| Flow Studies of Axisymmetric Bodies at Extreme Angles of Attack, |
18 AUG 1972 |
|
| Authors:
Lloyd H. Smith; Robert H. Nunn; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
 | Results of a background investigation and initial theoretical models are described for the flow about axisymmetric bodies at extreme angles of attack. Present state-of-the-art is described with the general conclusions that the current understanding of extreme angle of attack flow phenomena is relatively well developed for angles of attack up to about 40 degrees (symmetric vortex pair in the wake) and that for higher angles of attack there are several ... |
|
| ASM IMU Electronics Development Program. |
AUG 1972 |
|
| Authors:
Barry N. Levitt; Gerald M. Nearman; RAYTHEON CO BEDFORD MA MISSILE SYSTEMS DIV
|
| This research and development effort is part of an Air Force program to develop a low-cost, small midcourse inertial guidance system for tactical air-to-ground weapons. Previous Air Force-sponsored related efforts include sled test evaluation of the Raytheon prototype Low Cost Platform (LCP II), followed by development directed toward cost reduction, design simplification, and size improvement of the inertial measurement unit (IMU) for the LCP III. The effort covered by this ... |
|
| Surface Attack Guided Missile (SAGMI) Loads Analyses. |
AUG 1972 |
|
| Authors:
William W. Dyess Jr; AIR FORCE ARMAMENT LAB EGLIN AFB FL
|
| This report covers the SAGMI (Surface Attack Guided Missile) to launcher interface reaction loads analysis and the SAGMI/launcher to AERO-27/F-4 interface reaction loads analyses. The basic approach used was that delineated in specification MIL-A-8591D. Several modifications to the methodology of derivation of inputs were used to simulate more accurately the conditions expected during flight. (Author) |
|
| The Design of a Solid-State Replacement for Chassis 5 of the AIM-4A Guidance Unit. |
AUG 1972 |
|
| Authors:
J. Pilcicki; ARINC RESEARCH CORP ANNAPOLIS MD
|
| Chassis 5 of the AIM-4A guidance system has exhibited a high failure rate. With the primary purpose of improving the reliability of Chassis 5, Warner Robins Air Materiel Area (WRAMA) authorized ARINC Research Corporation to redesign the chassis, replacing the vacuum tubes with solid-state devices as the active elements in the circuits. The design goal was a module that is directly interchangeable with the vacuum tube chassis. This objective required ... |
|
| Optimization of the Short Range Weapons Control System. |
JUN 1972 |
|
| Authors:
James Warren Allen; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
| The report deals with the evaluation of the performance of a strapped down air-to-air tracker for the Short Range Weapons Control System. The system was designed, built, and evaluated at the Naval Weapons Center. The subsystems of the tracker which contributed to the problem areas discovered by flight tests are described. An evaluation of the shortcomings of the tracking scan mode and the automatic gain control circuit is discussed and ... |
|
| Failure Recurrence Control Plan for Sparrow III AIM-7F-4 Guidance and Control Section. |
JUN 1972 |
|
| Authors:
RAYTHEON CO LOWELL MA RELIABILITY DEPT
|
| The AIM-7F Failure Recurrence Control Plan provides a formalized, documented system for the collection, reduction and analysis of all factory test failure information. This data is used as the schedule and priority-setting criteria for the performance of failure analysis, analysis reporting, corrective action assignment and follow-up. The status and results of the failure analysis, cause of isolation corrective action assignment and corrective action monitoring and closeout are documented in both ... |
|
| General Comments on Nuclear Radiation Hardening for the SCAD. |
JUN 1972 |
|
| Authors:
R. H. Dickhaut; CORNELL AERONAUTICAL LAB INC BUFFALO NY
|
| The nuclear radiation environment in which the SCAD must function can produce transient and permanent system effects through component radiation response. The general procedure when considering nuclear survival involves the following three steps: (1) a study of system to estimate the nuclear radiation vulnerability levels; (2) verification of the vulnerability estimates that fall below the nuclear specification; (3) hardening the system or other corrective measures as required. The report reviews ... |
