The United States of America As Represented by the Administrator of the

John P McManamen

Clarence J Wesselski

Jon B Kahn

John A Schliesing

Timothy E Pelischek

Edgar O Castro

Margaret E Grimaldi

Bruce H Becker

Gregory A Lange

Winston D Goodrich

A Shuttle type of aircraft (10) with an escape hatch (12) has an arcuately shaped pole housing (16) attachable to an interior wall and ceiling with its open end adjacent to the escape hatch. The pole housing 16 contains a telescopically arranged and arcuately shaped primary pole member (22) and extension pole member (23) which are guided by roller assemblies (30,35). The extension pole member (23) is slidable and extendable relative to the primary pole member (22). For actuation, a spring actuated system includes a spring (52) in the pole housing. A locking member (90) engages both pole members (22,23) through notch portions (85,86) in the pole members. The locking member selectively releases the extension pole member (23) and the primary pole member (22). An internal one-way clutch or anti-return mechanism prevents retraction of the extension pole member from an extended position. Shock absorbers (54)(150,152) are for absoring the energy of the springs. A manual backup deployment system is provided which includes a canted ring (104) biased by a spring member (108). A lever member (100) with a slot and pin connection (102) permits the mechanical manipulation of the canted ring to move the primary pole member. The ring (104) also prevents retraction of the main pole. The crew escape mechanism includes a magazine (60) and a number of lanyards (62), each lanyard being mounted by a roller loop (68) over the primary pole member (22). The strap on the roller loop has stitching for controlled release, a protection sheath (74) to prevent tangling and a hook member (69) for attachment to a crew harness.

Orbiter escape pole

A system for docking a space vehicle 11 to a space station 12 where a connecting tunnel for in-flight transfer of personnel is required. Cooperable coupling mechanisms 51, 52 include docking rings 56, 61 on the space vehicle 11 and space station 12, respectively. The space station is provided with a tunnel structure 15, a retraction mechanism 30, and a docking ring 56 attached thereto. The vehicle coupling mechanism 52 is designed to capture the station coupling mechanism 51, arrest relative spacecraft motions while limiting loads to acceptable levels, and then realign the spacecraft for final docking and tunnel interconnection. The docking ring 61 of the space vehicle coupling mechanism is supported by linear attenuator actuator devices 63 each of which is controlled by a control system (FIG. 10) which receives loading information signals and attenuator stroke information signals from each device 63 and supplies output signals for controlling its linear actuation to attenuate impact loading or to realign the spacecraft for final docking and tunnel interconnection. Retraction mechanism 30 is used to draw the spacecraft together after initial contact and coupling. Tunnel trunnions 21, 22, 23, 25 cooperative with latches 67 on the space vehicle 11 constitute the primary structural tie between the spacecraft in final docked configuration.

Docking mechanism for spacecraft

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Houston, TX, United States of America

John P McManamen