTH. - NIKE Missile Base C-84, Missile Test & Assembly Building, North of Launch Area Entrance Drive & east of Mess Hall, Barrington, Cook County, IL

  16. 2. MISSILE TEST AND ASSEMBLY BUILDING, RIGHT SIDE, LOOKING WEST. ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    2. MISSILE TEST AND ASSEMBLY BUILDING, RIGHT SIDE, LOOKING WEST. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  17. 4. MISSILE TEST AND ASSEMBLY BUILDING, LEFT SIDE, LOOKING NORTH. ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    4. MISSILE TEST AND ASSEMBLY BUILDING, LEFT SIDE, LOOKING NORTH. - NIKE Missile Base SL-40, Missile Test & Assembly Building, South end of launch area, northeast of Generator Building No. 3, Hecker, Monroe County, IL

  18. 2. View from missile site control building (south to north) ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    2. View from missile site control building (south to north) of missile launch area, showing warhead handling building in background - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

  19. National Missile Defense: What, When, and Why?

    SciTech Connect

    Garwin, Richard L.

    2001-12-05

    The Bush Administration is steaming ahead with the deployment of the Clinton-designed mid-course hit-to-kill intercept system for national missile defense. This has serious disabilities against even the simplest strategic ballistic missiles. What is the threat to the United States from such missiles, in context? Is NMD a rational response, considering the always limited resources of the U.S. government? What are the other threats and needs? If protection is demanded against potential emerging missile states, what are the options? Answers to these questions will be provided in the talk and some are already available at the author's web site: http://www.fas.org/rlg.

  20. Test and evaluation of the tactical missile

    SciTech Connect

    Eichblatt, E.J. Jr.

    1989-01-01

    Practical test and evaluation (T E) methods for tactical missiles are described in chapters contributed by experts. Topics addressed include missile performance criteria; flight tests; laboratory and field tests; simulations; launchers; T E of insensitive munitions; T E of reliability; testing for EM-environment effects; logistics, missile tests, and suitability evaluation; and the evaluation of weapon-system integration. To demonstrate effective T E planning strategies, the phases of a typical missile program are outlined. Extensive diagrams, drawings, graphs, and tables of numerical data are provided.

  1. Application of IPAD to missile design

    NASA Technical Reports Server (NTRS)

    Santa, J. E.; Whiting, T. R.

    1974-01-01

    The application of an integrated program for aerospace-vehicle design (IPAD) to the design of a tactical missile is examined. The feasibility of modifying a proposed IPAD system for aircraft design work for use in missile design is evaluated. The tasks, cost, and schedule for the modification are presented. The basic engineering design process is described, explaining how missile design is achieved through iteration of six logical problem solving functions throughout the system studies, preliminary design, and detailed design phases of a new product. Existing computer codes used in various engineering disciplines are evaluated for their applicability to IPAD in missile design.

  2. Fuzzy logic and guidance algorithm design

    SciTech Connect

    Leng, G.

    1994-12-31

    This paper explores the use of fuzzy logic for the design of a terminal guidance algorithm for an air to surface missile against a stationary target. The design objectives are (1) a smooth transition, at lock-on, (2) large impact angles and (3) self-limiting acceleration commands. The method of reverse kinematics is used in the design of the membership functions and the rule base. Simulation results for a Mach 0.8 missile with a 6g acceleration limit are compared with a traditional proportional navigation scheme.

  3. Principles of Guided Missiles and Nuclear Weapons.

    ERIC Educational Resources Information Center

    Naval Personnel Program Support Activity, Washington, DC.

    Fundamentals of missile and nuclear weapons systems are presented in this book which is primarily prepared as the second text of a three-volume series for students of the Navy Reserve Officers' Training Corps and the Officer Candidate School. Following an introduction to guided missiles and nuclear physics, basic principles and theories are…

  4. Missile Defense and International Space Law

    NASA Astrophysics Data System (ADS)

    Hashimoto, Y.

    2002-01-01

    By the withdrawal from Anti Ballistic Missile (ABM) Treaty of 1972 by the United States of America, there will emerge the age of no concrete legal restrictions for ballistic missiles defense in the outer space.On the other hand, because the proliferation of ballistic missile technology has been the problem to be solved as soon as possible, we have to build new regulations for the adequate missile defense and other related activities including the use of outer space.In this paper, the implication of ABM Treaty in the Cold War era will be reviewed and the present and future situation and ideal legal scheme for missile defense and outer space usage will be considered.

  5. New near-optimal feedback guidance algorithms for space missions

    NASA Astrophysics Data System (ADS)

    Hawkins, Matthew Jay

    This dissertation describes several different spacecraft guidance algorithms, with applications including asteroid intercept and rendezvous, planetary landing, and orbital transfer. A comprehensive review of spacecraft guidance algorithms for asteroid intercept and rendezvous. Zero-Effort-Miss/Zero-Effort-Velocity (ZEM/ZEV) guidance is introduced and applied to asteroid intercept and rendezvous, and to a wealth of different example problems, including missile intercept, planetary landing, and orbital transfer. It is seen that the ZEM/ZEV guidance law can be used in many different scenarios, and that it provides near-optimal performance where an analytical optimal guidance law does not exist, such as in a non-linear gravity field.

  6. Application of partial sliding mode in guidance problem.

    PubMed

    Shafiei, M H; Binazadeh, T

    2013-03-01

    In this paper, the problem of 3-dimensional guidance law design is considered and a new guidance law based on partial sliding mode technique is presented. The approach is based on the classification of the state variables within the guidance system dynamics with respect to their required stabilization properties. In the proposed law by using a partial sliding mode technique, only trajectories of a part of states variables are forced to reach the partial sliding surfaces and slide on them. The resulting guidance law enables the missile to intercept highly maneuvering targets within a finite interception time. Effectiveness of the proposed guidance law is demonstrated through analysis and simulations.

  7. THIRD LEVEL OF MISSILE LAB (SECOND FLOOR OF BUILDING) SHOWING ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    THIRD LEVEL OF MISSILE LAB (SECOND FLOOR OF BUILDING) SHOWING MISSILE TUBE. VIEW FACING SOUTH - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  8. OVERVIEW OF FOURTH LEVEL OF MISSILE LAB (ROOFTOP LEVEL OF ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    OVERVIEW OF FOURTH LEVEL OF MISSILE LAB (ROOFTOP LEVEL OF BUILDING) SHOWING TOP OF MISSILE TUBE. VIEW FACING WEST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  9. 3. View from missile site control building (southeast to northwest) ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    3. View from missile site control building (southeast to northwest) of missile launch area showing universal missile building on left and warhead handling building in background. - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

  10. Spin Stabilized Impulsively Controlled Missile (SSICM)

    NASA Astrophysics Data System (ADS)

    Crawford, J. I.; Howell, W. M.

    1985-12-01

    This patent is for the Spin Stabilized Impulsively Controlled Missile (SSICM). SSICM is a missile configuration which employs spin stabilization, nutational motion, and impulsive thrusting, and a body mounted passive or semiactive sensor to achieve very small miss distances against a high speed moving target. SSICM does not contain an autopilot, control surfaces, a control actuation system, nor sensor stabilization gimbals. SSICM spins at a rate sufficient to provide frequency separation between body motions and inertial target motion. Its impulsive thrusters provide near instantaneous changes in lateral velocity, whereas conventional missiles require a significant time delay to achieve lateral acceleration.

  11. Implications of defenses against tactical ballistic missiles

    SciTech Connect

    Flax, A.

    1994-05-01

    The growing number of short- to medium-range ballistic missiles (SMBMs) in the inventories of many smaller states that have had recent or less recent armed conflicts with one another has been a source of concern to many countries. Inevitably this concern over ballistic missiles had been linked to their use as delivery vehicles for {open_quotes}weapons of mass destruction{close_quotes}, a category that now includes nuclear, chemical and biological weapons. But it can be argued that this categorization is not particularly useful as a point of departure for discussions of ballistic missile defense (BMD) against SMBMs.

  12. Missile rolling tail brake torque system. [simulating bearing friction on canard controlled missiles

    NASA Technical Reports Server (NTRS)

    Davis, W. T. (Inventor)

    1984-01-01

    Apparatus for simulating varying levels of friction in the bearings of a free rolling tail afterbody on a canard-controlled missile to determine friction effects on aerodynamic control characteristics is described. A ring located between the missile body and the afterbody is utilized in a servo system to create varying levels of friction between the missile body and the afterbody to simulate bearing friction.

  13. Defending against ballistic missile attacks

    SciTech Connect

    Frelk, J.J.; Tait, G.E.

    1990-01-01

    This book is a compendium of information on the proliferation of ballistic missiles and other defense issues. This volume describes recent SDI advances in crystal clear language. It explains how the marriage of ultra-compact electronics and rocketry has created the smart bullet or brilliant pebble--a projectile with a tiny but powerful compute brain. The brilliant pebble tracks it target by sensing the heat the target emits, as a snake does when tracking a small mammal. Then, guided by its miniaturized computer brain, the brilliant pebble steers itself into the target and destroys it by force of the impact. In this latest form, the brilliant pebble even has the ability to take sightings on the stars, setting its course by celestial navigation.

  14. Experimental and Computational Induced Aerodynamics from Missile Jet Reaction Controls at Angles of Attack to 75 Degrees

    NASA Technical Reports Server (NTRS)

    Capone, Francis J.; Ashbury, Scott C.; Deere, Karen A.

    1996-01-01

    An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine induced aerodynamic effects from jet reaction controls of an advanced air-to-air missile concept. The 75-percent scale model featured independently controlled reaction jets located near the nose and tail of the model. Aerodynamic control was provided by four fins located near the tail of the model. This investigation was conducted at Mach numbers of 0.35 and 0.60, at angles of attack up to 75 deg and at nozzle pressure ratios up to 90. Jet-reaction thrust forces were not measured by the force balance but jet-induced forces were. In addition, a multiblock three-dimensional Navier-Stokes method was used to calculate the flowfield of the missile at angles of attack up to 40 deg. Results indicate that large interference effects on pitching moment were induced from operating the nose jets with the the off. Excellent correlation between experimental and computational pressure distributions and pitching moment were obtained a a Mach number of 0.35 and at angles of attack up to 40 deg.

  15. National Missile Defense: What, When and Why?

    SciTech Connect

    Garwin, Richard L

    2009-12-05

    The Bush Administration is steaming ahead with the deployment of the Clinton-designed mid-course hit-to-kill intercept system for national missile defense. This has serious disabilities against even the simplest strategic ballistic missiles. What is the threat to the United States from such missiles, in context? Is NMD a rational response, considering the always limited resources of the U.S. government? What are the other threats and needs? If protection is demanded against potential emerging missile states, what are the options? Answers to these questions will be provided in the talk and some are already available at the author’s web site: http://www.fas.org/rlg.

  16. 15 CFR 742.5 - Missile technology.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Country Chart (see Supplement No. 1 to part 738 of the EAR). (2) The term “missiles” is defined as rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets) and...

  17. The model of dynamics and control of modified optical scanning seeker in anti-aircraft rocket missile

    NASA Astrophysics Data System (ADS)

    Gapinski, Daniel; Koruba, Zbigniew; Krzysztofik, Izabela

    2014-04-01

    The paper presents the concept of a modified optical scanning seeker. Programmed and tracking controls have been developed with the simultaneous influence of external interferences from the direction of self-guiding rocket missile. The numerical analysis for the proposed scanning seeker has been conducted. It appears from the conducted research that the seeker maintains accurately the set direction in space despite the occurrence of large angular accelerations of the missile. Moreover, the control of the seeker's axis is done with sufficient accuracy for self-guidance with the use of small control moments.

  18. A novel guidance law using fast terminal sliding mode control with impact angle constraints.

    PubMed

    Sun, Lianghua; Wang, Weihong; Yi, Ran; Xiong, Shaofeng

    2016-09-01

    This paper is concerned with the question of, for a missile interception with impact angle constraints, how to design a guidance law. Firstly, missile interception with impact angle constraints is modeled; secondly, a novel guidance law using fast terminal sliding mode control based on extended state observer is proposed to optimize the trajectory and time of interception; finally, for stationary targets, constant velocity targets and maneuvering targets, the guidance law and the stability of the closed loop system is analyzed and the stability of the closed loop system is analyzed, respectively. Simulation results show that when missile and target are on a collision course, the novel guidance law using fast terminal sliding mode control with extended state observer has more optimized trajectory and effectively reduces the time of interception which has a great significance in modern warfare. PMID:27238736

  19. A novel guidance law using fast terminal sliding mode control with impact angle constraints.

    PubMed

    Sun, Lianghua; Wang, Weihong; Yi, Ran; Xiong, Shaofeng

    2016-09-01

    This paper is concerned with the question of, for a missile interception with impact angle constraints, how to design a guidance law. Firstly, missile interception with impact angle constraints is modeled; secondly, a novel guidance law using fast terminal sliding mode control based on extended state observer is proposed to optimize the trajectory and time of interception; finally, for stationary targets, constant velocity targets and maneuvering targets, the guidance law and the stability of the closed loop system is analyzed and the stability of the closed loop system is analyzed, respectively. Simulation results show that when missile and target are on a collision course, the novel guidance law using fast terminal sliding mode control with extended state observer has more optimized trajectory and effectively reduces the time of interception which has a great significance in modern warfare.

  20. Missile sizing for ascent-phase intercept

    SciTech Connect

    Hull, D.G.; Salguero, D.E.

    1994-11-01

    A computer code has been developed to determine the size of a ground-launched, multistage missile which can intercept a theater ballistic missile before it leaves the atmosphere. Typical final conditions for the inteceptor are 450 km range, 60 km altitude, and 80 sec flight time. Given the payload mass (35 kg), which includes a kinetic kill vehicle, and achievable values for the stage mass fractions (0.85), the stage specific impulses (290 sec), and the vehicle density (60 lb/ft{sup 3}), the launch mass is minimized with respect to the stage payload mass ratios, the stage burn times, and the missile angle of attack history subject to limits on the angle of attack (10 deg), the dynamic pressure (60,000 psf), and the maneuver load (200,000 psf deg). For a conical body, the minimum launch mass is approximately 1900 kg. The missile has three stages, and the payload coasts for 57 sec. A trade study has been performed by varying the flight time, the range, and the dynamic pressure Emits. With the results of a sizing study for a 70 lb payload and q{sub max} = 35,000 psf, a more detailed design has been carried out to determine heat shield mass, tabular aerodynamics, and altitude dependent thrust. The resulting missile has approximately 100 km less range than the sizing program predicted primarily because of the additional mass required for heat protection. On the other hand, launching the same missile from an aircraft increases its range by approximately 100 km. Sizing the interceptor for air launch with the same final conditions as the ground-launched missile reduces its launch mass to approximately 1000 kg.

  1. 43. Launch Area, Underground Missile Storage Structure, detail of air ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    43. Launch Area, Underground Missile Storage Structure, detail of air vent VIEW NORTHWEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  2. 42. Launch Area, Underground Missile Storage Structure, detail of escape ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    42. Launch Area, Underground Missile Storage Structure, detail of escape hatch, elevator and air vent VIEW SOUTH - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  3. 36. Launch Area, Underground Missile Storage Structure, detail showing elevator, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    36. Launch Area, Underground Missile Storage Structure, detail showing elevator, air ventilators and personnel entrance VIEW SOUTHEAST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  4. 37. Launch Area, Underground Missile Storage Structure, detail of personnel ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    37. Launch Area, Underground Missile Storage Structure, detail of personnel entrance VIEW NORTH - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  5. 40. Launch Area, Underground Missile Storage Structure, detail of escape ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    40. Launch Area, Underground Missile Storage Structure, detail of escape hatch and decontamination shower VIEW WEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  6. 38. Launch Area, Underground Missile Storage Structure, detail of conduit ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    38. Launch Area, Underground Missile Storage Structure, detail of conduit service junction - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  7. 41. Launch Area, Underground Missile Storage Structure, detail of elevator ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    41. Launch Area, Underground Missile Storage Structure, detail of elevator and air vents VIEW NORTHEAST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  8. 11. View from heat sink, south oblique of missile site ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    11. View from heat sink, south oblique of missile site control building - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

  9. 2. Missile Alert Facility, south side, view from baseball bleachers. ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    2. Missile Alert Facility, south side, view from baseball bleachers. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  10. 6. PHOTOCOPY, WATER TREATMENT PUMPING AND STORAGE BUILDING, MISSILE TEST ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    6. PHOTOCOPY, WATER TREATMENT PUMPING AND STORAGE BUILDING, MISSILE TEST AND ASSEMBLY BUILDING, GENERATOR BUILDING No. 3, AND WARHEADING BUILDING OF LAUNCH AREA. - NIKE Missile Base SL-40, Beck Road between Nike & M Roads, Hecker, Monroe County, IL

  11. 5. VIEW OF MISSILE ASSEMBLY CALLED 'FIRE HOUSE,' LOOKING NORTH, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    5. VIEW OF MISSILE ASSEMBLY CALLED 'FIRE HOUSE,' LOOKING NORTH, LOCATED NEAR GATE AT ENTRANCE TO LAUNCH AREA Marilyn Ziemer, photographer, April 1988 - Los Pinetos Nike Missile Site, Santa Clara Road, Los Angeles National Forest, Sylmar, Los Angeles County, CA

  12. VIEW OF THIRD LEVEL OF MISSILE LAB (SECOND FLOOR OF ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    VIEW OF THIRD LEVEL OF MISSILE LAB (SECOND FLOOR OF BUILDING) SHOWING MISSILE TUBE IN CENTER WITH OPEN HATCH AT RIGHT. VIEW FACING NORTHEAST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  13. Dr. von Braun In Front of a Display of Missiles

    NASA Technical Reports Server (NTRS)

    1960-01-01

    In this photo, Director of the US Army Ballistic Missile Agency (ABMA) Development Operations Division, Dr. Wernher von Braun, is standing before a display of Army missiles celebrating ABMA's Fourth Open House. The missiles in the background include (left to right) a satellite on a Juno II shroud with a Nike Ajax pointing left in front of a Jupiter missile. The Lacrosse is in front of the Juno II. The Nike Hercules points skyward in front of the Juno II and the Redstone.

  14. DETAIL OF OPEN HATCH SHOWING INTERIOR OF MISSILE TUBE AND ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    DETAIL OF OPEN HATCH SHOWING INTERIOR OF MISSILE TUBE AND OPEN HATCH AND DOOR ON OPPOSITE SIDE OF TUBE (AT THIRD LEVEL OF MISSILE LAB). VIEW FACING WEST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  15. Hardware-in-the-loop test facility for the standard missile-3 kinetic warhead

    NASA Astrophysics Data System (ADS)

    Patchan, Robert M.

    2005-05-01

    The Guidance System Evaluation Laboratory of The Johns Hopkins University Applied Physics Laboratory developed a hardware-in-the-loop (HWIL) simulation facility in 2000 for the test and evaluation of the Aegis Ballistic Missile Defense Standard Missile-3 (SM-3) kinetic warhead. We continue to expand on this architecture to facilitate the test of the tactically deployed SM-3 system. An overview and philosophy of the HWIL facility is described. Each of the key test equipment devices is described, along with an upgrade path that provides more accuracy and reliability, as well as increased test capability. The key components are the body dynamics simulation control computer, a scene rendering computer, a resistive-array IR scene projector, and support optics.

  16. Infrared tracker for a portable missile launcher

    SciTech Connect

    Carlson, J.J.

    1993-07-13

    An infrared beam tracker is described for arrangement to a housing that is unitary with a portable missile launcher, comprising: a rotating beam splitter positioned to intercept the infrared beam passing a first portion of the beam through the beam splitter along a first direction and reflecting the remaining portion along a different direction; a first infrared detector for receiving the beam reflected portion from the beam splitter and produce electric signals responsive thereto; a second infrared detector for receiving the beam portion that passes through the beam splitter and providing electric signals responsive thereto; and means interconnected to the first and second infrared detectors and responsive to the electric signals generated by said detectors for determining errors in missile flight direction and communicating course correction information to the missile.

  17. VIEW OF MISSILE TUBE AT THE GROUND FLOOR LEVEL. VIEW ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    VIEW OF MISSILE TUBE AT THE GROUND FLOOR LEVEL. VIEW FACING SOUTH - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  18. DETAIL OF INTERIOR OF MISSILE TUBE AT GROUND FLOOR LEVEL ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    DETAIL OF INTERIOR OF MISSILE TUBE AT GROUND FLOOR LEVEL SHOWING AIR COMPRESSOR TANKS AND CURVING STEEL PIECE. VIEW FACING EAST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  19. DETAIL OF MISSILE TUBE HATCH WITH MILLED FITTINGS AT GROUND ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    DETAIL OF MISSILE TUBE HATCH WITH MILLED FITTINGS AT GROUND FLOOR LEVEL. VIEW FACING EAST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  20. VIEW OF MISSILE TUBE AT THE GROUND FLOOR LEVEL. VIEW ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    VIEW OF MISSILE TUBE AT THE GROUND FLOOR LEVEL. VIEW FACING EAST - U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  1. 22 CFR 120.29 - Missile Technology Control Regime.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 22 Foreign Relations 1 2010-04-01 2010-04-01 false Missile Technology Control Regime. 120.29... DEFINITIONS § 120.29 Missile Technology Control Regime. (a) For purposes of this subchapter, Missile Technology Control Regime (MTCR) means the policy statement between the United States, the United...

  2. 22 CFR 120.29 - Missile Technology Control Regime.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 22 Foreign Relations 1 2011-04-01 2011-04-01 false Missile Technology Control Regime. 120.29... DEFINITIONS § 120.29 Missile Technology Control Regime. (a) For purposes of this subchapter, Missile Technology Control Regime (MTCR) means the policy statement between the United States, the United...

  3. 22 CFR 120.29 - Missile Technology Control Regime.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 22 Foreign Relations 1 2012-04-01 2012-04-01 false Missile Technology Control Regime. 120.29... DEFINITIONS § 120.29 Missile Technology Control Regime. (a) For purposes of this subchapter, Missile Technology Control Regime (MTCR) means the policy statement between the United States, the United...

  4. 22 CFR 120.29 - Missile Technology Control Regime.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 22 Foreign Relations 1 2013-04-01 2013-04-01 false Missile Technology Control Regime. 120.29... DEFINITIONS § 120.29 Missile Technology Control Regime. (a) For purposes of this subchapter, Missile Technology Control Regime (MTCR) means the policy statement between the United States, the United...

  5. 22 CFR 120.29 - Missile Technology Control Regime.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 22 Foreign Relations 1 2014-04-01 2014-04-01 false Missile Technology Control Regime. 120.29... DEFINITIONS § 120.29 Missile Technology Control Regime. (a) For purposes of this subchapter, Missile Technology Control Regime (MTCR) means the policy statement among the United States, the United Kingdom,...

  6. 1. View from missile site control building (southeast to northwest) ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    1. View from missile site control building (southeast to northwest) of universal missile building. Note earth mounding. On the far right can be seen the exit tunnel; the small "boxes" on top are the roof ventilators. This building was salvaged and sealed after site inactivation - Stanley R. Mickelsen Safeguard Complex, Universal Missile Building, Between Tactical Road South & Patrol Road, Nekoma, Cavalier County, ND

  7. Missile Captive Carry Monitoring using a Capacitive MEMS Accelerometer

    SciTech Connect

    Hatchell, Brian K.; Mauss, Fredrick J.; Santiago-Rojas, Emiliano; Amaya, Ivan A.; Skorpik, James R.; Silvers, Kurt L.; Marotta, Steve

    2010-04-08

    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. One of the most significant exposures to vibration occurs when the missile is being carried by an aviation platform, which is a condition known as captive carry. If the duration of captive carry exposure could be recorded during the missile’s service life, several advantages could be realized. Missiles that have been exposed to durations outside the design envelop could be flagged or screened for maintenance or inspection; lightly exposed missiles could be selected for critical mission applications; and missile allocation to missions could be based on prior use to avoid overuse. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing health monitoring systems to assess and improve reliability of missiles during storage and field exposures. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the HELLFIRE II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the HELLFIRE II missile to record the cumulative hours the host missile has been in captive carry mode and thereby assess the overall health of the missile. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to identify captive carry, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  8. Antitank missiles night firing from Aerospatiale helicopters

    NASA Astrophysics Data System (ADS)

    Dewinter, G.

    A day/night firing system for HOT antitank missiles was developed and mounted on a HAC/PAH2 helicopter, equipped with a suitably adapted sight. Night fighting requirements for a helicopter that is armed with antitank missiles are recalled. The selection of a sensor is discussed. The design of a platform in order to fulfill the observation and firing mission is described. Night antitank action is analyzed. Characteristics of a thermal imager which solves the identified problems of night firing are given.

  9. Theater missile defense programs: Status and prospects

    SciTech Connect

    Pike, J.

    1994-09-01

    The Clinton administration now calls the Strategic Defense Initiative (SDI) the ballistic missile defense program. But the names have simply been changed to protect the guilty - the new program exhibits substantial continuity with the old in technology and goals. While acronyms have been changed, many of the programs continued by the Clinton administration date from the Reagan or Bush eras. And most strikingly, the Clinton administrations` ambitions for a virtually perfect defense against theater ballistic missiles harken to the unattainable goals for strategic defense initially set by President Reagan over a decade ago.

  10. An autonomous rendezvous and docking system using cruise missile technologies

    NASA Technical Reports Server (NTRS)

    Jones, Ruel Edwin

    1991-01-01

    In November 1990 the Autonomous Rendezvous & Docking (AR&D) system was first demonstrated for members of NASA's Strategic Avionics Technology Working Group. This simulation utilized prototype hardware from the Cruise Missile and Advanced Centaur Avionics systems. The object was to show that all the accuracy, reliability and operational requirements established for a space craft to dock with Space Station Freedom could be met by the proposed system. The rapid prototyping capabilities of the Advanced Avionics Systems Development Laboratory were used to evaluate the proposed system in a real time, hardware in the loop simulation of the rendezvous and docking reference mission. The simulation permits manual, supervised automatic and fully autonomous operations to be evaluated. It is also being upgraded to be able to test an Autonomous Approach and Landing (AA&L) system. The AA&L and AR&D systems are very similar. Both use inertial guidance and control systems supplemented by GPS. Both use an Image Processing System (IPS), for target recognition and tracking. The IPS includes a general purpose multiprocessor computer and a selected suite of sensors that will provide the required relative position and orientation data. Graphic displays can also be generated by the computer, providing the astronaut / operator with real-time guidance and navigation data with enhanced video or sensor imagery.

  11. Evaluation of wind/tornado-generated missile impact

    SciTech Connect

    Singhal, M.K.; Walls, J.C.

    1993-09-01

    Simplified empirical formulae and some tabular data for the design/evaluation of structure barriers to resist wind/tornado generated missiles impact are presented in this paper. The scope is limited to the missiles defined by UCRL-15910 which are to be considered for moderate and high hazard facilities only. The method presented herein are limited to consideration of local effects on the barrier, i.e., the barrier must be capable of stopping the missile, and the barrier must no cause the generation of secondary missiles due to scabbing. Overall structural response to missile impact and structural effects derived from wind pressure are not addressed in this paper.

  12. The Cuban Missile Crisis. Lesson Plan.

    ERIC Educational Resources Information Center

    Miller, Linda K.; McAuliffe, Mary

    1994-01-01

    Presents a secondary lesson plan based on primary sources recently released by the Central Intelligence Agency on the Cuban Missile Crisis. Provides a background essay on the event. Includes five maps and three documents, all of which have been declassified from top secret or secret status. (CFR)

  13. Nondestructive inspection of a composite missile launcher

    NASA Astrophysics Data System (ADS)

    Ley, O.; Chung, S.; Butera, M.; Valatka, T.; Triplett, M. H.; Godinez, V.

    2012-05-01

    Lighter weight alternatives are being sought to replace metallic components currently used in high performance aviation and missile systems. Benefits of lightweight, high strength carbon fiber reinforced composites in missile launchers and rocket motor cases include improved fuel economy, increased flight times, enhanced lethality and/or increased velocity. In this work, various nondestructive inspection techniques are investigated for the damage assessment of a composite missile launcher system for use in U.S. Army attack helicopters. The launcher system, which includes rails and a hardback, can be subject to impact damage from accidental tool drops, routine operation, and/or ballistic threats. The composite hardback and the launch rails both have complex geometries that can challenge the inspection process. Scanning techniques such as line scanning thermography, ultrasonic, and acousto-ultrasonics will be used and compared to determine damage detection accuracy, reliability, and efficiency. Results will also be compared with visual observations to determine if there is a correlation. The goal is to establish an inspection method that quickly and accurately assesses damage extent in order to minimize service time and return the missile system back into the field [1].

  14. Ring Wing for an underwater missile

    NASA Astrophysics Data System (ADS)

    August, Henry; Carapezza, Edward

    Hughes Aircraft has performed exploratory wind tunnel studies of compressed carriage missile designs having extendable Ring Wing and wrap-around tail control surfaces. These force and moment data indicate that significant improvements in a missile's lift and aerodynamic efficiency can be realized. Low speed test results of these data were used to estimate potential underwater improved hydrodynamic characteristics that a Ring Wing and wrap-around tails can bring to an advanced torpedo design. Estimates of improved underwater flight performance of a heavyweight torpedo (4000 lbs.) having an extendable Ring Wing and wrap-around tails were made. The compressed volume design of this underwater missile is consistent with tube-launch constraints and techniques. Study results of this novel Ring Wing torpedo design include extended flight performance in range and endurance due to lowered speeds capable of sustaining underwater level flight. Correspondingly, reduced radiated noise for enhanced stealth qualities is projected. At high speeds, greater maneuverability and aimpoint selection can be realized by a Ring Wing underwater missile.

  15. Remote video assessment for missile launch facilities

    SciTech Connect

    Wagner, G.G.; Stewart, W.A.

    1995-07-01

    The widely dispersed, unmanned launch facilities (LFs) for land-based ICBMs (intercontinental ballistic missiles) currently do not have visual assessment capability for existing intrusion alarms. The security response force currently must assess each alarm on-site. Remote assessment will enhance manpower, safety, and security efforts. Sandia National Laboratories was tasked by the USAF Electronic Systems Center to research, recommend, and demonstrate a cost-effective remote video assessment capability at missile LFs. The project`s charter was to provide: system concepts; market survey analysis; technology search recommendations; and operational hardware demonstrations for remote video assessment from a missile LF to a remote security center via a cost-effective transmission medium and without using visible, on-site lighting. The technical challenges of this project were to: analyze various video transmission media and emphasize using the existing missile system copper line which can be as long as 30 miles; accentuate and extremely low-cost system because of the many sites requiring system installation; integrate the video assessment system with the current LF alarm system; and provide video assessment at the remote sites with non-visible lighting.

  16. Cruise missiles should not stop START

    SciTech Connect

    Tsipis, K.

    1988-11-01

    A method for verifying a cruise-missile agreement that would be acceptable to the military, industrial, and intelligence communities in both nations must be as unintrusive as possible, while remaining immune to cheating of any significance. This is the goal of the technical solutions outlined here. The elements of a verification regime described do not require routine, intrusive, on-site visits to naval vessels, aircraft, air bases, or weapons magazines where missiles may be stored. They do not interfere with the operational readiness of the missiles, and they protect legitimate military secrets of the inspected nation. If supported by competent national technical means of verification such as those both sides already employ, with a small number of on-site challenge inspections, a combination of technical solutions and procedures such as these could be effective. They would adequately safeguard the national security and sovereignty of the participating nations while providing policymakers with the option of a treaty that limits the number of long-range nuclear cruise missiles or eliminates them completely. As discussed, there are problems that remain to be addressed, but they should not be allowed to block a U.S.-Soviet agreement significantly reducing strategic nuclear arsenals.

  17. Experimental aerodynamic characteristics of missiles with square cross sections

    NASA Astrophysics Data System (ADS)

    Zollars, G. J.; Yechout, R. T.; Daniel, D. C.; Lijewski, L. E.

    1983-05-01

    A series of quantitative and qualitative tests were conducted to expand the aerodynamic data base of square cross-section missiles. Quantitative tests included measuring forces and moments acting on square missiles, and measuring flowfield pressures on the leeward side of square missiles at various configurations and orientations in a subsonic wind tunnel. Force and moment data is presented showing the effects of variation in body corner radius, nose and fin shapes, pitch angle, and roll angle. Flowfield pressure and crossflow velocity data are presented for missiles of various pitch angles, roll angles, body corner radii, and fineness ratios (length to width ratio). In addition, flowfield data is shown along the axial length of a square missile. Qualitative tests included photographic tuft grids in the flowfield and photographing oil shear stress patterns on the surface of various missiles. These qualitative photographs are presented for various missile configurations and orientations.

  18. Rationale for wind-borne missile criteria for DOE facilities

    SciTech Connect

    McDonald, J R; Murray, R

    1999-09-01

    High winds tend to pick up and transport various objects and debris, which are referred to as wind-borne missiles or tornado missiles, depending on the type of storm. Missiles cause damage by perforating the building envelope or by collapsing structural elements such as walls, columns or frames. The primary objectives of this study are as follows: (1) to provide a basis for wind-borne or tornado missile criteria for the design and evaluation of DOE facilities, and (2) to provide guidelines for the design and evaluation of impact-resistant missile barriers for DOE facilities The first objective is accomplished through a synthesis of information from windstorm damage documentation experience and computer simulation of missile trajectories. The second objective is accomplished by reviewing the literature, which describes various missile impact tests, and by conducting a series of impact tests at a Texas Tech University facility to fill in missing information.

  19. The Fiberoptle Guided Missile (FOG-M)

    NASA Astrophysics Data System (ADS)

    Jacobs, Paul L.

