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公开(公告)号：US09180976B2
公开(公告)日：2015-11-10
申请号：US14193161
申请日：2014-02-28
Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
Inventor： Hiroshi Kobayashi , Akira Nishizawa
Abstract: The present invention provides an electric propulsion system control apparatus that uses electric means alone so that effects pertaining to weight and cost are suppressed, is capable of accurate detection even when an airspeed has a binary relationship with a torque and a rotation speed of a propeller, and thereby exhibits improved detection precision and responsiveness. The electric propulsion system control apparatus drives a propulsion propeller to rotate, and is configured to estimate the airspeed from a data set stored in advance in relation to the airspeed and a propeller characteristic, and a plurality of torque and rotation speed estimation values detected under different driving conditions.
Abstract translation: 本发明提供了一种电动推进系统控制装置，其单独使用电气装置，以便抑制与重量和成本有关的影响，即使当空速与螺旋桨的转矩和转速具有二元关系时，也能够进行精确检测， 从而表现出提高的检测精度和响应性。 电动推进系统控制装置驱动推进螺旋桨旋转，并且被配置为从相对于空速和螺旋桨特性预先存储的数据集估计空速，以及在不同的速度下检测的多个转矩和转速估计值 驾驶条件。
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公开(公告)号：US20150082797A1
公开(公告)日：2015-03-26
申请号：US14557877
申请日：2014-12-02
Inventor： Ryusuke MATSUYAMA , Masayoshi KOBAYASHI , Atsushi HORIKAWA , Hitoshi FUJIWARA
CPC classification number: F23R3/16 , F23R3/14 , F23R3/18 , F23R3/28 , F23R3/34 , F23R3/343 , Y02T50/675
Abstract: A fuel injection device for supplying a fuel to a compressed air includes: a pilot fuel injector; a main fuel injector located at an outer periphery of the pilot fuel injector; and an air injection unit located between an outlet end portion of the pilot fuel injector and the main fuel injector. The air injection unit includes: a partition wall plate separating the air injection unit from a combustion chamber; a flame stabilization plate provided at a downstream side of the partition wall plate; a first opening at a downstream side between the flame stabilization plate and the outlet end portion of the pilot fuel injector; and a second opening provided in the partition wall plate and through which the compressed air is supplied. The flame stabilization plate includes an inclined portion inclined in a radially outward and downstream direction with respect to an axis.
Abstract translation: 用于向压缩空气供给燃料的燃料喷射装置包括：先导燃料喷射器; 主燃料喷射器，位于引燃燃料喷射器的外周; 以及位于先导燃料喷射器的出口端部与主燃料喷射器之间的空气喷射单元。 空气喷射单元包括：分隔壁板，其将空气喷射单元与燃烧室分离; 设置在隔壁板的下游侧的火焰稳定板; 在火焰稳定板和引燃燃料喷射器的出口端部之间的下游侧的第一开口; 以及设置在分隔壁板中的第二开口，通过该第二开口供应压缩空气。 火焰稳定板包括相对于轴线沿径向向外和向下游方向倾斜的倾斜部分。
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43.发明授权Device to reflect in a desired direction a laser beam emitted by a laser device mounted with an aircraft 有权用于以期望的方向反射由安装有飞行器的激光装置发射的激光束的装置公开(公告)号：US08956022B2
公开(公告)日：2015-02-17
申请号：US13633417
申请日：2012-10-02
Applicant: Japan Aerospace Exploration Agency
Inventor： Hamaki Inokuchi
CPC classification number: B64D47/02 , G01S7/4972 , G01S17/933
Abstract: A laser light reflection device for an aircraft-installed laser apparatus with which, when a function check is performed on the aircraft-installed laser apparatus by emitting laser light from a parked aircraft to a body exterior, the emitted laser light can be reflected in a desired direction safely and efficiently. A reflection mirror is capable of autorotation about at least an in-plane horizontal axis thereof, and a support ring is attached to the reflection mirror to be capable of rotating about an in-plane vertical axis and the in-plane horizontal axis of the reflection mirror. A laser pointer unit formed by inserting a laser pointer into a sleeve pipe is attached to the support ring so as to be oriented toward an in-plane of the reflection mirror. A guide scope is attached to the support ring such that an optical axis thereof matches an optical axis of the laser pointer unit.
