公开(公告)号：KR101408073B1

公开(公告)日：2014-06-17

申请号：KR1020130029957

申请日：2013-03-20

Applicant: 국방과학연구소

Inventor： 박영근 ,  이대열 ,  이인원 ,  이기두 ,  임상수

IPC: G05D1/04

CPC classification number: G05D1/101 ,  G05D1/042

Abstract: The present invention relates to a flight altitude control device for an unmanned glide vehicle for enabling an unmanned glide vehicle to reach a ground target point by controlling the altitude of the unmanned glide vehicle if the unmanned glide vehicle is not able to reach the ground target point in a normal flight state since the altitude of the unmanned glide vehicle is excessively raised due to external factors during the flight. According to an embodiment disclosed in the present specification, the flight altitude control device for an unmanned glide vehicle includes: a position detection unit which detect the position of an unmanned glide vehicle in real time; an altitude detection unit which detects the flight altitude of the unmanned glide vehicle; and a control unit which, if the current flight altitude of the unmanned glide vehicle exceeds a predefined flight altitude, controls the unmanned glide vehicle to descend to the predefined flight altitude while circling round and then to fly in a direction towards the ground target point.

Abstract translation: 本发明涉及一种无人滑行车辆的飞行高度控制装置，用于无人滑行车辆无法到达地面目标点时，通过控制无人滑翔车辆的高度，使无人滑行车辆能够到达地面目标点 由于在飞行期间由于外部因素而使无人驾驶车辆的高度过度升高，所以在正常飞行状态。 根据本说明书中公开的实施例，无人滑行车辆的飞行高度控制装置包括：位置检测单元，其实时检测无人滑翔车辆的位置; 高度检测单元，其检测无人滑行车辆的飞行高度; 以及控制单元，如果无人滑行车辆的当前飞行高度超过预定飞行高度，则控制无人滑行车辆在盘旋时向下降到预定飞行高度，然后沿着朝向地面目标点的方向飞行。

公开(公告)号：KR101275099B1

公开(公告)日：2013-06-17

申请号：KR1020110102173

申请日：2011-10-07

Applicant: 국방과학연구소

Inventor： 이기두 ,  이인원 ,  임상수 ,  박영근 ,  김길훈

IPC: B64C13/04 ,  G01G3/14

Abstract: 본 발명의 항공기 조종간 하중 측정장치는 항공기 조종간에 직접 부착되어 상기 조종간의 하중을 감지하는 센서 모듈과, 상기 센서 모듈로부터 출력되는 신호를 처리하는 신호처리 모듈과, 상기 신호처리 모듈로부터 출력되는 데이터를 저장하는 자료저장 모듈을 구비한다.

公开(公告)号：KR100934925B1

公开(公告)日：2010-01-06

申请号：KR1020080092735

申请日：2008-09-22

Applicant: 국방과학연구소

Inventor： 안종민 ,  임상수 ,  권종광

IPC: G06F9/455 ,  G06F9/30 ,  G06F3/0362 ,  G06F15/00

CPC classification number: B64F5/60 ,  G06F9/4812 ,  G08C19/00

Abstract: PURPOSE: A flight control rule software testing device and a method thereof capable of safely converting a flying control between a flying control rule and a test object flying control rule are provided to secure the safety of the flying by securing the characteristics of the flight. CONSTITUTION: A primary FLCC(Flight Control Computer)(110) controls a flight according to a flight control rule converting instruction. An SWMC(Switch Mechanism Computer)(120) computes the SWMC test target flight control rule. An FCTP(Flight Control Test Panel)(130) for the flight control test transmits the flight control rule transfer instruction and all kinds of the control commands with a main part flight control computer.

Abstract translation: 目的：提供一种飞行控制规则软件测试装置及其能够安全地转换飞行控制规则和测试对象飞行控制规则之间的飞行控制的方法，以通过确保飞行特性来确保飞行的安全性。 规定：主要FLCC（飞行控制计算机）（110）根据飞行控制规则转换指令控制飞行。 SWMC（开关机构计算机）（120）计算SWMC测试目标飞行控制规则。 用于飞行控制测试的FCTP（飞行控制测试面板）（130）用主飞行控制计算机发送飞行控制规则传输指令和各种控制命令。

公开(公告)号：KR1020130037761A

公开(公告)日：2013-04-17

申请号：KR1020110102173

申请日：2011-10-07

Applicant: 국방과학연구소

Inventor： 이기두 ,  이인원 ,  임상수 ,  박영근 ,  김길훈

IPC: B64C13/04 ,  G01G3/14

Abstract: PURPOSE: A load measuring device for an aircraft control stick is provided to reduce cost and time required for remodeling an aircraft by quantitatively measuring the load of the aircraft control stick with a direct sensor module. CONSTITUTION: A loading measuring device for an aircraft control stick comprises a sensor module(110), a signal processing module(130), and a data storing module(150). The sensor module is directly attached to an aircraft control stick to load the weight of the aircraft control stick. The signal processing module processes signals outputted from the sensor module. The data storing module stores data outputted from the signal processing module. [Reference numerals] (110) Sensor module; (130) Signal processing module; (134) Power supply; (136) Output terminal; (150) Data storing module; (152) Storage device; (154) Output unit;

Abstract translation: 目的：提供用于飞机控制杆的载荷测量装置，以通过用直接传感器模块定量测量飞行器控制杆的载荷来减少重建飞机所需的成本和时间。 构成：飞行器控制棒的装载测量装置包括传感器模块（110），信号处理模块（130）和数据存储模块（150）。 传感器模块直接连接到飞机控制杆上，以装载飞机控制杆的重量。 信号处理模块处理从传感器模块输出的信号。 数据存储模块存储从信号处理模块输出的数据。 （附图标记）（110）传感器模块; （130）信号处理模块; （134）电源; （136）输出端子; （150）数据存储模块; （152）存储设备; （154）输出单元;