Practical Applications of a Building Method to Construct Aerodynamic Database of Guided Missile Using Wind Tunnel Test Data

NASA Astrophysics Data System (ADS)

Kim, Duk-hyun; Lee, Hyoung-Jin

2018-04-01

A study of efficient aerodynamic database modeling method was conducted. A creation of database using periodicity and symmetry characteristic of missile aerodynamic coefficient was investigated to minimize the number of wind tunnel test cases. In addition, studies of how to generate the aerodynamic database when the periodicity changes due to installation of protuberance and how to conduct a zero calibration were carried out. Depending on missile configurations, the required number of test cases changes and there exist tests that can be omitted. A database of aerodynamic on deflection angle of control surface can be constituted using phase shift. A validity of modeling method was demonstrated by confirming that the result which the aerodynamic coefficient calculated by using the modeling method was in agreement with wind tunnel test results.

Debugging embedded computer programs. [tactical missile computers

NASA Technical Reports Server (NTRS)

Kemp, G. H.

1980-01-01

Every embedded computer program must complete its debugging cycle using some system that will allow real time debugging. Many of the common items addressed during debugging are listed. Seven approaches to debugging are analyzed to evaluate how well they treat those items. Cost evaluations are also included in the comparison. The results indicate that the best collection of capabilities to cover the common items present in the debugging task occurs in the approach where a minicomputer handles the environment simulation with an emulation of some kind representing the embedded computer. This approach can be taken at a reasonable cost. The case study chosen is an embedded computer in a tactical missile. Several choices of computer for the environment simulation are discussed as well as different approaches to the embedded emulator.

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.

Supersonic aerodynamic characteristics of conformal carriage monoplanar circular missile configurations with low-profile quadriform tail fins

NASA Technical Reports Server (NTRS)

Blair, A. B., Jr.

1990-01-01

Wind tunnel tests were conducted on monoplanar circular missile configurations with low-profile quadriform tail fins to provide an aerodynamic data base to study and evaluate air-launched missile candidates for efficient conformal carriage on supersonic-cruise-type aircraft. The tests were conducted at Mach numbers from 1.70 to 2.86 for a constant Reynolds number per foot of 2,000,000. Selected test results are presented to show the effects of tail-fin dihedral angle, wing longitudinal and vertical location, and nose-body strakes on the static longitudinal and lateral-directional aerodynamic stability and control characteristics.

Status report on the Aeronautical Research Institute of Sweden version of the missile aerodynamics program LARV, for calculation of static aerodynamic properties and longitudinal aerodynamic damping derivatives. Part 1: Theory

NASA Astrophysics Data System (ADS)

Weibust, E.

Improvements to a missile aerodynamics program which enable it to (a) calculate aerodynamic coefficients as input for a flight mechanics model, (b) check manufacturers' data or estimate performance from photographs, (c) reduce wind tunnel testing, and (d) aid optimization studies, are discussed. Slender body theory is used for longitudinal damping derivatives prediction. Program predictions were compared to known values. Greater accuracy is required in the estimation of drag due to excrescences on actual missile configurations, the influence of a burning motor, and nonlinear effects in the stall region. Prediction of pressure centers on wings and on bodies in presence of wings must be improved.

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.

Prediction of the Aerodynamic Characteristics of Cruciform Missiles Including Effects of Roll Angle and Control Deflection

DTIC Science & Technology

1986-08-01

CHARACTERISTICS OF CRU.CIFORM MISSILES INCLUDING EFFECTS OF ROLL ANGLE AND CONTROL DEFLECTION N by Daniel J. Lesieutre Michael R. Mendenhall Susana M. Nazario...ANGLE AND CONTROL DEFLECTION Daniel J. Lesieutre Michael R. Mendenhal. Susana M. Nazario Nielsen Engineering & Research, Inc.00 Mountain View, CA 94043...Lo PREDICTION OF THE AERODYNAMIC CHARACTERISTICS OF CRU.CIFORM MISSILES - INCLUDING EFFECTS OF ROLL ANGLE AND CONTROL DEFLECTION by Daniel J

Ramjet Tactical Missile Propulsion Status

DTIC Science & Technology

2002-11-01

EM Linear Actuator Figure 25 - MAR C-R-282Ramjet Figure 26 - AL4RC-R-282Ramjet Testing HIGH SPEED ANTI-RADIATION MISSILE DEMONSRATION ( HSAD ) The High...Speed Anti-Radiation Demonstration ( HSAD ) Project is focused on maturing an advanced propulsion concept that is compatible with the guidance...navigation and control (GNC) section of the Air-Ground Missile-88E (AGM-88f), Advanced Anti-Radiation Guided Missile (AARGM) Program. The HSAD Project

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.

Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

NASA Technical Reports Server (NTRS)

Allen, Julian H

1957-01-01

An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry.

Missile Aerodynamics

DTIC Science & Technology

1979-02-01

aimed to emphasize these differences in the aerodynamic design features of both guided and unguided weapons. In addition to treating the component parts...the subject. Lectures generally started with a review of fundamentals and paid particular attention to practical methods of estimation and design and...George G Brebner Aerodynamics Department Royal Aircraft Establishment Farnborough, Hants, GU14 6TD, UK SUMMARY The differences in design objectives and

Supersonic aerodynamic characteristics of a maneuvering canard-controlled missile with fixed and free-rolling tail fins

NASA Technical Reports Server (NTRS)

Blair, A. B., Jr.

1990-01-01

Wind tunnel investigations were conducted on a generic cruciform canard-controlled missile configuration. The model featured fixed or free-rolling tail-fin afterbodies to provide an expanded aerodynamic data base with particular emphasis on alleviating large induced rolling moments and/or for providing canard roll control throughout the entire test angle-of-attack range. The tests were conducted in the NASA Langley Unitary Plan Wind Tunnel at Mach numbers from 2.50 to 3.50 at a constant Reynolds number per foot of 2.00 x 10 to the 6th. Selected test results are presented to show the effects of a fixed or free-rolling tail-fin afterbody on the static longitudinal and lateral-directional aerodynamic characteristics of a canard-controlled missile with pitch, yaw, and roll control at model roll angles of 0 deg and 45 deg.

A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

NASA Technical Reports Server (NTRS)

Allen, H Julian; Eggers, A J , Jr

1958-01-01

A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.

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

Historical review of missile aerodynamic developments

NASA Technical Reports Server (NTRS)

Spearman, M. Leroy

1989-01-01

A comprehensive development history to about 1970 is presented for missile technologies and their associated capabilities and difficulties. Attention is given to the growth of an experimental data base for missile design, as well as to the critical early efforts to develop analytical methods applicable to missiles. Most of the important missile development efforts made during the period from the end of the Second World War to the early 1960s were based primarily on experiences gained through wind tunnel and flight testing; analytical techniques began to demonstrate their usefulness in the design process only in the late 1960s.

Survey of engineering computational methods and experimental programs for estimating supersonic missile aerodynamic characteristics

NASA Technical Reports Server (NTRS)

Sawyer, W. C.; Allen, J. M.; Hernandez, G.; Dillenius, M. F. E.; Hemsch, M. J.

1982-01-01

This paper presents a survey of engineering computational methods and experimental programs used for estimating the aerodynamic characteristics of missile configurations. Emphasis is placed on those methods which are suitable for preliminary design of conventional and advanced concepts. An analysis of the technical approaches of the various methods is made in order to assess their suitability to estimate longitudinal and/or lateral-directional characteristics for different classes of missile configurations. Some comparisons between the predicted characteristics and experimental data are presented. These comparisons are made for a large variation in flow conditions and model attitude parameters. The paper also presents known experimental research programs developed for the specific purpose of validating analytical methods and extending the capability of data-base programs.

Ballistic Missile Intercept from UCAV

DTIC Science & Technology

2011-12-01

aerodynamic forces acting on the ballistic missile , generates a ballistic flight path of the ballistic missile target based on the model developed by...for use against ballistic missile targets) [14] Hutchins, R., ME4703 “ Missile Flight Analysis ” Course Notes, Spring 2005. [15] Stevens, B., and...NAVAL POSTGRADUATE SCHOOL MONTEREY, CALIFORNIA THESIS Approved for public release; distribution is unlimited BALLISTIC MISSILE

Wind-tunnel studies of the effects of simulated damage on the aerodynamic characteristics of airplanes and missiles

NASA Technical Reports Server (NTRS)

Spearman, M. L.

1979-01-01

In order to assess the effects on static aerodynamic characteristics of battle damage to an aircraft or missile, wind tunnel studies were performed on models from which all or parts of the wing or horizontal or vertical tail had been removed. The effects of damage on the lift, longitudinal stability, lateral stability and directional stability of a swept-wing fighter are presented, along with the effects of wing removal on the control requirements of a delta-wing fighter. Results indicate that the loss of a major part of the vertical tail will probably result in the loss of the aircraft at any speed, while the loss of major parts of the horizontal tail generally results in catastrophic instability at subsonic speeds but, at low supersonic speeds, may allow the aircraft to return to friendly territory before pilot ejection. Major damage to the wing may be sustained without the loss of aircraft or pilot. The loss of some of the aerodynamic surfaces of cruise or surface-to-air missiles may result in catastrophic instability or may permit a ballistic trajectory to be maintained, depending upon the location of the lost surface with respect to the center of gravity of the missile.

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.

A design proposal of a certain missile tactical command system based on Beidou satellite communication and GPS positioning techniques

NASA Astrophysics Data System (ADS)

Ma, Jian; Hao, Yongsheng; Miao, Jian; Zhang, Jianmao

2007-11-01

This paper introduced a design proposal of tactical command system that applied to a kind of anti-tank missile carriers. The tactical command system was made up of embedded computer system based on PC104 bus, Linux operating system, digital military map, Beidou satellite communication equipments and GPS positioning equipments. The geographic coordinates was measured by the GPS receiver, the positioning data, commands and information were transmitted real-time between tactical command systems, tactical command systems and command center, by the Beidou satellite communication systems. The Beidou satellite communication equipments and GPS positioning equipments were integrated to an independent module, exchanging data with embedded computer through RS232 serial ports and USB ports. The decision support system software based on information fusion, calculates positioning data, geography information and battle field information synthetically, shows the position of allies and the position of enemy on the military map, and assesses the various threats of different enemy objects, educes a situation assessment and threat assessment.

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.

Regional Power Ballistic Missiles. An Emerging Threat to Deployed US forces?

DTIC Science & Technology

1990-05-01

packaging and dispensing submunitions are straightforward: the MLRS submunitions are simply nestled in polyurethane foam ; and cluster munitions such as the...several U.S. mobile ballistic missile systems, both ground-launched and air-launched. The Army Tactical Missile System ( ATACMS ), a mobile TBM...weight class have also been presented. (99:185-187) Warheads with "light" submunitions are used on the US LANCE and Army Tactical Missile System ( ATACMS

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

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.

Supersonic aerodynamic characteristics of a Sparrow 3 type missile model with wing controls and comparison with existing tail-control results

NASA Technical Reports Server (NTRS)

Monta, W. J.

1977-01-01

An experimental investigation was conducted on a model of a wing control version of the Sparrow III type missile to determine the static aerodynamic characteristics over an angle of attack range from 0 deg to 40 deg for Mach numbers from 1.50 to 4.60.

The equivalent angle-of-attack method for estimating the nonlinear aerodynamic characteristics of missile wings and control surfaces

NASA Technical Reports Server (NTRS)

Hemsch, M. J.; Nielsen, J. N.

1982-01-01

A method has been developed for estimating the nonlinear aerodynamic characteristics of missile wing and control surfaces. The method is based on the following assumption: if a fin on a body has the same normal-force coefficient as a wing alone composed of two of the same fins joined together at their root chords, then the other force and moment coefficients of the fin and the wing alone are the same including the nonlinearities. The method can be used for deflected fins at arbitrary bank angles and at high angles of attack. In the paper, a full derivation of the method is given, its accuracy demonstrated and its use in extending missile data bases is shown.

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

Symmetric Missile Dynamic Instabilities - A Review

DTIC Science & Technology

1980-03-01

and a Magnus side moment must be added to the total aerodynamic moment. Since statically stable missiles are usually spun to reduce the effect of...Identify by block~ numbef) Symmetric Missile Roil Moment Resonance Spin Dynamic Stability Side Moment Damxping Moment Trim Moment Magnus Moment Moving...dlamping moments for nonspin- ning re-entry vehicles, nonlinear Magnus moments for spinning missiles, and internal resonances with moving payload

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.

Theater Missile Defenses and U.S. Foreign Policy

DTIC Science & Technology

1992-01-01

Tactical Missile Defense Initiative, which have as primary objectives the following: (A) The development of deployable and rapidly relocatable...countries as having some form of ballistic missile. Missiles are not only growing in numbers, but also in capabilities. In an even more disturbing trend...are advantageous in that they offer a specific counter to a growing threat that has until now gone unanswered without inherently increasing the

MISSILE DATA COMPENDIUM (DATCOM) User Manual 2014 Revision

DTIC Science & Technology

2014-10-01

2014 revision of the Missile Datcom computer program. It supersedes AFRL-RB- WP-TR-2011-3071. 15. SUBJECT TERMS aerodynamics , stability and control...45 3.1.8 Namelist TRIM - Trim Aerodynamics ............................................................. 46 3.1.9... Aerodynamic Output Summary .......................... 64 4.2 PARTIAL OUTPUT

Bodies with noncircular cross sections and bank-to-turn missiles

NASA Technical Reports Server (NTRS)

Jackson, C. M., Jr.; Sawyer, W. C.

1986-01-01

An evaluation is made of prospective missile applications for noncircular cross section bodies, and of recent developments in bank-to-turn missile configuration aerodynamics. The discussion encompasses cross-flow analysis techniques, as well as study results obtained for bodies with elliptical and square cross sections and with variable cross sections. Attention is given to both the performance advantages and the stability and control problems of bank-to-turn missile configurations; the aerodynamic data presented for monoplanar configurations extend to those incorporating airbreathing propulsion systems.

Aerodynamic Characteristics of a 45 Degree Swept-wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

NASA Technical Reports Server (NTRS)

Oehman, Waldo I; Turner, Kenneth L

1958-01-01

An investigation was performed in the Langley Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 450 swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Also included was a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. Tests were performed at Mach numbers of 1.57, 1.87, 2.16, and 2.53. The Reynolds numbers for the tests, based on the mean aerodynamic chord of the wing, varied from about 0.9 x 10(exp 6) to 5 x 10(exp 6). The results are presented with minimum analysis.

Aerodynamic characteristics of a canard-controlled missile at Mach numbers of 1.5 and 2.0.

NASA Technical Reports Server (NTRS)

Kassner, D. L.; Wettlaufer, B.

1977-01-01

A typical missile model with nose mounted canards and cruciform tail surfaces was tested in the Ames 6- by 6-Foot Wind Tunnel to determine the contributions of the component aerodynamic surfaces to the static aerodynamic characteristics at Mach numbers of 1.5 and 2.0 and Reynolds number of 1 million based on body diameter. Data were obtained at angles of attack ranging from -3 deg to 12 deg for various stages of model build-up (i.e., with and without canard and/or tail surfaces). Results were obtained both with the model unrolled and rolled 45 deg. For the canard and tail arrangements investigated, the model was trimmable at angles of attack up to about 10 deg with canard deflections of 9 deg. Also, the tail arrangements studied provided ample pitch stability. there were no appreciable effects of model roll orientation.

Aerodynamic Performance Predictions of a SA- 2 Missile Using Missile DATCOM

DTIC Science & Technology

2009-09-01

transformation that is given by Eqs. (4) and (5). Eqs. (8)–(10) show the formulation in the body and wind axis terminology. 2,0D AC C kC   L (8) 10 cos...by Teo (2008) using Missile LAB code. However, the missile geometry then was set up from a rudimentary drawing and not one that represented a high...provided by MSIC. These particular cases were run forcing turbulent flow with a surface roughness of 0.001016 cm, which was found by Teo (2008) to

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.

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

USAF Development Of Optical Correlation Missile Guidance

NASA Astrophysics Data System (ADS)

Kaehr, Ronald; Spector, Marvin

1980-12-01

In 1965, the Advanced Development Program (ADP)-679A of the Avionics Laboratory initiated development of guidance systems for stand-off tactical missiles. Employing project engineering support from the Aeronautical Systems Division, WPAFB, the Avionics Laboratory funded multiple terminal guidance concepts and related midcourse navigation technology. Optical correlation techniques which utilize prestored reference information for autonomous target acquisition offered the best near-term opportunity for meeting mission goals. From among the systems studied and flight tested, Aimpoint* optical area guidance provided the best and most consistent performance. Funded development by the Air Force ended in 1974 with a MK-84 guided bomb drop test demonstration at White Sands Missile Range and the subsequent transfer of the tactical missile guidance development charter to the Air Force Armament Laboratory, Eglin AFB. A historical review of optical correlation development within the Avionics Laboratory is presented. Evolution of the Aimpoint system is specifically addressed. Finally, a brief discussion of trends in scene matching technology is presented.

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.

Bodies with noncircular cross sections and bank-to-turn missiles

NASA Technical Reports Server (NTRS)

Jackson, C. M., Jr.; Sawyer, W. C.

1992-01-01

A development status evaluation is presented for the aerodynamics of missile configurations with noncircular cross-sections and bank-to-turn maneuvering systems, giving attention to cases with elliptical and square cross-sections, as well as bodies with variable cross-sections. The assessment of bank-to-turn missile performance notes inherent stability/control problems. A summary and index are provided for aerodynamic data on monoplanar configurations, including those which incorporate airbreathing propulsion systems.

Definition of an anti-missile ballistic defense architecture for Europe

NASA Astrophysics Data System (ADS)

Deas, M.; Tanter, A.

1995-01-01

The end of the Seventies and beginning of the Eighties showed significant technological developments in ballistic missiles, in particular,impact precision. These improvements caused Western strategists to be concerned with use of ballistic missiles equipped with conventional loads against military objectives (the Pact of Varsovie). The concept of ballistic missile tactical had been born. The ballistic vector, which until this time was marked with a 'strategic' label, was then 'standardized' and has interested a number of countries in the process of its development. The world has just entered the era of the ballistic proliferation. From the very start of the Eighties, the United States and, to a lesser degree, NATO lead studies and reflections concerned with defense against tactical ballistic missiles within a East West framework. From these studies the ATBM (Anti Tactical Ballistic Missile) made its appearance. In spite of the attempts at control, missile proliferation has accelerated and led, towards the end of the Eighties and the beginning of the Nineties, to the awakening of a new risk known as proliferating. The 1991 Gulf War was accelerated in this manner. This conflict also clarified the fact that the ballistic weapon constituted a formidable means of pressure for countries which had it, in spite of the PATRIOT, which demonstrated the feasibility of an active defense against ballistic missiles, in spite of their limited performances. This present presentation proposes an overall analysis of the ballistic risk and the possible threat which could result from it and examines the means available for protection against this risk by looking further into all the defensive means. This will constitute the main part of the speech. Lastly, we will endeavor to evaluate the difficulties faced by the architects of the DAMB.

Supersonic aerodynamic characteristics of a low-aspect-ratio missile model with wing and tail controls and with tails in line and interdigitated

NASA Technical Reports Server (NTRS)

Graves, E. B.

1972-01-01

A study has been made to determine the aerodynamic characteristics of a low-aspect ratio cruciform missile model with all-movable wings and tails. The configuration was tested at Mach numbers from 1.50 to 4.63 with the wings in the vertical and horizontal planes and with the wings in a 45 deg roll plane with tails in line and interdigitated.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Mendenhall, M.R.

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 themore » interaction of exhaust plumes with missile airframes.« less

An analysis of aerodynamic requirements for coordinated bank-to-turn autopilots

NASA Technical Reports Server (NTRS)

Arrow, A.

1982-01-01

Two planar missile airframes were compared having the potential for improved bank-to-turn control but having different aerodynamic properties. The comparison was made with advanced level autopilots using both linear and nonlinear 3-D aerodynamic models to obtain realistic missile body angular rates and control surface incidence. Cortical cross-coupling effects are identified and desirable aerodynamics are recommended for improved coordinated (BTT) (CBTT) performance. In addition, recommendations are made for autopilot control law analyses and design techniques for improving CBTT performance.

State-of-the-Art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations

DTIC Science & Technology

1993-11-01

ON COMPLETE MISSILE CONFIGURATIONS BY FRANK G. MOORE WEAPONS SYSTEMS DEPARTMENT NOVEMBER 1993 DTIC ,A -LECTE. DEC 1 3 1993 7;] Approved for public...Di t ib , tio Av J,fia ii !y Cc,,jes Approved for public release; distribution is unlimited. Avii j iUr Di"t NAVAL SURFACE WARFARE CENTER DAHLGREN...CONTENTS Setion 1.0 INTRODUCTION AND BACKGROUND .................... 1 - 1 1.1 USES FOR AERODYNAMICS ........................... 1 - 1 1.2 TYPES OF

Remote control missile model test

NASA Technical Reports Server (NTRS)

Allen, Jerry M.; Shaw, David S.; Sawyer, Wallace C.

1989-01-01

An extremely large, systematic, axisymmetric body/tail fin data base was gathered through tests of an innovative missile model design which is described herein. These data were originally obtained for incorporation into a missile aerodynamics code based on engineering methods (Program MISSILE3), but can also be used as diagnostic test cases for developing computational methods because of the individual-fin data included in the data base. Detailed analysis of four sample cases from these data are presented to illustrate interesting individual-fin force and moment trends. These samples quantitatively show how bow shock, fin orientation, fin deflection, and body vortices can produce strong, unusual, and computationally challenging effects on individual fin loads. Comparisons between these data and calculations from the SWINT Euler code are also presented.

Hyperheat: a thermal signature model for super- and hypersonic missiles

NASA Astrophysics Data System (ADS)

van Binsbergen, S. A.; van Zelderen, B.; Veraar, R. G.; Bouquet, F.; Halswijk, W. H. C.; Schleijpen, H. M. A.

2017-10-01

In performance prediction of IR sensor systems for missile detection, apart from the sensor specifications, target signatures are essential variables. Very often, for velocities up to Mach 2-2.5, a simple model based on the aerodynamic heating of a perfect gas was used to calculate the temperatures of missile targets. This typically results in an overestimate of the target temperature with correspondingly large infrared signatures and detection ranges. Especially for even higher velocities, this approach is no longer accurate. Alternatives like CFD calculations typically require more complex sets of inputs and significantly more computing power. The MATLAB code Hyperheat was developed to calculate the time-resolved skin temperature of axisymmetric high speed missiles during flight, taking into account the behaviour of non-perfect gas and proper heat transfer to the missile surface. Allowing for variations in parameters like missile shape, altitude, atmospheric profile, angle of attack, flight duration and super- and hypersonic velocities up to Mach 30 enables more accurate calculations of the actual target temperature. The model calculates a map of the skin temperature of the missile, which is updated over the flight time of the missile. The sets of skin temperature maps are calculated within minutes, even for >100 km trajectories, and can be easily converted in thermal infrared signatures for further processing. This paper discusses the approach taken in Hyperheat. Then, the thermal signature of a set of typical missile threats is calculated using both the simple aerodynamic heating model and the Hyperheat code. The respective infrared signatures are compared, as well as the difference in the corresponding calculated detection ranges.

Configuration aerodynamics

NASA Technical Reports Server (NTRS)

Polhamus, E. C.; Gloss, B. B.

1981-01-01

Static aerodynamic research related to aircraft configurations in their cruise or combat modes is discussed. Subsonic transport aircraft, transonic tactical aircraft, and slender wing aircraft are considered. The status and plans of Langley's NTF configuration research program are reviewed. Recommendations for near term configuration research are made.

The expectation of applying IR guidance in medium range air-to-air missiles

NASA Astrophysics Data System (ADS)

Li, Lijuan; Liu, Ke

2016-10-01

IR guidance has been widely used in near range dogfight air-to-air missiles while radar guidance is dominant in medium and long range air-to-air missiles. With the development of stealth airplanes and advanced electronic countermeasures, radar missiles have met with great challenges. In this article, the advantages and potential problems of applying IR guidance in medium range air-to-air missiles are analyzed. Approaches are put forward to solve the key technologies including depressing aerodynamic heating, increasing missiles' sensitivity and acquiring target after launch. IR medium range air-to-air missiles are predicted to play important role in modern battle field.

Aerodynamics of an Axisymmetric Missile Concept Having Cruciform Strakes and In-Line Tail Fins From Mach 0.60 to 4.63

NASA Technical Reports Server (NTRS)

Allen, Jerry M.

2005-01-01

An experimental study has been performed to develop a large force and moment aerodynamic data set on a slender axisymmetric missile configuration having cruciform strakes and in-line control tail fins. The data include six-component balance measurements of the configuration aerodynamics and three-component measurements on all four tail fins. The test variables include angle of attack, roll angle, Mach number, model buildup, strake length, nose size, and tail fin deflection angles to provide pitch, yaw, and roll control. Test Mach numbers ranged from 0.60 to 4.63. The entire data set is presented on a CD-ROM that is attached to this paper. The CD-ROM also includes extensive plots of both the six-component configuration data and the three-component tail fin data. Selected samples of these plots are presented in this paper to illustrate the features of the data and to investigate the effects of the test variables.

Computer simulation of a cruise missile using brushless dc motor fin control

NASA Astrophysics Data System (ADS)

Franklin, G. C.

1985-03-01

This thesis describes a computer simulation developed in order to provide a method of establishing the potential of brushless dc motors for applications to tactical cruise missile control surface positioning. In particular, an altitude hold controller has been developed that provides an operational load test condition for the evaluation of the electromechanical actuator. A proportional integral control scheme in conjunction with tachometer feedback provides the position control for the missile tailfin surfaces. The fin control system is further imbedded in a cruise missile model to allow altitude control of the missile. The load on the fin is developed from the dynamic fluid environment that the missile will be operating in and is proportional to such factors as fin size and air density. The program written in CSMP language is suitable for parametric studies including motor and torque load characteristics, and missile and control system parameters.

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.

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.

Unconventional missile concepts from consideration of varied mission requirements

NASA Technical Reports Server (NTRS)

Spearman, M. L.

1984-01-01

Missile concepts for volumetric efficiency, minimum carriage constraints, and aerodynamic performance to achieve mission requirements. The mission requirements considered include air to surface roles such as defense suppression or antishipping where payload and range may have priority over high maneuver capability, and air to air and surface to air roles paying attention to good maneuvering capability. The concepts are intended to provide for ease of storage or carriage. The concepts include monoplanes with highly swept, thick delta wings, highly swept delta wings mounted either high or low on a semicircular body, some ring wing and semiring wing arrangements, parasol wing, and elliptical lifting bodies. The missile configurations indicate possible approaches toward resolving problems of carriage and storage while retaining good volumetric and aerodynamic efficiency. The configurations can accomplish a variety of possible missions with relatively simple vehicle shapes.

Multiradar tracking for theater missile defense

NASA Astrophysics Data System (ADS)

Sviestins, Egils

1995-09-01

A prototype system for tracking tactical ballistic missiles using multiple radars has been developed. The tracking is based on measurement level fusion (`true' multi-radar) tracking. Strobes from passive sensors can also be used. We describe various features of the system with some emphasis on the filtering technique. This is based on the Interacting Multiple Model framework where the states are Free Flight, Drag, Boost, and Auxiliary. Measurement error modeling includes the signal to noise ratio dependence; outliers and miscorrelations are handled in the same way. The launch point is calculated within one minute from the detection of the missile. The impact point, and its uncertainty region, is calculated continually by extrapolating the track state vector using the equations of planetary motion.

Aerodynamics of an Axisymmetric Missile Concept Having Cruciform Strakes and In-Line Tail Fins From Mach 0.60 to 4.63, Supplement

NASA Technical Reports Server (NTRS)

Allen, Jerry M.

2005-01-01

An experimental study has been performed to develop a large force and moment aerodynamic data set on a slender axisymmetric missile configuration having cruciform strakes and in-line control tail fins. The data include six-component balance measurements of the configuration aerodynamics and three-component measurements on all four tail fins. The test variables include angle of attack, roll angle, Mach number, model buildup, strake length, nose size, and tail fin deflection angles to provide pitch, yaw, and roll control. Test Mach numbers ranged from 0.60 to 4.63. The entire data set is presented on a CD-ROM that is attached to this paper. The CD-ROM also includes extensive plots of both the six-component configuration data and the three-component tail fin data. Selected samples of these plots are presented in this paper to illustrate the features of the data and to investigate the effects of the test variables.

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.

Design and Performance Evaluation Study of a Prototype of a Tactical Unmanned Aerial Vehicle

DTIC Science & Technology

2007-12-01

Sperwer B – Sagem , France ................................................................8 B. EXISTING TACTICAL UAV SYSTEMS...Predator B armed with Hellfire missiles 8 2. Sperwer B – Sagem , France Sperwer B was designed and developed by Sagem , France, to support Intelligence...that can carry external loads of up to 30kg each. Sagem has already demonstrated the integration of Sperwer B with the Spike LR missile. They are

Special Course on Missile Aerodynamics (L’Aerodynamique des Missiles).

DTIC Science & Technology

1994-06-01

AGARD-R-804 wAGAIRD3 ADVISORY GROUP FOR AEROSPACE RESEARCH & DEVELOPMENT 7 RUE ANCELLE 92200 NEUILLY SUR SEINE FRANCE DTIC fELECTE JUNJ2AZ 19515...Panels which are composed of experts appointed by the National Delegates, the Consultant and Exchange Programme and the Aerospace Applications Studies ...Lifting Vehicles AGARD CP-428. November 1987 Aerodynamic and Related Hydrodynamic Studies Using Water Facilities AGARD CP-413. June 1987 Applications of

A Limited Study of a Hypothetical Winged Anti-ICBM Point-Defense Missile

NASA Technical Reports Server (NTRS)

Brown, Clarence A., Jr.; Edwards, Frederick G.

1959-01-01

A preliminary investigation was conducted to determine whether a warhead stage of an antimissile missile could be placed within an arbitrary 2-nautical-mile-radius maneuver cylinder around an intercontinental-ballistic-missile (ICBM) flight path above an altitude of 140,000 feet, a horizontal range of 40 nautical miles, at a flight-path angle of approximately 20 deg, and within 50 seconds after take-off using only aerodynamic forces to turn the antimissile missile. The preliminary investigation indicated that an antimissile missile using aerodynamic forces for turning was capable of intercepting the ICBM for the stated conditions of this study although the turning must be completed below an altitude of approximately 70,000 feet to insure that the antimissile missile will be at the desired flight-path angle. Trim lift coefficients on the order of 2 to 3 and a maximum normal-acceleration force of from 25g to 35g were necessary to place the warhead stage in intercept position. The preliminary investigation indicated that for the two boosters investigated the booster having a burning time of 10 seconds gave greater range up the ICBM flight path than did the booster having a burning time of 15 seconds for the same trim lift coefficient and required the least trim lift coefficient for the same range.

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.

Nonlinear aerodynamic wing design

NASA Technical Reports Server (NTRS)

Bonner, Ellwood

1985-01-01

The applicability of new nonlinear theoretical techniques is demonstrated for supersonic wing design. The new technology was utilized to define outboard panels for an existing advanced tactical fighter model. Mach 1.6 maneuver point design and multi-operating point compromise surfaces were developed and tested. High aerodynamic efficiency was achieved at the design conditions. A corollary result was that only modest supersonic penalties were incurred to meet multiple aerodynamic requirements. The nonlinear potential analysis of a practical configuration arrangement correlated well with experimental data.

Guidance and Control Aspects of Tactical Air-Launched Missiles

DTIC Science & Technology

1980-10-01

information; - Continuously stimulating advances in the aerospace sciences relevant to strengthening the common defence pusture; -- Improving the co...Symposium on Precision Delivery Systems was held at Eglin Air Force Base , Florida. USA. Many important advances in guidance sensor technology, control system...paper concentrates primarily or the US Army Missile Command’s technology base for development of the precision pointing and tracking or fire control

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.

