Processing math: 100%
  • Title/Summary/Keyword: Simulated Flight Test

Search Result 52, Processing Time 0.031 seconds

Study of Engine Control/Performance Modeling for Helicopter Simulator (헬리콥터 시뮬레이터용 엔진 제어 및 성능 모델링 기법 연구)

  • Jun, Hyang-Sig;Jeon, Dae-Keun;Choi, Hyoung-Sik;Choi, Young-Kiu
    • Journal of the Korea Institute of Information and Communication Engineering
    • /
    • v.12 no.12
    • /
    • pp.2239-2246
    • /
    • 2008
  • Engine control/performance model for helicopter simulator if one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model bated on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-327 were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tablet, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the round/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

Progressive Test and Evaluation Strategy for Verification of KF-X AESA Radar Development (한국형 전투기(KF-X) AESA 레이다 개발 검증을 위한 점진적인 시험평가 전략)

  • Shinyoung Cho;Yongkil Kwak;Hyunseok Oh;Hyesun Ju;Hongwoo Park
    • Journal of the Korea Institute of Military Science and Technology
    • /
    • v.27 no.3
    • /
    • pp.387-394
    • /
    • 2024
  • This paper describes a progressive test and evaluation strategy for verification of Korean Fighter eXperimental (KF-X) AESA(Active Electronically Scanned Array) radar development. Three progressive stages of development test and evaluation were officially performed from simulated test conditions to actual operating conditions according to standards: radar function/performance and avionics integration. KF-X AESA radar development is repeatedly verified by progressive stages consisting of five tests: Roof-lab ground test, System Integration Laboratory(SIL) ground test, Flying Test Bed(FTB) test, KF-X ground test, and KF-X flight test. As a result, the risk factor decreases as stages and tests progress. Therefore, development test and evaluation of KF-X AESA radar are successfully performed at low development risk.

Customized Pilot Training Platform with Collaborative Deep Learning in VR/AR Environment (VR/AR 환경의 협업 딥러닝을 적용한 맞춤형 조종사 훈련 플랫폼)

  • Kim, Hee Ju;Lee, Won Jin;Lee, Jae Dong
    • Journal of Korea Multimedia Society
    • /
    • v.23 no.8
    • /
    • pp.1075-1087
    • /
    • 2020
  • Aviation ICT technology is a convergence technology between aviation and electronics, and has a wide variety of applications, including navigation and education. Among them, in the field of aerial pilot training, there are many problems such as the possibility of accidents during training and the lack of coping skills for various situations. This raises the need for a simulated pilot training system similar to actual training. In this paper, pilot training data were collected in pilot training system using VR/AR to increase immersion in flight training, and Customized Pilot Training Platform with Collaborative Deep Learning in VR/AR Environment that can recommend effective training courses to pilots is proposed. To verify the accuracy of the recommendation, the performance of the proposed collaborative deep learning algorithm with the existing recommendation algorithm was evaluated, and the flight test score was measured based on the pilot's training data base, and the deviations of each result were compared. The proposed service platform can expect more reliable recommendation results than previous studies, and the user survey for verification showed high satisfaction.

Design and Test of On-Board Flight Data Acquisition System based on the RS485 Star Network (RS485 Star 구조의 비행체 탑재용 데이터 수집시스템 구현 및 성능시험)

  • Lee, Sang-Rae;Lee, Jae-Deuk
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.32 no.7
    • /
    • pp.83-90
    • /
    • 2004
  • This paper describes on-board decentralized data acquisition system that acquires and encodes the numerous sensor data distributed on the big flight vehicles efficiently. The system's sub-units which have one encoder unit and several remote units were designed and simulated according to the communication protocols and the control, sequence logics based on the FPGA chip. And we have made the functional verification of the acquisition, collection and formatting of remote analog and digital data for the manufactured hardwares.

The Design and Manufacture of Ku-Band Circular Waveguide with Circular Polarizaed Wave Characteristic (원편파 특성을 갖는 Ku-밴드 원형도파관 안테나 설계 및 제작)

  • 이성재
    • Journal of the Korea Institute of Military Science and Technology
    • /
    • v.4 no.1
    • /
    • pp.124-136
    • /
    • 2001
  • In this paper, we designed and manufactured the Ku-band circular waveguide antenna to do wireless communication with a ground radar as on-board antenna of missile. Using the MATLAB and the HFSS, we designed the circular polarizer which has a characteristic of circular polarization and broadband using the capacitive pin method, the feeder to feed coaxial line to circular waveguide, and a stopper to prevent a conductor material from being inserted. Then we simulated the designed antenna using the HFSS, obtained the gain and the radiation pattern. Because of a difficulty of manufacture, we established a manufacture process procedure. Antenna is manufactured with this procedure, test results of the manufactured antenna are the axial ratio of 1.37 ~ 1.72, the 3 ㏈ beamwidth of 72.2378.54, and the gain of 3.26 ~ 4.61 ㏈ within frequency band. We knew that these results are similar with simulation results. Also, we confirmed that the manufactured antenna is satisfied with requirement conditions through performance test, environmental test and flight test.