|
| A Method for Aerodynamic and Propulsion Design Optimization of the Short Range Dogfight Missile. |
MAY 1972 |
|
| Authors:
Carl A. Forbrich; Roger W. Gallington; John E. Hatlelid; John Paul Hyde; Richard C. Murrow; FRANK J SEILER RESEARCH LAB UNITED STATES AIR FORCE ACADEMY COLO
|
| The purpose of this study was to develop a computer program by which to optimize the various missile parameters available to the missile designer of a short range (one to ten mile radius) missile. The missile model used in this study was required to have the capability of intercepting a target with an unspecified heading at an initial range of three miles, and an angle-off-boresight of 45 deg. The missile ... |
|
| 'Activision' Optimization. Volume II. Utilization of 'Activision' for Air to Ground Missile Guidance. |
MAY 1972 |
|
| Authors:
Gerald A. Boothroyd; GENERAL ELECTRIC CO UTICA NY AEROSPACE ELECTRONIC SYSTEMS DEPT
|
| This volume documents the equipment, installation and testing of Activision in the Nite Gazelle/Nite LARS weapon delivery system. The Activision equipment includes a pulsed Gallium Arsenide Illuminator, an intensified isocon television camera with range gating capability and range data display generators. Data gathered by General Electric during evaluation tests at Nellis AFB is presented. The modifications incorporated in a government furnished isocon camera utilized in the program are described. (Author) ... |
|
| An Analysis of a Digital Correlation Technique for Multi-Sensor Terminal Guidance in an Air-to-Surface Missile |
APR 1972 |
53 pages |
| Authors:
John A. Pavco; NAVAL RESEARCH LAB WASHINGTON DC
|
 | A terminal guidance map-matching technique was evaluated on a digital computer. Imagery of known quality, from flights of the AN/APQ-97 radar and AN/ AAR-33 microwave radiometer, were correlated for targets of varying contrast levels. System performance, Characterized by a C.E.P. of 26 ft. excluding missile airframe steering and response errors, was obtained on targets having large areas with high contrast, such as bridges, airfields, and boatdocks. Examples of these target ... |
|
| Short Range Air-to-Air Weapon Control Requirements |
APR 1972 |
|
| Authors:
James V. Smith; H. L. Burke; Gerald Glaubitz; Jacqueline Imes; Clair M. Loughmiller; NAVAL RESEARCH LAB WASHINGTON DC
|
| The primary objective of this study is to define the dogfight environment in terms of a tracking system. The secondary objective is to apply this dogfight definition to present AI radars. This study is divided into two efforts, a determination of the primary weapon control requirements and a parameter interaction study. The purpose of the primary weapon control requirements study is to define the dogfight environment and to investigate the ... |
|
| AGILE Missile System Safety Engineering Plan. |
APR 1972 |
|
| Authors:
Lawrence H. Jackson II; NAVAL WEAPONS LAB DAHLGREN VA
|
| A plan is presented for safety engineering to be applied to the AGILE missile system development program. The plan outlines those tasks to be performed during the remainder of the advanced development phase and throughout the engineering development phase of the program. The culmination of the effort will be a recommendation to the Weapon System Explosives Safety Review Board (WSESRB) with regard to the safety release of the AGILE weapon ... |
|
| Evaluation of SAGMI and HAST Airloads at the F-4C Centerline Carriage Position for Subsonic and Transonic Mach Numbers. |
MAR 1972 |
|
| Authors:
Richard W. Butler; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| A wind tunnel investigation was conducted to determine the airloads on the SAGMI and HAST vehicles at the F-4C centerline carriage position. In the process of obtaining these loads, a limited amount of sting interference data on the SAGMI vehicle was obtained. Force and moment data were recorded at Mach numbers from 0.50 to 1.20 for angles of attack from -4 to 12 deg and angles of sideslip from -8 ... |
|
| ASM Gimbal IMU Development Program. |
MAR 1972 |
|
| Authors:
