• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.60-67
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• 2022

An Electro-Optical Tracking System (EOTS) is an electric optical system with EO/IR cameras, laser sensors, and an IMU. The EOTS calculates coordinates of targets, using attitude and acceleration measured by the IMU. In particular for an armed aircraft, the performance of the weapon system depends on how quickly and accurately it acquires the target coordinates. The IMU should be operated after alignment is complete, to meet the coordinate accuracy required by the weapon system so the initial stabilization time of the IMU should be reduced, by quickly measuring the attitude and acceleration. Alignment is the process of determining the initial attitude by resolving the attitude error of the IMU, and the IMU of mission equipment such as an airborne EOTS, uses velocity matching based on the velocity from GPS/INS for aircraft navigation. In this paper, a method is presented to improve the transfer alignment performance of the airborne EOTS, by maneuvering aircraft and the mission equipment. First, the performance factor of the alignment was identified, as a heading error through the velocity matching model and simulation results. Then acceleration maneuvers and attitude changes were necessary, to correct the error. As a result of flight tests applied to an EOTS on a OOO aircraft system, the transfer alignment performance was improved as the duration time was decreased, by more than five times when the aircraft accelerated by more than 0.2g and the EOTS was moving until 6.7deg/s.

• The Korean Journal of Air & Space Law and Policy
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• v.33 no.2
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• pp.443-469
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• 2018

In the sixty year since the first launch of Sputnik 1, it has become impossible to consider economic, political, or scientific human life in the communication field without reference to outer space. But, there is a growing groundswell of public opinion aimed at preventing arms race in space. Therefore it is necessary to establish some institution or mechanism such a code of conduct, international law. But every nation has a different posture on the grounds of national interest, or different levels of space development, the conditions required for the successful negotiation of a comprehensive treaty are not yet ripe. It is hoped that by beginning with soft measures (TCBM, Code of Conduct) for which it is easier to secure voluntary participation it may be possible to build up to a comprehensive treaty. The participation of the Space powers (US, Russia, China) in a dialogue of mutual exchange and shared information would contribute to international peace and give a long term benefit to humankind. It is also necessary to promote partnership through regional and bilateral cooperation. We should guide and shape opinion so that more nations ratify and sign existing international legal covenants in order to contribute to the efficency of Space law. International law needs to enforce PAROS and Space Security.

• The Korean Journal of Air & Space Law and Policy
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• v.26 no.1
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• pp.31-63
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• 2011

Since Korea has invested only on developing an aircraft, it is true that Korea has neglected detailed standards and procedures about certification activities including essential safety procedures. Most developed countries have implemented mandatory airworthiness system by legislating it for operational safety of aircraft based on ICAO Annex 8, and the U.S. Department of Defense and the FAA's Airworthiness system have been adapted it to the realities of their circumstance. Therefore, Airworthiness system that can guarantee the safety of the aircraft at international level is necessary to enhance flight safety and to create export opportunities of an aircraft as a country which can develop an aircraft by itself To achieve this, a study on the improvement of aircraft airworthiness was carried out by analyzing the problem of domestic airworthiness system and by reflecting international best practices on the establishment of a system for improved Airworthiness.

• Journal of Aerospace System Engineering
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• v.15 no.3
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• pp.65-70
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• 2021

This study presents a method to efficiently advance the Republic of Korea's Unmanned Systems through the analysis of the development of the U.S. Unmanned System Policy. After the occurrence of the September 11 attacks, the U.S. developed Unmanned Systems as a part of RMA and became the leader in this area. The system went through numerous trials and errors during the development and acquisition. From these experiences, the U.S. had embodied Unmanned Systems acquisition methods by establishing Unmanned Systems Development Guidance and DoD Autonomy Community of Interest in 2012. In addition, as diverse unmanned programs started to proceed, it promoted Core Technology development sharing and simplification of functions of the Unmanned Systems to exclude budget-wasting elements such as duplication of programs. The Republic of Korea must politically build a collaborative system between industry/academia/research institute/military and apply evolutionary development strategies from the first step of the development of the Unmanned Systems the future Game Changer. In operations, concepts of the Manned/Unmanned Systems complex operation should be established and intelligent S/W, Open System, and Cyber Security technologies to materialize them developed.

