• Title, Summary, Keyword: flight software

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Development & Verification of On-Board Flight Software on Software-based Spacecraft Simulator (소프트웨어 기반의 위성 시뮬레이터를 이용한 위성 탑재소프트웨어 개발 및 검증 방안)

  • Choi, Jong-Wook;Shin, Hyun-Kyu;Lee, Jae-Seung;Cheon, Yee-Jin
    • Journal of Satellite, Information and Communications
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    • v.5 no.2
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    • pp.1-7
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    • 2010
  • For many years the development and verification of on-board flight software have been essentially performed on STB (Software Test Bed) environments which consist of real hardware in KARI. During development of on-board flight software on STB, we experienced many difficulties such as the late delivery of target hardware and limitation to access STB simultaneously by multiple developers. And it takes too much time and cost to build up multiple STBs. In order to successfully resolve this kind of problems, the software-based spacecraft simulator has been developed. The simulator emulates the on-board computer, I/O modules and power controller units and it supports the debugging and test facilities to software engineers for developing flight software. Also the flight software can be loaded without any modification and can be executed as pseudo real-time. This paper presents the architecture and design of software-based spacecraft simulator, and flight software development and verification under this environment.

FLIGHT SOFTWARE DEVELOPMENT FOR THE KODSAT

  • Choi Eun-Jung;Park Suk-June;Kang Suk-Joo;Seo Min-Suk;Chae Jang-Soo;Oh Tae-Sik
    • Bulletin of the Korean Space Science Society
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    • pp.364-367
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    • 2004
  • This paper presents the flight software of KoDSat (KSLV-l Demonstration Satellite) which performs demonstrating the KSLV-l (Korea Space Launch Vehicle-l)'s satellite launch capability. The KoDSat Flight Software executes in a single-processor, multi-function flight computer on the spacecraft, the OBC (On Board Computer). The flight software running on the single processor is responsible for all real-time processing associated with: processor startup and hardware initialization, task scheduling, RS422 handling function, command and data handling including uplink command and down-link telemetry, attitude determination and control, battery state of charge monitoring and control, thermal control processing.

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Derivation and Validation of Aerodynamic Parameters of Small Airplanes Using Design Software and Subjective Tests (설계용 S/W를 활용한 소형비행기의 비행특성 매개변수 추출과 주관적 시험평가방식에 관한 연구)

  • 이숙경;공지영;최유환;윤석준
    • Proceedings of the Korea Society for Simulation Conference
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    • pp.142-147
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    • 2004
  • It is very difficult to acquire high-fidelity flight test data for small airplanes such as typical unmanned aerial vehicles because MEMS-type small sensors used in the tests do not present reliable data in general. Besides, it is not practical to conduct expensive flight tests for low-cost small airplanes in order to simulate their flight characteristics. A practical approach to obtain acceptable flight data, including stability and control derivatives and data of weight and balance, is proposed in this study. Aircraft design software such as Darcorp's AAA is used to generate aerodynamic data for small airplanes, and moments of inertia are calculated using CATIA, structural design software. These flight data from simulation software are evaluated subjectively and tailored using simulation flight by experienced pilots, based on the certified procedures in FAA AC 120-45A and 40B, which are used for manned airplane simulators.

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DESIGN AND FLIGHT SOFTWARE EMBEDDING OF KOMPSAT-2 SIMULATOR

  • Lee, Sang-Uk;Cho, Sung-Ki;Kim, Jae-Hoon
    • Journal of Astronomy and Space Sciences
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    • v.19 no.2
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    • pp.97-106
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    • 2002
  • The design feature of KOMPSAT-2 simulator based on object oriented design methodology in terms of unified modeling language (UML) has been discussed in this paper. Also, we present how to embed flight software into the simulator. Flight software em-bedding for KOMPSAT-2 simulator is compared to that of the KOMPSAT-1 simulator.

THE IP FUNCTION DEVELOPMENT IN THE COMS FLIGHT SOFTWARE

  • Kang, Soo-Yeon;Yang, Koon-Ho;Choi, Seong-Bong
    • Proceedings of the KSRS Conference
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    • pp.171-174
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    • 2007
  • The COMS flight software is implemented by ADA language and the high level application program language (APL). The APL is used to implement the Interpreted Program (IP) functions which are running on the processor. The IP functions have been developed for the payload management and monitoring with the automatic on-board operational procedure. The IP allows an easier re-programming if necessary. The ground can load or unload IP separately from ADA code in the RAM flight software. The uploaded IP is interpreted and executed by the Interpreted Program Environment (IPE) which is one of the functions implemented in the RAM flight software. In this paper, we introduce the IP and IPE function.

