中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

271 records (took 0.03 seconds)

    스텔스 항공기
    261.
    发明公开
    스텔스 항공기 审中-实审
    STEALTH AERIAL VEHICLE

    公开(公告)号：KR1020120136283A

    公开(公告)日：2012-12-18

    申请号：KR1020120047856

    申请日：2012-05-07

    Applicant: 이에이디에스 도이치란트 게엠베하

    Inventor： 돈왈트,요헨 ,  비츨러,바르솔로메우스

    IPC: B64C1/00 ,  B64C7/00 ,  B64C39/00

    CPC classification number: B64C39/10 ,  B64C25/10 ,  B64C25/16 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/121 ,  B64C2201/22 ,  B64D1/06 ,  B64D7/00 ,  B64D7/02 ,  B64D7/06 ,  B64D27/10 ,  B64D27/14

    Abstract: PURPOSE: A stealth aircraft is provided to optimize a stealth property by always facing a clean second face to radar threat. CONSTITUTION: A stealth aircraft(10) comprises a turbine and bays(20,24). The turbine propels an aircraft having at least one turbine holes(14,16). Other components of the aircraft are received inside the aircraft through the bays. The aircraft is designed to have a small radar signature. The turbine holes and the bays are arranged on a first face(12) of the aircraft. A second face(30) of the aircraft has the small radar signature smaller than the first face.

    Abstract translation: 目的：提供隐形飞机，通过总是面对清洁的第二面对雷达威胁来优化隐形财产。 构成：隐形飞机（10）包括涡轮机和海湾（20,24）。 涡轮驱动具有至少一个涡轮孔（14,16）的飞行器。 飞机的其他部件通过海湾接收在飞机内。 该飞机的设计是具有一个小的雷达签名。 涡轮孔和海湾布置在飞行器的第一面（12）上。 飞机的第二面（30）具有小于第一面的小型雷达标志。

    Automatic armament selection apparatus and method for operating the same of UAV
    262.
    发明授权
    Automatic armament selection apparatus and method for operating the same of UAV 有权
    自动装备选择装置及其操作方法

    公开(公告)号：KR101195909B1

    公开(公告)日：2012-11-05

    申请号：KR20120038015

    申请日：2012-04-12

    IPC: B64D1/00 ,  F41G9/00 ,  H04B7/185

    CPC classification number: B64D1/04 ,  B64C39/024 ,  B64C2201/121 ,  F41G9/02 ,  H04B7/185

    Abstract: PURPOSE: An automatic armament selection apparatus and a method thereof for an armed unmanned aerial vehicle are provided to prevent mission failure due to the fact that an initially selected armament is not launched when a target is certainly attacked because mission is accomplished by selecting loaded armaments capable of automatically launching. CONSTITUTION: An automatic armament selection apparatus for an armed unmanned aerial vehicle comprises a data link part(21), a target detecting part(22), an armament launching determination part(23), and an armament control part(24). The data link part wirelessly communicates with a ground control center. The target detecting part obtains information about the current position and type of targets. The armament launching determination part determines the satisfaction of armament launching conditions. The armament control part selects an initial armament according to missions wirelessly applied from the data link part and locks the initial armament, selected when the armament launching conditions are satisfied, on the current position of the targets. The armament control part resets the armaments when the armament launching conditions are not satisfied. [Reference numerals] (21) Data link part; (22) Target detecting part; (23) Armament launching determination part; (24) Armament control part

    Abstract translation: 目的：提供一种用于武装无人驾驶飞行器的自动装备选择装置及其方法，以防止任务故障，原因是当目标被攻击时，最初选定的装备不被启动，因为任务是通过选择装载的武器来实现的 的自动启动。 构成：一种用于武装无人飞行器的自动装备选择装置，包括数据连接部分（21），目标检测部分（22），装备发射确定部分（23）和武器控制部分（24）。 数据链路部分与地面控制中心无线通信。 目标检测部分获取关于目标的当前位置和类型的信息。 装备发射确定部分决定了装备发射条件的满意度。 装备控制部根据从数据链路部无线应用的任务选择初始装备，并将当装备发射条件满足时选择的初始武器锁定在目标的当前位置。 当装备发射条件不满足时，装备控制部分复位装备。 （附图标记）（21）数据链接部; （22）目标检测部; （23）装备发射确定部分; （24）装备控制部

    화재 진압 드론
    264.
    发明公开
    화재 진압 드론 审中-公开

    公开(公告)号：KR20180066376A

    公开(公告)日：2018-06-19

    申请号：KR20160166847

    申请日：2016-12-08

    Applicant: PARK SEONG YEON

    Inventor： PARK SEONG YEON

    IPC: B64C39/02 ,  A62C3/02 ,  B64D1/06 ,  B64D47/08

    CPC classification number: B64C39/024 ,  A62C3/025 ,  B64C2201/121 ,  B64D1/00 ,  B64D1/06 ,  B64D47/08

    Abstract: 본발명은화재진압드론에관한것이다. 본발명에따른화재진압드론은개방탄을발사하여유리창등을깨뜨린후 소화탄을건물내부로투척하여화재진압을한다. 본발명은개방탄및 소화탄발사시반대방향으로압축공기를발사하여화재진압드론이뒤로밀리는것을방지할수 있다. 본발명의화재진압드론은광센서를이용하여유리창이위치하는지점을정확하게파악할수 있다.