Toward New Horizons. Volume 8. Guided Missiles and Pilotless Aircraft

DTIC Science & Technology

1946-05-01

wings required for sustentation at high speeds than for normal aircraft in which take-off and landing requirements must be met. Thus aerodynamic data...the Langley Memorial Laboratory of the National Advisory Committee for Aeronautics. 13 (2) Free-flight tests of missiles instrumented to give

Generation of Aerodynamics Via Physics-Based Virtual Flight Simulations

DTIC Science & Technology

2008-12-01

problems associated with projectile and missile aerodynamics. For maneuvering munitions, the effect of many new weapon control mechanisms being...dynamic simulation. The terms containing YPAC constitute the Magnus air load acting at the Magnus center of pressure while the terms containing 0 2...an unsteady aerodynamic moment along with terms due to the fact that the center of pressure and center of Magnus are not located at the mass

Conceptual study of hypersonic airbreathing missiles

NASA Technical Reports Server (NTRS)

Hunt, J. L.; Lawing, P. L.; Marcum, D. C.; Cubbage, J. M.

1978-01-01

The purpose of this paper is to report recent results of an in-house conceptual study to evaluate the performance potential and research needs of airbreathing hypersonic missiles. An alkylated-borane (noncryogenic) fueled, dual-mode, ramjet/scramjet propulsion system structured with a Rene 41 inlet and a carbon-carbon combustor was assumed along with a Lockalloy heat sink fuselage structure and beryllium wings and control surfaces. Performance for an air-launched baseline missile with a 961 pound staging weight containing a 100 pound payload indicated excellent long range cruise, moderate acceleration and high maneuverability potential. A sizing study indicates that Mach 6 cruise ranges of the order of 2500 nautical miles for payloads of 300 pounds can be achieved with moderate size missile carry weights (9000 lbs.). Aerodynamic heating analyses indicate that unprotected heat-sink structures with internal insulation are feasible for ranges of several hundred miles. For ranges of several thousands of miles a multiwall radiation shield (Inconel/titanium) was selected for protection of the internally insulated heat sink structure.

Aerodynamic characteristics of a canard-controlled missile at Mach numbers of 0.8, 1.3, and 1.75. [in the Ames 6 by 6 foot wind tunnel

NASA Technical Reports Server (NTRS)

Kassner, D. L.; Wettlaufer, B.

1977-01-01

A typical missile model with nose-mounted canards and cruciform tail surfaces was tested in the Ames 6- by 6-Foot Wind Tunnel to determine the contributions of the component aerodynamic surfaces to the static aerodynamic characteristics at Mach numbers of 0.8, 1.3, and 1.75 and Reynolds number of 625,000 based on body diameter. Data were obtained at angles of attack ranging from 0 deg to 24 deg for various stages of model build-up (i.e., with and without canard and/or tail surfaces). In addition, two different sets of canards and tail surfaces were investigated. For the canard and tail arrangements investigated, the model was trimmable at angles of attack up to about 7 deg with canard deflections of about 10 deg. Also, the tail arrangements studied provided ample pitch stability.

Missile sizing for ascent-phase intercept

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 anglemore » 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.« less

Study of Swept Angle Effects on Grid Fins Aerodynamics Performance

NASA Astrophysics Data System (ADS)

Faza, G. A.; Fadillah, H.; Silitonga, F. Y.; Agoes Moelyadi, Mochamad

2018-04-01

Grid fin is an aerodynamic control surface that usually used on missiles and rockets. In the recent several years many researches have conducted to develop a more efficient grid fins. There are many possibilities of geometric combination could be done to improve aerodynamics characteristic of a grid fin. This paper will only discuss about the aerodynamics characteristics of grid fins compared by another grid fins with different swept angle. The methodology that used to compare the aerodynamics is Computational Fluid Dynamics (CFD). The result of this paper might be used for future studies to answer our former question or as a reference for related studies.

Analysis of selected data from the triservice missile data base

NASA Technical Reports Server (NTRS)

Allen, Jerry M.; Shaw, David S.; Sawyer, Wallace C.

1989-01-01

An extremely large, systematic, axisymmetric-body/tail-fin data base has been gathered through tests of an innovative missile model design which is described herein. These data were originally obtained for incorporation into a missile aerodynamics code based on engineering methods (Program MISSILE3), but these data are also valuable as diagnostic test cases for developing computational methods because of the individual-fin data included in the data base. Detailed analyses of four sample cases from these data are presented to illustrate interesting individual-fin force and moment trends. These samples quantitatively show how bow shock, fin orientation, fin deflection, and body vortices can produce strong, unusual, and computationally challenging effects on individual fin loads. Flow-visualization photographs are examined to provide physical insight into the cause of these effects.

Aerodynamic characteristics of a Sparrow 3 missile model in the flow field of a generalized parent body at Mach 2.86

NASA Technical Reports Server (NTRS)

Stallings, R. L., Jr.

1984-01-01

Longitudinal aerodynamic characteristics of a Sparrow 3 wing control missile model were measured through a range of separation distances relative to a flat plate surface that represented the parent-body configuration. Measurements were obtained with and without two dimensional circular arc protuberances attached to the flat plate surface. The tests were conducted at a Mach number of 2.86 and a Reynolds number per meter of 6.56 million. The behavior of these longitudinal characteristics with varying separation distance in the flow field created by the flat plate and protuberance was generally as would be expected on the basis of flow field boundaries determined from the second order approximation of Friedrich. In general, varying roll angle from 0 deg to 45 deg caused no significant effect on the store separation characteristics.

Dynamic characteristics of a two-stage variable-mass flexible missile with internal flow

NASA Technical Reports Server (NTRS)

Meirovitch, L.; Bankovskis, J.

1972-01-01

A general formulation of the dynamical problems associated with powered flight of a two stage flexible, variable-mass missile with internal flow, discrete masses, and aerodynamic forces is presented. The formulation comprises six ordinary differential equations for the rigid body motion, 3n ordinary differential equations for the n discrete masses and three partial differential equations with the appropriate boundary conditions for the elastic motion. This set of equations is modified to represent a single stage flexible, variable-mass missile with internal flow and aerodynamic forces. The rigid-body motion consists then of three translations and three rotations, whereas the elastic motion is defined by one longitudinal and two flexural displacements, the latter about two orthogonal transverse axes. The differential equations are nonlinear and, in addition, they possess time-dependent coefficients due to the mass variation.

Aerodynamic flight control to increase payload capability of future launch vehicles

NASA Technical Reports Server (NTRS)

Cochran, John E., Jr.

1995-01-01

The development of new launch vehicles will require that designers use innovative approaches to achieve greater performance in terms of pay load capability. The objective of the work performed under this delivery order was to provide technical assistance to the Contract Officer's Technical Representative (COTR) in the development of ideas and concepts for increasing the payload capability of launch vehicles by incorporating aerodynamic controls. Although aerodynamic controls, such as moveable fins, are currently used on relatively small missiles, the evolution of large launch vehicles has been moving away from aerodynamic control. The COTR reasoned that a closer investigation of the use of aerodynamic controls on large vehicles was warranted.

Static aeroelastic analysis and tailoring of missile control fins

NASA Technical Reports Server (NTRS)

Mcintosh, S. C., Jr.; Dillenius, M. F. E.

1989-01-01

A concept for enhancing the design of control fins for supersonic tactical missiles is described. The concept makes use of aeroelastic tailoring to create fin designs (for given planforms) that limit the variations in hinge moments that can occur during maneuvers involving high load factors and high angles of attack. It combines supersonic nonlinear aerodynamic load calculations with finite-element structural modeling, static and dynamic structural analysis, and optimization. The problem definition is illustrated. The fin is at least partly made up of a composite material. The layup is fixed, and the orientations of the material principal axes are allowed to vary; these are the design variables. The objective is the magnitude of the difference between the chordwise location of the center of pressure and its desired location, calculated for a given flight condition. Three types of constraints can be imposed: upper bounds on static displacements for a given set of load conditions, lower bounds on specified natural frequencies, and upper bounds on the critical flutter damping parameter at a given set of flight speeds and altitudes. The idea is to seek designs that reduce variations in hinge moments that would otherwise occur. The block diagram describes the operation of the computer program that accomplishes these tasks. There is an option for a single analysis in addition to the optimization.

Control characteristics for wrap-around fins on cruise missiles configurations

NASA Technical Reports Server (NTRS)

Sawyer, W. C.; Monta, W. J.; Carter, W. V.; Alexander, W. K.

1981-01-01

This paper presents selected results of a panel loads study conducted as part of the final phase of an extensive investigation of an air-breathing missile concept employing wrap-around aerodynamic surfaces. Typical results for M = 2.36 are presented for the fin load results, plus a brief review of basic results of the previously reported tests. Vapor screen results are also discussed. The present results indicate that the fin load characteristics are nearly identical for planar and curved fins having the same projected planform and would permit the use of planar-surface predictions for supersonic speeds in the preliminary design stages of missiles employing wrap-around curved fins.

High-angle-of-attack aerodynamics - Lessons learned

NASA Technical Reports Server (NTRS)

Chambers, J. R.

1986-01-01

Recently, the military and civil technical communities have undertaken numerous studies of the high angle-of-attack aerodynamic characteristics of advanced airplane and missile configurations. The method of approach and the design methodology employed have necessarily been experimental and exploratory in nature, due to the complex nature of separated flows. However, despite the relatively poor definition of many of the key aerodynamic phenomena involved for high-alpha conditions, some generic guidelines for design consideration have been identified. The present paper summarizes some of the more important lessons learned in the area of high angle-of-attack aerodynamics with examples of a number of key concepts and with particular emphasis on high-alpha stability and control characteristics of high performance aircraft. Topics covered in the discussion include the impact of design evolution, forebody flows, control of separated flows, configuration effects, aerodynamic controls, wind-tunnel flight correlation, and recent NASA research activities.

Results from Sandia National Laboratories/Lockheed Martin Electromagnetic Missile Launcher (EMML).

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lockner, Thomas Ramsbeck; Skurdal, Ben; Gaigler, Randy

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, specificmore » pulsed power system component details, system operation, and demonstration results.« less

PNS predictions for supersonic/hypersonic flows over finned missile configurations

NASA Technical Reports Server (NTRS)

Bhutta, Bilal A.; Lewis, Clark H.

1992-01-01

Finned missile design entails accurate and computationally fast numerical techniques for predicting viscous flows over complex lifting configurations at small to moderate angles of attack and over Mach 3 to 15; these flows are often characterized by strong embedded shocks, so that numerical algorithms are also required to capture embedded shocks. The recent real-gas Flux Vector Splitting technique is here extended to investigate the Mach 3 flow over a typical finned missile configuration with/without side fin deflections. Elliptic grid-generation techniques for Mach 15 flows are shown to be inadequate for Mach 3 flows over finned configurations and need to be modified. Fin-deflection studies indicate that even small amounts of missile fin deflection can substantially modify vehicle aerodynamics. This 3D parabolized Navier-Stokes scheme is also extended into an efficient embedded algorithm for studying small axially separated flow regions due to strong fin and control surface deflections.

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.

Adaptive Missile Flight Control for Complex Aerodynamic Phenomena

DTIC Science & Technology

2017-08-09

at high maneuvering conditions motivate guidance approaches that can accommodate uncertainty. Flight control algorithms are one component...performance, but system uncertainty is not directly addressed. Linear, parameter-varying37,38 approaches for munitions expand on optimal control by... post -canard stall. We propose to model these complex aerodynamic mechanisms and use these models in formulating flight controllers within the

Analytical Investigation of a Flicker-Type Roll Control for a Mach Number 6 Missile with Aerodynamic Controls Over An Altitude Range of 82,000 to 282,000 feet

NASA Technical Reports Server (NTRS)

Lundstrom, Reginald R.; Whitman, Ruth I.

1959-01-01

An analytical investigation has been carried out to determine the responses of a flicker-type roll control incorporated in a missile which traverses a range of Mach number of 6.3 at an altitude of 82,000 feet to 5.26 at an altitude of 282,000 feet. The missile has 80 deg delta wings in a cruciform arrangement with aerodynamic controls attached to the fuselage near the wing trailing edge and indexed 450 to the wings. Most of the investigation was carried out on an analog computer. Results showed that roll stabilization that may be adequate for many cases can be obtained over the altitude range considered, providing that the rate factor can be changed with altitude. The response would be improved if the control deflection were made larger at the higher altitudes. lag times less than 0.04 second improve the response appreciably. Asymmetries that produce steady rolling moments can be very detrimental to the response in some cases. The wing damping made a negligible contribution to the response.

Aerodynamic Validation of Emerging Projectile and Missile Configurations

DTIC Science & Technology

2010-12-01

Inflation Layers at the Surface of the M549 Projectile....................................39 Figure 33. Probe Profile from Nose to Shock Front...behavior is critical for the design of new projectile shapes. The conventional approach to predict this aerodynamic behavior is through wind tunnel ...tool to study fluid flows and complements empirical methods and wind tunnel testing. In this study, the computer program ANSYS CFX was used to

Report of the analysis of the joint medium range air to surface missile program

NASA Astrophysics Data System (ADS)

1980-01-01

The objective of this effort completed between July, 1979 and January, 1980 was to investigate technical alternatives and make recommendations concerning management approaches to accomplish the project goals. The purpose of this report is to formalize those recommendations and to identify future courses of action alternatives. The basic concepts incorporated in a supersonic stand-off, air-to-surface missile have existed in Navy advance planning for many years. Navy action on this concept was formalized in 1967 with the decision to initiate a funded technology program to produce a system technology prototype of an advance tactical stand-off missile. Parallel development of propulsion, guidance, and other subsystem technologies conducted by the Air Force, industry, and other countries have also contributed to the current technology base. In May 1978, the Chief of Naval Operations established a requirement for a survivable medium range air-to-surface missile with the issuance of operational requirement W-0650-TW, 'Medium Range Air-to-Surface Missile'. The requirements delineate the need for an offensive air-to-surface missile that can penetrate and survive against defenses expected to be encountered in the 80's and 90's.

Trajectory prediction for ballistic missiles based on boost-phase LOS measurements

NASA Astrophysics Data System (ADS)

Yeddanapudi, Murali; Bar-Shalom, Yaakov

1997-10-01

This paper addresses the problem of the estimation of the trajectory of a tactical ballistic missile using line of sight (LOS) measurements from one or more passive sensors (typically satellites). The major difficulties of this problem include: the estimation of the unknown time of launch, incorporation of (inaccurate) target thrust profiles to model the target dynamics during the boost phase and an overall ill-conditioning of the estimation problem due to poor observability of the target motion via the LOS measurements. We present a robust estimation procedure based on the Levenberg-Marquardt algorithm that provides both the target state estimate and error covariance taking into consideration the complications mentioned above. An important consideration in the defense against tactical ballistic missiles is the determination of the target position and error covariance at the acquisition range of a surveillance radar in the vicinity of the impact point. We present a systematic procedure to propagate the target state and covariance to a nominal time, when it is within the detection range of a surveillance radar to obtain a cueing volume. Mont Carlo simulation studies on typical single and two sensor scenarios indicate that the proposed algorithms are accurate in terms of the estimates and the estimator calculated covariances are consistent with the errors.

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.

U.S. Unmanned Aerial Vehicles (UAVs) and Network Centric Warfare (NCW): Impacts on Combat Aviation Tactics from Gulf War I Through 2007 Iraq

DTIC Science & Technology

2008-03-01

early warning AIM Air-intercept missile AJCN Adaptive, joint, C4ISR node AOR Area of responsibility ARM Anti-radiation missile ATARS Advanced...Tactical Airborne Reconnaissance System ( ATARS ) on F-16 and F/A-18 aircraft, and satellites. Manned platforms were adapted to multiple mission scenarios... Psychological Ops X Tern/Leaflet Dispensing, 2004 All Weather/ Night Strike X DASH/Vietnam, 1960s Predator/Afghanistan/Iraq, 2001 36

A CSMP Commutation Model for Design Study of a Brushless DC Motor Power Conditioner for a Cruise Missile Fin Control Actuator.

DTIC Science & Technology

1985-06-01

STUDY OF A BRUSHLESS DC MOTOR POWER CONDITIONER FOR A CRUISE MISSILE FIN CONTROL ACTUATOR CA. by Peter Norman MacMillan June 1985 Thesis Advisor: A...TYPE OF REPORT & PERIOD COVERED A CSMP Commutation Model for Design Master’s Thesis Study of a Brushless DC Motor Power June, 1985 Conditioner for a...tactical missiles. A dynamic equivalent circuit model for the analysis of a small four pole brushless DC motor fed ty a transistorized power conditioner

Effects of canard location on the aerodynamic characteristics of a blunt-nosed missile at Mach numbers of 1.5 and 2.0. [in the Ames 6x6 wind tunnel

NASA Technical Reports Server (NTRS)

Kassner, D. L.; Wettlaufer, B.

1977-01-01

A blunt-nosed missile model with nose-mounted canards and cruciform tail surfaces was tested in the Ames 6 by 6-Foot Wind Tunnel to determine the contributions of the component aerodynamic surfaces to the static aerodynamic characteristics at Mach numbers of 1.5 and 2.0 and Reynolds number of 1 million based on body diameter. Data were obtained at angles of attack ranging from -3 deg to 12 deg and canard-deflection angles from -3 deg to 15 deg for various stages of model build-up (i.e., with and without canard and/or tail surfaces). Results were obtained with the canards at two different nose locations. For the canard and tail arrangements investigated, the model was trimmable at angles of attack up to about 4 deg or 5 deg with canard deflections of 9 deg. For this blunt-nosed model, there was little effect of canard location on trim angle of attack. The tail arrangements studied provided ample pitch stability.

Supersonic Flight Dynamics Test: Trajectory, Atmosphere, and Aerodynamics Reconstruction

NASA Technical Reports Server (NTRS)

Kutty, Prasad; Karlgaard, Christopher D.; Blood, Eric M.; O'Farrell, Clara; Ginn, Jason M.; Shoenenberger, Mark; Dutta, Soumyo

2015-01-01

The Supersonic Flight Dynamics Test is a full-scale flight test of a Supersonic Inflatable Aerodynamic Decelerator, which is part of the Low Density Supersonic Decelerator technology development project. The purpose of the project is to develop and mature aerodynamic decelerator technologies for landing large mass payloads on the surface of Mars. The technologies include a Supersonic Inflatable Aerodynamic Decelerator and Supersonic Parachutes. The first Supersonic Flight Dynamics Test occurred on June 28th, 2014 at the Pacific Missile Range Facility. This test was used to validate the test architecture for future missions. The flight was a success and, in addition, was able to acquire data on the aerodynamic performance of the supersonic inflatable decelerator. This paper describes the instrumentation, analysis techniques, and acquired flight test data utilized to reconstruct the vehicle trajectory, atmosphere, and aerodynamics. The results of the reconstruction show significantly higher lofting of the trajectory, which can partially be explained by off-nominal booster motor performance. The reconstructed vehicle force and moment coefficients fall well within pre-flight predictions. A parameter identification analysis indicates that the vehicle displayed greater aerodynamic static stability than seen in pre-flight computational predictions and ballistic range tests.

Dynamic characteristics of a variable-mass flexible missile

NASA Technical Reports Server (NTRS)

Meirovitch, L.; Bankovskis, J.

1970-01-01

The general motion of a variable mass flexible missile with internal flow and aerodynamic forces is considered. The resulting formulation comprises six ordinary differential equations for rigid body motion and three partial differential equations for elastic motion. The simultaneous differential equations are nonlinear and possess time-dependent coefficients. The differential equations are solved by a semi-analytical method leading to a set of purely ordinary differential equations which are then solved numerically. A computer program was developed for the numerical solution and results are presented for a given set of initial conditions.

Wave drag reduction with a self-aligning aerodisk on a missile configuration

NASA Astrophysics Data System (ADS)

Schnepf, C.; Wysocki, O.; Schülein, E.

2017-06-01

A self-aligning aerodisk to reduce the wave drag on a pitching missile is numerically investigated. The motion and the Mach number were chosen to match a maneuver flight of an actual missile: pitching frequency f = 7.5 Hz, Mach number M = 2.2, and range of angle of attack 0° < < 21° . The self-alignment was realized with a coupling of the §ow solver with a 6DoF (6 degrees of freedom) tool. In the entire range of angle of attack, the drag could be reduced with the self-aligning aerodisk. A comparison with experimental data showed in parts a quite good agreement in the aerodynamic coe©cients, in the shock structure, and in the alignment of the aerodisk.

Improvements to the missile aerodynamic prediction code DEMON3

NASA Technical Reports Server (NTRS)

Dillenius, Marnix F. E.; Johnson, David L.; Lesieutre, Daniel J.

1992-01-01

The computer program DEMON3 was developed for the aerodynamic analysis of nonconventional supersonic configurations comprising a body with noncircular cross section and up to two wing or fin sections. Within a wing or fin section, the lifting surfaces may be cruciform, triform, planar, or low profile layouts; the planforms of the lifting surfaces allow for breaks in sweep. The body and fin sections are modeled by triplet and constant u-velocity panels, respectively, accounting for mutual body-fin interference. Fin thickness effects are included for the use of supersonic planar source panels. One of the unique features of DEMON3 is the modeling of high angle of attack vortical effects associated with the lifting surfaces and the body. In addition, shock expansion and Newtonian pressure calculation methods can be optionally engaged. These two dimensional nonlinear methods are augmented by aerodynamic interference determined from the linear panel methods. Depending on the geometric details of the body, the DEMON3 program can be used to analyze nonconventional configurations at angles of attack up to 25 degrees for Mach numbers from 1.1 to 6. Calculative results and comparisons with experimental data demonstrate the capabilities of DEMON3. Limitations and deficiencies are listed.

Redstone Missile

NASA Technical Reports Server (NTRS)

2004-01-01

The image depicts Redstone missile being erected. The Redstone ballistic missile was a high-accuracy, liquid-propelled, surface-to-surface missile developed by Army Ballistic Missile Agency, Redstone Arsenal, in Huntsville, Alabama, under the direction of Dr. von Braun. The Redstone engine was a modified and improved version of the Air Force's Navaho cruise missile engine of the late forties. The A-series, as this would be known, utilized a cylindrical combustion chamber as compared with the bulky, spherical V-2 chamber. By 1951, the Army was moving rapidly toward the design of the Redstone missile, and the production was begun in 1952. Redstone rockets became the 'reliable workhorse' for America's early space program. As an example of the versatility, Redstone was utilized in the booster for Explorer 1, the first American satellite, with no major changes to the engine or missile

The Fifth Symposium on Numerical and Physical Aspects of Aerodynamic Flows

NASA Technical Reports Server (NTRS)

1992-01-01

This volume contains the papers presented at the Fifth Symposium on Numerical and Physical Aspects of Aerodynamic Flows, held at the California State University, Long Beach, from 13 to 15 January 1992. The symposium, like its immediate predecessors, considers the calculation of flows of relevance to aircraft, ships, and missiles with emphasis on the solution of two-dimensional unsteady and three-dimensional equations.

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

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

Longitudinal Stability and Control Characteristics as Determined by the Rocket-model Technique for an Inline, Cruciform, Canard Missile Configuration with a Low-aspect-ratio Wing Having Trailing-edge Flap Controls for a Mach Number Range of 0.7 to 1.

NASA Technical Reports Server (NTRS)

Baber, Hal T , Jr; Moul, Martin T

1955-01-01

Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-ratio wing equipped with flap-type controls were flight tested in order to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach number from 0.7 to 1.8. Nonlinear lift and moment curves were noted for the angle - of-attack range of this test (0 deg to 8 deg). The aerodynamic-center location for angles of attack near 50 remained nearly constant for supersonic speeds at 13.5 percent of the mean aerodynamic chord; whereas for angles of attack near 0 deg, there was a rapid forward movement of the aerodynamic center as the Mach number increased. At a control deflection of 0 deg, the missile's response to the longitudinal control was in an essentially fixed space plane which was not coincident with the pitch plane as a result of the missile rolling. As a consequence, stability characteristics were determined from the resultant of pitch and yaw motions. The damping-in-pitch derivatives for the two angle -of-attack ranges of the test are in close agreement and varied only slightly with Mach number. The horn-balanced trailing-edge flap was effective in producing angle of attack over the Mach number range.

Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration with a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8

NASA Technical Reports Server (NTRS)

Baber, H. T., Jr.; Moul, M. T.

1955-01-01

Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-ratio wing equipped with flap-type controls were flight tested in order to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach number from 0.7 to 1.8. Nonlinear lift and moment curves were noted for the angle-of-attack range of this test (0 deg to 8 deg ). The aerodynamic-center location for angles of attack near 5 deg remained nearly constant for supersonic speeds at 13.5 percent of the mean aerodynamic chord; whereas for angles of attack near O deg, there was a rapid forward movement of the aerodynamic center as the Mach number increased. At a control deflection of O deg, the missile's response to the longitudinal control was in an essentially fixed space plane which was not coincident with the pitch plane as a result of the missile rolling. As a consequence, stability characteristics were determined from the resultant of pitch and yaw motions. The damping-in-pitch derivatives for the two angle-of-attack ranges of the test are in close agreement and varied only slightly with Mach number. The horn-balanced trailing-edge flap was effective in producing angle of attack over the Mach number range.

Supersonic Flight Dynamics Test 2: Trajectory, Atmosphere, and Aerodynamics Reconstruction

NASA Technical Reports Server (NTRS)

Karlgaard, Christopher D.; O'Farrell, Clara; Ginn, Jason M.; Van Norman, John W.

2016-01-01

The Supersonic Flight Dynamics Test is a full-scale flight test of aerodynamic decelerator technologies developed by the Low Density Supersonic Decelerator technology demonstration project. The purpose of the project is to develop and mature aerodynamic decelerator technologies for landing large-mass payloads on the surface of Mars. The technologies include a Supersonic Inflatable Aerodynamic Decelerator and supersonic parachutes. The first Supersonic Flight Dynamics Test occurred on June 28th, 2014 at the Pacific Missile Range Facility. The purpose of this test was to validate the test architecture for future tests. The flight was a success and, in addition, was able to acquire data on the aerodynamic performance of the supersonic inflatable decelerator. The Supersonic Disksail parachute developed a tear during deployment. The second flight test occurred on June 8th, 2015, and incorporated a Supersonic Ringsail parachute which was redesigned based on data from the first flight. Again, the inflatable decelerator functioned as predicted but the parachute was damaged during deployment. This paper describes the instrumentation, analysis techniques, and acquired flight test data utilized to reconstruct the vehicle trajectory, main motor thrust, atmosphere, and aerodynamics.

Design and testing of a caseless solid-fuel integral-rocket ramjet engine for use in small tactical missiles

NASA Astrophysics Data System (ADS)

Fruge, Keith J.

1991-09-01

An investigation was conducted to determine the feasibility of a low cost, caseless, solid fuel integral rocket ramjet (IRSFRJ) that has no ejecta. Analytical design of a ramjet powered air-to-ground missile capable of being fired from a remotely piloted vehicle or helicopter was accomplished using current JANNAF and Air Force computer codes. The results showed that an IRSFRJ powered missile can exceed the velocity and range of current systems by more than a two to one ratio, without an increase in missile length and weight. A caseless IRSFRJ with a nonejecting port cover was designed and tested. The experimental results of the static tests showed that a low cost, caseless IRSFRJ with a nonejectable port cover is a viable design. Rocket ramjet transition was demonstrated and ramjet ignition was found to be insensitive to the booster tail off to air injection timing sequence.

Effects of Base Cavity Depth on a Free Spinning Wrap-Around Fin Missile Configuration

DTIC Science & Technology

1995-12-01

packaging problem. Current missile systems which possess wrap-around fin designs are the Army’s Multiple Launch Rocket System (MLRS) and the Hard Target...aerodynamic irregularities (2). Of particular importance to projectile designers is the side force/moment inherent to wrap-around fin configurations. During...virtual instrument programs integrated to perform all necessary aspects of calibration, data collection, and reduction. The details surrounding the design

Ground-Based Missile Defense (National Missile Defense): Is It Feasible?

DTIC Science & Technology

2004-03-19

Westview Press), 191. 47 Ibid. 192. 48 Dr. Nicholas Berry, National Missile Defense: What Does It All Mean ? National Missile Defense: Views from Asia...153. 18 19 BIBLIOGRAPHY Berry, Nicholas. National Missile Defense: What Does It All Mean ? National Missile Defense: Views from Asia, Center for

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

Structural analysis of high-rpm composite propfan blades for a cruise missile wind tunnel model

NASA Technical Reports Server (NTRS)

Carek, David A.

1993-01-01

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.

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

NASA Technical Reports Server (NTRS)

Arbic, R. G.

1955-01-01

Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.

Wind tunnel test results for the direction controlled antitank DCAT missile at Mach numbers from 0.64 to 2.50

NASA Technical Reports Server (NTRS)

Martin, T. A.; Spring, D. J.

1973-01-01

Wind tunnel test results are presented to show aerodynamic characteristics over the Mach number range of 0.64 to 2.50 of the DCAT missile. Data are presented showing the interference created by the rear mounted reaction control system. Two candidate fins were installed on the model during tests: a flat folding fin and a curved wrap around fin.

Missile Defense: Ballistic Missile Defense System Testing Delays Affect Delivery of Capabilities

DTIC Science & Technology

2016-04-28

Page 1 GAO- 16 -339R Ballistic Missile Defense 441 G St. N.W. Washington, DC 20548 April 28, 2016 Congressional Committees Missile Defense...Ballistic Missile Defense System Testing Delays Affect Delivery of Capabilities For over half a century , the Department of Defense (DOD) has been...81, § 232 (a) (2011). 2 GAO- 16 -339R Ballistic Missile Defense baselines, we analyzed the testing goals for selected elements, which are

Performance assessment of MEMS adaptive optics in tactical airborne systems

NASA Astrophysics Data System (ADS)

Tyson, Robert K.

1999-09-01

Tactical airborne electro-optical systems are severely constrained by weight, volume, power, and cost. Micro- electrical-mechanical adaptive optics provide a solution that addresses the engineering realities without compromising spatial and temporal compensation requirements. Through modeling and analysis, we determined that substantial benefits could be gained for laser designators, ladar, countermeasures, and missile seekers. The developments potential exists for improving seeker imagery resolution 20 percent, extending countermeasures keep-out range by a factor of 5, doubling the range for ladar detection and identification, and compensating for supersonic and hypersonic aircraft boundary layers. Innovative concepts are required for atmospheric pat hand boundary layer compensation. We have developed design that perform these tasks using high speed scene-based wavefront sensing, IR aerosol laser guide stars, and extended-object wavefront beacons. We have developed a number of adaptive optics system configurations that met the spatial resolution requirements and we have determined that sensing and signal processing requirements can be met. With the help of micromachined deformable mirrors and sensor, we will be able to integrate the systems into existing airborne pods and missiles as well as next generation electro-optical systems.

Missiles in the cardiovascular system.

PubMed

Symbas, P N; Symbas, P J

1997-05-01

A missile in the cardiovascular system is a rare complication of a projectile wound. A missile in the heart should be suspected in the patient with a projectile wound of the thorax and in whom, on chest radiography, a missile is seen in the cardiac silhouette. A missile should be suspected in the patient with a projectile wound elsewhere with similar radiographic findings, no exit wound, and no missile in the area of injury. A missile in the arterial system should be suspected when no exit wound and no projectile are seen in the traumatized area. In such a case, radiography of the entire body should be done. The diagnosis of a suspected missile in the cardiovascular system is confirmed by echocardiography or angiography. Treatment should be individualized according to the clinical manifestations of the patient and the site of the missile.