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IMA based Platform Architecture for Improving Portability of Flight Software (비행 소프트웨어의 이식성 향상을 위한 IMA 기반 플랫폼 아키텍처)

  • Seo, Yongjin;Kim, Hyeon Soo
    • Journal of Internet Computing and Services
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    • v.15 no.1
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    • pp.1-17
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    • 2014
  • Flight software operated on the on-board computers in the satellite has requirements such as real-time, high reliability. These requirements make dependency between the flight software and operating environments. Further, whenever a new system is built, such problem drives that all flight software are redeveloped. Thus, the dependency problem between them should be solved. And the problem can be resolved by improving the portability of the flight software. In order to improve the portability it is required to minimize the porting cost. In this paper, we classify the portability with the portability achieving methods. Using the classified portability, we propose a platform architecture that is based on the IMA concept and provides various portability capabilities. The proposed architecture enables us to solve the problem about the development of the flight software.

Design & Implementation of Flight Software Satellite Simulator based on Parallel Processing (병렬처리 기반의 위성 탑재소프트웨어 시뮬레이터 설계 및 개발)

  • Choi, Jong-Wook;Nam, Byeong-Gyu
    • Journal of Satellite, Information and Communications
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    • v.7 no.2
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    • pp.80-86
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    • 2012
  • The software-based satellite simulator has been developed from the start of the project to resolve the restriction and limitation of using hardware-based software development platform. It enables the development of flight software to be performed continuously since initial phase. The satellite simulator emulates the on-board computer, I/O modules, electronics and payloads, and it can be easily adapted and changed on hardware configuration change. It supports the debugging and test facilities for software engineers to develop flight software. Also the flight software can be loaded without any modification and can be executed as faster than real-time. This paper presents the architecture and design of software-based GEO satellite simulator which has hot-standby redundancy mechanism, and flight software development and test under this environment.

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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H-IMA : IMA based Hybrid Platform Architecture for Improving Portability of Flight Software (H-IMA : 비행 소프트웨어의 이식성 향상을 위한 IMA 기반의 혼합형 플랫폼 아키텍처)

  • Seo, Yongjin;Yun, Sangpil;Joe, Hyunwoo;Kwon, Cheolsoon;Kim, Hyungshin;Kim, Hyeon Soo
    • KIPS Transactions on Software and Data Engineering
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    • v.3 no.1
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    • pp.7-18
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    • 2014
  • Flight software operated on the on-board computers in the satellite has requirements such as real-time and high reliability. These requirements make dependency between the flight software and operating environments. Further, whenever a new system is built, such problem drives that all flight software are redeveloped. Thus, the dependency between them should be removed. And the work can be achieved by improving the portability of the flight software. In this paper, we propose a platform architecture based on the IMA architecture. The platform architecture is a hybrid one built by blending two kinds of realizations of the IMA architecture in order to maximize portability. In addition, we implement a prototype system and analyze the execution results of the system to justify the proposed architecture. The proposed architecture enables us to remove the dependency between fight software and operating environments.

Development of Software for Fidelity Test of Flight Dynamic Model on Fixed Wing Aircraft (고정익 항공기의 비행역학 모델 충실도 테스트를 위한 소프트웨어 개발)

  • Baek, Seung-Jae;Kang, Mun-Hye;Choi, Seong-Hwan;Kim, Byoung Soo;Moon, Yong Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.8
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    • pp.631-640
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    • 2020
  • Currently, aircraft simulator has drawn a great attention because it has significant advantages of economic, temporal, and spatial costs compared with pilot training with real aircraft. Among the components of the aircraft simulator, flight dynamic model plays a key role in simulating the flight of an actual aircraft. Hence, it is important to verify the fidelity of flight dynamic model with an automated tool. In this paper, we develop a software to automatically verify the fidelity of the flight mechanics model for the efficient development of the aircraft simulator. After designing the software structure and GUI based on the requirements derived from the fidelity verification process, the software is implemented with C # language in Window-based environment. Experimental results on CTSW models show that the developed software is effective in terms of function, performance and user convenience.