• Title, Summary, Keyword: flight software

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Development of Distributed Generic Simulator (GenSim) through Invention of Simulated Network (simNetwork)

  • Koo, Cheol-Hea;Lee, Hoon-Hee;Cheon, Yee-Jin
    • Journal of Astronomy and Space Sciences
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    • v.28 no.3
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    • pp.241-252
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    • 2011
  • A simulated network protocol provides the capability of distributed simulation to a generic simulator. Through this, full coverage of management of data and service handling among separated simulators is achieved. The distributed simulation environment is much more conducive to handling simulation load balancing and hazard treatment than a standalone computer. According to the simulated network protocol, one simulator takes on the role of server and the other simulators take on the role of client, and client is controlled by server. The purpose of the simulated network protocol is to seamlessly connect multiple simulator instances into a single simulation environment. This paper presents the development of a simulated network (simNetwork) that provides the capability of distributed simulation to a generic simulator (GenSim), which is a software simulator of satellites that has been developed by the Korea Aerospace Research Institute since 2010, to use as a flight software validation bench for future satellite development.

Flight Control System Design and Verification Process (비행제어시스템 설계 및 검증 절차)

  • Kim, Chong-Sup
    • Journal of Institute of Control, Robotics and Systems
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    • v.14 no.8
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    • pp.824-836
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    • 2008
  • Relaxed static stability(RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. Therefore, flight control systems are necessary to stabilize an unstable aircraft, and provides adequate handling qualities and achieve performance enhancements. Standard FCSDVP (Flight Control System Design and Verification Process) is provided to reduce development period of the flight control system. In addition, if this process is employed in developing flight control system, it reduces the trial and error for development and verification of flight control system. This paper addresses the flight control system design and verification process for the RSS aircraft utilizing design goal based on military specifications, linear and nonlinear system design and verification based on universal software, handling quality test based on HILS(Hardware In-the-Loop Simulator) environment, and ground and flight test results to verify aircraft dynamic flight responses.

SMI Compatible Simulation Scheduler Design for Reuse of Model Complying with SMP Standard

  • Koo, Cheol-Hea;Lee, Hoon-Hee;Cheon, Yee-Jin
    • Journal of Astronomy and Space Sciences
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    • v.27 no.4
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    • pp.407-412
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    • 2010
  • Software reusability is one of key factors which impacts cost and schedule on a software development project. It is very crucial also in satellite simulator development since there are many commercial simulator models related to satellite and dynamics. If these models can be used in another simulator platform, great deal of confidence and cost/schedule reduction would be achieved. Simulation model portability (SMP) is maintained by European Space Agency and many models compatible with SMP/simulation model interface (SMI) are available. Korea Aerospace Research Institute (KARI) is developing hardware abstraction layer (HAL) supported satellite simulator to verify on-board software of satellite. From above reasons, KARI wants to port these SMI compatible models to the HAL supported satellite simulator. To port these SMI compatible models to the HAL supported satellite simulator, simulation scheduler is preliminary designed according to the SMI standard.

A Study on the Design of Hardware Switching Mechanism using TCP/IP Communication (TCP/IP를 이용한 하드웨어 전환장치 설계에 관한 연구)

  • Kim, Chong-Sup;Cho, In-Je;Lim, Sang-Soo;Ahn, Jong-Min;Kang, Im-Ju
    • Journal of Institute of Control, Robotics and Systems
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    • v.13 no.7
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    • pp.694-702
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    • 2007
  • The SSWM(Software Switching Mechanism) of I-processor concept using non-real time in-house software simulation program is an effective method in order to develop the flight control law in desktop or HQS environment. And, this system has some advantages compare to HSWM(Hardware Switching Mechanism) such as remove the time delay effectiveness and reduce the costs of development. But, if this system loading to the OFP(Operational Flight Program), the OFP guarantee the enough throughput in order to calculate the two control law at once. Therefore, the HSWM(Hardware Switching Mechanism) of 2-processor concept is necessary. This paper addresses the concept of HSWM of the HQS-PC interface using TCP/IP(Transmission Control Protocol/Internet Protocol) communication based on flight control law of advanced supersonic trainer. And, the fader logic of TFS(Transient Free Switch) and stand-by mode of reset '0' type are designed in order to reduce the abrupt transient response and minimize the integrator effect in pitch axis. The result of the analysis based on HQS pilot simulation using HSWM reveals that the flight control systems are switching between two computers without any problem.

Method of Conducting and Verification for Failure Mode Effect Test of Rotary Automatic Flight Control System Software (회전익 자동비행제어시스템 소프트웨어의 FMET 수행 및 검증 방안)

  • Yeom, WooSung;Ha, Seokwun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.1
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    • pp.55-62
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    • 2020
  • It is necessary to develop digital flight control system by digital control technology to ensure stability and maneuverability of rotary helicopter. It is important to meet functional requirements of helicopter flight control system OFP and verify system reliability directly linked to flight safety as a core technology that avoids the transfer of technology by overseas advanced helicopter manufacturer. In this paper, we studied how to perform FMET for operational flight program of rotary automatic flight control system.

Design of Flight Software for Heater Control in LEO Satellites (저궤도 관측위성의 히터제어를 위한 위성비행소프트웨어 설계)

  • Lee, Jae-Seung;Shin, Hyun-Kyu;Choi, Jong-Wook;Cheon, Yee-Jin
    • Aerospace Engineering and Technology
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    • v.10 no.1
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    • pp.141-148
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    • 2011
  • LEO satellites have many heaters for thermal control, such as bus module heaters, payload heaters and battery internal heaters. Some of these heaters are controlled by thermisters, and others can be controlled by flight software. These heaters are divided into various types of group according to the location, telemetry variables, flight software logic, power distribution, etc. Thus, it is difficult to find out which heaters are included in a certain group and modify heater control logic for a new/other software developers. This document describes about the general/special control logic for satellite heaters and groups/arrays for heaters.

