MIL-STD-810F, Test Method Standard for Environmental Engineering Considerations and Laboratory Tests

Caruso, Hank

doi:10.17764/jiet.44.3.f45015p217843r36

Cited by 44 publications

(5 citation statements)

References 1 publication

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“…The mesh quality was considered excellent and could be used for numerical calculations. Afterwards, the blades model was imported into Ansys-Fluent 18.0 to conduct the erosion study of the moving mesh, the erosion parameters under the discrete phase model (DPM) model were defined, the particle was defined as SiO 2 , the particle density was 2200 kg/m 3 , and the incident velocity was defined as 20 m/s [30], which was perpendicular to the inlet surface. The particle mass flow rate was preferentially defined as 0.5 kg/s, and regular particles with an average diameter of 100 µm were injected from the entrance at the same impact velocity, while different blade rotation speeds were set (500, 1000, or 2000 rpm).…”

Section: Erosion Modelmentioning

confidence: 99%

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Solid Particle Erosion Area of Rotor Blades: Application on Small-Size Unmanned Helicopters

et al. 2021

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Rotor blades play an important role in unmanned helicopters, and it is of great significance to study the erosion of rotor blades. In this study, titanium alloy (Ti-4Al-1.5Mn) was used as the helicopter rotor blades’ surface material. The commercial software Ansys-Fluent 18.0 was mainly used to study the erosion of solid particles on the helicopter rotor blades. The moving mesh method and the discrete phase method (DPM) were used to construct an erosion model of the blades at different speeds (500, 1000, or 2000 rpm), and at different particle mass flow rates (0.5, 1, or 1.5 kg/s). The results show that the erosion of helicopter blades is mainly observed at the leading edge and at the tip of the blades. At different particle mass flow rates, greater particle mass flow rates lead to greater DPM erosion rates. As the blade speed increases, the maximum DPM erosion rate decreases, but the severely eroded area increases. Finally, the values of the severely eroded area of the helicopter rotor blades and the ratios of the severely eroded area growth are obtained through the image processing method.

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Section: Erosion Modelmentioning

confidence: 99%

“…Digital image processing is the use of computers to process images [30]. Image recognition technology is a common method in image processing, and is used in this section.…”

Section: Eroded Areamentioning

confidence: 99%

Solid Particle Erosion Area of Rotor Blades: Application on Small-Size Unmanned Helicopters

et al. 2021

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“…Typical non-Gaussian loads include the excitation of rail irregularity and pressure fluctuations for an aircraft. It is proposed in military environmental standards that the non-Gaussian loads case under extreme conditions need to be considered [ 7 , 8 ]. There are several studies that were published in recent years to show how non-Gaussian excitation impacts vibration fatigue life.…”

Section: Introductionmentioning

confidence: 99%

Vibration Fatigue Damage Estimation by New Stress Correction Based on Kurtosis Control of Random Excitation Loadings

Wang

Serra

2021

Sensors

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In the pioneer CAE stage, life assessment is the essential part to make the product meet the life requirement. Commonly, the lives of flexible structures are determined by vibration fatigue which accrues at or close to their natural frequencies. However, existing PSD vibration fatigue damage estimation methods have two prerequisites for use: the behavior of the mechanical system must be linear and the probability density function of the response stresses must follow a Gaussian distribution. Under operating conditions, non-Gaussian signals are often recorded as excitation (usually observed through kurtosis), which will result in non-Gaussian response stresses. A new correction is needed to make the PSD approach available for the non-Gaussian vibration to deal with the inevitable extreme value of high kurtosis. This work aims to solve the vibration fatigue estimation under the non-Gaussian vibration; the key is the probability density function of response stress. This work researches the importance of non-Gaussianity numerically and experimentally. The beam specimens with two notches were used in this research. All excitation stays in the frequency range that only affects the second natural frequency, although their kurtosis is different. The results show that the probability density function of response stress under different kurtoses can be obtained by kurtosis correction based on the PSD approach of the frequency domain.

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“…The problem lies in that the practical time variant subsystem hazard rate cannot be considered across mission procedures. In aircraft mission reliability assessment, however, the differences among missions should be considered, because load conditions are diverse under different missions …”

Section: Introductionmentioning

confidence: 99%

“…In aircraft mission reliability assessment, however, the differences among missions should be considered, because load conditions are diverse under different missions. 8 Researchers have also conducted mission reliability analysis from the viewpoint of maintenance rate. [9][10][11][12] This kind of method is only applicable to products that can be repaired at its normal operating condition, such as ships, submarines, and trains.…”

mentioning

confidence: 99%

Aircraft reliability assessment for an individual mission based on recordable flight parameters

Wang

Guan

2018

Quality & Reliability Eng

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Reliability of aircraft varies with different missions, because load conditions are always diverse. In limited sample size circumstances, convention aircraft mission reliability assessment method can only give an average result for a kind of mission. Motivated by the practical need of reliability assessment for an individual mission, this paper constructs a novel method, which can assess reliability for a specific mission based on flight parameters. The mission reliability model can be established according to the relationship between flight loads, flight parameters, and reliability via adopting fault data and flight parameters synthetically. Statistical inference of aircraft failure rate is proposed, and then, the mission reliability can be assessed according to the fault data of the focused aircraft. It is worth noticing that the proposed method can also assess the reliability for a mission category via conducting an average calculation across all individual missions belonging to the target mission category. An illustrative example shows that the proposed method not only can give reliability assessments with a same precision with existing approaches for a specific mission category but also can reasonably assess the reliability regarding an individual mission.

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MIL-STD-810F, Test Method Standard for Environmental Engineering Considerations and Laboratory Tests

Cited by 44 publications

References 1 publication

Solid Particle Erosion Area of Rotor Blades: Application on Small-Size Unmanned Helicopters

Solid Particle Erosion Area of Rotor Blades: Application on Small-Size Unmanned Helicopters

Vibration Fatigue Damage Estimation by New Stress Correction Based on Kurtosis Control of Random Excitation Loadings

Aircraft reliability assessment for an individual mission based on recordable flight parameters

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