Abstract: A flexible membrane is attached to an internal wall of the fairing of a flight vehicle. The membrane is inflated with gas to achieve a shape that couples with and thereby attenuates the first acoustic resonance occurring within the volume enclosed by the fairing. A sensor senses the varying ambient atmospheric pressure during flight. A pressure regulating system includes an inflation valve and pressure relief valve. Based on the sensed ambient atmospheric pressure, this system adjusts the membrane's gauge pressure throughout the flight trajectory to maintain the desired coupling gauge pressure. Acoustic blankets can also be attached to the internal walls of the fairing to abate resonances having frequencies greater than 500 Hz. Inflating the membrane with helium enhances the attenuation otherwise obtained. Multiple membranes can be individually tuned to respectively attenuate multiple acoustic resonances.

Abstract: A vibration isolation assembly for an aerodynamic object comprises a viscoelastic inner layer disposed on the aerodynamic object and being configured to attenuate vibration. The vibration isolation assembly further comprises a rigid or stiff outer layer disposed on an inner layer. The vibration isolation assembly may attenuate the transmission of aerodynamically-induced vibration to components contained or mounted to the aerodynamic object.

Abstract: Systems and methods according to one or more embodiments are disclosed to provide a dynamic variable shape optical element for wavefront correction. In an embodiment, a variable shape optical element assembly includes an optical element having a front surface and a back surface with specified curvature characteristics. The variable shape optical element assembly also includes back knife edges having a designated shape disposed on the back surface of the optical element and front knife edges having a designated shape disposed on the front surface of the optical element. The variable shape optical element assembly further includes a mechanical arrangement adapted to apply a dynamic mechanical force to create the specified curvature characteristics.

Abstract: Systems and methods according to one or more embodiments are disclosed to provide a dynamic variable shape optical element for wavefront correction. In an embodiment, a variable shape optical element assembly includes an optical element having a front surface and a back surface with specified curvature characteristics. The variable shape optical element assembly also includes back knife edges having a designated shape disposed on the back surface of the optical element and front knife edges having a designated shape disposed on the front surface of the optical element. The variable shape optical element assembly further includes a mechanical arrangement adapted to apply a dynamic mechanical force to create the specified curvature characteristics.

Abstract: A damper containing magneto-rheological (“MR”) fluid and a plunger lies between and is mechanically coupled both to a fixture and a vibration source. The plunger has a head immersed in the MR fluid. Annular magnets circumscribe the damper and produce a magnetic field surrounding the damper. A tubular shielding sleeve composed of magnetically impermeable material surrounds a portion of the damper. The sleeve is mechanically coupled both to the fixture and the vibration source by springs, and can translate relative to the damper to affect the strength of the magnetic field acting on the MR fluid surrounding the plunger head. The sleeve oscillates responsive to vibration of the vibration source and controls the viscosity of the MR fluid surrounding the plunger head in proportion to the amplitude of the sleeve's oscillation. The resonant frequency of the sleeve is adjusted to approximate the fundamental resonance of the fixture.

Abstract: A laser beam correction system and related methods of use and manufacture are provided. In one example, a laser beam correction system includes a mirror having a first surface and a second surface. An actuator comprising a piezoelectric ceramic disk and a plurality of conductive electrodes on substantially opposing sides of the disk is bonded to the second surface of the mirror. The actuator includes an aperture in a center portion. A wave-front sensor is adapted to measure optical wave-front characteristics of a laser beam received by the mirror and provide electronic signals corresponding to the wave-front characteristics.

Abstract: A laser beam correction system and related methods of use and manufacture are provided. In one example, a laser beam correction system includes a mirror having a first surface and a second surface. An actuator comprising a piezoelectric ceramic disk and a plurality of conductive electrodes on substantially opposing sides of the disk is bonded to the second surface of the mirror. The actuator includes an aperture in a center portion. A wave-front sensor is adapted to measure optical wave-front characteristics of a laser beam received by the mirror and provide electronic signals corresponding to the wave-front characteristics.

Abstract: A fixture is isolated from the transmission of vibration emanating from a vibration source by a damper containing magneto-rheological (“MR”) fluid and a plunger mechanically coupling the damper and the fixture. The isolation apparatus is mechanically coupled to the vibration source. The viscosity of the MR fluid contained in the damper is controlled by a magnetic field produced by the vibration of an isolation system responsive to the vibration of the vibration source. The resonant frequency of the isolation system is adjusted to approximate that of the fixture.

Abstract: A lightweight self-contained vibro-acoustic device is disclosed for dissipating low frequency vibration and acoustic energy within the payload fairing of launch vehicles. The device can be mounted on the interior surfaces of a fairing and adaptively tuned to match targeted structural and acoustic dynamics using electronic feedback loops.

Abstract: A system is disclosed that provides sound control for an acoustic musical instrument. Typical to all acoustic instruments, the instruments have a structure or housing that defines a vented acoustic chamber. An input or sound inducing mechanism (such as strings of a guitar) imparts a vibration to the structure which causes acoustic waves to resonate within the acoustic chamber. The motion of air in and out of the vent causes acoustic waves to emanate from the chamber that combine with the acoustic waves emanating from the structure to form sound/musical notes. In accordance with the invention, a system controls the sound emanating from such an acoustic instrument. In accordance with one embodiment of the invention, at least one integral or smart sensor is disposed adjacent a sensing location of the structure, and the sensor is configured to generate sensed electric signals indicative of the magnitude of structural vibration of the structure at the sensing location.

Abstract: A modular reusable transport container system is described for safely transporting small or medium size satellites and other sensitive cargo. The invention incorporates shock and vibration isolation systems, environmental control systems, integrated power converters, battery backup systems, and monitoring systems.

Abstract: This invention presents a passive vibroacoustic device that serves the dual function of attenuating the vibration of a flexible structure, and providing acoustic dissipation to the volume or cavity enclosed by the structure. This reduces the transmission of sound from external sources into the enclosure, and reduces vibration of the structure. By design of the shunting resistor and the mass and suspension properties, the device can be optimized to achieve high levels of both structural vibration attenuation and acoustic attenuation. Incorporating a feedback loop or adaptation mechanism will permit the device to maintain optimum attenuation in the case of time varying systems.

Abstract: A whole-spacecraft passive isolation system consisting of a plurality of titanium flexures that act as soft springs to isolate a satellite from its launch vehicle is improved by the addition of piezoceramic wafers attached to the flexures. A low-pass filter feedforward controller is used to cancel out disturbances by applying out-of-phase signals to the piezoceramic wafers thereby creating a hybrid isolation system that significantly reduces the dynamic loads on the spacecraft.

Abstract: The smart patch includes two piezoceramic actuators which operate on both sides of a structural member at the same fixed distance from the neutral axis to produce a bending method. The piezoceramic actuators are configured such that when subjected to a voltage, one shrinks and one expands. This provides the moment. One piezoceramic could also be used to provide half the moment provided that it was the same distance from the neutral axis of the structural member. There is a piezoceramic sensor that senses the vibrational mode to be suppressed. Finally there are control electronics that consist of a charge amplifier, a two pole low pass filter and a bridge amplifier. All of these elements are integrated into one entity.