| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 人检测装置和包括该人检测装置的图像形成装置 | CN201210080382.4 | 2012-03-23 | CN102692277A | 2012-09-26 | 桝元孝介; 梅田史郎; 田中敏明 |
| 本发明提供一种能够高精度地判定人的位置或者移动状态的人检测装置和包括该人检测装置的图像形成装置等。包括：传感器，检测红外线的变化；以及透镜组，多个第一透镜围绕传感器而环状配置且可旋转。由各个第一透镜形成第一单位检测区域，该第一单位检测区域具有在透镜组的径向延伸的第一检测距离和在旋转方向延伸的狭小的宽度，且包括一个或者多个第一单位检测区域的第一局部检测区和不存在第一单位检测区域的非检测区在透镜组的旋转方向上交替地形成多个。基于旋转驱动装置对于透镜组的旋转驱动时的传感器的输出以及由旋转位置检测部件检测出的透镜组的旋转位置，判定进入了在透镜组的径向外侧形成的传感器的第一检测范围的人的位置和/或移动状态。 | ||||||
| 2 | 人检测装置和包括该人检测装置的图像形成装置 | CN201210080382.4 | 2012-03-23 | CN102692277B | 2015-01-14 | 桝元孝介; 梅田史郎; 田中敏明 |
| 提供一种能够高精度地判定人的位置或者移动状态的人检测装置和包括该人检测装置的图像形成装置等。包括：传感器，检测红外线的变化；以及透镜组，多个第一透镜围绕传感器而环状配置且可旋转。由各个第一透镜形成第一单位检测区域，该第一单位检测区域具有在透镜组的径向延伸的第一检测距离和在旋转方向延伸的狭小的宽度，且包括一个或者多个第一单位检测区域的第一局部检测区和不存在第一单位检测区域的非检测区在透镜组的旋转方向上交替地形成多个。基于旋转驱动装置对于透镜组的旋转驱动时的传感器的输出以及由旋转位置检测部件检测出的透镜组的旋转位置，判定进入了在透镜组的径向外侧形成的传感器的第一检测范围的人的位置和/或移动状态。 | ||||||
| 3 | Projectile seeker | EP05010352.2 | 2005-05-12 | EP1598633A1 | 2005-11-23 | Chishinski, Ehud |
The present invention relates to a projectile seeker which comprises: (a) A hollow in the projectile for accommodating a light sensor; (b) A light sensor located within said hollow for sensing light which is emitted or reflected from a target, and for producing an electronic signal upon sensing such emitted light; and (c) A longitudinal shaped opening at the slanted front-side surface of the projectile for enabling a shaped field of view to said light sensor which is limited by the boundaries of said opening, the opening width varies in a direction from the front to the back of the projectile in order to cause said electronic signal to depend on the spinning of the projectile and to be proportional to the orientation of the projectile with respect to the object. |
||||||
| 4 | A DETECTION SYSTEM FOR USE IN AN AIRCRAFT | EP91907594 | 1991-04-09 | EP0525007A4 | 1993-06-02 | PRATA, ALFREDO, JOSE; BARTON, IAN, JAMES |
| A detection system for use in an aircraft which is able to monitor atmospheric conditions ahead of the aircraft, generate an alarm signal if adverse atmospheric conditions exist ahead of the aircraft and generate information which indicates the position of the adverse conditions so the adverse conditions can be avoided. The system is able to detect the presence of volcanic ash cloud ahead of the aircraft and, if desired, can also be used to detect a high density of sulphur dioxide gas and/or clear air turbulence ahead of the aircraft. The system monitors infrared radiation received by the aircraft, generates intensity signals representative of at least one predetermined wavelength of the radiation and compares intensity signals with reference signals or intensity signals of another infrared wavelength. If the results of the comparison which indicate the adverse conditions are present, an adverse condition warning signal is generated and the device is also able to generate video display signals for producing a video display which indicates the position of the adverse conditions relative to the aircraft. | ||||||
| 5 | METHOD AND APPARATUS FOR MEASUREMENT OF DIRECTION | EP91913367.0 | 1991-07-19 | EP0540594A1 | 1993-05-12 | Gorham, Barry James; Dudley, James Richard |
| L'invention décrit un procédé et un instrument correspondant servant à mesurer la direction d'une source de rayonnement éloignée, l'instrument comportant un moyen de support, une tête de détection montée rotative sur lesdits moyens pour tourner autour d'un axe fixe et un moyen d'indication de position qui produit un signal de sortie indiquant la position de rotation de la tête de détection, cette dernière étant pourvue d'un moyen de détection (15) sensible au rayonnement émis par la source éloignée et d'un moyen de formation d'une image de la source qui traverse le moyen de détection pendant la rotation de la tête de détection; le moyen de formation d'image est conçu de telle façon que l'image comprend deux éléments ligne-image (L, T) situés transversalement par rapport à la direction de transit et qui s'inclinent en position opposée vers cette direction; le moyen de détection (15) est conçu pour provoquer, en réaction au transit de chaque élément image-ligne, l'enregistrement de la position angulaire instantanée de la tête de détection, comme indiquée par le moyen d'indication de position, par un moyen informatisé qui se trouve en plus dans le dispositif et qui calcule des mesures composées de deux éléments correspondant à la direction de la source, respectivement à partir de la moyenne des deux positions angulaires enregistrées et de leur différence. | ||||||
