• Title, Summary, Keyword: flight software

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Software Design and Verification Method of Flight Data Recorder for Unmanned Aerial Vehicle (무인항공기용 비행자료 기록장치 소프트웨어 설계 및 검증 방안)

  • Yang, Seo-hee
    • Journal of Advanced Navigation Technology
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    • v.24 no.3
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    • pp.163-172
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    • 2020
  • Flight data recorder (FDR) for accident investigation is required to comply with EUROCAE(ED-112) standard so that flight data can be restored when exposed to extreme conditions due to aircraft crash. Since the ED-112 standard defines the general requirements for all aircraft, it is essential to analyze detailed requirements for FDR software to apply appropriate requirements selectively according to the configuration and operation concept of a specific aircraft. In this paper, the software requirements applicable to unmanned aircraft will be analyzed and the FDR software design will be proposed. Also, a software verification method for each requirement will be presented to verify that the implemented software is designed to satisfy all requirements.

A Study of the flight s/w test environment for the LEO satellite (저궤도위성 탑재소프트웨어 시험환경에 대한 연구)

  • Chae, Dong-Seok;Lee, Jae-Seung;Choi, Jong-Wook;Yang, Seung-Eun;Lee, Jong-In
    • Aerospace Engineering and Technology
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    • v.6 no.2
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    • pp.45-51
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    • 2007
  • The various levels of test are performed to verify the correctness, completeness, and quality of the developed flight software. The three main test levels are unit test, integration test and verification test. The flight software unit test is performed on the individual PC environment using target simulator. And integration and verification test is mainly performed on STB(S/W Test Bed) which provides test and debugging environments for flight software on the target board This document is to present the test environment for the next generation low earth orbit satellite flight software development.

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Flight Software Reprogramming for Next Generation LEO Satellites (차세대 저궤도 위성의 비행소프트웨어 리프로그래밍)

  • Yoo, Bum-Soo;Jeong, Jae-Yeop;Choi, Jong-Wook
    • Journal of Satellite, Information and Communications
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    • v.12 no.3
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    • pp.93-97
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    • 2017
  • In satellites, even a small error in flight software could cause a failure of missions. Therefore, there are strict development and verification processes for a high reliability of flight software. However, satellites on orbits could meet unexpected situations including hardware malfunction. In this case, it is necessary for flight software to be updated to cope with the unexpected situations and to continue their missions. This paper reviews reprogramming capability of next generation LEO satellites.

States and Modes Analysis for Flight Control of Smart UAV (스마트 무인기 비행제어 상태/모드 분석)

  • Oh, Soo Hun
    • Journal of the Korea Society of Systems Engineering
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    • v.1 no.2
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    • pp.43-48
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    • 2005
  • This paper describes the results of applying States and Modes Analysis, one of the requirements analysis techniques, to the development requirements of flight control software for Smart UAV. State/mode table enabled us to investigate various operation and design concepts, and as a result essential requirements for flight control software were established without omitting necessary requirements. Through the use of scenario-specific state transition diagrams, dynamic behaviours and control/response interfaces between each state and mode could been clearly identified, which made it possible to establish requirements related to dynamic behaviours of states and modes which are essential to the design of flight control software.

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CHANGES OF SOFTWARE UNIT TESTING TOOL - ATTOL TO TESTRT

  • Paek, Su-Hyun;Kang, Soo-Yeon;Yang, Koon-Ho;Choi, Seong-Bong
    • Proceedings of the KSRS Conference
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    • pp.84-87
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    • 2008
  • ATTOL is a software unit testing tool produced by the ATTOL Testware SA in France. It automates the entire software unit testing process: test plan template and test program generation, test program execution, test result analysis and test report generation. ATTOL is suited for the development of embedded software as it allows programmers to operate in native and cross development environments. Particularly, it is used for the development of the flight software which is embedded in the Communication Ocean Meteorological Satellite (COMS). As the flight software is mission-critical, it requires the strict software quality and high testing constraints. The flight software of COMS is verified by ATTOL in native and cross platforms. In 2002, ATTOL was taken over by the IDM Rational Software and has been supplied with the name of Test RealTime (TestRT). The test process of TestRT becomes different from that of ATTOL as TestRT provides the new functionalities that were absent from ATTOL. TestRT provides the new features in the test script language, as well. In this paper, we compare the test process of ATTOL to TestRT With an example of COMS and explain what has been changed in the test script language.

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A Study on Software Based Fault-Tolerance Techniques for Flight Control Computer (비행조종컴퓨터 소프트웨어 기반 고장허용 설계 기법 연구)

  • Yoon, Hyung-Sik;Kim, Yeon-Gyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.3
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    • pp.256-265
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    • 2016
  • Software based fault tolerance techniques are designed to allow a system to tolerate software faults in the system. Fault tolerance techniques are divided into two groups : software based fault tolerance techniques and hardware based fault tolerance techniques. We need a proper design method according to characteristics of the system. In this paper, the concepts of software based fault tolerance techniques for Dual Flight Control Computer are described. For software based fault tolerance design, we classified software failure, designed a way for failure detection and the way of recovery. Eventually the effectiveness of software based fault tolerance techniques was verified through the Software Test Environment(STE).

