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 |
|---|---|---|---|---|---|---|
| 21 | Methods of laser powering unmanned aerial vehicles with heat engines | US15009080 | 2016-01-28 | US09920706B1 | 2018-03-20 | Dmitriy Yavid; Stephen Jon Blank |
| Methods of laser powering unmanned aerial vehicles (UAV) with heat engines are disclosed. The laser powered heat engines are used in conjunction with devices for absorbing laser optical radiation, turning the laser optical radiation into heat, supplying the heat to a working fluid of the heat engine and harvesting mechanical work from expanding working fluid in the heat engine. | ||||||
| 22 | Hybrid propulsion power system for aerial vehicles | US14867152 | 2015-09-28 | US09376214B2 | 2016-06-28 | Ankita Ghoshal |
| This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles. The hybrid propulsion system includes a combustor, a thermophotovoltaic generator, and a thermoelectric generator. The combustor burns a chemical based fuel to produce radiation and heat that are converted into electricity used to power the aerial vehicle. The thermophotovoltaic generator is positioned to receive radiation and remnant heat generated by flames in the combustor while the thermoelectric generator receives heat from exhausted flue gases from the combustor. | ||||||
| 23 | Unmanned aerial vehicle angular reorientation | US14016602 | 2013-09-03 | US09211947B2 | 2015-12-15 | Carlos Miralles |
| A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | ||||||
| 24 | AIRCRAFT WITH FREEWHEELING ENGINE | US14251850 | 2014-04-14 | US20140367509A1 | 2014-12-18 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 25 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION | US14016602 | 2013-09-03 | US20140172200A1 | 2014-06-19 | Carlos Miralles |
| A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | ||||||
| 26 | AIRCRAFT WITH FREEWHEELING ENGINE | US13442544 | 2012-04-09 | US20120234968A1 | 2012-09-20 | FRICK A. SMITH |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 27 | MULTI-ROTOR AERIAL VEHICLE | EP15854629 | 2015-10-28 | EP3212502A4 | 2018-04-04 | LJUNG ANDERS |
| Multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″), wherein the control of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31. | ||||||
| 28 | 멀티 로터 항공기 | KR1020177014767 | 2015-10-28 | KR1020170101200A | 2017-09-05 | 엘정,앤더스 |
| 멀티로터항공기(1, 1', 1", 1"', 1"", 1""', 1""")로서, 각각이전용제1, 제2, 및제3 유압모터(11, 21, 31)에의해회전가능한적어도제1, 제2, 및제3 로터(10, 20, 30), 동력유닛(2), 상기각각의제1, 제2, 및제3 유압모터(11, 21, 31)에전용되는적어도제1, 제2, 및제3 유압펌프(12, 22, 32), 여기서, 상기각 유압펌프(12, 22, 32)는유압모터(11, 21, 31)에동력을공급하여각각의로터(10, 20, 30)를회전시키는각각의유압모터(11, 21, 31)에가압유체를제공하도록배치됨, 상기멀티로터항공기(1, 1', 1", 1"',1"",1""',1""")의작동을제어하기위한제어유닛(6)을포함하고, 상기멀티로터항공기(1, 1', 1", 1"', 1"", 1""', 1""")의제어는각각의유압모터(11, 21, 31)에분배된가압유체의흐름을변경함으로써수행되도록배치되고, 상기각각의유압모터(11, 21, 31)에제공된가압유체의흐름은각각의유압펌프(12, 22, 32)로부터전용유압모터(11, 21, 31)로의가압유체의흐름을제어하도록구성된적어도하나의제어밸브(13, 23, 33)에의해각각제어가능하다. | ||||||
| 29 | 다용도 지역감시, 촬영, 정찰 및 통신용 수직이착륙무인전동비행체 | KR1020000014650 | 2000-03-22 | KR1020010092603A | 2001-10-26 | 권데이비드철 |
