Review on the Test Method of Adhesive Failure in Solid Rocket Motor

Chen, Li; Gao, Lu; Jiang, Jin-Yong; Ge, Qiang; Wang, Shaoguang; Wang, Bin

doi:10.2991/jimet-15.2015.126

Cited by 4 publications

(3 citation statements)

References 4 publications

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“…To prevent this incident, the installation of thermal insulation must be done carefully and using the appropriate material. The installation of thermal insulation should also be checked using the NDT method [20,21].…”

Section: Discussionmentioning

confidence: 99%

“…Ultrasonic Test (UT) NDT method also can detect cracks, voids, debonding and delamination. UT method is mostly used to detect the delamination between casing, insulation and propellant in the solid rocket motor [19,20]. In practical implementation, these two NDT methods (X-ray and UT) are used simultaneously to check the structure of the casing, thermal insulation and propellant.…”

Section: Discussionmentioning

confidence: 99%

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Risk Assessment of Solid Propellant Rocket Motor using a Combination of HAZOP and FMEA Methods

Deswandri,

Ratih Luhuring Tyas,

Dinnia Intaningrum

et al. 2023

ARFMTS

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The development of rockets in Indonesia has long been carried out by the National Aeronautics and Space Agency (LAPAN), which has now been integrated into the National Research and Innovation Agency (BRIN). The Research Centre for Rocket Technology, which is one of the centres within BRIN, has been developing solid propellant-based rockets with a various sizes and types. Solid-propellant rocket technology is commonly used because of their reliability, cost-effectiveness, and simple design. However, this technology is one of the high-risk technologies, whose failure can harm humans, damage the environment and cause huge losses to assets. As a high-risk technology, risk assessment activities must be carried out, starting from the design, manufacturing, testing and up to the launching stage. In this paper, we studied a risk assessment for general Solid-propellant Rocket Motor (SRM). SRM is basically a device that processes chemical energy in solid propellant into thrust (kinetic energy) in a container that functions as a pressure vessel. The risk assessment methods commonly used in this technology are the HAZOP or FMEA methods. The HAZOP is excellent in identifying failure modes systematically through identifying the deviation of physical process parameters but has difficulties in prioritizing the risk. The FMEA has effectiveness in understanding failure mechanisms and establishing necessary countermeasures, but for a product with a lot of components, the worksheet is also complex. By combining these two methods, integrating the superiority of each method, this research can identify modes, causes and effects of failure that may occur in SRM effective and accurately. In addition, this research also proposes corrective or preventive actions for each failure mode. As the objective of the risk assessment, results of the research can be used as input for the designers to improve their design and as inspection and surveillance objects for QC officers.

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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Risk Assessment of Solid Propellant Rocket Motor using a Combination of HAZOP and FMEA Methods

Deswandri,

Ratih Luhuring Tyas,

Dinnia Intaningrum

et al. 2023

ARFMTS

View full text Add to dashboard Cite

show abstract

“…Ultrasonic testing (UT) provided valuable insights into internal structures but had challenges in detecting surface defects. X-ray inspection and computed tomography (CT) imaging offered comprehensive internal views but were limited in surface defect detection [28]. Magnetic particle inspection excelled in surface flaw identification but struggled with subsurface defects.…”

Section: Non Destructive Testing: Imaging Approachesmentioning

confidence: 99%

Structural Health Monitoring of Solid Rocket Motors: From Destructive Testing to Perspectives of Photonic-Based Sensing

Korompili,

Mußbach,

Riziotis

2024

Instruments

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In the realm of space exploration, solid rocket motors (SRMs) play a pivotal role due to their reliability and high thrust-to-weight ratio. Serving as boosters in space launch vehicles and employed in military systems, and other critical & emerging applications, SRMs’ structural integrity monitoring, is of paramount importance. Traditional maintenance approaches often prove inefficient, leading to either unnecessary interventions or unexpected failures. Condition-based maintenance (CBM) emerges as a transformative strategy, incorporating advanced sensing technologies and predictive analytics. By continuously monitoring crucial parameters such as temperature, pressure, and strain, CBM enables real-time analysis, ensuring timely intervention upon detecting anomalies, thereby optimizing SRM lifecycle management. This paper critically evaluates conventional SRM health diagnosis methods and explores emerging sensing technologies. Photonic sensors and fiber-optic sensors, in particular, demonstrate exceptional promise. Their enhanced sensitivity and broad measurement range allow precise monitoring of temperature, strain, pressure, and vibration, capturing subtle changes indicative of degradation or potential failures. These sensors enable comprehensive, non-intrusive monitoring of multiple SRM locations simultaneously. Integrated with data analytics, these sensors empower predictive analysis, facilitating SRM behavior prediction and optimal maintenance planning. Ultimately, CBM, bolstered by advanced photonic sensors, promises enhanced operational availability, reduced costs, improved safety, and efficient resource allocation in SRM applications.

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Detection of Debonding Defects in Carbon Fiber-Reinforced Polymer (CFRP)–Rubber Bonded Structures Based on Active Lamb Wave Energy Analysis

Yang,

Ren,

Shi

et al. 2024

Sensors

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Carbon fiber-reinforced polymers (CFRPs) are widely used in the fabrication of solid rocket motor casings due to their exceptional performance. However, the bonding interface between CFRP and viscoelastic materials (rubber) is prone to debonding damage during service and storage under complex environmental conditions, which poses a significant threat to the structural integrity and reliability of the engine. Existing nondestructive testing (NDT) methods, such as X-ray imaging, infrared thermography, and ultrasonic testing, although somewhat effective, exhibit significant limitations in detecting interfacial defects in deep or multilayered composite materials, particularly under the challenging conditions of service and storage. This study proposes an innovative method based on active Lamb wave energy analysis and introduces the Damage Evolution Factor (DEF), specifically designed to detect and evaluate interfacial debonding defects in CFRP–rubber bonded structures within solid rocket motors during service and storage. Through numerical simulations and experimental validation, we selected the A0 mode Lamb wave, which is more sensitive to interfacial damage, as the incident wave and excited it on the surface of the structure. Displacement time-history response signals at observation points under different damage models were extracted and analyzed, and DEF values were calculated. The results show that DEF values increase with the size of the interfacial debonding damage. Similar trends were observed in experimental studies, further validating the effectiveness of this method and demonstrating that DEF can be used for the quantitative evaluation of interfacial debonding defects in CFRP–rubber bilayer bonded structures.

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Review on the Test Method of Adhesive Failure in Solid Rocket Motor

Cited by 4 publications

References 4 publications

Risk Assessment of Solid Propellant Rocket Motor using a Combination of HAZOP and FMEA Methods

Risk Assessment of Solid Propellant Rocket Motor using a Combination of HAZOP and FMEA Methods

Structural Health Monitoring of Solid Rocket Motors: From Destructive Testing to Perspectives of Photonic-Based Sensing

Detection of Debonding Defects in Carbon Fiber-Reinforced Polymer (CFRP)–Rubber Bonded Structures Based on Active Lamb Wave Energy Analysis

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