• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.46 no.9
• /
• pp.723-734
• /
• 2018

A structural weight estimation methodology for the multicopter design process is presented. In general, a multicopter is composed of an airframe, motors, propellers, battery and so on. Among these, the weight of motors, propellers and battery can be obtained from the weight trends with respect to design parameters. However, the structural weight is hard to be estimated due to the various configurations and design concepts of multicopters. Moreover, the airframe weights of most commercial multicopter products are not provided. Thus, an accurate airframe weight model is required for the reliable mutlcopter design process. Firstly, the standard configuration of multicopters is defined. Then, we proposed the structural weight estimation method using the number and diameter of propellers determined from the initial step of sizing process. Finally, we validated our suggested method using the commerical products.

• Journal of Aerospace System Engineering
• /
• v.16 no.5
• /
• pp.78-85
• /
• 2022

Multicopter-type unmanned aerial vehicles (UAV) are increasingly for cargo transportation to mountainous and island regions, image information acquisition in disaster areas, and emergency rescue transport. In order to successfully perform these tasks, the aircraft structure must be able to safely support the loads induced by flight conditions while ensuring the vibration and aeroelastic stability of the prop-rotor. This study introduced a structural analysis model of a 40kg payload multicopter with an engine-generator hybrid power system. The deformation and stress distribution are investigated depending on the load conditions. In addition, the vibration characteristics and aeroelastic stability of the prop-rotor were also presented to flight speed and aircraft pitch angle. The maximum thrust generated by the prop-rotor and the landing load applied to the multicopter under normal and emergency landing conditions were reviewed., It confirmed that the structure could support without failure. In addition, it confirmed that the damping characteristics of each primary locate in the constant region according to the aircraft's flight speed and the prop-rotors rotating speed.

• Proceedings of the Materials Research Society of Korea Conference
• /
• 2003.11a
• /
• pp.239-239
• /
• 2003

탄소재료의 산화반응을 설명한 대부분의 논문은 TGA(Thermo Gravimetric Analysis)를 이용한 연구이다. TGA 장치는 가열이 필요한 물질의 반응연구에 다양하게 이용되고 있는데, 온도에 대한 무게 변화를 간편하게 알 수 있다는 장점과 함께 보편적으로 편리한 Arrhenius형태의 속도식으로 해석된다. 많은 연구자들은 TGA를 이용하여 다양한 탄소재료에 대한 반응속도상수를 구하였으며, 반응기체, 반응온도 및 원료물질에 따라 다른 속도를 나타내는 실험결과를 표준화된 속도식으로 표현하고자 하는 노력이 있었다. 그러나 이런 대부분의 연구는 coal 등과 같은 탄소재료의 연소특성을 이용하려는 에너지 변환 연구가 주를 이루어 왔으며, 탄소섬유의 산화반응에 대한 표준화 식으로 해석한 보고는 거의 없는 실정이다. 이 연구에서는 내부구조가 현격하게 차이나는 다른 두 종류의 피치계 탄소섬유를 TGA를 이용하여 등온 산화반응 시켰다. 반응기체의 종류와 반응온도를 변화시켜 산화반응조건에 따른 중량변화를 관찰하였고, 여러 산화조건에서 얻어진 산화속도를 Kasaoka 등에 의해 제안된 표준화식을 이용하여 산화반응의 평균 속도상수 K와 전환율이 0.5일 때의 속도상수 $k_{f=0.5}$ 결과를 비교하여 산화 반응속도를 정량적으로 해석하고자 하였다.다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.11a
• /
• pp.122-126
• /
• 2006

Two types of pressurization system and low weight feeding piping system are developed. With sub-system tests, ullage pressure control performance was verified for 1 step and 2 step pressurization system and the feeding performance of feeding piping system was also verified. The weight of the feeding piping system is low enough for the application of launch vehicle. In addition, LOX conditioning system is developed for avoiding geysering and LOX temperature rise. Integrated performance was verified through integrated on-board feeding system performance tests.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.47 no.10
• /
• pp.738-746
• /
• 2019

Instead of hydraulic actuation systems, an electromechanical actuation system is more efficient in terms of weight, cost, and test evaluation in the thrust vector control of the 7-ton gimbal engine used in the Korea Space Launch Vehicle-II(KSLV-II) $3^{rd}$ stage. The electromechanical actuator is a kind of servo actuator with position feedback and uses a BLDC motor that can operate at high vacuum. In the case of the gimballed rocket engine, a synthetic resonance phenomenon may occur due to a combination of a vibration mode of the actuator itself, a bending mode of the launcher structure, and an inertial load of the gimbals engine. When the synthetic resonance occurs, the control of the rocket attitude becomes unstable. Therefore, the requirements for the stiffness have been applied in consideration of the gimbal engine characteristics, the support structure, and the actuating system. For the 7-ton gimbal engine of the KSLV-II $3^{rd}$ stage, the stiffness requirement of the actuation system is $3.94{\times}10^7N/m$, and the direct drive type electromechanical actuator is designed to satisfy this requirement. In this paper, an equivalent stiffness analysis model of a direct drive electromechanical actuator designed based on the stiffness requirements is proposed and verified by experimental results.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.43 no.8
• /
• pp.699-705
• /
• 2015

Aircraft needs high lift-to-drag ratio and weight reduction of the structure for long endurance flight with a small power. Generally high aspect ratio wing is applied to HALE(High Altitude Long Endurance) aircraft. Also high modulus, and high strength CFRP(Carbon Fiber Reinforced Plastic) has been used in primary structures. and thin mylar(membrane material) film has been applied to skin of wing. As a result, wing is more flexible than the other structures. and the stiffness of thin mylar film has an affect on dynamic stability. In this study, the membrane characteristic of mylar film has been simulated using nonlinear gap elements. And equivalent modeling method using shell elements is presented using the nonlinear simulation result. The linear equivalent model has verified using the results of nonlinear membrane method. Proposed linear equivalent shell model has applied to mode analysis for estimate the effect of mylar mechanical properties on natural frequency.