Abstract translation: 一种用于飞行器安装的激光装置的激光反射装置，当通过从停放的飞行器发射激光到身体外部对飞行器安装的激光装置进行功能检查时，发射的激光可以被反射在 期望方向安全有效。 反射镜能够围绕其至少一个平面内的水平轴自转，并且支撑环附接到反射镜以能够围绕平面内垂直轴线旋转并且反射的平面内水平轴线 镜子。 通过将激光指示器插入到套筒管中而形成的激光指示器单元被安装到支撑环上以朝向反射镜的平面内。 引导范围附接到支撑环，使得其光轴与激光指示器单元的光轴匹配。
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公开(公告)号：US20140257599A1
公开(公告)日：2014-09-11
申请号：US14193161
申请日：2014-02-28
Applicant: Japan Aerospace Exploration Agency
Inventor： Hiroshi Kobayashi , Akira Nishizawa
IPC: B64D31/06
Abstract: The present invention provides an electric propulsion system control apparatus that uses electric means alone so that effects pertaining to weight and cost are suppressed, is capable of accurate detection even when an airspeed has a binary relationship with a torque and a rotation speed of a propeller, and thereby exhibits improved detection precision and responsiveness. The electric propulsion system control apparatus drives a propulsion propeller to rotate, and is configured to estimate the airspeed from a data set stored in advance in relation to the airspeed and a propeller characteristic, and a plurality of torque and rotation speed estimation values detected under different driving conditions.
Abstract translation: 本发明提供了一种电动推进系统控制装置，其单独使用电气装置，以便抑制与重量和成本有关的影响，即使当空速与螺旋桨的转矩和转速具有二元关系时，也能够进行精确检测， 从而表现出提高的检测精度和响应性。 电动推进系统控制装置驱动推进螺旋桨旋转，并且被配置为从相对于空速和螺旋桨特性预先存储的数据集估计空速，以及在不同的速度下检测的多个转矩和转速估计值 驾驶条件。
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45.发明申请PROCESS FOR PRODUCING CERAMIC FIBER-REINFORCED COMPOSITE MATERIAL AND CERAMIC FIBER-REINFORCED COMPOSITE MATERIAL 审中-公开生产陶瓷纤维增强复合材料和陶瓷纤维增强复合材料的方法公开(公告)号：US20130184141A1
公开(公告)日：2013-07-18
申请号：US13743293
申请日：2013-01-16
Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
Inventor： Toshio Ogasawara , Takuya Aoki , Masaki Kotani
IPC: C04B35/80
CPC classification number: C04B35/80 , C04B35/58092 , C04B35/62863 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/806 , C04B41/009 , C04B41/5096 , C04B41/85 , C04B2235/3826 , C04B2235/3891 , C04B2235/424 , C04B2235/428 , C04B2235/48 , C04B2235/608 , C04B2235/614 , C04B2235/616 , C04B2235/80 , C04B2235/96 , C04B2235/9684 , C22C49/14 , F05D2300/6033 , C04B35/565 , C04B38/00 , C04B41/4515 , C04B41/4523 , C04B41/4545 , C04B41/5071
Abstract: To obtain a ceramic fiber-reinforced composite material, by melt-infiltrating a composite material substrate obtained by forming ceramic fibers into a composite with a matrix formed of an inorganic substance, with an alloy having a composition that is constituted by a disilicate of at least one or more transition metal among transition metals that belong to Group 3A, Group 4A or Group 5A of the Periodic Table and silicon as the remainder, and having the silicon content ratio of 66.7 at % or more.
Abstract translation: 为了获得陶瓷纤维增强复合材料，将通过将由陶瓷纤维形成的复合材料基体熔融渗透到由无机物形成的基体的复合材料中，与由至少由二硅酸盐构成的组成的合金熔融渗透 属于3A族，4A族或5A族元素的过渡金属中的一种以上的过渡金属，余量为硅，硅含量比为66.7at％以上。
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Patent Agency Ranking
46.发明申请公开(公告)号：US20130100688A1
公开(公告)日：2013-04-25
申请号：US13633417
申请日：2012-10-02
Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
Inventor： Hamaki Inokuchi
IPC: B64D47/02
CPC classification number: B64D47/02 , G01S7/4972 , G01S17/933
Abstract: A laser light reflection device for an aircraft-installed laser apparatus with which, when a function check is performed on the aircraft-installed laser apparatus by emitting laser light from a parked aircraft to a body exterior, the emitted laser light can be reflected in a desired direction safely and efficiently. A reflection mirror is capable of autorotation about at least an in-plane horizontal axis thereof, and a support ring is attached to the reflection mirror to be capable of rotating about an in-plane vertical axis and the in-plane horizontal axis of the reflection mirror. A laser pointer unit formed by inserting a laser pointer into a sleeve pipe is attached to the support ring so as to be oriented toward an in-plane of the reflection mirror. A guide scope is attached to the support ring such that an optical axis thereof matches an optical axis of the laser pointer unit.
