公开(公告)号：KR1020040018614A

公开(公告)日：2004-03-04

申请号：KR1020020050004

申请日：2002-08-23

Applicant: 한국항공우주연구원

Inventor： 정석훈 ,  이창호 ,  김형진 ,  양수석 ,  이대성

IPC: B64C15/00

CPC classification number: B64C15/12 ,  F16H1/06

Abstract: PURPOSE: A thrust vector control system for an aircraft is provided to improve reliability by transmitting the accurate thrust deflection angle to a controller with using a position sensor, and to control precisely and reduce take-off and landing distance by controlling the direction with rotating a propeller disk. CONSTITUTION: A thrust vector control system is composed of a rotating part(1) of the thrust vector control system connected to a motor or an engine and rotated with an internal spur gear; a fixing part(2) of the thrust vector control system connected to the rotating part by a bearing(3), composed of a pinion gear engaged with the internal spur gear and connected to the servo motor through a shaft, and fixed to the outer shell of an aircraft; and a position sensor(4) connected to the rotating part of the thrust vector control system by a position sensor motion transmission shaft(5) to indicate thrust vector.

Abstract translation: 目的：提供一种用于飞机的推力矢量控制系统，以通过使用位置传感器将精确的推力偏转角传递给控制器​​来提高可靠性，并通过旋转方向控制方向来精确控制并降低起飞和着陆距离 螺旋桨盘 构成：推力矢量控制系统由与马达或发动机连接的推力矢量控制系统的旋转部分（1）组成，并与内部正齿轮一起旋转; 推力矢量控制系统的固定部分（2）由轴承（3）连接到旋转部分，由与内部正齿轮啮合并通过轴连接到伺服电动机的小齿轮组成，并固定到外部 飞机外壳; 以及位置传感器（4），其通过位置传感器运动传递轴（5）连接到推力矢量控制系统的旋转部分，以指示推力矢量。

公开(公告)号：KR100472560B1

公开(公告)日：2005-03-08

申请号：KR1020020050004

申请日：2002-08-23

Applicant: 한국항공우주연구원

Inventor： 정석훈 ,  이창호 ,  김형진 ,  양수석 ,  이대성

IPC: B64C15/00

Abstract: 본 발명은 비행선구조물에 추력편향장치를 설치하여 비행선의 저속 조종성 및 이착륙거리 단축을 위하여 필요한 추력편향(벡터추력)기능을 구현하기 위한 장치로 추력을 발생시키는 프로펠러 디스크를 회전시켜 원하는 방향의 추력을 얻기 위한 비행선용 추력편향장치에 관한 것이다.
이러한 본 발명은 모터 또는 엔진에 연결되며 내접 스퍼어기어와 함께 회전되는 추력편향장치 회전부와,
상기 추력편향장치 회전부와 베어링으로 연결되며 내접 스퍼어기어에 내접된 피니언기어가 샤프트를 통하여 서보모터에 연결되고 비행선 외피에 고정되는 추력편향장치 고정부와,
상기 추력편향장치 회전부와 포지션 센서용 움직임 전달용 축으로 연결되어 추력방향을 알려주는 포지션 센서로 구성됨을 특징으로 하는 것이다.

公开(公告)号：KR100436178B1

公开(公告)日：2004-06-16

申请号：KR1020020050002

申请日：2002-08-23

Applicant: 한국항공우주연구원

Inventor： 정석훈 ,  이창호 ,  김형진 ,  양수석 ,  이대성

IPC: B64D27/24

CPC classification number: Y02T50/62

Abstract: PURPOSE: An aircraft propulsion system using electric energy is provided to improve responsiveness by detecting the present condition of the propulsion system accurately and quickly with a propulsion controller. CONSTITUTION: An aircraft propulsion system comprises a gas turbine engine(3) driving by receiving fuel from a fuel tank(2); a generator(4) connected to a rotating shaft of the gas turbine engine to generate power; a power control unit(5) supplying power from the generator to units with converting properly, performing self-diagnosis on output of the generator and load connection, and supplying electric energy by automatically converting into the emergency battery in cutting off power; a propulsion controller(6) transmitting the command to units by receiving signals from a flight control unit(7), and transmitting information on the propulsion system to the flight control unit; the flight control unit transmitting information from the propulsion controller to a pilot, and controlling the propulsion controller; a motor driver(8) regulating rpm and output of a main motor(9) according to the control signal by receiving power from the power control unit; a tilt servo motor(10) driving a thrust vector controller according to the control signal by receiving power; a start battery(11) starting the engine according to the control signal; an emergency battery(12) supplying minimum power till landing in cutting off main power; a battery charger/discharger(13) charging and discharging the batteries; and an ECU(14) controlling the engine to receive power by transmitting information to the gas turbine engine, and transmitting the state of the gas turbine engine to the propulsion controller.

