To the Question of Establishing Safety Coefficient and Assurance Coefficient at a Given Probability of Non-Destruction of Load-Bearing Structures

P., Pokhabov Yu.; Шендалев, Д О; Kolobov, A. Yu.; Nagovitsyn, V. N.; Ivanov, E. A.

doi:10.31772/2712-8970-2021-22-1-166-176

SAJ

2021

DOI: 10.31772/2712-8970-2021-22-1-166-176

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To the Question of Establishing Safety Coefficient and Assurance Coefficient at a Given Probability of Non-Destruction of Load-Bearing Structures

Pokhabov Yu. P.¹,

Д О Шендалев²,

A. Yu. Kolobov³

et al.

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Cited by 6 publications

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On the Reliability of the Functioning of the Deploying Landing Module Mechanisms

Pokhabov¹,

Blinov

Kolobov

2022

HoBMSTU.SME

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The development of mechanisms for deploying, fixing nodes and systems of interplanetary automatic spacecraft landing modules is the most difficult engineering task, errors in its solution lead to critical or fatal failures. The fact that interplanetary missions are rare and the implementation of each of them is very expensive leads to the need for practically trouble-free operation of deploying mechanisms, which in turn requires improving the efficiency of design techniques and computational and experimental reliability assurance in the face of limited statistical data and incomplete knowledge of the conditions and effects of planets on interplanetary spacecraft. In contrast to foreign experience, in domestic practice insufficient attention is payed to the methodology for designing highly reliable opening and fixation mechanisms. The article considers approaches to the computational and experimental reliability assurance of the functioning the mechanisms for deploying landing modules. The factors having a decisive effect on the reliability of the deploying and fixation mechanisms are analyzed. It is shown that the reliability of the functioning the deploying and fixation mechanisms largely determines the reserves of driving moments (forces) of the deploying drives, taking into account design and technological factors, and for the landing module mechanisms, they should be calculated based on the conditions and effects of the destination planets (climatic, atmospheric and gravitational)

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On the Reliability of the Functioning of the Deploying Landing Module Mechanisms

Pokhabov¹,

Blinov

Kolobov

2022

HoBMSTU.SME

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Methodology of the helical cylindrical compression spring design calculation

Kaverin,

Pokhabov

2023

EJSI

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Helical cylindrical compression springs are most often used in the one-time actuation mechanisms in rocket and space applications as the push drives to perform useful work in moving detachable parts of the aerospace vehicles. Such drives possess maximum energy characteristics with minimal weight and cost. The paper proposes the pusher spring design calculation methodology making it possible to take into account the design values range determined by the given initial spring parameters, where the strength condition is satisfied. The calculation methodology takes into account the spring design values range and makes it possible to create an effective computational algorithm. It is introduced for a targeted and consistent search of satisfactory solutions in designing spring units and mechanisms with the required performance and reliability (dimensions, ability to overcome resistive forces along the motion path and move control objects to the required distance, as well as strength). Based on the computational algorithm, a software program was created for the design and verifying calculation of the helical cylindrical compression springs, which makes it possible to quickly find effective solutions to be introduced in the practical activities of designers and calculators.

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Certain conclusions on results of introducing the reliability design and technological analysis in rocket and space production. Part 2

Pokhabov

2023

EJSI

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The paper generalizes results of introducing procedures of reliability design and technological analysis (RDTA) in the one-time actuation mechanisms of the spacecraft rotary structures (hereinafter referred to as the mechanisms). It provides principles of the mechanisms design and examples of establishing the design documentation requirements in their design process. The differences between processes of the mechanism design and construction are presented, and examples of design and technological factors that could lead to potential failures of such mechanisms are given. Principles of substantiating the spacecraft onboard equipment performance and reliability are considered. Commonality and differences in substantiating performance and reliability of mechanisms and of other onboard equipment of spacecraft are provided. As a result of the RDTA introduction, it was revealed that methods were missing in substantiating performance and reliability of the products for various purposes that were different in form. Only the content of engineering tasks that ensured fulfillment of their service purpose was varying. Moreover, solutions to such problems could be verified using the formalized procedures in reliability design and technological analysis.

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To the Question of Establishing Safety Coefficient and Assurance Coefficient at a Given Probability of Non-Destruction of Load-Bearing Structures

Cited by 6 publications

References 0 publications

On the Reliability of the Functioning of the Deploying Landing Module Mechanisms

On the Reliability of the Functioning of the Deploying Landing Module Mechanisms

Methodology of the helical cylindrical compression spring design calculation

Certain conclusions on results of introducing the reliability design and technological analysis in rocket and space production. Part 2

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