GB1605397A

GB1605397A - Improvements in or relating to missiles

Info

Publication number: GB1605397A
Application number: GB4704164A
Authority: GB
Inventors: Maurice Colbert Mcmahon; Eric Nicholson
Original assignee: Short Brothers and Harland Ltd
Current assignee: Short Brothers PLC
Priority date: 1964-11-18
Filing date: 1964-11-18
Publication date: 1995-04-26
Anticipated expiration: 1980-11-18

Description

(54) IMPROVEMENTS IN OR RELATING TO MISSILES (71) We, SHORT BROTHERS & BR< HARLAND LIMITED, a Northern Ireland Company, of Airport road, Belfast, Northern Ireland, do hereby declare the invention, for which we pray that a patent may be granted to us and the method by which it is to be performed to be particularly described in and by the following statement: The present invention relates to missiles and other moving bodies and is particularly though not exclusively concerned with an anti-aircraft missile carrying an explosive charge and adapted to be fired into the air at a target such as an aircraft.

In our copending British Patent Application No. 7298/63 (Specification No 1605400) there is described a missile in which the nose portion is rotatably mounted in bearings on the forward end of a cylindrical main body portion of the missile for rotation about the longitudinal axis of the missile, and is provided with a pair of aileron control surfaces and a pair of elevator control surfaces pivotally mounted on the nose portion, and a remote control system is employed by means of which an operator at a ground station can bring the nose portion of the missile to a preselected roll attitude by appropriate operation of the aileron control surfaces and then subject the missile to a lateral steering thrust by appropriate operation of the elevator control surfaces.

The missile described in our copending patent application is eminently suitable for use by armed land forces against attacks by aircraft flying at low level. A launcher for the missile is however required which can readily be carried by one man and held by him during firing of the missile so that he can direct the missile against the approaching aircraft. The launcher may therefore conveniently consist of a long cylindrical tube carried on a supporting structure which can be held by the operator or carried for example on his shoulder. With the missile mounted in the tube the latter may be directed by the operator toward the target and the missile rocket motor fire so that the missile is ejected forwardly out of the tube at a considerable speed.

In the missile described in our copending application, four radially extending fins are mounted in spaced relation round the rear end of the main body portion of the missile to serve as stabilising; fins and it is considered essential to provide such stabilisation. Unfortunately the presence of such stabilising fins at the rear of the missile has hitherto made it necessary to employ a launching tube of considerably larger diameter than the diameter of the main portion of the missile and it is an object of the present invention to provide an arrangement of stabilising fins on a missile which will obviate the need for a large launching tube.

According to the present invention, there is provided a missile or other moving body having an elongated body portion carrying a sleeve slidably mounted thereon and fitted with outwardly extending stabilising fins, whereby the missile can be loaded into a launching tube with the body portion of the missile as a sliding fit in the tube and with the sleeve carrying the stabilising fins arranged at the forward end of the main body portion, subsequent firing of the missile causing the missile to be thrust forwardly out of the tube and to engage with the sleeve carrying the stabilising fins as it leaves the tube and the arrangement being such that the rear end of the main body portion of the missile cooperates with the sleeve on such a manner that the sleeve is brought to its position at the rear end of the main body portion under conditions of controlled acceleration.

One embodiment of the invention will now be described by way of example with reference to the accompanying drawings in which: Fig. 1 is a part sectional side elevation showing a missile according to the invention mounted in its launcher tube prior to firing, Fig. 2 is a part sectional side elevation of the missile shown in Fig. 1 upon it leaving the launcher tube, Fig. 3 is a part sectional side elevation of the rear end of the missile shown in Fig. 2, and Fig. 4 is a scrap section of the missile and launcher tube assembly shown in Fig. 1.

Referring to the drawings, a missile 11 comprises a main body portion 12 upon the forward end of which is mounted a nose portion 13 arranged for free rotation about the longitudinal axis of the missile. The nose portion 13 carries a pair of elevator control surfaces 14 and 15 and a pair of aileron control surfaces one of which is shown in Figs. 1 and 2 and indicated by the reference numeral 16. The main body portion 12 of the missile houses electrical control apparatus by means of which the aileron and elevator control surfaces on the nose portion 13 are actuated, an explosive charge and a detonating mechanism, and a solid fuel rocket motor is housed in a terminal section 17 of the missile, which section is of slightly greater diameter than the remainder of the main body portion 12.

