子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Information transmitting system | US968855 | 1978-12-12 | US4277778A | 1981-07-07 | Paul M. Persson |
| A system for transmitting information from a plurality of observation stations to a central station, especially for military purposes. Every observation station is equipped with a coder and a code transmitter for selecting and transmitting code signs corresponding to the observations. Preferably the coder comprises a key set provided with a key for each kind of observation. The coded information from the different observation stations is transmitted on separated wave-lengths or channels and received in a central station and stored together with time information in a computer memory to be presented in assembled form whenever needed. | ||||||
| 82 | Ballistic missile defense system | US829188 | 1959-07-22 | US3982713A | 1976-09-28 | John J. Martin |
| 1. The method of determining the trajectory of a ballistic missile having trajectory substantially defined by the formula:y = - g + .rho..infin. g(y).sup.2 /2 .beta. sin .gamma.x = .rho..infin. g (x).sup.2 /2 .beta. cos .gamma.comprising the steps of measuring the velocity and flight path angle of the missile at a reference altitude, measuring the radiation emitted by the gases in the proximate environment of the missile, measuring the time required for the missile to travel from the reference altitude to the occurrence of maximum radiation, measuring the altitude at which maximum radiation occurs, computing the value of "a" from the following formula: ##EQU1## COMPUTING THE VALUE OF ".beta." FROM THE FORMULA:A = .rho..sub.O G/2 C .beta. SIN .gamma.whereV = velocity at altitude yV.sub.e = velocity at altitude y.sub.o.gamma. = flight path anglee = base of natural logarithmsc = constanta = .rho..sub.o g/2 c .beta. sin .gamma..rho..sub.o = density of the atmosphere at sea level.rho..infin. = density of the atmosphere at altitude "y"g = acceleration due to gravity.beta. = ballistic coefficientp = constantt.sub.I.sbsb.m.sbsb.a.sbsb.x = time required for missile to travel from altitude y.sub.o to yy = altitude at which maximum radiation occurs = (ln p a)/ cy.sub.o = reference altitudey = first derivative of altitude with respect to timey = second derivative of altitude with respect to timex = first derivative of distance in the horizontal plane with respect to timex = second derivative of distance in the horizontal plane with respect to timeSubstituting the value of ".beta." from the solution of the last mentioned formula in the first mentioned formulas and computing the values of "y" and "x". | ||||||
| 83 | Method and apparatus for aiding in solution of three-dimensional fire control problems | US36367664 | 1964-04-23 | US3883070A | 1975-05-13 | MAUDLIN LLOYD Z |
| 1. Apparatus for aiding in the solution of a fire control problem for a weapon adapted to attack an underwater target, said weapon being of a type traveling along an air-trajectory to a point on the surface of the water in the vicinity of the target and thence along an underwater trajectory in response to a self contained control, said control causing the weapon to have predetermined characteristics affecting the likelihood of hitting a target under various spacial and relative motion situations, said apparatus comprising; A. AN AIR-TRAJECTORY DISPERSION ERROR CURVE REPRESENTING PROBABLE AREA WITHIN WHICH THE WEAPON WILL ENTER THE WATER FOR A GIVEN AIMPOINT, B. A RIGID ELEMENT INCLUDING C. A REFERENCE MARKER REPRESENTING A POSITION DATUM OF THE TARGET, SAID POSITION DATUM CONSISTING OF THE AZIMUTHAL COORDINATES ONLY OF THE TARGET POSITION; AND D. A STACK OF PARALLEL SPACED TRANSPARENT MEMBERS, THE INDIVIDUAL MEMBERS OF SAID STACK EACH REPRESENTING THE AREA ON THE SURFACE OF THE WATER WITHIN WHICH THE WEAPON SHOULD ENTER THE WATER IN ORDER TO HAVE A DESIRED LIKELIHOOD OF HITTING A TARGET AT SAID DATUM POSITION FOR A DIFFERENT DEPTH LEVEL OF A PREDETERMINED SERIES OF SEPARATED DEPTH LEVELS, SAID INDIVIDUAL MEMBERS OF THE STACK BEING STACKED IN ORDER OF THE DEPTH LEVEL THEY REPRESENT, AND E. THE CONSTRUCTION AND ARRANGEMENT BEING SUCH THAT SAID STACKED MEMBERS PROVIDE A THREE-DIMENSIONAL IMAGE OF DESIRED WATER ENTRY AREAS FOR DIFFERENT TARGET DEPTHS IN SUPERPOSED RELATIONSHIP TO THE AIR-TRAJECTORY DISPERSION ERROR CURVE, SAID DISPERSION ERROR CURVE AND SAID RIGID ELEMENT BEING MOVABLE RELATIVELY WHEREBY THE EFFECT OF VARIOUS ADJUSTMENTS OF AIMPOINT RELATIVE TO THE TARGET POSITION DATUM UPON THE FIRE CONTROL PROBLEM SOLUTION FOR VARIOUS DEPTH LEVELS OF THE TARGET MAY BE READILY ENVISIONED.