Barry N. Levitt; Gerald M. Nearman; RAYTHEON CO BEDFORD MA MISSILE SYSTEMS DIV
|
| An Air Force requirement exists for a low-cost inertial midcourse guidance system for tactical weapon delivery. The Raytheon LCP 2, delivered and evaluated under an earlier contract, is a candidate platform for this application. The effort covered by this report concerns further development of the platform inertial measurement unit (IMU) in the areas of cost reduction, design simplification and miniaturization. The report discusses the developmental investigations conducted, provides a detailed ... |
|
| Aerocooling of a 12-Inch Diameter Missile During Air Carry. |
FEB 1972 |
|
| Authors:
H. C. Schafer; NAVAL WEAPONS CENTER CHINA LAKE CA
|
| A series of flights using A6A aircraft and the small Bullpup airframe were made at 40,000, 30,000 and 20,000 feet. The resulting continuous time-temperature records of the JP-4 and JP-5 filled motor section are presented. The guidance and control section thermal response is also presented. Flight parameters included meteorological air temperatures of -78F for 2 1/2 hours exposure time. (Author) |
|
| Airworthiness Evaluation UH-1C XM156/Hornet Missile System. |
JAN 1972 |
|
| Authors:
James S. Kishi; Albert L. Winn; ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA
|
| A limited airworthiness evaluation was conducted on the UH-1C helicopter armed with the XM156/Hornet missile system. The test was conducted to verify a safe flight envelope, which would be the basis for a safety-of-flight release for the US Army Missile Command to conduct a feasibility study of the Hornet missile using an XM156 mount. Static longitudinal stability and static lateral-directional stability were evaluated at 50 and 80 knots indicated airspeed ... |
|
| Multi-Service Test and Evaluation: Maverick Two-Sided Test Design (Combat Hunter, Phase III) Volume I. Main Paper and Appendix A, |
JAN 1972 |
|
| Authors:
Larry F. Brown; Richard P. McLean; Joseph A. Navarro; Frederick Stahl; Earl A. Thomas; INSTITUTE FOR DEFENSE ANALYSES ARLINGTON VA SYSTEMS EVALUATION DIV
|
| Purpose of this report is to develop a detailed test design for the two-sided test of the MAVERICK (AGM-65) weapons system against a simulated Soviet combined arms unit in a European environment. Data from the resulting test is to be utilized in an operational evaluation of the MAVERICK weapons system. |
|
| Long-Range Missile-Equipped. A Soviet View, |
1972 |
|
| Authors:
B. A. Vasil'yev; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
|
|
| Qualification of Twenty-five Mirror Damper Assemblies. |
22 DEC 1971 |
|
| Authors:
NAVAL WEAPONS CENTER CHINA LAKE CA
|
| The mirror dampers furnished perform properly in the gyro assembly and meet the requirements except for diameter. |
|
| Antenna, Fuze, MARK 28 MODS 1 and 2 and Electronic Assembly, Fuze, MARK 5 MOD 1; Description, Handling, and Testing. |
DEC 1971 |
|
| Authors:
H. M. Forrester; NAVAL WEAPONS CENTER CHINA LAKE CALIF
|
| Brief physical and functional descriptions of the Antenna, Fuze, MARK 28 MODS 1 and 2 and Electronic Assembly, Fuze, MARK 5 MOD 1 are presented. Instructions are given for handling, assembling, and testing. (Author) |
|
| Close Air Support Missile Guidance and Control Study. Volume I. Six- Degree-of-Freedom Simulation |
DEC 1971 |
|
| Authors:
J. Mahig; FLORIDA UNIV GAINESVILLE DEPT OF MECHANICAL ENGINEERING
|
| This report describes in detail a six-degree-of-freedom program which can be used to determine the trajectory and miss distance of a missile system. The options for the program are such as to permit variation of the aerodynamics, seeker, autopilot actuator and missile motor performance for the purpose of accurately simulating a given missile design and evaluating the effects of changes in system parameters. Sufficient detail has been included in the ... |
|
| Close Air Support Missile Guidance and Control Study. Volume 2. Three- Degree-of-Freedom Simulation |
DEC 1971 |
|
| Authors:
J. Mahig; FLORIDA UNIV GAINESVILLE DEPT OF MECHANICAL ENGINEERING
|