  • PDF

A Electric Power Source Modeling and Simulation for Electric Propulsion Systems of a Fuel Cell Powered Small UAV (소형 연료전지 무인기의 전기추진시스템용 전력원 모델링 및 시뮬레이션)

  • Lee, Bo-Hwa;Park, Poo-Min;Kim, Chun-Taek;Kim, Sung-Yug;Yang, Soo-Seok;Ahn, Seok-Min
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.39 no.10
    • /
    • pp.959-965
    • /
    • 2011
  • A modeling and power simulation of a small UAV's electric propulsion systems is described. Each power source is modeled and simulated in Matlab/Simulink and it is compared flight test data during 4 hr 30 min with simulation results about 200 W electric propulsion system using fuel cell and battery as a main power sources. In result, it is properly simulated performance and dynamic characteristic of each electric power source. Through this, it is revealed that the simulation is available as a means of predicting power characteristic variation for electric propulsion systems of different class.

Development of an ACMI Simulator Based on LVC Integrating Architecture (LVC 통합 아키텍처 기반 실기동급 ACMI 모의기 개발)

  • Jang, Youngchan;Oh, Jihyun;Myung, Hyunsam;Kim, Cheonyoung;Hong, Youngseok
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.43 no.6
    • /
    • pp.540-547
    • /
    • 2015
  • This paper describes development contents and flight tests of an ACMI simulator based on LVC integrating architecture. ACMI is the system that provides air combat training and ground bombing training for improving fighting efficiency, that is the live simulation involving real people to operate real systems. ACMI simulator was developed for technic acquisition of LVC interoperability by using data link communication. ACMI simulator simulated maneuvering of a fighter by operating an UAV, a fighter can be distinguished from an UAV by maneuvering characteristics. This study proposes maneuvering simulation method by using flight data of the UAV, and performed its flight test for verifying similarity of fighter maneuvering.

Modeling and Parameter Identification of the Slung Load System of an Unmanned Rotorcraft using a Flexible Cable

  • Lee, Byung-Yoon;Moon, Gun-Hee;Lee, Dong-Yeon;Tahk, Min-Jea;Oh, Hyun-Shik
    • International Journal of Aeronautical and Space Sciences
    • /
    • v.18 no.2
    • /
    • pp.365-377
    • /
    • 2017
  • In this paper, we propose a method to identify the parameters of a rotorcraft slung load system using the modal characteristics of a flexible cable. The proposed method estimates the length of the cable and the mass of the payload by means of a frequency analysis. Dynamic equations of the slung load system with the flexible cable are derived using Udwadia-Kalaba equation (UKE) in order to build a simulation program, and the similarity of the simulated slung load movement is verified by comparison with flight test results. Using the computer simulation program, we show that the proposed method works well within various parameter ranges.

Protector Design and Shock Analysis for a Launch-Reconnaissance Robot (발사형 정찰로봇을 위한 보호체 설계 및 충격해석)

  • Kang, Bong-Soo;Park, Moon-Sik
    • Transactions of the Korean Society of Mechanical Engineers A
    • /
    • v.35 no.8
    • /
    • pp.971-976
    • /
    • 2011
  • This paper presents the design concepts of a protector for a launch-reconnaissance robot that is to be deployed for data-collection in hazardous regions. The protector protects the reconnaissance robot inside from shock induced during the process of launch, flight, and landing. Since the outer shells of the protector are automatically opened wide by the unlocking mechanism during the landing stage, the reconnaissance robot can easily exit the protector and move around to carry out its mission. We carefully simulated a finite-element model of the protector with the robot and compared the results with the actual dynamic behavior of the system. Shock- response tests using a droptable showed that the proposed protector filled with silicon material successfully attenuated external shock.

Airborne Hyperspectral Imagery availability to estimate inland water quality parameter (수질 매개변수 추정에 있어서 항공 초분광영상의 가용성 고찰)

  • Kim, Tae-Woo;Shin, Han-Sup;Suh, Yong-Cheol
    • Korean Journal of Remote Sensing
    • /
    • v.30 no.1
    • /
    • pp.61-73
    • /
    • 2014
  • This study reviewed an application of water quality estimation using an Airborne Hyperspectral Imagery (A-HSI) and tested a part of Han River water quality (especially suspended solid) estimation with available in-situ data. The estimation of water quality was processed two methods. One is using observation data as downwelling radiance to water surface and as scattering and reflectance into water body. Other is linear regression analysis with water quality in-situ measurement and upwelling data as at-sensor radiance (or reflectance). Both methods drive meaningful results of RS estimation. However it has more effects on the auxiliary dataset as water quality in-situ measurement and water body scattering measurement. The test processed a part of Han River located Paldang-dam downstream. We applied linear regression analysis with AISA eagle hyperspectral sensor data and water quality measurement in-situ data. The result of linear regression for a meaningful band combination shows 24.847+0.013L560 as 560 nm in radiance (L) with 0.985 R-square. To comparison with Multispectral Imagery (MSI) case, we make simulated Landsat TM by spectral resampling. The regression using MSI shows -55.932 + 33.881 (TM1/TM3) as radiance with 0.968 R-square. Suspended Solid (SS) concentration was about 3.75 mg/l at in-situ data and estimated SS concentration by A-HIS was about 3.65 mg/l, and about 5.85mg/l with MSI with same location. It shows overestimation trends case of estimating using MSI. In order to upgrade value for practical use and to estimate more precisely, it needs that minimizing sun glint effect into whole image, constructing elaborate flight plan considering solar altitude angle, and making good pre-processing and calibration system. We found some limitations and restrictions such as precise atmospheric correction, sample count of water quality measurement, retrieve spectral bands into A-HSI, adequate linear regression model selection, and quantitative calibration/validation method through the literature review and test adopted general methods.