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| 84 | Sighting means for missiles | US3721420D | 1962-08-01 | US3721420A | 1973-03-20 | FORD B; CLAPP M |
| 1. A SIGHTING DEVICE FOR USE IN COMBINATION WITH A COMPUTER FOR PROGRAMMING THE FLIGHTS OF A BATTERY OF GUIDED MISSILES WITH A PLURALITY OF LAUNCHING POINTS DISPLACED FROM THE POSITION OF THE SIGHTING DEVICE, COMPRISING IN COMBINATION A VISUAL SIGHT MOUNTED ON A VERTICAL SIGHTING SHAFT JOURNALLED IN A FIXED SUPPORT FOR ROTATION OF THE SIGHT ABOUT THE VERTICAL SHAFT AXIS, A PLURALITY OF GANGED ROTARY ELECTRICAL POTENTIOMETERS RESPECTIVELY ASSOCIATED WITH THE LAUNCHING POINTS AND MOUNTED ONE ABOVE THE OTHER COAXIALLY WITH THE VERTICAL SIGHTING SHAFT, HAVING ROTORS OF ALL THE POTENTIOMETERS CONNECTED TO THE SIGHTING SHAFT FOR ROTATION THEREWITH IN UNISON, AND HAVING THE BODIES OF THE POTENTIOMETERS MOUNTED ONE ABOVE ANOTHER COAXIALLY WITH THE SIGHTING SHAFT TO ROTATE THEREWITH BY FRICTIONAL ENGAGEMENT OF THE ROTORS WITH THE BODIES, INDEPENDENTLY ACTUABLE FRICTIONAL CLAMPING MEANS TO CLAMP THE BODY OF EACH POTENTIOMETER SELECTIVELY IN A PRESET ANGULAR POSITION WHILE ITS ROTOR ROTATES WITH THE SIGHTING SHAFT, SAID INDEPENDENTLY ACTUABLE FRICTIONAL CLAMPING MEANS COMPRISING A RELEASABLE FRICTION BRAKE ACTING BETWEEN EACH POTENTIOMETER BODY AND THE FIXED SUPPORT, THE BRAKE WHEN ENGAGED HOLDING THE BODY IN A GIVEN ANGULAR POSITION AGAINST ROTATION RELATIVE TO THE SUPPORT, AND A SEPARATE AND INDEPENDENTLY-OPERABLE MOTOR MEANS ASSOCIATED WITH EACH FRICTION BRAKE AND OPERABLE TO ENGAGE AND RELEASE SAID BRAKE, A SEPARATE FRICTION BRAKE IN PERMANENT BUT SLIPPABLE ENGAGEMENT BETWEEN EACH POTENTIOMETER BODY AND THE SAID SIGHTING SHAFT TO AUGMENT THE FRICTIONAL TORQUE TRANSMISSIBLE BETWEEN THE SHAFT AND THE BODY OF THE POTENTIOMETER VIA ITS ROTOR, EACH SAID SEPARATE FRICTION BRAKE CAUSING ITS ASSOCIATED POTENTIOMETER BODY TO ROTATE WITH THE SHAFT WHEN THE ASSOCIATED RELEASABLE FRICTION BRAKE IS DISENGAGED, A STOP MEMBER ON EACH POTENTIOMETER BODY AND A CO-OPERATING ABUTMENT ON THE FIXED SUPPORT ARRANGED TO BE ENGAGED BY THE STOP MEMBER TO LIMIT THE ANGULAR ROTATION OF EACH POTENTIOMETER AT AN EXTREME DATUM POSITION, AND ELECTRIC CIRCUIT MEANS CONNECTED WITH SAID POTENTIOMETERS TO SUPPLY PROGRAMMING INFORMATION TO THE COMPUTER FOR EFFECTING AUTOMATIC PARALLAX CORRECTIONS FOR RESPECTIVE LAUNCHING POINTS RESPONSIVE TO THE POSITION OF THE SIGHTING SHAFT.
