GB2434191A

GB2434191A - Missile launch apparatus

Info

Publication number: GB2434191A
Application number: GB9500770A
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: GB2434190A; GB2434191B; GB9500772D0; DE19501861B3; DE19501864B3; GB9500770D0; GB2434193A; GB9500769D0; DE19501862B3; GB2434192A; GB2434193B; GB9401221D0; GB9500771D0; GB2434192B; DE19501865B3; GB2434190B

Abstract

Apparatus suitable for the deployment of a fibre optic cable (14) from a missile (10) during launch includes a protective can (32) which encloses the spool (12) of fibre optic cable (14) and beacons (33 protecting both from any motor efflux. Wrapped around the outside of the can (32) is enough fibre optic cable to reach approximately half way down a launch tube (16). Once the rear of the missile (10) reaches approximately half way down the tube (16) the can is pulled off. 'Pit' pins (35) secure the can (32) to the missile (10) until cables (34) pull them out, and the can (32) off when taut as a result of the missile reaching half distance along the tube. At this point the cable (14) starts to pay out from the spool (12) with strain relief provided by an optional rear-mounted damper (18).

Description

-1-2434191 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 difring 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 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 shield means comprises a generally cylindrical member housed within the missile outer shield surrounding the command line spool and co-operates with the missile rear fairing to shield said portion.

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.

J"n 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 through an embodiment of missile launch apparatus in accordance with the invention; and Figure 2 is a scrap view showing the protective can of the arrangement of Figure 4, immediately prior to removal by the can pull-off cables.

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 125 pm 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 rearwardly to be attached to a damper 18. The damper is of the type described in our co-pending British Zpp1ication 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 in the rear of the launch tube 16 and includes a cowling 31 to shield it from the efflux from the missile launch motor. From the damper 18, the command line 14 runs forwardly to be shielded between the cylindrical wall of a protective can 32 surrounding the spool 12, and the adjacent surface of the missile rear fairing temporarily surrounding the protective can. The can 32 has a cylindrical portion terminating at the rear end with an inwardly extending annular wall, so that the can encloses and protects the spool 12 and missile beacons 33 from efflux during launch. Temporarily attached to the top surface of the can 32 is sufficient (typically about 0.5m) command line 14 to accommodate the distance travelled by the missile down the launch tube 16 until the ejector motor of the missile has burnt out. The can 32 is tethered to the launch tube by pull-off cables 34 slightly shorter than the length of command line 14 wrapped on the can 32, so that the can is pulled off after burn out of the eject motor, whereafter the command line is unwound from the spool 12. The can 32 is releasably secured to the aft end of the missile by "pit" pins 35 for example, attached to slightly shorter branches of the pull-off cables 34. Alternatively the can could be secured with a low-strength glue. The portion of command line 14 wrapped on the can 32 may also be secured by low strength glue.

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 shield means comprises a generally cylindrical member housed within the missile outer shield, surrounding the command line spool and co-operates with the missile rear fairing to shield said portion.

2. pparatus according to claim 1 including means for removing said cylindrical member during launch of the missile comprising a flexible element connected at one end of said launch tube and at the other to said cylindrical shield member.

3. Ppparatus according to Claim 2, wherein said flexible element includes means operable to release a pin element securing the cylindrical shield element to said missile, shortly before removing said shield element.

4. I-pparatus according to any of Claims 1 to 3, wherein said missile includes beacon means in an aft region and said shield means covers said beacon means prior to launch. *1

5. Ppparatus according to any preceding claim, wherein said cylindrical shield element comprises a hollow tubular portion.

5. Apparatus according to any preceding claim, wherein said cylindrical shield element comprises a hollow tubular portion.

6. Apparatus according to any preceding Claim, wherein said anchorage means includes shock absorbing means, for preventing or reducing shock loads experienced by said command line.

7. Missile launch apparatus substantially 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 shield means comprises a generally cylindrical member housed within the missile outer shield, surrounding the command line spool and co-operates with the missile rear fairing to shield said portion.

2. apparatus according to claim 1 including means for removing said cylindrical member during launch of the missile comprising a flexible element connected at one end of said launch tube and at the other to said cylindrical shield member.

3. apparatus according to Claim 2, wherein said flexible element includes means operable to release a pin element securing the cylindrical shield element to said missile, shortly before removing said shield element.

4. Apparatus according to any of Claims 1 to 3, wherein said missile includes beacon means in an aft region and said shield means covers said beacon means prior to launch.

5. Apparatus according to any preceding claim, wherein said cylindrical shield element comprises a hollow tubular portion.

5. Apparatus according to any preceding claim, wherein said cylindrical shield element comprises a hollow tubular portion.

6. Apparatus according to any preceding Claim, wherein said anchorage means includes shock absorbing means, for preventing or reducing shock loads experienced by said command line.

7. Missile launch apparatus substantially as hereinbefore described with reference to the drawings.