Variable spacer for a separation system of a launch vehicle
AssigneeThe Boeing Company
InventorKenneth N. Telford
Life of this patent
Estimating the term…
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.
Claims19
A variable spacer for a separation system of a launch vehicle, the variable spacer comprising:
- a plate having a first surface and a second surface, said plate having a hole integrally formed therein and extending from said first surface to said second surface, said hole being intended to receive a bolt therethrough for attaching a first wall to a second wall, said plate being composed of a material having a desired thermal expansion coefficient in a thickness direction, said plate having a first thickness, said plate having a second thickness when said plate is compressed for attaching the first wall to the second wall, said plate having third thickness when a plate temperature of said plate is raised to an elevated temperature, said plate having a fourth thickness when said plate temperature of said plate is reduced to a lowered temperature.
A fastener assembly comprising:
- a bolt having a head, said head having a shaft extending therefrom, said shaft disposed within a first hole of a first wall and a second hole of a second wall;
- a nut coupled to said shaft of said bolt, said first wall and said second wall being disposed between said nut and said head;
- and
- a variable spacer operatively coupled to said bolt and applying a preload thereto, said variable spacer comprising a plate, said plate being composed of a material having a desired thermal expansion coefficient, said plate having a first thickness, said plate having a second thickness when said plate is compressed for attaching the first wall to the second wall, said plate having third thickness when a plate temperature of said plate is raised to an elevated temperature, said plate having a fourth thickness when said plate temperature of said plate is reduced to a lowered temperature.
A method for attaching a spacecraft to a launch vehicle, the method comprising:
- providing a first load on a bolt for coupling the spacecraft to the launch vehicle;
- increasing said first load to a second load during a turbulent stage;
- and
- decreasing said second load to a third load during a separation stage.
Dependencies are inferred from the claim text.