| The purpose of the report is to describe in detail the equations used and the form required for the input data to a three-degree-of-freedom simulation of a laser guided missile system. The primary purpose of a three-degree-of- freedom simulation is to make possible the study of the characteristics of a given missile system quickly and economically. Since cross-coupling effects influence a missile's performance through the seeker, autopilot, and missile dynamics, ... |
|
| Rain-Erosion Tests on Walleye. |
NOV 1971 |
|
| Authors:
Max R. Smith; NAVAL WEAPONS CENTER CHINA LAKE CA
|
| The necessity to protect the glass dome window on optically guided weapon systems became a firm requirement with the reports of weapon damage to Fleet-returned missiles. A test program was initiated to determine the range and extent of rain-erosion damage to a typical electro-optically guided weapon system, the Walleye. The developmental end item was a lightweight, open-ended frustum of a cone that attaches to the nose of the weapon. The ... |
|
| Consolidation and Carrying Case for the AGM-69 SRAM Operational Test Launch Kit, |
OCT 1971 |
|
| Authors:
Rudolph F. Quinter; AIR FORCE PACKAGING EVALUATION AGENCY WRIGHT-PATTERSON AFB OHIO
|
| The operational test launch kit for the AGM-69 (SRAM) missile is composed of seven components which are presently packaged in individual containers. To facilitate ease of handling and use, it was decided to develop a consolidation and carrying case for the units. Prototype containers and items were fabricated by the Air Force Packaging Evaluation Agency to verify the container cushioning design. When tested in accordance with Federal Test Method Standard ... |
|
| Aircraft Guided Missile Subsystems |
01 SEP 1971 |
24 pages |
| Authors:
ARMY TEST AND EVALUATION COMMAND ABERDEEN PROVING GROUND MD
|
| The procedure provides guidance for conducting engineering tests of aircraft guided missile subsystems, with references for the testing of subsystem components. (Author) |
|
| A Study of Guidance Schemes for Air-to-Air Missiles. |
JUL 1971 |
|
| Authors:
John R. Stewart; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
|
| A number of guidance laws which may be used in an air-to-air homing missile are presented. Primary emphasis is given to forms which use proportional navigation augmented by line of sight acceleration. It is concluded that the addition of the line of sight acceleration to proportional navigation does not significantly improve the terminal accuracy of homing missiles. (Author) |
|
| A Preliminary Evaluation of Thrust Magnitude Control for Bomber Defense Missiles. |
JUL 1971 |
|
| Authors:
David M. Salmon; Lewis Meier; Stephen R. McReynolds; SYSTEMS CONTROL INC PALO ALTO CALIF
|
| The report presents the findings of a preliminary study to evaluate thrust magnitude control in Air Force Missions in general and for bomber defense missiles in particular. The first two phases of the study--a survey of the application of optimal control theory to the analysis of thrust magnitude control, and preparation of mathematical formulations for quantative analysis of specific applications--are reviewed. Then the techniques employed and results obtained in the ... |
|
| Test and Evaluation of MK 470 Container for Sparrow III Missile with Modified Wings and Fins. |
JUN 1971 |
|
| Authors:
W. Howard Trowbridge; Ralph J. Mercurio; NAVAL WEAPONS HANDLING LAB COLTS NECK N J
|
| To insure that the MK 470 MOD O Container provides adequate and secure storage space for a complete set of four modified wings and four modified fins, a series of rough-handling tests was conducted by the Naval Weapons Handling Laboratory. The test results show that the MK 470 MOD O Container has satisfactory stowage capabilities for the modified wings and fins of the NATO SPARROW 3 Missile. (Author) |
|
| Qualification on Twenty Piston Assemblies, |
08 APR 1971 |
|
| Authors:
G. Manikas; NAVAL WEAPONS CENTER CHINA LAKE CA
|
| The pistons were tested for use in the Solid State Sidewinder Missile. |
|
| Simulation of Supersonic Flow over a Scale Model Missile with Aft-Mounted Inlets Using an Axisymmetric Jet Stretcher. |
APR 1971 |
|
| Authors:
R. L. Barebo; E. H. Matkins; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
|
