• 제목/요약/키워드: Simulated Flight Test

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Geometric Modeling and Data Simulation of an Airborne LIDAR System (항공라이다시스템의 기하모델링 및 데이터 시뮬레이션)

  • Kim, Seong-Joon;Min, Seong-Hong;Lee, Im-Pyeong;Choi, Kyung-Ah
    • Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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    • v.26 no.3
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    • pp.311-320
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    • 2008
  • A LIDAR can rapidly generate 3D points by densely sampling the surfaces of targets using laser pulses, which has been efficiently utilized to reconstruct 3D models of the targets automatically. Due to this advantage, LIDARs are increasingly applied to the fields of Defense and Security, for examples, being employed to intelligently guided missiles and manned/unmanned reconnaissance planes. For the prior verification of the LIDAR applicability, this study aims at generating simulated LIDAR data. Here, we derived the sensor equation by modelling the geometric relationships between the LIDAR sub-modules, such as GPS, IMU, LS and the systematic errors associated with them. Based on this equation, we developed a program to generate simulated data with the system parameters, the systematic errors, the flight trajectories and attitudes, and the reference terrain model given. This program had been applied to generating simulated LIDAR data for urban areas. By analyzing these simulated data, we verified the accuracy and usefulness of the simulation. The simulator developed in this study will provide economically various test data required for the development of application algorithms and contribute to the optimal establishment of the flight and system parameters.

Development of a University-Based Simplified H2O2/PE Hybrid Sounding Rocket at KAIST

  • Huh, Jeongmoo;Ahn, Byeonguk;Kim, Youngil;Song, Hyunki;Yoon, Hosung;Kwon, Sejin
    • International Journal of Aeronautical and Space Sciences
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    • v.18 no.3
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    • pp.512-521
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    • 2017
  • This paper reports development process of a university-based sounding rocket using simplified hybrid rocket propulsion system for low-altitude flight application. A hybrid propulsion system was tried to be designed with as few components as possible for more economical, simpler and safer propulsion system, which is essential for the small scale sounding rocket operation as a CanSat carrier. Using blow-down feeding system and catalytic ignition as combustion starter, 250 N class hybrid rocket system was composed of three components: a composite tank, valves, and a thruster. With a composite tank filled with both hydrogen peroxide(H2O2H2O2) as an oxidizer and nitrogen gas(N2) as a pressurant, the feeding pressure was operated in blowdown mode during thruster operation. The MnO2/Al2O3 catalyst was fabricated for propellant decomposition, and ground test of propulsion system showed the almost theoretical temperature of decomposed H2O2 at the catalyst reactor, indicating sufficient catalyst efficiency for propellant decomposition. Auto-ignition of the high density polyethylene(HDPE) fuel grain successfully occurred by the decomposed H2O2 product without additional installation of any ignition devices. Performance test result was well matched with numerical internal ballistics conducted prior to the experimental propulsion system ground test. A sounding rocket using the developed hybrid rocket was designed, fabricated, flight simulated and launch tested. Six degree-of-freedom trajectory estimation code was developed and the comparison result between expected and experimental trajectory validated the accuracy of the developed trajectory estimation code. The fabricated sounding rocket was successfully launched showing the effectiveness of the simplified hybrid rocket propulsion system.

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
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    • v.27 no.4
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    • pp.407-412
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    • 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.

Development of Simulation Environment for Proximity Flight Using Simulink and X-Plane (Simulink와 X-Plane을 이용한 모의 근접비행 시뮬레이션 환경 개발연구)

  • Lee, Sanghoon;Park, Chanhwi;Park, Younghoo;Lee, Daewoo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.6
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    • pp.465-472
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    • 2021
  • Prior to the actual flight test of the separation-reintegration situation of fixed-wing mother and child UAVs in the air, it is necessary to verify the flight control system of child UAV through simulations. In this paper, we build a simulation environment for the development of a child UAV flight control system in a lab environment based on the wake turbulence of X-Plane. To this end, the aerodynamics analysis of child UAV was performed, and Simulink was used to simulate aircraft, and X-Plane was utilized to implement visualization, wind, gusts, and mother UAV movements. The simulation environment built by performing simulated proximity flights was verified by applying the guidance and control algorithm to the child UAV model within Simulink. Furthermore, the flight results confirm the area in which the child UAV can safely fly from the rear of the mother UAV.

Development of a Preliminary Formation-Flying Testbed for Satellite Relative Navigation and Control

