Miniature vibration isolation system (MVIS)

Abstract

In recent years, there has been a significant interest in, and move towards using highly sensitive, precision payloads on space vehicles. In order to perform tasks such as communicating at extremely high data rates between satellites using laser cross-links, or searching for new planets in distant solar systems using sparse aperture optical elements, a satellite bus and its payload must remain relatively motionless. The ability to hold a precision payload steady is complicated by disturbances from reaction wheels, control moment gyroscopes, solar array drives, stepper motors, and other devices. Because every satellite is essentially unique in its construction, isolating or damping unwanted vibrations usually requires a robust system over a wide bandwidth. The disadvantage of these systems is that they typically are not retrofittable and not tunable to changes in payload size or inertias. Previous work, funded by the Air Force Research Laboratory, Defense Advanced Research Product Agency, Ballistic Missile Defense Organization and others, developed technology building blocks that provide new methods to control vibrations of spacecraft. The technology of smart materials enables an unprecedented level of integration of sensors, actuators, and structures; this integration provides the opportunity for new structural designs that can adaptively influence their surrounding environment. To date, several demonstrations have been conducted to mature these technologies. Making use of recent advances in smart materials, microelectronics, Micro-Electro Mechanical Systems (MEMS) sensors, and Multi-Functional Structures (MFS), the Air Force Research Laboratory along with its partner DARPA, have initiated a program to develop a Miniature Vibration Isolation System (MVIS) (patent pending) for space applications. The MVIS program is a systems-level demonstration of the application of advanced smart materials and structures technology that will enable programmable and retrofittable vibration control of spacecraft precision payloads. The current effort has been awarded to Honeywell Satellite Systems Operation.AFFX is providing in-house research and testing in support of the program as well. The MVIS program will culminate

Study Regarding the Transmissibility Vibrations about Hand-Arm System, Using Vibration Attenuation

“…Also, the purpose of the paper was to demonstrate that, the mechanical vibrations transmitted from an excitation source (ex. Machine-Tool) to the human operator (hand-arm system) are reduced from the hand to the elbow joint by mounting an attenuator device along the forearm [18,19]. All these studies were done in order to avoid or reduce the action of the vibrations on the human body (in this case the hand-arm system) at the workplace, and respectively the reduction of their effect and the prevention of occupational illnesses.…”

Simulation and experiment on the performance of a passive/active micro-vibration isolator

“…Brackett et al (2000) presented a vibration isolator, the Miniature Vibration Isolation System (MVIS), which is able to isolate the interference from reaction wheels, solar panel drivers and other components; thus, the high-speed, accurate and stable data passing among the satellites can be guaranteed. Based on the MVIS-I, McMickell et al (2007) presented the MVIS-II system that significantly improves the performance of MVIS-I with better adaptability and system utilization.…”

Development of multi-degree-of-freedom microvibration emulator for efficient jitter test of spacecraft

“…Many researchers have also developed various types of vibration isolation systems for space structures (Davis et al, 1986, 1994; Hanieh et al, 2002; Neat et al, 1998; Pendergast and Schauwecker, 1998; Zuo, 2005). Note that smart actuators have been successfully utilized as active components in satellite missions such as the Satellite Ultraquiet Isolation Technology Experiment (SUITE) and the Miniature Vibration Isolation System (MVIS) for on-orbit jitter isolation of satellite payloads (Anderson et al, 2000; Brackett et al, 2000).…”