GB2434192A

GB2434192A - Missile launch apparatus

Info

Publication number: GB2434192A
Application number: GB9500771A
Authority: GB
Inventors: Richard W Grainge; Anthony Machell; Anthony J Mann
Original assignee: British Aerospace PLC; Matra Bae Dynamics UK Ltd; MBDA UK Ltd
Current assignee: Matra Bae Dynamics UK Ltd
Priority date: 1994-01-22
Filing date: 1995-01-16
Publication date: 2007-07-18
Anticipated expiration: 2015-01-16
Also published as: GB9500770D0; DE19501864B3; GB2434191A; GB2434190A; GB2434191B; GB2434192B; GB9401221D0; GB9500772D0; GB2434190B; GB9500771D0; DE19501861B3; DE19501865B3; GB2434193B; GB2434193A; DE19501862B3; GB9500769D0

Abstract

Apparatus suitable for deploying a fibre optic cable (14) from a missile-mounted spool (12) on launch of the missile (10). A portion of the cable is releasably secured to an inner wall of an external cowling (38), said portion peeling away therefrom as the missile (10) moves along the launch tube (16). In one embodiment a damper (18) is provided in order to lessen shock loads on the cable (14) as it deploys. The damper is secured to the missile by a bracket 36 which runs in a slot in the launch tube until it reaches a stop 40 whereupon the bracket separates from the missile.

Description

-1-2434192 Missile Launch ADparatus This invention relates to missile

launch apparatus including a command line extending between the missile and the launch station and along which data may be transmitted and/or received.

The command line may be a fibre optic cable or an electrically conducting cable. The command line is typically stored on a payout spool at the rear of the missile and unwinds during launch and throughout missile flight. Great care must be taken to prevent damage to the cable during launch, for example from the effect of the launch motor, from excessive tension loads, from kinking or bending, or from the cable being caught between the missile and the launch tube. A fibre optic cable will tend to be more fragile than an electrically conducting cable. The term "launch tube" is used to describe any container or other support in which the missile may be located prior to launch.

US 4,573,647 describes one particular type of launch apparatus in which an optical fibre passes beneath a cover (running along the missile body) which includes a tear strip attached to a fixed anchorage point. On launch, the tear strip rips away a central part of the cover thus exposing the optical fibre without applying significant load thereto.

According to this invention, a missile launch apparatus, includes:-a launch tube, a missile provided within said launch tube, a command line extending between said missile and an anchorage point associated with said launch tube, means for shielding a portion of said command lIne adjacent to the missile during launch, wherein said shielding means comprises a cowling located on an outer surface of said launch tube, said portion being releasably secured to an inner wall of said cowling.

The anchorage point may be on a launch platform, ground vehicle or helicopter with which the launch tube is associated, or may be on the launch tube itself.

The cowling may form an integral part of the launch tube or may be a separate element attached thereto.

An embodiment of the invention will now be described, by way of example only, with reference to the drawings of which: Figure 1 is a schematic side view of the rear end of an embodiment of missile launch apparatus in accordance with the invention; and Figure 2 is a schematic transverse view on lines A-A of Figure 1.

A missile 10 has at its rear end a payout spool 12 on which is wound a command line 14, here in the form of a graded index multimode fibure of 1251.tm diameter and having an acrylic buffer coat. The tethered end of the command line 14 is attached to or otherwise fixed with respect to a launch tube 16.

The command line 14 extends from the spool 12 forwardly ocver the missile body to be attached to a damper 18. The damper is of the type described in our co-pending British Application No. 9009563.9, to which attention is directed, and comprises a helical spring surrounding the control line 14 and attached at least at its forward end to the control line. The damper 18 is provided with a shield 31 to protect it from blast from the missile launch motor.

Referring to Figures 1 and 2, the command line 14 passes from the spool 12 to the damper 18 which is releasably secured to the rear of the missile by a bracket 36. From the rear of the damper 18 the command line passes through a length of rigid tubing 37 into a cowling 38 projecting externally from the launch tube 16.

Within the cowling 38 a portion of command line 14 is lightly bonded to the wall of the cowling. This portion unpeels as the bracket 36 moves forward with the missile during launch. The launch tube 16 is slotted adjacent to the cowling 38 for about half the length of the launch tube and, during launch, the bracket 36 runs in the slot until it reaches a damper stop 40, whereupon the damper bracket 36 separates from the missile, and the command line then unwinds from the spool.

Claims

CLAIMS

1. A missile launch apparatus including:-a launch tube, a missile provided within said launch tube, a command line extending between said missile and an anchorage point associated with said launch tube, means for shielding a portion of said command line adjacent to the missile during launch, wherein said shielding means comprises a cowling located on an outer surface of said launch tube, said portion being releasably secured to an inner wall of said cowling.

2. Apparatus according to Claim 1, including bracket means removably secured to said missile and providing a further anchorage point for said command line, and means for separating said bracket means following forward movement of the missile during launch.

3. Apparatus according to Claim 2, wherein said bracket means includes shock absorbing means for preventing or reducing shock loads experienced by said command line.

4. A missile launch apparatus substantially as hereinbefore described with reerence to the drawings.