Shock isolation system

• US 5,353,677 A
• Filed: 08/31/1993
• Issued: 10/11/1994
• Est. Priority Date: 08/31/1993
• Status: Expired due to Fees

• Current Assignee: Northrop Grumman Corporation
• Original Assignee: Westinghouse Electric Company LLC (Brookfield Asset Management Incorporated)
• Inventors: Kennedy, Robert E.
• Primary Examiner(s): Brown, David
• Application Number:
  US08/114,884
• Time in Patent Office: 406 Days
• Field of Search: 89/1.816, 89/1.81, 89/1.809, 89/1.817, 89/1.819
• US Class Current: 89/1.816
• CPC Class Codes: F41F 3/052 Means for securing the rocket in the launching apparatus
• CPC Class Codes: F41F 3/073 Silos for rockets, e.g. mounting or sealing rockets therein F41F3/077 takes precedence

Abstract

In a canister carrying a missile having two stages of different diameters, flexible pads are provided to cushion the smaller diameter stage of the missile. The pad is a relatively flexible elastomer folded over on itself which, when the missile is fired, unrolls to a stowed position to allow passage of the larger diameter first stage of the missile.

Claims

1. In a shock isolation system for a structure having at least a first cylinder and a second cylinder of a smaller diameter, both having a common longitudinal axis and being joined by a conical transition member and adapted for axial movement in a container, with the second cylinder leading, the improvement comprising:

a) a flexible elastomeric pad adapted to be folded over on itself and being coupled to said container and positioned to contact and cushion said second cylinder during periods of non-axial movement;

b) the folded over portion of said pad being in the travel path of said first cylinder and being adapted to unroll when contacted by said first cylinder during said travel to allow passage of said first cylinder.

2. Apparatus according to claim 1 wherein:

a) said folded over portion of said pad includes a plurality of notches therein to facilitate said unrolling.

3. Apparatus according to claim 1 wherein:

a) the portion of said pad which contacts said second cylinder has a relatively high friction coating thereon;

b) the portion of said pad which is folded over on itself has a relatively low friction coating thereon.

4. Apparatus according to claim 1 wherein:

a) said pad includes a sloping end portion having a slope matching the slope of said transition member.

5. Apparatus according to claim 1 which includes:

a) at least three of said pads disposed around the inside of said container.

6. Apparatus according to claim 1 wherein:

a) said container is a launch container for said missile.

7. Apparatus according to claim 1 wherein:

a) at least three of said pads are disposed around the inside of said container;

b) the non folded over portion of each said pad being bonded to respective plate members;

c) said container including at least three apertures around the periphery thereof;

d) each said pad being inserted through a respective one of said apertures;

e) each of said plate members being connected to said container.

8. Apparatus according to claim 7 wherein:

a) at least three of said pads are disposed around the inside of said container;

b) said pads being bonded directly to the inside of said container.

9. Apparatus according to claim 1 which includes:

a) shock isolation means arranged about said first cylinder;

b) a plurality of guide rails extending from said shock isolation means longitudinally along the inside of said container for limiting radial movement of said first cylinder during said axial movement.

10. Apparatus according to claim 9 wherein:

a) said pad is disposed between two adjacent ones of said guide rails.

11. Apparatus according to claim 10 wherein:

a) said pad includes side wall portions having projections thereon which contact said adjacent guide rails as said pad unrolls;

b) said unrolled pad being held in position by wedging action of said projections against said adjacent guide rails.