The design, assembly, and test processes followed in developing a space-qualified aperture door system are described. A blackbody calibration source is mounted inside the door, requiring the assembly to open and close a minimum of 150 cycles for instrument recalibration. Within the door system are four separate mechanisms, three of which are redundant; a pyro launch latch, a hinge bearing assembly, and a pair of pivot mechanisms. Decoupling devices within the pivot mechanisms allow an active drive unit to automatically overdrive a failed drive unit. The door is also stowable for possible Shuttle retrieval and re-entry. Illustrations and photographs of the flight hardware help acquaint the reader with the design. The aim is to pass on lessons learned in all phases of developing this spaceflight mechanism.
Development of the CLAES instrument aperture door system
01.04.1990
Aufsatz (Konferenz)
Keine Angabe
Englisch
Indication of convectively generated gravity waves observed by CLAES
Online Contents | 2005
|Early results of validation and application of claes data
Elsevier | 1994
|Early Results of Validation and Application of CLAES Data
British Library Conference Proceedings | 1994
|