Session
Poster Session 1
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
Spacecrafts experience significant vibrations primarily during launch and sometimes in orbit, posing challenges to structural integrity and instrument performance. The methods to mitigate these vibrations, (or vibrations) in general primarily fall into two categories: disturbance absorption and source or receiver isolation. Among these two, isolation is preferred as fundamentally this is an additional system that either separates the source of the disturbance or the receiver effected in comparison to absorbers that reduce the magnitude of disturbance. Furthermore, its ability to provide greater control across varying frequency ranges relevant to spacecraft systems, provides the option of developing isolation systems with high efficiency. Isolation systems are further divided into passive and active approaches. Passive systems, which rely on mechanical components, are favored for their simplicity, reliability, and cost efficiency. Active systems, while offering finer control, are more complex, consume more power, and are relatively less reliable.
This research presents an analytical framework for designing passive isolation systems that address both transmitting and receiving elements. By systematically evaluating parameters such as mass, damping, and spring stiffness, the framework enables more targeted and efficient isolation system designs that align with spacecraft constraints. The study also compares the behavior of single-stage and two-stage isolators, offering insights into overcoming performance limitations associated with the former. By replacing traditional manual design methods with a structured analytical approach, this research simplifies the design process and broadens the practical integration of vibration isolation in small spacecraft.
Document Type
Event
Analytical Method to Design and Develop 2-Stage Passive Vibration Isolator for Spacecrafts and Its On-Board Payloads
Salt Palace Convention Center, Salt Lake City, UT
Spacecrafts experience significant vibrations primarily during launch and sometimes in orbit, posing challenges to structural integrity and instrument performance. The methods to mitigate these vibrations, (or vibrations) in general primarily fall into two categories: disturbance absorption and source or receiver isolation. Among these two, isolation is preferred as fundamentally this is an additional system that either separates the source of the disturbance or the receiver effected in comparison to absorbers that reduce the magnitude of disturbance. Furthermore, its ability to provide greater control across varying frequency ranges relevant to spacecraft systems, provides the option of developing isolation systems with high efficiency. Isolation systems are further divided into passive and active approaches. Passive systems, which rely on mechanical components, are favored for their simplicity, reliability, and cost efficiency. Active systems, while offering finer control, are more complex, consume more power, and are relatively less reliable.
This research presents an analytical framework for designing passive isolation systems that address both transmitting and receiving elements. By systematically evaluating parameters such as mass, damping, and spring stiffness, the framework enables more targeted and efficient isolation system designs that align with spacecraft constraints. The study also compares the behavior of single-stage and two-stage isolators, offering insights into overcoming performance limitations associated with the former. By replacing traditional manual design methods with a structured analytical approach, this research simplifies the design process and broadens the practical integration of vibration isolation in small spacecraft.
