公开(公告)号：KR1020140079174A

公开(公告)日：2014-06-26

申请号：KR1020120148834

申请日：2012-12-18

Applicant: 한국항공우주연구원

Inventor： 김근배 ,  박부민 ,  이보화

IPC: B64C11/32 ,  B64C27/59

Abstract: The present invention relates to a device for controlling the pitch of propeller blades, having simplified components and non-motorized structure. Compared with a traditional technique, the size and weight are reduced, and the manipulation is easy. Regardless of the number of blades, the present invention can be applied to a small airplane or an unmanned aerial vehicle, and is improved of convenience in maintenance.

Abstract translation: 本发明涉及一种用于控制螺旋桨叶片间距的装置，其具有简化的部件和非机动结构。 与传统技术相比，尺寸和重量减少，操作容易。 不管叶片的数量如何，本发明可以应用于小型飞机或无人飞行器，并且提高了维护的便利性。

公开(公告)号：KR1020130073244A

公开(公告)日：2013-07-03

申请号：KR1020110140984

申请日：2011-12-23

Applicant: 한국항공우주연구원

Inventor： 이보화 ,  김춘택 ,  박부민

IPC: H02J7/34 ,  H02J7/35

Abstract: PURPOSE: An active power control system for a hybrid power source and a method thereof are provided to implement a stability of a propulsion system by merging a solar cell, a fuel cell, and a battery. CONSTITUTION: A solar cell changes solar energy into electric energy. A fuel cell (200) changes chemical energy into electric energy. The fuel cell outputs electric power which is necessary for propulsion of a flying object. A battery (300) stores the outputted electric power and outputs if necessary. An electric power management module (400) supplies the outputted electric power to the flying object. [Reference numerals] (100,AA,BB) Solar cell; (200,CC) Fuel cell; (300) Battery; (410) Main control unit; (420) Charge and discharge control unit; (430,DD) DC-DC converter; (500) Motor control unit; (600) Motor

Abstract translation: 目的：提供一种用于混合动力源的有源功率控制系统及其方法，以通过合并太阳能电池，燃料电池和电池来实现推进系统的稳定性。 规定：太阳能电池将太阳能转化为电能。 燃料电池（200）将化学能变成电能。 燃料电池输出用于推进飞行物体所需的电力。 电池（300）存储输出的电力，如果需要输出。 电力管理模块（400）向飞行物提供输出的电力。 （100，AA，BB）太阳能电池; （200，CC）燃料电池; （300）电池; （410）主控单元; （420）充放电控制单元; （430，DD）DC-DC转换器; （500）电机控制单元; （600）电机

公开(公告)号：KR1020100025037A

公开(公告)日：2010-03-09

申请号：KR1020080083635

申请日：2008-08-27

Applicant: 한국항공우주연구원

Inventor： 김형모 ,  박부민 ,  전병호 ,  양수석

IPC: F02C7/00

Abstract: PURPOSE: A cooled window for flame visualization is provided to enable stable flame visualization despite high temperature exposure for long time by installing a heat radiation fin for cooling in a connection part. CONSTITUTION: A visualization window is coupled with the inner circumference of a cyclic casing part(101). A combustion system connection unit(108) is formed inside a casing part. A sealing part(102) is coupled with the outside of the casing part. A cooled air inflow part(103) is formed on the outside of the casing part. A cooled air outflow part(105) is connected to the cooled air inflow part. The visualization window is interposed between the inner area of the casing part and the inner area of the sealing part.

Abstract translation: 目的：提供用于火焰可视化的冷却窗口，以便通过安装用于冷却连接部件的散热片长时间高温暴露来实现稳定的火焰可视化。 构成：可视化窗口与循环壳体部分（101）的内周耦合。 燃烧系统连接单元（108）形成在壳体部分内。 密封部分（102）与壳体部分的外部联接。 冷却空气流入部（103）形成在壳体部的外侧。 冷却空气流出部（105）与冷却空气流入部连接。 可视化窗口插入在壳体部分的内部区域和密封部分的内部区域之间。

公开(公告)号：KR1020090066109A

公开(公告)日：2009-06-23

申请号：KR1020070133730

申请日：2007-12-18

Applicant: 한국항공우주연구원

Inventor： 박부민 ,  김형모 ,  최영호 ,  양수석

IPC: F02C7/14 ,  F02C7/22 ,  F02C7/18

Abstract: A fuel cooling apparatus for a low temperature function test of a gas turbine engine combustor is provided to prevent increase of fuel cost caused by cooling the fuel more than needed. A fuel cooling apparatus for a low temperature function test of a gas turbine engine combustor comprises an air guiding unit(110) and a fuel cooling unit(120). The air conducting unit guides the low temperature air to the combustor(140) entrance of a gas turbine engine. The fuel cooling unit comprises the fuel cooling part(122), the fuel offer part(124), and the fuel supply part(126). The fuel cooling part is equipped inside the air conducting unit. The fuel is cooled in the fuel cooling part through the heat transmission with the low temperature air. The fuel offer part is connected to one end of the fuel cooling part. The fuel offer part provides the fuel to the fuel cooling part.

Abstract translation: 提供了一种用于燃气涡轮发动机燃烧室的低温功能试验的燃料冷却装置，以防止由于燃料冷却而导致的燃料成本增加超过所需燃料。 一种用于燃气涡轮发动机燃烧室的低温功能试验的燃料冷却装置包括空气引导单元（110）和燃料冷却单元（120）。 导气单元将低温空气引导到燃气涡轮发动机的燃烧器（140）入口。 燃料冷却单元包括燃料冷却部分（122），燃料供应部分（124）和燃料供应部分（126）。 燃料冷却部件配备在导气单元的内部。 通过与低温空气的热传递，燃料在燃料冷却部件中被冷却。 燃料供应部分连接到燃料冷却部分的一端。 燃料供应部分向燃料冷却部分提供燃料。