Longitudinal Aerodynamic Characteristics and Effect of Rocket Jet on Drag of Models of the Hermes A-3A and A-3B Missiles in Free Flight at Mach Numbers From 0.6 to 2.0

NASA Technical Reports Server (NTRS)

Jackson, H. Herbert

1955-01-01

A free-flight investigation over a Mach number range from 0.6 to 2.0 has been conducted to determine the longitudinal aerodynamic characteristics and effect of rocket jet on zero-lift drag of 1/5-scale models of two ballistic-type missiles, the Hermes A-3A and A-3B. Models of both types of missiles exhibited very nearly linear normal forces and pitching moments over the angle-of-attack range of 8 deg to -4 deg and Mach number range tested. The centers of pressure for both missiles were not appreciably affected by Mach number over the subsonic range; however, between a Mach number of 1.02 and 1.50 the center of pressure for the A-3A model moved forward 0.34 caliber with increasing Mach number. At a trim angle-of-attack of approximately 30 deg, the A-3A model indicated a total drag coefficient 30% higher than the power-off zero-lift drag over the subsonic Mach number range and 10% higher over the supersonic range. Under the conditions of the present test, and excluding the effect of the jet on base drag, there was no indicated effect of the propulsive jet on the total drag of the A-3A model. The propulsive jet operating at a jet pressure ratio p(sub j)/p(sub o) of 0.8 caused approximately 100% increase in base drag over the Mach number range M = 0.6 to 1.0. This increase in base drag amounts to 15% of the total drag. An underexpanded jet operating at jet pressure ratios corresponding approximately to those of the full-scale missile caused a 22% reduction in base drag at M = 1.55 (p(sub j)/p(sub o) = 1.76) but indicated no change at M = 1.30 (p(sub j)/p(sub o) = 1.43). At M = 1.1 and p(sub j)/p(sub o) = 1.55, the jet caused a 50% increase in base drag.

Aeroservoelastic DAP missile fin development. [directionally attached piezoelectric actuator

NASA Technical Reports Server (NTRS)

Barrett, Ron

1993-01-01

The development of an active aeroservoelastic missile fin using directionally attached piezoelectric (DAP) actuator elements is detailed. Several different types of actuator elements are examined, including piezoelectric polymers, piezoelectric fiber composites, and conventionally attached piezoelectric (CAP) and DAP elements. These actuator elements are bonded to the substrate of a torque plate. The root of the torque plate is attached to a fuselage hard point or folding pivot. The tip of the plate is bonded to an aerodynamic shell which undergoes a pitch change as the plate twists. The design procedures used on the plate are discussed. A comparison of the various actuator element shows that DAP elements provide the highest deflections with the highest torsional stiffness. A torque plate was constructed from 0.2032 mm thick DAP elements bonded to a 0.127 mm thick AISI 1010 steel substrate. The torque plate produced static twist deflections in excess of +/- 3 deg. An aerodynamic shell with a modified NACA 0012 profile was added to the torque plate. This fin was tested in a wind tunnel at speeds up to 50 ms/sec. The static deflection of the fin was predicted to within 6 percent of the experimental data.

Missile Misdistance Reduction: An Instructive Methodology for Developing Terminal Guidance Control Systems to Minimize Missile Misdistance.

DTIC Science & Technology

1982-10-01

ZHTAM NORMAS IZED MISSILE*S DISPLACEMENT OFF-L.O.S * NCAACC NORMALIZED MISSILE’S ACCELERATION &YAN TAM "(I/(I-N(K) ))*(I-TIMEI*flL-TIMEJ**(N(KI-)--I...Interceptor Missiles, April 1976. 8. George, L. C., "Missile Guidance and Control System De- sign Trends," SAE paper, National Aerospace Engineering and

Lessons Learned in the High-Speed Aerodynamic Research Programs of the NACA/NASA

NASA Technical Reports Server (NTRS)

Spearman, M. Leroy

2004-01-01

The achievement of flight with manned, powered, heavier-than-air aircraft in 1903 marked the beginning of a new era in the means of transportation. A special advantage for aircraft was in speed. However, when an aircraft penetrates the air at very high speeds, the disturbed air is compressed and there are changes in the density, pressure and temperature of the air. These compressibility effects change the aerodynamic characteristics of an aircraft and introduce problems in drag, stability and control. Many aircraft designed in the post-World War II era were plagued with the effects of compressibility. Accordingly, the study of the aerodynamic behavior of aircraft, spacecraft and missiles at high-speed became a major part of the research activity of the NACA/NASA. The intent of the research was to determine the causes and provide some solutions for the aerodynamic problems resulting from the effects of compressibility. The purpose of this paper is to review some of the high-speed aerodynamic research work conducted at the Langley Research Center from the viewpoint of the author who has been active in much of the effort.

A high-fidelity, six-degree-of-freedom batch simulation environment for tactical guidance research and evaluation

NASA Technical Reports Server (NTRS)

Goodrich, Kenneth H.

1993-01-01

A batch air combat simulation environment, the tactical maneuvering simulator (TMS), is presented. The TMS is a tool for developing and evaluating tactical maneuvering logics, but it can also be used to evaluate the tactical implications of perturbations to aircraft performance or supporting systems. The TMS can simulate air combat between any number of engagement participants, with practical limits imposed by computer memory and processing power. Aircraft are modeled using equations of motion, control laws, aerodynamics, and propulsive characteristics equivalent to those used in high-fidelity piloted simulations. Data bases representative of a modern high-performance aircraft with and without thrust-vectoring capability are included. To simplify the task of developing and implementing maneuvering logics in the TMS, an outer-loop control system, the tactical autopilot (TA), is implemented in the aircraft simulation model. The TA converts guidance commands by computerized maneuvering logics from desired angle of attack and wind-axis bank-angle inputs to the inner loop control augmentation system of the aircraft. The capabilities and operation of the TMS and the TA are described.

An experimental and theoretical study of the aerodynamic characteristics of some generic missile concepts at Mach numbers from 2 to 6.8

NASA Technical Reports Server (NTRS)

Spearman, M. Leroy; Braswell, Dorothy O.

1994-01-01

A study has been made of the experimental and theoretical aerodynamic characteristics for some generic high-speed missile concepts at Mach numbers from 2 to 6.8. The basic body for this study had a length-to-diameter ratio of 10 with the forward half being a modified blunted ogive and the rear half being a cylinder. Modifications made to the basic body included the addition of an after body flare, the addition of highly swept cruciform wings and the addition of highly swept aft tails. The effects of some controls were also investigated with all-moving wing controls on the flared body and trailing-edge flap controls on the winged body. The results indicated that the addition of a flare, wings, or tails to the basic body all provided static longitudinal stability with varying amounts of increased axial force. The control arrangements were effective in producing increments of normal-force and pitching-moment at the lower Mach numbers. At the highest Mach number, the flap control on the winged body was ineffective in producing normal-force or pitching-moment but the all-moving wing control on the flared body, while losing pitch effectiveness, still provided normal-force increments. Calculated results obtained through the use of hypersonic impact theory were in generally good agreement with experiment at the higher Mach numbers but were not accurate at the lower Mach numbers.

Application of Discrete Guidance and Control Theory to Future Army Modular Missiles.

DTIC Science & Technology

1980-09-30

30 April - I May, Dr. Pastrick and Dr. Seltzer-attended the 1980 Tactical Missiles Conference at Eglin Air Force Base. !7 t ’ I 9 * I. - , Ji ...1.7140E+00 P2= 9.0903E- 61 WnTm 1.8221E+00 DET=-1.8519E-03 P1= I.7093E+00 P2= 9.0568E-01 SWrT= 1.850E+00 DET=-1.8416E-03 Piz 1.7055E+00 P2= 9.0290E-01 * WrT...fl-n~-~a~ 4 - - I I I TECHNICAL REPORT T-79-64 I SAMPLED-DATA ANALYSIS IN PARAMETER SPACE S.M. Seltzer Technology Laboratory June 1979 Ji j edet•one

Ballistic missile defense technologies

NASA Astrophysics Data System (ADS)

1985-09-01

A report on Ballistic Missile Technologies includes the following: Executive summary; Introduction; Ballistic missiles then and now; Deterrence, U.S. nuclear strategy, and BMD; BMD capabilities and the strategic balance; Crisis stability, arms race stability, and arms control issues; Ballistic missile defense technologies; Feasibility; Alternative future scenarios; Alternative R&D programs.

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.

Ballistic missile defense effectiveness

NASA Astrophysics Data System (ADS)

Lewis, George N.

2017-11-01

The potential effectiveness of ballistic missile defenses today remains a subject of debate. After a brief discussion of terminal and boost phase defenses, this chapter will focus on long-range midcourse defenses. The problems posed by potential countermeasures to such midcourse defenses are discussed as are the sensor capabilities a defense might have available to attempt to discriminate the actual missile warhead in a countermeasures environment. The role of flight testing in assessing ballistic missile defense effectiveness is discussed. Arguments made about effectiveness by missile defense supporters and critics are summarized.

Redstone Missile on Launch Pad

NASA Technical Reports Server (NTRS)

1958-01-01

Redstone missile No. 1002 on the launch pad at Cape Canaveral, Florida, on May 16, 1958. The Redstone ballistic missile was a high-accuracy, liquid-propelled, surface-to-surface missile developed by the Army Ballistic Missile Agency, Redstone Arsenal, in Huntsville, Alabama, under the direction of Dr. von Braun. The Redstone engine was a modified and improved version of the Air Force's Navaho cruise missile engine of the late forties. The A-series, as this would be known, utilized a cylindrical combustion chamber as compared with the bulky, spherical V-2 chamber. By 1951, the Army was moving rapidly toward the design of the Redstone missile, and production was begun in 1952. Redstone rockets became the 'reliable workhorse' for America's early space program. As an example of the versatility, Redstone was utilized in the booster for Explorer 1, the first American satellite, with no major changes to the engine or missile

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.

The Modern Design of Experiments for Configuration Aerodynamics: A Case Study

NASA Technical Reports Server (NTRS)

DeLoach, Richard

2006-01-01

The effects of slowly varying and persisting covariate effects on the accuracy and precision of experimental result is reviewed, as is the rationale for run-order randomization as a quality assurance tactic employed in the Modern Design of Experiments (MDOE) to defend against such effects. Considerable analytical complexity is introduced by restrictions on randomization in configuration aerodynamics tests because they involve hard-to-change configuration variables that cannot be randomized conveniently. Tradeoffs are examined between quality and productivity associated with varying degrees of rigor in accounting for such randomization restrictions. Certain characteristics of a configuration aerodynamics test are considered that may justify a relaxed accounting for randomization restrictions to achieve a significant reduction in analytical complexity with a comparably negligible adverse impact on the validity of the experimental results.

Alternatives for Boost-Phase Missile Defense

DTIC Science & Technology

2004-07-01

NFIRE ) to better understand the characteristics of that signature for intercontinental ballistic missiles (ICBMs). The information that NFIRE might...ballistic missile Isp: specific impulse kg: kilogram km: kilometer MDA: Missile Defense Agency NFIRE : Near-Field Infrared Experiment NMD: national missile

Strategic Missile Defense & Nuclear Deterrence

NASA Astrophysics Data System (ADS)

Grego, Laura

The United States has pursued defenses against nuclear-armed long-range ballistic missiles since at least the 1950s. At the same time, concerns that missile defenses could undermine nuclear deterrence and potentially spark an arms race led the United States and Soviet Union to negotiate limits on these systems. The 1972 Anti-Ballistic Missile Treaty constrained strategic missile defenses for thirty years. After abandoning the treaty in 2002, President George W. Bush began fielding the Ground-based Midcourse Defense (GMD) homeland missile defense system on an extremely aggressive schedule, nominally to respond to threats from North Korea and Iran. Today, nearly fifteen years after its initial deployment, the potential and the limits of this homeland missile defense are apparent. Its test record is poor and it has no demonstrated ability to stop an incoming missile under real-world conditions. No credible strategy is in place to solve the issue of discriminating countermeasures. Insufficient oversight has not only exacerbated the GMD system's problems, but has obscured their full extent, which could encourage politicians and military leaders to make decisions that actually increase the risk of a missile attack against the United States. These are not the only costs. Both Russia and China have repeatedly expressed concerns that U.S. missile defenses adversely affect their own strategic capabilities and interests, particularly taken in light of the substantial US nuclear forces. This in turn affects these countries' nuclear modernization priorities. This talk will provide a technical overview of the US strategic missile defense system, and how it relates to deterrence against non-peer adversaries as well as how it affects deterrence with Russia and China and the long-term prospects for nuclear reductions

15 CFR 742.5 - Missile technology.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 15 Commerce and Foreign Trade 2 2010-01-01 2010-01-01 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 Control...

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.

Diode Pumped Alkaline Laser System: A High Powered, Low SWaP Directed Energy Option for Ballistic Missile Defense High-Level Summary - April 2017

DOE Office of Scientific and Technical Information (OSTI.GOV)

Wisoff, P. J.

The Diode-Pumped Alkali Laser (DPAL) system is an R&D effort funded by the Missile Defense Agency (MDA) underway at Lawrence Livermore National Laboratory (LLNL). MDA has described the characteristics needed for a Boost Phase directed energy (DE) weapon to work against ICBM-class threat missiles. In terms of the platform, the mission will require a high altitude Unmanned Aerial Vehicle (UAV) that can fly in the “quiet” stratosphere and display long endurance – i.e., days on station. In terms of the laser, MDA needs a high power, low size and weight laser that could be carried by such a platform andmore » deliver lethal energy to an ICBM-class threat missile from hundreds of kilometers away. While both the military and industry are pursuing Directed Energy for tactical applications, MDA’s objectives pose a significantly greater challenge than other current efforts in terms of the power needed from the laser, the low size and weight required, and the range, speed, and size of the threat missiles. To that end, MDA is funding two R&D efforts to assess the feasibility of a high power (MWclass) and low SWaP (size, weight and power) laser: a fiber combining laser (FCL) project at MIT’s Lincoln Laboratory, and LLNL’s Diode-Pumped Alkali Laser (DPAL) system.« less

6. View from heat sink (south to north), west oblique ...

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

6. View from heat sink (south to north), west 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

Options for Deploying Missile Defenses in Europe

DTIC Science & Technology

2009-02-01

missile attacks from North Korea or Iran. The GMD system consists of interceptors (missiles designed to destroy other missiles) located at Fort Greely... location yet to be specified. This Congressional Budget Office (CBO) study—prepared at the request of the Chairman and Ranking Member of the House...Options 57FiguresS-1. Components of the Options for European Missile Defenses and Their Locations xivS-2. Distances from a Potential Missile Launch

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.

Missile Aerodynamics

DTIC Science & Technology

1988-01-01

considered preferable to inadequate treatment of more material. Readers frequently wonder what motivates the author in his arrange- ment of material. The...fins: M11, = Mn22 +~p’I (a2/sl)n/2]4"n - (2)21 in1, = 01*a rn13 = 0 ’n23 = 0 M33, =.533ps’ n =3 a =0 =n Ps4 n =4 a =0 7r . n=P8 n. fins H. Regular

Trident II (D-5) Sea Launched Ballistic Missile UGM 133A (Trident II Missile)

DTIC Science & Technology

2015-12-01

Selected Acquisition Report ( SAR ) RCS: DD-A&T(Q&A)823-178 Trident II (D-5) Sea-Launched Ballistic Missile UGM 133A (Trident II Missile) As of FY...December 2015 SAR March 17, 2016 12:10:33 UNCLASSIFIED 2 Table of Contents Common Acronyms and Abbreviations for MDAP Programs 3 Program...Acquisition Unit Cost Trident II Missile December 2015 SAR March 17, 2016 12:10:33 UNCLASSIFIED 3 PB - President’s Budget PE - Program Element PEO - Program

Missile vascular injuries: 19-year experience.

PubMed

Ahanger, Abdul Gani; Wani, Mohd Lateef; Lone, Reyaz Ahmad; Singh, Shyam; Hussain, Zahur; Mir, Ishtiyak A; Irshad, Ifat; Ashraf, Hakeem Zubair; Dar, Abdul Majeed; Lone, Ghulam Nabi; Bhat, Mohammad Akbar; Sharma, Mukand Lal

2010-03-01

Missile vascular injuries have reached an epidemic proportion in Kashmir valley since the eruption of militancy. The present study was undertaken to analyze the mode, pattern, presentation, and management of missile vascular injuries. A retrospective study of patients with missile vascular injury from January 1990 to October 2008 was undertaken. Five hundred eighty patients with missile vascular injury were studied. All patients with vascular injury due to causes other than missiles were excluded from the study. Most of the patients were treated by interpositional saphenous vein graft or end-to-end anastomosis. The most common complication was wound infection (22.7%) followed by graft occlusion (3.8%). The amputation rate was 3.3% and was higher in patients with a delay of >6 hours to revascularization and associated fractures. Missile vascular injury requires prompt resuscitation and revascularization. Preoperative angiography is seldom necessary. Doppler study may sometimes be needed to aid in the diagnosis.

7. View from heat sink (south to north), west oblique ...

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

7. View from heat sink (south to north), west oblique of missile site control building, emphasizing southwest face - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

Tactical Infrasound

DTIC Science & Technology

2005-05-01

received briefings on a variety of infra - sonic sensor systenis. Materials were also received from the 2001 and 2002 Infrasonic Technology Workshops and...Systems to Tactical Acoustic Sys- tems One issue to be considered in the evaluation of a p)otential tactical infra - sonic system is the ability to...Communication range Fixed Fixed 5 km 7.4 A Design Approach for a Future Tactical Infra - sonic Sensor System This section describes a procedure used to

15 CFR 742.5 - Missile technology.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 15 Commerce and Foreign Trade 2 2014-01-01 2014-01-01 false Missile technology. 742.5 Section 742... BASED CONTROLS § 742.5 Missile technology. (a) License requirements. (1) In support of U.S. foreign policy to limit the proliferation of missiles, a license is required to export and reexport items related...

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 policy to limit the proliferation of missiles, a license is required to export and reexport items related...

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 policy to limit the proliferation of missiles, a license is required to export and reexport items related...

Missile Aerodynamics (Aerodynamique des Missiles)

DTIC Science & Technology

1998-11-01

Magnus effect. effects on a spinning finned cylindrical body. Despite the large As noted above, the source, magnitude and even the direction amount of...axis, and to circular- cylindrical bodies in combination with determine directly the pressures acting on the body. triangular, rectangular, or...pressure drop in smooth cylindrical codes, as well as for testing and checking CFD-based tubes", NACA ARR L4C16, 1944. results. 6. Nielsen, J. N. and

UCAV path planning in the presence of radar-guided surface-to-air missile threats

NASA Astrophysics Data System (ADS)

Zeitz, Frederick H., III

This dissertation addresses the problem of path planning for unmanned combat aerial vehicles (UCAVs) in the presence of radar-guided surface-to-air missiles (SAMs). The radars, collocated with SAM launch sites, operate within the structure of an Integrated Air Defense System (IADS) that permits communication and cooperation between individual radars. The problem is formulated in the framework of the interaction between three sub-systems: the aircraft, the IADS, and the missile. The main features of this integrated model are: The aircraft radar cross section (RCS) depends explicitly on both the aspect and bank angles; hence, the RCS and aircraft dynamics are coupled. The probabilistic nature of IADS tracking is accounted for; namely, the probability that the aircraft has been continuously tracked by the IADS depends on the aircraft RCS and range from the perspective of each radar within the IADS. Finally, the requirement to maintain tracking prior to missile launch and during missile flyout are also modeled. Based on this model, the problem of UCAV path planning is formulated as a minimax optimal control problem, with the aircraft bank angle serving as control. Necessary conditions of optimality for this minimax problem are derived. Based on these necessary conditions, properties of the optimal paths are derived. These properties are used to discretize the dynamic optimization problem into a finite-dimensional, nonlinear programming problem that can be solved numerically. Properties of the optimal paths are also used to initialize the numerical procedure. A homotopy method is proposed to solve the finite-dimensional, nonlinear programming problem, and a heuristic method is proposed to improve the discretization during the homotopy process. Based upon the properties of numerical solutions, a method is proposed for parameterizing and storing information for later recall in flight to permit rapid replanning in response to changing threats. Illustrative examples are

Cruise Missile Engines

NASA Technical Reports Server (NTRS)

1982-01-01

Williams International's F107 fanjet engine is used in two types of cruise missiles, Navy-sponsored Tomahawk and the Air Force AGM-86B Air Launched Cruise Missile (ALCM). Engine produces about 600 pounds thrust, is one foot in diameter and weighs only 141 pounds. Design was aided by use of a COSMIC program in calculating airflows in engine's internal ducting, resulting in a more efficient engine with increased thrust and reduced fuel consumption.

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

NASA Technical Reports Server (NTRS)

Robinson, Ross B; Bernot, Peter T

1958-01-01

An investigation has been made to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and with all-movable control surfaces. The flaps were tested on a configuration having low-aspect-ratio cruciform fins with an apex angle of 5 deg the all-movable controls were mounted at the 46.7-percent body station on a configuration having a 10 deg flared afterbody. The tests were made through an angle-of-attack range of -2 deg to 20 deg at zero sideslip in the Langley 11-inch hypersonic tunnel. The results indicated that the all-movable controls on the flared afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge -flap configuration. The flared -after body configuration had considerably higher drag than the cruciform-fin model but only slightly lower values of lift drag ratio.

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

NASA Technical Reports Server (NTRS)

Bernot, P. T.; Robinson, R. B.

1958-01-01

An investigation has been made to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and with all-movable control surfaces. The flaps were tested on a configuration having low-aspect-ratio cruciform fins with an apex angle of 5 degrees; the all-movable controls were mounted at the 46.7-percent body station on a configuration having a 10 degrees flared afterbody. The tests were made through an angle-of-attack range of -2 degrees to 20 degrees at zero sideslip in the Langley 11-inch hypersonic tunnel. The results indicated that the all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. The flared-afterbody configuration had considerably higher drag than the cruciform-fin model but only slightly lower values of lift-drag ratio.

Hardware-in-the-loop tow missile system simulator

DOE Office of Scientific and Technical Information (OSTI.GOV)

Waldman, G.S.; Wootton, J.R.; Hobson, G.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 generatingmore » 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.« less

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.

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... sensitive missile-relevant transfers based on the MTCR Annex, and any amendments thereto. (b) The term MTCR...

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... restrict sensitive missile-relevant transfers based on the MTCR Annex, and any amendments thereto; (b) The...

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... restrict sensitive missile-relevant transfers based on the MTCR Annex, and any amendments thereto; (b) The...

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... restrict sensitive missile-relevant transfers based on the MTCR Annex, and any amendments thereto; (b) The...

Aerodynamic distortion propagation calculation in application of high-speed target detection by laser

NASA Astrophysics Data System (ADS)

Zheng, Yonghui; Sun, Huayan; Zhao, Yanzhong; Chen, Jianbiao

2015-10-01

Active laser detection technique has a broad application prospect in antimissile and air defense, however the aerodynamic flow field around the planes and missiles cause serious distortion effect on the detecting laser beams. There are many computational fluid dynamics(CFD) codes that can predict the air density distribution and also the density fluctuations of the flow field, it's necessary for physical optics to be used to predict the distortion properties after propagation through the complex process. Aiming at the physical process of laser propagation in "Cat-eye" lenses and aerodynamic flow field for twice, distortion propagation calculation method is researched in this paper. In the minds of dividing the whole process into two parts, and tread the aero-optical optical path difference as a phase distortion, the incidence and reflection process are calculated using Collins formula and angular spectrum diffraction theory respectively. In addition, turbulent performance of the aerodynamic flow field is estimated according to the electromagnetic propagation theory through a random medium, the rms optical path difference and Strehl ratio of the turbulent optical distortion are obtained. Finally, Computational fluid mechanics and aero-optical distortion properties of the detecting laser beams are calculated with the hemisphere-on-cylinder turret as an example, calculation results are showed and analysed.

Prediction methodologies for target scene generation in the aerothermal targets analysis program (ATAP)

NASA Astrophysics Data System (ADS)

Hudson, Douglas J.; Torres, Manuel; Dougherty, Catherine; Rajendran, Natesan; Thompson, Rhoe A.

2003-09-01

The Air Force Research Laboratory (AFRL) Aerothermal Targets Analysis Program (ATAP) is a user-friendly, engineering-level computational tool that features integrated aerodynamics, six-degree-of-freedom (6-DoF) trajectory/motion, convective and radiative heat transfer, and thermal/material response to provide an optimal blend of accuracy and speed for design and analysis applications. ATAP is sponsored by the Kinetic Kill Vehicle Hardware-in-the-Loop Simulator (KHILS) facility at Eglin AFB, where it is used with the CHAMP (Composite Hardbody and Missile Plume) technique for rapid infrared (IR) signature and imagery predictions. ATAP capabilities include an integrated 1-D conduction model for up to 5 in-depth material layers (with options for gaps/voids with radiative heat transfer), fin modeling, several surface ablation modeling options, a materials library with over 250 materials, options for user-defined materials, selectable/definable atmosphere and earth models, multiple trajectory options, and an array of aerodynamic prediction methods. All major code modeling features have been validated with ground-test data from wind tunnels, shock tubes, and ballistics ranges, and flight-test data for both U.S. and foreign strategic and theater systems. Numerous applications include the design and analysis of interceptors, booster and shroud configurations, window environments, tactical missiles, and reentry vehicles.

Missile pulmonary embolus secondary to abdominal gunshot wound.

PubMed

Mctyre, Emory; McGill, Lee; Miller, Nessa

2012-01-01

Missile pulmonary emboli are rare sequelae of traumatic entry of projectile missiles-generally bullets or bullet fragments-in which access to the systemic venous circulation is established by the missile, making it possible for the missile to migrate to the pulmonary arteries. In the case introduced here, a 24-year-old male presented to the ER with a gunshot wound to the abdomen. In the early course of his care, it was determined that he had suffered a missile pulmonary embolus secondary to a large fragment of a bullet penetrating the IVC. Despite the large perfusion defect created by this missile embolus, the patient recovered uneventfully without embolectomy.

Whither Ballistic Missile Defense?

DTIC Science & Technology

1992-11-30

Conference on Technical Marketing 2000: Opportunities and Strategies for a Changing World) I intend to discuss the prospects for SDI in a changing...Technical Marketing 2000: Opportunities and Strategies for a Changing World) Descriptors, Keywords: Cooper Speech Ballistic Missile Defense...WHITHER BALLISTIC MISSILE DEFENSE? BY AMBASSADOR HENRY F. COOPER NOVEMBER 30,1992 TECHNICAL MARKETING SOCIETY OF AMERICA WASHINGTON, DC

Pulmonary embolism from gunshot missiles.

PubMed

Bernini, C O; Junqueira, A R; Horita, L T; Birolini, D; Branco, P D; de Oliveira, M R

1983-05-01

In patients having missile wounds, the most bizarre trajectories and lodgment sites have been reported. Entry of the missile into the blood stream and subsequent embolization is quite an uncommon event. Isolated reports published in the literature date back to the beginning of the century. This article was undertaken to present two instances of pulmonary embolism due to gunshot missiles. Most investigators agree that the missile should be removed when located in the pulmonary artery and its branches because of the high risk of severe complications, such as pulmonary infarction, secondary thrombosis, infection, erosion of the arterial wall and local hemorrhage. In such instances, a thoracotomy is recommended. The alternative treatment in the instances reported herein, conceived and successfully performed by us, was embolectomy through percutaneous cardiovascular catheterization. As a novel procedure, the method has proved effective and liable to minimal risk.

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.

Cost Effective Regional Ballistic Missile Defense

DTIC Science & Technology

2016-02-16

deploying advanced air defense systems18, such as the Russian S-300 and S-500, and concealing them in hardened, camouflaged sites, such as extensive... Russian objections to the European Phased Adaptive Approach (EPAA) and fund homeland defense priorities.39 Furthermore, the PTSS system was also... Theatre Ballistic Missile Defence Capability Becomes Operational,” Jane’s Missiles & Rockets, 1 February 2011. 55 Joseph W. Kirschbaum, REGIONAL MISSILE

Evaluation of wind/tornado-generated missile impact

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 addressedmore » in this paper.« less

Tactical visualization module

NASA Astrophysics Data System (ADS)

Kachejian, Kerry C.; Vujcic, Doug

1999-07-01

The Tactical Visualization Module (TVM) research effort will develop and demonstrate a portable, tactical information system to enhance the situational awareness of individual warfighters and small military units by providing real-time access to manned and unmanned aircraft, tactically mobile robots, and unattended sensors. TVM consists of a family of portable and hand-held devices being advanced into a next- generation, embedded capability. It enables warfighters to visualize the tactical situation by providing real-time video, imagery, maps, floor plans, and 'fly-through' video on demand. When combined with unattended ground sensors, such as Combat- Q, TVM permits warfighters to validate and verify tactical targets. The use of TVM results in faster target engagement times, increased survivability, and reduction of the potential for fratricide. TVM technology can support both mounted and dismounted tactical forces involved in land, sea, and air warfighting operations. As a PCMCIA card, TVM can be embedded in portable, hand-held, and wearable PCs. Thus, it leverages emerging tactical displays including flat-panel, head-mounted displays. The end result of the program will be the demonstration of the system with U.S. Army and USMC personnel in an operational environment. Raytheon Systems Company, the U.S. Army Soldier Systems Command -- Natick RDE Center (SSCOM- NRDEC) and the Defense Advanced Research Projects Agency (DARPA) are partners in developing and demonstrating the TVM technology.

Cost of space-based laser ballistic missile defense

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 bemore » used in a ballistic missile defense system is still extremely uncertain, it is useful to examine methods for calculating the cost-exchange ration. 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. 28 references, 2 tables.« less

Cardiac missiles. A review of the literature and personal experience.

PubMed Central

Symbas, P N; Picone, A L; Hatcher, C R; Vlasis-Hale, S E

1990-01-01

The management of retained missiles in the heart is still controversial. In an attempt to define the issue more clearly, the reported cases in the English literature from 1940 to 1988 (group 1) and our experience from 1968 to 1988 (group 2) were reviewed. In group 1 there were 222 missiles retained in the hearts of 201 patients. The retained missiles were 45 bullets in 45 patients, 109 shrapnel in 99 patients, 18 pellets in 7 patients, and 50 unidentified missiles in 50 patients. Thirteen of the missiles were completely embedded intramyocardial missiles, 122 were partially intramyocardial, 47 were free in a cardiac chamber, and 40 were intrapericardial. One hundred four of the missiles were removed and 118 were left in place. In group 2 there were 24 missiles, 18 bullets, 1 bullet fragment, and 5 pellets retained in the hearts of 24 patients. Ten missiles were removed, no attempt was made in 13 patients, and an unsuccessful attempt was made to remove one other. From group 1 patients, 6 died, 2 with intracavitary missiles, 3 patients with partially intramyocardial, and 1 patient with an intrapericardial missile, all of whom had either unsuccessful or no attempt to remove the missile. Twenty-seven patients had symptoms, all of whom, except two, had either unsuccessful or no attempt to remove the missile. All group 2 patients did well and had been free of symptoms related to the missiles. This review suggests that the management of missiles in the heart should be individualized according to the patient's clinical course, the site, shape, and size of the missile, and that in selected patients missiles in the heart are tolerated well. PMID:2187422

Cardiac missiles. A review of the literature and personal experience.

PubMed

Symbas, P N; Picone, A L; Hatcher, C R; Vlasis-Hale, S E

1990-05-01

The management of retained missiles in the heart is still controversial. In an attempt to define the issue more clearly, the reported cases in the English literature from 1940 to 1988 (group 1) and our experience from 1968 to 1988 (group 2) were reviewed. In group 1 there were 222 missiles retained in the hearts of 201 patients. The retained missiles were 45 bullets in 45 patients, 109 shrapnel in 99 patients, 18 pellets in 7 patients, and 50 unidentified missiles in 50 patients. Thirteen of the missiles were completely embedded intramyocardial missiles, 122 were partially intramyocardial, 47 were free in a cardiac chamber, and 40 were intrapericardial. One hundred four of the missiles were removed and 118 were left in place. In group 2 there were 24 missiles, 18 bullets, 1 bullet fragment, and 5 pellets retained in the hearts of 24 patients. Ten missiles were removed, no attempt was made in 13 patients, and an unsuccessful attempt was made to remove one other. From group 1 patients, 6 died, 2 with intracavitary missiles, 3 patients with partially intramyocardial, and 1 patient with an intrapericardial missile, all of whom had either unsuccessful or no attempt to remove the missile. Twenty-seven patients had symptoms, all of whom, except two, had either unsuccessful or no attempt to remove the missile. All group 2 patients did well and had been free of symptoms related to the missiles. This review suggests that the management of missiles in the heart should be individualized according to the patient's clinical course, the site, shape, and size of the missile, and that in selected patients missiles in the heart are tolerated well.

