| 摘要 |
<p>An acceleration force isolator assembly (32) for attaching a payload (10), such as a spacecraft or satellite, to a launch vehicle (12) wherein axial acceleration forces on the payload (10) are attenuated. The attachment includes an upper interface ring (54) that is secured to the payload (10) and a lower interface ring (46) that is secured to the launch vehicle (12). Flexure of the upper interface ring (54) provides axial compliance when axial acceleration forces are transmitted from the launch vehicle (12).</p> |
