Technical and programmatic constraints in dynamic verification of satellite mechanical systems

Stavrinidis, C.; Klein, M.; Brunner, O.; Newerla, A.

doi:10.1016/0094-5765(95)00122-0

Cited by 3 publications

(4 citation statements)

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“…Typical technical requirements for the spacecraft structure relate to the following items [46]: -structural strength, -stiffness, -mass properties, -dynamic characteristics of the structure, -the range of vibration accelerations and displacements of spacecraft structural elements in the longitudinal and transverse directions (dynamic envelope [42]), -damping, -interface (connection of the spacecraft with the launch vehicle).…”

Section: Flight Dynamic Loads From the Side Of The Modern Launch Vehi...mentioning

confidence: 99%

“…In the theory of vibration protection systems (see, for example, [14,19,24,42]), methods and means of protection against vibration are classified. By this classification, methods that reduce vibration transmission by using additional devices built into the structure of machines and building structures are divided according to the principle of their action: vibration isolation methods and vibration damping methods.…”

Section: Introductionmentioning

confidence: 99%

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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: Flight Dynamic Loads From the Side Of The Modern Launch Vehi...mentioning

confidence: 99%

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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“…In 1966 Wilkey [1] was granted a patent for an experimental rocket system where a key feature was the use of a Marman clamp to hold the nal velocity package in place. This method of holding packages such as satellites into delivery vehicles remains the pre- ferred method as described by NASA¹ and Stravrindis et al [2]. Release of the satellite once in the correct orbit is achieved by exploding the T-bolt using a pyrotechnic device.…”

Section: Introductionmentioning

confidence: 98%

“…Firstly, small separation of the anges with elastic deformation of the V-band retainer, where the anges reconnect again after the axial load is taken o . Although no physical damage takes place, this failure is undesirable, as especially in turbocharger applications, uid leakage may occur or components may clash (Shoghi [14]), and in aerospace applications failure of the whole system due to chatter may occur (Stavrindis et al [2]). …”

Section: Introductionmentioning

confidence: 99%

Classical and numerical approaches to determining V-section band clamp axial stiffness

2014

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Classical and numerical approaches to determining V-section band clamp axial sti nessAbstract: V-band clamp joints are used in a wide range of applications to connect circular anges, for ducts, pipes and the turbocharger housing. Previous studies and research on V-bands are either purely empirical or analytical with limited applicability on the variety of V-band design and working conditions. In this paper models of the V-band are developed based on the classical theory of solid mechanics and the nite element method to study the behaviour of the V-bands under axial loading conditions. The good agreement between results from the developed FEA and the classical model support the suitability of the latter to model V-band joints with diameters greater than 110 mm under axial loading. The results from both models suggest that the axial sti ness for this V-band cross section reaches a peak value for V-bands with radius of approximately 150 mm across a wide range of coe cients of friction. Also, it is shown that the coe cient of friction and the wedge angle have a signi cant e ect on the axial sti ness of V-bands.

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Stress in V-section band clamps

Shoghi

Barrans

Rao

2004

Proceedings of the Institution of Mechanical Engineers, Part C:

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This paper presents an analysis of the stresses in V-section band clamps by examining the correlation between experimental work and theoretical models. Theoretical models incorporating traditional beam-bending theories and allowing for friction were developed to calculate the stress distribution and displacements within the clamps. The theoretical models demonstrated that the normal manufacturing tolerances associated with this type of component, combined with the uncontrolled operating parameters, will produce a wide variation in working stresses.These theoretical models were validated using strain and displacement measurements from a test with a V-section band clamp positioned around rigid anges. The experimental results all fell within the range of stresses predicted by the theoretical models. The paper provides a knowledge base for the rational design of V-section band clamps.

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Technical and programmatic constraints in dynamic verification of satellite mechanical systems

Cited by 3 publications

References 0 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

Classical and numerical approaches to determining V-section band clamp axial stiffness

Stress in V-section band clamps

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