| A complex 0.4-scale model of a Boeing air-to-ground missile having two aft-mounted inlets was utilized with a Mach 2.5 jet stretcher to determine the capability of the jet stretcher to provide accurate forebody and inlet flow simulation at 0-deg angle of attack. Basically, the jet stretcher is an aerodynamically tailored device which replaces a known streamline in the supersonic flow field about the vehicle forebody with a boundary layer corrected ... |
|
| Laboratory Evaluation Program for EX 330 Mod 1 Fuze for Use with Improved Shrike Missile. |
APR 1971 |
|
| Authors:
Donald G. Crafts; NAVAL WEAPONS CENTER CHINA LAKE CALIF
|
| To assess the capability of the EX 330 Mod 1 Fuze to provide adequate safety and reliability in the Improved Shrike Missile application, the fuze was subjected to an extensive evaluation program. The program consisted of four sets of tests: reliability, safety, storage, and production lot tests. This report describes the tests, presents a failure analysis, and discusses results upon which conclusions and recommendations are based. It also records action ... |
|
| Brassboard Air-to-Surface Missile Computer Memory Integration. |
APR 1971 |
|
| Authors:
George V. Podraza; Roland S. Gregg; Albert D. Goldstein; BUNKER-RAMO CORP WESTLAKE VILLAGE CA ELECTRONIC SYSTEMS DIV
|
| The report describes the results of a task performed by The Bunker-Ramo Corporation's Electronic Systems Division to integrate a program memory and a scratchpad memory into the Air-to-Surface Missile (ASM) brassboard computer. The basic report describes the integration effort, the equipments involved, and the modifications necessary to achieve a working interface between the several systems. Results of the integration tests and descriptions of programs to test and evaluate the system, ... |
|
| Battery, Thermal. |
08 MAR 1971 |
|
| Authors:
NAVAL WEAPONS CENTER CHINA LAKE CA
|
| This purchase description covers one type of thermal battery intended for use as an electrical power supply during flight for the SIDEWINDER and CHAPARRAL Guidance and Control Groups (Mark 18 and Mark 28, respectively). (Author) |
|
| A Computer Simulation Aided Method for Predicting Expenditures of a Short Range, Semi-Active Homing Missile System. |
MAR 1971 |
|
| Authors:
Robert Sinclair Holman; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
| The thesis presents a computer simulation aided method for predicting expenditures of a short range, semi-active homing missile system engaged in an amphibious assault. The methodology used considers varying threat size, enemy strategy, and expected missile kill probabilities. Only a single-shot firing doctrine is considered. The results obtained, displayed for varying missile kill probabilities, provide the user with expenditure information on which to base missile procurement policy. (Author) |
|
| Method for Predicting the Static Aerodynamic Characteristics of Typical Missile Configurations for Angles of Attack to 180 Degrees. |
MAR 1971 |
|
| Authors:
Bernard F. Saffell Jr.; Millard L. Howard; Eugene N. Brooks Jr; NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
|
| A method for predicting the static, longitudinal aerodynamic characteristics of typical missile configurations at zero roll angle (i.e., in a plus configuration) has been developed and programmed for use on the IBM 7090 digital computer. It can be applied throughout the subsonic, transonic, and supersonic speed regimes to slender bodies of revolution or to nose-cylinder body combinations with low aspect-ratio lifting surfaces. The aerodynamic characteristics can be computed for missile ... |
|
| Feasibility Study of Modifying Mark 312 Fuze for Use with Mark 8 Mod 2 Rocket Motor. |
MAR 1971 |
|
| Authors:
J. O. Eaton; NAVAL WEAPONS CENTER CHINA LAKE CA
|
| The report describes a study to determine whether it is feasible to modify the Mk 312 fuze to make it compatible with the Mk 8 Mod 2 rocket motor under all launch conditions. The study concludes that the modification is feasible and can be accomplished by reducing the required arming acceleration of the fuze from 12 to 7.5 g. Recommendations for and estimated costs of follow-on development of the modification ... |
|
| Techniques for Generating Guidance Signals from Body-Fixed Sensors. |
09 FEB 1971 |
|