Abstract translation: 一种用于飞行器安装的激光装置的激光反射装置，当通过从停放的飞行器发射激光到身体外部对飞行器安装的激光装置进行功能检查时，发射的激光可以被反射在 期望方向安全有效。 反射镜能够围绕其至少一个平面内的水平轴自转，并且支撑环附接到反射镜以能够围绕平面内垂直轴线旋转并且反射的平面内水平轴线 镜子。 通过将激光指示器插入到套筒管中而形成的激光指示器单元被安装到支撑环上以朝向反射镜的平面内。 引导范围附接到支撑环，使得其光轴与激光指示器单元的光轴匹配。
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47.发明申请COLORED NOISE REDUCTION METHOD AND DEVICE FOR OPTICAL REMOTE AIRFLOW MEASUREMENT APPARATUS 有权用于光学遥控气流测量装置的彩色噪声减少方法和装置公开(公告)号：US20130088705A1
公开(公告)日：2013-04-11
申请号：US13644573
申请日：2012-10-04
Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
Inventor： Takashi Asahara , Hamaki Inokuchi
IPC: G01P3/36
CPC classification number: G01S17/95 , G01S7/4876 , G01S17/58 , Y02A90/19
Abstract: A colored noise reduction method for an optical remote airflow measurement apparatus, which emits laser light into the atmosphere as a transmission signal and measures a wind speed of an airflow in a remote region on the basis of a Doppler shift amount of a frequency between the transmission signal and a reception signal, includes: considering a signal strength of scattered light to be substantially non-existent in a remotest region and beyond; calculating a noise distribution by performing processing to average the signal strength in respective Doppler frequency components divided at intervals of a certain frequency in the remotest measurement region and beyond, and performing subtraction processing in each of the Doppler frequency components on all signal strength distributions of the measurement region, which are obtained by dividing the noise distribution at intervals of a certain distance.
Abstract translation: 一种用于光学远程气流测量装置的彩色降噪方法，其将激光发射到大气中作为传输信号，并且基于传输之间的频率的多普勒频移量来测量远程区域中的气流的风速 信号和接收信号，包括：考虑到在最远的区域以内基本上不存在散射光的信号强度; 通过对最远的测量区域以外的特定频率的间隔分割的各个多普勒频率成分的信号强度进行平均化处理来计算噪声分布，对所述多普勒频率成分的各信号强度分布进行减法处理 测量区域，其通过以一定距离的间隔分割噪声分布而获得。
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公开(公告)号：US12255397B2
公开(公告)日：2025-03-18
申请号：US17907566
申请日：2022-03-10
Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
Inventor： Toshihiro Sezai
Abstract: An antenna according to an embodiment of the present invention includes a primary radiator and a reflector mirror. The primary radiator radiates radio waves. The reflector mirror reflects radio waves radiated from the primary radiator, has same aperture diameter and height as a parabolic reflector mirror whose aperture diameter is equal to or less than 1.7 times a wavelength of the radio waves, and has a non-parabolic surface as a mirror surface shape.
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公开(公告)号：USD1060002S1
公开(公告)日：2025-02-04
申请号：US29808989
申请日：2021-09-24
Designer： Yutaka Umemura , Takeshi Miyakita , Masanori Saitoh
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公开(公告)号：US20240278913A1
公开(公告)日：2024-08-22
申请号：US18569965
申请日：2022-07-06
Applicant: Japan Aerospace Exploration Agency
Inventor： Daichi WADA , Atsushi OSEDO
CPC classification number: B64C39/026 , B64C3/56 , B64C15/02 , B64D45/00
Abstract: This flight equipment (100) includes a thrust device (10) that provides thrust during flight, wings (20) that maintain an attitude during flight and change a direction of flight, a control unit that controls strength of an output from the thrust device (10), and an attachment and detachment unit (30) that can be worn or removed by a user (H).
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