GB2434190A

GB2434190A - Missile launch apparatus

Info

Publication number: GB2434190A
Application number: GB9500769A
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: GB9500771D0; GB2434191A; GB2434190B; DE19501865B3; GB2434191B; DE19501862B3; GB2434192A; DE19501861B3; GB9500770D0; GB9401221D0; GB2434192B; GB2434193A; GB9500769D0; DE19501864B3; GB9500772D0; GB2434193B

Abstract

A deployment mechanism for shielding and deploying an optical fibre (14) on the launch of a missile (10) incorporating a rigid, elongate guide (30) running along the outer surface of the missile (10) and to which a portion of the fibre is releasably attached. An end of the fibre is attached to an anchorage point 18 on the launch tube. On launch, the fibre (14) peels away from the guide without sustaining any excessive load before the remaining fibre (14) pays out from a spool (12) mounted within the missile (10).

Description

-1-2434190 Missile 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.

Accordingly this invention provides 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 l.ine adjacent to the missile during launch, wherein said anchorage point is disposed forwardly of the rear end of the missile and said portion of said command line passes rearwardly over at least part of the missile body, and said shield means comprises a rigid elongate shield member which co-operates with an inner surface of the launch tube to shield said portion, said member being adapted to move with the missile as the missile moves forwardly during launch, thereby progressively to expose said portion.

The shield member may be caused to or allowed to separate from the missile when the rear of the missile reaches the front of the tube on launch.

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 drawings of which; Figure 1 shows a schematic side view of launch apparatus; and Figures 2 and 3 are scrap transverse section views on lines A-A of Figure 1, showing alternative two-component releasable fastenings.

In 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 fibre of 125pm 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 extends from the spool 12 forwardly over 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 rearward end is attached to a wall of the launch tube 16, so that the damper absorbs shock loads experienced by the control line 14.

The damper 18 is mounted outside the launch tube, with the command line passing back over the missile body to the spool 12. A shield is provided in the form of a J-shaped, or walking stick-shaped, elongate externally channelled guide 30 which is attached to the rear of the missile 10 and extends adjacent the inner surface of the launch tube 16 for almost all of its length. The command line 14 is fixed to the guide 30 by a low strength glue, or a peelable strip arrangement.

The presence of the guide 30 enables a straight length of line 14 to be run along the missile body 10 rather than it having to follow the contours of the missile 10.

On launch, as the missile 10 moves forward, the command line 14 is progressively unpeeled from the front of the guide 30 to the rear of the guide as the guide 30 moves forwards with the missile 10. The unpeeling of the command line 14 is achieved without applying a significant load to the command line 14. When the rear of the missile reaches the front of the launch tube 16, the guide 30 is severed at its point of attachment to the missile 10 by a cutter 21 mounted on the front end of the launch tube 16. Thus the guide 30 is left behind with the launch tube 16 and the missile 10 exits the tube 16 and the spool 12 pays out. Any shock loads on the control line 14 are absorbed by the damper 18.

The aforementioned peelable strip arrangement may take, for example, one of two forms.

Figures 2 and 3 show examples of two possible configurations of strip, each comprising a two component system, with one component being bonded to or otherwise fixed to the guide 30, and the other constituting a peelable portion. In Figure 2 a flexible elongate male rib 22 is releasable received in a resiliently deformable elongate female valley 24 in the base of which lies the command line 14. In Figure 3 the two components are hooked and looped strips 26, 28, similar to the Velcro (RTM) system, with at least one of the strips 26 having a longitudinal gap in which the command line 14 lies. The gap may be provided by laying a strip of plastics fibre between the command line 14 and the "hooks".

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 anchorage point is disposed forwardly of the rear end of the missile and said portion of said command line passes rearwardly over at least part of the missile body, and said shield means comprises a rigid elongate shield member to which said portion is releasably attached, said member being adapted to move with the missile as the missile moves forwardly during launch thereby progressively to expose said portion.

2. Apparatus according to Claim 1, wherein said shield member is releasably secured to said missile.

3. Apparatus according to Claim 1 or 2, including means for causing said shield member to separate from said missile when the missile leaves the launch tube.

4. Apparatus according to Claim 2, wherein said shield member is secured to a rearward portion of said missile.

5. Apparatus according to any preceding claim in which said portion is releasably attached to said shield member by a weak glue.

6. Apparatus according to any of Claims 1 to 4 in which said portion is releasably attached to said shield member by a strip element.

7. Apparatus according to Claim 6, wherein said strip element comprises means releasably engageable with a corresponding region attached to said shield member.

8. Apparatus according to Claim 7 wherein said strIp element and the corresponding region comprise mutually engageable hooked and looped fastening elements.

9. Apparatus according to Claim 7, wherein said strip element and the corresponding region or element comprises mutually engageable male and female parts.

10. Apparatus according to Claim 9, wherein the male part comprises a substantially continuous elongate rib element locatable in a substantially elongate channel element.

11. Apparatus according to any preceding claim wherein said anchorage point includes shock absorbing means for preventing or reducing shock loads experienced by said command line on launch of the missile.

12. Missile launch apparatus substarLtially as hereinbefOre described with reference to the 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 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 anchorage point is disposed forwardly of the rear end of the missile and said portion of said command line passes rearwardly over at least part of the missile body, and said shield means comprises a detachable rigid elongate shield member to which said portion is releasably attached, said member being adapted to move with the missile as the missile moves forwardly during launch thereby progressively to expose said portion.

2. pparatus according to Claim 1, wherein said shield member is releasably secured to said missile.

3. pparatus according to Claim 1 or 2, including means for causing said shield member to separate from said missile when the missile leaves the launch tube.

4. Apparatus according to Claim 2, wherein said shield member is secured to a rearward portion of said missile. to

5. Apparatus according to any preceding claim in which said portion is releasably attached to said shield member by a weak glue.

6. Apparatus according to any of Claims 1 to 4 in which said portion is releasably attached to said shield member by a strip element.

7. Apparatus according to Claim 6, wherein said strip element comprises means releasably engageable with a corresponding region attached to said shield member.

8. Apparatus according to Claim 7 wherein said strip element and the corresponding region comprise mutually engageable hooked and looped fastening elements.

9. Apparatus according to Claim 7, wherein said strip element and the corresponding region or element comprises mutually engageable male and female parts.

10. Apparatus according to Claim 9, wherein the male part comprises a substantially continuous elongate rib element locatable in a substantially elongate channel element.

ii. Apparatus according to any preceding claim wherein said anchorage point includes shock absorbing means for Il preventing or reducing shock loads experienced by said command line on launch of the missile.

12. Missile launch apparatus substantially as hereinbefOre described with reference to the drawings.