    1989-02-01

    The Fiberoptic Guided Missile (FOG-M) was developed in the U.S. Army's Research, Development, and Engineering Center (RDEC) as a demonstration system for killing armor in an infantry application. The RDEC design uses a television sensor in the nose of the missile for in-flight target acquisition, bringing the video signal down a fiberoptic link that pays out behind the missile as it flies, to a gunner securely hidden in a defiladed launch vehicle. The gunner is able to select the target on a video screen and lock on an autotracker or alternately manually track the target to impact. The system design would use a common warhead for either armor or helicopter targets. The system is currently mounted on the High Mobility, Multipurpose Wheeled Vehicle (HMMWV), containing the gunner's station, launcher, and flight missiles. The gunner's station includes the capability for detailed mission planning, digital map display based on the Defense Mapping Agency's digital map databases, and display of the air battle situation for the gunner. Automatic targeting, control of multiple missiles in the air simultaneously, navigation using a digital correlator, and autotracking of moving targets in cluttered backgrounds with gunner selectable offset tracking capability are also available. The system has a capability to train the gunner using a perspective view scene generator that mimics the video scene he would be presented during missile flight. The scene generator uses the same hardware that displays the digital map, while a simulation of the missile runs in one of the system's computer processors to accurately move the seeker presentation around the scene. All of the other hardware used in embedded training is the same as the actual firing hardware. The system concept has been chosen by the Army as the non-line-of-sight (NLOS) component of the Forward Area Air Defense System (FAADS). The initial design is being upgraded for the MIL SPEC environment to allow early operational

  20. Robust Image-Based Visual Servo Control of an Uncertain Missile Airframe

    NASA Astrophysics Data System (ADS)

    Aygun, Murat Tunca

    A nonlinear vision-based guidance law is presented for a missile-target scenario in the presence of model uncertainty and unknown target evasive maneuvers. To ease the readability of this thesis, detailed explanations of any relevant mathematical tools are provided, including stability definitions, the procedure of Lyapunov-based stability analysis, sliding mode control fundamentals, basics on visual servo control, and other basic nonlinear control tools. To develop the vision-based guidance law, projective geometric relationships are utilized to combine the image kinematics with the missile dynamics in an integrated visual dynamic system. The guidance law is designed using an image-based visual servo control method in conjunction with a sliding-mode control strategy, which is shown to achieve asymptotic target interception in the presence of the aforementioned uncertainties. A Lyapunov-based stability analysis is presented to prove the theoretical result, and numerical simulation results are provided to demonstrate the performance of the proposed robust controller for both stationary and non-stationary targets.

  1. Non-Rocket Missile Rope Launcher

    NASA Technical Reports Server (NTRS)

    Bolonkin, Alexander

    2002-01-01

    The method, installation, and estimation for delivering payload and missiles into outer space are presented. This method uses, in general, the engines and straight or closed-loop cables disposed on a planet surface. The installation consists of a space apparatus, power drive stations located along trajectory of the apparatus, the cables connected to the apparatus and to the power stations, a system for suspending the cable, and disconnected device. The drive stations accelerate the apparatus up to hypersonic speed. The estimations and computations show the possibility of making these projects a reality in a short period of time (see attached project: launcher for missiles and loads). The launch will be very cheap $1-$2 per LB. We need only light strong cable, which can be made from artificial fibers, whiskers, nanotubes, which exist in industry and scientific laboratories.

  2. Using NASTRAN to model missile inertia loads

    NASA Technical Reports Server (NTRS)

    Marvin, R.; Porter, C.

    1985-01-01

    An important use of NASTRAN is in the area of structural loads analysis on weapon systems carried aboard aircraft. The program is used to predict bending moments and shears in missile bodies, when subjected to aircraft induced accelerations. The missile, launcher and aircraft wing are idealized, using rod and beam type elements for solution economy. Using the inertia relief capability of NASTRAN, the model is subjected to various acceleration combinations. It is found to be difficult to model the launcher sway braces and hooks which transmit compression only or tension only type forces respectively. A simple, iterative process was developed to overcome this modeling difficulty. A proposed code modification would help model compression or tension only contact type problems.

  3. Ballistic Missile Silo Door Monitoring Analysis

    SciTech Connect

    EDENBURN,MICHAEL W.; TROST,LAWRENCE C.

    2000-01-01

    This paper compares the cost and effectiveness of several potential options that may be used to monitor silo-based ballistic missiles. Silo door monitoring can be used to verify that warheads removed to deactivate or download silo-based ballistic missiles have not been replaced. A precedent for monitoring warhead replacement using reentry vehicle on site inspections (RV-OSIs) and using satellites has been established by START-I and START-II. However, other monitoring options have the potential to be less expensive and more effective. Three options are the most promising if high verification confidence is desired: random monitoring using door sensors; random monitoring using manned or unmanned aircraft; and continuous remote monitoring using unattended door sensors.

  4. Average deployments versus missile and defender parameters

    SciTech Connect

    Canavan, G.H.

    1991-03-01

    This report evaluates the average number of reentry vehicles (RVs) that could be deployed successfully as a function of missile burn time, RV deployment times, and the number of space-based interceptors (SBIs) in defensive constellations. Leakage estimates of boost-phase kinetic-energy defenses as functions of launch parameters and defensive constellation size agree with integral predictions of near-exact calculations for constellation sizing. The calculations discussed here test more detailed aspects of the interaction. They indicate that SBIs can efficiently remove about 50% of the RVs from a heavy missile attack. The next 30% can removed with two-fold less effectiveness. The next 10% could double constellation sizes. 5 refs., 7 figs.

  5. Countermeasures to the US National Missile Defense

    NASA Astrophysics Data System (ADS)

    Gronlund, Lisbeth

    2001-04-01

    One of the key technical questions about national missile defenses is whether they can be expected to work under real-world conditions if the attacker takes steps to defeat the defense. This talk will discuss steps that an emerging missile state could take to confuse, overwhelm, or otherwise defeat the planned US NMD system developed by the Clinton administration. It will consider three such ``countermeasures" that would be within the technical capability of a state that could develop and deploy a long-range missile capable of reaching the United States, which is the threat the NMD system is intended to defend against. The talk will be based on the April 2000 report ``Countermeasures: A Technical Evaluation of the Operational Effectiveness of the Planned US National Missile Defense System," which was co-authored by the speaker and 10 other physicists and engineers. Although the talk will refer to the ground-based NMD system under development, the conclusions are applicable to any mid-course NMD system using hit-to-kill infrared-homing interceptors, regardless of their basing mode. The three countermeasures considered are: (1) biological weapons deployed on 100 or more small bomblets, or submunitions, that would be released shortly after the boost phase; (2) nuclear warheads with anti-simulation balloon decoys, in which the attacker disguises the warhead by enclosing it in an aluminum-coated mylar balloon and releasing it along with a large number of otherwise similar but empty balloons; and (3) nuclear warheads with cooled shrouds, in which the attacker foils the kill vehicle's homing process by covering each nuclear warhead with a double-walled cone containing liquid nitrogen.

  6. The North Korean missile program: How advanced is it?

    SciTech Connect

    Wright, D.; Kadyshev, T.

    1994-04-01

    For the past three years there have been increasing numbers of reports that North Korea is developing a 1,000-1,300-kilometer range missile generally referred to as the NoDongg-1. Pyongyang`s missile program has generated international concern because of North Korea`s potential nuclear capabilities, its proximity to South Korea and Japan and its reported missile sales to Iran, Syria and Libya. In June 1993, Japanese and South Korean wire services reported that North Korea had test fired several missiles into the Sea of Japan in late May, at least two of which were though to be NoDong-1 missiles. A missile with a 1,300-kilometer range would give North Korea the capability to reach all of Japan, and give Iran and Libya the capability to reach all of Israel.

  7. Space-based ballistic-missile defense

    SciTech Connect

    Bethe, H.A.; Garwin, R.L.; Gottfried, K.; Kendall, H.W.

    1984-10-01

    This article, based on a forthcoming book by the Union for Concerned Scientists, focuses on the technical aspects of the issue of space-based ballistic-missile defense. After analysis, the authors conclude that the questionable performance of the proposed defense, the ease with which it could be overwhelmed or circumvented, and its potential as an antisatellite system would cause grievous damage to the security of the US if the Strategic Defense Initiative were to be pursued. The path toward greater security lies in quite another direction, they feel. Although research on ballistic-missile defense should continue at the traditional level of expenditure and within the constraints of the ABM Treaty, every effort should be made to negotiate a bilateral ban on the testing and use of space weapons. The authors think it is essential that such an agreement cover all altitudes, because a ban on high-altitude antisatellite weapons alone would not viable if directed energy weapons were developed for ballistic-missile defense. Further, the Star Wars program, unlikely ever to protect the entire nation against a nuclear attack, would nonetheless trigger a major expansion of the arms race.

  8. An Aerodynamic Analysis of a Spinning Missile with Dithering Canards

    NASA Technical Reports Server (NTRS)

    Meakin, Robert L.; Nygaard, Tor A.

    2003-01-01

    A generic spinning missile with dithering canards is used to demonstrate the utility of an overset structured grid approach for simulating the aerodynamics of rolling airframe missile systems. The approach is used to generate a modest aerodynamic database for the generic missile. The database is populated with solutions to the Euler and Navier-Stokes equations. It is used to evaluate grid resolution requirements for accurate prediction of instantaneous missile loads and the relative aerodynamic significance of angle-of-attack, canard pitching sequence, viscous effects, and roll-rate effects. A novel analytical method for inter- and extrapolation of database results is also given.

  9. 3. MAGAZINE P STAIRWAY ENCLOSURE, LOOKING NORTHEAST. NIKE Missile ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    3. MAGAZINE P STAIRWAY ENCLOSURE, LOOKING NORTHEAST. - NIKE Missile Base C-84, Underground Storage Magazines & Launcher-Loader Assemblies, Easternmost portion of launch area, Barrington, Cook County, IL

  10. Profile of missile-induced cardiovascular injuries in Kashmir, India

    PubMed Central

    Wani, Mohd Lateef; Ahangar, Abdul Gani; Lone, Gh Nabi; Hakeem, Zubair Ashraf; Dar, Abdul Majeed; Lone, Reyaz Ahmad; Bhat, Mohd Akbar; Singh, Shyam; Irshad, Ifat

    2011-01-01

    Background: Missile cardiovascular injuries have taken an epidemic proportion in Kashmir valley since the eruption of militancy in 1990. Present study was undertaken to analyse the pattern, presentation and management of missile cardiovascular injuries. Patients and Methods: Three hundred and eighty-six patients with missile cardiovascular injuries since Jan 1996 to Oct 2008 were studied retrospectively. All patients of cardiovascular injuries due to causes other than missiles were excluded from the study. Results: All patients of missile cardiac injuries were treated by primary cardiorrhaphy. Right ventricle was the most commonly affected chamber. Left anterior thoracotomy was most common approach used. Most of the patients of missile vascular group were treated by reverse saphenous vein graft or end-to-end anastomosis. Most common complication was wound infection (20.83%) followed by graft occlusion (1.94%) in missile vascular group. Amputation rate was 4.66%. Amputation rate was higher in patients with delay of >6 hours and associated fractures. Conclusion: Missile cardiac injuries should be operated early without wasting time for investigations. Clinical status at arrival, time interval till management, nature of injury and associated injuries, tell upon the mortality. Missile vascular injury needs prompt resuscitation and revascularization at the earliest. Time interval till revascularization and associated fractures has a bearing on mortality and morbidity. PMID:21769201

  11. Utilizing COTS software for the infrared scene generation process used for weapon system simulation

    NASA Astrophysics Data System (ADS)

    Ammon, James D.

    1999-07-01

    Raytheon Missile Systems Company operates all digital and real-time hardware-in-the-loop simulations in support of infrared guided missile development. These simulations exercise the missile guidance algorithms with inputs reflective of an engagement scenario. When air to air weapon system is achieved it receives pointing cues from the launcher and the infrared seeker slaves to acquire the target image within its field of view. The images are processed by the tracker algorithms to locate salient features in the scene. The resulting target track provides a precise target-relative position update for missile guidance.

  12. Cost of space-based laser ballistic missile defense.

    PubMed

    Field, G; Spergel, D

    1986-03-21

    Orbiting platforms carrying infrared lasers have been proposed as weapons forming the first tier of a ballistic missile defense system under the President's Strategic Defense Initiative. As each laser platform can destroy a limited number of missiles, one of several methods of countering such a system is to increase the number of offensive missiles. Hence it is important to know whether the cost-exchange ratio, defined as the ratio of the cost to the defense of destroying a missile to the cost to the offense of deploying an additional missile, is greater or less than 1. Although the technology to be used in a ballistic missile defense system is still extremely uncertain, it is useful to examine methods for calculating the cost-exchange ratio. As an example, the cost of an orbiting infrared laser ballistic missile defense system employed against intercontinental ballistic missiles launched simultaneously from a small area is compared to the cost of additional offensive missiles. If one adopts lower limits to the costs for the defense and upper limits to the costs for the offense, the cost-exchange ratio comes out substantially greater than 1. If these estimates are confirmed, such a ballistic missile defense system would be unable to maintain its effectiveness at less cost than it would take to proliferate the ballistic missiles necessary to overcome it and would therefore not satisfy the President's requirements for an effective strategic defense. Although the method is illustrated by applying it to a space-based infrared laser system, it should be straightforward to apply it to other proposed systems. PMID:17748077

  13. Cost of space-based laser ballistic missile defense.

    PubMed

    Field, G; Spergel, D

    1986-03-21

    Orbiting platforms carrying infrared lasers have been proposed as weapons forming the first tier of a ballistic missile defense system under the President's Strategic Defense Initiative. As each laser platform can destroy a limited number of missiles, one of several methods of countering such a system is to increase the number of offensive missiles. Hence it is important to know whether the cost-exchange ratio, defined as the ratio of the cost to the defense of destroying a missile to the cost to the offense of deploying an additional missile, is greater or less than 1. Although the technology to be used in a ballistic missile defense system is still extremely uncertain, it is useful to examine methods for calculating the cost-exchange ratio. As an example, the cost of an orbiting infrared laser ballistic missile defense system employed against intercontinental ballistic missiles launched simultaneously from a small area is compared to the cost of additional offensive missiles. If one adopts lower limits to the costs for the defense and upper limits to the costs for the offense, the cost-exchange ratio comes out substantially greater than 1. If these estimates are confirmed, such a ballistic missile defense system would be unable to maintain its effectiveness at less cost than it would take to proliferate the ballistic missiles necessary to overcome it and would therefore not satisfy the President's requirements for an effective strategic defense. Although the method is illustrated by applying it to a space-based infrared laser system, it should be straightforward to apply it to other proposed systems.

  14. US and USSR Military Aircraft and Missile Aerodynamics 1970-1980. A selected, annotated bibliography, volume 1

    NASA Technical Reports Server (NTRS)

    Tuttle, M. H.; Maddalon, D. V.

    1981-01-01

    The purpose of this selected bibliography (281 citations) is to list available, unclassified, unlimited publications which provide aerodynamic data on major aircraft and missiles currently used by the military forces of the United States of America and the Union of Soviet Socialist Republics. Technical disciplines surveyed include aerodynamic performance, static and dynamic stability, stall-spin, flutter, buffet, inlets nozzles, flap performance, and flying qualities. Concentration is on specific aircraft including fighters, bombers, helicopters, missiles, and some work on transports, which are or could be used for military purposes. The bibliography is limited to material published from 1970 to 1980. The publications herein illustrate many of the types of aerodynamic data obtained in the course of aircraft development programs and may therefore provide some guidance in identifying problems to be expected in the conduct of such work. As such, this information may be useful in planning future research programs.

  15. 10. Photocopy of drawing of missile shipping container from Procedures ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    10. Photocopy of drawing of missile shipping container from Procedures and Drills for the NIKE Ajax System, Department of the Army Field Manual, FM-44-80 from Institute for Military History, Carlisle Barracks, Carlisle, PA 1956. - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  16. 12. Photocopy of drawing of underground missile storage, elevator and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    12. Photocopy of drawing of underground missile storage, elevator and ground-level launchers from 'Procedures and Drills for the NIKE Ajax System,' Department of the Army Field Manual, FM-44-80 from Institute for Military History, Carlisle Barracks, Carlisle, PA, 1956 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  17. 13. Photocopy of drawing of missile launcher from 'Procedures and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    13. Photocopy of drawing of missile launcher from 'Procedures and Drills for the NIKE Ajax System,' Department of the Army Field Manual, FM-44-80 from Institute for Military History, Carlisle Barracks, Carlisle, PA, 1956 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  18. 11. Photocopy of drawing of underground missile storage and elevator ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    11. Photocopy of drawing of underground missile storage and elevator controls from 'Procedures and Drills for the NIKE Ajax System,' Department of the Army Field Manual, FM-44-80 from Institute for Military History, Carlisle Barracks, Carlisle, PA, 1956 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  19. 7. Photocopy of photograph showing four Ajax missiles in launch ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    7. Photocopy of photograph showing four Ajax missiles in launch position from ARADCOM Argus pg. 14, from Institute for Military History, Carlisle Barracks, Carlisle, PA, October 1, 1963 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  20. 6. Photocopy of photograph showing an Ajax and Hercules Missile ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    6. Photocopy of photograph showing an Ajax and Hercules Missile from ARADCOM Argus pg. 3, from Institute for Military History, Carlisle Barracks, Carlisle, PA, October 1, 1958 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  1. Paths of Target Seeking Missiles in Two Dimensions

    NASA Technical Reports Server (NTRS)

    Watkins, Charles E.

    1946-01-01

    Parameters that enter into equation of trajectory of a missile are discussed. Investigation is made of normal pursuit, of constant, proportional, and line--of-sight methods of navigation employing target seeker, and of deriving corresponding pursuit paths. Pursuit paths obtained under similar conditions for different methods are compared. Proportional navigation is concluded to be best method for using target seeker installed in missile.

  2. 13. Missile site control building, third and fourth floor interior, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    13. Missile site control building, third and fourth floor interior, showing east corner and former electrical equipment area, room #306. This building was salvaged and sealed in the 1970's; the lower floors also suffered flooding - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

  3. 10. East oblique of missile site control building, with better ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    10. East oblique of missile site control building, with better view of exhaust (the taller columns) and intake shafts - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

  4. Aerodynamic Prediction for Supersonic Canard-Tail Missiles

    NASA Technical Reports Server (NTRS)

    Dillenius, M. F.

    1986-01-01

    LRCDM2 computer program developed to calculate pressure distribution at points on surfaces of complete supersonic missile. Missile comprises up to two finned sections attached to axisymmetric body of circular cross section. Includes effects of vortex shedding due to forebody and forward fins, providing more accurate rolling moments. LRCDM2 written in FORTRAN IV.

  5. Officials of the Army Ballistic Missile Agency

    NASA Technical Reports Server (NTRS)

    1956-01-01

    Hermann Oberth (forefront) with officials of the Army Ballistic Missile Agency at Huntsville, Alabama in 1956. Left to right: Dr. Ernst Stuhlinger (seated); Major General H.N. Toftoy, Commanding Officer and person responsible for 'Project Paperclip,' which took scientists and engineers out of Germany after World War II to design rockets for American military use. Many of the scientists later helped to design the Saturn V rocket that took the Apollo 11 astronauts to the Moon. Dr. Eberhard Rees, Deputy Director, Development Operations Division Wernher von Braun, Director, Development Operations Division.

  6. The Clinton plan for theater missile defenses: Costs and alternatives

    SciTech Connect

    Mosher, D.; Hall, R.

    1994-09-01

    Since the Gulf War, the Department of Defense has placed a high priority on developing defenses against theater ballistic missiles (TBMs). Over the past two years the Clinton administration has redirected the focus of the Ballistic Missile Organization (BMDO, formerly the Strategic Defense Initiative Organization) away from a national missile defense system and toward the development of theater missile defenses (TMDs). But the plan put forward by the administration is expensive - as much as $50 billion through the year 2010 - and it also raises several important issues about compliance with the Anti-Ballistic Missile (ABM) Treaty. But other approaches to TMD would address some of these cost and compliance concerns, so it is worthwhile to look at several alternatives and analyze their costs and effects on capability.

  7. Solid rocket history at TRW Ballistic Missiles Division

    SciTech Connect

    Kennedy, W.S.; Kovacic, S.M.; Rea, E.C. )

    1992-07-01

    The development of ballistic missiles and particularly intercontinental ballistic missiles (ICBMs) by the U.S. space technology manufacturer is examined. Collaboration by the company with the U.S. Air Force is described which began in the 1950s and combined systems engineering and technical assistance. Missile products reviewed in this paper include Atlas, Thor, Titans I and II, Minuteman I, II, III, the Peacekeeper, and the small ICBM. The company developed facilities and programs to support the R and D activities for the missile products, and descriptions are given of the Space Technologies Laboratory and the Ballistic Missiles Division. Contributions to ICBM technologies by the concern include carbon-carbon nozzle materials, propellant formulation data, movable nozzles, casting techniques for large volumes of propellants, and studies of fracture mechanics. 41 refs.

  8. The science, technology, and politics of ballistic missile defense

    SciTech Connect

    Coyle, Philip E.

    2014-05-09

    America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about $10 billion per year, and proposes to add about $5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

  9. The science, technology, and politics of ballistic missile defense

    NASA Astrophysics Data System (ADS)

    Coyle, Philip E.

    2014-05-01

    America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about 10 billion per year, and proposes to add about 5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

  10. Modelling cavitating flow around underwater missiles

    NASA Astrophysics Data System (ADS)

    Petitpas, Fabien; Saurel, Richard; Ahn, Byoung-Kwon; Ko, Sungho

    2011-12-01

    The diffuse interface model of Saurel et al. (2008) is used for the computation of compressible cavitating flows around underwater missiles. Such systems use gas injection and natural cavitation to reduce drag effects. Consequently material interfaces appear separating liquid and gas. These interfaces may have a really complex dynamics such that only a few formulations are able to predict their evolution. Contrarily to front tracking or interface reconstruction method the interfaces are computed as diffused numerical zones, that are captured in a routinely manner, as is done usually with gas dynamics solvers for shocks and contact discontinuity. With the present approach, a single set of partial differential equations is solved everywhere, with a single numerical scheme. This leads to very efficient solvers. The algorithm derived in Saurel et al. (2009) is used to compute cavitation pockets around solid bodies. It is first validated against experiments done in cavitation tunnel at CNU. Then it is used to compute flows around high speed underwater systems (Shkval-like missile). Performance data are then computed showing method ability to predict forces acting on the system.

  11. Optics At White Sands Missile Range

    NASA Astrophysics Data System (ADS)

    Fronczek, Ron C.; Hayslett, Charles R.

    1985-11-01

    We present an overview of the optics and optical data gathering programs conducted at White Sands Missile Range. Activities at White Sands Missile Range have always been diverse - the first test conducted there was the world's first nuclear explosion. In the forty years since that event the range has hosted a large assortment of vehicles including V2, Nike, Aerobee, Space Shuttle, Cruise, and the Copperhead. The last three of these devices illustrate the difficulty of the White Sands optical data gathering task. One is acquired in orbit, one as it crosses through a mountain pass, and one as it issues from the muzzle of a cannon. A combination of optical, radar, video, computer, and communications technology has produced a versatile system that can satisfy the data gathering requirements of most range users. Another example of the diverse optics programs at the range is the development of the High Energy Laser Systems Test Facility (HELSTF). Because of the nature of the systems being tested, the HELSTF is full of optics and optical systems including the TRW MIRACL laser and the Hughes SEA LITE Beam Director.

  12. Innovation in Aerodynamic Design Features of Soviet Missiles

    NASA Technical Reports Server (NTRS)

    Spearman, M. Leroy

    2006-01-01

    Wind tunnel investigations of some tactical and strategic missile systems developed by the former Soviet Union have been included in the basic missile research programs of the NACA/NASA. Studies of the Soviet missiles sometimes revealed innovative design features that resulted in unusual or unexpected aerodynamic characteristics. In some cases these characteristics have been such that the measured performance of the missile exceeds what might have been predicted. In other cases some unusual design features have been found that would alleviate what might otherwise have been a serious aerodynamic problem. In some designs, what has appeared to be a lack of refinement has proven to be a matter of expediency. It is a purpose of this paper to describe some examples of unusual design features of some Soviet missiles and to illustrate the effectiveness of the design features on the aerodynamic behavior of the missile. The paper draws on the experience of the author who for over 60 years was involved in the aerodynamic wind tunnel testing of aircraft and missiles with the NACA/NASA.

  13. Missiles caused by severe pressurized-water reactor accidients

    SciTech Connect

    Krieg, R.

    1995-07-01

    For future pressurized-water reactors, which should be designed against core-meltdown accidents, missiles generated inside the containment present a severe problem for its integrity. The masses and geometries of the missiles, as well as their velocities, may vary to a great extent. Therefore a reliable proof of the containment integrity is very difficult. In this article the potential sources of missiles are discussed, and the conclusion was reached that the generation of heavy missiles must be prevented. Steam explosions must not damage the reactor vessel head. Thus fragments of the head cannot become missiles that endanger the containment shell. Furthermore, during a melt-through failure of the reactor vessel under high pressure, the resulting forces must not catapult the whole vessel against the containment shell. Only missiles caused by hydrogen explosions may be tolerable, but shielding structures that protect the containment shell may be required. Further investigations are necessary. Finally, measures are described showing that the generation of heavy missiles can indeed be prevented. Investigations are currently being carried out that will confirm the strength of the reactor vessel head. In addition, a device for retaining the fragments of a failing reactor vessel is discussed.

  14. High performance dash on warning air mobile, missile system. [intercontinental ballistic missiles - systems analysis

    NASA Technical Reports Server (NTRS)

    Levin, A. D.; Castellano, C. R.; Hague, D. S.

    1975-01-01

    An aircraft-missile system which performs a high acceleration takeoff followed by a supersonic dash to a 'safe' distance from the launch site is presented. Topics considered are: (1) technological feasibility to the dash on warning concept; (2) aircraft and boost trajectory requirements; and (3) partial cost estimates for a fleet of aircraft which provide 200 missiles on airborne alert. Various aircraft boost propulsion systems were studied such as an unstaged cryogenic rocket, an unstaged storable liquid, and a solid rocket staged system. Various wing planforms were also studied. Vehicle gross weights are given. The results indicate that the dash on warning concept will meet expected performance criteria, and can be implemented using existing technology, such as all-aluminum aircraft and existing high-bypass-ratio turbofan engines.

  15. Depleted uranium investigation at missile impact sites in White Sands Missile Range

    SciTech Connect

    Van Etten, D.M.; Purtymun, W.D.

    1994-01-01

    An investigation for residual depleted uranium was conducted at Pershing missile impact sites on the White Sands Missile Range. Subsurface core soil samples were taken at Chess, Salt Target, and Mine Impact Sites. A sampling pump was installed in a monitoring well at Site 65 where a Pershing earth penetrator was not recovered. Pumping tests and water samples were taken at this site. Chess Site, located in a gypsum flat, was the only location showing elevated levels of depleted uranium in the subsurface soil or perched groundwater. Small fragments can still be found on the surface of the impact sites. The seasonal flooding and near surface water has aided in the movement of surface fragments.

  16. Experimental study of ELF signatures developed by ballistic missile launch

    SciTech Connect

    Peglow, S.G.; Rynne, T.M.

    1993-04-08

    The Lawrence Livermore National Laboratory (Livermore, CA) and SARA, Inc. participated in the ATMD missile launch activities that occurred at WSMR during January 1993. These tests involved the launch of Lance missiles with a subsequent direction of F-15Es into the launch area for subsequent detection and simulated destruction of redeployed missile launchers, LLNL and SARA deployed SARN`s ELF sensors and various data acquisition systems for monitoring of basic phenomena. On 25 January 1993, a single missile launch allowed initial measurements of the phenomena and an assessment of appropriate sensor sensitivity settings as well as the appropriateness of the sensor deployment sites (e.g., with respect to man-made ELF sources such as power distributions and communication lines). On 27 January 1993, a measurement of a double launch of Lance missiles was performed. This technical report covers the results of the analysis of latter measurements. An attempt was made to measure low frequency electromagnetic signatures that may be produced during a missile launch. Hypothetical signature production mechanisms include: (1) Perturbations of the earth geo-potential during the launch of the missile. This signature may arise from the interaction of the ambient electric field with the conducting body of the missile as well as the partially ionized exhaust plume. (2) Production of spatial, charge sources from triboelectric-like mechanisms. Such effects may occur during the initial interaction of the missile plume with the ground material and lead to an initial {open_quotes}spike{close_quotes} output, Additionally, there may exist charge transfer mechanisms produced during the exhausting of the burnt fuel oxidizer.

  17. Missile Aerodynamics for Ascent and Re-entry

    NASA Technical Reports Server (NTRS)

    Watts, Gaines L.; McCarter, James W.

    2012-01-01

    Aerodynamic force and moment equations are developed for 6-DOF missile simulations of both the ascent phase of flight and a tumbling re-entry. The missile coordinate frame (M frame) and a frame parallel to the M frame were used for formulating the aerodynamic equations. The missile configuration chosen as an example is a cylinder with fixed fins and a nose cone. The equations include both the static aerodynamic coefficients and the aerodynamic damping derivatives. The inclusion of aerodynamic damping is essential for simulating a tumbling re-entry. Appended information provides insight into aerodynamic damping.

  18. 1. Northeast face of missile site control building, commonly known ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    1. Northeast face of missile site control building, commonly known as the missile site radar building, showing open blast door #BD2. This emergency escape, at stair no. 12, is NEMP/RFI-shielded and 16" thick. The large circle in the center is the radar face, also known as the antennae array aperture. The small circle to the right of the radar face is the "Q" channel. The antennae atop the turret provided lightning protection for the building - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

  19. The present status and the future of missile aerodynamics

    NASA Technical Reports Server (NTRS)

    Nielsen, Jack N.

    1988-01-01

    Some recent developments in the state of the art in missile aerodynamics are reviewed. Among the subjects covered are: (1) tri-service/NASA data base, (2) wing-body interference, (3) nonlinear controls, (4) hypersonic transition, (5) vortex interference, (6) airbreathers, supersonic inlets, (7) store separation problems, (8) correlation of missile data, (9) CFD codes for complete configurations, (10) engineering prediction methods, and (11) future configurations. Suggestions are made for future research and development to advance the state of the art of missile aerodynamics.

  20. Multisensor target and missile tracking for a point defense missile system

    NASA Astrophysics Data System (ADS)

    Hall, Stephen L.

    2003-08-01

    The strengths and weaknesses of centimetre, (I Band), millimetric (Ka band) and EO systems (daylight TV, Thermal Imager Sensors) are discussed, as applied to both the problems of acquiring and tracking naval threats, in order to achieve optimum engagements with Command to Line of Sight (CLOS) weapons. The limitations of the centimetre, millimetre and EO bands with varying target heights, seastates and visibility conditions are identified, including multipath geometry, filtering to counter multipath and utilisation of EO sensors in the Naval environment worldwide. Mechanisms of combining both Radar and EO Sensors to produce an accurate differential tracking output (target to missile), in order to control a CLOS missile are described, together with filter configurations allowing a true differential output to be produced, de-coupled from sensor sightline motion. This includes the application of sensor merging, Kalman filtering and Command Off the Line of Sight (COLOS) techniques. Finally there is a description of both an in-service and projected fire control system controlling a Point Defence Missile System (PDMS), including the results from a practical demonstration of multi-sensor tracking of an air target in a sea going environment.

  1. Non-singular terminal dynamic surface control based integrated guidance and control design and simulation.

    PubMed

    Cong, Zhang; Yun-Jie, Wu

    2016-07-01

    In this paper, a novel cascade type design model is transformed from the simulation model, which has a broader scope of application, for integrated guidance and control (IGC). A novel non-singular terminal dynamic surface control based IGC method is proposed. It can guarantee the missile with multiple disturbances fast hits the target with high accuracy, while considering the terminal impact angular constraint commendably. And the stability of the closed-loop system is strictly proved. The essence of integrated guidance and control design philosophy is reached that establishing a direct relation between guidance and attitude equations by "intermediate states" and then designing an IGC law for the obtained integrated cascade design model. Finally, a series of simulations and comparisons with a 6-DOF nonlinear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.

  2. Non-singular terminal dynamic surface control based integrated guidance and control design and simulation.

    PubMed

    Cong, Zhang; Yun-Jie, Wu

    2016-07-01

    In this paper, a novel cascade type design model is transformed from the simulation model, which has a broader scope of application, for integrated guidance and control (IGC). A novel non-singular terminal dynamic surface control based IGC method is proposed. It can guarantee the missile with multiple disturbances fast hits the target with high accuracy, while considering the terminal impact angular constraint commendably. And the stability of the closed-loop system is strictly proved. The essence of integrated guidance and control design philosophy is reached that establishing a direct relation between guidance and attitude equations by "intermediate states" and then designing an IGC law for the obtained integrated cascade design model. Finally, a series of simulations and comparisons with a 6-DOF nonlinear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method. PMID:27049772

  3. Sidewall reflections in streamlined missile radomes

    NASA Astrophysics Data System (ADS)

    Huddleston, G. K.; Crockett, M. P.

    Predicted and measured patterns are presented which serve as dramatic illustrations of the 'LLoyd's mirror' effect, in which direct and reflected waves generate interference in the form of unexpected peaks and nulls in radome-enclosed receiving antenna patterns. These effects are associated with a low-gain antenna which is offset from the centerline of a streamlined tangent ogive radome intended for high-speed missile applications. Since many other airborne radome applications require that more than one antenna be located inside a radome cavity, these data furnish insight into what may be expected for offset-antenna locations. The geometrical optics approximations used to obtain reflected wave contributions are noted to be exceptionally accurate foir the small antennas considered.

  4. GPU-enabled projectile guidance for impact area constraints

    NASA Astrophysics Data System (ADS)

    Rogers, Jonathan

    2013-05-01

    Guided projectile engagement scenarios often involve impact area constraints, in which it may be less desirable to incur miss distance on one side of a target or within a specified boundary near the target area. Current projectile guidance schemes such as impact point predictors cannot handle these constraints within the guidance loop, and may produce dispersion patterns that are insensitive to these constraints. In this paper, a new projectile guidance law is proposed that leverages real-time Monte Carlo impact point prediction to continually evaluate the probability of violating impact area constraints. The desired aim point is then adjusted accordingly. Real-time Monte Carlo simulation is enabled within the feedback loop through use of graphics processing units (GPU's), which provide parallel pipelines through which a dispersion pattern can routinely be predicted. The result is a guidance law that can achieve minimum miss distance while avoiding impact area constraints. The new guidance law is described and formulated as a nonlinear optimization problem which is solved in real-time through massively-parallel Monte Carlo simulation. An example simulation is shown in which impact area constraints are enforced and the methodology of stochastic guidance is demonstrated. Finally, Monte Carlo simulations are shown which demonstrate the ability of the stochastic guidance scheme to avoid an arbitrary set of impact area constraints, generating an impact probability density function that optimally trades miss distance within the restricted impact area. The proposed guidance scheme has applications beyond smart weapons to include missiles, UAV's, and other autonomous systems.