At a position just forward of the terminal section 17 of the missile, the outer casing of the main body portion 12 is provided with a circumferential enlargement 18. Upon the main body portion 12 of the missile is arranged ametal sleeve 19 which can freely slide along the body portion 12 and is provided with four equiangularly spaced radially projecting fins 20 welded to the sleeve 19. Each fin 20 has a swept back leading edge commencing at the forward end of the sleeve and a trailing edge which terminates at the sleeve just forward of the rear end of the sleeve, thereby leaving a free rear terminal portion 21 of the sleeve which in a manner hereinafter to be described cooperates with the circumferential enlargement 18 on the main body portion 12 of the missile.

A launcher 22 is provided comprising a metal tube 23 of slightly larger diameter than the main body portion 12 of the missile and in a preferred embodiment the tube 23 is mounted on the upper end of a vertically arranged support (not shown) for pivotal movement about a horizontal axis, and the support is adapted to rest upon the shoulder of the operator who is also provided with a hand control bar mounted on the launcher tube 23 and by means of which he can direct the tube 23 at the required angle of elevation and by turning round with the launcher follow the target.

The missile is mounted in the launcher tube 23 as shown in Fig. 1 by bringing the sleeve 19 carrying the stabilising fins 20 forward on the main body portion 12 of the missile and inserting the missile 11, with its rear end first, into the forward end of the tube 23, the sleeve 19 being held forward of the launcher tube by the abutment of the fins 20 with the ends of slots 25 cut into the forward end of the launcher tube 23 and being fixed by a weak shear pin arrangement to the launcher tube 23, taking up the position shown in Fig. 1. The shear pin arrangement, which is shown in Fig. 4, comprises a leaf spring 26 secured at one end by a rivet 27 to the tube 23 and carrying at its other end an inwardly directed shear pin 28 which is thus resiliently mounted and engages in a locating hole in the sleeve 19.

During transportation and storage the forward end of the missile 11 is protected by a pyramidal cap or cover which fits over the nose portion 13 and the sleeve 19 with its stabilising fins 20 and which is secured to a flange 24 carried on the forward end of the launcher tube 23.

In preparation for firing of the missile the protective cap is removed. The launcher tube is then directed by the operator towards a target and the rocket motor of the missile is electrically ignited, whereupon the missile 11 is propelled forwardly in the tube and ejected from the forward end thereof at very high speed. The sleeve 19 carrying the stabilising fins 20, being free on the main body portion 12 of the missile, is almost instantaneously gathered by the rear end of the missile 11 as the latter leaves the end of the launcher tube 23, as shown in Fig. 2, the pin 28 shearing and the rear terminal portion 21 of the sleeve 19 riding up on to the circumferential enlargement 18 at the rear of the main body portion 12 of the missile as shown in Fig 3.The dimensions of the sleeve 19 and circumferential enlargement 18 are arranged to be such that the sleeve 19 is brought to rest with respect to the missile when about 1/3 of the rear terminal portion 21 of the sleeve has passed over the enlargement 18. In this way, the abrupt snatching of the sleeve 19 can be avoided and by suitable choice of materials for the sleeve 19 and enlargement 18 a controlled acceleration can be provided.

Provision may, if desired be made for imparting to the missile a spin about the longitudinal axis of the missile and it will be appreciated that where such spin is provided the sleeve 19 carrying the stabilising fins 20 will be caused to rotate with the missile when forced on to the circumferential enlargement 18.

It will be appreciated that in the embodiment hereinbefore described the terminal section of the sleeve 19 is deformed outwardly by its engagement with the circumferential enlargement 18. In an alternative arrangement the wedging action may be replaced by a shearing action in which the sleeve 19 is caused to shear away a comparatively soft metal from the main body portion 12 and in doing so be brought to rest with respect to the missile.

