• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.193-201
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• 2013

Propeller is an important component of Human Powered Aircraft (HPA) propulsion system. HPA uses large diameter low rotational speed propeller to get high propeller efficiency. The propeller was designed by HPA propeller designing program. The propeller pitch is adjustable by rotating the blade axis angle at ground. Performance of the propeller for various parameters are analysed by the same program used for design. Off-design condition performance was also checked including pilot power change and flight speed change. The propeller was manufactured in ultra-light structure using carbon composite material down to 950g. The propeller was ground tested on ironbird and installed on KARI HPA. Finally the HPA flew 291m with this propeller.

• International Journal of Aeronautical and Space Sciences
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• v.11 no.4
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• pp.338-344
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• 2010

This paper discusses the development of the control system of a mini quadrotor in Konkuk University for indoor applications. The attitude control system consists of a stability augmentation system, which acts as the inner loop control, and a modern control approach based on modeling will be implemented as the outer loop. The inner loop control was experimentally satisfied by a proportional-derivative controller; this was used to support the flight test in order to validate the modeling. This paper introduces the mathematical model for the simulation and design of the optimal control on the outer loop control. To perform the experimental tests, basic electronic hardware was developed using simple configurations; a microcontroller used as the embedded controller, a low-cost 100 Hz inertial sensors used for the inertial sensing, infra-red sensors were employed for horizontal ranging, an ultrasonic sensor was used for ground ranging and a high performance propeller system built on an quadrotor airframe was also employed. The results acquired from this compilation of hardware produced an automatic hovering ability of the system with ground control system support for the monitoring and fail-safe system.

• Journal of Institute of Control, Robotics and Systems
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• v.12 no.8
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• pp.729-738
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• 2006

In recent days, navigation technology becomes more important as location based service (LBS) such as E911 and telematics are considered as attractive business fields. Commercial LBS requires that navigation system should be inexpensive and available anytime and anywhere - indoors and outdoors. If we consider these requirements, it is out of question that GPS is the most favorite system in the world. However, GPS has a serious problem. The one is that GPS does not operate indoors well. This is because GPS satellites are about 20,000km above the ground so that indoor signals are too weak to be tracked in GPS receiver. And the other is that vertical accuracy is less than horizontal accuracy, because of GPS satellites' geometry. To solve these problems, many researches have been done around the world since 1990s. This paper is also one of them and we will introduce an excellent solution by use of pseudolite. Pseudolite is a kind of signal generator, which transmits GPS-like signal. So it is same as GPS satellite in ground. In this paper, we will propose the integrated navigation system of GPS and pseudolite and show the flight test results using RC airplane to proof our navigation system. As a result, we could improve the vertical accuracy of airplane into the horizontal accuracy.

• Korean Journal of Remote Sensing
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• v.34 no.6_1
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• pp.847-855
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• 2018

GMTI (Ground Moving Target Indicator) is a kind of airborne radar function that is used widely in military applications to detect the moving targets on the ground. In this paper, GMTI signal processing technique was presented and its performance was verified using sum and difference channels raw data obtained by the captive flight test.

• The Journal of Korea Robotics Society
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• v.17 no.4
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• pp.438-446
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• 2022

In this paper, we propose an intelligent three-legged landing system that can maintain stability and level even on rough terrain than conventional four-legged landing systems. Conventional landing gear has the limitation that it requires flat terrain for landing. The 3-leg landing system proposed in this paper extends the usable range of the legs and reduces the weight, allowing the quadcopter to operate in various environments. To do this, kinematics determine the joint angles and coordinates of the legs of the two-link structure. Based on the angle value of the quadcopter detected via the IMU sensor, the leg control method that corrects the posture is determined. A force sensor attached to the end of the leg is used to detect contact with the ground. At the moment of contact with the ground, landing control starts according to the value of the IMU sensor. The proposed system verifies its reliability in various environments through an indoor landing test stand. Finally, in an outdoor environment, the quadcopter lands on a 20 degree incline and 20 cm rough terrain after flight. This demonstrates the stability and effectiveness of the 3-leg landing system even on rough terrain compared to the 4-leg landing system.

• Proceedings of the IEEK Conference
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• 2005.11a
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• pp.439-442
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• 2005

An airborne radar performance can be sensitive to the variation of the Doppler center frequency and the spectral spread of the ground clutter return due to the radar platform moving and aspect angle of the scanning beam to the target. In this paper, for the performance test of the airborne pulsed Doppler radar system developed, the high-speed radar data acquisition system is implemented for acquiring the raw radar signal in real-time. Based on the various test scenarios from airborne-platform to the moving platform, the various radar target and clutter signals are collected and their spectrum is analyzed for the verification of the radar performance in the real-time flight test environments.

• Advances in aircraft and spacecraft science
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• v.5 no.2
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• pp.205-223
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• 2018

During launch a spacecraft is subjected to a variety of dynamical loads transmitted through the launcher to spacecraft interface or air-born transmission excitations in the acoustic pressure field inside the fairing. As a result, spacecraft are tested on ground to ensure and demonstrate the global integrity of the structure against these loads, to screen the flight hardware for quality of workmanship and to validate mathematical models. This paper addresses the numerical modelling and simulation of the low frequency sine and random vibration tests performed on electrodynamic shaker facilities to comprise the mechanical-borne transmission loads through the launcher to spacecraft interface. Consequently, the paper reviews techniques and methodologies to derive a reliable and representative coupled virtual vibration testing simulation environment based on experimental data. These technologies are explored with the main objectives to ensure a stable, reliable and accurate control while testing. As a result, the use of the derived simulation models in combination with the added value of improved control and signal processing algorithms can lead to a safer and smoother vibration test control of the entire environmental test campaign.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.4
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• pp.76-82
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• 2006

Flutter analyses are performed for the KF-16D aircraft with brand new ALQ-X ECM pod. A flutter analysis method using test modal data is proposed and validated using published F-16 modal data and flutter analysis results. Ground vibration test is performed for KF-16D stands on its landing gears. Attained modal data are transformed to free-free condition of KF-16D aircraft with ALQ-X pod and ALQ-119 pod, respectively. As the results of comparison of flutter analyses, ALQ-X is cleared to be operated in the flight envelope authorized for existing ECM pods.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.48-55
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• 2019

This paper presents a study on Fault History Management Equipment (FHME) of Unmanned Aerial Systems (UAS). UAS comprise of various types of electronic equipment for high reliability design for flight safety. Consequently, it is mandatory for each on-board equipment to have its own Built-In-Test (BIT) function, because rapid fault-detections for UAS are necessary. FHME is developed for the purposes of display, storage and management of such BIT results on ground. This paper describes the outline, development requirements, design and verification process of FHME.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.1-8
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• 2013

A liquid-monopropellant hydrazine thruster has several outstanding advantages such as relatively-simple structure, long/stable propellant storability, clean exhaust products, and so on. Therefore hydrazine thruster has such a wide application as orbit and attitude control system (ACS) for space vehicles. A hydrazine thruster with the medium-level thrust to be used in the ACS of space launch vehicles (SLV) has been developed, and its ground firing test result is presented in terms of thrust, impulse bit, temperature, and chamber pressure. It is verified through the performance test that the response and repeatability of thrust are very excellent, and the thrust efficiencies compared to its ideal requirement are larger than 93%.