Abstract translation: 目的：提供一种利用电能的飞机推进系统，以通过推进控制器准确快速地检测推进系统的当前状况来提高响应性。 构成：飞机推进系统包括通过接收来自燃料箱（2）的燃料驱动的燃气涡轮发动机（3）; 与燃气涡轮发动机的旋转轴连接并发电的发电机（4） 功率控制单元（5），用于从发电机向正常转换的单元供电，对发电机的输出和负载连接进行自诊断，并通过在切断电源时自动转换成应急电池来供应电能; 推进控制器（6），通过从飞行控制单元（7）接收信号向单元发送命令，并且将关于推进系统的信息传送给飞行控制单元; 所述飞行控制单元从所述推进控制器向驾驶员传输信息，并且控制所述推进控制器; 电动机驱动器（8），通过接收来自所述电力控制单元的电力，根据所述控制信号来调节主电动机（9）的转速和输出; 倾斜伺服电机（10），通过接收电力根据控制信号驱动推力矢量控制器; 根据控制信号启动发动机的启动电池（11） 应急电池（12），用于在切断主电源之前提供最小功率直到着陆; 电池充电器/放电器（13），对电池充电和放电; 和控制发动机通过向燃气涡轮发动机传输信息来接收动力并将燃气涡轮发动机的状态传输到推进控制器的ECU（14）。

公开(公告)号：KR1020040018612A

公开(公告)日：2004-03-04

申请号：KR1020020050002

申请日：2002-08-23

Applicant: 한국항공우주연구원

Inventor： 정석훈 ,  이창호 ,  김형진 ,  양수석 ,  이대성

IPC: B64D27/24

CPC classification number: Y02T50/62

Abstract: PURPOSE: An aircraft propulsion system using electric energy is provided to improve responsiveness by detecting the present condition of the propulsion system accurately and quickly with a propulsion controller. CONSTITUTION: An aircraft propulsion system comprises a gas turbine engine(3) driving by receiving fuel from a fuel tank(2); a generator(4) connected to a rotating shaft of the gas turbine engine to generate power; a power control unit(5) supplying power from the generator to units with converting properly, performing self-diagnosis on output of the generator and load connection, and supplying electric energy by automatically converting into the emergency battery in cutting off power; a propulsion controller(6) transmitting the command to units by receiving signals from a flight control unit(7), and transmitting information on the propulsion system to the flight control unit; the flight control unit transmitting information from the propulsion controller to a pilot, and controlling the propulsion controller; a motor driver(8) regulating rpm and output of a main motor(9) according to the control signal by receiving power from the power control unit; a tilt servo motor(10) driving a thrust vector controller according to the control signal by receiving power; a start battery(11) starting the engine according to the control signal; an emergency battery(12) supplying minimum power till landing in cutting off main power; a battery charger/discharger(13) charging and discharging the batteries; and an ECU(14) controlling the engine to receive power by transmitting information to the gas turbine engine, and transmitting the state of the gas turbine engine to the propulsion controller.

Abstract translation: 目的：提供使用电能的飞机推进系统，以通过用推进控制器准确，快速地检测推进系统的现状来提高响应性。 构成：飞机推进系统包括通过从燃料箱（2）接收燃料而驱动的燃气涡轮发动机（3）; 连接到所述燃气涡轮发动机的旋转轴以产生动力的发电机（4） 从发电机向正确转换的单元供电的电力控制单元（5），对发电机的输出和负载连接进行自诊断，以及通过在切断电力时自动转换为紧急电池来供电; 推进控制器（6），通过从飞行控制单元（7）接收信号将命令发送到单元，以及将关于推进系统的信息传送到飞行控制单元; 所述飞行控制单元将信息从所述推进控制器发送到飞行员，并且控制所述推进控制器; 电动机驱动器（8），其通过从所述功率控制单元接收电力来根据所述控制信号调节转速和主电动机（9）的输出; 倾斜伺服电动机（10），通过接收功率根据控制信号驱动推力矢量控制器; 启动电池（11），根据控制信号启动发动机; 紧急电池（12），其在切断主电源时提供最低功率直至着陆; 电池充电器/放电器（13）对电池充电和放电; 以及ECU（14），其通过向燃气涡轮发动机发送信息来控制发动机接收动力，并将所述燃气涡轮发动机的状态传递到所述推进控制器。