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| 85 | SYSTEM UND VERFAHREN ZUR WAFFENSYSTEMAUSWAHL | EP17189541.0 | 2017-09-06 | EP3309499A1 | 2018-04-18 | Gilch, Joachim; Müller, Jörg |
Ein Verfahren zur Waffensystemauswahl umfasst die Schritte des Erzeugens einer bildlichen Darstellung eines Ziels bzw. Zielgebietes für ein Waffensystem, des Auswählens eines Waffensystems auf der Basis eines oder mehrerer Waffensystemparameter, die bekannte, geschätzten und/oder vorausberechneten Eigenschaften des ausgewählten Waffensystems angeben, des Erzeugens graphischer Symbolelemente der Waffensystemparameter des ausgewählten Waffensystems, des Überlagerns der graphischen Symbolelemente über die bildliche Darstellung des Ziels bzw. Zielgebietes, des Änderns von Werten eines oder mehrerer der Waffensystemparameter durch einen Nutzer, des Modifizierens der graphischen Symbolelemente auf der Basis der geänderten Werten eines oder mehrerer der Waffensystemparameter, und des Modifizierens der Überlagerung der graphischen Symbolelemente über die bildliche Darstellung des Ziels bzw. Zielgebietes.
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| 86 | A NETWORK OF INTERCOMMUNICATING BATTLEFIELD DEVICES | EP14841869 | 2014-09-03 | EP3044904A4 | 2018-01-17 | COMPTON DAVID WALTER; TEED BRENTON STEWART; DOWNING WARREN; CROCKER GARY EDWARD |
| A plurality of battlefield devices that communicate with a battle management system using a communications network to form a network of intercommunicating battlefield devices that may be deployed in a battlefield environment. Each battlefield device comprising one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the battlefield device. The processor configured to cause the data to be sent to another location and to process other data received from other locations over said communications network. | ||||||
| 87 | A NETWORKED BATTLE SYSTEM OR FIREARM | EP14851134.8 | 2014-09-09 | EP3044905A1 | 2016-07-20 | COMPTON, David Walter; TEED, Brenton Stewart; DOWNING, Warren; CROCKER, Gary Edward |
| A firearm includes one or more rails to which accessories may be mounted. The rails provide a communication path over which data may be transferred between the accessories and a processor located in the rails or in the firearm. The processor may cause the data to be sent to another location and may receive other data from other locations to provide a network of intercommunicating firearms that may deployed in a battlefield environment. | ||||||
| 88 | A METHOD FOR DUEL HANDLING IN A COMBAT AIRCRAFT | EP12868452 | 2012-02-16 | EP2815201A4 | 2015-11-11 | LUNDQVIST ANDERS; KENSING VIBEKE |
| 89 | A METHOD FOR DETERMINING THREAT STATUS FOR COMBAT AIRCRAFTS | EP12868862 | 2012-02-16 | EP2815202A4 | 2015-10-28 | LUNDQVIST ANDERS; KENSING VIBEKE |
| The invention relates to a method for decision support of a first combat aircraft (1) in a combat situation comprising the steps of: a) detecting (3) a second combat aircraft (2), wherein the second combat aircraft (2) is different from the first combat aircraft (1), b) analyzing (4) the second combat aircraft (2) to determine its type, its sensor capacity and its total weapons capacity, and c) recording (5) the sensor capacity and the total weapons capacity of the second combat aircraft (2) to determine a first geographic zone adapted for defining the detection limit of the second combat aircraft (2) and a second geographic zone adapted for defining a shoot-down limit of the second combat aircraft (2), respectively, wherein the first and the second geographic zone are adapted for decision support of the first combat aircraft (1) in the combat situation with the second combat aircraft (2). In this way, a possibility is provided to assist the pilot in decision support in complicated combat situations while being reliable, fast and easy to handle for the pilot in order to make a quick and efficient decision. | ||||||
| 90 | INTEGRATED COMBAT RESOURCE MANAGEMENT SYSTEM | EP13801186.1 | 2013-06-07 | EP2859746A1 | 2015-04-15 | TURCOTTE, Stephane; BLANCHETTE, Remi; BELANGER, David; RIOUX, Francois; RIVEST, Martin; ROMANO, Paul; CURRY, Bill |
| An integrated combat resource management device is in the form of a smartphone with a display screen and user input device. The smartphone has a set of integrated applications stored therein which when executed provide an interactive display offering dynamic real-time situational awareness information to the user. Configuration files contain user-specific profiles. A launcher application offers access control and the management of several user profiles on the same smartphone such that upon successful login the appropriate user-specific profile is applied. | ||||||
