• Title/Summary/Keyword: flight software

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A Study of the Boot ROM S/W Design and Verification for the Next Generation LEO Satellite (차세대 저궤도 위성의 Boot ROM 소프트웨어 설계 및 검증에 대한 연구)

  • Choi, Jong-Wook;Lee, Jae-Seung;Yang, Seung-Eun;Shin, Hyun-Kyu;Chae, Dong-Seok;Lee, Jong-In
    • Aerospace Engineering and Technology
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    • v.7 no.1
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    • pp.83-90
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    • 2008
  • The next generation LID satellite has 64KB PROM which contains the boot loader and the monitor software, and two 4MB NVMEMs which are used for flight software storage. The boot loader has two operation modes which are the flight software mode and the monitor mode. In the flight software mode, it checks CRC checksum of selected NVMEM and copies flight software image from NVMEM to RAM And then it starts VxWorks RTOS in RAM, creates flight software tasks, and starts execution of flight software. In the monitor mode, it activates monitor software which performs NVMEM reprogramming and board-level testing on the ground. This paper is to present the design of Boot ROM software and verification method using simulator.

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

  • Oh, Soo Hun
    • Journal of the Korean 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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    • 2008.10a
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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).

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.

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 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 Attitude Estimation of UAV Using Image Processing (영상 처리를 이용한 UAV의 자세 추정에 관한 연구)

  • Paul, Quiroz;Hyeon, Ju-Ha;Moon, Yong-Ho;Ha, Seok-Wun
    • Journal of Convergence for Information Technology
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    • v.7 no.5
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    • pp.137-148
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    • 2017
  • Recently, researchers are actively addressed to utilize Unmanned Aerial Vehicles(UAV) for military and industry applications. One of these applications is to trace the preceding flight when it is necessary to track the route of the suspicious reconnaissance aircraft in secret, and it is necessary to estimate the attitude of the target flight such as Roll, Yaw, and Pitch angles in each instant. In this paper, we propose a method for estimating in real time the attitude of a target aircraft using the video information that is provide by an external camera of a following aircraft. Various image processing methods such as color space division, template matching, and statistical methods such as linear regression were applied to detect and estimate key points and Euler angles. As a result of comparing the X-plane flight data with the estimated flight data through the simulation experiment, it is shown that the proposed method can be an effective method to estimate the flight attitude information of the previous flight.