• Title/Summary/Keyword: Flight Test Computer

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Ground Test and Evaluation of a Flight Control Systemfor Unmanned Aerial Vehicles

  • Suk, Jin-Young
    • International Journal of Aeronautical and Space Sciences
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    • v.5 no.1
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    • pp.57-63
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    • 2004
  • UAV(Unmanned Aerial Vehicle) has become one of the most popularmilitary/commercial aerial robots in the new millennium. In spite of all theadvantages that UAVs inherently have, it is not an easv job to develop a UAVbecause it requires very systematic and complete approaches in full developmentenvelop. The ground test and evaluation phase has the utmost importance in thesense that a well-developed system can be best verified on the ground. In addition,many of the aircraft crashes in the flight tests were resulted from the incompletedevelopment procedure. In this research, a verification procedure of the wholeairbome integrated system was conducted including the flight management system.An airbome flight control computer(FCC) senses the extemal environment from thepehpheral devices and sends the control signal to the actuating system using theassigned control logic and flight test strategy. A ground test station controls themission during the test while the downlink data are transferred from the flightmanagement computer using the serial communication interface. The pilot controlbox also applies additional manual actuating commands. The whole system wastested/verified on the wind-tunnel system, which gave a good pitch controlperformance with a preUspecified flight test procedure. The ground test systemguarantees the performance of fundamental functions of airbome electronic systemfor the future flight tests.

Design on Flight-Critical Function of Mission Computer for KUH (한국형기동헬기 임무컴퓨터 비행필수기능 설계)

  • Yu, Yeon-Woon;Kim, Tae-Yeol;Jang, Won-Hong;Kim, Sung-Woo;Lim, Jong-Bong
    • Journal of the Korea Institute of Military Science and Technology
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    • v.14 no.2
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    • pp.213-221
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    • 2011
  • Avionics system tends to be designed to have the integrated architecture, and it is getting difficult and complex to verify the flight-critical function because of sophisticated structure. In Korean Utility Helicopter, mission computer acts as the MUX Bus Controller to handle the data from both communication, identification, mission/display and survivability equipment inside Mission Equipment Package and aircraft subsystems such as fuel system and electrical system while it is interfacing with Automatic Flight Control System and Full-Authority Digital Engine Control via ARINC-429 bus. The Flight Displays which is classified as flight-critical function in aircraft is implemented on Primary Flight Display after mission computer processes data from AFCS in order to generate graphics. This paper defines the flight-critical function implemented in mission computer for KUH, and presents the static and dynamic test procedures which is performed on System Integration Laboratory along with Playback Recorder prior to flight test.

System Identification and Stability Evaluation of an Unmanned Aerial Vehicle From Automated Flight Tests

  • Jinyoung Suk;Lee, Younsaeng;Kim, Seungjoo;Hueonjoon Koo;Kim, Jongseong
    • Journal of Mechanical Science and Technology
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    • v.17 no.5
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    • pp.654-667
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    • 2003
  • This paper presents a consequence of the systematic approach to identify the aerodynamic parameters of an unmanned aerial vehicle (UAV) equipped with the automatic flight control system. A 3-2-1-1 excitation is applied for the longitudinal mode while a multi-step input is applied for lateral/directional excitation. Optimal time step for excitation is sought to provide the broad input bandwidth. A fully automated programmed flight test method provides high-quality flight data for system identification using the flight control computer with longitudinal and lateral/directional autopilots, which enable the separation of each motion during the flight test. The accuracy of the longitudinal system identification is improved by an additional use of the closed-loop flight test data. A constrained optimization scheme is applied to estimate the aerodynamic coefficients that best describe the time response of the vehicle. An appropriate weighting function is introduced to balance the flight modes. As a result, concurrent system models are obtained for a wide envelope of both longitudinal and lateral/directional flight maneuvers while maintaining the physical meanings of each parameter.

A Study on Processor Monitoring for Integration Test of Flight Control Computer equipped with A Modern Processor (최신 프로세서 탑재 비행제어 컴퓨터의 통합시험을 위한 프로세서 모니터링 연구)

  • Lee, Cheol;Kim, Jae-Cheol;Cho, In-Jae
    • Journal of Institute of Control, Robotics and Systems
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    • v.14 no.10
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    • pp.1081-1087
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    • 2008
  • This paper describes limitations and solutions of the existing processor-monitoring concept for a military supersonics aircraft Flight Control Computer (FLCC) equipped with modern architecture processor to perform the system integration test. Safecritical FLCC integration test, which requires automatic test for thousands of test cases and real-time input/output test condition generation, depends on the processor-monitoring device called Processor Interface (PI). The PI, which relies upon on the FLCC processor's external address and data-bus data, has some limitations due to multi-fetching capability of the modern sophisticated military processors, like C6000's VLIW (Very-Long Instruction Word) architecture and PowerPC's Superscalar architecture. Several techniques for limitations were developed and proper monitoring approach was presented for modem processor-adopted FLCC system integration test.

