Spacecraft Failure Analysis From the Perspective of Design Decision-Making

Kattakuri, Vikranth; Panchal, Jitesh H.

doi:10.1115/detc2019-98420

Cited by 7 publications

(1 citation statement)

References 9 publications

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“…Furthermore, the spacecraft must resist the actual action of all vibration loads. Therefore, its structure, components, and measuring instruments must be designed so that vibration indicators are minimal in a wide frequency range [12,21,27,46,47].…”

Section: Introductionmentioning

confidence: 99%

Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

PYLYPENKO,

KHOROSHYLOV,

NIKOLAYEV

2023

Kosm. nauka tehnol.

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Vibration loads on the launch vehicle and spacecraft can reach a high level, leading to abnormal and emergency situations. Therefore, the spacecraft structure must not only support the payload and subsystems of the spacecraft but also have sufficient strength and rigid- ity to exclude any emergencies (damage, destruction, unwanted deformations of the structure, failure and failure of instruments and equipment) that may interfere with the success of the mission. The article aims to analyze the state of research on the design of vibration protection systems for spacecraft launched into working orbits by modern launch vehicles. The results of this analysis will contribute to the development of fundamental schemes of vibration protection systems and methods for effectively suppressing spacecraft spatial vibrations. It is shown that the development of new promising vibration protection systems will take place in the following directions: increasing the frequency range and damping parameters of the dynamic coupled system of “spacecraft and vibration isolation system”; changing approach to vibration suppression of the entire spacecraft (as a whole unit) to setting up the system for damping individual (the most re- sponsible and vibration-sensitive) spacecraft; the use the spacecraft active vibration suppression system in combination with a passive vibration protection system; use of schematic diagrams of spacecraft vibration protection systems with the introduction of hydraulic, electromagnetic and mechanical functional elements in order to increase the efficiency of vibration isolation systems; active suppres- sion of random vibrations in outer space during the operation of various spacecraft systems (due to disturbances from engines of orbit correction systems, etc.); using the adapter structure to perform the functions of a passive vibration protection system of the spacecraft.

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Section: Introductionmentioning

confidence: 99%

Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

PYLYPENKO,

KHOROSHYLOV,

NIKOLAYEV

2023

Kosm. nauka tehnol.

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Fault-tolerant ADCS for Small Satellites Using Bayesian Networks

Yildirim,

Soken

2024

2024 IEEE Aerospace Conference

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How Uncertain Is Too Uncertain? Validity Tests for Early Resilient and Risk-Based Design Processes

Hulse

Hoyle

Tumer

et al. 2020

Journal of Mechanical Design

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A variety of risk and resilience-based design methods have been put forward over the years that seek to provide designers the tools to reduce the effects of potential hazards in the early design phase. However, because of the high level of uncertainty and low-fidelity design representations, one might justifiably wonder if using a resilient design process in the early design phase will reliably produce useful results that would improve the realized design. This paper provides tests that can be performed on a design process to determine whether it gives meaningful results when applied to an uncertain problem. These tests check three metrics: the change in the design when uncertainty is considered, the increase in the expected value of the design, and the cost of choice-related uncertainty: to see if they stay within desirable bounds. This approach is illustrated using two case studies to demonstrate how both discrete and continuous parametric uncertainty can be considered in the testing procedure. These case studies show that early design process validity is sensitive to the level of uncertainty and magnitude of design changes, suggesting that while there is a justifiable decision-theoretic case to consider high-level high-impact design changes during the early design phase, there is less of a case to choose between relatively similar design options because the cost of making the choice under high uncertainty is greater than the expected improvement in value of choosing the better design.

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Spacecraft Failure Analysis From the Perspective of Design Decision-Making

Cited by 7 publications

References 9 publications

Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

Fault-tolerant ADCS for Small Satellites Using Bayesian Networks

How Uncertain Is Too Uncertain? Validity Tests for Early Resilient and Risk-Based Design Processes

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