• Title/Summary/Keyword: flight software

Search Result 352, Processing Time 0.023 seconds

Korea Pathfinder Lunar Orbiter Flight Dynamics Simulation and Rehearsal Results for Its Operational Readiness Checkout

  • Song, Young-Joo;Bae, Jonghee;Hong, SeungBum;Bang, Jun
    • Journal of Astronomy and Space Sciences
    • /
    • v.39 no.4
    • /
    • pp.181-194
    • /
    • 2022
  • Korea Pathfinder Lunar Orbiter (KPLO), also known as Danuri, was successfully launched on 4 Aug. from Cape Canaveral Space Force Station using a Space-X Falcon-9 rocket. Flight dynamics (FD) operational readiness was one of the critical parts to be checked before the flight. To demonstrate FD software's readiness and enhance the operator's contingency response capabilities, KPLO FD specialists planned, organized, and conducted four simulations and two rehearsals before the KPLO launch. For the efficiency and integrity of FD simulation and rehearsal, different sets of blind test data were prepared, including the simulated tracking measurements that incorporated dynamical model errors, maneuver execution errors, and other errors associated with a tracking system. This paper presents the simulation and rehearsal results with lessons learned for the KPLO FD operational readiness checkout. As a result, every functionality of FD operation systems is firmly secured based on the operation procedure with an enhancement of contingency operational response capability. After conducting several simulations and rehearsals, KPLO FD specialists were much more confident in the flight teams' ability to overcome the challenges in a realistic flight and FD software's reliability in flying the KPLO. Moreover, the results of this work will provide numerous insights to the FD experts willing to prepare deep space flight operations.

Development of An Integrated Display Software Platform for Small UAV with Parallel Processing Technique (병렬처리 기법을 이용한 소형 무인비행체용 통합 시현 소프트웨어 플랫폼 개발)

  • Lee, Young-Min;Hwang, In-So;Lim, Bae-Hyeon;Moon, Yong-Ho
    • IEMEK Journal of Embedded Systems and Applications
    • /
    • v.11 no.1
    • /
    • pp.21-27
    • /
    • 2016
  • An integrated display software platform for small UAV is developed based on parallel processing technique in this paper. When the small UAV with high-performance camera and avionic modules is employed to various surveillance-related missions, it is important to reduce the operator's workload and increase the monitoring efficiency. For this purpose, it is needed to develop an efficient monitoring software enable to manipulate the image and flight data obtained during flight within the given processing time and display them simultaneously. In this paper, we set up requirements and suggest the architecture for the software platform. The integrated software platform is implemented with parallel processing scheme. Based on AR drone, we verified that the various data are concurrently displayed by the suggest software platform.

Program development for playback time estimation (플레이백 시간 예측 프로그램 개발)

  • Chae, Dong-Seok;Yang, Seung-Eun;Lee, Jae-Seung
    • Proceedings of the Korea Information Processing Society Conference
    • /
    • 2012.04a
    • /
    • pp.492-494
    • /
    • 2012
  • 저궤도 위성은 위성과 지상과의 통신시간이 제한되어 있으므로 제한된 시간에 위성의 대용량메모리(Mass Memory)에 저장된 데이터를 전송받아야 하는데, 이를 위해 저장되는 데이터 량을 정확히 예측할 수 있어야 하고, 저장된 데이터 량에 따라 지상으로 전송하는데 소요되는 시간을 예측할 수 있어야 한다. 본 논문은 위성에 저장되고 있는 Telemetry 종류에 따라 대용량메모리에 저장되는 데이터 량을 예측하고, 저장된 데이터 량에 따라 지상으로 전송하는데 소요되는 시간을 계산하기 위해 개발된 플레이백 시간 예측 프로그램에 대해 서술한 것이다.

Playback Data Analysis and File Combine/Split Program Development (플레이백 데이터 분석 및 파일 병합/분할 프로그램 구현)

  • Chae, Dong-Seok;Yang, Seung-Eun;Lee, Jae-Seung
    • Proceedings of the Korea Information Processing Society Conference
    • /
    • 2011.11a
    • /
    • pp.520-522
    • /
    • 2011
  • 위성으로부터 전송받은 Telemetry 플레이백 데이터 파일들을 적절한 크기로 또는 저장된 시간에 따라 병합하거나 분할할 수 있는 플레이백 파일 병합/분할 프로그램을 구현하였다. 기존에 플레이백 데이터가 정상적으로 수신되었는지를 점검하기 위한 플레이백 데이터 자동 분석 프로그램이 있는데, 기존의 프로그램을 윈도우 기반으로 보다 편리하게 사용할 수 있도록 전체적으로 보완하였고, 여기에 플레이백 파일 병합/분할 기능을 추가하여 전체적으로 하나로 통합하였다. 본 논문은 차세대 저궤도 위성에서 수행되는 데이터 저장 및 전송에 대한 내용과 새롭게 개선된 플레이백 데이터 자동분석 프로그램 및 플레이백 파일 병합/분할 프로그램에 대해 기술한 것이다.

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

  • Kim, Chong-Sup
    • Journal of Institute of Control, Robotics and Systems
    • /
    • v.14 no.8
    • /
    • pp.824-836
    • /
    • 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.

Static Analysis and Improvement Opportunities for Open Source of UAV Flight Control Software (무인비행체 비행제어 Open Source 소프트웨어에 대한 정적분석 및 개선방안)

  • Jang, Jeong-hoon;Kang, Yu-sun;Lee, Ji-hyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.49 no.6
    • /
    • pp.473-480
    • /
    • 2021
  • In this paper, We analyze and present improvements to problems in software quality through Static Analysis for Open Source, which is widely used as the Flight Controller software for small unmanned aerial vehicle drones. MISRA coding rules, which are widely applied based on software quality, have been selected. Static analysis tools were used by LDRA tools certified international tools used in all industries, including automobiles, railways, nuclear power and healthcare, as well as aviation. We have identified some safety-threatening problems across the quality of the software, such as structure of open source modules, analysis of usage data, compliance with coding rules, and quality indicators (complexity and testability), and have presented improvements.

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
    • /
    • v.28 no.3
    • /
    • pp.241-252
    • /
    • 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.

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
    • /
    • v.27 no.4
    • /
    • pp.407-412
    • /
    • 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
    • /
    • v.13 no.7
    • /
    • pp.694-702
    • /
    • 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
    • /
    • v.48 no.1
    • /
    • pp.55-62
    • /
    • 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.