Detection technique of targets for missile defense system

NASA Astrophysics Data System (ADS)

Guo, Hua-ling; Deng, Jia-hao; Cai, Ke-rong

2009-11-01

Ballistic missile defense system (BMDS) is a weapon system for intercepting enemy ballistic missiles. It includes ballistic-missile warning system, target discrimination system, anti-ballistic-missile guidance systems, and command-control communication system. Infrared imaging detection and laser imaging detection are widely used in BMDS for surveillance, target detection, target tracking, and target discrimination. Based on a comprehensive review of the application of target-detection techniques in the missile defense system, including infrared focal plane arrays (IRFPA), ground-based radar detection technology, 3-dimensional imaging laser radar with a photon counting avalanche photodiode (APD) arrays and microchip laser, this paper focuses on the infrared and laser imaging detection techniques in missile defense system, as well as the trends for their future development.

Army National Guard Air Defense Artillery Modernization: A Vision for the Future

DTIC Science & Technology

1994-05-15

plan to replace Stinger Under Armor (SUA) for the ARNG, and no guarantee that the BSFV will be in the future ARNG force, divisional assets will remain...Ballistic Missile SUA Stinger Under Armor TAA Total Army Analysis TAAD Theater Area Air Defense TASM Tactical Air-to-Surface Missiles TBM Tactical

Missiles for Asia The Need for Operational Analysis of U.S. Theater Ballistic Missiles in the Pacific

DTIC Science & Technology

2016-01-01

C O R P O R A T I O N Missiles for Asia? The Need for Operational Analysis of U.S. Theater Ballistic Missiles in the Pacific Jacob L. Heim • The...durability of the Intermediate-Range Nuclear Forces Treaty is in doubt. • China’s rapid military modernization could threaten U.S. forces. • Theater ...conventional land-based theater ballistic missiles (TBMs) could add to the U.S. portfolio of strike capabilities. In particular, the U.S. Army should ana- lyze

Selective management of embolized intracardiac missiles.

PubMed

Gandhi, S K; Marts, B C; Mistry, B M; Brown, J W; Durham, R M; Mazuski, J E

1996-07-01

Intracardiac projectiles are occasionally found in stable patients who have sustained penetrating trauma. These missiles may arise from embolization from a peripheral injury site. We describe 3 patients with embolized intracardiac projectiles. The diagnosis was suggested by the presence of a foreign body within the cardiac silhouette on chest roentgenograms and was confirmed using fluoroscopy, echocardiography, or computed tomography. The management of embolized intracardiac missiles should be individualized to each patient. All of our patients had fixed intracavitary right-sided missiles and were successfully managed expectantly.

Secondary missile injury from lightning strike.

PubMed

Blumenthal, Ryan

2012-03-01

A 48-year-old-woman was struck dead by lightning on October 24, 2010, in Pretoria, South Africa. The cause of death was due to direct lightning strike. Examination showed secondary missile injury on her legs. This secondary missile (shrapnel) injury was caused by the lightning striking the concrete pavement next to her. Small pieces of concrete were located embedded within the shrapnel wounds. This case report represents the first documented case of secondary missile formation (shrapnel injury) due to lightning strike in the literature.

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

PubMed

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

2011-04-01

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. 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. 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. 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.

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

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 Kingdom...

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

Calculation and design of a ramjet missile

NASA Astrophysics Data System (ADS)

Schubert, Johannes

The fundamentals for the design of a ramjet missile are treated. The chemical fundamentals of the solid rocket propellants used for ramjet missiles are outlined. The determination of the most favorable flying speed is discussed. The thermodynamic fundamentals (calculation of the solid propellant missile, calculation of the mixing procedure and the after burning in the pressure nozzle, and power calculation) are presented. The design specifications of the propulsion system are given.

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

17. Missile mural, third flight of stairs. Lyon Whiteman ...

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

17. Missile mural, third flight of stairs. Lyon - Whiteman Air Force Base, Minuteman Missile Launch Facility Trainer T-12, Northeast of Oscar-01 Missile Alert Facility, Knob Noster, Johnson County, MO

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.

New techniques for test development for tactical auto-pilots using microprocessors

NASA Astrophysics Data System (ADS)

Shemeta, E. H.

1980-07-01

This paper reports on a demonstration of the application of the method to generate system level tests for a typical tactical missile autopilot. The test algorithms are based on the autopilot control law. When loaded on the tester with appropriate control information, the complete autopilot is tested to establish if the specified control law requirements are met. Thus, the test procedure not only checks to see if the hardware is functional, but also checks the operational software. The technique also uses a 'learning' mode to allow minor timing or functional deviations from the expected responses to be incorporated in the test procedures. A potential application of this test development technique is the extraction of production test data for the various subassemblies. The technique will 'learn' the input-output patterns forming the basis for developement and production tests. If successful, these new techniques should allow the test development process to keep pace with semiconductor progress.

23 CFR 660.519 - Missile installations and facilities.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 23 Highways 1 2014-04-01 2014-04-01 false Missile installations and facilities. 660.519 Section... OPERATIONS SPECIAL PROGRAMS (DIRECT FEDERAL) Defense Access Roads § 660.519 Missile installations and...). (1) To implement 23 U.S.C. 210(h), DOD must make the determination that a contractor for a missile...

23 CFR 660.519 - Missile installations and facilities.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 23 Highways 1 2013-04-01 2013-04-01 false Missile installations and facilities. 660.519 Section... OPERATIONS SPECIAL PROGRAMS (DIRECT FEDERAL) Defense Access Roads § 660.519 Missile installations and...). (1) To implement 23 U.S.C. 210(h), DOD must make the determination that a contractor for a missile...

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

Review of the tactical evaluation tools for youth players, assessing the tactics in team sports: football.

PubMed

González-Víllora, Sixto; Serra-Olivares, Jaime; Pastor-Vicedo, Juan Carlos; da Costa, Israel Teoldo

2015-01-01

For sports assessment to be comprehensive, it must address all variables of sports development, such as psychological, social-emotional, physical and physiological, technical and tactical. Tactical assessment has been a neglected variable until the 1980s or 1990s. In the last two decades (1995-2015), the evolution of tactical assessment has grown considerably, given its importance in game performance. The aim of this paper is to compile and analyze different tactical measuring tools in team sports, particularly in soccer, through a bibliographical review. Six tools have been selected on five different criteria: (1) Instruments which assess tactics, (2) The studies have an evolution approach related to the tactical principles, (3) With a valid and reliable method, (4) The existence of publications mentioning the tool in the method, v. Applicable in different sports contexts. All six tools are structured around seven headings: introduction, objective(s), tactical principles, materials, procedures, instructions/rules of the game and published studies. In conclusion, the teaching-learning processes more tactical oriented have useful tactical assessment instrument in the literature. The selection of one or another depends some context information, like age and level of expertise of the players.

Hypersonic missile propulsion system

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 technologymore » 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.« less

POLARIS MISSILE DISPLAY AT THE USS BOWFIN MUSEUM AT PEARL ...

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

POLARIS MISSILE DISPLAY AT THE USS BOWFIN MUSEUM AT PEARL HARBOR. POLARIS A1 MISSILE IS ON THE LEFT (IN FOREGROUND) AND POLARIS A3 MISSILE IS ON THE 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

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.

[Traumatology due to ancient lead missile projectiles].

PubMed

Moog, Ferdinand Peter

2002-01-01

The lead missiles of slingers in antiquity, known as glans or molybdis, are widely considered to have been very dangerous projectiles of the ancient armies. Ballistic investigations and results of experimental archaeology seem to confirm this. However, the findings of medical history concerning these missiles disagree with this view. In ancient medical texts these missiles are only mentioned sporadically, as in Celsus or Paul of Aigina, and wounds caused by them are merely discussed incidentally. There is so far no evidence at all on them in palaeopathology. It is undisputed however that in individual cases these missiles were able to cause serious injuries, especially when they hit unprotected parts of the body. Accordingly, their main effect seems to have consisted in the intimidation of the enemy.

Time-to-impact estimation in passive missile warning systems

NASA Astrophysics Data System (ADS)

Şahıngıl, Mehmet Cihan

2017-05-01

A missile warning system can detect the incoming missile threat(s) and automatically cue the other Electronic Attack (EA) systems in the suit, such as Directed Infrared Counter Measure (DIRCM) system and/or Counter Measure Dispensing System (CMDS). Most missile warning systems are currently based on passive sensor technology operating in either Solar Blind Ultraviolet (SBUV) or Midwave Infrared (MWIR) bands on which there is an intensive emission from the exhaust plume of the threatening missile. Although passive missile warning systems have some clear advantages over pulse-Doppler radar (PDR) based active missile warning systems, they show poorer performance in terms of time-to-impact (TTI) estimation which is critical for optimizing the countermeasures and also "passive kill assessment". In this paper, we consider this problem, namely, TTI estimation from passive measurements and present a TTI estimation scheme which can be used in passive missile warning systems. Our problem formulation is based on Extended Kalman Filter (EKF). The algorithm uses the area parameter of the threat plume which is derived from the used image frame.

The North Korean missile program: How advanced is it?

DOE Office of Scientific and Technical Information (OSTI.GOV)

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-kilometermore » range would give North Korea the capability to reach all of Japan, and give Iran and Libya the capability to reach all of Israel.« less

Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

NASA Technical Reports Server (NTRS)

Martin, Andrew; Hunter, Harlo A.

1949-01-01

An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale moue1 of the Fairchild Lark missile, The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses. The wind-tunnel-test data indicate that rolling the missile 22.5 deg. had no serious effect on the static longitudinal stability. The desired maneuvering acceleration could not be attained with any of the horizontal wings tested, even with the horizontal wing flaps deflected 50 deg. The flaps on the 64A-209 wing (with small trailing-edge angles and flat sides) were effective at all flap deflections, while the flaps on the 16-series wings (with large trailing-edge angles) lost effectiveness at small flap deflections. The data showed that rolling moment existed when the vertical wing flaps were deflected with the model at other than zero angle of attack. A similar rolling moment probably would be found . with the horizontal wing flaps deflected and the model yawed.

Missile war injuries of the face.

PubMed

Kummoona, Raja K

2011-11-01

In a society struggling to rebuild its country after 3 decades of years of dictatorships and wars, Iraqi maxillofacial and craniofacial surgeons play a critical role in treatment of many most serious terrorist missile injuries of the face by ongoing conflict in Iraq. This study reflects our surgical techniques of treating explosive missile injuries and other combat- and terrorism-related injuries and also evaluates the immediate and secondary phase managements of patients with missile injuries. This study includes 235 patients with missile war injuries of the face during a period of 4 years; all injured patients were treated in the Maxillofacial Unit of Surgical Specialties Hospital, Medical City, Baghdad. There were 195 men and 40 women; their ages ranged from 1 to 70 years (mean, 39.5 years). Posttraumatic missile facial deformities were classified as follows: 95 patients (40.43%) had bone loss; 72 patients (30.64%) had soft tissue loss; 33 patients (14.05%) had orbital injuries; and 35 patients (14.90%) had other deformities of scar contracture, fistula, and sinus formation. Two techniques were used for reconstruction of the bony defect, either by bone chips carried by osteomesh tray harvested from the iliac crest or by free block of corticocancellous bone graft from the iliac crest. Soft tissue reconstruction was done by local flaps and regional flaps such as lateral cervical and cervicofacial flaps, and the orbit was reconstructed by bone graft, lyophilized dura, and sialastic implant. Scar contracture was treated by scar revision and sinus tract excised at the same time of scar revision. In conclusion, the primary phase required an urgent airway management, controlling an active bleeding by surgical intervention; most entrance and exit wounds as well as retained missiles were located in the cheek, chin, and mandibular body, with few cases of mortality due to complications related to head injuries. The secondary phase management of deformities of the face as a

15 CFR 742.5 - Missile technology.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 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 unmanned... missile and space programs of the recipient country; (iv) The nonproliferation credentials of the...

The new politics of missile proliferation

DOE Office of Scientific and Technical Information (OSTI.GOV)

Karp, A.

1996-10-01

The author addresses the most consequential proliferation battle of the 1990s which occurred in Washington over the interpretation of the long-term threat to the United States from ballistic missiles. In the early 1970s, the stabilization of the US-Soviet strategic relationship led to new disputes over the other side`s future intentions, seen most graphically in Western debates over the implications of the Soviet SS-18 and SS-20 missile programs. Today, in much the same way, proliferation politics has matured to the point that surprises are few and the most challenging problem is anticipating the more distant future. Washington`s ballistic missile proliferation battlemore » was sparked by National Intelligence Estimate (NIE) 95-19, entitled {open_quotes}Emerging Threats to North America During the Next 15 Years,{close_quotes} released by the National Intelligence Council in November 1995. This document updated the evidence of regional missile programs reviewed in a similar report issued in 1993, and recapitulated the previous finding that {open_quotes}No country, other than the major declared nuclear powers, will develop or otherwise acquire a ballistic missile in the next 15 years that could threatened the contiguous 48 states or Canada.{close_quotes} The new report confirmed what several other studies of missile proliferation had already established: that besides the five nuclear-weapon states (the United States, Russia, China, France and Britain), only India, Israel and Japan are in a position to develop an ICBM during the foreseeable future, and while all have relevant capabilities, none are undertaking the steps necessary to develop an actual ICBM.« less

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

The science, technology, and politics of ballistic missile defense

DOE Office of Scientific and Technical Information (OSTI.GOV)

Coyle, Philip E.

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 billionmore » 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.« less

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.

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

The Art and Science of Tactics

DTIC Science & Technology

1977-01-01

THE ART AND SCIENCE OF TACTICS by MAJOR ROBERT A. DOUGHTY, US ARMY E stablishing the nature of tactics has been a pastime of professional...tactics in the US Army have implicitly begun to assume that tactics is more an exact science than an " art and science ." As one recent military writer...and 19th centuries generally agreed that tactics was more an art than it was a science . Many agreed with the terse definition given by Antoine

2. Missile transfer building, interior, transporter/erector on left, storage and ...

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

2. Missile transfer building, interior, transporter/erector on left, storage and shipping container, ballistic missile (SSCBM) containing minuteman II missile on right - Ellsworth Air Force Base, Delta Flight, Missile Roll Transfer Building, 920 Kennedy Road, Interior, Jackson County, SD

Deterrence and Space-Based Missile Defense

DTIC Science & Technology

2009-01-01

8. Curt Weldon , “Charting a New Course on Missile Defense,” in Spacepower for a New Millen­ nium: Space and U.S. National Security, ed. Peter L...Stimson Center, 2003), 4. 45. See Baker Spring , “The Enduring Features of the Debate over Missile Defense,” Backgrounder no. 1972, Heritage Foundation

Development of guidance laws for a variable-speed missile

DOE Office of Scientific and Technical Information (OSTI.GOV)

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. Guidancemore » 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.« less

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

Modelling the infrared ManPAD Track Angle Bias missile countermeasure

NASA Astrophysics Data System (ADS)

Birchenall, Richard Peter; Richardson, Mark A.; Butters, Brian; Walmsley, Roy

2011-09-01

The paper describes the concept of missile evolution and the development of a range of missile advancements designed to defeat the evolving array of aircraft defensive measures. The paper describes a typical military aircraft infrared signature and looks at how examination of different spectral parts of the target signature can be used to determine if an aircraft has deployed flare countermeasures. This information can then be used to trigger a missile countermeasure in attempt for the missile to continue with a successful engagement. The paper examines the Track Angle Bias missile countermeasure and details the results of over 1000 engagement simulations designed to test the effectiveness of the missile countermeasure. The paper references the work published in IRPT Volume 53, Issue 5, September 2010, Pages 372-380.

Missile Defense Acquisition: Failure Is Not An Option

DTIC Science & Technology

2016-01-26

Missile Defense Acquisition: Failure is Not an Option 8 capabilities. Retired Marine General James Mattis ’ renowned quote rings true, “The enemy...american-missile-defense-why-failure-is- an-option. 18 Vago Muradian, “Interview: Gen. James Mattis , Commander, U.S. Joint Forces Command,” 23 May...2010, http://archive.defensenews.com/article/20100523/DEFFEAT03/5230301/Gen- James - Mattis . 19 Institute for Defense Analyses, p. II-3. 20 Missile

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

77 FR 3514 - Protection Against Turbine Missiles

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-24

... NUCLEAR REGULATORY COMMISSION [NRC-2009-0481] Protection Against Turbine Missiles AGENCY: Nuclear... (NRC or Commission) is issuing a revision to Regulatory Guide 1.115, ``Protection Against Turbine... structures, systems, and components against missiles resulting from turbine failure by the appropriate...

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

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

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

Experimental study at low supersonic speeds of a missile concept having opposing wraparound tails

NASA Technical Reports Server (NTRS)

Allen, Jerry M.; Watson, Carolyn B.

1994-01-01

A wind-tunnel investigation has been performed at low supersonic speeds (at Mach numbers of 1.60, and 2.16) to evaluate the aerodynamic characteristics of a missile concept capable of being tube launched and controlled with a simple one-axis canard controller. This concept, which features an axisymmetric body with two planar canards and four wraparound tail fins arranged in opposing pairs, must be in rolling motion to be controllable in any radial plane with the planar canards. Thus, producing a constant rolling moment that is invariant with speed and attitude to provide the motion is desirable. Two tail-fin shaping designs, one shaved and one beveled, were evaluated for their efficiency in producing the needed rolling moments, and the results showed that the shaved fins were much more desirable for this task than the beveled fins.

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.

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

European Missile Defense and Russia

DTIC Science & Technology

2014-07-01

defense system in Europe by 2018 , which involved four phases at the time. The first phase consisted of an early warning radar estab- lished in Turkey...bal- listic missile interceptor site in Europe, slated to be operational in Redizkowo, Poland, by 2018 , equipped with the SM-3 Block IIA interceptor...fourth phases, that is towards 2018 and 2020, the U.S. missile defence sector almost reaches Russia’s Urals. This is not what we have agreed on.29

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

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

Tactical Missile Conceptual Design,

DTIC Science & Technology

1980-09-01

Temperature ..... ........... 110 a. Example I .... ................. 111 6 Page b. Example II ... ............... .. 112 6. Simple IR System...meet a current threat. An example of this might be an advance in material science, which allows higher inlet turbine temperatures for a turbojet...Pmin = k TO B n N 0)min Boltzmans constant is k = 1.38 x 10- 2 3 joule/ k. The value of kT0 at room temperature is 4 x 10 - 21 watt/cps of bandwidth

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

14. Photographic copy of photograph, dated 21 July 1971 (original ...

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

14. Photographic copy of photograph, dated 21 July 1971 (original print in possession of U.S. Space & Strategic Defense Command Historic Office CSSD-HO, Huntsville, AL). Photographer unknown. View of missile site control building turret wall during early construction, illustrating the massive amount of rebar utilized in the project. - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

Aerodynamic potpourri

NASA Technical Reports Server (NTRS)

Wilson, R. E.

1981-01-01

Aerodynamic developments for vertical axis and horizontal axis wind turbines are given that relate to the performance and aerodynamic loading of these machines. Included are: (1) a fixed wake aerodynamic model of the Darrieus vertical axis wind turbine; (2) experimental results that suggest the existence of a laminar flow Darrieus vertical axis turbine; (3) a simple aerodynamic model for the turbulent windmill/vortex ring state of horizontal axis rotors; and (4) a yawing moment of a rigid hub horizontal axis wind turbine that is related to blade coning.

Sherborne Missile Fire Frequency with Unconstraint Parameters

NASA Astrophysics Data System (ADS)

Dong, Shaquan

2018-01-01

For the modeling problem of shipborne missile fire frequency, the fire frequency models with unconstant parameters were proposed, including maximum fire frequency models with unconstant parameters, and actual fire frequency models with unconstant parameters, which can be used to calculate the missile fire frequency with unconstant parameters.

Communication networks for the tactical edge

NASA Astrophysics Data System (ADS)

Evans, Joseph B.; Pennington, Steven G.; Ewy, Benjamin J.

2017-04-01

Information at the tactical level is increasingly critical in today's conflicts. The proliferation of commercial tablets and smart phones has created the ability for extensive information sharing at the tactical edge, beyond the traditional tactical voice communications and location information. This is particularly the case in Gray Zone conflicts, in which tactical decision making and actions are intertwined with information sharing and exploitation. Networking of tactical devices is the key to this information sharing. In this work, we detail and analyze two network models at different parts of the Gray Zone spectrum, and explore a number of networking options including Named Data Networking. We also compare networking approaches in a variety of realistic operating environments. Our results show that Named Data Networking is a good match for the disrupted networking environments found in many tactical situations

A Hybrid Location Method for Missile Security Team Positioning

DTIC Science & Technology

2007-01-01

Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. A Hybrid Location Method for Missile Security...Bell and Weir A Hybrid Location Method for Missile Security Team Positioning Chief Master Sergeant Michael C. Dawson Air Force Logistics Management...problem oj locating security teams over a geographic area to maintain security Jor US Air Force Intercontinental Ballistic Missile Systems. A

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.

75 FR 43156 - Federal Advisory Committee; Missile Defense Advisory Committee

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-23

... DEPARTMENT OF DEFENSE Office of the Secretary Federal Advisory Committee; Missile Defense Advisory Committee AGENCY: Missile Defense Agency (MDA), DoD. ACTION: Notice of closed meeting. SUMMARY: Under the... Defense announces that the Missile Defense Advisory Committee will meet on August 4 and 5, 2010, in...

Recovery of a Missile Embolus From the Right Ventricle.

PubMed

Marshall, Clement D; Ma, Michael R; Park, Julia; Sheckter, Clifford C; Massoudi, Rustin A; Ligman, Cathleen M; Jou, Ronald M; Ogden, William D

2017-01-01

Missile embolism is a clinical entity in which a projectile object enters a blood vessel and is carried to a distant part of the body. We present a case of the discovery of an iliac vein to right ventricle missile embolus in a young man, with successful extraction through a right atriotomy. We provide a historical overview of the literature concerning missile embolism, and we argue that whereas acute embolized projectiles should be removed in almost all cases, it may be reasonable to simply observe an asymptomatic chronic missile embolus. Copyright © 2017 The Society of Thoracic Surgeons. Published by Elsevier Inc. All rights reserved.

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.

The use of laterally vectored thrust to counter thrust asymmetry in a tactical jet aircraft

NASA Technical Reports Server (NTRS)

1983-01-01

A nonlinear, six degree-of-freedom flight simulator for a twin engine tactical jet was built on a hybrid computer to investigate lateral vectoring of the remaining thrust component for the case of a single engine failure at low dynamic pressures. Aircraft control was provided by an automatic controller rather than a pilot, and thrust vector control was provided by an open-loop controller that deflected a vane (located on the periphery of each exhaust jet and normally streamlined for noninterference with the flow). Lateral thrust vectoring decreased peak values of lateral control deflections, eliminated the requirement for steady-state lateral aerodynamic control deflections, and decreased the amount of altitude lost for a single engine failure.

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

DOE Office of Scientific and Technical Information (OSTI.GOV)

Park, Y.J.; Reich, M.

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.

MissileLab User’s Guide

DTIC Science & Technology

2009-02-01

extension) that contain the airframe geometry specific to a single configuration. Results from a MissileLab run will be stored in a directory...re)created and contain all APE results and associated input files. C. Background In the early stages of missile system design, it is necessary to...Copying the AeroEngine Files After installation, the subdirectories in the “AeroEngine” directory contain contact information on how to obtain valid

Experimental study of ELF signatures developed by ballistic missile launch

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 deploymentmore » 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.« less

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…

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

DOE Office of Scientific and Technical Information (OSTI.GOV)

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.more » The seasonal flooding and near surface water has aided in the movement of surface fragments.« less

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

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

[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.

The Gulf War's impact on ballistic missile defense systems

DOE Office of Scientific and Technical Information (OSTI.GOV)

Likourezos, G.

1993-01-01

During Desert Storm the United States and its allies had an overwhelming advantage over the Iraqi armed forces. Nonetheless, the Iraqis managed to strike Israel and Saudi Arabia with Scud missiles. Because of the changing political climate and the expanding transfer of technology among nations, there is great concern by the US Government about missile proliferation and the ability of any country to obtain weapons of mass destruction. The US Government tried to downplay this concern for many years until the recent events in the Middle East affirmed its seriousness. The truth is that every year countries once thought tomore » pose no international threat are acquiring biological, chemical, and nuclear weapons. Moreover, state-sponsored terrorist organizations could conceivably acquire these weapons in the future. In response to these concerns and in light of the lessons learned from the Gulf War, President George Bush in January 1991 redirected the SDI Program to concentrate on providing protection from limited ballistic missile strikes, rather than from an all-out nuclear missile attack by the Soviet Union. The Patriot air defense system, after knocking out Iraqi Scuds in the Gulf War with a near perfect record, appears for now to be the working model for the development of advanced ballistic missile defense systems - direct-kill missiles and projectiles instead of laser and particle beams. Even though the Patriot's use in Desert Storm has been argued by some to have been militarily insignificant, it has managed to change the viewpoint of many political and scientific leaders into believing that ballistic missile defense systems are needed to defend peaceful population centers and military installations from missile strikes like the ones on Israel and Saudi Arabia. 18 refs.« less

Bone as a secondary missile: an experimental study in the fragmenting of bone by high-velocity missiles.

PubMed

Amato, J J; Syracuse, D; Seaver, P R; Rich, N

1989-05-01

Destruction to soft tissues by bone fragments has been described in the literature. Civilian and military injuries have been reported in which bone fragments have acted as secondary missiles. This experimental study demonstrates, in detail, the formation of the temporary cavity within bone and the forward motion of these bone spicules. The knowledge of the ballistics will assist in the treatment of wounds caused by high-velocity missiles.

Stackable In-Line Surface Missile Launch System for a Modular Payload Bay

DTIC Science & Technology

2004-11-08

stacked modules 14 are connected 8 and sealed to form a single long continuous missile tube . 9 Flexible seals may be used at the base of each missile...vehicles, such as missiles, 22 both through vertical launch via specialized launch tubes on the 23 submarine, and horizontal launch via the submarine’s...torpedo 24 tubes . In some cases, the missiles are quite large, such as the 1 1 Tomahawk missile, which requires sufficient support for the 2 large

10. 351st Missile Wing Maintenance insignia on wall opposite the ...

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

10. 351st Missile Wing Maintenance insignia on wall opposite the entrance. Lyon - Whiteman Air Force Base, Minuteman Missile Launch Facility Trainer T-12, Northeast of Oscar-01 Missile Alert Facility, Knob Noster, Johnson County, MO

Fluid dynamic mechanisms and interactions within separated flows and their effects on missile aerodynamics

NASA Astrophysics Data System (ADS)

Addy, A. L.; Chow, W. L.; Korst, H. H.; White, R. A.

1983-05-01

Significant data and detailed results of a joint research effort investigating the fluid dynamic mechanisms and interactions within separated flows are presented. The results were obtained through analytical, experimental, and computational investigations of base flow related configurations. The research objectives focus on understanding the component mechanisms and interactions which establish and maintain separated flow regions. Flow models and theoretical analyses were developed to describe the base flowfield. The research approach has been to conduct extensive small-scale experiments on base flow configurations and to analyze these flows by component models and finite-difference techniques. The modeling of base flows of missiles (both powered and unpowered) for transonic and supersonic freestreams has been successful by component models. Research on plume effects and plume modeling indicated the need to match initial plume slope and plume surface curvature for valid wind tunnel simulation of an actual rocket plume. The assembly and development of a state-of-the-art laser Doppler velocimeter (LDV) system for experiments with two-dimensional small-scale models has been completed and detailed velocity and turbulence measurements are underway. The LDV experiments include the entire range of base flowfield mechanisms - shear layer development, recompression/reattachment, shock-induced separation, and plume-induced separation.

The Evolution of the Cruise Missile

DTIC Science & Technology

1985-09-01

the country is to remain militarily strong. A leading student of military technology has put it this way: ... new and more effective weapons have...make the best decisions and plans. Students of the cruise missile sould focus on the basic characteristics of the weapon. Consequently, this study...Hughes, "Competition Optios for the Medium Range Air-t- ace Missile Pmgram." unpublished MA Thesis, American Uiversity , 1981, 23, 24; "Navy Sees MRASM

The Clinton plan for theater missile defenses: Costs and alternatives

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 approachesmore » 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.« less

OBLIQUE VIEW OF MISSILE LAB WITH CRANE SHOWING SOUTHWEST AND ...

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

OBLIQUE VIEW OF MISSILE LAB WITH CRANE SHOWING SOUTHWEST AND NORTHWEST SIDES. 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

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

OBLIQUE VIEW OF MISSILE LAB WITH CRANE SHOWING SOUTHEAST AND ...

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

OBLIQUE VIEW OF MISSILE LAB WITH CRANE SHOWING SOUTHEAST AND SOUTHWEST SIDES. VIEW FACING NORTH/NORTHWEST - 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

NASA aerodynamics program

NASA Technical Reports Server (NTRS)

Williams, Louis J.; Hessenius, Kristin A.; Corsiglia, Victor R.; Hicks, Gary; Richardson, Pamela F.; Unger, George; Neumann, Benjamin; Moss, Jim

1992-01-01

The annual accomplishments is reviewed for the Aerodynamics Division during FY 1991. The program includes both fundamental and applied research directed at the full spectrum of aerospace vehicles, from rotorcraft to planetary entry probes. A comprehensive review is presented of the following aerodynamics elements: computational methods and applications; CFD validation; transition and turbulence physics; numerical aerodynamic simulation; test techniques and instrumentation; configuration aerodynamics; aeroacoustics; aerothermodynamics; hypersonics; subsonics; fighter/attack aircraft and rotorcraft.

75 FR 77848 - Closed Meeting of the Missile Defense Advisory Committee

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-14

... DEPARTMENT OF DEFENSE Office of the Secretary Closed Meeting of the Missile Defense Advisory Committee AGENCY: Department of Defense; Missile Defense Agency (MDA). ACTION: Notice. SUMMARY: Under the... Defense announces that the following Federal advisory committee meeting of the Missile Defense Advisory...

76 FR 71556 - Missile Defense Advisory Committee; Notice of Closed Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-18

... DEPARTMENT OF DEFENSE Office of the Secretary Missile Defense Advisory Committee; Notice of Closed Meeting AGENCY: Missile Defense Agency (MDA), Department of Defense. ACTION: Notice of closed meeting... Missile Defense Advisory Committee will take place. DATES: Tuesday, December 13, 2011 through Wednesday...

75 FR 77849 - Closed Meeting of the Missile Defense Advisory Committee

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-14

... DEPARTMENT OF DEFENSE Office of the Secretary Closed Meeting of the Missile Defense Advisory Committee AGENCY: Department of Defense; Missile Defense Agency (MDA). ACTION: Notice. SUMMARY: Under the... Defense announces that the following Federal advisory committee meeting of the Missile Defense Advisory...

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

DOE Office of Scientific and Technical Information (OSTI.GOV)

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, whilemore » 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.« less

Research on conformal dome of Karman-curve shape

NASA Astrophysics Data System (ADS)

Zhang, Yunqiang; Chang, Jun; Niu, Yajun

2018-01-01

Because the conformal optical technology can obviously improve the aerodynamic performance of the infrared guidance missile, it has been studied deeply in recent years. By comparing the performance of the missiles with conformal dome and conventional missiles, the advantages of the conformal optical technology are demonstrated in the maneuverability and stealth of the missile. At present, the study of conformal optical systems focuses on ellipsoid or quadratic curve types. But in actual use, the dome using these curves is not the best choice. In this paper, the influence of different shape of the dome on aerodynamic performance, aerodynamic heating, internal space volume and other properties is discussed. The result shows infrared optical system with conformal dome of Karman-curve shape has a good application prospect, is the future direction of development. Finally, the difficult problems of conformal dome of Karman-curve shape are discussed.

