• Journal of Advanced Navigation Technology
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• v.19 no.2
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• pp.91-97
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• 2015

This paper specifies several considerations about assessing safety-critical software in the aerospace domain. In order to evaluate safety critical software in the aerospace industry, it is required to identify an information of evaluation criteria of software under evaluation. The information is specified in the standard, but determination of evaluation criteria cannot be decided by itself and depends on the results of safety assessment of a system and system design. Thus, this paper explains required information of system development standard and safety assessment standard to determine software evaluation criteria. It surveys existing methodologies about evaluating software, and suggests method which is adapted to evaluation of an advanced surface movement guidance and control system (A-SMGCS) software.

• Korean Journal of Artificial Intelligence
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• v.12 no.3
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• pp.9-15
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• 2024

This paper addresses the critical need for quadcopters in GPS-denied indoor environments by proposing a novel attitude control mechanism that enables autonomous navigation without external guidance. Utilizing AR marker detection integrated with a dual PID controller algorithm, this system ensures accurate maneuvering and positioning of the quadcopter by compensating for the absence of GPS, a common limitation in indoor settings. This capability is paramount in environments where traditional navigation aids are ineffective, necessitating the use of quadcopters equipped with advanced sensors and control systems. The actual position and location of the quadcopter is achieved by AR marker detection technique with the image processing system. Moreover, in order to enhance the reliability of the attitude PID control, the dual closed loop control feedback PID control with dual update periods is suggested. With AR marker detection technique and autonomous attitude control, the proposed quadcopter system decreases the need of additional sensor and manual manipulation. The experimental results are demonstrated that the quadrotor's autonomous attitude control and operation with the dual closed loop control feedback PID controller with hierarchical (inner-loop and outer-loop) command update period is successfully performed under the non-GPS aided indoor environment and it enhanced the reliability of the attitude and the position PID controllers within 17 seconds. Therefore, it is concluded that the proposed attitude control mechanism is very suitable to GPS-denied indoor environments, which enables a quadcopter to autonomously navigate and hover without external guidance or control.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2015.10a
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• pp.9-10
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• 2015

e-navigation is a Strategy developed by the IMO. It aims to implement the strategy in 2018. To this end, e-navigation Software Quality Assurance and Human-Centred Design Guidelines has been developing for the implementation and development of e-Navigation. The IMO MSC approved this guideline as a MSC circular in June 2015. In this paper, international standards of software quality assurance and human-centred design has been surveyed and analyzed in terms of usability testing for the practical application of this guideline. The result is planning to be reflected in the practical application guidance for the development of e-navigation equipment hardware-software combination.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.9
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• pp.839-847
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• 2011

This paper proposes a new guidance law for increasing the lethality of munitions. The well known PNG (Proportional Navigation Guidance) is inadequate for the munitions because of some weaknesses. Even if the munition does not have the impact point error, the acceleration command is non zero because the line-of-sight changes at all times in flight. Therefore, we use a difference between a target and an impact point. This proposed guidance law is similar to PNG in the form, but this guidance law concentrates a correction rate of flight path angle instead of the LOS (Line of Sight) rate. The correction of flight path angle is defined as the amount of impact point error. This impact point error can be calculated by neural networks rapidly. Finally, we show that the simulation results prove the suitability of this law.

• Journal of Advanced Navigation Technology
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• v.20 no.5
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• pp.401-407
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• 2016

This paper introduces 3-dimensional path planning and guidance including power model for high altitude long endurance (HALE) UAV using solar energy. Dubins curve used in this paper has advantage of being directly available to apply path planning. However, most of the path planning problems using Dubins curve are defined in a two-dimensional plan. So, we used 3-dimensional Dubins path generation algorithm which was studied by Randal W. Beard. The aircraft model which used in this paper does not have an aileron. So we designed lateral controller by using a rudder. And then, we were conducted path tracking simulations by using a nonlinear path tracking algorithm. We generate examples according to altitude conditions. From the path tracking simulation results, we confirm that the path tracking is well on the flight path. Finally, we were modeling the power system of HALE UAVs and conducting path tracking simulation during 48hours. Modeling the amount of power generated by the solar cell through the calculation of the solar energy yield. And, we show the 48hours path tracking simulation results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.288-293
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• 2010

