Space shuttle damping and isolating device
A device used for providing dynamic isolation and damping of dynamic vibrations, in a passive way, originated in the launch vehicle of a space shuttle and reaching the payload or satellite. The device comprises a plurality of identical elementary unit elements, such that the device is designed in a modular way, allowing the individual modularity of each of the elementary unit elements. Each of the elementary unit elements is tailored and designed individually, and the complete device can be designed for each particular application and payload needed as a function of each of the elementary unit elements allowing an easy design and lower costs, for a wide range of payload applications. Each elementary unit element comprises a spring component and a damping component, such that the functionalities provided for each component are separated and can be individually tailored, thus providing a device having a wider range of adaptation capabilities.
1. A device capable of providing dynamic isolation and damping of dynamic vibrations originated in a launch vehicle of a space shuttle reaching at least one of a payload or satellite, the device interfering a load path from the launch vehicle to the space shuttle, the device comprising:
a plurality of elementary unit elements, each of the elements comprising a spring component, providing stiffness properties of each of the elementary unit elements, and a damping component, providing damping properties of each of the elementary unit elements, the spring component being formed by two symmetric stacks, characterized in that the damping component is not arranged in the load path from the launch vehicle to the space shuttle, ends of the damping component being joined to ends of the stacks, and in that each line joining each end of the stacks with the top or bottom parts of the stacks forms an angle (α) with the damping component, so that the damping properties and the stiffness properties of the device are designed individually by the variation of the angle (α).
2. The device according to claim 1 wherein the two symmetric stacks have a radial relative displacement and an axial relative displacement, such that a ratio of the axial relative displacement and of the radial relative displacement is directly related to the angle (α) in such a way that: when the ratio is <1, the angle (α) is <45°, when the ratio is equal to 1, the angle (α) is of 45°, and when the ratio is >1, the angle (α) is >45°.
3. The device according to claim 2 wherein when the ratio is less than 1, the angle (α) is less than 45°, so that the damping properties are higher than the stiffness properties in the device.
4. The device according to claim 2 wherein when the ratio is 1, the angle (α) is 45°, so that the damping properties and the stiffness properties in the device are equivalent.
5. The device according to claim 2 wherein when the ratio is greater than 1, the angle (α) is greater than 45°, so that the stiffness properties are higher than the damping properties in the device.
6. The device according to claim 1 , wherein each of the two symmetric stacks comprises a plurality of leaf springs, the damping component comprising a plurality of damping leafs, the stacks and the damping component being joined together at their ends.
7. The device according to claim 6 , wherein each leaf spring comprises a plurality of flat pads, with edge holes located at the edges, and an interface hole located at a center.
8. The device according to claim 6 , wherein the stacks and the damping component are joined together at each of their ends by mechanically preloaded bolt elements.
9. The device according to claim 1 , further comprising 144 elementary unit elements configured for at least one of a space shuttle and a payload in a range of 4.5 to 6 tons.
10. The device according to claim 1 , comprising 72 elementary unit elements configured for at least one of a space shuttle and a payload in a range of 3.5 to 4.5 tons.
11. The device according to claim 1 , comprising 36 elementary unit elements configured for at least one of a space shuttle and a payload of less than 3.5 tons.
12. The device according to claim 1 , wherein the elementary unit elements are manufactured of composite material.
13. The device according to claim 1 , wherein the elementary unit elements are manufactured of carbon fiber reinforced polymer, CFRP.