  5. Engineering Features Clear Air Force Station, Ballistic Missile Early ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    Engineering Features - Clear Air Force Station, Ballistic Missile Early Warning System Site II, One mile west of mile marker 293.5 on Parks Highway, 5 miles southwest of Anderson, Anderson, Denali Borough, AK

  6. 8. PHOTOCOPY, HEATING DRAWING FOR ADMINISTRATION BUILDING. NIKE Missile ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    8. PHOTOCOPY, HEATING DRAWING FOR ADMINISTRATION BUILDING. - NIKE Missile Base SL-40, Administration Building, East central portion of base, southeast of Mess Hall, northeast of HIPAR Equipment Building, Hecker, Monroe County, IL

  7. 100. MISSILE ORDNANCE TEST FIXTURE (FLEMING UNIT) ON NORTHEAST WALL ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    100. MISSILE ORDNANCE TEST FIXTURE (FLEMING UNIT) ON NORTHEAST WALL OF LANDLINE INSTRUMENTATION ROOM (106), LSB (BLDG. 770) - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  8. The development of Soviet rocket engines (For strategic missiles)

    SciTech Connect

    Bolonkin, A.

    1991-01-01

    A first-hand account of developments in the Soviet rocket industry is presented. The organization and leadership of the rocket and missile industry are traced from its beginning in the 1920s. The development of the Glushko Experimental Design Bureau, where the majority of Soviet rocket engines were created, is related. The evolution of Soviet rocket engines is traced in regard to both their technical improvement and their application in missiles and space vehicles. Improved Glushko engines and specialized Isaev and Kosberg engines are discussed. The difficulties faced by the Soviet missile and space program, such as the pre-Sputnik failures, the oscillation problem of 1965/1966, which exposed a weakness in Soviet ICBM missiles, and the Nedelin disaster of 1960, which cost the lives of more than 200 scientists and engineers, as well as the Commander-in-Chief of the Strategic Rocket Forces, Marshall Nedelin, are examined. 122 refs.

  9. Missile Warning Operations Center (MWOC) Beale Air Force Base, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    Missile Warning Operations Center (MWOC) - Beale Air Force Base, Perimeter Acquisition Vehicle Entry Phased-Array Warning System, Techinical Equipment Building, End of Spencer Paul Road, north of Warren Shingle Road (14th Street), Marysville, Yuba County, CA

  10. ATLAS F MISSILE FIELDS IN THE UNITED STATES, ATLAS F ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    ATLAS F MISSILE FIELDS IN THE UNITED STATES, ATLAS F- TEXAS RING OF TWELVE - Dyess Air Force Base, Atlas F Missle Site S-8, Approximately 3 miles east of Winters, 500 feet southwest of Highway 177, Winters, Runnels County, TX

  11. The secret of guided missile re-entry

    NASA Astrophysics Data System (ADS)

    Chen, Jingzhong; An, Sehua

    1986-06-01

    The history and development of reentry vehicles especially as related to guided missiles is studied. The development of fiber reinforced composites to avoid the combustion of reentry vehicle heads is described. The ionization of molecules caused by high temperature friction with the air during high speed reeentry is briefly described. Reentry remote sensing as an important basis for developing configuration and predicting accuracy of point of impact of the guided missile is also discussed.

  12. 101. View of transmitter building no. 102, missile warning operation ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    101. View of transmitter building no. 102, missile warning operation center, close up view of DRED (detection radar environmental display) console in operation showing target. Official photograph BMEWS Project by Hansen, 14 March 1963, clear as negative no. A-8803. - Clear Air Force Station, Ballistic Missile Early Warning System Site II, One mile west of mile marker 293.5 on Parks Highway, 5 miles southwest of Anderson, Anderson, Denali Borough, AK

  13. Aerodynamics of powered missile separation from F/A-18 aircraft

    NASA Technical Reports Server (NTRS)

    Ahmad, J. U.; Shanks, S. P.; Buning, P. G.

    1993-01-01

    A 3D dynamic 'chimera' algorithm that solves the thin-layer Navier-Stokes equations over multiple moving bodies was modified to numerically simulate the aerodynamics, missile dynamics, and missile plume interactions of a missile separating from a generic wing and from an F/A-18 aircraft in transonic flow. The missile is mounted below the wing for missile separation from the wing and on the F/A-18 fuselage at the engine inlet side for missile separation from aircraft. Static and powered missile separation cases are considered to examine the influence of the missile and plume on the wing and F/A-18 fuselage and engine inlet. The aircraft and missile are at two degrees angle of attack, Reynolds number of 10 million, freestream Mach number of 1.05 and plume Mach number of 3.0. The computational results show the details of the flow field.

  14. Missile injuries of the anterior skull base.

    PubMed

    Bhatoe, Harjinder Singh

    2004-02-01

    Missile injuries of the anterior skull base usually occur during war or war-like situations. These injuries may be isolated or associated with multiple traumatic injuries. We report 23 such cases managed during military conflicts and peacekeeping operations. All were adult males. Four of these patients sustained bullet injuries; the rest were injured from shrapnel. Eighteen patients had injury to the visual apparatus with permanent blindness. Proptosis was seen in 16, cerebrospinal fluid (CSF) leak from the wound in seven, and CSF orbitorrhea in three patients. Sixteen had irreparable injury to the eye necessitating evisceration/enucleation, and two had retrobulbar optic nerve injury. Three patients were comatose [Glasgow Coma Scale (GCS) 3/15], and 14 had altered sensorium. Six patients were fully conscious. All were investigated by computed tomography (CT), which revealed injury to the eyeball and skull base, orbital fracture, frontal hematoma, contusion, and pneumocephalus. Seventeen patients underwent emergency surgery, and six patients were initially managed conservatively. Neurosurgical management consisted of making bifrontal flaps, craniotomy/craniectomy, debridement, and repair of the base with fascia lata. Reconstruction of the orbital rim was required in three cases. All were managed postoperatively with cerebral decongestants and antibiotics in anti-meningitic dosages. There was one death in the postoperative period; outcome was good in 16 and moderate in four patients. Twelve patients had retained intracranial splinters; three of these developed recurrent suppurative meningitis. Of the six patients initially managed conservatively, three were subsequently operated for CSF rhinorrhea. Gross communition, dural loss, and injury to the frontal scalp often preclude the use of pericranial repair of the skull base. Fascia lata is extremely useful for reconstruction and repair. Anterior cranial fossa injury probably carries a better prognosis; however, there

  15. Analytical impact time and angle guidance via time-varying sliding mode technique.

    PubMed

    Zhao, Yao; Sheng, Yongzhi; Liu, Xiangdong

    2016-05-01

    To concretely provide a feasible solution for homing missiles with the precise impact time and angle, this paper develops a novel guidance law, based on the nonlinear engagement dynamics. The guidance law is firstly designed with the prior assumption of a stationary target, followed by the practical extension to a moving target scenario. The time-varying sliding mode (TVSM) technique is applied to fulfill the terminal constraints, in which a specific TVSM surface is constructed with two unknown coefficients. One is tuned to meet the impact time requirement and the other one is targeted with a global sliding mode, so that the impact angle constraint as well as the zero miss distance can be satisfied. Because the proposed law possesses three guidance gain as design parameters, the intercept trajectory can be shaped according to the operational conditions and missile׳s capability. To improve the tolerance of initial heading errors and broaden the application, a new frame of reference is also introduced. Furthermore, the analytical solutions of the flight trajectory, heading angle and acceleration command can be totally expressed for the prediction and offline parameter selection by solving a first-order linear differential equation. Numerical simulation results for various scenarios validate the effectiveness of the proposed guidance law and demonstrate the accuracy of the analytic solutions.

  16. Analytical impact time and angle guidance via time-varying sliding mode technique.

    PubMed

    Zhao, Yao; Sheng, Yongzhi; Liu, Xiangdong

    2016-05-01

    To concretely provide a feasible solution for homing missiles with the precise impact time and angle, this paper develops a novel guidance law, based on the nonlinear engagement dynamics. The guidance law is firstly designed with the prior assumption of a stationary target, followed by the practical extension to a moving target scenario. The time-varying sliding mode (TVSM) technique is applied to fulfill the terminal constraints, in which a specific TVSM surface is constructed with two unknown coefficients. One is tuned to meet the impact time requirement and the other one is targeted with a global sliding mode, so that the impact angle constraint as well as the zero miss distance can be satisfied. Because the proposed law possesses three guidance gain as design parameters, the intercept trajectory can be shaped according to the operational conditions and missile׳s capability. To improve the tolerance of initial heading errors and broaden the application, a new frame of reference is also introduced. Furthermore, the analytical solutions of the flight trajectory, heading angle and acceleration command can be totally expressed for the prediction and offline parameter selection by solving a first-order linear differential equation. Numerical simulation results for various scenarios validate the effectiveness of the proposed guidance law and demonstrate the accuracy of the analytic solutions. PMID:26952314

  17. Cryocoolers for infrared missile warning systems

    NASA Astrophysics Data System (ADS)

    Filis, Avishai; Pundak, Nachman; Zur, Yoav; Broyde, Ramon; Barak, Moshe

    2010-04-01

    The growth in world demand for infrared missile warning systems (MWS) has impelled the development of new technologies, in particular, special cryogenic coolers. Since the cryocooler is a core component in MWS RICOR has met the challenge by developing new models able to withstand high ambient temperatures above 110°C as well as harsh vibration levels, both derived from airborne fighter applications. The development focused on a cryocooler regenerator and cold finger optimization in order to achieve high cooling capacity and a thermodynamic efficiency of about 4.4% at 95°C ambient for one of the cooler models. In order to withstand harsh environmental vibration, the cold finger and outer Dewar structure have been significantly ruggedized; efficient heat sinking methods have been applied and also novel vibration isolation methods have been implemented. The electronic design concept is based on an analog controller, the PCB of which has been designed with internal heat sinking paths and special components being able to withstand ambients temperatures up to 125°C. As a final stage of development, such cryocoolers were successfully qualified by RICOR and system manufacture in harsh environmental conditions and life demonstration tests were performed.

  18. A peek at the French missile complex

    SciTech Connect

    Kennedy, W.A.; Marshall, M.G.

    1989-09-01

    Using a spot satellite image, Grayscale, an image analysis firm, analyzed the features of a complex on the Plateau d'Albion, where French intermediate-range ballistic missiles are thought to be deployed. The project was undertaken at the request of the Carnegie Endowment, as part of the Endowment's study of the security implications of commercial remote-sensing satellites. The area studied is in southern France, near the intersection of the Vaucluse, Alpes-de-Haute-Provence, and Drome provinces. Features seen in relief on an image shown here are the foot-hills just west of the Alpes Maritimes. The French acknowledge publicly that they have deployed 18 IRBMs - all S-3s. Recognizing the military habits of regimentation and organization, we believed that these weapons might be organized into two groups of nine, which could be further divided into subgroups of three. Such subgroups could be firing battalions of a brigade, or two brigades with a division-level headquarters controlling both. On this basis, the authors selected candidate sites throughout the image for closer examination, and results are discussed.

  19. Decision support system for theater missile defense

    NASA Astrophysics Data System (ADS)

    Gonsalves, Paul; Burge, Janet; Popp, Ben

    2003-08-01

    Military services require C4I systems that support a full spectrum of operations. This is specifically relevant to the theatre missile defense (TMD) mission planning and analysis community where there have been several recent concept changes; advancements in information technology, sensors, and weapons; and expansion in the diversity and capabilities of potential adversaries. To fully support campaign development and analysis in this new environment, there is a need for systems and tools that enhance understanding of adversarial behavior, assess potential threat capabilities and vulnerabilities, perform C4I system trades, and provide methods to identify macro-level novel or emergent combat tactics and behavior derived from simpler micro-level rules. Such systems must also be interactive, collaborative, and semi-autonomous, providing the INTEL analyst with the means for exploration and potential exploitation of novel enemy behavior patterns. To address these issues we have developed an Intelligent Threat Assessment Processor (ITAP) to provide prediction and interpretation of enemy courses of actions (eCOAs) for the TMD domain. This system uses a combination of genetic algorithm-based optimization in tandem with the spatial analysis and visualization capabilities of a commercial-off-the-shelf (COTS) geographic information system to generate and evaluate potential eCOAs.

  20. Cooled and uncooled infrared detectors for missile seekers

    NASA Astrophysics Data System (ADS)

    Fraenkel, Rami; Haski, Jacob; Mizrahi, Udi; Shkedy, Lior; Shtrichman, Itay; Pinsky, Ephi

    2014-06-01

    Electro-optical missile seekers pose exceptional requirements for infrared (IR) detectors. These requirements include: very short mission readiness (time-to-image), one-time and relatively short mission duration, extreme ambient conditions, high sensitivity, fast frame rate, and in some cases small size and cost. SCD is engaged in the development and production of IR detectors for missile seeker applications for many years. 0D, 1D and 2D InSb focal plane arrays (FPAs) are packaged in specially designed fast cool-down Dewars and integrated with Joule-Thomson (JT) coolers. These cooled MWIR detectors were integrated in numerous seekers of various missile types, for short and long range applications, and are combat proven. New technologies for the MWIR, such as epi-InSb and XBn-InAsSb, enable faster cool-down time and higher sensitivity for the next generation seekers. The uncooled micro-bolometer technology for IR detectors has advanced significantly over the last decade, and high resolution - high sensitivity FPAs are now available for different applications. Their much smaller size and cost with regard to the cooled detectors makes these uncooled LWIR detectors natural candidates for short and mid-range missile seekers. In this work we will present SCD's cooled and uncooled solutions for advanced electro-optical missile seekers.

  1. [Ballistic approach in head injuries caused by missiles].

    PubMed

    Jourdan, P; Billant, J B; Desgeorges, M

    1989-01-01

    If the missile head injury treatment is relatively well codified, wound ballistic, on the other hand, is not well known of neurosurgeons. Different means of study and tissue simulants are being listed. In face of numerous contradictory results, we shall only retain the M.L. Fackler method with 10% gelatin. Experimental results will depend on: 1. Missile parameters. For instance, in soft homogeneous tissue, one can discern shells with an uncertain path, full jacketed bullets which tumble after a variable "neck", and non jacketed missiles which cause wound through "mushrooming" and/or fragmentation effect. Buckshot wounds obey the rule "all or none". 2. Body reactions, particularly the clash with a hard material like bone, which can overturn everything described in soft tissues. These wound ballistic notions have lead us to formulate two pathogenic hypothesizes, allowing us to understand sometime case reports which had first seemed paradoxical: the brain structure, enclosed in the skull will not able to survive any major temporary cavity, the more or less deep missile pathway through the skull will be very different according to the type and energy of the missile, and to the hardness of pierced bone. PMID:2699004

  2. Ultraviolet scene simulation for missile approach warning system testing

    NASA Astrophysics Data System (ADS)

    Giza, Robert H.; Acevedo, Paul A.; Bliss, John D.

    1997-07-01

    Ultraviolet (UV) extensions have been incorporated in the Real-time IR/EO Scene Simulator to support hardware-in-the- loop (HWIL) testing of UV missile warning systems. The UV extensions add capability to model missile plume signatures and off-axis atmospheric scattering in the solar blind UV spectral region (200 - 400 nm). Preliminary testing and validation of the UV rendering algorithms were performed. Simulated UV missile signatures were compared to measured static and free-flight test data. This work was performed to support the test and evaluation of modern missile warning systems at Wright labs Integrated Defensive Avionics Lab. This paper will discuss development of HWIL testing capability for UV missile warning receiver systems. Requirements for real-time UV simulation will be defined and a real-time architecture that addresses these requirements will be discussed. Specifically, the development of real- time UV rendering algorithms to support modeling of atmospherics and backgrounds to the UV solar blind wavelength region will be outlined. Issues regarding implementation of spatial UV scattering effects in a real- time rendering environment will be addressed. Development of the UV sensor model, and its potential implementation in a real-time hardware/software direct injection device will be illustrated. The results of some preliminary validation using laboratory and live firing test data will also be discussed.

  3. Missile launch detection electric field perturbation experiment. Final report

    SciTech Connect

    Kane, R.J.; Rynne, T.M.

    1993-04-28

    The Lawrence Livermore National Laboratory and SARA Inc. participated in the ATMD missile launch activities that occurred at WSMR during January 1993. LLNL and SARA deployed sensors for monitoring of basic phenomena. An attempt was made to measure perturbations of the earth geo-potential during the launch of a Lance missile. The occurrence of the perturbation is expected from the conducting body of the missile and the exhaust plume. A set of voltage-probe antennas were used to monitor the local electric field perturbation from the launch at ranges of approximately 1 km. Examination of the data acquired during the launch period failed to show identifiable correlation of the field variations with the launch event. Three reasons are ascribed to this lack of event data: (1) The electric field potential variations have a limited spatial correlation length - the fields measured in one region have little correlation to measurements made at distances of a kilometer away. The potential variations are related to localized atmospheric disturbances and are generally unpredictable. A value for the spatial correlation length is also not known. (2) The conductivity of the plume and missile body are not adequate to produce a field perturbation of adequate magnitude. Phenomena related to the exhaust plume and missile may exist and be outside of the collection range of the equipment employed for these measurements. (3) The presence of 60 Hz power line noise was of sufficient magnitude to irreversibly contaminate measurements.

  4. 47. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    47. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, detail of elevator VIEW EAST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  5. 44. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    44. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, general interior view VIEW SOUTHWEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  6. 48. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    48. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, interior detail of water and hydraulic pumps VIEW WEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  7. 10. Site D57 & 58L, Underground Missile Storage Structure, Type ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    10. Site D-57 & 58-L, Underground Missile Storage Structure, Type B, Plans, U.S. Army Corps of Engineers, 13 December 1953 - Newport NIKE Missile Battery D-57/58, Launch Area, Newport Road, Carleton, Monroe County, MI

  8. 49. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    49. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, interior detail of air vent system VIEW WEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  9. Tactical missile aerodynamics - Prediction methodology. Progress in Astronautics and Aeronautics. Vol. 142

    SciTech Connect

    Mendenhall, M.R. )

    1992-01-01

    The present volume discusses tactical missile aerodynamic drag, drag-prediction methods for axisymmetric missile bodies, an aerodynamic heating analysis for supersonic missiles, a component buildup method for engineering analysis of missiles at low-to-high angles of attack, experimental and analytical methods for missiles with noncircular fuselages, and a vortex-cloud model for body vortex shedding and tracking. Also discussed are panel methods with vorticity effects and corrections for nonlinear compressibility, supersonic full-potential methods for missile body analysis, space-marching Euler solvers, the time-asymptotic Euler/Navier-Stokes methods for subsonic and transonic flows, 3D boundary layers on missiles, Navier-Stokes analyses of flows over slender airframes, and the interaction of exhaust plumes with missile airframes.

  10. Hardware-in-the-loop missile simulation facility

    NASA Astrophysics Data System (ADS)

    Eguchi, Hirofumi; Obana, Kazumitu; Kamiya, Masanori

    1998-07-01

    A Hardware-in-the-loop (HWIL) simulation facility has been successfully contributing to the development and evaluation of missiles at the 3rd Research Center, Technical Research & Development Institute, Japan Defense Agency. This facility has two main characteristics. First, it has ability to generate both various RF target and background echoes in several frequency bands. Second, it can be used for the HWIL simulation tests of missiles which have RF/IR dual mode seekers. After the outline of this facility is presented, a technique to overcome the line-of-sight (LOS) angle limitation is proposed, because LOS angle limitation is inevitable in these HWIL simulation facilities. Moreover, a simulation method for the dual mode seeker missile is shown by using this proposed simulation technique.

  11. High performance infrared fast cooled detectors for missile applications

    NASA Astrophysics Data System (ADS)

    Reibel, Yann; Espuno, Laurent; Taalat, Rachid; Sultan, Ahmad; Cassaigne, Pierre; Matallah, Noura

    2016-05-01

    SOFRADIR was selected in the late 90's for the production of 320×256 MW detectors for major European missile programs. This experience has established our company as a key player in the field of missile programs. SOFRADIR has since developed a vast portfolio of lightweight, compact and high performance JT-based solutions for missiles. ALTAN is a 384x288 Mid Wave infrared detector with 15μm pixel pitch, and is offered in a miniature ultra-fast Joule- Thomson cooled Dewar. Since Sofradir offers both Indium Antimonide (InSb) and Mercury Cadmium Telluride technologies (MCT), we are able to deliver the detectors best suited to customers' needs. In this paper we are discussing different figures of merit for very compact and innovative JT-cooled detectors and are highlighting the challenges for infrared detection technologies.

  12. The Pershing 2 Mobile Ballistic Surface-to-Surface Missile

    NASA Astrophysics Data System (ADS)

    A detailed presentation is made of the Pershing 2 missile characteristics and perforance. Development, operation, deployment and trial flights are covered. Differences between the Pershing 2 and Pershing 1A are discussed and include the former's single upper element and elongated reentry vehicle with trimming flaps. The Pershing 2, fueled by hydroxyl terminated polybutadiene powder, has an estimated maximum range of 2500 km with a 667 kg reentry vehicle. Radar mapping data are compared in the missile's correlator to a previously generated or prerecorded reference image, memorized in digital form on magnetic tape; this allows readjustment of the missile's inertial platform and a 20-40 m target strike precision. Additional data are given on the nuclear warhead, launching and reentry trajectories, and costs.

  13. Missile placement analysis based on improved SURF feature matching algorithm

    NASA Astrophysics Data System (ADS)

    Yang, Kaida; Zhao, Wenjie; Li, Dejun; Gong, Xiran; Sheng, Qian

    2015-03-01

    The precious battle damage assessment by use of video images to analysis missile placement is a new study area. The article proposed an improved speeded up robust features algorithm named restricted speeded up robust features, which combined the combat application of TV-command-guided missiles and the characteristics of video image. Its restrictions mainly reflected in two aspects, one is to restrict extraction area of feature point; the second is to restrict the number of feature points. The process of missile placement analysis based on video image was designed and a video splicing process and random sample consensus purification were achieved. The RSURF algorithm is proved that has good realtime performance on the basis of guarantee the accuracy.

  14. A different approach to missile induced head injuries.

    PubMed

    Pabuscu, Yüksel; Bulakbasi, Nail; Kocaoglu, Murat; Ustünsöz, Bahri; Tayfun, Cem

    2003-01-01

    Missile induced head injuries can be influenced by the anatomical location of the injury, i.e. type of tissue and by the ballistic properties such as the design of the weapon and the mass, shape and construction of the projectile, as well as its velocity characteristics and trajectory angle. In the diagnostic work up of the patients with missile induced head injuries, every available modality can be used. It is important, however, to recognize that CT scan is the primary and most efficacious diagnostic tool in such patients. In this article we have identified risk factors for both morbidity and mortality in patients with missile induced head injury with excluding the patients who had also extracranial serious trauma and systemic disease. PMID:12821033

  15. Flexible missile autopilot design studies with PC-MATLAB/386

    NASA Technical Reports Server (NTRS)

    Ruth, Michael J.

    1989-01-01

    Development of a responsive, high-bandwidth missile autopilot for airframes which have structural modes of unusually low frequency presents a challenging design task. Such systems are viable candidates for modern, state-space control design methods. The PC-MATLAB interactive software package provides an environment well-suited to the development of candidate linear control laws for flexible missile autopilots. The strengths of MATLAB include: (1) exceptionally high speed (MATLAB's version for 80386-based PC's offers benchmarks approaching minicomputer and mainframe performance); (2) ability to handle large design models of several hundred degrees of freedom, if necessary; and (3) broad extensibility through user-defined functions. To characterize MATLAB capabilities, a simplified design example is presented. This involves interactive definition of an observer-based state-space compensator for a flexible missile autopilot design task. MATLAB capabilities and limitations, in the context of this design task, are then summarized.

  16. Missile injuries of the limbs: an Iraqi perspective.

    PubMed

    Hamdan, T A

    2006-01-01

    Missiles include pistol or rifle bullets, shell fragments, land mines, and grenades. Medium- and high-velocity missiles produce damage by laceration and crushing, shock waves, and cavitational effects. Low-velocity missiles produce damage by laceration and crushing only. Land mine injuries cause damage by the primary blast effect, secondarily by fragments, and thirdly by the effect induced by whole-body propulsion and by burns. Severity of injuries should be graded according to the degree of soft-tissue damage, bone defect or comminution, and vascular or neural injury. Among other factors, successful management of these injuries requires prompt and vigorous resuscitation, careful wound inspection, aggressive exploration, liberal débridement, and prompt removal of fragments. In addition, in these circumstances, one must stay alert for overlooked injuries and be aware of associated psychological trauma. PMID:17003203

  17. 75 FR 52732 - Renewal of Department of Defense Federal Advisory Committee; Missile Defense Advisory Committee

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-27

    ... of the Secretary Renewal of Department of Defense Federal Advisory Committee; Missile Defense... notice that it is renewing the charter for the Missile Defense Advisory Committee (hereafter referred to... Secretary of Defense for Acquisition, Technology & Logistics and the Director, Missile Defense...

  18. Fly-away restraint pin mechanism for the Army's PATRIOT missile system

    NASA Technical Reports Server (NTRS)

    Knight, F. W.

    1977-01-01

    The development of the longitudinal restraint mechanism for the Army's Patriot missile system is reviewed. The initial design was an ordnance pin puller with a shear plane. Because of reliability problems and a desire to reduce cost, a fly-away restraint mechanism was chosen. After being manually unlocked, the restraint pin disengages the missile during launch by missile motion.

  19. 76 FR 63541 - Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-13

    ... COMMISSION 10 CFR Parts 50 and 52 Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants... Hurricane and Hurricane Missiles for Nuclear Power Plants.'' This regulatory guide provides licensees and...- basis hurricane and design-basis hurricane-generated missiles that a nuclear power plant should...

  20. 78 FR 70537 - Takes of Marine Mammals Incidental to Specified Activities; Target and Missile Launch Activities...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-26

    .... SUMMARY: NMFS has received a request from the U.S. Navy (Navy), Naval Air Warfare Center Weapons Division... conducted for testing new types of targets. Missiles vary from tactical and developmental weapons to target missiles used to test defensive strategies and other weapons systems. Up to 200 missiles may be...

  1. 103. View of transmitter building no. 102, missile warning operation ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    103. View of transmitter building no. 102, missile warning operation center, overall view of center in operation with staff at consoles. Note defcon (defense condition) display panel (upper right) showing "simulated status"activity level. Also note fiber optic display panel at upper right-center. Official photograph BMEWS Project by Hansen 30 September, 1976, clear as negative no. A-14568. - Clear Air Force Station, Ballistic Missile Early Warning System Site II, One mile west of mile marker 293.5 on Parks Highway, 5 miles southwest of Anderson, Anderson, Denali Borough, AK

  2. Converting the Minuteman missile into a small satellite launch system

    NASA Technical Reports Server (NTRS)

    Alexander, Bill; Gonzalez, Rodolfo; Humble, Greg; Mackay, Gordon; Mchaty, Rod; Pham, VU

    1993-01-01

    Due to the Strategic Arms Reduction Talks (START) treaty between the United States and Ex-Soviet Union, 450 Minuteman 2 (MM 2) missiles were recently taken out of service. Minotaur Designs Incorporated (MDI) intends to convert the MM 2 ballistic missile from a nuclear warhead carrier into a small satellite launcher. MDI will perform this conversion by acquiring the Minuteman stages, purchasing currently available control wafers, and designing a new shroud and interfaces for the satellite. MDI is also responsible for properly integrating all systems.

  3. Consolidation of data base for Army generalized missile model

    NASA Technical Reports Server (NTRS)

    Klenke, D. J.; Hemsch, M. J.

    1980-01-01

    Data from plume interaction tests, nose mounted canard configuration tests, and high angle of attack tests on the Army Generalized Missile model are consolidated in a computer program which makes them readily accessible for plotting, listing, and evaluation. The program is written in FORTRAN and will run on an ordinary minicomputer. It has the capability of retrieving any coefficient from the existing DATAMAN tapes and displaying it in tabular or plotted form. Comparisons of data taken in several wind tunnels and of data with the predictions of Program MISSILE2 are also presented.

  4. Converting the Minuteman missile into a small satellite launch system

    NASA Astrophysics Data System (ADS)

    Alexander, Bill; Gonzalez, Rodolfo; Humble, Greg; Mackay, Gordon; McHaty, Rod; Pham, Vu

    1993-11-01

    Due to the Strategic Arms Reduction Talks (START) treaty between the United States and Ex-Soviet Union, 450 Minuteman 2 (MM 2) missiles were recently taken out of service. Minotaur Designs Incorporated (MDI) intends to convert the MM 2 ballistic missile from a nuclear warhead carrier into a small satellite launcher. MDI will perform this conversion by acquiring the Minuteman stages, purchasing currently available control wafers, and designing a new shroud and interfaces for the satellite. MDI is also responsible for properly integrating all systems.

  5. Tornado missile simulation and design methodology. Volume 2: model verification and data base updates. Final report

    SciTech Connect

    Twisdale, L.A.; Dunn, W.L.

    1981-08-01

    A probabilistic methodology has been developed to predict the probabilities of tornado-propelled missiles impacting and damaging nuclear power plant structures. Mathematical models of each event in the tornado missile hazard have been developed and sequenced to form an integrated, time-history simulation methodology. The models are data based where feasible. The data include documented records of tornado occurrence, field observations of missile transport, results of wind tunnel experiments, and missile impact tests. Probabilistic Monte Carlo techniques are used to estimate the risk probabilities. The methodology has been encoded in the TORMIS computer code to facilitate numerical analysis and plant-specific tornado missile probability assessments.

  6. Unified powered flight guidance

    NASA Technical Reports Server (NTRS)

    Brand, T. J.; Brown, D. W.; Higgins, J. P.

    1973-01-01

    A complete revision of the orbiter powered flight guidance scheme is presented. A unified approach to powered flight guidance was taken to accommodate all phases of exo-atmospheric orbiter powered flight, from ascent through deorbit. The guidance scheme was changed from the previous modified version of the Lambert Aim Point Maneuver Mode used in Apollo to one that employs linear tangent guidance concepts. This document replaces the previous ascent phase equation document.

  7. Missile Defense: LBJ's Bid To Curb Arms Race Gains Support.

    PubMed

    Carter, L J

    1967-04-14

    In the article of 31 March on antiballistic missile defense, the last sentence of paragraph 2, p. 1654, should read: "Manpower for producing . . . but the outer limit would be about 200,000, or half the number of contractor employees and civil servants working for NASA at the peak of the Apollo program." PMID:17741142

  8. 23 CFR 660.519 - Missile installations and facilities.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... extraordinary maintenance as necessary to keep the roads serviceable and maintain adequate supporting records of... OPERATIONS SPECIAL PROGRAMS (DIRECT FEDERAL) Defense Access Roads § 660.519 Missile installations and...) Restoration under the contract. (1) The highway agency having jurisdiction over the road shall...

  9. Missile Defense and Space: What's Changed? What Hasn't?

    NASA Astrophysics Data System (ADS)

    Coyle, Philip E., III

    2005-04-01

    In late 2004, the Bush Administration appeared to be eager to declare a nascent operational capability at its deployment sites in Alaska and California. In early December a flight intercept test failed, as had the previous test two years earlier. By the time of the inauguration, the Administration appeared to be backing away from a formal declaration of operational capability. Where does the system stand today? What has happened in important flight tests in more recent months? What has happened to the budgets for missile defense? What has happened with boost-phase missile defense, with Patriot, with the Airborne Laser, and other missile defense programs? And how have recent programmatic and budgetary changes affected the likelihood that missile defense will be the first U.S. military program to place strike weapons in space? Philip Coyle, Senior Advisor with the Center for Defense Information and former Assistant Secretary of Defense for Test and Evaluation, will review the latest developments and describe from a technical, programmatic, and policy point of view, ``What's Changed? and What Hasn't?"

  10. 5. PRELIMINARY SKETCH OF THE GUIDED MISSILE TEST FACILITIES FOR ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    5. PRELIMINARY SKETCH OF THE GUIDED MISSILE TEST FACILITIES FOR TEST AREA NUMBER 2. TODAY IR IS KNOWN AS MARSHALL SPACE FLIGHT CENTER'S EAST TEST AREA. HANNES LUEHRSEN COLLECTION, MSFC MASTER PLANNING OFFICE. - Marshall Space Flight Center, East Test Area, Dodd Road, Huntsville, Madison County, AL

  11. CMC occasional papers : a missile stability regime for South Asia.

    SciTech Connect

    Khan, Feroz Hassan; Vannoni, Michael Geoffrey; Rajen, Gaurav

    2004-06-01

    India and Pakistan have created sizeable ballistic missile forces and are continuing to develop and enlarge them. These forces can be both stabilizing (e.g., providing a survivable force for deterrence) and destabilizing (e.g., creating strategic asymmetries). Missile forces will be a factor in bilateral relations for the foreseeable future, so restraint is necessary to curtail their destabilizing effects. Such restraint, however, must develop within an atmosphere of low trust. This report presents a set of political and operational options, both unilateral and bilateral, that decreases tensions, helps rebuild the bilateral relationship, and prepares the ground for future steps in structural arms control. Significant steps, which build on precedents and do not require extensive cooperation, are possible despite strained relations. The approach is made up of three distinct phases: (1) tension reduction measures, (2) confidence building measures, and (3) arms control agreements. The goal of the first phase is to initiate unilateral steps that are substantive and decrease tensions, establish missiles as a security topic for bilateral discussion, and set precedents for limited bilateral cooperation. The second phase would build confidence by expanding current bilateral security agreements, formalizing bilateral understandings, and beginning discussion of monitoring procedures. The third phase could include bilateral agreements limiting some characteristics of national missile forces including the cooperative incorporation of monitoring and verification.