| PURPOSE: A multi-purpose unmanned aircraft for local monitoring, taking pictures, watching and communication is provided to promote long-time specific local monitoring and watching impossible for an airplane or a helicopter by improving the structure for vertical rising and falling as well as flight at a standstill. CONSTITUTION: An unmanned aircraft(1) is fixed as each ring hinged from a foothold portion in the center of a truck is connected to four hooks under the aircraft. To launch the unmanned aircraft, a worker unlocks the four hooks from the rings of the foothold. Then, the worker sets a multi-step aircraft control switch on a control console to a lower step of falling and turns on a power switch. A motor(3) of the unmanned aircraft is driven and blades(2) connected to the motor are rotated at the minimum speed. The rotation speed of the blades rises up slowly when the worker changes the multi-step aircraft control switch to a higher step of rising from the lower step of falling. The lift force of the unmanned aircraft rises up gradually and the unmanned aircraft is lifted vertically. In addition, the unmanned aircraft can fly at a standstill when the control switch is fixed by a locking bar at the desired height. The unmanned aircraft is useful for long-time local monitoring, taking pictures and watching. Therefore, the unmanned aircraft promotes the maximum efficiency and good points in cost to effect. | ||||||
| 30 | 재난 구조 장치 | KR20160093081 | 2016-07-22 | KR20180010637A | 2018-01-31 | |
| 상기과제를해결하기위한본 발명의실시예에따른재난구조장치는재난이벤트가발생한경우상기재난이벤트가발생한재난현장으로이동하기위한동력을제공하는구동부; 상기이동과정중에상기재난현장에속하는재난자를탐색하고, 상기탐색된재난자의생체신호를감지하는센서부; 상기감지된생체신호를기초로상기탐색된재난자의현재상태를판단하는재난자상태판단부및 상기판단된현재상태에따라상기재난자에대하여수행할구호조치를상이하게판단하는동작판단부를포함하는제어부; 및상기제어부의제어에따라상기재난자에게대피방법을안내하는지도를표시하는화면부를포함한다. | ||||||
| 31 | 3절 링크를 이용한 날개 구동 장치 | KR1020030046082 | 2003-07-08 | KR1020050006376A | 2005-01-17 | 박지형; 이광락; 김광호 |
| PURPOSE: A blade apparatus and an airplane thereof are provided to freely fly in any directions by realizing the motion of a bird or an insect's wings. CONSTITUTION: A driving apparatus comprises an actuator(101), a 3-fold-linkage(102), a guide cylinder(103), a driving arm(104) and a vertical guide slot(13). The actuator is fixed in a frame(106). The 3-link is moved by receiving the force and the displacement through the actuator. The one end of the 3-fold-linkage is fixed in the frame. The guide cylinder forms a passage to slide the other end of the 3-fold-linkage by inserting the other end of the 3-fold-linkage. The driving arm is fixed in the 3-fold-linkage. The vertical guide slot is formed by vertically connecting between an upper frame and a lower frame of the frame. An airplane to freely flap, lag and hover is realized by connecting two driving apparatuses through a coupling. | ||||||
| 32 | 촬영용 무인 헬리콥터 | KR1020000033013 | 2000-06-15 | KR1020010112782A | 2001-12-22 | 이종국; 홍성표 |
| The invention comprises the use of compounds of formula (I) wherein the dotted line represents an optional bond; X is oxygen or sulfur; R 1 is hydrogen, C 1-12 alkyl, Ar 1, Ar 2 C 1-6 alkyl, quinolinylC 1-6 alkyl, pyridylC 1-6 alkyl, hydroxyC 1-6 alkyl, C 1-6 alkyloxyC 1-6 alkyl, mono- or di(C 1-6 alkyl)aminoC 1-6 alkyl, aminoC 1-6 alkyl, or a radical of formula -Alk 1 -C(=O)-R 9, -Alk 1 -S(O)-R 9 or -Alk 1 -S(O) 2 -R 9 ; R 2, R 3 and R16 each independently are hydrogen, hydroxy, halo, cyano, C 1-6 alkyl, C 1-6 alkyloxy, hydroxyC 1-6 alkyloxy, C 1-6 alkyloxyC 1-6 alkyloxy, aminoC 1-6 alkyloxy, mono- or di(C 1-6 alkyl)aminoC 1-6 alkyloxy, Ar 1, Ar 2 C 1-6 alkyl, Ar 2 oxy, Ar 