• Title/Summary/Keyword: 추력 자세각 명령

Search Result 6, Processing Time 0.031 seconds

High-Altitude Terminal Guidance and Control Loop Design Using Thrust Vector Control (추력벡터제어를 이용한 고고도 종말 유도조종 루프 설계)

  • Jeon, Ha-Min;Park, Jongho;Ryoo, Chang-Kyung
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.50 no.6
    • /
    • pp.393-400
    • /
    • 2022
  • The Divert and Attitude Control System(DACS) used in high-altitude engagements is expensive and complex. In this paper, we design a high-altitude terminal guidance and control loop of guided-missile equipped with a Thrust Vector Control(TVC) that is less expensive and simpler than DACS. The proposed system utilizes a quaternion feedback control technique to track the thrust attitude command converted from the acceleration command of true proportional navigation guidance. The performance analysis of the proposed terminal guidance and control loop is conducted through engagement simulations against ballistic targets at a high altitude.

Trajectory Optimization and Guidance for Terminal Velocity Constrained Missiles (종말 속도벡터 구속조건을 갖는 유도탄의 궤적최적화 및 유도)

  • Ryoo, Chang-Kyung;Tahk, Min-Jea;Kim, Jong-Han
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.32 no.6
    • /
    • pp.72-80
    • /
    • 2004
  • In this paper, the design procedure of a guidance algorithm in the boosting phase of missiles with free-flight after thrust cut-off is introduced. The purpose of the guidance is to achieve a required velocity vector at the thrust cut-off. Trajectory optimizations for four cost functions are performed to investigate implementable trajectories in the pitch plane. It is observed from the optimization results that high angle of attack maneuver in the beginning of the flight are required to satisfy the constraints. The proposed guidance algorithm consists of the pitch program to produce open-loop pitch attitude command and the yaw attitude command generator to nullify the velocity to go. The pitch program utilizes the pitch attitude histories obtained from the trajectory optimization.

Research for Thrust Distribution Method of DACS for Response to Pintle Actuating Failure (DACS 추진기관의 핀틀 구동장치 고장을 허용하는 추력 분배기법 연구)

  • Ki, Taeseok
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.21 no.5
    • /
    • pp.61-70
    • /
    • 2017
  • Robust thrust distribution method of solid DACS is researched. For the case of the system which has higher number of actuation nozzles than the degree of freedom of thrust to be controlled, the robust thrust allocation law which accommodate the abnormal operation is suggested. Assuming the situation that some nozzles are uncontrollable, the error between nozzle throat area command and response can be calculated. The error is used for realtime reshaping of weighting matrix. From the weighting effect, the nozzle which operated abnormally has low responsibility for the command then, the thrust error is reduced. The suggested algorithm is verified by the simulation of abnormal operation condition of DCS and ACS nozzle respectively.

고기동 위성의 자세제어계 하드웨어 초기운용 성능 분석

  • Im, Jo-Ryeong;Yun, Hyeong-Ju;Park, Geun-Ju;Kim, Yong-Bok;Seo, Hyeon-Ho;Choe, Hong-Taek
    • The Bulletin of The Korean Astronomical Society
    • /
    • v.37 no.2
    • /
    • pp.166.2-166.2
    • /
    • 2012
  • 국내에서 개발한 고기동 저궤도 위성이 일본 다네가시마 우주센터에서 2012년 5월 18일 발사되었다. 자세제어계는 위성의 임무수행을 완수할 수 있도록 발사 후부터 위성 수명 기간 동안 자세명령을 생성하고 제어 및 결정을 하며, 궤도 조정과 모멘텀 덤핑등의 임무를 수행한다. 이러한 임무 수행을 가능하게 하기 위해 자세제어계는 적절한 센서와 구동기 조합을 사용하여 추력기 기반 안전모드, 궤도 조정을 위한 Del-V Burn 기동 모드, 태양지향 서브모드 및 목표지향 서브모드 등을 설계했다. 고기동 위성의 초기 운용 중 자세제어계는 자세제어계 하드웨어의 초기 구동 및 점검을 수행하고 설계한 각 모드의 기능과 성능 확인을 수행하게 된다. 본 연구는 성공적으로 완료한 자세제어계 하드웨어의 초기 점검 결과를 소개하는 것이 목적이다. 초기 운용은 위성이 발사된 직후 탑재컴퓨터가 깨어나면서부터 시작되는데, 발사 후 최초 접속시 추력기 기반 안전모드에서 태양 획득 성능 및 제어 성능을 확인한 후 정상 상태 모드인 태양지향 자세로 전환하기 위해 자세제어계 하드웨어인 별 추적기, 자기토커, 반작용휠의 초기 구동 및 점검을 수행하였다. 본 연구에서는 각 하드웨어의 초기 구동 점검과 성능 및 기능 요구조건 만족에 대한 성능 분석 결과를 정리하였다.

  • PDF

Pressure Guidance and Thrust Allocation Law of Solid DACS (고체 추진 DACS의 압력 유도 및 추력 분배기법)

  • Park, Iksoo;Hong, Seokhyun;Ki, Taeseok;Park, Jungwoo
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.19 no.2
    • /
    • pp.9-16
    • /
    • 2015
  • The control law for simultaneous pressure and thrust control of solid DACS(Divert Attitude Control System) is suggested. To regulate the two variables effectively, the control structure of sequential loop closer is applied to the system considering the physical characteristics of each variable and the weighted pseudo-inverse method is suggested to allocate effective command for indeterminate system. Also, the pressure guidance law for safe and high acceleration is applied to the homing stage to verify the effectiveness of the command distribution.

Nonlinear Acceleration Controller Design for DACS Type Kill Vehicle (DACS형 직격요격비행체의 비선형 가속도 조종루프 설계)

  • Lee, Chang-Hun;Kim, Tae-Hun;Jun, Byung-Eul
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.19 no.3
    • /
    • pp.54-64
    • /
    • 2015
  • This paper deals with an acceleration controller design for a kill vehicle equipped with a divert and attitude control system (DACS). In the proposed method, the attitude control system (ACS) is used to produce the thrust command to nullify angle-of-attack. For the angle-of-attack control, a nonlinear angle-of-attack controller is proposed based on the feedback linearization methodology. Since the flight path angle is identical to the attitude angle under the condition of zero angle-of-attack, the divert control system (DCS) can directly produce the lateral acceleration which is demanded from the guidance loop. In the proposed method, we can minimize the aerodynamic uncertainty due to the propulsive force. Additionally, we can simplify the operation logic of DCS and ACS. In this paper, nonlinear simulations are performed to show the performance of the proposed method.