Abstract: Provided is a swing speed analyzer for mounting on a swinging implement and comprising a first accelerometer, a processor and a shock attenuator. The processor uses an output from the first accelerometer to compute a swing speed of the swinging implement. The shock attenuator is comprised of a material that is sized and dimensioned to dampen an impact shock wave by more than 50% at 125 Hz. The material is preferably sized and dimensioned to dampen the impact shock wave from more than 1000 g to less than 500 g. Suitable attenuators can include viscoelastomeric materials such as foam. The swing speed analyzer can advantageously include any of a releasable attachment mechanism, a liquid crystal or other visual display, a second accelerometer, and a strain gauge. The analyzer can advantageously be attached to a golf club, a tennis racket, a baseball bat, or a hockey stick.

Abstract: An apparatus is provided for attenuating shock and vibration energy levels within a spacecraft interface isolation system. The apparatus includes one or more spring plate assemblies fitted with mechanical stops and damping devices. The isolation system is typically incorporated into an interface unit, which is connected between the launch vehicle and the payload, in order to reduce the shock and vibration load energy imposed on the payload during the fairing separation processes. The mechanical stops maintain a desired level of stiffness for the payload supporting structure during lift-off and Max q, and the damping devices reduce the spring plate oscillation tendency during fairing separation. The combination of spring plate, stop, and damping device provides a significant reduction in shock and vibration energy levels in the approximate frequency range of 100 to 300 Hz.

Abstract: A variable spacer includes a plate having a first surface and a second surface. At least one hole is integrally formed within the plate, extending from the first surface to the second surface. The hole receives a shaft of a separation bolt used for attaching a spacecraft to a launch vehicle. The plate increases a first load within the separation bolt to a second load during a turbulent stage. The second load reduces a gapping that occurs between the launch vehicle and the spacecraft. Thereafter, the plate reduces the second load within the separation bolt to a third load during a separation stage. The third load decreases a shock level experienced by the spacecraft and the launch vehicle.

Abstract: A variable spacer includes a plate having a first surface and a second surface. At least one hole is integrally formed within the plate, extending from the first surface to the second surface. The hole receives a shaft of a separation bolt used for attaching a spacecraft to a launch vehicle. The plate increases a first load within the separation bolt to a second load during a turbulent stage. The second load reduces a gapping that occurs between the launch vehicle and the spacecraft. Thereafter, the plate reduces the second load within the separation bolt to a third load during a separation stage. The third load decreases a shock level experienced by the spacecraft and the launch vehicle.

Abstract: A satellite dispenser adapted to be coupled to a launch vehicle. The dispenser includes a single-piece, integrally formed tubular shell for supporting a plurality of independent satellites thereon. The tubular shell is significantly lighter than multi-piece dispenser shells that require a connecting ring for coupling the post portion and base portion of the shell together. The single piece shell also significantly reduces the cost and simplifies the manufacture of the dispenser shell. The dispenser shell, in certain preferred embodiments, includes a tapered post portion which enables satellites being carried on the upper portion of the post portion to extend further into a fairing disposed over the satellites and dispenser shell during flight, thus making more efficient use of the envelope defined by the interior area of the fairing. A frusto-conical base portion integrally formed with the post portion enables the load supported by the dispenser shell to be evenly distributed throughout the base portion.

Abstract: A satellite dispenser adapted to be coupled to a launch vehicle. The dispenser includes a single-piece, integrally formed tubular shell for supporting a plurality of independent satellites thereon. The tubular shell is significantly lighter than multi-piece dispenser shells that require a connecting ring for coupling the post portion and base portion of the shell together. The single piece shell also significantly reduces the cost and simplifies the manufacture of the dispenser shell. The dispenser shell, in certain preferred embodiments, includes a tapered post portion which enables satellites being carried on the upper portion of the post portion to extend further into a fairing disposed over the satellites and dispenser shell during flight, thus making more efficient use of the envelope defined by the interior area of the fairing. A frusto-conical base portion integrally formed with the post portion enables the load supported by the dispenser shell to be evenly distributed throughout the base portion.