| Authors:
L. D. Holland; R. D. Wetherington; GEORGIA INST OF TECH ATLANTA ENGINEERING EXPERIMENT STATION
|
| The feasibility of using a relatively simple guidance technique and a strapdown sensor for guidance of a small tactical missile has been investigated. The principal method investigated was Dynamic Lead Guidance (DLG). Theoretical analyses were carried out to determine workable system parameters, to determine the required sensor characteristics, and to investigate the performance of DLG for sampled data input. Simulation runs were used to examine the dependence of system performance ... |
|
| Short Range Bomber Defense Missile Design Study. Volume VII. Autopilot and Controls. Appendix A-Analysis Data. Part I. |
FEB 1971 |
|
| Authors:
Ross Dutton; John Muller; Charles Ford; RAYTHEON CO BEDFORD MA MISSILE SYSTEMS DIV
|
| The appendix contains transient response plots, root locus plots and open loop transfer functions. This part covers the following designs: M1FA, M1TA, M1FA, M2FA, M2TA, and M2AA. |
|
| Short Range Bomber Defense Missile Design Study. Volume VII. Autopilot and Controls. Appendix A-Analysis Data. Part II. |
FEB 1971 |
|
| Authors:
Ross Dutton; John Muller; Charles Ford; RAYTHEON CO BEDFORD MA MISSILE SYSTEMS DIV
|
| The appendix contains transient response plots, root locus plots and open loop transfer functions. This part covers the following: M4FA, M4TA, M4AA, and Small step transient response data. |
|
| Short Range Bomber Defense Missile Design Study. Volume VII. Autopilot and Controls. Appendix A-Analysis Data. Part 3. |
FEB 1971 |
|
| Authors:
Ross Dutton; John Muller; Charles Ford; RAYTHEON CO BEDFORD MA MISSILE SYSTEMS DIV
|
| The appendix contains transient response plots, root locus plots and open loop transfer functions. This part covers the following designs: M2FM, M2TM, M2AM, M4FM, M4TM, M4AM, and M8FM. |
|
| Missile, Air-To-Ground |
12 JAN 1971 |
29 pages |
| Authors:
ARMY TEST AND EVALUATION COMMAND ABERDEEN PROVING GROUND MD
|
| There are continuing requirements for the development of new and improved aircraft-mounted, point and area target weapon subsystems which utilize air-to-ground guided missiles. These subsystems are needed to increase the maximum effective target engagement range in order to grant a standoff capability to the launching aircraft and thereby reduce its vulnerability to small arms fire and antiaircraft defenses. These missiles are required to possess low susceptibility to countermeasures through favorable ... |
|
| Close Air Support Weapon Engineering Design Study. Volume VI. Missile Simulation. |
JAN 1971 |
|
| Authors:
W. S. Walker; G. E. Blackshaw; R. W. Knowles; HUGHES AIRCRAFT CO CANOGA PARK CA
|
| The objective of the engineering design study of the close air support weapon (CASW) was to provide design considerations for the new close air support missile (CASM). The derivation of the missile was undertaken based on the modification of an existing missile. This study incorporates operational requirement and warhead effectiveness studies for various close air support targets leading to warhead and launch envelope recommendations. A thorough analysis of the system ... |
|
| Report on Modification of AIM-40 Falcon Missile Container to Accommodate Guidance and Control Section of AIM-7E/E2 Sparrow Missile. |
DEC 1970 |
|
| Authors:
Rudolph F. Quinter; AIR FORCE PACKAGING EVALUATION AGENCY WRIGHT-PATTERSON AFB OHIO
|
| A shortage of usable AIM-7 missile containers existed and the refurbishment operations were not capable of providing the quantity required. Also the new procurement containers would not be available for several months. Therefore, the possibility of an interim and/or back-up container was investigated. An AIM-4D Falcon container (FSN 8140-546-3527) was modified to accommodate the guidance and control sections of the AIM-7E/E2 Sparrow missile. The modification included removal of part of ... |
|
| Dynamic Response of the SHRIKE Missile during Flight Aboard A-4F Aircraft. |
20 NOV 1970 |
|
| Authors:
NAVAL WEAPONS CENTER CHINA LAKE CA
|