  12. The conception, birth, and growth of a missile umbilical system

    NASA Technical Reports Server (NTRS)

    Nordman, G. W.

    1977-01-01

    The design development of the Sprint 2 and the Improved Sprint 2 Missile System umbilical system is reviewed. Unique system requirements, umbilical designs considered to meet the requirements, and the problems encountered and solutions derived during the design and development testing of the selected systems are described.

  13. 18. LAUNCH CONTROL SUPPORT BUILDING. 'MISSILE ART' MURAL PAINTED ON ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    18. LAUNCH CONTROL SUPPORT BUILDING. 'MISSILE ART' MURAL PAINTED ON INTERIOR WALL OF ELEVATOR SHAFT. VIEW TO EAST. - Minuteman III ICBM Launch Control Facility November-1, 1.5 miles North of New Raymer & State Highway 14, New Raymer, Weld County, CO

  14. 28. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    28. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW MEMBERS (FRONT TO BACK) LIEUTENANT KEVIN R. MCCLUNEY AND CAPTAIN JAMES L. KING, JR. SHOCK ISOLATOR AND ELECTRONIC EQUIPMENT RACK AT FAR LEFT. VIEW TO SOUTH. - Minuteman III ICBM Launch Control Facility November-1, 1.5 miles North of New Raymer & State Highway 14, New Raymer, Weld County, CO

  15. 26. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    26. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW MEMBER LIEUTENANT KEVIN R. MCCLUNEY AT COMMUNICATIONS CONSOLE. LAUNCH CONTROL CONSOLE IN FOREGROUND. VIEW TO NORTH. - Minuteman III ICBM Launch Control Facility November-1, 1.5 miles North of New Raymer & State Highway 14, New Raymer, Weld County, CO

  16. Photograph and Speech Related to the Cuban Missile Crisis

    ERIC Educational Resources Information Center

    Bredhoff, Stacey; Potter, Lee Ann

    2012-01-01

    On Sunday, October 14, 1962, an American U-2 aircraft, flying a photographic reconnaissance mission over Cuba, took 928 images (one is included with this article). The next day, analysts at the National Photographic Interpretation Center concluded that the photographs showed evidence of Soviet missile site construction in Cuba and conveyed their…

  17. When Fear Ruled: Rethinking the Cuban Missile Crisis.

    ERIC Educational Resources Information Center

    Paterson, Thomas G.

    1995-01-01

    Provides an insightful look at the administrative and negotiative processes that accompanied the 1962 Cuban missile crisis. Although John F. Kennedy and Nikita Khrushchev both worked to avoid nuclear war, the stress and exhaustion of the negotiating process created serious blunders. Eventually both sides backed away from nuclear annihilation. (MJP)

  18. 23 CFR 660.519 - Missile installations and facilities.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... extraordinary maintenance as necessary to keep the roads serviceable and maintain adequate supporting records of... OPERATIONS SPECIAL PROGRAMS (DIRECT FEDERAL) Defense Access Roads § 660.519 Missile installations and...) Restoration under the contract. (1) The highway agency having jurisdiction over the road shall...

  19. Atmospheric Turbulence Relative to Aviation, Missile, and Space Programs

    NASA Technical Reports Server (NTRS)

    Camp, Dennis W. (Editor); Frost, Walter (Editor)

    1987-01-01

    The purpose of the workshop was to bring together various disciplines of the aviation, missile, and space programs involved in predicting, measuring, modeling, and understanding the processes of atmospheric turbulence. Working committees re-examined the current state of knowledge, identified present and future needs, and documented and prioritized integrated and cooperative research programs.

  20. A hybrid optical system for broadband imaging in guidance and control

    NASA Astrophysics Data System (ADS)

    Wu, Xiaofang; Jiang, Yuesong; Shen, Chunyan; Zhao, Yiming

    2006-11-01

    A binary optics method has been adopted to improve upon a conventional optical system in guidance and control, and a hybrid broadband imaging system that includes a binary surface is analyzed and evaluated by optical design software ZEMAX. The practical design shows that the introduction of binary optics can simplify the structure of the imaging system and reduce the size and weight of the broadband guidance and control system. Moreover, it can help to acquire images of radiation of different wavelengths from targets; hence it will result in improved overall performance of missiles in wars.

  1. Fuzzy logic sliding mode control for command guidance law design.

    PubMed

    Elhalwagy, Y Z; Tarbouchi, M

    2004-04-01

    Recently, the combination of sliding mode and fuzzy logic techniques has emerged as a promising methodology for dealing with nonlinear, uncertain, dynamical systems. In this paper, a sliding mode control algorithm combined with a fuzzy control scheme is developed for the trajectory control of a command guidance system. The acceleration command input is mathematically derived. The proposed controller is used to compensate for the influence of unmodeled dynamics and to alleviate chattering. Simulation results show that the proposed controller gives good system performance in the face of system parameters variation and external disturbances. In addition, they show the effectiveness of the proposed missile guidance law against different engagement scenarios where the results demonstrate better performance over the conventional sliding mode control.

  2. Temporal uncertainty analysis of human errors based on interrelationships among multiple factors: a case of Minuteman III missile accident.

    PubMed

    Rong, Hao; Tian, Jin; Zhao, Tingdi

    2016-01-01

    In traditional approaches of human reliability assessment (HRA), the definition of the error producing conditions (EPCs) and the supporting guidance are such that some of the conditions (especially organizational or managerial conditions) can hardly be included, and thus the analysis is burdened with incomprehensiveness without reflecting the temporal trend of human reliability. A method based on system dynamics (SD), which highlights interrelationships among technical and organizational aspects that may contribute to human errors, is presented to facilitate quantitatively estimating the human error probability (HEP) and its related variables changing over time in a long period. Taking the Minuteman III missile accident in 2008 as a case, the proposed HRA method is applied to assess HEP during missile operations over 50 years by analyzing the interactions among the variables involved in human-related risks; also the critical factors are determined in terms of impact that the variables have on risks in different time periods. It is indicated that both technical and organizational aspects should be focused on to minimize human errors in a long run. PMID:26360211

  3. Temporal uncertainty analysis of human errors based on interrelationships among multiple factors: a case of Minuteman III missile accident.

    PubMed

    Rong, Hao; Tian, Jin; Zhao, Tingdi

    2016-01-01

    In traditional approaches of human reliability assessment (HRA), the definition of the error producing conditions (EPCs) and the supporting guidance are such that some of the conditions (especially organizational or managerial conditions) can hardly be included, and thus the analysis is burdened with incomprehensiveness without reflecting the temporal trend of human reliability. A method based on system dynamics (SD), which highlights interrelationships among technical and organizational aspects that may contribute to human errors, is presented to facilitate quantitatively estimating the human error probability (HEP) and its related variables changing over time in a long period. Taking the Minuteman III missile accident in 2008 as a case, the proposed HRA method is applied to assess HEP during missile operations over 50 years by analyzing the interactions among the variables involved in human-related risks; also the critical factors are determined in terms of impact that the variables have on risks in different time periods. It is indicated that both technical and organizational aspects should be focused on to minimize human errors in a long run.

  4. The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Introduction and Problem Formulation for a Multiple Stressor Risk Assessment

    SciTech Connect

    Efroymson, Rebecca Ann; Peterson, Mark J; Jones, Daniel Steven; Suter, Glenn

    2008-01-01

    An ecological risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework (MERAF). The focus of the assessment was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, i.e., M60-A1 tanks. The problem formulation for the assessment included conceptual models for three component activities of the test, helicopter overflight, missile firing, and tracked vehicle movement, and two ecological endpoint entities, woody desert wash communities and desert mule deer (Odocoileus hemionus crooki) populations. An activity-specific risk assessment framework was available to provide guidance for assessing risks associated with aircraft overflights. Key environmental features of the study area include barren desert pavement and tree-lined desert washes. The primary stressors associated with helicopter overflights were sound and the view of the aircraft. The primary stressor associated with Hellfire missile firing was sound. The principal stressor associated with tracked vehicle movement was soil disturbance, and a resulting, secondary stressor was hydrological change. Water loss to washes and wash vegetation was expected to result from increased ponding, infiltrationand/or evaporation associated with disturbances to desert pavement. A plan for estimating integrated risks from the three military activities was included in the problem formulation.

  5. Ionospheric effects of the missile destruction on December 9, 2009

    NASA Astrophysics Data System (ADS)

    Kozlovsky, Alexander; Shalimov, Sergey; Lukianova, Renata

    2014-05-01

    We report on ionosonde and meteor radar observations made in Sodankyla Geophysical Observatory (SGO, 67N, 27E, Finland) on December 9, 2009 during a test launch of the Russian solid propellant military missile. Because of the technical problem the missile was self-destroyed around 07 UT at ionospheric height (170-260 km) over the Kola Peninsula (Russia), at a distance about 500 km to east from the observatory. Products of the explosion, including long-lived ionized aluminum oxides, were spread into the large area and reached the region of SGO meteor radar observations in about 2 hours (around 09 UT). After about 3 hours (around 10 UT) a sporadic E layer presumably composed of the remains was observed close to the zenith of the SGO ionosonde. We present the data and discuss possible mechanisms accounting for both vertical and horizontal transport of the remains. Theoretical estimations suggest that the observed transport could be likely due to thermospheric turbulence.

  6. Study of Subsonic Flow Over a TOW 2B Missile

    NASA Astrophysics Data System (ADS)

    Goudarzi, Koorosh; Jamali, Mehdi

    2016-01-01

    The objective of this investigation is to study the subsonic flow over a missile. In this paper, a model of TOW 2B missile is studied. Two computational approaches are being explored, namely solutions based on the Reynolds-averaged compressible Navier-Stokes equations and solutions based on the inviscid flow (small disturbance theory). The simulations are performed at the Mach number of 0.6, 0.7, 0.8, 0.9 and 1.0 at four angles of attack of 2, 4, 6 and 8 degree. Results obtained from analytical simulation are compared with numerical data. It is found that lift and drag coefficients would go up by increasing of the angle of attack and the Mach number. Trend of changes of the results that obtained from the small disturbance theory is roughly as same as the numeric solution.

  7. Demonstration of the Military Ecological Risk Assessment Framework (MERAF): Apache Longbow - Hell Missile Test at Yuma Proving Ground

    SciTech Connect

    Efroymson, R.A.

    2002-05-09

    This ecological risk assessment for a testing program at Yuma Proving Ground, Arizona, is a demonstration of the Military Ecological Risk Assessment Framework (MERAF; Suter et al. 2001). The demonstration is intended to illustrate how risk assessment guidance concerning-generic military training and testing activities and guidance concerning a specific type of activity (e.g., low-altitude aircraft overflights) may be implemented at a military installation. MERAF was developed with funding from the Strategic Research and Development Program (SERDP) of the Department of Defense. Novel aspects of MERAF include: (1) the assessment of risks from physical stressors using an ecological risk assessment framework, (2) the consideration of contingent or indirect effects of stressors (e.g., population-level effects that are derived from habitat or hydrological changes), (3) the integration of risks associated with different component activities or stressors, (4) the emphasis on quantitative risk estimates and estimates of uncertainty, and (5) the modularity of design, permitting components of the framework to be used in various military risk assessments that include similar activities. The particular subject of this report is the assessment of ecological risks associated with a testing program at Cibola Range of Yuma Proving Ground, Arizona. The program involves an Apache Longbow helicopter firing Hellfire missiles at moving targets, i.e., M60-A1 tanks. Thus, the three component activities of the Apache-Hellfire test were: (1) helicopter overflight, (2) missile firing, and (3) tracked vehicle movement. The demonstration was limited, to two ecological endpoint entities (i.e., potentially susceptible and valued populations or communities): woody desert wash communities and mule deer populations. The core assessment area is composed of about 126 km{sup 2} between the Chocolate and Middle Mountains. The core time of the program is a three-week period, including fourteen days of

  8. Finger Seal: A Novel Approach to Air to Air Sealing

    NASA Technical Reports Server (NTRS)

    Arora, Gul; Steinetz, Bruce; Proctor, Margaret

    2006-01-01

    The gas turbine industry used a variety of sealing mechanisms to contain and direct secondary flows into and around components for cooling, and to limit leakage into and from bearing and disk cavities. The function of these seals is very important to the component efficiencies and attendant engine performance. Most of these seals are labyrinth seals, which are high-leakage seals that are costly to manufacture. In recent years, brush seals have been introduced which have demonstrated significantly reduced leakage, although they are still expensive and have exhibited wear and hysteresis difficulties. A new innovative concept called finger seal, patented by AlliedSignal, has demonstrated leakage similar to brush seals and is cheaper. The finger seal is comprised of a stack of precision photo-etched sheet metal elements, which allows intricate features to be made at very low cost and with the potential to resist wear and provide the compliance necessary to accomodate rotor excursions. Initial testing in the high-speed/high-temperature seal test facility, at the NASA Lewis Research Center, has corroborated the finger seal performance. The testing also revealed hysteresis problems with the current design. A NASA funded research project is in progress to correct the functional deficiencies of the finger seal and to refine its features to provide sufficient seal life for commercial transport engines and other long-life applications. This research will benefit the aeronautical gas turbine industry as a whole in terms of fuel consumption, operational characteristics, and cost. The first phase of this research to reduce finger seal hysteresis has been in progress for the last one year. This paper presents the results of this research to date. In future the research program will address seal performance, manufacturing, cost and life issues. The research program is expected to be completed by December 1998.

  9. Theory and Experiments on Supersonic Air-to-Air Ejectors.

    NASA Technical Reports Server (NTRS)

    Fabri, J; Paulon, J

    1958-01-01

    A comparison of experiment with theory is made for air ejectors having cylindrical mixing sections and operating under conditions of supersonic primary flow and either mixed or supersonic regimes of mixing. The effect on ejector performance of such parameters as mixer length and cross section, terminating diffuser, primary Mach number, and primary nozzle position is presented in terms of mass flow and pressure ratio.

  10. Self-defrosting recuperative air-to-air heat exchanger

    DOEpatents

    Drake, Richard L.

    1993-01-01

    A heat exchanger includes a stationary spirally or concentrically wound heat exchanger core with rotating baffles on upper and lower ends thereof. The rotating baffles include rotating inlets and outlets which are in communication with respective fixed inlets and outlets via annuli. The rotation of the baffles causes a concurrent rotation of the temperature distribution within the stationary exchanger core, thereby preventing frost build-up in some applications and preventing the formation of hot spots in other applications.

  11. Self-defrosting recuperative air-to-air heat exchanger

    DOEpatents

    Drake, R.L.

    1993-12-28

    A heat exchanger is described which includes a stationary spirally or concentrically wound heat exchanger core with rotating baffles on upper and lower ends thereof. The rotating baffles include rotating inlets and outlets which are in communication with respective fixed inlets and outlets via annuli. The rotation of the baffles causes a concurrent rotation of the temperature distribution within the stationary exchanger core, thereby preventing frost build-up in some applications and preventing the formation of hot spots in other applications. 3 figures.

  12. 7. "AERIAL VIEW OF THE TEST AREA, DIRECTORATE OF MISSILE ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    7. "AERIAL VIEW OF THE TEST AREA, DIRECTORATE OF MISSILE CAPTIVE TEST, EDWARDS AFB. 8 AUG 57." In upper left corner, photo no. "8462 57" cropped out: "A-AFFTC 8 AUG 57, RETL TEST AREA" This photo is a high oblique view, showing the wing of the photo plane and Test Area 1-115. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Leuhman Ridge near Highways 58 & 395, Boron, Kern County, CA

  13. Analyzing and designing object-oriented missile simulations with concurrency

    NASA Astrophysics Data System (ADS)

    Randorf, Jeffrey Allen

    2000-11-01

    A software object model for the six degree-of-freedom missile modeling domain is presented. As a precursor, a domain analysis of the missile modeling domain was started, based on the Feature-Oriented Domain Analysis (FODA) technique described by the Software Engineering Institute (SEI). It was subsequently determined the FODA methodology is functionally equivalent to the Object Modeling Technique. The analysis used legacy software documentation and code from the ENDOSIM, KDEC, and TFrames 6-DOF modeling tools, including other technical literature. The SEI Object Connection Architecture (OCA) was the template for designing the object model. Three variants of the OCA were considered---a reference structure, a recursive structure, and a reference structure with augmentation for flight vehicle modeling. The reference OCA design option was chosen for maintaining simplicity while not compromising the expressive power of the OMT model. The missile architecture was then analyzed for potential areas of concurrent computing. It was shown how protected objects could be used for data passing between OCA object managers, allowing concurrent access without changing the OCA reference design intent or structure. The implementation language was the 1995 release of Ada. OCA software components were shown how to be expressed as Ada child packages. While acceleration of several low level and other high operations level are possible on proper hardware, there was a 33% degradation of 4th order Runge-Kutta integrator performance of two simultaneous ordinary differential equations using Ada tasking on a single processor machine. The Defense Department's High Level Architecture was introduced and explained in context with the OCA. It was shown the HLA and OCA were not mutually exclusive architectures, but complimentary. HLA was shown as an interoperability solution, with the OCA as an architectural vehicle for software reuse. Further directions for implementing a 6-DOF missile modeling

  14. The conception, birth, and growth of a missile umbilical system

    NASA Technical Reports Server (NTRS)

    Nordman, G. W.

    1977-01-01

    The design development was traced for the sprint 2 and improved sprint 2 missile system (ISMS) umbilical system. The unique system requirements, umbilical designs considered to meet the requirements, and the problems encountered and solutions derived during the design, and development testing of the selected systems are described. The sprint 2 development effort consisted of design, analysis, and testing activities. The ISMS effort involved the performance of an extensive trade study to determine the optimum design to meet the ISMS conditions.

  15. The theater missile defense threat to US security

    SciTech Connect

    Keeny, S.M. Jr.

    1994-09-01

    The Clinton administration has embraced a major program to develop a family of theater missile defense (TMD) systems to protect US forces and allies overseas. The large scale of the undertaking is reflected in Congressional Budget Office estimates that currently planned development and procurement alone will cost around $50 billion through the year 2010. This figure could easily double if the proposed advanced-capability systems are actually deployed and the historical pattern of cost escalation of high-technology programs prevails.

  16. An autonomous rendezvous and docking system using cruise missile technology

    NASA Technical Reports Server (NTRS)

    Jones, ED; Nicholson, Bruce

    1991-01-01

    In November 1990 General Dynamics demonstrated an AR&D system for members of the Strategic Avionics Technology Working Group. This simulation utilized prototype hardware derived from the Cruise Missile and Centaur avionics systems. The object of this proof of concept demonstration was to show that all the accuracy, reliability, and operational requirements established for a spacecraft to dock with Space Station Freedom could be met by the proposed AR&D system.

  17. 23. "A CAPTIVE ATLAS MISSILE EXPLODED DURING THE TEST ON ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    23. "A CAPTIVE ATLAS MISSILE EXPLODED DURING THE TEST ON TEST STAND 1-A, 27 MARCH 1959, PUTTING THAT TEST STAND OUT-OF-COMMISSION. STAND WAS NOT REPAIRED FOR THE ATLAS PROGRAM BUT TRANSFERRED TO ROCKETDYNE AND MODIFIED FOR THE F-l ENGINE PROGRAM." - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Test Stand 1-A, Test Area 1-120, north end of Jupiter Boulevard, Boron, Kern County, CA

  18. 25. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    25. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW MEMBERS (FRONT TO BACK) CAPTAIN JAMES L. KING, JR. AT LAUNCH CONTROL CONSOLE AND LIEUTENANT KEVIN R. MCCLUNEY AT COMMUNICATIONS CONSOLE. RADIO TRANSMITTER AND RECEIVER RACKS AT FAR RIGHT; ELECTRONIC EQUIPMENT RACKS AT FAR LEFT. VIEW TO NORTH. - Minuteman III ICBM Launch Control Facility November-1, 1.5 miles North of New Raymer & State Highway 14, New Raymer, Weld County, CO

  19. 29. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    29. LAUNCH CONTROL CAPSULE. ACOUSTICAL ENCLOSURE WITH MISSILE COMBAT CREW MEMBERS (FRONT TO BACK) LIEUTENANT KEVIN R. MCCLUNEY AND CAPTAIN JAMES L. KING, JR. AT CONSOLES. REFRIGERATOR AT RIGHT FLANKED BY RADIO EQUIPMENT (RIGHT) AND FILE CABINETS (LEFT). VIEW TO SOUTHWEST. - Minuteman III ICBM Launch Control Facility November-1, 1.5 miles North of New Raymer & State Highway 14, New Raymer, Weld County, CO

  20. The proliferation of aerospace weapons technology: Ballistic missiles and the case of Brazil

    NASA Astrophysics Data System (ADS)

    Vossen, Terrence John

    1993-04-01

    The rationale behind the development of ballistic missile production in Brazil is examined by exploring the political, military, and economic determinants of ballistic missile demand in that country. To ascertain how Brazil developed missile production capabilities, the contributions of aerospace industries in industrialized states, the Brazilian space program, trade between less-developed countries, and illicit trade in missile technology are assessed. It is argued that missile development increasingly became a function of economic as opposed to security considerations, and that technologies transferred from developed country aerospace firms and Brazil's space program were primarily responsible for the creation of production capabilities. It is also contended that the proliferation of missile technology to Brazil was consistent with the workings of a system evident in the aerospace weapons technology market that sustains the horizontal spread of weapons production capabilities.

  1. Sensors and sensor systems for guidance and navigation II; Proceedings of the Meeting, Orlando, FL, Apr. 22, 23, 1992

    NASA Technical Reports Server (NTRS)

    Welch, Sharon S. (Editor)

    1992-01-01

    Topics discussed in this volume include aircraft guidance and navigation, optics for visual guidance of aircraft, spacecraft and missile guidance and navigation, lidar and ladar systems, microdevices, gyroscopes, cockpit displays, and automotive displays. Papers are presented on optical processing for range and attitude determination, aircraft collision avoidance using a statistical decision theory, a scanning laser aircraft surveillance system for carrier flight operations, star sensor simulation for astroinertial guidance and navigation, autonomous millimeter-wave radar guidance systems, and a 1.32-micron long-range solid state imaging ladar. Attention is also given to a microfabricated magnetometer using Young's modulus changes in magnetoelastic materials, an integrated microgyroscope, a pulsed diode ring laser gyroscope, self-scanned polysilicon active-matrix liquid-crystal displays, the history and development of coated contrast enhancement filters for cockpit displays, and the effect of the display configuration on the attentional sampling performance.

  2. Soviet concepts of ballistic missile defense. Master's thesis

    SciTech Connect

    Seavey, K.P.

    1988-06-01

    This thesis characterizes the Soviet concept of ballistic missile defense (BMD) in order to better understand and predict future Soviet BMD decision making. The Soviet concept of BMD is fundamentally different from that in the West. Soviet BMD is clearly an integral component of a much larger Soviet strategic defense effort which consists of strategic air defense as well as passive measures, such as mobility, deep underground command and control facilities, and civil defense. As the Soviet military literature demonstrates, Soviet strategic air defense encompasses defense against a continuum of threats -- from aircraft to ballistic missiles to satellites to 'space-strike weapons'. Soviet strategic air defense weapons therefore appear optimized to counter a wide range of airborne threats. In the Soviet view, surface-to-air missiles may be a primary tactical BMD weapon. Additionally, Soviet strategic BMD weapons may be a primary Soviet anti-satellite weapon. Furthermore, manned space platforms play a particularly significant role in Soviet thinking about the future of BMD and space warfare.

  3. The art and science of missile defense sensor design

    NASA Astrophysics Data System (ADS)

    McComas, Brian K.

    2014-06-01

    A Missile Defense Sensor is a complex optical system, which sits idle for long periods of time, must work with little or no on-­board calibration, be used to find and discriminate targets, and guide the kinetic warhead to the target within minutes of launch. A short overview of the Missile Defense problem will be discussed here, as well as, the top-level performance drivers, like Noise Equivalent Irradiance (NEI), Acquisition Range, and Dynamic Range. These top-level parameters influence the choice of optical system, mechanical system, focal plane array (FPA), Read Out Integrated Circuit (ROIC), and cryogenic system. This paper will not only discuss the physics behind the performance of the sensor, but it will also discuss the "art" of optimizing the performance of the sensor given the top level performance parameters. Balancing the sensor sub-­systems is key to the sensor's performance in these highly stressful missions. Top-­level performance requirements impact the choice of lower level hardware and requirements. The flow down of requirements to the lower level hardware will be discussed. This flow down directly impacts the FPA, where careful selection of the detector is required. The flow down also influences the ROIC and cooling requirements. The key physics behind the detector and cryogenic system interactions will be discussed, along with the balancing of subsystem performance. Finally, the overall system balance and optimization will be discussed in the context of missile defense sensors and expected performance of the overall kinetic warhead.

  4. Worldwide missile defense and the war on terrorism

    NASA Astrophysics Data System (ADS)

    Kane, Francis X.

    2002-07-01

    At the end of a long developmental road, dating back nearly a half-century, we are on the verge of having a defense against ballistic missiles. Starting some fifty years ago, we have initiated, and halted various programs to explore technology for missile defense. The reason for the go and stop program was the theological debate on deterrence. The issue was whether we would deter the Soviets from attacking us if we were to deploy a defense against their ballistic missiles. Our assessment was it would not, because they would expand their offensive. If you watched the President on TV after 9/11, you could sense the depth of his reaction. He is determined that it won't happen again. Furthermore, he must be conscious that this attack was the first time in nearly two centuries when an enemy caused damage in the US. He has created a new national effort to insure that it doesn't happen again. The efforts devoted to this objective are many, complex, and innovative. I will try to cover the most important activities, then describe how they are integrated to reach that objective in dynamic circumstances, of a long war.

  5. Application of a Complex Lead Compensator for a Laser Guided Missile

    NASA Astrophysics Data System (ADS)

    Akhila, M. R.; Gopika, S.; Abraham, R. J.

    2013-01-01

    This paper discusses the application of a lead compensator with complex pole and complex zero for a missile. It is compared with a lead compensator with real pole and real zero. A typical laser guided missile control system is considered for the performance comparison of both the compensators. Simulation studies carried out with MATLAB brings out the scope of using complex compensator in missile guided systems.

  6. Probabilistic wind/tornado/missile analyses for hazard and fragility evaluations

    SciTech Connect

    Park, Y.J.; Reich, M.

    1995-10-01

    Detailed analysis procedures and examples are presented for the probabilistic evaluation of hazard and fragility against high wind, tornado, and tornado-generated missiles. In the tornado hazard analysis, existing risk models are modified to incorporate various uncertainties including modeling errors. A significant feature of this paper is the detailed description of the Monte-Carlo simulation analyses of tornado-generated missiles. A simulation procedure, which includes the wind field modeling, missile injection, solution of flight equations, and missile impact analysis, is described with application examples.

  7. Corporate information management guidance

    SciTech Connect

    1997-08-01

    At the request of the Department of Energy`s (DOE) Information Management (IM) Council, IM representatives from nearly all Headquarters (HQ) organizations have been meeting over the past year as the Corporate Guidance Group (CGG) to develop useful and sound corporate information management (IM) guidance. The ability of the Department`s IM community to develop such unified guidance continues to be critical to the success of future Departmental IM planning processes and the establishment of a well-coordinated IM environment between Headquarters and field organizations. This report, with 26 specific corporate IM guidance items documented and unanimously agreed to, as well as 12 items recommended for further development and 3 items deferred for future consideration, represents a highly successful effort by the IM community. The effort has proven that the diverse DOE organizations can put aside individual preferences and work together towards a common and mutually beneficial goal. In examining most areas and issues associated with information management in the Department, they have developed specific, far-reaching, and useful guidance. The IM representatives recommend that the documented guidance items provided in this report and approved by the DOE IM Council be followed by all IM organizations. The representatives also strongly recommend that the guidance process developed by the CGG be the single process for developing corporate IM guidance.

  8. Aiding Vertical Guidance Understanding

    NASA Technical Reports Server (NTRS)

    Feary, Michael; McCrobie, Daniel; Alkin, Martin; Sherry, Lance; Polson, Peter; Palmer, Everett; McQuinn, Noreen

    1998-01-01

    A two-part study was conducted to evaluate modern flight deck automation and interfaces. In the first part, a survey was performed to validate the existence of automation surprises with current pilots. Results indicated that pilots were often surprised by the behavior of the automation. There were several surprises that were reported more frequently than others. An experimental study was then performed to evaluate (1) the reduction of automation surprises through training specifically for the vertical guidance logic, and (2) a new display that describes the flight guidance in terms of aircraft behaviors instead of control modes. The study was performed in a simulator that was used to run a complete flight with actual airline pilots. Three groups were used to evaluate the guidance display and training. In the training, condition, participants went through a training program for vertical guidance before flying the simulation. In the display condition, participants ran through the same training program and then flew the experimental scenario with the new Guidance-Flight Mode Annunciator (G-FMA). Results showed improved pilot performance when given training specifically for the vertical guidance logic and greater improvements when given the training and the new G-FMA. Using actual behavior of the avionics to design pilot training and FMA is feasible, and when the automated vertical guidance mode of the Flight Management System is engaged, the display of the guidance mode and targets yields improved pilot performance.

  9. Guidance for Total Development.

    ERIC Educational Resources Information Center

    Van Hoose, William H.

    Elementary guidance, deriving much of its content from the developmental phenomena of middle childhood, is viewed as the maximization of human potentiality in the total range of the population. Included in the list of elementary school guidance objectives are (1) aiding academic development, (2) helping children develop health self-concepts, (3)…

  10. The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Ecological Risk Assessment for Missile Firing

    SciTech Connect

    Jones, Daniel Steven; Efroymson, Rebecca Ann; Hargrove, William Walter; Suter, Glenn; Pater, Larry

    2008-01-01

    A multiple stressor risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework. The focus was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, M60- A1 tanks. This paper describes the ecological risk assessment for the missile launch and detonation. The primary stressor associated with this activity was sound. Other minor stressors included the detonation impact, shrapnel, and fire. Exposure to desert mule deer (Odocoileus hemionus crooki) was quantified using the Army sound contour program BNOISE2, as well as distances from the explosion to deer. Few effects data were available from related studies. Exposure-response models for the characterization of effects consisted of human "disturbance" and hearing damage thresholds in units of C-weighted decibels (sound exposure level) and a distance-based No Observed Adverse Effects Level for moose and cannonfire. The risk characterization used a weight-of-evidence approach and concluded that risk to mule deer behavior from the missile firing was likely for a negligible number of deer, but that no risk to mule deer abundance and reproduction is expected.

  11. Hypervelocity orbital intercept guidance using certainty control

    SciTech Connect

    Alfano, S.; Fosha, C.E., Jr. Colorado, University, Colorado Springs )

    1991-06-01

    Terminal guidance of a hypervelocity exoatmospheric orbital interceptor with free end time is examined. A new approach called certainty control is developed where control energy expenditure is reduced by constraining the expected final state to a function of projected estimate error. Conceptually, the constraint produces a shrinking sphere about the predicted impact point with the radius being a function of estimated error. If the predicted miss is inside or touching the sphere, thrusting is not necessary. The interceptor is modeled as a satellite with lateral thrusting capability using two-body orbital dynamics. The target is modeled as an intercontinental ballistic missile (IBM) in its final boost phase prior to burnout. Filtering is accomplished using an eight-state extended Kalman filter with line-of-sight and range updates. The estimated relative trajectory and variances are propagated numerically to predicted impact time and then approximated by splines, eliminating the need to propagate new data repeatedly when present conditions are varied. A search is then made for a new impact time and point that will minimize present interceptor velocity changes and final mass distance. This control strategy, which is applied to two intercept problems, substantially reduces fuel consumption. 28 refs.

  12. 46. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    46. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, interior view of elevator system with overhead doors in open position and hydraulic shaft in left foreground VIEW WEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  13. 45. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    45. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, general interior view of elevator system and wall-mounted control pad VIEW EAST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  14. 50. Quincy, MA, BO37, Launch Area, Underground Missile Storage Structure, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    50. Quincy, MA, BO-37, Launch Area, Underground Missile Storage Structure, view of staircase, access to personnel quarters with circular air shaft in ceiling VIEW EAST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

  15. Ballistic missile proliferation a national security focus for the 21st century. Research report

    SciTech Connect

    Peterson, J.F.

    1994-04-21

    The global proliferation of ballistic missiles and weapons of mass destruction (WMD) has become one of the most immediate and dangerous threats to U.S. national security. Ballistic missiles were used in four of the last six major wars. Some 190 missiles were fired by Iraqis over a six week period at Iranian cities in 1988, during the 'War of the Cities'. Iraq's firing of Scuds against coalition forces and Israel during the Gulf War provided a vivid reminder of the threat these weapons can present to the world community. During the 1980's, many Third World countries assigned a high priority to the acquisition of ballistic missiles. By 1991, more than 20 of these nations either possessed ballistic missiles or were attempting to obtain them. Today 43 nations possess ballistic missiles. Seventeen of these probably have a nuclear weapon capability, with 20 of them possessing also a chemical or biological capability. This paper seeks to: define the military challenge ballistic missiles represent; review current U.S. counter-proliferation and nonproliferation initiatives and, finally make recommendations on other potential methods or considerations to reduce ballistic missile proliferation.

  16. 33 CFR 334.1440 - Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 33 Navigation and Navigable Waters 3 2014-07-01 2014-07-01 false Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. 334.1440 Section 334.1440 Navigation and Navigable Waters CORPS OF....1440 Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. (a) The warning...

  17. 33 CFR 334.1440 - Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. 334.1440 Section 334.1440 Navigation and Navigable Waters CORPS OF....1440 Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. (a) The warning...

  18. 33 CFR 334.1440 - Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. 334.1440 Section 334.1440 Navigation and Navigable Waters CORPS OF....1440 Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. (a) The warning...

  19. 33 CFR 334.1440 - Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 33 Navigation and Navigable Waters 3 2013-07-01 2013-07-01 false Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. 334.1440 Section 334.1440 Navigation and Navigable Waters CORPS OF....1440 Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. (a) The warning...

