公开(公告)号：KR1020040004955A

公开(公告)日：2004-01-16

申请号：KR1020020039198

申请日：2002-07-08

Applicant: 한국항공우주연구원

Inventor： 안이기 ,  유창선 ,  주광혁 ,  유혁

IPC: B64D43/00

Abstract: PURPOSE: A pressure sensor is used to measure pressure difference between both wings of an airplane, thereby measuring position angle of the wings. CONSTITUTION: More than two pressure measuring members(10) are installed in both wings of an airplane through atmosphere connection pipes(2,3). A loaded computer(4) is installed to calculate position angle with the measured pressure of the pressure measuring members.

Abstract translation: 目的：使用压力传感器来测量飞机两翼之间的压力差，从而测量机翼的位置角度。 构成：通过大气连接管（2,3），两个以上的压力测量部件（10）安装在飞机的两翼上。 装载的计算机（4）被安装以用测量的压力测量构件的压力来计算位置角度。

公开(公告)号：KR1020030054450A

公开(公告)日：2003-07-02

申请号：KR1020010084611

申请日：2001-12-26

Applicant: 한국항공우주연구원

Inventor： 박무혁 ,  안이기

IPC: G05B19/00

CPC classification number: G05D1/0011 ,  B64C39/024 ,  B64C2201/146 ,  G05B11/28 ,  G05B11/40

Abstract: PURPOSE: A PWM(Pulse Width Modulation) signal source switching circuit for controlling servo motors of an unmanned plane and a model plane is provided to perform safely a flying test by using a PWM signal as a driving signal. CONSTITUTION: A PWM signal source switching circuit includes a computer signal input portion(10), a remote signal input portion(20), a switching sense portion(30), and a switch(40). The computer signal input portion receives control signals from a model plane and an unmanned plane. The remote signal input portion receives a remote control signal from a remote controller. The switching sense portion senses a PWM control signal of the remote signal input portion. The switch is used for outputting selectively signals of the computer signal input portion and the remote signal input portion to a servo output portion(50).

Abstract translation: 目的：提供用于控制无人机平面和模型平面的伺服电机的PWM（脉宽调制）信号源切换电路，通过使用PWM信号作为驱动信号，安全执行飞行测试。 构成：PWM信号源切换电路包括计算机信号输入部分（10），远程信号输入部分（20），开关感测部分（30）和开关（40）。 计算机信号输入部分从模型平面和无人机平面接收控制信号。 远程信号输入部分从遥控器接收遥控信号。 切换感测部分感测远程信号输入部分的PWM控制信号。 该开关用于选择性地将计算机信号输入部分和远程信号输入部分的信号输出到伺服输出部分（50）。

公开(公告)号：KR1020000067382A

公开(公告)日：2000-11-15

申请号：KR1019990015141

申请日：1999-04-28

Applicant: 한국항공우주연구원

Inventor： 임철호 ,  염찬홍 ,  남기욱 ,  황창전 ,  안이기

IPC: B64B1/10

Abstract: PURPOSE: An airship direction control system is provided to control the direction of an airship by periodically varying the current speed of a propeller and asymmetrically generating the rear current speed of the propeller. CONSTITUTION: Blades(8,8'), rods(10,10') for varying a pitch angle and an upper plate(11) for controlling a variable pitch angle rotate with a rotary shaft(7). A lower plate(12) for controlling a variable pitch angle does not rotate. In this state, when inclination is applied in a desired direction, the length of the rods(10,10') is fixed so that the pitch angle of the blades(8,8') is varied. In addition, in equally varying the pitch angle of the blades, a collective pitch angle increase plate(13) is moved along a rotary shaft(7).

Abstract translation: 目的：提供飞艇方向控制系统，以通过周期性地改变螺旋桨的当前速度并且不对称地产生螺旋桨的后方当前速度来控制飞艇的方向。 构成：用于改变桨距角的叶片（8,8'），杆（10,10'）和用于控制可变桨距角的上板（11）与旋转轴（7）一起旋转。 用于控制可变桨距角的下板（12）不旋转。 在这种状态下，当沿期望的方向施加倾斜时，杆（10,10'）的长度被固定，使得叶片（8,8'）的俯仰角变化。 此外，在等效地改变叶片的俯仰角的同时，沿着旋转轴（7）移动集体俯仰角增加板（13）。