| 91 | A METHOD FOR RESOURCE ALLOCATION IN MISSION PLANNING | EP12876280.4 | 2012-05-11 | EP2847720A1 | 2015-03-18 | ANDERSSON, Magnus; LUNDBERG, Kristian; QUTTINEH, Nils-Hassan |
| The present invention relates to a method for planning attacking to optimize the use of own available resources and effecting attacking of targets in a target area (15) based upon information on own resources available for attacking and information on protected and non-protected targets located in the target area. The method comprises collecting different attack tactics in a first library (5) and collecting strategies to defend a target area to be attacked in a second library (6), allotting each target (16, 17, 18) in the target area (15) a reward value, evaluating different attack tactics for a chosen defend tactic to find an optimal attack tactic having highest possible collected reward value, the found optimal attack tactic being used to create an attack plan involving information on inter alia resources needed, targets to attack and attacking directions The object of the invention is to obtain a more effective use of available resources. | ||||||
| 92 | SYSTEMS AND METHODS FOR VEHICLE SURVIVABILITY PLANNING | EP13795608.2 | 2013-05-03 | EP2844950A2 | 2015-03-11 | HERMAN, Carl R.; HOWE, David |
| System and methods for improving vehicle survivability. In some embodiments, Mission information may be obtained regarding a mission of at least one vehicle. The mission may comprise a plurality of mission stages, and the mission information may comprise at least one model associated with the at least one vehicle and at least one threat to the at least one vehicle. A potential action of the at least one vehicle may be selected by calculating a numerical measure for the potential action based at least in part on a mission stage of the plurality of mission stages during which the potential action is to be taken and the at least one model. | ||||||
| 93 | GUIDANCE METHOD AND APPARATUS | EP11749495.5 | 2011-08-23 | EP2609475A1 | 2013-07-03 | GATE, Martin,Simon |
| A method of guiding a pursuer to a target is provided, and is of particular use when the possible target location is described by non-Gaussian statistics. Importantly, the method takes into account the fact that different potential target tracks in the future have significantly different times to go. That can give rise to emergent behaviour, in which the guidance method covers several possible outcomes at the same time in an optimal way. An example embodiment of the method combines Particle Filter ideas with Swarm Optimization techniques to form a method for generating guidance commands for systems with non- Gaussian statistics. That example method is then applied to a dynamic mission planning example, to guide an airborne pursuer to a ground target travelling on a network of roads where the pursuer has no-go areas, to avoid collateral damage. | ||||||
| 94 | VERFAHREN UND VORRICHTUNG ZUR PROGRAMMIERUNG EINES PROJEKTILS | EP11705150.8 | 2011-01-28 | EP2531807A1 | 2012-12-12 | FRICK, Henry, Roger |
| The invention relates to inductively or capacitively programming a projectile (5). According to the invention, a waveguide (2, 11) is used for the programming, the electromagnetic field being concentrated in the waveguide. The used programming unit (1) consists of at least one waveguide (2, 11) which is preferably located and/or integrated in the region of the muzzle, for example in front of the muzzle brake (6). A transmission coupler (3) for the transmission is fed by a signal generator (4). Said information relating to the projectile (5) is modulated to the carrier frequency (f 1) in the modulator (18). A reception coupler (8) integrated on/in the projectile (5),is electrically interconnected to a store or processor (19) in the projectile (5). Said reception coupler receives the modulated signal and transmits it to the processor (19) which is where the eventual programming takes place. | ||||||
| 95 | KNOWLEDGE BASED AUTOMATIC THREAT EVALUATION AND WEAPON ASSIGNMENT | EP98957350.6 | 1998-10-22 | EP1029216B1 | 2003-09-24 | BARNES, Gregory, R. |
| A knowledge based threat evaluation and weapon assignment (TEWA) system and method. Upon identification of a hostile class track, if the track is outside national boundaries or defensive zones, a threat index is calculated to evaluate the threat. The index considers track speed, heading, altitude, and any known amplifying information such as flight size, airframe type, weapons load or missile type. If a threat enters a defensive zone, it becomes a target. Automatically a trial intercept calculation (TIC) will be calculated against the target. The TIC will utilize resources allocated to the zone; and with the aid of a zone target priority knowledge database and a target/weapon pairing database, the TIC will select the best available weapon to neutralize the target. The result of the TIC will be a weapon recommendation to the weapon's controller. | ||||||