Modeling Powered Aerodynamics for the Orion Launch Abort Vehicle Aerodynamic Database

NASA Technical Reports Server (NTRS)

Chan, David T.; Walker, Eric L.; Robinson, Philip E.; Wilson, Thomas M.

2011-01-01

Modeling the aerodynamics of the Orion Launch Abort Vehicle (LAV) has presented many technical challenges to the developers of the Orion aerodynamic database. During a launch abort event, the aerodynamic environment around the LAV is very complex as multiple solid rocket plumes interact with each other and the vehicle. It is further complicated by vehicle separation events such as between the LAV and the launch vehicle stack or between the launch abort tower and the crew module. The aerodynamic database for the LAV was developed mainly from wind tunnel tests involving powered jet simulations of the rocket exhaust plumes, supported by computational fluid dynamic simulations. However, limitations in both methods have made it difficult to properly capture the aerodynamics of the LAV in experimental and numerical simulations. These limitations have also influenced decisions regarding the modeling and structure of the aerodynamic database for the LAV and led to compromises and creative solutions. Two database modeling approaches are presented in this paper (incremental aerodynamics and total aerodynamics), with examples showing strengths and weaknesses of each approach. In addition, the unique problems presented to the database developers by the large data space required for modeling a launch abort event illustrate the complexities of working with multi-dimensional data.

Experimental missile wound to the brain.

PubMed

Carey, M E; Sarna, G S; Farrell, J B; Happel, L T

1989-11-01

Among civilians in the United States, 33,000 gunshot wound deaths occur each year; probably half of these involve the head. In combat, head wounds account for approximately half of the immediate mortality when death can be attributed to a single wound. No significant reduction in the neurosurgical mortality associated with these wounds has occurred between World War II and the Vietnam conflict, and very little research into missile wounds of the brain has been undertaken. An experimental model has been developed in the anesthetized cat whereby a ballistic injury to the brain may be painlessly reproduced in order that the pathophysiological effects of brain wounding may be studied and better treatments may be designed to lower the mortality and morbidity rates associated with gunshot wounds. Prominent among physiological effects observed in this model was respiratory arrest even though the missile did not injure the brain stem directly. The incidence of prolonged respiratory arrest increased with increasing missile energy, but arrest was often reversible provided respiratory support was given. It is possible that humans who receive a brain wound die from missile-induced apnea instead of brain damage per se. The mortality rate in humans with brain wounding might be reduced by prompt respiratory support. Brain wounding was associated with persistently increased intracranial pressure and reduced cerebral perfusion pressure not entirely attributable to intracranial bleeding. The magnitude of these derangements appeared to be missile energy-dependent and approached dangerous levels in higher-energy wounds. All wounded cats exhibited postwounding increases in blood glucose concentrations consistent with a generalized stress reaction. A transient rise in hematocrit also occurred immediately after wounding. Both of these phenomena could prove deleterious to optimal brain function after injury.

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

78 FR 7449 - Boundary Revision of Minuteman Missile National Historic Site

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-01

... of Minuteman Missile National Historic Site AGENCY: National Park Service, Interior. ACTION... Act of November 29, 1999 (Pub. L. 106-115, 113 Stat. 1540-1543), the boundary of Minuteman Missile...; and at the Office for the Superintendent, Minuteman Missile National Historic Site, 21208 SD Hwy. 240...

Wind-tunnel investigation at supersonic speeds of a remote-controlled canard missile with a free-rolling-tail brake torque system

NASA Technical Reports Server (NTRS)

Blair, A. B., Jr.

1985-01-01

Wind tunnel tests were conducted at Mach numbers 1.70, 2.16, and 2.86 to determine the static aerodynamic characteristics of a cruciform canard-controlled missile with fixed or free rolling tailfin afterbodies. Mechanical coupling effects of the free-rolling-tail afterbody were investigated by using an electronic electromagnetic brake system providing arbitrary tail-fin brake torques with continuous measurements of tail-to-mainframe torque and tail roll rate. Remote-controlled canards were deflected to provide pitch, yaw, and roll control. Results indicate that the induced rolling moment coefficients due to canard yaw control are reduced and linearized for the free-rolling-tail (free-tail) configuration. The canards of the latter provide conventional roll control for the entire angle-of-attack test range. For the free-tail configuration, the induced rolling moment coefficient due to canard yaw control increased and the canard roll control decreased with increases in brake torque, which simulated bearing friction torque. It appears that a compromise in regard to bearing friction, for example, low-cost bearings with some friction, may allow satisfactory free-tail aerodynamic characteristics that include reductions in adverse rolling-moment coefficients and lower tail roll rates.

NASA aerodynamics program

NASA Technical Reports Server (NTRS)

Holmes, Bruce J.; Schairer, Edward; Hicks, Gary; Wander, Stephen; Blankson, Isiaiah; Rose, Raymond; Olson, Lawrence; Unger, George

1990-01-01

Presented here is a comprehensive review of the following aerodynamics elements: computational methods and applications, computational fluid dynamics (CFD) validation, transition and turbulence physics, numerical aerodynamic simulation, drag reduction, test techniques and instrumentation, configuration aerodynamics, aeroacoustics, aerothermodynamics, hypersonics, subsonic transport/commuter aviation, fighter/attack aircraft and rotorcraft.

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].

Remote video assessment for missile launch facilities

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 viamore » 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.« less

Exposure assessment of JAVELIN missile combustion products

NASA Astrophysics Data System (ADS)

Lundy, Donald O.; Langford, Roland E.

1994-02-01

Characterization and analysis of combustion products resulting from firing the JAVELIN missile were performed. Of those combustion products analyzed, it was determined that airborne lead concentrations exceeded the OSHA PEL of 50 micrograms each time the missile was fired while in the enclosure. Since the OSHA PEL standard is based upon a continuous rather than a short-term exposures blood lead concentrations were sought to ascertain the relationship between a short duration airborne exposure and its physiological effect on the body. Blood lead levels were taken on 49 test subjects prior to various JAVELIN missile test firings. Of those 49, 21 were outfitted With personal sampling equipment to determine airborne concentrations at the Assistant Gunner and Gunner positions. Periodic blood sampling after a single exposure showed an average increase of 2.27 micrograms/dL for all test subjects. Recommendations were made to consider changes in the positioning of the enclosure inhabitants to minimize airborne lead concentrations, to limit the number of missiles fired (situation dependent), and replacement of the lead B-resorcyolate with a non-lead containing burn rate modifier for the launch motor.

32 CFR 644.531 - Warning to public of danger in handling explosive missiles.

Code of Federal Regulations, 2013 CFR

2013-07-01

... explosive missiles. 644.531 Section 644.531 National Defense Department of Defense (Continued) DEPARTMENT OF... handling explosive missiles. When any land which has been contaminated with explosive objects, or chemical..., in the event of the discovery of an explosive missile, or an object resembling an explosive missile...

32 CFR 644.531 - Warning to public of danger in handling explosive missiles.

Code of Federal Regulations, 2011 CFR

2011-07-01

... explosive missiles. 644.531 Section 644.531 National Defense Department of Defense (Continued) DEPARTMENT OF... handling explosive missiles. When any land which has been contaminated with explosive objects, or chemical..., in the event of the discovery of an explosive missile, or an object resembling an explosive missile...

Program LRCDM2: Improved aerodynamic prediction program for supersonic canard-tail missiles with axisymmetric bodies

NASA Technical Reports Server (NTRS)

Dillenius, Marnix F. E.

1985-01-01

Program LRCDM2 was developed for supersonic missiles with axisymmetric bodies and up to two finned sections. Predicted are pressure distributions and loads acting on a complete configuration including effects of body separated flow vorticity and fin-edge vortices. The computer program is based on supersonic panelling and line singularity methods coupled with vortex tracking theory. Effects of afterbody shed vorticity on the afterbody and tail-fin pressure distributions can be optionally treated by companion program BDYSHD. Preliminary versions of combined shock expansion/linear theory and Newtonian/linear theory have been implemented as optional pressure calculation methods to extend the Mach number and angle-of-attack ranges of applicability into the nonlinear supersonic flow regime. Comparisons between program results and experimental data are given for a triform tail-finned configuration and for a canard controlled configuration with a long afterbody for Mach numbers up to 2.5. Initial tests of the nonlinear/linear theory approaches show good agreement for pressures acting on a rectangular wing and a delta wing with attached shocks for Mach numbers up to 4.6 and angles of attack up to 20 degrees.

Overcoming Space and Time Disadvantages in Joint Theater Missile Defense

DTIC Science & Technology

2002-02-04

Disadvantages in Joint Theater Missile Defense (Unclassified) 9. Personal Authors: Major Robert Kelley 10.Type of Report: FINAL 11. Date of Report...Classification of This Page Unclassified NAVAL WAR COLLEGE Newport, RI Overcoming Space and Time Disadvantages in Joint Theater Missile Defense By Robert...Covered (from... to) - Title and Subtitle Overcoming Space and Time Disadvantages in Joint Theater Missile Defense Contract Number Grant Number

Theater Land Attack Cruise Missile Defense: Guarding the Back Door

DTIC Science & Technology

1999-06-01

employ radio command, laser, anti- radiation homing, or electro-optical guidance systems. TASMs will benefit from the same technological developments...mile-range Al-Husayn missile within range of all major Israeli cities, and its nuclear facilities in the Negev desert. The existence of these sites...solutions (“engage on remote”), or simply launch missiles without radiating , and allow the AFCR to guide the missiles to the target

The Full Costs of Ballistic Missile Defense

DTIC Science & Technology

2003-01-01

following words: “We assess that countries developing ballistic missiles would also develop various responses to US theater and national defenses. Russia...and China each have developed numerous countermeasures and probably are willing to sell the requisite technologies. • Many countries , such as North...penetration aids and countermeasures. • These countries could develop countermeasures based on these technologies by the time they flight test their missiles

32 CFR 644.531 - Warning to public of danger in handling explosive missiles.

Code of Federal Regulations, 2010 CFR

2010-07-01

... missiles. 644.531 Section 644.531 National Defense Department of Defense (Continued) DEPARTMENT OF THE ARMY... explosive missiles. When any land which has been contaminated with explosive objects, or chemical/biological..., in the event of the discovery of an explosive missile, or an object resembling an explosive missile...

32 CFR 644.531 - Warning to public of danger in handling explosive missiles.

Code of Federal Regulations, 2014 CFR

2014-07-01

... missiles. 644.531 Section 644.531 National Defense Department of Defense (Continued) DEPARTMENT OF THE ARMY... explosive missiles. When any land which has been contaminated with explosive objects, or chemical/biological..., in the event of the discovery of an explosive missile, or an object resembling an explosive missile...

32 CFR 644.531 - Warning to public of danger in handling explosive missiles.

Code of Federal Regulations, 2012 CFR

2012-07-01

... missiles. 644.531 Section 644.531 National Defense Department of Defense (Continued) DEPARTMENT OF THE ARMY... explosive missiles. When any land which has been contaminated with explosive objects, or chemical/biological..., in the event of the discovery of an explosive missile, or an object resembling an explosive missile...

Ballistic Missile Early Warning System Clear Air Force Station, ...

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

Ballistic Missile Early Warning System - 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

Five Pioneers with Scale Models of Their Missiles

NASA Technical Reports Server (NTRS)

1950-01-01

Five pioneers pose with scale models of their missiles they created in the 1950s. From left to right: Dr. Ernst Stuhlinger, a member of the original German rocket team who directed the Research Projects Office, Army Ballistic Missile Agency (ABMA); Major General Holger Toftoy, who consolidated U.S. missile and rocketry development; Professor Herman Oberth, a rocket pioneer and Dr. von Braun's mentor; Dr. Wernher von Braun, Director, Development Operation Division, ABMA; and Dr. Robert Lusser, who served as assistant director for Reliability Engineering for ABMA. This photographis was taken February 1, 1956 by Hank Walker and appeared in February 27, 1956 issue of Life magazine.

Airborne Tactical Crossload Planner

DTIC Science & Technology

2017-12-01

set out in the Airborne Standard Operating Procedure (ASOP). 14. SUBJECT TERMS crossload, airborne, optimization, integer linear programming ...they land to their respective sub-mission locations. In this thesis, we formulate and implement an integer linear program called the Tactical...to meet any desired crossload objectives. xiv We demonstrate TCP with two real-world tactical problems from recent airborne operations: one by the

Infrared tracker for a portable missile launcher

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 themore » 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.« less

1999 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

Hahne, David E. (Editor)

1999-01-01

NASA's High-Speed Research Program sponsored the 1999 Aerodynamic Performance Technical Review on February 8-12, 1999 in Anaheim, California. The review was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in the areas of Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High Lift, and Flight Controls. The review objectives were to: (1) report the progress and status of HSCT aerodynamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientists and engineers working on HSCT aerodynamics. In particular, single and midpoint optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT simulation results were presented, along with executive summaries for all the Aerodynamic Performance technology areas. The HSR Aerodynamic Performance Technical Review was held simultaneously with the annual review of the following airframe technology areas: Materials and Structures, Environmental Impact, Flight Deck, and Technology Integration. Thus, a fourth objective of the Review was to promote synergy between the Aerodynamic Performance technology area and the other technology areas of the HSR Program. This Volume 1/Part 1 publication covers configuration aerodynamics.

Vector neural network signal integration for radar application

NASA Astrophysics Data System (ADS)

Bierman, Gregory S.

1994-07-01

The Litton Data Systems Vector Neural Network (VNN) is a unique multi-scan integration algorithm currently in development. The target of interest is a low-flying cruise missile. Current tactical radar cannot detect and track the missile in ground clutter at tactically useful ranges. The VNN solves this problem by integrating the energy from multiple frames to effectively increase the target's signal-to-noise ratio. The implementation plan is addressing the APG-63 radar. Real-time results will be available by March 1994.

Civilian casualties of Iraqi ballistic missile attack to Tehran, capital of Iran.

PubMed

Khaji, Ali; Fallahdoost, Shoaodin; Soroush, Mohammad-Reza; Rahimi-Movaghar, Vafa

2012-01-01

To determine the pattern of causalities of Iraqi ballistic missile attacks on Tehran, the capital of Iran, during Iraq-Iran war. Data were extracted from the Army Staff Headquarters based on daily reports of Iranian army units during the war. During 52 days, Tehran was stroked by 118 Al-Hussein missiles (a modified version of Scud missile). Eighty-six missiles landed in populated areas. During Iraqi missile attacks, 422 civilians died and 1 579 injured (4.9 deaths and 18.3 injuries per missile). During 52 days, 8.1 of the civilians died and 30.4 injured daily. Of the cases that died, 101 persons (24%) were excluded due to the lack of information. Among the remainders, 179 (55.8%) were male and 142 (44.2%) were female. The mean age of the victims was 25.3 years+/-19.9 years. Our results show that the high accuracy of modified Scud missiles landed in crowded areas is the major cause of high mortality in Tehran. The presence of suitable warning system and shelters could reduce civilian casualties. The awareness and readiness of civilian defense forces, rescue services and all medical facilities for dealing with mass casualties caused by ballistic missile attacks are necessary.

An Ada Object Oriented Missile Flight Simulation

DTIC Science & Technology

1991-09-01

identify by block number) This thesis uses the Ada programming language in the design and development of an air-to-air missile flight simulation with...object oriented techniques and sound software engineering principles. The simulation is designed to be more understandable, modifiable, efficient and...Department of Computer Science ii ABSTRACT This thesis uses the Ada programming language in the design and development of an air-to-air missile flight

Analysis of the development of missile-borne IR imaging detecting technologies

NASA Astrophysics Data System (ADS)

Fan, Jinxiang; Wang, Feng

2017-10-01

Today's infrared imaging guiding missiles are facing many challenges. With the development of targets' stealth, new-style IR countermeasures and penetrating technologies as well as the complexity of the operational environments, infrared imaging guiding missiles must meet the higher requirements of efficient target detection, capability of anti-interference and anti-jamming and the operational adaptability in complex, dynamic operating environments. Missileborne infrared imaging detecting systems are constrained by practical considerations like cost, size, weight and power (SWaP), and lifecycle requirements. Future-generation infrared imaging guiding missiles need to be resilient to changing operating environments and capable of doing more with fewer resources. Advanced IR imaging detecting and information exploring technologies are the key technologies that affect the future direction of IR imaging guidance missiles. Infrared imaging detecting and information exploring technologies research will support the development of more robust and efficient missile-borne infrared imaging detecting systems. Novelty IR imaging technologies, such as Infrared adaptive spectral imaging, are the key to effectively detect, recognize and track target under the complicated operating and countermeasures environments. Innovative information exploring techniques for the information of target, background and countermeasures provided by the detection system is the base for missile to recognize target and counter interference, jamming and countermeasure. Modular hardware and software development is the enabler for implementing multi-purpose, multi-function solutions. Uncooled IRFPA detectors and High-operating temperature IRFPA detectors as well as commercial-off-the-shelf (COTS) technology will support the implementing of low-cost infrared imaging guiding missiles. In this paper, the current status and features of missile-borne IR imaging detecting technologies are summarized. The key

1998 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

McMillin, S. Naomi (Editor)

1999-01-01

NASA's High-Speed Research Program sponsored the 1998 Aerodynamic Performance Technical Review on February 9-13, in Los Angeles, California. The review was designed to bring together NASA and industry HighSpeed Civil Transport (HSCT) Aerodynamic Performance technology development participants in areas of. Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High-Lift, and Flight Controls. The review objectives were to: (1) report the progress and status of HSCT aerodynamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientists and engineers working HSCT aerodynamics. In particular, single and multi-point optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT simulation results were presented along with executive summaries for all the Aerodynamic Performance technology areas. The HSR Aerodynamic Performance Technical Review was held simultaneously with the annual review of the following airframe technology areas: Materials and Structures, Environmental Impact, Flight Deck, and Technology Integration. Thus, a fourth objective of the Review was to promote synergy between the Aerodynamic Performance technology area and the other technology areas of the HSR Program.

1998 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

McMillin, S. Naomi (Editor)

1999-01-01

NASA's High-Speed Research Program sponsored the 1998 Aerodynamic Performance Technical Review on February 9-13, in Los Angeles, California. The review was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in areas of Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High-Lift, and Flight Controls. The review objectives were to (1) report the progress and status of HSCT aerodynamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientists and engineers working HSCT aerodynamics. In particular, single and multi-point optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT simulation results were presented along with executive summaries for all the Aerodynamic Performance technology areas. The HSR Aerodynamic Performance Technical Review was held simultaneously with the annual review of the following airframe technology areas: Materials and Structures, Environmental Impact, Flight Deck, and Technology Integration. Thus, a fourth objective of the Review was to promote synergy between the Aerodynamic Performance technology area and the other technology areas of the HSR Program.

Test launch of a Topol/SS-25 missile

NASA Image and Video Library

2013-10-10

View of test launch of a Topol/SS-25 missile on Oct. 10, 2013 as seen by the Expedition 37 crew aboard the International Space Station (ISS). The missile was launched at 17:39 MSK (13:39 UTC) from Kapustin Yar to the Sary Shagan test site in Kazakhstan. Also sent as Twitter message.

Generic Surface-to-Air Missile Model.

DTIC Science & Technology

1979-10-01

describes the Generic Surface-to-Air Missile Model (GENSAM) which evaluates the outcome of an engagement between a surface-to-air missile system and an...DETAILS OF THE GENERIC SAM MODEL 3-1 3.1 Coordinate Transformations 3-1 3.1.1 Coordinate Systems 3-1 3.1.2 Coordinate Transformations 3-4 3.1.3 Functions...Tracking Radars 3-54 3.3.11 Deception Jamming and Tracking Radars 3-55 3.3.12 Jaming and Track Radar Downlinks 3-56 3.3.13 Infrared Surveillance Systems 3

Enveloping Aerodynamic Decelerator

NASA Technical Reports Server (NTRS)

Nock, Kerry T. (Inventor); Aaron, Kim M. (Inventor); McRonald, Angus D. (Inventor); Gates, Kristin L. (Inventor)

2018-01-01

An inflatable aerodynamic deceleration method and system is provided for use with an atmospheric entry payload. The inflatable aerodynamic decelerator includes an inflatable envelope and an inflatant, wherein the inflatant is configured to fill the inflatable envelope to an inflated state such that the inflatable envelope surrounds the atmospheric entry payload, causing aerodynamic forces to decelerate the atmospheric entry payload.

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.

Development and qualification of the US Cruise Missile Propulsion System

NASA Astrophysics Data System (ADS)

Reardon, William H.; Cifone, Anthony J.

1992-09-01

This paper provides a description of the very successful Cruise Missile gas turbine propulsion program managed by the United States Department of Defense. The paper contains a summary of the procurement process, the technical and programmatic milestones, issues and challenges, and lessons learned. In the past fifteen years, testing at the Naval Air Propulsion Center has included over 800 cruise engine development and component substantiation efforts spanning the engine specification qualification requirements. This paper provides a detailed account of environmental test techniques used to qualify the F107 family of gas turbine engines which propel the U.S. Cruise Missile. In addition, a missile freestream flight test simulation for the TOMAHAWK Cruise Missile is discussed along with current and future program efforts.

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

22. Launch Area, Missile Assembly Building VIEW SOUTHWEST, EAST AND ...

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

22. Launch Area, Missile Assembly Building VIEW SOUTHWEST, EAST AND NORTH ELEVATION - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

20. Launch Area, Missile Assembly Building VIEW SOUTHEAST, NORTH AND ...

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

20. Launch Area, Missile Assembly Building VIEW SOUTHEAST, NORTH AND WEST ELEVATION - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

21. Launch Area, Missile Assembly Building VIEW NORTHWEST, SOUTH AND ...

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

21. Launch Area, Missile Assembly Building VIEW NORTHWEST, SOUTH AND EAST ELEVATION - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

Modeling of the 6DOF Missile Dynamics using the NED Axes System

DTIC Science & Technology

1997-08-01

representer le corps du missile, l’autodirecteur ainsi que Ia ligne missile-but. Le systeme d’axes le plus couramment utilise dans le domaine de la ...simulation de missiles tactiques ainsi que dans la librairie de composantes de modele de simulation du CRDV est le systeme d’axes NED, qui utilise l’axe x...RESEARCH ESTABLISHMENT CENTRE DE RECHERCHES POUR LA DEFENSE VALCARTIER,QuEBEC DREV- N-9703 MODELING OF THE 6DOF MISSILE DYNAMICS USING THE NED AXES

15. Photographic copy of photograph, dated 30 August 1971 (original ...

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

15. Photographic copy of photograph, dated 30 August 1971 (original print in possession of CSSD-HO, Huntsville, AL). Photographer unknown. View (southwest to northeast) of missile site control building. Of particular interest is the uncompleted subterranean portion and the workers, who give an indication of the actual scale of the building. In the foreground can be seen the beginning of the heat sink - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

1999 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

Hahne, David E. (Editor)

1999-01-01

NASA's High-Speed Research Program sponsored the 1999 Aerodynamic Performance Technical Review on February 8-12, 1999 in Anaheim, California. The review was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in the areas of Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High Lift, and Flight Controls. The review objectives were to (1) report the progress and status of HSCT aerodynamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientists and engineers working on HSCT aerodynamics. In particular, single and midpoint optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT simulation results were presented, along with executive summaries for all the Aerodynamic Performance technology areas. The HSR Aerodynamic Performance Technical Review was held simultaneously with the annual review of the following airframe technology areas: Materials and Structures, Environmental Impact, Flight Deck, and Technology Integration. Thus, a fourth objective of the Review was to promote synergy between the Aerodynamic Performance technology area and the other technology areas of the HSR Program. This Volume 1/Part 2 publication covers the design optimization and testing sessions.

24. Launch Area, Missile Assembly Building, detail of original work ...

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

24. Launch Area, Missile Assembly Building, detail of original work cabinets VIEW NORTHWEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

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

19. Launch Area, general view of Missile Assembly Building and ...

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

19. Launch Area, general view of Missile Assembly Building and Generator Building VIEW SOUTHWEST - NIKE Missile Battery PR-79, Launch Area, East Windsor Road south of State Route 101, Foster, Providence County, RI

Civilian casualties of Iranian cities by ballistic missile attacks during the Iraq-Iran war (1980-1988).

PubMed

Khaji, Ali; Fallahdoost, Shoaodin; Soroush, Mohammad Reza

2010-04-01

To determine the nature and extent of Iranian casualties by ballistic missile attacks during the eight years of the Iraq-Iran war. The data collected about Iraqi missile strikes on Iranian cities included the following: date and time, number and type of missiles, cities targeted, and injuries and deaths resulting from impacts of missiles in civilian areas. The data were extracted from a database that was constructed by the army staff headquarters based on daily reports of Iranian army units during the war. Over a period of eight years (1980-1988), Iraqi army fired 533 ballistic missiles at Iranian territories. From those, 414 missiles (77.7%) landed on Iranian cities. The impacts of these missiles caused the deaths of 2,312 civilians and injured 11,625 others. Three types of ballistic missiles were used: FROG-7, Scud, and Al-Hussein (a modified version of the Scud missile). Twenty-seven cities in Iran were struck by Iraqi ballistic missiles. The highest mortalities from ballistic missiles were in Dezful and Tehran. Iraqi missile attacks continued for 90 months (2,748 days). Our results point to the necessity of investigating the psychological consequences of Iraqi ballistic missile attacks among survivors in 27 Iranian cities during the eight years of the Iraq-Iran war.

Modular Digital Missile Guidance, Phase I2

DTIC Science & Technology

1976-01-28

at OMR. The revised study plan was fornally approved by ONR on 29 May 1975, confining the sinulatlon analysis work to a Class II missile with...functions analyzed in tne Phase I and Phase 11 studies . It can be seen thatf tnere practicable» (based on the results of function partitioning trade...llaillAU AS a result of this study » three generic missile families have oeen established and» relative to this classification» on

Final Environmental Assessment for Conventional Strike Missile Demonstration

DTIC Science & Technology

2010-08-11

impacts of conducting a single demonstration flight test of the Conventional Strike Missile (CSM). The CSM Demonstration flight test vehicle would...Vehicle would glide at hypersonic velocities in the upper atmosphere, prior to a land or ocean impact at the US Army Kwajalein Atoll/Reagan Test Site...SIGNIFICANT IMPACT ENVIRONMENTAL ASSESSMENT FOR CONVENTIONAL STRIKE MISSILE DEMONSTRATION AGENCY: United States Air Force (USAF) BACKGROUND

The Science and Technology of the US National Missile Defense System

NASA Astrophysics Data System (ADS)

Postol, Theodore A.

2010-03-01

The National Missile Defense System utilizes UHF and X-band radars for search, track and discrimination, and interceptors that use long-wave infrared sensors to identify and home on attacking warheads. The radars and infrared sensors in the missile defense system perform at near the theoretical limits predicted by physics. However, in spite of the fantastic technical advances in sensor technology, signal processing, and computational support functions, the National Missile Defense System cannot be expected to ever work in realistic combat environments. This talk will describe why these impressive technologies can never deliver on the promise of a credible defense against long-range ballistic missiles.

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.

Longitudinal Stability and Control Characteristics from a Flight Investigation of a Cruciform Canard Missile Configuration Having an Exposed Wing-canard Area Ratio of 16:1

NASA Technical Reports Server (NTRS)

Moul, Martin T; Wineman, Andrew R

1952-01-01

A flight investigation has been made to determine the longitudinal stability and control characteristics of a 60 0 delta-wing-canard missile configuration with an exposed wing-canard area ratio of 16:1. The results presented include the longitudinal stability derivatives, control effectiveness, and drag characteristics for a Mach number range of 0.75 to 1.80 and are compared with the results of a similar configuration having larger 6ontrols. Stability characteristics are also presented from the flights of an interdigitated canard configuration at a Mach number of 2.08 and a wing-body configuration at Mach numbers of 1.25 to 1.45. The stability derivatives varied gradually with Mach number with the exception of the damping-in-pitch derivative. Aerodynamic damping in pitch decreased to a minimum at a Mach number of 1.0 3, then increased to a peak value at a Mach number of 1.26 followed by a gradual decrease at higher Mach numbers. The aerodynamic-center location of the in-line canard configuration shifted rearward 13 percent of the mean aerodynamic chord at transonic speeds. The pitching-moment curve slope was 25 percent greater for the model having no canards than for the in-line configuration. No large effects of interdigitation were noted in the stability derivatives. Pitching effectiveness of the in-line configuration was maintained throughout the Mach number range. A comparison of the stability and control characteristics of two canard configurations having different area controls showed that decreasing the control area 44 percent decreased the pitching effectiveness proportionally, shifted the aerodynamic-center location rearward 9 to 14 percent of the mean aerodynamic chord, and reduced the total hinge moments required for 10 trimmed flight about 50 percent at transonic speeds.

Conventional Prompt Global Strike and Long-Range Ballistic Missiles: Background and Issues

DTIC Science & Technology

2016-02-24

13 The FALCON Study...range strike capabilities. These include bombers, cruise missiles, ballistic missiles, and boost-glide technologies that would mate a rocket booster...Command, Hearing, April 4, 2005. 23 Grossman, Elaine M., “U.S. General: Precise Long-Range Missiles may Enable Big Nuclear Cuts,” Inside the Pentagon

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

10. Storage and shipping container, ballistic missile, mounted on ballistic ...

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

10. Storage and shipping container, ballistic missile, mounted on ballistic missile trailer, view from left front - Ellsworth Air Force Base, Delta Flight, 10 mile radius around Exit 127 off Interstate 90, Interior, Jackson County, SD

11. Storage and shipping container, ballistic missile, mounted on ballistic ...

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

11. Storage and shipping container, ballistic missile, mounted on ballistic missile trailer, view from left side - Ellsworth Air Force Base, Delta Flight, 10 mile radius around Exit 127 off Interstate 90, Interior, Jackson County, SD

Training and Tactical Operationally Responsive Space Operations

NASA Astrophysics Data System (ADS)

Sorensen, B.; Strunce, R., Jr.

Current space assets managed by traditional space system control resources provide communication, navigation, intelligence, surveillance, and reconnaissance (ISR) capabilities using satellites that are designed for long life and high reliability. The next generation Operationally Responsive Space (ORS) systems are aimed at providing operational space capabilities which will provide flexibility and responsiveness to the tactical battlefield commander. These capabilities do not exist today. The ORS communication, navigation, and ISR satellites are being designed to replace or supplement existing systems in order to enhance the current space force. These systems are expected to rapidly meet near term space needs of the tactical forces. The ORS concept includes new tactical satellites specifically designed to support contingency operations such as increased communication bandwidth and ISR imagery over the theater for a limited period to support air, ground, and naval force mission. The Concept of Operations (CONOPS) that exists today specifies that in addition to operational control of the satellite, the tasking and scheduling of the ORS tactical satellite for mission data collection in support of the tactical warfighter will be accomplished within the Virtual Mission Operations Center (VMOC). This is very similar to what is currently being accomplished in a fixed Mission Operations Center on existing traditional ISR satellites. The VMOC is merely a distributed environment and the CONOPS remain virtually the same. As a result, there is a significant drawback to the current ORS CONOPS that does not account for the full potential of the ORS paradigm for supporting tactical forces. Although the CONOPS approach may be appropriate for experimental Tactical Satellites (TacSat), it ignores the issues associated with the In-Theater Commander's need to own and operate his dedicated TacSat for most effective warfighting as well as the Warfighter specific CONOPS. What is needed

Conceptual design of an ascent-phase interceptor missile

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 mmore » 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.« less

1997 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

Baize, Daniel G. (Editor)

1999-01-01

The High-Speed Research Program and NASA Langley Research Center sponsored the NASA High-Speed Research Program Aerodynamic Performance Workshop on February 25-28, 1997. The workshop was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in areas of Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High-Lift, Flight Controls, Supersonic Laminar Flow Control, and Sonic Boom Prediction. The workshop objectives were to (1) report the progress and status of HSCT aerodynamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientist and engineers working HSCT aerodynamics. In particular, single- and multi-point optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT Motion Simulator results were presented along with executive summaries for all the Aerodynamic Performance technology areas.

