| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Photoelectric proximity fuse mounting | US50712343 | 1943-10-21 | US3070017A | 1962-12-25 | CLARK EARL K |
| 142 | Light-sensitive proximity fuze | US56802044 | 1944-12-13 | US3064578A | 1962-11-20 | HENDERSON JOSEPH E; HAFSTAD LAWRENCE R; ROBERTS RICHARD B |
| 143 | Projectile nose structure | US52009744 | 1944-01-28 | US3040661A | 1962-06-26 | ROSS DANIEL W |
| 144 | Passive radiation proximity detector | US73324058 | 1958-05-01 | US3036219A | 1962-05-22 | THOMPSON ARTHUR V |
| 145 | Photoelectric influence detector and arming device for torpedoes | US16149550 | 1950-05-12 | US3026805A | 1962-03-27 | BECKER ROBERT A |
| 146 | Automatic bias shift circuit | US53178544 | 1944-04-19 | US2921203A | 1960-01-12 | HOFFMAN JOSEPH G |
| 147 | Directed missile | US41849741 | 1941-11-10 | US2520433A | 1950-08-29 | ROBINSON MARION B |
| 148 | Torpedo | US522035 | 1935-02-06 | US2060205A | 1936-11-10 | HAMMOND JR JOHN HAYS |
| 149 | Calorific radiation detonator | US70535934 | 1934-01-05 | US2060203A | 1936-11-10 | HAMMOND JR JOHN HAYS |
| 150 | Hyper-velocity penetrating probe for spectral characterization | US15151666 | 2016-05-11 | US10024696B2 | 2018-07-17 | Thomas M. Crawford; Richard J. Wright; James G. Sierchio |
| A hyper-velocity impact sensor including an optical fiber probe that transmits an optical pulse generated during impact with an object, a spectroscopic analyzer that receives the optical pulse and produces spectral information about the optical pulse, a connecting optical fiber configured to convey the optical pulse between the optical fiber probe and the spectroscopic analyzer, and at least one processor coupled to the spectroscopic analyzer and configured to receive and analyze the spectral information to determine at least one chemical element or compound contained in the object. | ||||||
| 151 | HYPER-VELOCITY PENETRATING PROBE FOR SPECTRAL CHARACTERIZATION | US15151666 | 2016-05-11 | US20170328742A1 | 2017-11-16 | Thomas M. Crawford; Richard J. Wright; James G. Sierchio |
| A hyper-velocity impact sensor including an optical fiber probe that transmits an optical pulse generated during impact with an object, a spectroscopic analyzer that receives the optical pulse and produces spectral information about the optical pulse, a connecting optical fiber configured to convey the optical pulse between the optical fiber probe and the spectroscopic analyzer, and at least one processor coupled to the spectroscopic analyzer and configured to receive and analyze the spectral information to determine at least one chemical element or compound contained in the object. | ||||||
| 152 | PROJECTILE DELIVERY OF DISRUPTIVE MEDIA FOR TARGET PROTECTION FROM DIRECTED ENERGY | US15088286 | 2016-04-01 | US20170284780A1 | 2017-10-05 | Mark J. Clemen, JR.; Donald V. Drouin, JR. |
| Methods, devices, and systems may protect a target from undesirable electromagnetic radiation by detecting electromagnetic radiation (including coherent radiation such as laser beams) aimed at a target from a source; calculating a first release position to disrupt the electromagnetic radiation thereby protecting the target; launching a projectile that may include a disruptive medium or a disruptive-medium precursor; directing the projectile to the first release position; and releasing the disruptive medium from the projectile at the first release position, such that the releasing of the disruptive medium forms a cloud of the disruptive medium. | ||||||
| 153 | Infra red proximity fuzes | US05843051 | 1977-10-13 | US07673565B1 | 2010-03-09 | James Proctor |
| An infra-red proximity fuze system for a homing missile is provided that has Mercury Cadmium Telluride detector cells cooled to at least −40° C., and a frequency response range of 5-7 microns, so as to be sensitive to target skin radiation due to kinetic heating and insensitive to jet-exhaust plume radiation. Three optics/detector modules are equidistantly spaced around the missile axis and each has first and second detector elements the three first elements being connected in a common channel to constitute a guard beam and the three second elements being likewise connected to constitute a firing beam, the guard beam field being displaced angularly from the firing beam field in the forward missile axis direction by about 6°. | ||||||
| 154 | SPECTRAL FILTER WITH DYE-IMPREGNATED RESONANT NANO-SPHERES | US11948874 | 2007-11-30 | US20090141343A1 | 2009-06-04 | Francis Lawrence Leard |