    무장 무인기의 무장 해제 장치 및 무장 해제 방법
    269.
    发明授权
    무장 무인기의 무장 해제 장치 및 무장 해제 방법 有权
    用于组装无人驾驶飞机的装置及其操作方法

    公开(公告)号：KR101209787B1

    公开(公告)日：2012-12-11

    申请号：KR1020120036759

    申请日：2012-04-09

    Applicant: 한화시스템 주식회사

    Inventor： 이동호

    IPC: B64D1/00 ,  B64C19/00 ,  G05B19/04

    CPC classification number: B64D1/04 ,  B64C39/024 ,  B64C2201/121 ,  B64D2045/0085

    Abstract: PURPOSE: A disarming device for unmanned armed aerial vehicles and a disarming method thereof are provided to remove factors which can threat land power when emergency situations are generated during the flight of unmanned armed aerial vehicles. CONSTITUTION: A disarming device for unmanned armed aerial vehicles comprises a data link part(21), a data link monitoring part(22), a body detect monitoring part(23), a flight control part(26), a disarming procedure database(24), and a disarming management part(25). The data link part wirelessly communicates with a ground control center. The data link monitoring part monitors the rupture of data link in real time. The body detect monitoring part monitors the defect of a body containing the malfunction of body components in real time. The flight control part monitors abnormal flight control and abnormal navigation information. The disarming procedure database stores disarming procedures for performing according to each disarming reason. The disarming management part extracts the disarming procedures matched with the generated disarming reasons from the disarming procedure database and blocks disarming power according to the disarming procedures. [Reference numerals] (21) Data link part; (22) Data link monitoring part; (23) Body defect monitoring part; (24) Disarming procedure database; (25) Disarming management part; (26) Flight control part

    Abstract translation: 目的：提供无人驾驶飞行器的解除装置及其解除武装的方法，以便在无人驾驶飞行器飞行期间产生紧急情况时，消除可能威胁土地权力的因素。 规定：无人驾驶飞行器的解除装置包括数据链接部分（21），数据链路监视部分（22），身体检测监视部分（23），飞行控制部分（26），撤防程序数据库 24）和解除管理部分（25）。 数据链路部分与地面控制中心无线通信。 数据链路监控部分实时监控数据链路的破裂。 身体检测监控部分实时监测身体部位故障的身体缺陷。 飞行控制部分监控异常飞行控制和异常导航信息。 撤防程序数据库根据每个撤防原因存储执行程序。 解除武装管理部门从撤防程序数据库中提取与撤销原因相符合的解除武装的程序，并根据撤防程序阻止撤防。 （附图标记）（21）数据链接部; （22）数据链路监控部分; （23）身体缺陷监测部分; （24）撤防程序数据库; （25）解除管理部门; （26）飞行控制部分

    일반폭탄 비행보조체의 비행조종장치 및 방법
    270.
    发明公开
    일반폭탄 비행보조체의 비행조종장치 및 방법 有权
    用于控制用于通用燃料的飞行支持装置的飞行器的装置和方法

    公开(公告)号：KR1020100058052A

    公开(公告)日：2010-06-03

    申请号：KR1020080116721

    申请日：2008-11-24

    Applicant: 국방과학연구소

    Inventor： 윤형식 ,  이광현 ,  이은용

    IPC: F42B15/01 ,  G05D1/00

    CPC classification number: F42B10/60 ,  B64C2201/121 ,  G05D1/105

    Abstract: PURPOSE: A flight control apparatus of a flight assist device for general purpose bombs is provided to improve the accuracy of bomb-dropping by guiding general purpose bombs to a target using a guidance and control program of a flight control computer without an aviator's command. CONSTITUTION: A flight control apparatus of a flight assist device for general bombs comprises an inertia detector(202), a navigation module(203), a bomb drop sensor(204), an unfolded wing sensor(205), and a flight control computer(206). The inertia detector detects the speed and the acceleration of a general purpose bomb. The navigation module provides information for the guidance operation of the general purpose bomb using signals from the inertia detector and a GPS(Global Positioning System). The bomb drop sensor senses the dropping of the general purpose bomb and transmits sensing signals. The unfolded wing sensor senses the unfolding of the left and right main wings of the flight assist device and transmits the sensing signals. The flight control computer receives the sensing signals and generates the operation command of a flaperon actuator(207).

    Abstract translation: 目的：提供用于通用炸弹的飞行辅助装置的飞行控制装置，以通过使用没有飞行员指令的飞行控制计算机的引导和控制程序将通用炸弹引导到目标来提高炸弹的准确性。 构成：用于一般炸弹的飞行辅助装置的飞行控制装置包括惯性检测器（202），导航模块（203），炸弹落下传感器（204），未折叠翼传感器（205）和飞行控制计算机 （206）。 惯性检测器检测通用炸弹的速度和加速度。 导航模块使用来自惯性检测器和GPS（全球定位系统）的信号提供用于通用炸弹导向操作的信息。 炸弹传感器检测到通用炸弹的落下并传输感应信号。 展开的机翼传感器感测飞行辅助装置的左右主翼的展开并传送感测信号。 飞行控制计算机接收感测信号并产生襟副翼致动器（207）的操作命令。

Patent Agency Ranking