| 6 | Système optoélectrique de détection et de localisation angulaire de sources lumineuses, à haute immunité envers les contre-mesures | EP85401297.8 | 1985-06-27 | EP0169128B1 | 1988-11-09 | Couderc, Georges; Pepin, Christian; Symaniec, Leonid |
| 7 | 광검출 장치 및 차량용 냉각 시스템 제어 장치 | KR1019890010054 | 1989-07-14 | KR100152962B1 | 1998-12-01 | |
| 내용 없음. | ||||||
| 8 | Infrarotsensor für einen Erdsatelliten | EP93105032.2 | 1993-03-26 | EP0563823B1 | 1996-01-10 | Ziegler, Fred |
| 9 | A DETECTION SYSTEM FOR USE IN AN AIRCRAFT | EP91907594.0 | 1991-04-09 | EP0525007A1 | 1993-02-03 | PRATA, Alfredo, Jose; BARTON, Ian, James |
| Un système de détection utilisé dans un avion, capable de contrôler les conditions atmosphériques qu'un avion va rencontrer, produit un signal d'alarme si l'avion va rencontrer des conditions atmosphériques défavorables et il produit des informations indiquant la position des conditions défavorables de manière à éviter ces dernières. Le système est capable de détecter la présence d'un nuage de cendres volcaniques se trouvant sur la route de l'avion et, si désiré, on peut également l'utiliser afin de détecter une densité élevée de gaz de dioxyde de soufre et/ou des turbulences d'air clair situées devant l'avion. Le système contrôle le rayonnement infrarouge reçu par l'avion, il produit des signaux d'intensité représentant au moins une longueur d'onde prédéterminée du rayonnement et il compare les signaux d'intensité avec des signaux de référence ou des signaux d'intensité d'une autre longueur d'onde d'infrarouges. Si les résultats de la comparaison indiquent la présence de conditions défavorables, un signal d'avertissement de conditions défavorables est émis, le dispositif étant également capable de produire des signaux d'affichage vidéo afin de produire un affichage vidéo indiquant la position des conditions défavorables par rapport à l'avion. | ||||||
| 10 | Vorrichtung zur Ausrichtung einer richtungssteuerbaren Einrichtung auf eine Lichtquelle | EP85107475.7 | 1985-06-15 | EP0166352B1 | 1992-09-09 | Uhlemann, Reinhard, Dr.; Oster, Walter |
| 11 | Photodetector system with controllable position-dependent sensitivity | EP89112665.8 | 1989-07-11 | EP0350866A1 | 1990-01-17 | Hegyi, Dennis J. |
A photodetector system (10) for producing electrical signals responsive to the orientation of a light source, such as the sun, with respect thereto utilizes in certain embodiments a diffuser (11) to eliminate position-dependent sensitivities of the photocathode. The extent to which the diffuser (11) or the photocathode itself is exposed to the incident radiation can be controlled by a shroud (12) or by applying an absorptive coating (32) in a predetermined pattern on an absorber cap (40), or on the diffuser (11) directly. In a shrouded embodiment of the invention, the diffuser element (11) is arranged within a mountable body (13) with the shroud (12) extending thereover. The shroud (12), by its configuration and its height above the photodetector, defines the range of angles of elevation and azimuth at which the diffuser (11) can be illuminated. Such angles can also be controlled with printed or sprayed-on markings (30) on the diffuser or absorber cover (11) which form an opaque coating so as to prevent light transmission over predetermined regions. In addition to transmissive and nontransmissive regions, a fine dot pattern (32) may be applied to the diffuser or the absorber cover (11), which may be translucent or transparent, or to the diffuser (11) directly, so that only partial transmission of the light can be achieved therethrough. The absorber cover (11) may be provided with a light absorbing coloration or dye therethrough, and have a predetermined variation in thickness, so that the amount of light transmitted therethrough is responsive to the thickness at the point of incidence of the light. Thus, the light which is transmitted to the photodetector is modulated in response to the orientation of the light source with respect to the photodetector system. |
||||||
| 12 | Devices for the preparation of the displacement signal and or the current signal for a satellite that is directed onto the earth | JP28586785 | 1985-12-20 | JPH0613978B2 | 1994-02-23 | FURITSUTSU HAABERURU |