1997 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

Baize, Daniel G. (Editor)

1999-01-01

The High-Speed Research Program and NASA Langley Research Center sponsored the NASA High-Speed Research Program Aerodynamic Performance Workshop on February 25-28, 1997. The workshop was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in area of Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High-Lift, Flight Controls, Supersonic Laminar Flow Control, and Sonic Boom Prediction. The workshop objectives were to (1) report the progress and status of HSCT aerodynamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientist and engineers working HSCT aerodynamics. In particular, single- and multi-point optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT Motion Simulator results were presented along with executive summaries for all the Aerodynamic Performance technology areas.

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

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

Conventional Prompt Global Strike and Long-Range Ballistic Missiles: Background and Issues

DTIC Science & Technology

2014-05-05

13 The FALCON Study...bombers, cruise missiles, ballistic missiles, and boost-glide technologies that would mate a rocket booster with a hypersonic glide vehicle. Congress has...Strategic Command, Hearing, April 4, 2005. 23 Grossman, Elaine M., “U.S. General: Precise Long-Range Missiles may Enable Big Nuclear Cuts,” Inside the

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.

Radar waveform requirements for reliable detection of an aircraft-launched missile

NASA Astrophysics Data System (ADS)

Blair, W. Dale; Brandt-Pearce, Maite

1996-06-01

When tracking a manned aircraft with a phase array radar, detecting a missile launch (i.e., a target split) is particularly important because the missile can have a very small radar cross section (RCS) and drop below the horizon of the radar shortly after launch. Reliable detection of the launch is made difficult because the RCS of the missile is very small compared to that of the manned aircraft and the radar typically revisits a manned aircraft every few seconds. Furthermore, any measurements of the aircraft and missile taken shortly after the launch will be merged until the two targets are resolved in range, frequency, or space. In this paper, detection of the launched missile is addressed through the detection of the presence of target multiplicity with the in-phase and quadrature monopulse measurements. The probability of detecting the launch using monopulse processing will be studied with regard to the tracking signal-to-noise ratio and the number of pulses n the radar waveform.

Dispelling myths about verification of sea-launched cruise missiles.

PubMed

Lewis, G N; Ride, S K; Townsend, J S

1989-11-10

It is widely believed that an arms control limit on nuclear-armed sea-launched cruise missiles would be nearly impossible to verify. Among the reasons usually given are: these weapons are small, built in nondistinctive industrial facilities, deployed on a variety of ships and submarines, and difficult to distinguish from their conventionally armed counterparts. In this article, it is argued that the covert production and deployment of nuclear-armed sealaunched cruise missiles would not be so straightforward. A specific arms control proposal is described, namely a total ban on nuclear-armed sea-launched cruise missiles. This proposal is used to illustrate how an effective verification scheme might be constructed.

Alternative reproductive tactics and the propensity of hybridization.

PubMed

Tynkkynen, K; Raatikainen, K J; Häkkilä, M; Haukilehto, E; Kotiaho, J S

2009-12-01

One explanation for hybridization between species is the fitness benefits it occasionally confers to the hybridizing individuals. This explanation is possible in species that have evolved alternative male reproductive tactics: individuals with inferior tactics might be more prone to hybridization provided it increases their reproductive success and fitness. Here we experimentally tested whether the propensity of hybridization in the wild depends on male reproductive tactic in Calopteryx splendens damselflies. Counter to our expectation, it was males adopting the superior reproductive tactic (territoriality) that had greatest propensity to hybridize than males adopting the inferior tactics (sneakers and floaters). Moreover, among the territorial males, the most ornamented males had greatest propensity to hybridize whereas the pattern was reversed in the sneaker males. Our results suggest that there is fluctuating selection on male mate discrimination against heterospecific females depending on both ornament size and the male's reproductive tactic.

Joint Tactical Networks (JTN)

DTIC Science & Technology

2013-12-01

Selected Acquisition Report (SAR) RCS: DD-A&T(Q&A)823-284 Joint Tactical Networks (JTN) As of FY 2015 President’s Budget... Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection...to 00-00-2013 4. TITLE AND SUBTITLE Joint Tactical Networks (JTN) 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S

18. Photographic copy of photograph, dated 20 April 1971 (original ...

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

18. Photographic copy of photograph, dated 20 April 1971 (original print in possession of CSSD-HO, Huntsville, AL). Photographer unknown. View of missile site control building interior. At the interior of the turret, one can see the inspection fixture (furnished by the weapon system contractor) being installed on the antenna array support ring. This fixture was used to check the locations of the tapped holes through 36 shear key lugs - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

Aerodynamics of a linear oscillating cascade

NASA Technical Reports Server (NTRS)

Buffum, Daniel H.; Fleeter, Sanford

1990-01-01

The steady and unsteady aerodynamics of a linear oscillating cascade are investigated using experimental and computational methods. Experiments are performed to quantify the torsion mode oscillating cascade aerodynamics of the NASA Lewis Transonic Oscillating Cascade for subsonic inlet flowfields using two methods: simultaneous oscillation of all the cascaded airfoils at various values of interblade phase angle, and the unsteady aerodynamic influence coefficient technique. Analysis of these data and correlation with classical linearized unsteady aerodynamic analysis predictions indicate that the wind tunnel walls enclosing the cascade have, in some cases, a detrimental effect on the cascade unsteady aerodynamics. An Euler code for oscillating cascade aerodynamics is modified to incorporate improved upstream and downstream boundary conditions and also the unsteady aerodynamic influence coefficient technique. The new boundary conditions are shown to improve the unsteady aerodynamic influence coefficient technique. The new boundary conditions are shown to improve the unsteady aerodynamic predictions of the code, and the computational unsteady aerodynamic influence coefficient technique is shown to be a viable alternative for calculation of oscillating cascade aerodynamics.

Accidental low velocity atypical missile injury to the head.

PubMed

Chattopadhyay, Saurabh

2008-12-01

Missile injuries on the head are mostly due to firearms. Atypical missiles may be encountered in case of shrapnel of bomb explosions but rarely because of stones. The present case is a rare case where a stone propelled by the pressure from the rear wheel of a speeding truck on the highway, struck the head of a 7-year-old girl resulting in fatality. Reconstruction of the incident on the basis of history and postmortem findings throws some light on the mechanism. The case is unique as it is the first reported case of an accidental missile injury to the head resulting in fatality without any direct human involvement for propulsion of the projectile.

Missiles in the heart causing coronary artery disease 44 years after injury.

PubMed

Seipelt, R G; Vazquez-Jimenez, J F; Messmer, B J

2000-09-01

We present a case of two missiles in the heart causing coronary artery disease with first onset 44 years after the injury. The missiles were close to the right coronary artery and the left anterior descending coronary artery. The missiles initiated local arteriosclerosis in these vessels, with an extremely stretched time frame from injury to the onset of symptoms for coronary artery disease.

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

Federal Register 2010, 2011, 2012, 2013, 2014

2011-10-13

... Hurricane Missiles for Nuclear Power Plants AGENCY: Nuclear Regulatory Commission. ACTION: Regulatory guide... regulatory guide, (RG) 1.221, ``Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants... missiles that a nuclear power plant should be designed to withstand to prevent undue risk to the health and...

Tactical expertise assessment in youth football using representative tasks.

PubMed

Serra-Olivares, Jaime; Clemente, Filipe Manuel; González-Víllora, Sixto

2016-01-01

Specific football drills improve the development of technical/tactical and physical variables in players. Based on this principle, in recent years it has been possible to observe in daily training a growing volume of small-sided and conditioned games. These games are smaller and modified forms of formal games that augment players' perception of specific tactics. Despite this approach, the assessment of players' knowledge and tactical execution has not been well documented, due mainly to the difficulty in measuring tactical behavior. For that reason, this study aims to provide a narrative review about the tactical assessment of football training by using representative tasks to measure the tactical expertise of youth football players during small-sided and conditioned games. This study gives an overview of the ecological approach to training and the principles used for representative task design, providing relevant contribution and direction for future research into the assessment of tactical expertise in youth football.

Classical Aerodynamic Theory

NASA Technical Reports Server (NTRS)

Jones, R. T. (Compiler)

1979-01-01

A collection of papers on modern theoretical aerodynamics is presented. Included are theories of incompressible potential flow and research on the aerodynamic forces on wing and wing sections of aircraft and on airship hulls.

Issues in national missile defense

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 ofmore » 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.« less

Another Brick in the Wall: The Israeli Experience in Missile Defense

DTIC Science & Technology

2015-04-01

region. In particular, the way the Is- raelis decapitated the Egyptian Air Force on June 5 in only 3 hours engendered tremendous awe among the Arab...in a memo, “Iraq has the most aggressive and advanced ballistic missile development program in the Arab World.”8 Like the Egyptians , the Iraqis...range ballistic missile (SRBM) delivered in 1973 shortly be- fore the war with Israel. Like the Egyptians , the Syr- ians also used their missiles

Behavioural Thermoregulatory Tactics in Lacustrine Brook Charr, Salvelinus fontinalis

PubMed Central

Bertolo, Andrea; Pépino, Marc; Adams, Julie; Magnan, Pierre

2011-01-01

The need to vary body temperature to optimize physiological processes can lead to thermoregulatory behaviours, particularly in ectotherms. Despite some evidence of within-population phenotypic variation in thermal behaviour, the occurrence of alternative tactics of this behaviour is rarely explicitly considered when studying natural populations. The main objective of this study was to determine whether different thermal tactics exist among individuals of the same population. We studied the behavioural thermoregulation of 33 adult brook charr in a stratified lake using thermo-sensitive radio transmitters that measured hourly individual temperature over one month. The observed behavioural thermoregulatory patterns were consistent between years and suggest the existence of four tactics: two “warm” tactics with both crepuscular and finer periodicities, with or without a diel periodicity, and two “cool” tactics, with or without a diel periodicity. Telemetry data support the above findings by showing that the different tactics are associated with different patterns of diel horizontal movements. Taken together, our results show a clear spatio-temporal segregation of individuals displaying different tactics, suggesting a reduction of niche overlap. To our knowledge, this is the first study showing the presence of behavioural thermoregulatory tactics in a vertebrate. PMID:21490935

The Intercontinental Ballistic Missile and Post Cold War Deterrence

DTIC Science & Technology

2010-02-17

Bonnetain, Hugues and Philippe Mazzoni. " Histoire De Missiles...Le 1er GMS Du Plateau D’Albion." http://www.capcomespace.net/dossiers/espace_europeen...Mazzoni, " Histoire De Missiles...Le 1er GMS Du Plateau D’Albion," http://www.capcomespace.net/dossiers/espace_europeen/albion/; Ministère de la Défense

The Secret of Guided Missile Re-Entry,

DTIC Science & Technology

1986-06-25

I RD-PAI169 598 THE SECRET OF GUIDED MISSILE RE-ENTRY(U) FOREIGN / I TECHNOLOGY DIV NRIGHT-PATTERSON RFB OH J CHEN ET AL. I 25 JUN 96 FTD-ID(RS)T...TECHNOLOGY DIVISION THE SECRET OF GUIDED MISSILE RE-ENTRY by Chen Jingzhong, An Sehua J L 0 7 ’:;85’ ’ 0 *Approved for public release; Distribution...unlimite t d. :. 86 7 034.. FTD- ID(RS)T-0459-86 HUMAN TRANSLATION FTD-ID(RS)T-0459-86 25 June 1986 MICROFICHE NR: F - - 0Q 9? THE SECRET OF GUIDED

Aeroelastic stability analyses of two counter rotating propfan designs for a cruise missile model

NASA Technical Reports Server (NTRS)

Mahajan, Aparajit J.; Lucero, John M.; Mehmed, Oral; Stefko, George L.

1992-01-01

Aeroelastic stability analyses were performed to insure structural integrity of two counterrotating propfan blade designs for a NAVY/Air Force/NASA cruise missile model wind tunnel test. This analysis predicted if the propfan designs would be flutter free at the operating conditions of the wind tunnel test. Calculated stability results are presented for the two blade designs with rotational speed and Mach number as the parameters. A aeroelastic analysis code ASTROP2 (Aeroelastic Stability and Response of Propulsion Systems - 2 Dimensional Analysis), developed at LeRC, was used in this project. The aeroelastic analysis is a modal method and uses the combination of a finite element structural model and two dimensional steady and unsteady cascade aerodynamic models. This code was developed to analyze single rotation propfans but was modified and applied to counterrotating propfans for the present work. Modifications were made to transform the geometry and rotation of the aft rotor to the same reference frame as the forward rotor, to input a non-uniform inflow into the rotor being analyzed, and to automatically converge to the least stable aeroelastic mode.

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

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

Missile launch detection electric field perturbation experiment. Final report

DOE Office of Scientific and Technical Information (OSTI.GOV)

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 periodmore » 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.« less

Certification of tactics and strategies in aviation

NASA Technical Reports Server (NTRS)

Koelman, Hartmut

1994-01-01

The paper suggests that the 'tactics and strategies' notion is a highly suitable paradigm to describe the cognitive involvement of human operators in advanced aviation systems (far more suitable than classical functional analysis), and that the workload and situational awareness of operators are intimately associated with the planning and execution of their tactics and strategies. If system designers have muddled views about the collective tactics and strategies to be used during operation, they will produce sub-optimum designs. If operators use unproven and/or inappropriate tactics and strategies, the system may fail. The author wants to make a point that, beyond certification of people or system designs, there may be a need to go into more detail and examine (certify?) the set of tactics and strategies (i.e., the Operational Concept) which makes the people and systems perform as expected. The collective tactics and strategies determine the information flows and situational awareness which exists in organizations and composite human-machine systems. The available infrastructure and equipment (automation) enable these information flows and situational awareness, but are at the same time the constraining factor. Frequently, the tactics and strategies are driven by technology, whereas we would rather like to see a system designed to support an optimized Operational Concept, i.e., to support a sufficiently coherent, cooperative and modular set of anticipation and planning mechanisms. Again, in line with the view of MacLeod and Taylor (1993), this technology driven situation may be caused by the system designer's and operator job designer's over-emphasis on functional analysis (a mechanistic engineering concept), at the expense of a subject which does not seem to be well understood today: the role of the (human cognitive and/or automated) tactics and strategies which are embedded in composite human-machine systems. Research would be needed to arrive at a generally

Organizational Commitment through Organizational Socialization Tactics

ERIC Educational Resources Information Center

Filstad, Cathrine

2011-01-01

Purpose: The aim of this paper is to investigate how organizational socialization tactics affect newcomers' organizational commitment and learning processes. Design/methodology/approach: A survey was conducted using a measurement tool based on Van Maanen and Schein's theory on organizational socialization tactics and Kuvaas' measurement tools of…

Tactical AI in Real Time Strategy Games

DTIC Science & Technology

2015-03-26

TACTICAL AI IN REAL TIME STRATEGY GAMES THESIS Donald A. Gruber, Capt, USAF AFIT-ENG-MS-15-M-021 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE...protection in the United States. AFIT-ENG-MS-15-M-021 TACTICAL AI IN REAL TIME STRATEGY GAMES THESIS Presented to the Faculty Department of Electrical...DISTRIBUTION STATEMENT A APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED. AFIT-ENG-MS-15-M-021 TACTICAL AI IN REAL TIME STRATEGY GAMES THESIS Donald A

Cyber threat model for tactical radio networks

NASA Astrophysics Data System (ADS)

Kurdziel, Michael T.

2014-05-01

The shift to a full information-centric paradigm in the battlefield has allowed ConOps to be developed that are only possible using modern network communications systems. Securing these Tactical Networks without impacting their capabilities has been a challenge. Tactical networks with fixed infrastructure have similar vulnerabilities to their commercial counterparts (although they need to be secure against adversaries with greater capabilities, resources and motivation). However, networks with mobile infrastructure components and Mobile Ad hoc Networks (MANets) have additional unique vulnerabilities that must be considered. It is useful to examine Tactical Network based ConOps and use them to construct a threat model and baseline cyber security requirements for Tactical Networks with fixed infrastructure, mobile infrastructure and/or ad hoc modes of operation. This paper will present an introduction to threat model assessment. A definition and detailed discussion of a Tactical Network threat model is also presented. Finally, the model is used to derive baseline requirements that can be used to design or evaluate a cyber security solution that can be scaled and adapted to the needs of specific deployments.

Experimental Flight Characterization of a Canard-Controlled, Subsonic Missile

DTIC Science & Technology

2017-08-01

ARL-TR-8086 ● AUG 2017 US Army Research Laboratory Experimental Flight Characterization of a Canard- Controlled , Subsonic Missile...Laboratory Experimental Flight Characterization of a Canard- Controlled , Subsonic Missile by Frank Fresconi, Ilmars Celmins, James Maley, and...valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 1. REPORT DATE (DD-MM-YYYY) August 2017 2. REPORT TYPE Technical

Comparison of Theodorsen's Unsteady Aerodynamic Forces with Doublet Lattice Generalized Aerodynamic Forces

NASA Technical Reports Server (NTRS)

Perry, Boyd, III

2017-01-01

This paper identifies the unsteady aerodynamic forces and moments for a typical section contained in the NACA Report No. 496, "General Theory of Aerodynamic Instability and the Mechanism of Flutter," by Theodore Theodorsen. These quantities are named Theodorsen's aerodynamic forces (TAFs). The TAFs are compared to the generalized aerodynamic forces (GAFs) for a very high aspect ratio wing (AR = 20) at zero Mach number computed by the doublet lattice method. Agreement between TAFs and GAFs is very-good-to-excellent. The paper also reveals that simple proportionality relationships that are known to exist between the real parts of some GAFs and the imaginary parts of others also hold for the real and imaginary parts of the corresponding TAFs.

Tactics for Improving Parenting Skills (TIPS).

ERIC Educational Resources Information Center

Algozzine, Bob, Ed.; Ysseldyke, Jim, Ed.

This manual presents 99 one-sheet informational brochures designed to improve parenting skills. Each brochure is in a format suitable for duplicating, folding, and distributing. Each parenting "tactic" offers references to related brochures. Tactics are grouped under the following broad areas: (1) home/family involvement (e.g., accepting "The…

Soft-assembled Multilevel Dynamics of Tactical Behaviors in Soccer

PubMed Central

Ric, Angel; Torrents, Carlota; Gonçalves, Bruno; Sampaio, Jaime; Hristovski, Robert

2016-01-01

This study aimed to identify the tactical patterns and the timescales of variables during a soccer match, allowing understanding the multilevel organization of tactical behaviors, and to determine the similarity of patterns performed by different groups of teammates during the first and second halves. Positional data from 20 professional male soccer players from the same team were collected using high frequency global positioning systems (5 Hz). Twenty-nine categories of tactical behaviors were determined from eight positioning-derived variables creating multivariate binary (Boolean) time-series matrices. Hierarchical principal component analysis (PCA) was used to identify the multilevel structure of tactical behaviors. The sequential reduction of each set level of principal components revealed a sole principal component as the slowest collective variable, forming the global basin of attraction of tactical patterns during each half of the match. In addition, the mean dwell time of each positioning-derived variable helped to understand the multilevel organization of collective tactical behavior during a soccer match. This approach warrants further investigations to analyze the influence of task constraints on the emergence of tactical behavior. Furthermore, PCA can help coaches to design representative training tasks according to those tactical patterns captured during match competitions and to compare them depending on situational variables. PMID:27761120

Powered-Lift Aerodynamics and Acoustics. [conferences

NASA Technical Reports Server (NTRS)

1976-01-01

Powered lift technology is reviewed. Topics covered include: (1) high lift aerodynamics; (2) high speed and cruise aerodynamics; (3) acoustics; (4) propulsion aerodynamics and acoustics; (5) aerodynamic and acoustic loads; and (6) full-scale and flight research.

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.

Real-Time Target Motion Animation for Missile Warning System Testing

DTIC Science & Technology

2006-04-01

T. Perkins, R. Sundberg, J. Cordell, Z. Tun , and M. Owen, Real-time Target Motion Animation for Missile Warning System Testing, Proc. SPIE Vol 6208...Z39-18 Real-time target motion animation for missile warning system testing Timothy Perkins*a, Robert Sundberga, John Cordellb, Zaw Tunb, Mark

Extended Range Intercept Technology

DTIC Science & Technology

1991-09-01

particle size other than Freon class fluids. The requirements for a solvent used in grinding ammonium perchlorate to a one micron particle size are high...demonstrate a preprototype missile and launch control systems technology for tactical missile defense applications, including performance ...these two flights would be to verify flight performance and stability of the basic air frame and control system design (LTV Missiles and 1 -2 wp«-2a

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.

Departure Queue Prediction for Strategic and Tactical Surface Scheduler Integration

NASA Technical Reports Server (NTRS)

Zelinski, Shannon; Windhorst, Robert

2016-01-01

A departure metering concept to be demonstrated at Charlotte Douglas International Airport (CLT) will integrate strategic and tactical surface scheduling components to enable the respective collaborative decision making and improved efficiency benefits these two methods of scheduling provide. This study analyzes the effect of tactical scheduling on strategic scheduler predictability. Strategic queue predictions and target gate pushback times to achieve a desired queue length are compared between fast time simulations of CLT surface operations with and without tactical scheduling. The use of variable departure rates as a strategic scheduler input was shown to substantially improve queue predictions over static departure rates. With target queue length calibration, the strategic scheduler can be tuned to produce average delays within one minute of the tactical scheduler. However, root mean square differences between strategic and tactical delays were between 12 and 15 minutes due to the different methods the strategic and tactical schedulers use to predict takeoff times and generate gate pushback clearances. This demonstrates how difficult it is for the strategic scheduler to predict tactical scheduler assigned gate delays on an individual flight basis as the tactical scheduler adjusts departure sequence to accommodate arrival interactions. Strategic/tactical scheduler compatibility may be improved by providing more arrival information to the strategic scheduler and stabilizing tactical scheduler changes to runway sequence in response to arrivals.

1997 NASA High-Speed Research Program Aerodynamic Performance Workshop. Volume 1; Configuration Aerodynamics

NASA Technical Reports Server (NTRS)

Baize, Daniel G. (Editor)

1999-01-01

The High-Speed Research Program and NASA Langley Research Center sponsored the NASA High-Speed Research Program Aerodynamic Performance Workshop on February 25-28, 1997. The workshop was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in area of Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization), High-Lift, Flight Controls, Supersonic Laminar Flow Control, and Sonic Boom Prediction. The workshop objectives were to (1) report the progress and status of HSCT aerodyamic performance technology development; (2) disseminate this technology within the appropriate technical communities; and (3) promote synergy among the scientist and engineers working HSCT aerodynamics. In particular, single- and multi-point optimized HSCT configurations, HSCT high-lift system performance predictions, and HSCT Motion Simulator results were presented along with executive summaries for all the Aerodynamic Performance technology areas.

Enabling information management systems in tactical network environments

NASA Astrophysics Data System (ADS)

Carvalho, Marco; Uszok, Andrzej; Suri, Niranjan; Bradshaw, Jeffrey M.; Ceccio, Philip J.; Hanna, James P.; Sinclair, Asher

2009-05-01

Net-Centric Information Management (IM) and sharing in tactical environments promises to revolutionize forward command and control capabilities by providing ubiquitous shared situational awareness to the warfighter. This vision can be realized by leveraging the tactical and Mobile Ad hoc Networks (MANET) which provide the underlying communications infrastructure, but, significant technical challenges remain. Enabling information management in these highly dynamic environments will require multiple support services and protocols which are affected by, and highly dependent on, the underlying capabilities and dynamics of the tactical network infrastructure. In this paper we investigate, discuss, and evaluate the effects of realistic tactical and mobile communications network environments on mission-critical information management systems. We motivate our discussion by introducing the Advanced Information Management System (AIMS) which is targeted for deployment in tactical sensor systems. We present some operational requirements for AIMS and highlight how critical IM support services such as discovery, transport, federation, and Quality of Service (QoS) management are necessary to meet these requirements. Our goal is to provide a qualitative analysis of the impact of underlying assumptions of availability and performance of some of the critical services supporting tactical information management. We will also propose and describe a number of technologies and capabilities that have been developed to address these challenges, providing alternative approaches for transport, service discovery, and federation services for tactical networks.

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

Could missile attacks trigger acute myocardial infarction?

PubMed

Zubaid, Mohammad; Suresh, Cheiyil G; Thalib, Lukman; Rashed, Wafa

2006-08-01

During the Gulf war in 2003, Kuwait was targeted with missile attacks for 10 consecutive days. Our objective is to evaluate the influence of missile attacks on the incidence of acute myocardial infarction (AMI). We retrospectively compared the number of admissions for AMI presenting to a major general hospital during missile attacks period (MAP) in 2003 with four control periods. MAP and each control period consisted of the same number of days (10 days). The four control periods were the 10 days immediately before and after MAP; and the same time period as MAP for the years 2001 and 2002. The number of admissions for AMI was highest during MAP, 21 cases compared to 14-16 cases in the four control periods, with a trend towards increase during MAP (incidence rate ratio = 1.59; 95% CI 0.95 to 2.66, p < 0.07). The number of admissions for AMI during the first 5 days of MAP was significantly higher compared to the first 5 days of the four control periods (incidence rate ratio = 2.43; 95% CI 1.23 to 4.26, p < 0.01). The observed AMI admission rate during the first 5 days of MAP was significantly higher than expected for a 5-day period in the years 2001, 2002 and 2003. This increase was specific to AMI and did not affect other acute cardiac conditions. Missile attacks were associated with an increase in the incidence of AMI. This increase was specific to AMI and did not influence acute cardiac conditions.

76 FR 14589 - Defense Federal Acquisition Regulation Supplement; Repeal of Restriction on Ballistic Missile...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-17

...-AH18 Defense Federal Acquisition Regulation Supplement; Repeal of Restriction on Ballistic Missile...). Section 222 repeals the restriction on purchase of Ballistic Missile Defense research, development, test... Ballistic Missile Defense research, development, test, and evaluation that was required by section 222 of...

The need for command and control instant message adaptive interfaces: lessons learned from Tactical Tomahawk human-in-the-loop simulations.

PubMed

Cummings, M L

2004-12-01

In the recent development of a human-in-the-loop simulation test bed designed to examine human performance issues for supervisory control of the Navy's new Tactical Tomahawk missile, measurements of operator situation awareness (SA) and workload through secondary tasking were taken through an embedded instant messaging program. Instant message interfaces (otherwise known as "chat"), already a means of communication between Navy ships, allow researchers to query users in real-time in a natural, ecologic setting, and thus provide more realistic and unobtrusive measurements. However, in the course of this testing, results revealed that some subjects fixated on the real-time instant messaging secondary task instead of the primary task of missile control, leading to the overall degradation of mission performance as well as a loss of SA. While this research effort was the first to quantify command and control performance degradation as a result of instant messaging, the military has recognized that in its network centric warfare quest, instant messaging is a critical informal communication tool, but has associated problems. Recently, a military spokesman said that managing chat in current military operations was sometimes a "nightmare," because military personnel have difficulty in handling large amounts of information through chat, and then synthesizing knowledge from this information. This research highlights the need for further investigation of the role of instant messaging interfaces both on task performance and situation awareness, and how the associated problems could be ameliorated through adaptive display design.

White Sands Missile Range Overview & Introduction: Test Capabilities Briefing

DTIC Science & Technology

2011-11-07

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Army Test and Evaluation Command (ATEC),White Sands Missile Range,White Sands Missile Range,NM,88002...5000 8. PERFORMING ORGANIZATION REPORT NUMBER 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR’S ACRONYM(S) 11. SPONSOR...solar radiation, icing, salt fog, etc. • Instrumented for system performance / diagnostics  Climatics testing capabilities • Fixed and mobile test

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

Definitions of Tactical and Strategic: An Informal Study

NASA Technical Reports Server (NTRS)

Schutte, Paul C.

2004-01-01

Seventeen subject matter experts defined tactical and strategic within the aviation domain. They provided five verbs and a sentence describing both behaviors. The verbs for strategic behavior were Plan, Think, Arrange, Formulate, Intend, Devise, Anticipate, and Order. The verbs for tactical behavior were Act, Fly, Respond, Do, Avoid, Control, React, and Move. Verbs that were common to both were Get Information, Navigate, Know, Execute, Manage, Perceive, Understand, Direct, Concentrate, and Point. The responses highlight the difference between planning (strategic) and carrying out those plans (tactical). Tactical verbs are more action-oriented that change the state of the world after they have been accomplished. Strategic verbs are more prescriptive in that they do not change the state of the world but offer a procedure or program for changing the world. The pilot is in a tactical mode when actually moving the aircraft and in a strategic mode when thinking about moving it.

Study on combat effectiveness of air defense missile weapon system based on queuing theory

NASA Astrophysics Data System (ADS)

Zhao, Z. Q.; Hao, J. X.; Li, L. J.

2017-01-01

Queuing Theory is a method to analyze the combat effectiveness of air defense missile weapon system. The model of service probability based on the queuing theory was constructed, and applied to analyzing the combat effectiveness of "Sidewinder" and "Tor-M1" air defense missile weapon system. Finally aimed at different targets densities, the combat effectiveness of different combat units of two types' defense missile weapon system is calculated. This method can be used to analyze the usefulness of air defense missile weapon system.

The National Research Council study: "Making sense of ballistic missile defense"

NASA Astrophysics Data System (ADS)

Wilkening, Dean A.

2014-05-01

This chapter explains and summarizes the main findings of a recent National Research Council study entitled Making Sense of Ballistic Missile Defense: An Assessment of Concepts and Systems for U.S. Boost-Phase Missile Defense in Comparison to Other Alternatives.

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

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

Final Environmental Assessment of the Joint Air-to-Surface Stand-Off Missile (JASSM) Development and Evaluation Testing, White Sands Missile Range, New Mexico

DTIC Science & Technology

2001-12-01

Explosive Test Site Program Definition and Risk Reduction Permissible Exposure Limit Program Executive Office Propellants, Explosives, and...each test vehicle is flown in the captive mode and critical systems are functioned to further remove risk of failure due to the flight environment...of other inferior missiles would require a larger number of missiles, at increased procurement costs and risk to aircraft and crew, in order to

Aerodynamics Via Acoustics: Application of Acoustic Formulas for Aerodynamic Calculations

NASA Technical Reports Server (NTRS)

Farassat, F.; Myers, M. K.

1986-01-01

Prediction of aerodynamic loads on bodies in arbitrary motion is considered from an acoustic point of view, i.e., in a frame of reference fixed in the undisturbed medium. An inhomogeneous wave equation which governs the disturbance pressure is constructed and solved formally using generalized function theory. When the observer is located on the moving body surface there results a singular linear integral equation for surface pressure. Two different methods for obtaining such equations are discussed. Both steady and unsteady aerodynamic calculations are considered. Two examples are presented, the more important being an application to propeller aerodynamics. Of particular interest for numerical applications is the analytical behavior of the kernel functions in the various integral equations.

China and Proliferation of Weapons of Mass Destruction and Missiles: Policy Issues

DTIC Science & Technology

2007-05-09

medium-range ballistic missile (MRBM), which is based on the North Korean No Dong missile. U.S. intelligence was said to suspect that China Poly Ventures...stories, the DCI reported in August 2000 that, besides North Korean help, PRC entities provided “increased assistance” to Pakistan’s ballistic missile...development of the Shahab-3 and Shahab-4 MRBMs (with ranges, respectively, of about 800 mi. and 1,250 mi.). Over 100 PRC and North Korean experts worked there

Engine sizing and integration requirements for hypersonic airbreathing missile applications

NASA Astrophysics Data System (ADS)

Waltrup, P. J.; Billig, F. S.; Stockbridge, R. D.

