Patent ID: 8936419
Filing Date: 2015-01-20
Classification: B64C,B64D

Abstract:
1. A restraint mechanism for releasably restraining a unit load device in an aircraft, the restraint mechanism comprising: a housing adapted to be connected to the aircraft; a pawl pivotally coupled to said housing for pivotal movement about a pivot axis with respect to said housing between a locked position and an unlocked position, said pawl including a first foot pivotally coupled to said housing, and a head adapted to releasably restrain movement of the unit load device when said pawl is in said locked position; a first cam assembly having a first end and a second end, said second end of said first cam assembly coupled to said pawl, said cam assembly including a first link and a second link, said first link pivotally coupled to said second link, said first link including said first end of said cam assembly and said second link including said second end of said cam assembly; and an actuator shaft coupled to said housing for selective rotation about a rotational axis with respect to said housing, said actuator shaft being coupled to said first link of said first cam assembly such that said first link conjointly pivots with said actuator shaft about said rotational axis; whereby rotational movement of said actuator shaft in a first rotational direction about said rotational axis pivots said pawl about said pivot axis toward said locked position of said pawl wherein said pawl is adapted to restrain movement of the unit load device, and wherein rotational movement of said actuator shaft in a second rotational direction about said rotational axis pivots said pawl about said pivot axis toward said unlocked position of said pawl wherein said pawl permits movement of the unit load device.