  20. 33 CFR 334.1440 - Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. 334.1440 Section 334.1440 Navigation and Navigable Waters CORPS OF....1440 Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. (a) The warning...

  1. Slender body treatment of some specialized problems associated with elliptic-cross-section missile configurations

    NASA Technical Reports Server (NTRS)

    Barger, R. L.

    1977-01-01

    Slender body methods were applied to some specialized problems associated with missile configurations with elliptic cross sections. Expressions are derived for computing the velocity distribution on the nose section when the ellipse eccentricity is varying longitudinally on the missile. The cross flow velocity on a triform fin section is also studied.

  2. U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    U.S. Naval Base, Pearl Harbor, Ford Island Polaris Missile Lab & U.S. Fleet Ballistic Missile Submarine Training Center, Between Lexington Boulvevard and the sea plane ramps on the southwest side of Ford Island, Pearl City, Honolulu County, HI

  3. 48 CFR 225.7016 - Restriction on Ballistic Missile Defense research, development, test, and evaluation.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 3 2010-10-01 2010-10-01 false Restriction on Ballistic Missile Defense research, development, test, and evaluation. 225.7016 Section 225.7016 Federal Acquisition... Acquisition 225.7016 Restriction on Ballistic Missile Defense research, development, test, and evaluation....

  4. Computer assessment of electromagnetic means of detecting approaching cruise missiles

    SciTech Connect

    Burke, G.J.; King, R.J.; Lytle, R.J.; Miller, E.K.

    1983-11-01

    Numerical modeling of Beverage and monopole antennas shows the fields of both antennas to have a similar dependence on range and height above ground, with the Beverage antenna having slightly greater gain in the forward direction due to its directivity. The use of multiple Beverage antennas closely spaced was found to increase the efficiency and gain in the forward direction for short Beverage antennas. For the longer antenna considered for the cruise missile radar, the decrease in directivity for two closely spaced antennas reduced the forward gain.

  5. Renewable Energy Opportunities at White Sands Missile Range, New Mexico

    SciTech Connect

    Chvala, William D.; Solana, Amy E.; States, Jennifer C.; Warwick, William M.; Weimar, Mark R.; Dixon, Douglas R.

    2008-09-01

    The document provides an overview of renewable resource potential at White Sands Missile Range (WSMR) based primarily upon analysis of secondary data sources supplemented with limited on-site evaluations. The effort was funded by the U.S. Army Installation Management Command (IMCOM) as follow-on to the 2005 DoD Renewable Energy Assessment. This effort focuses on grid-connected generation of electricity from renewable energy sources and also ground source heat pumps (GSHPs) for heating and cooling buildings, as directed by IMCOM.

  6. 48 CFR 252.228-7005 - Accident reporting and investigation involving aircraft, missiles, and space launch vehicles.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... investigation involving aircraft, missiles, and space launch vehicles. 252.228-7005 Section 252.228-7005 Federal... investigation involving aircraft, missiles, and space launch vehicles. As prescribed in 228.370(d), use the following clause: Accident Reporting and Investigation Involving Aircraft, Missiles, and Space...

  7. Computer aided design and manufacturing of composite propfan blades for a cruise missile wind tunnel model

    NASA Technical Reports Server (NTRS)

    Thorp, Scott A.; Downey, Kevin M.

    1992-01-01

    One of the propulsion concepts being investigated for future cruise missiles is advanced unducted propfans. To support the evaluation of this technology applied to the cruise missile, a joint DOD and NASA test project was conducted to design and then test the characteristics of the propfans on a 0.55-scale, cruise missile model in a NASA wind tunnel. The configuration selected for study is a counterrotating rearward swept propfan. The forward blade row, having six blades, rotates in a counterclockwise direction, and the aft blade row, having six blades, rotates in a clockwise direction, as viewed from aft of the test model. Figures show the overall cruise missile and propfan blade configurations. The objective of this test was to evaluate propfan performance and suitability as a viable propulsion option for next generation of cruise missiles. This paper details the concurrent computer aided design, engineering, and manufacturing of the carbon fiber/epoxy propfan blades as the NASA Lewis Research Center.

  8. Preventing ballistic missile proliferation: Lessons from Iraq. Master`s thesis

    SciTech Connect

    Talay, B.J.

    1996-12-01

    This thesis examines the case of Iraq to assess the performance of the missile nonproliferation regime since 1970. By analyzing the methods used by Iraq to obtain missile systems and missile technology, this thesis assesses the ability of the international community to prevent ballistic missile proliferation. Understanding Iraq`s past capabilities as well as its post-war efforts to rebuild weapons programs and procurement networks, this thesis provides suggestions for improving the regime`s performance. This thesis finds that (1) prior to 1992, the Missile Technology Control Regime (MTCR) failed in its attempts to prevent proliferation; (2) the existence of the MTCR, while necessary to slow proliferation, is not sufficient to prevent proliferation; and (3) additional enforcement is needed to counter weapons of mass destruction acquisition by resourceful and determined states.

  9. Comprehensive Guidance Programs That Work.

    ERIC Educational Resources Information Center

    Gysbers, Norman C.; And Others

    This monograph describes how the comprehensive guidance model is transforming elementary-secondary school guidance and counseling programs in schools across the country. It incorporates the ideas and experiences of 12 guidance program developers in the actual use of the comprehensive guidance model in diverse school and cultural settings. The book…

  10. Passive millimetre wave imaging for ballistic missile launch detection

    NASA Astrophysics Data System (ADS)

    Higgins, Christopher J.; Salmon, Neil A.

    2008-10-01

    QinetiQ has used a suite of modelling tools to predict the millimetric plume signatures from a range of ballistic missile types, based on the accepted theory that Bremsstrahlung emission, generated by the collision of free electrons with neutral species in a rocket motor plume, is the dominant signature mechanism. Plume signatures in terms of radiation temperatures varied from a few hundred Kelvin to over one thousand Kelvin, and were predicted to be dependent on emission frequency, propellant type and missile thrust. Two types of platform were considered for the passive mmw imager launch detection system; a High Altitude Platform Station (HAPS) and a satellite based platform in low, mid and geosynchronous earth orbits. It was concluded that the optimum operating frequency for a HAPS based imager would be 35GHz with a 4.5m aperture and a sensitivity of 20mK providing visibility through 500 vertical feet of cloud. For a satellite based platform with a nadir view, the optimum frequency is 220 GHz. With such a system, in a low earth orbit at an altitude of 320km, with a sensitivity of 20mK, a 29cm aperture would be desirable.

  11. Ionospheric effects of the missile destruction on 9 December 2009

    NASA Astrophysics Data System (ADS)

    Kozlovsky, Alexander; Shalimov, Sergey; Lukianova, Renata; Lester, Mark

    2014-05-01

    We report on ionosonde and meteor radar observations made in Sodankylä Geophysical Observatory (SGO, 67°22'N, 26°38'E, Finland) on 9 December 2009, during a test launch of the Russian solid propellant military missile. Due to a technical problem, the missile was self-destroyed around 07 UT at an ionospheric height (near 200 km altitude) over the Kola Peninsula (Russia), at a distance about 500 km to east from the observatory. Products of the explosion were spread into a large area and reached the region of SGO meteor radar observations in about 2 h (around 09 UT). After about 3 h (around 10 UT), a sporadic E layer presumably composed of the remains including long-lived metallic (aluminum and its oxides) ions, was observed near the zenith of the SGO ionosonde. We discuss possible mechanisms accounting for transport of the remains. (1) Since the event occurred during a long-lasting period of extremely low solar and magnetic activity, the ionospheric electric field was unlikely to play a substantial role in the transport of the remains and sporadic E layer formation. (2) The horizontal transport of the remains cannot be explained by the neutral winds based on empirical models. (3) Theoretical estimations suggest that the observed transport could be due to thermospheric turbulence.

  12. Six-degree-of-freedom missile simulation using the ADI AD 100 digital computer and ADSIM simulation language

    NASA Technical Reports Server (NTRS)

    Zwaanenburg, Koos

    1989-01-01

    The use of an AD 100 computer and the ADSIM language in the six-degree-of-freedom digital simulation of an air-to-ground missile is illustrated. The missile is launched from a moving platform, typically a helicopter, and is capable of striking a mobile target up to 10 kilometers away. The missile could be any tactical missile. The performance numbers of the AD 100 show that it is possible to implement a high performance missile model in a real-time simulation without the problems associated with an implementation on a general purpose computer using FORTRAN.

  13. Vocational Guidance and the Labour Market: Guidance to Transform or Guidance to Domesticate?

    ERIC Educational Resources Information Center

    Kann, Ulla

    1988-01-01

    Explores the conflict in guidance arising from the desire to consider the needs of society while guaranteeing individual freedom of choice. Discusses the theoretical basis of vocational guidance. Gives examples of "domestication" and "transformation" approaches to guidance and discusses the consequences of viewing guidance as a change strategy.(KO)

  14. History of flight motion simulators used for hardware-in-the-loop testing of missile systems

    NASA Astrophysics Data System (ADS)

    Carter, John M.; Willis, Kenneth E.

    1998-07-01

    All hardware-in-the-loop (HWIL) missile simulations use motion platforms that position the missile seeker and simulated target to relative positions and motions that reproduce a live engagement. These motion platforms are usually called Flight Motion Simulators (FMS). Real-time control computers manage the engagement by simulating the aerodynamic and kinematic responses the missile anticipates, and commanding the missile and target motions to simulate the engagement. The advantages of this technique over live firings are well known: shorter development time, reduced development cost, greater variety in the test scenarios, and generation of objective, measurable, and repeatable criteria for subsystem and system evaluation. This paper focuses on the history of the FMS used in HWIL missile testing and the current applications of these systems. Systems with up to nine axes of rotary motion have been developed for infrared missile seeker simulation, and large target positioning systems have been deployed for RF and point IR target movement. As digital computers have become more powerful and semiconductor infrared scene generation systems developed, new demands have been placed on the FMS. Several of these applications are described. The use of aeroload simulators to study the response of missile aerodynamic control surfaces is also briefly described.

  15. A three-dimensional robust nonlinear terminal guidance law with ISS finite-time convergence

    NASA Astrophysics Data System (ADS)

    Li, Guilin; Ji, Haibo

    2016-05-01

    This paper presents a novel three-dimensional nonlinear terminal guidance law with finite-time convergence for intercepting manoeuvring targets. Different from the usual method of decoupling the missile-target relative motion into two-dimensional planes, this law is designed via using the coupled dynamics. The guidance law is derived based on the theory of finite-time input-to-state stability (ISS), which needs no assumption of the linearisation and the estimation of target accelerations. Under this law, the line-of-sight angular rates can be stabilised to a small domain of convergence around zero in finite time. The convergence rate and convergence domain can be adjusted by changing the guidance parameters. First, a sufficient condition on finite-time ISS of the guidance system is given, and is subsequently used to design the guidance law. Finally, simulation results are provided to show that the proposed guidance law possesses fast convergence rate and strong robustness to target manoeuvres.

  16. Adaptive nonlinear control of missiles using neural networks

    NASA Astrophysics Data System (ADS)

    McFarland, Michael Bryan

    Research has shown that neural networks can be used to improve upon approximate dynamic inversion for control of uncertain nonlinear systems. In one architecture, the neural network adaptively cancels inversion errors through on-line learning. Such learning is accomplished by a simple weight update rule derived from Lyapunov theory, thus assuring stability of the closed-loop system. In this research, previous results using linear-in-parameters neural networks were reformulated in the context of a more general class of composite nonlinear systems, and the control scheme was shown to possess important similarities and major differences with established methods of adaptive control. The neural-adaptive nonlinear control methodology in question has been used to design an autopilot for an anti-air missile with enhanced agile maneuvering capability, and simulation results indicate that this approach is a feasible one. There are, however, certain difficulties associated with choosing the proper network architecture which make it difficult to achieve the rapid learning required in this application. Accordingly, this technique has been further extended to incorporate the important class of feedforward neural networks with a single hidden layer. These neural networks feature well-known approximation capabilities and provide an effective, although nonlinear, parameterization of the adaptive control problem. Numerical results from a six-degree-of-freedom nonlinear agile anti-air missile simulation demonstrate the effectiveness of the autopilot design based on multilayer networks. Previous work in this area has implicitly assumed precise knowledge of the plant order, and made no allowances for unmodeled dynamics. This thesis describes an approach to the problem of controlling a class of nonlinear systems in the face of both unknown nonlinearities and unmodeled dynamics. The proposed methodology is similar to robust adaptive control techniques derived for control of linear

  17. A ram-air-spoiler roll stabilization device for forward control cruciform missiles

    NASA Technical Reports Server (NTRS)

    Blair, A. B., Jr.; Sawyer, W. C.; Jackson, C. M., Jr.

    1978-01-01

    An experimental investigation has been made at supersonic Mach numbers to determine the feasibility of using a ram-air-spoiler roll control device on a typical canard control missile configuration. As a basis for roll control comparisons, conventional aileron controls on the tail fins were also tested. Results are presented which indicate that the addition of nacelles on the missile tail fins resulted in satisfactory roll control effectiveness and only small changes in basic missile stability. The ram-air-spoiler roll control effectiveness is relatively constant over the range of vehicle attitudes and Mach numbers investigated.

  18. Origins of the Strategic Defense Initiative: Ballistic Missile Defense, 1944-1983. Final report

    SciTech Connect

    Baucom, D.R.

    1989-12-01

    America's ballistic missile defense program may be said to have its roots in the V-2 attacks on London in 1944. This document traces the development of antiballistic missile defense policy from the V-2 attacks up to President Reagan's 1983 speech announcing the new strategic defense initiative. The history follows the policy debates from the NIKE-X, SALT I and SALT II, the ABM Treaty, and SAFEGUARD through research and development innovations in the areas of computers, optical sensors, interceptors, and directed energy weapons. The emergence of political organizations and individuals who either opposed or championed ballistic missile defense is also included.

  19. Hypersonic airbreathing missile concepts under study at NASA Langley Research Center

    NASA Technical Reports Server (NTRS)

    Hunt, J. L.; Johnston, P. J.; Cubbage, J. M.; Dillon, J. L.; Richie, C. B.; Marcum, D. C., Jr.; Carlson, C. H.

    1982-01-01

    The design and performance of several tactical and strategic hypersonic airbreathing missile concepts under study at the NASA Langley Research Center are discussed from an evolutionary perspective. A mid- and chin inlet missile design, constrained to the Navy's vertical box launcher, was investigated; a performance comparison is presented that is favorable to the mid-inlet approach. Parasol wing, confined flow field, and spatula-like cruise missile configurations were examined with strategic applications in mind. The preliminary results are encouraging with respect to aerodynamic and volumetric efficiency and choice of engine integration schemes.

  20. Quality in Careers Guidance.

    ERIC Educational Resources Information Center

    Plant, Peter

    This paper examines quality issues in career guidance, counseling, and information services in Europe and elsewhere from a range of different perspectives related to economic, ethical, and/or effectiveness criteria. Selected examples from the European Union member states, Canada, and the United States are used to illustrate how quality is…

  1. Vocational Development and Guidance.

    ERIC Educational Resources Information Center

    Tennyson, W. Wesley; And Others

    The vocational education volume considers questions of career development, the role of guidance in the school, vocational training, the relation of self-concept to vocational choice, and occupational information. Twenty-six papers deal with theories of vocational behavior, the success of vocational education programs, and testing information.…

  2. Regulatory guidance document

    SciTech Connect

    1994-05-01

    The Office of Civilian Radioactive Waste Management (OCRWM) Program Management System Manual requires preparation of the OCRWM Regulatory Guidance Document (RGD) that addresses licensing, environmental compliance, and safety and health compliance. The document provides: regulatory compliance policy; guidance to OCRWM organizational elements to ensure a consistent approach when complying with regulatory requirements; strategies to achieve policy objectives; organizational responsibilities for regulatory compliance; guidance with regard to Program compliance oversight; and guidance on the contents of a project-level Regulatory Compliance Plan. The scope of the RGD includes site suitability evaluation, licensing, environmental compliance, and safety and health compliance, in accordance with the direction provided by Section 4.6.3 of the PMS Manual. Site suitability evaluation and regulatory compliance during site characterization are significant activities, particularly with regard to the YW MSA. OCRWM`s evaluation of whether the Yucca Mountain site is suitable for repository development must precede its submittal of a license application to the Nuclear Regulatory Commission (NRC). Accordingly, site suitability evaluation is discussed in Chapter 4, and the general statements of policy regarding site suitability evaluation are discussed in Section 2.1. Although much of the data and analyses may initially be similar, the licensing process is discussed separately in Chapter 5. Environmental compliance is discussed in Chapter 6. Safety and Health compliance is discussed in Chapter 7.

  3. The use of tags in monitoring limits on mobile missiles

    SciTech Connect

    Fetter, S.

    1987-03-01

    Three tagging systems were considered in this paper: as a supplement to on-site inspection (OSI), as a supplement to national technical means (NTM), and as a supplement to site surveillance systems. Each system would require a different type of tag, perhaps ranging from microchip tags with infrared transponders to navigation receivers. Use of tags as a supplement to OSIs may be the simplest system to implement because it places the least demands on technology. Tags may make OSI more acceptable by replacing humans with remote sensors, thereby decreasing the perceived potential for espionage. Using tags as a supplement to NTM decreases the necessity for human OSI even further, but places higher demands on technology and may affect the normal operation of deployment areas. Site surveillance systems using tags have the potential for excellent missile verification, but they may be excessively intrusive and expensive, and could have a large effect on the normal operation of declared facilities.

  4. Enhancing Access to Vocational Guidance.

    ERIC Educational Resources Information Center

    Clayton, Pam

    1998-01-01

    Issues in vocational guidance for adults include lack of provision, especially for unemployed or disadvantaged people and the need to publicize existing excellent guidance services and demonstrate their usefulness to this population. (SK)

  5. Radar signal analysis of ballistic missile with micro-motion based on time-frequency distribution

    NASA Astrophysics Data System (ADS)

    Wang, Jianming; Liu, Lihua; Yu, Hua

    2015-12-01

    The micro-motion of ballistic missile targets induces micro-Doppler modulation on the radar return signal, which is a unique feature for the warhead discrimination during flight. In order to extract the micro-Doppler feature of ballistic missile targets, time-frequency analysis is employed to process the micro-Doppler modulated time-varying radar signal. The images of time-frequency distribution (TFD) reveal the micro-Doppler modulation characteristic very well. However, there are many existing time-frequency analysis methods to generate the time-frequency distribution images, including the short-time Fourier transform (STFT), Wigner distribution (WD) and Cohen class distribution, etc. Under the background of ballistic missile defence, the paper aims at working out an effective time-frequency analysis method for ballistic missile warhead discrimination from the decoys.

  6. Ballistic Missile Defense: National Security and the High Frontier of Space.

    ERIC Educational Resources Information Center

    Adragna, Steven P.

    1985-01-01

    Ballistic missile defense is discussed, and the rationale behind the proposal to place defensive weapons in space is examined. Strategic defense is a national security, political, and moral imperative. (RM)

  7. A low cost maritime control aircraft-ship-weapons system. [antiship missile defense

    NASA Technical Reports Server (NTRS)

    Fluk, H.

    1981-01-01

    It is pointed out that the long-range antiship standoff missile is emerging as the foremost threat on the seas. Delivered by high speed bombers, surface ships, and submarines, a missile attack can be mounted against selected targets from any point on the compass. An investigation is conducted regarding the configuration of a system which could most efficiently identify and destroy standoff threats before they launch their weapons. It is found that by using ships for carrying and launching missiles, and employing aircraft with a powerful radar only for search and missile directing operations, aircraft cost and weight can be greatly reduced. The employment of V/STOL aircraft in preference to other types of aircraft makes it possible to use ships of smaller size for carrying the aircraft. However, in order to obtain an all-weather operational capability for the system, ships are selected which are still big enough to display the required stability in heavy seas.

  8. 76 FR 73600 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to Missile Launch...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-29

    ..., were issued on June 2, 2009, and remain in effect until June 2, 2014 (74 FR 26580, June 3, 2009). For... acoustic monitoring or missile launches and visual monitoring of pinnipeds. The Navy submitted their...

  9. The Commercial Application of Missile/Space Technology, Parts 1 and 2

    NASA Technical Reports Server (NTRS)

    Welles, John G.; Marts, Lloyd G.; Waterman, Robert H., Jr.; Gilmore, John S.; Venuti, Robert

    1963-01-01

    This report is concerned with the transfer of technology from missile and space programs to non-missile/space applications in the United States. It presents the findings of a University of Denver Research Institute study sponsored by a National Aeronautics and Space Administration (NASA) grant awarded in November 1961. Initial stimulation for the unsolicited proposal leading to this study came from a 1960 Brookings Institution report to NASA, Proposed Studies on the Implications of Peaceful Space Activities for Human Affairs.

  10. Missile Captive Carry Monitoring and Helicopter Identification Using a Capacitive Microelectromechanical Systems Accelerometer

    SciTech Connect

    Hatchell, Brian K.; Mauss, Fredrick J.; Amaya, Ivan A.; Skorpik, James R.; Silvers, Kurt L.; Marotta, Steve

    2012-03-27

    Military missiles are exposed to many sources of mechanical vibration that can affect system reliability, safety, and mission effectiveness. The U. S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC) has been developing missile health monitoring systems to assess and improve reliability, reduce life cycle costs, and increase system readiness. One of the most significant exposures to vibration occurs when the missile is being carried by a helicopter or other aviation platform, which is a condition known as captive carry. Recording the duration of captive carry exposure during the missile’s service life can enable the implementation of predictive maintenance and resource management programs. Since the vibration imparted by each class of helicopter varies in frequency and amplitude, tracking the vibration exposure from each helicopter separately can help quantify the severity and harmonic content of the exposure. Under the direction of AMRDEC staff, engineers at the Pacific Northwest National Laboratory have developed a Captive Carry Health Monitor (CCHM) for the Hellfire II missile. The CCHM is an embedded usage monitoring device installed on the outer skin of the Hellfire II missile to record the cumulative hours the host missile has been in captive carry mode. To classify the vibration by class of helicopter, the CCHM analyzes the amplitude and frequency content of the vibration with the Goertzel algorithm to detect the presence of distinctive rotor harmonics. Cumulative usage data are accessible in theater from an external display; monthly usage histograms are accessible through an internal download connector. This paper provides an overview of the CCHM electrical and package design, describes field testing and data analysis techniques used to monitor captive carry identify and the class of helicopter, and discusses the potential application of missile health and usage data for real-time reliability analysis and fleet management.

  11. Vocational Guidance and Human Development.

    ERIC Educational Resources Information Center

    Herr, Edwin L., Ed.

    New knowledge and practices in the area of vocational guidance and human growth and development that have occurred since 1964 as well as future directions for guidance, both nationally and internationally, are covered in this second volume of a decennial volume series sponsored by the National Vocational Guidance Association to up-date the…

  12. Trajectory shaping rendezvous guidance

    NASA Astrophysics Data System (ADS)

    Klumpp, A. R.

    The Space Station will bring a great increase in rendezvous traffic. Formerly, rendezvous has been expensive in terms of time and crew involvement. Multiple trajectory adjustments on separate orbits have been required to meet safety, lighting, and geometry requirements. This paper describes a new guidance technique in which the approach trajectory is shaped by a sequence of velocity increments in order to satisfy multiple constraints within a single orbit. The approach phase is planned before the mission, leaving a group of free parameters that are optimized by onboard guidance. Fuel penalties are typically a few percent, compared to unshaped Hohmann transfers, and total fuel costs can be less than those of more time-consuming ways of meeting the same requirements.

  13. Solutions of thin-layer Navier-Stokes equations for missile configurations

    NASA Astrophysics Data System (ADS)

    Pourtakdoust, Seid Hossein

    1989-12-01

    Solutions of the thin-layer Navier-Stokes equations were obtained for two typical missile bodies as well as two complete missile configurations. The finite-differenced three-dimensional equations are solved using a modified NASA Ames solver code on a body-fitted curvi-linear grid system developed in conjunction with the flowfield solver. The grid program is based on the method of algebraic interpolation and is capable of generating three-dimensional grid systems for missile bodies and finned-missiles having up to eight control surfaces. The numerical procedure is based on an implicit approximate factorization algorithm employing a multi-grid approach in the simulation of flow about complex finned-missile configurations. The present procedures are proven effective in dealing with complete missile configurations flying at high angles of attack. The predicted aerodynamic loading coefficients and pressure distributions match the available wind-tunnel data with good accuracy. Flow non-linearities such as shock, streamwise and cross-flow separations, and reverse flow were detected and verified with the available experimental reports. Leading-edge separation and classical patterns of vortical flow were also numerically obtained and studied for interaction effects. The Mach number and Reynolds number effects on the convergence of the numerical process are also discussed.

  14. Cooperative Monitoring Center Occasional Paper/9: De-Alerting Strategic Ballistic Missiles

    SciTech Connect

    Connell, Leonard W.; Edenburn, Michael W.; Fraley, Stanley K.; Trost, Lawrence C.

    1999-03-01

    This paper presents a framework for evaluating the technical merits of strategic ballistic missile de-alerting measures, and it uses the framework to evaluate a variety of possible measures for silo-based, land-mobile, and submarine-based missiles. De-alerting measures are defined for the purpose of this paper as reversible actions taken to increase the time or effort required to launch a strategic ballistic missile. The paper does not assess the desirability of pursuing a de-alerting program. Such an assessment is highly context dependent. The paper postulates that if de-alerting is desirable and is used as an arms control mechanism, de-alerting measures should satisfy specific cirteria relating to force security, practicality, effectiveness, significant delay, and verifiability. Silo-launched missiles lend themselves most readily to de-alerting verification, because communications necessary for monitoring do not increase the vulnerabilty of the weapons by a significant amount. Land-mobile missile de-alerting measures would be more challenging to verify, because monitoring measures that disclose the launcher's location would potentially increase their vulnerability. Submarine-launched missile de-alerting measures would be extremely challlenging if not impossible to monitor without increasing the submarine's vulnerability.

  15. Countermeasure effectiveness against an intelligent imaging infrared anti-ship missile

    NASA Astrophysics Data System (ADS)

    Gray, Greer J.; Aouf, Nabil; Richardson, Mark; Butters, Brian; Walmsley, Roy

    2013-02-01

    Ship self defense against heat-seeking anti-ship missiles is of great concern to modern naval forces. One way of protecting ships against these threats is to use infrared (IR) offboard countermeasures. These decoys need precise placement to maximize their effectiveness, and simulation is an invaluable tool used in determining optimum deployment strategies. To perform useful simulations, high-fidelity models of missiles are required. We describe the development of an imaging IR anti-ship missile model for use in countermeasure effectiveness simulations. The missile model's tracking algorithm is based on a target recognition system that uses a neural network to discriminate between ships and decoys. The neural network is trained on shape- and intensity-based features extracted from simulated imagery. The missile model is then used within ship-decoy-missile engagement simulations, to determine how susceptible it is to the well-known walk-off seduction countermeasure technique. Finally, ship survivability is improved by adjusting the decoy model to increase its effectiveness against the tracker.

  16. Environmental guidance regulatory bulletin

    SciTech Connect

    1997-01-31

    This document describes the background on expanding public participation in the Resource Conservation and Recovery Act and DOE`s response. The bulletin also describes the changes made by the final rule to existing regulations, guidance provided by EPA in the preamble and in the revised RCRA Public Participation Manual, the relationship between public participation and environmental justice, and DOE`s recent public participation and environmental justice initiatives.

  17. Superconducting matching networks in monopole antennas. Final report, 1 Aug 89-31 Jul 91

    SciTech Connect

    Piatnicia, A.Y.; Talisa, S.H.; Buckley, M.J.; Gavaler, J.R.; Janocko, M.A.

    1991-08-01

    The goals of this program were to demonstrate the performance advantages of UHF Super Directive Array using a monopole antenna matching network made of high temperature superconducting (HTS) material over a monopole antenna matching network made of gold and to demonstrate the feasibility of using HTS material matching networks to feed a two element electrically small superdirective monopole array. In both cases only the matching networks were made of HTS material. The radiators were made of silver, copper, and steel. The electrically small monopole antenna and the electrically small element monopole antenna array were operated in the UHF band because the need exists for a high efficiency electrically small array operating in the UHF range as part of a multispectral seeker of an air-to-air missile. To date no antenna system consisting of electrically small conventional metal monopole radiators and HTS material matching networks has been demonstrated. An electrically small superdirective monopole array with superconducting matching networks is a candidate for use in an air-to-air missile as part of a multispectral seeker. The seeker must have a multispectral capability in order to successfully engage advanced Low Observable aircraft and missiles. The air-to-air missile guidance is initially provided by a surveillance and control aircraft.

  18. Recent advances in antitank missile systems and technologies

    NASA Astrophysics Data System (ADS)

    Iyer, Narayana R.

    1999-11-01

    This paper focuses on the recent advances in tactical Anti- tank (ATGM) systems and related technologies. The growth profile of ATGM systems and related technologies has been discussed with special emphasis on technologies pertaining to guidance systems. 'Fire and forget' and 'Top attach' capabilities are the most important operational requirements of the third generation ATGM systems. Realization of 'Fire and forget' capability for tactical ATGMs calls for use of a passive or active homing system. The need for such a system has been the main driving factor for mobilizing the advanced technologies relating to IR and Millimetric Wave seeker based guidance systems. Generic design considerations and system constraints as well as technological aspects of these two types of guidance systems are covered. The 'Top attack' requirement calls for optimization of suitable trajectory schemes and it also impose design constants, mainly on the homing seeker. Use of tandem shaped charge warhead is essential to defeat modern tanks equipped with Explosive Reactive Armor. The implications of using the tandem shaped charge warhead on the design of the seeker as well as at system level design are briefly analyzed. In the concluding part, the emerging technological trends relating to ATGM systems with focus on guidance systems are presented.

  19. Preliminary scramjet design for hypersonic airbreathing missile application

    NASA Technical Reports Server (NTRS)

    Carlson, C. H.

    1983-01-01

    A conceptual design study of a scramjet engine was conducted for a hypersonic surface to air missile (HYSAM). The definition of the engine was based upon the requirements of accelerating the HYSAM from Mach 4 at 20,000 feet to Mach 6 at 100,000 feet and the cruise conditions at Mach 6. The resulting external and internal environmental conditions were used by various engineering disciplines performing design, stress and heat transfer analysis. A detailed structural analysis was conducted along with an indepth thermal analysis. Structurally all the components within the system exhibit positive margins of safety. A feasible concept was defined which uses state-of-the-art materials and existing TMC technology. The engine basically consists of a three dimensional carbon/carbon combustor/nozzle secured to an FS-85 columbium inlet. The carbon/carbon liner is sheathed with carbon felt insulation to thermally protect the FS-85 structure and skin. The thermal analysis of the engine indicates that a thermally viable configuration exists.

  20. A report on missile injuries in Cyprus 1974.

    PubMed

    Malpass, C P; Winter, J S

    1976-06-01

    This paper details the experiences of the Princess Mary's Royal Air Force Hospital, Akrotiri (TPMH), during the last 6 months of 1974. TPMH was at that time a small hospital (120 beds) with a clinical staff of 17 situated in the south of Cyprus (fig. 1). The series comprises 71 patients injured by bullets, shrapnel, bomb-blasts or mines, drawn from British personnel, United Nations Forces and the local Cypriot military and civilian population, resulting from the coup d'état of 15 July 1974 and the subsequent Turkish invasion and air attacks. The casualties were often severely wounded beyound the capabilities of the local hospitals. They were mostly admitted during a 2-week period, but many required multiple operations extending over the next 3 or 4 months, and altogether 119 operations were carried out on 41 patients at TPMH. The organization of the limited resources of the medical, nursing and supporting staff is outlined. The correct treatment of missile wounds is emphasized. Resuscitation, wound excision, splintage and delayed suture or grafting are essential. Minimal morbidity and mortality are gained by a practised approach to the compounded results of violence. PMID:1276680

  1. Air intakes for a probative missile of rocket ramjet

    NASA Technical Reports Server (NTRS)

    Laruelle, G.

    1984-01-01

    The methods employed to test air intakes for a supersonic guided ramjet powered missile being tested by ONERA are described. Both flight tests and wind tunnel tests were performed on instrumented rockets to verify the designs. Consideration as given to the number of intakes, with the goal of delivering the maximum pressure to the engine. The S2, S4, and S5 wind tunnels were operated at Mach nos. 1.5-3 for the tests, which were compartmentalized into fuselage-intake interaction, optimization of the intake shapes, and the intake performance. Tests were performed on the length and form of the ogive, the presence of grooves, the height of traps in the boundary layer, the types and number of intakes and the lengths and forms of diffusers. Attention was also given to the effects of sideslip, effects of the longitudinal and circumferential positions of the intakes were also examined. Near optimum performance was realized during Mach 2.2 test flights of the prototype rockets.

  2. Solar-blind ultraviolet optical system design for missile warning

    NASA Astrophysics Data System (ADS)

    Chen, Yu; Huo, Furong; Zheng, Liqin

    2015-03-01

    Solar-blind region of Ultraviolet (UV) spectrum has very important application in military field. The spectrum range is from 240nm to 280nm, which can be applied to detect the tail flame from approaching missile. A solar-blind UV optical system is designed to detect the UV radiation, which is an energy system. iKon-L 936 from ANDOR company is selected as the UV detector, which has pixel size 13.5μm x 13.5 μm and active image area 27.6mm x 27.6 mm. CaF2 and F_silica are the chosen materials. The original structure is composed of 6 elements. To reduce the system structure and improve image quality, two aspheric surfaces and one diffractive optical element are adopted in this paper. After optimization and normalization, the designed system is composed of five elements with the maximum spot size 11.988μ m, which is less than the pixel size of the selected CCD detector. Application of aspheric surface and diffractive optical element makes each FOV have similar spot size, which shows the system almost meets the requirements of isoplanatic condition. If the focal length can be decreased, the FOV of the system can be enlarged further.

