Payload depolyment from shuttle employing an ejection restraint

Aeronautics and astronautics – Spacecraft – Spacecraft formation – orbit – or interplanetary path

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Details

244160, B64G 122

Patent

active

046797521

ABSTRACT:
Apparatus for use in gyroscopically ejecting a spacecraft supported in the open end of a spacecraft supporting cradle. The invention comprises a separable ejection restraint mechanism attached between the cradle and the spacecraft. The mechanism restrains the thrust force applied to the spacecraft for a predetermined time period in order to dissipate undetermined forces acting upon the spacecraft prior to the ejection thereof. The mechanism comprises a separable resilient portion and a releasable clamp portion coupled thereto. The resilient portion comprises a spring loaded anchor rod arrangement while the releasable clamp portion comprises a spring loaded split ball clamp arrangement. The invention also contemplates the use of a flexible carrier coupled between the spacecraft and the cradle. The invention acts as a tether connected between the cradle and spacecraft which acts to establish a determinant state of force on the cargo and eliminate unwanted ejection-related problems prior to cargo deployment. In addition, the release of a single tether employed as the sole cargo release initiator minimizes the possible imparting of uncontrolled momentum to the cargo due to structural deformation energy.

REFERENCES:
patent: 4324374 (1982-04-01), Wittmann et al.
patent: 4355775 (1982-10-01), Ganssle
patent: 4359201 (1982-11-01), Thomson et al.
patent: 4506852 (1985-03-01), Adams et al.

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