• Journal of Aerospace System Engineering
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• v.15 no.3
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• pp.71-78
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• 2021

Since most functions of modern aircraft are controlled by software, software errors are directly related to aircraft safety. The criterion in Chapter 15 of the MIL-HDBK-516C addresses safe development and verification of military aircraft software. As the U.S. Air Force repeatedly experienced non-compliance with Chapter 15 criterion of the MIL-HDBK-516C, it published an Airworthiness Circular (AC-17-01) as a guide to meeting the criterion. In this paper, Chapter 15 of MIL-HDBK-516C, AC-17-01 and the SW Qualification Guideline (DO-178C) as applied by the Federal Aviation Administration are compared and analyzed. For the analysis, a matching ratio formula between the MIL-HDBK-516C criteria specified in AC-17-01 and the DO-178C specified in MIL-HDBK-516C criteria is defined. The sections that satisfy MIL-HDBK-516C criterion are derived when AC-17-01 or DO-178C matches. Based on the analysis results, the aircraft software development process is established and examples of application of Chapter 15 of MIL-HDBK-516C are addressed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.7
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• pp.565-572
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• 2021

In this study, a study on the performance and aging of explosive bolts stored for a long time among pyrotechnic mechanical devices(PMD) used as separation devices in the defense field is conducted. For this, explosive bolts that had been installed in the weapon system for about 10 years are secured. Performance and life extension test procedures are established based on the AIAA Standard and MIL-STD. Before performance evaluation, non-functional tests are performed to check whether external changes or failures occurred. Next, circuit inspection and X-ray tests are conducted to check the failure in internal circuits and structures. After that, performance test is carried out to confirm the operation of the samples that passed the non-functional test. Through this test, separation of bolt and separation time are measured, and some samples are tested after a high temperature storage test to confirm the remaining life and the possibility of extension. Finally, the remaining life and reliability are predicted based on the results of the test and the Arrhenius model to identify remaining shelf life and reliability depend on time.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.11
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• pp.1112-1120
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• 2008

The real-time distributed simulation at the present age concentrates on the construction of a system development environment in order to accomplish a synthetic battlefield environment connected with Live-Virtual-Constructive simulation and to realize the Simulation Based Acquisition which supports the life cycle of weapon system. Accordingly this paper describes the development environment of the UML modeling and simulation which integrates the system analysis and design methods performed during the conceptual design phase of the reconnaissance UAV system development. An integrated framework linked with the UML simulation and X-plane visualization is suggested to efficiently perform the system analysis and design, and finally the implementation contents, the analysis of experiment results and concluding remarks are described.

• Journal of Aerospace System Engineering
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• v.15 no.1
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• pp.56-62
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• 2021

The purpose of this study was to address a Remote Airborne Control Simulator that could simulate manned-unmanned teaming (MUM-T mission) for fixed wing UAV. With rapid technological development of unmanned aerial vehicle (UAV), the mission capability of UAV has tremendously grown. The role of UAV extends from simple reconnaissance to highly automated wingman. Accordingly, the requirement of UAV ground simulator should be modified as well to meet function requirements for simulating a MUM-T mission. A developed remote airborne control simulator was developed for conducting fixed wing UAV MUM-T operation simulations on the ground. The newest MUM-T examples, usage, and application of the developed remote airborne control simulator for MUM-T simulation are also presented in this study.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.11
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• pp.1123-1129
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• 2010

Angular Deviation(AD) on transparency applied to TA-50 Aircraft deteriorates armament system's accuracy because it makes a difference in between actual and theoretical targets. In order to increase accuracy, therefore, TA-50 Aircraft measures AD on transparency and provide the measured values for the integrated mission display computer as a type of AD coefficients. This makes AD revised so that pilots can accurately see the actual target on their head-up display. In order to implement such mechanism into a real field, we develop a new device and system automatically measuring AD for the first time. We also deal with basic concept including AD induction formula as well as operating systems. As a consequence of testing the accuracy and precision for verifying reliability of the system, we got satisfactory results. In specific, the accuracy was within the resultant criterion of 1%. The precision was also satisfied with respect to the whole criteria. The system developed through this research is qualified as a military standard equipment for transparency of the canopy.

• Journal of Aerospace System Engineering
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• v.15 no.3
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• pp.105-113
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• 2021

This paper delineates the applied thermal environmental test profiles using test conditions and procedures based on MIL-STD-810 Method 501 (High Temperature Test Method) and Method 502 (Low Temperature Test Method). The test profiles have been optimized in order to comply with export customer's requirements and product reliability in high and low temperature environment for XKT-1 (KT-1 Export Version) aircraft. Additionally, the tests are suitable for large sized environmental chambers, which is one of the facilities of ADD (Agency for Defense Development) according to ETEMP (Environmental Test and Evaluation Master Plan). The results of these test profiles and test executions satisfy the customer requirements and product reliability. The present paper can be applied to the other export programs with more severe temperature conditions.