  3. An affinity-directed protein missile system for targeted proteolysis

    PubMed Central

    Fulcher, Luke J.; Macartney, Thomas; Bozatzi, Polyxeni; Hornberger, Annika; Rojas-Fernandez, Alejandro

    2016-01-01

    The von Hippel–Lindau (VHL) protein serves to recruit the hypoxia-inducible factor alpha (HIF1α) protein under normoxia to the CUL2 E3 ubiquitin ligase for its ubiquitylation and degradation through the proteasome. In this report, we modify VHL to engineer an affinity-directed protein missile (AdPROM) system to direct specific endogenous target proteins for proteolysis in mammalian cells. The proteolytic AdPROM construct harbours a cameloid anti-green fluorescence protein (aGFP) nanobody that is fused to VHL for either constitutive or tetracycline-inducible expression. For target proteins, we exploit CRISPR/Cas9 to rapidly generate human kidney HEK293 and U2OS osteosarcoma homozygous knock-in cells harbouring GFP tags at the VPS34 (vacuolar protein sorting 34) and protein associated with SMAD1 (PAWS1, aka FAM83G) loci, respectively. Using these cells, we demonstrate that the expression of the VHL-aGFP AdPROM system results in near-complete degradation of the endogenous GFP-VPS34 and PAWS1-GFP proteins through the proteasome. Additionally, we show that Tet-inducible destruction of GFP-VPS34 results in the degradation of its associated partner, UVRAG, and reduction in levels of cellular phosphatidylinositol 3-phosphate. PMID:27784791

  4. A decade of missile-induced vascular trauma.

    PubMed Central

    D'Sa, A. A.

    1982-01-01

    During 10 years of serious strife the Royal Victoria Hospital, Belfast, has dealt with trauma inflicted by a wide variety of missiles. Injuries involving 316 vessels were sustained by 192 patients. A group of "knee-cappings' accounted for a large proportion of popliteal vessel injuries. A majority of patients also suffered damage to other regions of the body. Hypotension was a notable feature and several patients arrived in extremis, particularly those with injuries to a major vessel trunks and vital organs. The benefits of rapid evacuation in relation to ischaemia time are discussed. The operative management of a wide range of arterial and venous injuries is described. The use of simple and compound vein grafts allowed adequate excision of damaged vessels. The advantages of meticulous repair, timely fasciotomy, and early reintervention are reflected in the results, contributing to the small lower-lib amputation rate of 5.1%. Images fig. 2 fig. 3 fig. 4 fig. 5 fig. 6 fig. 7 fig. 8 PMID:7055366

  5. Guidance of Nonlinear Systems

    NASA Technical Reports Server (NTRS)

    Meyer, George

    1997-01-01

    The paper describes a method for guiding a dynamic system through a given set of points. The paradigm is a fully automatic aircraft subject to air traffic control (ATC). The ATC provides a sequence of way points through which the aircraft trajectory must pass. The way points typically specify time, position, and velocity. The guidance problem is to synthesize a system state trajectory which satisfies both the ATC and aircraft constraints. Complications arise because the controlled process is multi-dimensional, multi-axis, nonlinear, highly coupled, and the state space is not flat. In addition, there is a multitude of possible operating modes, which may number in the hundreds. Each such mode defines a distinct state space model of the process by specifying the state space coordinatization, the partition of the controls into active controls and configuration controls, and the output map. Furthermore, mode transitions must be smooth. The guidance algorithm is based on the inversion of the pure feedback approximations, which is followed by iterative corrections for the effects of zero dynamics. The paper describes the structure and modules of the algorithm, and the performance is illustrated by several example aircraft maneuvers.

  6. Guidance of Nonlinear Systems

    NASA Technical Reports Server (NTRS)

    Meyer, George; Null, Cynthia H. (Technical Monitor)

    1996-01-01

    The paper describes a method for guiding a dynamic system through a given set of points. The paradigm is a fully automatic aircraft subject to air traffic control (ATC). The ATC provides a sequence of way points through which the aircraft trajectory must pass. The way points typically specify time, position, and velocity. The guidance problem is to synthesize a system state trajectory which satisfies both the ATC and aircraft constraints. Complications arise because the controlled process is multi-dimensional, multi-axis, nonlinear, highly coupled, and the state space is not flat. In addition, there is a multitude of possible operating modes, which may number in the hundreds. Each such mode defines a distinct state space model of the process by specifying the state space coordination, the partition of the controls into active controls and configuration controls, and the output map. Furthermore, mode transitions must be smooth. The guidance algorithm is based on the inversion of the pure feedback approximations, which is followed by iterative corrections for the effects of zero dynamics. The paper describes the structure and modules of the algorithm, and the performance is illustrated by several example aircraft maneuvers.

  7. Controls and guidance: Space

    NASA Technical Reports Server (NTRS)

    Dibattista, John D.

    1988-01-01

    The Space Controls and Guidance Research and Technology Program is directed toward enabling the next generation of space transportation systems, large future spacecraft, and space systems such as the Space Station to have large communication antennas and high precision segmented reflector astrophysical telescopes. The new generation of transportation vehicles has demanding requirements to provide for an order of magnitude reduction in cost as well as an increase in capability. The future orbital facilities have demanding control requirements for pointing and stabilization, momentum management, build-up and growth accomodation, and disturbance management. To address these advanced requirements, the research and development program is designed to provide the generic technology base to support the implementation of advanced guidance, navigation, and control. The area of computational controls will be stressed in order to develop cost effective, high speed, high fidelity control system simulation and analysis and synthesis tools. The trust of this work will be to develop methods and software to enable analysis and real-time hardware-in-the-loop simulation of complex spacecraft for control design certification. To address future orbital facilities requirements, an advanced technology program is underway in system identification, distributed control, integrated controls/structures design methods, and advanced sensors and actuators. Because the behavior of large, light weight per unit area deployable/assembled spacecraft is greatly influenced by the ground environment, the testing and verification activity is both ground- and space-based.

  8. Bilinear tangent yaw guidance

    NASA Technical Reports Server (NTRS)

    Brusch, R. G.

    1979-01-01

    This paper presents a parametric yaw steering law which has been used to provide closed-loop yaw guidance for the launch of the HEAO (High Energy Astronomy Observatory) satellite mission using the Atlas/Centaur launch vehicle. This bilinear tangent steering law provides near optimal yaw steering for maneuvers requiring insertion into orbits with a specified inclination and node. Bilinear tangent steering is shown to be optimal in both the pitch and yaw planes when a uniform gravitational field is assumed. The conditions under which the general bilinear tangent laws degenerate into linear tangent and constant attitude laws are presented. The flight computer implementation of these laws in a rotating coordinate system using real-time integration of the equations of motion is detailed. Explicit solution of the parametric guidance equations requires the inflight solution of (2x2) two-point boundary value problems in the pitch and yaw planes. Excellent results are obtained even for very large (greater than 50 deg) out-of-plane steering angles.

  9. Volatile organic components of air samples collected from Vertical Launch Missile capsules. Summary report

    SciTech Connect

    Tappan, D.V.; Knight, D.R.; Heyder, E.; Weathersby, P.K.

    1988-09-27

    Gas chromatographic/mass spectroscopic analyses are presented for the volatile organic components found in air samples collected from the inboard vents from Vertical Launch System (VLS) missile capsules aboard a 688 class submarine. Similar analyses were also conducted for a sample of the ship's high pressure air used to fill the missile tubes. A wide variety of organics was detected in the air from the missile capsules; and while no unique components have yet been identified, a significant contribution has been shown to be made by pressure-ventilation of the VLS capsules into the submarine atmosphere which is already heavily laden with volatile organic compounds. The most apparent conclusion from these preliminary analyses is that the mixtures of organic components in the air within VLS missile capsules vary greatly from capsule to capsule (and probably from time to time). Many such samples need to be investigated to provide sufficient information to judge the seriousness of the possibility of venting toxic components into the submarine atmosphere during the maintenance or firing of VLS missiles.

  10. Full-scale turbine-missile-casing tests. Final report. [PWR; BWR

    SciTech Connect

    Yoshimura, H.R.; Schamaun, J.T.

    1983-01-01

    Results are presented of two full-scale tests simulating the impact of turbine disk fragments on simple ring and shell structures that represent the internal stator blade ring and the outer housing of an 1800-rpm steam turbine casing. The objective was to provide benchmark data on both the energy-absorbing mechanisms of the impact process and, if breakthrough occured, the exit conditions of the turbine missile. A rocket sled was used to accelerate a 1527-kg (3366-lb) segment of a turbine disk, which impacted a steel ring 12.7 cm (5 in.) thick and a steel shell 3.2 cm (1.25 in.) thick. The impact velocity of about 150 m/s (492 ft/s) gave a missile kinetic energy corresponding to the energy of a fragment from a postulated failure at the design overspeed (120% of operating speed). Depending on the orientation of the missile at impact, the steel test structure either slowed the missile to 60% of its initial translational velocity or brought it almost to rest (an energy reduction of 65 and 100%, respectively). The report includes structural and finite element analysis and data interpretation, estimates of energy during impact, missile displacement and velocity histories, and selected strain gage data.

  11. Use of noise attenuation modeling in managing missile motor detonation activities.

    PubMed

    McFarland, Michael J; Watkins, Jeffrey W; Kordich, Micheal M; Pollet, Dean A; Palmer, Glenn R

    2004-03-01

    The Sound Intensity Prediction System (SIPS) and Blast Operation Overpressure Model (BOOM) are semiempirical sound models that are employed by the Utah Test and Training Range (UTTR) to predict whether noise levels from the detonation of large missile motors will exceed regulatory thresholds. Field validation of SIPS confirmed that the model was effective in limiting the number of detonations of large missile motors that could potentially result in a regulatory noise exceedance. Although the SIPS accurately predicted the impact of weather on detonation noise propagation, regulators have required that the more conservative BOOM model be employed in conjunction with SIPS in evaluating peak noise levels in populated areas. By simultaneously considering the output of both models, in 2001, UTTR detonated 104 missile motors having net explosive weights (NEW) that ranged between 14,960 and 38,938 lb without a recorded public noise complaint. Based on the encouraging results, the U.S. Department of Defense is considering expanding the application of these noise models to support the detonation of missile motors having a NEW of 81,000 lb. Recent modeling results suggest that, under appropriate weather conditions, missile motors containing up to 96,000 lb NEW can be detonated at the UTTR without exceeding the regulatory noise limit of 134 decibels (dB).

  12. Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint.

    PubMed

    Wang, Xingliang; Zhang, Youan; Wu, Huali

    2016-03-01

    The problem of impact angle control guidance for a field-of-view constrained missile against non-maneuvering or maneuvering targets is solved by using the sliding mode control theory. The existing impact angle control guidance laws with field-of-view constraint are only applicable against stationary targets and most of them suffer abrupt-jumping of guidance command due to the application of additional guidance mode switching logic. In this paper, the field-of-view constraint is handled without using any additional switching logic. In particular, a novel time-varying sliding surface is first designed to achieve zero miss distance and zero impact angle error without violating the field-of-view constraint during the sliding mode phase. Then a control integral barrier Lyapunov function is used to design the reaching law so that the sliding mode can be reached within finite time and the field-of-view constraint is not violated during the reaching phase as well. A nonlinear extended state observer is constructed to estimate the disturbance caused by unknown target maneuver, and the undesirable chattering is alleviated effectively by using the estimation as a compensation item in the guidance law. The performance of the proposed guidance law is illustrated with simulations. PMID:26782929

  13. Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint.

    PubMed

    Wang, Xingliang; Zhang, Youan; Wu, Huali

    2016-03-01

    The problem of impact angle control guidance for a field-of-view constrained missile against non-maneuvering or maneuvering targets is solved by using the sliding mode control theory. The existing impact angle control guidance laws with field-of-view constraint are only applicable against stationary targets and most of them suffer abrupt-jumping of guidance command due to the application of additional guidance mode switching logic. In this paper, the field-of-view constraint is handled without using any additional switching logic. In particular, a novel time-varying sliding surface is first designed to achieve zero miss distance and zero impact angle error without violating the field-of-view constraint during the sliding mode phase. Then a control integral barrier Lyapunov function is used to design the reaching law so that the sliding mode can be reached within finite time and the field-of-view constraint is not violated during the reaching phase as well. A nonlinear extended state observer is constructed to estimate the disturbance caused by unknown target maneuver, and the undesirable chattering is alleviated effectively by using the estimation as a compensation item in the guidance law. The performance of the proposed guidance law is illustrated with simulations.

  14. Beyond Discipline to Guidance: A Primer on the Guidance Alternative.

    ERIC Educational Resources Information Center

    Gartrell, Dan

    As early childhood teachers apply principles of guidance rather than punishment in their classrooms, they face the challenge of avoiding a slippage into traditional discipline practices and transcending the punitive aspects of discipline. Guidance is designed to teach children democratic life skills and therefore goes beyond discipline. Teachers…

  15. Endangerment assessment guidance

    SciTech Connect

    Not Available

    1985-11-22

    The directive clarifies the requirement that an endangerment assessment be developed to support all administrative and judicial enforcement actions under Section 106 of the Comprehensive Environmental Response, Compensation, and Liability Act (CERCLA) and Section 7003 of the Resource Conservation and Recovery Act (RCRA). Before taking enforcement action under these provisions to abate the hazards or potential hazards at a site, the Environmental Protection Agency (EPA) must be able to properly document and justify its assertion that an imminent and substantial endangerment to public health or welfare or the environment may exist. The endangerment assessment provides this documentation and justification. The endangerment assessment is not necessary to support Section 104 actions. It also provides guidance on the content, timing, level of detail, format, and resources required for the preparation of endangerment assessments.

  16. 33 CFR 334.1390 - Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility. 334.1390 Section 334.1390 Navigation and Navigable... REGULATIONS § 334.1390 Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility....

  17. 33 CFR 334.1390 - Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility. 334.1390 Section 334.1390 Navigation and Navigable... REGULATIONS § 334.1390 Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility....

  18. 33 CFR 334.1390 - Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility. 334.1390 Section 334.1390 Navigation and Navigable... REGULATIONS § 334.1390 Pacific Ocean at Barking Sands, Island of Kauai, Hawaii; missile range facility....

  19. Elegant irrelevance: The anti-ballistic missile treaty in the new world disorder. Report for August-December 1994

    SciTech Connect

    Roberts, G.B.

    1994-11-15

    Concern over global proliferation of theater ballistic missiles has prompted calls for limited national and effective theater ballistic missile defense (TBMD) programs. However, the ABM Treaty, a cold war relic, is a major stumbling block to such programs because it prohibits the deployment of ABM defenses, and does not distinguish between prohibited ABM defenses and TBMD systems.

  20. 75 FR 54918 - Draft Regulatory Guide, DG-1247, “Design-Basis Hurricane and Hurricane Missiles for Nuclear Power...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-09

    ... August 31, 2010 (75 FR 53352), the U.S. Nuclear Regulatory Commission (NRC) published a notice of... missile velocities must also be defined. The NRC commissioned a report, NUREG/CR 7004, on design-basis hurricane-borne missile velocities. This report describes the method used to calculate velocities...

  1. 78 FR 31614 - Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-24

    ... 2007 (ML070630003). On October 22, 2012 (77 FR 64564), the staff issued the proposed DC/COL-ISG-024... COMMISSION Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles AGENCY....221, ``Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants,'' in support of...

  2. 33 CFR 334.1390 - Pacific Ocean off the Pacific Missile Range Facility at Barking Sands, Island of Kauai, Hawaii...

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 33 Navigation and Navigable Waters 3 2014-07-01 2014-07-01 false Pacific Ocean off the Pacific... AND RESTRICTED AREA REGULATIONS § 334.1390 Pacific Ocean off the Pacific Missile Range Facility at... Pacific Missile Range Facility range boats, beach markings including beach signs along the north and...

  3. Application of an advanced trajectory optimization method to ramjet propelled missiles

    NASA Technical Reports Server (NTRS)

    Paris, S. W.; Fink, L. E.; Joosten, B. K.

    1980-01-01

    The mission performance characteristics of ramjet-propelled missiles are highly dependent upon the trajectory flown. Integration of the trajectory profile with the ramjet propulsion system performance characteristics to achieve optimal missile performance is very complex. Past trajectory optimization methods have been extremely problem dependent and require a high degree of familiarity to achieve success. A general computer code (CTOP) has been applied to ramjet-powered missiles to compute open-loop optimal trajectories. CTOP employs Chebyshev polynomial representations of the states and controls. This allows a transformation of the continuous optimal control problem to one of parameter optimization. With this method, the trajectory boundary conditions are always satisfied. State dynamics and path constraints are enforced via penalty functions. The presented results include solutions to minimum fuel-to-climb, minimum time-to-climb, and minimum time-to-target intercept problems.

  4. Range maximization method for ramjet powered missiles with flight path constraints

    NASA Astrophysics Data System (ADS)

    Schoettle, U. M.

    1982-03-01

    Mission performance of ramjet powered missiles is strongly infuenced by the trajectory flown. The trajectory optimization problem considered is to obtain the control time histories (i.e., propellant flow rate and angle of attack) which maximize the range of ramjet powered supersonic missiles with preset initial and terminal fight conditions and operational constraints. The approach chosen employs a parametric control model to represent the infinite-dimensional controls by a finite set of parameters. The resulting suboptimal parameter optimization problem is solved by means of nonlinear programming methods. Operational constraints on the state variables are treated by the method of penalty functions. The presented method and numerical results refer to a fixed geometry solid fuel integral rocket ramjet missile for air-to-surface or surface-to-surface missions. The numerical results demonstrate that continuous throttle capabilities increase range performance by about 5 to 11 percent when compared to more conventional throttle control.

  5. A method for simulating the atmospheric entry of long-range ballistic missiles

    NASA Technical Reports Server (NTRS)

    Eggers, A J , Jr

    1958-01-01

    It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory. Since both the motion and aerodynamic heating of a missile tend to be simulated in the model tests, this combination of hypervelocity gun and supersonic nozzle is termed an atmosphere entry simulator.

  6. Telemetry recording and reduction equipment for shipboard support of missile exercises

    NASA Astrophysics Data System (ADS)

    Daniel, J. T.; Jones, G. P.

    The Telemetry Recording and Reduction Equipment (TRRE) is designed to process both the pulse amplitude modulation (PAM) telemetry data formats of existing missile designs and the pulse code modulation (PCM) data formats of evolving missile designs. Through preprogrammed telemeter formats and programmable decommutation tables, the TRRE design minimizes the required operator interface. The decommutation hardware configuration is programmed by a microprocessor. The TRRE system comprises two signal-processing chassis, a magnetic tape recorder, and an oscillograph; interfaces are provided for an external printer and spectrum analyzer. The primary purpose of the TRRE on board a ship is to document the missile firing by making a telemetry recording and providing a 'quick-look' and analysis capability at the completion of the flight.

  7. Improved manufacturing techniques for rf and laser hardening of missile domes, phase 1

    NASA Astrophysics Data System (ADS)

    Pawlewicz, W. T.; Mann, I. B.; Martin, P. M.; Hays, D. D.; Graybeal, A. G.

    1982-07-01

    The adaptation of an existing Pacific Northwest Laboratory (PNL) optical coating capability developed for high power fusion laser applications to the case of RF and laser hardening of plastic missile domes used by US Army (MICOM) is reported. RF hardening of Hellfire and Copperhead 1.06 micron missile domes by use of transparent conductive Indium Tin Oxide (ITO) coatings is demonstrated. The project involved adaptation of a coating material and process developed for flat glass components used in fusion lasers to the case of hemispherical or conical heat sensitive plastic domes used on laser guided missiles. Specific ITO coating property goals are an electrical sheet resistance of 10 ohms/square, a coated dome transmission of 80% or more at 1.06 micron wavelength (compared to 90% for a bare dome), and good adhesion. The sheet resistance goal of 10 ohms/square was expected to result in an RF attenuation of 30 dB at the frequencies of importance.

  8. Guidance: Agent of the Counterculture.

    ERIC Educational Resources Information Center

    Patouillet, Raymond A.; Marin, Roselyn L.

    1979-01-01

    This article was an introduction to a convention program presented at the Florida Personnel and Guidance Association Convention (Tampa, Nov., 1977) by Raymond Patouillet, shortly before his sudden death. It encapsulates his guidance philosophy, his understanding of the human condition, and his faith in the crucial role of the caring profession.…

  9. Innovative Approaches to Career Guidance.

    ERIC Educational Resources Information Center

    Freeman, Andrew R.

    A key part of a broad-based approach to career education in Australian schools is vocational/career guidance. Various vocational guidance programs have been developed for specific groups in Australian society, including work experience, caravans, and micrographics technology for the handicapped; pre-employment courses and a family education center…

  10. Automated Guidance for Student Inquiry

    ERIC Educational Resources Information Center

    Gerard, Libby F.; Ryoo, Kihyun; McElhaney, Kevin W.; Liu, Ou Lydia; Rafferty, Anna N.; Linn, Marcia C.

    2016-01-01

    In 4 classroom experiments we investigated uses for technologies that automatically score student generated essays, concept diagrams, and drawings in inquiry curricula. We used the automatic scores to assign typical and research-based guidance and studied the impact of the guidance on student progress. Seven teachers and their 897 students…

  11. Considerations for Middle School Guidance

    ERIC Educational Resources Information Center

    Knudsen, Grace

    1971-01-01

    Middle school guidance appears to be neglected. Yet this is a time of searching when pupils who are able to relate are usually willing to be helped. The characteristics of both elementary and secondary school guidance need to be evaluated in order to provide continuity in the junior high schools. (Author/BY)

  12. Guidance Services in Spanish Universities

    ERIC Educational Resources Information Center

    Vidal, Javier; Diez, Gloria; Vieira, Maria J.

    2003-01-01

    Since the 80s, higher education in Spain has undergone important modifications such as greater autonomy, expansion in the number of students and the introduction of more flexible programmes. In this context, guidance services have proliferated in an unstructured way. This paper presents a description of guidance services in Spanish universities…

  13. Guidance in the Secondary School

    ERIC Educational Resources Information Center

    Kumar, V. Jurist Lional

    2010-01-01

    Secondary School Students face a lot of problems in their body as well as in mind due to puberty that tends to adolescence stage. Adolescence has peculiar characters of their own. They need proper Guidance and Counselling to tackle their own problems. Guidance is described as a counselling service to assist the individual in achieving self…

  14. A Guide to Career Guidance.

    ERIC Educational Resources Information Center

    Nejedlo, Robert J., Ed.

    The nineteen articles in this guidebook are by former consultants for vocational guidance workshops at Northern Illinois University. Articles are organized in five parts: identifying students' career guidance needs, providing students with helpful career information, assisting students pursuing career programs, preparing students for career…

  15. Tornado missile simulation and design methodology. Volume 1: simulation methodology, design applications, and TORMIS computer code. Final report

    SciTech Connect

    Twisdale, L.A.; Dunn, W.L.

    1981-08-01

    A probabilistic methodology has been developed to predict the probabilities of tornado-propelled missiles impacting and damaging nuclear power plant structures. Mathematical models of each event in the tornado missile hazard have been developed and sequenced to form an integrated, time-history simulation methodology. The models are data based where feasible. The data include documented records of tornado occurrence, field observations of missile transport, results of wind tunnel experiments, and missile impact tests. Probabilistic Monte Carlo techniques are used to estimate the risk probabilities. The methodology has been encoded in the TORMIS computer code to facilitate numerical analysis and plant-specific tornado missile probability assessments. Sensitivity analyses have been performed on both the individual models and the integrated methodology, and risk has been assessed for a hypothetical nuclear power plant design case study.

  16. Signaling from Axon Guidance Receptors

    PubMed Central

    Bashaw, Greg J.; Klein, Rüdiger

    2010-01-01

    Determining how axon guidance receptors transmit signals to allow precise pathfinding decisions is fundamental to our understanding of nervous system development and may suggest new strategies to promote axon regeneration after injury or disease. Signaling mechanisms that act downstream of four prominent families of axon guidance cues—netrins, semaphorins, ephrins, and slits—have been extensively studied in both invertebrate and vertebrate model systems. Although details of these signaling mechanisms are still fragmentary and there appears to be considerable diversity in how different guidance receptors regulate the motility of the axonal growth cone, a number of common themes have emerged. Here, we review recent insights into how specific receptors for each of these guidance cues engage downstream regulators of the growth cone cytoskeleton to control axon guidance. PMID:20452961

  17. Signaling from axon guidance receptors.

    PubMed

    Bashaw, Greg J; Klein, Rüdiger

    2010-05-01

    Determining how axon guidance receptors transmit signals to allow precise pathfinding decisions is fundamental to our understanding of nervous system development and may suggest new strategies to promote axon regeneration after injury or disease. Signaling mechanisms that act downstream of four prominent families of axon guidance cues--netrins, semaphorins, ephrins, and slits--have been extensively studied in both invertebrate and vertebrate model systems. Although details of these signaling mechanisms are still fragmentary and there appears to be considerable diversity in how different guidance receptors regulate the motility of the axonal growth cone, a number of common themes have emerged. Here, we review recent insights into how specific receptors for each of these guidance cues engage downstream regulators of the growth cone cytoskeleton to control axon guidance. PMID:20452961

  18. Fabrication of composite propfan blades for a cruise missile wind tunnel model

    NASA Technical Reports Server (NTRS)

    Fite, E. Brian

    1993-01-01

    This report outlines the procedures that were employed in fabricating prototype graphite-epoxy composite prop fan blades. These blades were used in wind tunnel tests that investigated prop fan propulsion system interactions with a missile airframe in order to study the feasibility of an advanced-technology-propfan-propelled missile. Major phases of the blade fabrication presented include machining of the master blade, mold fabrication, ply cutting and assembly, blade curing, and quality assurance. Specifically, four separate designs were fabricated, 18 blades of each geometry, using the same fabrication technique for each design.

  19. Exhaust plumes and their interaction with missile airframes - A new viewpoint

    NASA Technical Reports Server (NTRS)

    Dash, S. M.; Sinha, N.

    1992-01-01

    The present, novel treatment of missile airframe-exhaust plume interactions emphasizes their simulation via a formal solution of the Reynolds-averaged Navier-Stokes (RNS) equation and is accordingly able to address the simulation requirements of novel missiles with nonconventional/integrated propulsion systems. The method is made possible by implicit RNS codes with improved artificial dissipation models, generalized geometric capabilities, and improved two-equation turbulence models, as well as by such codes' recent incorporation of plume thermochemistry and multiphase flow effects.

  20. Advancements in hardware-in-the-loop simulations at the U.S. Army Aviation and Missile Command

    NASA Astrophysics Data System (ADS)

    Buford, James A.; Jolly, Alexander C.; Mobley, Scott B.; Sholes, William J.

    2000-07-01

    A greater awareness of and increased interest in the use of modeling and simulation (M&S) has been demonstrated at many levels within the Department of Defense (DoD) and all the Armed Services agencies in recent years. M&S application is regarded as a viable means of lowering the life cycle costs of missile defense and tactical missile weapon system acquisition beginning with studies of new concepts of war-fighting through user training and post-deployment support. The Aviation and Missile Research, Engineering, and Development Center (AMRDEC) of the U.S. Army Aviation and Missile Command (AMCOM) has an extensive history of applying all types of M&S to weapons system development and has been a particularly strong advocate of hardware-in-the-loop (HWIL) simulation and test for many years. Over the past 40 years AMRDEC has developed and maintained the Advanced Simulation Center (ASC) which provides world-class, high fidelity, specific and dedicated HWIL simulation and test capabilities for the Army's missile defense and tactical missile program offices in both the infrared and radio frequency sensor domains. The ASC facility uses M&S to conduct daily HWIL missile simulations and tests to support flight tests, missile/system development, independent verification and validation of weapon system embedded software and simulations, and missile/system performance against current and future threat environments. This paper describes the ASC role, recaps the past year, describes the HWIL components and advancements, and outlines the path-ahead for the ASC in terms of both missile and complete system HWIL simulations and test with a focus on the imaging infrared systems.

  1. RH Packaging Program Guidance

    SciTech Connect

    Washington TRU Solutions LLC

    2008-01-12

    The purpose of this program guidance document is to provide the technical requirements for use, operation, inspection, and maintenance of the RH-TRU 72-B Waste Shipping Package (also known as the "RH-TRU 72-B cask") and directly related components. This document complies with the requirements as specified in the RH-TRU 72-B Safety Analysis Report for Packaging (SARP), and Nuclear Regulatory Commission (NRC) Certificate of Compliance (C of C) 9212. If there is a conflict between this document and the SARP and/or C of C, the C of C shall govern. The C of C states: "...each package must be prepared for shipment and operated in accordance with the procedures described in Chapter 7.0, Operating Procedures, of the application." It further states: "...each package must be tested and maintained in accordance with the procedures described in Chapter 8.0, Acceptance Tests and Maintenance Program of the Application." Chapter 9.0 of the SARP tasks the Waste Isolation Pilot Plant (WIPP) Management and Operating (M&O) Contractor with assuring the packaging is used in accordance with the requirements of the C of C. Because the packaging is NRC-approved, users need to be familiar with Title 10 Code of Federal Regulations (CFR) §71.8, "Deliberate Misconduct." Any time a user suspects or has indications that the conditions of approval in the C of C were not met, the U.S. Department of Energy (DOE) Carlsbad Field Office (CBFO) shall be notified immediately. The CBFO will evaluate the issue and notify the NRC if required.In accordance with 10 CFR Part 71, "Packaging and Transportation of Radioactive Material," certificate holders, packaging users, and contractors or subcontractors who use, design, fabricate, test, maintain, or modify the packaging shall post copies of (1) 10 CFR Part 21, "Reporting of Defects and Noncompliance," regulations, (2) Section 206 of the Energy Reorganization Act of 1974, and (3) NRC Form 3, Notice to Employees. These documents must be posted in a

  2. Autonomous landing guidance program

    NASA Astrophysics Data System (ADS)

    Brown, John A.

    1996-05-01

    The Autonomous Landing Guidance program is partly funded by the US Government under the Technology Reinvestment Project. The program consortium consists of avionics and other equipment vendors, airlines and the USAF. A Sextant Avionique HUD is used to present flight symbology in cursive form as well as millimeter wave radar imagery from Lear Astronics equipment and FLIR Systems dual-channel, forward-looking, infrared imagery. All sensor imagery is presented in raster form. A future aim is to fuse all imagery data into a single presentation. Sensor testing has been accomplished in a Cessna 402 operated by the Maryland Advanced Development Laboratory. Development testing is under way in a Northwest Airlines simulator equipped with HUD and image simulation. Testing is also being carried out using United Airlines Boeing 727 and USAF C-135C (Boeing 707) test aircraft. The paper addresses the technology utilized in sensory and display systems as well as modifications made to accommodate the elements in the aircraft. Additions to the system test aircraft include global positioning systems, inertial navigation systems and extensive data collection equipment. Operational philosophy and benefits for both civil and military users are apparent. Approach procedures have been developed allowing use of Category 1 ground installations in Category 3 conditions.

  3. Uprated fine guidance sensor study

    NASA Technical Reports Server (NTRS)

    1984-01-01

    Future orbital observatories will require star trackers of extremely high precision. These sensors must maintain high pointing accuracy and pointing stability simultaneously with a low light level signal from a guide star. To establish the fine guidance sensing requirements and to evaluate candidate fine guidance sensing concepts, the Space Telescope Optical Telescope Assembly was used as the reference optical system. The requirements review was separated into three areas: Optical Telescope Assembly (OTA), Fine Guidance Sensing and astrometry. The results show that the detectors should be installed directly onto the focal surface presented by the optics. This would maximize throughput and minimize point stability error by not incoporating any additional optical elements.

  4. Composite hardbody and missile plume (CHAMP 98) IR scene generation program

    NASA Astrophysics Data System (ADS)

    Crow, Dennis R.; Coker, Charles F.

    1998-07-01

    The Composite Hardbody and Missile Plume (CHAMP) program is a computer simulation used to provide time dependent high- fidelity infrared (IR) simulations of airborne vehicles. CHAMP computational algorithms are based on first principle physics that compute hardbody and exhaust plume radiation (absorption, emission, and reflection) for arbitrary vehicle operational state, position, orientation and atmospheric condition. All computations are performed as a function of time to allow complex vehicle dynamics to be simulated. Image processing functions are included to generate anti-aliased focal plane imagery. CHAMP can be utilized to simulate post-boost vehicle, re-entry vehicle, boost missile, theater missile, cruise missile, aircraft, and helicopter applications. CHAMP development is sponsored by the Kinetic Kill Vehicle Hardware- In-the-Loop Simulator (KHILS) facility at Eglin AFB, Florida. CHAMP is routinely utilized by KHILS to support on-going hardware-in-the-loop testing of IR seekers. Many of these tests are complex and diversified. CHAMP has been structured to support these tests by employing current generation object oriented design methodologies that facilitate adaptation to specific test requirements.

  5. Tests of a Hermes A-2 Missile Body at Mach Number 4.04

    NASA Technical Reports Server (NTRS)

    Ulmann, Edward F.; Lord, Douglas R.

    1950-01-01

    Force tests on a proposed body shape of the Hermes A-2 missile with and without longitudinal spoilers were made at Mach number 4.04. Values of normal force coefficient, pitching-moment coefficient, and center-of-pressure position were obtained.

  6. Casualties from guided missile impact in warships from another point of view.

    PubMed

    Ebeling, C F

    1991-06-01

    From Kamikaze to Exocet, by learning from history a tool for casualty calculation in modern naval warfare is available, indicating absolute casualty figures per SS guided missile hit. The figures 35 wounded and 30 killed per hit ought to be used. PMID:1852281

  7. Health-hazard evaluation report HETA 83-186-1628, Raytheon Missile Systems Division, Bristol, Tennessee

    SciTech Connect

    Salisbury, S.; Lucas, C.

    1985-09-01

    Environmental and breathing-zone samples were analyzed for cutting-oil mists, metal working fluids, and mineral spirits at Raytheon Missile Systems Divisions, Bristol, Tennessee in July, 1985. The evaluation was requested confidentially to investigate the occurrence of skin rashes in Machine-Department employees.

  8. Military aircraft and missile technology at the Langley Research Center: A selected bibliography

    NASA Technical Reports Server (NTRS)

    Maddalon, D. V.

