Session
Technical Session X: Delivery Systems
Abstract
Small launch vehicles present an economically viable method for placing small satellites into orbit. These launch vehicles would be even more attractive to satellite customers if they could provide a softer ride to orbit. Passive whole-spacecraft vibration isolation systems have been developed for small launch vehicles to greatly reduce the dynamic launch loads. To date, two types of isolation systems have been designed. The first is a single-axis “SoftRide” axial isolation system that provides isolation for predominantly axial loads. This type of system has been flown successfully three times on the Taurus/GFO mission in February 1998, the Taurus/STEX mission in October 1998, and the Taurus/MTI mission in March 2000. The second type of isolation system is a multi-axis device that provides vibration isolation in three axes. This type of system is needed to alleviate dynamic launch loads on the Minotaur vehicle (Figure 1). This multi-axis “SoftRide” system inserts flexibility and damping in three orthogonal axes between the launch vehicle and the satellite. The result is that dynamic launch loads with both axial and lateral components can be effectively mitigated. Additionally, these isolation systems provide extreme reductions to shock and structure-borne acoustic loads. The multi-axis isolation system is a logical extension of the single-axis system and has the same qualities of being simple, passive, small, lightweight, reliable, and highly effective. Two flights have demonstrated this new isolation system to date: these are the Minotaur/JAWSAT mission in January of 2000 and the Minotaur/MightySat mission in July 2000. Coupled loads analyses and flight telemetry data indicate that the new multi-axis vibration isolation system performed as expected and greatly reduced dynamic launch loads for the satellites. This new isolation system can be sized for any satellite and is being considered for other small and large launch vehicle missions.
Whole-Spacecraft Vibration Isolation Flown on the Minotaur Launch Vehicle
Small launch vehicles present an economically viable method for placing small satellites into orbit. These launch vehicles would be even more attractive to satellite customers if they could provide a softer ride to orbit. Passive whole-spacecraft vibration isolation systems have been developed for small launch vehicles to greatly reduce the dynamic launch loads. To date, two types of isolation systems have been designed. The first is a single-axis “SoftRide” axial isolation system that provides isolation for predominantly axial loads. This type of system has been flown successfully three times on the Taurus/GFO mission in February 1998, the Taurus/STEX mission in October 1998, and the Taurus/MTI mission in March 2000. The second type of isolation system is a multi-axis device that provides vibration isolation in three axes. This type of system is needed to alleviate dynamic launch loads on the Minotaur vehicle (Figure 1). This multi-axis “SoftRide” system inserts flexibility and damping in three orthogonal axes between the launch vehicle and the satellite. The result is that dynamic launch loads with both axial and lateral components can be effectively mitigated. Additionally, these isolation systems provide extreme reductions to shock and structure-borne acoustic loads. The multi-axis isolation system is a logical extension of the single-axis system and has the same qualities of being simple, passive, small, lightweight, reliable, and highly effective. Two flights have demonstrated this new isolation system to date: these are the Minotaur/JAWSAT mission in January of 2000 and the Minotaur/MightySat mission in July 2000. Coupled loads analyses and flight telemetry data indicate that the new multi-axis vibration isolation system performed as expected and greatly reduced dynamic launch loads for the satellites. This new isolation system can be sized for any satellite and is being considered for other small and large launch vehicle missions.