Development of drone flight control system using marker image processing technique (마커 영상처리기술을 이용한 드론 비행 제어 시스템 개발)

  • Yun, Tae-Jin;Jang, Jae-Ho;Ok, Ung-Seok;Kim, Jong-In;Choi, Da-Young
    • Proceedings of the Korean Society of Computer Information Conference
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    • pp.131-132
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    • 2020
  • 본 논문에서는 OpenCV의 Marker Detection 기술을 이용하여 특정지점의 마커를 영상처리기술로 인식하여 드론의 자동 이착륙 및 주변 위기상황, 미션수행 등을 마커를 통해서 드론에게 전달하여 비행 제어할 수 있는 체계를 개발한다. 드론은 OpenCV Aruco모듈을 이용하여 Marker ID별로 특정 명령어를 데이터 베이스와 비교하여 비행제어 명령을 수행한다. 지상에서는 마커의 변경을 통해서 실시간으로 미션변경을 할 수 있다. 이를 통해 드론은 제어용 송수신 채널을 통해서 통신을 하고는 있으나, 주파수 채널수가 제한이 되어 있으므로 구체적인 비행 제어 명령을 마커를 통해 이착륙시 추가적이며, 자동적인 진행이 가능하다.

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Introduction to the COMS Flight Software (천리안 위성 비행소프트웨어 소개)

  • Kang, Soo-Yeon;Koo, Cheol-Heo;Park, Su-Hyun
    • Proceedings of the Korea Information Processing Society Conference
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    • pp.76-79
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    • 2011
  • 천리안 위성은 우리나라 최초의 정지궤도 복합 지구관측 위성으로 기상관측, 해양관측과 통신서비스 임무를 수행하는 중대형위성으로 2011년 6월 27일에 성공적으로 발사되어 약 6개월간의 시험운영기간을 거쳐 현재는 실시간 서비스를 제공하고 있다. 천리안 위성은 한국항공우주연구원(KARI) 총괄 주관하에 2003년 9월 개발을 시작으로 프랑스의 EADS-Astrium과 공동 개발되었다. 천리안 위성은 이미 EADS-Astrium에 의해 통신 위성 본체 플랫폼으로 우주 인증된 Eurostar3000(이하 E3000) 플랫폼을 근간으로 제작되었다. 본 논문에서는 천리안 위성 플랫폼 탑재컴퓨터에 탑재되어 위성체 전반을 운영하는 비행소프트웨어의 구성 및 기능에 대해 기술한다. 또한 기존의 EADS-Astrium사의 E3000 비행소프트웨어 생산라인을 바탕으로 천리안 위성 비행소프트웨어를 개발하기 위한 개발 절차 형상을 소개한다. 본 논문에서 기술한 재생산을 위한 개발 절차에 대한 접근 방법은 위성 임베디드 소프트웨어 시스템과 같은 mission critical 시스템이면서 이미 검증된 소프트웨어를 재사용하고 사용자의 요구사항을 만족시키기 위해 일부 기능을 변경 및 추가 개발하여 통합된 소프트웨어를 생산해야하는 소프트웨어 개발체계의 실질적인 한 예를 보여주고 있다.

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Development of Ground Control Software Platform for Industrial Application with Multiple small UAVs (복수 소형무인비행체 산업 응용을 위한 지상관제소프트웨어 플랫폼 개발)

  • Lim, Bae-Hyeon;Ha, Seok-Wun;Moon, Yong-Ho
    • Journal of Convergence for Information Technology
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    • v.7 no.5
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    • pp.75-82
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    • 2017
  • Recently, as the roles and utilization fields of UAV become more diverse, demand for high - level mission has been increasing. To solve this issue, researches on the operation of multiple small UAVs and related systems have been actively carried out. The multiple small UAVs based application system has a problem that the task complexity of control personnel increases because the control personnel must continuously control and manage several small UAVs. Hence, it is necessary to develop a software platform that can perform efficient control in order to employ a multiple small UAVs based application system successfully. In this paper, we propose an effective ground control software platform for application systems using multiple small UAVs. We first analyze the requirements for the software platform, and design and implement software based on the analysis. Simulation using the X-plane flight simulator shows that multiple flight data are effectively displayed and that the image data transmitted from many small UAVs are simultaneously displayed in real time.

Command Generator / Telemetry Analyzer

  • 강수연
    • Proceedings of the Korean Information Science Society Conference
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    • pp.230-232
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    • 1999
  • KOMPSAT(KOrea Multi-Purpose SATEllite) Flight Software[2]의 개발 단계에서 통합 및 시험, 검증 시험을 위해 실제 시스템과 유사한 환경을 제공하는 개발도구로서 STB(Software Test BED)를 개발하였으며 STB 구성중에서 Command/Telemetry (CMD/TLM) 테스트를 위해 개발한 Command Generator / Telemetry Analyzer에 관한 내용을 본 논문에서 설명하고자 한다. 통신간에 사용되는 프로토콜은 [1]에서 언급한 바와 같이 CCSDS 프로토콜을 따르고 모든 관련된 Command 와 Telemetry 형식 또한 [1]에서 언급한 바와 같다. 이 구현된 소프트웨어를 이용하여 Flight Soaftware내의 CMD/TLM 처리 소프트웨어의 기능시험과 검증시험을 수행하였다.

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