GB2434193A

GB2434193A - Missile launch apparatus

Info

Publication number: GB2434193A
Application number: GB9500772A
Authority: GB
Inventors: Graham Patrick Wallis
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: GB2434192A; GB2434190B; DE19501862B3; GB9401221D0; GB2434190A; GB9500772D0; GB2434191A; DE19501861B3; GB9500769D0; DE19501864B3; GB9500770D0; GB2434193B; DE19501865B3; GB9500771D0; GB2434192B; GB2434191B

Abstract

A deployment mechanism for deploying an optical fibre (14) on the launching of a missile (10) incorporating a coiled tubular spring (42) located at the rear of the missile through which the fibre (14) passes. The spring (42) serves to protect the fibre (14) from motor blast and also acts as a damper for the fibre as it begins to unwind on launch from a spool (12) carried on board the missile (10).

Description

-1-2434193 ssi1e Launch ApparatuS 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.

This invention provides a missile launch apparatus, including -a launch tube, a missile provided within said launch tube, a command line extending from said missile, means for shielding a portion of said command line adjacent to the missile during launch, wherein said shielding means comprises a stowable elongate tubular shield member disposed in the rear of the launch tube, through which said portion passes.

The command line is anchored at a point remote from the missile.

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

An embodiment of the invention will now be described, by way of example only, with reference to the drawing which shows a schematic side view of missile launch apparatus.

In the drawing, 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 fibre of 125 im 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 embodiment includes shielding means which protects the command line during launch without placing an excessive load on the command line.

The command line 14 runs from the spool 12 through a hollow tubular spring 42. The spring 42 is anchored at one end to the inside rear of the launch tube, with the other end being compressed against the spool 12. The tubular spring protects the command line from motor blast and also acts as a damper for the command line when It starts unwinding. The uncompressed length of the spring is typically about one half the length of the launch tube 16, so that command line beings to unwind from the spool only when the missile is halfway down the launch tube 16.

Claims

CLAIMS

1. A missile launch apparatus including:-a launch tube, a missile provided within said launch tube, a command line extending from said missile, means for shielding a portion of said command line adjacent to the missile during launch, wherein said shielding means comprises a stowable elongate tubular shield member disposed in the rear of the launch tube, through which said portion passes.

2. Apparatus according to Claim 1, wherein said elongate tubular shield member is of coiled form.

3. Apparatus according to Claim 1 or 2, wherein said elongate tubular shield member is resiliently deformable to prevent or reduce shock loads experienced by said command line.

4. Missile launch apparatus, substantially as hereinbefore described, with reference to, and as illustrated in the accompanying drawings.

Amendments to the claims have been filed as follows 1. A missile launch apparatus including:-a launch tube, a missile provided within said launch tube, a conmiand line exteixling fran said missile, means for shielding a portion of said conmiand line adjacent to the missile during launch, wherein said shielding means cxnprises a sta,able elongate tubular shield manber disposed in the rear of the launch tube, through which said portion passes, wherein said elongate tubular shield manber is of coiled form.

2. Apparatus according to Claim 1 or 2, wherein said elongate tubular shield mauber is resiliently deformable to prevent or reduce shock loads experienced by said connuand line.

3. Missile launch apparatus substantially as hereinbef ore described, with reference to, and as illustrated in the accompanying drawings.