    1980-01-01

    A compilation of reference material is presented on the Langley Research Center's efforts in developing advanced military aircraft and missile technology over the past twenty years. Reference material includes research made in aerodynamics, performance, stability, control, stall-spin, propulsion integration, flutter, materials, and structures.

  9. 78 FR 42430 - Revisions to the Export Administration Regulations Based on the 2012 Missile Technology Control...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-16

    ... Technology Control Regime (MTCR) Annex that were agreed to by MTCR member countries at the October 2012... export control arrangement among 34 nations, including most of the world's advanced suppliers of missiles... countries implement in accordance with their national export controls. The MTCR seeks to limit the risk...

  10. Fly-away restraint pin mechanism for the Army's PATRIOT missile system

    NASA Technical Reports Server (NTRS)

    Knight, F. W.

    1977-01-01

    The development of the longitudinal restraint mechanism for the PATRIOT missile system is reviewed. Two approaches for the restraint pin design are discussed: an initial ordnance mechanism, and a passive fly-away mechanism. Because of reliability problems and a desire to reduce cost the fly-away restraint mechanism was chosen.

  11. Space radiation studies at the White Sands Missile Range Fast Burst Reactor

    NASA Technical Reports Server (NTRS)

    Delapaz, A.

    1972-01-01

    The operation of the White Sands Missile Range Fast Burst Reactor is discussed. Space radiation studies in radiobiology, dosimetry, and transient radiation effects on electronic systems and components are described. Proposed modifications to increase the capability of the facility are discussed.

  12. 76 FR 4322 - Availability of the Fiscal Year 2009 Missile Defense Agency Services Contracts Inventory Pursuant...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-25

    ... United States Code as amended by the National Defense Authorization Act for Fiscal Year 2008 (NDAA 08... of the Secretary Availability of the Fiscal Year 2009 Missile Defense Agency Services Contracts... Procurement and Acquisition Policy, Office of Strategic Sourcing (DPAP/SS) will make available to the...

  13. 32 CFR 644.531 - Warning to public of danger in handling explosive missiles.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... 32 National Defense 4 2014-07-01 2013-07-01 true Warning to public of danger in handling explosive missiles. 644.531 Section 644.531 National Defense Department of Defense (Continued) DEPARTMENT OF THE ARMY (CONTINUED) REAL PROPERTY REAL ESTATE HANDBOOK Disposal Clearance of Explosive Hazards and Other Contamination from Proposed Excess Land...

  14. Using hardware-in-the-loop (HWIL) simulation to provide low-cost testing of TMD IR missile systems

    NASA Astrophysics Data System (ADS)

    Buford, James A., Jr.; Paone, Thad

    1998-07-01

    A greater awareness of and increased interest in the use of modeling and simulation (M&S) has been demonstrated at many levels within the Department of Defense (DoD) and all the Armed Services agencies in recent years. M&S application is regarded as a viable means of lowering the life cycle costs of theater missile defense (TMD) weapon system acquisition beginning with studies of new concepts of warfighting through user training and post-deployment support. The Missile Research, Engineering, and Development Center (MRDEC) of the U.S. Army Aviation and Missile Command (AMCOM) has an extensive history of applying all types of M&S to TMD weapon system development and has been a particularly strong advocate of hardware-in-the-loop (HWIL) simulation for many years. Over the past 10 years MRDEC has developed specific and dedicated HWIL capabilities for TMD applications in both the infrared and radio frequency sensor domains. This paper provides an overview of the infrared-based TMD HWIL missile facility known as the Imaging Infrared System Simulation (I2RSS) which is used to support the Theater High Altitude Air Defense (THAAD) missile system. This facility uses M&S to conduct daily THAAD HWIL missile simulations to support flight tests, missile/system development, independent verification and validation of weapon system embedded software and simulations, and missile/system performance against current and future threat environments. This paper describes the THAAD TMD HWIL role, process, major components, HWIL verification/validation, and daily HWIL support areas in terms of both missile and complete system.

  15. Deterrence of ballistic missile systems and their effects on today's air operations

    NASA Astrophysics Data System (ADS)

    Durak, Hasan

    2015-05-01

    Lately, the effect-based approach has gained importance in executing air operations. Thus, it makes more successful in obtaining the desired results by breaking the enemy's determination in a short time. Air force is the first option to be chosen in order to defuse the strategic targets. However, the problems such as the defense of targets and country, radars, range…etc. becoming serious problems. At this level ballistic missiles emerge as a strategic weapon. Ultimate emerging technologies guided by the INS and GPS can also be embedded with multiple warheads and reinforced with conventional explosive, ballistic missiles are weapons that can destroy targets with precision. They have the advantage of high speed, being easily launched from every platform and not being easily detected by air defense systems contrary to other air platforms. While these are the advantages, there are also disadvantages of the ballistic missiles. The high cost, unavailability of nuclear, biological and chemical weapons, and its limited effect while using conventional explosives against destroying the fortified targets are the disadvantages. The features mentioned above should be considered as limitation to the impact of the ballistic missiles. The aim is to impose the requests on enemies without starting a war with all components and to ensure better implementation of the operation functions during the air operations. In this study, effects of ballistic missiles in the future on air battle theatre will be discussed in the beginning, during the process and at the end phase of air operations within the scope of an effect-based approach.

  16. A Note for Missile Autopilot Performance Evaluation Test

    NASA Astrophysics Data System (ADS)

    Eguchi, Hirofumi

    The essential benefit of HardWare-In-the-Loop (HWIL) simulation can be summarized as that the performance of autopilot system is evaluated realistically without the modeling error by using actual hardware such as seeker systems, autopilot systems and servo equipments. The most important requirement at the HWIL simulation test is to set the homing seeker at the 3-axis gimbals center of the flight motion table. But, because of the various reasons such as the length of the homing seeker, the structure of the flight motion table and the shape of attachments, this requirement on setting is not able to be satisfied. In this paper, the effect of this position error on the guidance and control system performance is analyzed and evaluated.

  17. One Class of Nonlinear Model Solutions for Flight Vehicles and Applications to Targeting and Guidance Schemes

    NASA Astrophysics Data System (ADS)

    Azimov, D.; Bishop, R.

    2012-09-01

    A complete analytical integration of the kinematic and dynamic equations of motion and applications of their integrals to targeting and guidance schemes for various dynamical models of various flight vehicles are presented. The general integral of these equations consists of six independent first integrals of motion and describes a class of non-steady flight trajectories in a maneuver plane. These first integrals represent explicit relationships for time, components of position and velocity vectors, and propulsive and aerodynamic accelerations. This explicitness with respect to the problem parameters can make these relationships useful in the design of airspace trajectories, and targeting and guidance schemes. It is also shown that the equations represent a 3rd-order vector differential equation used to develop the nonlinear maneuver model of a flight vehicle, and the state estimation and prediction schemes. Similarity in the dynamical models makes the first integrals valid for re-entry vehicles and missiles. An illustrative example has shown that the general integral provides a complete set of analytical solutions for nonlinear tracking, targeting, guidance and control problems with a wide range of terminal conditions, accelerations due to propulsive thrust and aerodynamic forces.

  18. Measuring Client Progression in Adult Guidance

    ERIC Educational Resources Information Center

    Hearne, Lucy

    2007-01-01

    Currently, in the field of guidance, relevant stakeholders including guidance practitioners, educators and policy makers, have identified progression for adults in education and employment as one of the key outcomes of educational guidance. Lifelong guidance is now inextricably linked with lifelong learning as a mechanism to enhance individual…

  19. 33 CFR 385.5 - Guidance memoranda.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ..., Circulars, Manuals, or Pamphlets, or other appropriate form of guidance. (2) Guidance on the following six... for development of six program-wide guidance memoranda. The Corps of Engineers and the South Florida... agencies, develop the six guidance memoranda described in paragraph (a) of this section for approval by...

  20. Vocational Guidance: A Primary Function of Education.

    ERIC Educational Resources Information Center

    Roehrs, Hermann

    1992-01-01

    Perceives vocational orientation/guidance as a school responsibility. Discusses changing work attitudes, vocational guidance as counseling for life, parents' roles, work experience for 14-16 year olds, continuity between vocational guidance and competent career choice, vocational ethics, and midcareer and retirement guidance. Cites research on…

  1. Information Paper 18: Guidance in Secondary Schools.

    ERIC Educational Resources Information Center

    Ashton, Terry

    1986-01-01

    Traces impetus for introduction of structured guidance into Scottish secondary schools. Identifies 1968 "Orange Paper" as first attempt to set out rationale for guidance. Describes how guidance is organized; outlines tasks of guidance teachers; and presents current developments, training requirements, and trends. (NEC)

  2. Guidelines for Comprehensive Guidance and Counseling Services.

    ERIC Educational Resources Information Center

    Stefkovich, Jacqueline; And Others

    These guidelines are designed to assist local school districts and their Boards of Education in developing and implementing comprehensive guidance and counseling services in thier school systems. The components of the comprehensive guidance program are comprehensive guidance services, certified personnel, and comprehensive guidance facilities.…

  3. Resources for Guidance Program Improvement. Volume 2.

    ERIC Educational Resources Information Center

    Frenza, Mary C., Comp.; and Others

    This guide, for guidance personnel and teachers, is designed to provide ready access to current, practical programs, activities, and references for improving guidance programs. The resources are organized in four sections representing areas of basic concern for guidance personnel. Section 1 presents selected portions of guidance programs from…

  4. Cooperative Monitoring Center Occasional Paper/4: Missile Control in South Asia and the Role of Cooperative Monitoring Technology

    SciTech Connect

    Kamal, N.; Sawhney, P.

    1998-10-01

    The succession of nuclear tests by India and Pakistan in May 1998 has changed the nature of their missile rivalry, which is only one of numerous manifestations of their relationship as hardened adversaries, deeply sensitive to each other's existing and evolving defense capabilities. The political context surrounding this costly rivalry remains unmediated by arms control measures or by any nascent prospect of detente. As a parallel development, sensible voices in both countries will continue to talk of building mutual confidence through openness to avert accidents, misjudgments, and misinterpretations. To facilitate a future peace process, this paper offers possible suggestions for stabilization that could be applied to India's and Pakistan's missile situation. Appendices include descriptions of existing missile agreements that have contributed to better relations for other countries as well as a list of the cooperative monitoring technologies available to provide information useful in implementing subcontinent missile regimes.

  5. The guidance system for Ariane

    NASA Astrophysics Data System (ADS)

    Angus, Alex M.; Gordon, Colin S.; Brunschvig, Alain

    1991-05-01

    The various subsystems that comprise the complete Ariane guidance system are described along with a brief background of earlier developmental instruments and their applications. The Centrale Inertielle is a part of the control and guidance system of the Ariane launcher whose function is to provide a space-stable datum allowing measurement of acceleration and attitude relative to that datum. Consideration is given to the inertial platform, the electronics unit, thermal requirements, coarse alignment and fine-leveling, and the Vehicle Equipment Bay (VEB). The VEB is the main component of the electrical system and is designed to support all the equipment handling the following functions: guidance, navigation and control, sequencer and pyro management, localization and safety management, and telemetry.

  6. Autonomous Guidance, Navigation and Control

    NASA Astrophysics Data System (ADS)

    Bordano, A. J.; McSwain, G. G.; Fernandes, S. T.

    The NASA Autonomous Guidance, Navigation and Control (GN&C) Bridging program is reviewed to demonstrate the program plan and GN&C systems for the Space Shuttle. The ascent CN&C system is described in terms of elements such as the general-purpose digital computers, sensors for the navigation subsystem, the guidance-system software, and the flight-control subsystem. Balloon-based and lidar wind soundings are used for operations assessment on the day of launch, and the guidance software is based on dedicated units for atmospheric powered flight, vacuum powered flight, and abort-specific situations. Optimization of the flight trajectories is discussed, and flight-control responses are illustrated for wavelengths of 500-6000 m. Alternate sensors are used for load relief, and adaptive GN&C systems based on alternate gain synthesis are used for systems failures.

  7. Information architecture. Volume 3: Guidance

    SciTech Connect

    1997-04-01

    The purpose of this document, as presented in Volume 1, The Foundations, is to assist the Department of Energy (DOE) in developing and promulgating information architecture guidance. This guidance is aimed at increasing the development of information architecture as a Departmentwide management best practice. This document describes departmental information architecture principles and minimum design characteristics for systems and infrastructures within the DOE Information Architecture Conceptual Model, and establishes a Departmentwide standards-based architecture program. The publication of this document fulfills the commitment to address guiding principles, promote standard architectural practices, and provide technical guidance. This document guides the transition from the baseline or defacto Departmental architecture through approved information management program plans and budgets to the future vision architecture. This document also represents another major step toward establishing a well-organized, logical foundation for the DOE information architecture.

  8. The Effects of Plasma Shield on the Radar Cross Section of a Generic Missile in UHF Band

    NASA Astrophysics Data System (ADS)

    Chung, Shen

    2011-10-01

    RF Stealth is the dominant technology in today's military aircraft, and most is achieved by shape design with a few reductions achieved by RAM, but most of these effects are only valid in X band. With the popularity of UHF radar again rising, the possibility of detecting a stealth object has increased due to resonance effect, and this is difficult to decrease with previous means due to the long wavelength. A plasma shield generated in front of an object may be suitable to alter the RCS in specific band without physically changing its shape. We examine the RCS of a generic missile in UHF band, and compared it with one with a cone-shape plasma generated in front of the missile. We find the plasma effectively changes the RCS of the missile, though not necessarily smaller. The RCS of the missile with the plasma shield is now dominated by the plasma instead of the missile. The RCS is a function of the size, shape, and density of the plasma shield. For higher frequency signals like the X band radar, it can still penetrate the plasma, and sees the original RCS of the missile. Due to the relatively lower UHF frequency, the plasma density needed is lower than one in X band and thus more practical to achieve.

  9. Comparison of head-steered and aircraft-fixed infrared imagery for employing the AGM-65 Maverick missile

    NASA Astrophysics Data System (ADS)

    Osgood, Robert K.; Wells, Maxwell J.; Meador, Douglas P.

    1995-05-01

    Eight veteran USAF fighter pilots, experienced with AGM-65 Maverick air-to-ground missiles, flew a night, low-level ground attack mission in a flight simulator equipped with a helmet-mounted display (HMD). The mission was performed by delivering five Maverick missiles against ground vehicles using either an aircraft-fixed forward-looking infrared (FLIR) sensor image on a head-up display (HUD) or a head-steered FLIR as the missile aiming device. Additionally, the pilots employed their weapons by two methods: fixing and launching missiles singly or in varying numbers (multiple method). The purpose of the experiment was to determine what, if any, advantage there is to employing the AGM-65 using the HMD FLIR image to slew the missile seeker onto the target versus the conventional method of using the FLIR image displayed on the HUD. With a head-steered sensor (and fixing and launching weapons singly) subjects released their weapons quicker (14.6 second interval between launches vs. 17.1 sec.), at a higher altitude (1739 feet vs. 1603 ft.), and slightly farther from the target (3.42 nautical miles vs. 3.37 nm). Furthermore, data indicated the pilots looked farther off-boresight when searching for and locking the weapon onto a target, thereby more effectively using the full field-of-regard of the missile seeker. The participants also contributed their opinions of the advantages and disadvantages of the two mechanizations.

  10. Guidance for state attainment plans

    SciTech Connect

    Strait, R.

    1994-06-01

    Title I of the Clean Air act Amendments of 1990 significantly changed requirements for regulatory agencies to prepare state implementation plans that demonstrate attainment of the ozone National Ambient Air Quality Standards. State agencies now are required to submit plans that show how they will meet the standards by their attainment date. EPA has published a series of guidance documents to assist states in preparing their plans. In addition, the agency is developing software to assist states in projecting emissions and tracking reductions. This article summarizes the guidance documents and software program.

  11. Gun burner injury: a peculiar accidental self-inflicted missile head injury.

    PubMed

    Komolafe, E O; Olateju, O S; Adeolu, A A

    2004-06-01

    The objective of this study was to report the pattern of unusual accidental missile head injuries from the use of the locally-manufactured Dane gun, which presented at the Obafemi Awolowo University Teaching Hospitals Complex, Ile-Ife, Nigeria. Six illustrative patients are presented, each with a peculiar injury. All the patients except one, who died prior to surgery, had wound debridement and elevation of associated fractures with removal of the metallic foreign body. With the exception of the patient that died prior to surgical intervention, all did well without noticeable neurological deficits. Missile injury to the head is increasing. Firearm-related death is also on the increase and our environment is not exempted. Accidental injuries from stray bullets are fairly common; however, self-inflicted injuries are usually due to the improper handling of firearms, particularly by novices, suicide attempts and faulty technology of locally made firearms.

  12. Overview of dynamic scene projectors at the U.S. Army Aviation and Missile Command

    NASA Astrophysics Data System (ADS)

    Beasley, D. Brett; Saylor, Daniel A.; Buford, James A.

    2002-07-01

    The Aviation and Missile Research, Engineering, and Development Center (AMRDEC) of the US Army Aviation and Missile Command (AMCOM) has an extensive history of applying all types of modeling and simulation to weapon system development and has been a particularly strong advocate of hardware-in-the-loop (HWIL) simulation and test for many years. Key to the successful application of HWIL testing at AMCOM has been the use of state-of-the-art IR Scene Projector technologies. This paper describes recent advancements within the AMRDEC Advanced Simulation Center HWIL facilities with a specific emphasis on the sate of the various IRSP technologies employed. Included in these IRSP technologies are the latest Honeywell and Santa Barbara IR emitter arrays, the DMD-based IR projectors, and the laser diode array projector.

  13. Cartesian-Grid Simulations of a Canard-Controlled Missile with a Free-Spinning Tail

    NASA Technical Reports Server (NTRS)

    Murman, Scott M.; Aftosmis, Michael J.; Kwak, Dochan (Technical Monitor)

    2002-01-01

    The proposed paper presents a series of simulations of a geometrically complex, canard-controlled, supersonic missile with free-spinning tail fins. Time-dependent simulations were performed using an inviscid Cartesian-grid-based method with results compared to both experimental data and high-resolution Navier-Stokes computations. At fixed free stream conditions and canard deflections, the tail spin rate was iteratively determined such that the net rolling moment on the empennage is zero. This rate corresponds to the time-asymptotic rate of the free-to-spin fin system. After obtaining spin-averaged aerodynamic coefficients for the missile, the investigation seeks a fixed-tail approximation to the spin-averaged aerodynamic coefficients, and examines the validity of this approximation over a variety of freestream conditions.

  14. The application of some lifting-body reentry concepts to missile design

    NASA Technical Reports Server (NTRS)

    Spearman, M. L.

    1985-01-01

    The aerodynamic characteristics of some lifting-body concepts are examined with a view to the applicability of such concepts to the design of missiles. A considerable amount of research has been done in past years with vehicle concepts suitable for manned atmospheric-entry and atmospheric flight. Some of the concepts appear to offer some novel design approaches for missiles for a variety of missions and flight profiles, including long-range orbital/reentry with transatmospheric operation for strategic penetration, low altitude penetration, and battlefield tactical. The concepts considered include right triangular pyramidal configurations, a lenticular configuration, and various 75-degree triangular planform configurations with variations in body camber and control systems. The aerodynamic features are emphasized but some observations are also made relative to other factors such as heat transfer, structures, carriage, observability, propulsion, and volumetric efficiency.

  15. Modular Open System Architecture for Reducing Contamination Risk in the Space and Missile Defense Supply Chain

    NASA Technical Reports Server (NTRS)

    Seasly, Elaine

    2015-01-01

    To combat contamination of physical assets and provide reliable data to decision makers in the space and missile defense community, a modular open system architecture for creation of contamination models and standards is proposed. Predictive tools for quantifying the effects of contamination can be calibrated from NASA data of long-term orbiting assets. This data can then be extrapolated to missile defense predictive models. By utilizing a modular open system architecture, sensitive data can be de-coupled and protected while benefitting from open source data of calibrated models. This system architecture will include modules that will allow the designer to trade the effects of baseline performance against the lifecycle degradation due to contamination while modeling the lifecycle costs of alternative designs. In this way, each member of the supply chain becomes an informed and active participant in managing contamination risk early in the system lifecycle.

  16. Investigation on Stability in Roll of Square Section Missile at High Angle of Attack

    NASA Astrophysics Data System (ADS)

    Tao, Yang; Fan, Zhaolin; Wu, Jifei; Wu, Wenhua

    An experimental investigation of the stability in roll of a square section missile at high incidence was conducted in FL-23 wind tunnel. Dynamic motions were obtained on a square section missile that is free to rotate about its longitudinal axis. Different dynamic rolling motions were observed depending on the incidence of the model sting. These dynamic regimes include damped oscillations, quasi-limit-cycle wing-rock motion, and constant rolling. A coupling numerical method was established by solving the fluid dynamics equations and the rigid-body dynamics equations synchronously in order to predict the onset and the development of uncommented motions and then explore the unsteady movement characteristics of the aircraft. The study indicates that the aircraft loss stability at high incidence is caused by the asymmetric vertex on the level fin tip liftoff and attach alternately. The computation results are in line with the experiment results.

  17. Average-passage simulation of counter-rotating propfan propulsion systems as applied to cruise missiles

    NASA Technical Reports Server (NTRS)

    Mulac, Richard A.; Schneider, Jon C.; Adamczyk, John J.

    1989-01-01

    Counter-rotating propfan (CRP) propulsion technologies are currently being evaluated as cruise missile propulsion systems. The aerodynamic integration concerns associated with this application are being addressed through the computational modeling of the missile body-propfan flowfield interactions. The work described in this paper consists of a detailed analysis of the aerodynamic interactions between the control surfaces and the propfan blades through the solution of the average-passage equation system. Two baseline configurations were studied, the control fins mounted forward of the counter-rotating propeller and the control fins mounted aft of the counter-rotating propeller. In both cases, control fin-propfan separation distance and control fin deflection angle were varied.

  18. Does war hurt? Effects of media exposure after missile attacks on chronic pain.

    PubMed

    Lerman, Sheera F; Rudich, Zvia; Shahar, Golan

    2013-03-01

    This study focused on the effects of exposure to terrorist missile attacks on the physical and mental well being of chronic pain patients. In this prospective and longitudinal design, 55 chronic pain patients treated at a specialty pain clinic completed self-report questionnaires regarding their pain, depression and anxiety pre- and post a three week missile attack on the southern region of Israel. In addition, levels of direct and indirect exposure to the attacks were measured. Results of regression analyses showed that exposure to the attacks through the media predicted an increase in pain intensity and in the sensory component of pain during the pre-post war period, but did not predict depression, anxiety or the affective component of pain. These findings contribute to the understanding of the effects of terrorism on physical and emotional distress and identify chronic pain patients as a vulnerable population requiring special attention during terrorism-related stress.

  19. A computer code (SKINTEMP) for predicting transient missile and aircraft heat transfer characteristics

    NASA Astrophysics Data System (ADS)

    Cummings, Mary L.

    1994-09-01

    A FORTRAN computer code (SKINTEMP) has been developed to calculate transient missile/aircraft aerodynamic heating parameters utilizing basic flight parameters such as altitude, Mach number, and angle of attack. The insulated skin temperature of a vehicle surface on either the fuselage (axisymmetric body) or wing (two-dimensional body) is computed from a basic heat balance relationship throughout the entire spectrum (subsonic, transonic, supersonic, hypersonic) of flight. This calculation method employs a simple finite difference procedure which considers radiation, forced convection, and non-reactive chemistry. Surface pressure estimates are based on a modified Newtonian flow model. Eckert's reference temperature method is used as the forced convection heat transfer model. SKINTEMP predictions are compared with a limited number of test cases. SKINTEMP was developed as a tool to enhance the conceptual design process of high speed missiles and aircraft. Recommendations are made for possible future development of SKINTEMP to further support the design process.

  20. Results from Sandia National Laboratories/Lockheed Martin Electromagnetic Missile Launcher (EMML).

    SciTech Connect

    Lockner, Thomas Ramsbeck; Skurdal, Ben; Gaigler, Randy; Basak, L; Root, G; Aubuchon, Matthew S.; Turman, Bobby N.; Floyd, Mendel D.

    2005-05-01

    Sandia national laboratories (SNL) and lockheed martin MS2 are designing an electromagnetic missile launcher (EMML) for naval applications. The EMML uses an induction coilgun topology with the requirement of launching a 3600 lb. missile up to a velocity of 40 m/s. To demonstrate the feasibility of the electromagnetic propulsion design, a demonstrator launcher was built that consists of approximately 10% of the propulsion coils needed for a tactical design. The demonstrator verified the design by launching a 1430 lb weighted sled to a height of 24 ft in mid-December 2004 (Figure 1). This paper provides the general launcher design, specific pulsed power system component details, system operation, and demonstration results.

  1. Guidance for evidence-informed policies about health systems: rationale for and challenges of guidance development.

    PubMed

    Bosch-Capblanch, Xavier; Lavis, John N; Lewin, Simon; Atun, Rifat; Røttingen, John-Arne; Dröschel, Daniel; Beck, Lise; Abalos, Edgardo; El-Jardali, Fadi; Gilson, Lucy; Oliver, Sandy; Wyss, Kaspar; Tugwell, Peter; Kulier, Regina; Pang, Tikki; Haines, Andy

    2012-01-01

    In the first paper in a three-part series on health systems guidance, Xavier Bosch-Capblanch and colleagues examine how guidance is currently formulated in low- and middle-income countries, and the challenges to developing such guidance.

  2. 78 FR 48503 - Proposed Revision to Missiles Generated by Extreme Winds

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-08

    ... extreme winds. The revision also incorporates guidance on regulatory treatment of nonsafety systems. DATES... Safety Analysis Reports for Nuclear Power Plants: LWR Edition.'' This revision incorporates guidance and... Power Plants,'' and Interim Staff Guidance DC/COL- ISG-024, ``Implementation of Regulatory Guide...

  3. Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile

    NASA Technical Reports Server (NTRS)

    1950-01-01

    A wind-tunnel investigation has been conducted to determine the stability and control characteristics of a full-size model of the Hughes MX-904 missile. Aerodynamic characteristics of the complete model through moderate ranges of angles of attack and yaw, with an additional test made through an angle of attack of 180 degrees, are presented. The effects of horizontal tail deflection are also included.

  4. Structural analysis of high-rpm composite propfan blades for a cruise missile wind tunnel model

    NASA Astrophysics Data System (ADS)

    Carek, David A.

    1993-03-01

    Analyses were performed on a high-speed composite blade set for the Department of Defense Propfan Missile Interactions Project. The final design iteration, which resulted in the CM2D-2 blade design, is described in this report. Mode shapes, integral order excitation, and stress margins were examined. In addition, geometric corrections were performed to compensate for blade deflection under operating conditions with respect to the aerodynamic design shape.

  5. Application of fleet ballistic missile components/designs for expendable launch vehicles

    NASA Astrophysics Data System (ADS)

    Grizzell, Norman E.

    This paper describes the orbital performance and configuration attributes of an expendable launch vehicle (ELV) derived from flight-qualified components. Representative logistical and programmatic data are also provided. The backbone of the ELV program described is the cost-effective use of proven Fleet Ballistic Missile components/designs coupled with other high confidence 'off-the-shelf' equipment. The ELV defined can place over a thousand pounds (1000 lb) of spacecraft (payload) into Low Earth Orbit.

  6. Test wells T27 and T28, White Sands Missile Range, Dona Ana County, New Mexico

    USGS Publications Warehouse

    Myers, R.G.; Pinckley, K.M.

    1985-01-01

    Two test wells, T27 and T28, were drilled at White Sands Missile Range in south-central New Mexico as part of a joint military training program sponsored by the U.S. Army in February and March 1983. Test wells T27 and T28 were drilled as observation wells in the vicinity of the Liquid Propellant Storage Area. Information obtained from these wells includes lithologic logs, driller 's logs, and borehole-geophysical logs from the cased wells. (USGS)

  7. Evolution of Fuel-Air and Contaminant Clouds Resulting from a Cruise Missile Explosion Scenario

    SciTech Connect

    Grossman, A S; Kul, A L

    2005-06-22

    A low-mach-number hydrodynamics model has been used to simulate the evolution of a fuel-air mixture and contaminant cloud resulting from the detonation of a cruise missile. The detonation has been assumed to be non-nuclear. The cloud evolution has been carried out to a time of 5.5 seconds. At this time the contaminant has completely permeated the initial fuel-air mixture cloud.

  8. The proliferation of surface-to-surface missiles and weapons of mass destruction and the emerging role of tactical missile defenses in Israel, Syria and Iran

    SciTech Connect

    Clark, T.H.

    1993-01-01

    The proliferation of surface-to-surface missiles (SSMs) and weapons of mass destruction has become one of the more serious security threats to post-Cold War peace. This dissertation examines the history of proliferation within the Middle East by focusing primarily on three trend-setting countries: Israel, Syria and Iran. Building on the theoretical framework established by Lewis A. Dunn and Herman Kahn, this dissertation examines why and how Israel, Syria and Iran have procured SSMs and weapons of mass destruction. The author also includes an analysis of tactical missile defenses and their impact on proliferation trends. The final section investigates the numerous arms control treaties and supplier cartels designed to halt or slow the pace of unconventional weapons proliferation. In many instances, Iraq serves as the primary example of how well-intentioned nonproliferation efforts have fallen short. This dissertation reveals some of the major flaws in these regimes while proposing necessary improvements if nonproliferation efforts are to succeed. In conclusion, this dissertation returns to the expanded Dunn-Kahn nuclear proliferation model. By categorizing the various reasons as to why countries choose to procure unconventional weapons, a more successful nonproliferation policy can be constructed. However, this dissertation warns that without political solutions to long-term disputes in the region, western-imposed nonproliferation regimes will fail. Thus, nonproliferation policies must be accompanied or preceded by a vigorous diplomatic and political effort to solve seemingly intractable differences.

  9. Parametric Fin-Body and Fin-Plate Database for a Series of 12 Missile Fins

    NASA Technical Reports Server (NTRS)

    Allen, Jerry M.

    2001-01-01

    A cooperative experimental investigation has been performed to obtain a systematic fin-body and fin-plate database for a series of 12 missile fins. These data are intended to complement and extend the information contained in the Triservice missile project and to provide a systematic set of experimental data from which fin-body interference factors can be derived. Data were obtained with the fins mounted on both an axisymmetric body and on a flat plate that was used to simulate fin-alone measurements. The experiments were conducted at Mach numbers from 0.60 to 3.95; fin deflection angles of 0 deg, 10 deg, and -10 deg; and angles of attack up to 30 deg on the body and up to 95 deg on the flat plate. The data were obtained from three-component balances attached to the fins and a six-component balance located in the axisymmetric body. The data obtained in this project are documented in tabular form in this report. In addition, selected data are presented in graphical form to illustrate the effects of the test variables. These variables are configuration angle of attack; Mach number; and fin parameters of deflection angle, planform size, taper ratio, and aspect ratio. A very limited comparison with the Triservice missile data is made to illustrate the consistency between the data from these two projects.

  10. Improved manufacturing techniques for RF and laser hardening of missile domes. Phase I. Technical report

    SciTech Connect

    Pawlewicz, W.T.; Mann, I.B.; Martin, P.M.; Hays, D.D.; Graybeal, A.G.

    1982-07-01

    This report summarizes key results and accomplishements during the first year of a Manufacturing Methods and Technology project to adapt an existing Pacific Northwest Laboratory (PNL) optical coating capability developed for high-power fusion-laser applications to the case of rf and laser hardening of plastic missile domes used by the US Army (MICOM). The primary objective of the first year's work was to demonstrate rf hardening of Hellfire and Copperhead 1.06-micron missile domes by use of transparent conductive Indium Tin Oxide (ITO) coatings. The project thus involved adaptation of a coating material and process developed for flat glass components used in fusion lasers to the case of hemispherical or conical heat-sensitive plastic domes used on laser-guided missiles. Specific ITO coating property goals were an electrical sheet resistance of 10 Ohms/square, a coated-dome transmission of 80% or more at 1.06 micron wavelength (compared to 90% for a bare dome), and good adhesion. The sheet resistance goal of 10 Ohms/square was expected to result in an rf attenuation of 30 dB at the frequencies of importance.

  11. A Homing Missile Control System to Reduce the Effects of Radome Diffraction

    NASA Technical Reports Server (NTRS)

    Smith, Gerald L.

    1960-01-01

    The problem of radome diffraction in radar-controlled homing missiles at high speeds and high altitudes is considered from the point of view of developing a control system configuration which will alleviate the deleterious effects of the diffraction. It is shown that radome diffraction is in essence a kinematic feedback of body angular velocities which causes the radar to sense large apparent line-of-sight angular velocities. The normal control system cannot distinguish between the erroneous and actual line-of-sight rates, and entirely wrong maneuvers are produced which result in large miss distances. The problem is resolved by adding to the control system a special-purpose computer which utilizes measured body angular velocity to extract from the radar output true line-of-sight information for use in steering the missile. The computer operates on the principle of sampling and storing the radar output at instants when the body angular velocity is low and using this stored information for maneuvering commands. In addition, when the angular velocity is not low the computer determines a radome diffraction compensation which is subtracted from the radar output to reduce the error in the sampled information. Analog simulation results for the proposed control system operating in a coplanar (vertical plane) attack indicate a potential decrease in miss distance to an order of magnitude below that for a conventional system. Effects of glint noise, random target maneuvers, initial heading errors, and missile maneuverability are considered in the investigation.

  12. EATS and APATS telemetry antenna performance comparison in a ballistic missile terminal area support role

    NASA Astrophysics Data System (ADS)

    Cline, J. F.; Blackwell, E. G.

