• Journal of the Korean Society of Manufacturing Process Engineers
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• v.17 no.2
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• pp.109-117
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• 2018

The experimental results are presented of an autonomous flight algorithm of a foldable quadcopter with airdrop launching functions. A foldable wing structure enabled the quadcopter to be inserted into a rocket container with limited space. The foldable quadcopter was then separated from the rocket in the air. The flight pattern was tracked using a global positioning system (GPS) with various sensors, including an inertial measurement unit (IMU) module until a designated target position was reached. Extensive field tests were conducted through an international rocket competition, ARLISS 2017, which was held in Black Rock Desert, Nevada, USA. The flight trajectory record of the experiments is stored in electrically erasable programmable read-only memory (EEPROM) embedded in the main control unit. The flight record confirmed that the quadcopter successfully separated from the rocket, executed flight toward the target for a certain length of time, and stably landed on the ground.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.4
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• pp.57-65
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• 2015

In this study, MBTI(Myers-Briggs Type Indicator) test was carried out targeting flight instructors and student pilots in charge of introductory flight training course. The results was analyzed in accordance with the personality type, the preferred indicator, and the combination of preferred indicators in order to see how these characteristics affect the flight training results. Most of personality types of the instructor, regardless of the attitude category such as E or I, were -STJ(70.6%), however the student pilot showed a variety of personality types, rather than professors. Sensing-type(S) students showed higher academic achievement scores than Intuition-type(N), and Judging-type(J) students showed higher academic achievement scores and pilot qualification scores than Perceiving-type(P). The success rate of Extraversion-type(E) student pilots was higher than that of Introversion-type(I) student pilots. As the personality combinations of instructor and student pilot, the academic achievement scores of Judging-Judging(J-J) type were higher than those of Perceiving-Perceiving(P-P) type. The combination of Extraversion-Extraversion(E-E) type showed higher success rate than Extraversion-Introversion(E-I). This result suggests that if both instructor and student pilot have same attitude of Extroversion(E), good training results can be expected.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.10
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• pp.1010-1016
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• 2009

In this paper, we have described an aircraft captive flight test for the development test of weapon systems. We have conducted a captive flight test for the development of core onboard parts and sensors of airborne weapons and guided missiles. We have used KTX-1/XKO-1 aircraft as a platform for the captive flight test. In order to perform a captive flight test, we have made a captive test pod as a shape of external fuel tank in the XKO-1 and have modified XKO-1 aircraft for a system interface. We have taken a development test about all kinds of seekers, navigation & guidance systems, and core part of guided missile through the aircraft captive flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.1012-1020
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• 2018

In order to improve the capability of mission flight of tiltrotor UAV that has been developed by Korea Aerospace Research Institute, a simulation study on the formation flight of autonomous control 5 level has been performed. The formation flight is based on the centralized method with leader and follower airplanes. The formation flight controller was verified through numerical simulation with 3 followers and hardware-in-the loop simulation with 1 follower. This paper describes controller design methods, hardware-in-the-looped simulation test, and performance verification using simulation.

• Journal of Aerospace System Engineering
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• v.5 no.1
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• pp.36-40
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• 2011

In this report US and Korea civil and military simulator certification system is researched, and a plan for improvement is proposed. Korean simulator certification system should adopt FAA's system and improve upon it. Certification criteria should have a basis on FAA certification criteria and add military operation characteristics selectively. Flight test data, used as comparison criteria in certification, should be acquired in package during aircraft development or overseas acquisition. The establishment of certification system is expected to improve external credibility and improve competitiveness in overseas market.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.325-326
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• 2004

Experiment of laser propulsion in free flight has never been conducted. At Institute of Fluid Science (IFS), Tohoku University, propulsive impulse generation by focusing on a rest projectile was demonstrated. Based on the ideas obtained from this experiment, experiment of laser propulsion of a projectile in flight by focusing $CO_2$ laser beam is being prepared for. The objective velocity increment in experiment is about 50 m/s.

• 제어로봇시스템학회:학술대회논문집
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• 2004.08a
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• pp.1375-1379
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• 2004

Unmanned Helicopter has several abilities such as vertical Take off, hovering, low speed flight at low altitude. Such vehicles are becoming popular in actual applications such as search and rescue, aerial reconnaissance and surveillance. These vehicles also used under risky environments without threatening the life of a pilot. Since a small aerial vehicle is very sensitive to environmental conditions, it is generally known that the flight control is very difficult problems. In this paper, a flight control system was designed for an unmanned helicopter. This paper was concentrated on describing the mechanical design, electronic equipments and their interconnections for acquiring autonomous flight. The design methodologies and performance of the helicopter were illustrated and verified with a linearized equation of motion. The LQG based estimator and controller was designed and tested for this unmanned helicopter.

• Proceedings of the Korean Society for Cognitive Science Conference
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• 2005.05a
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• pp.9-13
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• 2005

A comprehension-based computational model of pilot action planning called ADAPT is presented to model pilot performance in a flight simulation context. Individual pilots were asked to execute a series of flight maneuvers using a flight simulator, and their eye-scanning, control movements, and flight performance were recorded in a time-synched database. Computational models of each of the 25 individual pilots were constructed, and the individual models simulated execution of the same flight maneuvers performed by human pilots. The time-synched eye-scanning, control movements, and flight performance of individual pilots and their respective models were compared to test ADAPT's predictive validity.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.215-218
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• 2003

In this study, a performance model of the Smart UAV propulsion system with ducts, tip jets and variable main nozzle, which has flight capability of the rotary wing mode for the take-off/landing and low speed forward flight as well as the fixed wing mode for high speed forward flight, has been newly developed. With the proposed model, steady-state performance analysis was performed at various flight modes and conditions, such as rotary wing mode, fixed wing mode, compound wing, mode altitude and flight speed.