| Embodiments of spectral filters with dye-impregnated nano-spheres are described herein. Other embodiments may be described and claimed. In some embodiments, a spectral filter comprises a host material that includes a plurality of nano-particles embedded within. The particles include a dye having an absorption band of wavelengths and have a size selected to resonate at a range of wavelengths that is within the absorption band. The particles may be selected to resonate in either a plasmon mode or a whispering-gallery mode. | ||||||
| 155 | Integration of a semi-active laser seeker into the DSU-33 proximity sensor | US10301522 | 2002-11-21 | US06919840B2 | 2005-07-19 | William A. Friedrich; Lyle H. Johnson; Mark K. Conrad |
| A proximity sensor for use with a guidance system of a smart bomb including a ranging radar proximity sensor configured for mounting on a smart bomb and a radome connected to the ranging radar proximity sensor. A laser radiation sensor system is attached to the proximity sensor, which is configured and arranged to detect laser radiation reflected from a target which passes through the radome and output the azimuth and elevation angles to the target to the guidance system. | ||||||
| 156 | INTEGRATION OF A SEMI-ACTIVE LASER SEEKER INTO THE DSU-33 PROXIMITY SENSOR | US10301522 | 2002-11-21 | US20050030219A1 | 2005-02-10 | William Friedrich; Lyle Johnson; Mark Conrad |
| A proximity sensor for use with a guidance system of a smart bomb including a ranging radar proximity sensor configured for mounting on a smart bomb and a radome connected to the ranging radar proximity sensor. A laser radiation sensor system is attached to the proximity sensor, which is configured and arranged to detect laser radiation reflected from a target which passes through the radome and output the azimuth and elevation angles to the target to the guidance system. | ||||||
| 157 | Imaging-infrared skewed cone fuze | US09922360 | 2001-08-04 | US20020020321A1 | 2002-02-21 | Hayden N. Ringer; Abraham Shrekenhamer |
| A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity. | ||||||
| 158 | Optronic fuse device for a flying object | US09894027 | 2001-06-28 | US20020000172A1 | 2002-01-03 | Adreas Ganghofer |
| Described is an optronic fuse device (10) for a flying object such as a drone, a rocket or an aircraft, comprising a sensor window (14) which is provided for its optical arrangement (12) and with which is associated an air deflection device (16) in order to keep the air flow of the flying object in flight away from the sensor window (14) and to deflect it past the sensor window (14) and in that way to prevent fouling and/or icing of the sensor window during the mission of the flying object. | ||||||
| 159 | Detector circuit with a stationary potential amplifier input | US09438634 | 1999-11-12 | US06300616B1 | 2001-10-09 | Martin Regensburger |
| The detector circuit (11) of a radiation-sensitive sensor (10) with capacitive high pass coupling (14) between a pre-amplifier (13) and a signal amplifier (15) is blocked for a prolonged period of time (T2) even after termination of an overexcitation effect, because of the high filter time constant of the series capacitor (25), because the capacitor (25) only slowly experiences charge reversal and therefore the signal amplifier (15) following it initially still remains overdriven until the capacitor (25) has reversed charge again to a dc voltage level in the actuation range (39) of the signal amplifier (15). That dead time period (T2) is however curtailed to a short fraction (T1) if upon termination of overexcitation at the input side the capacitor (25) at the output side, that is to say upstream of the signal amplifier (15), is forcibly returned to the—virtual—ground potential at the amplifier input, for potential reduction purposes, by way of a low-resistance switching section (31). Such charge reversal can also be triggered under software control if no useful signals (17) which can be utilised have occurred over a relatively long period of time because for example permanently high actuation of the sensor (10) has resulted in an excessive potential displacement at the coupling capacitor (25). | ||||||
| 160 | Imaging-infrared skewed-cone fuze | US09049360 | 1998-03-27 | US06279478B1 | 2001-08-28 | Hayden N. Ringer; Abraham Shrekenhamer |
| A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity. | ||||||
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