2 C 1-6 alkyloxy, hydroxycarbonyl, C 1-6 alkyloxycarbonyl, trihalomethyl, trihalomethoxy, C 2-6 alkenyl; R 4 and R 5 each independently are hydrogen, halo, Ar 1, C 1-6 alkyl, hydroxyC 1-6 alkyl, C 1-6 alkyloxyC 1-6 alkyl, C 1-6 alkyoloxy, C 1-6 alkylthio, amino, hydroxycarbonyl, C 1-6 alkyloxycarbonyl, C 1-6 alkylS(O)C 1-6 alkyl or C 1-6 alkylS(O) 2 C 1-6 alkyl; R 6 and R 7 each independently are hydrogen, halo, cyano, C 1-6 alkyl, 4,4-dimethyl-oxazolyl, C 1-6 alkyloxy or Ar 2 oxy; R 8 is hydrogen, C 1-6 alkyl, cyano, hydroxycarbonyl, C 1-6 alkyloxycarbonyl, C 1-6 alkylcarbonylC 1-6 alkyl, cyanoC 1-6 alkyl, C 1-6 alkyloxycarbonylC 1-6 alkyl, carboxyC 1-6 alkyl, hydroxyC 1-6 alkyl, aminoC 1-6 alkyl, mono- or di(C 1-6 alkyl)aminoC 1-6 alkyl, imidazolyl, haloC 1-6 alkyl, C1-6 alkyloxyC 1-6 alkyl, aminocarbonylC 1-6 alkyl, or a radical of formula -O-R 10, -S-R 10, -N-R 11 0 12 ; R 17 is hydrogen, halo, cyano, C 1-6 alkyl, C 1-6 alkyloxycarbonyl, Ar 1 ; R 18 is hydrogen, C 1-6 alkyl, C 1-6 alkyloxy or halo; R 19 is hydrogen or C 1-6 alkyl; for the manufacture of a medicament to inhibit smooth muscle cell proliferation. | ||||||
| 33 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION | PCT/US2012027619 | 2012-03-02 | WO2012119132A3 | 2014-04-24 | MIRALLES CARLOS |
| A system comprising an unmanned aerial vehicle (UAV) (100) having wing elements (141, 142) and tail elements (143, 144) configured to roll to angularly orient the UAV (100) by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor (940) a boresight angle error correction value (850) bases on distance between a target point (812) and a boresight point (820) of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point (812) to a re-oriented target point (814) in the body-fixed frame, to maintain the offset angle via (850) the offset angle correction value. | ||||||
| 34 | 무인 비행체 및 그의 비행 방법 | KR1020170149260 | 2017-11-10 | KR101899408B1 | 2018-09-17 | 임성혁; 천세범; 허문범 |
| 본발명은무인비행체및 그의비행방법에관한것으로, 본발명에따른무인비행체는자기장을발생시키는자기장발생부, 그리고무인비행체가전력전송선로아래에서비행할경우무인비행체와전력전송선로사이에인력이발생되도록제어하고, 무인비행체가전력전송선로위에서비행할경우무인비행체와전력전송선로사이에척력이발생되도록제어하는제어부를포함한다. 본발명에의하면, 무인비행체가전력전송선로아래를비행할경우무인비행체와전력전송선로사이에인력을발생시키고, 무인비행체가전력전송선로위를비행할경우무인비행체와전력전송선로사이에척력을발생시킴으로써전력전송선로주변을비행하는무인비행체의에너지효율을크게향상시킬수 있다. | ||||||
| 35 | 개량형 하이브리드 드론 | KR1020180036411 | 2018-03-29 | KR101895366B1 | 2018-09-05 | 이호형; 이완형 |
| 본발명은주축방향으로설치되는동체(100); 상기동체(100)에직각축방향으로결합되어보조날개(210)와플랩(230)이설치된주익(200); 상기주익(200)의좌측및 우측에주축방향으로각각설치된 2개의모터튜브프레임(800); 후방에서상기 2개의모터튜브프레임(800)을연결하여결합되어엘리베이터(310)가설치된수평안정판(300); 상기모터튜브프레임(800) 후방상부에결합되어러더(410)가설치된수직안정판(400); 을포함하여구성되되, 상기동체(100) 후단에는엔진으로구동되는주프로펠러(700)가설치되고, 상기모터튜브프레임(800) 전단과후단에는각각모터로구동되는전방프로펠러(500)와후방프로펠러(600)가설치되는것을특징으로하는개량형하이브리드드론을제공한다. | ||||||
| 36 | 꽃가루 비행 분사장치 | KR1020170064042 | 2017-05-24 | KR101828830B1 | 2018-02-13 | 장명동 |
| 본발명은수집된꽃가루를비행부를통해공중에서균일하게분사하여꽃가루의소모량및 분사작업을편리하도록하며, 빠르게꽃가루를분사하여식물이수분되도록하는꽃가루비행분사장치에관한것으로서, 수집된꽃가루가저장되며, 상부에입구가형성되고, 하부에토출구가형성되는저장부; 상기저장부의토출구와결합되어토출구를통해토출되는꽃가루를분사부로이송시키는이송부; 상기이송부를통해이송되는꽃가루를바람을통해하부로분사되도록하는분사부; 상기저장부, 이송부및 분사부가연결되어무선조종신호를통해저장부, 이송부및 분사부의작동을제어하는제어부; 상기저장부, 이송부및 분사부가결합되며, 무선조종신호를수신받아비행할수 있는비행부및 상기비행부를무선조종신호로조종하며, 비행부에서송신되는비행부의상태신호및 촬영신호를무선신호로전송하며, 상기저장부, 이송부및 분사부의구동을제어하는조종부를포함하는것을특징으로한다. | ||||||
| 37 | 무인 비행체의 멀티 로터 프레임 및 이를 이용한 프레임의 조립 방법 | KR1020150020731 | 2015-02-11 | KR1020160099137A | 2016-08-22 | 현명택; 양정환 |
