Papers by Keyword: Airplane

Paper TitlePage

Authors: Shigeru Sunada
Abstract: The goal of our research is to develop a micro air vehicle (MAV) that is strongly stable in a wind gust. After observation of flights of an insect and a bird, we conjectured that an ornithopter would be a promising candidate as a high-performance MAV. In this paper we demonstrate the clear advantage of an ornithopter over an airplane with propellers. The variations in the aerodynamic forces acting on the two aircrafts, which generate the same thrust under the condition of no wind gust, were compared when they encountered gusts of wind. The consumed power, or alternately the period of one cycle of flapping motion and that of one rotation of propeller(s), remained constant before and after they encountered a wind gust. The following results were obtained: The variations of the aerodynamic force of an ornithopter by vertical and frontal wind gusts were slightly smaller than those of an airplane with one or two propellers. The variation in the aerodynamic force of the former by a side wind gust was smaller than that of the latter when the tip speed of the propeller and the flapping amplitude of the ornithopter were small.
66
Authors: Dao Lai Cheng, Qing Cheng Wang, Chui Jie Yi, Hong Yu Yao
Abstract: The characteristic of cockpit sound recorded by CVR is the key evidence in investigating accident causes for wrecked airplane. But many factors from inside and outside cockpit affects the analysis results, especially noise. And some analysis methods (such as FFT, WT, CZT, and so on) were impacted by internal and external environmental sound in aircraft cockpit. To solve the problems, further analysis and research for typical cockpit Sound’ ICA de-noising based on blind source separation principle. Firstly, the principle of de-noising analysis based on ICA are made in details ,including blind source separation and analysis of OGWE, maximum ratio of signal to noise of blind source separation algorithm; Then, process of cabin sound de-noising analysis based on ICA is done. Research indicates the de-noising of typical cockpit sounds is identical with the de-noising based on wavelet packet analysis in Matlab; more easy and reliable for the research and analysis of typical cockpit sound.
209
Authors: Xiao Gang Li, Zhou Zhou, Ke Qiang Cao, Chao Xia, Na Li
Abstract: In order to start performance testing and experimental research for enclosure of airplanes’ fuel systems, a type of integrative testing system is designed in this paper. This system can accomplish function and performance tests for enclosures in airplanes’ fuel system, and also can execute troubleshooting experiments.
258
Authors: Tao Zou, Heng Cheng Xu, Wen Jie Yang
Abstract: Electromechanical controlling devices (ECDs) plays an important role in electromechanical controlling system. There is a large quantity of electromechanical controlling devices (ECDs) on an airplane which concerning every specialists, and it has a very complex logic control. We developed this system because the construction ,working principle and working condition of the ECD often result in latent failure an some kind of failure that hard to carry out troubleshooting .The system centered by an embedded IPC applies module design in both hardware and software system, and it develop testing application with AVI running under Windows XP operating system, which makes it bound to have certain qualities ,such as good universality, integrity, complete functions, easy to operate and high degree of automation, also it is reliable , maintainable, flexible, adaptive, and the ability on expansion is very impressing . Application of this system will greatly improve the working efficiency and cut the time of inspection and troubleshooting, which means better intact rate of combat readiness of aircraft and mission availability rate, with significant military and economic benefit.
541
Authors: Ze Feng Tao, Yan Huang, Dong Wen Zhan, She Sheng Zhang
Abstract: By using solid-fluid coupling, momentum conservation, motion equation and pressure drag, a difference algorithm is employed to find the posture of airliner landing onto water in bowing stage for the different angle. The results show that the final velocity is positive correlated with impact angle when the angle is less than 80; the final velocity is negative correlated with impact angle when the angle is more than 80, waves make the immersed part decrease, which leads to a buoyancy reduction and acceleration increment.
1987
Authors: Lin Yin Luo, Yan Bin He, Xuan Liu, Xiao Hu Yao
Abstract: In the case of aircraft emergency landing, occupants’ safety analysis and research is one of the indispensable links in the verification of airworthiness safety. However, traditional experimental methods is time-consuming, complex and costly, seriously affect the development of new models to market. This paper established a finite element model of the full-size aircraft cockpit according to a certain type of amphibious light aircraft, and adding the dummy and safety belt occupant restraint system finite element model on this basis. In accordance with the requirements of CCAR-23 test conditions, using large dynamic finite element analysis software LS-DYNA numerical simulation was processed to study this aircraft’s emergency landing procedure. This paper investigated the dynamic response of the dummy and head injury criterion (HIC) value etc. The results provide certain reference for aircraft emergency landing safety design.
2513
Authors: Wu Wen Yao, Ping Zhou, Sheng Li Hou, Yun Kui Gao
Abstract: In order to solve the fight problem of damaged airplane in war, based on linear elasticity, elastoplasticity and net section yield criterion, the calculation model for residual strength of plate with smooth circular hole is founded. Furthermore, the flexibility of calculation models using these three methods is analyzed through examples. All above can be basis for airplane battle damage assessment.
31
Authors: Ivo Jebáček, Marek Horák
Abstract: This article provides information about in-flight measurement of a small sport aircraft. The strain gauges were used as sensors for load monitoring on the nose landing gear structure. To obtain overall forces it was necessary to do the calibration procedure. After the calculation of strain gauge coefficients the equations for calculating of total force, total force direction and individual force components were determined. During test flights the data acquisition system was installed into the aircraft. The data from strain gauges were collected together with other flight parameters like speed, altitude and data from inertial measurement unit which determined the exact movements of the aircraft before landing. The data recorded during fifty-six flights were analysed to obtain loads acting in the aircraft structure. These results were compared with calculated values.
325
Authors: Andrzej Zbrowski, Andrzej Majcher
Abstract: The article presents the structure of the developed pneumatic propellant system for impact tests particularly conducted in the aviation. The solution is intended for the realization of experimental tests enabling the simulation and recreation of the event of collision of the aircraft, or other means of transport, with the solid object or a bird in motion. The projectile thrower has been designed in form of a 250 mm pneumatic cannon. The size and the energy parameters of the cannon enable the objects weighing several kilograms to be thrown with the speed reflecting the actual collision of the aircraft with a big bird, both in the areas of subsonic and supersonic crash speed. In order for the complex realisation of the impact tests, the structure of the test system for impact tests with the option to record the event by means of a synchronised vision path and an impact force measurement path, has been developed.
366
Authors: Wen Jun Ge, Qin Yun Lv, Cheng Bao Xia
Abstract: In order to solve the restoring problem of the high-strength steel accessories on the airplane, the feasibility study about restoring the high-strength steel accessories by electro-brush plating has been done. The restoring technics was discussed, furthermore, we test the rigidity, binding force and abrasion resistance of the parts after restoring. It indicates that the restoring technology owns many advantages, such as simple technology flow, convenient operation, low cost, strong binding force between the coating and substrate and good abrasion resistance, which could meet the request of the use completely. So it is worth extending.
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