DOI QR코드

DOI QR Code

광섬유 센서를 사용한 항공기용 하중 모니터링 시스템 개발과 지상시험 적용

Aircraft Load Monitoring System Development & Application to Ground Tests Using Optical Fiber Sensors

  • 투고 : 2017.05.24
  • 심사 : 2017.07.10
  • 발행 : 2017.08.01

초록

본 논문에서는 군용 항공기를 위한 새로운 하중 모니터링 시스템에 대하여 소개하였다. 이 시스템은 항공기에 장착되는 센서와 탑재장비 및 지상에서 운용되는 지상분석장비로 구성된다. 이 시스템을 이용하여 항공기에 작용하는 구조정적하중을 비행파라미터로 추정할 수 있을 뿐 아니라, 정적하중, 동적하중 및 예상치 못한 이벤트에 의한 구조물의 응답을 센서로 측정할 수 있다. 특히 다점 측정이 가능한 광섬유 센서를 사용하였다. 탑재장비는 관련 군사규격서의 요구도를 만족하도록 설계되었으며, 일련의 환경시험으로 입증하였다. 본 시스템은 비행시험에 앞서 지상구조시험에 사용되고 평가되었으며, 향후 비행시험평가를 통하여 군용 항공기의 구조하중 모니터링 시스템으로 사용될 예정이다.

In this paper, a new load monitoring system for military aircraft is introduced. This system consists of sensors, an onboard device and an ground analysis equipment. The sensors and onboard device are mounted on the aircraft and the ground analysis equipment is operated on the ground. Through this system, structural static load can be estimated with flight parameters and structural responses can be measured by sensors due to static load, dynamic load and unexpected events. Especially, optical fiber sensors with mutiplexing capability are utilized. The onboard device was specially designed for complying the requirements of relevant military specifications and was verified through a series of the environment tests. This system was used and evaluated through ground structural tests before flight tests. In the near future, this system will be applied to military aircraft as a structural load monitoring system after flight test evaluation.

키워드

참고문헌

  1. MIL-STD-1530C(USAF) - Aircraft Structural Integrity Program (ASIP), Department of Defense, 2005.
  2. Gallagher, J. P., Giessler, F. J., and Berens, A. P., "USAF Damage Tolerance Design Handbook: Guidelines for the Analysis and Design of Damage Tolerant Aircraft Structure," University of Dayton Research Institute, 1984
  3. JSSG-2006 - Joint Service Specification, Aircraft Structures, Department of Defense, 1998.
  4. Molent, L., "Proposed Specifications for an Unified Strain and Flight Parameter Based Aircraft Fatigue Usage Monitoring System," USAF ASIP Conference San Antonio, Texas, 1-3 Dec 1998
  5. DeGarmo, M., and Nelson, G. M., "Prospective Unmanned Aerial Vehicle Operations in the Future National Airspace System." Proceedings of AIAA 4th Aviation Technology, Integration and Operations Forum, 2004.
  6. Neubauer M., Gunteher G., and Fullhas K., "Structural Design Aspects and Criteria for Military UAV," RTO-MP-AVT 145 UAV Design Processes and Criteria, 2007.
  7. Park C. Y., Kim J. H., Jun S.-M. "A Structural Health Monitoring Project for a Composite Unmanned Aerial Vehicle Wing: Overview and Evaluation Tests," Structural Control and Health Monitoring, 19(7), 2012, 567-579. https://doi.org/10.1002/stc.1491
  8. MIL-STD-1553B - Aircraft Internal Time Division Command/Response Multiplex Data Bus, Department of Defense, 1978
  9. MIL-STD-810G - Test Method Standard, Environmental Engineering Considerations and Laboratory Tests, Department of Defense, 2008.
  10. MIL-STD-461F - Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment, Department of Defense, 2007
  11. Ha J. S., Park C. Y. and Lee K. B. "Low Temperature Structural Tests of a Composite Wing with Room Temperature-Curing Adhesive Bond," J. of The Korean Society for Aeronautical and Space Sciences 43(10), 2015, 928-935. https://doi.org/10.5139/JKSAS.2015.43.10.928
  12. CMH-17-3G - Composite Materials Handbook, Volume 3. Polymer Matrix Composites Materials Usage, Design, and Analysis, SAE International, 2012