Abstract:
본 발명은 고체모터 추진기관의 시험평가장치에 관한 것으로서, 보다 상세하게는 고체모터 연소특성 및 가동노즐의 비선형 운동특성과 연계된 구동장치 시스템의 기능 및 성능 특성을 용이하게 시험할 수 있고 평가할 수 있는 추력벡터 제어용 구동장치를 위한 시험평가장치에 관한 것이다. 본 발명은 추력벡터 제어용 구동장치를 위한 시험평가장치에 있어서, 지면에 고정안치되는 시험장치프레임; 상기 시험장치프레임 상부에 안치되는 고체모터의 후방부돔에 장착되는 가동노즐 연결디스크, 상기 가동노즐 연결디스크 하면에 장착되는 플렉스실 조인트, 상기 플렉스실 조인트 하면에 위치하며 상기 고체모터 후방부돔에 장착되는 후방부돔연결디스크, 및 상기 가동노즐 연결디스크에 결합되는 가동노즐로 구성되는 노즐부; 상기 노즐부와 연결되는 링크부; 상기 링크부에 연결되어 상기 링크부를 작동시키며, 상기 시험장치프레임에 고정결합되는 공압작동부; 및 상기 공압작동부와 연결되어 상기 공압작동부를 제어하는 제어부;로 구성된 것을 특징으로 한다.
Abstract:
PURPOSE: A GPS receiver having three radio frequency receiving ends is provided to calculate navigation information of a scientific sounding rocket and a satellite launch vehicle by using a received satellite signal. CONSTITUTION: Antennas(12-14) installed at intervals of 120 degrees on a surface of a scientific sounding rocket and a satellite launch vehicle receive satellite signals. Radio frequency receiving ends(1-3) convert the satellite signals received by the antennas(12-14) into baseband frequency and output it as digital data. Correlators(4-6) sample satellite signals which have been converted into the digital data, correlate satellite signals generated from the correlators themselves according to the received satellite signals and a control signal transferred through an interface circuit(7) from a CPU(8), and process them. The CPU(8) calculates information required for satellite navigation by using a satellite signal which has passed the interface circuit(7) after being outputted from the correlators(4-6), transmits a control signal that can construct a satellite tracking loop to the correlators(4-6), and handles external inputting/outputting.
Abstract:
PURPOSE: A servo driving apparatus of a gimbal engine driving device is provided to remove the reciprocal interference effect by installing a spherical joint at an earth end part and a load end part and forming a universal joint with a gimbal structure. CONSTITUTION: An engine mount(3) is placed above a gimbal engine(1). A pitch axis controller(4) is installed at a pitch axis and a main axis controller(5) is installed at a main axis. A piston is installed in a cylinder. A load end bearing connected to the pitch axis or flank axis is provided in the piston. A magnet is fixed to an inner end of the piston. An earth end assembly is connected to the cylinder through a knuckle ring. A position detecting sensor is installed in a housing. A spherical joint is used in the load end bearing and the earth end assembly, and a universal joint is used in a gimbal engine shaft(2). A center axis of the load end bearing is connected to the engine mount(3).
Abstract:
PURPOSE: A dynamic stiffness measuring system is provided to easily measure dynamic stiffness of an electric-hydraulic position servo operating system by generating disturbance load using a hydraulic servo operating system. CONSTITUTION: A dynamic stiffness measuring system includes a load actuator(1), a position servo actuator(4) and a frequency characteristic analyzer(7). The load actuator(1) is provided at a front portion thereof with a load cell(2) and is connected to a load servo controller(3) so as to generate a minute movement displacement. The servo actuator(4) is connected to the load cell(2) in order to fix a control input signal of a position servo controller(6) to a zero signal. The frequency characteristic analyzer(7) is connected to a displacement measuring sensor(5) and the load cell(2) so as to calculate dynamic stiffness. A linear guide is provided to guide and measure a linear movement between the load cell(2) and the position servo actuator(4).
Abstract:
본 발명에 따르면, 힘전달 경로 상의 기계적 요소와 고립된 유압작동유기둥의 개별 강성값의 조합을 이용하여 상기 서보구동기(2)가 갖는 무한주파수 강성을 예측하는 무한주파수 강성 측정부; 인장 및 압축부하 경로 상에 위치하는 단순한 기계적 형상 구동기 구성요소의 개수를 고려하여 초기 구성요소의 등가강성값을 할당하고 해석식에 의하여 구성요소의 주요 치수를 설계하는 치수설계부; 구동기 해당 구성요소에 의하여 설계된 확장 및 수축 유압격실 작동유기둥의 등가강성값을 설계하는 등가강성값 설계부; 및 설계한 기계적 구성요소들과 작동유기둥의 등가강성을 조합하여 구동기의 무한주파수 강성값을 설계하는 무한주파수 강성설계부;를 포함하는 제어강성 요구조건을 충족시키는 구동기 설계시스템을 개시한다.