| Both inflight and laboratory vibration responses of the SHRIKE missile were recorded and analyzed during the series of tests described herein. The primary purpose of flight testing was to determine the internal dynamic response of the SHRIKE Missile to a captive flight environment, and to apply these results toward the establishment of meaningful qualification vibration requirements at the component level. In order to accomplish this, appropriate transducers were affixed to ... |
|
| Phoenix Weapon Control System. Radome Improvement Program; PMS 340-1/2324. Volume I. Design and R-F Measurement. |
OCT 1970 |
|
| Authors:
HUGHES AIRCRAFT CO CANOGA PARK CALIF MISSILE SYSTEMS DIV
|
| The development of a new radome for the YAIM-54A Phoenix Missile is described. The radome is a secant ogive shape which replaces the old tangent ogive and features a manufacturing process of lapping the inside contour instead of grinding to achieve low manufacturing cost. Low aerodynamic drag is achieved with the new more pointed shape and improved rain erosion resistance is achieved by virtue of the metal tip which is ... |
|
| A Study of Systems Interfacing: A Case Description and Analysis of the AGM-69A/FB-111A Interface. |
OCT 1970 |
|
| Authors:
Joseph W. Mock; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| This paper emphasizes the importance of interfacing in today's world. A general background in the area of interfacing is presented. The organization and documentation of interfacing, the character of the integrator, the types and areas of interfacing, and the problems encountered in interfacing are discussed. The interfacing of the AGM-69A, which is a short-range attack missile, with the FB-111A long-range bomber is used as an example to illustrate managerial relationships, ... |
|
| Project CHECO Southeast Asia Report. Second Generation Weaponry in SEA |
10-Sep-1970 |
119 pages |
| Authors:
Melvin F Porter; PACIFIC AIR FORCES HICKAM AFB HI CHECO DIV
|
| The application of technological advances in weaponry received new impetus as a result of Southeast Asian operations. Weapons such as laser guided bombs and video guided missiles were tested, evaluated, and introduced into operational inventories with impressive results. Highlights and lessons learned since the introduction of these and other new weapons are recorded in this Project CHECO Report. |
|
| The Effect of F-8 Aircraft Maneuvers on ATOLL (AA-2) Performance |
SEP 1970 |
43 pages |
| Authors:
Harold Toothman; Clair Loughmiller; NAVAL RESEARCH LAB WASHINGTON DC
|
| An analysis was made to determine the capability of the F-8 aircraft to evade the ATOLL missile by maneuver. Realistic computer simulations of both the ATOLL and the F-8 were combined with the IR characteristics of the F-8 and the atmosphere to provide the tool for analysis. The simulation results define maneuver requirements for the F-8 in the air combat maneuvering environment. It is concluded that maneuver alone is not ... |
|
| Response of the AIM-9D (Sidewinder) Missile to Captive-Flight-Vibration Environment, |
JUL 1970 |
|
| Authors:
W. W. Parmenter; NAVAL WEAPONS CENTER CHINA LAKE CALIF
|
| Measurement of the vibration response for the AIM-9D (Sidewinder) guided missile was made during captive flights on F-4B and F-8E aircraft. The missile was mounted on the LAU-7/A launcher. Signals from accelerometers mounted at various locations on the missile and launcher structure were recorded on magnetic tape. These signals were digitally analyzed to obtain comparisons of power spectral density curves for various flight conditions. Typical autocorrelation curves and rms ... |
|
| A MINMAX STUDY OF AIM ANGLE FOR PROPORTIONAL NAVIGATION MISSILE (THE PLANAR CASE). |
MAY 1970 |
|
| Authors:
Glenn Paul Orgeron; LOUISIANA STATE UNIV BATON ROUGE DEPT OF ELECTRICAL ENGINEERING
|
| The problem of minimizing the maximum terminal miss of a planar case, proportional navigation missile attacking a high performance aircraft by optimally selecting missile launch angle is studied. System models are developed for both the aircraft and the missile; constraints are introduced to preserve physical realism. An algorithm based upon a worst-case error analysis is applied to find the optimum missile launch angle. Recurring patterns have been found for target ... |
|
Air- and Space-Launched Guided Missiles