    1981-06-01

    A comparative analysis was made of the performance of the U.S. Navy EATS multibeam phased array telemetry antenna, currently under development by Pacific Missile Test Center and the planned APATS antenna intended for use by the U.S. Air Force ARIA Fleet. The comparison was made in the context of a ballistic missile terminal area test support role for the collection of telemetry data from MK-4 and MK-12 instrumented RVs during reentry. In this comparison, two levels of upgrade were examined for the EATS antenna, one as a minimum required upgrade (dual-polarization), and the other as an upgrade with dual-polarization and increased elevation scan angle commensurate with the APATS specification. Study findings indicate that the second EATS upgrade option results in telemetry collection performance essentially equal to that of the APATS. RV telemetry blackout (SNR < 13 dB) for the EATS upgraded antenna lasted slightly longer than the blackout of the APATS antenna. Blackout is relatively unimportant in the MK-4 application, but may be more consequential in the MK-12 application. The minimum EATS antenna upgrade (dual-polarization) does not perform well for ballistic missile telemetry support, so that the full upgrade is indicated for the EATS telemetry antenna in this mission role.

  13. Abortion Information: A Guidance Viewpoint

    ERIC Educational Resources Information Center

    Wolleat, Patricia L.

    1975-01-01

    A number of questions relating to providing abortion information to teenagers can be raised from legal, ethical and philosophical standpoints. The purpose of this article is to examine abortion information-giving from the perspective of counseling and guidance theory and practice. (Author)

  14. THE STRESSOR IDENTIFICATION GUIDANCE DOCUMENT

    EPA Science Inventory

    THE STRESSOR IDENTIFICATION GUIDANCE DOCUMENT

    Susan M. Cormier, ORD/NRMRL, Susan B. Norton, ORD/NCEA, Glenn W. Suter, II ORD/NCEA, William Swietlik, OW lOST

    Science Question(s):

    MYP Science Question: How can multiple and possibly related causes of biological ...

  15. Project Inspire: Vocational Guidance Institute.

    ERIC Educational Resources Information Center

    National Alliance of Businessmen, Washington, DC.

    Two introductory speeches suggest the general social and interracial climate in the United States. It is against this backdrop that Project Inspire is described. Its purpose is the development of a vocational guidance component within the broader school curriculum. Its major objective is elevating the awareness level of students to the work world…

  16. Axon guidance: FLRTing promotes attraction.

    PubMed

    Lowery, Laura Anne

    2014-03-01

    A recent study demonstrates a new mechanism by which crosstalk between multiple guidance cues is integrated during axon pathfinding. FLRT3 is a novel co-receptor for Robo1 that acts as a context-dependent modulator of Netrin-1 attraction in thalamocortical axons.

  17. Reading Guidance: Death and Grief.

    ERIC Educational Resources Information Center

    Smith, Alice Gullen

    1989-01-01

    Gives guidelines for the librarian using reading guidance (similar to bibliotherapy). Provides a nine-item annotated bibliography of novels for children and adolescents on the subject of death and grief. Appends an embryo list of categories suitable for content analysis of any file librarians might wish to keep on books suitable for use in this…

  18. Teacher Guidance of Knowledge Construction

    ERIC Educational Resources Information Center

    Schwarz, Baruch; Dreyfus, Tommy; Hadas, Nurit; Hershkowitz, Rina

    2004-01-01

    This paper focuses on how teachers guide construction of knowledge in classrooms. We suggest that guidance hinges on the kind of dialogue teachers choose to engage students in. We propose several classroom dialogue types relevant for the construction of knowledge and suggest that critical dialogue is particularly effective for knowledge…

  19. Developing Local Lifelong Guidance Strategies.

    ERIC Educational Resources Information Center

    Watts, A. G.; Hawthorn, Ruth; Hoffbrand, Jill; Jackson, Heather; Spurling, Andrea

    1997-01-01

    Outlines the background, rationale, methodology, and outcomes of developing local lifelong guidance strategies in four geographic areas. Analyzes the main components of the strategies developed and addresses a number of issues relating to the process of strategy development. Explores implications for parallel work in other localities. (RJM)

  20. Humanizing Education Through Guidance Counseling.

    ERIC Educational Resources Information Center

    Accola, W. V.

    A computerized information retrieval system has been designed to support the secondary school counseling effort. The system, entitled Total Guidance Information Support System (TGISS), runs on an IBM System/360 Model 65 facility and uses the IBM 2848 Display Control Unit. The software consists of an interactive communications program developed in…

  1. DOE Waste Treatability Group Guidance

    SciTech Connect

    Kirkpatrick, T.D.

    1995-01-01

    This guidance presents a method and definitions for aggregating U.S. Department of Energy (DOE) waste into streams and treatability groups based on characteristic parameters that influence waste management technology needs. Adaptable to all DOE waste types (i.e., radioactive waste, hazardous waste, mixed waste, sanitary waste), the guidance establishes categories and definitions that reflect variations within the radiological, matrix (e.g., bulk physical/chemical form), and regulated contaminant characteristics of DOE waste. Beginning at the waste container level, the guidance presents a logical approach to implementing the characteristic parameter categories as part of the basis for defining waste streams and as the sole basis for assigning streams to treatability groups. Implementation of this guidance at each DOE site will facilitate the development of technically defined, site-specific waste stream data sets to support waste management planning and reporting activities. Consistent implementation at all of the sites will enable aggregation of the site-specific waste stream data sets into comparable national data sets to support these activities at a DOE complex-wide level.

  2. A guidance concept for hypersonic aerospacecrafts

    NASA Astrophysics Data System (ADS)

    Ishimoto, Shinji

    In this paper a guidance concept for hypersonic re-entry flights is presented. The method uses a closed-form guidance technique based on a drag acceleration reference profile. A guidance law for range control is developed. It employs a physical relation between vehicle energy and range instead of a prediction-correction technique used for Shuttle entry guidance. Simulation results show that the algorithm provides good performance.

  3. 48 CFR 225.7302 - Guidance.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 3 2010-10-01 2010-10-01 false Guidance. 225.7302 Section 225.7302 Federal Acquisition Regulations System DEFENSE ACQUISITION REGULATIONS SYSTEM, DEPARTMENT OF... Guidance. For guidance on the role of the contracting officer in FMS programs that will require...

  4. Why Guidance Counseling Needs to Change

    ERIC Educational Resources Information Center

    Johnson, Jean; Rochkind, Jon; Ott, Amber

    2010-01-01

    Looking back on their high school experiences, young adults give the guidance counseling system "stunningly poor reviews," write the authors of this article. Using data from recent surveys of young people conducted by Public Agenda, the article describes a guidance system in which one-half of all students believe their guidance counselor sees them…

  5. Providing Career Guidance for Young Women.

    ERIC Educational Resources Information Center

    Colby, Pamela G.

    This module is directed at personnel working or planning to work in the areas of guidance, counseling, placement and follow-through in junior and senior high school settings, grades 7-12. The module topic is career guidance for young women of junior and senior high school age, aand the focus will be on providing nonbiased career guidance which…

  6. Quality Assurance in University Guidance Services

    ERIC Educational Resources Information Center

    Simon, Alexandra

    2014-01-01

    In Europe there is no common quality assurance framework for the delivery of guidance in higher education. Using a case study approach in four university career guidance services in England, France and Spain, this article aims to study how quality is implemented in university career guidance services in terms of strategy, standards and models,…

  7. 21 CFR 314.445 - Guidance documents.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... HUMAN USE APPLICATIONS FOR FDA APPROVAL TO MARKET A NEW DRUG Miscellaneous Provisions § 314.445 Guidance documents. (a) FDA has made available guidance documents under § 10.115 of this chapter to help you to...) maintains a list of guidance documents that apply to CDER's regulations. The list is maintained on...

  8. The Self in Guidance: Assumptions and Challenges.

    ERIC Educational Resources Information Center

    Edwards, Richard; Payne, John

    1997-01-01

    Examines the assumptions of "self" made in the professional and managerial discourses of guidance. Suggests that these assumptions obstruct the capacity of guidance workers to explain their own practices. Drawing on contemporary debates over identity, modernity, and postmodernity, argues for a more explicit debate about the self in guidance. (RJM)

  9. 78 FR 57450 - State Rail Plan Guidance

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-18

    ... requirements for State rail plans. The State Rail Plan Guidance is available on FRA's Web site at http://www.fra.dot.gov/Page/P0511 . DATES: The final State Rail Plan Guidance is effective as of the publication....dot.gov/Page/P0511 . The purpose of FRA's final State Rail Plan Guidance is to describe the...

  10. Microfluidic control of axonal guidance

    NASA Astrophysics Data System (ADS)

    Gu, Ling; Black, Bryan; Ordonez, Simon; Mondal, Argha; Jain, Ankur; Mohanty, Samarendra

    2014-10-01

    The precision of axonal pathfinding and the accurate formation of functional neural circuitry are crucial for an organism during development as well as during adult central and peripheral nerve regeneration. While chemical cues are believed to be primarily responsible for axonal pathfinding, we hypothesize that forces due to localized fluid flow may directly affect neuronal guidance during early organ development. Here, we report direct evidence of fluid flow influencing axonal migration, producing turning angles of up to 90°. Microfluidic flow simulations indicate that an axon may experience significant bending force due to cross-flow, which may contribute to the observed axonal turning. This method of flow-based guidance was successfully used to fasciculate one advancing axon onto another, showcasing the potential of this technique to be used for the formation of in vitro neuronal circuits.

  11. Optical guidance vidicon test program

    NASA Technical Reports Server (NTRS)

    Eiseman, A. R.; Stanton, R. H.; Voge, C. C.

    1976-01-01

    A laboratory and field test program was conducted to quantify the optical navigation parameters of the Mariner vidicons. A scene simulator and a camera were designed and built for vidicon tests under a wide variety of conditions. Laboratory tests characterized error sources important to the optical navigation process and field tests verified star sensitivity and characterized comet optical guidance parameters. The equipment, tests and data reduction techniques used are described. Key test results are listed. A substantial increase in the understanding of the use of selenium vidicons as detectors for spacecraft optical guidance was achieved, indicating a reduction in residual offset errors by a factor of two to four to the single pixel level.

  12. Teleautonomous guidance for mobile robots

    NASA Technical Reports Server (NTRS)

    Borenstein, J.; Koren, Y.

    1990-01-01

    Teleautonomous guidance (TG), a technique for the remote guidance of fast mobile robots, has been developed and implemented. With TG, the mobile robot follows the general direction prescribed by an operator. However, if the robot encounters an obstacle, it autonomously avoids collision with that obstacle while trying to match the prescribed direction as closely as possible. This type of shared control is completely transparent and transfers control between teleoperation and autonomous obstacle avoidance gradually. TG allows the operator to steer vehicles and robots at high speeds and in cluttered environments, even without visual contact. TG is based on the virtual force field (VFF) method, which was developed earlier for autonomous obstacle avoidance. The VFF method is especially suited to the accommodation of inaccurate sensor data (such as that produced by ultrasonic sensors) and sensor fusion, and allows the mobile robot to travel quickly without stopping for obstacles.

  13. Review of soil contamination guidance

    SciTech Connect

    Mueller, M.A.; Kennedy, W.E. Jr.; Soldat, J.K.

    1981-08-01

    A review of existing and proposed radioactive soil contamination standards and guidance was conducted for United Nuclear Corporation (UNC), Office of Surplus Facilities Management. Information was obtained from both government agencies and other sources during a literature survey. The more applicable standards were reviewed, evaluated, and summarized. Information pertaining to soil contamination for both facility operation and facility decommissioning was obtained from a variety of sources. These sources included: the Code of Federal Regulations, regulatory guides, the Federal Register, topical reports written by various government agencies, topical reports written by national laboratories, and publications from the American National Standards Institute (ANSI). It was difficult to directly compare the standards and guidance obtained from these sources since each was intended for a specific situation and different units or bases were used. However, most of the information reviewed was consistent with the philosophy of maintaining exposures at levels as low as reasonably achievable (ALARA).

  14. Guidance on future art commissioning.

    PubMed

    2009-05-01

    Delegates at Building Better Healthcare's recent "National Patient Environment and the Arts Conference 2009" in London heard how national public arts think tank ixia has appointed Bristol-based arts and wellbeing development agency Willis Newson to write "concise and convincing guidance" on commissioning art for new healthcare facilities. A key message, during a joint presentation, was that integrating artwork into hospitals and other healthcare premises requires the earliest possible consideration to reap the maximum rewards.

  15. Mars Science Laboratory Entry Guidance

    NASA Technical Reports Server (NTRS)

    Mendeck, Gavin F.

    2011-01-01

    The Mars Science Laboratory will be the first Mars mission to attempt a guided entry with the objective of safely delivering the entry vehicle to a survivable parachute deploy state within 12.5 km of the pre-designated parachute deploy coordinates. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control range based on deviations in range, altitude rate, and drag acceleration from a reference trajectory. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Performance tradeoffs between ellipse size and deploy altitude will be presented, along with imposed constraints of entry acceleration and heating. Performance sensitivities to the bank reversal deadbands, heading alignment, attitude initialization error, and entry delivery errors are presented.

  16. A new terminal guidance sensor system for asteroid intercept or rendezvous missions

    NASA Astrophysics Data System (ADS)

    Lyzhoft, Joshua; Basart, John; Wie, Bong

    2016-02-01

    This paper presents the initial conceptual study results of a new terminal guidance sensor system for asteroid intercept or rendezvous missions, which explores the use of visual, infrared, and radar devices. As was demonstrated by NASA's Deep Impact mission, visual cameras can be effectively utilized for hypervelocity intercept terminal guidance for a 5 kilometer target. Other systems such as Raytheon's EKV (Exoatmospheric Kill Vehicle) employ a different scheme that utilizes infrared target information to intercept ballistic missiles. Another example that uses infrared information is the NEOWISE telescope, which is used for asteroid detection and tracking. This paper describes the signal-to-noise ratio estimation problem for infrared sensors, minimum and maximum range of detection, and computational validation using GPU accelerated simulations. Small targets (50-100 m in diameter) are considered, and scaled polyhedron models of known objects, such as the Rosetta mission's Comet 67P/Churyumov-Gerasimenko, 101,955 Bennu, target of the OSIRIS-REx mission, and asteroid 433 Eros, are utilized. A parallelized ray tracing algorithm to simulate realistic surface-to-surface shadowing of a given celestial body is developed. By using the simulated models and parameters given from the formulation of the different sensors, impact mission scenarios are used to verify the feasibility for intercepting a small target.

  17. An Explicit Linear Filtering Solution for the Optimization of Guidance Systems with Statistical Inputs

    NASA Technical Reports Server (NTRS)

    Stewart, Elwood C.

    1961-01-01

    The determination of optimum filtering characteristics for guidance system design is generally a tedious process which cannot usually be carried out in general terms. In this report a simple explicit solution is given which is applicable to many different types of problems. It is shown to be applicable to problems which involve optimization of constant-coefficient guidance systems and time-varying homing type systems for several stationary and nonstationary inputs. The solution is also applicable to off-design performance, that is, the evaluation of system performance for inputs for which the system was not specifically optimized. The solution is given in generalized form in terms of the minimum theoretical error, the optimum transfer functions, and the optimum transient response. The effects of input signal, contaminating noise, and limitations on the response are included. From the results given, it is possible in an interception problem, for example, to rapidly assess the effects on minimum theoretical error of such factors as target noise and missile acceleration. It is also possible to answer important questions regarding the effect of type of target maneuver on optimum performance.

  18. Analysis of septic morbidity following gunshot wounds to the colon: the missile is an adjuvant for abscess.

    PubMed

    Poret, H A; Fabian, T C; Croce, M A; Bynoe, R P; Kudsk, K A

    1991-08-01

    Over a 7-year period, 151 patients with gunshot wounds to the colon surviving beyond 24 hours were managed. The bullet was retained in the body in 66% and exited in 34%. Thirty-four (23%) developed major septic complications (diffuse peritonitis, 21%; intraperitoneal abscesses 24%; and extraperitoneal abdominal abscesses, 56%). The septic complication rate was 26% in the bullet-present group compared with 16% in the remainder (p less than 0.15). The increased septic rate in those with bullets present was the result of abscesses developing around the retained missile. That group with missile abscesses had a lesser degree of injury as measured by the abdominal trauma index compared with the other patients with septic complications (p less than 0.001). Fifteen (79%) of the 19 patients with missile and missile track abscesses had them develop in the psoas muscle. These abscesses occur by fecal contamination of the muscle following inoculation by the bullet, which passes through the large bowel. Computed tomography-guided and operative drainage tend to fail if the foreign body is not removed. Computed tomography-guided or operative drainage should be successful in draining missile track abscesses when the bullet has exited the patient. PMID:1831510

  19. Analysis of the Dryden Wet Bulb GLobe Temperature Algorithm for White Sands Missile Range

    NASA Technical Reports Server (NTRS)

    LaQuay, Ryan Matthew

    2011-01-01

    In locations where workforce is exposed to high relative humidity and light winds, heat stress is a significant concern. Such is the case at the White Sands Missile Range in New Mexico. Heat stress is depicted by the wet bulb globe temperature, which is the official measurement used by the American Conference of Governmental Industrial Hygienists. The wet bulb globe temperature is measured by an instrument which was designed to be portable and needing routine maintenance. As an alternative form for measuring the wet bulb globe temperature, algorithms have been created to calculate the wet bulb globe temperature from basic meteorological observations. The algorithms are location dependent; therefore a specific algorithm is usually not suitable for multiple locations. Due to climatology similarities, the algorithm developed for use at the Dryden Flight Research Center was applied to data from the White Sands Missile Range. A study was performed that compared a wet bulb globe instrument to data from two Surface Atmospheric Measurement Systems that was applied to the Dryden wet bulb globe temperature algorithm. The period of study was from June to September of2009, with focus being applied from 0900 to 1800, local time. Analysis showed that the algorithm worked well, with a few exceptions. The algorithm becomes less accurate to the measurement when the dew point temperature is over 10 Celsius. Cloud cover also has a significant effect on the measured wet bulb globe temperature. The algorithm does not show red and black heat stress flags well due to shorter time scales of such events. The results of this study show that it is plausible that the Dryden Flight Research wet bulb globe temperature algorithm is compatible with the White Sands Missile Range, except for when there are increased dew point temperatures and cloud cover or precipitation. During such occasions, the wet bulb globe temperature instrument would be the preferred method of measurement. Out of the 30

  20. Reconnaissance radiological characterization for the White Point Nike Missile Site, San Pedro, California

    SciTech Connect

    Espegren, M.L.; Jensen, M.K.; Pierce, G.A. ); Smith, S.M. )

    1993-01-01

    This report is the result of field work performed at the former White Point Nike Missile Site, San Pedro, California. The Hazardous Waste Remedial Actions Program tasked the Oak Ridge National Laboratory Pollutant Assessments Group in Grand Junction, Colo., with this project. The objective was to determine whether or not radioisotopes possibly associated with past Department of Defense (DOD) operations were present and within accepted background levels. The radiation survey was accomplished by performing three independent radiation surveys, both outdoors and indoors, and random soil sampling. Initially, the site was land surveyed to develop a grid block system. A background radiation investigation was performed out in the San Pedro area.

  1. Shock capturing finite difference algorithms for supersonic flow past fighter and missile type configurations

    NASA Technical Reports Server (NTRS)

    Osher, S.

    1984-01-01

    The construction of a reliable, shock capturing finite difference method to solve the Euler equations for inviscid, supersonic flow past fighter and missile type configurations is highly desirable. The numerical method must have a firm theoretical foundation and must be robust and efficient. It should be able to treat subsonic pockets in a predominantly supersonic flow. The method must also be easily applicable to the complex topologies of the aerodynamic configuration under consideration. The ongoing approach to this task is described and for steady supersonic flows is presented. This scheme is the basic numerical method. Results of work obtained during previous years are presented.

  2. Bumblebee program, aerodynamic data. Part 2: Flow fields at Mach number 2.0. [supersonic missiles

    NASA Technical Reports Server (NTRS)

    Barnes, G. A.; Cronvich, L. L.

    1979-01-01

    Available flow field data which can be used in validating theoretical procedures for computing flow fields around supersonic missiles are presented. Tabulated test data are given which define the flow field around a conical-nosed cylindrical body in a crossflow plane corresponding to a likely tail location. The data were obtained at a Mach number of 2.0 for an angle of attack of 0 to 23 degrees. The data define the flow field for cases both with and without a forward wing present.

  3. Reconnaissance radiological characterization for the White Point Nike Missile Site, San Pedro, California

    SciTech Connect

    Espegren, M.L.; Jensen, M.K.; Pierce, G.A.; Smith, S.M.

    1993-05-01

    This report is the result of field work performed at the former White Point Nike Missile Site, San Pedro, California. The Hazardous Waste Remedial Actions Program tasked the Oak Ridge National Laboratory Pollutant Assessments Group in Grand Junction, Colo., with this project. The objective was to determine whether or not radioisotopes possibly associated with past Department of Defense (DOD) operations were present and within accepted background levels. The radiation survey was accomplished by performing three independent radiation surveys, both outdoors and indoors, and random soil sampling. Initially, the site was land surveyed to develop a grid block system. A background radiation investigation was performed out in the San Pedro area.

  4. Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds (The Efficiency of Shock Diffusers)

    NASA Technical Reports Server (NTRS)

    Oswatitsch, K.

    1947-01-01

    The problem of the intake of air is treated for a missile flying at supersonic speeds and of changing the kinetic energy of the air into pressure with the least possible losses. Calculations are carried out concerning the results which can be attained. After a discussion of several preliminary experiments, the practical solution of the problem at hand is indicated by model experiments. The results proved very satisfactory in view of the results which had been attained previously and the values which were anticipated theoretically.

  5. Supersonic aerodynamic characteristics of a tail-control cruciform maneuverable missile with and without wings

    NASA Technical Reports Server (NTRS)

    Spearman, M. L.

    1983-01-01

    The aerodynamic characteristics for a winged and wingless cruciform missile configuration were examined. The configuration had an ogive-cylinder body with a 3.5 caliber forebody; an overall length-to-diameter ratio of 11.667; and had cruciform tails that were trapezoidal in planform. Tests were made both with and without 72.9 degree cruciform delta wings. The investigation was made for Mach numbers from 1.50 to 4.63, roll attitudes of 0 degrees and 45 degrees, angles of attack from -4 degrees to 22 degrees, and tail control deflections from 10 degrees to -40 degrees.

  6. Army Tactical Missile System (TACMS) Block II Insensitive Munitions Test Results

    NASA Astrophysics Data System (ADS)

    Fisher, Jamie M.; Nelson, Steven G.

    2002-04-01

    The Army TACMS Block II missile system provides the soldier with long range precision fire against moving armored combat vehicles in support of deep operations beyond the capability of other currently existing munitions. As part of an ongoing IM program for the ATACMS/BAT, warhead components were subject to IM threats identified in the system's Threat Hazard Assessment. These tests were conducted to assess the reaction of the Block II warhead, containing BAT submunitions, to bullet impact, fragment impact and fast cook-off. This paper will provide a summary of the test item configurations, test setups, results and preliminary assessments.

  7. BUILDING A196 BARRACKS, SECOND FLOOR PLAN. Naval Guided Missile and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    BUILDING A-196 BARRACKS, SECOND FLOOR PLAN. Naval Guided Missile and Tactical Data System School, Naval Schools Command, Mare Island, CA. Milton T. Pflueger, Architect, 580 Market Street, San Francisco, CA. Sheet 127 to 145, specification 36050/61, approved for the Bureau of Yards and Docks, October 26, 1961. Yards and Docks drawing no. 892275; DPWO drawing no. B-75275; file no. 930-CR-2. 72 cm x 98 cm. Sepia tone print - Mare Island Naval Shipyard, Guard House & Barracks, Railroad Avenue near Eighteenth Street, Vallejo, Solano County, CA

  8. BUILDING A196 BARRACKS, FIRST FLOOR PLAN. Naval Guided Missile and ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    BUILDING A-196 BARRACKS, FIRST FLOOR PLAN. Naval Guided Missile and Tactical Data System School, Naval Schools Command, Mare Island, California. Milton T. Pflueger, Architect, 580 Market Street, San Francisco, CA. Sheet 126 of 145, specification 36050-61, approved for the Bureau of Yards and Docks, October 26, 1961. Yards and Docks drawing no. 892274; DPWO drawing no. B-75274; file no. 930-CR-1. 72 cm x 98 xm. Sepia tone print - Mare Island Naval Shipyard, Guard House & Barracks, Railroad Avenue near Eighteenth Street, Vallejo, Solano County, CA

  9. Complete analysis of steady and transient missile aerodynamic/propulsive/plume flowfield interactions

    NASA Astrophysics Data System (ADS)

    York, B. J.; Sinha, N.; Dash, S. M.; Hosangadi, A.; Kenzakowski, D. C.; Lee, R. A.

    1992-07-01

    The analysis of steady and transient aerodynamic/propulsive/plume flowfield interactions utilizing several state-of-the-art computer codes (PARCH, CRAFT, and SCHAFT) is discussed. These codes have been extended to include advanced turbulence models, generalized thermochemistry, and multiphase nonequilibrium capabilities. Several specialized versions of these codes have been developed for specific applications. This paper presents a brief overview of these codes followed by selected cases demonstrating steady and transient analyses of conventional as well as advanced missile systems. Areas requiring upgrades include turbulence modeling in a highly compressible environment and the treatment of particulates in general. Recent progress in these areas are highlighted.

  10. Low-Cost Phased Array Antenna for Sounding Rockets, Missiles, and Expendable Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Mullinix, Daniel; Hall, Kenneth; Smith, Bruce; Corbin, Brian

    2012-01-01

    A low-cost beamformer phased array antenna has been developed for expendable launch vehicles, rockets, and missiles. It utilizes a conformal array antenna of ring or individual radiators (design varies depending on application) that is designed to be fed by the recently developed hybrid electrical/mechanical (vendor-supplied) phased array beamformer. The combination of these new array antennas and the hybrid beamformer results in a conformal phased array antenna that has significantly higher gain than traditional omni antennas, and costs an order of magnitude or more less than traditional phased array designs. Existing omnidirectional antennas for sounding rockets, missiles, and expendable launch vehicles (ELVs) do not have sufficient gain to support the required communication data rates via the space network. Missiles and smaller ELVs are often stabilized in flight by a fast (i.e. 4 Hz) roll rate. This fast roll rate, combined with vehicle attitude changes, greatly increases the complexity of the high-gain antenna beam-tracking problem. Phased arrays for larger ELVs with roll control are prohibitively expensive. Prior techniques involved a traditional fully electronic phased array solution, combined with highly complex and very fast inertial measurement unit phased array beamformers. The functional operation of this phased array is substantially different from traditional phased arrays in that it uses a hybrid electrical/mechanical beamformer that creates the relative time delays for steering the antenna beam via a small physical movement of variable delay lines. This movement is controlled via an innovative antenna control unit that accesses an internal measurement unit for vehicle attitude information, computes a beam-pointing angle to the target, then points the beam via a stepper motor controller. The stepper motor on the beamformer controls the beamformer variable delay lines that apply the appropriate time delays to the individual array elements to properly

  11. High angle canard missile test in the Ames 11-foot transonic wind tunnel

    NASA Technical Reports Server (NTRS)

    Schwind, R. G.

    1978-01-01

    Four blunted ogive-cylinder missile models with a length-to-diameter ratio of 10.4 were tested at transonic speeds and large angles of attack. The configurations are: body, body with tail panels, body with canards, and body with canards and tails. Forces and moments from the entire model and each of the eight fins were measured over the pitch range of 20 deg to 50 deg and 0 deg to 45 deg roll. Canard deflection angles between 0 deg and 15 deg were tested. Exploratory vapor screen flow visualization testing was also performed. Sample force and moment data are reported along with observations from the vapor screen tests.

  12. Experimental study of tail-span effects on a generic canard-controlled missile

    NASA Technical Reports Server (NTRS)

    Blair, A. B., Jr.; Dillon, James L.; Watson, Carolyn B.

    1992-01-01

    An experimental investigation was conducted on a cruciform canard controlled missile configuration to determine the effects of tail span/canard span ratio on controllability. The investigation was conducted over the Mach number range of 1.75 to 3.50. Reductions of tail span/canard span ratio produced lower static margins and higher trim angle of attack. The results show that canard controls can provide pitch- and yaw-control as well as roll-control by proper selection of the tail span/canard span ratio.

  13. Remote control canard missile with a free-rolling tail brake torque system

    NASA Technical Reports Server (NTRS)

    Blair, A. B., Jr.

    1981-01-01

    An experimental wind-tunnel investigation has been conducted at supersonic Mach numbers to determine the static aerodynamic characteristics of a cruciform canard-controlled missile with fixed and free-rolling tail-fin afterbodies. Mechanical coupling effects of the free-rolling tail afterbody were investigated using an electronic/electromagnetic brake system that provides arbitrary tail-fin brake torques with continuous measurements of tail-to-mainframe torque and tail-roll rate. Results are summarized to show the effects of fixed and free-rolling tail-fin afterbodies that include simulated measured bearing friction torques on the longitudinal and lateral-directional aerodynamic characteristics.

  14. 76 FR 43332 - Guidance for Industry and Food and Drug Administration Staff; Class II Special Controls Guidance...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-20

    ...; Class II Special Controls Guidance Document: Focused Ultrasound Stimulator System for Aesthetic Use... Guidance Document: Focused Ultrasound Stimulator System for Aesthetic Use.'' This guidance document... ``Class II Special Controls Guidance Document: Focused Ultrasound Stimulator System for Aesthetic Use''...

  15. The synergistic roles of test and simulation in the life cycle of the Army Tactical Missile System

    NASA Astrophysics Data System (ADS)

    Curry, David M.; Ricks, Gayle; Thomas, Tony L.

    2010-04-01

    The Army Tactical Missile System (ATACMS) has been fielded with the US Army for almost 20 years as a deep strike precision weapon, capable of engaging time critical targets at high precision under all weather conditions. This paper will describe the use of the HWIL simulation in the design of the missile, validation of the simulation, the role of the simulation in the production and test process, how the simulation is used to support system shelf life and obsolescence issues and how the simulation is used to answer critical user questions on the performance of the system.

  16. Tests of the Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Wing Modifications

    NASA Technical Reports Server (NTRS)

    Graham, David

    1950-01-01

    Wind-tunnel tests were conducted to determine the longitudinal stability characteristics of a full-scale Northrop XSSM-A-3 missile. Various wing modifications were investigated in an effort to provide a configuration that would maintain longitudinal stability to lift coefficients necessary for landing the missile during flight tests. The results of the tests led to the choice of a wing with an increased leading-edge radius. A short discussion of the results is presented, but no analysis of the data has been made in order to make the data available as soon as possible.

  17. Test wells TW1 and TW2, and TW3, White Sands Missile Range, Otero County, New Mexico

    USGS Publications Warehouse

    Myers, R.G.; Pinckley, K.M.

    1987-01-01

    Three test wells, TW1, TW2, and TW3, were drilled at White Sands Missile Range in south-central New Mexico in July, August, and October 1983 as part of a joint military training program sponsored by the U.S. Navy and U.S. Army in July, August, and October 1983. The test wells were drilled as exploratory and monitoring wells for the toxic waste storage facility at White Sands Missile Range. Information obtained from these wells includes lithologic logs for all wells and borehole-geophysical logs for the cased wells. (Author 's abstract)

  18. Research strategy for the electro-optics sensors domain of the Materials and Components for Missiles Innovative Technology Partnership

    NASA Astrophysics Data System (ADS)

    Bray, Mark; Panella, Isabella

    2010-04-01

    We describe the Materials and Components for Missile (MCM) Innovation and Technology Partnership (ITP) programme. The MCM - ITP is an Anglo-French research programme started in 2007 to encourage early stage research in future weapons technology. SELEX Galileo leads the domain related to the Electro-Optic Sensor within future guided weapons. Our objective is to capture cutting edge ideas in the research community and develop them for exploitation in future missile generations. We provide a view of two areas where we believe development of enhanced seeker capability should be focussed. Examples of current research within and outside the ITP that may be harnessed to deliver these capabilities are provided.

  19. Flight Guidance System Requirements Specification

    NASA Technical Reports Server (NTRS)

    Miller, Steven P.; Tribble, Alan C.; Carlson, Timothy M.; Danielson, Eric J.

    2003-01-01

    This report describes a requirements specification written in the RSML-e language for the mode logic of a Flight Guidance System of a typical regional jet aircraft. This model was created as one of the first steps in a five-year project sponsored by the NASA Langley Research Center, Rockwell Collins Inc., and the Critical Systems Research Group of the University of Minnesota to develop new methods and tools to improve the safety of avionics designs. This model will be used to demonstrate the application of a variety of methods and techniques, including safety analysis of system and subsystem requirements, verification of key properties using theorem provers and model checkers, identification of potential sources mode confusion in system designs, partitioning of applications based on the criticality of system hazards, and autogeneration of avionics quality code. While this model is representative of the mode logic of a typical regional jet aircraft, it does not describe an actual or planned product. Several aspects of a full Flight Guidance System, such as recovery from failed sensors, have been omitted, and no claims are made regarding the accuracy or completeness of this specification.

  20. Family planning methods: new guidance.

    PubMed

    1996-10-01

    Presented in this report are the recommendations of two expert groups, the Technical Guidance/Competence Working Group of the US Agency for International Development's Maximizing Access and Quality Initiative and the World Health Organization's Family Planning and Population Unit, regarding currently available family planning methods. The former group addressed key biomedical questions and formulated recommendations about 11 groups of family planning methods: combined oral contraceptives, progestin-only pills during breast feeding, progestin-only injectables, combined injectable contraceptives, Norplant implants, copper-bearing IUDs, tubal occlusion, vasectomy, lactational amenorrhea method, natural family planning, and barrier methods. A table presents the relative importance, by method, of procedures such as pelvic exam, blood pressure reading, breast exam, and screening for sexually transmitted diseases and cervical cancer. The medical eligibility recommendations for each method are also presented in tabular form, with four categories for temporary methods: 1) no restrictions on use, 2) advantages generally outweigh theoretical or proven risks, 3) theoretical or proven risks usually outweigh the advantages, and 4) unacceptable health risks. Included among the 41 conditions for which eligibility criteria are specified are age, smoking, thromboembolic disorder, headaches, irregular vaginal bleeding, family history of breast cancer, obesity, drug interactions, parity, breast feeding, postpartum, and postabortion. The new guidance presented in this report enables providers to give family planning clients expanded contraceptive choices while ensuring method safety and effectiveness. PMID:9342775