1982-03-01

A procedure that provides a rational means for selecting an inlet/combustor configuration for a hypersonic airbreathing missile is presented. The particular problem that is addressed is the design of the sustained engine of a two stage missile that is constrained to be launched from a stowage volume that is either square or circular in cross section. The sustainer engine accelerates from a low altitude separation at Mach 4 and climbs to high altitude for cruise at Mach 8. The results show that a missile with an axisymmetric nose inlet provides a somewhat higher thrust capability and slightly better fuel efficiency than a chin type inlet. Aft entry inlets are shown to have a substantially lower thrust potential and lower engine efficiency. A criterion for determining the maximum contraction ratio of a fixed geometry inlet is established and applied to the exemplary missile designs. Combustor area ratio is examined and found to have a relatively small effect on engine performance for area ratios equal to or larger than that required to obtain maximum thrust at the take-over Mach number.

Feasibility Study On Missile Launch Detection And Trajectory Tracking

DTIC Science & Technology

2016-09-01

Vehicles ( UAVs ) in military operations, their role in a missile defense operation is not well defined. The simulation program discussed in this thesis ...targeting information to an attacking UAV to reliably intercept the missile. B . FURTHER STUDIES The simulation program can be enhanced to improve the...intercept the threat. This thesis explores the challenges in creating a simulation program to process video footage from an unstable platform and the

Precession missile feature extraction using sparse component analysis of radar measurements

NASA Astrophysics Data System (ADS)

Liu, Lihua; Du, Xiaoyong; Ghogho, Mounir; Hu, Weidong; McLernon, Des

2012-12-01

According to the working mode of the ballistic missile warning radar (BMWR), the radar return from the BMWR is usually sparse. To recognize and identify the warhead, it is necessary to extract the precession frequency and the locations of the scattering centers of the missile. This article first analyzes the radar signal model of the precessing conical missile during flight and develops the sparse dictionary which is parameterized by the unknown precession frequency. Based on the sparse dictionary, the sparse signal model is then established. A nonlinear least square estimation is first applied to roughly extract the precession frequency in the sparse dictionary. Based on the time segmented radar signal, a sparse component analysis method using the orthogonal matching pursuit algorithm is then proposed to jointly estimate the precession frequency and the scattering centers of the missile. Simulation results illustrate the validity of the proposed method.

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.

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.

Analysis of interference performance of tactical radio network

NASA Astrophysics Data System (ADS)

Nie, Hao; Cai, Xiaoxia; Chen, Hong

2017-08-01

Mobile Ad hoc network has a strong military background for its development as the core technology of the backbone network of US tactical Internet. And which tactical radio network, is the war in today's tactical use of the Internet more mature form of networking, mainly used in brigade and brigade following forces. This paper analyzes the typical protocol AODV in the tactical radio network, and then carries on the networking. By adding the interference device to the whole network, the battlefield environment is simulated, and then the throughput, delay and packet loss rate are analyzed, and the performance of the whole network and the single node before and after the interference is obtained.

Design and Analysis of Discrete Lateral Autopilots for Coordinated Bank- to-Turn Missiles

DTIC Science & Technology

1985-12-01

ANALYSIS OF DISCRETE LATERAL AUTOPILOTS FOR COORDINATED BANK-TO-TURN MISSILES * by Christos 1. Karadimas C)__ December 1935 LAJ *Thesis Advisor: Daniel .J...Include Security Clastfication) DESIGN AND ANALYSIS OF DISCRETE LATERAL AUTOPILOTS FOR .- COORDINATED BANK-TO-TURN MISSILES A - H . R o KARADIMAS ...Coordinated Bank-to-Turn Missiles - by Christos I. Karadimas Lieutenant, Hellenic Navy B.S., Hellenic Naval Academy, 1976 Submitted in partial

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

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

Posttraumatic missile injuries of the orofacial region.

PubMed

Kummoona, Raja

2008-03-01

Iraq became the world's battlefield for terrorist attack to the victims by different types of weapons of missile including explosive cars, explosive belt, fragments, rifle bullets, and handgun bullets. This situation in Iraq has been present for the last 3 years. As surgeons, we cannot influence the surge of this violence, but we are surely called upon to care for its victims. Missile injuries to the orofacial region have special features that provide the surgeon with multiple medical and surgical challenges when dealing with these injuries. This study include 140 patients who were treated in the maxillofacial unit, hospital of specialized surgery, in Medical City, Baghdad, during a period of 2 years; we had 28 women and 112 men, with ages ranging from 9 to 60 years (mean, 34.5 years), suffering from posttraumatic orofacial deformities. Deformities of the face as a complication of missile injuries were classified as bone loss, soft tissue loss, combined bone and soft tissue loss, and others (sinus tracts and poor scars); 62 patients (44%) had bone loss, 45 (32%) had soft tissue loss, 9 (6.4%) had combined bone and soft tissue loss, and 22 (15.7%) had other deformities.

Conventional Prompt Global Strike and Long-Range Ballistic Missiles: Background and Issues

DTIC Science & Technology

2012-02-13

Ballistic Missiles Congressional Research Service Forward-Based Global Strike ( FBGS ...missiles in the CPGS program. Forward-Based Global Strike ( FBGS ) Analysts have also explored the option of deploying long-range land-based ballistic

78 FR 48503 - Proposed Revision to Missiles Generated by Extreme Winds

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-08

...-0800, ``Standard Review Plan for the Review of Safety Analysis Reports for Nuclear Power Plants: LWR..., ``Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants,'' and Interim Staff Guidance DC... and Hurricane Missiles for Nuclear Power Plants'' (ADAMS, Accession No. ML110940300), and Interim...

About White Sands Missile Range

NASA Technical Reports Server (NTRS)

1991-01-01

Information on the White Sands Missile Range is given in viewgraph form. Navy programs, test sites, rocket programs, research rockets' booster capacity, current boost capabilities, ordnance and payload assembly areas, commercial space launch history and agreements, and lead times are among the topics covered.

Annual water resources review, White Sands Missile Range, New Mexico, 1980

USGS Publications Warehouse

Cruz, R.R.

1981-01-01

Ground-water data were collected in 1980 at White Sands Missile Range in south-central New Mexico. The total water pumped at White Sands Missile Range in 1980 was 725,053,000 gallons, which was 32.5 million gallons more than in 1979. The Post Headquarters well field, which produces more than 98 percent of the water used at White Sands Missile Range, pumped 712,909,000 gallons, which was 31.1 million gallons more in 1980 than in 1979. Data were collected for specific Range areas north of the Post Headquarters area that might have potential for future water-supply development. (USGS)

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.

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.

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).

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

Code of Federal Regulations, 2012 CFR

2012-07-01

..., 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 area...°43′00″ N., longitude 167°43′00″ E. Intermittent hazardous missile operations will be conducted within...

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

Code of Federal Regulations, 2010 CFR

2010-07-01

..., 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 area...°43′00″ N., longitude 167°43′00″ E. Intermittent hazardous missile operations will be conducted within...

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

Code of Federal Regulations, 2011 CFR

2011-07-01

..., 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 area...°43′00″ N., longitude 167°43′00″ E. Intermittent hazardous missile operations will be conducted within...

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

Code of Federal Regulations, 2013 CFR

2013-07-01

..., 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 area...°43′00″ N., longitude 167°43′00″ E. Intermittent hazardous missile operations will be conducted within...

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

Code of Federal Regulations, 2014 CFR

2014-07-01

..., 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 area...°43′00″ N., longitude 167°43′00″ E. Intermittent hazardous missile operations will be conducted within...

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.

Distributed Aerodynamic Sensing and Processing Toolbox

NASA Technical Reports Server (NTRS)

Brenner, Martin; Jutte, Christine; Mangalam, Arun

2011-01-01

A Distributed Aerodynamic Sensing and Processing (DASP) toolbox was designed and fabricated for flight test applications with an Aerostructures Test Wing (ATW) mounted under the fuselage of an F-15B on the Flight Test Fixture (FTF). DASP monitors and processes the aerodynamics with the structural dynamics using nonintrusive, surface-mounted, hot-film sensing. This aerodynamic measurement tool benefits programs devoted to static/dynamic load alleviation, body freedom flutter suppression, buffet control, improvement of aerodynamic efficiency through cruise control, supersonic wave drag reduction through shock control, etc. This DASP toolbox measures local and global unsteady aerodynamic load distribution with distributed sensing. It determines correlation between aerodynamic observables (aero forces) and structural dynamics, and allows control authority increase through aeroelastic shaping and active flow control. It offers improvements in flutter suppression and, in particular, body freedom flutter suppression, as well as aerodynamic performance of wings for increased range/endurance of manned/ unmanned flight vehicles. Other improvements include inlet performance with closed-loop active flow control, and development and validation of advanced analytical and computational tools for unsteady aerodynamics.

Nature's Ballistic Missile.

PubMed

Robb, E J; Barron, G L

1982-12-17

The parasitic fungus Haptoglossa mirabilis infects its rotifer host by means of a gun-shaped attack cell. The anterior end of the cell is elongated to form a barrel; the wall at the mouth is invaginated deep into the cell to form a bore. A walled chamber at the base of the bore houses a complex, missile-like attack apparatus. The projectile is fired from the gun cell at high speed to accomplish initial penetration of the host.

Air-to-Air Missile Enhanced Scoring with Kalman Smoothing

DTIC Science & Technology

2012-03-01

Samuel and Robert Popoli. Modern Tracking Systems. Artech House, 1999. 3. Brown , Robert G. and Patrick Y. C. Hwang . Introduction to Random Signals and...Air-to-Air Missile Enhanced Scoring with Kalman Smoothing THESIS Jonathon Gipson, Captain, USAF AFIT/GE/ENG/12-18 DEPARTMENT OF THE AIR FORCE AIR...AFIT/GE/ENG/12-18 Air-to-Air Missile Enhanced Scoring with Kalman Smoothing THESIS Presented to the Faculty Department of Electrical and Computer

Conventional Prompt Global Strike and Long-Range Ballistic Missiles: Background and Issues

DTIC Science & Technology

2013-01-10

and Long-Range Ballistic Missiles Congressional Research Service Forward-Based Global Strike ( FBGS ...they may address the nuclear ambiguity issues raised by long-range ballistic missiles in the CPGS program. Forward-Based Global Strike ( FBGS

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.

Direct use of linear time-domain aerodynamics in aeroservoelastic analysis: Aerodynamic model

NASA Technical Reports Server (NTRS)

Woods, J. A.; Gilbert, Michael G.

1990-01-01

The work presented here is the first part of a continuing effort to expand existing capabilities in aeroelasticity by developing the methodology which is necessary to utilize unsteady time-domain aerodynamics directly in aeroservoelastic design and analysis. The ultimate objective is to define a fully integrated state-space model of an aeroelastic vehicle's aerodynamics, structure and controls which may be used to efficiently determine the vehicle's aeroservoelastic stability. Here, the current status of developing a state-space model for linear or near-linear time-domain indicial aerodynamic forces is presented.

Five Stage Missile Research Rocket, Wallops Island , 1957

NASA Image and Video Library

1957-11-19

**Note also copied and numbered as L90-3749. -- L57-4827 caption: Take off of a five-stage missile research rocket from Wallops Island in 1957. The first two stages propelled the model to about 100,000 feet the last three stages were fired on a descending path to simulate the reentry conditions of ballistic missiles. -- Photograph published in Winds of Change, 75th Anniversary NASA publication (page 72), by James Schultz. -- Photograph also published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen (page 380).

Artefact in forensic medicine: non-missile penetrating injury.

PubMed

Patel, F

1994-12-01

Gunshot wounds are well characterised in forensic textbooks and atypical or unusual ballistic characteristics feature regularly in forensic literature. Forensic practitioners receive continuing education in recognising a variety of gunshot wounds which are created by bullet missiles. Awareness of a non-missile penetrating injury mimicking a gunshot wound is also relevant to forensic medical examiners or others who are likely to attend a scene of death. In this case, which involved self-stabbing with a metal nail, a homicidal firearm death investigation was instigated because of a misinterpretation by crime scene investigators.

A CSMP commutation model for design study of a brushless dc motor power conditioner for a cruise missile fin control actuator

NASA Astrophysics Data System (ADS)

MacMillan, P. N.

1985-06-01

Recent improvements in rare earth magnets have made it possible to construct strong, lightweight, high horsepower dc motors. This has occasioned a reassessment of electromechanical actuators as alternatives to comparable pneumatic and hydraulic systems for use as flight control actuators for tactical missiles. A dynamic equivalent circuit model for the analysis of a small four pole brushless dc motor fed by a transistorized power conditioner utilizing high speed switching power transistors as final elements is presented. The influence of electronic commutation on instantaneous dynamic motor performance is particularly demonstrated and good correlation between computer simulation and typical experimentally obtained performance data is achieved. The model is implemented in CSMP language and features more accurate air gap flux representation over previous work. Hall effect sensor rotor position feedback is simulated. Both constant and variable air gap flux is modeled and the variable flux model treats the flux as a fundamental and one harmonic.

Distributed tactical reasoning framework for intelligent vehicles

NASA Astrophysics Data System (ADS)

Sukthankar, Rahul; Pomerleau, Dean A.; Thorpe, Chuck E.

1998-01-01

In independent vehicle concepts for the Automated Highway System (AHS), the ability to make competent tactical-level decisions in real-time is crucial. Traditional approaches to tactical reasoning typically involve the implementation of large monolithic systems, such as decision trees or finite state machines. However, as the complexity of the environment grows, the unforeseen interactions between components can make modifications to such systems very challenging. For example, changing an overtaking behavior may require several, non-local changes to car-following, lane changing and gap acceptance rules. This paper presents a distributed solution to the problem. PolySAPIENT consists of a collection of autonomous modules, each specializing in a particular aspect of the driving task - classified by traffic entities rather than tactical behavior. Thus, the influence of the vehicle ahead on the available actions is managed by one reasoning object, while the implications of an approaching exit are managed by another. The independent recommendations form these reasoning objects are expressed in the form of votes and vetos over a 'tactical action space', and are resolved by a voting arbiter. This local independence enables PolySAPIENT reasoning objects to be developed independently, using a heterogenous implementation. PolySAPIENT vehicles are implemented in the SHIVA tactical highway simulator, whose vehicles are based on the Carnegie Mellon Navlab robots.

Missile Diaphragmatic Injuries: Kashmir Experience

PubMed Central

Lone, Reyaz A; Akbar, Bhat M; Sharma, ML; Lateef, Wani M; Ahangar, AG; Lone, GN; Dar, A M; Singh, Shyam; Shah, Mubbashir; Hussain, Zahur; Irshad, Ifat; Rasool, Fouzia

2009-01-01

Background: Importance of repairing a diaphragmatic tear due to a missile injury cannot be overemphasized. Even a small diaphragmatic rent should be repaired because of morbidity and mortality caused by subsequent herniation and strangulation. Methods: Fifty-three cases with diaphragmatic injuries caused by penetrating missiles were studied from January 1997 to January 2007. All the patients were primarily explored either for thoracic or abdominal penetrating trauma; the diaphragmatic injury was an associated incidental intraoperative finding. Thoracotomy was performed in 18 patients, Laprotomy in 33 patients and in two patients combined thorocoabdominal approach was utilised for managing associated visceral injuries. Results: Overall mortality was 37.7%. Mortality was dependent on associated injuries of thoracic and abdominal viscera. Most patients died due to associated injuries and septicaemia. None of the patients had any sequelae of diaphragmatic repair. Conclusion: Immediate repair of diaphragmatic injury is of paramount importance to prevent subsequent complications of herniation and strangulation. PMID:21475506

Advocates and critics for tactical behaviors in UGV navigation

NASA Astrophysics Data System (ADS)

Hussain, Talib S.; Vidaver, Gordon; Berliner, Jeffrey

2005-05-01

Critical to the development of unmanned ground vehicle platforms is the incorporation of adaptive tactical behaviors for the planning of high-level navigation and tactical actions. BBN Technologies recently completed a simulation-based project for the Army Research Lab (ARL) in which we applied an evolutionary computation approach to navigating through a terrain to capture flag objectives while faced with one or more mobile enemies. Our Advocates and Critics for Tactical Behaviors (ACTB) system evolves plans for the vehicle that control its movement goals (in the form of waypoints), and its future actions (e.g., pointing cameras). We apply domain-specific, state-dependent genetic operators called advocates that promote specific tactical behaviors (e.g., adapt a plan to stay closer to walls). We define the fitness function as a weighted sum of a number of independent, domain-specific, state-dependent evaluation components called critics. Critics reward plans based upon specific tactical criteria, such as minimizing risk of exposure or time to the flags. Additionally, the ACTB system provides the capability for a human commander to specify the "rules of engagement" under which the vehicle will operate. The rules of engagement determine the planning emphasis required under different tactical situations (e.g., discovery of an enemy), and provide a mechanism for automatically adapting the relative selection probabilities of the advocates, the weights of the critics, and the depth of planning in response to tactical events. The ACTB system demonstrated highly effective performance in a head-to-head testing event, held by ARL, against two competing tactical behavior systems.

The effect of deliberate play on tactical performance in basketball.

PubMed

Greco, Pablo; Memmert, Daniel; Morales, Juan C P

2010-06-01

This field-based study analyzed effects of a deliberate-play training program in basketball on tactical game intelligence and tactical creativity. 22 youth basketball players, ages 10 to 12 years, completed basketball training in one of two equal-sized groups. The deliberate-play training program contained unstructured game forms in basketball. The placebo group played in traditional structured basketball game forms. Tactical intelligence and creativity was assessed before and after an 18-lesson intervention. Analysis showed significant training improvement only for the deliberate-play group. In addition, this outperformance of the placebo group was not only observed for tactical creativity but also for tactical intelligence.

Numerical Aerodynamic Simulation

NASA Technical Reports Server (NTRS)

1989-01-01

An overview of historical and current numerical aerodynamic simulation (NAS) is given. The capabilities and goals of the Numerical Aerodynamic Simulation Facility are outlined. Emphasis is given to numerical flow visualization and its applications to structural analysis of aircraft and spacecraft bodies. The uses of NAS in computational chemistry, engine design, and galactic evolution are mentioned.

Corrugated QWIP for Tactical Army Applications

DTIC Science & Technology

2008-12-01

1 CORRUGATED QWIP FOR TACTICAL ARMY APPLICATIONS David. P. Forrai, Darrel W. Endres L-3 Communications Cincinnati Electronics Mason, OH 45040...Directorate (NVESD) have been developing the corrugated quantum well infrared photodetector (C- QWIP ) technology for applications in tactical LWIR...imaging. The C- QWIP was invented at ARL and shows promise to overcome some of the limitations in commercially available QWIPs . The C- QWIP uses micro

Annual water-resources review, White Sands Missile Range: 1971

USGS Publications Warehouse

Cruz, R.R.

1972-01-01

This report presents water-resource information that was collected at White Sands Missile Range during 1971 and early 1972 by personnel of the U.S. Geological Survey, Water Resources Division. Data on ground-water pumpage and resulting water-level fluctuation, chemical quality, percipitation, and surface-water runoff are summarized in the report. The data were obtained as a result of the continuing water-resources basic-data collection program sponsored by the Facilities Engineering Directorate, White Sands Missile Range.

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.

A novel navigation method used in a ballistic missile

NASA Astrophysics Data System (ADS)

Qian, Hua-ming; Sun, Long; Cai, Jia-nan; Peng, Yu

2013-10-01

The traditional strapdown inertial/celestial integrated navigation method used in a ballistic missile cannot accurately estimate the accelerometer bias. It might cause a divergence of navigation errors. To solve this problem, a new navigation method named strapdown inertial/starlight refractive celestial integrated navigation is proposed. To verify the feasibility of the proposed method, a simulated program of a ballistic missile is presented. The simulation results indicated that, when multiple refraction stars are used, the proposed method can accurately estimate the accelerometer bias, and suppress the divergence of navigation errors completely. Specifically, in order to apply this method to a ballistic missile, a novel measurement equation based on stellar refraction was developed. Furthermore a method to calculate the number of refraction stars observed by the stellar sensor was given. Finally, the relationship between the number of refraction stars used and the navigation accuracy is analysed.

Cognitive representations and cognitive processing of team-specific tactics in soccer.

PubMed

Lex, Heiko; Essig, Kai; Knoblauch, Andreas; Schack, Thomas

2015-01-01

Two core elements for the coordination of different actions in sport are tactical information and knowledge about tactical situations. The current study describes two experiments to learn about the memory structure and the cognitive processing of tactical information. Experiment 1 investigated the storage and structuring of team-specific tactics in humans' long-term memory with regard to different expertise levels. Experiment 2 investigated tactical decision-making skills and the corresponding gaze behavior, in presenting participants the identical match situations in a reaction time task. The results showed that more experienced soccer players, in contrast to less experienced soccer players, possess a functionally organized cognitive representation of team-specific tactics in soccer. Moreover, the more experienced soccer players reacted faster in tactical decisions, because they needed less fixations of similar duration as compared to less experienced soccer players. Combined, these experiments offer evidence that a functionally organized memory structure leads to a reaction time and a perceptual advantage in tactical decision-making in soccer. The discussion emphasizes theoretical and applied implications of the current results of the study.

Cognitive Representations and Cognitive Processing of Team-Specific Tactics in Soccer

PubMed Central

Lex, Heiko; Essig, Kai; Knoblauch, Andreas; Schack, Thomas

2015-01-01

Two core elements for the coordination of different actions in sport are tactical information and knowledge about tactical situations. The current study describes two experiments to learn about the memory structure and the cognitive processing of tactical information. Experiment 1 investigated the storage and structuring of team-specific tactics in humans’ long-term memory with regard to different expertise levels. Experiment 2 investigated tactical decision-making skills and the corresponding gaze behavior, in presenting participants the identical match situations in a reaction time task. The results showed that more experienced soccer players, in contrast to less experienced soccer players, possess a functionally organized cognitive representation of team-specific tactics in soccer. Moreover, the more experienced soccer players reacted faster in tactical decisions, because they needed less fixations of similar duration as compared to less experienced soccer players. Combined, these experiments offer evidence that a functionally organized memory structure leads to a reaction time and a perceptual advantage in tactical decision-making in soccer. The discussion emphasizes theoretical and applied implications of the current results of the study. PMID:25714486

Testing of Tactical Performance in Youth Elite Soccer

PubMed Central

2010-01-01

This is a twofold study with the goals of evaluating tactical oriented game test situations for 12-13-year old highly-talented soccer players and to analyze dynamic, intra-individual developments of the players. A cross-sectional design was carried in study 1, using game test situations to measure specific tactics and creative performance for 195 expert players. The results from five evaluation criteria show that both diagnostic instruments can be used for recording football-specific creativity and game intelligence in talented young players. They produced tactical indicators that can be described as objective and valid, exhibit a sufficient degree of differentiation and are easy to record. Study 2 uses a longitudinal design to present a dynamic performance diagnostic tool for analyzing intra-individual improvements of German Soccer Foundation talents according to football-specific creativity and game intelligence. The results with respect to divergent tactical thinking clearly show that very different change processes were observed in the German Soccer Foundation players. Finally, the practical implications for the training process are discussed on the basis of both studies. Key points With game test situations it is possible to assess tactical performance as game intelligence and creativity objective, valid, with a sufficient degree of differentiation, and economically. The results with respect to game intelligence and creativity show that very different change processes were observed in the German Soccer Foundation players dependend on the bases (trainers). Current literature on tactics for school sports as well as for children’s, youth and high performance soccer at the club level should place much more emphasis on individual and group-tactical requirements in soccer. PMID:24149686

Testing of tactical performance in youth elite soccer.

PubMed

Memmert, Daniel

2010-01-01

This is a twofold study with the goals of evaluating tactical oriented game test situations for 12-13-year old highly-talented soccer players and to analyze dynamic, intra-individual developments of the players. A cross-sectional design was carried in study 1, using game test situations to measure specific tactics and creative performance for 195 expert players. The results from five evaluation criteria show that both diagnostic instruments can be used for recording football-specific creativity and game intelligence in talented young players. They produced tactical indicators that can be described as objective and valid, exhibit a sufficient degree of differentiation and are easy to record. Study 2 uses a longitudinal design to present a dynamic performance diagnostic tool for analyzing intra-individual improvements of German Soccer Foundation talents according to football-specific creativity and game intelligence. The results with respect to divergent tactical thinking clearly show that very different change processes were observed in the German Soccer Foundation players. Finally, the practical implications for the training process are discussed on the basis of both studies. Key pointsWith game test situations it is possible to assess tactical performance as game intelligence and creativity objective, valid, with a sufficient degree of differentiation, and economically.The results with respect to game intelligence and creativity show that very different change processes were observed in the German Soccer Foundation players dependend on the bases (trainers).Current literature on tactics for school sports as well as for children's, youth and high performance soccer at the club level should place much more emphasis on individual and group-tactical requirements in soccer.

Aerodynamic mathematical modeling - basic concepts

NASA Technical Reports Server (NTRS)

Tobak, M.; Schiff, L. B.

1981-01-01

The mathematical modeling of the aerodynamic response of an aircraft to arbitrary maneuvers is reviewed. Bryan's original formulation, linear aerodynamic indicial functions, and superposition are considered. These concepts are extended into the nonlinear regime. The nonlinear generalization yields a form for the aerodynamic response that can be built up from the responses to a limited number of well defined characteristic motions, reproducible in principle either in wind tunnel experiments or flow field computations. A further generalization leads to a form accommodating the discontinuous and double valued behavior characteristics of hysteresis in the steady state aerodynamic response.

A Method for Evaluation of Microcomputers for Tactical Applications.

DTIC Science & Technology

1980-06-01

application. The computational requirements of a tactical application are specified in terms of performance parameters. The presently marketed microcomputer...computational requirements of a tactical application are specified in terms of performance parameters. The presently marketed microcomputer and multi...also to provide a method to evaluate microcomputer systems for tactical applications, i.e., Command Control Communications (C 3), weapon systems, etc

The Effect of Aerodynamic Heating on Air Penetration by Shaped Charge Jets and Their Particles

NASA Astrophysics Data System (ADS)

Backofen, Joseph

2009-06-01

The goal of this paper is to present recent work modeling thermal coupling between shaped charge jets and their particles with air while it is being penetrated to form a crater that subsequently collapses back onto the jet. This work complements research published at International Symposia on Ballistics: 1) 1987 - Shaped Charge Jet Aerodynamics, Particulation and Blast Field Modeling; and 2) 2007 - Air Cratering by Eroding Shaped Charge Jets. The current work shows how and when a shaped charge jet's tip and jet particles are softened enough that they can erode in a hydrodynamic manner as modeled in these papers. This paper and its presentation includes models for heat transfer from shocked air as a function of jet velocity as well as heat flow within the jet or particle. The work is supported by an extensive bibliographic search including publications on meteors and ballistic missile re-entry vehicles. The modeling shows that a jet loses its strength to the depth required to justify hydrodynamic erosion when its velocity is above a specific velocity related to the shock properties of air and the jet material's properties. As a result, the portion of a jet's kinetic energy converted at the aerodynamic shock into heating transferred back onto the jet affects the energy deposited into the air through drag and ablation which in turn affect air crater expansion and subsequent collapse back onto the jet and its particles as shown in high-speed photography.

Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2

NASA Technical Reports Server (NTRS)

Spahr, J. R.

1954-01-01

The lift, pitching-moment, and drag characteristics of a missile configuration having a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 were measured at a Mach number of 1.99 and a Reynolds number of 6.0 million, based on the body length. The tests were performed through an angle-of-attack range of -5 deg to 28 deg to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components (body, wing, and tail). Theoretical lift and moment characteristics of the configuration and its components were calculated by the use of existing theoretical methods which have been modified for application to high angles of attack, and these characteristics are compared with experiment. The lift and drag characteristics of all combinations of the body, wing, and tail were independent of roll angle throughout the angle-of-attack range. The pitching-moment characteristics of the body-wing and body-wing-tail combinations, however, were influenced significantly by the roll angle at large angles of attack (greater than 10 deg). A roll from 0 deg (one pair of wing panels horizontal) to 45 deg caused a forward shift in the center of pressure which was of the same magnitude for both of these combinations, indicating that this shift originated from body-wing interference effects. A favorable lift-interference effect (lift of the combination greater than the sum of the lifts of the components) and a rearward shift in the center of pressure from a position corresponding to that for the components occurred at small angles of attack when the body was combined with either the exposed wing or tail surfaces. These lift and center-of-pressure interference effects were gradually reduced to zero as the angle of attack was increased to large values. The effect of wing-tail interference, which influenced primarily the pitching-moment characteristics, is dependent on the distance

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.

Volpe Participation In Cooperative Threat Reduction: Nuclear Missiles In The Former USSR

DOT National Transportation Integrated Search

2000-08-01

This article discusses the supporting efforts of the Volpe Center to reduce the missile arsenal of the former USSR in accordance with international treaties. The safe transportation of the missiles by rail is a key component of the cooperative effort...

Tactical Synthesis Of Efficient Global Search Algorithms

NASA Technical Reports Server (NTRS)

Nedunuri, Srinivas; Smith, Douglas R.; Cook, William R.

2009-01-01

Algorithm synthesis transforms a formal specification into an efficient algorithm to solve a problem. Algorithm synthesis in Specware combines the formal specification of a problem with a high-level algorithm strategy. To derive an efficient algorithm, a developer must define operators that refine the algorithm by combining the generic operators in the algorithm with the details of the problem specification. This derivation requires skill and a deep understanding of the problem and the algorithmic strategy. In this paper we introduce two tactics to ease this process. The tactics serve a similar purpose to tactics used for determining indefinite integrals in calculus, that is suggesting possible ways to attack the problem.

Range Reference Atmosphere 0-70 Km Altitude. Kwajalein Missile Range, Kwajalein, Marshall Islands

DTIC Science & Technology

1982-01-01

DOCUMENT 360-82 KWAJALEIN MISSILE RANGE KWAJALEIN, MARSHALL ISLANDS RANGE REFERENCE ATMOSPHERE 0-70 KM ALTITUDE, C00 L’’I METEOROLOGY GROUP .RANGE...34Reference Atmosphere (Part 1), Kwajale 4n Missile Range, Kwajalein, Marshall Islands ," ADA002664. * 19. KEY WORDS (Continue on revorsae d. If necoeewy...CLASSIFICATION OF TIlS PAGE (Whe~n Data EnterecD -v DOCUMENT 360-82 Vo- KWAJALEIN MISSILE RANGE KWAJALEIN, MARSHALL ISLANDS RANGE REFERENCE ATMOSPHERE 0-70 km

Photogrammetric point cloud compression for tactical networks

NASA Astrophysics Data System (ADS)

Madison, Andrew C.; Massaro, Richard D.; Wayant, Clayton D.; Anderson, John E.; Smith, Clint B.

2017-05-01

We report progress toward the development of a compression schema suitable for use in the Army's Common Operating Environment (COE) tactical network. The COE facilitates the dissemination of information across all Warfighter echelons through the establishment of data standards and networking methods that coordinate the readout and control of a multitude of sensors in a common operating environment. When integrated with a robust geospatial mapping functionality, the COE enables force tracking, remote surveillance, and heightened situational awareness to Soldiers at the tactical level. Our work establishes a point cloud compression algorithm through image-based deconstruction and photogrammetric reconstruction of three-dimensional (3D) data that is suitable for dissimination within the COE. An open source visualization toolkit was used to deconstruct 3D point cloud models based on ground mobile light detection and ranging (LiDAR) into a series of images and associated metadata that can be easily transmitted on a tactical network. Stereo photogrammetric reconstruction is then conducted on the received image stream to reveal the transmitted 3D model. The reported method boasts nominal compression ratios typically on the order of 250 while retaining tactical information and accurate georegistration. Our work advances the scope of persistent intelligence, surveillance, and reconnaissance through the development of 3D visualization and data compression techniques relevant to the tactical operations environment.