This paper presents to calculate the lethality of missile for the simulation test program and to verify the simulation results. In order to calculate a reliable lethality we need may data and experiments of fuse and warhead, but in reality it is hard to perform a task. Therefore, this paper obtained from the reference paper to analyze the lethality data for the calculation of the lethality. We form the 6 DOF simulation model using the MATLAB/SIMULINK. And formed the autopilot algorithm using the vertical and horizontal acceleration feedback and PNG (Proportional Navigation Guidance) command be used to the guidance algorithm. Finally, we evaluate the results about three cases, front launch, side launch and rear launch to simulate the simulation program, and the target is designed to have a constant speed and direction.

• Journal of Institute of Control, Robotics and Systems
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• v.20 no.11
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• pp.1103-1111
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• 2014

The results of control law design for a tilt-rotor unmanned aerial vehicle that has a nacelle mounted wing extension (WE) are presented in this paper. It consists of a control surface mixer, stability and control augmentation system (SCAS), hold mode for altitude / speed / heading, and a guidance mode for preprogram and point navigation which includes automatic take-off and landing. The conversion corridor and the control moments derivatives between the original tilt-rotor and its variant of the nacelle mounted WE were compared to show the effectiveness of the WE. The nacelle conversion of the original tilt-rotor starts when the airspeed is greater than 30 km/h but its WE variant starts at 0 km/h in order to reduce the drag caused by the high incidence angle of the WE. The stability margins of the inner loop are presented with the optimization approach. The outer loops for the hold mode are designed with trial and error methods with linear and nonlinear simulation. The main control parameter for altitude control of the helicopter mode is thrust command and it is transferred to the pitch attitude command in airplane mode. Otherwise, the control parameter for the speed of the helicopter mode is the pitch attitude command and it is transferred to the thrust command in airplane mode. Therefore the speed and altitude hold mode are coupled to each other and are engaged at the same time when an internal pilot engages any of the altitude or speed hold modes. The nonlinear simulation results of the guidance control for the preprogrammed mode and point navigation are also presented including automatic take-off and landing in order to prove the full control law.

• Journal of Advanced Navigation Technology
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• v.19 no.1
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• pp.33-40
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• 2015

Advanced surface movement guidance and control system (A-SMGCS) is a system providing routing, guidance and surveillance for the control of aircraft and vehicles in order to maintain the predetermined surface movement rate under all weather conditions while maintaining the required level of safety. In the present study, system engineering was introduced to develop the compliance procedure for the A-SMGCS. At first, requirements for the level IV A-SMGCS were defined and analyzed from the concept of operations (CONOPS). Then, system architecture and specifications were constructed through the functional analysis and allocation. After that, work breakdown structure (WBS) and related integrated master schedule (IMS) were established. Lastly, compliance checklist (CCL) and test and evaluation master plan (TEMP) were developed to verify and validate the system.

• Journal of Advanced Navigation Technology
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• v.18 no.6
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• pp.562-568
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• 2014

This study is safety assessment standard for advanced surface movement guidance control system (A-SMGCS) and case study of the past research project. A-SMGCS providing routing, guidance and surveillance for the control of aircraft and vehicles in order to maintain the declared surface movement rate under all weather conditions within the aerodrome visibility operational level while maintaining the required level of safety. Recently, in korea and europe are developing A-SMGCS system for the safety control of the airport movement area. In safety oriented industry such as aviation that it is necessary to verify and ensure for operating system. In this case study, analysis of safety assessment standard for verified A-SMGCS target level of safety (TLS) and previous developed A-SMGCS research project.

• Journal of Korean Society for Geospatial Information Science
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• v.18 no.3
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• pp.67-74
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• 2010

The aim of this paper is to come up with a methodology of migration for current transportation digital map in order to construct NDRM, which is the most essential map data for car navigation system. The model suggested through our study is able to efficiently produce navigable service map for route finding and guidance as well as to make the best of general road network developed by KOTI.