Arm removal system

Abstract

An arm removal system for removing an arm. The system includes an anvil, and a removal assembly with at least two jackscrews. The arm has an extension radially extending from the arm and an arm outer surface. The arm is disposed within a wedge shaped collet that is disposed within a socket in an aircraft with an aircraft outer surface. The removal assembly includes an extension engaging surface and threaded jackscrew holes for accepting the jackscrews, such that when the jackscrews are tightened within the jackscrew holes, the jackscrews apply force on the anvil and the aircraft outer surface in the direction away from the removal assembly such that the arm is eventually removed entirely from the aircraft.

Claims

1. An arm removal system for removing an arm, the arm having an extension radially extending from the arm and an arm outer surface, the arm disposed within a wedge shaped collet and the wedge shaped collet disposed within a socket in an aircraft with an aircraft outer surface, the arm removal system comprising: an anvil having an aircraft engaging surface that corresponds to the aircraft outer surface, and an inner surface that corresponds to the arm outer surface, such that when attached to each other the anvil envelops the arm outer surface and engages with the aircraft outersurface; at least two jack screws; a removal assembly having a removal system inner surface corresponding to a portion of the arm outer surface, the removal assembly having an extension engaging surface and threaded jack screw holes for accepting the jackscrews, such that when the jack screws are tightened within the jack screw holes, they apply force on the anvil and the aircraft outer surface in a direction away from the removal assembly and as a result the extension engaging surface applies an opposite force on the extension such that the arm is moved axially along the socket and eventually removed entirely from the aircraft.

Description

DRAWINGS

(1) These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims, and accompanying drawings wherein:

(2) FIG. 1 is a perspective view of the anvil of the arm removal system;

(3) FIG. 2 is a perspective view of the removal assembly with jackscrews;

(4) FIG. 3 is a perspective view of the arm removal system on the arm; and,

(5) FIG. 4 is a perspective view of the arm and socket without the removal system.

DESCRIPTION

(6) The preferred embodiments of the present invention are illustrated by way of example below and in FIGS. 1-4. As seen in FIGS. 3 and 4, the arm removal system 10 for removing an arm 50 includes an anvil 100, and a removal assembly 300 with at least two jackscrews 200. The arm 50 has an extension 55 radially extending from the arm 50 and an arm outer surface 56 having a circumference 22. The arm 50 is disposed within a wedge shaped collet 60 and the collet 60 is disposed within a socket 70 in an aircraft 80 with an aircraft outer surface 81. As shown in FIG. 1, the anvil 100 has an aircraft engaging surface 120 that corresponds to the aircraft outer surface 81, and an inner surface 130 that corresponds to the arm outer surface 56, such that when in place, the anvil 100 envelopes the arm outer surface 56 and engages with the aircraft outer surface 81. The removal assembly 300 has a removal system inner surface 305 that corresponds to a portion of the arm outer surface 56. As shown in FIG. 2, the removal assembly 300 also includes an extension engaging surface and threaded jackscrew holes 310 for accepting the jackscrews 200, such that when the jackscrews 200 are tightened within the jackscrew holes 310, the jackscrews 200 apply force on the anvil 100 and the aircraft outer surface in the direction away from the removal assembly 300 and as a result the extension engaging surface applies an opposite force on the extension 55 such that the arm 50 is moved axially along the socket and eventually removed entirely from the aircraft.

(7) In the description of the present invention, the invention will be discussed in a military aircraft environment; however, this invention can be utilized for any type of application that requires use of an arm removal system.

(8) In operation, the anvil 100 is placed over the arm 50 (or a universal weapons pylon on a military aircraft). The removal assembly 300 is then placed on the arm 50 so that corresponding surfaces are engaged. The jackscrews 200 are then threaded through the jackscrew holes 310, and turned until the jackscrews 200 engage the anvil 100. The jackscrews 200 are tightened until the arm is extracted from the socket.

(9) In another embodiment of the invention, there may be a variant of the engaging style. The other embodiment may include an extension on the removal assembly 300 to engage a groove in the arm 50.

(10) When introducing elements of the present invention or the preferred embodiment(s) thereof, the articles “a,” “an,” “the,” and “said” are intended to mean there are one or more of the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.

(11) Although the present invention has been described in considerable detail with reference to certain preferred embodiments thereof, other embodiments are possible. Therefore, the spirit and scope of the appended claims should not be limited to the description of the preferred embodiment(s) contained herein.