Smart tunnel - docking mechanism

• US 4,860,975 A
• Filed: 12/30/1988
• Issued: 08/29/1989
• Est. Priority Date: 12/30/1988
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Edenborough, Kevin L., Schliesing, John A.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US07/292,131
• Time in Patent Office: 242 Days
• Field of Search: 244/158 R, 244/159, 244/160, 244/161, 244/162, 244/137.2, 14/71.5, 405/188, 405/189, 405/192, 166/340-343, 166/349, 166/338
• US Class Current: 244/172.4
• CPC Class Codes: B64G 1/641 Interstage or payload connectors docking systems B64G1/646
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refueling in space B64G1/4024

Abstract

A docking mechanism for the docking of a space vehicle 11 to a space station 12 comprising a flexible tunnel frame structure which is deployable from the space station. The tunnel structure comprises a plurality of series connected frame sections 21, one end section of which is attached to the space station and the other end attached to a docking module 15 of a configuration adapted for docking in the payload bay of the space vehicle 11. The docking module is provided with trunnions 41, 42 adapted for latching engagement with latches 17 installed in the vehicle payload bay and with hatch means 44 connectable to a hatch of the crew cabin of the space vehicle. Each frame section 21 comprises a pair of spaced ring members 31a, 31b interconnected by actuator-attenuator devices 33 which are individually controllable by an automatic control means to impart relative movement of one ring member to the other in six degrees of freedom of motion. The control means includes computer logic responsive to sensor signals of range and attitude information, capture latch condition, structural loads, and actuator stroke for generating commands to the on-board flight control system and the individual actuator-attenuators to deploy the tunnel to effect a coupling with the space vehicle or to adjust the relative attitude of the space vehicle and space station after coupling. A tubular fluid-impervious liner, preferably fabric 51, is disposed through the frame sections 21 of a size sufficient to accommodate the passage of personnel and cargo.

Claims

1. A docking mechanism for the docking and undocking of a space vehicle with a space station or another space vehicle, said docking mechanism comprising:

a deployable extensible tunnel structure mounted on said space station, said tunnel structure comprising a plurality of interconnected serially arranged frame sections with an end frame section of said series of frame sections being connected about an egress hatch of the space station, each said frame section including a pair of docking ring members interconnected in a normally coaxial spaced apart relationship defining an unobstructed central opening through said frame section;

actuator control means connected to said docking ring members for imparting a relative motion between said docking ring members of each said frame section in six degrees of freedom of movement;

a docking module attached to the other end section of said series of connected frame sections and provided with an opening communicating with the central opening of the adjacent frame section to which it is attached;

a plurality of latch mechanisms mounted on the space vehicle;

a plurality of trunnion members affixed to said docking module and adapted for interconnection with said latch mechanisms whereby said trunnion members are latchable thereto for coupling the space vehicle to the space station;

a pressurizeable tubular member disposed to extend through the central openings defined by said series of interconnected frame sections and of a cross section diameter suitable for the passage of personnel and cargo therethrough, said tubular member being attached at one end about said egress hatch in sealing relationship with the space station;

hatch means provided on said docking module adapted for interconnection in sealing relationship with the space vehicle for establishing communication therebetween when said docking module trunnions are latched to said space vehicle; and

means interconnecting said tubular member with said docking module in sealing relationship therewith about said opening of the docking module when the docking module trunnions are latched to the space vehicle, said tunnel structure being controllable in movement with respect to its end attachment to the space station by the control by said actuator means of the individual frame sections in six degrees of freedom of movement.

2. A docking mechanism as set forth in claim 1 wherein said pressurizeable tubular member is a flexible fluid-impervious fabric connected at its ends in sealing relationship with the space station and the docking module, respectively.

3. A docking mechanism as set forth in claim 1 wherein said actuator means is automatically responsive to the latched condition of said latching mechanisms and the loads imposed on said tunnel structure on docking impact of the space station and spare vehicle for controlling the motion of said tunnel structure.