Abstract:
본 발명에 따르면, 서보작동기에 장착된 압력센서에 의해 상기 서보작동기 내의 실린더 확장격실의 압력 및 실린더 수축격실의 압력이 각각 측정되는 실린더 압력측정 단계; 상기 실린더 확장격실의 압력값과 실린더 수축격실의 압력값이 합산기로 전달되어 압력차 신호가 생성되는 압력차 신호 생성 단계; 상기 압력차 신호는 고주파 통과 필터로 전달되어, 상기 고주파 통과 필터의 절점 주파수(ω cf )보다 낮은 대역을 갖는 압력차 신호는 감쇠되며, 상기 고주파 통과 필터의 절점 주파수(ω cf )보다 높은 대역을 갖는 압력차 신호는 상기 고주파 통과 필터를 통과하여 동적압력 되먹임 제어기 이득값(k DPF )과 곱해져서 동적압력 되먹임 제어신호를 생성하는 동적압력 되먹임 제어신호 생성 단계; 및 상기 동적압력 되먹임 제어신호는 위치 오차신호와 상호 상쇄되어, 서보앰프로 전달되는 합성 오차신호의 크기가 감소됨으로써 상기 서보작동기의 동작을 제한시키는 공진 억제 단계;를 포함하는 위치서보 비행제어 구동장치시스템의 공진 억제 제어기법이 개시된다. 서보작동기, 고주파 통과 필터, 동적압력
Abstract:
PURPOSE: A device and a method for measuring thrust are provided to accurately measure thrust even if a shaft for a thruster is not the same as a shaft for the device and to easily obtain calibration data for measuring thrust. CONSTITUTION: A device for measuring thrust comprises a thruster adapter(110), a second base(120), a measuring load cell(130), a calibrating load cell, and a controller. The thruster adapter is composed of a fixing member which fixes a thruster(200). The second base is installed in the bottom of the thruster adapter and is horizontally moved on a first base. The measuring load cell has a measuring load cell bar and a measuring adapter. The calibrating load cell gas a calibrating load cell bar(141) and a calibration adapter(143). The controller calculates and corrects an error value of the measuring load cell.
Abstract:
PURPOSE: A resonance suppression control technique of precision position servo flight control actuator system is provided to facilitate the selection of a controller variable by applying a dynamic pressure feedback control technique. CONSTITUTION: A resonance suppression control technique of precision position servo flight control actuator system is as follows. The pressure of a cylinder expansion compartment and that of a cylinder contraction compartment in a servo actuator(2) are measured. The pressure(15) of the cylinder expansion compartment and the pressure(16) of the cylinder contraction compartment are delivered to an adder and a pressure difference signal is generated. The pressure difference signal is delivered to a high pass filter(17). A pressure difference signal having a band lower than the corner frequency of the high pass filter is attenuated. A pressure difference signal having a band higher than the corner frequency of the high pass filter passes through the high pass filter and is multiplied by a dynamic pressure feedback controller gain value(18) to generate a dynamic pressure feedback control signal. The dynamic pressure feedback control signal is offset by a position error signal and the size of the synthesized error signal delivered to a servo amp(12) diminishes. The operation of a servo actuator is suppressed.
Abstract:
PURPOSE: A patch type antenna device for mounted on the cylinder is provided to prevent the deformation of the signal quality of the patch type antenna by mounting the external side of the cylindrical gas in the flat state of the patch type antenna. CONSTITUTION: A base(120) adheres closely to one side of a cylinder(200). A patch type antenna(110) is installed inside the base. A plurality of joint grooves A is formed in one side of the cylinder. A fastener A is formed at corresponding location to the joint groove A. The fastener A is inserted into the joint groove A. An insertion unit(130) is inserted to an insertion hole(210) formed in the one side of the cylinder. One side of the insertion unit is combined in the lower surface of the base. A space unit having the fixed size is formed inside the insertion unit. The active antenna module or the signal-connected passive antenna module is installed with the patch type antenna in the space unit.