| 본발명은개선된무인비행체의멀티로터프레임및 이를이용한프레임의조립방법에관한것으로, 중공형의메인플레이트와상기메인플레이트상부에다수개의고정핀을구비한본체부; 상기본체부의고정핀을관통하여일측단이결합된다수개의붐; 상기본체부와상기붐을고정시키는커버부; 를포함하여이루어지는것을특징으로하는무인비행체의멀티로터프레임에관한것이다. 또한, 중공형의메인플레이트와상기메인플레이트상부에다수개의고정핀을구비한본체부; 상기본체부의고정핀을관통하여일측단이결합된다수개의붐; 상기본체부와상기붐을고정시키는커버부; 를포함하여이루어지는것을특징으로하는무인비행체의멀티로터프레임에따른멀티로터프레임에구동또는제어를위한컨트롤러, 전자모듈, 엔진, 모터, 프로펠러, 배터리, 짐벌장치및 촬영장치를더 포함하여이루어지는것을특징으로하는멀티로터프레임을포함한무인비행체에관한것이다. 또한, (a) 중공형의메인플레이트와상기메인플레이트상부에다수개의고정핀을구비한본체부의상부에상기본체부의고정핀과결합가능하도록일단에하나이상의통공이있는붐을상하직선운동으로상기고정핀을관통하여결합하는단계; (b) 상기붐의상부에상기고정핀을관통하여결합되는중공형의고정커버를상하직선운동으로상기고정핀을관통하여결합하는단계; 및 (c) 상기고정커버상부에고정링으로고정시키는단계; 를포함하여이루어지는것을특징으로하는무인비행체의멀티로터프레임조립방법에관한것이다. | ||||||
| 38 | 무인 항공기 하이브리드 동력 시스템 및 동력 제어 방법 | KR1020140184419 | 2014-12-19 | KR1020160075020A | 2016-06-29 | 박준석 |
| 본발명은무인항공기하이브리드동력시스템및 동력제어방법에관한것으로서, 본발명에따른무인항공기동력시스템은무인항공기에전력을공급하는전원부; 상기무인항공기에추진력을부여하는부스터(booster); 및상기무인항공기의이륙시에는상기부스터가동력을제공하도록하는부스터동작모드를활성화하고, 상기무인항공기가미리정해진고도에진입한이후에는상기부스터동작모드를비활성화하고, 상기전원부로부터의전력을기반으로하는모터부의작동을통해운행되는전원동작모드를활성화하는동력제어모듈을포함하는것을특징으로한다. 이와같이, 부스터동작모드와전원동작모드의하이브리드동력모드를채용함으로써, 전력공급원의수명을연장할수 있고, 무인항공기의운행시간및 운행거리를연장할수 있는효과가있다. | ||||||
| 39 | 자유로운 날갯짓을 구현하는 날개 구동 장치 | KR1020030046081 | 2003-07-08 | KR1020050006375A | 2005-01-17 | 박지형; 이광락 |
| PURPOSE: A blade apparatus and an air vehicle thereof are provided to realizing the motion of flapping, lagging, feathering as the motion of a bird or an insect's wings. CONSTITUTION: A blade apparatus comprises a pair of blades(11), flapping guide slot and a lagging guide slot. The flapping guide slot moves vertically by inserting shafts of each blade. The lagging guide slot moves horizontally by inserting the shafts of each blade. In operating horizontal and vertical force to the ends of the shafts while inserting the ends of the shafts into the guide slots sequentially, the other ends of the shafts are rotated in an oval. A pair of reciprocation apparatuses and couplings are added. The reciprocation apparatuses are crossed at a certain angle by putting in a parallel plane. The couplings connect the ends of the reciprocation apparatuses with the shafts of the blades. Thereby, an airplane to be freely flown upward, downward, frontward and backward is realized. | ||||||
| 40 | 압전 엑추에이터를 이용한 날개 구동 장치 | KR1020030046080 | 2003-07-08 | KR1020050006374A | 2005-01-17 | 박지형; 이광락 |
| PURPOSE: A driving apparatus and an air vehicle are provided to make a flying object fly upward, downward, frontward and backward freely by realizing the motion of a bird or an insect's wings. CONSTITUTION: A flapping apparatus(300) and a lagging apparatus(400) comprise driving arms, rotors, piezoelectric actuators, housings, insertion grooves and guide slots respectively. The driving arms generate flapping or lagging displacement by adding force to the end of blades. The rotors rotate the driving arms vertically or horizontally. The piezoelectric actuators rotate the rotors by forming driving grooves in the rotors and inserting in the driving grooves. The housings store the rotors. The insertion grooves are formed in the housings to insert the piezoelectric actuators. The guide slots guide flapping or lagging movement passages of the blades by the driving arms. Thereby, an airplane to be freely flown upward, downward, frontward and backward is realized. | ||||||
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