| 13 | JPH0113543B2 - | JP11710983 | 1983-06-30 | JPH0113543B2 | 1989-03-07 | SUZUKI KEIZO |
| 14 | JPS628753B2 - | JP14378277 | 1977-11-29 | JPS628753B2 | 1987-02-24 | RAGUNAA FUORUSHUFUDO; AANORUDO YOHANSON; ERURANTO PETSUTAASON |
| 15 | Device for preparing displacement signal and/or present signal for satellite directed onto earth | JP28586785 | 1985-12-20 | JPS61155099A | 1986-07-14 | FURITSUTSU HAABERURU |
| 16 | Reticle tracking receiver | JP11710983 | 1983-06-30 | JPS6010189A | 1985-01-19 | SUZUKI KEIZOU |
| PURPOSE:To remove the effect of noise with an autonomous recognition of an obstructing source by amplifying a detector output with band pass amplifiers with the center angle frequency of momega and momega/2 respectively to generate a reference signal for synchronous detection. CONSTITUTION:When a reticle 21A rotates at an angular speed omega, a signal in which double side-band waves exist on both sides of momega/2 in the angular frequency respectively with the center frequency of momega in the carrier appears at the output of a detector 22. Output of the detector 22 are amplified with band pass amplifiers 27 and 31 with the center frequency of momega and momega/2 respectively and the output of the amplifier 27 is divided with a 1/2 frequency divider 28 to make a reference signal with the center frequency of momega/2. The reference signal is used to perform a synchronous detection of the output of the amplifier 31 or it is added to the output of the amplifier 31 to fetch error signals Az and El by an amplitude detection. | ||||||
| 17 | Coaxial rotation type reticle | JP11710883 | 1983-06-30 | JPS6010188A | 1985-01-19 | SUZUKI KEIZOU |
| PURPOSE:To improve the tracking performance with an autonomous recognition of an obstructing source by arranging a term given by a product between a term increasing toward the periphery and a m/2 cycle function into a function indicating the boundary line of a reticle pattern equally divided in (m) radially near the center of the pattern. CONSTITUTION:The pattern of a reticle 21A is equally divided in (m) radially near the center thereof while a term given by the product between a term increasing toward the periphery of the pattern and a term of a m/2 cycle function is included into a function indicating the boundary line of the pattern. Therefore, as in the periphery of the pattern, a transparent section, a non-transparent section and a semi-transparent section are formed in an unbalanced division, as the reticle 21A rotates at an angular speed omega, a detector 22 outputs a signal in which double side-band waves exist on both sides of the angular frequency momega/2 with the center angle frequency of momega in the carrier. Thus, the effect of obstruction can be minimized to allow the fetching of an elevation error signal El and an azimuth error signal Az. | ||||||
| 18 | Human detection device and image formation device with human detection device | JP2011067080 | 2011-03-25 | JP2012202793A | 2012-10-22 | MASUMOTO KOSUKE; UMEDA SHIRO; TANAKA TOSHIAKI |
| PROBLEM TO BE SOLVED: To provide a human detection device etc., capable of precisely determining a position and a moving state of a person.SOLUTION: A human detection device includes a sensor 11 which detects change of infrared rays and a lens group 12 which has a plurality of first lenses annularly arranged around the sensor, and is rotatable. Each of the first lenses forms a first unit detection region 121 which has a first detection distance extending in a radial direction of the lens group and a narrow width extending in a rotating direction, and further pluralities of first local detection zones 125 including one or a plurality of first unit detection regions and non-detection zones 126 in which none of the first unit detection regions are present are formed alternately in the rotating direction of the lens group. A position and/or a moving state of a person who enters a first detection range 123 of the sensor formed radially outside the lens group 12 is determined based upon an output of the sensor 11 when a rotary driving device 13 drives and rotates the lens group 12 and a rotational position of the lens group detected by rotational position detection means 14. | ||||||
| 19 | JPH05508921A - | JP51256091 | 1991-07-19 | JPH05508921A | 1993-12-09 | |
| 20 | JPH0347469B2 - | JP7513284 | 1984-04-16 | JPH0347469B2 | 1991-07-19 | SUZUKI KEIZO |
QQ群二维码
意见反馈
意见反馈