  • Park, Jae-Ik;Park, Han-Earl;Shim, Sun-Hwa;Park, Sang-Young;Choi, Kyu-Hong
    • Bulletin of the Korean Space Science Society
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    • 2008.10a
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    • pp.26.3-26.3
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    • 2008
  • This research develops a GPS-based formation-flying testbed (FFTB) for formation navigation and control. The FFTB is a simulator in which spacecraft simulation and modeling software and loop test capabilities are integrated for test and evaluation of spacecraft navigation and formation control technologies. The FFTB is composed of a GPS measurement simulation computer, flight computer, environmental computer for providing true environment data and 3D visualization computer. The testbed can be simulated with one to two spacecraft, thus enabling a variety of navigation and control algorithms to be evaluated. In a formation flying simulation, GPS measurement are generated by a GPS measurement simulator to produce pseudorange, carrier phase measurements, which are collected and exchanged by the flight processors and subsequently processed in a navigation filter to generate relative and/or absolute state estimates. These state estimates are the fed into control algorithm, which are used to generate maneuvers required to maintain the formation. In this manner, the flight processor also serves as a test platform for candidate formation control algorithm. Such maneuvers are fed back through the controller and applied to the modeled truth trajectories to close simulation loop. Currently, The FFTB has a closed-loop capability of simulating a satellite navigation solution using software based GPS measurement, we move forward to improve using SPIRENT GPS RF signal simulator and space-based GPS receiver

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Development of a Comprehensive Performance Test Facility for Small Millimeter-wave Tracking Radar (소형 추적 레이다용 종합성능시험 시설 개발)

  • Kim, Hong-Rak;Kim, Youn-Jin;Woo, Seon-Keol;An, Se-Hwan
    • The Journal of the Institute of Internet, Broadcasting and Communication
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    • v.20 no.3
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    • pp.121-127
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    • 2020
  • The small tracking radar targets the target in a real-time, fast-moving, fast-moving target against aircraft with a large RCS that is maneuvering at low speed and a small RCS aircraft maneuvering at high speed (fighters, drones, helicopters, etc.) It is a pulsed radar that detects and tracks. Performing a performance test on a tracking radar in a real environment is expensive, and it is difficult to quantitatively measure performance in a real environment. Describes the composition of the laboratory environment's comprehensive performance test facility and the main requirements and implementation of each configuration.Anechoic chambers to simulate the room environment, simulation target generator to simulate the signal of the room target, target It is composed of a horn antenna driving device to simulate the movement of a vehicle and a Flight Motion Simulatior (FMS) to simulate the flight environment of a tracking radar, and each design and implementation has been described.

The Communication Satellite Transponder Testing by EGSE System

  • Jo, Jin-Ho;Woo, Hyung-Je;Lee, Seong-Pal
    • Journal of Satellite, Information and Communications
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    • v.2 no.2
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    • pp.36-40
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    • 2007
  • EGSE is used to check out satellite payload during the development prior to launch. The EGSE represented in this paper is a test system for Ka band communication transponder of COMS. The EGSE consist of two subsystems as CTS subsystem and PCTS subsystem. Communication Test subsystem (CTS) performs satellite transponder RF performance testing, data analysis and trending. Most of transponder RF performances are automatically tested by the CTS subsystem. Power, Command & Telemetry subsystem (PCTS) monitor telemetry messages from the transponder and send tele-commands to satellite transponder for the configuration change. PCTS also provide simulated S/C power to the transponder during the ground validation testing. The EGSE test functions are verified by the transponder simulator testing and will be used for the flight model transponders testing.

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Implementation of ZUPT on RPA Navigation System for GNSS Denied Ground Test

  • Shin, Hyeoncheol
    • Journal of Positioning, Navigation, and Timing
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    • v.9 no.2
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    • pp.125-129
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    • 2020
  • In this paper, Zero velocity UPdaTe (ZUPT) is implemented on the navigation system of Remotely Piloted Aircraft for GNSS denied environment. RPA's navigation system suffers from lack or loss of satellite signal while maintenance or ground test inside a hangar. Although some of the hangars install GPS repeaters for indoor tests, the anti-jamming equipment with array antenna blocks the repeater signal regarding them as hostile jamming signal. With ZUPT, an aircraft navigation system can be tested free from the divergence of navigation solution without line-of-sight satellites. The designed ZUPT aided centralized Kalman Filter is implemented on the Embedded GPS&INS and simulated with Captive Flight Test data. The simulation result shows stable navigation solution without GNSS updates.

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
    • Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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    • 2008.10a
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    • pp.183-188
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    • 2008
  • Engine control/performance model for helicopter simulator is 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 based 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-32T 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 tables, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the ground/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

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Measurement of the Flow Field Around a Quadcopter in Vertical Descending Flight (수직 하강 비행 조건에서의 쿼드콥터 주위의 유동장 계측)

  • Kwon, Min-Jeong;Kwon, Ki-Jung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.46 no.5
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    • pp.359-367
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    • 2018
  • The vortex ring state that occurs during the descending flight of a rotorcraft generates a circulating flow like a donut near the rotating surface, and it often causes a rotorcraft fall due to loss of thrust. In this paper, we have physically identified the flow field in the vortex ring state of the quadcopter, one of the types of unmanned aerial vehicles. The descending flight of the quadcopter was simulated in a 1m subsonic wind tunnel of the Korea Aerospace Research Institute(KARI) and the Particle Image Velocimetry(PIV) was used for the flow field measurement. The induced velocity in the hovering state is estimated by using the momentum theory and the test was carried out in the range of descent rate at which the vortex ring condition could be caused. The development and the direction of the vortex ring were confirmed by the measurement of the flow field according to not only the descent rate but also propeller separation distance. In addition, the results of the study show the vortex ring state can be predicted sufficiently by measuring the flow velocity around the quadcopter.