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

...-Basis Hurricane and Hurricane Missiles AGENCY: Nuclear Regulatory Commission. ACTION: Proposed interim...-ISG-024, ``Implementation of Regulatory Guide 1.221 on Design-Basis Hurricane and Hurricane Missiles....221, ``Design-Basis Hurricane and Hurricane Missiles for Nuclear Power Plants.'' DATES: Submit...

Personal Area Networks in Tactical Mobile Devices

DTIC Science & Technology

2014-08-01

TECHNICAL DOCUMENT 2047 August 2014 Personal Area Networks in Tactical Mobile Devices Brian Visser...Tactical Mobile Devices Brian Visser Approved for public release. SSC Pacific San Diego, CA 92152-5001 SB...consistent power source, which is normally not available to patrols. In addition to the lack of computer resources, robust network infrastructure

Cruise Missile Penaid Nonproliferation: Hindering the Spread of Countermeasures Against Cruise Missile Defenses

DTIC Science & Technology

2014-01-01

this report treats cruise missile penaids and UAV penaids, sometimes called “self-protection” (see La Franchi , 2004), interchangeably. 8 Cruise...Penaid Export Controls 41 2. Anti-Jam Equipment MTCR Item 11.A.3.b.3 (Avionics): Current text: “Receiving equipment for Global Navigation Satellite...subsystems beyond those for global navigation satellite systems to all sensor, navigation, and communications systems, and add “including multi-mode

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.…

Affective Decision-Making and Tactical Behavior of Under-15 Soccer Players

PubMed Central

Gonzaga, Adeilton dos Santos; Albuquerque, Maicon Rodrigues; Malloy-Diniz, Leandro Fernandes; Greco, Pablo Juan; Teoldo da Costa, Israel

2014-01-01

Affective decision-making is a type of Executive Function related to cost benefit analysis in situations where gains and losses imply direct consequences for the subject. The purpose of this study was to explore the influence of the affective decision-making on tactical behavior in soccer players under the age of 15 years old. The System of Tactical Assessment in Soccer (FUT-SAT) was used to assess tactical behavior. To evaluate affective decision-making, we used the neuropsychological test called The Iowa Gambling Task (IGT). The values of the offensive, defensive and game tactical behavior of participants were used to create performance groups. The low (≤25%) and high (≥75%) groups, according to offensive, defensive and game tactical behavior, were compared and shown to be different. The values of the IGT net score of the participants with low and high tactical behavior were compared using the non-parametric Mann-Whitney test. Statistically significant differences between the groups were observed for Defensive Tactical Behavior (Z = −3.133; p = 0.002; r = −0.355) and Game Tactical Behavior (Z = −2.267; p = 0.023; r = −0.260). According to these results, it is possible to state that affective decision-making can influence the tactical behavior of under-15 soccer players. PMID:24978030

Guide for Transitioning Army Missile Systems From Development to Production.

DTIC Science & Technology

1981-07-01

cost reduction ideas. 3 e! M. atumtion0 !eM . One missile system currently In fall *"I* develoluft, MM9 bee foregone the traditional engineering... costs , delivery schedules and deployment dates. Because of these difficulties and a desire to improve the weapon systems acquisition process, the...tered during the transition of new missile systems into production include: 1. High production unit costs - Occasionally the number of systems to be

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

An operational computer program to control Self Defense Surface Missile System operations

DOE Office of Scientific and Technical Information (OSTI.GOV)

Roe, C.L.

1991-12-01

An account is given of the system architecture and operational protocols of the NATO Seasparrow Surface Missile System (NSSMS) Operational Computer Program (OCP) which has been developed, and is being deployed multinationally, to respond against antiship missiles. Flowcharts are presented for the target detection and tracking, control, and engagement phases of the Self Defense Surface Missile System that is controlled by the OCP. USN and other NATO vessels will carry the NSSMS well into the next century; the OCP presently described will be deployed in the course of 1992 to enhance the self-defense capabilities of the NSSMS-equipped fleet. 8 refs.

Penaid Nonproliferation: Hindering the Spread of Countermeasures Against Ballistic Missile Defenses

DTIC Science & Technology

2014-01-01

50 Penaid Nonproliferation: Hindering the Spread of Countermeasures Against Ballistic Missile Defenses 42 /2010! Plume Signature Control...and Richard Speier, “Penaid Nonproliferation: Analysis and Recommendations,” briefing, Veridian Corp., Arlington, Va., June 29, 2000. “ Missile ...is a nonprofit institution that helps improve policy and decisionmaking through research and analysis . This electronic document was made available

Fusion interfaces for tactical environments: An application of virtual reality technology

NASA Technical Reports Server (NTRS)

Haas, Michael W.

1994-01-01

The term Fusion Interface is defined as a class of interface which integrally incorporates both virtual and nonvirtual concepts and devices across the visual, auditory, and haptic sensory modalities. A fusion interface is a multisensory virtually-augmented synthetic environment. A new facility has been developed within the Human Engineering Division of the Armstrong Laboratory dedicated to exploratory development of fusion interface concepts. This new facility, the Fusion Interfaces for Tactical Environments (FITE) Facility is a specialized flight simulator enabling efficient concept development through rapid prototyping and direct experience of new fusion concepts. The FITE Facility also supports evaluation of fusion concepts by operation fighter pilots in an air combat environment. The facility is utilized by a multidisciplinary design team composed of human factors engineers, electronics engineers, computer scientists, experimental psychologists, and oeprational pilots. The FITE computational architecture is composed of twenty-five 80486-based microcomputers operating in real-time. The microcomputers generate out-the-window visuals, in-cockpit and head-mounted visuals, localized auditory presentations, haptic displays on the stick and rudder pedals, as well as executing weapons models, aerodynamic models, and threat models.

Missile defense and strategic stability: Terminal High Altitude Area Defense (THAAD) in South Korea

DOE PAGES

Sankaran, Jaganath; Fearey, Bryan L.

2017-02-06

South Korea is threatened by its troubled relationship with North Korea. North Korea possesses a large cache of missiles as well as chemical and biological weapons, and the future potential to mount nuclear weapons on its missiles. The United States is also challenged because of its defense commitments to Seoul. As a countermeasure, the United States and South Korea decided to deploy Terminal High Altitude Area Defense (THAAD) missile defenses in South Korea. However, China has objected. Chinese scholars believe the THAAD radar would be able to track Chinese inter-continental ballistic missiles, thereby weakening their deterrent. A technical analysis doesmore » not support this assertion. But, it is vital for South Korea, given its proximity and economic interdependence, to reassure China. The United States Forces Korea will deploy THAD and that is not a commitment by Seoul to become part of U.S.-led missile defenses in the Asia-Pacific.« less

Missile defense and strategic stability: Terminal High Altitude Area Defense (THAAD) in South Korea

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sankaran, Jaganath; Fearey, Bryan L.

South Korea is threatened by its troubled relationship with North Korea. North Korea possesses a large cache of missiles as well as chemical and biological weapons, and the future potential to mount nuclear weapons on its missiles. The United States is also challenged because of its defense commitments to Seoul. As a countermeasure, the United States and South Korea decided to deploy Terminal High Altitude Area Defense (THAAD) missile defenses in South Korea. However, China has objected. Chinese scholars believe the THAAD radar would be able to track Chinese inter-continental ballistic missiles, thereby weakening their deterrent. A technical analysis doesmore » not support this assertion. But, it is vital for South Korea, given its proximity and economic interdependence, to reassure China. The United States Forces Korea will deploy THAD and that is not a commitment by Seoul to become part of U.S.-led missile defenses in the Asia-Pacific.« less

21. Photographic copy of original design drawing, dated January 1970, ...

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

21. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Roof plan - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

The space shuttle launch vehicle aerodynamic verification challenges

NASA Technical Reports Server (NTRS)

Wallace, R. O.; Austin, L. D.; Hondros, J. G.; Surber, T. E.; Gaines, L. M.; Hamilton, J. T.

1985-01-01

The Space Shuttle aerodynamics and performance communities were challenged to verify the Space Shuttle vehicle (SSV) aerodynamics and system performance by flight measurements. Historically, launch vehicle flight test programs which faced these same challenges were unmanned instrumented flights of simple aerodynamically shaped vehicles. However, the manned SSV flight test program made these challenges more complex because of the unique aerodynamic configuration powered by the first man-rated solid rocket boosters (SRB). The analyses of flight data did not verify the aerodynamics or performance preflight predictions of the first flight of the Space Transportation System (STS-1). However, these analyses have defined the SSV aerodynamics and verified system performance. The aerodynamics community also was challenged to understand the discrepancy between the wind tunnel and flight defined aerodynamics. The preflight analysis challenges, the aerodynamic extraction challenges, and the postflight analyses challenges which led to the SSV system performance verification and which will lead to the verification of the operational ascent aerodynamics data base are presented.

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

Code of Federal Regulations, 2012 CFR

2012-10-01

... 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 Launch...

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 Launch...

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

Code of Federal Regulations, 2010 CFR

2010-10-01

... 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 Launch...

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

Code of Federal Regulations, 2011 CFR

2011-10-01

... 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 Launch...

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

Code of Federal Regulations, 2013 CFR

2013-10-01

... 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 Launch...

Aerodynamic design on high-speed trains

NASA Astrophysics Data System (ADS)

Ding, San-San; Li, Qiang; Tian, Ai-Qin; Du, Jian; Liu, Jia-Li

2016-04-01

Compared with the traditional train, the operational speed of the high-speed train has largely improved, and the dynamic environment of the train has changed from one of mechanical domination to one of aerodynamic domination. The aerodynamic problem has become the key technological challenge of high-speed trains and significantly affects the economy, environment, safety, and comfort. In this paper, the relationships among the aerodynamic design principle, aerodynamic performance indexes, and design variables are first studied, and the research methods of train aerodynamics are proposed, including numerical simulation, a reduced-scale test, and a full-scale test. Technological schemes of train aerodynamics involve the optimization design of the streamlined head and the smooth design of the body surface. Optimization design of the streamlined head includes conception design, project design, numerical simulation, and a reduced-scale test. Smooth design of the body surface is mainly used for the key parts, such as electric-current collecting system, wheel truck compartment, and windshield. The aerodynamic design method established in this paper has been successfully applied to various high-speed trains (CRH380A, CRH380AM, CRH6, CRH2G, and the Standard electric multiple unit (EMU)) that have met expected design objectives. The research results can provide an effective guideline for the aerodynamic design of high-speed trains.

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.

Aerodynamic Noise Generated by Shinkansen Cars

NASA Astrophysics Data System (ADS)

KITAGAWA, T.; NAGAKURA, K.

2000-03-01

The noise value (A -weighted sound pressure level, SLOW) generated by Shinkansen trains, now running at 220-300 km/h, should be less than 75 dB(A) at the trackside. Shinkansen noise, such as rolling noise, concrete support structure noise, and aerodynamic noise are generated by various parts of Shinkansen trains. Among these aerodynamic noise is important because it is the major contribution to the noise generated by the coaches running at high speed. In order to reduce the aerodynamic noise, a number of improvements to coaches have been made. As a result, the aerodynamic noise has been reduced, but it still remains significant. In addition, some aerodynamic noise generated from the lower parts of cars remains. In order to investigate the contributions of these noises, a method of analyzing Shinkansen noise has been developed and applied to the measured data of Shinkansen noise at speeds between 120 and 315 km/h. As a result, the following conclusions have been drawn: (1) Aerodynamic noise generated from the upper parts of cars was reduced considerably by smoothing car surfaces. (2) Aerodynamic noise generated from the lower parts of cars has a major influence upon the wayside noise.

Ionospheric disturbances induced by a missile launched from North Korea on 12 December 2012

NASA Astrophysics Data System (ADS)

Kakinami, Yoshihiro; Yamamoto, Masayuki; Chen, Chia-Hung; Watanabe, Shigeto; Lin, Charles; Liu, Jenn-Yanq; Habu, Hiroto

2013-08-01

disturbances caused by a missile launched from North Korea on 12 December 2012 were investigated by using the GPS total electron content (TEC). The spatial characteristic of the front edge of V-shaped disturbances produced by missiles and rockets was first determined. Considering the launch direction and the height of estimated ionospheric points at which GPS radio signal pierces the ionosphere, the missile passed through the ionosphere at heights of 391, 425, and 435 km at 0056:30, 0057:00, and 0057:30 UT, respectively. The observed velocities of the missile were 2.8 and 3.2 km/s at that time, which was estimated from the traveling speed of the front edge of V-shaped disturbances. Westward and eastward V-shaped disturbances propagated at 1.8-2.6 km/s. The phase velocities of the westward and eastward V-shaped disturbances were much faster than the speed of acoustic waves reported in previous studies, suggesting that sources other than acoustic waves may have played an important role. Furthermore, the plasma density depletion that is often observed following missile and rocket launches was not found. This suggests that the depletion resulting from the missile's exhaust was not strong enough to be observed in the TEC distribution in the topside ionosphere.

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

..., 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. (a... individual basis, by prior arrangement with the Commanding Officer, Pacific Missile Range Facility, Hawaiian...

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

..., 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. (a... individual basis, by prior arrangement with the Commanding Officer, Pacific Missile Range Facility, Hawaiian...

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

Code of Federal Regulations, 2013 CFR

2013-07-01

..., 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. (a... individual basis, by prior arrangement with the Commanding Officer, Pacific Missile Range Facility, Hawaiian...

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

..., 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. (a... individual basis, by prior arrangement with the Commanding Officer, Pacific Missile Range Facility, Hawaiian...

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.

AirLand Battle and Tactical Command and Control Automation,

DTIC Science & Technology

1987-01-07

Army Tactical Command and Control System (ATCCS) are the primary subjects of the last period. The precepts of AirLand Battle doctrine are examined to...AirLand Battle and the Army Tactical Command and Control System (ATCCS) are thE primary subjects of the last period. The precepts of AirLand Battle...centralized control is identified. AirLand Battle and the Army Tactical Command and Control System (ATCCS) are the primary subjects of the last

Precession feature extraction of ballistic missile warhead with high velocity

NASA Astrophysics Data System (ADS)

Sun, Huixia

2018-04-01

This paper establishes the precession model of ballistic missile warhead, and derives the formulas of micro-Doppler frequency induced by the target with precession. In order to obtain micro-Doppler feature of ballistic missile warhead with precession, micro-Doppler bandwidth estimation algorithm, which avoids velocity compensation, is presented based on high-resolution time-frequency transform. The results of computer simulations confirm the effectiveness of the proposed method even with low signal-to-noise ratio.

Information Management Principles Applied to the Ballistic Missile Defense System

DTIC Science & Technology

2007-03-01

of a BMDS. From this, the Army produced the Nike -Zeus system comprised of four radars, the Zeus missile, and a computer fire control system (General...made the Nike -Zeus our first National Missile Defense (NMD) system named Sentinel. The architecture was to cover 14 locations, 10 of which were...1999). Additionally, there are cultural impacts (Gordon & Gordon, 1999). A company choosing an Apple OS may have to wage a big fight against the

46th Annual Gun and Missile Systems Conference and Exhibition

DTIC Science & Technology

2011-09-01

Grade Sensors Through Use of Accelerated Aging Principles Mr. Scott Gift 11657 Modeling of the Autofrettage Processes of a Gun Barrel Mr. Sudhir...Emissions Measured on the Outer Portion of a Composite Barrel Ms. Rushie Ghimire GUN & MISSILE SYSTEMS ADDITIONAL AUTHORS GUN & MISSILE SYSTEMS...X 3BCT 2BCT X 1BCT TACP COLT • BLUFOR scout squad engaged by enemy infantry and are overwhelmed by heavy machine gun fire 100m to their northwest

Mind-Sets and Missiles: A First Hand Account of the Cuban Missile Crisis

DTIC Science & Technology

2009-09-01

was still in session, Deputy Secretary of Defense Roswell Gilpatric gave a speech to the Business Council at White Sulfur Springs, West Virginia...Bundy and Roswell Gilpatric in Paris to warn them that he believed the Soviets would place offensive missiles in Cuba. In a series of cables between...repeat missions of recent reconnaissance operations which [Deputy Secretary of Defense Roswell ] Gilpatric advises informative. Also I support use of R

Using the HARV simulation aerodynamic model to determine forebody strake aerodynamic coefficients from flight data

NASA Technical Reports Server (NTRS)

Messina, Michael D.

1995-01-01

The method described in this report is intended to present an overview of a process developed to extract the forebody aerodynamic increments from flight tests. The process to determine the aerodynamic increments (rolling pitching, and yawing moments, Cl, Cm, Cn, respectively) for the forebody strake controllers added to the F/A - 18 High Alpha Research Vehicle (HARV) aircraft was developed to validate the forebody strake aerodynamic model used in simulation.

Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration with a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers from 1.2 to 2.1

NASA Technical Reports Server (NTRS)

Brown, Clarence A , Jr

1957-01-01

A full- scale rocket-powered model of a cruciform canard missile configuration with a low- aspect - ratio wing and blunt nose has been flight tested by the Langley Pilotless Aircraft Research Division. Static and dynamic longitudinal stability and control derivatives of this interdigitated canard-wing missile configuration were determined by using the pulsed- control technique at low angles of attack and for a Mach number range of 1.2 to 2.1. The lift - curve slope showed only small nonlinearities with changes in control deflection or angle of attack but indicated a difference in lift- .curve slope of approximately 7 percent for the two control deflections of delta = 3.0 deg and delta= -0.3 deg . The large tail length of the missile tested was effective in producing damping in pitch throughout the Mach number range tested. The aerodynamic- center location was nearly constant with Mach number for the two control deflections but was shown to be less stable with the larger control deflection. The increment of lift produced by the controls was small and positive throughout the Mach number range tested, whereas the pitching moment produced by the controls exhibited a normal trend of reduced effectiveness with increasing Mach number.The effectiveness of the controls in producing angle of attack, lift, and pitching moment was good at all Mach numbers tested.

Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration with a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers from 1.2 to 2.1

NASA Technical Reports Server (NTRS)

Brown, C. A., Jr.

1957-01-01

A full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose has been flight tested by the Langley Pilotless Aircraft Research Division. Static and dynamic longitudinal stability and control derivatives of this interdigitated canard-wing missile configuration were determined by using the pulsed-control technique at low angles of attack and for a Mach number range of 1.2 to 2.1. The lift-curve slope showed only small nonlinearities with changes in control deflection or angle of attack but indicated a difference in lift-curve slope of approximately 7 percent for the two control deflections of delta = 3.0 deg and delta = -0.3 deg. The large tail length of the missile tested was effective in producing damping in pitch throughout the Mach number range tested. The aerodynamic-center location was nearly constant with Mach number for the two control deflections but was shown to be less stable with the larger control deflection. The increment of lift produced by the controls was small and positive throughout the Mach number range tested, whereas the pitching moment produced by the controls exhibited a normal trend of reduced effectiveness with increasing Mach number. The effectiveness of the controls in producing angle of attack, lift, and pitching moment was good at all Mach numbers tested.

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.

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

... DEPARTMENT OF DEFENSE Office of the Secretary Availability of the Fiscal Year 2009 Missile Defense... Act AGENCY: Missile Defense Agency (MDA), DoD. ACTION: Notice of availability. SUMMARY: In accordance... for Fiscal Year 2008 (NDAA 08) Section 807, the Director of the Missile Defense Agency and the Office...

19. Photographic copy of original design drawing, dated January 1970, ...

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

19. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Elevation and section "A" - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

25. Photographic copy of original design drawing, dated January 1970, ...

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

25. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Composite second floor plan - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

24. Photographic copy of original design drawing, dated January 1970, ...

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

24. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Composite mezzanine floor plan - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

22. Photographic copy of original design drawing, dated January 1970, ...

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

22. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Partial underfloor plan of first floor - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

29. Photographic copy of original design drawing, dated January 1970, ...

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

29. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Interior elevations, fourth floor - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

27. Photographic copy of original design drawing, dated January 1970, ...

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

27. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Interior elevations, third floor - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

23. Photographic copy of original design drawing, dated January 1970, ...

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

23. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Composite first floor plan - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

26. Photographic copy of original design drawing, dated January 1970, ...

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

26. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Composite removable third floor and duplexer area - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

20. Photographic copy of original design drawing, dated January 1970, ...

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

20. Photographic copy of original design drawing, dated January 1970, revised 2 January 1974 (original Army Operation Drawing in possession of the U.S. Army Corps of Engineers, Huntsville Division) Sections "B" and "C" - Stanley R. Mickelsen Safeguard Complex, Missile Site Control Building, Northeast of Tactical Road; southeast of Tactical Road South, Nekoma, Cavalier County, ND

Dictionary of Missile and Artillery Terms

DTIC Science & Technology

1982-05-20

arrangement and layout of missile nodes. KOMPRESSORNYY VOZDUShNO-REAKTIVNYY DVICATEL’ LAir -Breathing Compressor Rocket Engine] - variety of air-breathing...law. It will depend on dispersion of trajectories and nonconformity of fuse action due to nonuniform combustion of the time composition. Burst probable

An Investigation of Bank-to-Turn Missiles.

DTIC Science & Technology

1986-06-01

Aerodynamic Model and Analysis The aerodynamic transfer functions of the uncoupled yaw channel autopilot are according to Karadimas , C. thesis [Ref. 41: a...Thesis, Naval Postgraduate School, Monterey California, December 1985 3. Ogata, K., Modern Control Engineering, Prentice-Hall Inc., 1970. 4. Karadimas

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.

Aerodynamic Shutoff Valve

NASA Technical Reports Server (NTRS)

Horstman, Raymond H.

1992-01-01

Aerodynamic flow achieved by adding fixed fairings to butterfly valve. When valve fully open, fairings align with butterfly and reduce wake. Butterfly free to turn, so valve can be closed, while fairings remain fixed. Design reduces turbulence in flow of air in internal suction system. Valve aids in development of improved porous-surface boundary-layer control system to reduce aerodynamic drag. Applications primarily aerospace. System adapted to boundary-layer control on high-speed land vehicles.

Signature analysis of ballistic missile warhead with micro-nutation in terahertz band

NASA Astrophysics Data System (ADS)

Li, Ming; Jiang, Yue-song

2013-08-01

In recent years, the micro-Doppler effect has been proposed as a new technique for signature analysis and extraction of radar targets. The ballistic missile is known as a typical radar target and has been paid many attentions for the complexities of its motions in current researches. The trajectory of a ballistic missile can be generally divided into three stages: boost phase, midcourse phase and terminal phase. The midcourse phase is the most important phase for radar target recognition and interception. In this stage, the warhead forms a typical micro-motion called micro-nutation which consists of three basic micro-motions: spinning, coning and wiggle. This paper addresses the issue of signature analysis of ballistic missile warhead in terahertz band via discussing the micro-Doppler effect. We establish a simplified model (cone-shaped) for the missile warhead followed by the micro-motion models including of spinning, coning and wiggle. Based on the basic formulas of these typical micro-motions, we first derive the theoretical formula of micro-nutation which is the main micro-motion of the missile warhead. Then, we calculate the micro-Doppler frequency in both X band and terahertz band via these micro-Doppler formulas. The simulations are given to show the superiority of our proposed method for the recognition and detection of radar micro targets in terahertz band.

Effect of static shape deformation on aerodynamics and aerothermodynamics of hypersonic inflatable aerodynamic decelerator

NASA Astrophysics Data System (ADS)

Guo, Jinghui; Lin, Guiping; Bu, Xueqin; Fu, Shiming; Chao, Yanmeng

2017-07-01

The inflatable aerodynamic decelerator (IAD), which allows heavier and larger payloads and offers flexibility in landing site selection at higher altitudes, possesses potential superiority in next generation space transport system. However, due to the flexibilities of material and structure assembly, IAD inevitably experiences surface deformation during atmospheric entry, which in turn alters the flowfield around the vehicle and leads to the variations of aerodynamics and aerothermodynamics. In the current study, the effect of the static shape deformation on the hypersonic aerodynamics and aerothermodynamics of a stacked tori Hypersonic Inflatable Aerodynamic Decelerator (HIAD) is demonstrated and analyzed in detail by solving compressible Navier-Stokes equations with Menter's shear stress transport (SST) turbulence model. The deformed shape is obtained by structural modeling in the presence of maximum aerodynamic pressure during entry. The numerical results show that the undulating shape deformation makes significant difference to flow structure. In particular, the more curved outboard forebody surface results in local flow separations and reattachments in valleys, which consequently yields remarkable fluctuations of surface conditions with pressure rising in valleys yet dropping on crests while shear stress and heat flux falling in valleys yet rising on crests. Accordingly, compared with the initial (undeformed) shape, the corresponding differences of surface conditions get more striking outboard, with maximum augmentations of 379 pa, 2224 pa, and 19.0 W/cm2, i.e., 9.8%, 305.9%, and 101.6% for the pressure, shear stress and heat flux respectively. Moreover, it is found that, with the increase of angle of attack, the aerodynamic characters and surface heating vary and the aeroheating disparities are evident between the deformed and initial shape. For the deformable HIAD model investigated in this study, the more intense surface conditions and changed flight

Space System Applications to Tactical Operations.

DTIC Science & Technology

1984-10-01

AD-AI51 884 SPACE SYSTEM APPLICATIONS TO TACTICAL OPERATIONSIU) I, ADVISORY GROU)P FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILIT-SUR-SEINE (FRANCE...FOR1’ AIIII [ I [IiP[E REEAC [ [llllvd[ N I AGARD CONFERENCE PROCEEDINGS No.344 Space System Applications to Tactical Operations DTIC ELECTE...nota %ii. .tm’ ih1.1i .Il t oning oiii.ian later oil Ili thre centturv are charaeteri/ed. Bloth the ad’.antage’. and limitation%. iii space ’.’.’tem

Configuration Aerodynamics: Past - Present - Future

NASA Technical Reports Server (NTRS)

Wood, Richard M.; Agrawal, Shreekant; Bencze, Daniel P.; Kulfan, Robert M.; Wilson, Douglas L.

1999-01-01

The Configuration Aerodynamics (CA) element of the High Speed Research (HSR) program is managed by a joint NASA and Industry team, referred to as the Technology Integration Development (ITD) team. This team is responsible for the development of a broad range of technologies for improved aerodynamic performance and stability and control characteristics at subsonic to supersonic flight conditions. These objectives are pursued through the aggressive use of advanced experimental test techniques and state of the art computational methods. As the HSR program matures and transitions into the next phase the objectives of the Configuration Aerodynamics ITD are being refined to address the drag reduction needs and stability and control requirements of High Speed Civil Transport (HSCT) aircraft. In addition, the experimental and computational tools are being refined and improved to meet these challenges. The presentation will review the work performed within the Configuration Aerodynamics element in 1994 and 1995 and then discuss the plans for the 1996-1998 time period. The final portion of the presentation will review several observations of the HSR program and the design activity within Configuration Aerodynamics.

Missileer: The Dawn, Decline, and Reinvigoration of America’s Intercontinental Ballistic Missile Operators

DTIC Science & Technology

2017-06-01

Group, resulting in all missiles entering ‘ radio mode’ and making them air-launch accessible.1 This loss of communications was an anomaly caused by an...MEECN) Program (MMP) Part of MEECN program that replaced legacy Survivable Low Frequency Communications System (SLFCS) with integrated extremely high...very low/low frequency (EHF/VLF/LF) communications capability. Began in 2003 and finished in 2005. Security Modernization (Three phases: Fast

An Assessment of Small Submarines and Encapsulation of Ballistic Missiles--Phase 2 Survey

DTIC Science & Technology

1980-11-01

capsules will tend to offset the reduced investment costs of the submarine. It would be necessary to deter- mine total sytem costs (including RDT&E...missile basing concepts and missile performance characteristics required to counter potential Soviet strategic offensive forces and ABM proliferation

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)

Tactical Nuclear Weapons: Their Purpose and Placement

DTIC Science & Technology

2015-06-01

War II, nuclear scientists argued against the development of fusion weapons .3 In the 1970s, politicians debated the use of neutron bombs, weapons ...Tactical Nuclear Weapons : Their Purpose and Placement BY EDWARD G. FERGUSON A THESIS SUBMITTED TO THE FACULTY OF THE...This study answers the question -- Why does America have tactical nuclear weapons (TNWs) in Europe today? – treating America and the North

Online Pedagogical Tutorial Tactics Optimization Using Genetic-Based Reinforcement Learning.

PubMed

Lin, Hsuan-Ta; Lee, Po-Ming; Hsiao, Tzu-Chien

2015-01-01

Tutorial tactics are policies for an Intelligent Tutoring System (ITS) to decide the next action when there are multiple actions available. Recent research has demonstrated that when the learning contents were controlled so as to be the same, different tutorial tactics would make difference in students' learning gains. However, the Reinforcement Learning (RL) techniques that were used in previous studies to induce tutorial tactics are insufficient when encountering large problems and hence were used in offline manners. Therefore, we introduced a Genetic-Based Reinforcement Learning (GBML) approach to induce tutorial tactics in an online-learning manner without basing on any preexisting dataset. The introduced method can learn a set of rules from the environment in a manner similar to RL. It includes a genetic-based optimizer for rule discovery task by generating new rules from the old ones. This increases the scalability of a RL learner for larger problems. The results support our hypothesis about the capability of the GBML method to induce tutorial tactics. This suggests that the GBML method should be favorable in developing real-world ITS applications in the domain of tutorial tactics induction.

Online Pedagogical Tutorial Tactics Optimization Using Genetic-Based Reinforcement Learning

PubMed Central

Lin, Hsuan-Ta; Lee, Po-Ming; Hsiao, Tzu-Chien

2015-01-01

Tutorial tactics are policies for an Intelligent Tutoring System (ITS) to decide the next action when there are multiple actions available. Recent research has demonstrated that when the learning contents were controlled so as to be the same, different tutorial tactics would make difference in students' learning gains. However, the Reinforcement Learning (RL) techniques that were used in previous studies to induce tutorial tactics are insufficient when encountering large problems and hence were used in offline manners. Therefore, we introduced a Genetic-Based Reinforcement Learning (GBML) approach to induce tutorial tactics in an online-learning manner without basing on any preexisting dataset. The introduced method can learn a set of rules from the environment in a manner similar to RL. It includes a genetic-based optimizer for rule discovery task by generating new rules from the old ones. This increases the scalability of a RL learner for larger problems. The results support our hypothesis about the capability of the GBML method to induce tutorial tactics. This suggests that the GBML method should be favorable in developing real-world ITS applications in the domain of tutorial tactics induction. PMID:26065018

Coupling measurements on intelligent missiles at microwave frequencies

NASA Astrophysics Data System (ADS)

Braun, Ch.; Guidi, P.; Schmidt, H. U.

1995-03-01

This paper describes our low power microwave coupling measurements on terminally guided missiles in the frequency range between 100 and 8000 MHz. The plane wave excitation experiments have been carried out in our field coupling facility, which consists of an asymmetric triplate transmission line with maximum field levels of about 40 V/m in the working volume. As test objects we examined five (semi) autonomous guided missiles. Three of them, former experimental studies from the Diehl company (GE), are presented in this paper. The test objects were positioned in the simulator in three orthogonal orientation with respect to the external field and were not connected to a power supply (inactive condition). In order to be able to systematically analyze the interaction of the external electromagnetic fields with the avionics and its wiring, we had to divide the investigations into three independent phases, namely, external interaction with the fuselage, mode of penetration to the interior of the missile and excitation of the electrical systems and the cabling. The coupling paths depend very much on the design principles of the airframe. The main threat identified was back door coupling via those wings and fins, which are not attached galvanically to the outer surface of the hull. Because of flight guidance, these parts are fastened through slots to the bearings of the motor drives inside the missile. The dominant cable resonances sometimes can be traced back to the resonances of the wings and/or fins and the type of cabling. Another threat was coupling via the long slots required for the folding wings. These shafts penetrate the whole body and enable the external fields to couple into the interior. The peak amplitudes at the ends of the cables were found to be between 50 to 500 (micro A/(V/m)), depending on the test object.