Design and Flight Test of Path Following System for an Unmanned Airship (무인 비행선의 자동 경로 추종 시스템 개발 및 비행시험)

  • Jung, Kyun-Myung;Sung, Jae-Min;Kim, Byoung-Soo;Je, Jeong-Hyeong;Lee, Sung-Gun
    • Journal of Institute of Control, Robotics and Systems
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    • v.16 no.5
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    • pp.498-509
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    • 2010
  • In this paper, a waypoint guidance law Line Tracking algorithm is designed for testing an Unmanned Airship. In order to verify, we develop an autonomous flight control and test system of unmanned airship. The flight test system is composed FCC (Flight Control Computer), GCS (Ground Control System), Autopilot & Guidance program, GUI (Graphic User Interface) based analysis program, and Test Log Sheet for the management of flight test data. It contains flight test results of single-path & multi-path following, one point continuation turn, LOS guidance, and safe mode for emergency.

Development of FCC Redundancy System for Tiltrotor UAV (틸트로터 무인기 비행제어컴퓨터 이중화 시스템 개발)

  • Park, Bum-Jin;Kang, Young-Shin;Yoo, Chang-Sun;Cho, Am
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.2
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    • pp.133-139
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    • 2017
  • Flight control computer of tiltrotor UAV was designed by redundancy system with primary and secondary channels to improve reliability. The redundancy functions consist of channel switching and data recovery. The channel switching function consists of software method by using cross channel data link and hardware method by using watchdog timer. The data recovery is the function to maintain flight condition when the flight control computer is restarted exceptionally in operation. The redundancy system was verified by flight control computer bench test, system integration test and HILS test. This paper describes the redundancy function of tiltrotor UAV flight control computer and test-verification method.

Parameter identification of the nonlinear stall motion from flight test data (비행시험을 통한 항공기의 비선형 실속 운동시의 매개변수 추정)

  • 전일환;황명신;이정훈
    • 제어로봇시스템학회:학술대회논문집
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    • 1996.10b
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    • pp.199-202
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    • 1996
  • In this paper, we used the maximum likelihood method for 2-point aerodynamic model to determine the parameters of the ChangGong-91. Since the estimation from the flight test of real aircraft is the most reliable, we performed the flight test of ChangGong-91 to get the parameters such as velocity, height, 3 axis acceleration, 3 axis angular rate, pitch angle, angle of attack, temperature and so on. We recorded the flight test data in S-VHS tapes and stored them to personal computer using A/D(analog to digital) converter. Flight test was done in stall motion, and the acquired data was be processed with parameter identification method.

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Simulation of the control force of the light aircraft using flight test data (비행시험 자료를 이용한 경항공기의 조종력 시뮬레이션)

  • 김정환;황명신;이정훈
    • 제어로봇시스템학회:학술대회논문집
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    • 1996.10b
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    • pp.203-206
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    • 1996
  • The purpose of this paper is to find how to determine the parameters of the basic control system design such as hinge moment coefficients and to display the controllability of the ChangCong-91. Since the estimation from the flight test of real aircraft is the most reliable, we performed the flight test of ChangGong-91 to get the various parameters such as velocity, height, control force, control surface deflection, 3 axis acceleration, 3 axis angular rate, pitch angle, angle of attack temperature and so on. We recorded the flight test data in VHS tapes and stored them to personal computer using A/D(analog to digital) converter. Flight test was done in various conditions, and the acquired data was processed with parameter identification method such as least square method. These data will be utilized for the development of Autopilot System design and Control Loading System design.

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A Study on Parameter Estimation for General Aviation Canard Aircraft

  • Kim, Eung Tai;Seong, Kie-Jeong;Kim, Yeong-Cheol
    • International Journal of Aeronautical and Space Sciences
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    • v.16 no.3
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    • pp.425-436
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    • 2015
  • This paper presents the procedures used for estimating the stability and control derivatives of a general aviation canard aircraft from flight data. The maximum likelihood estimation method which accounts for both process and measurement noise was used for the flight data analysis of a four seat canard aircraft, the Firefly. Without relying on the parameter estimation method, several aerodynamic derivatives were obtained by analyzing the steady state flight data. A wind tunnel test, a flight test of a 1/4 scaled remotely controlled model aircraft, and the prediction of aerodynamic coefficients using the USAF Stability and Control Digital Data Compendium (DATCOM), Advanced Aircraft Analysis (AAA), and Computer Fluid Dynamics (CFD) were performed during the development phase of the Firefly and the results were compared with flight determined derivatives of a full scaled flight prototype. A correlation between the results from each method could be used for the design of the canard aircraft as well as for building the aerodynamic database.

Implementation of a Real-time Data fusion Algorithm for Flight Test Computer (비행시험통제컴퓨터용 실시간 데이터 융합 알고리듬의 구현)

  • Lee, Yong-Jae;Won, Jong-Hoon;Lee, Ja-Sung
    • Journal of the Korea Institute of Military Science and Technology
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    • v.8 no.4 s.23
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    • pp.24-31
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    • 2005
  • This paper presents an implementation of a real-time multi-sensor data fusion algorithm for Flight Test Computer. The sensor data consist of positional information of the target from a radar, a GPS receiver and an INS. The data fusion algorithm is designed by the 21st order distributed Kalman Filter which is based on the PVA model with sensor bias states. A fault detection and correction logics are included in the algorithm for bad measurements and sensor faults. The statistical parameters for the states are obtained from Monte Carlo simulations and covariance analysis using test tracking data. The designed filter is verified by using real data both in post processing and real-time processing.