In a further alternative arrangement a ring of soft metal is provided on the rear end of the main body portion 12 and the sleeve 19 is brought to rest with respect to the missile body by striking the ring and deforming it.

In yet another arrangement, a ring of resilient metal is loosely attached to the rear end of the sleeve 19 which, upon being reached by the rear end of the missile during firing, is caused to ride up an inclined surface on the main body portion 12 and to be expanded thereby, the ring absorbing the energy which would otherwise be absorbed by the sleeve 19.

What we claim is:- 1. A missile or other moving body having an elongated body portion carrying a sleeve slidably mounted thereon and fitted with outwardly extending stabilising fins whereby the missile

**WARNING** end of DESC field may overlap start of CLMS **.

Claims

**WARNING** start of CLMS field may overlap end of DESC **. and 15 and a pair of aileron control surfaces one of which is shown in Figs. 1 and 2 and indicated by the reference numeral 16. The main body portion 12 of the missile houses electrical control apparatus by means of which the aileron and elevator control surfaces on the nose portion 13 are actuated, an explosive charge and a detonating mechanism, and a solid fuel rocket motor is housed in a terminal section 17 of the missile, which section is of slightly greater diameter than the remainder of the main body portion 12. At a position just forward of the terminal section 17 of the missile, the outer casing of the main body portion 12 is provided with a circumferential enlargement 18. Upon the main body portion 12 of the missile is arranged ametal sleeve 19 which can freely slide along the body portion 12 and is provided with four equiangularly spaced radially projecting fins 20 welded to the sleeve 19. Each fin 20 has a swept back leading edge commencing at the forward end of the sleeve and a trailing edge which terminates at the sleeve just forward of the rear end of the sleeve, thereby leaving a free rear terminal portion 21 of the sleeve which in a manner hereinafter to be described cooperates with the circumferential enlargement 18 on the main body portion 12 of the missile. A launcher 22 is provided comprising a metal tube 23 of slightly larger diameter than the main body portion 12 of the missile and in a preferred embodiment the tube 23 is mounted on the upper end of a vertically arranged support (not shown) for pivotal movement about a horizontal axis, and the support is adapted to rest upon the shoulder of the operator who is also provided with a hand control bar mounted on the launcher tube 23 and by means of which he can direct the tube 23 at the required angle of elevation and by turning round with the launcher follow the target. The missile is mounted in the launcher tube 23 as shown in Fig. 1 by bringing the sleeve 19 carrying the stabilising fins 20 forward on the main body portion 12 of the missile and inserting the missile 11, with its rear end first, into the forward end of the tube 23, the sleeve 19 being held forward of the launcher tube by the abutment of the fins 20 with the ends of slots 25 cut into the forward end of the launcher tube 23 and being fixed by a weak shear pin arrangement to the launcher tube 23, taking up the position shown in Fig. 1. The shear pin arrangement, which is shown in Fig. 4, comprises a leaf spring 26 secured at one end by a rivet 27 to the tube 23 and carrying at its other end an inwardly directed shear pin 28 which is thus resiliently mounted and engages in a locating hole in the sleeve 19. During transportation and storage the forward end of the missile 11 is protected by a pyramidal cap or cover which fits over the nose portion 13 and the sleeve 19 with its stabilising fins 20 and which is secured to a flange 24 carried on the forward end of the launcher tube 23. In preparation for firing of the missile the protective cap is removed. The launcher tube is then directed by the operator towards a target and the rocket motor of the missile is electrically ignited, whereupon the missile 11 is propelled forwardly in the tube and ejected from the forward end thereof at very high speed. The sleeve 19 carrying the stabilising fins 20, being free on the main body portion 12 of the missile, is almost instantaneously gathered by the rear end of the missile 11 as the latter leaves the end of the launcher tube 23, as shown in Fig. 2, the pin 28 shearing and the rear terminal portion 21 of the sleeve 19 riding up on to the circumferential enlargement 18 at the rear of the main body portion 12 of the missile as shown in Fig 3.The dimensions of the sleeve 19 and circumferential enlargement 18 are arranged to be such that the sleeve 19 is brought to rest with respect to the missile when about 1/3 of the rear terminal portion 21 of the sleeve has passed over the enlargement 18. In this way, the abrupt snatching of the sleeve 19 can be avoided and by suitable choice of materials for the sleeve 19 and enlargement 18 a controlled acceleration can be provided. Provision may, if desired be made for imparting to the missile a spin about the longitudinal axis of the missile and it will be appreciated that where such spin is provided the sleeve 19 carrying the stabilising fins 20 will be caused to rotate with the missile when forced on to the circumferential enlargement 18. It will be appreciated that in the embodiment hereinbefore described the terminal section of the sleeve 19 is deformed outwardly by its engagement with the circumferential enlargement 18. In an alternative arrangement the wedging action may be replaced by a shearing action in which the sleeve 19 is caused to shear away a comparatively soft metal from the main body portion 12 and in doing so be brought to rest with respect to the missile. In a further alternative arrangement a ring of soft metal is provided on the rear end of the main body portion 12 and the sleeve 19 is brought to rest with respect to the missile body by striking the ring and deforming it. In yet another arrangement, a ring of resilient metal is loosely attached to the rear end of the sleeve 19 which, upon being reached by the rear end of the missile during firing, is caused to ride up an inclined surface on the main body portion 12 and to be expanded thereby, the ring absorbing the energy which would otherwise be absorbed by the sleeve 19. What we claim is:-

