Shock Response Analysis of Mechanical Hardware of Flight Data Recorder

Navuri, Karteek; Prakash, D.; Mani, P. Beulah; Kumar, A. Eswara

doi:10.1016/j.matpr.2017.07.137

Cited by 3 publications

(2 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As the core of the projectile-borne recorder, the processor is responsible for data storage and reading. Considering the performance and programming simplicity of the processor, STM32F411 is selected as the main control unit [21,22]. The processor has the following characteristics:…”

Section: Processor Stm32mentioning

confidence: 99%

Design of a Projectile-Borne Data Recorder Triggered by Overload

Wang

Zhu

et al. 2020

Electronics

View full text Add to dashboard Cite

The projectile-borne data recorder is used to measure and record the position and attitude data of exterior ballistic flights, which experience high overload during the launching process. The navigation algorithm can be optimized by analyzing the data stored in the recorder. As the primary means of acquiring the navigation data, the micro inertial measurement unit (MIMU) is an inevitable part of the projectile equipment. However, its mechanical structure could hardly bear the high overload during operation. In view of the above problems, a novel projectile-borne data recorder triggered by overload is designed in this paper. The recorder could have the navigation system powered when the projectile leaves the barrel so as to activate the data recording of the high overload. Furthermore, the viability of the MIMU of the high overload is guaranteed through a specific way of system encapsulation. In the proposed design, the overload switch redundancy and the power supply redundancy were adopted to improve reliability. The proposed design is tested with practical experiments, and the results show that the proposed recorder could be effectively triggered by overloading, and the supply voltage is stable, which helps record reliable data for the projectile.

show abstract

Section: Processor Stm32mentioning

confidence: 99%

Design of a Projectile-Borne Data Recorder Triggered by Overload

Wang

Zhu

et al. 2020

Electronics

View full text Add to dashboard Cite

show abstract

“…Mechanical shock can be produced either by the stress wave propagations and reflections in the structural domain due to the application of an intensive transient loading, or directly by a transient loading with high frequency oscillations due to the structural behaviour of packaging protector (e.g., progressive crushing) [14][15][16]. Shock response spectrum (SRS), introduced initially by Biot [17], is an efficient approach to assess the severity of shock environment (e.g., [18,19]), which has different types of indicators, i.e. absolute acceleration (AA), pseudo acceleration (PA), pseudo velocity (PV), acceleration pseudo velocity (APV) and relative displacement (RD), as summarised in [20][21][22].…”

Section: Introductionmentioning

confidence: 99%

Dual damage criteria in a crash stop

Yang

2020

International Journal of Mechanical Sciences

View full text Add to dashboard Cite

This study proposes a method to apply dual criteria for the assessment of product damage based on the deceleration signal in a crash-stop incident. To evaluate the shock effects, a procedure is proposed to decompose the original crash signal into two components, i.e. an equivalent crash signal and a residual shock signal. The characteristics of crash signals are analysed in both time and frequency domains. It is found that the equivalent crash signal can represent the original crash signal if the dominant frequency (fn) of the product structure is relatively lower than the effective frequency (fs) of the crash signal, i.e. ≤ 1 5 . Otherwise, the original crash signal should be used in the assessment of product damage if > 1 5. The dual damage criteria method is proposed by combing the maximum-acceleration vs. velocity-change (Amax-V) diagram and shock response spectrum (SRS), i.e. the former can offer a lower bound of damage boundary on Amax-V diagram while the latter can define an upper bound of damage boundary on SRS graph. The method of dual damage criteria is illustrated numerically using two types of cantilever beams, as an example. The proposed method can be applied with the critical SRS (Sc) method recommended in ASTM D3332-99 for the packaging design and test, and may also be considered in the design and test of other impact energy absorbers in a crash-stop incident.

show abstract

Finite Element Analysis and Experimental Verification of Flight Data Recorder Design for Rotary Wing Aircraft

Kalaycıoğlu¹,

Arslan²,

Yapar³

2019

Uluslararası Muhendislik Arastirma Ve Gelistirme Dergisi

View full text Add to dashboard Cite

ÖzetBu çalışmada, helikopterlerde kullanılmak üzere Uçuş Verileri Kayıt Cihazının hafıza modülünün tasarımı ve üretimi gerçekleştirilmiş, uluslararası havacılık standartlarına uyum göstermesi için gerekli testlere tabi tutulmuştur. Tasarım çalışmalarında ANSYS R.16.2 Sonlu Eleman Programı yardımıyla hafıza modülünün dinamik serbest düşme, statik basma ve ısıl geçirgenlik analizleri sayısal olarak yapılmıştır. Deneysel çalışmalarda ise sayısal olarak bilgisayar ortamında yapılan analizlerin laboratuvar koşullarında testleri gerçekleştirilmiştir. Dinamik serbest düşme testinde alt kısmında çelik bir pim bulunan, 227 kg ağırlığındaki bir aparat 3 m yükseklikten hafıza modülünün üzerine serbest düşürülmüştür. Parça üzerindeki kalıcı şekil değişimi deneysel çalışmada 2.12 mm ölçülmüş, aynı değer sayısal analizde 1.99 mm olarak hesaplanmıştır. Statik basma testinde hafıza modülü hidrolik bir pres yardımıyla 4500 kg lık bir basma kuvvetine maruz bırakılarak sıkıştırılmaya çalışılmıştır. Basma testi için yapılan hem sayısal analiz hem de deneysel çalışmalar sonucunda hafıza modülünde belirgin bir deformasyonun olmadığı, şekil değişiminin elastik bölgede kaldığı görülmüştür. Isıl geçirgenlik testinde, hafıza modülünün üst cidarına 1100 0 C sıcaklık 1800 s süresince uygulanmış ve model içerisindeki sıcaklık dağılımı incelenmiştir. Sayısal çözüm ve deneysel çalışmalar sonucu; hafıza modülü içerisindeki 150 0 C dereceye dayanıklı kartın 90 0 C sıcaklığa maruz kaldığı görülmüştür. Yapılan çalışmalar sonucunda, tasarımı ve üretimi gerçekleştirilen Uçuş Verileri Kayıt Cihazına ait hafıza modülünün mekanik ve ısıl analiz sonuçlarının uluslararası havacılık standartları ile uyumlu olduğu sonucuna varılmıştır.

show abstract

Shock Response Analysis of Mechanical Hardware of Flight Data Recorder

Cited by 3 publications

References 4 publications

Design of a Projectile-Borne Data Recorder Triggered by Overload

Design of a Projectile-Borne Data Recorder Triggered by Overload

Dual damage criteria in a crash stop

Finite Element Analysis and Experimental Verification of Flight Data Recorder Design for Rotary Wing Aircraft

Contact Info

Product

Resources

About