Development of UAV Flight Control Software using Model-Based Development(MBD) Technology (모델기반 개발기술을 적용한 무인항공기 비행제어 소프트웨어 개발)

  • Moon, Jung-Ho;Shin, Sung-Sik;Choi, Seung-Kie;Cho, Shin-Je;Rho, Eun-Jung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.12
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    • pp.1217-1222
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    • 2010
  • This paper describes the Model-Based Development(MBD) process behind the flight control software of a close-range unmanned aerial vehicle(KUS-9). An integrated development environment was created using a commercial tool(MATLAB $Simulink^{(R)}$), which was utilized to design models for linear/nonlinear simulation, flight control law, operational logic and HILS(Hardware In the Loop Simulation) system. Software requirements were validated through flight simulations and peer reviews during the design process, whereas the models were verified through the application of a DO-178B verification tool. The integrity of automatically generated C code was verified by using a separate S/W testing tool. The finished software product was embedded on two different types of hardware and real-time operating system(uC/OS-II, VxWorks) to perform HILS and flight tests. The key findings of this study are that MBD Technology enables the development of a reusable and an extensible software product and auto-code generation technology allows the production of a highly reliable flight control software under a compressed time schedule.

A Study on the Conversion Time to Minimize of Transient Response during Inter-Conversion between Control Laws (제어법칙 간 상호 전환 시 과도응답 최소화를 위한 전환시간에 관한 연구)

  • Kim, Chongsup
    • Journal of Aerospace System Engineering
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    • v.9 no.1
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    • pp.12-18
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    • 2015
  • The inter-conversion between different control laws in flight has a lot of risk. The SWM(Switching Mechanism) including logic and stand-by mode is designed to analyze the transient response of aircraft during inter-conversion between different control laws, based on the in-house software for non-real-time and real-time simulation. The SWM applies the fader logic of TFS(Transient Free Switch) to minimize the transient response of an aircraft during the inter-conversion, and applies the reset '0' type of the stand-by mode to prevent surface saturation due to integrator effect in the disengaged flight control law. The transition time is also important to minimize the objectionable transient response in the inter-conversion, as well as the transition control law design. This paper addresses the results of non-real-time simulation for the characteristics of transient response to different transition time to select the adequate transient time, and the real-time pilot evaluation, using SSWM(Software Switching Mechanism) and HSWM(Hardware Switching Mechanism), which is met for Level 1 flying qualities and assures safety of flight.

Introduction to Automatic Generation of Design Documents for Flight Software using Doxygen (Doxygen을 이용한 위성비행소프트웨어 설계문서 작성 자동화 방안 소개)

  • Lee, Jae-Seung;Yang, Seung-Eun;Choi, Jong-Wook;Cheon, Yee-Jin;Yun, Jeong-Oh
    • Proceedings of the Korea Information Processing Society Conference
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    • pp.844-847
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    • 2012
  • 인공위성의 개발은 오랜 기간에 걸쳐 다양한 분야의 전문가들에 의해 개발된 결과물들이 통합되어 완성될 수 있다. 위성개발과 같이 많은 개발자가 공동으로 작업하여 하나의 결과물을 생산하는 경우 개발과정에서 방대한 양의 문서작업이 수반된다. 특히 비행소프트웨어와 같이 서로 다른 개발자에 의해 작성된 코드들이 하나의 이미지로 통합되어 빌드될 경우 발생하는 문제점들을 해결하고 요구되는 기능들을 디버깅하기 위해서는 개발과정 및 소스코드에 대한 문서들이 필수적이다. 이러한 소프트웨어 설계에 대한 문서는 그 양이 방대하고 소스코드와의 연계성이 필요하기 때문에 소스코드를 작성한 각 개발자들이 직접 수작업으로 문서를 작성하였다. 예를 들면, 기존의 위성비행소프트웨어 개발과정에서는 이러한 문서들 중 전체 위성비행소프트웨어의 단위 코드별 입출력, 수행기능 등의 상세 설계 내용을 기록하는 SDD(Software Design Description)는 개발자가 작성한 코드를 기반으로 수작업을 통하여 작성되었다. 이러한 작성방식은 작성자의 입력오류가 발생할 수도 있으며 소프트웨어 개발과 별도로 수작업이 요구되어 문서작성에 소요되는 시간적 손해가 발생하게 된다. 유럽에서는 이러한 문제점을 보완하기 위하여 C, C++, C#, JAVA, VHDL 등 다양한 언어를 사용하는 소프트웨어 개발에 적용 가능한 자동적 문서작성 도구인 Doxygen을 설계 및 개발문서 작성에 활용하고 있다. Doxygen은 PDF, HTML, Latex, RTF 등 다양한 출력 포맷도 지원한다. 본 논문에서는 Doxygen을 활용하여 위성비행소프트웨어 개발문서의 작성 시 소요시간을 단축하고 소스코드로부터 해당 설계 내용을 추출하여 자동적으로 문서를 작성할 수 있는 방안에 대하여 소개한다.

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A Study of Data Slaving Software Module for Instrumentation Systems on Multi-Target Environment (다중표적 환경에서 추적시스템을 위한 연동 소프트웨어 모듈 연구)

  • Oh, Se-Jin
    • Journal of the Korea Institute of Military Science and Technology
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    • v.14 no.4
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    • pp.622-629
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    • 2011
  • In this paper, you can see the structure of data slaving software module that is in use on flight test and result of the test with the slaving. The data slaving software module has many functions, data slaving for various instrumentation systems(instrumentation radars, telemetry systems for missile, aircraft and so on), setting some slaving group for multi-target, communicating with the instrumentation systems in a far away site and sending a specific value as slaving data. This fits the requests for flight test that is being performed and improves performance of the instrumentation systems.