1. A missile or other moving body having an elongated body portion carrying a sleeve slidably mounted thereon and fitted with outwardly extending stabilising fins whereby the missile

can be loaded into a launching tube with the body portion of the missile as a sliding fit in the tube and with the sleeve carrying the stabilising fins arranged at the forward end of the main body portion, subsequent firing of the missile causing the missile to be thrust forwardly out of the tube and to engage with the sleeve carrying the stabilising fins as it leaves the tube and the arrangement being such that the rear end of the main body portion of the missile cooperates with the sleeve in such a manner that the sleeve is brought to its position at the rear end of the main body portion under conditions of controlled acceleration.

2. A missile according to claim 1, wherein the main body portion of the missile is provided with a circumferential enlargement and wherein the dimensions of the sleeve and the circumferential enlargement are such that upon the missile being thrust forwardly out of its launcher tube and forwardly relatively to the sleeve a rear terminal portion of the sleeve rides up on to the circumferential enlargement causing the sleeve to be brought to rest with respect to the missile.

3. A missile according to claim 2, wherein the dimensions of the sleeve and the circumferential enlargement and the material or materials from which they are made are such that the rear terminal portion of the sleeve is deformed outwardly by its engagement with the circumferential enlargement.

4. A missile according to claim 1, wherein the sleeve is brought to rest at the rear end of the missile by a shearing action on which the sleeve is caused to shear away a comparatively soft metal from the main body portion of the missile.

5. A missile according to claim 1, wherein a ring of a soft metal is provided on the rear end of the main body portion and wherein the sleeve is brought to rest with respect to the missile body by striking the ring and deforming it.

6. A missile according to claim 1, wherein a ring of a resilient metal is loosely attached to the rear end of the sleeve which, upon being reached by the rear end of the missile during firing is caused to ride up an inclined surface on the main body portion of the missile and to be expanded thereby, the ring absorbing the energy which would otherwise be absorbed by the sleeve.

7. A missile according to any of the preceding claims, wherein the sleeve is arranged to be held at the forward end of the launching tube by a shear pin which connects the sleeve to the tube and which shears when the sleeve is gathered by the body portion as it leaves the launching tube.

8. A missile according to claim 7, wherein the shear pin is resiliently mounted on the forward end of the tube, the shear pin extending inwardly through a hole in the tube and into a location hole in the sleeve.

9. A missile according to any of the preceding claims, wherein the sleeve is arranged at the forward end of the tube with the fins engaging in axial slots in the tube and abutting against the rear ends of the slots.

10. A missile substantially as hereinbefore described with reference to the accompanying drawings.