4. A docking mechanism as set forth in claim 1 wherein said actuator means comprises:

a plurality of actuator-attenuator devices connecting the docking ring members of each said frame section, each said device being in the form of a pair of linearly adjustable telescopic members and pivotally connected at its ends to the respective ring members of a frame section;

a plurality of sensor means for sensing and signalling the latched or unlatched condition of said latching means, the range and attitude orientation of the space station with respect to the space vehicle, loads imposed on said tunnel structure and the length of strokes of the telescopic devices; and

computer logic circuitry responsive to said sensor signals for generating command signals for controlling the actuator-attenuator devices to effect the deployment and maneuvering of the tunnel structure.

5. A docking mechanism as set forth in claim 1 wherein said actuator control means comprises at least six telescopic actuator-attenuator devices for each said frame section, each said device being comprised of linearly adjustable telescopic members and pivotally connected at its ends to the respective ring members of the frame section wherein the attachment points for the devices on a first ring member of a frame section are arranged in pairs and the points in each pair are relatively closely adjacent to one another with the midpoints between the pairs being equiangularly spaced about the ring member and the attachment points on the other ring member are similarly arranged in pairs at locations with respect to their angular relation to the central axes of the ring members which are intermediate the pairs of attachment points on said first ring member and each actuator-attenuator device which connects at the same pair of attachment points on said first ring member being connected to the other ring member of the frame section at attachment points located in different pairs on said other ring member.

6. A docking mechanism for the coupling and docking of a space vehicle with a space station, said docking mechanism comprising:

a deployable extensible tunnel structure mounted on said space station, said tunnel structure comprising a plurality of interconnected serially arranged frame sections with an end frame section of said series of frame sections being connected about an egress hatch of the space station, each said frame section including a pair of docking ring members interconnected in a normally coaxial spaced apart relationship defining an unobstructed central opening through said frame section of a size sufficient to accommodate the passage of personnel and cargo therethrough;

actuator means connected to said docking ring members for imparting a relative motion between said docking ring members of each said frame section in six degrees of freedom of movement;

a docking module attached to the other end section of said series of connected frame sections and provided with an opening communicating with the central opening of the adjacent frame section to which it is attached;

a fluid impervious flexible tubular member of a diameter corresponding substantially to that of said ring members and disposed to extend through the central openings defined by said series of interconnected frame sections, said tubular member being attached at its ends in sealing relationship with said space station and said docking module about the egress hatch of the space station and said opening of said docking module, respectively;

a plurality of latch mechanisms mounted on the space vehicle;

a plurality of trunnion members affixed to said docking module and adapted for interconnection with said latch mechanisms whereby said trunnion members are latchable thereto; and

hatch means provided on said docking module for interconnection in sealing relationship with the space vehicle for establishing communication therebetween when said docking module trunnions are latched to said space vehicle, said tunnel structure being controllable in movement through control by said actuator means of said individual frame sections in six degrees of freedom of movement to thereby effect a coupling with the space vehicle when in proximity thereto and the subsequent adjustment of the attitude orientation of the space vehicle relative to the space station after coupling.

7. A docking mechanism as set forth in claim 6 wherein said actuator means includes a plurality of linear actuator-attenuator devices interconnecting the spaced ring members of each said frame section and wherein each said actuator-attenuator device is responsive to electrical command signals for controlling the relative movement of one ring member to the other.

8. A docking mechanism as set forth in claim 6 wherein said actuator means includes logic circuit means responsive to a latched condition of said latching mechanisms and structural loads imposed on said tunnel structure by the coupling of the space station and the space vehicle for simultaneously controlling the movement of each of said frame sections and thereby controlling the movement of said tunnel structure to attenuate the docking impact nd for adjusting the attitude orientation of the space vehicle with respect to the space station subsequent to coupling.