| 96 | KNOWLEDGE BASED AUTOMATIC THREAT EVALUATION AND WEAPON ASSIGNMENT | EP98957350.6 | 1998-10-22 | EP1029216A1 | 2000-08-23 | BARNES, Gregory, R. |
| A knowledge based threat evaluation and weapon assignment (TEWA) system and method. Upon identification of a hostile class track, if the track is outside national boundaries or defensive zones, a threat index is calculated to evaluate the threat. The index considers track speed, heading, altitude, and any known amplifying information such as flight size, airframe type, weapons load or missile type. If a threat enters a defensive zone, it becomes a target. Automatically a trial intercept calculation (TIC) will be calculated against the target. The TIC will utilize resources allocated to the zone; and with the aid of a zone target priority knowledge database and a target/weapon pairing database, the TIC will select the best available weapon to neutralize the target. The result of the TIC will be a weapon recommendation to the weapon's controller. | ||||||
| 97 | Vorrichtung zum Erzeugen eines Lagebildes einer Gefechtslage auf See | EP80107883.3 | 1980-12-13 | EP0031110B1 | 1985-02-20 | Arens, Egidius; Hampe, Christoph; Anding, Norbert; Karlowsky, Ingo; Meyersieck, Manfred; Schwarz, Hans Dieter; Leisterer, Reinhard |
| 98 | Motion analysis unit | US15331157 | 2016-10-21 | US09846011B1 | 2017-12-19 | Alan Clark; Aaron C. Lattimore |
| A motion analysis system includes an acceleration measuring device, an acceleration processor, a velocity processor, a distance processor, a peak velocity processor, a profile correlation processor, and a vehicle action processor. The system determines a time for an initiation of an action for a vehicle by determining that a distance traveled by the vehicle is greater than a safe separation distance and that a peak velocity is greater than a minimum velocity. The system initiates the action for the vehicle based on the verified position of the vehicle and the confirmed profile data as determined by the profile correlation processor, and based on the determination that the distance traveled by the vehicle is greater than the safe separation distance and that the peak velocity is greater than the minimum velocity as determined by the vehicle action processor. | ||||||
| 99 | Vehicle Based Independent Range System (VBIRS) | US15589440 | 2017-05-08 | US20170328678A1 | 2017-11-16 | Edmund David Burke; Martin Stewart Waldman |
| A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers. | ||||||
| 100 | Test and analysis system and a method for threat evaluation and sensor/weapon assignment algorithms | US14241076 | 2013-03-25 | US09779185B2 | 2017-10-03 | Inci Yuksel Ergun; Melih Gunay |
| The present invention relates to a system comprising threat evaluation and sensor/weapon assignment algorithm operating units which are adapted such that they will operate any threat evaluation and sensor/weapon assignment algorithm, a simulation and analysis unit which is adapted such that it will form the area, in which threat evaluation and sensor/weapon assignment algorithms will be operated, as a virtual scenario by forming an air picture in accordance with the data it receives, an external communication unit which is in communication with the simulation and analysis unit; which can communicate correspondingly with a threat evaluation and sensor/weapon assignment algorithm operating unit; which is adapted such that it will transfer the current scenario information to the threat evaluation and sensor/weapon assignment algorithm when it is necessary and transfer the engagement results to the simulation and analysis unit by taking them back, and a communication unit which is adapted such that it will transfer the scenario, which is formed by communicating with a client, to the client and will receive data through the client; and a method comprising the steps of sending and arranging the data to the simulation and analysis unit through at least one client, transferring the virtual scenario to the TESWA algorithm operating units and receiving the engagement data, combining the engagement data with each other and the data received from the clients and updating the scenario status, approving and disapproving the engagement, analyzing the engagement data and transferring the results to a client partially or completely. | ||||||
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